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FLIGHT PLANNING AND PERFORMANCE MANUAL

0. Chapter Name-Section Name FLIGHT PLANNING AND PERFORMANCE MANUAL

737-800 CFM56-7B26 JAA/JAROPS KG/°C/M CATEGORY C BRAKES

OPTIONS 24K Derate 22K Derate

Copyright © 2000 The Boeing Company All Rights Reserved PUBLISHED BY FLIGHT OPERATIONS ENGINEERING BOEING COMMERCIAL AIRPLANE GROUP SEATTLE, WASHINGTON U.S.A BOEING DOCUMENT NUMBER: D632A008-ZZ022 Revision Number: 4 Revision Date: November 01, 2006

Copyright Information Boeing claims copyright in each page of this document only to the extent that the page contains copyrightable subject matter. Boeing also claims copyright in this document as a compilation and/or collective work. The right to reproduce, distribute, display, and make derivative works from this document, or any portion thereof, requires a license from Boeing. For more information, contact The Boeing Company, P.O. Box 3707, Seattle, Washington 98124. Boeing 707, 717, 727, 737, 747, 757, 767, 777, 787, DC-8, DC-9, DC-10, MD-10, MD-11, MD-80, MD-90, BBJ, Boeing Business Jet, the Boeing logo symbol, Boeing livery are all trademarks owned by The Boeing Company; and no trademark license (either expressed or implied) is granted in connection with this document or otherwise.

Flight Planning and Performance Manual

Preface

Table of Contents

0.0 Preface-Table of Contents

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Table of Contents . . . . Introduction . . . . . . . . Revision Record . . . . . List of Effective Pages Bulletin Record . . . . .

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Introduction

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Section 1

General

This Flight Planning and Performance Manual has been prepared by Boeing Commercial Airplanes, Commercial Aviation Services. The purpose of this manual is to provide a complete operational performance data reference including dispatch and inflight performance data applicable to a specific airframe, engine rating, and regulatory agency as identified on the cover page of the document. This manual is suitable for use for any airplane configuration that meets the criteria identified on the cover page of the document. Owners/operators are solely responsible for ensuring the performance documentation they are using is complete and matches the current configuration identified on the cover page of the document. This includes the accuracy and validity of all information furnished by the owner/operator or any other party. The manual is periodically revised to incorporate pertinent flight planning and performance information. Items of a more critical nature will be incorporated in Flight Planning and Performance Manual Bulletins and will be distributed in a timely manner. In all cases, such revisions and changes must remain compatible with the approved AFM with which the operator must comply. In the event of conflict with the AFM, the AFM shall supersede. This manual assumes the user is familiar with basic jet airplane performance and regulatory requirements common to airplanes of this type. Any questions about the content or use of this manual can be directed to: Commercial Aviation Services Boeing Commercial Airplanes P.O. Box 3707, M/C 20-88 Seattle, Washington 98124-2207 USA Attention: Manager, Performance Data Flight Operations Engineering

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Revision Record

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Revision Transmittal Letter

To: All holders of Flight Planning and Performance Manual, Boeing Document Number D632A008-ZZ022. Subject: Flight Planning and Performance Manual Revision This revision reflects the most current information available to The Boeing Company 45 days before the subject revision date. The following revision highlights explain changes in this revision. General information below explains the use of revision bars to identify new or revised information.

Revision Record

No.

0 02 4

Revision Date

March 15, 2002 September 27, 2004 November 1, 2006

Date Filed

No.

01 03

Revision Date

September 26, 2003 November 1, 2005

Date Filed

General

The Boeing Company issues Flight Planning and Performance Manual revisions to provide new or revised information. Formal revisions also incorporate appropriate information from previously issued Flight Planning and Performance Manual bulletins. The revision date is the approximate date the manual is mailed to the customer. Formal revisions include a new Revision Record, Revision Highlights, and a current List of Effective Pages. Use the information on the new Revision Record and List of Effective Pages to verify the Flight Planning and Performance Manual content. Pages containing revised material have revision bars associated with the changed text or illustration. The Revision Record should be completed by the person incorporating the revision into the manual.

Filing Instructions

Consult the List of Effective Pages (0.3.1). Pages identified with an asterisk (*) are either replacement pages or new (original) issue pages. Remove corresponding old pages and replace or add new pages. Remove pages marked DELETED; there are no replacement pages for deleted pages. Be careful when inserting changes not to throw away pages from the manual that are not replaced. The List of Effective Pages determines the correct content of the manual.

Revision Highlights

This section (0.2) replaces the existing section 0.2 in your manual. This manual is published from a database; the text and illustrations are marked with configuration information. Occasionally, because the editors rearrange the database markers, or mark items with configuration information due to the addition of new database content, some customers may receive revision bars on content that appears to be unchanged. Pages may also be republished without revision bars due to slight changes in the flow of the document.

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Chapter 1 - TAKEOFF AND LANDING Section 1 - Text Takeoff 1.1.1 - New methodology used for calculating line-up allowance based on ICAO recommended tire face safety margin (Dimension "M") for both the main and nose gears throughout the maneuver. 1.1.3 - Added missing paragraph. 1.1.4 - Revised to be consistent in text between FPPM and PI. 1.1.4 - Revised text to make reference to the fact that assumed temperature reduced thrust cannot be used when operating the "bump" rating. 1.1.4 - Revised from (C.G.) to (C.G. %MAC) to be consistent with other models. Takeoff Alternate Ratings 1.1.4 - Revised text to encompass bump as well as derate alternate ratings. Section 2 - Takeoff Obstacle Limit 1.2.18-22 - Amended for coverage up to 10000 ft pressure altitude. Brake Energy Limits VMBE 1.2.25 - Added "or improved climb" to footnote to be consistent with text. Slush/Standing Water Takeoff 1.2.38-39 - Amended for coverage up to 10000 ft pressure altitude. 1.2.38-39 - Added note "V1 not to exceed VR" to footnote. Slippery Runway Takeoff 1.2.40-41 - Amended for coverage up to 10000 ft pressure altitude. 1.2.40-41 - Added note "V1 not to exceed VR" to footnote. Section 3 - Takeoff Alternate Ratings Obstacle Limit (24K Derate) 1.3.16-20 - Updated for coverage up to 10000 ft and 50 degree Celsius. Brake Energy Limits VMBE (24K Derate) 1.3.23 - Added "or improved climb" to footnote to be consistent with text. Slush/Standing Water Takeoff (24K Derate) 1.3.36 - Amended for coverage up to 10000 ft pressure altitude. 1.3.36-37 - Added note "V1 not to exceed VR" to footnote. Slippery Runway Takeoff (24K Derate) 1.3.38 - Amended for coverage up to 10000 ft pressure altitude. 1.3.38-39 - Added note "V1 not to exceed VR" to footnote. Obstacle Limit (22K Derate) 1.3.58-62 - Updated for coverage up to 10000 ft and 50 degree Celsius. Brake Energy Limits VMBE (22K Derate) 1.3.64 - Added "or improved climb" to footnote to be consistent with text. Slush/Standing Water Takeoff (22K Derate) 1.3.76 - Amended for coverage up to 10000 ft pressure altitude.

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1.3.76-77 - Added note "V1 not to exceed VR" to footnote. Slippery Runway Takeoff (22K Derate) 1.3.78 - Amended for coverage up to 10000 ft pressure altitude. 1.3.78-79 - Added note "V1 not to exceed VR" to footnote. Section 4 - Landing Landing Field Length Limit 1.4.1-2 - Revised chart to match PD data. 1.4.3-4 - Revised data due to change in BLM modeling. Normal Configuration Landing Distances 1.4.10-11 - Extended coverage for Altitudes up to 14000 ft. 1.4.10 - In cases where the reference distance for lower autobrake settings showed better performance than max autobrake, the reference distance was adjusted to be the same as max autobrake. This was done to more accurately reflect autobrake characteristics on slippery runways. Also, simplified the notes and added a landing distance adjustment for max manual braking using manual speedbrakes. Chapter 2 - FLIGHT PLANNING Section 1 - Text Simplified Flight Planning 2.1.3 - Corrected text to read 10000 ft instead of 1000 ft. Section 2 - Simplified Flight Planning Short Trip Cruise Altitude 2.2.1 - Revised altitude adjustments to match the FMC Supplementary Data Document. Section 3 - Driftdown Net Level Off Weight 2.3.1 - Revised data to reflect speed change. Driftdown Profiles Net Flight Path 2.3.2-5 - Revised data to reflect speed change. Chapter 3 - ENROUTE Section 3 - Engine Inoperative 330 KIAS Cruise Table 3.3.17 - Revised table format to be consistency with other models. Chapter 4 - NON-STANDARD CONFIGURATION Section 1 - Text Gear Down 4.1.1 - Added Gear Down Section. 4.1.1 - Removed "and can account for air conditioning packs off" from Obstacle limit text. 4.1.1 - Added information for adjusting the obstacle limit weight. Section 2 - Gear Down, Planning Landing Climb Limit 4.2.6 - Removed "( )" from degrees in the header.

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Page

Date

FPPM * Title Page * Copyright * 0.0.1-2 * 0.1.1-2 November 1, 2006 November 1, 2006 November 1, 2006 November 1, 2006 Revision Record (tab) * 0.2.1-4 * 0.3.1-2 November 1, 2006 November 1, 2006

NON-STANDARD CONFIGURATION (tab) * 4.TOC.0.1-2 * 4.1.1-2 * 4.2.1-14 * 4.3.1-10 * 4.4.1-8 * 4.5.1-2 November 1, 2006 November 1, 2006 November 1, 2006 November 1, 2006 November 1, 2006 November 1, 2006 (blank tab)

Bulletins (tab) * 0.4.1-2 November 1, 2006

TAKEOFF AND LANDING (tab) * 1.TOC.0.1-2 * 1.1.1-6 * 1.2.1-44 * 1.3.1-82 * 1.4.1-12 November 1, 2006 November 1, 2006 November 1, 2006 November 1, 2006 November 1, 2006

FLIGHT PLANNING (tab) * 2.TOC.0.1-2 * 2.1.1-4 * 2.2.1-16 * 2.3.1-6 * 2.4.1-18 November 1, 2006 November 1, 2006 November 1, 2006 November 1, 2006 November 1, 2006 ENROUTE (tab) * 3.TOC.0.1-2 * 3.1.1-2 * 3.2.1-18 * 3.3.1-24 November 1, 2006 November 1, 2006 November 1, 2006 November 1, 2006

* = Revised, Added, or Deleted

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Bulletin Record

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General

The Boeing Company issues Flight Planning and Performance Manual Bulletins to provide important information prior to the next formal revision of the Flight Planning and Performance Manual. Bulletins are dated and numbered sequentially. When appropriate, the next formal Flight Planning and Performance Manual revision will include an updated bulletin record page to reflect current bulletin status. Bulletin status is defined as follows: · In Effect (IE) ­ the bulletin contains pertinent information not otherwise covered in the Flight Planning and Performance Manual. The bulletin remains active and should be retained in the manual · Incorporated (INC) ­ the bulletin operating information has been incorporated into the Flight Planning and Performance Manual. The bulletin remains active and should be retained in the manual · Cancelled (CANC) ­ the bulletin is no longer active and should be removed from the Flight Planning and Performance Manual. All bulletins previously cancelled are no longer listed in the Bulletin Record. The person filing a new or revised bulletin should amend the Bulletin Record as instructed in the Administrative Information section of the bulletin. When a bulletin includes replacement pages for the Flight Planning and Performance Manual, the included pages should be filed as instructed in the Flight Planning and Performance Manual Information section of the bulletin.

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TAKEOFF AND LANDING Table of Contents

Flight Planning and Performance Manual

TAKEOFF AND LANDING

Table of Contents

1.0 TAKEOFF. AND. LANDING-Table of . . . . . Text . . . . . . . . . . . . . . Contents

Chapter 1

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Introduction . . . . . . . . . . . Takeoff . . . . . . . . . . . . . . Takeoff Alternate Ratings Landing . . . . . . . . . . . . . .

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Takeoff . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1.2.1 Altimeter Setting to Station Pressure . . . . . . . . . . . Wind Component . . . . . . . . . . . . . . . . . . . . . . . . . . Takeoff Field Limit - Dry Runway . . . . . . . . . . . . . Takeoff Field Limit - Wet Runway . . . . . . . . . . . . . Takeoff Climb Limit . . . . . . . . . . . . . . . . . . . . . . . Obstacle Limit . . . . . . . . . . . . . . . . . . . . . . . . . . . . Tire Speed Limit . . . . . . . . . . . . . . . . . . . . . . . . . . Brake Energy Limits VMBE . . . . . . . . . . . . . . . . . Improved Climb Field Length Limit - Dry Runway . Improved Climb Tire Speed Limit - Dry Runway . . Improved Climb Field Length Limit - Wet Runway Improved Climb Tire Speed Limit - Wet Runway . . Slush/Standing Water Takeoff . . . . . . . . . . . . . . . . Slippery Runway Takeoff . . . . . . . . . . . . . . . . . . . Takeoff Speeds - Dry Runway . . . . . . . . . . . . . . . . Takeoff Speeds - Wet Runway . . . . . . . . . . . . . . . . Takeoff %N1 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Stab Trim Setting . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1.2.1 . 1.2.2 . 1.2.3 . 1.2.8 1.2.13 1.2.18 1.2.23 1.2.25 1.2.26 1.2.30 1.2.32 1.2.36 1.2.38 1.2.40 1.2.42 1.2.43 1.2.44 1.2.44

Takeoff Alternate Ratings . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1.3.1 Takeoff Field Limit - Dry Runway (24K Derate) . . . . . . . . . . . . Takeoff Field Limit - Wet Runway (24K Derate) . . . . . . . . . . . . Takeoff Climb Limit (24K Derate) . . . . . . . . . . . . . . . . . . . . . . . Obstacle Limit (24K Derate) . . . . . . . . . . . . . . . . . . . . . . . . . . . Tire Speed Limit (24K Derate) . . . . . . . . . . . . . . . . . . . . . . . . . . Brake Energy Limits VMBE (24K Derate) . . . . . . . . . . . . . . . . . Improved Climb Field Length Limit - Dry Runway (24K Derate) Improved Climb Tire Speed Limit - Dry Runway (24K Derate) . . Improved Climb Field Length Limit - Wet Runway (24K Derate) Improved Climb Tire Speed Limit - Wet Runway (24K Derate) . Slush/Standing Water Takeoff (24K Derate) . . . . . . . . . . . . . . . . Slippery Runway Takeoff (24K Derate) . . . . . . . . . . . . . . . . . . .

Copyright © The Boeing Company. See title page for details.

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737-800/CFM56-7B26 JAA/JAROPS Category C Brakes

Takeoff Speeds - Dry Runway (24K Derate) . . . . . . . . . . . . . . . . . Takeoff Speeds - Wet Runway (24K Derate) . . . . . . . . . . . . . . . . . Takeoff %N1 (24K Derate) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Stab Trim Setting (24K Derate) . . . . . . . . . . . . . . . . . . . . . . . . . . Takeoff Field Limit - Dry Runway (22K Derate) . . . . . . . . . . . . . Takeoff Field Limit - Wet Runway (22K Derate) . . . . . . . . . . . . . Takeoff Climb Limit (22K Derate) . . . . . . . . . . . . . . . . . . . . . . . . Obstacle Limit (22K Derate) . . . . . . . . . . . . . . . . . . . . . . . . . . . . Tire Speed Limit (22K Derate) . . . . . . . . . . . . . . . . . . . . . . . . . . . Brake Energy Limits VMBE (22K Derate) . . . . . . . . . . . . . . . . . . Improved Climb Field Length Limit - Dry Runway (22K Derate) . Improved Climb Tire Speed Limit - Dry Runway (22K Derate) . . . Improved Climb Field Length Limit - Wet Runway (22K Derate) . Improved Climb Tire Speed Limit - Wet Runway (22K Derate) . . . Slush/Standing Water Takeoff (22K Derate) . . . . . . . . . . . . . . . . . Slippery Runway Takeoff (22K Derate) . . . . . . . . . . . . . . . . . . . . Takeoff Speeds - Dry Runway (22K Derate) . . . . . . . . . . . . . . . . . Takeoff Speeds - Wet Runway (22K Derate) . . . . . . . . . . . . . . . . . Takeoff %N1 (22K Derate) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Stab Trim Setting (22K Derate) . . . . . . . . . . . . . . . . . . . . . . . . . .

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1.3.40 1.3.41 1.3.42 1.3.42 1.3.43 1.3.48 1.3.53 1.3.58 1.3.63 1.3.64 1.3.65 1.3.69 1.3.71 1.3.74 1.3.76 1.3.78 1.3.80 1.3.81 1.3.82 1.3.82

Landing . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1.4.1 Landing Field Length Limit . . . . . . . . . . Landing Climb Limit Weight . . . . . . . . . Go-Around Climb Gradient . . . . . . . . . . Quick Turnaround Limit . . . . . . . . . . . . Recommended Brake Cooling Schedule . Normal Configuration Landing Distances . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1.4.1 . 1.4.5 . 1.4.6 . 1.4.8 . 1.4.9 1.4.10

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Text

TAKEOFF AND LANDING Text

Flight Planning and Performance Manual

1.1 TAKEOFF AND LANDING-Text Introduction

This chapter contains data to determine takeoff and landing performance limitations, based on engine bleed effects for normal air conditioning operation and antiice off, i.e., two packs at normal flow, one pack bleed from each engine. The data is presented in simplified form and is therefore conservative. In the event of any conflict between data presented in this section and those contained in the approved Airplane Flight Manual, the Flight Manual shall always take precedence.

accelerate to the decision speed and either stop at the end of the runway or climb to either 35 ft for a dry runway or 15 ft for a wet runway. These field limited weights do not account for clearway or stopway. The reference takeoff condition for a given flap position is zero slope and wind. To determine the field length limit brake release weight, enter the appropriate chart for the desired flap position and runway condition at the left portion of the chart with OAT, move vertically to airport pressure altitude and project a line horizontally to the field length reference line. Enter the right hand portion of the chart with field length available, correct for slope and wind, then continue vertically to intersect the OAT/altitude line projected along the guidelines from the field length reference line. At this intersection, read the field length limit weight to the right. Adjust the field length limit weight according to the notes below the chart to account for the appropriate engine bleed configuration. When finding a maximum weight for a wet runway, the dry runway limit weight must also be found and the lower of the two weights used. Regulations require that the runway length be adjusted to account for alignment of the airplane prior to takeoff. The table below provides TORA, TODA and ASDA adjustments for both 90 degree taxiway entry and 180 degree turnaround. For the 180 degree turnaround case, adjustments are provided for both a nominal 60 m (200 ft) runway as well as the minimum required for the stated minimum pavement width. These values may be used when obtaining takeoff weights from the AFM or a takeoff analysis program. When using line-up allowances with the Field Length Limit chart, the field length available must be reduced by the ASDA adjustment.

180 DEGREE TURNAROUND 60 M (200 FT) 45 M (150 FT) RUNWAY RUNWAY MINIMUM LINE-UP NOMINAL LINE-UP MINIMUM LINE-UP DISTANCE - M (FT) DISTANCE - M (FT) DISTANCE - M (FT) 90 DEGREE TAXIWAY ENTRY TORA & TODA ASDA 11 (35) 26 (86) 19 (64) 35 (115) 19 (64) 35 (115)

Takeoff

The maximum brake release weight is the least of the field length, climb, obstacle, tire speed, brake energy and structural limit weights. Altimeter Setting To Station Pressure The determination of thrust setting and takeoff/landing performance generally requires station pressure altitude. If station pressure or station pressure altitude are not available, enter the chart with altimeter setting (QNH) and read the pressure altitude adjustment. Apply this correction to the station elevation to obtain station pressure altitude. For boundary QNH values, read the midpoint between tabulated corrections to elevation, e.g., for QNH of 29.66 inches (1004 mb), the elevation adjustment is 250 ft. If station pressure (QFE) is required, use conversion scale on left of chart for station pressure altitude versus QFE. Alternatively, station pressure altitude may be determined by setting the cockpit altimeter to 29.92 inches (1013.2 mb); the altimeter will then read station pressure altitude. Wind Component The Wind Component chart provides crosswind and head/tail wind components, appropriate to the runway headings, reported wind velocity and direction. To use the chart, find the intersection between reported wind velocity in knots (circular lines) and the angle in degrees between reported wind direction and the runway (radial lines). Then read head/tail wind component to the left and crosswind component from the bottom scale. Takeoff Field Limit Maximum field length limited brake release weights are presented for the certified takeoff flap settings for dry and wet runways. The field length available is the amount of paved surface which may be used to

Takeoff Climb Limit Maximum climb limited brake release weights are presented for the certified takeoff flap settings. The weights are limited by second segment climb performance and do not account for obstacles. To determine the climb limit weight, enter the appropriate flap position chart with OAT, move vertically to airport pressure altitude, and read the climb limit weight to the left. Adjust the climb limit weight according to the notes below the chart to account for the appropriate engine bleed configuration.

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November 1, 2006

D632A008-ZZ022

1.1.1

TAKEOFF AND LANDING Text

Flight Planning and Performance Manual

737-800/CFM56-7B26 JAA/JAROPS Category C Brakes

Obstacle Limit Obstacle clearance charts are provided for each certified takeoff flap setting. The charts are intended for use only when an airport analysis is not available. Detailed analysis for the specific case from the Airplane Flight Manual may result in a less restrictive weight. The data is not valid for takeoffs using improved climb technique. To determine the obstacle limit weight, enter with obstacle height (measured from the lowest point on the runway) and move horizontally to the obstacle distance from brake release. Follow the guidelines vertically, adjusting for OAT, pressure altitude and wind as necessary. Read obstacle limit weight at the top. Adjust the obstacle limit weight according to the notes below the chart to account for the appropriate engine bleed configuration. When using line-up allowances with the Obstacle Limit chart, the obstacle distance from brake release must be reduced by the ASDA adjustment. Tire Speed Limit Maximum tire speed limited weights are presented for 225 MPH tires. To determine the tire speed limit weight, enter the chart with OAT, move vertically to airport pressure altitude and read the Flaps 1 tire speed limit weight to the left. Adjust the tire speed limit weight according to the notes below the chart to account for flap position and wind. Brake Energy Limit VMBE For normal takeoffs V1 will not generally be limited by maximum brake energy. Brake energy speed limits should be checked at hot/high airports, or when operating with tailwinds and/or improved climb where higher V1's are involved. To determine if brake energy speed (VMBE) is limiting, enter the upper portion of the chart with brake release weight and airport pressure altitude. If inside the shaded area making a normal takeoff with no tailwind, brake energy will not be limiting and VMBE does not need to be checked. If outside the shaded area making a normal takeoff, brake energy may be limiting and VMBE must be checked. Always check VMBE when operating with a tailwind or when using improved climb performance. To check VMBE, move horizontally at the airport pressure altitude to the airport OAT, proceed vertically downwards to the brake release weight and read VMBE to the right. Adjust VMBE for slope and wind. If V1 exceeds VMBE for a normal takeoff, decrease brake release weight as indicated for each knot that V1 exceeds VMBE and determine normal takeoff speeds, V1, VR, and V2 for the lower brake release

weight. If V1 exceeds VMBE for improved climb takeoff, decrease the climb weight improvement by the amount indicated for each knot that V1 exceeds VMBE and determine new V1, VR, and V2 increments for the lower climb weight improvement. Improved Climb Performance If the maximum brake release weight is limited by climb, the climb performance limited weight may be increased by use of improved climb technique. This increase in climb weight is obtained by using the excess runway available to accelerate to higher takeoff speeds thereby achieving higher gradient capability. Charts are provided for determining the climb weight improvement available in terms of the difference between the climb limit weight and either the field or tire limit weight. For a given climb weight improvement the associated takeoff speed increments to be added to the normal V1, VR and V2's are also shown. To determine the maximum allowable climb weight improvement and associated takeoff speed increments, enter the appropriate chart for the desired flap position and runway condition at the left horizontal scale with the weight difference (field or tire limit minus climb limit), move vertically to intersect the line for the appropriate normal climb limit weight, and read climb weight improvement to the left and normal takeoff speed increments to the right adjusting for normal climb limit weight. The horizontal lines indicate the maximum climb weight improvement for normal climb limited weights. These values are based on the maximum allowable improved climb for each flap position. The improved climb weight is the normal climb weight plus the climb weight improvement. The maximum improved climb weight is the lower of the field limit and tire limit improved climb weights. Apply the associated takeoff speed increments to the normal speeds for the improved climb weight. Brake Energy Limits should be checked. Slush/Standing Water Takeoff Experience has shown that aircraft performance may deteriorate significantly on runways covered with snow, slush, standing water or ice. Therefore, reductions in runway/obstacle limited takeoff weight and revised takeoff speeds are necessary. The tables are intended for guidance in accordance with advisory material and assume an engine failure at the critical point during takeoff. The entire runway is assumed to be completely covered by a contaminant of uniform thickness and density. Therefore this information is conservative when

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1.1.2

D632A008-ZZ022

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737-800/CFM56-7B26 JAA/JAROPS Category C Brakes

TAKEOFF AND LANDING Text

Flight Planning and Performance Manual

operating under typical colder weather conditions where patches of slush exist and some degree of sanding is common. Takeoffs in slush depths greater than 13 mm (0.5 inches) are not recommended because of possible airplane damage as a result of slush impingement on the airplane structure. Operation on runways with slush/ standing water depths of more than 6 mm (0.25 inch) is not recommended at altitudes greater than 8,000 ft. The use of assumed temperature method for reduced thrust is not allowed on contaminated runways. Interpolation for slush/standing water depths between the values shown is permitted. Takeoff weight determination: 1. Enter the Weight Adjustment table with the dry field/ obstacle limit weight to obtain the weight reduction for the slush/standing water depth and airport pressure altitude. 2. Adjust field length available for temperature by amount shown beneath V1(MCG) limit weight table. 3. Enter the V1(MCG) Limit Weight table with the adjusted field length and pressure altitude to obtain the slush/standing water limit weight with respect to minimum field length required for V1(MCG) speed. 4. The maximum allowable takeoff weight in slush/ standing water is the lesser of the limit weights found in steps 1 and 3. Takeoff speed determination: 1. Determine takeoff speeds V1, VR and V2 for actual brake release weight using the Dry Runway Takeoff Speeds table for the appropriate flap setting and thrust rating. 2. If V1(MCG) limited, set V1 = V1(MCG). If not limited by V1(MCG) considerations, enter the V1 Adjustment table with actual brake release weight to determine the V1 reduction to apply to V1 speed. If the adjusted V1 is less than V1(MCG), set V1 = V1(MCG). Slippery Runway Takeoff Airplane braking action is reported as good, medium or poor, depending on existing runway conditions. If braking action is reported as good, conditions should not be expected to be as good as on clean, dry runways. The value "good" is comparative and is intended to mean that airplanes should not experience braking or directional control difficulties when stopping. The performance level used to calculate the "good" data is consistent with wet runway testing done on early Boeing jets. The performance level used to calculate the "poor" data reflects a runway covered with wet ice.

Performance is based on a 15 ft screen height at the end of the runway. The tables provided are used in the same manner as the Slush/Standing Water tables. Takeoff Speeds The speeds presented in the Takeoff Speeds table as well as FMC computed takeoff speeds can be used for all performance conditions except where adjustments must be made to V1 for clearway, stopway, anti-skid inoperative, thrust reverser inoperative, improved climb, contaminated runway situations, or brake energy limits. These speeds may be used for weights less than or equal to the performance limited weight. The FMC will protect for minimum control speeds by increasing V1, VR and V2 as required. However, the FMC will not compute takeoff speeds for weights where the required speed increase exceeds the maximum certified speed increase. This typically occurs at full rated thrust and light weights. In this case, the message "V SPEEDS UNAVAILABLE" will appear on the FMC scratchpad and the takeoff speed entries will be blank. Takeoff is not permitted in this condition as certified limits have been exceeded. The options are to select a smaller flap setting, select derate thrust and/or add weight (fuel). Selecting derate thrust is the preferred method as this will reduce the minimum control speeds. Note that the assumed temperature method will not help this condition as the minimum control speeds are determined at the actual temperature and therefore are not reduced. Normal takeoff speeds, V1, VR, and V2 are read from the table by entering with takeoff flap setting and brake release weight. Use the tables provided to correct takeoff speeds for altitude and actual temperature or assumed temperature for reduced thrust takeoffs. Slope and wind adjustments to V1 are obtained by entering the Slope and Wind V1 Adjustment table. If takeoffs are scheduled using these simplified speeds in conjunction with airport analyses that include clearway and/or stopway credits, adjustments to V1 speed are required. Adjust V1 by the amount shown in the Clearway/ Stopway table. The adjusted V1 must not exceed VR. If the adjusted V1 speed is greater than VR, reduce V1 equal to VR. The maximum allowable clearway limits shown on the takeoff speeds page are provided for guidance when more precise data is unavailable.

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November 1, 2006

D632A008-ZZ022

1.1.3

TAKEOFF AND LANDING Text

Flight Planning and Performance Manual

737-800/CFM56-7B26 JAA/JAROPS Category C Brakes

Minimum Control Speeds Regulations prohibit scheduling takeoff with a V1 less than minimum V1 for control on the ground, V1(MCG). It is therefore necessary to compare the adjusted V1 to V1(MCG). The V1(MCG) presented in this manual is conservative for all weight and bleed configurations. To find V1(MCG) enter the V1(MCG) table with the airport pressure altitude and actual OAT. If the adjusted V1 is less than V1(MCG), set V1 equal to V1(MCG). If the adjusted VR is less than V1(MCG), set VR equal to V1(MCG), and determine a new V2 by adding the difference between the normal VR and V1(MCG) to the normal V2. No takeoff weight adjustment is necessary provided that the actual field length exceeds the minimum field length shown on the Takeoff Field Limit charts. Anti-Skid Inoperative When operating with anti-skid inoperative, the field limit weight and V1 must be reduced to account for the effect on accelerate-stop performance. Anti-skid inoperative is only allowed on a dry runway. A simplified method which conservatively accounts for the effects of anti-skid inoperative is to reduce the normal dry field limit and obstacle limit weights by 8500 kg and the V1 associated with the reduced weight by the amount shown in the table below.

ANTI-SKID INOPERATIVE V1 ADJUSTMENTS FIELD LENGTH (M) V1 ADJUSTMENT (KIAS) 2000 -19 2500 -16 3000 -14 3500 -12 4000 -11

normal wet runway/obstacle limited weight by 1050 kg and the V1 associated with the reduced weight by 2 knots. If the resulting V1 is less than minimum V1, takeoff is permitted with V1 set equal to V1(MCG) provided the accelerate-stop distance available corrected for wind and slope exceeds approximately 1200 m. Detailed analysis for the specific case from the Airplane Flight Manual may yield a less restrictive penalty. Takeoff %N1 To find Max Takeoff %N1 based on normal engine bleed for air conditioning packs on, enter Takeoff %N1 Table with airport pressure altitude and airport OAT and read %N1. For packs off apply the %N1 adjustment shown below the table. No takeoff %N1 adjustment is required for engine or wing anti-ice. Assumed Temperature Reduced Thrust Regulations permit the use of up to 25% takeoff thrust reduction for operation with assumed temperature reduced thrust. Use of assumed temperature reduced thrust is not allowed with anti-skid inoperative or on runways contaminated with standing water, ice, slush or snow. Guidance for setting reduced thrust is provided for the flight crew in the Performance Inflight Chapter of the QRH. Use of assumed temperature reduced thrust is not recommended if potential windshear conditions exist. Stab Trim Setting To find takeoff stabilizer trim setting, enter the appropriate Stab Trim Setting table with anticipated brake release weight and center of gravity (C.G. %MAC) and read required stabilizer trim units.

If the resulting V1 is less than minimum V1, takeoff is permitted with V1 set equal to V1(MCG) provided the dry accelerate-stop distance corrected for wind and slope exceeds approximately 1800 m. Detailed analysis for the specific case from the Airplane Flight Manual may yield a less restrictive penalty. Thrust Reverser Inoperative When dispatching on a wet runway with both thrust reversers operative, an operative anti-skid system, and all brakes operating, regulations allow deceleration credit for one thrust reverser in the engine failure case and two thrust reversers in the all engine stop case. When dispatching on a wet runway with one thrust reverser inoperative, the runway/obstacle limited weight and V1 must be reduced to account for the effect on accelerate-stop performance. A simplified method, which conservatively accounts for this, is to reduce the

Takeoff Alternate Ratings

This section contains takeoff performance limitations, thrust settings, takeoff speeds, and stabilizer trim settings for takeoff at alternate engine ratings. The data is provided in the same format as the data shown for the basic thrust rating.

Landing

Charts are provided for determining the maximum landing weight as limited by field length or climb requirements for flap positions 30 and 40. Maximum performance landing weight is the smaller of the field length limit weight and climb limit weight; do not exceed maximum structural landing weight.

Copyright © The Boeing Company. See title page for details.

1.1.4

D632A008-ZZ022

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737-800/CFM56-7B26 JAA/JAROPS Category C Brakes

TAKEOFF AND LANDING Text

Flight Planning and Performance Manual

Landing Field Length Limit To determine the field length limit landing weight, enter the appropriate field length limit chart with field length available and correct for wind and runway condition. Proceed vertically to the airport pressure altitude and read the field length limited weight at the right. Landing Climb Limit Weight To determine climb limit weight, enter the climb limit chart with airport OAT, move vertically to airport pressure altitude and read the climb limit weight to the left. Adjust the climb limit weight according to the notes below the chart to account for the appropriate engine bleed configuration. When operating in icing conditions during any part of the flight with forecast landing temperature below 10°C, make the appropriate ice correction as shown on the chart. Go-Around Climb Gradient To determine go-around climb gradient, enter the chart with airport OAT and pressure altitude and then proceed vertically to find airplane weight. Continue down the chart to the proper airspeed in terms of deviation from VREF, following the reference lines as appropriate. Read the go-around climb gradient directly from the chart and then apply the necessary corrections for engine bleed configuration and icing conditions as noted. Quick Turnaround Limit Maximum quick turnaround weights are presented for flap positions 30 and 40. If landing weight exceeds the maximum quick turnaround weight for the airport OAT and pressure altitude shown in the table, adjusted for slope and wind, wait the specified time and check that the wheel thermal plugs have not melted before executing a subsequent takeoff or ensure the brake temperature is within limits using the alternate procedure described on the page. Recommended Brake Cooling Schedule The Recommended Brake Cooling Schedule chart is advisory information intended to assist the operator in avoiding problems associated with hot brakes. The Maximum Quick Turnaround Weight table takes precedence over the brake cooling schedule in case of conflict. For normal operations most landings are at weights below the quick turnaround limit. Application of the recommended cooling procedures shown will avoid brake overheat and fuse plug problems that could result from repeated landings at short time intervals or a rejected takeoff. The chart shows the brake energy per brake added by a single stop. Total brake energy is

assumed to be equally distributed among the operating brakes. Total brake energy is the sum of the residual energy from previous stops plus the energy added. To determine the brake energy added by a single stop enter the top of the chart with weight, proceed horizontally to the brakes on indicated airspeed corrected for wind, then vertically downwards adjusting for airport pressure altitude and OAT. If the ground speed at brakes on is known from the navigation display, use ground speed and ignore the wind, airport pressure altitude, and OAT corrections. The chart is based on a rejected takeoff with maximum manual braking effort. Make the adjustments shown for braking during normal landing using either maximum manual braking effort or a preselected autobrake setting. Increase the brake energy per brake by one million foot pounds for every mile of taxi distance. Continue vertically downwards at the brake energy per brake to determine the recommended cooling procedures. In general, the brakes on indicated airspeed during landing will be 5-7 knots lower than approach speed when recommended braking procedures are followed due to deceleration in the flare to touchdown. To conservatively account for wind gusts, adjust the brakes on speed by subtracting one-half the headwind or adding 1.5 times the tailwind. Brake Temperature Monitor System (BTMS) indications are also shown. If brake cooling is determined from the BTMS, use the hottest brake indication 10 to 15 minutes after the airplane has come to a complete stop, or inflight with gear retracted to determine recommended cooling schedule. CAT III Automatic Landing The following advisory information is presented to assist operators in determining landing field length corrections with CAT III Autoland. This guidance information may be used to comply with NPA JARAWO-2, All Weather Operations. To obtain CAT III Autoland field lengths, enter the Landing Field Length Limit chart for the selected flap, read field length required for a given weight, then add 125 m (400 ft) to this field length to obtain JAA Autoland Landing field length required. To determine the maximum CAT III Autoland weight when landing field length available is known, subtract 125 m (400 ft) from field length available and enter the Landing Field Length Limit chart for the selected flap to read maximum landing weight.

Copyright © The Boeing Company. See title page for details.

November 1, 2006

D632A008-ZZ022

1.1.5

TAKEOFF AND LANDING Text

Flight Planning and Performance Manual

737-800/CFM56-7B26 JAA/JAROPS Category C Brakes

Normal Configuration Landing Distance The normal configuration landing distance tables are provided as advisory information to help determine the actual landing distance performance of the airplane for different runway surface conditions and brake configurations. Flaps 30 and 40 landing distances and adjustments are provided for dry runways as well as runways with good, medium, and poor reported braking actions, which are commonly referred to as slippery runway conditions. Landing distances for slippery runways are 115% of the actual landing distances. If the surface is affected by water, snow or ice, and the braking action is reported as "good", conditions should not be expected to be as good as on clean, dry runways. The value "good" is comparative and is intended to mean that airplanes should not experience braking or directional control difficulties when landing. The performance level used to calculate the "good" data is consistent with wet runway testing done on early Boeing jets. The performance level used to calculate "poor" data reflects runways covered with wet ice. Dry runway landing performance is shown for max manual braking configuration and autobrake settings max, 3, 2, and 1. Use of autobrake setting 1 is not recommended for landings on slippery runways, and is therefore not provided for these conditions. The autobrake performance may be used to assist in the selection of the most desirable autobrake setting for a given field length. Selection of an autobrake setting results in a constant rate of deceleration. Maximum effort manual braking should achieve shorter landing distance than the max autobrake setting. The reference landing distance is a reference distance from 50 ft above the threshold to stop based on a reference landing weight and normal approach speed for the selected landing flap at sea level, zero wind, zero slope, and two engine detent reverse thrust. Subsequent columns provide adjustments for off-reference landing weight, altitude, wind, slope, temperature, speed, and reverse thrust. Each adjustment is independently added to the reference landing distance.

Copyright © The Boeing Company. See title page for details.

1.1.6

D632A008-ZZ022

November 1, 2006

737-800/CFM56-7B26 JAA/JAROPS Category C Brakes

TAKEOFF AND LANDING Takeoff

Flight Planning and Performance Manual

Takeoff

1.2 TAKEOFF Setting to Station Pressure Altimeter AND LANDING-Takeoff

QFE Station Pressure

QNH to Pressure Altitude

QNH (IN. HG.) 28.81 28.91 CORRECTION TO ELEVATION FOR PRESS ALT (FT) 28.91 29.02 29.12 29.23 29.34 29.44 29.55 29.66 29.76 29.87 29.97 30.08 30.19 30.30 30.41 30.52 30.63 30.74 30.85 30.96 31.07 1000 900 800 700 600 500 400 300 200 100 0 -100 -200 -300 -400 -500 -600 -700 -800 -900 -1000 976 979 983 986 990 994 997 1001 1004 1008 1012 1015 1019 1022 1026 1030 1034 1037 1041 1045 1048 QNH (MILLIBARS)

MBS

1000 FT

700

10

to to to to to to to to to to to to to to to to to to to to to

to to to to to to to to to to to to to to to to to to to to to

979 983 986 990 994 997 1001 1004 1008 1012 1015 1019 1022 1026 1030 1034 1037 1041 1045 1048 1052

9

29.02 29.12

750

8

29.23 29.34

7

29.44

800 6

29.55 29.66

850

5

29.76 29.87

4

29.97 30.08

900 3

30.19 30.30 30.41

2 950

1 1000 0

30.52 30.63 30.74 30.85

1050

-1

30.96 Example:

-2

1100

Elevation = 2500 FT QNH = 29.48 IN. HG. Correction = 400 FT Press Alt = 2900 FT

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November 1, 2006

D632A008-ZZ022

1.2.1

TAKEOFF AND LANDING Takeoff

Flight Planning and Performance Manual

Takeoff

737-800/CFM56-7B26 JAA/JAROPS Category C Brakes

Wind Component

50

ANGL E BE 10 AND R TWEEN W UNWA IND D IR Y (D EGREECTION ES) 20

70

40

65

W VE 60 TY CI LO

D IN

WIND COMPONENT PARALLEL TO RUNWAY (KTS)

30

55 ) TS (K

40

30

50 45

50

40

35

20

30 25

60

70

20

10

10 5

15

80

0

90

100

-10

110

12

13 0 14 0

0

15

-20

170

0

160

0

10

20 30 40 CROSSWIND COMPONENT (KTS)

50

60

Copyright © The Boeing Company. See title page for details.

1.2.2

D632A008-ZZ022

November 1, 2006

737-800/CFM56-7B26 JAA/JAROPS Category C Brakes

TAKEOFF AND LANDING Takeoff

Flight Planning and Performance Manual

Takeoff Field Limit - Dry Runway

Flaps 1

Based on engine bleed for packs on and anti-ice off

88

84

-2 -1 0

80

76

1

2

3

4

72

68

5

6

7

9

64

AIR

PO

RT

MINIMUM FIELD LENGTH

ENV

10 PR E (10 SSU RE 00 FT AL ) TIT U

TAL LIMI

8

60

IRON

MEN

56

52

DE

48 REF LINE

44

F

WIND (KTS)

-60 -40 -20 0 20 40 60 80 100 120 140 -60 -50 -40 -30 -20 -10 0 10 20 30 40 50 60 70 HEAD 40 C AIRPORT OAT 20 REF LINE 0 -10 TAIL REF LINE

40

2 0

-2 5 6 7 8 9 10 11 12 13 1000 FT 4 DOWN 100 M 12 14 16 18 20 22 24 26 28 30 32 34 36 38 40 42 FIELD LENGTH AVAILABLE

With engine bleed for packs off, increase weight by 350 kg. With engine anti-ice on, decrease weight by 200 kg. With engine and wing anti-ice on, decrease weight by 750 kg (optional system).

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November 1, 2006

D632A008-ZZ022

RUNWAY SLOPE (%)

UP

1.2.3

FIELD LENGTH LIMIT BRAKE RELEASE WEIGHT

T

(1000 KG)

TAKEOFF AND LANDING Takeoff

Flight Planning and Performance Manual

737-800/CFM56-7B26 JAA/JAROPS Category C Brakes

Takeoff Field Limit - Dry Runway

Flaps 5

Based on engine bleed for packs on and anti-ice off

88

84

-2 -1 0

80

1

2

3

4

76

72

5

6

7

9 10

68

64

AIR

TAL LIMI T

8

PO RT

60

MINIMUM FIELD LENGTH

ENV

PR E (10 SSU RE 00 FT AL ) TIT UD E

IRON

56

52

48 REF LINE

44

F

WIND (KTS)

-60 -40 -20 0 20 40 60 80 100 120 140 -60 -50 -40 -30 -20 -10 0 10 20 30 40 50 60 70 HEAD 40 C AIRPORT OAT 20 REF LINE 0 -10 TAIL REF LINE

40

2 0

-2 5 6 7 8 9 10 11 12 13 1000 FT 4 DOWN 100 M 12 14 16 18 20 22 24 26 28 30 32 34 36 38 40 42 FIELD LENGTH AVAILABLE

With engine bleed for packs off, increase weight by 350 kg. With engine anti-ice on, decrease weight by 200 kg. With engine and wing anti-ice on, decrease weight by 950 kg (optional system).

Copyright © The Boeing Company. See title page for details.

1.2.4

D632A008-ZZ022

November 1, 2006

RUNWAY SLOPE (%)

UP

FIELD LENGTH LIMIT BRAKE RELEASE WEIGHT

MEN

(1000 KG)

737-800/CFM56-7B26 JAA/JAROPS Category C Brakes

TAKEOFF AND LANDING Takeoff

Flight Planning and Performance Manual

Takeoff Field Limit - Dry Runway

Flaps 10

Based on engine bleed for packs on and anti-ice off

88

84

-2 -1 0

80

1

2

3

4

76

72

5

6

7

68

8

AIR

9

64

PO

RT

10

PR E (10 SSU RE 00 FT AL TIT ) UD E

60

56 MINIMUM FIELD LENGTH

52

48 REF LINE

44

F

WIND (KTS)

-60 -40 -20 0 20 40 60 80 100 120 140 -60 -50 -40 -30 -20 -10 0 10 20 30 40 50 60 70 HEAD 40 C AIRPORT OAT 20 REF LINE 0 -10 TAIL REF LINE

40

2 0

-2 5 6 7 8 9 10 11 12 13 1000 FT 4 DOWN 100 M 12 14 16 18 20 22 24 26 28 30 32 34 36 38 40 42 FIELD LENGTH AVAILABLE

With engine bleed for packs off, increase weight by 400 kg. With engine anti-ice on, decrease weight by 200 kg. With engine and wing anti-ice on, decrease weight by 950 kg (optional system).

Copyright © The Boeing Company. See title page for details.

November 1, 2006

D632A008-ZZ022

RUNWAY SLOPE (%)

UP

1.2.5

FIELD LENGTH LIMIT BRAKE RELEASE WEIGHT

ENV

IRON

MEN

TAL LIMI

T

(1000 KG)

TAKEOFF AND LANDING Takeoff

Flight Planning and Performance Manual

737-800/CFM56-7B26 JAA/JAROPS Category C Brakes

Takeoff Field Limit - Dry Runway

Flaps 15

Based on engine bleed for packs on and anti-ice off

88

-2 -1 0

84

1

2

3

4

80

76

5

6

7

72

68

8

AI

9

RP

OR T

10

PR E (10 SSU 00 R FT E A LT ) ITU DE

TAL LIMIT

64

60

IRON

56 MINIMUM FIELD LENGTH

52

48 REF LINE

44

F

WIND (KTS)

-60 -40 -20 0 20 40 60 80 100 120 140 -60 -50 -40 -30 -20 -10 0 10 20 30 40 50 60 70 HEAD 40 C AIRPORT OAT 20 REF LINE 0 -10 TAIL REF LINE

40

2 0

-2 5 6 7 8 9 10 11 12 13 1000 FT 4 DOWN 100 M 12 14 16 18 20 22 24 26 28 30 32 34 36 38 40 42 FIELD LENGTH AVAILABLE

With engine bleed for packs off, increase weight by 400 kg. With engine anti-ice on, decrease weight by 200 kg. With engine and wing anti-ice on, decrease weight by 950 kg (optional system).

Copyright © The Boeing Company. See title page for details.

1.2.6

D632A008-ZZ022

November 1, 2006

RUNWAY SLOPE (%)

UP

FIELD LENGTH LIMIT BRAKE RELEASE WEIGHT

ENV

MEN

(1000 KG)

737-800/CFM56-7B26 JAA/JAROPS Category C Brakes

TAKEOFF AND LANDING Takeoff

Flight Planning and Performance Manual

Takeoff Field Limit - Dry Runway

Flaps 25

Based on engine bleed for packs on and anti-ice off

88

-2 -1 0

84

1

2

3

4

80

76

5

6

7

72

68

TAL LIMIT

8

AIR

9

64

PO

RT

10

PR E (10 SSU RE 00 FT AL TIT ) UD

IRON

MEN

60

56 MINIMUM FIELD LENGTH

ENV

E

52

48 REF LINE

44

F

WIND (KTS)

-60 -40 -20 0 20 40 60 80 100 120 140 -60 -50 -40 -30 -20 -10 0 10 20 30 40 50 60 70 HEAD 40 C AIRPORT OAT 20 REF LINE 0 -10 TAIL REF LINE

40

2 0

-2 5 6 7 8 9 10 11 12 13 1000 FT 4 DOWN 100 M 12 14 16 18 20 22 24 26 28 30 32 34 36 38 40 42 FIELD LENGTH AVAILABLE

With engine bleed for packs off, increase weight by 400 kg. With engine anti-ice on, decrease weight by 200 kg. With engine and wing anti-ice on, decrease weight by 950 kg (optional system).

Copyright © The Boeing Company. See title page for details.

November 1, 2006

D632A008-ZZ022

RUNWAY SLOPE (%)

UP

1.2.7

FIELD LENGTH LIMIT BRAKE RELEASE WEIGHT

(1000 KG)

TAKEOFF AND LANDING Takeoff

Flight Planning and Performance Manual

737-800/CFM56-7B26 JAA/JAROPS Category C Brakes

Takeoff Field Limit - Wet Runway

Flaps 1

Based on engine bleed for packs on and anti-ice off

88

84

80

-2 -1 0

76

2

3

4

72

68

5

6

7

64

AI

RP

9

OR T

MINIMUM FIELD LENGTH

ENV

10 PR E (10 SSU RE 00 FT AL ) TIT UD E

TAL LIMI T

8

60

56

IRON

52

48 REF LINE

44

F

WIND (KTS)

-60 -40 -20 0 20 40 60 80 100 120 140 -60 -50 -40 -30 -20 -10 0 10 20 30 40 50 60 70 HEAD 40 C AIRPORT OAT 20 REF LINE 0 -10 TAIL REF LINE

40

2 0

-2 5 6 7 8 9 10 11 12 13 1000 FT 4 DOWN 100 M 12 14 16 18 20 22 24 26 28 30 32 34 36 38 40 42 FIELD LENGTH AVAILABLE

With engine bleed for packs off, increase weight by 350 kg. With engine anti-ice on, decrease weight by 200 kg. With engine and wing anti-ice on, decrease weight by 800 kg (optional system).

Copyright © The Boeing Company. See title page for details.

1.2.8

D632A008-ZZ022

November 1, 2006

RUNWAY SLOPE (%)

UP

FIELD LENGTH LIMIT BRAKE RELEASE WEIGHT

1

MEN

(1000 KG)

737-800/CFM56-7B26 JAA/JAROPS Category C Brakes

TAKEOFF AND LANDING Takeoff

Flight Planning and Performance Manual

Takeoff Field Limit - Wet Runway

Flaps 5

Based on engine bleed for packs on and anti-ice off

88

84

-2 -1 0

80

1

2

3

4

76

72

5

6

7

68

64

8

AI RP

TAL LIMI

9

OR T

10

PR E (10 SSU 00 R FT E A LT ) ITU

60

56 MINIMUM FIELD LENGTH

ENV

DE

52

48 REF LINE

44

F

WIND (KTS)

-60 -40 -20 0 20 40 60 80 100 120 140 -60 -50 -40 -30 -20 -10 0 10 20 30 40 50 60 70 HEAD 40 C AIRPORT OAT 20 REF LINE 0 -10 TAIL REF LINE

40

2 0

-2 5 6 7 8 9 10 11 12 13 1000 FT 4 DOWN 100 M 12 14 16 18 20 22 24 26 28 30 32 34 36 38 40 42 FIELD LENGTH AVAILABLE

With engine bleed for packs off, increase weight by 350 kg. With engine anti-ice on, decrease weight by 200 kg. With engine and wing anti-ice on, decrease weight by 800 kg (optional system).

Copyright © The Boeing Company. See title page for details.

November 1, 2006

D632A008-ZZ022

RUNWAY SLOPE (%)

UP

1.2.9

FIELD LENGTH LIMIT BRAKE RELEASE WEIGHT

IRON

MEN

T

(1000 KG)

TAKEOFF AND LANDING Takeoff

Flight Planning and Performance Manual

737-800/CFM56-7B26 JAA/JAROPS Category C Brakes

Takeoff Field Limit - Wet Runway

Flaps 10

Based on engine bleed for packs on and anti-ice off

88

84

-2 -1 0

80

1

2

3

4

76

72

5

6

7

68

64

TAL LIMI T

8

AIR

9

60

PO

RT

MINIMUM FIELD LENGTH

ENV

10 PR E (10 SSU RE 00 FT AL ) TIT U

56

DE

52

48 REF LINE

44

F

WIND (KTS)

-60 -40 -20 0 20 40 60 80 100 120 140 -60 -50 -40 -30 -20 -10 0 10 20 30 40 50 60 70 HEAD 40 C AIRPORT OAT 20 REF LINE 0 -10 TAIL REF LINE

40

2 0

-2 5 6 7 8 9 10 11 12 13 1000 FT 4 DOWN 100 M 12 14 16 18 20 22 24 26 28 30 32 34 36 38 40 42 FIELD LENGTH AVAILABLE

With engine bleed for packs off, increase weight by 350 kg. With engine anti-ice on, decrease weight by 200 kg. With engine and wing anti-ice on, decrease weight by 800 kg (optional system).

Copyright © The Boeing Company. See title page for details.

1.2.10

D632A008-ZZ022

November 1, 2006

RUNWAY SLOPE (%)

UP

FIELD LENGTH LIMIT BRAKE RELEASE WEIGHT

IRON

MEN

(1000 KG)

737-800/CFM56-7B26 JAA/JAROPS Category C Brakes

TAKEOFF AND LANDING Takeoff

Flight Planning and Performance Manual

Takeoff Field Limit - Wet Runway

Flaps 15

Based on engine bleed for packs on and anti-ice off

88

84

-2 -1 0

80

1

2

3

76

72

4

5

6

7

9

68

64

TAL LIMIT

8

AIR PO

RT

10

PR E (10 SSU RE 00 FT AL TIT ) UD E

60

56 MINIMUM FIELD LENGTH

52

48 REF LINE

44

F

WIND (KTS)

-60 -40 -20 0 20 40 60 80 100 120 140 -60 -50 -40 -30 -20 -10 0 10 20 30 40 50 60 70 HEAD 40 C AIRPORT OAT 20 REF LINE 0 -10 TAIL REF LINE

40

2 0

-2 5 6 7 8 9 10 11 12 13 1000 FT 4 DOWN 100 M 12 14 16 18 20 22 24 26 28 30 32 34 36 38 40 42 FIELD LENGTH AVAILABLE

With engine bleed for packs off, increase weight by 350 kg. With engine anti-ice on, decrease weight by 200 kg. With engine and wing anti-ice on, decrease weight by 800 kg (optional system).

Copyright © The Boeing Company. See title page for details.

November 1, 2006

D632A008-ZZ022

1.2.11

RUNWAY SLOPE (%)

UP

FIELD LENGTH LIMIT BRAKE RELEASE WEIGHT

ENV

IRON

MEN

(1000 KG)

TAKEOFF AND LANDING Takeoff

Flight Planning and Performance Manual

737-800/CFM56-7B26 JAA/JAROPS Category C Brakes

Takeoff Field Limit - Wet Runway

Flaps 25

Based on engine bleed for packs on and anti-ice off

88

84

-2 -1 0

80

1

2

3

4

76

72

5

6

7

9

68

AIR

PO

TAL LIMIT

8

RT

64

MINIMUM FIELD LENGTH

ENV

PR E (10 SSU RE 00 FT AL ) TIT UD E

10

60

IRON

56

52

48 REF LINE

44

F

WIND (KTS)

-60 -40 -20 0 20 40 60 80 100 120 140 -60 -50 -40 -30 -20 -10 0 10 20 30 40 50 60 70 HEAD 40 C AIRPORT OAT 20 REF LINE 0 -10 TAIL REF LINE

40

2 0

-2 5 6 7 8 9 10 11 12 13 1000 FT 4 DOWN 100 M 12 14 16 18 20 22 24 26 28 30 32 34 36 38 40 42 FIELD LENGTH AVAILABLE

With engine bleed for packs off, increase weight by 350 kg. With engine anti-ice on, decrease weight by 200 kg. With engine and wing anti-ice on, decrease weight by 800 kg (optional system).

Copyright © The Boeing Company. See title page for details.

1.2.12

D632A008-ZZ022

November 1, 2006

RUNWAY SLOPE (%)

UP

FIELD LENGTH LIMIT BRAKE RELEASE WEIGHT

MEN

(1000 KG)

737-800/CFM56-7B26 JAA/JAROPS Category C Brakes

TAKEOFF AND LANDING Takeoff

Flight Planning and Performance Manual

Takeoff Climb Limit

Flaps 1

Based on engine bleed for packs on and anti-ice off

90

86

-2 -1 0 1

82

2 3

78 (1000 KG) 4 5 6 70 7 8

L L IM ENV IRO NME

74

CLIMB LIMIT BRAKE RELEASE WEIGHT

9 10

62

AIRPORT PRESSURE ALTITUDE (1000 FT)

58

54

50

46 -60

-60 -50

-40 -40

-20 0 -30 -20

20 40 60 80 100 -10 0 10 20 30 40 AIRPORT OAT

120 50

NTA

IT

66

140 60

70

F C

With engine bleed for packs off, increase weight by 1400 kg. With engine anti-ice on, decrease weight by 250 kg. With engine and wing anti-ice on (optional system), decrease weight by 1450 kg.

Copyright © The Boeing Company. See title page for details.

November 1, 2006

D632A008-ZZ022

1.2.13

TAKEOFF AND LANDING Takeoff

Flight Planning and Performance Manual

737-800/CFM56-7B26 JAA/JAROPS Category C Brakes

Takeoff Climb Limit

Flaps 5

Based on engine bleed for packs on and anti-ice off

86 -2 -1 0 1 2 78 3 74 (1000 KG) 4 5 70 6 7 66 8 9 62 10 AIRPORT PRESSURE ALTITUDE (1000 FT)

82

CLIMB LIMIT BRAKE RELEASE WEIGHT

58

54

50

46

42 -60

-60 -50

-40 -40

-20 0 -30 -20

20 40 60 80 100 -10 0 10 20 30 40 AIRPORT OAT

ENV

IRO

NME

120 50

NTA

L L IM

IT

140 60

70

F C

With engine bleed for packs off, increase weight by 1250 kg. With engine anti-ice on, decrease weight by 250 kg. With engine and wing anti-ice on (optional system), decrease weight by 1400 kg.

Copyright © The Boeing Company. See title page for details.

1.2.14

D632A008-ZZ022

November 1, 2006

737-800/CFM56-7B26 JAA/JAROPS Category C Brakes

TAKEOFF AND LANDING Takeoff

Flight Planning and Performance Manual

Takeoff Climb Limit

Flaps 10

Based on engine bleed for packs on and anti-ice off

82

78

-2 -1 0 1

74

2 3

(1000 KG)

70

4 5

CLIMB LIMIT BRAKE RELEASE WEIGHT

66

6 7

62 8 9 58 10 AIRPORT PRESSURE ALTITUDE (1000 FT)

L L IMIT ENV IRO NME

54

50

46

42 -60

-60 -50

-40 -40

-20 0 -30 -20

20 40 60 80 100 -10 0 10 20 30 40 AIRPORT OAT

120 50

NTA

140 60

70

F C

With engine bleed for packs off, increase weight by 1150 kg. With engine anti-ice on, decrease weight by 250 kg. With engine and wing anti-ice on (optional system), decrease weight by 1300 kg.

Copyright © The Boeing Company. See title page for details.

November 1, 2006

D632A008-ZZ022

1.2.15

TAKEOFF AND LANDING Takeoff

Flight Planning and Performance Manual

737-800/CFM56-7B26 JAA/JAROPS Category C Brakes

Takeoff Climb Limit

Flaps 15

Based on engine bleed for packs on and anti-ice off

78 -2 -1 0 74 1 2 70 3 4 (1000 KG) 66 5 6 62 7 8 9 10 54 AIRPORT PRESSURE ALTITUDE (1000 FT)

L L IMIT ENV IRO NME

CLIMB LIMIT BRAKE RELEASE WEIGHT

58

50

46

42

38 -60

-60 -50

-40 -40

-20 0 -30 -20

20 40 60 80 100 -10 0 10 20 30 40 AIRPORT OAT

120 50

NTA

140 60

70

F C

With engine bleed for packs off, increase weight by 1100 kg. With engine anti-ice on, decrease weight by 200 kg. With engine and wing anti-ice on (optional system), decrease weight by 1300 kg.

Copyright © The Boeing Company. See title page for details.

1.2.16

D632A008-ZZ022

November 1, 2006

737-800/CFM56-7B26 JAA/JAROPS Category C Brakes

TAKEOFF AND LANDING Takeoff

Flight Planning and Performance Manual

Takeoff Climb Limit

Flaps 25

Based on engine bleed for packs on and anti-ice off

78

74

-2 -1 0 1

70

2 3

(1000 KG)

66

4 5

CLIMB LIMIT BRAKE RELEASE WEIGHT

62

6 7

58

8 9

L L IMIT ENV IRO NME

54

AIRPORT PRESSURE ALTITUDE (1000 FT) 50

46

42

38 -60

-60 -50

-40 -40

-20 0 -30 -20

20 40 60 80 100 -10 0 10 20 30 40 AIRPORT OAT

120 50

NTA

10

140 60

70

F C

With engine bleed for packs off, increase weight by 1100 kg. With engine anti-ice on, decrease weight by 200 kg. With engine and wing anti-ice on (optional system), decrease weight by 1250 kg.

Copyright © The Boeing Company. See title page for details.

November 1, 2006

D632A008-ZZ022

1.2.17

TAKEOFF AND LANDING Takeoff

Flight Planning and Performance Manual

737-800/CFM56-7B26 JAA/JAROPS Category C Brakes

Obstacle Limit

Flaps 1

Based on engine bleed for packs on and anti-ice off

OBSTACLE LIMIT WEIGHT 40 HEAD 40 WIND (KTS) 20 0 REF LINE 50 60 70 (1000 KG) 80 90

TAIL 20 PRESS ALT (1000 FT) 10 5 0 ( C) ( F) 50 120 40 OAT 30 20 10 0 (M) 300 40 (FT)

85 80 75 70 65 60 55 50 45

REF LINE

100 REF LINE 80 60

40

35

30

DI E AK BR ) M OM 00 FR (1 CE SE AN A ST ELE R

90

OBSTACLE HEIGHT

800

25

200

600 400 200

100

0

0

When using line-up allowances, the obstacle distance from brake release must be reduced by the ASDA adjustment. Obstacle height must be calculated from the lowest point of the runway to conservatively account for runway slope. With engine bleed for packs off, increase weight by 650 kg. With engine anti-ice on, decrease weight by 250 kg. With engine and wing anti-ice on, decrease weight by 1550 kg (optional system).

Copyright © The Boeing Company. See title page for details.

1.2.18

D632A008-ZZ022

November 1, 2006

737-800/CFM56-7B26 JAA/JAROPS Category C Brakes

TAKEOFF AND LANDING Takeoff

Flight Planning and Performance Manual

Obstacle Limit

Flaps 5

Based on engine bleed for packs on and anti-ice off

OBSTACLE LIMIT WEIGHT 40 HEAD 40 WIND (KTS) 20 0 REF LINE 50 60 70 (1000 KG) 80 90

TAIL 20 PRESS ALT (1000 FT) 10 5 0 ( C) ( F) 50 120 40 OAT 30 20 10 0 (M) 300 40 (FT)

85 80 75 70 65 60 55 50 45

40

35

REF LINE

100 REF LINE 80 60

90

DI

30

E AK BR ) M OM 00 FR (1 CE SE AN A ST ELE R

OBSTACLE HEIGHT

800

25

200

600 400 200

100

0

0

When using line-up allowances, the obstacle distance from brake release must be reduced by the ASDA adjustment. Obstacle height must be calculated from the lowest point of the runway to conservatively account for runway slope. With engine bleed for packs off, increase weight by 650 kg. With engine anti-ice on, decrease weight by 250 kg. With engine and wing anti-ice on, decrease weight by 1550 kg (optional system).

Copyright © The Boeing Company. See title page for details.

November 1, 2006

D632A008-ZZ022

1.2.19

TAKEOFF AND LANDING Takeoff

Flight Planning and Performance Manual

737-800/CFM56-7B26 JAA/JAROPS Category C Brakes

Obstacle Limit

Flaps 10

Based on engine bleed for packs on and anti-ice off

OBSTACLE LIMIT WEIGHT 40 HEAD 40 WIND (KTS) 20 0 REF LINE 50 60 70 (1000 KG) 80 90

TAIL 20 PRESS ALT (1000 FT) 10 5 0 ( C) ( F) 50 120 40 OAT 30 20 10 0 (M) 300 40 (FT)

90 85 80 75 70 65 60 55 50 45 40

35

REF LINE

100 REF LINE 80 60

DI

OBSTACLE HEIGHT

800 200

25

600 400 200

30

E AK BR ) M OM 0 FR (10 CE E AN AS ST ELE R

100

0

0

When using line-up allowances, the obstacle distance from brake release must be reduced by the ASDA adjustment. Obstacle height must be calculated from the lowest point of the runway to conservatively account for runway slope. With engine bleed for packs off, increase weight by 650 kg. With engine anti-ice on, decrease weight by 250 kg. With engine and wing anti-ice on, decrease weight by 1550 kg (optional system).

Copyright © The Boeing Company. See title page for details.

1.2.20

D632A008-ZZ022

November 1, 2006

737-800/CFM56-7B26 JAA/JAROPS Category C Brakes

TAKEOFF AND LANDING Takeoff

Flight Planning and Performance Manual

Obstacle Limit

Flaps 15

Based on engine bleed for packs on and anti-ice off

OBSTACLE LIMIT WEIGHT 40 HEAD 40 WIND (KTS) 20 0 REF LINE 50 60 70 (1000 KG) 80 90

TAIL 20 PRESS ALT (1000 FT) 10 5 0 ( C) ( F) 50 120 40 OAT 30 20 10 0 (M) 300 40 (FT)

85 80 75 70 65 60 55 50 45 40

35

REF LINE

100 REF LINE 80 60

90

DI

OBSTACLE HEIGHT

800 200

25

600 400 200

30

E AK BR ) M OM 0 FR (10 CE E AN AS ST ELE R

100

0

0

When using line-up allowances, the obstacle distance from brake release must be reduced by the ASDA adjustment. Obstacle height must be calculated from the lowest point of the runway to conservatively account for runway slope. With engine bleed for packs off, increase weight by 650 kg. With engine anti-ice on, decrease weight by 250 kg. With engine and wing anti-ice on, decrease weight by 1550 kg (optional system).

Copyright © The Boeing Company. See title page for details.

November 1, 2006

D632A008-ZZ022

1.2.21

TAKEOFF AND LANDING Takeoff

Flight Planning and Performance Manual

737-800/CFM56-7B26 JAA/JAROPS Category C Brakes

Obstacle Limit

Flaps 25

Based on engine bleed for packs on and anti-ice off

OBSTACLE LIMIT WEIGHT 40 HEAD 40 WIND (KTS) 20 0 REF LINE 50 60 70 (1000 KG) 80 90

TAIL 20 PRESS ALT (1000 FT) 10 5 0 ( C) ( F) 50 120 40 OAT 30 20 10 0 (M) 300 40 (FT) 100 REF LINE 80 60 REF LINE

90 85 80 75 70 65 60 55 50 45 40

35

DI E AK BR ) OM 0 M FR (10 CE E AN AS ST ELE R

OBSTACLE HEIGHT

800 200

25

600 400 200

30

100

0

0

When using line-up allowances, the obstacle distance from brake release must be reduced by the ASDA adjustment. Obstacle height must be calculated from the lowest point of the runway to conservatively account for runway slope. With engine bleed for packs off, increase weight by 650 kg. With engine anti-ice on, decrease weight by 250 kg. With engine and wing anti-ice on, decrease weight by 1550 kg (optional system).

Copyright © The Boeing Company. See title page for details.

1.2.22

D632A008-ZZ022

November 1, 2006

737-800/CFM56-7B26 JAA/JAROPS Category C Brakes

TAKEOFF AND LANDING Takeoff

Flight Planning and Performance Manual

Tire Speed Limit

Flaps 1

88

0

1

84

2

3

(1000 KG)

4

80

5

6

7

TIRE SPEED LIMIT WEIGHT

76

8

AI O RP RT PR

10

9

72

ES SU RE TI AL

68

TU DE (1 00 0

64

FT )

60 -60

-60 -50

-40 -40

-20 0 -30 -20

20 40 60 80 100 -10 0 10 20 30 40 AIRPORT OAT

120 50

140 60

70

F C

Increase tire speed limit weight by 500 kg per knot headwind. Decrease tire speed limit weight by 1100 kg per knot tailwind.

Copyright © The Boeing Company. See title page for details.

November 1, 2006

D632A008-ZZ022

1.2.23

TAKEOFF AND LANDING Takeoff

Flight Planning and Performance Manual

737-800/CFM56-7B26 JAA/JAROPS Category C Brakes

Tire Speed Limit

Flaps 5

88

3

84

4

(1000 KG)

5

R AI RT PO

6

80

7

TIRE SPEED LIMIT WEIGHT

8

SU ES PR

9

76

10

UD

RE

TIT AL

72

E (10 00 FT )

68

64 -60

-60 -50

-40 -40

-20 0 -30 -20

20 40 60 80 100 -10 0 10 20 30 40 AIRPORT OAT

120 50

140 60

70

F C

Increase tire speed limit weight by 600 kg per knot headwind. Decrease tire speed limit weight by 1100 kg per knot tailwind.

Copyright © The Boeing Company. See title page for details.

1.2.24

D632A008-ZZ022

November 1, 2006

737-800/CFM56-7B26 JAA/JAROPS Category C Brakes

TAKEOFF AND LANDING Takeoff

Flight Planning and Performance Manual

Brake Energy Limits VMBE

AIRPORT PRESSURE ALTITUDE (1000 FT) 10 8 6 4 2 0 -2 40 50 60 70 80 BRAKE RELEASE WEIGHT (1000 KG)

E R (10 ELEA 00 SE KG W ) EIG 42 HT

AIR PO RT

OA T

°C

( °F

)

50

(12

2)

-50 (-40 58) ( -30 -40) (-20 22) -10 ( -4) (1 0 4) 30 20 10 ( 32) ( 86 ( 68 ( 50 ) 40 ) ) (10 4)

210

200

BR

190

46

AK

50

62

66

170

70

74

78

82

86

160

150

140

Check VMBE when outside shaded area or when operating with tailwind or improved climb. Increase VMBE by 1 knots per 1% uphill runway slope. Decrease VMBE by 4 knots per 1% downhill runway slope. Increase VMBE by 3 knots per 10 knots headwind. Decrease VMBE by 19 knots per 10 knots tailwind. Normal takeoff: Decrease brake release weight by 500 kg for each knot V1 exceeds VMBE. Determine normal V1, VR, V2 speeds for lower brake release weight. Improved climb takeoff: Determine climb weight improvement by 200 kg for each knot V1 exceeds VMBE. Determine V1, VR, V2 speed increments for the lower climb weight improvement.

Copyright © The Boeing Company. See title page for details.

November 1, 2006

D632A008-ZZ022

1.2.25

VMBE (KIAS)

58

54

180

TAKEOFF AND LANDING Takeoff

Flight Planning and Performance Manual

737-800/CFM56-7B26 JAA/JAROPS Category C Brakes

Improved Climb Field Length Limit - Dry Runway

Flaps 1

NORMAL TAKEOFF SPEED INCREMENT (KIAS) V1 VR V2 7

90 6 (1000 KG)

GH T

22 80 70 20 18 16 14 60 50 12 10 9 8 7 6 5 4 3 REF LINE

CL I (1 MB 00 0 LIM KG IT ) W EI

5

28 26 24 22 20 18 16 14 12 10 9 8 7 6 5 4 3 2 1

26 24 22 20 18 16 14 12 10 9 8 7 6 5 4 3 2 1

CLIMB WEIGHT IMPROVEMENT

4

NO RM

3

2

1

AL

2 1

0 0 4 8 12 16 (FIELD LIMIT WEIGHT) MINUS (CLIMB LIMIT WEIGHT) (1000 KG) 20 50

60 70 80 90 NORMAL CLIMB LIMIT WEIGHT (1000 KG)

Copyright © The Boeing Company. See title page for details.

1.2.26

D632A008-ZZ022

November 1, 2006

737-800/CFM56-7B26 JAA/JAROPS Category C Brakes

TAKEOFF AND LANDING Takeoff

Flight Planning and Performance Manual

Improved Climb Field Length Limit - Dry Runway

Flaps 5

NORMAL TAKEOFF SPEED INCREMENT (KIAS) V1 VR V2 6 90

(1000 KG)

CL I (1 MB 00 0 LIMI KG T W ) EI G

5

HT

80 18 16 14 12 10 9 8 7 6 40 5 4 3 REF LINE 24 22 20 18 16 14 12 10 9 8 7 6 5 4 3 2 1 1 22 20 18 16 14 12 10 9 8 7 6 5 4 3 2 1

70

CLIMB WEIGHT IMPROVEMENT

4

60 50

2

1

NO

RM

3

AL

2

0 0 4 8 12 16 (FIELD LIMIT WEIGHT) MINUS (CLIMB LIMIT WEIGHT) (1000 KG) 20 50

60 70 80 90 NORMAL CLIMB LIMIT WEIGHT (1000 KG)

Copyright © The Boeing Company. See title page for details.

November 1, 2006

D632A008-ZZ022

1.2.27

TAKEOFF AND LANDING Takeoff

Flight Planning and Performance Manual

737-800/CFM56-7B26 JAA/JAROPS Category C Brakes

Improved Climb Field Length Limit - Dry Runway

Flaps 10

NORMAL TAKEOFF SPEED INCREMENT (KIAS) V1 VR V2

CL I (1 MB 00 0 LIM KG IT ) W EI G HT

(1000 KG)

3

CLIMB WEIGHT IMPROVEMENT

80 70 60 50

2

1

REF LINE

12 11 10 9 8 7 6 5 4 3 2 1 70 80

RM

18 16 14 12 10 8 6 5 4 3 2 1

16 14 12 10 8 6 5 4 3 2 1

0 0 4 8 12 16 50 (FIELD LIMIT WEIGHT) MINUS (CLIMB LIMIT WEIGHT) (1000 KG)

NO

AL

60

NORMAL CLIMB LIMIT WEIGHT (1000 KG)

Copyright © The Boeing Company. See title page for details.

1.2.28

D632A008-ZZ022

November 1, 2006

737-800/CFM56-7B26 JAA/JAROPS Category C Brakes

TAKEOFF AND LANDING Takeoff

Flight Planning and Performance Manual

Improved Climb Field Length Limit - Dry Runway

Flaps 15

NORMAL TAKEOFF SPEED INCREMENT (KIAS) V1 VR V2

(1000 KG)

3

EI G

HT

CLIMB WEIGHT IMPROVEMENT

CL I (1 MB 00 0 LIM KG IT W )

80 70 60 50

12 10 8 6 5 4 3 2 1 70 80

2

RM AL

18 16 14 12 10 8 6 5 4 3 2 1

16 14 12 10 8 6 5 4 3 2 1

NO

1

0 0 4 8 12 16 50 (FIELD LIMIT WEIGHT) MINUS (CLIMB LIMIT WEIGHT) (1000 KG)

NORMAL CLIMB LIMIT WEIGHT (1000 KG)

Flaps 25

(1000 KG)

REF LINE 60

NO R LI MA M L I (1 T W CL 00 0 EIG IMB KG H ) T

2

NORMAL TAKEOFF SPEED INCREMENT (KIAS) V1 VR V2 80 70 60 50 REF LINE 12 10 8 6 4 2 1 70 80 18 16 14 12 10 8 6 4 2 1 16 14 12 10 8 6 4 2 1

CLIMB WEIGHT IMPROVEMENT

1

0 0 4 8 12 16 50 (FIELD LIMIT WEIGHT) MINUS (CLIMB LIMIT WEIGHT) (1000 KG)

60

NORMAL CLIMB LIMIT WEIGHT (1000 KG)

Copyright © The Boeing Company. See title page for details.

November 1, 2006

D632A008-ZZ022

1.2.29

TAKEOFF AND LANDING Takeoff

Flight Planning and Performance Manual

737-800/CFM56-7B26 JAA/JAROPS Category C Brakes

Improved Climb Tire Speed Limit - Dry Runway

Flaps 1

NORMAL TAKEOFF SPEED INCREMENT (KIAS) V1 VR V2 90 6 (1000 KG)

G EI H T

7

80

22 20 18

26 24 22 20 18 16 14 12 10 9 8 7 6 5 4 3 2 1

24 22 20 18 16 14 12 10 9 8 7 6 5 4 3 2 1

5

CLIMB WEIGHT IMPROVEMENT

4

N O R M

IT M LI G) B M 0K LI C 100 ( AL

W

70

16 14

60

12 10 9 8 7 6 5 4 REF LINE

50 3

2

1

3 2 1

0 0 4 8 12 16 20 (TIRE LIMIT WEIGHT) MINUS (CLIMB LIMIT WEIGHT) (1000 KG) 24 28 50

60 70 80 90 NORMAL CLIMB LIMIT WEIGHT (1000 KG)

Copyright © The Boeing Company. See title page for details.

1.2.30

D632A008-ZZ022

November 1, 2006

737-800/CFM56-7B26 JAA/JAROPS Category C Brakes

TAKEOFF AND LANDING Takeoff

Flight Planning and Performance Manual

Improved Climb Tire Speed Limit - Dry Runway

Flaps 5

NORMAL TAKEOFF SPEED INCREMENT (KIAS) V1 VR V2 6 90

(1000 KG)

EI G

H

T

5

C L (1 IMB 00 0 LIM KG IT ) W

80 16 14 12 10 9 8 7 6 5 4 3 REF LINE 20 18 16 14 12 10 9 8 7 6 5 4 3 2 1 1 20 18 16 14 12 10 9 8 7 6 5 4 3 2 1

70

CLIMB WEIGHT IMPROVEMENT

4

60

R

3

N

M

AL

50

2

1

O

2

0 0 4 8 12 16 20 (TIRE LIMIT WEIGHT) MINUS (CLIMB LIMIT WEIGHT) (1000 KG) 24 28 50

60 70 80 90 NORMAL CLIMB LIMIT WEIGHT (1000 KG)

Copyright © The Boeing Company. See title page for details.

November 1, 2006

D632A008-ZZ022

1.2.31

TAKEOFF AND LANDING Takeoff

Flight Planning and Performance Manual

737-800/CFM56-7B26 JAA/JAROPS Category C Brakes

Improved Climb Field Length Limit - Wet Runway

Flaps 1

NORMAL TAKEOFF SPEED INCREMENT (KIAS) V1 VR V2

7

90 (1000 KG)

EI GH

6

T

CL I (1 MB 00 0 LIM KG IT W )

80 18 70 60 12 50 10 9 8 7 6 5 4 REF LINE 3 2 1 16 14 22 20 18 16 14 12 10 9 8 7 6 5 4 3 2 1 20 18 16 14 12 10 9 8 7 6 5 4 3 2 1

5

CLIMB WEIGHT IMPROVEMENT

3

2

1

0 0 4 8 12 16 (FIELD LIMIT WEIGHT) MINUS (CLIMB LIMIT WEIGHT) (1000 KG) 20 50

NO

RM

4

AL

60 70 80 90 NORMAL CLIMB LIMIT WEIGHT (1000 KG)

Copyright © The Boeing Company. See title page for details.

1.2.32

D632A008-ZZ022

November 1, 2006

737-800/CFM56-7B26 JAA/JAROPS Category C Brakes

TAKEOFF AND LANDING Takeoff

Flight Planning and Performance Manual

Improved Climb Field Length Limit - Wet Runway

Flaps 5

NORMAL TAKEOFF SPEED INCREMENT (KIAS) V1 VR V2

6

90

(1000 KG)

EI GH T

5

80 18 16 14 12 10 9 8 7 6 5 4 3 REF LINE 22 20 18 16 14 12 10 9 8 7 6 5 4 3 2 1 1 20 18 16 14 12 10 9 8 7 6 5 4 3 2 1

CL I (1 MB 00 0 LIM KG IT W )

70

CLIMB WEIGHT IMPROVEMENT

4

60

NO

3

RM

AL

50

2

1

2

0 0 4 8 12 16 (FIELD LIMIT WEIGHT) MINUS (CLIMB LIMIT WEIGHT) (1000 KG) 20 50

60 70 80 90 NORMAL CLIMB LIMIT WEIGHT (1000 KG)

Copyright © The Boeing Company. See title page for details.

November 1, 2006

D632A008-ZZ022

1.2.33

TAKEOFF AND LANDING Takeoff

Flight Planning and Performance Manual

737-800/CFM56-7B26 JAA/JAROPS Category C Brakes

Improved Climb Field Length Limit - Wet Runway

Flaps 10

(1000 KG) NORMAL TAKEOFF SPEED INCREMENT (KIAS) V1 VR V2

3

CLIMB WEIGHT IMPROVEMENT

2

1

N

O

R

M

M LI ) B KG M 0 LI C 100 ( AL

IT

W

G EI

H

T

80 70 60 50 10 9 8 7 6 5 4 3 2 1 70 80 14 12 10 8 6 5 4 3 2 1 14 12 10 8 6 5 4 3 2 1

0 0 4 8 12 16 50 (FIELD LIMIT WEIGHT) MINUS (CLIMB LIMIT WEIGHT) (1000 KG)

NORMAL CLIMB LIMIT WEIGHT (1000 KG)

Copyright © The Boeing Company. See title page for details.

REF LINE 60

1.2.34

D632A008-ZZ022

November 1, 2006

737-800/CFM56-7B26 JAA/JAROPS Category C Brakes

TAKEOFF AND LANDING Takeoff

Flight Planning and Performance Manual

Improved Climb Field Length Limit - Wet Runway

Flaps 15

(1000 KG) NORMAL TAKEOFF SPEED INCREMENT (KIAS) V1 VR V2 80 70 60 50 10 8 6 5 4 3 2 1 70 80 16 14 12 10 8 6 5 4 3 2 1 14 12 10 8 6 5 4 3 2 1

3

CL (1 IMB 00 0 LIM KG IT ) W EI G HT

CLIMB WEIGHT IMPROVEMENT

2

1

NO

RM

AL

0 0 4 8 12 16 50 (FIELD LIMIT WEIGHT) MINUS (CLIMB LIMIT WEIGHT) (1000 KG)

NORMAL CLIMB LIMIT WEIGHT (1000 KG)

Flaps 25

(1000 KG) NORMAL TAKEOFF SPEED INCREMENT (KIAS) V1 VR V2 2

B M LI HT C G I AL WE G) M K R IT NO IM 000 L (1

CLIMB WEIGHT IMPROVEMENT

80 70 60 50 REF LINE 10 8 6 4 3 2 1 70 80 14 12 10 8 6 4 3 2 1 12 10 8 6 4 3 2 1

1

0 0 4 8 12 16 50 (FIELD LIMIT WEIGHT) MINUS (CLIMB LIMIT WEIGHT) (1000 KG)

REF LINE 60 60 NORMAL CLIMB LIMIT WEIGHT (1000 KG)

Copyright © The Boeing Company. See title page for details.

November 1, 2006

D632A008-ZZ022

1.2.35

TAKEOFF AND LANDING Takeoff

Flight Planning and Performance Manual

737-800/CFM56-7B26 JAA/JAROPS Category C Brakes

Improved Climb Tire Speed Limit - Wet Runway

Flaps 1

NORMAL TAKEOFF SPEED INCREMENT (KIAS) V1 VR V2 90 6 (1000 KG)

G EI H T

7

80

22 20 18

26 24 22 20 18 16 14 12 10 9 8 7 6 5 4 3 2 1

24 22 20 18 16 14 12 10 9 8 7 6 5 4 3 2 1

5

CLIMB WEIGHT IMPROVEMENT

4

N O R M

IT M LI G) B M 0K LI C 100 ( AL

W

70

16 14

60

12 10 9 8 7 6 5 4 REF LINE

50 3

2

1

3 2 1

0 0 4 8 12 16 20 (TIRE LIMIT WEIGHT) MINUS (CLIMB LIMIT WEIGHT) (1000 KG) 24 28 50

60 70 80 90 NORMAL CLIMB LIMIT WEIGHT (1000 KG)

Copyright © The Boeing Company. See title page for details.

1.2.36

D632A008-ZZ022

November 1, 2006

737-800/CFM56-7B26 JAA/JAROPS Category C Brakes

TAKEOFF AND LANDING Takeoff

Flight Planning and Performance Manual

Improved Climb Tire Speed Limit - Wet Runway

Flaps 5

NORMAL TAKEOFF SPEED INCREMENT (KIAS) V1 VR V2 6 90

(1000 KG)

EI G

H

T

5

C L (1 IMB 00 0 LIM KG IT ) W

80 16 14 12 10 9 8 7 6 5 4 3 REF LINE 20 18 16 14 12 10 9 8 7 6 5 4 3 2 1 1 20 18 16 14 12 10 9 8 7 6 5 4 3 2 1

70

CLIMB WEIGHT IMPROVEMENT

4

60

R

3

N

M

AL

50

2

1

O

2

0 0 4 8 12 16 20 (TIRE LIMIT WEIGHT) MINUS (CLIMB LIMIT WEIGHT) (1000 KG) 24 28 50

60 70 80 90 NORMAL CLIMB LIMIT WEIGHT (1000 KG)

Copyright © The Boeing Company. See title page for details.

November 1, 2006

D632A008-ZZ022

1.2.37

TAKEOFF AND LANDING Takeoff

Flight Planning and Performance Manual

737-800/CFM56-7B26 JAA/JAROPS Category C Brakes

ADVISORY INFORMATION

Slush/Standing Water Takeoff

Maximum Reverse Thrust Weight Adjustments (1000 KG)

DRY FIELD/OBSTACLE LIMIT WEIGHT (1000 KG) 95 90 85 80 75 70 65 60 55 50 45 40 3 mm (0.12 INCHES) PRESSURE ALTITUDE (FT) S.L. 5000 10000 -12.7 -15.0 -17.3 -11.7 -14.0 -16.3 -10.7 -13.0 -15.3 -9.7 -12.0 -14.3 -8.8 -11.0 -13.3 -7.8 -10.1 -12.3 -6.9 -9.2 -11.4 -6.0 -8.3 -10.5 -5.2 -7.4 -9.7 -4.3 -6.6 -8.9 -3.5 -5.8 -8.1 -2.8 -5.0 -7.3 SLUSH/STANDING WATER DEPTH 6 mm (0.25 INCHES) PRESSURE ALTITUDE (FT) S.L. 5000 10000 -15.6 -17.8 -20.1 -14.2 -16.5 -18.7 -12.8 -15.1 -17.4 -11.5 -13.8 -16.0 -10.2 -12.5 -14.7 -9.0 -11.2 -13.5 -7.8 -10.0 -12.3 -6.7 -8.9 -11.2 -5.6 -7.9 -10.2 -4.7 -6.9 -9.2 -3.8 -6.0 -8.3 -2.9 -5.2 -7.5 SLUSH/STANDING WATER DEPTH 6 mm (0.25 INCHES) PRESSURE ALTITUDE (FT) S.L. 5000 10000 45.4 65.2 86.8 13 mm (0.50 INCHES) PRESSURE ALTITUDE (FT) S.L. 5000 10000 -21.5 -23.8 -26.0 -19.4 -21.7 -23.9 -17.3 -19.6 -21.8 -15.2 -17.5 -19.7 -13.2 -15.5 -17.8 -11.4 -13.6 -15.9 -9.7 -11.9 -14.2 -8.1 -10.4 -12.7 -6.7 -9.0 -11.2 -5.4 -7.7 -10.0 -4.3 -6.6 -8.8 -3.3 -5.5 -7.8

V1(MCG) Limit Weight (1000 KG)

ADJUSTED FIELD LENGTH (M) 1200 1400 1600 1800 2000 2200 3 mm (0.12 INCHES) PRESSURE ALTITUDE (FT) S.L. 5000 10000 41.8 61.5 83.3 13 mm (0.50 INCHES) PRESSURE ALTITUDE (FT) S.L. 5000 10000 33.4 51.5 36.3 71.1 54.6 39.2 92.5 74.4 57.7 96.1 77.8 99.7

44.9 64.9 87.1

48.0 68.4 90.9

48.5 68.5 90.5

32.8 51.7 72.0 94.1

1. Enter Weight Adjustment table with slush/standing water depth and dry field/obstacle limit weight to obtain slush/standing water weight adjustment. 2. Adjust field length available by -30 m/+30 m for every 5°C above/below 4°C. 3. Find V1(MCG) limit weight for adjusted field length and pressure altitude. 4. Max allowable slush/standing water limited weight is lesser of weights from 1 and 3.

V1 Adjustment (KIAS)

WEIGHT (1000 KG) 90 85 80 75 70 65 60 55 50 45 40 3 mm (0.12 INCHES) PRESSURE ALTITUDE (FT) S.L. 5000 10000 -15 -10 -5 -16 -11 -6 -18 -13 -8 -19 -14 -9 -20 -15 -10 -21 -16 -11 -22 -17 -12 -23 -18 -13 -24 -19 -14 -25 -20 -15 -25 -20 -15 SLUSH/STANDING WATER DEPTH 6 mm (0.25 INCHES) PRESSURE ALTITUDE (FT) S.L. 5000 10000 -7 -2 0 -10 -5 0 -12 -7 -2 -14 -9 -4 -16 -11 -6 -17 -12 -7 -19 -14 -9 -20 -15 -10 -22 -17 -12 -23 -18 -13 -24 -19 -14 13 mm (0.50 INCHES) PRESSURE ALTITUDE (FT) S.L. 5000 10000 0 0 0 0 0 0 0 0 0 0 0 0 -4 0 0 -8 -3 0 -11 -6 -1 -14 -9 -4 -17 -12 -7 -19 -14 -9 -21 -16 -11

1. Obtain V1, VR and V2 for the actual weight using the Dry Runway Takeoff Speeds table. 2. If V1(MCG) limited, set V1 = V1(MCG). If not V1(MCG) limited, enter V1 Adjustment table with the actual weight to obtain V1 speed adjustment. If adjusted V1 is less than V1(MCG), set V1 = V1(MCG). V1 not to exceed VR.

Copyright © The Boeing Company. See title page for details.

1.2.38

D632A008-ZZ022

November 1, 2006

737-800/CFM56-7B26 JAA/JAROPS Category C Brakes

TAKEOFF AND LANDING Takeoff

Flight Planning and Performance Manual

ADVISORY INFORMATION

Slush/Standing Water Takeoff

No Reverse Thrust Weight Adjustments (1000 KG)

DRY FIELD/OBSTACLE LIMIT WEIGHT (1000 KG) 95 90 85 80 75 70 65 60 55 50 45 40 3 mm (0.12 INCHES) PRESSURE ALTITUDE (FT) S.L. 5000 10000 -14.6 -17.3 -20.1 -13.6 -16.3 -19.1 -12.6 -15.4 -18.1 -11.7 -14.4 -17.1 -10.6 -13.3 -16.0 -9.5 -12.2 -14.9 -8.4 -11.1 -13.8 -7.3 -10.0 -12.8 -6.3 -9.0 -11.7 -5.4 -8.1 -10.9 -4.7 -7.4 -10.1 -4.0 -6.7 -9.5 SLUSH/STANDING WATER DEPTH 6 mm (0.25 INCHES) PRESSURE ALTITUDE (FT) S.L. 5000 10000 -17.7 -20.4 -23.1 -16.3 -19.0 -21.7 -14.9 -17.6 -20.3 -13.5 -16.2 -18.9 -12.0 -14.8 -17.5 -10.6 -13.4 -16.1 -9.3 -12.0 -14.7 -8.0 -10.7 -13.4 -6.8 -9.5 -12.3 -5.8 -8.5 -11.2 -4.9 -7.6 -10.4 -4.1 -6.9 -9.6 SLUSH/STANDING WATER DEPTH 6 mm (0.25 INCHES) PRESSURE ALTITUDE (FT) S.L. 5000 10000 32.3 56.0 37.9 81.3 61.9 43.5 87.6 67.9 94.0 13 mm (0.50 INCHES) PRESSURE ALTITUDE (FT) S.L. 5000 10000 -23.9 -26.6 -29.3 -21.7 -24.4 -27.1 -19.4 -22.1 -24.9 -17.2 -19.9 -22.6 -15.0 -17.8 -20.5 -13.1 -15.8 -18.5 -11.2 -13.9 -16.7 -9.5 -12.2 -15.0 -8.0 -10.7 -13.4 -6.6 -9.3 -12.0 -5.4 -8.1 -10.8 -4.2 -6.9 -9.6

V1(MCG) Limit Weight (1000 KG)

ADJUSTED FIELD LENGTH (M) 1600 1800 2000 2200 2400 3 mm (0.12 INCHES) PRESSURE ALTITUDE (FT) S.L. 5000 10000 46.7 73.2 101.8 13 mm (0.50 INCHES) PRESSURE ALTITUDE (FT) S.L. 5000 10000 47.4 31.6 69.3 52.5 36.5 92.9 74.7 57.6 98.6 80.3 104.3

52.8 79.9

33.6 59.0 86.7

1. Enter Weight Adjustment table with slush/standing water depth and dry field/obstacle limit weight to obtain slush/standing water weight adjustment. 2. Adjust field length available by -45 m/+45 m for every 5°C above/below 4°C. 3. Find V1(MCG) limit weight for adjusted field length and pressure altitude. 4. Max allowable slush/standing water limited weight is lesser of weights from 1 and 3.

V1 Adjustment (KIAS)

WEIGHT (1000 KG) 90 85 80 75 70 65 60 55 50 45 40 3 mm (0.12 INCHES) PRESSURE ALTITUDE (FT) S.L. 5000 10000 -20 -10 0 -22 -12 -2 -24 -14 -4 -25 -15 -5 -27 -17 -7 -28 -18 -8 -29 -19 -9 -30 -20 -10 -31 -21 -11 -32 -22 -12 -32 -22 -12 SLUSH/STANDING WATER DEPTH 6 mm (0.25 INCHES) PRESSURE ALTITUDE (FT) S.L. 5000 10000 -11 -1 0 -14 -4 0 -16 -6 0 -19 -9 0 -21 -11 -1 -23 -13 -3 -25 -15 -5 -27 -17 -7 -28 -18 -8 -30 -20 -10 -31 -21 -11 13 mm (0.50 INCHES) PRESSURE ALTITUDE (FT) S.L. 5000 10000 0 0 0 0 0 0 0 0 0 0 0 0 -6 0 0 -11 -1 0 -15 -5 0 -19 -9 0 -22 -12 -2 -25 -15 -5 -27 -17 -7

1. Obtain V1, VR and V2 for the actual weight using the Dry Runway Takeoff Speeds table. 2. If V1(MCG) limited, set V1 = V1(MCG). If not V1(MCG) limited, enter V1 Adjustment table with the actual weight to obtain V1 speed adjustment. If adjusted V1 is less than V1(MCG), set V1 = V1(MCG). V1 not to exceed VR.

Copyright © The Boeing Company. See title page for details.

November 1, 2006

D632A008-ZZ022

1.2.39

TAKEOFF AND LANDING Takeoff

Flight Planning and Performance Manual

737-800/CFM56-7B26 JAA/JAROPS Category C Brakes

ADVISORY INFORMATION

Slippery Runway Takeoff

Maximum Reverse Thrust Weight Adjustments (1000 KG)

DRY FIELD/OBSTACLE LIMIT WEIGHT (1000 KG) 95 90 85 80 75 70 65 60 55 50 45 40 GOOD PRESSURE ALTITUDE (FT) S.L. 5000 10000 -0.8 -0.8 -0.8 -1.0 -1.0 -1.0 -1.3 -1.3 -1.3 -1.4 -1.4 -1.4 -1.5 -1.5 -1.5 -1.6 -1.6 -1.6 -1.5 -1.5 -1.5 -1.5 -1.5 -1.5 -1.3 -1.3 -1.3 -1.1 -1.1 -1.1 -0.8 -0.8 -0.8 -0.5 -0.5 -0.5 REPORTED BRAKING ACTION MEDIUM PRESSURE ALTITUDE (FT) S.L. 5000 10000 -6.4 -6.4 -6.4 -6.4 -6.4 -6.4 -6.3 -6.3 -6.3 -6.1 -6.1 -6.1 -5.9 -5.9 -5.9 -5.7 -5.7 -5.7 -5.4 -5.4 -5.4 -5.0 -5.0 -5.0 -4.5 -4.5 -4.5 -4.0 -4.0 -4.0 -3.4 -3.4 -3.4 -2.8 -2.8 -2.8 REPORTED BRAKING ACTION MEDIUM PRESSURE ALTITUDE (FT) S.L. 5000 10000 POOR PRESSURE ALTITUDE (FT) S.L. 5000 10000 -11.5 -11.5 -11.5 -11.1 -11.1 -11.1 -10.6 -10.6 -10.6 -10.1 -10.1 -10.1 -9.6 -9.6 -9.6 -9.0 -9.0 -9.0 -8.4 -8.4 -8.4 -7.6 -7.6 -7.6 -6.9 -6.9 -6.9 -6.1 -6.1 -6.1 -5.2 -5.2 -5.2 -4.3 -4.3 -4.3

V1(MCG) Limit Weight (1000 KG)

ADJUSTED FIELD LENGTH (M) 1000 1200 1400 1600 1800 2000 2200 2400 2600 2800 GOOD PRESSURE ALTITUDE (FT) S.L. 5000 10000 39.6 72.0 57.3 42.4 103.9 89.4 74.8 POOR PRESSURE ALTITUDE (FT) S.L. 5000 10000

46.2 69.6 95.6

31.3 53.3 77.5 104.1

38.1 60.6 85.6

41.6 55.7 71.2 88.8

40.7 54.7 70.1 87.5

39.8 53.7 69.0 86.3

1. Enter Weight Adjustment table with reported braking action and dry field/obstacle limit weight to obtain slippery runway weight adjustment. 2. Adjust "Good" field length available by -20 m/+20 m for every 5°C above/below 4°C. Adjust "Medium" field length available by -20 m/+20 m for every 5°C above/below 4°C. Adjust "Poor" field length available by -35 m/+35 m for every 5°C above/below 4°C. 3. Find V1(MCG) limit weight for adjusted field length and pressure altitude. 4. Max allowable slippery runway limited weight is lesser of weights from 1 and 3.

V1 Adjustment (KIAS)

WEIGHT (1000 KG) 90 85 80 75 70 65 60 55 50 45 40 GOOD PRESSURE ALTITUDE (FT) S.L. 5000 10000 -5 -2 0 -6 -3 -1 -7 -4 -2 -8 -5 -3 -9 -6 -4 -9 -7 -4 -10 -8 -5 -11 -9 -6 -12 -9 -7 -13 -10 -8 -14 -11 -9 REPORTED BRAKING ACTION MEDIUM PRESSURE ALTITUDE (FT) S.L. 5000 10000 -13 -11 -8 -15 -13 -10 -17 -14 -12 -18 -16 -13 -20 -17 -15 -21 -19 -16 -22 -20 -17 -24 -21 -19 -25 -22 -20 -26 -24 -21 -27 -25 -22 POOR PRESSURE ALTITUDE (FT) S.L. 5000 10000 -25 -23 -20 -27 -24 -22 -29 -26 -24 -31 -28 -26 -33 -30 -28 -35 -32 -30 -37 -34 -32 -38 -36 -33 -40 -37 -35 -41 -39 -36 -42 -40 -37

1. Obtain V1, VR and V2 for the actual weight using the Dry Runway Takeoff Speeds table. 2. If V1(MCG) limited, set V1 = V1(MCG). If not V1(MCG) limited, enter V1 Adjustment table with the actual weight to obtain V1 speed adjustment. If adjusted V1 is less than V1(MCG), set V1 = V1(MCG). V1 not to exceed VR.

Copyright © The Boeing Company. See title page for details.

1.2.40

D632A008-ZZ022

November 1, 2006

737-800/CFM56-7B26 JAA/JAROPS Category C Brakes

TAKEOFF AND LANDING Takeoff

Flight Planning and Performance Manual

ADVISORY INFORMATION

Slippery Runway Takeoff

No Reverse Thrust Weight Adjustments (1000 KG)

DRY FIELD/OBSTACLE LIMIT WEIGHT (1000 KG) 95 90 85 80 75 70 65 60 55 50 45 40 GOOD PRESSURE ALTITUDE (FT) S.L. 5000 10000 -2.1 -2.1 -2.1 -2.4 -2.4 -2.4 -2.7 -2.7 -2.7 -2.9 -2.9 -2.9 -3.1 -3.1 -3.1 -3.2 -3.2 -3.2 -3.2 -3.2 -3.2 -3.1 -3.1 -3.1 -3.0 -3.0 -3.0 -2.8 -2.8 -2.8 -2.5 -2.5 -2.5 -2.2 -2.2 -2.2 REPORTED BRAKING ACTION MEDIUM PRESSURE ALTITUDE (FT) S.L. 5000 10000 -9.3 -9.3 -9.3 -9.2 -9.2 -9.2 -9.1 -9.1 -9.1 -9.0 -9.0 -9.0 -8.7 -8.7 -8.7 -8.4 -8.4 -8.4 -8.0 -8.0 -8.0 -7.5 -7.5 -7.5 -7.0 -7.0 -7.0 -6.3 -6.3 -6.3 -5.6 -5.6 -5.6 -4.8 -4.8 -4.8 REPORTED BRAKING ACTION MEDIUM PRESSURE ALTITUDE (FT) S.L. 5000 10000 POOR PRESSURE ALTITUDE (FT) S.L. 5000 10000 -15.9 -15.9 -15.9 -15.2 -15.2 -15.2 -14.5 -14.5 -14.5 -13.8 -13.8 -13.8 -13.0 -13.0 -13.0 -12.2 -12.2 -12.2 -11.3 -11.3 -11.3 -10.4 -10.4 -10.4 -9.4 -9.4 -9.4 -8.4 -8.4 -8.4 -7.3 -7.3 -7.3 -6.2 -6.2 -6.2

V1(MCG) Limit Weight (1000 KG)

ADJUSTED FIELD LENGTH (M) 1200 1400 1600 2000 2200 2400 3200 3400 3600 3800 GOOD PRESSURE ALTITUDE (FT) S.L. 5000 10000 38.0 86.5 67.4 43.5 89.8 POOR PRESSURE ALTITUDE (FT) S.L. 5000 10000

72.9

33.7 86.8

53.8 100.0 75.7 70.0 63.9 101.4

1. Enter Weight Adjustment table with reported braking action and dry field/obstacle limit weight to obtain slippery runway weight adjustment. 2. Adjust "Good" field length available by -25 m/+25 m for every 5°C above/below 4°C. Adjust "Medium" field length available by -25 m/+25 m for every 5°C above/below 4°C. Adjust "Poor" field length available by -40 m/+40 m for every 5°C above/below 4°C. 3. Find V1(MCG) limit weight for adjusted field length and pressure altitude. 4. Max allowable slippery runway limited weight is lesser of weights from 1 and 3.

V1 Adjustment (KIAS)

WEIGHT (1000 KG) 90 85 80 75 70 65 60 55 50 45 40 GOOD PRESSURE ALTITUDE (FT) S.L. 5000 10000 -7 -2 0 -8 -3 0 -9 -4 0 -11 -6 -1 -12 -7 -2 -14 -9 -4 -15 -10 -5 -17 -12 -7 -18 -13 -8 -20 -15 -10 -22 -17 -12 REPORTED BRAKING ACTION MEDIUM PRESSURE ALTITUDE (FT) S.L. 5000 10000 -19 -14 -9 -21 -16 -11 -24 -19 -14 -26 -21 -16 -28 -23 -18 -31 -26 -21 -34 -29 -24 -37 -32 -27 -40 -35 -30 -43 -38 -33 -46 -41 -36 POOR PRESSURE ALTITUDE (FT) S.L. 5000 10000 -39 -34 -29 -42 -37 -32 -45 -40 -35 -49 -44 -39 -52 -47 -42 -56 -51 -46 -59 -54 -49 -63 -58 -53 -66 -61 -56 -70 -65 -60 -74 -69 -64

1. Obtain V1, VR and V2 for the actual weight using the Dry Runway Takeoff Speeds table. 2. If V1(MCG) limited, set V1 = V1(MCG). If not V1(MCG) limited, enter V1 Adjustment table with the actual weight to obtain V1 speed adjustment. If adjusted V1 is less than V1(MCG), set V1 = V1(MCG). V1 not to exceed VR.

Copyright © The Boeing Company. See title page for details.

November 1, 2006

D632A008-ZZ022

1.2.41

TAKEOFF AND LANDING Takeoff

Flight Planning and Performance Manual

737-800/CFM56-7B26 JAA/JAROPS Category C Brakes

Takeoff Speeds - Dry Runway

V1, VR, V2 for Max Takeoff Thrust

WEIGHT (1000 KG) 90 85 80 75 70 65 60 55 50 45 40 V1 169 163 158 153 147 141 135 128 121 113 105 FLAPS 1 VR 171 166 160 155 149 143 136 129 122 114 106 V2 175 171 167 162 158 153 148 143 137 131 125 V1 161 157 152 147 141 135 129 123 116 109 101 FLAPS 5 VR 163 159 154 148 143 137 131 124 117 110 102 V2 168 164 160 156 152 147 143 137 132 126 120 V1 156 151 146 140 134 128 122 115 108 100 FLAPS 10 VR 157 152 147 141 136 129 123 116 108 101 V2 162 158 154 150 146 141 136 130 125 119 V1 FLAPS 15 VR V2 V1 FLAPS 25 VR V2

148 142 137 131 125 119 112 105 98

149 144 138 133 126 120 113 106 99

155 151 147 143 138 133 128 122 117

145 140 135 129 123 117 110 103 96

146 141 136 130 124 118 111 104 97

153 149 145 140 136 131 126 120 115

Check V1(MCG).

V1, VR, V2 Adjustments*

TEMP °C 70 60 50 40 30 20 -60 °F 158 140 122 104 86 68 -76 -2 5 4 2 1 0 0 0 V1 PRESSURE ALTITUDE (1000 FT) 0 2 4 6 8 6 5 6 7 3 4 5 6 7 1 3 4 5 6 0 1 2 4 5 0 1 2 3 4 0 1 2 3 4 SLOPE (%) 0 0 0 0 0 0 0 0 0 0 0 0 10 -2 4 3 2 1 0 0 0 VR PRESSURE ALTITUDE (1000 FT) 0 2 4 6 8 5 4 5 6 3 4 5 6 7 1 3 4 5 6 0 1 3 4 5 0 1 2 3 4 0 1 2 3 4 10 -2 -3 -2 -2 -1 0 0 0 V2 PRESSURE ALTITUDE (1000 FT) 0 2 4 6 8 -3 -3 -3 -4 -2 -3 -3 -4 -5 -1 -2 -2 -3 -4 0 -1 -2 -2 -3 0 -1 -1 -2 -3 0 -1 -1 -2 -2 10

9 7 6 5 5

8 7 6 5 5

-6 -5 -4 -3 -3

Slope and Wind V1 Adjustments*

WEIGHT (1000 KG) 90 85 80 75 70 65 60 55 50 45 40 -2 -4 -4 -3 -3 -2 -2 -2 -1 -1 0 0 -1 -2 -2 -2 -2 -1 -1 -1 -1 0 0 0 1 1 1 1 1 1 1 1 1 0 0 0 2 1 1 1 1 1 1 1 1 1 0 0 -15 -2 -2 -2 -2 -2 -2 -2 -2 -2 -2 -2 -10 -2 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -5 -1 -1 -1 -1 -1 -1 -1 -1 0 0 0 WIND (KTS) 0 10 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 20 0 0 0 0 1 1 1 1 1 0 0 30 0 1 1 1 1 1 1 1 1 0 0 40 1 1 1 1 1 1 1 1 1 0 0

Clearway and Stopway V1 Adjustments*

NORMAL V1 (KIAS) 160 140 120 100 300 -4 -3 -4 -5 200 -3 -3 -4 -5 100 -2 -2 -2 -3 CLEARWAY MINUS STOPWAY (M) 0 -100 0 1 0 1 0 1 0 1 -200 1 1 1 1 -300 1 1 1 1

*V1 not to exceed VR

Max Allowable Clearway for V1 Adjustment

FIELD LENGTH (M) MAX ALLOWABLE CLEARWAY (M) 1200 150 1600 180 2000 210 2400 240 2800 270 3200 290

V1(MCG)

Max Takeoff Thrust

TEMP °C 70 60 50 40 30 20 -60 °F 158 140 122 104 86 68 -76 -2000 95 95 97 101 104 104 106 0 93 93 95 99 103 104 105 2000 92 92 96 100 101 102 PRESSURE ALTITUDE (FT) 4000 90 90 93 96 98 99 6000 8000 10000

88 89 92 94 95

86 86 88 90 92

83 83 85 87 89

Copyright © The Boeing Company. See title page for details.

1.2.42

D632A008-ZZ022

November 1, 2006

737-800/CFM56-7B26 JAA/JAROPS Category C Brakes

TAKEOFF AND LANDING Takeoff

Flight Planning and Performance Manual

Takeoff Speeds - Wet Runway

V1, VR, V2 for Max Takeoff Thrust

WEIGHT (1000 KG) 90 85 80 75 70 65 60 55 50 45 40 V1 164 157 151 145 139 133 126 119 111 104 96 FLAPS 1 VR 171 166 160 155 149 143 136 129 122 114 106 V2 175 171 167 162 158 153 148 143 137 131 125 V1 156 150 145 139 133 127 121 114 107 99 92 FLAPS 5 VR 164 159 154 148 143 137 131 124 117 110 102 V2 168 164 160 156 152 148 143 137 132 126 120 V1 151 145 139 133 127 120 113 106 99 91 FLAPS 10 VR 157 152 147 141 136 129 123 116 108 101 V2 162 158 154 150 146 141 136 130 125 119 V1 FLAPS 15 VR V2 V1 FLAPS 25 VR V2

141 136 130 124 117 111 104 96 89

149 144 138 133 126 120 113 106 99

155 151 147 143 138 133 128 122 117

140 134 128 122 115 109 102 95 87

146 141 136 130 124 118 111 104 97

153 149 145 140 136 131 126 120 115

Check V1(MCG).

V1, VR, V2 Adjustments*

TEMP °C 70 60 50 40 30 20 -60 °F 158 140 122 104 86 68 -76 -2 7 5 3 1 0 0 0 V1 PRESSURE ALTITUDE (1000 FT) 0 2 4 6 8 8 6 7 9 4 5 6 8 9 2 3 4 6 7 0 1 3 4 6 0 1 2 4 5 0 1 2 4 5 SLOPE (%) 0 0 0 0 0 0 0 10 -2 4 3 2 1 0 0 0 VR PRESSURE ALTITUDE (1000 FT) 0 2 4 6 8 5 4 5 6 3 4 5 6 7 1 3 4 5 6 0 1 3 4 5 0 1 2 3 4 0 1 2 3 4 10 -2 -3 -2 -2 -1 0 0 0 V2 PRESSURE ALTITUDE (1000 FT) 0 2 4 6 8 -4 -3 -3 -4 -2 -3 -3 -4 -5 -1 -2 -2 -3 -4 0 -1 -2 -2 -3 0 -1 -1 -2 -2 0 -1 -1 -2 -2 10

12 9 7 6 7

8 7 6 5 5

-6 -5 -4 -3 -3

Slope and Wind V1 Adjustments*

WEIGHT (1000 KG) 90 80 70 60 50 40 -2 -5 -5 -4 -3 -2 -1 -1 -3 -2 -2 -1 -1 0 1 3 3 2 2 1 1 2 6 5 4 3 3 2 -15 -3 -4 -4 -4 -4 -5 -10 -2 -2 -2 -3 -3 -3 STOPWAY (M) 0 0 0 0 0 100 1 2 2 2 200 2 2 3 4 300 2 3 5 6 -5 -1 -1 -1 -1 -1 -1 WIND (KTS) 0 10 0 1 0 1 0 1 0 1 0 1 0 1 20 2 2 1 2 2 3 30 2 2 2 2 3 4 40 3 3 3 3 4 5

Stopway V1 Adjustments*

NORMAL V1 (KIAS) 160 140 120 100

Use of clearway not allowed on wet runways. *V1 not to exceed VR

V1(MCG)

Max Takeoff Thrust

TEMP °C 70 60 50 40 30 20 -60 °F 158 140 122 104 86 68 -76 -2000 95 95 97 101 104 104 106 0 93 93 95 99 103 104 105 2000 92 92 96 100 101 102 PRESSURE ALTITUDE (FT) 4000 90 90 93 96 98 99

6000

8000

10000

88 89 92 94 95

86 86 88 90 92

83 83 85 87 89

Copyright © The Boeing Company. See title page for details.

November 1, 2006

D632A008-ZZ022

1.2.43

TAKEOFF AND LANDING Takeoff

Flight Planning and Performance Manual

737-800/CFM56-7B26 JAA/JAROPS Category C Brakes

Takeoff %N1

Based on engine bleeds for packs on, engine and wing anti-ice on or off

OAT (°C) 60 55 50 45 40 35 30 25 20 15 10 5 0 -5 -10 -15 -20 -25 -30 -35 -40 -45 -50 -2000 94.8 95.4 96.0 96.8 97.4 98.0 97.6 96.8 96.0 95.2 94.5 93.7 92.9 92.0 91.2 90.4 89.6 88.7 87.9 87.0 86.1 85.3 84.4 -1000 95.4 96.0 96.6 97.4 98.1 98.7 98.8 98.1 97.3 96.5 95.8 95.0 94.2 93.4 92.6 91.7 90.9 90.1 89.2 88.4 87.5 86.6 85.7 0 95.8 96.5 97.1 97.8 98.6 99.4 100.3 99.5 98.8 98.0 97.2 96.4 95.6 94.8 94.0 93.2 92.4 91.6 90.7 89.9 89.0 88.2 87.3 1000 95.9 96.6 97.3 98.0 98.7 99.5 100.3 100.1 99.3 98.6 97.8 97.0 96.3 95.5 94.7 93.9 93.0 92.2 91.4 90.5 89.7 88.8 87.9 2000 96.0 96.7 97.4 98.1 98.8 99.6 100.4 100.7 99.9 99.2 98.4 97.6 96.9 96.1 95.3 94.5 93.7 92.9 92.0 91.2 90.3 89.5 88.6 AIRPORT PRESSURE ALTITUDE (FT) 3000 4000 5000 96.1 96.2 96.3 96.8 96.9 97.1 97.6 97.7 97.8 98.3 98.4 98.5 98.9 99.0 99.2 99.7 99.8 99.9 100.4 100.5 100.5 100.8 100.7 100.7 100.2 100.5 100.8 99.5 99.8 100.1 98.7 99.0 99.4 98.0 98.3 98.6 97.2 97.5 97.9 96.4 96.7 97.1 95.6 96.0 96.3 94.8 95.2 95.6 94.0 94.4 94.8 93.2 93.6 94.0 92.4 92.8 93.2 91.6 91.9 92.4 90.7 91.1 91.5 89.9 90.3 90.7 89.0 89.4 89.9 6000 96.2 96.9 97.7 98.4 99.1 99.8 100.4 100.7 100.8 100.5 99.7 99.0 98.2 97.5 96.7 95.9 95.2 94.4 93.6 92.8 91.9 91.1 90.3 7000 95.9 96.6 97.4 98.1 98.8 99.5 100.3 100.7 100.9 100.9 100.1 99.4 98.6 97.9 97.1 96.3 95.6 94.8 94.0 93.1 92.3 91.5 90.6 8000 95.8 96.3 97.1 97.8 98.5 99.2 100.0 100.6 100.8 101.1 100.5 99.8 99.0 98.3 97.5 96.7 95.9 95.2 94.3 93.5 92.7 91.9 91.0 9000 95.7 95.7 96.6 97.5 98.4 99.1 99.9 100.6 100.8 101.1 101.0 100.3 99.5 98.7 98.0 97.2 96.4 95.6 94.8 94.0 93.1 92.3 91.5 10000 95.7 95.0 96.1 97.1 98.1 99.0 99.9 100.7 100.8 101.1 101.5 100.7 100.0 99.2 98.4 97.6 96.8 96.0 95.2 94.4 93.6 92.7 91.9

%N1 Adjustments for Engine Bleeds

BLEED COFIGURATION PACKS OFF -2000 0.7 -1000 0.8 0 0.8 1000 0.9 2000 0.9 AIRPORT PRESSURE ALTITUDE (FT) 3000 4000 5000 6000 0.9 1.0 1.0 1.0 7000 1.0 8000 1.0 9000 1.0 10000 1.0

Stab Trim Setting

Max Takeoff Thrust Flaps 1 and 5

WEIGHT (1000 KG) 85 80 75 70 65 60 55 50 45 40 6 8 1/2 8 1/2 8 1/4 8 7 3/4 7 1/4 6 3/4 6 1/2 6 6 8 8 1/2 8 1/2 8 7 3/4 7 1/4 7 6 1/2 6 5 3/4 5 3/4 9 8 1/2 8 1/4 7 3/4 7 1/2 7 6 3/4 6 1/2 6 5 1/2 5 1/2 11 8 1/4 7 3/4 7 1/2 7 1/4 6 3/4 6 1/2 6 1/4 5 3/4 5 1/2 5 1/2 16 7 6 3/4 6 1/2 6 1/4 6 5 3/4 5 1/2 5 4 3/4 4 3/4 C.G. (%MAC) 21 6 1/4 6 5 3/4 5 1/2 5 1/4 5 4 3/4 4 1/2 4 4 26 5 1/2 5 1/4 5 4 3/4 4 1/2 4 1/4 4 1/4 3 3/4 3 1/2 3 1/2 30 4 3/4 4 1/2 4 1/2 4 1/4 4 3 3/4 3 1/2 3 1/4 3 3 32 4 1/2 4 1/4 4 3 3/4 3 3/4 3 1/2 3 1/4 3 2 1/2 2 1/2 34 4 1/4 4 3 3/4 3 1/2 3 1/4 3 1/4 3 2 3/4 2 1/2 2 1/2 36 3 3/4 3 1/2 3 1/2 3 1/4 3 2 3/4 2 3/4 2 1/4 2 1/4 2 1/4

Flaps 10, 15 and 25

WEIGHT (1000 KG) 85 80 75 70 65 60 55 50 45 40 6 8 1/2 8 1/2 8 1/2 8 1/2 8 1/4 7 3/4 7 6 5 5 8 8 1/2 8 1/2 8 1/2 8 1/4 7 3/4 7 6 1/2 5 3/4 4 3/4 4 3/4 9 8 1/2 8 1/2 8 1/2 8 1/4 7 1/2 6 3/4 6 1/4 5 1/2 4 1/2 4 1/2 11 8 1/2 8 1/2 7 3/4 7 1/4 6 3/4 6 1/4 5 3/4 5 4 1/2 4 1/2 16 6 1/2 6 5 3/4 5 1/2 5 1/4 4 3/4 4 1/2 4 3 1/2 3 1/2 C.G. (%MAC) 21 5 1/2 5 4 3/4 4 1/2 4 1/4 4 3 3/4 3 1/4 2 3/4 2 3/4 26 4 1/4 4 3 3/4 3 1/2 3 1/4 3 2 3/4 2 1/2 2 1/4 2 1/4 30 3 1/2 3 1/4 3 2 3/4 2 1/2 2 1/4 2 1/4 2 1/4 2 1/4 2 1/4 32 3 2 3/4 2 1/2 2 1/2 2 1/4 2 1/4 2 1/4 2 1/4 2 1/4 2 1/4 34 2 1/2 2 1/2 2 1/4 2 1/4 2 1/4 2 1/4 2 1/4 2 1/4 2 1/4 2 1/4 36 2 1/4 2 1/4 2 1/4 2 1/4 2 1/4 2 1/4 2 1/4 2 1/4 2 1/4 2 1/4

Copyright © The Boeing Company. See title page for details.

1.2.44

D632A008-ZZ022

November 1, 2006

737-800/CFM56-7B26 JAA/JAROPS Category C Brakes

TAKEOFF AND LANDING Takeoff Alternate Ratings

Flight Planning and Performance Manual

Takeoff Alternate Ratings

1.3 TAKEOFF AND Limit - Dry Runway (24K Derate) Takeoff Field LANDING-Takeoff Alternate Ratings

Flaps 1

Based on engine bleed for packs on and anti-ice off

88

84

80

-2 -1 0

76

1 2 3 4

5 6 7

AI

72

68

64

TAL LIMI

RP

8 9

OR T

60

MINIMUM FIELD LENGTH

IRON

10 PR E (10 SSU RE 00 FT AL ) TIT UD E

56

52

ENV

48 REF LINE

44

F

WIND (KTS)

-60 -40 -20 0 20 40 60 80 100 120 140 -60 -50 -40 -30 -20 -10 0 10 20 30 40 50 60 70 HEAD 40 C AIRPORT OAT 20 REF LINE 0 -10 TAIL REF LINE

40

2 0

-2 5 6 7 8 9 10 11 12 13 1000 FT 4 DOWN 100 M 12 14 16 18 20 22 24 26 28 30 32 34 36 38 40 42 FIELD LENGTH AVAILABLE

With engine bleed for packs off, increase weight by 400 kg. With engine anti-ice on, decrease weight by 200 kg. With engine and wing anti-ice on, decrease weight by 750 kg (optional system).

Copyright © The Boeing Company. See title page for details.

November 1, 2006

D632A008-ZZ022

RUNWAY SLOPE (%)

UP

1.3.1

FIELD LENGTH LIMIT BRAKE RELEASE WEIGHT

MEN

T

(1000 KG)

TAKEOFF AND LANDING Takeoff Alternate Ratings

Flight Planning and Performance Manual

Takeoff Alternate Ratings

737-800/CFM56-7B26 JAA/JAROPS Category C Brakes

Takeoff Field Limit - Dry Runway (24K Derate)

Flaps 5

Based on engine bleed for packs on and anti-ice off

88

84

80

-2 -1 0

76

2

3

4

72

5

6 7

8

AI RP

9 10

68

64

IRON

DE

MINIMUM FIELD LENGTH

PR E (10 SSU 00 R FT E A LT ) ITU

TAL LIMI T

OR T

60

56

52

48 REF LINE

44

F

WIND (KTS)

-60 -40 -20 0 20 40 60 80 100 120 140 -60 -50 -40 -30 -20 -10 0 10 20 30 40 50 60 70 HEAD 40 C AIRPORT OAT 20 REF LINE 0 -10 TAIL REF LINE

40

2 0

-2 5 6 7 8 9 10 11 12 13 1000 FT 4 DOWN 100 M 12 14 16 18 20 22 24 26 28 30 32 34 36 38 40 42 FIELD LENGTH AVAILABLE

With engine bleed for packs off, increase weight by 400 kg. With engine anti-ice on, decrease weight by 200 kg. With engine and wing anti-ice on, decrease weight by 900 kg (optional system).

Copyright © The Boeing Company. See title page for details.

1.3.2

D632A008-ZZ022

November 1, 2006

RUNWAY SLOPE (%)

UP

FIELD LENGTH LIMIT BRAKE RELEASE WEIGHT

1

ENV

MEN

(1000 KG)

737-800/CFM56-7B26 JAA/JAROPS Category C Brakes

TAKEOFF AND LANDING Takeoff Alternate Ratings

Flight Planning and Performance Manual

Takeoff Alternate Ratings

Takeoff Field Limit - Dry Runway (24K Derate)

Flaps 10

Based on engine bleed for packs on and anti-ice off

88

84

80

-2 -1 0

76

2

3

4

72

5

6 7 8

AI

68

64

MINIMUM FIELD LENGTH

ENV

IRON

PR E (10 SSU 00 R FT E A LT ) ITU DE

TAL LIMI

T

RP

OR T

9 10

60

56

52

48 REF LINE

44

F

WIND (KTS)

-60 -40 -20 0 20 40 60 80 100 120 140 -60 -50 -40 -30 -20 -10 0 10 20 30 40 50 60 70 HEAD 40 C AIRPORT OAT 20 REF LINE 0 -10 TAIL REF LINE

40

2 0

-2 5 6 7 8 9 10 11 12 13 1000 FT 4 DOWN 100 M 12 14 16 18 20 22 24 26 28 30 32 34 36 38 40 42 FIELD LENGTH AVAILABLE

With engine bleed for packs off, increase weight by 400 kg. With engine anti-ice on, decrease weight by 200 kg. With engine and wing anti-ice on, decrease weight by 900 kg (optional system).

Copyright © The Boeing Company. See title page for details.

November 1, 2006

D632A008-ZZ022

1.3.3

RUNWAY SLOPE (%)

UP

FIELD LENGTH LIMIT BRAKE RELEASE WEIGHT

1

MEN

(1000 KG)

TAKEOFF AND LANDING Takeoff Alternate Ratings

Flight Planning and Performance Manual

Takeoff Alternate Ratings

737-800/CFM56-7B26 JAA/JAROPS Category C Brakes

Takeoff Field Limit - Dry Runway (24K Derate)

Flaps 15

Based on engine bleed for packs on and anti-ice off

88

84

-2 -1 0

80

1

2

3

4

76

72

5

6

7 8

68

64

OR T

TAL LIMI T

AI

RP

9 10

60

MINIMUM FIELD LENGTH

IRON

PR E (10 SSU 00 R FT E A LT ) ITU DE

MEN

56

52

48 REF LINE

44

F

WIND (KTS)

-60 -40 -20 0 20 40 60 80 100 120 140 -60 -50 -40 -30 -20 -10 0 10 20 30 40 50 60 70 HEAD 40 C AIRPORT OAT 20 REF LINE 0 -10 TAIL REF LINE

40

2 0

-2 5 6 7 8 9 10 11 12 13 1000 FT 4 DOWN 100 M 12 14 16 18 20 22 24 26 28 30 32 34 36 38 40 42 FIELD LENGTH AVAILABLE

With engine bleed for packs off, increase weight by 400 kg. With engine anti-ice on, decrease weight by 200 kg. With engine and wing anti-ice on, decrease weight by 900 kg (optional system).

Copyright © The Boeing Company. See title page for details.

1.3.4

D632A008-ZZ022

November 1, 2006

RUNWAY SLOPE (%)

UP

FIELD LENGTH LIMIT BRAKE RELEASE WEIGHT

ENV

(1000 KG)

737-800/CFM56-7B26 JAA/JAROPS Category C Brakes

TAKEOFF AND LANDING Takeoff Alternate Ratings

Flight Planning and Performance Manual

Takeoff Alternate Ratings

Takeoff Field Limit - Dry Runway (24K Derate)

Flaps 25

Based on engine bleed for packs on and anti-ice off

88

84

-2 -1 0

80

1

2

3 4

76

72

5

6

7

68

8

T

AIR

9

64

TAL LIMI

PO

RT

10

PR E (10 SSU RE 00 FT AL ) TIT UD

60

MEN

56 MINIMUM FIELD LENGTH

IRON

E

52

48 REF LINE

44

F

WIND (KTS)

-60 -40 -20 0 20 40 60 80 100 120 140 -60 -50 -40 -30 -20 -10 0 10 20 30 40 50 60 70 HEAD 40 C AIRPORT OAT 20 REF LINE 0 -10 TAIL REF LINE

40

2 0

-2 5 6 7 8 9 10 11 12 13 1000 FT 4 DOWN 100 M 12 14 16 18 20 22 24 26 28 30 32 34 36 38 40 42 FIELD LENGTH AVAILABLE

With engine bleed for packs off, increase weight by 400 kg. With engine anti-ice on, decrease weight by 200 kg. With engine and wing anti-ice on, decrease weight by 900 kg (optional system).

Copyright © The Boeing Company. See title page for details.

November 1, 2006

D632A008-ZZ022

RUNWAY SLOPE (%)

UP

1.3.5

FIELD LENGTH LIMIT BRAKE RELEASE WEIGHT

ENV

(1000 KG)

TAKEOFF AND LANDING Takeoff Alternate Ratings

Flight Planning and Performance Manual

737-800/CFM56-7B26 JAA/JAROPS Category C Brakes

Takeoff Field Limit - Wet Runway (24K Derate)

Flaps 1

Based on engine bleed for packs on and anti-ice off

88

84

80

72

1

2

3 4 5

68

64

6 7 8

OR T

60

TAL LIMI T

AI

RP

9 10

56 MINIMUM FIELD LENGTH

IRON

PR E (10 SSU 00 R FT E A LT ) ITU DE

52

ENV

48 REF LINE

44

F

WIND (KTS)

-60 -40 -20 0 20 40 60 80 100 120 140 -60 -50 -40 -30 -20 -10 0 10 20 30 40 50 60 70 HEAD 40 C AIRPORT OAT 20 REF LINE 0 -10 TAIL REF LINE

40

2 0

-2 5 6 7 8 9 10 11 12 13 1000 FT 4 DOWN 100 M 12 14 16 18 20 22 24 26 28 30 32 34 36 38 40 42 FIELD LENGTH AVAILABLE

With engine bleed for packs off, increase weight by 350 kg. With engine anti-ice on, decrease weight by 200 kg. With engine and wing anti-ice on, decrease weight by 750 kg (optional system).

Copyright © The Boeing Company. See title page for details.

1.3.6

D632A008-ZZ022

November 1, 2006

RUNWAY SLOPE (%)

UP

FIELD LENGTH LIMIT BRAKE RELEASE WEIGHT

-2 -1 0

76

MEN

(1000 KG)

737-800/CFM56-7B26 JAA/JAROPS Category C Brakes

TAKEOFF AND LANDING Takeoff Alternate Ratings

Flight Planning and Performance Manual

Takeoff Field Limit - Wet Runway (24K Derate)

Flaps 5

Based on engine bleed for packs on and anti-ice off

88

84

80

-2 -1 0

76

2

3

4 5

72

68

6 7 8

TAL LIMI

OR T

64

MINIMUM FIELD LENGTH

ENV

IRON

PR E (10 SSU 00 R FT E A LT ) ITU DE

T

AI

RP

9 10

60

56

52

48 REF LINE

44

F

WIND (KTS)

-60 -40 -20 0 20 40 60 80 100 120 140 -60 -50 -40 -30 -20 -10 0 10 20 30 40 50 60 70 HEAD 40 C AIRPORT OAT 20 REF LINE 0 -10 TAIL REF LINE

40

2 0

-2 5 6 7 8 9 10 11 12 13 1000 FT 4 DOWN 100 M 12 14 16 18 20 22 24 26 28 30 32 34 36 38 40 42 FIELD LENGTH AVAILABLE

With engine bleed for packs off, increase weight by 350 kg. With engine anti-ice on, decrease weight by 200 kg. With engine and wing anti-ice on, decrease weight by 800 kg (optional system).

Copyright © The Boeing Company. See title page for details.

November 1, 2006

D632A008-ZZ022

RUNWAY SLOPE (%)

UP

1.3.7

FIELD LENGTH LIMIT BRAKE RELEASE WEIGHT

1

MEN

(1000 KG)

TAKEOFF AND LANDING Takeoff Alternate Ratings

Flight Planning and Performance Manual

737-800/CFM56-7B26 JAA/JAROPS Category C Brakes

Takeoff Field Limit - Wet Runway (24K Derate)

Flaps 10

Based on engine bleed for packs on and anti-ice off

88

84

80

-2 -1 0 1

76

2

3 4

72

68

5

6 7

AI

64

OR T

MINIMUM FIELD LENGTH

DE

ENV

IRON

PR E (10 SSU 00 R FT E A LT ) ITU

TAL LIMI T

RP

8 9 10

60

56

52

48 REF LINE

44

F

WIND (KTS)

-60 -40 -20 0 20 40 60 80 100 120 140 -60 -50 -40 -30 -20 -10 0 10 20 30 40 50 60 70 HEAD 40 C AIRPORT OAT 20 REF LINE 0 -10 TAIL REF LINE

40

2 0

-2 5 6 7 8 9 10 11 12 13 1000 FT 4 DOWN 100 M 12 14 16 18 20 22 24 26 28 30 32 34 36 38 40 42 FIELD LENGTH AVAILABLE

With engine bleed for packs off, increase weight by 400 kg. With engine anti-ice on, decrease weight by 200 kg. With engine and wing anti-ice on, decrease weight by 750 kg (optional system).

Copyright © The Boeing Company. See title page for details.

1.3.8

D632A008-ZZ022

November 1, 2006

RUNWAY SLOPE (%)

UP

FIELD LENGTH LIMIT BRAKE RELEASE WEIGHT

MEN

(1000 KG)

737-800/CFM56-7B26 JAA/JAROPS Category C Brakes

TAKEOFF AND LANDING Takeoff Alternate Ratings

Flight Planning and Performance Manual

Takeoff Field Limit - Wet Runway (24K Derate)

Flaps 15

Based on engine bleed for packs on and anti-ice off

88

84

-2 -1 0

80

76

2

3

4

72

5

6

7

68

64

8

OR T

MINIMUM FIELD LENGTH

ENV

IRON

PR E (10 SSU 00 R FT E A LT ) ITU DE

TAL LIMI T

AI

RP

9 10

60

56

52

48 REF LINE

44

F

WIND (KTS)

-60 -40 -20 0 20 40 60 80 100 120 140 -60 -50 -40 -30 -20 -10 0 10 20 30 40 50 60 70 HEAD 40 C AIRPORT OAT 20 REF LINE 0 -10 TAIL REF LINE

40

2 0

-2 5 6 7 8 9 10 11 12 13 1000 FT 4 DOWN 100 M 12 14 16 18 20 22 24 26 28 30 32 34 36 38 40 42 FIELD LENGTH AVAILABLE

With engine bleed for packs off, increase weight by 400 kg. With engine anti-ice on, decrease weight by 200 kg. With engine and wing anti-ice on, decrease weight by 750 kg (optional system).

Copyright © The Boeing Company. See title page for details.

November 1, 2006

D632A008-ZZ022

RUNWAY SLOPE (%)

UP

1.3.9

FIELD LENGTH LIMIT BRAKE RELEASE WEIGHT

1

MEN

(1000 KG)

TAKEOFF AND LANDING Takeoff Alternate Ratings

Flight Planning and Performance Manual

737-800/CFM56-7B26 JAA/JAROPS Category C Brakes

Takeoff Field Limit - Wet Runway (24K Derate)

Flaps 25

Based on engine bleed for packs on and anti-ice off

88

84

-2 -1 0

80

1

2

3

4

76

72

5

6

7

68

OR T

MINIMUM FIELD LENGTH

IRON

PR E (10 SSU 00 R FT E A LT ) ITU DE

TAL LIMI T

AI

8 9

RP

64

10

60

56

52

48 REF LINE

44

F

WIND (KTS)

-60 -40 -20 0 20 40 60 80 100 120 140 -60 -50 -40 -30 -20 -10 0 10 20 30 40 50 60 70 HEAD 40 C AIRPORT OAT 20 REF LINE 0 -10 TAIL REF LINE

40

2 0

-2 5 6 7 8 9 10 11 12 13 1000 FT 4 DOWN 100 M 12 14 16 18 20 22 24 26 28 30 32 34 36 38 40 42 FIELD LENGTH AVAILABLE

With engine bleed for packs off, increase weight by 400 kg. With engine anti-ice on, decrease weight by 200 kg. With engine and wing anti-ice on, decrease weight by 750 kg (optional system).

Copyright © The Boeing Company. See title page for details.

1.3.10

D632A008-ZZ022

November 1, 2006

RUNWAY SLOPE (%)

UP

FIELD LENGTH LIMIT BRAKE RELEASE WEIGHT

ENV

MEN

(1000 KG)

737-800/CFM56-7B26 JAA/JAROPS Category C Brakes

TAKEOFF AND LANDING Takeoff Alternate Ratings

Flight Planning and Performance Manual

Takeoff Climb Limit (24K Derate)

Flaps 1

Based on engine bleed for packs on and anti-ice off

82

78

-2 -1 0 1 2

74

3 4

(1000 KG)

70

5 6 7

CLIMB LIMIT BRAKE RELEASE WEIGHT

66

8 9

62

10 AIRPORT PRESSURE ALTITUDE (1000 FT)

L L IMIT

58

54

50

46

42 -60

-60 -50

-40 -40

-20 0 -30 -20

20 40 60 80 100 -10 0 10 20 30 40 AIRPORT OAT

ENV

IRO

NME

120 50

NTA

140 60

70

F C

With engine bleed for packs off, increase weight by 1450 kg. With engine anti-ice on, decrease weight by 250 kg. With engine and wing anti-ice on (optional system), decrease weight by 1400 kg.

Copyright © The Boeing Company. See title page for details.

November 1, 2006

D632A008-ZZ022

1.3.11

TAKEOFF AND LANDING Takeoff Alternate Ratings

Flight Planning and Performance Manual

737-800/CFM56-7B26 JAA/JAROPS Category C Brakes

Takeoff Climb Limit (24K Derate)

Flaps 5

Based on engine bleed for packs on and anti-ice off

80

76

-2 -1 0 1

72

2 3

(1000 KG)

4 68 5 6 7 64 8 9 60 10 AIRPORT PRESSURE ALTITUDE (1000 FT)

L L IM IT

CLIMB LIMIT BRAKE RELEASE WEIGHT

56

48

44

40 -60

-60 -50

-40 -40

-20 0 -30 -20

20 40 60 80 100 -10 0 10 20 30 40 AIRPORT OAT

ENV

IRO

52

NME

120 50

NTA

140 60

70

F C

With engine bleed for packs off, increase weight by 1350 kg. With engine anti-ice on, decrease weight by 250 kg. With engine and wing anti-ice on (optional system), decrease weight by 1350 kg.

Copyright © The Boeing Company. See title page for details.

1.3.12

D632A008-ZZ022

November 1, 2006

737-800/CFM56-7B26 JAA/JAROPS Category C Brakes

TAKEOFF AND LANDING Takeoff Alternate Ratings

Flight Planning and Performance Manual

Takeoff Climb Limit (24K Derate)

Flaps 10

Based on engine bleed for packs on and anti-ice off

76

72

-2 -1 0 1

68 (1000 KG)

2 3 4

64

5 6 7

CLIMB LIMIT BRAKE RELEASE WEIGHT

60

8 9

56

10 AIRPORT PRESSURE ALTITUDE (1000 FT)

48

44

40 -60

-60 -50

-40 -40

-20 0 -30 -20

20 40 60 80 100 -10 0 10 20 30 40 AIRPORT OAT

ENV

IRO

NME

120 50

NTA

52

L L IMIT

140 60

70

F C

With engine bleed for packs off, increase weight by 1200 kg. With engine anti-ice on, decrease weight by 200 kg. With engine and wing anti-ice on (optional system), decrease weight by 1250 kg.

Copyright © The Boeing Company. See title page for details.

November 1, 2006

D632A008-ZZ022

1.3.13

TAKEOFF AND LANDING Takeoff Alternate Ratings

Flight Planning and Performance Manual

737-800/CFM56-7B26 JAA/JAROPS Category C Brakes

Takeoff Climb Limit (24K Derate)

Flaps 15

Based on engine bleed for packs on and anti-ice off

72 -2 -1 0 68 1 2 (1000 KG) 3 64 4 5 6 60 7 8 9 56 10 AIRPORT PRESSURE ALTITUDE (1000 FT) 52

CLIMB LIMIT BRAKE RELEASE WEIGHT

44

40 -60

-60 -50

-40 -40

-20 0 -30 -20

20 40 60 80 100 -10 0 10 20 30 40 AIRPORT OAT

ENV

IRO

48

120 50

NME

NTA

L L IM

IT

140 60

70

F C

With engine bleed for packs off, increase weight by 1200 kg. With engine anti-ice on, decrease weight by 200 kg. With engine and wing anti-ice on (optional system), decrease weight by 1200 kg.

Copyright © The Boeing Company. See title page for details.

1.3.14

D632A008-ZZ022

November 1, 2006

737-800/CFM56-7B26 JAA/JAROPS Category C Brakes

TAKEOFF AND LANDING Takeoff Alternate Ratings

Flight Planning and Performance Manual

Takeoff Climb Limit (24K Derate)

Flaps 25

Based on engine bleed for packs on and anti-ice off

72

68

-2 -1 0 1

(1000 KG)

2 64 3 4 5 60 6 7 8 56 9 10 52 AIRPORT PRESSURE ALTITUDE (1000 FT)

CLIMB LIMIT BRAKE RELEASE WEIGHT

48

44

40 -60

-60 -50

-40 -40

-20 0 -30 -20

20 40 60 80 100 -10 0 10 20 30 40 AIRPORT OAT

ENV

IRO

NM

ENT

120 50

AL

LIM

IT

140 60

70

F C

With engine bleed for packs off, increase weight by 1100 kg. With engine anti-ice on, decrease weight by 200 kg. With engine and wing anti-ice on (optional system), decrease weight by 1200 kg.

Copyright © The Boeing Company. See title page for details.

November 1, 2006

D632A008-ZZ022

1.3.15

TAKEOFF AND LANDING Takeoff Alternate Ratings

Flight Planning and Performance Manual

737-800/CFM56-7B26 JAA/JAROPS Category C Brakes

Obstacle Limit (24K Derate)

Flaps 1

Based on engine bleed for packs on and anti-ice off

OBSTACLE LIMIT WEIGHT 40 HEAD 40 WIND (KTS) 20 0 REF LINE 50 60 70 (1000 KG) 80 90

TAIL 20 PRESS ALT (1000 FT) 10 5 0 ( C) ( F) 50 120 40 OAT 30 20 10 0 (M) 300 40

DI

REF LINE

100 REF LINE 80 60

(FT)

85 80 75 70 65 60 55 50 45

40 35

AN ST CE

90

OBSTACLE HEIGHT

800

30

E AK BR ) M OM 0 FR (10

200

600

25

400 200 0 0

RE LE

100

When using line-up allowances, the obstacle distance from brake release must be reduced by the ASDA adjustment. Obstacle height must be calculated from the lowest point of the runway to conservatively account for runway slope. With engine bleed for packs off, increase weight by 650 kg. With engine anti-ice on, decrease weight by 250 kg. With engine and wing anti-ice on, decrease weight by 1400 kg (optional system).

AS E

Copyright © The Boeing Company. See title page for details.

1.3.16

D632A008-ZZ022

November 1, 2006

737-800/CFM56-7B26 JAA/JAROPS Category C Brakes

TAKEOFF AND LANDING Takeoff Alternate Ratings

Flight Planning and Performance Manual

Obstacle Limit (24K Derate)

Flaps 5

Based on engine bleed for packs on and anti-ice off

OBSTACLE LIMIT WEIGHT 40 HEAD 40 WIND (KTS) 20 0 REF LINE 50 60 70 (1000 KG) 80 90

TAIL 20 PRESS ALT (1000 FT) 10 5 0 ( C) ( F) 50 120 40 OAT 30 20 10 0 (M) 300 40

DI

REF LINE

100 REF LINE 80 60

(FT)

AN ST CE E AK BR ) OM 0 M FR (10

90 85 80 75 70 65 60 55 50 45 40 35

OBSTACLE HEIGHT

800

30

200

600

25

400 200 0 0

RE A LE

100

When using line-up allowances, the obstacle distance from brake release must be reduced by the ASDA adjustment. Obstacle height must be calculated from the lowest point of the runway to conservatively account for runway slope. With engine bleed for packs off, increase weight by 650 kg. With engine anti-ice on, decrease weight by 250 kg. With engine and wing anti-ice on, decrease weight by 1400 kg (optional system).

SE

Copyright © The Boeing Company. See title page for details.

November 1, 2006

D632A008-ZZ022

1.3.17

TAKEOFF AND LANDING Takeoff Alternate Ratings

Flight Planning and Performance Manual

737-800/CFM56-7B26 JAA/JAROPS Category C Brakes

Obstacle Limit (24K Derate)

Flaps 10

Based on engine bleed for packs on and anti-ice off

OBSTACLE LIMIT WEIGHT 40 HEAD 40 WIND (KTS) 20 0 REF LINE 50 60 70 (1000 KG) 80 90

TAIL 20 PRESS ALT (1000 FT) 10 5 0 ( C) ( F) 50 120 40 OAT 30 20 10 0 (M) 300 40 (FT)

DI

85 80 75 70 65 60 55 50 45 40

REF LINE

100 REF LINE 80 60

AN ST

90

35

CE

OBSTACLE HEIGHT

800

30

E AK BR ) M OM FR (100

200

600

25

400 200 0 0

RE

100

When using line-up allowances, the obstacle distance from brake release must be reduced by the ASDA adjustment. Obstacle height must be calculated from the lowest point of the runway to conservatively account for runway slope. With engine bleed for packs off, increase weight by 650 kg. With engine anti-ice on, decrease weight by 250 kg. With engine and wing anti-ice on, decrease weight by 1400 kg (optional system).

LE AS E

Copyright © The Boeing Company. See title page for details.

1.3.18

D632A008-ZZ022

November 1, 2006

737-800/CFM56-7B26 JAA/JAROPS Category C Brakes

TAKEOFF AND LANDING Takeoff Alternate Ratings

Flight Planning and Performance Manual

Obstacle Limit (24K Derate)

Flaps 15

Based on engine bleed for packs on and anti-ice off

OBSTACLE LIMIT WEIGHT 40 HEAD 40 WIND (KTS) 20 0 REF LINE 50 60 70 (1000 KG) 80 90

TAIL 20 PRESS ALT (1000 FT) 10 5 0 ( C) ( F) 50 120 40 OAT 30 20 10 0 (M) 300 40 100 REF LINE 80 60 REF LINE

DI

(FT)

AN ST CE

85 80 75 70 65 60 55 50 45 40

90

35

OBSTACLE HEIGHT

800 200 600

AK BR ) M OM FR (100

30

25

E RE

100

400 200

AS LE E

0

0

When using line-up allowances, the obstacle distance from brake release must be reduced by the ASDA adjustment. Obstacle height must be calculated from the lowest point of the runway to conservatively account for runway slope. With engine bleed for packs off, increase weight by 650 kg. With engine anti-ice on, decrease weight by 250 kg. With engine and wing anti-ice on, decrease weight by 1400 kg (optional system).

Copyright © The Boeing Company. See title page for details.

November 1, 2006

D632A008-ZZ022

1.3.19

TAKEOFF AND LANDING Takeoff Alternate Ratings

Flight Planning and Performance Manual

737-800/CFM56-7B26 JAA/JAROPS Category C Brakes

Obstacle Limit (24K Derate)

Flaps 25

Based on engine bleed for packs on and anti-ice off

OBSTACLE LIMIT WEIGHT 40 HEAD 40 WIND (KTS) 20 0 REF LINE 50 60 70 (1000 KG) 80 90

TAIL 20 PRESS ALT (1000 FT) 10 5 0 ( C) ( F) 50 120 40 OAT 30 20 10 0 (M) 300 40 (FT) 100 REF LINE 80 60 REF LINE

DI AN ST CE

OBSTACLE HEIGHT

800 200 600

100

400 200

85 80 75 70 65 60 55 50 45 40

90

35

E AK BR M) OM FR (100

30

25

RE LE E AS

0

0

When using line-up allowances, the obstacle distance from brake release must be reduced by the ASDA adjustment. Obstacle height must be calculated from the lowest point of the runway to conservatively account for runway slope. With engine bleed for packs off, increase weight by 650 kg. With engine anti-ice on, decrease weight by 250 kg. With engine and wing anti-ice on, decrease weight by 1400 kg (optional system).

Copyright © The Boeing Company. See title page for details.

1.3.20

D632A008-ZZ022

November 1, 2006

737-800/CFM56-7B26 JAA/JAROPS Category C Brakes

TAKEOFF AND LANDING Takeoff Alternate Ratings

Flight Planning and Performance Manual

Tire Speed Limit (24K Derate)

Flaps 1

88

0

84

1

2

3

(1000 KG)

4

80

5

AI RP T OR

7

6

TIRE SPEED LIMIT WEIGHT

76

PR ES SU RE

10

9

8

TI AL

72

TU DE (1 00

68

0 FT )

64

60 -60

-60 -50

-40 -40

-20 0 -30 -20

20 40 60 80 100 -10 0 10 20 30 40 AIRPORT OAT

120 50

140 60

70

F C

Increase tire speed limit weight by 500 kg per knot headwind. Decrease tire speed limit weight by 1150 kg per knot tailwind.

Copyright © The Boeing Company. See title page for details.

November 1, 2006

D632A008-ZZ022

1.3.21

TAKEOFF AND LANDING Takeoff Alternate Ratings

Flight Planning and Performance Manual

737-800/CFM56-7B26 JAA/JAROPS Category C Brakes

Tire Speed Limit (24K Derate)

Flaps 5

88

3

84

4

(1000 KG)

5

T OR RP AI

6

80

7

TIRE SPEED LIMIT WEIGHT

SU ES PR

8

9

76

RE

10

TIT AL UD E

72

(10 00 FT )

68

64 -60

-60 -50

-40 -40

-20 0 -30 -20

20 40 60 80 100 -10 0 10 20 30 40 AIRPORT OAT

120 50

140 60

70

F C

Increase tire speed limit weight by 600 kg per knot headwind. Decrease tire speed limit weight by 1100 kg per knot tailwind.

Copyright © The Boeing Company. See title page for details.

1.3.22

D632A008-ZZ022

November 1, 2006

737-800/CFM56-7B26 JAA/JAROPS Category C Brakes

TAKEOFF AND LANDING Takeoff Alternate Ratings

Flight Planning and Performance Manual

Brake Energy Limits VMBE (24K Derate)

AIRPORT PRESSURE ALTITUDE (1000 FT) 10 8 6 4 2 0 -2 40 50 60 70 80 BRAKE RELEASE WEIGHT (1000 KG)

E R (10 ELEA 00 SE KG W 42 ) EIG HT

AIR

PO

RT

OA T

°C

( °F

)

-50 ( -40 -58) ( -30 -40) (-2 -20 2) -10 ( -4) (1 0 ( 4) 50 30 20 10 ( 32) (12 ( 86 ( 6 50 2) ) 8) ) 40 (10 4) 210

200

BR

AK

190

46

50

58

62

66

170

70

74

78

82

86

160

150

140

Check VMBE when outside shaded area or when operating with tailwind or improved climb. Increase VMBE by 1 knots per 1% uphill runway slope. Decrease VMBE by 4 knots per 1% downhill runway slope. Increase VMBE by 3 knots per 10 knots headwind. Decrease VMBE by 19 knots per 10 knots tailwind. Normal takeoff: Decrease brake release weight by 550 kg for each knot V1 exceeds VMBE. Determine normal V1, VR, V2 speeds for lower brake release weight. Improved climb takeoff: Decrease climb weight improvement by 200 kg for each knot V1 exceeds VMBE. Determine V1, VR, V2 speed increments for the lower climb weight improvement.

Copyright © The Boeing Company. See title page for details.

November 1, 2006

D632A008-ZZ022

1.3.23

VMBE

(KIAS)

54

180

TAKEOFF AND LANDING Takeoff Alternate Ratings

Flight Planning and Performance Manual

737-800/CFM56-7B26 JAA/JAROPS Category C Brakes

Improved Climb Field Length Limit - Dry Runway (24K Derate)

Flaps 1

NORMAL TAKEOFF SPEED INCREMENT (KIAS) V1 VR V2 80 20 70 60 50 18 16 14 12 10 9 8 7 6 5 4 REF LINE 1 3 2 1 26 24 22 20 18 16 14 12 10 9 8 7 6 5 4 3 2 1 24 22 20 18 16 14 12 10 9 8 7 6 5 4 3 2 1

T

6

(1000 KG)

CLIMB WEIGHT IMPROVEMENT

4

3

2

0 0 4 8 12 16 (FIELD LIMIT WEIGHT) MINUS (CLIMB LIMIT WEIGHT) (1000 KG) 20

NO

RM AL

CL I (1 MB 00 0 L IM KG IT ) W

EI

5

GH

50 60 70 80 NORMAL CLIMB LIMIT WEIGHT (1000 KG)

Copyright © The Boeing Company. See title page for details.

1.3.24

D632A008-ZZ022

November 1, 2006

737-800/CFM56-7B26 JAA/JAROPS Category C Brakes

TAKEOFF AND LANDING Takeoff Alternate Ratings

Flight Planning and Performance Manual

Improved Climb Field Length Limit - Dry Runway (24K Derate)

Flaps 5

NORMAL TAKEOFF SPEED INCREMENT (KIAS) V1 VR V2

5 (1000 KG)

80

CL I (1 MB 00 0 LIM KG IT W ) EI G

HT

70 60 50 16 14 12 10 9 8 7 6 5 4 3 REF LINE 22 20 18 16 14 12 10 9 8 7 6 5 4 3 2 1 20 18 16 14 12 10 9 8 7 6 5 4 3 2 1

4

CLIMB WEIGHT IMPROVEMENT

3

2

1

NO RM AL

2 1

0 0 4 8 12 16 (FIELD LIMIT WEIGHT) MINUS (CLIMB LIMIT WEIGHT) (1000 KG) 20

50 60 70 80 NORMAL CLIMB LIMIT WEIGHT (1000 KG)

Copyright © The Boeing Company. See title page for details.

November 1, 2006

D632A008-ZZ022

1.3.25

TAKEOFF AND LANDING Takeoff Alternate Ratings

Flight Planning and Performance Manual

737-800/CFM56-7B26 JAA/JAROPS Category C Brakes

Improved Climb Field Length Limit - Dry Runway (24K Derate)

Flaps 10

NORMAL TAKEOFF SPEED INCREMENT (KIAS) V1 VR V2 22 20 16 20 18 14 18 16 12 16 14 14 10 12 12 10 8 10 8 8 6 6 6 4 4 4 3 3 3 2 2 2 1 1 1

CLIMB WEIGHT IMPROVEMENT (1000 KG)

3 NORMAL CLIMB LIMIT WEIGHT (1000 KG) 2 80 70 60 50 40 REF LINE 0 4 8 12 16 (FIELD LIMIT WEIGHT) MINUS (CLIMB LIMIT WEIGHT) (1000 KG) 20 40 2 NORMAL CLIMB LIMIT WEIGHT (1000 KG) 70 60 50 40

1

0

50 60 70 80 NORMAL CLIMB LIMIT WEIGHT (1000 KG)

Flaps 15

CLIMB WEIGHT IMPROVEMENT (1000 KG) NORMAL TAKEOFF SPEED INCREMENT (KIAS) V1 VR V2 8 6 REF LINE 4 3 2 1 12 10 8 6 4 3 2 1 10 8 6 4 3 2 1

1

0 0 4 8 12 16 (FIELD LIMIT WEIGHT) MINUS (CLIMB LIMIT WEIGHT) (1000 KG) 20

40 50 60 70 NORMAL CLIMB LIMIT WEIGHT (1000 KG)

Copyright © The Boeing Company. See title page for details.

1.3.26

D632A008-ZZ022

November 1, 2006

737-800/CFM56-7B26 JAA/JAROPS Category C Brakes

TAKEOFF AND LANDING Takeoff Alternate Ratings

Flight Planning and Performance Manual

Improved Climb Field Length Limit - Dry Runway (24K Derate)

Flaps 25

CLIMB WEIGHT IMPROVEMENT (1000 KG) NORMAL TAKEOFF SPEED INCREMENT (KIAS) V1 VR V2 NORMAL CLIMB LIMIT WEIGHT (1000 KG) 15 70 60 50 40 10 REF LINE 5 3 2 1 25 20 15 10 5 3 1 20 15 10 5 3 1

2

1

0 0 4 8 12 16 (FIELD LIMIT WEIGHT) MINUS (CLIMB LIMIT WEIGHT) (1000 KG) 20

40 50 60 70 NORMAL CLIMB LIMIT WEIGHT (1000 KG)

Copyright © The Boeing Company. See title page for details.

November 1, 2006

D632A008-ZZ022

1.3.27

TAKEOFF AND LANDING Takeoff Alternate Ratings

Flight Planning and Performance Manual

737-800/CFM56-7B26 JAA/JAROPS Category C Brakes

Improved Climb Tire Speed Limit - Dry Runway (24K Derate)

Flaps 1

NORMAL TAKEOFF SPEED INCREMENT (KIAS) V1 VR V2 80

6

(1000 KG)

5

CLIMB WEIGHT IMPROVEMENT

4

3

NO

RM

IM 0 CL 100 ( AL

B

LI

M

IT )

W

EI

G

HT

70

20 18 16 60 14 12 50 10 9 8 7 6 5 4 3

KG

26 24 22 20 18 16 14 12 10 9 8 7 6 5 4 3 2 1

24 22 20 18 16 14 12 10 9 8 7 6 5 4 3 2 1

2

REF LINE

1

2 1

0 0 4 8 12 16 20 (TIRE LIMIT WEIGHT) MINUS (CLIMB LIMIT WEIGHT) (1000 KG) 24 28

50 60 70 80 NORMAL CLIMB LIMIT WEIGHT (1000 KG)

Copyright © The Boeing Company. See title page for details.

1.3.28

D632A008-ZZ022

November 1, 2006

737-800/CFM56-7B26 JAA/JAROPS Category C Brakes

TAKEOFF AND LANDING Takeoff Alternate Ratings

Flight Planning and Performance Manual

Improved Climb Tire Speed Limit - Dry Runway (24K Derate)

Flaps 5

NORMAL TAKEOFF SPEED INCREMENT (KIAS) V1 VR V2

6

(1000 KG)

5

W ) EI G

80

HT

CLIMB WEIGHT IMPROVEMENT

4

3

NO

RM

B KG M LI 00 C 10 ( AL

LI

M

IT

70

60

22 20 18 16 14 12 10 9 8 7 6 5 4 3 REF LINE

50

30 28 26 24 22 20 18 16 14 12 10 9 8 7 6 5 4 3 2 1

2

28 26 24 22 20 18 16 14 12 10 9 8 7 6 5 4 3 2 1

1

2 1

0 0 4 8 12 16 (TIRE LIMIT WEIGHT) MINUS (CLIMB LIMIT WEIGHT) (1000 KG) 20 24

50 60 70 80 NORMAL CLIMB LIMIT WEIGHT (1000 KG)

Copyright © The Boeing Company. See title page for details.

November 1, 2006

D632A008-ZZ022

1.3.29

TAKEOFF AND LANDING Takeoff Alternate Ratings

Flight Planning and Performance Manual

737-800/CFM56-7B26 JAA/JAROPS Category C Brakes

Improved Climb Field Length Limit - Wet Runway (24K Derate)

Flaps 1

NORMAL TAKEOFF SPEED INCREMENT (KIAS) V1 VR V2 80 (1000 KG) 5 20 70 60 50 26 24 22 20 18 16 14 12 10 9 8 7 6 5 4 3 2 1 10 9 8 7 6 5 4 3 2 1 24 22 20 18 16 14 12

6

CL (1 IMB 00 0 L IM KG IT ) W EI G

HT

18 16 14 12 10 9 8 7 6 5 4 REF LINE 3 2 1

CLIMB WEIGHT IMPROVEMENT

4

3

2

1

0 0 4 8 12 16 (FIELD LIMIT WEIGHT) MINUS (CLIMB LIMIT WEIGHT) (1000 KG) 20

NO

RM

AL

50 60 70 80 NORMAL CLIMB LIMIT WEIGHT (1000 KG)

Copyright © The Boeing Company. See title page for details.

1.3.30

D632A008-ZZ022

November 1, 2006

737-800/CFM56-7B26 JAA/JAROPS Category C Brakes

TAKEOFF AND LANDING Takeoff Alternate Ratings

Flight Planning and Performance Manual

Improved Climb Field Length Limit - Wet Runway (24K Derate)

Flaps 5

NORMAL TAKEOFF SPEED INCREMENT (KIAS) V1 VR V2

5 (1000 KG)

80

G HT

CL (1 IMB 00 0 LIM KG I T ) W

4

EI

70 60 50 16 14 12 10 9 8 7 6 5 4 3 REF LINE 22 20 18 16 14 12 10 9 8 7 6 5 4 3 2 1 20 18 16 14 12 10 9 8 7 6 5 4 3 2 1

CLIMB WEIGHT IMPROVEMENT

3

2

1

NO RM

AL

2 1

0 0 8 12 16 (FIELD LIMIT WEIGHT) MINUS (CLIMB LIMIT WEIGHT) (1000 KG) 4 20

50 60 70 80 NORMAL CLIMB LIMIT WEIGHT (1000 KG)

Copyright © The Boeing Company. See title page for details.

November 1, 2006

D632A008-ZZ022

1.3.31

TAKEOFF AND LANDING Takeoff Alternate Ratings

Flight Planning and Performance Manual

737-800/CFM56-7B26 JAA/JAROPS Category C Brakes

Improved Climb Field Length Limit - Wet Runway (24K Derate)

Flaps 10

(1000 KG)

3

NORMAL TAKEOFF SPEED INCREMENT (KIAS) V1 VR V2

CLIMB WEIGHT IMPROVEMENT

2

REF LINE

1

IT M ) KG B M LI 000 C (1 AL T RM H O EIG N W LI

80 70 60 50 40

14 12 10 8 6 4 3 2 1

0 0 4 8 12 16 (FIELD LIMIT WEIGHT) MINUS (CLIMB LIMIT WEIGHT) (1000 KG) 20 40

18 16 14 12 10 8 6 4 3 2 1

16 14 12 10 8 6 4 3 2 1

50 60 70 80 NORMAL CLIMB LIMIT WEIGHT (1000 KG)

Flaps 15

CLIMB WEIGHT IMPROVEMENT (1000 KG) NORMAL TAKEOFF SPEED INCREMENT (KIAS) V1 VR V2 8 6 REF LINE 4 3 2 1 12 10 8 6 4 3 2 1 10 8 6 4 3 2 1

2

N EI CL OR G IM M H A T B L L (1 IMI 00 T 0 KG )

0

70 60 50 40

1

0 4 8 12 16 (FIELD LIMIT WEIGHT) MINUS (CLIMB LIMIT WEIGHT) (1000 KG) 20

W

40 50 60 70 NORMAL CLIMB LIMIT WEIGHT (1000 KG)

Copyright © The Boeing Company. See title page for details.

1.3.32

D632A008-ZZ022

November 1, 2006

737-800/CFM56-7B26 JAA/JAROPS Category C Brakes

TAKEOFF AND LANDING Takeoff Alternate Ratings

Flight Planning and Performance Manual

Improved Climb Field Length Limit - Wet Runway (24K Derate)

Flaps 25

NORMAL TAKEOFF SPEED INCREMENT (KIAS) V1 VR V2

CLIMB WEIGHT IMPROVEMENT (1000 KG)

2

REF LINE

1

W

0 0

AL IT G) K RM LIM NO B 00 10 IM ( CL T GH EI

15 70 60 50 40 10 5 3 2 1

25 20 15 10 5 3 1

20 15 10 5 3 1

4 8 12 16 (FIELD LIMIT WEIGHT) MINUS (CLIMB LIMIT WEIGHT) (1000 KG)

20

40 50 60 70 NORMAL CLIMB LIMIT WEIGHT (1000 KG)

Copyright © The Boeing Company. See title page for details.

November 1, 2006

D632A008-ZZ022

1.3.33

TAKEOFF AND LANDING Takeoff Alternate Ratings

Flight Planning and Performance Manual

737-800/CFM56-7B26 JAA/JAROPS Category C Brakes

Improved Climb Tire Speed Limit - Wet Runway (24K Derate)

Flaps 1

NORMAL TAKEOFF SPEED INCREMENT (KIAS) V1 VR V2 80 (1000 KG) 5

6

CLIMB WEIGHT IMPROVEMENT

4

3

N

O

R

M

M LI ) B KG M 0 LI C 100 ( AL

IT

W

G EI

H

T

70

20 18 16

60

14 12

26 24 22 20 18 16 14 12 10 9 8 7 6 5 4 3 2 1

24 22 20 18 16 14 12 10 9 8 7 6 5 4 3 2 1

50

40 2

10 9 8 7 6 5 4 3 REF LINE 2 1

1

0 0 4 8 12 16 (TIRE LIMIT WEIGHT) MINUS (CLIMB LIMIT WEIGHT) (1000 KG) 20 24

50 60 70 80 NORMAL CLIMB LIMIT WEIGHT (1000 KG)

Copyright © The Boeing Company. See title page for details.

1.3.34

D632A008-ZZ022

November 1, 2006

737-800/CFM56-7B26 JAA/JAROPS Category C Brakes

TAKEOFF AND LANDING Takeoff Alternate Ratings

Flight Planning and Performance Manual

Improved Climb Tire Speed Limit - Wet Runway (24K Derate)

Flaps 5

NORMAL TAKEOFF SPEED INCREMENT (KIAS) V1 VR V2

6

(1000 KG)

5

H T

80 75

EI G

70 65 60 55 50

CLIMB WEIGHT IMPROVEMENT

4

M LI G) M 0K LI C 100 ( AL B IT

W

22 20 18 16 14 12 10 9 8 7 6 5 4 3 REF LINE

3

O R M

30 28 26 24 22 20 18 16 14 12 10 9 8 7 6 5 4 3 2 1

N

2

28 26 24 22 20 18 16 14 12 10 9 8 7 6 5 4 3 2 1

1

2 1

0 0 4 8 12 16 (TIRE LIMIT WEIGHT) MINUS (CLIMB LIMIT WEIGHT) (1000 KG) 20 24

50 60 70 80 NORMAL CLIMB LIMIT WEIGHT (1000 KG)

Copyright © The Boeing Company. See title page for details.

November 1, 2006

D632A008-ZZ022

1.3.35

TAKEOFF AND LANDING Takeoff Alternate Ratings

Flight Planning and Performance Manual

737-800/CFM56-7B26 JAA/JAROPS Category C Brakes

ADVISORY INFORMATION

Slush/Standing Water Takeoff (24K Derate)

Maximum Reverse Thrust Weight Adjustments (1000 KG)

24K DERATE DRY FIELD/OBSTACLE LIMIT WEIGHT (1000 KG) 95 90 85 80 75 70 65 60 55 50 45 40 3 mm (0.12 INCHES) PRESSURE ALTITUDE (FT) S.L. 5000 10000 -12.8 -15.3 -17.8 -11.8 -14.3 -16.8 -10.9 -13.4 -15.9 -9.9 -12.4 -14.9 -9.0 -11.4 -13.9 -8.0 -10.5 -13.0 -7.1 -9.6 -12.1 -6.2 -8.7 -11.2 -5.4 -7.9 -10.4 -4.5 -7.0 -9.5 -3.6 -6.1 -8.6 -2.7 -5.2 -7.7 SLUSH/STANDING WATER DEPTH 6 mm (0.25 INCHES) PRESSURE ALTITUDE (FT) S.L. 5000 10000 -16.4 -18.9 -21.4 -14.8 -17.3 -19.8 -13.3 -15.8 -18.3 -11.9 -14.4 -16.9 -10.6 -13.1 -15.6 -9.3 -11.8 -14.3 -8.2 -10.6 -13.1 -7.1 -9.6 -12.0 -6.0 -8.5 -11.0 -4.9 -7.4 -9.9 -3.8 -6.3 -8.8 -2.7 -5.2 -7.7 SLUSH/STANDING WATER DEPTH 6 mm (0.25 INCHES) PRESSURE ALTITUDE (FT) S.L. 5000 10000 33.6 53.6 38.2 75.3 58.6 42.9 99.0 80.8 63.7 104.7 86.4 13 mm (0.50 INCHES) PRESSURE ALTITUDE (FT) S.L. 5000 10000 -25.3 -27.8 -30.3 -22.4 -24.9 -27.4 -19.5 -22.0 -24.5 -16.8 -19.3 -21.8 -14.4 -16.9 -19.4 -12.2 -14.7 -17.2 -10.2 -12.7 -15.2 -8.5 -11.0 -13.5 -7.1 -9.6 -12.1 -5.9 -8.4 -10.9 -4.9 -7.4 -9.9 -4.2 -6.7 -9.2

V1(MCG) Limit Weight (1000 KG)

ADJUSTED FIELD LENGTH (M) 1200 1400 1600 1800 2000 3 mm (0.12 INCHES) PRESSURE ALTITUDE (FT) S.L. 5000 10000 30.2 50.4 34.9 72.3 55.4 39.7 96.2 77.8 60.6 102.0 83.4 13 mm (0.50 INCHES) PRESSURE ALTITUDE (FT) S.L. 5000 10000 39.3 58.9 43.8 80.6 63.8 48.4 104.3 86.2 68.9 91.8

1. Enter Weight Adjustment table with slush/standing water depth and 24K Derate dry field/obstacle limit weight to obtain slush/ standing water weight adjustment. 2. Adjust field length available by -30 m/+30 m for every 5°C above/below 4°C. 3. Find V1(MCG) limit weight for adjusted field length and pressure altitude. 4. Max allowable slush/standing water limited weight is lesser of weights from 1 and 3.

V1 Adjustment (KIAS)

WEIGHT (1000 KG) 90 85 80 75 70 65 60 55 50 45 40 3 mm (0.12 INCHES) PRESSURE ALTITUDE (FT) S.L. 5000 10000 -13 -11 -8 -14 -12 -9 -15 -13 -10 -17 -14 -12 -18 -15 -13 -19 -16 -14 -20 -18 -15 -22 -19 -17 -22 -20 -17 -23 -20 -18 -23 -20 -18 SLUSH/STANDING WATER DEPTH 6 mm (0.25 INCHES) PRESSURE ALTITUDE (FT) S.L. 5000 10000 -7 -5 -2 -8 -6 -3 -9 -7 -4 -11 -8 -6 -12 -10 -7 -14 -12 -9 -16 -14 -11 -19 -16 -14 -20 -18 -15 -21 -18 -16 -21 -18 -16 13 mm (0.50 INCHES) PRESSURE ALTITUDE (FT) S.L. 5000 10000 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 -3 -1 0 -7 -5 -2 -11 -9 -6 -14 -12 -9 -17 -14 -12 -18 -15 -13

1. Obtain V1, VR and V2 for the actual weight using the 24K Derate Dry Runway Takeoff Speeds table. 2. If V1(MCG) limited, set V1 = V1(MCG). If not V1(MCG) limited, enter V1 Adjustment table with the actual weight to obtain V1 speed adjustment. If adjusted V1 is less than V1(MCG), set V1 = V1(MCG).V1 not to exceed VR.

Copyright © The Boeing Company. See title page for details.

1.3.36

D632A008-ZZ022

November 1, 2006

737-800/CFM56-7B26 JAA/JAROPS Category C Brakes

TAKEOFF AND LANDING Takeoff Alternate Ratings

Flight Planning and Performance Manual

ADVISORY INFORMATION

Slush/Standing Water Takeoff (24K Derate)

No Reverse Thrust Weight Adjustments (1000 KG)

24K DERATE DRY FIELD/OBSTACLE LIMIT WEIGHT (1000 KG) 95 90 85 80 75 70 65 60 55 50 45 40 3 mm (0.12 INCHES) PRESSURE ALTITUDE (FT) S.L. 5000 10000 -15.9 -19.1 -22.3 -14.6 -17.8 -21.0 -13.3 -16.5 -19.7 -12.1 -15.2 -18.4 -10.9 -14.0 -17.2 -9.7 -12.9 -16.1 -8.6 -11.8 -15.0 -7.6 -10.8 -13.9 -6.6 -9.8 -12.9 -5.7 -8.8 -12.0 -4.7 -7.9 -11.1 -3.8 -7.0 -10.1 SLUSH/STANDING WATER DEPTH 6 mm (0.25 INCHES) PRESSURE ALTITUDE (FT) S.L. 5000 10000 -19.6 -22.8 -25.9 -17.8 -20.9 -24.1 -15.9 -19.1 -22.3 -14.2 -17.4 -20.5 -12.5 -15.7 -18.9 -11.0 -14.2 -17.4 -9.6 -12.8 -16.0 -8.4 -11.5 -14.7 -7.2 -10.4 -13.5 -6.1 -9.3 -12.5 -5.1 -8.3 -11.4 -4.0 -7.2 -10.4 SLUSH/STANDING WATER DEPTH 6 mm (0.25 INCHES) PRESSURE ALTITUDE (FT) S.L. 5000 10000 45.5 72.4 102.0 13 mm (0.50 INCHES) PRESSURE ALTITUDE (FT) S.L. 5000 10000 -27.0 -30.1 -33.3 -24.1 -27.3 -30.5 -21.2 -24.4 -27.6 -18.5 -21.7 -24.9 -16.1 -19.3 -22.4 -13.8 -17.0 -20.2 -11.8 -15.0 -18.2 -10.1 -13.2 -16.4 -8.5 -11.7 -14.9 -7.1 -10.3 -13.5 -5.8 -9.0 -12.2 -4.5 -7.6 -10.8

V1(MCG) Limit Weight (1000 KG)

ADJUSTED FIELD LENGTH (M) 1400 1600 1800 2000 2200 2400 3 mm (0.12 INCHES) PRESSURE ALTITUDE (FT) S.L. 5000 10000 37.6 65.4 93.9 13 mm (0.50 INCHES) PRESSURE ALTITUDE (FT) S.L. 5000 10000 36.6 58.9 39.9 87.6 63.0 43.4 93.0 67.3 98.4

42.0 70.0 98.5

46.5 74.5 103.1

49.7 77.0

53.9 81.7

1. Enter Weight Adjustment table with slush/standing water depth and 24K Derate dry field/obstacle limit weight to obtain slush/ standing water weight adjustment. 2. Adjust field length available by -35 m/+30 m for every 5°C above/below 4°C. 3. Find V1(MCG) limit weight for available field length and pressure altitude. 4. Max allowable slush/standing water limited weight is lesser of weights from 1 and 3.

V1 Adjustment (KIAS)

WEIGHT (1000 KG) 95 90 85 80 75 70 65 60 55 50 45 40 3 mm (0.12 INCHES) PRESSURE ALTITUDE (FT) S.L. 5000 10000 -14 -12 -9 -16 -14 -11 -19 -16 -14 -21 -18 -16 -22 -20 -17 -24 -22 -19 -25 -23 -20 -27 -24 -22 -28 -25 -23 -29 -26 -24 -29 -27 -24 -30 -27 -25 SLUSH/STANDING WATER DEPTH 6 mm (0.25 INCHES) PRESSURE ALTITUDE (FT) S.L. 5000 10000 -2 0 0 -5 -3 0 -9 -6 -4 -12 -9 -7 -15 -12 -10 -17 -15 -12 -20 -17 -15 -22 -20 -17 -24 -21 -19 -26 -23 -21 -27 -25 -22 -28 -26 -23 13 mm (0.50 INCHES) PRESSURE ALTITUDE (FT) S.L. 5000 10000 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 -4 -2 0 -11 -8 -6 -15 -13 -10 -19 -17 -14 -22 -20 -17 -24 -21 -19

1. Obtain V1, VR and V2 for the actual weight using the 24K Derate Dry Runway Takeoff Speeds table. 2. If V1(MCG) limited, set V1 = V1(MCG). If not V1(MCG) limited, enter V1 Adjustment table with the actual weight to obtain V1 speed adjustment. If adjusted V1 is less than V1(MCG), set V1 = V1(MCG). V1 not to exceed VR.

Copyright © The Boeing Company. See title page for details.

November 1, 2006

D632A008-ZZ022

1.3.37

TAKEOFF AND LANDING Takeoff Alternate Ratings

Flight Planning and Performance Manual

737-800/CFM56-7B26 JAA/JAROPS Category C Brakes

ADVISORY INFORMATION

Slippery Runway Takeoff (24K Derate)

Maximum Reverse Thrust Weight Adjustments (1000 KG)

24K DERATE DRY FIELD/OBSTACLE LIMIT WEIGHT (1000 KG) 95 90 85 80 75 70 65 60 55 50 45 40 GOOD PRESSURE ALTITUDE (FT) S.L. 5000 10000 -0.3 -0.3 -0.3 -0.6 -0.6 -0.6 -1.0 -1.0 -1.0 -1.3 -1.3 -1.3 -1.4 -1.4 -1.4 -1.5 -1.5 -1.5 -1.6 -1.6 -1.6 -1.5 -1.5 -1.5 -1.4 -1.4 -1.4 -1.2 -1.2 -1.2 -0.9 -0.9 -0.9 -0.5 -0.5 -0.5 REPORTED BRAKING ACTION MEDIUM PRESSURE ALTITUDE (FT) S.L. 5000 10000 -5.8 -5.8 -5.8 -5.8 -5.8 -5.8 -5.9 -5.9 -5.9 -5.9 -5.9 -5.9 -5.8 -5.8 -5.8 -5.6 -5.6 -5.6 -5.3 -5.3 -5.3 -5.0 -5.0 -5.0 -4.6 -4.6 -4.6 -4.1 -4.1 -4.1 -3.5 -3.5 -3.5 -2.9 -2.9 -2.9 REPORTED BRAKING ACTION MEDIUM PRESSURE ALTITUDE (FT) S.L. 5000 10000 31.1 53.9 78.8 POOR PRESSURE ALTITUDE (FT) S.L. 5000 10000 -10.7 -10.7 -10.7 -10.5 -10.5 -10.5 -10.2 -10.2 -10.2 -9.9 -9.9 -9.9 -9.5 -9.5 -9.5 -9.0 -9.0 -9.0 -8.4 -8.4 -8.4 -7.7 -7.7 -7.7 -7.0 -7.0 -7.0 -6.1 -6.1 -6.1 -5.2 -5.2 -5.2 -4.2 -4.2 -4.2

V1(MCG) Limit Weight (1000 KG)

ADJUSTED FIELD LENGTH (M) 1000 1200 1400 1600 1800 2000 2200 2400 2600 2800 GOOD PRESSURE ALTITUDE (FT) S.L. 5000 10000 47.2 79.8 62.7 45.0 94.3 77.7 POOR PRESSURE ALTITUDE (FT) S.L. 5000 10000

34.7 57.8 83.1

38.3 61.8 87.4

33.8 47.5 62.7 79.9 99.7

30.8 44.4 59.3 75.9 95.3

41.3 55.9 72.1 90.8

1. Enter Weight Adjustment table with reported braking action and 24K Derate dry field/obstacle limit weight to obtain slippery runway weight adjustment. 2. Adjust "Good" field length available by -20 m/+20 m for every 5°C above/below 4°C. Adjust "Medium" field length available by -20 m/+20 m for every 5°C above/below 4°C. Adjust "Poor" field length available by -35 m/+35 m for every 5°C above/below 4°C. 3. Find V1(MCG) limit weight for adjusted field length and pressure altitude. 4. Max allowable slippery runway limited weight is lesser of weights from 1 and 3.

V1 Adjustment (KIAS)

WEIGHT (1000 KG) 90 85 80 75 70 65 60 55 50 45 40 GOOD PRESSURE ALTITUDE (FT) S.L. 5000 10000 -4 -3 -2 -5 -4 -3 -6 -5 -3 -7 -6 -4 -8 -6 -5 -9 -7 -6 -9 -8 -7 -10 -9 -8 -11 -10 -8 -12 -10 -9 -12 -11 -10 REPORTED BRAKING ACTION MEDIUM PRESSURE ALTITUDE (FT) S.L. 5000 10000 -13 -12 -10 -14 -12 -11 -15 -13 -12 -16 -15 -14 -18 -16 -15 -19 -18 -17 -21 -19 -18 -22 -21 -20 -23 -22 -21 -24 -23 -22 -25 -24 -22 POOR PRESSURE ALTITUDE (FT) S.L. 5000 10000 -24 -23 -21 -25 -23 -22 -26 -25 -23 -28 -26 -25 -30 -28 -27 -32 -30 -29 -34 -33 -31 -36 -34 -33 -37 -36 -35 -39 -37 -36 -39 -38 -37

1. Obtain V1, VR and V2 for the actual weight using the 24K Derate Dry Runway Takeoff Speeds table. 2. If V1(MCG) limited, set V1 = V1(MCG). If not V1(MCG) limited, enter V1 Adjustment table with the actual weight to obtain V1 speed adjustment. If adjusted V1 is less than V1(MCG), set V1 = V1(MCG). V1 not to exceed VR.

Copyright © The Boeing Company. See title page for details.

1.3.38

D632A008-ZZ022

November 1, 2006

737-800/CFM56-7B26 JAA/JAROPS Category C Brakes

TAKEOFF AND LANDING Takeoff Alternate Ratings

Flight Planning and Performance Manual

ADVISORY INFORMATION

Slippery Runway Takeoff (24K Derate)

No Reverse Thrust Weight Adjustments (1000 KG)

24K DERATE DRY FIELD/OBSTACLE LIMIT WEIGHT (1000 KG) 95 90 85 80 75 70 65 60 55 50 45 40 GOOD PRESSURE ALTITUDE (FT) S.L. 5000 10000 -1.4 -1.4 -1.4 -1.7 -1.7 -1.7 -1.9 -1.9 -1.9 -2.2 -2.2 -2.2 -2.3 -2.3 -2.3 -2.4 -2.4 -2.4 -2.4 -2.4 -2.4 -2.3 -2.3 -2.3 -2.1 -2.1 -2.1 -1.9 -1.9 -1.9 -1.7 -1.7 -1.7 -1.3 -1.3 -1.3 REPORTED BRAKING ACTION MEDIUM PRESSURE ALTITUDE (FT) S.L. 5000 10000 -8.0 -8.0 -8.0 -7.9 -7.9 -7.9 -7.8 -7.8 -7.8 -7.7 -7.7 -7.7 -7.5 -7.5 -7.5 -7.2 -7.2 -7.2 -6.8 -6.8 -6.8 -6.4 -6.4 -6.4 -5.9 -5.9 -5.9 -5.3 -5.3 -5.3 -4.6 -4.6 -4.6 -3.9 -3.9 -3.9 REPORTED BRAKING ACTION MEDIUM PRESSURE ALTITUDE (FT) S.L. 5000 10000 POOR PRESSURE ALTITUDE (FT) S.L. 5000 10000 -14.2 -14.2 -14.2 -13.6 -13.6 -13.6 -13.1 -13.1 -13.1 -12.4 -12.4 -12.4 -11.8 -11.8 -11.8 -11.0 -11.0 -11.0 -10.3 -10.3 -10.3 -9.4 -9.4 -9.4 -8.5 -8.5 -8.5 -7.6 -7.6 -7.6 -6.6 -6.6 -6.6 -5.5 -5.5 -5.5

V1(MCG) Limit Weight (1000 KG)

ADJUSTED FIELD LENGTH (M) 1000 1200 1400 1600 1800 2000 2200 2400 2600 2800 3000 3200 3400 GOOD PRESSURE ALTITUDE (FT) S.L. 5000 10000 32.8 71.9 55.0 36.4 90.2 74.9 POOR PRESSURE ALTITUDE (FT) S.L. 5000 10000

50.2 83.2

60.8 93.3

37.4 71.2 103.3 45.3 67.2 92.8 39.3 60.4 84.8

33.6 53.9 77.1 103.8

1. Enter Weight Adjustment table with reported braking action and 24K Derate dry field/obstacle limit weight to obtain slippery runway weight adjustment. 2. Adjust "Good" field length available by -25 m/+20 m for every 5°C above/below 4°C. Adjust "Medium" field length available by -25 m/+20 m for every 5°C above/below 4°C. Adjust "Poor" field length available by -45 m/+40 m for every 5°C above/below 4°C. 3. Find V1(MCG) limit weight for adjusted field length and pressure altitude. 4. Max allowable slippery runway limited weight is lesser of weights from 1 and 3.

V1 Adjustment (KIAS)

WEIGHT (1000 KG) 95 90 85 80 75 70 65 60 55 50 45 40 GOOD PRESSURE ALTITUDE (FT) S.L. 5000 10000 -4 -2 0 -5 -3 0 -6 -4 -1 -7 -5 -2 -8 -6 -3 -9 -7 -4 -11 -8 -6 -12 -9 -7 -13 -10 -8 -14 -11 -9 -15 -12 -10 -15 -13 -10 REPORTED BRAKING ACTION MEDIUM PRESSURE ALTITUDE (FT) S.L. 5000 10000 -15 -13 -10 -16 -14 -11 -17 -15 -12 -19 -16 -14 -20 -18 -15 -22 -20 -17 -24 -22 -19 -26 -24 -21 -28 -26 -23 -30 -28 -25 -31 -29 -26 -32 -30 -27 POOR PRESSURE ALTITUDE (FT) S.L. 5000 10000 -31 -28 -26 -32 -30 -27 -34 -31 -29 -36 -33 -31 -38 -35 -33 -40 -38 -35 -43 -41 -38 -46 -43 -41 -48 -46 -43 -50 -48 -45 -52 -49 -47 -53 -50 -48

1. Obtain V1, VR and V2 for the actual weight using the 24K Derate Dry Runway Takeoff Speeds table. 2. If V1(MCG) limited, set V1 = V1(MCG). If not V1(MCG) limited, enter V1 Adjustment table with the actual weight to obtain V1 speed adjustment. If adjusted V1 is less than V1(MCG), set V1 = V1(MCG). V1 not to exceed VR.

Copyright © The Boeing Company. See title page for details.

November 1, 2006

D632A008-ZZ022

1.3.39

TAKEOFF AND LANDING Takeoff Alternate Ratings

Flight Planning and Performance Manual

737-800/CFM56-7B26 JAA/JAROPS Category C Brakes

Takeoff Speeds - Dry Runway (24K Derate)

V1, VR, V2

WEIGHT (1000 KG) 90 85 80 75 70 65 60 55 50 45 40 V1 172 166 160 155 149 143 137 130 122 115 107 FLAPS 1 VR 172 167 162 156 150 144 138 131 123 116 108 V2 174 170 166 161 157 152 147 142 136 130 124 V1 159 154 149 143 137 131 124 118 110 103 FLAPS 5 VR 160 155 150 144 138 132 125 118 111 103 V2 163 159 155 151 147 142 136 131 125 119 V1 FLAPS 10 VR V2 V1 FLAPS 15 VR V2 V1 FLAPS 25 VR V2

148 142 136 130 123 116 109 102

148 143 137 131 124 117 110 102

153 149 145 140 135 129 124 118

145 139 133 127 121 114 107 99

145 140 134 128 121 115 107 100

150 146 142 137 132 127 121 116

142 137 131 125 118 112 105 97

142 137 131 125 119 112 105 98

148 144 139 135 130 125 119 114

Check V1(MCG).

V1, VR, V2 Adjustments*

TEMP °C 70 60 50 40 30 20 -60 °F 158 140 122 104 86 68 -76 -2 5 4 2 1 0 0 0 V1 PRESSURE ALTITUDE (1000 FT) 0 2 4 6 8 6 5 5 6 3 4 5 6 7 2 3 4 5 6 0 1 3 4 5 0 1 1 2 4 0 1 1 2 3 SLOPE (%) 0 0 0 0 0 0 0 0 0 0 0 0 10 -2 5 3 2 1 0 0 0 VR PRESSURE ALTITUDE (1000 FT) 0 2 4 6 8 5 4 5 6 3 4 5 6 7 2 3 4 5 6 0 1 2 4 5 0 1 1 2 4 0 1 1 2 3 10 -2 -3 -2 -2 -1 0 0 0 V2 PRESSURE ALTITUDE (1000 FT) 0 2 4 6 8 -4 -3 -3 -4 -2 -3 -3 -4 -4 -1 -2 -2 -3 -4 0 -1 -1 -2 -3 0 0 -1 -1 -2 0 0 -1 -1 -1 10

8 7 6 5 4

8 7 6 5 4

-5 -4 -4 -3 -2

Slope and Wind V1 Adjustments*

WEIGHT (1000 KG) 90 85 80 75 70 65 60 55 50 45 40 -2 -4 -4 -3 -3 -2 -2 -1 -1 -1 -1 0 -1 -2 -2 -2 -1 -1 -1 -1 -1 0 0 0 1 0 0 1 1 1 1 1 1 0 0 0 2 0 1 1 1 1 1 1 1 0 0 0 -15 -2 -2 -2 -2 -1 -1 -1 -1 -2 -2 -2 -10 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -5 -1 -1 -1 0 0 0 0 0 0 0 0 WIND (KTS) 0 10 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 20 0 0 0 1 1 1 1 1 0 0 0 30 0 0 1 1 1 1 1 1 0 0 0 40 0 1 1 1 1 1 1 1 0 0 0

Clearway and Stopway V1 Adjustments*

NORMAL V1 (KIAS) 160 140 120 100 300 -4 -3 -4 -5 200 -3 -3 -4 -5 100 -2 -2 -2 -3 CLEARWAY MINUS STOPWAY (M) 0 -100 0 1 0 1 0 1 0 1 -200 1 1 1 1 -300 1 1 1 1

*V1 not to exceed VR

Max Allowable Clearway for V1 Adjustment

FIELD LENGTH (M) MAX ALLOWABLE CLEARWAY (M) 1200 150 1600 180 2000 210 PRESSURE ALTITUDE (FT) 4000 85 85 88 92 95 96 2400 240 2800 270 3200 290

V1(MCG)

TEMP °C 70 60 50 40 30 20 -60 °F 158 140 122 104 86 68 -76 -2000 90 90 92 97 100 100 101 0 88 88 90 95 99 99 101 2000 87 87 91 95 97 98 6000 8000 10000

83 84 88 92 94

81 81 85 88 91

79 79 81 85 89

Copyright © The Boeing Company. See title page for details.

1.3.40

D632A008-ZZ022

November 1, 2006

737-800/CFM56-7B26 JAA/JAROPS Category C Brakes

TAKEOFF AND LANDING Takeoff Alternate Ratings

Flight Planning and Performance Manual

Takeoff Speeds - Wet Runway (24K Derate)

V1, VR, V2

WEIGHT (1000 KG) 90 85 80 75 70 65 60 55 50 45 40 V1 167 161 155 149 142 136 129 122 114 107 98 FLAPS 1 VR 172 167 162 156 150 144 138 131 123 116 108 V2 174 170 166 161 157 152 147 142 136 130 124 V1 154 148 142 136 130 123 116 109 102 94 FLAPS 5 VR 160 155 150 144 138 132 125 118 111 103 V2 163 159 155 151 147 142 136 131 125 119 V1 FLAPS 10 VR V2 V1 FLAPS 15 VR V2 V1 FLAPS 25 VR V2

142 136 129 123 116 109 101 93

148 143 137 131 124 117 110 102

153 149 145 140 135 129 124 118

139 133 127 120 113 106 99 92

145 140 134 128 121 115 107 100

150 146 142 137 132 127 121 115

137 131 125 118 111 104 97 90

142 137 131 125 119 112 105 98

148 144 139 135 130 125 119 114

Check V1(MCG).

V1, VR, V2 Adjustments*

TEMP °C 70 60 50 40 30 20 -60 °F 158 140 122 104 86 68 -76 -2 8 5 3 1 0 0 0 V1 PRESSURE ALTITUDE (1000 FT) 0 2 4 6 8 8 6 8 9 4 5 7 8 10 2 3 5 6 7 0 1 3 4 6 0 1 1 2 4 0 1 1 2 3 SLOPE (%) 0 0 0 0 0 0 0 0 0 0 0 0 10 -2 5 3 2 1 0 0 0 VR PRESSURE ALTITUDE (1000 FT) 0 2 4 6 8 5 4 5 6 3 4 5 6 7 2 3 4 5 6 0 1 3 4 5 0 1 1 2 4 0 1 1 2 3 10 -2 -3 -2 -2 -1 0 0 0 V2 PRESSURE ALTITUDE (1000 FT) 0 2 4 6 8 -4 -3 -3 -4 -2 -3 -3 -4 -4 -1 -2 -2 -3 -4 0 -1 -1 -2 -3 0 0 -1 -1 -2 0 0 -1 -1 -1 10

11 9 7 5 4

8 7 6 5 4

-5 -4 -4 -3 -2

Slope and Wind V1 Adjustments*

WEIGHT (1000 KG) 90 85 80 75 70 65 60 55 50 45 40 -2 -6 -5 -5 -5 -4 -4 -3 -3 -2 -2 -1 -1 -3 -3 -3 -2 -2 -2 -2 -1 -1 -1 0 1 3 3 3 2 2 2 2 1 1 1 1 2 6 5 5 5 4 4 3 3 3 2 2 -15 -3 -3 -3 -3 -3 -4 -4 -4 -4 -4 -5 -10 -2 -2 -2 -2 -2 -2 -2 -2 -3 -3 -3 STOPWAY (M) 0 0 0 0 0 100 1 1 2 3 200 1 2 4 6 300 1 3 6 7 -5 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 WIND (KTS) 0 10 0 1 0 1 0 1 0 1 0 1 0 1 0 1 0 1 0 1 0 1 0 1 20 1 1 1 1 1 1 1 2 2 2 2 30 2 2 2 2 2 2 2 2 3 3 3 40 2 2 2 2 2 3 3 3 3 4 4

Stopway V1 Adjustments*

NORMAL V1 (KIAS) 160 140 120 100

Use of clearway not allowed on wet runways. *V1 not to exceed VR

V1(MCG)

TEMP °C 70 60 50 40 30 20 -60 °F 158 140 122 104 86 68 -76 -2000 90 90 92 97 100 100 101 0 88 88 90 95 99 99 101 2000 87 87 91 95 97 98 PRESSURE ALTITUDE (FT) 4000 85 85 88 92 95 96 6000 8000 10000

83 84 88 92 94

81 81 85 88 91

79 79 81 85 89

Copyright © The Boeing Company. See title page for details.

November 1, 2006

D632A008-ZZ022

1.3.41

TAKEOFF AND LANDING Takeoff Alternate Ratings

Flight Planning and Performance Manual

737-800/CFM56-7B26 JAA/JAROPS Category C Brakes

Takeoff %N1 (24K Derate)

Based on engine bleeds for packs on, engine and wing anti-ice on or off

OAT (°C) 60 55 50 45 40 35 30 25 20 15 10 5 0 -5 -10 -15 -20 -25 -30 -35 -40 -45 -50 -2000 90.3 91.0 91.8 92.6 93.4 94.2 93.8 93.1 92.3 91.6 90.8 90.0 89.2 88.4 87.6 86.8 86.0 85.2 84.4 83.5 82.7 81.8 81.0 -1000 90.8 91.6 92.4 93.2 94.0 94.8 95.0 94.3 93.5 92.7 92.0 91.2 90.4 89.6 88.8 88.0 87.1 86.3 85.5 84.6 83.8 82.9 82.0 0 91.2 92.0 92.8 93.6 94.4 95.2 96.1 95.4 94.6 93.8 93.0 92.2 91.4 90.6 89.8 89.0 88.2 87.3 86.5 85.6 84.8 83.9 83.0 1000 91.2 92.0 92.8 93.6 94.4 95.2 96.0 95.9 95.1 94.3 93.6 92.8 92.0 91.2 90.4 89.5 88.7 87.9 87.0 86.2 85.3 84.4 83.5 2000 91.1 92.0 92.8 93.6 94.4 95.2 96.0 96.4 95.7 94.9 94.1 93.3 92.5 91.7 90.9 90.0 89.2 88.4 87.5 86.6 85.8 84.9 84.0 AIRPORT PRESSURE ALTITUDE (FT) 3000 4000 5000 91.1 91.0 91.1 91.9 91.9 91.9 92.7 92.7 92.7 93.6 93.5 93.5 94.3 94.3 94.2 95.1 95.1 95.0 96.0 95.9 95.8 96.7 96.7 96.6 96.3 96.9 97.6 95.5 96.1 96.8 94.7 95.3 96.0 93.9 94.5 95.2 93.1 93.7 94.4 92.3 92.9 93.6 91.5 92.1 92.8 90.6 91.3 92.0 89.8 90.5 91.2 89.0 89.6 90.3 88.1 88.8 89.5 87.3 87.9 88.6 86.4 87.0 87.8 85.5 86.2 86.9 84.6 85.3 86.0 PRESSURE ALTITUDE (FT) 3000 4000 5000 0.7 0.8 0.8 6000 91.2 92.0 92.7 93.5 94.2 95.0 95.8 96.6 97.5 97.5 96.7 95.9 95.1 94.3 93.5 92.7 91.9 91.0 90.2 89.3 88.5 87.6 86.7 7000 91.0 91.9 92.6 93.4 94.1 94.9 95.7 96.5 97.5 98.2 97.5 96.7 95.9 95.1 94.3 93.5 92.6 91.8 91.0 90.1 89.3 88.4 87.5 8000 91.2 91.7 92.6 93.3 94.1 94.8 95.7 96.4 97.4 98.6 98.2 97.4 96.7 95.9 95.1 94.3 93.5 92.6 91.8 91.0 90.1 89.3 88.4 9000 91.3 91.3 92.2 93.1 94.0 94.8 95.6 96.4 97.3 98.6 99.1 98.4 97.6 96.8 96.1 95.3 94.5 93.7 92.9 92.1 91.2 90.4 89.5 10000 91.4 90.8 91.8 92.8 93.8 94.7 95.6 96.3 97.2 98.5 100.0 99.3 98.5 97.7 97.0 96.2 95.4 94.6 93.8 93.0 92.2 91.4 90.5

%N1 Adjustments for Engine Bleeds

BLEED CONFIGURATION PACKS OFF -2000 0.7 -1000 0.7 0 0.7 1000 0.7 2000 0.7 6000 0.8 7000 0.8 8000 0.8 9000 0.9 10000 1.0

Stab Trim Setting (24K Derate)

Flaps 1 and 5

WEIGHT (1000 KG) 85 80 75 70 65 60 55 50 45 40 6 8 1/2 8 1/2 8 1/4 8 7 3/4 7 1/2 7 1/4 6 3/4 6 1/2 6 1/2 8 8 1/2 8 1/4 8 7 3/4 7 1/2 7 1/4 7 6 1/2 6 1/4 6 1/4 10 8 1/4 8 7 3/4 7 1/2 7 1/4 7 6 3/4 6 1/4 6 6 16 7 1/2 7 6 3/4 6 1/2 6 1/4 6 5 3/4 5 1/2 5 5 C.G. (%MAC) 21 26 6 1/2 5 3/4 6 1/4 5 1/2 6 5 1/4 5 3/4 5 5 1/2 4 3/4 5 1/2 4 3/4 5 1/4 4 1/2 4 3/4 4 4 1/2 3 3/4 4 1/2 3 3/4 30 5 4 3/4 4 1/2 4 1/2 4 1/4 4 3 3/4 3 1/2 3 3 32 4 1/2 4 1/2 4 1/4 4 4 3 3/4 3 1/2 3 1/4 2 3/4 2 3/4 34 4 1/4 4 4 3 3/4 3 1/2 3 1/4 3 1/4 2 3/4 2 1/2 2 1/2 36 3 3/4 3 3/4 3 1/2 3 1/4 3 1/4 3 2 3/4 2 1/2 2 1/4 2 1/4

Flaps 10, 15 and 25

WEIGHT (1000 KG) 85 80 75 70 65 60 55 50 45 40 6 8 1/2 8 1/2 8 1/2 8 1/2 8 1/4 7 3/4 7 6 1/2 5 3/4 5 3/4 8 8 1/2 8 1/2 8 1/2 8 1/4 7 3/4 7 1/4 6 3/4 6 5 1/2 5 1/2 10 8 1/2 8 1/2 8 1/4 7 3/4 7 1/4 6 3/4 6 1/4 5 3/4 5 5 16 6 3/4 6 1/2 6 1/4 6 5 1/2 5 1/4 5 4 1/2 4 1/4 4 1/4 C.G. (%MAC) 21 26 5 1/2 4 1/2 5 1/2 4 1/2 5 1/4 4 1/4 5 4 4 3/4 3 3/4 4 1/4 3 1/2 4 3 1/4 3 3/4 3 3 1/2 2 3/4 3 1/2 2 3/4 30 3 3/4 3 1/2 3 1/2 3 1/4 3 2 3/4 2 1/2 2 1/4 2 1/4 2 1/4 32 3 1/4 3 1/4 3 2 3/4 2 1/2 2 1/4 2 1/4 2 1/4 2 1/4 2 1/4 34 2 3/4 2 3/4 2 1/2 2 1/4 2 1/4 2 1/4 2 1/4 2 1/4 2 1/4 2 1/4 36 2 1/2 2 1/4 2 1/4 2 1/4 2 1/4 2 1/4 2 1/4 2 1/4 2 1/4 2 1/4

Copyright © The Boeing Company. See title page for details.

1.3.42

D632A008-ZZ022

November 1, 2006

737-800/CFM56-7B26 JAA/JAROPS Category C Brakes

TAKEOFF AND LANDING Takeoff Alternate Ratings

Flight Planning and Performance Manual

Takeoff Field Limit - Dry Runway (22K Derate)

Flaps 1

Based on engine bleed for packs on and anti-ice off

AIR

88

PO

76 72 68 64

LIMIT

60 56 MINIMUM FIELD LENGTH 52 48 REF LINE 44 40

With engine bleed for packs off, increase weight by 450 kg. With engine anti-ice on, decrease weight by 150 kg. With engine and wing anti-ice on, decrease weight by 600 kg (optional system).

Copyright © The Boeing Company. See title page for details.

November 1, 2006

D632A008-ZZ022

RUNWAY SLOPE (%)

-60 -40 -20 0 20 40 60 80 100 120 140 -60 -50 -40 -30 -20 -10 0 10 20 30 40 50 60 70 HEAD 40 C AIRPORT OAT 20 0 REF LINE -10 TAIL WIND (KTS)

F

UP 2 REF LINE 0 -2 1000 FT 4 5 6 7 8 9 10 11 12 13 DOWN 100 M 12 14 16 18 20 22 24 26 28 30 32 34 36 38 40 42 FIELD LENGTH AVAILABLE

1.3.43

FIELD LENGTH LIMIT BRAKE RELEASE WEIGHT (1000 KG)

RT PR E (10 SSU 00 RE F A -2 T) LTITU DE -1 0 1 2 3 4 5 6 7 8 9 10

84 80

ENVIR ONME

NTAL

TAKEOFF AND LANDING Takeoff Alternate Ratings

Flight Planning and Performance Manual

737-800/CFM56-7B26 JAA/JAROPS Category C Brakes

Takeoff Field Limit - Dry Runway (22K Derate)

Flaps 5

Based on engine bleed for packs on and anti-ice off

76 72 68 64

LIMIT

60 56 MINIMUM FIELD LENGTH 52 48 REF LINE 44 40

With engine bleed for packs off, increase weight by 450 kg. With engine anti-ice on, decrease weight by 150 kg. With engine and wing anti-ice on, decrease weight by 600 kg (optional system).

Copyright © The Boeing Company. See title page for details.

1.3.44

D632A008-ZZ022

November 1, 2006

RUNWAY SLOPE (%)

-60 -40 -20 0 20 40 60 80 100 120 140 -60 -50 -40 -30 -20 -10 0 10 20 30 40 50 60 70 HEAD 40 C AIRPORT OAT 20 0 REF LINE -10 TAIL WIND (KTS)

F

UP 2 REF LINE 0 -2 1000 FT 4 5 6 7 8 9 10 11 12 13 DOWN 100 M 12 14 16 18 20 22 24 26 28 30 32 34 36 38 40 42 FIELD LENGTH AVAILABLE

FIELD LENGTH LIMIT BRAKE RELEASE WEIGHT (1000 KG)

AI ALT RPOR ITU T DE -2 -1 0 1 2 3 4 5 6 7 8 9 10

88

PR E (10 SSUR 00 E FT)

84 80

ENVIR ONME

NTAL

737-800/CFM56-7B26 JAA/JAROPS Category C Brakes

TAKEOFF AND LANDING Takeoff Alternate Ratings

Flight Planning and Performance Manual

Takeoff Field Limit - Dry Runway (22K Derate)

Flaps 10

Based on engine bleed for packs on and anti-ice off

76 72 68 64

LIMIT

60 56 MINIMUM FIELD LENGTH 52 48 REF LINE 44 40

With engine bleed for packs off, increase weight by 450 kg. With engine anti-ice on, decrease weight by 150 kg. With engine and wing anti-ice on, decrease weight by 600 kg (optional system).

Copyright © The Boeing Company. See title page for details.

November 1, 2006

D632A008-ZZ022

RUNWAY SLOPE (%)

1.3.45

-60 -40 -20 0 20 40 60 80 100 120 140 -60 -50 -40 -30 -20 -10 0 10 20 30 40 50 60 70 HEAD 40 C AIRPORT OAT 20 0 REF LINE -10 TAIL WIND (KTS)

F

UP 2 REF LINE 0 -2 1000 FT 4 5 6 7 8 9 10 11 12 13 DOWN 100 M 12 14 16 18 20 22 24 26 28 30 32 34 36 38 40 42 FIELD LENGTH AVAILABLE

FIELD LENGTH LIMIT BRAKE RELEASE WEIGHT (1000 KG)

AI ALT RPOR ITU T DE -2 -1 0 1 2 3 4 5 6 7 8 9 10

88

PR E (10 SSUR 00 E FT)

84 80

ENVIR ONME

NTAL

TAKEOFF AND LANDING Takeoff Alternate Ratings

Flight Planning and Performance Manual

737-800/CFM56-7B26 JAA/JAROPS Category C Brakes

Takeoff Field Limit - Dry Runway (22K Derate)

Flaps 15

Based on engine bleed for packs on and anti-ice off

76 72 68 64

LIMIT

60 56 MINIMUM FIELD LENGTH 52 48 REF LINE 44 40

With engine bleed for packs off, increase weight by 450 kg. With engine anti-ice on, decrease weight by 150 kg. With engine and wing anti-ice on, decrease weight by 600 kg (optional system).

Copyright © The Boeing Company. See title page for details.

1.3.46

D632A008-ZZ022

November 1, 2006

RUNWAY SLOPE (%)

-60 -40 -20 0 20 40 60 80 100 120 140 -60 -50 -40 -30 -20 -10 0 10 20 30 40 50 60 70 HEAD 40 C AIRPORT OAT 20 0 REF LINE -10 TAIL WIND (KTS)

F

UP 2 REF LINE 0 -2 1000 FT 4 5 6 7 8 9 10 11 12 13 DOWN 100 M 12 14 16 18 20 22 24 26 28 30 32 34 36 38 40 42 FIELD LENGTH AVAILABLE

FIELD LENGTH LIMIT BRAKE RELEASE WEIGHT (1000 KG)

AI ALT RPOR ITU T DE -2 -1 0 1 2 3 4 5 6 7 8 9 10

88

PR E (10 SSUR 00 E FT)

84 80

ENVIR ONME

NTAL

737-800/CFM56-7B26 JAA/JAROPS Category C Brakes

TAKEOFF AND LANDING Takeoff Alternate Ratings

Flight Planning and Performance Manual

Takeoff Field Limit - Dry Runway (22K Derate)

Flaps 25

Based on engine bleed for packs on and anti-ice off

76 72 68 64

LIMIT NTAL

60 56 MINIMUM FIELD LENGTH 52 48 REF LINE 44 40

With engine bleed for packs off, increase weight by 450 kg. With engine anti-ice on, decrease weight by 200 kg. With engine and wing anti-ice on, decrease weight by 600 kg (optional system).

Copyright © The Boeing Company. See title page for details.

November 1, 2006

D632A008-ZZ022

RUNWAY SLOPE (%)

1.3.47

-60 -40 -20 0 20 40 60 80 100 120 140 -60 -50 -40 -30 -20 -10 0 10 20 30 40 50 60 70 HEAD 40 C AIRPORT OAT 20 0 REF LINE -10 TAIL WIND (KTS)

F

UP 2 REF LINE 0 -2 1000 FT 4 5 6 7 8 9 10 11 12 13 DOWN 100 M 12 14 16 18 20 22 24 26 28 30 32 34 36 38 40 42 FIELD LENGTH AVAILABLE

FIELD LENGTH LIMIT BRAKE RELEASE WEIGHT (1000 KG)

AI ALT RPOR ITU T DE -2 -1 0 1 2 3 4 5 6 7 8 9 10

88

PR E (10 SSUR 00 E FT)

84 80

ENVIR ONME

TAKEOFF AND LANDING Takeoff Alternate Ratings

Flight Planning and Performance Manual

737-800/CFM56-7B26 JAA/JAROPS Category C Brakes

Takeoff Field Limit - Wet Runway (22K Derate)

Flaps 1

Based on engine bleed for packs on and anti-ice off

AIR

88

PO

76 72 68 64 60 56 MINIMUM FIELD LENGTH 52 48 REF LINE 44 40

With engine bleed for packs off, increase weight by 400 kg. With engine anti-ice on, decrease weight by 150 kg. With engine and wing anti-ice on, decrease weight by 600 kg (optional system).

Copyright © The Boeing Company. See title page for details.

1.3.48

D632A008-ZZ022

November 1, 2006

RUNWAY SLOPE (%)

-60 -40 -20 0 20 40 60 80 100 120 140 -60 -50 -40 -30 -20 -10 0 10 20 30 40 50 60 70 HEAD 40 C AIRPORT OAT 20 0 REF LINE -10 TAIL WIND (KTS)

F

ENVIR ONME

UP 2 REF LINE 0 -2 1000 FT 4 5 6 7 8 9 10 11 12 13 DOWN 100 M 12 14 16 18 20 22 24 26 28 30 32 34 36 38 40 42 FIELD LENGTH AVAILABLE

FIELD LENGTH LIMIT BRAKE RELEASE WEIGHT (1000 KG)

NTAL

LIMIT

RT PR E (10 SSU 00 RE F A -2 T) LTITU DE -1 0 1 2 3 4 5 6 7 8 9 10

84 80

737-800/CFM56-7B26 JAA/JAROPS Category C Brakes

TAKEOFF AND LANDING Takeoff Alternate Ratings

Flight Planning and Performance Manual

Takeoff Field Limit - Wet Runway (22K Derate)

Flaps 5

Based on engine bleed for packs on and anti-ice off

76 72 68 64

LIMIT

60 56 MINIMUM FIELD LENGTH 52 48 REF LINE 44 40

With engine bleed for packs off, increase weight by 400 kg. With engine anti-ice on, decrease weight by 150 kg. With engine and wing anti-ice on, decrease weight by 600 kg (optional system).

Copyright © The Boeing Company. See title page for details.

November 1, 2006

D632A008-ZZ022

RUNWAY SLOPE (%)

1.3.49

-60 -40 -20 0 20 40 60 80 100 120 140 -60 -50 -40 -30 -20 -10 0 10 20 30 40 50 60 70 HEAD 40 C AIRPORT OAT 20 0 REF LINE -10 TAIL WIND (KTS)

F

UP 2 REF LINE 0 -2 1000 FT 4 5 6 7 8 9 10 11 12 13 DOWN 100 M 12 14 16 18 20 22 24 26 28 30 32 34 36 38 40 42 FIELD LENGTH AVAILABLE

FIELD LENGTH LIMIT BRAKE RELEASE WEIGHT (1000 KG)

AI ALT RPO ITU RT DE -2 -1 0 1 2 3 4 5 6 7 8 9 10

88

PR E (10 SSU 00 RE FT )

84 80

ENVIR ONME

NTAL

TAKEOFF AND LANDING Takeoff Alternate Ratings

Flight Planning and Performance Manual

737-800/CFM56-7B26 JAA/JAROPS Category C Brakes

Takeoff Field Limit - Wet Runway (22K Derate)

Flaps 10

Based on engine bleed for packs on and anti-ice off

76 72 68 64

LIMIT

60 56 MINIMUM FIELD LENGTH 52 48 REF LINE 44 40

With engine bleed for packs off, increase weight by 400 kg. With engine anti-ice on, decrease weight by 150 kg. With engine and wing anti-ice on, decrease weight by 600 kg (optional system).

Copyright © The Boeing Company. See title page for details.

1.3.50

D632A008-ZZ022

November 1, 2006

RUNWAY SLOPE (%)

-60 -40 -20 0 20 40 60 80 100 120 140 -60 -50 -40 -30 -20 -10 0 10 20 30 40 50 60 70 HEAD 40 C AIRPORT OAT 20 0 REF LINE -10 TAIL WIND (KTS)

F

UP 2 REF LINE 0 -2 1000 FT 4 5 6 7 8 9 10 11 12 13 DOWN 100 M 12 14 16 18 20 22 24 26 28 30 32 34 36 38 40 42 FIELD LENGTH AVAILABLE

FIELD LENGTH LIMIT BRAKE RELEASE WEIGHT (1000 KG)

AI ALT RPOR ITU T DE -2 -1 0 1 2 3 4 5 6 7 8 9 10

88

PR E (10 SSUR 00 E FT)

84 80

ENVIR ONME

NTAL

737-800/CFM56-7B26 JAA/JAROPS Category C Brakes

TAKEOFF AND LANDING Takeoff Alternate Ratings

Flight Planning and Performance Manual

Takeoff Field Limit - Wet Runway (22K Derate)

Flaps 15

Based on engine bleed for packs on and anti-ice off

76 72 68 64

LIMIT

7 8 9 10

60 56 MINIMUM FIELD LENGTH 52 48 REF LINE 44 40

With engine bleed for packs off, increase weight by 400 kg. With engine anti-ice on, decrease weight by 150 kg. With engine and wing anti-ice on, decrease weight by 600 kg (optional system).

Copyright © The Boeing Company. See title page for details.

November 1, 2006

D632A008-ZZ022

RUNWAY SLOPE (%)

1.3.51

-60 -40 -20 0 20 40 60 80 100 120 140 -60 -50 -40 -30 -20 -10 0 10 20 30 40 50 60 70 HEAD 40 C AIRPORT OAT 20 0 REF LINE -10 TAIL WIND (KTS)

F

UP 2 REF LINE 0 -2 1000 FT 4 5 6 7 8 9 10 11 12 13 DOWN 100 M 12 14 16 18 20 22 24 26 28 30 32 34 36 38 40 42 FIELD LENGTH AVAILABLE

FIELD LENGTH LIMIT BRAKE RELEASE WEIGHT (1000 KG)

AI ALT RPOR ITU T DE -2 -1 0 1 2 3 4 5 6

88

PR E (10 SSUR 00 E FT)

84 80

ENVIR ONME

NTAL

TAKEOFF AND LANDING Takeoff Alternate Ratings

Flight Planning and Performance Manual

737-800/CFM56-7B26 JAA/JAROPS Category C Brakes

Takeoff Field Limit - Wet Runway (22K Derate)

Flaps 25

Based on engine bleed for packs on and anti-ice off

76 72 68 64

LIMIT

7 8 9 10

5 6

60 56 MINIMUM FIELD LENGTH 52 48 REF LINE 44 40

With engine bleed for packs off, increase weight by 400 kg. With engine anti-ice on, decrease weight by 150 kg. With engine and wing anti-ice on, decrease weight by 600 kg (optional system).

Copyright © The Boeing Company. See title page for details.

1.3.52

D632A008-ZZ022

November 1, 2006

RUNWAY SLOPE (%)

-60 -40 -20 0 20 40 60 80 100 120 140 -60 -50 -40 -30 -20 -10 0 10 20 30 40 50 60 70 HEAD 40 C AIRPORT OAT 20 0 REF LINE -10 TAIL WIND (KTS)

F

UP 2 REF LINE 0 -2 1000 FT 4 5 6 7 8 9 10 11 12 13 DOWN 100 M 12 14 16 18 20 22 24 26 28 30 32 34 36 38 40 42 FIELD LENGTH AVAILABLE

FIELD LENGTH LIMIT BRAKE RELEASE WEIGHT (1000 KG)

AI ALT RPOR ITU T DE -2 -1 0 1 2 3 4

88

PR E (10 SSUR 00 E FT)

84 80

ENVIR ONME

NTAL

737-800/CFM56-7B26 JAA/JAROPS Category C Brakes

TAKEOFF AND LANDING Takeoff Alternate Ratings

Flight Planning and Performance Manual

Takeoff Climb Limit (22K Derate)

Flaps 1

Based on engine bleed for packs on and anti-ice off

76 -2 -1 0 72 1 2 3 4 68 (1000 KG) 5 6 64 7 8 9 60 10 AIRPORT PRESSURE ALTITUDE (1000 FT) 56

L L IMIT

CLIMB LIMIT BRAKE RELEASE WEIGHT

52

48

44

40 -60

-60 -50

-40 -40

-20 0 -30 -20

20 40 60 80 100 -10 0 10 20 30 40 AIRPORT OAT

ENV

IRO

NME

NTA

120 50

140 60

70

F C

With engine bleed for packs off, increase weight by 1450 kg. With engine anti-ice on, decrease weight by 200 kg. With engine and wing anti-ice on (optional system), decrease weight by 1100 kg.

Copyright © The Boeing Company. See title page for details.

November 1, 2006

D632A008-ZZ022

1.3.53

TAKEOFF AND LANDING Takeoff Alternate Ratings

Flight Planning and Performance Manual

737-800/CFM56-7B26 JAA/JAROPS Category C Brakes

Takeoff Climb Limit (22K Derate)

Flaps 5

Based on engine bleed for packs on and anti-ice off

72

-2 -1 0 1

68

2 3 4 5

(1000 KG)

64 6 7 60 8 9 10 56 AIRPORT PRESSURE ALTITUDE (1000 FT)

L L IMIT

CLIMB LIMIT BRAKE RELEASE WEIGHT

52

44

40 -60

-60 -50

-40 -40

-20 0 -30 -20

20 40 60 80 100 -10 0 10 20 30 40 AIRPORT OAT

ENV

IRO

48

NME

120 50

NTA

140 60

70

F C

With engine bleed for packs off, increase weight by 1400 kg. With engine anti-ice on, decrease weight by 200 kg. With engine and wing anti-ice on (optional system), decrease weight by 1050 kg.

Copyright © The Boeing Company. See title page for details.

1.3.54

D632A008-ZZ022

November 1, 2006

737-800/CFM56-7B26 JAA/JAROPS Category C Brakes

TAKEOFF AND LANDING Takeoff Alternate Ratings

Flight Planning and Performance Manual

Takeoff Climb Limit (22K Derate)

Flaps 10

Based on engine bleed for packs on and anti-ice off

68 -2 -1 0 1 64 (1000 KG) 2 3 4 5 60 6 7 8 56 9 10 52 AIRPORT PRESSURE ALTITUDE (1000 FT)

LIM IT

CLIMB LIMIT BRAKE RELEASE WEIGHT

40 -60

-60 -50

-40 -40

-20 0 -30 -20

20 40 60 80 100 -10 0 10 20 30 40 AIRPORT OAT

EN

44

VIR

ON

ME

120 50

NT

48

AL

140 60

70

F C

With engine bleed for packs off, increase weight by 1300 kg. With engine anti-ice on, decrease weight by 200 kg. With engine and wing anti-ice on (optional system), decrease weight by 1000 kg.

Copyright © The Boeing Company. See title page for details.

November 1, 2006

D632A008-ZZ022

1.3.55

TAKEOFF AND LANDING Takeoff Alternate Ratings

Flight Planning and Performance Manual

737-800/CFM56-7B26 JAA/JAROPS Category C Brakes

Takeoff Climb Limit (22K Derate)

Flaps 15

Based on engine bleed for packs on and anti-ice off

68 -2 -1 0 64 (1000 KG) 1 2 3 4 60 5 6 7 56 8 9 10 52 AIRPORT PRESSURE ALTITUDE (1000 FT)

L L IM IT

CLIMB LIMIT BRAKE RELEASE WEIGHT

48

40 -60

-60 -50

-40 -40

-20 0 -30 -20

20 40 60 80 100 -10 0 10 20 30 40 AIRPORT OAT

ENV

IRO

44

NME

120 50

NTA

140 60

70

F C

With engine bleed for packs off, increase weight by 1250 kg. With engine anti-ice on, decrease weight by 200 kg. With engine and wing anti-ice on (optional system), decrease weight by 950 kg.

Copyright © The Boeing Company. See title page for details.

1.3.56

D632A008-ZZ022

November 1, 2006

737-800/CFM56-7B26 JAA/JAROPS Category C Brakes

TAKEOFF AND LANDING Takeoff Alternate Ratings

Flight Planning and Performance Manual

Takeoff Climb Limit (22K Derate)

Flaps 25

Based on engine bleed for packs on and anti-ice off

68

64 (1000 KG)

-2 -1 0 1 2 3 4 5 6

60

CLIMB LIMIT BRAKE RELEASE WEIGHT

56

7 8 9

52

10

IT EN VIR ON

AIRPORT PRESSURE ALTITUDE (1000 FT) 48

NT AL

44

40 -60

-60 -50

-40 -40

-20 0 -30 -20

20 40 60 80 100 -10 0 10 20 30 40 AIRPORT OAT

120 50

ME

LIM

140 60

70

F C

With engine bleed for packs off, increase weight by 1200 kg. With engine anti-ice on, decrease weight by 200 kg. With engine and wing anti-ice on (optional system), decrease weight by 950 kg.

Copyright © The Boeing Company. See title page for details.

November 1, 2006

D632A008-ZZ022

1.3.57

TAKEOFF AND LANDING Takeoff Alternate Ratings

Flight Planning and Performance Manual

737-800/CFM56-7B26 JAA/JAROPS Category C Brakes

Obstacle Limit (22K Derate)

Flaps 1

Based on engine bleed for packs on and anti-ice off

OBSTACLE LIMIT WEIGHT 42 HEAD 40 WIND (KTS) 20 0 REF LINE 46 50 54 58 62 (1000 KG) 66 70 74 78

TAIL 20 PRESS ALT (1000 FT) 10 5 0 ( C) ( F) 50 120 40 OAT 30 20 10 0 (M) 300 40 (FT)

45

REF LINE

100 REF LINE 80 60

40

50

55

60

65

70

75 80 85 90

DIS

OBSTACLE HEIGHT

800 35 200 600 400 200 0 0

TA N

CE

FR

30

25

OM (10 BRA 0 M) KE R EL E

AS

E

100

When using line-up allowances, the obstacle distance from brake release must be reduced by the ASDA adjustment. Obstacle height must be calculated from the lowest point of the runway to conservatively account for runway slope. With engine bleed for packs off, increase weight by 700 kg. With engine anti-ice on, decrease weight by 250 kg. With engine and wing anti-ice on, decrease weight by 1150 kg (optional system).

Copyright © The Boeing Company. See title page for details.

1.3.58

D632A008-ZZ022

November 1, 2006

737-800/CFM56-7B26 JAA/JAROPS Category C Brakes

TAKEOFF AND LANDING Takeoff Alternate Ratings

Flight Planning and Performance Manual

Obstacle Limit (22K Derate)

Flaps 5

Based on engine bleed for packs on and anti-ice off

OBSTACLE LIMIT WEIGHT 40 HEAD 40 WIND (KTS) 20 0 REF LINE 44 48 52 56 60 (1000 KG) 64 68 72 76

TAIL 20 PRESS ALT (1000 FT) 10 5 0 ( C) ( F) 50 120 40 OAT 30 20 10 0 (M) 300 40 (FT) 100 REF LINE 80 60 REF LINE

40

35

45

50

55

60

65

70 75 80 85 90

DI ST AN CE

OBSTACLE HEIGHT

800 200 600 400 200 0 0

30

FR

25

100

OM (10 BR A 0 M) KE RE

LE

AS

E

When using line-up allowances, the obstacle distance from brake release must be reduced by the ASDA adjustment. Obstacle height must be calculated from the lowest point of the runway to conservatively account for runway slope. With engine bleed for packs off, increase weight by 700 kg. With engine anti-ice on, decrease weight by 250 kg. With engine and wing anti-ice on, decrease weight by 1150 kg (optional system).

Copyright © The Boeing Company. See title page for details.

November 1, 2006

D632A008-ZZ022

1.3.59

TAKEOFF AND LANDING Takeoff Alternate Ratings

Flight Planning and Performance Manual

737-800/CFM56-7B26 JAA/JAROPS Category C Brakes

Obstacle Limit (22K Derate)

Flaps 10

Based on engine bleed for packs on and anti-ice off

OBSTACLE LIMIT WEIGHT 40 HEAD 40 WIND (KTS) 20 0 REF LINE 44 48 52 56 (1000 KG) 60 64 68 72

TAIL 20 PRESS ALT (1000 FT) 10 5 0 ( C) ( F) 50 120 40 OAT 30 20 10 0 (M) 300 40 (FT)

45

50

REF LINE

100 REF LINE 80 60

55

60

65 70 75 80 85 90

40

DI

OBSTACLE HEIGHT

800 200 600 400 200 0 0

35

ST AN

CE

FR

30

25

OM (10 BR 0 A M) KE RE LE

100

AS

E

When using line-up allowances, the obstacle distance from brake release must be reduced by the ASDA adjustment. Obstacle height must be calculated from the lowest point of the runway to conservatively account for runway slope. With engine bleed for packs off, increase weight by 700 kg. With engine anti-ice on, decrease weight by 250 kg. With engine and wing anti-ice on, decrease weight by 1150 kg (optional system).

Copyright © The Boeing Company. See title page for details.

1.3.60

D632A008-ZZ022

November 1, 2006

737-800/CFM56-7B26 JAA/JAROPS Category C Brakes

TAKEOFF AND LANDING Takeoff Alternate Ratings

Flight Planning and Performance Manual

Obstacle Limit (22K Derate)

Flaps 15

Based on engine bleed for packs on and anti-ice off

OBSTACLE LIMIT WEIGHT 40 HEAD 40 WIND (KTS) 20 0 REF LINE 44 48 52 56 (1000 KG) 60 64 68 72

TAIL 20 PRESS ALT (1000 FT) 10 5 0 ( C) ( F) 50 120 40 OAT 30 20 10 0 (M) 300 40 (FT)

45 40

REF LINE

100 REF LINE 80 60

50

55

60 65 70 75 80 85 90

DI

ST AN

OBSTACLE HEIGHT

800 200 600 400 200 0 0

35

30

25

CE

FR

OM (1 00 BRA M) KE RE L

EA

SE

100

When using line-up allowances, the obstacle distance from brake release must be reduced by the ASDA adjustment. Obstacle height must be calculated from the lowest point of the runway to conservatively account for runway slope. With engine bleed for packs off, increase weight by 700 kg. With engine anti-ice on, decrease weight by 250 kg. With engine and wing anti-ice on, decrease weight by 1150 kg (optional system).

Copyright © The Boeing Company. See title page for details.

November 1, 2006

D632A008-ZZ022

1.3.61

TAKEOFF AND LANDING Takeoff Alternate Ratings

Flight Planning and Performance Manual

737-800/CFM56-7B26 JAA/JAROPS Category C Brakes

Obstacle Limit (22K Derate)

Flaps 25

Based on engine bleed for packs on and anti-ice off

OBSTACLE LIMIT WEIGHT 40 HEAD 40 WIND (KTS) 20 0 REF LINE 44 48 52 56 (1000 KG) 60 64 68

TAIL 20 PRESS ALT (1000 FT) 10 5 0 ( C) ( F) 50 120 40 OAT 30 20 10 0 (M) 300 40 (FT)

45

40

50

55

REF LINE

100 REF LINE 80 60

60 65 70 75 80 85 90

DI

ST AN

OBSTACLE HEIGHT

800 200 600 400 200 0 0

CE

35

30

25

FR (1

OM 00 BRA M) KE

RE L

EA

SE

100

When using line-up allowances, the obstacle distance from brake release must be reduced by the ASDA adjustment. Obstacle height must be calculated from the lowest point of the runway to conservatively account for runway slope. With engine bleed for packs off, increase weight by 700 kg. With engine anti-ice on, decrease weight by 250 kg. With engine and wing anti-ice on, decrease weight by 1150 kg (optional system).

Copyright © The Boeing Company. See title page for details.

1.3.62

D632A008-ZZ022

November 1, 2006

737-800/CFM56-7B26 JAA/JAROPS Category C Brakes

TAKEOFF AND LANDING Takeoff Alternate Ratings

Flight Planning and Performance Manual

Tire Speed Limit (22K Derate)

Flaps 1

88

0

84

1

2

3

(1000 KG)

4

80

5

R AI R PO

6

7

FLAPS 1 LIMIT WEIGHT

76

T

8

E PR SS UR E

10

9

72

AL TI TU DE (1

68

00 0 FT )

64

60 -60

-60 -50

-40 -40

-20 0 -30 -20

20 40 60 80 100 -10 0 10 20 30 40 AIRPORT OAT

120 50

140 60

70

F C

With flaps 5, increase flaps 1 weight by 4800 kg. Increase tire speed limit weight by 550 kg per knot headwind. Decrease tire speed limit weight by 1100 kg per knot tailwind.

Copyright © The Boeing Company. See title page for details.

November 1, 2006

D632A008-ZZ022

1.3.63

TAKEOFF AND LANDING Takeoff Alternate Ratings

Flight Planning and Performance Manual

737-800/CFM56-7B26 JAA/JAROPS Category C Brakes

Brake Energy Limits VMBE (22K Derate)

AIRPORT PRESSURE ALTITUDE (1000 FT) 10 8 6 4 2 0 -2 50 60 70 80 90 BRAKE RELEASE WEIGHT (1000 KG)

AI

RP

OR

T

OA

T

°C

(° F

)

-50

-40

50

(1

22

)

8) (-4 -30 0) 30 20 10 0 ( -10 -20 (-22 (8 (68 (50 32 (1 6) 4) (-4) ) ) ) ) 40 (1 04 )

(-5

210

200

44

48

190

52

56

180

68

72

76

80

84

88 W EI GH T

(1

00

0

KG

)

170

160

BR

E AK

RE

A LE

SE

150

140

Check VMBE when outside shaded area or when operating with tailwind or improved climb. Increase VMBE by 2 knots per 1% uphill runway slope. Decrease VMBE by 3 knots per 1% downhill runway slope. Increase VMBE by 4 knots per 10 knots headwind. Decrease VMBE by 18 knots per 10 knots tailwind. Normal takeoff: Decrease brake release weight by 500 kg for each knot V1 exceeds VMBE. Determine normal V1, VR, V2 speeds for lower brake release weight. Improved climb takeoff: Decrease climb weight improvement by 250 kg for each knot V1 exceeds VMBE. Determine V1, VR, V2 speed increments for the lower climb weight improvement.

Copyright © The Boeing Company. See title page for details.

1.3.64

D632A008-ZZ022

November 1, 2006

VMBE

(KIAS)

60

64

737-800/CFM56-7B26 JAA/JAROPS Category C Brakes

TAKEOFF AND LANDING Takeoff Alternate Ratings

Flight Planning and Performance Manual

Improved Climb Field Length Limit - Dry Runway (22K Derate)

Flaps 1

NORMAL TAKEOFF SPEED INCREMENT (KIAS) V1 VR V2 80 (1000 KG) 5

KG )

6

20 70 60 50 40 18 16 14 12 10 9 8 7 6 5 4 3 REF LINE 2 1

CLIMB WEIGHT IMPROVEMENT

(10

4

IG HT

26 24 22 20 18 16 14 12 10 9 8 7 6 5 4 3 2 1

24 22 20 18 16 14 12 10 9 8 7 6 5 4 3 2 1

3

LIM

0 0 4 8 12 16 (FIELD LIMIT WEIGHT) MINUS (CLIMB LIMIT WEIGHT) (1000 KG) 20 40

NO

1

RM

AL

CL

IM

2

B

IT

WE

00

50 60 70 80 NORMAL CLIMB LIMIT WEIGHT (1000 KG)

Copyright © The Boeing Company. See title page for details.

November 1, 2006

D632A008-ZZ022

1.3.65

TAKEOFF AND LANDING Takeoff Alternate Ratings

Flight Planning and Performance Manual

737-800/CFM56-7B26 JAA/JAROPS Category C Brakes

Improved Climb Field Length Limit - Dry Runway (22K Derate)

Flaps 5

NORMAL TAKEOFF SPEED INCREMENT (KIAS) V1 VR V2

5 (1000 KG)

KG )

80 70

(10

4

00

CLIMB WEIGHT IMPROVEMENT

3

LIM

WE IG

HT

60 50 40

CL

2

14 12 10 9 8 7 6 5 4 3 REF LINE 2 1

IT

20 18 16 14 12 10 9 8 7 6 5 4 3 2 1

18 16 14 12 10 9 8 7 6 5 4 3 2 1

0 0 4 8 12 16 (FIELD LIMIT WEIGHT) MINUS (CLIMB LIMIT WEIGHT) (1000 KG) 20 40

NO

1

RM

AL

IM

B

50 60 70 80 NORMAL CLIMB LIMIT WEIGHT (1000 KG)

Copyright © The Boeing Company. See title page for details.

1.3.66

D632A008-ZZ022

November 1, 2006

737-800/CFM56-7B26 JAA/JAROPS Category C Brakes

TAKEOFF AND LANDING Takeoff Alternate Ratings

Flight Planning and Performance Manual

Improved Climb Field Length Limit - Dry Runway (22K Derate)

Flaps 10

(1000 KG)

CLIMB WEIGHT IMPROVEMENT

2

70

NORMAL CLIMB LIMIT WEIGHT (1000 KG)

0 4 8 12 16 (FIELD LIMIT WEIGHT) MINUS (CLIMB LIMIT WEIGHT) (1000 KG) 20

0

40 50 60 70 NORMAL CLIMB LIMIT WEIGHT (1000 KG)

Flaps 15

(1000 KG)

REF LINE 60 50 40 REF LINE

1

60 50 40

NORMAL TAKEOFF SPEED INCREMENT (KIAS) V1 VR V2 8 10 12 10 8 6 8 6 4 6 4 4 2 2 2 1 1 1

CLIMB WEIGHT IMPROVEMENT

2

70

NORMAL TAKEOFF SPEED INCREMENT (KIAS) V1 VR V2 8 6 4 3 2 1 12 10 8 6 4 3 2 1 10 8 6 4 3 2 1

1 NORMAL CLIMB LIMIT WEIGHT (1000 KG) 0 0 4 8 12 16 (FIELD LIMIT WEIGHT) MINUS (CLIMB LIMIT WEIGHT) (1000 KG)

20

40 50 60 70 NORMAL CLIMB LIMIT WEIGHT (1000 KG)

Copyright © The Boeing Company. See title page for details.

November 1, 2006

D632A008-ZZ022

1.3.67

TAKEOFF AND LANDING Takeoff Alternate Ratings

Flight Planning and Performance Manual

737-800/CFM56-7B26 JAA/JAROPS Category C Brakes

Improved Climb Field Length Limit - Dry Runway (22K Derate)

Flaps 25

(1000 KG)

CLIMB WEIGHT IMPROVEMENT

2

NORMAL CLIMB LIMIT WEIGHT (1000 KG)

NORMAL TAKEOFF SPEED INCREMENT (KIAS) V1 VR V2 70 60 50 40 10 8 6 4 2 1 15 15 10 5 3 1 10 5 3 1

0 0 4 8 12 16 (FIELD LIMIT WEIGHT) MINUS (CLIMB LIMIT WEIGHT) (1000 KG) 20

40 50 60 70 NORMAL CLIMB LIMIT WEIGHT (1000 KG)

Copyright © The Boeing Company. See title page for details.

REF LINE

1

1.3.68

D632A008-ZZ022

November 1, 2006

737-800/CFM56-7B26 JAA/JAROPS Category C Brakes

TAKEOFF AND LANDING Takeoff Alternate Ratings

Flight Planning and Performance Manual

Improved Climb Tire Speed Limit - Dry Runway (22K Derate)

Flaps 1

NORMAL TAKEOFF SPEED INCREMENT (KIAS) V1 VR V2 80 (1000 KG) 5 70 18 24 22 20 18 16 14 12 10 9 8 7 6 5 4 3 2 1 22 20 18 16 14 12 10 9 8 7 6 5 4 3 2 1

6

)

CLIMB WEIGHT IMPROVEMENT

(1 00 0

4

KG

16 60 14 12 50 10 9 8 7 6 5 4 REF LINE 3 2 1

M

IT

W

3

EI G

HT

40

1

0 0 4 8 12 16 (TIRE LIMIT WEIGHT) MINUS (CLIMB LIMIT WEIGHT) (1000 KG) 20 24 40

NO

RM

AL

CL

2

IM

B

LI

50 60 70 80 NORMAL CLIMB LIMIT WEIGHT (1000 KG)

Copyright © The Boeing Company. See title page for details.

November 1, 2006

D632A008-ZZ022

1.3.69

TAKEOFF AND LANDING Takeoff Alternate Ratings

Flight Planning and Performance Manual

737-800/CFM56-7B26 JAA/JAROPS Category C Brakes

Improved Climb Tire Speed Limit - Dry Runway (22K Derate)

Flaps 5

NORMAL TAKEOFF SPEED INCREMENT (KIAS) V1 VR V2

6

(1000 KG)

5

80

70 4 18 16 14 12 10 9 8 7 6 5 4 3 REF LINE 2 1 24 22 20 18 16 14 12 10 9 8 7 6 5 4 3 2 1 22 20 18 16 14 12 10 9 8 7 6 5 4 3 2 1

(1 00 0 KG )

CLIMB WEIGHT IMPROVEMENT

60

W EI

3

LI M

G

HT

50

B

IT

1

0 0 4 8 12 16 (TIRE LIMIT WEIGHT) MINUS (CLIMB LIMIT WEIGHT) (1000 KG) 20 24 40

NO

RM

AL

CL

2

IM

40

50 60 70 80 NORMAL CLIMB LIMIT WEIGHT (1000 KG)

Copyright © The Boeing Company. See title page for details.

1.3.70

D632A008-ZZ022

November 1, 2006

737-800/CFM56-7B26 JAA/JAROPS Category C Brakes

TAKEOFF AND LANDING Takeoff Alternate Ratings

Flight Planning and Performance Manual

Improved Climb Field Length Limit - Wet Runway (22K Derate)

Flaps 1

NORMAL TAKEOFF SPEED INCREMENT (KIAS) V1 VR V2 80 (1000 KG) 5

6

EI G HT

CL (1 IMB 00 0 LIM KG IT ) W

70 60 50 40

20 18 16 14 12 10 9 8 7 6 5 4 REF LINE 3 2 1

CLIMB WEIGHT IMPROVEMENT

4

24 22 20 18 16 14 12 10 9 8 7 6 5 4 3 2 1

22 20 18 16 14 12 10 9 8 7 6 5 4 3 2 1

3

2

1

0 0 4 8 12 16 (FIELD LIMIT WEIGHT) MINUS (CLIMB LIMIT WEIGHT) (1000 KG) 20 40

NO RM

AL

50 60 70 80 NORMAL CLIMB LIMIT WEIGHT (1000 KG)

Copyright © The Boeing Company. See title page for details.

November 1, 2006

D632A008-ZZ022

1.3.71

TAKEOFF AND LANDING Takeoff Alternate Ratings

Flight Planning and Performance Manual

737-800/CFM56-7B26 JAA/JAROPS Category C Brakes

Improved Climb Field Length Limit - Wet Runway (22K Derate)

Flaps 5

NORMAL TAKEOFF SPEED INCREMENT (KIAS) V1 VR V2

5 (1000 KG)

EI G HT

80 70 60 50 40

4

CL I (1 MB 00 0 LIM KG IT ) W

CLIMB WEIGHT IMPROVEMENT

3

NO

2

14 12 10 9 8 7 6 5 4 3 REF LINE

RM AL

18 16 14 12 10 9 8 7 6 5 4 3 2 1

16 14 12 10 9 8 7 6 5 4 3 2 1

1

2 1

0 0 4 8 12 16 (FIELD LIMIT WEIGHT) MINUS (CLIMB LIMIT WEIGHT) (1000 KG) 20 40

50 60 70 80 NORMAL CLIMB LIMIT WEIGHT (1000 KG)

Flaps 10

CLIMB WEIGHT IMPROVEMENT (1000 KG) NORMAL TAKEOFF SPEED INCREMENT (KIAS) V1 VR V2 8 6 REF LINE 4 2 1 12 10 8 6 4 2 1 10 8 6 4 2 1

2

NORMAL CLIMB LIMIT WEIGHT (1000 KG) 70 60 50 40

1

0 0 4 8 12 16 (FIELD LIMIT WEIGHT) MINUS (CLIMB LIMIT WEIGHT) (1000 KG) 20

40 50 60 70 NORMAL CLIMB LIMIT WEIGHT (1000 KG)

Copyright © The Boeing Company. See title page for details.

1.3.72

D632A008-ZZ022

November 1, 2006

737-800/CFM56-7B26 JAA/JAROPS Category C Brakes

TAKEOFF AND LANDING Takeoff Alternate Ratings

Flight Planning and Performance Manual

Improved Climb Field Length Limit - Wet Runway (22K Derate)

Flaps 15

CLIMB WEIGHT IMPROVEMENT (1000 KG) NORMAL TAKEOFF SPEED INCREMENT (KIAS) V1 VR V2 8 6 REF LINE 4 3 2 1 12 10 8 6 4 2 1 10 8 6 4 2 1

2

NORMAL CLIMB LIMIT WEIGHT (1000 KG) 70 60 50 40

1

0 0 4 8 12 16 (FIELD LIMIT WEIGHT) MINUS (CLIMB LIMIT WEIGHT) (1000 KG) 20

40 50 60 70 NORMAL CLIMB LIMIT WEIGHT (1000 KG)

Flaps 25

CLIMB WEIGHT IMPROVEMENT (1000 KG) NORMAL TAKEOFF SPEED INCREMENT (KIAS) V1 VR V2 70 60 50 40 15 10 REF LINE 5 3 1 20 15 10 5 3 1 20 15 10 5 3 1

2

NORMAL CLIMB LIMIT WEIGHT (1000 KG)

1

0 0 4 8 12 16 (FIELD LIMIT WEIGHT) MINUS (CLIMB LIMIT WEIGHT) (1000 KG) 20

40 50 60 70 NORMAL CLIMB LIMIT WEIGHT (1000 KG)

Copyright © The Boeing Company. See title page for details.

November 1, 2006

D632A008-ZZ022

1.3.73

TAKEOFF AND LANDING Takeoff Alternate Ratings

Flight Planning and Performance Manual

737-800/CFM56-7B26 JAA/JAROPS Category C Brakes

Improved Climb Tire Speed Limit - Wet Runway (22K Derate)

Flaps 1

NORMAL TAKEOFF SPEED INCREMENT (KIAS) V1 VR V2 80 (1000 KG) 5

W E IG H T

6

70

CLIMB WEIGHT IMPROVEMENT

4

3

N

O

R

M

M LI G) K M LI 000 C 1 ( AL B

IT

60

20 18 16 14 12

26 24 22 20 18 16 14 12 10 9 8 7 6 5 4 3 2 1

24 22 20 18 16 14 12 10 9 8 7 6 5 4 3 2 1

50

40 2

10 9 8 7 6 5 4 3 REF LINE 2 1

1

0 0 4 8 12 16 (TIRE LIMIT WEIGHT) MINUS (CLIMB LIMIT WEIGHT) (1000 KG) 20 24 40

50 60 70 80 NORMAL CLIMB LIMIT WEIGHT (1000 KG)

Copyright © The Boeing Company. See title page for details.

1.3.74

D632A008-ZZ022

November 1, 2006

737-800/CFM56-7B26 JAA/JAROPS Category C Brakes

TAKEOFF AND LANDING Takeoff Alternate Ratings

Flight Planning and Performance Manual

Improved Climb Tire Speed Limit - Wet Runway (22K Derate)

Flaps 5

NORMAL TAKEOFF SPEED INCREMENT (KIAS) V1 VR V2

6

(1000 KG)

5

EI G H T

80 22 20 18 16 14 12 10 9 8 7 6 5 4 3 REF LINE 26 24 22 20 18 16 14 12 10 9 8 7 6 5 4 3 2 1

CLIMB WEIGHT IMPROVEMENT

4

C L (1 IMB 00 0 LIM KG IT ) W

70

60

O R

M

3

N

50

28 26 24 22 20 18 16 14 12 10 9 8 7 6 5 4 3 2 1

AL

2

40

1

2 1

0 0 4 8 12 16 (TIRE LIMIT WEIGHT) MINUS (CLIMB LIMIT WEIGHT) (1000 KG) 20 24 40

50 60 70 80 NORMAL CLIMB LIMIT WEIGHT (1000 KG)

Copyright © The Boeing Company. See title page for details.

November 1, 2006

D632A008-ZZ022

1.3.75

TAKEOFF AND LANDING Takeoff Alternate Ratings

Flight Planning and Performance Manual

737-800/CFM56-7B26 JAA/JAROPS Category C Brakes

ADVISORY INFORMATION

Slush/Standing Water Takeoff (22K Derate)

Maximum Reverse Thrust Weight Adjustments (1000 KG)

22K DERATE DRY FIELD/OBSTACLE LIMIT WEIGHT (1000 KG) 95 90 85 80 75 70 65 60 55 50 45 40 3 mm (0.12 INCHES) PRESSURE ALTITUDE (FT) S.L. 5000 10000 -12.9 -15.4 -17.9 -11.9 -14.4 -16.9 -10.9 -13.4 -15.9 -10.0 -12.5 -15.0 -9.0 -11.5 -14.0 -8.0 -10.5 -13.0 -7.1 -9.6 -12.1 -6.3 -8.8 -11.3 -5.5 -8.0 -10.5 -4.6 -7.1 -9.6 -3.8 -6.3 -8.8 -3.0 -5.5 -8.0 SLUSH/STANDING WATER DEPTH 6 mm (0.25 INCHES) PRESSURE ALTITUDE (FT) S.L. 5000 10000 -16.6 -19.1 -21.6 -15.2 -17.7 -20.2 -13.8 -16.3 -18.7 -12.3 -14.8 -17.3 -10.9 -13.4 -15.9 -9.5 -12.0 -14.5 -8.3 -10.8 -13.3 -7.2 -9.7 -12.2 -6.2 -8.7 -11.2 -5.1 -7.6 -10.1 -4.1 -6.6 -9.1 -3.0 -5.5 -8.0 SLUSH/STANDING WATER DEPTH 6 mm (0.25 INCHES) PRESSURE ALTITUDE (FT) S.L. 5000 10000 39.2 60.6 44.2 84.0 66.0 49.2 89.9 71.4 95.8 13 mm (0.50 INCHES) PRESSURE ALTITUDE (FT) S.L. 5000 10000 -31.8 -34.3 -36.8 -27.5 -30.0 -32.5 -23.3 -25.8 -28.3 -19.4 -21.9 -24.4 -16.0 -18.5 -21.0 -13.1 -15.6 -18.1 -10.7 -13.2 -15.7 -8.8 -11.3 -13.8 -7.4 -9.9 -12.4 -6.5 -9.0 -11.5 -6.1 -8.6 -11.1 -6.2 -8.7 -11.2

V1(MCG) Limit Weight (1000 KG)

ADJUSTED FIELD LENGTH (M) 1200 1400 1600 1800 2000 3 mm (0.12 INCHES) PRESSURE ALTITUDE (FT) S.L. 5000 10000 36.2 57.9 41.2 81.4 63.3 46.3 87.3 68.8 93.3 13 mm (0.50 INCHES) PRESSURE ALTITUDE (FT) S.L. 5000 10000 44.3 65.4 49.1 34.1 89.5 70.8 54.0 95.6 76.4 101.7

1. Enter Weight Adjustment table with slush/standing water depth and 22K Derate dry field/obstacle limit weight to obtain slush/ standing water weight adjustment. 2. Adjust field length available by -30 m/+30 m for every 5°C above/below 4°C. 3. Find V1(MCG) limit weight for adjusted field length and pressure altitude. 4. Max allowable slush/standing water limited weight is lesser of weights from 1 and 3.

V1 Adjustment (KIAS)

WEIGHT (1000 KG) 90 85 80 75 70 65 60 55 50 45 40 3 mm (0.12 INCHES) PRESSURE ALTITUDE (FT) S.L. 5000 10000 -12 -10 -7 -13 -10 -8 -14 -11 -9 -15 -12 -10 -16 -13 -11 -17 -15 -12 -19 -16 -14 -20 -18 -15 -21 -18 -16 -21 -19 -16 -21 -18 -16 SLUSH/STANDING WATER DEPTH 6 mm (0.25 INCHES) PRESSURE ALTITUDE (FT) S.L. 5000 10000 -7 -4 -2 -7 -4 -2 -7 -5 -2 -8 -6 -3 -10 -7 -5 -12 -9 -7 -14 -12 -9 -17 -14 -12 -18 -16 -13 -19 -17 -14 -19 -17 -14 13 mm (0.50 INCHES) PRESSURE ALTITUDE (FT) S.L. 5000 10000 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 -1 0 0 -5 -2 0 -9 -6 -4 -12 -10 -7 -14 -12 -9 -16 -14 -11

1. Obtain V1, VR and V2 for the actual weight using the 22K Derate Dry Runway Takeoff Speeds table. 2. If V1(MCG) limited, set V1 = V1(MCG). If not V1(MCG) limited, enter V1 Adjustment table with the actual weight to obtain V1 speed adjustment. If adjusted V1 is less than V1(MCG), set V1 = V1(MCG).V1 not to exceed VR.

Copyright © The Boeing Company. See title page for details.

1.3.76

D632A008-ZZ022

November 1, 2006

737-800/CFM56-7B26 JAA/JAROPS Category C Brakes

TAKEOFF AND LANDING Takeoff Alternate Ratings

Flight Planning and Performance Manual

ADVISORY INFORMATION

Slush/Standing Water Takeoff (22K Derate)

No Reverse Thrust Weight Adjustments (1000 KG)

22K DERATE DRY FIELD/OBSTACLE LIMIT WEIGHT (1000 KG) 95 90 85 80 75 70 65 60 55 50 45 40 3 mm (0.12 INCHES) PRESSURE ALTITUDE (FT) S.L. 5000 10000 -16.1 -19.5 -22.9 -14.8 -18.2 -21.6 -13.4 -16.8 -20.2 -12.2 -15.6 -19.0 -10.9 -14.3 -17.7 -9.8 -13.2 -16.6 -8.7 -12.1 -15.5 -7.7 -11.1 -14.5 -6.8 -10.2 -13.6 -5.9 -9.3 -12.7 -5.0 -8.4 -11.8 -4.1 -7.5 -10.9 SLUSH/STANDING WATER DEPTH 6 mm (0.25 INCHES) PRESSURE ALTITUDE (FT) S.L. 5000 10000 -20.3 -23.7 -27.1 -18.4 -21.8 -25.2 -16.4 -19.8 -23.2 -14.6 -18.0 -21.4 -12.9 -16.3 -19.7 -11.3 -14.7 -18.1 -9.9 -13.3 -16.7 -8.6 -12.0 -15.4 -7.4 -10.8 -14.2 -6.4 -9.8 -13.2 -5.3 -8.7 -12.1 -4.3 -7.7 -11.1 SLUSH/STANDING WATER DEPTH 6 mm (0.25 INCHES) PRESSURE ALTITUDE (FT) S.L. 5000 10000 30.9 57.8 35.1 87.3 62.4 39.4 92.3 67.0 97.3 13 mm (0.50 INCHES) PRESSURE ALTITUDE (FT) S.L. 5000 10000 -33.9 -37.3 -40.7 -29.6 -33.0 -36.4 -25.2 -28.6 -32.0 -21.2 -24.6 -28.0 -17.7 -21.1 -24.5 -14.7 -18.1 -21.5 -12.2 -15.6 -19.0 -10.3 -13.7 -17.1 -8.8 -12.2 -15.6 -7.7 -11.1 -14.5 -6.7 -10.1 -13.5 -5.7 -9.1 -12.5

V1(MCG) Limit Weight (1000 KG)

ADJUSTED FIELD LENGTH (M) 1400 1600 1800 2000 2200 3 mm (0.12 INCHES) PRESSURE ALTITUDE (FT) S.L. 5000 10000 51.3 80.5 13 mm (0.50 INCHES) PRESSURE ALTITUDE (FT) S.L. 5000 10000 44.3 70.0 48.0 103.8 74.9 51.9 80.1

56.1 85.2

31.5 60.8 89.9

1. Enter Weight Adjustment table with slush/standing water depth and 22K Derate dry field/obstacle limit weight to obtain slush/ standing water weight adjustment. 2. Adjust field length available by -35 m/+30 m for every 5°C above/below 4°C. 3. Find V1(MCG) limit weight for available field length and pressure altitude. 4. Max allowable slush/standing water limited weight is lesser of weights from 1 and 3.

V1 Adjustment (KIAS)

WEIGHT (1000 KG) 95 90 85 80 75 70 65 60 55 50 45 40 3 mm (0.12 INCHES) PRESSURE ALTITUDE (FT) S.L. 5000 10000 -9 -7 -4 -12 -10 -7 -15 -12 -10 -17 -15 -12 -19 -17 -14 -21 -19 -16 -23 -21 -18 -25 -22 -20 -26 -23 -21 -27 -24 -22 -28 -25 -23 -28 -26 -23 SLUSH/STANDING WATER DEPTH 6 mm (0.25 INCHES) PRESSURE ALTITUDE (FT) S.L. 5000 10000 0 0 0 0 0 0 -3 -1 0 -7 -5 -2 -11 -8 -6 -14 -11 -9 -17 -14 -12 -19 -17 -14 -22 -19 -17 -24 -21 -19 -25 -23 -20 -27 -24 -22 13 mm (0.50 INCHES) PRESSURE ALTITUDE (FT) S.L. 5000 10000 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 -6 -4 -1 -12 -10 -7 -16 -14 -11 -20 -17 -15 -22 -19 -17

1. Obtain V1, VR and V2 for the actual weight using the 22K Derate Dry Runway Takeoff Speeds table. 2. If V1(MCG) limited, set V1 = V1(MCG). If not V1(MCG) limited, enter V1 Adjustment table with the actual weight to obtain V1 speed adjustment. If adjusted V1 is less than V1(MCG), set V1 = V1(MCG).V1 not to exceed VR.

Copyright © The Boeing Company. See title page for details.

November 1, 2006

D632A008-ZZ022

1.3.77

TAKEOFF AND LANDING Takeoff Alternate Ratings

Flight Planning and Performance Manual

737-800/CFM56-7B26 JAA/JAROPS Category C Brakes

ADVISORY INFORMATION

Slippery Runway Takeoff (22K Derate)

Maximum Reverse Thrust Weight Adjustments (1000 KG)

22K DERATE DRY FIELD/OBSTACLE LIMIT WEIGHT (1000 KG) 95 90 85 80 75 70 65 60 55 50 45 40 GOOD PRESSURE ALTITUDE (FT) S.L. 5000 10000 0.0 0.0 0.0 0.0 0.0 0.0 -0.3 -0.3 -0.3 -0.7 -0.7 -0.7 -1.1 -1.1 -1.1 -1.3 -1.3 -1.3 -1.4 -1.4 -1.4 -1.4 -1.4 -1.4 -1.4 -1.4 -1.4 -1.2 -1.2 -1.2 -0.9 -0.9 -0.9 -0.5 -0.5 -0.5 REPORTED BRAKING ACTION MEDIUM PRESSURE ALTITUDE (FT) S.L. 5000 10000 -4.5 -4.5 -4.5 -4.8 -4.8 -4.8 -5.1 -5.1 -5.1 -5.3 -5.3 -5.3 -5.3 -5.3 -5.3 -5.3 -5.3 -5.3 -5.1 -5.1 -5.1 -4.9 -4.9 -4.9 -4.6 -4.6 -4.6 -4.1 -4.1 -4.1 -3.6 -3.6 -3.6 -2.9 -2.9 -2.9 REPORTED BRAKING ACTION MEDIUM PRESSURE ALTITUDE (FT) S.L. 5000 10000 36.4 60.3 86.3 POOR PRESSURE ALTITUDE (FT) S.L. 5000 10000 -9.9 -9.9 -9.9 -9.8 -9.8 -9.8 -9.6 -9.6 -9.6 -9.4 -9.4 -9.4 -9.1 -9.1 -9.1 -8.7 -8.7 -8.7 -8.2 -8.2 -8.2 -7.7 -7.7 -7.7 -7.1 -7.1 -7.1 -6.4 -6.4 -6.4 -5.6 -5.6 -5.6 -4.7 -4.7 -4.7

V1(MCG) Limit Weight (1000 KG)

ADJUSTED FIELD LENGTH (M) 1000 1200 1400 1600 1800 2000 2200 2400 2600 2800 GOOD PRESSURE ALTITUDE (FT) S.L. 5000 10000 53.4 35.2 85.4 68.7 51.2 99.6 83.4 POOR PRESSURE ALTITUDE (FT) S.L. 5000 10000

40.2 64.4 90.7

44.0 68.5 95.2

37.8 52.5 68.9 87.9

34.7 49.1 65.1 83.4 104.4

31.7 45.8 61.4 79.2 99.7

1. Enter Weight Adjustment table with reported braking action and 22K Derate dry field/obstacle limit weight to obtain slippery runway weight adjustment. 2. Adjust "Good" field length available by -20 m/+20 m for every 5°C above/below 4°C. Adjust "Medium" field length available by -20 m/+20 m for every 5°C above/below 4°C. Adjust "Poor" field length available by -30 m/+30 m for every 5°C above/below 4°C. 3. Find V1(MCG) limit weight for adjusted field length and pressure altitude. 4. Max allowable slippery runway limited weight is lesser of weights from 1 and 3.

V1 Adjustment (KIAS)

WEIGHT (1000 KG) 90 85 80 75 70 65 60 55 50 45 40 GOOD PRESSURE ALTITUDE (FT) S.L. 5000 10000 -5 -3 -2 -5 -4 -2 -5 -4 -3 -6 -5 -4 -7 -6 -5 -8 -7 -5 -9 -8 -6 -10 -8 -7 -10 -9 -8 -11 -10 -8 -11 -10 -8 REPORTED BRAKING ACTION MEDIUM PRESSURE ALTITUDE (FT) S.L. 5000 10000 -14 -13 -11 -13 -12 -11 -14 -12 -11 -15 -13 -12 -16 -15 -13 -17 -16 -15 -19 -18 -17 -21 -19 -18 -22 -21 -19 -23 -22 -20 -23 -22 -21 POOR PRESSURE ALTITUDE (FT) S.L. 5000 10000 -24 -23 -22 -24 -22 -21 -24 -23 -21 -25 -24 -23 -27 -26 -24 -29 -28 -26 -31 -30 -29 -33 -32 -31 -35 -34 -33 -37 -35 -34 -37 -36 -35

1. Obtain V1, VR and V2 for the actual weight using the 22K Derate Dry Runway Takeoff Speeds table. 2. If V1(MCG) limited, set V1 = V1(MCG). If not V1(MCG) limited, enter V1 Adjustment table with the actual weight to obtain V1 speed adjustment. If adjusted V1 is less than V1(MCG), set V1 = V1(MCG).V1 not to exceed VR.

Copyright © The Boeing Company. See title page for details.

1.3.78

D632A008-ZZ022

November 1, 2006

737-800/CFM56-7B26 JAA/JAROPS Category C Brakes

TAKEOFF AND LANDING Takeoff Alternate Ratings

Flight Planning and Performance Manual

ADVISORY INFORMATION

Slippery Runway Takeoff (22K Derate)

No Reverse Thrust Weight Adjustments (1000 KG)

22K DERATE DRY FIELD/OBSTACLE LIMIT WEIGHT (1000 KG) 95 90 85 80 75 70 65 60 55 50 45 40 GOOD PRESSURE ALTITUDE (FT) S.L. 5000 10000 0.0 0.0 0.0 0.0 0.0 0.0 -0.4 -0.4 -0.4 -0.9 -0.9 -0.9 -1.3 -1.3 -1.3 -1.6 -1.6 -1.6 -1.8 -1.8 -1.8 -1.9 -1.9 -1.9 -1.9 -1.9 -1.9 -1.8 -1.8 -1.8 -1.5 -1.5 -1.5 -1.2 -1.2 -1.2 REPORTED BRAKING ACTION MEDIUM PRESSURE ALTITUDE (FT) S.L. 5000 10000 -7.7 -7.7 -7.7 -7.8 -7.8 -7.8 -7.8 -7.8 -7.8 -7.8 -7.8 -7.8 -7.6 -7.6 -7.6 -7.4 -7.4 -7.4 -7.1 -7.1 -7.1 -6.7 -6.7 -6.7 -6.2 -6.2 -6.2 -5.6 -5.6 -5.6 -4.9 -4.9 -4.9 -4.1 -4.1 -4.1 REPORTED BRAKING ACTION MEDIUM PRESSURE ALTITUDE (FT) S.L. 5000 10000 POOR PRESSURE ALTITUDE (FT) S.L. 5000 10000 -12.0 -12.0 -12.0 -11.7 -11.7 -11.7 -11.5 -11.5 -11.5 -11.2 -11.2 -11.2 -10.8 -10.8 -10.8 -10.3 -10.3 -10.3 -9.8 -9.8 -9.8 -9.1 -9.1 -9.1 -8.3 -8.3 -8.3 -7.5 -7.5 -7.5 -6.5 -6.5 -6.5 -5.5 -5.5 -5.5

V1(MCG) Limit Weight (1000 KG)

ADJUSTED FIELD LENGTH (M) 1000 1200 1400 1600 1800 2000 2200 2400 2600 2800 3000 3200 GOOD PRESSURE ALTITUDE (FT) S.L. 5000 10000 41.9 78.9 60.2 39.1 94.1 76.7 POOR PRESSURE ALTITUDE (FT) S.L. 5000 10000

62.1 94.5

35.7 70.0 102.0

44.1 77.8 35.6 57.1 82.0

48.8 72.2 99.6

40.9 63.1 89.2

1. Enter Weight Adjustment table with reported braking action and 22K Derate dry field/obstacle limit weight to obtain slippery runway weight adjustment. 2. Adjust "Good" field length available by -25 m/+20 m for every 5°C above/below 4°C. Adjust "Medium" field length available by -25 m/+20 m for every 5°C above/below 4°C. Adjust "Poor" field length available by -40 m/+35 m for every 5°C above/below 4°C. 3. Find V1(MCG) limit weight for adjusted field length and pressure altitude. 4. Max allowable slippery runway limited weight is lesser of weights from 1 and 3.

V1 Adjustment (KIAS)

WEIGHT (1000 KG) 95 90 85 80 75 70 65 60 55 50 45 40 GOOD PRESSURE ALTITUDE (FT) S.L. 5000 10000 -5 -3 0 -6 -3 -1 -6 -4 -1 -7 -4 -2 -8 -5 -3 -9 -6 -4 -10 -7 -5 -11 -8 -6 -12 -9 -7 -13 -10 -8 -13 -11 -8 -14 -11 -9 REPORTED BRAKING ACTION MEDIUM PRESSURE ALTITUDE (FT) S.L. 5000 10000 -17 -14 -12 -17 -14 -12 -17 -14 -12 -17 -15 -12 -18 -16 -13 -20 -18 -15 -22 -20 -17 -24 -22 -19 -26 -24 -21 -28 -26 -23 -30 -27 -25 -31 -28 -26 POOR PRESSURE ALTITUDE (FT) S.L. 5000 10000 -32 -30 -27 -32 -30 -27 -32 -30 -27 -33 -30 -28 -35 -32 -30 -37 -34 -32 -40 -37 -35 -43 -40 -38 -45 -43 -40 -48 -45 -43 -49 -47 -44 -50 -48 -45

1. Obtain V1, VR and V2 for the actual weight using the 22K Derate Dry Runway Takeoff Speeds table. 2. If V1(MCG) limited, set V1 = V1(MCG). If not V1(MCG) limited, enter V1 Adjustment table with the actual weight to obtain V1 speed adjustment. If adjusted V1 is less than V1(MCG), set V1 = V1(MCG).V1 not to exceed VR.

Copyright © The Boeing Company. See title page for details.

November 1, 2006

D632A008-ZZ022

1.3.79

TAKEOFF AND LANDING Takeoff Alternate Ratings

Flight Planning and Performance Manual

737-800/CFM56-7B26 JAA/JAROPS Category C Brakes

Takeoff Speeds - Dry Runway (22K Derate)

V1, VR, V2

WEIGHT (1000 KG) 80 76 72 68 64 60 56 52 48 44 40 V1 162 158 153 148 143 138 132 127 121 115 108 FLAPS 1 VR 163 158 154 149 144 139 133 127 121 115 108 V2 165 162 158 155 151 147 142 138 133 128 123 V1 156 152 147 142 138 132 127 122 116 110 104 FLAPS 5 VR 156 152 147 143 138 133 128 122 116 111 104 V2 159 156 152 149 145 141 137 132 128 123 118 V1 FLAPS 10 VR V2 V1 FLAPS 15 VR V2 V1 FLAPS 25 VR V2

146 141 136 131 126 121 115 109 103

146 141 137 132 126 121 115 109 103

150 147 143 139 135 131 126 122 117

142 138 134 128 123 118 112 107 100

142 138 134 129 124 118 113 107 101

147 144 140 136 132 128 124 119 115

131 126 121 116 110 105 98

131 126 121 116 110 105 99

138 134 130 126 122 117 113

Check V1(MCG).

V1, VR, V2 Adjustments*

TEMP °C 70 60 50 40 30 20 -60 °F 158 140 122 104 86 68 -76 -2 5 4 2 1 0 0 0 V1 PRESSURE ALTITUDE (1000 FT) 0 2 4 6 8 5 4 5 6 3 4 5 6 7 2 3 4 5 6 0 1 2 3 5 0 0 1 2 3 0 0 1 2 2 SLOPE (%) 0 0 0 0 0 0 0 0 0 0 0 0 10 -2 5 4 2 1 0 0 0 VR PRESSURE ALTITUDE (1000 FT) 0 2 4 6 8 5 4 5 6 3 4 5 6 7 2 3 4 5 6 0 1 2 3 5 0 1 1 2 3 0 1 1 2 3 10 -2 -3 -2 -1 -1 0 0 0 V2 PRESSURE ALTITUDE (1000 FT) 0 2 4 6 8 -3 -3 -3 -4 -2 -2 -3 -3 -4 -1 -1 -2 -3 -3 0 -1 -1 -2 -3 0 0 -1 -1 -2 0 0 -1 -1 -1 10

8 7 6 5 3

8 7 6 5 3

-5 -4 -3 -3 -2

Slope and Wind V1 Adjustments*

WEIGHT (1000 KG) 80 76 72 68 64 60 56 52 48 44 40 -2 -3 -3 -2 -2 -2 -1 -1 -1 -1 0 0 -1 -2 -1 -1 -1 -1 -1 0 0 0 0 0 1 1 1 1 1 1 1 1 1 0 0 0 2 1 1 1 1 1 1 1 1 1 1 1 -15 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -10 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -5 0 0 0 0 0 0 0 0 0 0 0 WIND (KTS) 0 10 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 20 1 1 1 1 1 1 1 1 1 1 1 30 1 1 1 1 1 1 1 1 1 1 1 40 1 1 1 1 1 1 1 1 1 1 1

Clearway and Stopway V1 Adjustments*

NORMAL V1 (KIAS) 160 140 120 100 300 -3 -3 -3 -4 200 -2 -3 -3 -3 100 -1 -2 -2 -2 CLEARWAY MINUS STOPWAY (M) 0 -100 0 0 0 0 0 0 0 0 -200 0 0 0 0 -300 0 0 0 0

*V1 not to exceed VR

Max Allowable Clearway for V1 Adjustment

FIELD LENGTH (M) MAX ALLOWABLE CLEARWAY (M) 1200 150 1600 180 2000 210 PRESSURE ALTITUDE (FT) 4000 83 83 85 89 93 94 2400 240 2800 270 3200 290

V1(MCG)

TEMP °C 70 60 50 40 30 20 -60 °F 158 140 122 104 86 68 -76 -2000 87 87 89 94 96 97 98 0 85 85 87 91 96 96 98 2000 84 84 88 93 94 96 6000 8000 10000

81 82 86 90 91

79 79 82 86 89

77 77 79 82 87

Copyright © The Boeing Company. See title page for details.

1.3.80

D632A008-ZZ022

November 1, 2006

737-800/CFM56-7B26 JAA/JAROPS Category C Brakes

TAKEOFF AND LANDING Takeoff Alternate Ratings

Flight Planning and Performance Manual

Takeoff Speeds - Wet Runway (22K Derate)

V1, VR, V2

WEIGHT (1000 KG) 80 76 72 68 64 60 56 52 48 44 40 V1 157 152 147 142 136 131 125 119 113 107 100 FLAPS 1 VR 163 158 154 149 144 139 133 127 121 115 108 V2 165 162 158 155 151 147 142 138 133 128 123 V1 150 146 141 136 131 125 120 114 108 102 96 FLAPS 5 VR 156 152 147 143 138 133 128 122 116 111 104 V2 159 156 152 149 145 141 137 132 128 123 118 V1 FLAPS 10 VR V2 V1 FLAPS 15 VR V2 V1 FLAPS 25 VR V2

141 136 130 125 119 113 108 102 95

146 141 137 132 126 121 115 109 103

150 147 143 139 135 131 126 122 117

138 133 127 122 116 111 105 99 93

142 138 134 129 124 118 113 107 101

147 144 140 136 132 128 124 119 115

126 120 115 109 103 98 92

131 126 121 116 110 105 99

138 134 130 126 122 117 113

Check V1(MCG).

V1, VR, V2 Adjustments*

TEMP °C 70 60 50 40 30 20 -60 °F 158 140 122 104 86 68 -76 -2 8 6 4 1 0 0 0 V1 PRESSURE ALTITUDE (1000 FT) 0 2 4 6 8 8 6 7 9 4 5 6 8 10 2 3 4 6 8 0 1 2 4 6 0 0 1 2 4 0 0 1 2 3 SLOPE (%) 0 0 0 0 0 0 0 0 0 0 0 0 10 -2 5 4 2 1 0 0 0 VR PRESSURE ALTITUDE (1000 FT) 0 2 4 6 8 5 4 5 6 3 4 5 6 7 2 3 4 5 6 0 1 2 3 5 0 1 1 2 3 0 1 1 2 3 10 -2 -3 -2 -1 -1 0 0 0 V2 PRESSURE ALTITUDE (1000 FT) 0 2 4 6 8 -3 -3 -3 -4 -2 -2 -3 -3 -4 -1 -1 -2 -3 -3 0 -1 -1 -2 -3 0 0 -1 -1 -2 0 0 -1 -1 -1 10

11 9 7 5 4

8 7 6 5 3

-5 -4 -3 -3 -2

Slope and Wind V1 Adjustments*

WEIGHT (1000 KG) 80 76 72 68 64 60 56 52 48 44 40 -2 -5 -5 -4 -4 -3 -3 -3 -3 -2 -2 -2 -1 -3 -2 -2 -2 -2 -2 -1 -1 -1 -1 -1 1 3 3 2 2 2 2 2 1 1 1 1 2 5 5 5 4 4 4 3 3 2 2 2 -15 -3 -3 -3 -3 -3 -3 -4 -4 -4 -4 -5 -10 -2 -2 -2 -2 -2 -2 -2 -3 -3 -3 -3 STOPWAY (M) 0 0 0 0 0 100 0 1 1 1 200 0 2 3 4 300 1 2 3 4 -5 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -2 WIND (KTS) 0 10 0 1 0 1 0 1 0 1 0 1 0 1 0 1 0 1 0 1 0 1 0 1 20 1 1 1 1 1 1 2 2 2 2 2 30 2 2 2 2 2 2 2 2 2 3 3 40 2 2 2 3 3 3 3 3 3 3 4

Stopway V1 Adjustments*

NORMAL V1 (KIAS) 160 140 120 100

Use of clearway not allowed on wet runways. *V1 not to exceed VR

V1(MCG)

TEMP °C 70 60 50 40 30 20 -60 °F 158 140 122 104 86 68 -76 -2000 87 87 89 94 96 97 98 0 85 85 87 91 96 96 98 2000 84 84 88 93 94 96 PRESSURE ALTITUDE (FT) 4000 83 83 85 89 93 94 6000 8000 10000

81 82 86 90 91

79 79 82 86 89

77 77 79 82 87

Copyright © The Boeing Company. See title page for details.

November 1, 2006

D632A008-ZZ022

1.3.81

TAKEOFF AND LANDING Takeoff Alternate Ratings

Flight Planning and Performance Manual

737-800/CFM56-7B26 JAA/JAROPS Category C Brakes

Takeoff %N1 (22K Derate)

Based on engine bleeds for packs on, engine and wing anti-ice on or off

OAT (°C) 60 55 50 45 40 35 30 25 20 15 10 5 0 -5 -10 -15 -20 -25 -30 -35 -40 -45 -50 -2000 87.7 88.5 89.3 90.2 91.1 91.9 91.5 90.8 90.0 89.3 88.5 87.8 87.0 86.2 85.4 84.6 83.8 83.0 82.2 81.4 80.6 79.7 78.9 -1000 88.3 89.1 89.8 90.7 91.6 92.5 92.6 91.9 91.1 90.4 89.6 88.9 88.1 87.3 86.5 85.7 84.9 84.1 83.3 82.4 81.6 80.7 79.9 0 88.7 89.5 90.4 91.2 92.1 93.0 93.8 93.1 92.3 91.6 90.8 90.0 89.2 88.4 87.6 86.8 86.0 85.2 84.4 83.5 82.7 81.8 80.9 1000 88.8 89.7 90.5 91.3 92.2 93.1 93.9 93.7 93.0 92.2 91.4 90.7 89.9 89.1 88.3 87.5 86.6 85.8 85.0 84.1 83.3 82.4 81.5 2000 88.9 89.8 90.6 91.4 92.3 93.2 94.0 94.4 93.6 92.8 92.1 91.3 90.5 89.7 88.9 88.1 87.3 86.4 85.6 84.7 83.9 83.0 82.1 AIRPORT PRESSURE ALTITUDE (FT) 3000 4000 5000 89.1 89.2 89.2 89.9 90.0 90.0 90.7 90.9 90.8 91.5 91.7 91.6 92.4 92.5 92.4 93.2 93.3 93.3 94.0 94.1 94.0 94.8 94.9 94.8 94.3 95.0 95.6 93.6 94.3 94.8 92.8 93.5 94.0 92.0 92.7 93.2 91.2 91.9 92.4 90.4 91.1 91.6 89.6 90.3 90.8 88.8 89.4 90.0 87.9 88.6 89.1 87.1 87.8 88.3 86.3 86.9 87.4 85.4 86.1 86.6 84.5 85.2 85.7 83.7 84.3 84.8 82.8 83.4 83.9 6000 89.1 90.0 90.8 91.6 92.4 93.2 93.9 94.8 95.6 95.3 94.5 93.7 92.9 92.1 91.3 90.5 89.7 88.8 88.0 87.1 86.2 85.3 84.5 7000 88.6 89.5 90.4 91.2 92.1 92.9 93.7 94.4 95.3 95.9 95.1 94.3 93.5 92.7 91.9 91.1 90.3 89.4 88.6 87.7 86.8 86.0 85.1 8000 88.3 89.0 89.9 90.8 91.7 92.5 93.4 94.0 94.9 96.1 95.7 94.9 94.1 93.3 92.5 91.7 90.8 90.0 89.2 88.3 87.4 86.6 85.7 9000 88.7 88.8 89.7 90.7 91.6 92.5 93.3 94.0 94.8 95.9 96.4 95.6 94.8 94.0 93.2 92.4 91.6 90.7 89.9 89.0 88.2 87.3 86.4 10000 89.2 88.6 89.6 90.5 91.5 92.4 93.2 94.0 94.7 95.5 97.1 96.3 95.5 94.7 93.9 93.1 92.3 91.5 90.6 89.8 88.9 88.0 87.2

%N1 Adjustments for Engine Bleeds

BLEED CONFIGURATION PACKS OFF -2000 0.7 -1000 0.7 0 0.7 1000 0.7 2000 0.7 AIRPORT PRESSURE ALTITUDE (FT) 3000 4000 5000 6000 0.7 0.8 0.8 0.8 7000 0.8 8000 0.9 9000 0.9 10000 0.9

Stab Trim Setting (22K Derate)

Flaps 1 and 5

WEIGHT (1000 KG) 85 80 75 70 65 60 55 50 45 40 6 8 1/2 8 1/2 8 1/4 8 7 3/4 7 1/2 7 1/4 7 6 3/4 6 3/4 8 8 1/2 8 1/2 8 7 3/4 7 1/2 7 1/4 7 1/4 6 3/4 6 1/2 6 1/2 10 8 1/2 8 1/4 7 3/4 7 1/2 7 1/4 7 6 3/4 6 1/2 6 1/4 6 1/4 16 7 1/2 7 1/4 7 6 3/4 6 1/2 6 1/4 6 5 3/4 5 1/2 5 1/2 C.G. (%MAC) 21 26 6 3/4 6 6 1/2 5 3/4 6 1/4 5 1/2 6 5 1/4 5 3/4 5 5 1/2 5 5 1/2 4 3/4 5 4 1/4 4 3/4 4 4 3/4 4 30 5 1/2 5 4 3/4 4 1/2 4 1/2 4 1/4 4 3 3/4 3 1/2 3 1/2 33 5 4 3/4 4 1/4 4 1/4 4 3 3/4 3 1/2 3 1/4 3 3 35 4 3/4 4 1/4 4 3 3/4 3 3/4 3 1/2 3 1/4 3 2 3/4 2 3/4 36 4 1/2 4 1/4 3 3/4 3 3/4 3 1/2 3 1/4 3 1/4 3 2 3/4 2 3/4

Flaps 10, 15 and 25

WEIGHT (1000 KG) 85 80 75 70 65 60 55 50 45 40 6 8 1/2 8 1/2 8 1/2 8 1/2 8 1/4 7 3/4 7 6 1/2 6 6 8 8 1/2 8 1/2 8 1/2 8 1/4 7 3/4 7 1/4 6 3/4 6 1/4 5 3/4 5 3/4 10 8 1/2 8 1/2 8 1/4 7 3/4 7 1/4 6 3/4 6 1/4 5 3/4 5 1/2 5 1/2 16 6 3/4 6 3/4 6 1/2 6 1/4 5 3/4 5 1/2 5 1/4 4 3/4 4 1/2 4 1/2 C.G. (%MAC) 21 26 5 1/2 4 1/2 5 3/4 4 3/4 5 1/2 4 1/2 5 1/4 4 1/4 4 3/4 3 3/4 4 1/2 3 1/2 4 1/4 3 1/2 4 3 3 1/2 2 3/4 3 1/2 2 3/4 30 3 3/4 3 3/4 3 1/2 3 1/4 3 2 3/4 2 3/4 2 1/4 2 1/4 2 1/4 33 3 1/4 3 1/4 3 2 3/4 2 1/2 2 1/4 2 1/4 2 1/4 2 1/4 2 1/4 35 2 3/4 2 3/4 2 1/2 2 1/4 2 1/4 2 1/4 2 1/4 2 1/4 2 1/4 2 1/4 36 2 1/2 2 1/2 2 1/2 2 1/4 2 1/4 2 1/4 2 1/4 2 1/4 2 1/4 2 1/4

Copyright © The Boeing Company. See title page for details.

1.3.82

D632A008-ZZ022

November 1, 2006

737-800/CFM56-7B26 JAA/JAROPS Category C Brakes

TAKEOFF AND LANDING Landing

Flight Planning and Performance Manual

Landing

1.4 TAKEOFF AND LANDING-Landing Landing Field Length Limit

Flaps 30

Based on anti-skid operative and automatic speedbrakes

88

84

80

FT) (1000

76

E AL TITU

DE

SUR

10

8

6

4

-2 0 2

72

64

60

56

52

48

44

40 40 HEAD WIND (KTS) RUNWAY CONDITION 20 REF LINE

0 -5 -10 -15 TAIL WET

1000 FT

REF LINE 4 5 12 14 16

DRY 6 7 8 9 10 30 32 11 34 36 18 20 22 24 26 28 FIELD LENGTH AVAILABLE

100 M 10

With manual speedbrakes, decrease field limit weight by 4200 kg.

Copyright © The Boeing Company. See title page for details.

November 1, 2006

D632A008-ZZ022

FIELD LENGTH LIMIT WEIGHT

PRES

68

(1000 KG)

1.4.1

TAKEOFF AND LANDING Landing

Flight Planning and Performance Manual

Landing

737-800/CFM56-7B26 JAA/JAROPS Category C Brakes

Landing Field Length Limit

Flaps 40

Based on anti-skid operative and automatic speedbrakes

88

84

FT) (1000

80

ALTIT

UDE

SURE

-2 0 2 4 6 8 10

76

72

64

60

56

52

48

44

40 40 HEAD WIND (KTS) RUNWAY CONDITION 20 REF LINE

0 -5 -10 -15 TAIL WET

1000 FT

REF LINE 4 5 12 14

DRY 6 7 8 9 28 30

100 M 10

16 18 20 22 24 26 FIELD LENGTH AVAILABLE

With manual speedbrakes, decrease field limit weight by 4350 kg.

Copyright © The Boeing Company. See title page for details.

FIELD LENGTH LIMIT WEIGHT

68

(1000 KG)

PRES

1.4.2

D632A008-ZZ022

November 1, 2006

737-800/CFM56-7B26 JAA/JAROPS Category C Brakes

TAKEOFF AND LANDING Landing

Flight Planning and Performance Manual

Landing

Landing Field Length Limit

Flaps 30

Based on anti-skid inoperative and manual speedbrakes

88

84

00

FT)

SSU RE ALT ITU DE

(10

80

0

76

2

4

6

-2

72

64

60

56

52

48

44

40 40 HEAD

REF LINE

REF LINE 1000 FT 100 M 22 8 26 9 10 30 11 34 12 13 14 15 16 50 17 18 54 19 58

DRY 38 42 46 FIELD LENGTH AVAILABLE

Copyright © The Boeing Company. See title page for details.

November 1, 2006

D632A008-ZZ022

RUNWAY CONDITION

0 -5 -10 -15 TAIL WET

WIND (KTS)

20

FIELD LENGTH LIMIT WEIGHT

68

(1000 KG)

PRE

8

10

1.4.3

TAKEOFF AND LANDING Landing

Flight Planning and Performance Manual

Landing

737-800/CFM56-7B26 JAA/JAROPS Category C Brakes

Landing Field Length Limit

Flaps 40

Based on anti-skid inoperative and manual speedbrakes

88

84

80

0 F T)

ITU D

E

(100

76

ALT

0

72

2

4

RE

8

SSU

10

64

60

56

52

48

44

40 40 HEAD

REF LINE

REF LINE 1000 FT 6 7 22 8 26 9 10 30 11 12 13 14 15 46 16 50 17 54

DRY 34 38 42 FIELD LENGTH AVAILABLE

100 M 18

Copyright © The Boeing Company. See title page for details.

1.4.4

D632A008-ZZ022

November 1, 2006

RUNWAY CONDITION

0 -5 -10 -15 TAIL WET

WIND (KTS)

20

FIELD LENGTH LIMIT WEIGHT

68

PRE

(1000 KG)

-2

6

737-800/CFM56-7B26 JAA/JAROPS Category C Brakes

TAKEOFF AND LANDING Landing

Flight Planning and Performance Manual

Landing Climb Limit Weight

Valid for approach with flaps 15 and landing with flaps 30 or 40

Based on engine bleed for packs on and anti-ice off

82 -2 -1 0 1 78 2 3 4 70 CLIMB LIMIT LANDING WEIGHT 5 6 66 7 8 62 9 10 58 AIRPORT PRESSURE ALTITUDE (1000 FT)

(1000 KG)

74

54

50 -60

-60 -50

-40 -40

-20 0 -30 -20

20 40 60 80 100 -10 0 10 20 30 40 AIRPORT OAT

120 50

140 60

70

F C

With engine bleed for packs off, increase weight by 1200 kg. With engine anti-ice on, decrease weight by 300 kg. With engine and wing anti-ice on, decrease weight by 1400 kg. When operating in icing conditions during any part of the flight with the forecast landing temperature below 10°C, decrease the landing climb limit by 5500 kg.

Copyright © The Boeing Company. See title page for details.

November 1, 2006

D632A008-ZZ022

1.4.5

TAKEOFF AND LANDING Landing

Flight Planning and Performance Manual

737-800/CFM56-7B26 JAA/JAROPS Category C Brakes

ENGINE INOP

GO-AROUND THRUST

Go-Around Climb Gradient

Based on flaps 15 with gear up and engine bleed for packs on

AIRPORT PRESSURE ALTITUDE (1000 FT) -1

50

40 2 (°C) 3 30 6 20 8 9 10 10 7 4 5

0 1

AIRPORT OAT (1000 KG) WEIGHT

0 80

70

60

REF LINE

50 (KIAS) AIRSPEED +30 +20 +10

REF LINE 1 2 3 4 GROSS GRADIENT 5 (PERCENT) 6 7 8

VREF 40

With engine bleed for packs off, increase gradient by 0.2%. With engine anti-ice on, decrease gradient by 0.1%. With engine and wing anti-ice on, decrease gradient by 0.3%. When operating in icing conditions during any part of the flight with forecast landing temperature below 10°C, decrease gradient by 0.9%.

Copyright © The Boeing Company. See title page for details.

1.4.6

D632A008-ZZ022

November 1, 2006

737-800/CFM56-7B26 JAA/JAROPS Category C Brakes

TAKEOFF AND LANDING Landing

Flight Planning and Performance Manual

ENGINE INOP

GO-AROUND THRUST

Go-Around Climb Gradient - High Altitudes

Based on flaps 15 with gear up and engine bleed for packs on

40

AIRPORT OAT ( ° C)

30 11

AIRPORT PRESSURE ALTITUDE (1000 FT) 15 14 13 12 10

20

10

0 GROSS WEIGHT (1000 KG) 80 70 60 50 40 +30 +20 +10

REF. LINE

AIRSPEED (KIAS)

REF. LINE 0 1 2 3

VREF 40 -1

GROSS GRADIENT (PERCENT)

With engine bleed for packs off, increase gradient by 0.2%. With engine anti-ice on, decrease gradient by 0.4%. With engine and wing anti-ice on, decrease gradient by 0.6%. When operating in icing conditions during any part of the flight with forecast landing temperature below 10°C, decrease gradient by 0.6%.

Copyright © The Boeing Company. See title page for details.

November 1, 2006

D632A008-ZZ022

1.4.7

TAKEOFF AND LANDING Landing

Flight Planning and Performance Manual

737-800/CFM56-7B26 JAA/JAROPS Category C Brakes

Quick Turnaround Limit

Flaps 40 Limit Weight (1000 KG)

AIRPORT OAT (°C) 54 50 45 40 35 30 25 20 15 10 5 0 -5 -10 -15 -20 -30 -40 -50 -54 -2000 82.7 83.2 83.9 84.7 85.5 86.1 86.1 86.1 86.1 86.1 86.1 86.1 86.1 86.1 86.1 86.1 86.1 86.1 86.1 86.1 -1000 81.2 81.7 82.4 83.1 83.9 84.6 85.4 86.1 86.1 86.1 86.1 86.1 86.1 86.1 86.1 86.1 86.1 86.1 86.1 86.1 0 79.6 80.2 80.9 81.6 82.3 83.0 83.8 84.6 85.4 86.1 86.1 86.1 86.1 86.1 86.1 86.1 86.1 86.1 86.1 86.1 1000 78.7 79.3 80.0 80.8 81.5 82.2 82.9 83.7 84.5 85.4 86.1 86.1 86.1 86.1 86.1 86.1 86.1 86.1 86.1 2000 77.2 77.8 78.5 79.2 79.9 80.6 81.3 82.1 82.9 83.7 84.5 85.4 86.1 86.1 86.1 86.1 86.1 86.1 86.1 AIRPORT PRESSURE ALTITUDE (FT) 3000 4000 5000 6000 7000 8000 9000 10000

76.3 76.9 77.6 78.3 79.0 79.7 80.5 81.2 82.0 82.8 83.6 84.5 85.4 86.1 86.1 86.1 86.1 86.1

74.8 75.4 76.1 76.7 77.4 78.1 78.9 79.6 80.4 81.2 82.0 82.8 83.7 84.6 86.1 86.1 86.1 86.1

73.9 74.6 75.2 75.9 76.6 77.3 78.1 78.8 79.6 80.4 81.2 82.0 82.9 84.7 86.1 86.1 86.1

72.4 73.1 73.7 74.4 75.1 75.8 76.5 77.2 78.0 78.8 79.6 80.4 81.2 83.0 84.9 86.1 86.1

71.0 71.6 72.2 72.9 73.6 74.2 74.9 75.7 76.4 77.2 78.0 78.8 79.6 81.3 83.2 85.2 86.0

70.1 70.8 71.4 72.1 72.7 73.4 74.1 74.9 75.6 76.4 77.2 78.0 79.7 81.5 83.4 84.2

68.7 69.3 69.9 70.6 71.2 71.9 72.6 73.3 74.0 74.8 75.6 76.4 78.0 79.8 81.7 82.5

67.9 68.5 69.1 69.8 70.4 71.1 71.8 72.5 73.3 74.0 74.8 76.4 78.1 79.9 80.7

Flaps 30 Limit Weight (1000 KG)

AIRPORT OAT (°C) 54 50 45 40 35 30 25 20 15 10 5 0 -5 -10 -15 -20 -30 -40 -50 -54 -2000 77.9 78.4 79.1 79.8 80.5 81.3 82.0 82.8 83.6 84.4 85.3 86.1 86.1 86.1 86.1 86.1 86.1 86.1 86.1 86.1 -1000 76.5 77.0 77.6 78.3 79.0 79.7 80.4 81.2 82.0 82.8 83.6 84.5 85.3 86.1 86.1 86.1 86.1 86.1 86.1 86.1 0 75.1 75.6 76.2 76.9 77.5 78.2 78.9 79.6 80.4 81.2 82.0 82.9 83.7 84.6 85.5 86.1 86.1 86.1 86.1 86.1 1000 74.1 74.8 75.4 76.1 76.8 77.4 78.1 78.9 79.6 80.4 81.2 82.0 82.9 83.8 84.7 86.1 86.1 86.1 86.1 2000 72.7 73.3 74.0 74.6 75.3 76.0 76.6 77.3 78.1 78.8 79.6 80.4 81.2 82.1 83.0 84.9 86.1 86.1 86.1 AIRPORT PRESSURE ALTITUDE (FT) 3000 4000 5000 6000 7000 8000 9000 10000

71.9 72.5 73.1 73.8 74.5 75.1 75.8 76.6 77.3 78.0 78.8 79.6 80.4 81.3 83.2 85.1 86.1 86.1

70.5 71.1 71.7 72.3 73.0 73.6 74.3 75.0 75.8 76.5 77.3 78.0 78.8 79.6 81.5 83.4 85.4 86.1

69.7 70.3 70.9 71.5 72.2 72.9 73.6 74.3 75.0 75.7 76.5 77.3 78.1 79.8 81.7 83.7 84.5

68.3 68.9 69.5 70.1 70.8 71.4 72.1 72.8 73.5 74.2 75.0 75.8 76.6 78.2 80.0 82.0 82.8

66.9 67.5 68.1 68.7 69.3 70.0 70.6 71.3 72.0 72.7 73.5 74.2 75.0 76.7 78.4 80.3 81.1

66.1 66.7 67.3 67.9 68.6 69.2 69.9 70.6 71.3 72.0 72.7 73.5 75.1 76.8 78.6 79.4

64.8 65.3 65.9 66.5 67.1 67.8 68.4 69.1 69.8 70.5 71.2 72.0 73.6 75.2 77.0 77.8

64.1 64.6 65.2 65.8 66.4 67.0 67.7 68.4 69.1 69.8 70.5 72.0 73.7 75.4 76.2

Increase weight by 700 kg per 1% uphill slope. Decrease weight by 1200 kg per 1% downhill slope. Increase weight by 1850 kg per 10 knots headwind. Decrease weight by 7750 kg per 10 knots tailwind. After landing at weights exceeding those shown above, adjusted for slope and wind, wait at least 67 minutes and check that wheel thermal plugs have not melted before executing a subsequent takeoff. As an alternate procedure, ensure that each brake pressure plate temperature, without artificial cooling, is less than 218°C as follows: No sooner than 10 and no later than 15 minutes after parking, measure each brake pressure plate surface temperature at a minimum of two points per brake by an accurate method (using a Doric Microtemp 450 hand held thermometer or equivalent, hold temperature probe in place for 20 seconds or until reading stabilizes). If each measured temperature is less than 218°C, immediate dispatch is allowed; otherwise the required minimum ground wait period of 67 minutes applies. If a Brake Temperature Monitoring System (BTMS) is installed: No sooner than 10 and no later than 15 minutes after parking, check the BRAKE TEMP light. If the BRAKE TEMP light is not on, no ground waiting period is required. If the BRAKE TEMP light is on, do not dispatch until at least 67 minutes after landing, or until all the BTMS readings on the systems Display are below 3.5 and the BRAKE TEMP light is off. Check that wheel thermal plugs have not melted before making a subsequent takeoff. Note: If any brake temperature display digit is blank or indicates 0.0 or 0.1, then this method cannot be used.

Copyright © The Boeing Company. See title page for details.

1.4.8

D632A008-ZZ022

November 1, 2006

737-800/CFM56-7B26 JAA/JAROPS Category C Brakes

TAKEOFF AND LANDING Landing

Flight Planning and Performance Manual

Recommended Brake Cooling Schedule

BRAKES ON SPEED (KIAS)

80

60

40 0 PRESS ALT (1000 FT) 5 10 15 0 OAT ( C) 20 40 60

0

0

;;;;;;;;;;;;; ;;;;;;;;;;;;; ;;;;;;;;;;;;; ;;;;;;;;;;;;; ;;;;;;;;;;;;; ;;;;;;;;;;;;; ;;;;;;;;;;;;; ;;;;;;;;;;;;; ;;;;;;;;;;;;; ;;;;;;;;;;;;; ;;;;;;;;;;;;; ;;;;;;;;;;;;; ;;;;;;;;;;;;; ;;;;;;;;;;;;; ;;;;;;;;;;;;; ;;;;;;;;;;;;; ;;;;;;;;;;;;; ;;;;;;;;;;;;; ;;;;;;;;;;;;; ;;;;;;;;;;;;; ;;;;;;;;;;;;; ;;;;;;;;;;;;; ;;;;;;;;;;;;; ;;;;;;;;;;;;; ;;;;;;;;;;;;; ;;;;;;;;;;;;; ;;;;;;;;;;;;; ;;;;;;;;;;;;; ;;;;;;;;;;;;; ;;;;;;;;;;;;; ;;;;;;;;;;;;; ;;;;;;;;;;;;; ;;;;;;;;;;;;; ;;;;;;;;;;;;;

100

ADVISORY INFORMATION

(1000 KG)

Observe Maximum Quick Turnaround Limitation. To correct for wind, enter chart with brakes on speed minus one half the headwind or plus 1.5 times the tailwind. Chart shows energy per brake added by a single stop with all brakes operating. Energy is assumed to be equally distributed among the operating brakes. Total energy is the sum of residual energy plus energy added. Add 1.0 million foot pounds per brake for each taxi mile. If ground speed is used for brakes on speed, ignore wind, altitude, and OAT effects. 1 Wheel fuse plugs may melt. Delay takeoff and inspect after one hour. If overheating occurs after takeoff, extend gear soon for at least 7 minutes. 2 Clear runway immediately. Unless required, do not set parking brake. Do not approach gear or attempt to taxi for one hour. Tire, wheel and brake replacement may be required. If overheating occurs after takeoff, extend gear soon for at least 12 minutes. Brake Temperature Monitor Indication (BTMS) may be used 10 to 15 minutes after the airplane has come to a complete stop, or inflight with gear retracted to determine recommended cooling schedule.

0 16

0

0 18

60

80

WEIGHT

REF LINE

REF LINE

REF LINE

12

14

0

REJECTED TAKEOFF (NO REVERSE) LANDING

MAX MANUAL BRAKING

EVENT

MAX AUTOBRAKE AUTOBRAKE 3

AUTOBRAKE 2

AUTOBRAKE 1

SOLID LINES ARE BASED ON NO REVERSE

DASHED LINES ARE BASED ON 2 ENGINE REVERSE 10 20 30 40

50

60

BRAKE ENERGY PER BRAKE (MILLION FT LB)

COOLING CAUTION

FUSE PLUG

RECOMMENDED

MELT ZONE

4 8 7 0 1 2 3 9 5 6 INFLIGHT GEAR DOWN COOLING TIME ~ MIN

NO SPECIAL REQUIRED

PROCEDURES

1

2

0 10 20 30

40

50

60

70

80

90

GROUND COOLING TIME ~ MIN

2 5 7 9 3 6 1 4 8 BRAKE TEMPERATURE MONITOR INDICATION ON CDS SYSTEMS PAGE

Copyright © The Boeing Company. See title page for details.

November 1, 2006

D632A008-ZZ022

1.4.9

TAKEOFF AND LANDING Landing

Flight Planning and Performance Manual

737-800/CFM56-7B26 JAA/JAROPS Category C Brakes

ADVISORY INFORMATION

Normal Configuration Landing Distances

Flaps 30 Dry Runway

REFERENCE DISTANCE 60000 KG LANDING WEIGHT 900 1145 1610 2065 2270 LANDING DISTANCE AND ADJUSTMENT (M) WEIGHT ALTITUDE WIND ADJ SLOPE ADJ TEMP ADJ VREF ADJ ADJUSTMENT ADJ PER 10 KTS PER 1% PER 10°C PER 5000 KG PER 1000 FT HEAD PER 10 KTS TAIL DOWN UP ABOVE BELOW ABOVE/BELOW ABOVE STD/HIGH* WIND WIND HILL HILL ISA ISA 60000 KG VREF30 60/-50 20/25 -35 110 10 -10 20 -20 65 65/-60 25/30 -40 140 5 -5 25 -25 100 105/-105 40/55 -70 235 5 -5 45 -45 165 150/-150 60/80 -95 325 30 -35 55 -55 170 175/-175 70/95 -110 385 60 -65 65 -65 160 REVERSE THRUST ADJ ONE REV 15 0 0 65 200 NO REV 35 0 0 65 280

BRAKING CONFIGURATION MAX MANUAL MAX AUTO AUTOBRAKE 3 AUTOBRAKE 2 AUTOBRAKE 1

Good Reported Braking Action

MAX MANUAL MAX AUTO AUTOBRAKE 3 AUTOBRAKE 2 1440 1580 1860 2380 95/-90 95/-95 125/-125 175/-175 35/50 40/50 50/60 70/90 -60 -60 -80 -105 225 230 280 375 35 35 15 35 -25 -25 -10 -40 35 35 55 65 -35 -35 -50 -60 110 115 190 200 75 85 10 75 170 185 20 75

Medium Reported Braking Action

MAX MANUAL MAX AUTO AUTOBRAKE 3 AUTOBRAKE 2 1950 2040 2085 2435 140/-140 145/-140 145/-140 180/-180 60/70 60/70 60/80 70/90 -100 -100 -100 -120 370 370 380 430 90 90 70 65 -65 -65 -45 -60 55 55 55 65 -50 -50 -55 -65 140 140 190 200 205 210 150 115 490 500 445 250

Poor Reported Braking Action

MAX MANUAL MAX AUTO AUTOBRAKE 3 AUTOBRAKE 2 2575 2625 2625 2715 205/-190 205/-190 205/-190 215/-200 85/110 85/110 85/110 90/120 -150 -150 -150 -155 585 585 585 600 210 210 210 185 -130 -130 -130 -120 70 70 70 75 -65 -65 -65 -75 165 165 175 200 430 430 435 355 1145 1150 1150 1015

Reference distance is for sea level, standard day, no wind or slope, VREF30 approach speed and two engine detent reverse thrust. Max manual braking data valid for auto speedbrakes. Autobrake data valid for both auto and manual speedbrakes. For max manual braking and manual speedbrakes, increase reference landing distance by 55 m. Distances for GOOD, MEDIUM, and POOR are increased by 15%. Includes distance from 50 ft above threshold (305 m of air distance). *For landing distance at or below 8000 ft pressure altitude, apply the STD adjustment. For altitudes higher than 8000 ft, first apply the STD adjustment to derive a new reference landing distance for 8000 ft then apply the HIGH adjustment to this new reference distance.

Copyright © The Boeing Company. See title page for details.

1.4.10

D632A008-ZZ022

November 1, 2006

737-800/CFM56-7B26 JAA/JAROPS Category C Brakes

TAKEOFF AND LANDING Landing

Flight Planning and Performance Manual

ADVISORY INFORMATION

Normal Configuration Landing Distances

Flaps 40 Dry Runway

REFERENCE DISTANCE 60000 KG LANDING WEIGHT 860 1070 1485 1910 2115 LANDING DISTANCE AND ADJUSTMENT (M) WEIGHT ALTITUDE WIND ADJ SLOPE ADJ TEMP ADJ VREF ADJ ADJUSTMENT ADJ PER 10 KTS PER 1% PER 10°C PER 5000 KG PER 1000 FT HEAD PER 10 KTS TAIL DOWN UP ABOVE BELOW ABOVE/BELOW ABOVE STD/HIGH* WIND WIND HILL HILL ISA ISA 60000 KG VREF40 55/-45 15/25 -30 110 10 -10 15 -15 65 60/-55 20/30 -40 135 5 -5 25 -25 95 100/-95 35/50 -65 225 5 -5 40 -40 160 140/-135 55/70 -90 315 25 -30 50 -50 175 165/-160 65/85 -105 370 50 -60 60 -60 160 REVERSE THRUST ADJ ONE REV 15 0 0 35 155 NO REV 30 0 0 35 205

BRAKING CONFIGURATION MAX MANUAL MAX AUTO AUTOBRAKE 3 AUTOBRAKE 2 AUTOBRAKE 1

Good Reported Braking Action

MAX MANUAL MAX AUTO AUTOBRAKE 3 AUTOBRAKE 2 1375 1495 1745 2200 90/-85 95/-85 115/-105 165/-155 35/50 35/50 40/60 65/80 -60 -60 -75 -100 220 225 265 365 35 35 15 30 -25 -25 -10 -35 35 35 50 60 -35 -35 -40 -55 110 115 185 200 70 75 10 40 155 165 20 40

Medium Reported Braking Action

MAX MANUAL MAX AUTO AUTOBRAKE 3 AUTOBRAKE 2 1855 1930 1955 2255 135/-125 135/-130 140/-130 170/-160 55/70 55/70 55/70 65/90 -95 -95 -100 -115 365 365 370 410 90 90 70 60 -60 -60 -45 -50 45 45 50 55 -45 -45 -50 -60 140 140 185 205 185 185 155 90 445 445 420 215

Poor Reported Braking Action

MAX MANUAL MAX AUTO AUTOBRAKE 3 AUTOBRAKE 2 2395 2490 2490 2570 190/-175 190/-175 190/-175 200/-190 75/100 75/100 75/100 75/100 -150 -150 -150 -155 570 570 570 590 205 205 205 180 -130 -130 -130 -115 65 65 65 70 -60 -60 -60 -65 165 165 170 200 385 385 385 315 1020 1020 1025 915

Reference distance is for sea level, standard day, no wind or slope, VREF40 approach speed and two engine detent reverse thrust. Max manual braking data valid for auto speedbrakes. Autobrake data valid for both auto and manual speedbrakes. For max manual braking and manual speedbrakes, increase reference landing distance by 55 m. Distances for GOOD, MEDIUM, and POOR are increased by 15%. Includes distance from 50 ft above threshold (305 m of air distance). *For landing distance at or below 8000 ft pressure altitude, apply the STD adjustment. For altitudes higher than 8000 ft, first apply the STD adjustment to derive a new reference landing distance for 8000 ft then apply the HIGH adjustment to this new reference distance.

Copyright © The Boeing Company. See title page for details.

November 1, 2006

D632A008-ZZ022

1.4.11

TAKEOFF AND LANDING Landing

Flight Planning and Performance Manual

737-800/CFM56-7B26 JAA/JAROPS Category C Brakes

Intentionally Blank

Copyright © The Boeing Company. See title page for details.

1.4.12

D632A008-ZZ022

November 1, 2006

737-800/CFM56-7B26 JAA/JAROPS Category C Brakes

FLIGHT PLANNING Table of Contents

Flight Planning and Performance Manual

FLIGHT PLANNING

Table of Contents

Chapter 2

2.0 FLIGHT . . . . . . . . . Text . .PLANNING-Table .of. Contents. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2.1.1 ....

Introduction . . . . . . . . . . . Simplified Flight Planning Driftdown . . . . . . . . . . . . ETOPS . . . . . . . . . . . . . .

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2.1.1 2.1.1 2.1.3 2.1.3

Simplified Flight Planning . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2.2.1 Optimum Altitude . . . . . . . . . . . . . . . . . . . . . . . . . Short Trip Cruise Altitude . . . . . . . . . . . . . . . . . . . Long Range Cruise Trip Fuel and Time . . . . . . . . . .79M Trip Fuel and Time . . . . . . . . . . . . . . . . . . . . Cost Index 30 Trip Fuel and Time . . . . . . . . . . . . . Long Range Cruise Step Climb Trip Fuel and Time .79M Step Climb Trip Fuel and Time . . . . . . . . . . . Cost Index 30 Step Climb Trip Fuel and Time . . . . Long Range Cruise Short Trip Fuel and Time . . . . . Cost Index 30 Short Trip Fuel and Time . . . . . . . . . Holding Planning . . . . . . . . . . . . . . . . . . . . . . . . . . Passenger Oxygen Requirements . . . . . . . . . . . . . . Flight Crew Oxygen Requirements . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2.2.1 . 2.2.1 . 2.2.2 . 2.2.4 . 2.2.6 . 2.2.8 . 2.2.9 2.2.10 2.2.11 2.2.12 2.2.13 2.2.14 2.2.15

Driftdown . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2.3.1 Net Level Off Weight . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2.3.1 Driftdown Profiles Net Flight Path . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2.3.2 Driftdown/LRC Cruise Range Capability . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2.3.6 ETOPS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2.4.1 Area of Operation . . . . . . . . . . . . . . . . . . . . . . . . . . . . Long Range Cruise Critical Fuel Reserves . . . . . . . . . . 280 KIAS Cruise Critical Fuel Reserves . . . . . . . . . . . . 290 KIAS Cruise Critical Fuel Reserves . . . . . . . . . . . . 310 KIAS Cruise Critical Fuel Reserves . . . . . . . . . . . . 330 KIAS Cruise Critical Fuel Reserves . . . . . . . . . . . . Long Range Cruise Net Level Off Weight . . . . . . . . . . 280 KIAS Net Level Off Weight . . . . . . . . . . . . . . . . . 290 KIAS Net Level Off Weight . . . . . . . . . . . . . . . . . 310 KIAS Net Level Off Weight . . . . . . . . . . . . . . . . . 330 KIAS Net Level Off Weight . . . . . . . . . . . . . . . . . Long Range Cruise Driftdown/Cruise Range Capability

November 1, 2006 D632A008-ZZ022

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. 2.4.1 . 2.4.2 . 2.4.4 . 2.4.5 . 2.4.6 . 2.4.7 . 2.4.8 . 2.4.9 2.4.10 2.4.11 2.4.12 2.4.13

Copyright © The Boeing Company. See title page for details.

2.TOC.0.1

FLIGHT PLANNING Table of Contents

Flight Planning and Performance Manual

737-800/CFM56-7B26 JAA/JAROPS Category C Brakes

.76M/280 .79M/290 .79M/310 .79M/330

KIAS KIAS KIAS KIAS

Driftdown/Cruise Driftdown/Cruise Driftdown/Cruise Driftdown/Cruise

Range Range Range Range

Capability Capability Capability Capability

. . . .

. . . .

. . . .

. . . .

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2.4.14 2.4.15 2.4.16 2.4.17

Copyright © The Boeing Company. See title page for details.

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737-800/CFM56-7B26 JAA/JAROPS Category C Brakes

Text

FLIGHT PLANNING Text

Flight Planning and Performance Manual

2.1 FLIGHT PLANNING-Text Introduction

Altitude Selection Best fuel mileage for a given speed schedule is achieved at optimum altitude. Fuel mileage penalties for operation at off-optimum altitudes are shown in the following table.

OFF-OPTIMUM CONDITION 2000 FT ABOVE OPTIMUM ALTITUDE 2000 FT BELOW 4000 FT BELOW 6000 FT BELOW 8000 FT BELOW 10000 FT BELOW 12000 FT BELOW FUEL MILEAGE PENALTY % LRC .79M CI30 1 1 1 0 0 0 1 2 2 4 6 5 7 10 8 9 16 12 12 20 15 16 23 20

This chapter contains flight planning data to determine trip fuel/time, reserve fuel and enroute terrain clearance capability. The data includes engine bleed effects for normal air conditioning operation, i.e. two packs at normal flow, one pack bleeding each engine.

Simplified Flight Planning

Flight Planning Allowances Simplified Flight Planning charts enable rapid determination of estimated trip time and fuel from brake release to landing. Additional flight planning information, including maneuver allowances is summarized below. Ground Operations Fuel can be saved by minimizing APU utilization. Average APU fuel flow rate under normal operation is 105 kg per hour on the ground. Taxi fuel allowance is approximately 15 kg per minute. APU Operation During Flight For APU operation during flight, increase fuel flow according to the following table. These increments include the APU fuel flow and the effect of increased drag from the APU door.

PRESSURE ALTITUDE (1000 FT) 39 35 31 25 20 15 10 5 APU FUEL FLOW (KG/HR) 45 45 50 60 65 75 85 95

Cruise Long Range Cruise is the speed which gives 99% of the maximum fuel mileage at zero wind. For cruise within 2000 ft of optimum altitude Long Range Cruise may be approximated by a constant .79M or Cost Index 30. Increase total fuel flow during cruise approximately 45 kg/hr for engine anti-ice on or 140 kg/hr for engine and wing anti-ice on. Every 450 kg reduction in landing weight decreases trip fuel at optimum altitude by approximately 0.5%. Descent Optimum descent speeds for minimum trip fuel are a function of weight. Trip Fuel and Time charts are based on .78/280/250 descent speed, and include straight in approach allowances only. Each additional minute of flaps down maneuvering consumes approximately 50 kg of additional fuel with the gear retracted and 60 kg with the gear extended. Missed Approach Approximately 130 kg of additional fuel is burned during the missed approach maneuver, based on applying go-around power from the final approach configuration, retracting flaps and gear while climbing to 1500 ft and accelerating to 250 KIAS. Optimum Altitude Optimum altitude for best fuel mileage is presented for LRC/.79M speed schedule. Fuel mileage penalties for flying off-optimum altitude are tabulated under Flight Planning Allowances. Short Trip Cruise Altitude Short range operation may be limited by the distance required to perform the climb and descent. The Short Trip Cruise Altitude chart shows the maximum altitude at which it is possible to cruise for various times in level flight.

Climb Trip Fuel and Time charts are based on an initial climb speed of 280 KIAS. Local ATC may require that 250 KIAS not be exceeded below 10000 ft. Approximately 25 kg of additional fuel is burned when this restriction is imposed.

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The chart also shows the altitude profile for minimum trip fuel as used to determine Short Trip Fuel and Time. Trip Fuel and Time Trip Fuel and Time charts are provided for Long Range Cruise and .79M at constant altitude to determine trip fuel and time from brake release to touchdown. A similar chart for a cost index of 30 (which approximates Long Range Cruise) is also shown. APU usage, taxi, inflight flaps down maneuvering (other than straight in approach) and reserve fuel should be added to the trip fuel obtained from the trip fuel and time charts to obtain the total fuel required. These fuel allowances are presented under Flight Planning Allowances. Additional fuel for extended inflight traffic delays should be determined from the holding table. To determine trip fuel and time enter the appropriate chart with trip ground distance, adjust for the anticipated wind condition, and proceed vertically to cruise pressure altitude. Trip fuel is read to the right from the lower set of altitude lines by going to the reference landing weight and adjusting to the planned landing weight using the guidelines. Trip time is read to the left from the upper altitude lines, adjusting for ISA deviation as necessary. For winds greater than those shown, enter chart directly with adjusted ground distance and ignore wind adjustment guidelines. Adjusted ground distance is ground distance multiplied by the ratio Average TAS/ (Average TAS + Wind Component), where headwind is negative and tailwind is positive. Step Climb Trip Fuel and Time Best fuel mileage is obtained if the flight is planned at optimum altitude for the cruise weight and speed schedule. Since optimum altitude increases as the airplane weight decreases, a step climb procedure bracketing optimum altitude is necessary. The Step Climb Planning charts provide trip fuel and time for LRC, .79M and cost index 30 from brake release to touchdown, similar to the constant altitude Trip Fuel and Time charts. The charts are based on 4000 ft step climbs to 2000 ft above optimum altitude. Short Trip Fuel and Time Short Trip Fuel and Time charts include fuel and time to climb to cruise altitude, cruise, descent and straight in approach. The charts are based on the cruise altitude for minimum trip fuel for the planned landing weight. For distances greater than 500 nm, or other altitudes, use the Trip Fuel and Time charts.

To determine fuel and time, enter the appropriate chart with ground distance, adjust for wind and proceed vertically to the planned landing weight. Trip fuel is read to the right from the lower set of landing weight curves. Trip time is read to the left from the upper curve and is valid for all landing weights. Holding Planning This table provides total fuel flow information necessary for planning holding and reserve fuel requirements. The chart is based on the higher of the maximum endurance speed and the maneuvering speed. The fuel flow is based upon flight in a racetrack holding pattern. For holding in straight and level flight reduce the table values by 5%. Fuel Tankering The Fuel Tankering table below is provided for LRC/ .79M cruise schedule based on a step climb procedure to bracket optimum altitude. When a fuel price differential exists between two stations, this table may be used to determine if fuel may be economically transported for a subsequent flight sector. Enter the table with the trip distance to read the breakeven fuel price ratio. As noted, the break-even fuel price is the fuel price at departure multiplied by the breakeven fuel price ratio. To justify tanker operation economically, the fuel price at destination must be greater than the break-even fuel price.

TRIP DISTANCE (NM) 200 400 600 800 1000 2000 3000 4000 BREAK-EVEN PRICE RATIO 1.015 1.032 1.046 1.062 1.078 1.179 1.313 1.500

Passenger Oxygen Requirements This airplane is equipped with a 12 minute or optional 22 minute chemical passenger oxygen system. The altitude envelope provided shows the maximum altitude that the airplane may be flown during a cabin depressurization event and still support the physiological requirements of the passengers using the oxygen system installed. The envelope is intended to assist in terrain clearance planning. The maximum altitude envelope assumes an immediate descent is made to 10000 ft or the lowest safe altitude whichever is higher as stipulated in the Emergency Descent procedure of the Quick Reference Handbook. Should the presence of terrain necessitate a level-off at an altitude higher than 10000 ft, the required terrain clearance descent profile should at no time exceed the

Copyright © The Boeing Company. See title page for details.

2.1.2

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737-800/CFM56-7B26 JAA/JAROPS Category C Brakes

FLIGHT PLANNING Text

Flight Planning and Performance Manual

maximum altitude capability of the passenger oxygen system shown by the envelope. Once terrain is cleared, the descent to 10000 ft should be completed. JAROPS rules allow the first 30 minutes the airplane is flown at altitudes at or below 14000 ft but above 10000 ft to be without additional supplemental passenger oxygen. Flight Crew Oxygen Requirements Regulations require that sufficient oxygen be provided to the flight crew to account for the greater of supplemental breathing oxygen in the event of a cabin depressurization or protective breathing in the event of smoke or harmful fumes in the flight deck. This airplane model is equipped with a 12 minute or optional 22 minute chemical passenger oxygen system which limits the extent to which the airplane can be operated at altitudes above 10000 ft following depressurization. As a result the flight crew supplemental oxygen quantity requirement is determined using the fixed maximum cabin altitude profile allowed by the passenger oxygen system. Consideration must also be given to protective breathing oxygen, which is the quantity of oxygen necessary for 15 minutes of pressurized 100% oxygen flow (Emergency setting) for each flight crew member in a fully pressurized cabin (8000 ft cabin pressure altitude). The greater quantity of either the supplemental or protective breathing requirements is used to determine the minimum dispatch cylinder pressures provided. An additional 10% of oxygen quantity is supplied by the values provided in the tables to account for normal system leakage, ancillary crew usage, and other contingencies. To determine the minimum dispatch oxygen cylinder pressure enter the flight crew oxygen table with the number of crew plus observers using oxygen and read the minimum cylinder pressure required for the appropriate cylinder temperature.

altitude, proceed to the ISA deviation and read weight. Adjust weight for anti-ice operation with the weight adjustment shown on the chart. Driftdown Profiles Net Flight Path These charts are provided to determine the time, fuel and distance from engine failure at any point during driftdown for legal enroute terrain clearance. Data is based on net performance, Max Continuous Thrust following engine failure and level flight deceleration to optimum driftdown speed (speed for optimum climb gradient). To determine driftdown time, fuel and distance, enter the appropriate chart with pressure altitude for terrain clearance (terrain height plus 2000 ft), move horizontally to equivalent weight at engine failure (adjusted for ISA deviation and anti-ice operation as indicated) and read fuel burned from the point of engine failure by interpolating between dashed lines. Read time and ground distance from point of engine failure by moving vertically downward from equivalent weight, adjusting distance for wind. Driftdown/LRC Cruise Range Capability This chart shows the range capability from the start of driftdown/cruise based on level off following driftdown and targeting the one engine inoperative Long Range Cruise speed. To determine the fuel required, enter the chart with the desired ground distance, adjust for the anticipated wind, and proceed vertically to the start of driftdown weight and read the fuel required to the right. The time required is read to the left from the single weight line on top. The chart may be used in reverse to determine the range capability knowing the fuel remaining from the start of driftdown.

ETOPS

Regulations require that flights conducted over a route that contains a point further than one hour's time at "normal one engine inoperative speed" from an adequate diversion airport comply with rules set up specifically for extended range operation with two engine airplanes. If the airplane meets these requirements, the approved Airplane Flight Manual (AFM) will contain a statement to this effect. This section provides the planning and inflight performance information necessary to conduct operations under these regulations. Information is presented for several different driftdown/cruise speed schedules. The information is based on drifting down using Max Continuous Thrust at the Mach number shown until reaching the corresponding airspeed and

Driftdown

Net Level Off Weight This chart is used to determine the maximum weight for terrain clearance based on the approved Airplane Flight Manual net engine inoperative performance at the speed for optimum climb gradient. Regulations require terrain clearance flight planning based on net performance which is the gross (or actual) gradient performance degraded by 1.1%. The net level off pressure altitude must clear the terrain by 1000 ft. To determine the maximum weight for terrain clearance, enter with net level off pressure

Copyright © The Boeing Company. See title page for details.

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D632A008-ZZ022

2.1.3

FLIGHT PLANNING Text

Flight Planning and Performance Manual

737-800/CFM56-7B26 JAA/JAROPS Category C Brakes

maintaining that airspeed throughout the remainder of the driftdown and level cruise. Based on route requirements, operators may select any one of these speeds for their operation, or may elect to use an entirely different speed which is not contained in this section. Flight Planning The following information is shown for flight planning purposes and is intended for use mainly by ground personnel. Data is included for five basic schedules (LRC, .76/280, .79/290, .79/310 and .79/330) throughout this section to allow the operator to evaluate the effect of using speeds up to 330 KIAS (VMO -10). Area of Operation (Diversion Distance) The maximum diversion distance used to establish the Area of Operation may be obtained from this chart. The Area of Operation is defined as the region within which the operator is authorized to conduct extended range operation. The distance to the diversion airport from any point along the intended route must be covered within the approved time using the single engine cruise speed (assuming still air and ISA conditions) selected by the operator. Enter the chart for the appropriate speed with the weight at the point of diversion using the speed schedule and time selected and read the maximum diversion distance. Critical Fuel Reserves Regulations require reserve planning to include a "Critical Fuel Scenario" calculation. The information shown is the fuel required to satisfy the flight profile as described on the charts. This information is shown for two engine operation at Long Range Cruise, as well as single engine operation at LRC, 280, 290, 310 and 330 KIAS. The fuel required is the greater of the two engine fuel and the single engine fuel for the speed schedule selected. This fuel is compared to the amount of fuel normally onboard the airplane at that point in the route. If the fuel required by the critical fuel reserves exceeds the amount of fuel normally expected, the fuel load must be adjusted accordingly. To determine the fuel required, enter the appropriate chart with the desired diversion distance, correct for the anticipated wind, proceed vertically to the weight at critical point and read the fuel required to the right. Adjustments for non-standard conditions are shown at the bottom of the page. The data does not include an allowance for performance deterioration. Regulations require a 5% allowance for performance deterioration unless a value has been

established by the operator for inservice deterioration. However, as noted on the chart, an additional 5% allowance is included in the chart to account for wind errors. Net Level Off Weight These charts are used to determine the maximum weight for terrain clearance based on net engine inoperative performance for the speed schedules shown and is for planning purposes only. Regulations require terrain clearance flight planning based on net performance which is the gross (or actual) gradient performance degraded by 1.1%. Net level off weight is determined by entering the appropriate chart at the left with the desired level off pressure altitude, adjusting for anti-ice as shown, proceeding across to the correct ISA deviation line and reading the allowable weight at the bottom. The net level off altitude may be obtained by entering the chart with weight and proceeding up to the correct ISA deviation line and reading across to the altitude on the left. Driftdown/Cruise Range Capability These charts show range capability from the start of driftdown/cruise when the driftdown/cruise procedure outlined in this section is followed. Charts are shown for each of the speed schedules discussed previously. To determine the fuel required, enter the appropriate chart with the desired ground distance, correct for the anticipated wind, and proceed vertically to the start of driftdown weight and read the fuel required to the right. The time required is read to the left from the single weight line on top. The chart may be used in reverse to determine the range capability knowing the fuel remaining from the start of driftdown.

Copyright © The Boeing Company. See title page for details.

2.1.4

D632A008-ZZ022

November 1, 2006

737-800/CFM56-7B26 JAA/JAROPS Category C Brakes

FLIGHT PLANNING Simplified Flight Planning

Flight Planning and Performance Manual

Simplified Flight Planning

2.2 FLIGHT PLANNING-Simplified Flight Planning Optimum Altitude

42 (1000 FT) 40 38 36 34 32 30

.79M

PRESSURE ALTITUDE

LRC

40

44

48

52

56 60 CRUISE WEIGHT 56

64 (1000 KG)

68

72

76

80

42

44

46

48

50

52

54

58 62 70 60 64 68 66 BRAKE RELEASE WEIGHT (1000 KG)

72

74

76

78

80

Short Trip Cruise Altitude

(1000 FT)

TIM

SE

PRESSURE ALTITUDE

UI

CR

15

10

20

20

5

30

1

E

(M

IN

UT

ES

40

)

Altitude Adjustments

PARAMETER PARAMETER WEIGHT ADJUSTMENT ADJUSTMENT -220 FT/500 KG ABOVE 45000 KG KG -220 FT/500 KG ABOVE 45000 -1300 FT/10°CBELOW 45000 KG +220 FT/500 KG ABOVE STD +700 FT/10°C BELOW STD HEAD: FT/10°C BELOW STD +700 -200 FT/10 KTS TAIL: -1500 FT/10KTS HEAD: -200 FT/10 KTS

TAIL: -1500 FT/1000 ORIG: +100 FT/10 KTS FT ELEVATION DEST: +200 FT/1000 FT FT ELEVATION ORIG: +100 FT/1000 ELEVATION DEST: +200 FT/1000 FT ELEVATION -1300 FT/10°C ABOVE STD

10

MINIMUM TRIP FUEL

TEMPERATURE WIND

WIND TEMPERATURE

WEIGHT

AIRPORT ELEVATION

AIRPORT ELEVATION

0 50 150 250 350

TRIP DISTANCE NAUTICAL MILES

Copyright © The Boeing Company. See title page for details.

November 1, 2006

D632A008-ZZ022

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FLIGHT PLANNING Simplified Flight Planning

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Simplified Flight Planning

737-800/CFM56-7B26 JAA/JAROPS Category C Brakes

Long Range Cruise Trip Fuel and Time

200 to 1000 NM

Based on 280/.78 climb and .78/280/250 descent

3

(HOURS)

2

TRIP TIME

PR

1 REF LINE

ES

S

E UR

T AL

ITU

DE

& 37

(10

AB

00

F

T)

25 29 33

OV

E

DE

(1

20 10 0 -10 ISA DEV (°C)

TU

FT

0

00

25 33 3 2927 1

6

37

&

AB

O

35 E V

5

0

)

PR

ES

SU

RE

AL

TI

4

PRESSURE 25 37 ALTITUDE (1000 FT)

3

2

1 REF LINE

0 HEAD 100 (KTS) 50 0 WIND 50 REF LINE 40 50 60 70 LANDING WEIGHT (1000 KG)

TAIL 100 200 400 TRIP DISTANCE

600 800 1000 (NAUTICAL GROUND MILES)

Copyright © The Boeing Company. See title page for details.

2.2.2

D632A008-ZZ022

November 1, 2006

FUEL REQUIRED (1000 KG)

737-800/CFM56-7B26 JAA/JAROPS Category C Brakes

FLIGHT PLANNING Simplified Flight Planning

Flight Planning and Performance Manual

Simplified Flight Planning

Long Range Cruise Trip Fuel and Time

1000 to 5000 NM

Based on 280/.78 climb and .78/280/250 descent

13 12 11

FT )

25

00

&

(HOURS)

9 8

ES

2 33 31 29 27 5

10

TI TU DE

AB O

VE

31

32

0

AL

(1

35

28

TRIP TIME

PR

FT

00

35

&

6 5 4 REF LINE

RE UD E (10

AB

)

OV E

7

SU RE

24 FUEL REQUIRED (1000 KG)

3 2

ES

SU

AL

TIT

20

PR

16 PRESSURE 25 ALTITUDE 37 (1000 FT) 12

20 10 0 -10 ISA DEV (°C)

8 REF LINE

4 HEAD 100 (KTS) 50 0 WIND 50 REF LINE 40 50 60 70 LANDING WEIGHT (1000 KG)

TAIL 100 1000 2000 TRIP DISTANCE

3000 4000 5000 (NAUTICAL GROUND MILES)

Copyright © The Boeing Company. See title page for details.

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Flight Planning and Performance Manual

Simplified Flight Planning

737-800/CFM56-7B26 JAA/JAROPS Category C Brakes

.79M Trip Fuel and Time

200 to 1000 NM Trip Distance

Based on 280/.78 climb and .78/280/250 descent

3

(HOURS)

2

8

TRIP TIME

ALT ALL

1 REF LINE

ITU

D

ES

25

7

0

00

35 33 31 29

27

6 FUEL REQUIRED (1000 KG)

20 10 0 -10 ISA DEV (°C)

DE

0

FT

)

37

(1

SU

RE

AL

TI

TU

5

5 RE 2 SSU PRE E 7 TUD ALTI FT) 3 000 (1

PR

ES

4

3

2 REF LINE

1 HEAD 100 (KTS) 50 0 WIND 50 REF LINE 40 50 60 70 LANDING WEIGHT (1000 KG)

TAIL 100 200 400 TRIP DISTANCE

600 800 1000 (NAUTICAL GROUND MILES)

Copyright © The Boeing Company. See title page for details.

2.2.4

D632A008-ZZ022

November 1, 2006

737-800/CFM56-7B26 JAA/JAROPS Category C Brakes

FLIGHT PLANNING Simplified Flight Planning

Flight Planning and Performance Manual

Simplified Flight Planning

.79M Trip Fuel and Time

1000 to 5000 NM Trip Distance

Based on 280/.78 climb and .78/280/250 descent

12 11 10

FT ) & VE AB O AL TI TU DE (1 00 0 35

9 (HOURS) 8 7 6 5 4 REF LINE

PR

25

31

TRIP TIME

25

SU RE

ES

33

31

27 29

32

28

FT

00

(10

3 2

35

&

AB

OV

)

E

24 FUEL REQUIRED (1000 KG)

RE

20 10 0 -10 ISA DEV (°C)

AL

TIT

UD

E

25

RE SSU PRE TUDE I ALT T) 0 F 100 (

37

20

PR

ES

SU

16

12

8 REF LINE

HEAD 100 (KTS) 50 0 WIND 50 REF LINE

4 40 50 60 70 LANDING WEIGHT (1000 KG)

TAIL 100 1000 2000 TRIP DISTANCE

3000 4000 5000 (NAUTICAL GROUND MILES)

Copyright © The Boeing Company. See title page for details.

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Flight Planning and Performance Manual

Simplified Flight Planning

737-800/CFM56-7B26 JAA/JAROPS Category C Brakes

Cost Index 30 Trip Fuel and Time

200 to 1000 NM Trip Distance

3

25

(HOURS)

2

TRIP TIME

1 REF LINE

33 3 29 2 25 1 7

PR

ES

S

DE VE ITU BO LT A &A E 35 UR

00 (10

FT

)

7

6

0 20 10 0 -10 ISA DEV (°C)

TU DE 00 (1

35

&

A

0

BO

5

AL

4 PRESSURE 25 ALTITUDE 37 (1000 FT) 3

2 REF LINE

1 HEAD 100 (KTS) 50 0 WIND 50 REF LINE 40 50 60 70 LANDING WEIGHT (1000 KG)

TAIL 100 200 400 TRIP DISTANCE

600 800 1000 (NAUTICAL GROUND MILES)

Copyright © The Boeing Company. See title page for details.

2.2.6

D632A008-ZZ022

November 1, 2006

FUEL REQUIRED (1000 KG)

PR

ES

SU

RE

TI

FT )

VE

737-800/CFM56-7B26 JAA/JAROPS Category C Brakes

FLIGHT PLANNING Simplified Flight Planning

Flight Planning and Performance Manual

Simplified Flight Planning

Cost Index 30 Trip Fuel and Time

1000 to 5000 NM Trip Distance

12 11 10

AB

O

VE

25

(HOURS)

AL

TI

TU

8

DE

(1

9

33 31 29 2725

FT

)

00

0

35

&

32

28

RE

TRIP TIME

SU

ES

FT )

PR

(10

00

35

6 5 4 REF LINE 3 2 20 10 0 -10 ISA DEV (°C)

&

AB

OV

7

E

24 FUEL REQUIRED (1000 KG)

TIT

UD

E

PR

ES

SU

RE

AL

20

16 PRESSURE 25 ALTITUDE 37 (1000 FT) 12

8 REF LINE

4 HEAD 100 (KTS) 50 0 WIND 50 REF LINE 40 50 60 70 LANDING WEIGHT (1000 KG)

TAIL 100 1000 2000 TRIP DISTANCE

3000 4000 5000 (NAUTICAL GROUND MILES)

Copyright © The Boeing Company. See title page for details.

November 1, 2006

D632A008-ZZ022

2.2.7

FLIGHT PLANNING Simplified Flight Planning

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Simplified Flight Planning

737-800/CFM56-7B26 JAA/JAROPS Category C Brakes

Long Range Cruise Step Climb Trip Fuel and Time

Based on 280/.78 climb, long range cruise and .78/280/250 descent

12 11 10 (HOURS) 9 8 7 6 5 4 3

LA ND I AL L W EI G HT S NG

TRIP TIME

70 65

60 55

REF LINE

)

KG

45

24

40

LA

12

8

4 HEAD 100 (KTS) 50 0 WIND 50 REF LINE

TAIL 100 1000

2000

3000

4000

5000

TRIP DISTANCE

(NAUTICAL GROUND MILES)

Copyright © The Boeing Company. See title page for details.

TRIP FUEL

16

(1000 KG)

ND

ING

WE

2 20 10 0 -10 ISA DEV (°C)

IGH

T

(10

00

50

28

20

2.2.8

D632A008-ZZ022

November 1, 2006

737-800/CFM56-7B26 JAA/JAROPS Category C Brakes

FLIGHT PLANNING Simplified Flight Planning

Flight Planning and Performance Manual

Simplified Flight Planning

.79M Step Climb Trip Fuel and Time

Based on 280/.78 climb and .78/280/250 descent

12 11 10 (HOURS) 9

TRIP TIME

7 6 5 4 3

AL L

LA ND

IN

G

W

EI G HT

8

S

70 65 60 55

REF LINE

KG

)

45

(°C)

50

HT (10 00

28

2 20 10 0 -10

ND

LA

12

8

4 HEAD 100 (KTS) 50 0 REF LINE 50

TAIL 100 1000

WIND

2000

3000

4000

5000

TRIP DISTANCE

(NAUTICAL GROUND MILES)

Copyright © The Boeing Company. See title page for details.

November 1, 2006

D632A008-ZZ022

TRIP FUEL

16

(1000 KG)

ING

WE

IG

ISA DEV

40

24

20

2.2.9

FLIGHT PLANNING Simplified Flight Planning

Flight Planning and Performance Manual

Simplified Flight Planning

737-800/CFM56-7B26 JAA/JAROPS Category C Brakes

Cost Index 30 Step Climb Trip Fuel and Time

12 11 10 (HOURS) 9 8

EI G LA ND IN G W

TRIP TIME

7 6

L

HT S

70 65 60

REF LINE

4 3

AL

KG

)

45

24

40

HT

ND

LA

12

8

4 HEAD 100 (KTS) 50 0 REF LINE 50

TAIL 100 1000

WIND

2000

3000

4000

5000

TRIP DISTANCE

(NAUTICAL GROUND MILES)

Copyright © The Boeing Company. See title page for details.

TRIP FUEL

16

(1000 KG)

2 20 10 0 -10 ISA DEV (°C)

(10

00

50

IN G WE IG

5

55

28

20

2.2.10

D632A008-ZZ022

November 1, 2006

737-800/CFM56-7B26 JAA/JAROPS Category C Brakes

FLIGHT PLANNING Simplified Flight Planning

Flight Planning and Performance Manual

Simplified Flight Planning

Long Range Cruise Short Trip Fuel and Time

Based on 280/.78 climb and .78/280/250 descent at short trip cruise altitude

1.4 1.2 (HOURS) 1.0 0.8 0.6 0.4 0.2 0.0 4

70 65 60 55 50 45 40

TRIP TIME

AL

L

LA

I ND

NG

W

EIG

HT

S

(10 W EI GH T

00

KG

)

LA

N

N DI

G

1

0 HEAD 100 (KTS) 50 0 REF LINE 50

TAIL 100

WIND

0

100 TRIP DISTANCE

200

300

400

500

(NAUTICAL GROUND MILES)

Copyright © The Boeing Company. See title page for details.

November 1, 2006

D632A008-ZZ022

TRIP FUEL

2

(1000 KG)

3

2.2.11

FLIGHT PLANNING Simplified Flight Planning

Flight Planning and Performance Manual

Simplified Flight Planning

737-800/CFM56-7B26 JAA/JAROPS Category C Brakes

Cost Index 30 Short Trip Fuel and Time

1.4 1.2 (HOURS) 1.0 0.8 0.6 0.4 0.2 0.0 4

AL L N LA NG IG WE S

HT

TRIP TIME

DI

(10 W EI GH T

00

KG

LA

I ND

1

0 HEAD 100 (KTS) 50 0 REF LINE 50

TAIL 100

WIND

0

100 TRIP DISTANCE

200

300

400

500

(NAUTICAL GROUND MILES)

Copyright © The Boeing Company. See title page for details.

2.2.12

D632A008-ZZ022

November 1, 2006

TRIP FUEL

NG

2

(1000 KG)

)

70 65 60 55 50 45 40

3

737-800/CFM56-7B26 JAA/JAROPS Category C Brakes

FLIGHT PLANNING Simplified Flight Planning

Flight Planning and Performance Manual

Simplified Flight Planning

Holding Planning

Flaps Up

PRESSURE ALTITUDE (FT) 41000 35000 30000 25000 20000 15000 10000 5000 1500 85 80 3130 2860 2790 2780 2830 2840 2870 2910 75 2800 2660 2600 2600 2650 2670 2700 2750 70 2550 2470 2420 2430 2480 2500 2540 2590 TOTAL FUEL FLOW (KG/HR) WEIGHT (1000 KG) 65 60 2330 2280 2230 2270 2310 2340 2370 2420 2130 2090 2050 2110 2140 2180 2210 2260 55 2110 1940 1910 1890 1940 1980 2010 2050 2100 50 1890 1770 1750 1730 1780 1810 1850 1890 1950 45 1670 1590 1590 1610 1640 1680 1690 1730 1790 40 1480 1420 1440 1450 1480 1520 1560 1620 1670

3080 2980 2970 2990 3020 3030 3080

This table includes 5% additional fuel for holding in a racetrack pattern.

Copyright © The Boeing Company. See title page for details.

November 1, 2006

D632A008-ZZ022

2.2.13

FLIGHT PLANNING Simplified Flight Planning

Flight Planning and Performance Manual

Simplified Flight Planning

737-800/CFM56-7B26 JAA/JAROPS Category C Brakes

Passenger Oxygen Requirements

Maximum Altitude Envelope

Based on 12 minute chemical system

40 (1000 FT)

41000 FT

30

PRESSURE ALTITUDE

20

17000 FT

30 MIN 14000 FT 10000 FT

10

0

0

1

2

3

4

5

6

7

8 TIME

9 10 11 (MINUTES)

12

13

40

41

42

43

The passenger oxygen system will provide sufficient supplemental breathing oxygen for altitudes at or below this envelope.

Maximum Altitude Envelope

Based on optional 22 minute chemical system

41000 FT

40 (1000 FT)

30

29000 FT 25000 FT

PRESSURE ALTITUDE

20 30 MIN 10 14000 FT 10000 FT

0

0

2

4

6

8

10

12

14

16

18

20

22

24

48

50

52

54

56

TIME

(MINUTES)

The passenger oxygen system will provide sufficient supplemental breathing oxygen for altitudes at or below this envelope.

Copyright © The Boeing Company. See title page for details.

2.2.14

D632A008-ZZ022

November 1, 2006

737-800/CFM56-7B26 JAA/JAROPS Category C Brakes

FLIGHT PLANNING Simplified Flight Planning

Flight Planning and Performance Manual

Simplified Flight Planning

Flight Crew Oxygen Requirements

Required Pressure (PSI) for 76 Cubic Ft. Cylinder

BOTTLE TEMPERATURE °C °F 50 122 45 113 40 104 35 95 30 86 25 77 20 68 15 59 10 50 5 41 0 32 -5 23 -10 14 BOTTLE TEMPERATURE °C °F 50 122 45 113 40 104 35 95 30 86 25 77 20 68 15 59 10 50 5 41 0 32 -5 23 -10 14 2 735 725 715 700 690 680 670 655 645 635 620 610 600 NUMBER OF CREW USING OXYGEN 3 1055 1040 1020 1005 990 975 960 940 925 910 890 875 860 NUMBER OF CREW USING OXYGEN 3 735 725 715 700 690 680 670 655 645 635 620 610 600 4 1360 1340 1320 1300 1280 1255 1240 1215 1195 1175 1150 1130 1110

Required Pressure (PSI) for 114/115 Cubic Ft. Cylinder

2 530 520 510 505 495 485 480 470 460 455 445 440 430 4 945 930 915 900 885 870 860 840 830 815 800 785 770

Copyright © The Boeing Company. See title page for details.

November 1, 2006

D632A008-ZZ022

2.2.15

FLIGHT PLANNING Simplified Flight Planning

Flight Planning and Performance Manual

737-800/CFM56-7B26 JAA/JAROPS Category C Brakes

Intentionally Blank

Copyright © The Boeing Company. See title page for details.

2.2.16

D632A008-ZZ022

November 1, 2006

737-800/CFM56-7B26 JAA/JAROPS Category C Brakes

FLIGHT PLANNING Driftdown

Flight Planning and Performance Manual

2.3 FLIGHT PLANNING-Driftdown

ENGINE INOP

MAX CONTINUOUS THRUST

Driftdown

Net Level Off Weight

30 28 26 24 (1000 FT) 22 20 18 16 14 12 10 8 6

ISA DE VIA 0 ° C & TION +1 5 ° BELO W C +2 0 ° C

+1

PRESSURE ALTITUDE

40

44

48

52

56

60 WEIGHT

64 (1000 KG)

68

72

76

80

84

Anti-Ice Adjustments

ANTI-ICE CONFIGURATION ENGINE ONLY ENGINE AND WING 12 -1.9 -7.5 14 -1.8 -6.9 16 -1.7 -6.6 LEVEL OFF WEIGHT ADJUSTMENT (1000 KG) PRESSURE ALTITUDE (1000 FT) 18 20 22 -1.7 -1.6 -1.5 -6.5 -6.3 -5.8 24 -1.4 -5.2 26 -1.2 -4.8 28 -1.1

Copyright © The Boeing Company. See title page for details.

November 1, 2006

D632A008-ZZ022

2.3.1

FLIGHT PLANNING Driftdown

Flight Planning and Performance Manual

737-800/CFM56-7B26 JAA/JAROPS Category C Brakes

ENGINE INOP

MAX CONTINUOUS THRUST

Driftdown

Driftdown Profiles Net Flight Path

39000 FT & Above

40 85 80 WEIGHT AT ENGINE FAILURE (1000 KG) EQUIVALENT WEIGHT AT ENGINE FAILURE (1000 KG) 40 45 50 25 55 60 20

50

85 80 75 70 65 60 55 50 45 20 40 EQUIVALENT WEIGHT AT ENGINE FAILURE (1000 KG)

26 1.2 4.8

35

75 70 65 60 55 50 45

PRESSURE ALTITUDE

(1000 FT)

30

65 70

40 10 15 & BELOW ISA DEV

0

(°C)

15

10 0 HEAD 100 (KTS) 50

EN EL G BU IN E RN (K FA FR G IL UR OM ) E

10

FU

00

75 80

00 20 00

15

85

00

25

00

10

20

30

40

50

30

60

70 (MIN)

TIME FROM ENGINE FAILURE

WIND

0 REF LINE 50 0 100 200 300 400 500 (NM)

TAIL 100

GROUND DISTANCE FROM ENGINE FAILURE

Anti-Ice Adjustments

ANTI-ICE CONFIGURATION ENGINE ONLY ENGINE AND WING 12 1.9 7.5 14 1.8 6.9 16 1.7 6.6 EQUIVALENT WEIGHT ADJUSTMENT (1000 KG) PRESSURE ALTITUDE (1000 FT) 18 20 22 1.7 1.6 1.5 6.5 6.3 5.8 24 1.4 5.2 28 1.1

Copyright © The Boeing Company. See title page for details.

2.3.2

D632A008-ZZ022

November 1, 2006

737-800/CFM56-7B26 JAA/JAROPS Category C Brakes

FLIGHT PLANNING Driftdown

Flight Planning and Performance Manual

ENGINE INOP

MAX CONTINUOUS THRUST

Driftdown

Driftdown Profiles Net Flight Path

35000 FT to 37000 FT

35 WEIGHT AT ENGINE FAILURE (1000 KG) 40 30 (1000 FT) EQUIVALENT WEIGHT AT ENGINE FAILURE (1000 KG) 45 50 25 55 60 20

0

85 80 75 70 65 60 55 50 45 70 75 40 10 15 & BELOW 80

00 00

85 80 75 70 65 60 55 50 45 20 40 EQUIVALENT WEIGHT AT ENGINE FAILURE (1000 KG)

28 1.1

PRESSURE ALTITUDE

65

50

15

10 0 HEAD 100 (KTS) 50

FU EN EL G BU IN E RN (K FA FR G IL UR OM ) E

10

00

ISA DEV

(°C)

15

20

85

00

25

00

10

20

30

40

50

30

60

70 (MIN)

TIME FROM ENGINE FAILURE

WIND

0 REF LINE 50 0 100 200 300 400 500 (NM)

TAIL 100

GROUND DISTANCE FROM ENGINE FAILURE

Anti-Ice Adjustments

ANTI-ICE CONFIGURATION ENGINE ONLY ENGINE AND WING 12 1.9 7.5 14 1.8 6.9 16 1.7 6.6 EQUIVALENT WEIGHT ADJUSTMENT (1000 KG) PRESSURE ALTITUDE (1000 FT) 18 20 22 1.7 1.6 1.5 6.5 6.3 5.8 24 1.4 5.2 26 1.2 4.8

Copyright © The Boeing Company. See title page for details.

November 1, 2006

D632A008-ZZ022

2.3.3

FLIGHT PLANNING Driftdown

Flight Planning and Performance Manual

737-800/CFM56-7B26 JAA/JAROPS Category C Brakes

ENGINE INOP

MAX CONTINUOUS THRUST

Driftdown

Driftdown Profiles Net Flight Path

31000 FT to 33000 FT

85 WEIGHT AT ENGINE FAILURE (1000 KG) 30 45 EQUIVALENT WEIGHT AT ENGINE FAILURE (1000 KG) 50 (1000 FT) 25 55 60 20

0 50

85 EQUIVALENT WEIGHT AT ENGINE FAILURE (1000 KG)

28 1.1

80 75 70 65 60 55 50 20

80 75 70 65 60 55 50 45

PRESSURE ALTITUDE

65 70 75

10

15

10 0 HEAD 100 (KTS) 50

EN EL G BU IN E RN (K FA FR G IL UR OM ) E

FU

80

00

45 10 15 & BELOW ISA DEV

00

20

00

85

00

15

(°C)

00 25

10

20

30

40

50

30

60

70 (MIN)

TIME FROM ENGINE FAILURE

WIND

0 REF LINE 50 0 100 200 300 400 500 (NM)

TAIL 100

GROUND DISTANCE FROM ENGINE FAILURE

Anti-Ice Adjustments

ANTI-ICE CONFIGURATION ENGINE ONLY ENGINE AND WING 12 1.9 7.5 14 1.8 6.9 16 1.7 6.6 EQUIVALENT WEIGHT ADJUSTMENT (1000 KG) PRESSURE ALTITUDE (1000 FT) 18 20 22 1.7 1.6 1.5 6.5 6.3 5.8 24 1.4 5.2 26 1.2 4.8

Copyright © The Boeing Company. See title page for details.

2.3.4

D632A008-ZZ022

November 1, 2006

737-800/CFM56-7B26 JAA/JAROPS Category C Brakes

FLIGHT PLANNING Driftdown

Flight Planning and Performance Manual

ENGINE INOP

MAX CONTINUOUS THRUST

Driftdown

Driftdown Profiles Net Flight Path

27000 FT to 29000 FT

85 WEIGHT AT ENGINE FAILURE (1000 KG) 50 25 (1000 FT) 55 60 20

0 50

85 80 75 70 65 60 55 20 50 EQUIVALENT WEIGHT AT ENGINE FAILURE (1000 KG)

28 1.1

EQUIVALENT WEIGHT AT ENGINE FAILURE (1000 KG)

80 75 70 65 60 55

65 70 75

00

PRESSURE ALTITUDE

15

10 0 HEAD 100 (KTS) 50

FU EN EL G BU IN E RN (K FA FR G IL UR OM ) E

10

80

00

00

85

00

20

50 10 15 & BELOW ISA DEV

15

00

(°C)

25

10

20

30

40

30

50

60

70 (MIN)

80

TIME FROM ENGINE FAILURE

WIND

0 REF LINE 50 0 100 200 300 400 500 (NM)

TAIL 100

GROUND DISTANCE FROM ENGINE FAILURE

Anti-Ice Adjustments

ANTI-ICE CONFIGURATION ENGINE ONLY ENGINE AND WING 12 1.9 7.5 14 1.8 6.9 16 1.7 6.6 EQUIVALENT WEIGHT ADJUSTMENT (1000 KG) PRESSURE ALTITUDE (1000 FT) 18 20 22 1.7 1.6 1.5 6.5 6.3 5.8 24 1.4 5.2 26 1.2 4.8

Copyright © The Boeing Company. See title page for details.

November 1, 2006

D632A008-ZZ022

2.3.5

FLIGHT PLANNING Driftdown

Flight Planning and Performance Manual

737-800/CFM56-7B26 JAA/JAROPS Category C Brakes

ENGINE INOP

MAX CONTINUOUS THRUST

Driftdown

Driftdown/LRC Cruise Range Capability

Includes APU fuel burn

5 (HOURS) TIME FROM START OF DRIFTDOWN

4

3

2

70

12

1

00 KG )

65

60

0

N W EI

0 (1 GH T

55

10

50

45

40

6 8

A ST

RT

I DR

FT

D

OW

4

2

0 HEAD 100 (KTS) 50 0 REF LINE 50 400 600 800 1000 1200 1400 1600 1800

TAIL 100 200

WIND

DISTANCE

(NAUTICAL GROUND MILES)

Copyright © The Boeing Company. See title page for details.

2.3.6

D632A008-ZZ022

November 1, 2006

FUEL FROM START OF DRIFTDOWN

(1000 KG)

AL

L

A ST

RT

D

RIF

O TD

WN

W

EIG

HT

S

85

16

80

75

14

737-800/CFM56-7B26 JAA/JAROPS Category C Brakes

FLIGHT PLANNING ETOPS

Flight Planning and Performance Manual

2.4 FLIGHT PLANNING-ETOPS

ENGINE INOP

MAX CONTINUOUS THRUST

ETOPS

Area of Operation

Based on standard day and driftdown starting at or near optimum altitude.

SPEED (M/KIAS) .76/280 WEIGHT AT DIVERSION (1000 KG) 85 80 75 70 65 60 55 50 45 40 85 80 75 70 65 60 55 50 45 40 85 80 75 70 65 60 55 50 45 40 85 80 75 70 65 60 55 50 45 40 85 80 75 70 65 60 55 50 45 40 60 383 388 393 398 402 406 410 414 416 417 393 396 402 406 409 414 418 420 421 421 407 410 415 419 422 425 428 429 429 429 419 421 425 428 430 432 433 435 434 433 397 393 391 390 385 383 382 379 373 366 70 445 450 456 462 466 471 476 480 483 484 455 460 466 471 475 480 485 487 489 489 472 476 482 486 490 494 497 499 499 499 485 488 493 496 499 501 502 504 503 503 460 456 454 452 447 444 443 440 433 425 80 506 512 519 526 531 536 542 547 550 551 518 523 531 537 541 547 552 555 557 558 537 542 548 554 558 562 566 568 568 568 551 555 561 565 567 570 572 574 573 573 523 519 517 514 508 505 503 501 493 484 90 567 575 582 590 595 602 608 613 617 619 581 587 595 602 607 613 619 622 625 626 602 607 615 621 626 631 635 637 638 638 617 623 629 633 636 639 641 644 643 642 586 582 579 576 569 566 564 561 553 543 100 628 637 645 654 660 667 674 680 684 686 643 651 660 667 673 680 686 690 693 694 667 673 681 688 694 699 703 706 707 707 684 690 696 701 705 708 711 713 713 712 648 644 641 637 630 627 625 621 613 602 110 690 699 709 718 725 732 740 746 751 753 706 714 725 732 738 746 753 757 761 762 732 738 748 755 762 768 772 776 776 777 750 757 764 770 774 777 780 783 782 782 711 707 703 699 691 687 685 681 672 661 DIVERSION DISTANCE (NM) TIME (MINUTES) 120 130 140 751 812 874 762 824 886 772 835 898 781 845 909 789 854 918 798 863 928 806 872 938 813 879 946 818 884 951 820 888 955 769 831 894 778 841 905 789 854 918 798 863 928 804 870 936 813 879 946 820 887 954 825 892 960 828 896 964 830 898 966 796 861 926 804 870 935 814 881 947 823 890 957 830 898 966 837 905 974 841 910 979 845 914 983 846 915 985 847 916 986 816 883 949 824 891 958 832 900 967 838 906 975 842 911 980 847 916 985 850 919 989 853 922 992 852 922 992 851 921 991 773 836 898 769 831 893 765 827 889 760 822 883 752 813 874 748 808 868 745 805 865 741 801 860 731 790 849 719 778 836 150 935 949 961 973 983 994 1004 1012 1018 1022 956 969 983 993 1002 1012 1021 1027 1032 1034 991 1001 1013 1024 1034 1042 1048 1053 1054 1055 1015 1025 1035 1043 1049 1054 1058 1062 1061 1060 960 955 950 944 934 928 925 920 908 894 160 996 1011 1024 1037 1048 1059 1070 1079 1085 1089 1019 1032 1047 1059 1068 1079 1088 1095 1100 1102 1056 1066 1080 1092 1102 1111 1117 1122 1124 1125 1081 1092 1103 1111 1117 1123 1127 1131 1131 1130 1022 1017 1012 1005 995 988 985 979 967 952 170 1057 1073 1087 1101 1112 1124 1136 1145 1152 1157 1082 1096 1112 1124 1134 1145 1155 1162 1168 1170 1120 1132 1146 1159 1170 1180 1186 1191 1193 1194 1148 1159 1171 1180 1186 1192 1197 1201 1201 1199 1084 1079 1073 1066 1055 1048 1045 1039 1026 1010 180 1119 1136 1150 1165 1177 1189 1202 1212 1219 1224 1144 1159 1176 1189 1200 1212 1222 1230 1235 1238 1185 1198 1213 1226 1238 1248 1255 1260 1263 1264 1214 1226 1238 1248 1255 1261 1266 1271 1271 1269 1146 1140 1134 1127 1115 1108 1104 1098 1084 1068 190 1180 1198 1213 1229 1241 1255 1268 1279 1286 1291 1207 1223 1241 1254 1265 1278 1289 1297 1303 1306 1250 1264 1279 1293 1306 1317 1324 1330 1332 1333 1280 1293 1306 1316 1324 1331 1336 1340 1340 1338 1207 1202 1195 1187 1176 1168 1164 1157 1143 1126 200 1241 1260 1277 1292 1306 1320 1334 1345 1353 1358 1270 1287 1305 1319 1331 1345 1357 1365 1371 1374 1315 1329 1346 1361 1374 1385 1393 1399 1401 1403 1346 1360 1374 1385 1392 1400 1405 1410 1410 1408 1269 1263 1256 1248 1236 1227 1223 1216 1201 1183

.79/290

.79/310

.79/330

LRC

Copyright © The Boeing Company. See title page for details.

November 1, 2006

D632A008-ZZ022

2.4.1

FLIGHT PLANNING ETOPS

Flight Planning and Performance Manual

737-800/CFM56-7B26 JAA/JAROPS Category C Brakes

ALL ENGINES

Long Range Cruise Critical Fuel Reserves

Based on: Emergency descent to 10000 ft Level cruise at 10000 ft 250 KIAS descent to 1500 ft 15 minute hold at 1500 ft One missed approach, approach and land 5% allowance for wind errors Includes APU fuel burn

18

85 80 75 70 65 60 55 50 45

16

14

(1 PO T IN

0 00

10

W

G EI

HT

AT

CR

I

TI

8

6

4

2

0 HEAD 100 (KTS) 50 0 REF LINE 50 400 600 800 1000 1200 1400 1600 (NM) 1800

TAIL 100 200

WIND

DISTANCE TO DIVERSION AIRPORT FROM CRITICAL POINT

Increase fuel required by 0.5% for each 10°C hotter than ISA conditions. If icing conditions exist, increase fuel required by 15% to account for engine and wing anti-ice on (7%) and ice accumulation on unheated surfaces (8%). Allowance for performance deterioration not included. Compare the fuel required for all engine and engine inoperative critical fuel reserves and use the higher of the two.

Copyright © The Boeing Company. See title page for details.

2.4.2

D632A008-ZZ022

FUEL REQUIRED

L CA

(1000 KG)

KG

)

12

November 1, 2006

737-800/CFM56-7B26 JAA/JAROPS Category C Brakes

FLIGHT PLANNING ETOPS

Flight Planning and Performance Manual

ENGINE INOP

MAX CONTINUOUS THRUST

Long Range Cruise Critical Fuel Reserves

Based on: Emergency descent to 10000 ft Level cruise at 10000 ft 250 KIAS descent to 1500 ft 15 minute hold at 1500 ft One missed approach, approach and land 5% allowance for wind errors Includes APU fuel burn

18

(1 PO IN T

W

EI

G

HT

AT

C

8

6

4

2

0 HEAD 100 (KTS) 50 0 REF LINE 50 400 600 800 1000 1200 1400 1600 (NM) 1800

TAIL 100 200

WIND

DISTANCE TO DIVERSION AIRPORT FROM CRITICAL POINT

Increase fuel required by 0.5% for each 10°C hotter than ISA conditions. If icing conditions exist, increase fuel required by 15% to account for engine and wing anti-ice on (6%) and ice accumulation on unheated surfaces (9%). Allowance for performance deterioration not included. Compare the fuel required for all engine and engine inoperative critical fuel reserves and use the higher of the two.

Copyright © The Boeing Company. See title page for details.

November 1, 2006

D632A008-ZZ022

FUEL REQUIRED

T RI

IC

AL

10

(1000 KG)

0 00

KG

)

85 80 75 70 65 60 55 50 45

16

14

12

2.4.3

FLIGHT PLANNING ETOPS

Flight Planning and Performance Manual

737-800/CFM56-7B26 JAA/JAROPS Category C Brakes

ENGINE INOP

MAX CONTINUOUS THRUST

280 KIAS Cruise Critical Fuel Reserves

Based on: Emergency descent to 10000 ft Level cruise at 10000 ft 250 KIAS descent to 1500 ft 15 minute hold at 1500 ft One missed approach, approach and land 5% allowance for wind errors Includes APU fuel burn

18

85 80 75 70 65 60 55 50 45

16

14

12

00 0 KG )

(1 PO IN T

10

W

EI

G

HT

AT

C

T RI

IC

AL

8

6

4

2

0 HEAD 100 (KTS) 50 0 REF LINE 50 400 600 800 1000 1200 1400 1600 (NM) 1800

TAIL 100 200

WIND

DISTANCE TO DIVERSION AIRPORT FROM CRITICAL POINT

Increase fuel required by 0.5% for each 10°C hotter than ISA conditions. If icing conditions exist, increase fuel required by 16% to account for engine and wing anti-ice on (6%) and ice accumulation on unheated surfaces (10%). Allowance for performance deterioration not included. Compare the fuel required for all engine and engine inoperative critical fuel reserves and use the higher of the two.

Copyright © The Boeing Company. See title page for details.

2.4.4

D632A008-ZZ022

November 1, 2006

FUEL REQUIRED

(1000 KG)

737-800/CFM56-7B26 JAA/JAROPS Category C Brakes

FLIGHT PLANNING ETOPS

Flight Planning and Performance Manual

ENGINE INOP

MAX CONTINUOUS THRUST

290 KIAS Cruise Critical Fuel Reserves

Based on: Emergency descent to 10000 ft Level cruise at 10000 ft 250 KIAS descent to 1500 ft 15 minute hold at 1500 ft One missed approach, approach and land 5% allowance for wind errors Includes APU fuel burn

18

85 80 75 70 65 60 55 50 45

16

14

(1 PO T IN

0

00

10

W

EI

G

HT

AT

CR

IT

I

8

6

4

2

0 HEAD 100 (KTS) 50 0 REF LINE 50 400 600 800 1000 1200 1400 1600 (NM) 1800

TAIL 100 200

WIND

DISTANCE TO DIVERSION AIRPORT FROM CRITICAL POINT

Increase fuel required by 0.5% for each 10°C hotter than ISA conditions. If icing conditions exist, increase fuel required by 16% to account for engine and wing anti-ice on (6%) and ice accumulation on unheated surfaces (10%). Allowance for performance deterioration not included. Compare the fuel required for all engine and engine inoperative critical fuel reserves and use the higher of the two.

Copyright © The Boeing Company. See title page for details.

November 1, 2006

D632A008-ZZ022

FUEL REQUIRED

L CA

(1000 KG)

KG

)

12

2.4.5

FLIGHT PLANNING ETOPS

Flight Planning and Performance Manual

737-800/CFM56-7B26 JAA/JAROPS Category C Brakes

ENGINE INOP

MAX CONTINUOUS THRUST

310 KIAS Cruise Critical Fuel Reserves

Based on: Emergency descent to 10000 ft Level cruise at 10000 ft 250 KIAS descent to 1500 ft 15 minute hold at 1500 ft One missed approach, approach and land 5% allowance for wind errors Includes APU fuel burn

18

85

75 65 55

16

45

14

(1 PO IN T

W

EI

G

HT

AT

8

6

4

2

0 HEAD 100 (KTS) 50 0 REF LINE 50 400 600 800 1000 1200 1400 1600 (NM) 1800

TAIL 100 200

WIND

DISTANCE TO DIVERSION AIRPORT FROM CRITICAL POINT

Increase fuel required by 0.5% for each 10°C hotter than ISA conditions. If icing conditions exist, increase fuel required by 17% to account for engine and wing anti-ice on (5%) and ice accumulation on unheated surfaces (12%). Allowance for performance deterioration not included. Compare the fuel required for all engine and engine inoperative critical fuel reserves and use the higher of the two.

Copyright © The Boeing Company. See title page for details.

2.4.6

D632A008-ZZ022

November 1, 2006

FUEL REQUIRED

I CR

TI

CA

L

10

(1000 KG)

0 00

KG

)

12

737-800/CFM56-7B26 JAA/JAROPS Category C Brakes

FLIGHT PLANNING ETOPS

Flight Planning and Performance Manual

ENGINE INOP

MAX CONTINUOUS THRUST

330 KIAS Cruise Critical Fuel Reserves

Based on: Emergency descent to 10000 ft Level cruise at 10000 ft 250 KIAS descent to 1500 ft 15 minute hold at 1500 ft One missed approach, approach and land 5% allowance for wind errors Includes APU fuel burn

18

85 75 65 55

16

14

W

EI

G

HT

AT

8

6

4

2

0 HEAD 100 (KTS) 50 0 REF LINE 50 400 600 800 1000 1200 1400 1600 (NM) 1800

TAIL 100 200

WIND

DISTANCE TO DIVERSION AIRPORT FROM CRITICAL POINT

Increase fuel required by 0.5% for each 10°C hotter than ISA conditions. If icing conditions exist, increase fuel required by 18% to account for engine and wing anti-ice on (5%) and ice accumulation on unheated surfaces (13%). Allowance for performance deterioration not included. Compare the fuel required for all engine and engine inoperative critical fuel reserves and use the higher of the two.

Copyright © The Boeing Company. See title page for details.

November 1, 2006

D632A008-ZZ022

FUEL REQUIRED

CR

IT

IC

AL

PO

I

NT

10

(1000 KG)

(1

0

00

KG

)

12

2.4.7

FLIGHT PLANNING ETOPS

Flight Planning and Performance Manual

737-800/CFM56-7B26 JAA/JAROPS Category C Brakes

ENGINE INOP

MAX CONTINUOUS THRUST

Long Range Cruise Net Level Off Weight

32

28

24

(1000 FT)

20

N IO W AT O VI EL DE & B A °C IS °C 15 C 10 + 20° + +

PRESSURE ALTITUDE

16

12

8

4

0 40 50 60 WEIGHT 70 (1000 KG) 80 90

Anti-Ice Adjustments

ANTI-ICE CONFIGURATION ENGINE ONLY ENGINE AND WING 8 -2.5 -8.9 10 -2.4 -8.7 12 -2.3 -8.2 LEVEL OFF WEIGHT ADJUSTMENT (1000 KG) PRESSURE ALTITUDE (1000 FT) 14 16 18 20 22 -2.2 -2.1 -1.9 -1.7 -1.6 -7.6 -7.2 -6.9 -6.6 -6.0 24 -1.5 -5.4 26 -1.3 -5.1 28 -1.2 -4.8

Copyright © The Boeing Company. See title page for details.

2.4.8

D632A008-ZZ022

November 1, 2006

737-800/CFM56-7B26 JAA/JAROPS Category C Brakes

FLIGHT PLANNING ETOPS

Flight Planning and Performance Manual

ENGINE INOP

MAX CONTINUOUS THRUST

280 KIAS Net Level Off Weight

28

24

20 (1000 FT)

PRESSURE ALTITUDE

16

IS A + 1 DE 0°C VI & ATIO BE +1 LO N 5° W C +2 0°C

12

8

4

0 40 50 60 WEIGHT 70 (1000 KG) 80 90

Anti-Ice Adjustments

ANTI-ICE CONFIGURATION ENGINE ONLY ENGINE AND WING 8 -2.7 -12.3 10 -3.1 -13.7 LEVEL OFF WEIGHT ADJUSTMENT (1000 KG) PRESSURE ALTITUDE (1000 FT) 12 14 16 -4.1 -4.4 -4.7 -16.6 -19.7 -24.9 18 -5.5 -23.8 20 -5.4 -23.4

Copyright © The Boeing Company. See title page for details.

November 1, 2006

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ENGINE INOP

MAX CONTINUOUS THRUST

290 KIAS Net Level Off Weight

24

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ANTI-ICE CONFIGURATION ENGINE ONLY ENGINE AND WING 8 -3.6 -15.3 10 -3.9 -16.4 LEVEL OFF WEIGHT ADJUSTMENT (1000 KG) PRESSURE ALTITUDE (1000 FT) 12 14 -4.8 -5.7 -19.1 -20.5 16 -6.4 -18.7 18 -6.2 -22.7

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Flight Planning and Performance Manual

ENGINE INOP

MAX CONTINUOUS THRUST

310 KIAS Net Level Off Weight

20

16 (1000 FT)

ISA + 1 DE 0°C VIA & B TIO EL N OW +1 5°C

+2 0°C

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Anti-Ice Adjustments

ANTI-ICE CONFIGURATION ENGINE ONLY ENGINE AND WING 6 -4.5 -18.5 8 -5.0 -20.1 LEVEL OFF WEIGHT ADJUSTMENT (1000 KG) PRESSURE ALTITUDE (1000 FT) 10 12 -5.1 -7.2 -22.5 -25.6 14 -9.3 -30.7 16 -8.7

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ENGINE INOP

MAX CONTINUOUS THRUST

330 KIAS Net Level Off Weight

20

16 (1000 FT) PRESSURE ALTITUDE 12

ISA + 1 DEV 0°C IA & B TION EL OW +1 5°C

8

+2

4

0°C

0 40 50 60 WEIGHT 70 (1000 KG) 80 90

Anti-Ice Adjustments

ANTI-ICE CONFIGURATION ENGINE ONLY ENGINE AND WING 6 -5.7 -23.6 LEVEL OFF WEIGHT ADJUSTMENT (1000 KG) PRESSURE ALTITUDE (1000 FT) 8 -7.2 -37.8 10 -8.7

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Flight Planning and Performance Manual

ENGINE INOP

MAX CONTINUOUS THRUST

Long Range Cruise Driftdown/Cruise Range Capability

Includes APU fuel burn

5 (HOURS) TIME FROM START OF DRIFTDOWN

4

HT S

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FLIGHT PLANNING ETOPS

Flight Planning and Performance Manual

737-800/CFM56-7B26 JAA/JAROPS Category C Brakes

ENGINE INOP

MAX CONTINUOUS THRUST

.76M/280 KIAS Driftdown/Cruise Range Capability

Includes APU fuel burn

5 (HOURS) TIME FROM START OF DRIFTDOWN

4

TS

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(NAUTICAL GROUND MILES)

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FLIGHT PLANNING ETOPS

Flight Planning and Performance Manual

ENGINE INOP

MAX CONTINUOUS THRUST

.79M/290 KIAS Driftdown/Cruise Range Capability

Includes APU fuel burn

5 (HOURS) TIME FROM START OF DRIFTDOWN

4 16 3

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(NAUTICAL GROUND MILES)

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FLIGHT PLANNING ETOPS

Flight Planning and Performance Manual

737-800/CFM56-7B26 JAA/JAROPS Category C Brakes

ENGINE INOP

MAX CONTINUOUS THRUST

.79M/310 KIAS Driftdown/Cruise Range Capability

Includes APU fuel burn

5 (HOURS) TIME FROM START OF DRIFTDOWN

4 16 3

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(NAUTICAL GROUND MILES)

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FUEL FROM START OF DRIFTDOWN

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737-800/CFM56-7B26 JAA/JAROPS Category C Brakes

FLIGHT PLANNING ETOPS

Flight Planning and Performance Manual

ENGINE INOP

MAX CONTINUOUS THRUST

.79M/330 KIAS Driftdown/Cruise Range Capability

Includes APU fuel burn

5 (HOURS) TIME FROM START OF DRIFTDOWN

4

90

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(NAUTICAL GROUND MILES)

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ENROUTE Table of Contents

Flight Planning and Performance Manual

ENROUTE

Table of Contents

Chapter 3

3.0 ENROUTE-Table of . . . . Text . . . . . . . .Contents . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3.1.1

Introduction . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3.1.1 All Engines . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3.1.1 Engine Inoperative . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3.1.1 All Engine . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3.2.1 Long Range Cruise Maximum Operating Altitude 280/.78 Enroute Climb . . . . . . . . . . . . . . . . . . . . Long Range Cruise Enroute Fuel and Time . . . . . Long Range Cruise Table . . . . . . . . . . . . . . . . . . .79M Cruise Table . . . . . . . . . . . . . . . . . . . . . . . Wind-Altitude Trade . . . . . . . . . . . . . . . . . . . . . Descent . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Holding . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3.2.1 . 3.2.2 . 3.2.6 . 3.2.8 3.2.14 3.2.16 3.2.17 3.2.18

Engine Inoperative . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3.3.1 Speed Capability . . . . . . . . . . . . . . . . . . . . . Long Range Cruise Altitude Capability . . . . 280 KIAS Altitude Capability . . . . . . . . . . . 290 KIAS Altitude Capability . . . . . . . . . . . 310 KIAS Altitude Capability . . . . . . . . . . . 330 KIAS Altitude Capability . . . . . . . . . . . Long Range Cruise Table . . . . . . . . . . . . . . . 280 KIAS Cruise Table . . . . . . . . . . . . . . . . 290 KIAS Cruise Table . . . . . . . . . . . . . . . . 310 KIAS Cruise Table . . . . . . . . . . . . . . . . 330 KIAS Cruise Table . . . . . . . . . . . . . . . . Long Range Cruise Diversion Fuel and Time 280 KIAS Diversion Fuel and Time . . . . . . . 290 KIAS Diversion Fuel and Time . . . . . . . 310 KIAS Diversion Fuel and Time . . . . . . . 330 KIAS Diversion Fuel and Time . . . . . . . Holding . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3.3.1 . 3.3.2 . 3.3.3 . 3.3.4 . 3.3.5 . 3.3.6 . 3.3.7 3.3.11 3.3.13 3.3.15 3.3.17 3.3.19 3.3.20 3.3.21 3.3.22 3.3.23 3.3.24

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Text

ENROUTE Text

Flight Planning and Performance Manual

3.1 ENROUTE-Text Introduction

Wind-Altitude Trade Wind is a factor which may justify operations considerably above or below optimum altitude. For example, a favorable wind component may have an effect on ground speed which more than compensates for the loss in air range. Using the applicable table, it is possible to determine the break-even wind (advantage necessary or disadvantage that can be tolerated) to maintain the same range at another altitude. Tables are provided for Long Range Cruise and .79M. The tables make no allowance for climb or descent time, fuel or distance, and are based on comparing ground fuel mileage. Descent Time, fuel, and distance for descent are shown for two descent speed schedules. This data includes the effect of a 250 KIAS speed restriction below 10000 ft and includes a straight in approach with flaps down at the outer marker. Holding %N1 required, indicated airspeed and fuel flow information are tabulated for holding at flaps up based on the recommended holding speeds. Small variations in airspeed will not appreciably affect the overall endurance time. The fuel flow is based on a racetrack holding pattern. For holding in straight and level flight, these values may be reduced by 5%.

This chapter contains inflight data for use as general reference in airplane performance monitoring, flight planning studies and as a supplement to information provided in the Operations Manual.

All Engines

Long Range Cruise Maximum Operating Altitude These tables provide the maximum operating altitude in the same manner as the FMC. Maximum altitudes are shown for a given cruise weight and maneuver capability. Note that these tables consider both thrust and buffet limits, providing the more limiting of the two. Any data that is thrust limited is denoted by an asterisk and represents only a thrust limited condition in level flight with 100 ft/min residual rate of climb. Flying above these altitudes with sustained banks in excess of approximately 15° may cause the airplane to lose speed and/or altitude. The altitudes shown in the tables are limited to the maximum certified altitude of 41000 ft. Enroute Climb The Enroute Climb tables are based on 280 /.78 climb speed. Local ATC may require that 250 KIAS not be exceeded below 10000 ft. See Flight Planning Allowances in Chapter 2 for additional fuel burn when this restriction is imposed. Long Range Cruise Enroute Fuel and Time These charts are provided to determine if the fuel remaining is sufficient to complete the trip at Long Range Cruise and to approximate the time remaining. The charts also enable rapid determination of fuel and time required to proceed to an alternate airfield. Fuel and time are read in a similar manner to the Long Range Cruise trip fuel and time charts in Chapter 2 with distance to destination replacing total trip distance; i.e., climb phase is excluded. Cruise Table Cruise tables are provided for Long Range Cruise and .79M speed schedules with both engines operating assuming normal engine bleed for air conditioning (2 bleeds/2 packs on). These tables are similar to the cruise control tables presented in the Performance Inflight chapter of the QRH and are expanded to include true airspeed and Max Cruise Thrust setting information. To account for APU fuel burn, refer to the APU Operation During Flight table in the chapter 2 text.

Engine Inoperative

Speed Capability The chart provides one-engine inoperative cruise speed capability at Maximum Continuous Thrust. Enter the chart with airplane weight and pressure altitude, and read the cruise speed capability directly. Altitude Capability The Engine Inoperative Altitude Capability tables are based on the thrust limited capability with 100 ft/min residual rate of climb. For the engine inoperative case, buffet capability is not considered limiting. Tables are shown for Long Range Cruise and constant speeds of 280, 290, 310 and 330 KIAS for both Max Continuous and Max Cruise Thrust. Adjust the table values for thermal anti-ice operation as shown below the tables. Cruise Table Cruise tabulations for engine inoperative are based on use of Max Continuous Thrust. A heavy line is shown to denote the approximate Max Cruise Thrust limits. Tables are provided for Long Range Cruise and constant speeds of 280, 290, 310 and 330 KIAS for both Max

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Continuous and Max Cruise Thrust. The fuel flow values in these tables reflect only the engine fuel burn. To conservatively account for APU fuel burn, refer to the APU Operation During Flight table in the chapter 2 text. Diversion Fuel and Time These charts enable rapid determination of fuel and time required to proceed to an alternate airfield (or continue to destination) with one engine inoperative. Data are shown for Long Range Cruise and constant speeds of 280, 290, 310 and 330 KIAS. The fuel required is based on cruise plus descent with straight in approach to touchdown. Diversion fuel and time are determined in a manner similar to the All Engine Long Range Cruise Enroute Fuel and Time chart. Holding %N1 required, indicated airspeed and fuel flow are shown for one engine inoperative holding based on the recommended speeds described earlier in this chapter. The fuel flow is based on a racetrack holding pattern and may be reduced by 5% for holding in straight and level flight.

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All Engine

3.2 ENROUTE-AllCruise Long Range Engine

Maximum Operating Altitude

TAT (°C) -5 -8 -11 -15 -18 -18 -18 -18 -18 -18 MARGIN TO INITIAL BUFFET 'G' (BANK ANGLE) 1.25 (36°) 1.30 (39°) 1.40 (44°) 32800* 32700 31200 34400* 34000 32500 35900* 35400 33900 37300* 36800 35300 38700* 38300 36900 40200* 40000 38500 41000 41000 40300 41000 41000 41000 41000 41000 41000 41000 41000 41000 MARGIN TO INITIAL BUFFET 'G' (BANK ANGLE) 1.25 (36°) 1.30 (39°) 1.40 (44°) 30600* 30600* 30600* 32900* 32900* 32500 34800* 34800* 33900 36300* 36300* 35300 37800* 37800* 36900 39200* 39200* 38500 40800* 40800* 40300 41000 41000 41000 41000 41000 41000 41000 41000 41000 MARGIN TO INITIAL BUFFET 'G' (BANK ANGLE) 1.25 (36°) 1.30 (39°) 1.40 (44°) 27500* 27500* 27500* 30000* 30000* 30000* 32800* 32800* 32800* 34900* 34900* 34900* 36500* 36500* 36500* 38000* 38000* 38000* 39500* 39500* 39500* 41000 41000 41000 41000 41000 41000 41000 41000 41000

Max Cruise Thrust ISA + 10°C and Below

WEIGHT (1000 KG) 85 80 75 70 65 60 55 50 45 40 OPTIMUM ALT (FT) 30300 31600 33000 34500 36000 37700 39500 41000 41000 41000 1.20 (33°) 32800* 34400* 35900* 37300* 38700* 40200* 41000 41000 41000 41000 1.50 (48°) 29800 31100 32500 34000 35500 37200 39000 41000 41000 41000

ISA + 15°C

WEIGHT (1000 KG) 85 80 75 70 65 60 55 50 45 40 OPTIMUM ALT (FT) 30300 31600 33000 34500 36000 37700 39500 41000 41000 41000 TAT (°C) 0 -3 -6 -9 -13 -13 -13 -13 -13 -13 1.20 (33°) 30600* 32900* 34800* 36300* 37800* 39200* 40800* 41000 41000 41000 1.50 (48°) 29800 31100 32500 34000 35500 37200 39000 41000 41000 41000

ISA + 20°C

WEIGHT (1000 KG) 85 80 75 70 65 60 55 50 45 40 OPTIMUM ALT (FT) 30300 31600 33000 34500 36000 37700 39500 41000 41000 41000 TAT (°C) 6 3 0 -3 -7 -7 -7 -7 -7 -7 1.20 (33°) 27500* 30000* 32800* 34900* 36500* 38000* 39500* 41000 41000 41000 1.50 (48°) 27500* 30000* 32500 34000 35500 37200 39000 41000 41000 41000

*Denotes altitude thrust limited in level flight, 100 fpm residual rate of climb.

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280/.78 Enroute Climb

ISA & Below

PRESSURE ALTITUDE (FT) 41000 40000 39000 38000 37000 36000 35000 34000 33000 32000 31000 30000 29000 28000 27000 26000 25000 24000 23000 22000 21000 20000 18000 16000 14000 10000 1500 UNITS MIN/KG NM/KTAS TIME/FUEL DIST/SPD TIME/FUEL DIST/SPD TIME/FUEL DIST/SPD TIME/FUEL DIST/SPD TIME/FUEL DIST/SPD TIME/FUEL DIST/SPD TIME/FUEL DIST/SPD TIME/FUEL DIST/SPD TIME/FUEL DIST/SPD TIME/FUEL DIST/SPD TIME/FUEL DIST/SPD TIME/FUEL DIST/SPD TIME/FUEL DIST/SPD TIME/FUEL DIST/SPD TIME/FUEL DIST/SPD TIME/FUEL DIST/SPD TIME/FUEL DIST/SPD TIME/FUEL DIST/SPD TIME/FUEL DIST/SPD TIME/FUEL DIST/SPD TIME/FUEL DIST/SPD TIME/FUEL DIST/SPD TIME/FUEL DIST/SPD TIME/FUEL DIST/SPD TIME/FUEL DIST/SPD TIME/FUEL DIST/SPD TIME/FUEL BRAKE RELEASE WEIGHT (1000 KG) 85 80 75 70 65 60 23/1750 146/409 21/1650 130/404 19/1600 118/401 18/1550 109/397 17/1500 101/394 16/1450 95/391 16/1400 89/387 15/1350 84/384 14/1300 80/381 14/1250 74/377 13/1200 69/372 12/1150 64/367 11/1150 59/363 11/1100 55/358 10/1050 51/354 10/1000 47/350 9/950 43/347 9/950 40/343 8/900 37/339 8/850 35/336 8/800 32/333 7/800 29/329 6/700 25/323 6/650 21/317 5/600 17/312 4/450 11/302 2/200 55 19/1500 120/405 18/1450 110/402 17/1400 102/399 16/1350 95/396 15/1300 89/392 14/1250 84/389 14/1250 79/386 13/1200 75/383 13/1150 71/380 12/1150 66/376 11/1100 61/371 11/1050 57/366 10/1000 53/362 10/950 49/358 9/950 45/354 9/900 42/350 8/850 39/346 8/850 36/342 8/800 34/339 7/750 31/335 7/750 29/332 6/700 27/329 6/650 22/323 5/600 19/317 5/550 16/311 4/450 10/301 2/200 2000 -50 4000 -150 50 17/1300 102/403 16/1300 95/400 15/1250 89/397 14/1200 83/394 13/1150 78/391 13/1150 73/388 12/1100 70/385 12/1050 66/382 11/1050 62/379 11/1000 58/375 10/950 54/370 10/950 50/366 9/900 47/361 9/850 43/357 8/850 40/353 8/800 37/349 7/800 35/345 7/750 32/342 7/700 30/338 6/700 28/335 6/650 26/331 6/650 24/328 5/600 20/322 5/550 17/316 4/500 14/311 3/400 9/301 1/200 6000 -200 45 14/1150 88/401 14/1100 82/399 13/1100 77/396 12/1050 72/393 12/1050 68/390 11/1000 64/387 11/950 61/384 10/950 58/381 10/900 55/378 10/900 52/374 9/850 48/369 9/850 44/365 8/800 41/360 8/750 38/356 7/750 36/352 7/700 33/348 7/700 31/345 6/650 29/341 6/650 27/337 6/600 25/334 5/600 23/331 5/550 21/327 5/500 18/321 4/500 15/315 4/450 12/310 3/350 8/300 1/150 8000 -250 10000 -350 40 12/1000 75/400 12/1000 71/397 11/950 67/395 11/950 63/392 10/900 59/389 10/900 56/386 9/850 53/383 9/850 51/380 9/800 48/377 8/800 45/373 8/750 42/368 8/750 39/364 7/700 36/360 7/700 34/355 6/650 31/351 6/650 29/347 6/600 27/344 6/600 25/340 5/550 23/336 5/550 22/333 5/500 20/330 5/500 19/326 4/450 16/320 4/400 13/314 3/400 11/309 3/300 7/298 1/150 12000 -400

32/2650 196/402 28/2400 169/395 26/2300 153/390 24/2150 138/384 22/2050 124/378 21/1950 113/372 19/1850 102/367 18/1750 94/362 17/1650 86/358 16/1600 79/353 15/1500 72/349 14/1450 66/345 13/1400 61/342 12/1300 56/338 12/1250 52/335 11/1200 47/331 10/1100 40/325 9/1000 33/319 8/900 27/314 6/700 17/303 2/300

29/2350 176/401 26/2200 155/396 24/2100 142/391 23/2000 131/387 21/1950 120/382 20/1850 109/376 18/1750 99/371 17/1650 91/366 16/1600 84/361 15/1500 77/357 14/1450 71/353 13/1400 65/349 13/1350 60/345 12/1250 55/341 11/1200 51/338 11/1150 47/334 10/1100 43/331 9/1000 36/325 8/900 30/319 7/850 25/313 5/650 16/303 2/300

32/2500 205/411 26/2150 162/402 24/2050 144/397 22/1950 132/393 21/1850 123/389 20/1800 114/385 19/1750 106/380 18/1650 97/375 17/1600 89/370 16/1500 82/365 15/1450 75/360 14/1400 69/356 13/1350 64/352 12/1300 59/348 12/1200 54/344 11/1150 50/341 10/1100 46/337 10/1100 43/334 9/1050 39/331 8/950 33/324 7/850 28/319 7/750 23/313 5/600 14/303 2/300

28/2200 179/409 24/2000 150/402 22/1900 135/398 21/1800 124/394 20/1750 115/390 19/1700 108/387 18/1650 101/383 17/1550 94/379 16/1500 86/374 15/1450 79/369 14/1400 73/364 13/1300 68/360 13/1250 62/356 12/1200 58/351 11/1150 53/348 11/1100 49/344 10/1100 46/340 10/1050 42/337 9/1000 39/333 9/950 36/330 8/850 30/324 7/800 25/318 6/700 21/313 5/550 13/303 2/250

25/1950 160/408 23/1850 140/403 21/1750 127/399 20/1650 116/396 18/1600 108/392 18/1550 101/389 17/1500 95/385 16/1450 90/382 15/1400 84/378 14/1350 77/373 14/1300 71/368 13/1250 66/363 12/1200 61/359 11/1150 56/355 11/1100 52/351 10/1050 48/347 10/1000 45/343 9/1000 41/340 9/950 38/336 8/900 35/333 8/850 33/330 7/800 28/324 6/700 23/318 6/650 19/312 4/500 12/302 2/250

FUEL ADJUSTMENT FOR HIGH ELEVATION AIRPORTS EFFECT ON TIME AND DISTANCE IS NEGLIGIBLE

AIRPORT ELEVATION FUEL ADJUSTMENT

Shaded area approximates optimum altitude at LRC.

Copyright © The Boeing Company. See title page for details.

3.2.2

D632A008-ZZ022

November 1, 2006

737-800/CFM56-7B26 JAA/JAROPS Category C Brakes

ENROUTE All Engine

Flight Planning and Performance Manual

All Engine

280/.78 Enroute Climb

ISA + 10°C

PRESSURE ALTITUDE (FT) 41000 40000 39000 38000 37000 36000 35000 34000 33000 32000 31000 30000 29000 28000 27000 26000 25000 24000 23000 22000 21000 20000 18000 16000 14000 10000 1500 UNITS MIN/KG NM/KTAS TIME/FUEL DIST/SPD TIME/FUEL DIST/SPD TIME/FUEL DIST/SPD TIME/FUEL DIST/SPD TIME/FUEL DIST/SPD TIME/FUEL DIST/SPD TIME/FUEL DIST/SPD TIME/FUEL DIST/SPD TIME/FUEL DIST/SPD TIME/FUEL DIST/SPD TIME/FUEL DIST/SPD TIME/FUEL DIST/SPD TIME/FUEL DIST/SPD TIME/FUEL DIST/SPD TIME/FUEL DIST/SPD TIME/FUEL DIST/SPD TIME/FUEL DIST/SPD TIME/FUEL DIST/SPD TIME/FUEL DIST/SPD TIME/FUEL DIST/SPD TIME/FUEL DIST/SPD TIME/FUEL DIST/SPD TIME/FUEL DIST/SPD TIME/FUEL DIST/SPD TIME/FUEL DIST/SPD TIME/FUEL DIST/SPD TIME/FUEL BRAKE RELEASE WEIGHT (1000 KG) 85 80 75 70 65 60 24/1850 155/418 22/1750 138/413 20/1650 125/410 19/1600 116/406 18/1550 107/402 17/1500 100/399 16/1450 94/396 15/1400 89/392 15/1350 84/389 14/1300 78/384 13/1250 72/379 12/1200 67/375 12/1150 62/370 11/1150 57/366 11/1100 53/361 10/1050 49/357 9/1000 46/353 9/950 42/350 9/900 39/346 8/900 36/342 8/850 33/339 7/800 31/336 6/750 26/329 6/700 22/323 5/600 18/318 4/500 11/307 2/200 55 20/1600 128/414 19/1550 117/411 17/1450 108/407 17/1400 101/404 16/1350 94/401 15/1350 88/398 14/1300 83/395 14/1250 79/391 13/1200 74/388 12/1200 70/384 12/1150 64/379 11/1100 60/374 11/1050 55/369 10/1000 51/365 9/950 47/361 9/950 44/357 9/900 41/353 8/850 38/349 8/850 35/345 7/800 32/342 7/750 30/338 7/750 28/335 6/650 24/329 5/600 20/323 5/550 16/317 4/450 10/307 2/200 2000 -50 4000 -150 50 17/1400 108/412 16/1350 100/409 15/1300 94/406 14/1250 88/403 14/1200 82/400 13/1200 78/397 13/1150 73/394 12/1100 69/390 12/1100 66/387 11/1050 62/383 10/1000 57/378 10/1000 53/373 9/950 49/368 9/900 46/364 8/850 42/360 8/850 39/356 8/800 36/352 7/800 34/348 7/750 31/345 7/700 29/341 6/700 27/338 6/650 25/334 5/600 21/328 5/550 18/322 4/500 15/316 3/400 9/306 1/200 6000 -200 45 15/1200 93/410 14/1150 87/407 13/1150 81/404 13/1100 76/401 12/1050 72/398 12/1050 68/395 11/1000 64/393 11/1000 61/389 10/950 58/386 10/950 54/382 9/900 50/377 9/850 47/372 8/850 43/368 8/800 40/363 8/750 37/359 7/750 35/355 7/700 32/351 6/700 30/348 6/650 28/344 6/650 26/340 6/600 24/337 5/600 22/334 5/550 19/327 4/500 16/321 4/450 13/316 3/350 8/305 1/150 8000 -250 10000 -350 40 13/1050 80/409 12/1000 75/406 12/1000 70/403 11/950 66/400 11/950 63/397 10/900 59/394 10/900 56/392 9/850 53/388 9/850 51/385 9/800 47/381 8/800 44/376 8/750 41/371 7/750 38/367 7/700 35/363 7/700 33/358 6/650 31/354 6/650 28/350 6/600 26/347 5/600 24/343 5/550 23/339 5/550 21/336 5/500 19/333 4/500 16/326 4/450 14/320 3/400 11/314 3/300 7/304 1/150 12000 -400

33/2800 210/411 29/2550 180/404 27/2400 163/398 25/2250 146/392 23/2150 131/386 21/2000 119/380 20/1900 108/375 18/1800 98/370 17/1750 90/365 16/1650 82/360 15/1600 76/356 14/1500 70/352 13/1450 64/348 13/1350 59/344 12/1300 54/341 11/1250 50/337 10/1150 42/331 9/1000 35/325 8/900 28/319 6/700 18/309 2/300

30/2500 188/410 27/2350 165/404 25/2200 150/400 23/2100 139/395 22/2000 127/390 20/1900 115/384 19/1800 105/378 18/1750 96/373 17/1650 88/369 16/1600 81/364 15/1500 74/360 14/1450 68/355 13/1400 63/352 12/1300 58/348 12/1250 53/344 11/1200 49/341 10/1150 45/337 9/1050 38/331 8/950 32/325 7/850 26/319 5/650 16/309 2/300

27/2300 173/411 25/2150 153/405 23/2050 140/401 22/1950 130/397 21/1900 121/393 19/1800 112/388 18/1750 102/382 17/1650 93/377 16/1600 86/372 15/1500 79/368 14/1450 73/363 13/1400 67/359 13/1300 62/355 12/1250 57/351 11/1200 53/347 11/1150 49/344 10/1100 45/340 10/1050 41/337 8/950 35/330 8/900 29/324 7/800 24/319 5/600 15/308 2/300

30/2300 191/418 25/2100 160/412 23/2000 143/407 22/1900 131/403 20/1800 122/399 19/1750 114/395 18/1700 107/391 17/1650 99/387 16/1550 91/381 15/1500 84/376 14/1450 77/372 14/1400 71/367 13/1300 66/363 12/1250 61/358 12/1200 56/354 11/1150 52/351 10/1100 48/347 10/1050 44/343 9/1050 41/340 9/1000 38/336 8/900 32/330 7/800 26/324 6/750 22/318 5/600 14/308 2/250

26/2050 171/418 24/1900 149/412 22/1850 134/408 20/1750 123/404 19/1700 114/401 18/1650 107/397 17/1600 101/394 16/1550 95/390 16/1450 88/385 15/1400 81/380 14/1350 75/375 13/1300 69/371 12/1250 64/366 12/1200 59/362 11/1150 55/358 10/1100 51/354 10/1050 47/350 9/1000 43/346 9/1000 40/343 8/950 37/339 8/900 34/336 7/800 29/330 6/750 24/324 6/650 20/318 4/550 12/308 2/250

FUEL ADJUSTMENT FOR HIGH ELEVATION AIRPORTS EFFECT ON TIME AND DISTANCE IS NEGLIGIBLE

AIRPORT ELEVATION FUEL ADJUSTMENT

Shaded area approximates optimum altitude at LRC.

Copyright © The Boeing Company. See title page for details.

November 1, 2006

D632A008-ZZ022

3.2.3

ENROUTE All Engine

Flight Planning and Performance Manual

All Engine

737-800/CFM56-7B26 JAA/JAROPS Category C Brakes

280/.78 Enroute Climb

ISA + 15°C

PRESSURE ALTITUDE (FT) 41000 40000 39000 38000 37000 36000 35000 34000 33000 32000 31000 30000 29000 28000 27000 26000 25000 24000 23000 22000 21000 20000 18000 16000 14000 10000 1500 UNITS MIN/KG NM/KTAS TIME/FUEL DIST/SPD TIME/FUEL DIST/SPD TIME/FUEL DIST/SPD TIME/FUEL DIST/SPD TIME/FUEL DIST/SPD TIME/FUEL DIST/SPD TIME/FUEL DIST/SPD TIME/FUEL DIST/SPD TIME/FUEL DIST/SPD TIME/FUEL DIST/SPD TIME/FUEL DIST/SPD TIME/FUEL DIST/SPD TIME/FUEL DIST/SPD TIME/FUEL DIST/SPD TIME/FUEL DIST/SPD TIME/FUEL DIST/SPD TIME/FUEL DIST/SPD TIME/FUEL DIST/SPD TIME/FUEL DIST/SPD TIME/FUEL DIST/SPD TIME/FUEL DIST/SPD TIME/FUEL DIST/SPD TIME/FUEL DIST/SPD TIME/FUEL DIST/SPD TIME/FUEL DIST/SPD TIME/FUEL DIST/SPD TIME/FUEL BRAKE RELEASE WEIGHT (1000 KG) 85 80 75 70 65 60 28/2050 185/425 25/1900 160/420 23/1800 144/415 21/1700 132/411 20/1650 122/408 19/1600 113/404 18/1550 106/401 17/1500 100/397 16/1450 94/394 15/1400 88/389 14/1350 81/384 14/1250 75/379 13/1200 69/374 12/1150 64/369 11/1150 59/365 11/1100 55/361 10/1050 51/357 10/1000 47/353 9/950 43/349 9/900 40/346 8/900 37/342 8/850 34/339 7/750 29/333 6/700 24/327 5/650 20/321 4/500 13/310 2/200 55 23/1700 147/420 21/1600 134/416 19/1550 123/413 18/1500 114/409 17/1450 106/406 16/1400 99/403 16/1350 94/399 15/1300 88/396 14/1300 83/392 14/1250 78/388 13/1200 72/383 12/1150 66/378 11/1100 61/373 11/1050 57/369 10/1000 53/364 10/950 49/360 9/950 45/356 9/900 42/353 8/850 39/349 8/850 36/345 7/800 33/342 7/750 31/338 6/700 26/332 6/650 22/326 5/550 18/320 4/450 11/310 2/200 2000 -50 4000 -150 50 19/1450 123/418 18/1400 114/414 17/1350 106/411 16/1300 99/408 15/1300 93/405 14/1250 87/401 14/1200 82/398 13/1150 78/395 13/1150 73/391 12/1100 69/387 11/1050 63/382 11/1000 59/377 10/1000 54/372 10/950 50/368 9/900 47/364 9/850 43/360 8/850 40/356 8/800 37/352 7/750 35/348 7/750 32/345 7/700 30/341 6/700 27/338 6/600 23/332 5/550 20/326 4/500 16/320 3/400 10/309 1/200 6000 -200 45 16/1300 105/416 15/1250 98/413 15/1200 91/410 14/1150 86/406 13/1150 81/403 13/1100 76/400 12/1050 72/397 12/1050 68/394 11/1000 64/390 11/950 60/386 10/950 56/381 10/900 52/376 9/850 48/372 9/850 45/367 8/800 41/363 8/750 38/359 7/750 36/355 7/700 33/351 7/700 31/348 6/650 29/344 6/650 26/341 6/600 24/337 5/550 21/331 4/500 17/325 4/450 14/319 3/350 9/308 1/150 8000 -300 10000 -350 40 14/1100 90/414 13/1050 84/411 13/1050 79/408 12/1000 74/405 12/1000 70/402 11/950 66/399 11/950 63/396 10/900 59/393 10/900 56/390 9/850 53/385 9/800 49/380 8/800 45/376 8/750 42/371 8/750 39/367 7/700 36/362 7/700 34/358 6/650 31/354 6/650 29/350 6/600 27/347 6/600 25/343 5/550 23/340 5/550 21/336 4/500 18/330 4/450 15/324 4/400 13/318 3/300 8/307 1/150 12000 -450

34/2800 216/411 31/2600 191/404 28/2450 171/398 26/2300 152/391 24/2150 136/385 22/2050 123/379 20/1950 112/374 19/1850 102/369 18/1750 93/364 17/1650 85/360 16/1600 78/356 15/1500 72/352 14/1450 66/348 13/1350 61/344 12/1300 56/341 11/1200 47/334 9/1050 39/328 8/950 32/322 6/750 20/312 2/300

36/2800 233/419 31/2550 196/411 28/2400 176/406 26/2250 161/401 24/2150 146/395 23/2050 131/389 21/1950 119/383 20/1850 109/378 18/1750 99/373 17/1650 91/368 16/1600 83/363 15/1500 77/359 14/1450 71/355 13/1400 65/351 13/1300 60/347 12/1250 55/344 11/1200 51/340 10/1100 42/334 9/1000 35/328 8/900 29/322 6/700 18/312 2/300

32/2500 209/418 28/2300 179/412 26/2200 162/407 24/2100 149/402 23/2000 138/398 22/1900 127/393 20/1850 115/387 19/1750 106/382 18/1650 97/377 16/1600 89/372 15/1500 82/367 15/1450 75/363 14/1400 69/359 13/1350 64/355 12/1250 59/351 12/1200 54/347 11/1150 50/344 10/1100 46/340 9/1000 39/334 8/900 32/328 7/800 27/322 5/650 17/311 2/300

29/2300 191/418 26/2150 166/413 24/2000 151/408 23/1950 139/404 21/1850 130/400 20/1800 121/396 19/1750 112/391 18/1650 102/386 17/1550 94/381 16/1500 86/376 15/1450 80/371 14/1400 73/366 13/1300 68/362 13/1250 62/358 12/1200 58/354 11/1150 53/350 11/1100 49/347 10/1050 45/343 9/1000 42/340 8/950 35/333 7/850 29/327 7/750 24/322 5/600 15/311 2/250

32/2300 211/426 27/2100 174/419 24/1950 155/414 23/1850 141/410 21/1800 130/406 20/1700 121/402 19/1650 114/399 18/1600 107/395 17/1550 99/390 16/1500 91/385 15/1400 84/380 14/1350 77/375 13/1300 71/370 13/1250 66/366 12/1200 61/361 11/1150 56/357 11/1100 52/354 10/1050 48/350 10/1000 44/346 9/950 41/343 9/950 38/339 8/850 32/333 7/750 27/327 6/700 22/321 5/550 14/311 2/250

FUEL ADJUSTMENT FOR HIGH ELEVATION AIRPORTS EFFECT ON TIME AND DISTANCE IS NEGLIGIBLE

AIRPORT ELEVATION FUEL ADJUSTMENT

Shaded area approximates optimum altitude at LRC.

Copyright © The Boeing Company. See title page for details.

3.2.4

D632A008-ZZ022

November 1, 2006

737-800/CFM56-7B26 JAA/JAROPS Category C Brakes

ENROUTE All Engine

Flight Planning and Performance Manual

All Engine

280/.78 Enroute Climb

ISA + 20°C

PRESSURE ALTITUDE (FT) 41000 40000 39000 38000 37000 36000 35000 34000 33000 32000 31000 30000 29000 28000 27000 26000 25000 24000 23000 22000 21000 20000 18000 16000 14000 10000 1500 UNITS MIN/KG NM/KTAS TIME/FUEL DIST/SPD TIME/FUEL DIST/SPD TIME/FUEL DIST/SPD TIME/FUEL DIST/SPD TIME/FUEL DIST/SPD TIME/FUEL DIST/SPD TIME/FUEL DIST/SPD TIME/FUEL DIST/SPD TIME/FUEL DIST/SPD TIME/FUEL DIST/SPD TIME/FUEL DIST/SPD TIME/FUEL DIST/SPD TIME/FUEL DIST/SPD TIME/FUEL DIST/SPD TIME/FUEL DIST/SPD TIME/FUEL DIST/SPD TIME/FUEL DIST/SPD TIME/FUEL DIST/SPD TIME/FUEL DIST/SPD TIME/FUEL DIST/SPD TIME/FUEL DIST/SPD TIME/FUEL DIST/SPD TIME/FUEL DIST/SPD TIME/FUEL DIST/SPD TIME/FUEL DIST/SPD TIME/FUEL DIST/SPD TIME/FUEL BRAKE RELEASE WEIGHT (1000 KG) 85 80 75 70 65 60 34/2300 233/433 29/2050 192/426 26/1950 169/421 24/1850 153/417 22/1750 141/413 21/1700 131/409 20/1650 122/406 19/1600 115/402 18/1550 108/398 17/1450 100/394 16/1400 92/388 15/1350 85/383 14/1300 78/378 13/1250 72/374 13/1200 67/369 12/1150 62/365 11/1100 57/361 11/1050 53/357 10/1000 49/353 9/950 45/349 9/900 42/346 8/900 38/342 8/800 32/336 7/750 27/330 6/650 22/324 4/500 14/313 2/200 55 26/1850 174/427 24/1750 156/422 22/1650 142/418 21/1600 131/415 19/1550 122/411 18/1500 114/408 17/1450 107/404 17/1400 101/401 16/1350 95/397 15/1300 88/392 14/1250 81/387 13/1200 75/382 13/1150 69/377 12/1100 64/373 11/1050 59/368 11/1000 55/364 10/1000 51/360 10/950 47/356 9/900 44/353 9/850 40/349 8/850 37/345 8/800 34/342 7/700 29/336 6/650 24/329 5/600 20/324 4/450 13/313 2/200 2000 -50 4000 -150 50 22/1600 143/423 20/1500 131/420 19/1450 121/416 18/1400 113/413 17/1350 106/410 16/1300 99/406 15/1300 93/403 15/1250 88/400 14/1200 83/396 13/1150 78/392 13/1100 72/386 12/1050 66/381 11/1050 61/377 11/1000 57/372 10/950 53/368 9/900 49/364 9/850 45/360 9/850 42/356 8/800 39/352 8/750 36/348 7/750 33/345 7/700 31/342 6/650 26/335 5/600 22/329 5/550 18/323 4/400 11/312 1/200 6000 -250 45 18/1350 121/421 17/1300 112/418 16/1250 104/415 16/1250 98/412 15/1200 92/408 14/1150 86/405 13/1100 82/402 13/1100 77/399 12/1050 73/395 12/1000 68/391 11/1000 63/386 10/950 58/381 10/900 54/376 9/850 50/371 9/850 47/367 8/800 43/363 8/800 40/359 8/750 37/355 7/700 34/351 7/700 32/348 6/650 29/344 6/650 27/341 5/600 23/334 5/550 19/328 4/450 16/322 3/350 10/312 1/150 8000 -300 10000 -400 40 16/1200 102/419 15/1150 96/416 14/1100 90/413 13/1050 84/410 13/1050 79/407 12/1000 75/404 12/1000 71/401 11/950 67/398 11/950 64/394 10/900 59/390 10/850 55/385 9/850 51/380 9/800 47/375 8/750 44/371 8/750 41/366 7/700 38/362 7/700 35/358 7/650 33/354 6/650 30/351 6/600 28/347 6/600 26/343 5/550 24/340 5/500 20/334 4/450 17/327 4/400 14/322 3/350 9/311 1/150 12000 -450

42/3250 278/420 37/2950 236/412 33/2700 206/404 30/2500 181/397 27/2350 160/390 25/2200 144/384 23/2100 130/378 21/1950 118/373 20/1850 108/369 19/1800 98/364 17/1700 90/360 16/1600 82/355 15/1550 75/352 14/1450 69/348 13/1400 63/344 12/1250 53/338 10/1100 44/331 9/1000 36/325 7/750 22/315 2/300

37/2850 243/419 33/2650 212/413 31/2500 192/407 28/2350 172/401 26/2200 154/394 24/2100 138/388 22/1950 126/382 20/1850 115/377 19/1800 105/372 18/1700 96/368 17/1600 88/363 16/1550 81/359 15/1450 74/355 14/1400 68/351 13/1350 62/347 12/1250 57/344 11/1150 48/337 10/1050 40/331 8/900 33/325 6/700 20/314 2/300

33/2550 217/419 30/2400 194/413 28/2300 176/409 26/2200 162/404 24/2050 148/398 23/1950 134/392 21/1850 122/386 20/1750 111/381 18/1700 102/376 17/1600 93/371 16/1550 86/367 15/1450 79/362 14/1400 73/358 13/1350 67/354 13/1300 61/351 12/1200 56/347 11/1150 52/344 10/1050 44/337 9/950 36/331 8/850 30/325 6/650 19/314 2/300

35/2600 237/426 31/2350 200/420 28/2200 178/414 26/2100 163/410 24/2000 151/406 23/1950 140/401 22/1850 129/396 20/1750 118/390 19/1650 108/385 18/1600 99/380 17/1550 91/375 16/1450 83/371 15/1400 77/366 14/1350 71/362 13/1300 65/358 12/1200 60/354 12/1150 55/350 11/1100 51/347 10/1050 47/343 9/950 40/337 8/900 33/330 7/800 27/325 5/600 17/314 2/250

32/2300 212/426 28/2150 183/420 26/2000 165/416 24/1900 151/411 23/1850 141/408 21/1800 131/404 20/1700 123/400 19/1650 113/395 18/1550 104/389 17/1500 95/384 16/1450 88/379 15/1400 81/374 14/1300 75/370 13/1250 69/365 12/1200 64/361 12/1150 59/357 11/1100 54/353 11/1050 50/350 10/1000 46/346 9/950 43/343 8/900 36/336 7/800 30/330 6/700 25/324 5/550 15/314 2/250

FUEL ADJUSTMENT FOR HIGH ELEVATION AIRPORTS EFFECT ON TIME AND DISTANCE IS NEGLIGIBLE

AIRPORT ELEVATION FUEL ADJUSTMENT

Shaded area approximates optimum altitude at LRC.

Copyright © The Boeing Company. See title page for details.

November 1, 2006

D632A008-ZZ022

3.2.5

ENROUTE All Engine

Flight Planning and Performance Manual

All Engine

737-800/CFM56-7B26 JAA/JAROPS Category C Brakes

Long Range Cruise Enroute Fuel and Time

200 to 2000 NM

Based on .78/280/250 descent

8 7 (HOURS) 6 5 4 3 2 REF LINE 1 0

10 14

(1 AL T TI UD E

00

0

F

T)

20 24 28

TIME REQUIRED

PR

14

ES

S

E UR

10

14

12

FT

24

)

20

10 FUEL REQUIRED (1000 KG)

TU

DE

(1

20 10 0 -10 ISA DEV (°C)

00

28

0

ES

SU

RE

AL

TI

8

PRESSURE ALTITUDE 10 8 (1000 FT) 2

PR

6

4

2 REF LINE

0 40 HEAD 100 (KTS) 50 0 WIND 50 REF LINE 50 60 70 80 WEIGHT AT CHECK POINT (1000 KG)

TAIL 100

0

400

800 1200 1600 DISTANCE FROM CHECK POINT (NAUTICAL GROUND MILES)

2000

Copyright © The Boeing Company. See title page for details.

3.2.6

D632A008-ZZ022

November 1, 2006

737-800/CFM56-7B26 JAA/JAROPS Category C Brakes

ENROUTE All Engine

Flight Planning and Performance Manual

All Engine

Long Range Cruise Enroute Fuel and Time

500 to 5000 NM

Based on .78/280/250 descent

15 14 13 12 11 (HOURS) 10 9 8

SU TIT FT )

(10

00

39

&

AB

OV

E

37 35 33 31 29

TIME REQUIRED

RE

AL

UD

E

26

7 6 5

PR

29

31 33 35 37

O AB VE

)

22

ES

18

TU

3 REF LINE

AL RE

DE

(1

4

00

39

0

&

2 1

ES

SU

PRESSURE 29 ALTITUDE (1000 FT)

14

20 10 0 -10 ISA DEV (°C)

PR

10

6 REF LINE

2 40 HEAD 100 (KTS) 50 0 WIND 50 REF LINE 50 60 70 80 WEIGHT AT CHECK POINT (1000 KG)

TAIL 100

0

1000 2000 3000 4000 DISTANCE FROM CHECK POINT (NAUTICAL GROUND MILES)

5000

Copyright © The Boeing Company. See title page for details.

November 1, 2006

D632A008-ZZ022

FUEL REQUIRED (1000 KG)

TI

FT

39

3.2.7

ENROUTE All Engine

Flight Planning and Performance Manual

All Engine

737-800/CFM56-7B26 JAA/JAROPS Category C Brakes

Long Range Cruise Table

41000 FT to 36000 FT

PRESS ALT (1000 FT) (STD TAT) %N1 MAX TAT 41 KIAS MACH (-30) FF/ENG KTAS %N1 MAX TAT 40 KIAS MACH (-31) FF/ENG KTAS %N1 MAX TAT 39 KIAS MACH (-31) FF/ENG KTAS %N1 MAX TAT 38 KIAS MACH (-31) FF/ENG KTAS %N1 MAX TAT 37 KIAS MACH (-32) FF/ENG KTAS %N1 MAX TAT 36 KIAS MACH (-32) FF/ENG KTAS WEIGHT (1000 KG) 85 80 75 70 65 60 55 90.5 -10 235 .795 1076 456 88.9 -6 239 .791 1063 454 87.6 -1 243 .786 1055 451 86.5 247 .780 1052 448 85.5 250 .774 1054 444 84.6 254 .767 1056 440 50 87.9 -3 232 .786 973 451 86.7 1 236 .780 970 448 85.8 239 .774 972 444 84.8 242 .767 974 440 83.7 244 .757 971 434 82.6 245 .744 967 427 45 85.8 228 .773 901 443 84.9 231 .766 891 439 83.8 232 .755 888 433 82.6 233 .741 882 425 81.3 232 .723 872 415 80.1 231 .704 861 404 40 83.5 220 .749 813 430 82.3 220 .733 805 421 81.0 219 .714 795 410 79.8 218 .696 786 399 78.5 217 .679 778 389 77.3 216 .663 772 380

93.0 -15 263 .793 1449 455

91.8 -12 258 .795 1344 456 89.8 -7 264 .795 1322 456

93.4 -17 246 .793 1284 455 90.8 -10 252 .795 1248 456 89.1 -5 257 .793 1231 455 87.8 -1 262 .789 1221 452

91.8 -13 241 .795 1173 456 89.9 -8 246 .794 1155 456 88.4 -3 250 .790 1143 453 87.2 1 254 .785 1135 450 86.1 258 .779 1133 447

Max TAT not shown where %N1 can be set in ISA + 30°C conditions. Increase/decrease %N1 required by 1% per 5°C above/below standard TAT. Increase/decrease fuel flow 3% per 10°C above/below standard TAT. Increase/decrease KTAS by 1 knot per 1°C above/below standard TAT. Shaded area approximates optimum altitude.

Max Cruise %N1

PRESS ALT (1000 FT) 41 40 39 38 37 36 -65 86.3 86.4 86.5 86.6 86.7 86.4 -60 87.2 87.3 87.5 87.6 87.7 87.4 -55 88.2 88.3 88.4 88.5 88.6 88.3 -50 89.1 89.2 89.4 89.4 89.5 89.2 -45 90.0 90.2 90.3 90.3 90.5 90.2 -40 91.0 91.1 91.2 91.3 91.4 91.1 TAT (°C) -35 -30 91.9 92.7 92.0 92.9 92.1 93.0 92.2 93.1 92.3 93.2 92.0 92.9 -25 93.6 93.7 93.9 93.9 94.0 93.7 -20 94.4 94.6 94.4 94.3 94.1 93.9 -15 94.1 94.0 93.9 93.7 93.4 93.2 -10 93.4 93.4 93.3 93.0 92.6 92.4 -5 92.6 92.6 92.5 92.2 91.8 91.5 0 91.8 91.8 91.7 91.3 90.9 90.6

With engine anti-ice on, decrease limit %N1 by 0.9. With engine and wing anti-ice on, decrease limit %N1 by 3.4.

Copyright © The Boeing Company. See title page for details.

3.2.8

D632A008-ZZ022

November 1, 2006

737-800/CFM56-7B26 JAA/JAROPS Category C Brakes

ENROUTE All Engine

Flight Planning and Performance Manual

All Engine

Long Range Cruise Table

35000 FT to 30000 FT

PRESS ALT (1000 FT) (STD TAT) %N1 MAX TAT 35 KIAS MACH (-30) FF/ENG KTAS %N1 MAX TAT 34 KIAS MACH (-28) FF/ENG KTAS %N1 MAX TAT 33 KIAS MACH (-26) FF/ENG KTAS %N1 MAX TAT 32 KIAS MACH (-24) FF/ENG KTAS %N1 MAX TAT 31 KIAS MACH (-23) FF/ENG KTAS %N1 MAX TAT 30 KIAS MACH (-21) FF/ENG KTAS WEIGHT (1000 KG) 85 80 94.1 -16 269 .792 1562 456 91.7 -8 276 .795 1519 460 90.4 -3 282 .794 1507 462 89.4 1 287 .791 1500 462 88.7 5 291 .785 1499 461 88.0 9 296 .780 1505 460 75 90.8 -7 270 .795 1419 458 89.6 -2 276 .793 1410 459 88.7 3 280 .789 1405 459 88.0 7 284 .783 1406 458 87.4 10 288 .778 1414 456 86.8 13 292 .772 1427 455 70 88.7 -1 269 .791 1313 456 87.9 3 273 .786 1311 455 87.2 8 277 .781 1315 454 86.7 11 281 .775 1326 453 86.1 285 .768 1338 451 85.4 287 .759 1344 447 65 87.1 4 266 .783 1218 451 86.4 269 .777 1226 450 85.9 273 .771 1239 449 85.3 276 .763 1247 446 84.6 278 .752 1252 441 83.8 278 .738 1250 435 60 85.6 262 .773 1140 446 85.0 265 .766 1150 443 84.3 267 .755 1156 439 83.6 268 .742 1157 433 82.7 267 .725 1151 425 81.9 266 .707 1144 417 55 83.9 256 .757 1060 436 83.2 257 .744 1061 431 82.3 256 .727 1057 423 81.4 255 .709 1050 414 80.6 254 .692 1046 406 79.7 253 .675 1040 398 50 81.8 245 .727 962 419 80.9 243 .708 956 410 80.0 242 .691 952 402 79.1 241 .674 948 394 78.3 241 .659 946 387 77.6 242 .648 947 382 45 79.2 230 .687 858 396 78.3 229 .670 854 388 77.5 229 .656 854 382 76.9 230 .645 857 377 76.2 232 .635 862 373 75.6 233 .625 866 368 40 76.5 217 .650 774 375 75.9 218 .640 779 370 75.3 219 .630 784 366 74.6 221 .620 790 362 74.0 222 .611 797 358 73.4 224 .602 805 354

92.6 -9 282 .794 1623 462 91.1 -4 289 .795 1605 464 90.0 1 294 .792 1596 465 89.3 5 299 .787 1593 464

Max TAT not shown where %N1 can be set in ISA + 30°C conditions. Increase/decrease %N1 required by 1% per 5°C above/below standard TAT. Increase/decrease fuel flow 3% per 10°C above/below standard TAT. Increase/decrease KTAS by 1 knot per 1°C above/below standard TAT. Shaded area approximates optimum altitude.

Max Cruise %N1

PRESS ALT (1000 FT) 35 34 33 32 31 30 -60 87.0 86.3 85.7 85.2 84.8 84.2 -55 88.0 87.2 86.7 86.2 85.8 85.2 -50 88.9 88.2 87.7 87.1 86.7 86.1 -45 89.9 89.2 88.7 88.1 87.6 87.1 -40 90.8 90.1 89.6 89.0 88.5 88.0 -35 91.7 91.0 90.6 89.9 89.4 88.9 TAT (°C) -30 -25 92.6 93.4 92.0 92.9 91.5 92.4 90.8 91.7 90.3 91.2 89.8 90.7 -20 94.3 93.8 93.3 92.6 92.1 91.6 -15 93.6 94.0 94.2 93.5 93.0 92.5 -10 92.8 93.2 93.7 94.1 93.8 93.3 -5 91.9 92.3 92.8 93.2 93.8 94.2 0 91.1 91.5 91.9 92.3 92.9 93.2 5 90.2 90.6 91.0 91.5 92.0 92.4

With engine anti-ice on, decrease limit %N1 by 1.1. With engine and wing anti-ice on, decrease limit %N1 by 3.5.

Copyright © The Boeing Company. See title page for details.

November 1, 2006

D632A008-ZZ022

3.2.9

ENROUTE All Engine

Flight Planning and Performance Manual

All Engine

737-800/CFM56-7B26 JAA/JAROPS Category C Brakes

Long Range Cruise Table

29000 FT to 24000 FT

PRESS ALT (1000 FT) (STD TAT) %N1 MAX TAT 29 KIAS MACH (-20) FF/ENG KTAS %N1 MAX TAT 28 KIAS MACH (-18) FF/ENG KTAS %N1 MAX TAT 27 KIAS MACH (-17) FF/ENG KTAS %N1 MAX TAT 26 KIAS MACH (-15) FF/ENG KTAS %N1 MAX TAT 25 KIAS MACH (-14) FF/ENG KTAS %N1 MAX TAT 24 KIAS MACH (-13) FF/ENG KTAS WEIGHT (1000 KG) 85 88.6 9 303 .782 1597 463 88.0 13 307 .776 1604 461 87.5 16 311 .771 1616 460 86.9 19 314 .762 1622 457 86.2 23 316 .752 1625 453 85.5 316 .738 1624 446 80 87.4 13 300 .774 1516 458 86.9 16 303 .768 1527 456 86.3 20 306 .759 1530 453 85.6 307 .747 1532 448 84.8 307 .732 1526 441 84.0 306 .715 1518 432 75 86.2 17 295 .764 1436 452 85.6 297 .754 1439 448 84.9 298 .741 1437 442 84.1 297 .724 1429 434 83.2 296 .707 1419 425 82.4 294 .691 1414 418 70 84.8 288 .747 1347 442 84.0 288 .732 1341 435 83.2 287 .714 1331 426 82.4 285 .698 1323 418 81.5 284 .682 1316 410 80.7 283 .666 1310 403 65 83.0 277 .721 1243 427 82.2 276 .703 1234 418 81.4 275 .687 1227 410 80.5 274 .671 1219 402 79.7 274 .658 1216 396 79.1 275 .647 1219 391 60 81.0 265 .690 1138 409 80.2 264 .674 1131 401 79.4 263 .660 1126 394 78.7 264 .649 1126 389 78.1 265 .639 1130 385 77.5 267 .630 1137 381 55 78.9 252 .661 1037 391 78.3 253 .649 1037 386 77.6 255 .639 1040 382 77.0 256 .630 1044 378 76.4 257 .621 1050 374 75.8 259 .612 1060 370 50 77.0 243 .638 951 378 76.4 245 .629 955 374 75.8 246 .619 959 370 75.2 248 .610 967 366 74.6 249 .602 976 362 73.9 250 .591 984 357 45 75.0 234 .616 871 365 74.4 236 .607 879 361 73.8 237 .597 885 357 73.1 237 .587 890 352 72.3 238 .575 895 346 71.6 238 .564 900 341 40 72.7 224 .591 811 349 72.0 224 .579 816 344 71.2 224 .567 820 339 70.5 224 .556 806 333 69.7 224 .545 809 328 68.9 225 .534 814 323

Max TAT not shown where %N1 can be set in ISA + 30°C conditions. Increase/decrease %N1 required by 1% per 5°C above/below standard TAT. Increase/decrease fuel flow 3% per 10°C above/below standard TAT. Increase/decrease KTAS by 1 knot per 1°C above/below standard TAT.

Max Cruise %N1

PRESS ALT (1000 FT) 29 28 27 26 25 24 -50 85.6 85.1 84.7 84.4 84.0 83.8 -45 86.5 86.1 85.7 85.3 85.0 84.7 -40 87.5 87.0 86.6 86.2 85.9 85.6 -35 88.4 87.9 87.5 87.1 86.8 86.5 -30 89.3 88.8 88.4 88.0 87.7 87.4 -25 90.2 89.7 89.3 88.9 88.5 88.3 TAT (°C) -20 -15 91.1 92.0 90.6 91.5 90.2 91.0 89.8 90.6 89.4 90.3 89.2 90.1 -10 92.8 92.3 91.9 91.5 91.1 90.9 -5 93.7 93.2 92.8 92.4 92.0 91.8 0 93.5 93.6 93.6 93.2 92.9 92.6 5 92.6 92.7 92.8 93.0 93.2 93.2 10 91.8 91.8 92.0 92.1 92.4 92.4 15 90.8 90.8 91.0 91.2 91.4 91.5

With engine anti-ice on, decrease limit %N1 by 1.2. With engine and wing anti-ice on, decrease limit %N1 by 3.1.

Copyright © The Boeing Company. See title page for details.

3.2.10

D632A008-ZZ022

November 1, 2006

737-800/CFM56-7B26 JAA/JAROPS Category C Brakes

ENROUTE All Engine

Flight Planning and Performance Manual

All Engine

Long Range Cruise Table

23000 FT to 18000 FT

PRESS ALT (1000 FT) (STD TAT) %N1 MAX TAT 23 KIAS MACH (-11) FF/ENG KTAS %N1 MAX TAT 22 KIAS MACH (-10) FF/ENG KTAS %N1 MAX TAT 21 KIAS MACH (-8) FF/ENG KTAS %N1 MAX TAT 20 KIAS MACH (-7) FF/ENG KTAS %N1 MAX TAT 19 KIAS MACH (-5) FF/ENG KTAS %N1 MAX TAT 18 KIAS MACH (-4) FF/ENG KTAS WEIGHT (1000 KG) 85 84.7 315 .722 1620 438 83.9 314 .705 1616 430 83.0 312 .690 1615 422 82.2 311 .675 1611 414 81.4 311 .661 1610 408 80.7 312 .650 1615 403 80 83.2 304 .699 1514 424 82.4 303 .683 1512 416 81.5 302 .668 1509 409 80.7 302 .656 1512 403 80.1 303 .646 1519 398 79.4 305 .637 1531 395 75 81.6 293 .675 1410 410 80.8 293 .661 1410 403 80.0 294 .650 1416 398 79.4 295 .641 1425 394 78.7 297 .632 1437 390 78.1 298 .623 1449 386 70 79.9 284 .654 1313 397 79.3 285 .644 1321 393 78.6 287 .636 1333 389 78.0 288 .626 1343 385 77.4 290 .618 1357 381 76.8 291 .610 1374 377 65 78.4 276 .638 1228 387 77.8 278 .629 1239 383 77.2 279 .620 1252 379 76.5 281 .611 1267 376 75.9 282 .603 1284 372 75.2 283 .593 1296 367 60 76.8 268 .621 1148 377 76.2 270 .612 1161 373 75.6 272 .604 1178 370 74.9 272 .594 1191 365 74.2 273 .584 1201 360 73.5 273 .573 1210 355 55 75.2 261 .604 1074 366 74.5 261 .593 1086 362 73.8 262 .583 1097 357 73.0 262 .572 1106 351 72.3 262 .561 1113 346 71.5 262 .550 1119 341 50 73.2 250 .580 993 352 72.4 250 .569 1002 347 71.7 250 .558 1009 341 70.9 250 .547 1016 336 70.1 250 .537 1021 331 69.2 250 .526 1026 326 45 70.8 238 .553 906 335 70.0 238 .542 914 330 69.2 238 .531 920 325 68.3 238 .521 925 320 67.6 238 .511 930 315 66.8 238 .501 934 310 40 68.1 225 .523 820 318 67.2 225 .513 825 313 66.4 225 .503 830 308 65.7 225 .493 835 303 65.0 225 .484 841 298 64.3 225 .475 847 294

Max TAT not shown where %N1 can be set in ISA + 30°C conditions. Increase/decrease %N1 required by 1% per 5°C above/below standard TAT. Increase/decrease fuel flow 3% per 10°C above/below standard TAT. Increase/decrease KTAS by 1 knot per 1°C above/below standard TAT.

Max Cruise %N1

PRESS ALT (1000 FT) 23 22 21 20 19 18 -40 85.5 85.3 85.0 84.8 84.5 84.2 -35 86.4 86.2 85.9 85.7 85.4 85.1 -30 87.2 87.1 86.8 86.6 86.3 86.0 -25 88.1 87.9 87.7 87.4 87.2 86.8 -20 89.0 88.8 88.6 88.3 88.0 87.7 -15 89.9 89.7 89.4 89.2 88.9 88.5 TAT (°C) -10 -5 90.7 91.6 90.5 91.4 90.3 91.1 90.0 90.8 89.7 90.6 89.4 90.2 0 92.4 92.2 91.9 91.7 91.4 91.0 5 93.2 93.0 92.8 92.5 92.2 91.9 10 92.4 92.4 92.4 92.3 92.4 92.6 15 91.6 91.6 91.6 91.5 91.7 91.7 20 90.6 90.7 90.7 90.6 90.8 90.9 25 89.6 89.7 89.7 89.7 89.9 90.0

With engine anti-ice on, decrease limit %N1 by 1.2. With engine and wing anti-ice on, decrease limit %N1 by 2.9.

Copyright © The Boeing Company. See title page for details.

November 1, 2006

D632A008-ZZ022

3.2.11

ENROUTE All Engine

Flight Planning and Performance Manual

All Engine

737-800/CFM56-7B26 JAA/JAROPS Category C Brakes

Long Range Cruise Table

17000 FT to 12000 FT

PRESS ALT (1000 FT) (STD TAT) %N1 MAX TAT 17 KIAS MACH (-2) FF/ENG KTAS %N1 MAX TAT 16 KIAS MACH (-1) FF/ENG KTAS %N1 MAX TAT 15 KIAS MACH (1) FF/ENG KTAS %N1 MAX TAT 14 KIAS MACH (2) FF/ENG KTAS %N1 MAX TAT 13 KIAS MACH (4) FF/ENG KTAS %N1 MAX TAT 12 KIAS MACH (6) FF/ENG KTAS WEIGHT (1000 KG) 85 80.0 313 .641 1625 399 79.4 315 .633 1638 395 78.8 316 .624 1651 391 78.2 318 .616 1666 387 77.6 320 .608 1684 384 77.0 321 .600 1699 380 80 78.8 307 .628 1543 391 78.2 308 .620 1558 387 77.6 310 .612 1574 383 77.0 312 .604 1592 380 76.3 312 .595 1604 375 75.7 313 .585 1613 370 75 77.5 300 .615 1465 382 76.9 302 .607 1483 379 76.3 303 .598 1498 375 75.6 303 .588 1509 370 74.9 304 .578 1516 365 74.3 304 .568 1521 360 70 76.1 293 .601 1391 374 75.5 293 .591 1403 369 74.8 294 .581 1413 364 74.1 294 .571 1419 359 73.4 294 .560 1423 354 72.6 294 .550 1425 348 65 74.6 284 .583 1307 362 73.9 284 .572 1315 357 73.1 284 .562 1321 352 72.4 284 .551 1324 347 71.6 284 .541 1327 342 70.8 284 .532 1329 337 60 72.8 273 .562 1217 349 72.0 273 .551 1222 344 71.2 273 .541 1226 339 70.4 273 .531 1230 334 69.7 273 .522 1232 329 68.9 273 .512 1235 324 55 70.7 262 .540 1124 336 69.9 262 .530 1128 331 69.1 262 .520 1132 326 68.4 262 .510 1136 321 67.6 262 .501 1140 316 67.0 262 .492 1144 312 50 68.4 250 .517 1031 321 67.7 250 .507 1035 316 66.9 250 .497 1040 312 66.3 250 .488 1046 307 65.6 251 .479 1051 303 65.0 251 .471 1057 298 45 66.1 238 .492 940 306 65.4 238 .483 946 301 64.8 238 .474 952 297 64.1 238 .465 958 292 63.4 239 .457 964 288 62.7 239 .449 969 284 40 63.7 225 .466 853 290 63.0 225 .457 859 285 62.3 225 .449 865 281 61.5 226 .441 870 277 60.7 226 .433 875 273 59.9 226 .425 881 269

Max TAT not shown where %N1 can be set in ISA + 30°C conditions. Increase/decrease %N1 required by 1% per 5°C above/below standard TAT. Increase/decrease fuel flow 3% per 10°C above/below standard TAT. Increase/decrease KTAS by 1 knot per 1°C above/below standard TAT.

Max Cruise %N1

PRESS ALT (1000 FT) 17 16 15 14 13 12 -30 85.6 85.2 84.7 84.3 83.9 83.4 -25 86.5 86.0 85.6 85.2 84.7 84.3 -20 87.3 86.9 86.4 86.0 85.6 85.1 -15 88.2 87.7 87.3 86.8 86.4 85.9 -10 89.0 88.6 88.1 87.7 87.2 86.7 -5 89.8 89.4 88.9 88.5 88.0 87.6 TAT (°C) 0 5 90.7 91.5 90.2 91.0 89.8 90.6 89.3 90.1 88.8 89.6 88.4 89.1 10 92.3 91.8 91.3 90.9 90.4 89.9 15 91.8 91.8 91.9 91.7 91.2 90.7 20 91.0 91.0 91.0 91.0 90.9 90.9 25 90.1 90.2 90.2 90.2 90.2 90.1 30 89.2 89.3 89.4 89.4 89.3 89.3 35 88.2 88.3 88.4 88.5 88.5 88.5

With engine anti-ice on, decrease limit %N1 by 1.2. With engine and wing anti-ice on, decrease limit %N1 by 2.6.

Copyright © The Boeing Company. See title page for details.

3.2.12

D632A008-ZZ022

November 1, 2006

737-800/CFM56-7B26 JAA/JAROPS Category C Brakes

ENROUTE All Engine

Flight Planning and Performance Manual

All Engine

Long Range Cruise Table

11000 FT to 6000 FT

PRESS ALT (1000 FT) (STD TAT) %N1 MAX TAT 11 KIAS MACH (7) FF/ENG KTAS %N1 MAX TAT 10 KIAS MACH (9) FF/ENG KTAS %N1 MAX TAT 9 KIAS MACH (10) FF/ENG KTAS %N1 MAX TAT 8 KIAS MACH (12) FF/ENG KTAS %N1 MAX TAT 7 KIAS MACH (14) FF/ENG KTAS %N1 MAX TAT 6 KIAS MACH (15) FF/ENG KTAS WEIGHT (1000 KG) 85 76.4 322 .590 1709 375 75.7 322 .580 1717 370 75.0 322 .570 1722 365 74.3 322 .560 1724 360 73.5 322 .550 1726 355 72.8 322 .541 1728 350 80 75.0 313 .575 1619 365 74.3 313 .564 1623 360 73.6 313 .554 1624 355 72.8 313 .545 1627 350 72.0 313 .535 1629 345 71.3 313 .526 1631 341 75 73.5 304 .557 1523 355 72.8 304 .548 1526 350 72.0 304 .538 1528 345 71.2 304 .529 1530 340 70.5 304 .519 1532 335 69.8 304 .510 1536 330 70 71.8 294 .540 1427 344 71.1 294 .531 1429 339 70.3 294 .521 1432 334 69.6 294 .512 1435 329 68.9 294 .503 1439 324 68.3 294 .494 1444 320 65 70.0 284 .522 1332 332 69.3 284 .513 1335 327 68.6 284 .503 1339 322 68.0 284 .494 1343 318 67.3 284 .486 1349 314 66.7 284 .477 1356 309 60 68.2 273 .503 1239 320 67.5 273 .494 1244 315 66.9 273 .485 1249 311 66.3 274 .477 1255 306 65.7 274 .468 1262 302 65.0 274 .460 1268 298 55 66.3 262 .483 1150 307 65.7 262 .474 1156 303 65.1 263 .466 1162 299 64.4 263 .458 1168 294 63.7 263 .450 1174 290 62.9 263 .443 1180 287 50 64.4 251 .462 1062 294 63.7 251 .454 1068 290 62.9 251 .446 1074 286 62.2 252 .439 1080 282 61.4 252 .431 1086 278 60.6 252 .424 1093 274 45 62.0 239 .441 975 280 61.2 239 .433 980 276 60.4 239 .425 986 273 59.7 240 .418 992 269 59.0 240 .411 999 265 58.3 240 .404 1007 262 40 59.2 226 .418 886 266 58.5 226 .410 893 262 57.8 227 .403 899 258 57.1 227 .396 906 255 56.5 227 .390 914 251 55.9 228 .383 922 248

Max TAT not shown where %N1 can be set in ISA + 30°C conditions. Increase/decrease %N1 required by 1% per 5°C above/below standard TAT. Increase/decrease fuel flow 3% per 10°C above/below standard TAT. Increase/decrease KTAS by 1 knot per 1°C above/below standard TAT.

Max Cruise %N1

PRESS ALT (1000 FT) 11 10 9 8 7 6 -20 84.7 84.2 83.8 83.3 82.9 82.4 -15 85.5 85.0 84.6 84.1 83.7 83.2 -10 86.3 85.8 85.4 84.9 84.5 84.0 -5 87.1 86.6 86.2 85.7 85.3 84.8 0 87.9 87.4 87.0 86.5 86.1 85.6 5 88.7 88.2 87.8 87.3 86.8 86.3 TAT (°C) 10 15 89.5 90.2 89.0 89.7 88.5 89.3 88.1 88.8 87.6 88.3 87.1 87.8 20 90.9 90.5 90.0 89.6 89.1 88.5 25 90.0 89.9 90.0 90.0 89.8 89.3 30 89.3 89.2 89.2 89.2 89.2 89.3 35 88.4 88.4 88.4 88.4 88.4 88.5 40 87.5 87.5 87.5 87.6 87.6 87.7 45 86.5 86.5 86.6 86.7 86.8 86.8

With engine anti-ice on, decrease limit %N1 by 1.0. With engine and wing anti-ice on, decrease limit %N1 by 2.3.

Copyright © The Boeing Company. See title page for details.

November 1, 2006

D632A008-ZZ022

3.2.13

ENROUTE All Engine

Flight Planning and Performance Manual

All Engine

737-800/CFM56-7B26 JAA/JAROPS Category C Brakes

.79M Cruise Table

41000 FT to 32000 FT

PRESS ALT (1000 FT) 41 233 -29 453 239 -29 453 244 -29 453 250 -29 453 256 -29 453 262 -29 453 268 -27 455 274 -25 457 281 -23 459 287 -20 462 KIAS STD TAT KTAS %N1 MAX TAT FF/ENG %N1 MAX TAT FF/ENG %N1 MAX TAT FF/ENG %N1 MAX TAT FF/ENG %N1 MAX TAT FF/ENG %N1 MAX TAT FF/ENG %N1 MAX TAT FF/ENG %N1 MAX TAT FF/ENG %N1 MAX TAT FF/ENG %N1 MAX TAT FF/ENG WEIGHT (1000 KG) 85 80 75 70 65 60 55 90.3 -10 1064 88.9 -5 1060 87.8 -2 1065 86.9 2 1076 86.1 1091 85.5 1110 85.3 1138 85.1 1171 85.0 1209 85.0 1248 50 88.0 -3 982 87.2 0 992 86.4 1006 85.7 1023 85.1 1044 84.6 1068 84.5 1101 84.4 1138 84.4 1176 84.3 1216 45 86.5 2 923 85.8 940 85.2 959 84.7 982 84.2 1007 83.8 1035 83.7 1069 83.7 1106 83.7 1147 83.8 1190 40 85.3 888 84.8 900 84.3 923 83.9 948 83.4 975 83.1 1004 83.1 1041 83.2 1082 83.3 1127 83.5 1174

40

39

38

37

36

35

34

33

32

92.4 -9 1606 90.9 -3 1585

94.0 -16 1554 91.5 -8 1501 90.2 -2 1491 89.4 1 1498

92.8 -15 1437 90.6 -7 1400 89.5 -2 1398 88.8 2 1410 88.2 6 1429

91.5 -12 1330 89.6 -7 1307 88.7 -1 1309 88.1 3 1323 87.6 7 1345 87.3 9 1373

93.3 -17 1273 90.6 -10 1232 89.0 -5 1223 87.9 -1 1225 87.4 3 1240 86.9 7 1263 86.6 10 1292 86.4 1323

91.5 -13 1160 89.7 -8 1144 88.4 -3 1142 87.4 0 1149 86.6 3 1161 86.2 1185 86.0 1213 85.8 1245 85.6 1282

Max TAT not shown where %N1 can be set in ISA + 30°C conditions. Increase/decrease %N1 required by 1% per 5°C above/below standard TAT. Increase/decrease fuel flow 3% per 10°C above/below standard TAT. Increase/decrease KTAS by 1 knot per 1°C above/below standard TAT. Shaded area approximates optimum altitude.

Max Cruise %N1

PRESS ALT (1000 FT) 41 40 39 38 37 36 35 34 33 32 -60 87.4 87.5 87.6 87.7 87.8 87.5 87.2 86.4 85.8 85.3 -55 88.3 88.4 88.5 88.6 88.7 88.5 88.2 87.4 86.8 86.3 -50 89.3 89.4 89.5 89.6 89.7 89.4 89.1 88.3 87.8 87.2 -45 90.2 90.3 90.4 90.5 90.6 90.3 90.0 89.3 88.7 88.2 -40 91.1 91.2 91.3 91.4 91.5 91.2 90.9 90.2 89.7 89.1 -35 92.0 92.1 92.2 92.3 92.4 92.1 91.8 91.1 90.6 90.0 TAT (°C) -30 -25 92.9 93.7 93.0 93.8 93.1 94.0 93.2 94.1 93.3 94.2 93.0 93.9 92.7 93.6 92.1 93.0 91.6 92.5 90.9 91.8 -20 94.6 94.7 94.8 94.9 95.0 94.7 94.4 93.9 93.4 92.7 -15 94.4 94.5 94.6 94.6 94.7 94.6 95.0 94.7 94.3 93.6 -10 93.5 93.6 93.7 93.8 93.9 93.8 94.4 94.5 94.7 94.5 -5 92.8 92.9 93.0 93.1 93.2 93.1 93.6 93.8 94.0 94.1 0 92.1 92.2 92.4 92.5 92.6 92.5 92.9 93.1 93.3 93.3 5 91.3 91.5 91.8 91.9 92.0 91.9 92.3 92.6 92.8 92.8

With engine anti-ice on, decrease limit %N1 by 1.0. With engine and wing anti-ice on, decrease limit %N1 by 3.4.

Copyright © The Boeing Company. See title page for details.

3.2.14

D632A008-ZZ022

November 1, 2006

737-800/CFM56-7B26 JAA/JAROPS Category C Brakes

ENROUTE All Engine

Flight Planning and Performance Manual

All Engine

.79M Cruise Table

31000 FT to 25000 FT

PRESS ALT (1000 FT) 31 293 -18 464 300 -16 466 306 -14 468 313 -11 470 320 -9 472 326 -7 474 333 -5 476 KIAS STD TAT KTAS %N1 MAX TAT FF/ENG %N1 MAX TAT FF/ENG %N1 MAX TAT FF/ENG %N1 MAX TAT FF/ENG %N1 MAX TAT FF/ENG %N1 MAX TAT FF/ENG %N1 MAX TAT FF/ENG WEIGHT (1000 KG) 85 90.0 1 1589 89.4 4 1604 88.9 8 1627 88.6 11 1654 88.3 14 1686 88.1 17 1722 87.9 19 1764 80 88.9 5 1516 88.4 8 1540 88.1 11 1570 87.8 14 1602 87.6 17 1638 87.4 19 1679 87.3 21 1726 75 87.8 9 1455 87.6 11 1486 87.3 14 1519 87.1 17 1556 87.0 19 1597 86.9 21 1643 86.8 23 1692 70 87.0 12 1403 86.7 14 1437 86.6 17 1476 86.5 19 1518 86.4 21 1563 86.4 23 1610 86.4 25 1659 65 86.2 1358 86.1 1398 86.0 19 1440 85.9 21 1484 85.9 23 1530 85.9 25 1577 85.9 26 1629 60 85.5 1322 85.5 1364 85.4 1407 85.4 1452 85.4 1499 85.5 1550 85.6 28 1606 55 84.9 1289 84.9 1332 84.9 1377 84.9 1424 85.0 1476 85.2 1531 85.3 1591 50 84.3 1259 84.4 1305 84.5 1354 84.6 1406 84.8 1461 85.0 1520 85.2 1582 45 83.9 1237 84.0 1287 84.2 1340 84.4 1395 84.7 1453 84.9 1513 85.1 1577 40 83.7 1225 83.9 1277 84.1 1332 84.3 1389 84.6 1449 84.8 1511 85.1 1576

30

29

28

27

26

25

Max TAT not shown where %N1 can be set in ISA + 30°C conditions. Increase/decrease %N1 required by 1% per 5°C above/below standard TAT. Increase/decrease fuel flow 3% per 10°C above/below standard TAT. Increase/decrease KTAS by 1 knot per 1°C above/below standard TAT. Shaded area approximates optimum altitude.

Max Cruise %N1

PRESS ALT (1000 FT) 31 30 29 28 27 26 25 -45 87.7 87.0 86.4 85.8 85.3 84.7 84.2 -40 88.6 87.9 87.3 86.7 86.2 85.6 85.1 -35 89.5 88.8 88.2 87.6 87.1 86.5 86.0 -30 90.4 89.7 89.1 88.5 88.0 87.4 86.9 -25 91.3 90.6 90.0 89.4 88.8 88.3 87.8 -20 92.1 91.5 90.9 90.3 89.7 89.2 88.7 TAT (°C) -15 -10 93.0 93.9 92.4 93.3 91.8 92.7 91.2 92.0 90.6 91.5 90.0 90.9 89.5 90.4 -5 94.2 94.1 93.5 92.9 92.3 91.8 91.2 0 93.4 93.5 93.6 93.7 93.2 92.6 92.1 5 92.7 92.9 93.0 93.1 93.2 93.3 92.9 10 92.2 92.3 92.3 92.5 92.7 92.8 92.8 15 91.6 91.8 91.8 92.0 92.1 92.2 92.3 20 91.0 91.1 91.2 91.4 91.5 91.6 91.8

With engine anti-ice on, decrease limit %N1 by 1.2. With engine and wing anti-ice on, decrease limit %N1 by 3.1.

Copyright © The Boeing Company. See title page for details.

November 1, 2006

D632A008-ZZ022

3.2.15

ENROUTE All Engine

Flight Planning and Performance Manual

All Engine

737-800/CFM56-7B26 JAA/JAROPS Category C Brakes

Wind-Altitude Trade

LRC

PRESSURE ALTITUDE (1000 FT) 41 39 37 35 33 31 29 27 25 CRUISE WEIGHT (1000 KG) 85 80 75 70 24 7 0 2 9 19 32 47 65 10 1 1 7 17 30 44 60 60 12 2 1 6 16 28 43 58 74 55 2 0 5 15 27 42 58 74 90 50 0 5 15 27 42 58 75 91 107 45 6 16 29 44 61 77 94 111 126 40 18 32 48 65 82 99 116 132 147

25 7 1 1 7 17

12 2 0 5 14 25

18 4 0 3 11 22 35

.79M

PRESSURE ALTITUDE (1000 FT) 41 39 37 35 33 31 29 27 25 CRUISE WEIGHT (1000 KG) 85 80 75 70 33 8 0 5 20 42 69 100 65 12 0 3 16 37 64 95 127 60 16 1 2 14 34 61 91 124 159 55 2 1 12 32 59 90 123 159 194 50 1 12 32 59 91 125 161 197 233 45 13 34 62 95 130 167 203 240 276 40 40 69 103 139 177 214 252 288 323

34 9 0 4 17 37

16 1 1 12 30 55

24 4 0 8 25 48 75

Above wind factor tables are for calculation of wind required to maintain present range capability at new pressure altitude, i.e. break-even wind. Method: 1. Read wind factors for present and new altitudes from table. 2. Determine difference (new altitude wind factor minus present altitude wind factor); this difference may be positive or negative. 3. Break-even wind at new altitude is present altitude wind plus difference from step 2. Example: LRC at 33000 ft, 60000 kg, present wind -20 knots (headwind) To find break-even wind for: A) Climb to 37000 ft B) Descent to 29000 ft A) Wind factors from LRC table at 60000 kg are 16 (33000 ft) and 1 (37000 ft). Difference is -15 so break-even wind is -20 plus -15, i.e. -35 knots (headwind). B) Similarly, wind factors are 16 (33000 ft) and 43 (29000 ft). Difference is +27 so break-even wind is -20 plus (+27), i.e. +7 knots (tailwind).

Copyright © The Boeing Company. See title page for details.

3.2.16

D632A008-ZZ022

November 1, 2006

737-800/CFM56-7B26 JAA/JAROPS Category C Brakes

ENROUTE All Engine

Flight Planning and Performance Manual

All Engine

Descent

.78/280/250

PRESSURE ALTITUDE (FT) 41000 39000 37000 35000 33000 31000 29000 27000 25000 23000 21000 19000 17000 15000 10000 5000 1500 TIME (MIN) 26 25 24 24 23 22 21 20 19 18 17 16 15 14 10 7 4 FUEL (KG) 340 330 330 320 320 310 310 300 290 280 270 260 250 240 200 150 110 40 101 96 92 88 84 80 75 70 66 61 57 52 48 43 30 18 9 DISTANCE (NM) LANDING WEIGHT (1000 KG) 50 60 118 130 112 124 107 119 102 113 98 109 93 103 87 96 82 90 76 84 71 78 65 72 60 66 55 60 49 54 34 36 19 20 9 9 DISTANCE (NM) LANDING WEIGHT (1000 KG) 50 60 129 140 124 134 118 128 111 121 105 114 98 107 92 100 85 93 79 86 73 80 67 73 61 66 55 59 49 53 34 36 19 20 9 9 70 137 132 127 121 116 110 103 96 90 83 76 70 63 57 38 21 9

.78/250

PRESSURE ALTITUDE (FT) 41000 39000 37000 35000 33000 31000 29000 27000 25000 23000 21000 19000 17000 15000 10000 5000 1500 TIME (MIN) 28 27 27 26 25 23 22 21 20 19 18 17 15 14 10 7 4 FUEL (KG) 360 350 350 340 330 320 320 310 300 290 280 260 250 240 200 150 110 40 113 108 103 97 92 86 81 75 70 64 59 54 48 43 30 18 9 70 144 139 133 126 118 111 104 97 90 83 76 69 62 55 38 21 9

Allowances for a straight-in approach are included.

Copyright © The Boeing Company. See title page for details.

November 1, 2006

D632A008-ZZ022

3.2.17

ENROUTE All Engine

Flight Planning and Performance Manual

All Engine

737-800/CFM56-7B26 JAA/JAROPS Category C Brakes

Holding

Flaps Up

PRESSURE ALTITUDE (FT) %N1 41000 KIAS FF/ENG %N1 35000 KIAS FF/ENG %N1 30000 KIAS FF/ENG %N1 25000 KIAS FF/ENG %N1 20000 KIAS FF/ENG %N1 15000 KIAS FF/ENG %N1 10000 KIAS FF/ENG %N1 5000 KIAS FF/ENG %N1 1500 KIAS FF/ENG WEIGHT (1000 KG) 85 80 75 70 65 60 55 89.8 214 1050 81.7 210 970 77.4 208 950 73.0 207 950 68.7 205 970 64.6 204 990 60.5 203 1010 56.7 203 1030 54.2 202 1050 50 86.9 203 940 79.4 200 890 75.0 198 880 70.7 197 870 66.2 195 890 62.4 195 910 58.1 194 920 54.5 193 950 52.0 192 970 45 84.0 192 840 76.8 189 800 72.2 187 790 68.0 186 810 63.8 185 820 59.6 185 840 55.7 185 840 52.1 185 870 49.6 185 900 40 81.1 180 740 73.9 178 710 69.4 178 720 65.0 178 730 61.1 178 740 56.7 178 760 53.0 178 780 49.5 178 810 47.1 178 840

88.4 263 1540 84.1 259 1490 79.9 257 1480 75.6 255 1500 71.6 254 1510 67.7 253 1520 65.1 252 1540

94.0 250 1560 86.8 254 1430 82.6 251 1400 78.3 249 1390 74.0 247 1410 69.9 246 1420 66.2 245 1430 63.4 244 1460

90.2 249 1400 85.1 246 1330 81.0 243 1300 76.5 241 1300 72.5 239 1330 68.3 238 1340 64.7 238 1350 61.6 236 1370

88.0 240 1280 83.4 236 1230 79.2 234 1210 74.7 233 1220 70.6 231 1240 66.6 230 1250 62.8 229 1270 59.8 229 1290

85.9 230 1170 81.5 227 1140 77.3 225 1120 72.9 224 1140 68.6 223 1150 64.9 222 1170 60.7 221 1190 58.1 221 1210

83.9 220 1060 79.5 218 1050 75.2 216 1030 71.0 215 1050 66.7 214 1070 62.9 213 1090 58.7 212 1110 56.2 211 1130

This table includes 5% additional fuel for holding in a racetrack pattern. Increase/decrease fuel flow by 3% per 10°C above/below standard TAT.

Copyright © The Boeing Company. See title page for details.

3.2.18

D632A008-ZZ022

November 1, 2006

737-800/CFM56-7B26 JAA/JAROPS Category C Brakes

ENROUTE Engine Inoperative

Flight Planning and Performance Manual

3.3 ENROUTE-Engine Inoperative

ENGINE INOP

MAX CONTINUOUS THRUST

Engine Inoperative

Speed Capability

40

Based on standard day with A/C on

WEIGHT (1000 KG)

38

;;;;;;;;;;;;;;;; ;;;;;;;;;;;;;;;; ;;;;;;;;;;;;;;;; ;;;;;;;;;;;;;;;; ;;;;;;;;;;;;;;;; ;;;;;;;;;;;;;;;; ;;;;;;;;;;;;;;;; ;;;;;;;;;;;;;;;; ;;;;;;;;;;;;;;;; ;;;;;;;;;;;;;;;; ;;;;;;;;;;;;;;;; ;;;;;;;;;;;;;;;; ;;;;;;;;;;;;;;;; ;;;;;;;;;;;;;;;; ;;;;;;;;;;;;;;;; ;;;;;;;;;;;;;;;; ;;;;;;;;;;;;;;;; ;;;;;;;;;;;;;;;; ;;;;;;;;;;;;;;;; ;;;;;;;;;;;;;;;; ;;;;;;;;;;;;;;;; ;;;;;;;;;;;;;;;;

36 42 46 50 54 58 62 66 70 74 78 82 32 28 24 20 16 12 8 4 0 300 320 340 360 380 400

VM O

ALTITUDE

(1000 FT)

420

440

TRUE AIRSPEED

(KTAS)

Copyright © The Boeing Company. See title page for details.

November 1, 2006

D632A008-ZZ022

3.3.1

ENROUTE Engine Inoperative

Flight Planning and Performance Manual

737-800/CFM56-7B26 JAA/JAROPS Category C Brakes

ENGINE INOP

MAX CONTINUOUS THRUST

Engine Inoperative

Long Range Cruise Altitude Capability

Max Continuous Thrust, 100 ft/min residual rate of climb

WEIGHT (1000 KG) 85 80 75 70 65 60 55 50 45 40 ISA + 10°C & BELOW 13800 16100 18100 20200 21800 23400 25300 28100 30700 33200 PRESSURE ALTITUDE (FT) ISA + 15°C 11300 13700 16300 18500 20600 22300 24100 26700 29700 32300 ISA + 20°C 8900 11400 14000 16300 18600 20700 22700 24800 28100 31100

With engine anti-ice on, decrease altitude capability by 2100 ft. With engine and wing anti-ice on, decrease altitude capability by 5700 ft.

Max Cruise Thrust, 100 ft/min residual rate of climb

WEIGHT (1000 KG) 85 80 75 70 65 60 55 50 45 40 ISA + 10°C & BELOW 1700 4900 8400 12000 15500 18900 22000 25500 29000 31700 PRESSURE ALTITUDE (FT) ISA + 15°C 1800 5500 9000 12700 16300 19900 23400 26900 30400 ISA + 20°C

2200 6100 9700 13600 17300 21000 25200 28800

With engine anti-ice on, decrease altitude capability by 2100 ft. With engine and wing anti-ice on, decrease altitude capability by 4600 ft.

Copyright © The Boeing Company. See title page for details.

3.3.2

D632A008-ZZ022

November 1, 2006

737-800/CFM56-7B26 JAA/JAROPS Category C Brakes

ENROUTE Engine Inoperative

Flight Planning and Performance Manual

ENGINE INOP

MAX CONTINUOUS THRUST

Engine Inoperative

280 KIAS Altitude Capability

Max Continuous Thrust, 100 ft/min residual rate of climb

WEIGHT (1000 KG) 85 80 75 70 65 60 55 50 45 40 ISA + 10°C & BELOW 16100 17400 18600 19800 20700 21400 22200 22900 23400 23800 PRESSURE ALTITUDE (FT) ISA + 15°C 14700 16000 17200 18300 19500 20400 21200 21900 22400 22900 ISA + 20°C 12900 14400 15600 16700 17800 18800 19900 20600 21200 21700

With engine anti-ice on, decrease altitude capability by 1400 ft. With engine and wing anti-ice on, decrease altitude capability by 5400 ft.

Max Cruise Thrust, 100 ft/min residual rate of climb

WEIGHT (1000 KG) 85 80 75 70 65 60 55 50 45 40 ISA + 10°C & BELOW 7000 8900 10800 12700 14300 15700 17000 18200 19200 20000 PRESSURE ALTITUDE (FT) ISA + 15°C 3800 5800 7700 9400 11100 12800 14200 15500 16500 17400 ISA + 20°C 2600 4400 6200 7900 9400 11000 12400 13500 14500

With engine anti-ice on, decrease altitude capability by 2300 ft. With engine and wing anti-ice on, decrease altitude capability by 5100 ft.

Copyright © The Boeing Company. See title page for details.

November 1, 2006

D632A008-ZZ022

3.3.3

ENROUTE Engine Inoperative

Flight Planning and Performance Manual

737-800/CFM56-7B26 JAA/JAROPS Category C Brakes

ENGINE INOP

MAX CONTINUOUS THRUST

Engine Inoperative

290 KIAS Altitude Capability

Max Continuous Thrust, 100 ft/min residual rate of climb

WEIGHT (1000 KG) 85 80 75 70 65 60 55 50 45 40 ISA + 10°C & BELOW 15400 16500 17600 18700 19800 20600 21200 21700 22200 22600 PRESSURE ALTITUDE (FT) ISA + 15°C 13800 15100 16200 17200 18300 19300 20200 20800 21200 21600 ISA + 20°C 11800 13200 14400 15500 16500 17400 18400 19200 19900 20300

With engine anti-ice on, decrease altitude capability by 1500 ft. With engine and wing anti-ice on, decrease altitude capability by 5500 ft.

Max Cruise Thrust, 100 ft/min residual rate of climb

WEIGHT (1000 KG) 85 80 75 70 65 60 55 50 45 40 ISA + 10°C & BELOW 5300 7100 8800 10400 12100 13500 14700 15700 16600 17300 PRESSURE ALTITUDE (FT) ISA + 15°C 2100 3900 5600 7200 8700 10200 11600 12800 13800 14500 ISA + 20°C 400 2300 3900 5400 6900 8300 9400 10400 11300

With engine anti-ice on, decrease altitude capability by 2300 ft. With engine and wing anti-ice on, decrease altitude capability by 5000 ft.

Copyright © The Boeing Company. See title page for details.

3.3.4

D632A008-ZZ022

November 1, 2006

737-800/CFM56-7B26 JAA/JAROPS Category C Brakes

ENROUTE Engine Inoperative

Flight Planning and Performance Manual

ENGINE INOP

MAX CONTINUOUS THRUST

Engine Inoperative

310 KIAS Altitude Capability

Max Continuous Thrust, 100 ft/min residual rate of climb

WEIGHT (1000 KG) 85 80 75 70 65 60 55 50 45 40 ISA + 10°C & BELOW 13200 14300 15300 16300 17100 17900 18500 19100 19600 19900 PRESSURE ALTITUDE (FT) ISA + 15°C 11400 12500 13500 14600 15500 16300 16900 17500 18000 18300 ISA + 20°C 9100 10200 11300 12400 13300 14200 14900 15500 16000 16300

With engine anti-ice on, decrease altitude capability by 1600 ft. With engine and wing anti-ice on, decrease altitude capability by 5800 ft.

Max Cruise Thrust, 100 ft/min residual rate of climb

WEIGHT (1000 KG) 85 80 75 70 65 60 55 50 45 40 ISA + 10°C & BELOW 1200 2700 4200 5600 7000 8100 9100 10000 10700 11100 PRESSURE ALTITUDE (FT) ISA + 15°C ISA + 20°C

2200 3500 4600 5700 6700 7300 7700

1200 2300 3200 3800 4200

With engine anti-ice on, decrease altitude capability by 2300 ft. With engine and wing anti-ice on, decrease altitude capability by 4900 ft.

Copyright © The Boeing Company. See title page for details.

November 1, 2006

D632A008-ZZ022

3.3.5

ENROUTE Engine Inoperative

Flight Planning and Performance Manual

737-800/CFM56-7B26 JAA/JAROPS Category C Brakes

ENGINE INOP

MAX CONTINUOUS THRUST

Engine Inoperative

330 KIAS Altitude Capability

Max Continuous Thrust, 100 ft/min residual rate of climb

WEIGHT (1000 KG) 85 80 75 70 65 60 55 50 45 40 ISA + 10°C & BELOW 10500 11400 12300 13200 13800 14500 15000 15400 15600 15800 PRESSURE ALTITUDE (FT) ISA + 15°C 8300 9300 10200 11000 11700 12400 13000 13400 13700 13800 ISA + 20°C 5700 6800 7700 8500 9200 9900 10400 10900 11100 11300

With engine anti-ice on, decrease altitude capability by 1800 ft. With engine and wing anti-ice on, decrease altitude capability by 5700 ft.

Max Cruise Thrust, 100 ft/min residual rate of climb

WEIGHT (1000 KG) 85 80 75 70 65 60 55 50 45 40 ISA + 10°C & BELOW PRESSURE ALTITUDE (FT) ISA + 15°C ISA + 20°C

1000 2000 2800 3300 3600 3900

With engine anti-ice on, decrease altitude capability by 2300 ft. With engine and wing anti-ice on, decrease altitude capability by 4900 ft.

Copyright © The Boeing Company. See title page for details.

3.3.6

D632A008-ZZ022

November 1, 2006

737-800/CFM56-7B26 JAA/JAROPS Category C Brakes

ENROUTE Engine Inoperative

Flight Planning and Performance Manual

ENGINE INOP

MAX CONTINUOUS THRUST

Long Range Cruise Table

30000 FT to 25000 FT

PRESS ALT (1000 FT) (STD TAT) %N1 MAX TAT 30 KIAS MACH (-28) FF/ENG KTAS %N1 MAX TAT 29 KIAS MACH (-26) FF/ENG KTAS %N1 MAX TAT 28 KIAS MACH (-25) FF/ENG KTAS %N1 MAX TAT 27 KIAS MACH (-22) FF/ENG KTAS %N1 MAX TAT 26 KIAS MACH (-21) FF/ENG KTAS %N1 MAX TAT 25 KIAS MACH (-19) FF/ENG KTAS WEIGHT (1000 KG) 85 80 75 70 65 60 55 50 45 94.5 -7 223 .601 1659 354 93.2 -1 225 .593 1649 351 91.9 3 228 .587 1651 349 90.6 8 229 .578 1647 345 89.4 229 .567 1635 340 88.4 229 .556 1627 334 40 90.6 216 .582 1473 343 89.2 216 .571 1461 338 88.0 216 .559 1452 333 87.1 216 .548 1445 327 86.2 216 .536 1438 321 85.2 216 .525 1432 316

97.7 -10 244 .614 2060 366 96.0 -5 245 .605 2028 362 94.5 0 247 .597 2010 359

97.1 -11 233 .613 1873 363 95.4 -6 234 .603 1844 359 94.0 -1 236 .596 1829 356 92.8 3 239 .589 1828 353 91.7 8 241 .583 1831 351

Max TAT not shown where %N1 can be set in ISA + 30°C conditions. Increase/decrease %N1 required by 1% per 5°C above/below standard TAT. Increase/decrease fuel flow 3% per 10°C above/below standard TAT. Increase/decrease KTAS by 1 knot per 1°C above/below standard TAT. Heavy line approximates max cruise thrust limit.

Max Continuous %N1

PRESS ALT (1000 FT) 30 29 28 27 26 25 -55 92.3 91.7 91.2 90.4 90.0 89.7 -50 93.3 92.7 92.1 91.4 91.0 90.6 -45 94.3 93.6 93.1 92.4 92.0 91.6 -40 95.2 94.6 94.1 93.3 92.9 92.5 -35 96.2 95.5 95.0 94.3 93.9 93.5 -30 97.1 96.5 95.9 95.2 94.8 94.4 TAT (°C) -25 -20 98.0 99.0 97.4 98.3 96.9 97.8 96.1 97.0 95.7 96.6 95.3 96.2 -15 98.8 99.1 98.7 98.0 97.5 97.1 -10 98.1 98.4 98.5 98.6 98.4 97.9 -5 97.1 97.5 97.6 97.7 98.0 98.2 0 96.3 96.6 96.6 96.8 97.0 97.3 5 95.4 95.8 95.8 96.0 96.2 96.4 10 94.4 94.7 94.8 95.0 95.3 95.6

With engine anti-ice on, decrease limit %N1 by 1.2. With engine and wing anti-ice on, decrease limit %N1 by 4.8.

Copyright © The Boeing Company. See title page for details.

November 1, 2006

D632A008-ZZ022

3.3.7

ENROUTE Engine Inoperative

Flight Planning and Performance Manual

737-800/CFM56-7B26 JAA/JAROPS Category C Brakes

ENGINE INOP

MAX CONTINUOUS THRUST

Long Range Cruise Table

24000 FT to 19000 FT

PRESS ALT (1000 FT) (STD TAT) %N1 MAX TAT 24 KIAS MACH (-17) FF/ENG KTAS %N1 MAX TAT 23 KIAS MACH (-15) FF/ENG KTAS %N1 MAX TAT 22 KIAS MACH (-13) FF/ENG KTAS %N1 MAX TAT 21 KIAS MACH (-11) FF/ENG KTAS %N1 MAX TAT 20 KIAS MACH (-9) FF/ENG KTAS %N1 MAX TAT 19 KIAS MACH (-8) FF/ENG KTAS WEIGHT (1000 KG) 85 80 75 70 65 60 96.3 -1 256 .605 2209 365 94.9 5 258 .597 2192 362 93.8 11 260 .590 2192 360 92.8 16 263 .585 2207 358 91.7 23 263 .575 2200 353 90.7 263 .564 2197 348 55 93.4 6 249 .590 2007 357 92.4 12 252 .585 2018 355 91.2 18 252 .574 2009 350 90.2 253 .563 2005 345 89.3 253 .552 2002 339 88.4 252 .541 1999 334 50 90.5 241 .572 1819 345 89.4 241 .561 1814 340 88.5 241 .549 1811 335 87.6 241 .538 1808 329 86.7 241 .527 1805 324 85.8 240 .516 1803 318 45 87.5 229 .544 1621 329 86.6 229 .533 1618 323 85.7 229 .522 1615 318 84.7 228 .511 1613 312 83.8 228 .500 1610 307 82.9 227 .489 1609 302 40 84.3 216 .513 1428 310 83.4 215 .502 1425 305 82.5 215 .491 1422 299 81.5 214 .480 1420 294 80.7 214 .471 1424 289 79.9 214 .462 1428 285

99.0 4 283 .616 2802 378 97.4 9 284 .607 2768 374

97.7 4 274 .610 2591 373 96.2 10 276 .602 2568 370 95.1 15 278 .595 2565 367

97.9 -2 265 .612 2418 372 96.3 5 266 .604 2388 368 95.1 10 268 .596 2376 365 94.0 16 270 .590 2382 362 93.1 20 273 .584 2399 360

Max TAT not shown where %N1 can be set in ISA + 30°C conditions. Increase/decrease %N1 required by 1% per 5°C above/below standard TAT. Increase/decrease fuel flow 3% per 10°C above/below standard TAT. Increase/decrease KTAS by 1 knot per 1°C above/below standard TAT. Heavy line approximates max cruise thrust limit.

Max Continuous %N1

PRESS ALT (1000 FT) 24 23 22 21 20 19 -45 91.5 91.5 91.6 91.6 91.6 91.2 -40 92.5 92.4 92.6 92.6 92.6 92.1 -35 93.4 93.3 93.5 93.5 93.5 93.0 -30 94.3 94.2 94.4 94.4 94.4 93.9 -25 95.2 95.1 95.3 95.3 95.3 94.8 -20 96.1 96.0 96.2 96.2 96.2 95.7 TAT (°C) -15 -10 97.0 97.8 96.9 97.8 97.1 98.0 97.1 98.0 97.1 98.0 96.6 97.5 -5 98.7 98.6 98.9 98.8 98.8 98.3 0 97.9 98.5 99.1 99.7 99.7 99.2 5 97.0 97.5 98.0 98.6 99.2 99.6 10 96.2 96.7 97.1 97.6 98.1 98.5 15 95.2 95.7 96.3 96.8 97.3 97.6 20 94.2 94.7 95.2 95.8 96.3 96.8

With engine anti-ice on, decrease limit %N1 by 1.2. With engine and wing anti-ice on, decrease limit %N1 by 4.3.

Copyright © The Boeing Company. See title page for details.

3.3.8

D632A008-ZZ022

November 1, 2006

737-800/CFM56-7B26 JAA/JAROPS Category C Brakes

ENROUTE Engine Inoperative

Flight Planning and Performance Manual

ENGINE INOP

MAX CONTINUOUS THRUST

Long Range Cruise Table

18000 FT to 13000 FT

PRESS ALT (1000 FT) (STD TAT) %N1 MAX TAT 18 KIAS MACH (-6) FF/ENG KTAS %N1 MAX TAT 17 KIAS MACH (-4) FF/ENG KTAS %N1 MAX TAT 16 KIAS MACH (-2) FF/ENG KTAS %N1 MAX TAT 15 KIAS MACH (0) FF/ENG KTAS %N1 MAX TAT 14 KIAS MACH (1) FF/ENG KTAS %N1 MAX TAT 13 KIAS MACH (3) FF/ENG KTAS WEIGHT (1000 KG) 85 80 98.5 8 292 .612 2973 379 97.0 13 294 .603 2952 375 95.9 18 296 .596 2950 372 95.0 22 299 .590 2961 370 94.2 25 302 .585 2983 368 93.3 29 302 .575 2975 363 75 96.2 14 286 .599 2756 371 95.0 18 288 .593 2762 368 94.2 22 291 .587 2781 366 93.3 27 293 .579 2787 363 92.4 31 293 .569 2781 358 91.6 35 293 .559 2774 353 70 94.1 19 281 .589 2578 365 93.2 23 283 .582 2594 362 92.3 28 283 .572 2589 357 91.4 284 .562 2586 352 90.6 284 .551 2581 347 89.7 283 .541 2574 341 65 92.0 25 274 .574 2394 355 91.1 274 .563 2393 350 90.3 274 .553 2390 345 89.4 274 .542 2387 340 88.5 273 .532 2381 334 87.6 273 .521 2375 329 60 89.9 263 .553 2196 343 89.0 263 .543 2194 337 88.1 263 .532 2191 332 87.2 263 .521 2188 326 86.3 262 .511 2183 321 85.4 262 .500 2177 316 55 87.5 252 .530 1998 328 86.6 252 .520 1996 323 85.7 251 .509 1994 318 84.8 251 .498 1991 312 83.9 250 .488 1987 307 83.0 250 .478 1983 302 50 84.9 240 .505 1801 313 84.0 239 .495 1800 308 83.1 239 .484 1798 302 82.2 239 .475 1800 297 81.4 239 .466 1803 293 80.6 239 .458 1806 289 45 82.0 227 .478 1608 296 81.2 227 .469 1613 292 80.4 227 .461 1619 288 79.6 227 .452 1624 283 78.8 227 .444 1629 279 78.0 228 .437 1636 276 40 79.1 215 .453 1434 281 78.3 215 .445 1441 277 77.5 215 .437 1449 273 76.7 215 .429 1457 269 76.0 216 .422 1466 265 75.3 216 .415 1476 262

97.9 12 302 .607 3151 379 96.7 17 303 .600 3141 376 95.7 21 306 .593 3144 373 94.9 24 309 .588 3160 371

Max TAT not shown where %N1 can be set in ISA + 30°C conditions. Increase/decrease %N1 required by 1% per 5°C above/below standard TAT. Increase/decrease fuel flow 3% per 10°C above/below standard TAT. Increase/decrease KTAS by 1 knot per 1°C above/below standard TAT. Heavy line approximates max cruise thrust limit.

Max Continuous %N1

PRESS ALT (1000 FT) 18 17 16 15 14 13 -35 92.3 91.9 91.2 90.8 90.4 89.9 -30 93.3 92.8 92.2 91.8 91.3 90.8 -25 94.2 93.8 93.1 92.7 92.2 91.7 -20 95.1 94.7 94.0 93.6 93.1 92.6 -15 95.9 95.5 94.9 94.5 94.0 93.5 -10 96.8 96.4 95.8 95.4 94.9 94.4 TAT (°C) -5 0 97.7 98.5 97.3 98.1 96.6 97.5 96.3 97.1 95.8 96.6 95.3 96.1 5 99.4 98.9 98.3 98.0 97.5 96.9 10 98.9 99.2 99.1 98.8 98.3 97.8 15 98.0 98.4 98.8 99.2 98.9 98.6 20 97.2 97.6 98.0 98.4 98.3 98.2 25 96.2 96.7 97.2 97.7 97.5 97.4 30 95.3 95.8 96.3 96.8 96.8 96.8

With engine anti-ice on, decrease limit %N1 by 1.1. With engine and wing anti-ice on, decrease limit %N1 by 4.0.

Copyright © The Boeing Company. See title page for details.

November 1, 2006

D632A008-ZZ022

3.3.9

ENROUTE Engine Inoperative

Flight Planning and Performance Manual

737-800/CFM56-7B26 JAA/JAROPS Category C Brakes

ENGINE INOP

MAX CONTINUOUS THRUST

Long Range Cruise Table

12000 FT to 7000 FT

PRESS ALT (1000 FT) (STD TAT) %N1 MAX TAT 12 KIAS MACH (5) FF/ENG KTAS %N1 MAX TAT 11 KIAS MACH (6) FF/ENG KTAS %N1 MAX TAT 10 KIAS MACH (8) FF/ENG KTAS %N1 MAX TAT 9 KIAS MACH (9) FF/ENG KTAS %N1 MAX TAT 8 KIAS MACH (11) FF/ENG KTAS %N1 MAX TAT 7 KIAS MACH (13) FF/ENG KTAS WEIGHT (1000 KG) 85 94.1 28 311 .581 3169 368 93.3 32 311 .571 3160 363 92.5 36 311 .561 3152 358 91.7 40 311 .551 3145 353 90.8 44 311 .541 3138 348 90.0 311 .531 3132 342 80 92.5 33 302 .565 2967 358 91.7 37 302 .555 2959 353 90.8 41 302 .545 2951 348 90.0 302 .535 2944 343 89.1 302 .525 2938 337 88.3 301 .515 2932 332 75 90.8 293 .548 2766 347 89.9 293 .538 2758 342 89.0 293 .528 2751 337 88.2 292 .518 2745 332 87.4 292 .508 2739 326 86.5 291 .498 2733 321 70 88.8 283 .530 2566 336 88.0 283 .520 2559 331 87.1 282 .510 2552 325 86.3 282 .500 2547 320 85.4 281 .490 2542 315 84.5 281 .480 2537 310 65 86.8 273 .511 2368 324 85.9 272 .501 2361 318 85.1 271 .491 2356 313 84.2 271 .481 2351 308 83.4 271 .472 2353 304 82.6 271 .464 2357 299 60 84.6 261 .490 2172 310 83.7 261 .480 2166 305 82.9 261 .471 2168 301 82.1 261 .463 2171 297 81.4 261 .455 2175 293 80.6 261 .447 2181 289 55 82.2 250 .469 1985 297 81.5 250 .461 1988 293 80.7 250 .453 1991 289 79.9 251 .445 1997 285 79.1 251 .438 2004 281 78.4 251 .430 2013 278 50 79.8 239 .449 1810 285 79.1 239 .442 1815 281 78.3 240 .434 1822 277 77.6 240 .427 1831 274 76.9 241 .420 1841 270 76.3 241 .413 1851 267 45 77.2 228 .429 1643 272 76.5 229 .422 1652 268 75.9 229 .415 1661 265 75.3 230 .408 1672 262 74.6 230 .402 1683 258 74.0 231 .396 1695 255 40 74.6 217 .408 1485 259 74.0 218 .402 1496 255 73.4 218 .395 1506 252 72.7 219 .389 1518 249 72.0 220 .384 1530 247 71.3 221 .378 1543 244

Max TAT not shown where %N1 can be set in ISA + 30°C conditions. Increase/decrease %N1 required by 1% per 5°C above/below standard TAT. Increase/decrease fuel flow 3% per 10°C above/below standard TAT. Increase/decrease KTAS by 1 knot per 1°C above/below standard TAT. Heavy line approximates max cruise thrust limit.

Max Continuous %N1

PRESS ALT (1000 FT) 12 11 10 9 8 7 -25 91.2 90.8 90.4 90.0 89.6 89.2 -20 92.1 91.7 91.3 90.9 90.5 90.1 -15 93.0 92.6 92.2 91.8 91.4 90.9 -10 93.9 93.4 93.1 92.6 92.2 91.8 -5 94.7 94.3 93.9 93.5 93.1 92.6 0 95.6 95.1 94.8 94.4 93.9 93.5 TAT (°C) 5 10 96.4 97.2 96.0 96.8 95.6 96.4 95.2 96.0 94.7 95.6 94.3 95.1 15 98.0 97.6 97.2 96.8 96.4 95.9 20 98.1 98.1 98.0 97.6 97.1 96.7 25 97.4 97.3 97.2 97.2 97.3 97.4 30 96.7 96.6 96.5 96.5 96.5 96.5 35 95.9 95.9 95.8 95.8 95.8 95.8 40 95.0 95.0 94.9 94.9 95.0 95.0

With engine anti-ice on, decrease limit %N1 by 1.0. With engine and wing anti-ice on, decrease limit %N1 by 3.5.

Copyright © The Boeing Company. See title page for details.

3.3.10

D632A008-ZZ022

November 1, 2006

737-800/CFM56-7B26 JAA/JAROPS Category C Brakes

ENROUTE Engine Inoperative

Flight Planning and Performance Manual

ENGINE INOP

MAX CONTINUOUS THRUST

280 KIAS Cruise Table

29000 FT to 19000 FT

PRESS ALT (1000 FT) 29 KIAS STD TAT KTAS WEIGHT (1000 KG) 85 80 75 70 65 60 55 50 45 40

28

27

26

25 280 -12 398 280 -10 392 280 -9 386 280 -8 380 280 -6 375 280 -5 369 %N1 MAX TAT FF/ENG %N1 MAX TAT FF/ENG %N1 MAX TAT FF/ENG %N1 MAX TAT FF/ENG %N1 MAX TAT FF/ENG %N1 MAX TAT FF/ENG 96.4 0 2307 94.8 7 2272 93.7 13 2247 92.5 19 2232 91.5 2224 90.7 2222 95.6 2 2256 94.2 9 2224 93.1 15 2203 92.0 21 2192 91.0 2187 90.2 2185

24

23

22

21

20

19

98.7 6 2851

98.6 5 2757 96.8 11 2707

98.6 3 2676 96.8 10 2624 95.4 14 2589

96.8 7 2547 95.3 13 2510 94.0 18 2487

96.9 4 2482 95.3 11 2443 94.1 17 2417 92.9 22 2401

97.1 1 2423 95.4 8 2381 94.2 14 2354 93.0 20 2337 91.9 25 2328

95.7 5 2332 94.4 11 2301 93.2 17 2282 92.1 23 2271 91.2 2267

Max TAT not shown where %N1 can be set in ISA + 30°C conditions. Increase/decrease %N1 required by 1% per 5°C above/below standard TAT. Increase/decrease fuel flow 3% per 10°C above/below standard TAT. Increase/decrease KTAS by 1 knot per 1°C above/below standard TAT. Heavy line approximates max cruise thrust limit.

Max Continuous %N1

PRESS ALT (1000 FT) 24 23 22 21 20 19 -40 91.4 91.7 92.1 92.4 92.7 92.2 -35 92.3 92.7 93.0 93.3 93.6 93.2 -30 93.2 93.6 93.9 94.2 94.5 94.1 -25 94.1 94.5 94.8 95.1 95.4 95.0 -20 95.0 95.4 95.7 96.0 96.3 95.9 -15 95.9 96.2 96.6 96.9 97.2 96.8 TAT (°C) -10 -5 96.8 97.6 97.1 98.0 97.5 98.3 97.8 98.6 98.0 98.9 97.6 98.5 0 98.2 98.8 99.2 99.5 99.8 99.4 5 97.3 98.1 98.9 99.6 100.5 100.2 10 96.6 97.3 97.9 98.6 99.4 99.5 15 95.9 96.6 97.2 97.8 98.4 98.6 20 95.2 95.9 96.5 97.0 97.6 97.7 25 94.6 95.2 95.8 96.4 96.8 96.9

With engine anti-ice on, decrease limit %N1 by 1.2. With engine and wing anti-ice on, decrease limit %N1 by 4.3.

Copyright © The Boeing Company. See title page for details.

November 1, 2006

D632A008-ZZ022

3.3.11

ENROUTE Engine Inoperative

Flight Planning and Performance Manual

737-800/CFM56-7B26 JAA/JAROPS Category C Brakes

ENGINE INOP

MAX CONTINUOUS THRUST

280 KIAS Cruise Table

18000 FT to 8000 FT

PRESS ALT (1000 FT) 18 280 -3 363 280 -2 358 280 0 353 280 1 347 280 3 342 280 4 337 280 6 332 280 7 328 280 9 323 280 10 318 280 12 314 KIAS STD TAT KTAS %N1 MAX TAT FF/ENG %N1 MAX TAT FF/ENG %N1 MAX TAT FF/ENG %N1 MAX TAT FF/ENG %N1 MAX TAT FF/ENG %N1 MAX TAT FF/ENG %N1 MAX TAT FF/ENG %N1 MAX TAT FF/ENG %N1 MAX TAT FF/ENG %N1 MAX TAT FF/ENG %N1 MAX TAT FF/ENG WEIGHT (1000 KG) 85 99.0 -5 2965 97.2 12 2913 95.7 17 2878 94.3 22 2854 93.2 27 2835 92.3 31 2823 91.5 35 2813 90.6 2804 89.7 2797 88.9 2793 88.0 2790 80 96.9 11 2801 95.4 16 2768 94.1 22 2747 93.0 27 2732 92.1 31 2723 91.2 2714 90.4 2706 89.5 2699 88.7 2694 87.8 2692 87.0 2690 75 95.4 15 2674 94.1 20 2653 92.9 26 2640 92.0 31 2632 91.1 2626 90.2 2619 89.4 2613 88.5 2609 87.7 2606 86.9 2604 86.1 2605 70 94.0 19 2567 92.8 24 2554 91.9 29 2547 91.0 2543 90.2 2538 89.3 2534 88.5 2530 87.7 2527 86.9 2525 86.1 2526 85.3 2527 65 92.8 23 2474 91.9 28 2468 91.0 2466 90.2 2464 89.3 2461 88.5 2458 87.7 2456 86.9 2454 86.1 2454 85.3 2457 84.5 2459 60 91.9 26 2394 91.0 2393 90.2 2391 89.3 2389 88.5 2388 87.7 2387 86.9 2386 86.1 2386 85.3 2388 84.5 2390 83.7 2393 55 91.1 2326 90.2 2325 89.4 2324 88.6 2325 87.7 2325 87.0 2325 86.2 2325 85.4 2327 84.6 2329 83.8 2332 83.1 2334 50 90.4 2267 89.6 2266 88.7 2268 87.9 2270 87.1 2271 86.3 2272 85.6 2274 84.8 2276 84.0 2278 83.2 2281 82.5 2284 45 89.9 2222 89.0 2223 88.2 2225 87.4 2228 86.6 2229 85.8 2231 85.1 2233 84.3 2235 83.5 2237 82.7 2240 82.0 2243 40 89.4 2184 88.6 2185 87.7 2188 86.9 2191 86.2 2193 85.4 2196 84.6 2198 83.9 2201 83.1 2204 82.3 2206 81.6 2209

17

16

15

14

13

12

11

10

9

8

Max TAT not shown where %N1 can be set in ISA + 30°C conditions. Increase/decrease %N1 required by 1% per 5°C above/below standard TAT. Increase/decrease fuel flow 3% per 10°C above/below standard TAT. Increase/decrease KTAS by 1 knot per 1°C above/below standard TAT. Heavy line approximates max cruise thrust limit.

Max Continuous %N1

PRESS ALT (1000 FT) 18 17 16 15 14 13 12 11 10 9 8 -30 93.7 93.4 92.9 92.5 92.1 91.7 91.2 90.8 90.4 90.0 89.5 -25 94.6 94.3 93.8 93.4 93.0 92.6 92.1 91.7 91.3 90.9 90.4 -20 95.5 95.2 94.8 94.3 93.9 93.5 93.0 92.6 92.2 91.7 91.3 -15 96.4 96.1 95.6 95.2 94.8 94.4 93.9 93.5 93.1 92.6 92.1 -10 97.3 96.9 96.5 96.1 95.7 95.2 94.8 94.4 94.0 93.5 93.0 -5 98.2 97.8 97.4 97.0 96.5 96.1 95.7 95.2 94.8 94.4 93.9 TAT (°C) 0 5 99.0 99.8 98.6 99.5 98.2 99.0 97.8 98.7 97.4 98.2 96.9 97.8 96.5 97.3 96.1 96.9 95.7 96.5 95.2 96.0 94.7 95.5 10 99.7 99.8 99.9 99.5 99.1 98.6 98.2 97.7 97.3 96.8 96.3 15 98.8 99.0 99.2 99.3 99.3 99.4 99.0 98.5 98.2 97.7 97.2 20 97.8 98.0 98.2 98.5 98.5 98.6 98.6 98.7 98.8 98.5 97.9 25 97.1 97.2 97.4 97.7 97.7 97.7 97.8 97.8 97.9 97.9 97.9 30 96.4 96.6 96.8 97.0 97.0 97.0 97.0 97.1 97.1 97.1 97.2 35 95.7 95.9 96.1 96.4 96.4 96.5 96.5 96.4 96.4 96.5 96.5

With engine anti-ice on, decrease limit %N1 by 1.1. With engine and wing anti-ice on, decrease limit %N1 by 3.9.

Copyright © The Boeing Company. See title page for details.

3.3.12

D632A008-ZZ022

November 1, 2006

737-800/CFM56-7B26 JAA/JAROPS Category C Brakes

ENROUTE Engine Inoperative

Flight Planning and Performance Manual

ENGINE INOP

MAX CONTINUOUS THRUST

290 KIAS Cruise Table

29000 FT to 19000 FT

PRESS ALT (1000 FT) 29 KIAS STD TAT KTAS WEIGHT (1000 KG) 85 80 75 70 65 60 55 50 45 40

28

27

26

25

24 290 -9 405 290 -8 399 290 -6 393 290 -5 387 290 -3 382 %N1 MAX TAT FF/ENG %N1 MAX TAT FF/ENG %N1 MAX TAT FF/ENG %N1 MAX TAT FF/ENG %N1 MAX TAT FF/ENG 97.2 1 2473 95.6 9 2432 94.4 15 2405 93.3 21 2386 92.2 25 2377 96.6 3 2429 95.1 10 2393 94.0 16 2368 92.8 22 2353 91.9 26 2346

23

22

21

20

19

98.2 8 2856

98.3 7 2781 96.6 12 2735

98.6 -3 2720 96.8 11 2668 95.5 15 2634

97.1 8 2606 95.6 14 2570 94.4 18 2546

97.4 4 2558 95.8 11 2518 94.6 17 2490 93.5 21 2473

96.4 7 2485 95.0 13 2454 93.9 19 2432 92.8 23 2420

Max TAT not shown where %N1 can be set in ISA + 30°C conditions. Increase/decrease %N1 required by 1% per 5°C above/below standard TAT. Increase/decrease fuel flow 3% per 10°C above/below standard TAT. Increase/decrease KTAS by 1 knot per 1°C above/below standard TAT.

Max Continuous %N1

PRESS ALT (1000 FT) 23 22 21 20 19 -40 91.2 91.6 92.0 92.3 91.9 -35 92.1 92.6 92.9 93.3 92.8 -30 93.1 93.5 93.8 94.2 93.7 -25 93.9 94.4 94.7 95.1 94.6 -20 94.8 95.2 95.6 96.0 95.5 -15 95.7 96.1 96.5 96.8 96.4 TAT (°C) -10 -5 96.6 97.5 97.0 97.9 97.4 98.2 97.7 98.6 97.3 98.1 0 98.4 98.7 99.1 99.4 99.0 5 98.1 98.9 99.8 100.3 99.8 10 97.4 98.0 98.8 99.6 99.7 15 96.7 97.3 97.9 98.6 98.7 20 96.0 96.6 97.2 97.8 97.8 25 95.4 96.0 96.5 97.1 97.1

With engine anti-ice on, decrease limit %N1 by 1.2. With engine and wing anti-ice on, decrease limit %N1 by 4.3.

Copyright © The Boeing Company. See title page for details.

November 1, 2006

D632A008-ZZ022

3.3.13

ENROUTE Engine Inoperative

Flight Planning and Performance Manual

737-800/CFM56-7B26 JAA/JAROPS Category C Brakes

ENGINE INOP

MAX CONTINUOUS THRUST

290 KIAS Cruise Table

18000 FT to 8000 FT

PRESS ALT (1000 FT) 18 290 -2 376 290 -1 370 290 1 365 290 2 359 290 4 354 290 5 349 290 7 344 290 8 339 290 10 334 290 11 329 290 13 325 KIAS STD TAT KTAS %N1 MAX TAT FF/ENG %N1 MAX TAT FF/ENG %N1 MAX TAT FF/ENG %N1 MAX TAT FF/ENG %N1 MAX TAT FF/ENG %N1 MAX TAT FF/ENG %N1 MAX TAT FF/ENG %N1 MAX TAT FF/ENG %N1 MAX TAT FF/ENG %N1 MAX TAT FF/ENG %N1 MAX TAT FF/ENG WEIGHT (1000 KG) 85 80 98.2 9 2938 96.6 14 2897 95.2 19 2868 94.0 24 2848 93.0 29 2834 92.1 33 2825 91.3 37 2815 90.4 2808 89.6 2803 88.8 2800 88.0 2798 75 96.6 13 2813 95.2 18 2784 94.0 23 2764 93.0 28 2751 92.1 32 2743 91.3 36 2735 90.4 2728 89.6 2723 88.8 2720 88.0 2718 87.2 2718 70 95.3 16 2704 94.1 21 2685 93.0 26 2673 92.1 31 2667 91.3 2661 90.5 2656 89.6 2651 88.8 2648 88.0 2646 87.2 2646 86.4 2647 65 94.2 20 2613 93.1 24 2600 92.2 29 2594 91.3 2590 90.5 2585 89.7 2581 88.8 2578 88.0 2576 87.3 2575 86.5 2577 85.7 2580 60 93.2 23 2532 92.2 27 2525 91.4 32 2523 90.6 2520 89.8 2517 88.9 2515 88.1 2513 87.4 2512 86.6 2514 85.8 2516 85.0 2520 55 92.4 25 2465 91.6 30 2463 90.8 2461 89.9 2459 89.1 2458 88.3 2457 87.5 2457 86.8 2457 86.0 2460 85.2 2463 84.4 2466 50 91.9 27 2415 91.1 2414 90.2 2413 89.4 2414 88.6 2414 87.8 2414 87.1 2414 86.3 2415 85.5 2417 84.7 2420 84.0 2424 45 91.4 29 2374 90.6 2373 89.8 2373 88.9 2373 88.1 2373 87.4 2374 86.6 2374 85.8 2376 85.1 2379 84.3 2383 83.5 2386 40 91.1 2344 90.3 2343 89.4 2343 88.6 2344 87.8 2345 87.1 2347 86.3 2348 85.5 2351 84.8 2355 84.0 2359 83.3 2362

17

16

15

14

13

12

11

98.1 10 3028 96.6 15 2987 95.2 21 2959 94.0 25 2937 93.1 29 2922 92.2 33 2911 91.4 37 2901 90.5 2894 89.6 2889 88.8 2886

10

9

8

Max TAT not shown where %N1 can be set in ISA + 30°C conditions. Increase/decrease %N1 required by 1% per 5°C above/below standard TAT. Increase/decrease fuel flow 3% per 10°C above/below standard TAT. Increase/decrease KTAS by 1 knot per 1°C above/below standard TAT. Heavy line approximates max cruise thrust limit.

Max Continuous %N1

PRESS ALT (1000 FT) 18 17 16 15 14 13 12 11 10 9 8 -25 94.3 93.9 93.5 93.1 92.7 92.3 91.9 91.4 91.1 90.6 90.2 -20 95.2 94.8 94.4 94.0 93.6 93.2 92.8 92.3 91.9 91.5 91.0 -15 96.0 95.7 95.3 94.9 94.5 94.1 93.6 93.2 92.8 92.4 91.9 -10 96.9 96.6 96.2 95.8 95.4 95.0 94.5 94.1 93.7 93.2 92.8 -5 97.8 97.4 97.0 96.7 96.3 95.8 95.4 94.9 94.6 94.1 93.6 0 98.6 98.3 97.9 97.5 97.1 96.7 96.2 95.8 95.4 94.9 94.5 TAT (°C) 5 10 99.5 99.8 99.1 99.9 98.7 99.5 98.4 99.2 97.9 98.8 97.5 98.3 97.1 97.9 96.6 97.4 96.2 97.1 95.8 96.6 95.3 96.1 15 98.9 99.1 99.2 99.4 99.4 99.1 98.7 98.3 97.9 97.4 96.9 20 97.9 98.1 98.3 98.5 98.6 98.6 98.6 98.7 98.7 98.2 97.7 25 97.2 97.3 97.5 97.7 97.7 97.8 97.8 97.9 98.0 98.0 98.0 30 96.6 96.7 96.8 97.0 97.1 97.1 97.1 97.1 97.2 97.2 97.2 35 95.8 96.0 96.2 96.4 96.5 96.5 96.5 96.5 96.5 96.5 96.5 40 95.0 95.2 95.4 95.6 95.7 95.8 95.8 95.8 95.8 95.9 95.9

With engine anti-ice on, decrease limit %N1 by 1.1. With engine and wing anti-ice on, decrease limit %N1 by 3.9.

Copyright © The Boeing Company. See title page for details.

3.3.14

D632A008-ZZ022

November 1, 2006

737-800/CFM56-7B26 JAA/JAROPS Category C Brakes

ENROUTE Engine Inoperative

Flight Planning and Performance Manual

ENGINE INOP

MAX CONTINUOUS THRUST

310 KIAS Cruise Table

29000 FT to 19000 FT

PRESS ALT (1000 FT) 29 KIAS STD TAT KTAS WEIGHT (1000 KG) 85 80 75 70 65 60 55 50 45 40

28

27

26

25

24

23

22

21 310 -2 413 310 -1 407 %N1 MAX TAT FF/ENG %N1 MAX TAT FF/ENG 98.6 8 2887 96.9 13 2844 97.9 10 2835 96.4 15 2797 97.4 11 2796 96.0 16 2762 97.1 12 2773 95.8 16 2741

20

19

97.7 11 2903

Max TAT not shown where %N1 can be set in ISA + 30°C conditions. Increase/decrease %N1 required by 1% per 5°C above/below standard TAT. Increase/decrease fuel flow 3% per 10°C above/below standard TAT. Increase/decrease KTAS by 1 knot per 1°C above/below standard TAT.

Max Continuous %N1

PRESS ALT (1000 FT) 20 19 -35 92.4 91.9 -30 93.3 92.9 -25 94.2 93.7 -20 95.1 94.6 -15 96.0 95.5 -10 96.9 96.4 TAT (°C) -5 0 97.7 98.6 97.3 98.1 5 99.5 99.0 10 99.8 99.8 15 98.9 99.0 20 98.2 98.2 25 97.5 97.5 30 96.8 96.8

With engine anti-ice on, decrease limit %N1 by 1.1. With engine and wing anti-ice on, decrease limit %N1 by 4.2.

Copyright © The Boeing Company. See title page for details.

November 1, 2006

D632A008-ZZ022

3.3.15

ENROUTE Engine Inoperative

Flight Planning and Performance Manual

737-800/CFM56-7B26 JAA/JAROPS Category C Brakes

ENGINE INOP

MAX CONTINUOUS THRUST

310 KIAS Cruise Table

18000 FT to 8000 FT

PRESS ALT (1000 FT) 18 310 0 401 310 2 395 310 3 389 310 5 383 310 6 378 310 8 372 310 9 367 310 10 362 310 12 357 310 13 352 310 15 347 KIAS STD TAT KTAS %N1 MAX TAT FF/ENG %N1 MAX TAT FF/ENG %N1 MAX TAT FF/ENG %N1 MAX TAT FF/ENG %N1 MAX TAT FF/ENG %N1 MAX TAT FF/ENG %N1 MAX TAT FF/ENG %N1 MAX TAT FF/ENG %N1 MAX TAT FF/ENG %N1 MAX TAT FF/ENG %N1 MAX TAT FF/ENG WEIGHT (1000 KG) 85 80 75 70 65 97.2 13 2945 96.0 18 2916 94.8 22 2895 93.8 26 2881 92.9 30 2872 92.2 34 2865 91.3 38 2857 90.5 2852 89.7 2850 89.0 2850 88.2 2852 60 96.3 16 2870 95.2 20 2847 94.2 24 2832 93.2 28 2822 92.4 32 2816 91.6 36 2810 90.8 2804 90.0 2801 89.3 2801 88.5 2802 87.8 2804 55 95.8 17 2816 94.7 21 2796 93.6 26 2784 92.8 30 2776 92.0 34 2771 91.2 38 2765 90.4 2761 89.6 2758 88.8 2758 88.1 2759 87.3 2762 50 95.3 19 2771 94.2 23 2754 93.2 27 2744 92.4 31 2738 91.6 35 2732 90.8 2726 90.0 2722 89.2 2720 88.5 2720 87.7 2722 87.0 2726 45 94.9 20 2738 93.9 24 2723 92.9 28 2714 92.1 32 2710 91.3 36 2704 90.5 2699 89.7 2697 89.0 2696 88.2 2697 87.5 2701 86.8 2705 40 94.7 20 2719 93.7 25 2706 92.8 29 2700 92.0 33 2697 91.2 37 2693 90.4 2689 89.6 2687 88.9 2687 88.2 2688 87.4 2691 86.7 2696

17

16

15

14

13

12

11

10

9

8

97.5 15 3241 96.2 20 3205 95.1 24 3178 94.1 28 3160 93.2 32 3148 92.4 36 3138 91.6 40 3131 90.7 44 3127

97.7 14 3167 96.4 19 3132 95.2 23 3105 94.2 27 3086 93.3 31 3074 92.5 35 3065 91.7 39 3057 90.9 43 3053 90.1 3051

97.9 12 3102 96.7 17 3066 95.4 21 3038 94.3 25 3018 93.4 29 3004 92.6 34 2995 91.8 37 2986 91.0 41 2981 90.2 2978 89.4 2977

96.8 15 3000 95.6 20 2973 94.5 24 2953 93.6 28 2939 92.7 32 2930 92.0 36 2921 91.1 40 2914 90.3 2910 89.5 2909 88.8 2910

Max TAT not shown where %N1 can be set in ISA + 30°C conditions. Increase/decrease %N1 required by 1% per 5°C above/below standard TAT. Increase/decrease fuel flow 3% per 10°C above/below standard TAT. Increase/decrease KTAS by 1 knot per 1°C above/below standard TAT. Heavy line approximates max cruise thrust limit.

Max Continuous %N1

PRESS ALT (1000 FT) 18 17 16 15 14 13 12 11 10 9 8 -25 93.4 93.0 92.7 92.5 92.1 91.7 91.3 90.8 90.5 90.1 89.6 -20 94.3 93.9 93.6 93.4 93.0 92.6 92.1 91.7 91.3 90.9 90.5 -15 95.2 94.8 94.5 94.3 93.9 93.5 93.0 92.6 92.2 91.8 91.4 -10 96.0 95.7 95.4 95.2 94.8 94.4 93.9 93.5 93.1 92.7 92.2 -5 96.9 96.6 96.3 96.1 95.7 95.2 94.8 94.3 93.9 93.5 93.1 0 97.7 97.4 97.1 96.9 96.5 96.1 95.6 95.2 94.8 94.4 93.9 TAT (°C) 5 10 98.6 99.4 98.2 99.1 98.0 98.8 97.7 98.5 97.3 98.1 96.9 97.7 96.4 97.3 96.0 96.8 95.6 96.5 95.2 96.0 94.8 95.6 15 99.0 99.1 99.3 99.3 98.9 98.5 98.1 97.6 97.3 96.8 96.4 20 98.3 98.4 98.5 98.7 98.7 98.7 98.7 98.4 98.1 97.6 97.2 25 97.5 97.6 97.7 97.8 97.9 97.9 98.0 98.0 98.1 98.1 97.9 30 96.9 96.9 97.0 97.1 97.1 97.1 97.2 97.2 97.3 97.4 97.4 35 96.3 96.3 96.4 96.5 96.5 96.6 96.6 96.7 96.7 96.7 96.7 40 95.5 95.6 95.7 95.8 95.8 95.9 96.0 96.0 96.0 96.1 96.1

With engine anti-ice on, decrease limit %N1 by 1.1. With engine and wing anti-ice on, decrease limit %N1 by 3.9.

Copyright © The Boeing Company. See title page for details.

3.3.16

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737-800/CFM56-7B26 JAA/JAROPS Category C Brakes

ENROUTE Engine Inoperative

Flight Planning and Performance Manual

ENGINE INOP

MAX CONTINUOUS THRUST

330 KIAS Cruise Table

29000 FT to 19000 FT

PRESS ALT (1000 FT) 29 KIAS STD TAT KTAS WEIGHT (1000 KG) 85 80 75 70 65 60 55 50 45 40

28

27

26

25

24

PERFORMANCE THRUST LIMITED

23

22

21

20

19

Copyright © The Boeing Company. See title page for details.

November 1, 2006

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ENROUTE Engine Inoperative

Flight Planning and Performance Manual

737-800/CFM56-7B26 JAA/JAROPS Category C Brakes

ENGINE INOP

MAX CONTINUOUS THRUST

330 KIAS Cruise Table

18000 FT to 8000 FT

PRESS ALT (1000 FT) 18 KIAS STD TAT KTAS WEIGHT (1000 KG) 85 80 75 70 65 60 55 50 45 40

17 330 6 413 330 7 407 330 8 401 330 10 396 330 11 390 330 13 385 330 14 379 330 16 374 330 17 369 %N1 MAX TAT FF/ENG %N1 MAX TAT FF/ENG %N1 MAX TAT FF/ENG %N1 MAX TAT FF/ENG %N1 MAX TAT FF/ENG %N1 MAX TAT FF/ENG %N1 MAX TAT FF/ENG %N1 MAX TAT FF/ENG %N1 MAX TAT FF/ENG 97.5 7 3238 96.4 20 3208 95.4 24 3184 94.4 28 3167 93.6 32 3155 92.8 35 3146 92.1 39 3138 91.3 43 3134 90.5 47 3134 97.1 17 3196 96.0 21 3167 95.0 25 3145 94.1 29 3130 93.3 33 3120 92.5 36 3111 91.7 40 3103 91.0 44 3100 90.2 48 3100 96.8 18 3165 95.7 22 3138 94.7 26 3118 93.9 30 3104 93.1 33 3095 92.3 37 3086 91.5 41 3080 90.8 45 3078 90.0 3080 96.6 18 3147 95.5 23 3121 94.6 26 3104 93.8 30 3092 93.0 34 3084 92.2 38 3077 91.5 41 3072 90.7 45 3071 89.9 3072 96.6 18 3141 95.5 23 3117 94.6 27 3101 93.7 30 3091 93.0 34 3084 92.3 38 3078 91.5 41 3073 90.7 45 3071 89.9 3072

16

15

14

13

12

11

10

9

8

96.3 22 3471 95.3 27 3446 94.5 30 3431 93.7 34 3421 92.9 38 3413

96.6 21 3411 95.6 25 3384 94.6 29 3366 93.9 32 3355 93.1 36 3346 92.3 40 3340

97.0 19 3361 95.9 23 3332 94.9 27 3311 94.1 31 3298 93.3 34 3288 92.5 38 3280 91.7 42 3276

97.4 12 3317 96.3 21 3286 95.3 25 3262 94.4 29 3247 93.6 32 3237 92.8 36 3228 92.0 40 3222 91.2 44 3220

96.9 19 3258 95.8 23 3232 94.8 27 3212 94.0 30 3198 93.2 34 3189 92.4 38 3181 91.6 42 3176 90.9 45 3176

Max TAT not shown where %N1 can be set in ISA + 30°C conditions. Increase/decrease %N1 required by 1% per 5°C above/below standard TAT. Increase/decrease fuel flow 3% per 10°C above/below standard TAT. Increase/decrease KTAS by 1 knot per 1°C above/below standard TAT.

Max Continuous %N1

PRESS ALT (1000 FT) 16 15 14 13 12 11 10 9 8 -20 92.8 92.6 92.3 91.9 91.5 91.1 90.7 90.4 90.0 -15 93.7 93.5 93.2 92.8 92.4 92.0 91.6 91.2 90.8 -10 94.6 94.4 94.1 93.7 93.2 92.8 92.5 92.1 91.7 -5 95.5 95.3 94.9 94.5 94.1 93.7 93.3 92.9 92.5 0 96.3 96.1 95.8 95.4 94.9 94.5 94.2 93.8 93.4 5 97.2 97.0 96.6 96.2 95.8 95.4 95.0 94.6 94.2 TAT (°C) 10 15 98.0 98.8 97.8 98.6 97.4 98.3 97.0 97.8 96.6 97.4 96.2 97.0 95.8 96.6 95.4 96.2 95.0 95.8 20 98.7 98.8 98.8 98.6 98.2 97.8 97.4 97.0 96.6 25 97.9 98.0 98.1 98.1 98.1 98.1 98.2 97.8 97.4 30 97.2 97.3 97.3 97.3 97.3 97.4 97.4 97.5 97.5 35 96.7 96.7 96.7 96.7 96.7 96.7 96.7 96.8 96.9 40 96.0 96.1 96.1 96.1 96.1 96.1 96.1 96.2 96.2 45 95.3 95.4 95.4 95.4 95.4 95.4 95.5 95.5 95.5

With engine anti-ice on, decrease limit %N1 by 1.2. With engine and wing anti-ice on, decrease limit %N1 by 3.8.

Copyright © The Boeing Company. See title page for details.

3.3.18

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737-800/CFM56-7B26 JAA/JAROPS Category C Brakes

ENROUTE Engine Inoperative

Flight Planning and Performance Manual

ENGINE INOP

MAX CONTINUOUS THRUST

Long Range Cruise Diversion Fuel and Time

Based on .78/280/250 descent and includes APU fuel burn.

7 6 (HOURS) 5 4 3

PR S ES UR E TI T E UD (1 AL 0 00 FT

)

10 14 18 22

2

A 6&

BO

VE

TIME REQUIRED

14

2 1 0 20 10 0 -10 ISA DEV (°C) REF LINE 12

14

10

10 FUEL REQUIRED (1000 KG)

FT

)

00

0

DE

RE

AL

TI

TU

26

&

AB

22

18

(1

O

VE

8

PRESSURE ALTITUDE (1000 FT)

PR

ES

10 26

6

SU

4

2 REF LINE

0 40 HEAD 100 (KTS) 50 0 WIND 50 REF LINE 50 60 70 80 WEIGHT AT CHECK POINT (1000 KG)

TAIL 100

0

200

400 600 800 1000 1200 1400 1600 1800 DISTANCE FROM CHECK POINT (NAUTICAL GROUND MILES)

Copyright © The Boeing Company. See title page for details.

November 1, 2006

D632A008-ZZ022

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ENROUTE Engine Inoperative

Flight Planning and Performance Manual

737-800/CFM56-7B26 JAA/JAROPS Category C Brakes

ENGINE INOP

MAX CONTINUOUS THRUST

280 KIAS Diversion Fuel and Time

Based on 280/250 descent and includes APU fuel burn.

6

10

5

FT

(HOURS)

DE

22

4

(1 00 0

AB

O VE

)

18 14

14

&

10

TIME REQUIRED

SU

RE

PR

ES

FT

AB

)

O

2

22

0

VE

18

14

3

AL TI

TU

12

10 FUEL REQUIRED (1000 KG)

REF LINE

RE

AL

TI

TU

DE

1

(1

00

&

8

20 10 0 -10 ISA DEV (°C)

PR

ES

0

PRESSURE 10 ALTITUDE 22 (1000 FT)

SU

6

4

2 REF LINE

0 40 HEAD 100 (KTS) 50 0 WIND 50 REF LINE 50 60 70 80 WEIGHT AT CHECK POINT (1000 KG)

TAIL 100

0

200

400 600 800 1000 1200 1400 1600 1800 DISTANCE FROM CHECK POINT (NAUTICAL GROUND MILES)

Copyright © The Boeing Company. See title page for details.

3.3.20

D632A008-ZZ022

November 1, 2006

737-800/CFM56-7B26 JAA/JAROPS Category C Brakes

ENROUTE Engine Inoperative

Flight Planning and Performance Manual

ENGINE INOP

MAX CONTINUOUS THRUST

290 KIAS Diversion Fuel and Time

Based on 290/250 descent and includes APU fuel burn.

6

5

(HOURS)

(1

00

0

4

FT

)

22 18 14 10

14

TIME REQUIRED

TI T

UD

E

RE

AL

3

SU

14

10

12

ES

FT

2

AB

OV

PR

E

18

10 FUEL REQUIRED (1000 KG)

)

REF LINE

SU

RE

AL

TI

TU

1

DE

(1

00

0

22

&

8

20 10 0 -10 ISA DEV (°C)

PR

ES

0

PRESSURE 10 ALTITUDE 22 (1000 FT)

6

4

2 REF LINE

0 40 HEAD 100 (KTS) 50 0 WIND 50 REF LINE 50 60 70 80 WEIGHT AT CHECK POINT (1000 KG)

TAIL 100

0

200

400 600 800 1000 1200 1400 1600 1800 DISTANCE FROM CHECK POINT (NAUTICAL GROUND MILES)

Copyright © The Boeing Company. See title page for details.

November 1, 2006

D632A008-ZZ022

3.3.21

ENROUTE Engine Inoperative

Flight Planning and Performance Manual

737-800/CFM56-7B26 JAA/JAROPS Category C Brakes

ENGINE INOP

MAX CONTINUOUS THRUST

310 KIAS Diversion Fuel and Time

Based on 310/250 descent and includes APU fuel burn.

6

5

14 10

16

(HOURS)

(1

00

18

0

TIME REQUIRED

TI

RE

SU

ES

)

18

&

AB

OV

AL

E

3

TU

DE

14

10

FT

4

&

AB

O

VE

14

)

12

2

10

UD

1 REF LINE

20 10 0 -10 ISA DEV (°C)

PR

0

ES

SU

RE

PRESSURE ALTITUDE (1000 FT)

18 10

8

6

4

2 REF LINE

0 40 HEAD 100 (KTS) 50 0 WIND 50 REF LINE 50 60 70 80 WEIGHT AT CHECK POINT (1000 KG)

TAIL 100

0

200

400 600 800 1000 1200 1400 1600 1800 DISTANCE FROM CHECK POINT (NAUTICAL GROUND MILES)

Copyright © The Boeing Company. See title page for details.

3.3.22

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FUEL REQUIRED (1000 KG)

PR

AL

TIT

E

(10

00

FT

737-800/CFM56-7B26 JAA/JAROPS Category C Brakes

ENROUTE Engine Inoperative

Flight Planning and Performance Manual

ENGINE INOP

MAX CONTINUOUS THRUST

330 KIAS Diversion Fuel and Time

Based on 330/250 descent and includes APU fuel burn.

5

10

4

FT )

(HOURS)

14

&

AB

O

VE

16

(1 00 0

AL TI TU D

TIME REQUIRED

RE

SU

PR

2

ES

14

&

AB

OV

E

3

E

10

14

12

FT

)

REF LINE

UD

E

(10

1

10

0

SU

20 10 0 -10 ISA DEV (°C)

PR

PRESSURE ALTITUDE (1000 FT)

AL

16 10

8

6

4

2 REF LINE

0 40 HEAD 100 (KTS) 50 0 WIND 50 REF LINE 50 60 70 80 WEIGHT AT CHECK POINT (1000 KG)

TAIL 100

0

200

400 600 800 1000 1200 1400 1600 1800 DISTANCE FROM CHECK POINT (NAUTICAL GROUND MILES)

Copyright © The Boeing Company. See title page for details.

November 1, 2006

D632A008-ZZ022

FUEL REQUIRED (1000 KG)

ES

RE

TIT

00

3.3.23

ENROUTE Engine Inoperative

Flight Planning and Performance Manual

737-800/CFM56-7B26 JAA/JAROPS Category C Brakes

ENGINE INOP

MAX CONTINUOUS THRUST

Holding

Flaps Up

PRESSURE ALTITUDE (FT) %N1 35000 KIAS FF/ENG %N1 30000 KIAS FF/ENG %N1 25000 KIAS FF/ENG %N1 20000 KIAS FF/ENG %N1 15000 KIAS FF/ENG %N1 10000 KIAS FF/ENG %N1 5000 KIAS FF/ENG %N1 1500 KIAS FF/ENG WEIGHT (1000 KG) 85 80 75 70 65 60 55 50 45 40 96.3 178 1440 86.5 178 1310 81.6 178 1280 77.0 178 1280 72.8 178 1310 68.5 178 1330 64.6 178 1360 61.8 178 1380

94.1 255 2920 89.2 254 2850 84.9 253 2830 82.0 252 2820

92.0 247 2710 87.5 246 2660 83.2 245 2650 80.3 244 2650

96.9 241 2620 90.1 239 2520 85.6 238 2480 81.4 238 2480 78.6 236 2490

93.6 233 2380 88.1 231 2330 83.7 230 2310 79.4 229 2310 76.7 229 2330

90.7 224 2170 85.9 223 2150 81.6 222 2130 77.5 221 2150 74.7 221 2160

95.6 216 2080 88.3 215 1980 83.7 214 1970 79.4 213 1970 75.4 212 1980 72.5 211 2000

91.4 207 1840 85.8 205 1790 81.3 204 1790 77.0 203 1800 73.0 203 1820 70.1 202 1850

96.7 198 1780 87.9 197 1630 83.2 195 1620 78.7 195 1630 74.5 194 1640 70.4 193 1660 67.7 192 1690

91.2 187 1510 84.9 186 1450 80.3 185 1450 75.8 185 1470 71.7 185 1480 67.6 185 1510 64.9 185 1540

This table includes 5% additional fuel for holding in a racetrack pattern.

Copyright © The Boeing Company. See title page for details.

3.3.24

D632A008-ZZ022

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737-800/CFM56-7B26 JAA/JAROPS Category C Brakes

NON-STANDARD CONFIGURATION Table of Contents

Flight Planning and Performance Manual

NON-STANDARD CONFIGURATION

Table of Contents

Chapter 4

4.0 NON-STANDARD . . . . . . . . . . . . . . . . . . Text . . . . . . . CONFIGURATION-Table.of Contents. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 4.1.1

Gear Down . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 4.1.1 Alternate Mode EEC . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 4.1.2 Gear Down, Planning . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 4.2.1 Takeoff Climb Limit . . . . . . . . . . . . . . Landing Climb Limit . . . . . . . . . . . . . . Obstacle Limit . . . . . . . . . . . . . . . . . . . Net Level Off Weight . . . . . . . . . . . . . Driftdown Profiles Net Flight Path . . . . Long Range Cruise Trip Fuel and Time . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 4.2.1 . 4.2.6 . 4.2.7 4.2.12 4.2.13 4.2.14

Gear Down, All Engine . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 4.3.1 Long Range Cruise Long Range Cruise Long Range Cruise Descent . . . . . . . . Holding . . . . . . . . Altitude Capability . . Table . . . . . . . . . . . . . Enroute Fuel and Time .................. .................. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 4.3.1 4.3.2 4.3.8 4.3.9 4.3.9

Gear Down, Engine Inoperative . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 4.4.1 Driftdown/LRC Cruise Range Capability . . . Long Range Cruise Altitude Capability . . . . Long Range Cruise Diversion Fuel and Time Long Range Cruise Table . . . . . . . . . . . . . . . Holding . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 4.4.1 4.4.2 4.4.3 4.4.4 4.4.7

Alternate Mode EEC . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 4.5.1 Alternate Mode EEC Limit Weight . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 4.5.1 Alternate Mode EEC Max Takeoff %N1 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 4.5.1

Copyright © The Boeing Company. See title page for details.

November 1, 2006

D632A008-ZZ022

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NON-STANDARD CONFIGURATION Table of Contents

Flight Planning and Performance Manual

737-800/CFM56-7B26 JAA/JAROPS Category C Brakes

Intentionally Blank

Copyright © The Boeing Company. See title page for details.

4.TOC.0.2

D632A008-ZZ022

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Text

NON-STANDARD CONFIGURATION Text

Flight Planning and Performance Manual

4.1 NON-STANDARD CONFIGURATION-Text Gear Down

Introduction

This section contains performance data for airplane operation with landing gear extended. The data include engine bleed effects for normal air conditioning operation; i.e., two packs on at normal flow with all engines operating, and one pack at normal flow with an engine inoperative. Note: The Flight Management Computer System (FMCS) does not contain special provisions for operation with landing gear extended. As a result, the FMCS will generate inaccurate enroute speed schedules, display non-conservative predictions of fuel burn, estimated time of arrival (ETA), maximum altitude, and compute an overly-shallow descent path. To obtain accurate ETA predictions using the FMCS, gear down cruise speed and altitude should be entered on the CLB and CRZ pages. Gear down cruise speed should also be entered on the DES page and a STEP SIZE of zero should be entered on the PERF INIT or CRZ page. Use of VNAV during descent under these circumstances is not recommended.

from brake release. Move vertically to the OAT reference line and follow guidelines to correct for OAT as necessary. Repeat this procedure to correct for airport pressure altitude and wind, then continue vertically to read obstacle limit weight. Adjust the obstacle limit weight according to the notes below the chart to account for the appropiate engine bleed configuration. Net Level Off Weight This chart is provided to determine the dispatch maximum weight for terrain clearance based on the Approved Flight Manual net engine inoperative, gear down performance at the speed for optimum climb gradient. Refer to Chapter 2 text for description of net level off altitude chart. Driftdown Profiles Net Flight Path These charts are provided to determine the time, fuel and distance from engine failure at any point during driftdown for enroute terrain clearance. Data is based on gear-down net performance, Max Continuous thrust following engine failure and level flight deceleration to optimum driftdown speed (speed for optimum climb gradient). Refer to Chapter 2 for description of chart usage. Long Range Cruise Trip Fuel and Time A Long Range Cruise Trip Fuel and Time chart is provided at constant altitude to determine trip fuel and time from brake release to touchdown. Refer to Chapter 2 text for description of chart usage.

Planning

Takeoff/Landing Climb Limit Runway limited takeoff and landing weights are unchanged from those shown in Chapter 1. The climb limited takeoff and landing weights are tabulated in this section as a function of airport OAT and pressure altitude, with corrections for packs off and anti-ice operation. The landing climb limit weight is further restricted when operating in icing conditions during any part of the flight when the forecast landing temperature is below 10°C. Maximum allowable takeoff and landing weights are the lesser of the normal field/obstacle limit weight and the corresponding climb limit weight with gear down. Takeoff and landing speeds are unchanged from those shown in Chapter 1. Obstacle Limit Obstacle clearance charts are provided for each certified takeoff flap setting based on normal air conditioning operation. The charts are intended for use only when an airport analysis is not available. Detailed analysis for the specific case from the Airplane Flight Manual may result in less restrictive weight. The data is not valid for takeoffs using improved climb technique. To determine the obstacle limit weight, enter with obstacle height (measured from the lowest point on the runway) and move horizontally to the obstacle distance

All Engines

Long Range Cruise Altitude Capability Long Range Cruise Altitude Capability is provided at Max Cruise Thrust with 100 ft/min residual rate of climb. Long Range Cruise Table Long Range Cruise tabulations are provided in the same format as the gear up cruise control tables in Chapter 3. Long Range Cruise Enroute Fuel and Time This chart is provided to determine fuel and time required to proceed to an alternate airfield or to complete the scheduled trip at Long Range Cruise. The chart is used in a similar manner to the Trip Fuel and Time chart with distance to destination replacing total trip distance.

Copyright © The Boeing Company. See title page for details.

November 1, 2006

D632A008-ZZ022

4.1.1

NON-STANDARD CONFIGURATION Text

Flight Planning and Performance Manual

737-800/CFM56-7B26 JAA/JAROPS Category C Brakes

Descent Time, distance and fuel information is shown based on flight idle thrust at VREF40 + 70 KIAS and straight in approach. Holding All engine holding data is provided at VREF40 + 70 KIAS. %N1 required, IAS and fuel flow with gear down are shown as described in Chapter 3.

Limit Weight A simplified method which conservatively accounts for the effects of EEC in the alternate mode is to reduce the normal mode (ON EEC switch illuminated) performance limited weights. The Limit Weight table provides takeoff field, climb, and obstacle limit weights. To determine limit weights for operations with the EEC in alternate mode, enter the table with the limit weights for normal mode EEC operation, as determined in Chapter 1, and read the associated limit weight for each performance condition. The most limiting of the takeoff weights must be used. Analysis from the Airplane Flight Manual - Digital Performance Information may yield less restrictive limit weights. Takeoff Speed Adjustment Takeoff speeds for the reduced weight should be increased by the amount shown in the Takeoff Speeds Adjustment table. The adjusted V1 should not exceed the adjusted VR. NOTE: The FMC does not incorporate alternate mode EEC performance in its takeoff speeds calculations. Max Takeoff %N1 The alternate mode EEC thrust schedule provides equal or greater thrust than the normal mode thrust for the same thrust lever position. Thrust limit protection is not provided in alternate mode EEC and maximum rated thrust may be reached at thrust lever position less than full forward. As a result, thrust overboost may occur if the target alternate mode EEC Max Takeoff %N1 settings are not observed. To find alternate mode EEC Max Takeoff %N1 based on normal engine bleed for air conditioning packs on, enter the Alternate Mode EEC Max Takeoff %N1 Table with airport pressure altitude and airport OAT and read %N1. For packs off apply the %N1 adjustment provided below the table. No %N1 adjustment is required for engine or wing anti-ice.

Engine Inoperative

Driftdown/LRC Cruise Range Capability Engine inoperative range capability is provided to determine the time and fuel required for a specified distance when the recommended driftdown procedure is followed. Long Range Cruise Altitude Capability Long Range Cruise altitude capability is provided at Max Continuous Thrust with 100 ft/min residual rate of climb. Long Range Cruise Diversion Fuel and Time This chart enables rapid determination of fuel and time required to proceed to an alternate airfield (or continue to destination) at Long Range Cruise with an engine inoperative. Diversion fuel and time are determined in a manner similar to the enroute fuel and time. Long Range Cruise Tables Long Range Cruise tabulations for engine inoperative are based on use of Max Continuous Thrust Limits. Holding Engine inoperative holding data is provided at VREF40 + 70 KIAS. %N1 required, IAS and fuel flow with gear down are shown as described in Chapter 3.

Alternate Mode EEC

Introduction This section contains performance data for airplane operation with the Electronic Engine Control (EEC) in alternate mode (ALTN & EEC switch illuminated) for applicable thrust ratings. The data includes engine bleed effects for normal air conditioning operation i.e., two packs on at normal flow, all engines operating. Operation with derated and/or assumed temperature reduced takeoff thrust is not permitted with the EEC in the alternate mode.

Copyright © The Boeing Company. See title page for details.

4.1.2

D632A008-ZZ022

November 1, 2006

737-800/CFM56-7B26 JAA/JAROPS Category C Brakes

NON-STANDARD CONFIGURATION Gear Down, Planning

Flight Planning and Performance Manual

4.2 NON-STANDARD CONFIGURATION-Gear Down, Planning

Gear Down, Planning

GEAR DOWN

Takeoff Climb Limit

Flaps 1

Based on engine bleed for packs on and anti-ice off

AIRPORT OAT °C 70 68 66 64 62 60 58 56 54 52 50 48 46 44 42 40 38 36 34 32 30 28 26 24 22 20 18 16 14 12 10 0 -10 -20 -30 -40 -50 -54 °F 158 154 151 147 144 140 136 133 129 126 122 118 115 111 108 104 100 97 93 90 86 82 79 75 72 68 64 61 57 54 50 32 14 -4 -22 -40 -58 -65 -2000 56.3 57.1 58.0 58.8 59.7 60.6 61.4 62.4 63.3 64.4 65.6 66.8 68.1 69.3 70.5 71.7 72.9 74.1 75.2 75.3 75.4 75.4 75.5 75.6 75.6 75.7 75.8 75.8 75.9 76.0 76.0 76.2 76.4 76.5 76.5 76.6 76.7 76.7 -1000 54.9 55.7 56.6 57.5 58.3 59.2 60.1 61.0 62.0 63.1 64.3 65.4 66.6 67.8 69.0 70.2 71.4 72.6 73.8 75.0 75.1 75.1 75.2 75.3 75.3 75.4 75.5 75.5 75.6 75.6 75.7 75.9 76.1 76.2 76.2 76.3 76.3 76.3 0 53.3 54.1 55.0 55.9 56.7 57.6 58.6 59.4 59.6 60.9 62.3 63.6 64.9 66.1 67.3 68.5 69.7 70.8 72.1 73.4 74.6 74.7 74.8 74.8 74.9 75.0 75.0 75.1 75.1 75.2 75.2 75.4 75.5 75.6 75.7 75.7 75.7 75.8 1000 52.3 53.1 54.0 54.9 55.8 56.7 57.7 57.9 58.2 59.4 60.7 62.1 63.4 64.6 65.9 67.1 68.4 69.6 70.9 72.0 73.0 73.0 73.1 73.1 73.2 73.2 73.3 73.3 73.4 73.4 73.6 73.7 73.8 73.8 73.9 73.9 73.9 TAKEOFF CLIMB WEIGHT (1000 KG) AIRPORT PRESSURE ALTITUDE (FT) 2000 3000 4000 5000 6000 7000 8000 9000 10000

51.3 52.2 53.0 53.9 54.9 55.8 56.3 56.3 56.6 57.9 59.1 60.4 61.7 62.9 64.2 65.3 66.6 67.8 69.2 70.4 71.2 71.3 71.3 71.4 71.4 71.5 71.5 71.5 71.6 71.7 71.8 71.9 72.0 72.0 72.1 72.1

50.5 51.3 52.2 53.1 54.0 54.7 54.7 54.7 55.0 56.3 57.6 58.8 60.1 61.3 62.5 63.6 64.8 66.1 67.4 68.5 69.1 69.2 69.2 69.2 69.3 69.3 69.3 69.4 69.5 69.6 69.7 69.8 69.8 69.9 69.9

49.6 50.5 51.3 52.2 53.1 53.1 53.1 53.1 53.4 54.7 56.0 57.2 58.4 59.6 60.8 62.0 63.1 64.3 65.7 66.5 67.0 67.1 67.1 67.1 67.2 67.2 67.2 67.4 67.5 67.5 67.6 67.7 67.8 67.8

48.8 49.7 50.5 51.4 51.6 51.6 51.6 51.5 51.9 53.1 54.4 55.6 56.8 58.0 59.1 60.3 61.5 62.7 64.0 64.5 65.0 65.0 65.0 65.1 65.1 65.1 65.2 65.3 65.4 65.5 65.5 65.6 65.6

47.7 48.5 49.3 50.0 49.9 49.9 49.9 49.9 50.2 51.5 52.7 53.9 55.1 56.3 57.4 58.6 59.8 61.0 62.1 62.6 62.9 63.0 63.0 63.0 63.0 63.2 63.3 63.3 63.4 63.4 63.4 63.5

46.3 47.1 47.9 48.2 48.2 48.2 48.2 48.1 48.5 49.7 50.9 52.1 53.3 54.5 55.7 56.9 58.1 59.2 60.2 60.6 61.0 61.0 61.0 61.0 61.1 61.2 61.3 61.3 61.3 61.4 61.4

45.0 45.8 46.5 46.5 46.5 46.5 46.5 46.5 46.8 48.0 49.2 50.4 51.6 52.8 54.0 55.2 56.4 57.5 58.3 58.7 59.0 59.0 59.0 59.2 59.3 59.3 59.4 59.4 59.4 59.4

43.5 44.4 45.0 45.0 45.0 45.0 45.0 45.0 45.3 46.5 47.7 48.8 50.0 51.2 52.4 53.6 54.8 55.9 56.4 56.8 57.1 57.1 57.2 57.3 57.4 57.5 57.5 57.5 57.5

42.1 43.0 43.8 43.8 43.8 43.8 43.7 43.7 44.1 45.3 46.4 47.6 48.8 49.9 51.1 52.3 53.4 54.3 54.6 54.9 55.2 55.4 55.5 55.6 55.7 55.8 55.8 55.8

With engine bleeds for packs off, increase weight by 300 kg. With engine anti-ice on, decrease weight by 250 kg. With engine and wing anti-ice on, decrease weight by 3050 kg (optional system).

Copyright © The Boeing Company. See title page for details.

November 1, 2006

D632A008-ZZ022

4.2.1

NON-STANDARD CONFIGURATION Gear Down, Planning

Flight Planning and Performance Manual

737-800/CFM56-7B26 JAA/JAROPS Category C Brakes

GEAR DOWN

Gear Down, Planning

Takeoff Climb Limit

Flaps 5

Based on engine bleed for packs on and anti-ice off

AIRPORT OAT °C 70 68 66 64 62 60 58 54 52 50 48 46 44 42 40 38 36 34 32 30 28 26 24 22 20 18 16 14 12 10 0 -10 -20 -30 -40 -50 -54 °F 158 154 151 147 144 140 136 129 126 122 118 115 111 108 104 100 97 93 90 86 82 79 75 72 68 64 61 57 54 50 32 14 -4 -22 -40 -58 -65 -2000 55.2 56.0 56.9 57.7 58.5 59.4 60.3 62.1 63.2 64.3 65.5 66.8 68.0 69.1 70.3 71.5 72.6 73.7 73.8 73.9 73.9 74.0 74.1 74.2 74.2 74.3 74.3 74.4 74.5 74.5 74.7 74.9 75.0 75.0 75.1 75.2 75.2 -1000 53.9 54.7 55.5 56.4 57.2 58.1 59.0 60.8 61.9 63.0 64.2 65.3 66.5 67.7 68.9 70.0 71.2 72.3 73.5 73.6 73.7 73.8 73.8 73.9 73.9 74.0 74.1 74.1 74.2 74.2 74.5 74.6 74.7 74.7 74.8 74.8 74.8 0 52.3 53.1 53.9 54.8 55.7 56.6 57.5 59.3 60.4 61.5 62.6 63.8 64.9 66.0 67.2 68.3 69.5 70.7 72.0 73.2 73.3 73.3 73.4 73.4 73.5 73.6 73.6 73.7 73.7 73.8 74.0 74.1 74.1 74.2 74.2 74.3 74.3 1000 51.3 52.1 53.0 53.9 54.7 55.6 57.5 58.2 59.5 60.6 61.7 62.7 63.8 64.9 66.1 67.3 68.5 69.5 70.6 71.6 71.6 71.7 71.7 71.8 71.8 71.9 71.9 71.9 72.0 72.2 72.3 72.3 72.4 72.4 72.5 72.5 TAKEOFF CLIMB WEIGHT (1000 KG) AIRPORT PRESSURE ALTITUDE (FT) 2000 3000 4000 5000 6000 7000 8000 9000 10000

50.3 51.2 52.0 52.9 53.8 55.7 56.3 56.6 57.9 59.2 60.5 61.7 62.8 63.8 64.9 66.1 67.2 68.2 69.1 69.8 69.9 69.9 70.0 70.0 70.1 70.1 70.1 70.2 70.3 70.4 70.5 70.5 70.6 70.7 70.7

49.5 50.4 51.2 52.1 53.9 54.7 54.7 55.0 56.3 57.6 58.8 60.1 61.3 62.5 63.6 64.8 65.7 66.5 67.2 67.8 67.8 67.8 67.9 67.9 67.9 68.0 68.0 68.2 68.3 68.3 68.4 68.4 68.5 68.5

48.7 49.5 50.4 52.1 53.0 53.1 53.1 53.4 54.7 56.0 57.2 58.4 59.6 60.8 62.0 63.2 64.1 64.7 65.2 65.7 65.7 65.8 65.8 65.8 65.9 65.9 66.0 66.1 66.2 66.3 66.3 66.4 66.4

47.9 48.8 50.4 51.3 51.6 51.6 51.6 51.9 53.1 54.4 55.6 56.8 58.0 59.2 60.3 61.5 62.3 62.8 63.3 63.7 63.7 63.7 63.8 63.8 63.8 64.0 64.1 64.1 64.2 64.2 64.3 64.3

46.8 48.4 49.2 50.0 49.9 49.9 49.9 50.2 51.5 52.7 53.9 55.1 56.3 57.4 58.6 59.8 60.5 60.9 61.3 61.7 61.7 61.7 61.8 61.8 61.9 62.0 62.1 62.1 62.1 62.2 62.2

46.2 47.0 47.8 48.2 48.2 48.2 48.1 48.5 49.7 50.9 52.1 53.3 54.5 55.7 56.9 58.1 58.7 59.0 59.4 59.7 59.8 59.8 59.8 59.9 60.0 60.1 60.1 60.1 60.1 60.1

44.1 44.9 45.7 46.4 46.5 46.5 46.5 46.5 46.8 48.0 49.2 50.4 51.6 52.8 54.0 55.2 56.4 56.8 57.2 57.5 57.8 57.9 57.9 58.0 58.1 58.1 58.2 58.2 58.2 58.2

42.7 43.5 44.3 45.0 45.0 45.0 45.0 45.0 45.3 46.5 47.7 48.9 50.1 51.2 52.4 53.7 54.7 55.0 55.3 55.6 56.0 56.0 56.1 56.2 56.3 56.3 56.4 56.4 56.4

41.3 42.1 42.9 43.7 43.8 43.8 43.7 43.7 44.1 45.3 46.4 47.6 48.8 50.0 51.2 52.3 52.9 53.2 53.5 53.8 54.1 54.3 54.4 54.5 54.6 54.7 54.7 54.7

With engine bleeds for packs off, increase weight by 300 kg. With engine anti-ice on, decrease weight by 250 kg. With engine and wing anti-ice on, decrease weight by 1600 kg (optional system).

Copyright © The Boeing Company. See title page for details.

4.2.2

D632A008-ZZ022

November 1, 2006

737-800/CFM56-7B26 JAA/JAROPS Category C Brakes

NON-STANDARD CONFIGURATION Gear Down, Planning

Flight Planning and Performance Manual

GEAR DOWN

Gear Down, Planning

Takeoff Climb Limit

Flaps 10

Based on engine bleed for packs on and anti-ice off

AIRPORT OAT °C 70 68 66 64 62 60 58 56 54 52 50 48 46 44 42 40 38 36 34 32 30 28 26 24 22 20 18 16 14 12 10 0 -10 -20 -30 -40 -50 -54 °F 158 154 151 147 144 140 136 133 129 126 122 118 115 111 108 104 100 97 93 90 86 82 79 75 72 68 64 61 57 54 50 32 14 -4 -22 -40 -58 -65 -2000 52.3 53.1 53.9 54.7 55.5 56.3 57.1 57.9 58.8 59.9 60.9 62.1 63.2 64.3 65.4 66.5 67.6 68.7 69.7 69.8 69.9 70.0 70.1 70.1 70.2 70.2 70.3 70.3 70.4 70.5 70.5 70.7 70.9 70.9 71.0 71.1 71.2 71.2 -1000 51.0 51.8 52.6 53.4 54.2 55.0 55.9 56.7 57.6 58.6 59.7 60.8 61.9 63.0 64.1 65.2 66.3 67.4 68.5 69.6 69.7 69.7 69.8 69.9 69.9 70.0 70.0 70.1 70.2 70.2 70.3 70.5 70.6 70.7 70.7 70.8 70.8 70.8 0 49.5 50.3 51.1 51.9 52.7 53.6 54.4 55.3 56.2 57.2 58.2 59.3 60.4 61.4 62.5 63.6 64.7 65.8 66.9 68.1 69.3 69.4 69.4 69.5 69.5 69.6 69.6 69.7 69.7 69.8 69.8 70.0 70.1 70.2 70.2 70.3 70.3 70.3 1000 48.6 49.4 50.2 51.0 51.9 52.7 53.6 54.5 55.4 56.4 57.4 58.4 59.4 60.5 61.5 62.6 63.7 64.8 65.8 66.8 67.7 67.8 67.8 67.9 67.9 68.0 68.0 68.1 68.1 68.1 68.3 68.4 68.5 68.5 68.6 68.6 68.6 TAKEOFF CLIMB WEIGHT (1000 KG) AIRPORT PRESSURE ALTITUDE (FT) 2000 3000 4000 5000 6000 7000 8000 9000 10000

47.7 48.5 49.3 50.1 51.0 51.8 52.7 53.6 54.5 55.5 56.5 57.5 58.5 59.5 60.5 61.5 62.6 63.7 64.6 65.4 66.1 66.2 66.2 66.2 66.3 66.3 66.3 66.4 66.4 66.6 66.7 66.7 66.8 66.8 66.9 66.9

46.9 47.7 48.5 49.4 50.2 51.1 51.9 52.8 53.6 54.6 55.5 56.5 57.5 58.5 59.5 60.5 61.4 62.2 63.0 63.6 64.1 64.2 64.2 64.2 64.3 64.3 64.3 64.4 64.5 64.6 64.7 64.7 64.8 64.8 64.9

46.1 46.9 47.7 48.6 49.4 50.2 51.0 51.9 52.7 53.6 54.5 55.5 56.4 57.4 58.5 59.4 60.1 60.7 61.3 61.8 62.2 62.2 62.3 62.3 62.3 62.4 62.4 62.5 62.6 62.7 62.8 62.8 62.9 62.9

45.4 46.2 47.0 47.8 48.6 49.4 50.2 50.9 51.8 52.7 53.6 54.6 55.5 56.4 57.2 58.0 58.5 59.0 59.5 59.9 60.3 60.3 60.4 60.4 60.4 60.4 60.6 60.7 60.7 60.8 60.8 60.9 60.9

44.3 45.1 45.8 46.6 47.4 48.1 48.9 49.7 50.2 51.3 52.3 53.2 54.1 54.9 55.7 56.4 56.9 57.3 57.7 58.1 58.4 58.4 58.5 58.5 58.5 58.6 58.7 58.8 58.8 58.8 58.8 58.9

43.0 43.8 44.5 45.3 46.0 46.7 47.5 48.2 48.5 49.7 50.7 51.7 52.6 53.3 54.1 54.8 55.2 55.5 55.9 56.3 56.6 56.6 56.6 56.6 56.7 56.8 56.9 56.9 56.9 56.9 56.9

41.8 42.5 43.2 44.0 44.7 45.4 46.1 46.5 46.8 48.1 49.2 50.2 51.0 51.8 52.5 53.1 53.5 53.8 54.1 54.5 54.8 54.8 54.8 54.9 55.0 55.1 55.1 55.1 55.1 55.1

41.2 41.9 42.7 43.4 44.2 44.9 45.0 45.3 46.5 47.7 48.9 49.7 50.4 50.9 51.4 51.8 52.1 52.4 52.7 53.0 53.0 53.1 53.2 53.3 53.4 53.4 53.4 53.4

41.4 42.2 43.0 43.8 43.8 44.1 45.3 46.4 47.6 48.5 49.0 49.4 49.7 50.1 50.4 50.7 51.0 51.3 51.4 51.5 51.6 51.7 51.8 51.8 51.9

With engine bleeds for packs off, increase weight by 300 kg. With engine anti-ice on, decrease weight by 250 kg. With engine and wing anti-ice on, decrease weight by 1200 kg (optional system).

Copyright © The Boeing Company. See title page for details.

November 1, 2006

D632A008-ZZ022

4.2.3

NON-STANDARD CONFIGURATION Gear Down, Planning

Flight Planning and Performance Manual

737-800/CFM56-7B26 JAA/JAROPS Category C Brakes

GEAR DOWN

Gear Down, Planning

Takeoff Climb Limit

Flaps 15

Based on engine bleed for packs on and anti-ice off

AIRPORT OAT °C 70 68 66 64 62 60 58 56 54 52 50 48 46 44 42 40 38 36 34 32 30 28 26 24 22 20 18 16 14 12 10 0 -10 -20 -30 -40 -50 -54 °F 158 154 151 147 144 140 136 133 129 126 122 118 115 111 108 104 100 97 93 90 86 82 79 75 72 68 64 61 57 54 50 32 14 -4 -22 -40 -58 -65 -2000 51.7 52.4 53.2 54.0 54.8 55.6 56.4 57.2 58.1 59.1 60.2 61.3 62.4 63.5 64.6 65.7 66.8 67.8 68.8 68.9 69.0 69.1 69.1 69.2 69.3 69.3 69.4 69.4 69.5 69.5 69.6 69.8 69.9 70.0 70.1 70.2 70.2 70.2 -1000 50.4 51.2 52.0 52.7 53.5 54.3 55.2 56.0 56.9 57.9 59.0 60.1 61.1 62.2 63.3 64.4 65.4 66.5 67.6 68.7 68.8 68.8 68.9 69.0 69.0 69.1 69.1 69.2 69.2 69.3 69.4 69.6 69.7 69.8 69.8 69.8 69.9 69.9 0 48.9 49.7 50.5 51.3 52.1 52.9 53.8 54.6 55.5 56.5 57.5 58.6 59.7 60.7 61.8 62.8 63.9 65.0 66.1 67.3 68.4 68.5 68.5 68.6 68.6 68.7 68.7 68.8 68.8 68.9 68.9 69.1 69.2 69.3 69.3 69.3 69.4 69.4 1000 48.0 48.8 49.6 50.4 51.2 52.1 52.9 53.8 54.7 55.7 56.7 57.7 58.7 59.7 60.8 61.8 62.9 64.0 65.0 66.0 66.9 66.9 67.0 67.0 67.1 67.1 67.1 67.2 67.2 67.3 67.4 67.5 67.6 67.6 67.7 67.7 67.7 TAKEOFF CLIMB WEIGHT (1000 KG) AIRPORT PRESSURE ALTITUDE (FT) 2000 3000 4000 5000 6000 7000 8000 9000 10000

47.1 47.9 48.7 49.5 50.4 51.2 52.1 52.9 53.8 54.8 55.8 56.8 57.7 58.7 59.7 60.7 61.9 62.9 63.8 64.5 65.3 65.3 65.3 65.4 65.4 65.5 65.5 65.5 65.5 65.7 65.8 65.9 65.9 66.0 66.0 66.0

46.3 47.1 47.9 48.8 49.6 50.4 51.3 52.1 53.0 53.9 54.8 55.8 56.7 57.8 58.8 59.8 60.6 61.5 62.2 62.8 63.3 63.4 63.4 63.4 63.5 63.5 63.5 63.6 63.7 63.8 63.9 63.9 64.0 64.0 64.1

45.6 46.4 47.2 48.0 48.8 49.6 50.4 51.2 52.0 52.9 53.9 54.8 55.7 56.7 57.8 58.7 59.3 60.0 60.5 61.0 61.4 61.5 61.5 61.5 61.5 61.6 61.6 61.7 61.8 61.9 62.0 62.0 62.1 62.1

44.9 45.6 46.4 47.2 48.0 48.8 49.5 50.3 51.1 52.0 52.9 53.9 54.8 55.7 56.5 57.3 57.8 58.3 58.7 59.2 59.5 59.6 59.6 59.6 59.6 59.7 59.8 59.9 59.9 60.0 60.0 60.1 60.1

43.8 44.5 45.3 46.0 46.8 47.5 48.3 49.0 49.8 50.7 51.6 52.6 53.5 54.3 55.0 55.7 56.2 56.6 57.0 57.3 57.7 57.7 57.7 57.7 57.8 57.9 58.0 58.0 58.0 58.1 58.1 58.1

42.5 43.2 44.0 44.7 45.4 46.2 46.9 47.6 48.4 49.2 50.1 51.0 51.9 52.7 53.4 54.1 54.5 54.8 55.2 55.5 55.9 55.9 55.9 55.9 56.0 56.1 56.2 56.2 56.2 56.2 56.2

41.3 42.0 42.7 43.4 44.1 44.8 45.5 46.2 46.9 47.8 48.6 49.5 50.4 51.1 51.8 52.4 52.8 53.1 53.5 53.8 54.1 54.1 54.1 54.2 54.3 54.4 54.4 54.4 54.4 54.4

41.4 42.1 42.9 43.6 44.4 45.0 45.4 46.6 47.6 48.4 49.1 49.8 50.3 50.8 51.1 51.4 51.7 52.0 52.3 52.3 52.5 52.6 52.6 52.7 52.7 52.8 52.8

40.9 41.6 42.4 43.2 43.8 44.1 45.3 46.4 47.2 47.9 48.4 48.7 49.1 49.4 49.7 50.0 50.3 50.6 50.8 50.9 51.0 51.0 51.1 51.2 51.2

With engine bleeds for packs off, increase weight by 350 kg. With engine anti-ice on, decrease weight by 250 kg. With engine and wing anti-ice on, decrease weight by 1200 kg (optional system).

Copyright © The Boeing Company. See title page for details.

4.2.4

D632A008-ZZ022

November 1, 2006

737-800/CFM56-7B26 JAA/JAROPS Category C Brakes

NON-STANDARD CONFIGURATION Gear Down, Planning

Flight Planning and Performance Manual

GEAR DOWN

Gear Down, Planning

Takeoff Climb Limit

Flaps 25

Based on engine bleed for packs on and anti-ice off

AIRPORT OAT °C 70 68 66 64 62 60 58 56 54 52 50 48 46 44 42 40 38 36 34 32 30 28 26 24 22 20 18 16 14 12 10 0 -10 -20 -30 -40 -50 -54 °F 158 154 151 147 144 140 136 133 129 126 122 118 115 111 108 104 100 97 93 90 86 82 79 75 72 68 64 61 57 54 50 32 14 -4 -22 -40 -58 -65 -2000 50.7 51.5 52.2 53.0 53.8 54.5 55.3 56.1 57.0 58.0 59.0 60.1 61.3 62.3 63.4 64.4 65.5 66.5 67.5 67.6 67.7 67.7 67.8 67.9 67.9 68.0 68.0 68.1 68.2 68.2 68.3 68.5 68.6 68.7 68.7 68.8 68.9 68.9 -1000 49.5 50.2 51.0 51.8 52.6 53.3 54.2 55.0 55.8 56.8 57.9 59.0 60.0 61.1 62.1 63.2 64.2 65.2 66.3 67.4 67.5 67.5 67.6 67.7 67.7 67.8 67.8 67.9 67.9 68.0 68.0 68.2 68.4 68.4 68.5 68.5 68.5 68.5 0 48.0 48.8 49.6 50.4 51.1 52.0 52.8 53.6 54.5 55.5 56.5 57.5 58.5 59.6 60.6 61.7 62.7 63.8 64.9 66.0 67.1 67.2 67.2 67.3 67.3 67.4 67.4 67.5 67.5 67.6 67.6 67.8 67.9 67.9 68.0 68.0 68.1 68.1 1000 47.1 47.9 48.7 49.5 50.3 51.1 52.0 52.8 53.7 54.7 55.6 56.6 57.6 58.6 59.6 60.7 61.8 62.8 63.8 64.7 65.6 65.7 65.7 65.7 65.8 65.8 65.9 65.9 65.9 66.0 66.2 66.2 66.3 66.3 66.4 66.4 66.5 TAKEOFF CLIMB WEIGHT (1000 KG) AIRPORT PRESSURE ALTITUDE (FT) 2000 3000 4000 5000 6000 7000 8000 9000 10000

46.2 47.0 47.8 48.6 49.4 50.3 51.1 52.0 52.8 53.8 54.7 55.7 56.7 57.6 58.6 59.6 60.7 61.7 62.6 63.3 64.0 64.1 64.1 64.1 64.2 64.2 64.2 64.3 64.3 64.5 64.5 64.6 64.7 64.7 64.8 64.8

45.5 46.3 47.1 47.9 48.7 49.5 50.3 51.1 52.0 52.9 53.8 54.8 55.7 56.7 57.7 58.7 59.5 60.3 61.0 61.6 62.1 62.2 62.2 62.2 62.3 62.3 62.3 62.4 62.5 62.6 62.7 62.7 62.8 62.8 62.9

44.7 45.5 46.3 47.1 47.9 48.7 49.5 50.3 51.1 52.0 52.9 53.8 54.7 55.7 56.7 57.6 58.2 58.9 59.4 59.8 60.3 60.3 60.3 60.4 60.4 60.4 60.4 60.6 60.7 60.7 60.8 60.8 60.9 60.9

44.0 44.8 45.6 46.3 47.1 47.9 48.6 49.4 50.2 51.1 51.9 52.9 53.8 54.7 55.5 56.2 56.7 57.2 57.6 58.0 58.4 58.4 58.5 58.5 58.5 58.5 58.7 58.7 58.8 58.9 58.9 58.9 58.9

43.0 43.7 44.5 45.2 45.9 46.7 47.4 48.1 48.9 49.8 50.6 51.6 52.5 53.3 54.0 54.7 55.1 55.5 55.9 56.3 56.6 56.6 56.6 56.7 56.7 56.8 56.9 56.9 56.9 57.0 57.0 57.0

41.7 42.5 43.2 43.9 44.6 45.3 46.0 46.7 47.5 48.3 49.2 50.1 50.9 51.7 52.4 53.1 53.4 53.8 54.2 54.5 54.8 54.8 54.8 54.9 55.0 55.0 55.1 55.1 55.1 55.1 55.1

41.2 41.9 42.6 43.3 44.0 44.7 45.4 46.1 46.9 47.7 48.6 49.4 50.2 50.8 51.4 51.8 52.1 52.4 52.8 53.0 53.1 53.1 53.2 53.3 53.3 53.4 53.4 53.4 53.3

41.3 42.1 42.8 43.5 44.3 45.1 45.9 46.7 47.5 48.2 48.8 49.3 49.8 50.1 50.4 50.7 51.1 51.3 51.4 51.5 51.6 51.6 51.7 51.7 51.8 51.8

40.9 41.6 42.4 43.2 44.0 44.8 45.6 46.3 47.0 47.4 47.8 48.2 48.5 48.8 49.1 49.4 49.7 49.8 49.9 50.0 50.1 50.2 50.2 50.2

With engine bleeds for packs off, increase weight by 350 kg. With engine anti-ice on, decrease weight by 250 kg. With engine and wing anti-ice on, decrease weight by 1150 kg (optional system).

Copyright © The Boeing Company. See title page for details.

November 1, 2006

D632A008-ZZ022

4.2.5

NON-STANDARD CONFIGURATION Gear Down, Planning

Flight Planning and Performance Manual

737-800/CFM56-7B26 JAA/JAROPS Category C Brakes

GEAR DOWN

Gear Down, Planning

Landing Climb Limit

Valid for approach with Flaps 15 and landing with Flaps 30 or 40

Based on engine bleed for packs on and anti-ice off.

AIRPORT OAT °C 54 52 50 48 46 44 42 40 38 36 34 32 30 28 26 24 22 20 18 16 14 12 10 -40 °F 129 126 122 118 115 111 108 104 100 97 93 90 86 82 79 75 72 68 64 61 57 54 50 -40 -2000 58.8 59.9 60.9 62.1 63.3 64.4 65.5 66.6 67.7 68.8 69.8 70.0 70.0 70.1 70.2 70.2 70.3 70.4 70.4 70.5 70.5 70.6 70.7 71.2 -1000 57.2 58.6 59.7 60.8 61.9 63.0 64.2 65.2 66.3 67.5 68.6 69.7 69.8 69.9 69.9 70.0 70.1 70.1 70.2 70.2 70.3 70.3 70.4 71.0 0 55.4 56.8 58.3 59.4 60.5 61.5 62.6 63.7 64.8 65.9 67.0 68.3 69.4 69.5 69.6 69.6 69.7 69.7 69.8 69.8 69.9 69.9 70.0 70.5 1000 54.6 56.0 57.4 58.5 59.5 60.5 61.6 62.6 63.8 64.9 65.9 66.9 67.9 67.9 68.0 68.0 68.1 68.1 68.2 68.2 68.3 68.3 68.8 LANDING CLIMB LIMIT WEIGHT (1000 KG) AIRPORT PRESSURE ALTITUDE (FT) 2000 3000 4000 5000 6000 7000 8000 9000 10000

53.8 55.2 56.5 57.5 58.5 59.5 60.6 61.6 62.7 63.8 64.7 65.5 66.3 66.3 66.4 66.4 66.5 66.5 66.5 66.6 66.6 67.1

52.9 54.3 55.6 56.6 57.5 58.6 59.6 60.6 61.5 62.4 63.1 63.8 64.3 64.4 64.4 64.4 64.5 64.5 64.5 64.6 65.0

52.1 53.3 54.6 55.6 56.5 57.5 58.6 59.5 60.2 60.9 61.5 62.0 62.4 62.4 62.5 62.5 62.5 62.6 62.6 63.1

51.2 52.4 53.7 54.6 55.6 56.5 57.3 58.1 58.7 59.2 59.7 60.1 60.5 60.6 60.6 60.6 60.6 60.7 61.1

50.1 51.2 52.3 53.3 54.2 55.0 55.8 56.6 57.0 57.4 57.9 58.3 58.6 58.7 58.7 58.7 58.7 59.1

48.9 49.8 50.8 51.8 52.7 53.5 54.2 54.9 55.3 55.7 56.1 56.5 56.8 56.8 56.8 56.9 57.2

47.7 48.5 49.3 50.3 51.1 51.9 52.6 53.3 53.7 54.0 54.3 54.7 55.0 55.0 55.0 55.4

46.5 47.4 48.2 49.1 49.9 50.5 51.1 51.6 52.0 52.3 52.6 52.9 53.2 53.2 53.6

45.3 46.2 47.1 47.8 48.6 49.1 49.5 49.9 50.2 50.6 50.9 51.2 51.4 51.9

With engine bleeds for packs off, increase weight by 1150 kg. With engine and wing anti-ice on, decrease weight by 200 kg. With engine and wing anti-ice on, decrease weight by 1200 kg (optional system). When operating in icing conditions during any part of the flight when forecast landing temperature is below 10°C, decrease weight by 6200 kg.

Copyright © The Boeing Company. See title page for details.

4.2.6

D632A008-ZZ022

November 1, 2006

737-800/CFM56-7B26 JAA/JAROPS Category C Brakes

NON-STANDARD CONFIGURATION Gear Down, Planning

Flight Planning and Performance Manual

GEAR DOWN

Gear Down, Planning

Obstacle Limit

Flaps 1

Based on engine bleed for packs on and anti-ice off

OBSTACLE LIMIT WEIGHT 40 HEAD 40 WIND (KTS) 20 0 REF LINE 50 60 (1000 KG) 70 80

TAIL 20 PRESS ALT (1000 FT) 10 5 0 ( C) ( F) 50 120 40 30 OAT 20 10 0 -10 (M) 300 40 20

DI

REF LINE

100 REF LINE 80 60

(FT)

85 80 75 70 65 60 55 50 45 40

E AK BR ) M OM 0 FR (10 CE E AN AS ST ELE R

35

90

OBSTACLE HEIGHT

30 800

200

25 600

100

400 200

0

0

When using line-up allowances, the obstacle distance from brake release must be reduced by the ASDA adjustment. Obstacle height must be calculated from the lowest point of the runway to conservatively account for runway slope. With engine bleed for packs off, increase weight by 200 kg. With engine anti-ice on, decrease weight by 250 kg . With engine and wing anti-ice on, decrease weight by 4300 kg (optional system).

Copyright © The Boeing Company. See title page for details.

November 1, 2006

D632A008-ZZ022

4.2.7

NON-STANDARD CONFIGURATION Gear Down, Planning

Flight Planning and Performance Manual

737-800/CFM56-7B26 JAA/JAROPS Category C Brakes

GEAR DOWN

Gear Down, Planning

Obstacle Limit

Flaps 5

Based on engine bleed for packs on and anti-ice off

OBSTACLE LIMIT WEIGHT 40 HEAD 40 WIND (KTS) 20 0 REF LINE 50 60 (1000 KG) 70 80

TAIL 20 PRESS ALT (1000 FT) 10 5 0 ( C) ( F) 50 120 40 30 OAT 20 10 0 -10 (M) 300 40 20

90 85 80 75 70 65 60 55 50 45 40

REF LINE

100 REF LINE 80 60

(FT)

DI

35

E AK BR ) OM 0 M FR (10 CE SE AN A ST ELE R

OBSTACLE HEIGHT

30 800

200

25 600

100

400 200

0

0

When using line-up allowances, the obstacle distance from brake release must be reduced by the ASDA adjustment. Obstacle height must be calculated from the lowest point of the runway to conservatively account for runway slope. With engine bleed for packs off, increase weight by 200 kg. With engine anti-ice on, decrease weight by 250 kg . With engine and wing anti-ice on, decrease weight by 4300 kg (optional system).

Copyright © The Boeing Company. See title page for details.

4.2.8

D632A008-ZZ022

November 1, 2006

737-800/CFM56-7B26 JAA/JAROPS Category C Brakes

NON-STANDARD CONFIGURATION Gear Down, Planning

Flight Planning and Performance Manual

GEAR DOWN

Gear Down, Planning

Obstacle Limit

Flaps 10

Based on engine bleed for packs on and anti-ice off

OBSTACLE LIMIT WEIGHT 40 HEAD 40 WIND (KTS) 20 0 REF LINE 50 60 (1000 KG) 70 80

TAIL 20 PRESS ALT (1000 FT) 10 5 0 ( C) ( F) 50 120 40 30 OAT 20 10 0 -10 (M) 300 40 20 100 REF LINE 80 60 REF LINE

DI

85 80 75 70 65 60 55 50 45 40

(FT)

E AK BR ) OM 0 M FR (10 CE SE AN A ST ELE R

35

90

OBSTACLE HEIGHT

3 800 0

200

600 400 200

25

100

0

0

When using line-up allowances, the obstacle distance from brake release must be reduced by the ASDA adjustment. Obstacle height must be calculated from the lowest point of the runway to conservatively account for runway slope. With engine bleed for packs off, increase weight by 200 kg. With engine anti-ice on, decrease weight by 250 kg . With engine and wing anti-ice on, decrease weight by 4300 kg (optional system).

Copyright © The Boeing Company. See title page for details.

November 1, 2006

D632A008-ZZ022

4.2.9

NON-STANDARD CONFIGURATION Gear Down, Planning

Flight Planning and Performance Manual

737-800/CFM56-7B26 JAA/JAROPS Category C Brakes

GEAR DOWN

Gear Down, Planning

Obstacle Limit

Flaps 15

Based on engine bleed for packs on and anti-ice off

OBSTACLE LIMIT WEIGHT 40 HEAD 40 WIND (KTS) 20 0 REF LINE 50 60 (1000 KG) 70 80

TAIL 20 PRESS ALT (1000 FT) 10 5 0 ( C) ( F) 50 120 40 30 OAT 20 10 0 -10 (M) 300 40 20

85 80 75 70 5 6 60 55 50 45 40

REF LINE

100 REF LINE 80 60

(FT)

DI

35

90

E AK BR ) OM 0 M FR (10 CE SE AN A ST ELE R

OBSTACLE HEIGHT

800 30 200 600 400 200 0 0

25

100

When using line-up allowances, the obstacle distance from brake release must be reduced by the ASDA adjustment. Obstacle height must be calculated from the lowest point of the runway to conservatively account for runway slope. With engine bleed for packs off, increase weight by 200 kg. With engine anti-ice on, decrease weight by 250 kg . With engine and wing anti-ice on, decrease weight by 4300 kg (optional system).

Copyright © The Boeing Company. See title page for details.

4.2.10

D632A008-ZZ022

November 1, 2006

737-800/CFM56-7B26 JAA/JAROPS Category C Brakes

NON-STANDARD CONFIGURATION Gear Down, Planning

Flight Planning and Performance Manual

GEAR DOWN

Gear Down, Planning

Obstacle Limit

Flaps 25

Based on engine bleed for packs on and anti-ice off

OBSTACLE LIMIT WEIGHT 40 HEAD 40 WIND (KTS) 20 0 REF LINE 50 60 (1000 KG) 70

TAIL 20 PRESS ALT (1000 FT) 10 5 0 ( C) ( F) 50 120 40 30 OAT 20 10 0 -10 (M) 300 40 20 (FT) 35 100 REF LINE 80 60 REF LINE

OBSTACLE HEIGHT

800 30 200 600 25 400 200 0 0

OM FR ASE CE LE AN RE M) ST E DI AK 100 ( BR 85 80 75 70 65 60 55 50 45 40

90

100

When using line-up allowances, the obstacle distance from brake release must be reduced by the ASDA adjustment. Obstacle height must be calculated from the lowest point of the runway to conservatively account for runway slope. With engine bleed for packs off, increase weight by 200 kg. With engine anti-ice on, decrease weight by 250 kg . With engine and wing anti-ice on, decrease weight by 4300 kg (optional system).

Copyright © The Boeing Company. See title page for details.

November 1, 2006

D632A008-ZZ022

4.2.11

NON-STANDARD CONFIGURATION Gear Down, Planning

Flight Planning and Performance Manual

737-800/CFM56-7B26 JAA/JAROPS Category C Brakes

GEAR DOWN ENGINE INOP

Net Level Off Weight

24

20

PRESSURE ALTITUDE (1000 FT)

16

ISA

DE

12

+1

+1

+2

8

0

VIA T LO

O

5

C

C&

ION

O

0

C

BE

W

O

4

0

40

44

48

52

56

60 WEIGHT (1000 KG)

64

68

72

76

80

Anti-Ice Adjustment

ANTI-ICE CONFIGURATION ENGINE ONLY ENGINE AND WING 2 -1.2 -6.0 4 -1.2 -5.9 6 -1.3 -5.8 LEVEL OFF WEIGHT (1000 KG) PRESSURE ALTITUDE (1000 FT) 8 10 12 -1.3 -1.3 -1.3 -5.6 -5.4 -5.2 14 -1.2 -5.0 16 -1.2 -4.9 18 -1.1 -4.8

Copyright © The Boeing Company. See title page for details.

4.2.12

D632A008-ZZ022

November 1, 2006

737-800/CFM56-7B26 JAA/JAROPS Category C Brakes

NON-STANDARD CONFIGURATION Gear Down, Planning

Flight Planning and Performance Manual

GEAR DOWN ENGINE INOP

Driftdown Profiles Net Flight Path

25 WEIGHT AT ENGINE FAILURE (1000 KG)

75 70 65 60 55 50 45 20

75 70 65 60 55 50 45 40 EQUIVALENT WEIGHT AT ENGINE FAILURE (1000 KG)

18 1.1

20 (1000 FT)

40 45

EQUIVALENT WEIGHT AT ENGINE FAILURE (1000 KG)

15

0

50 55 60

00 50

PRESSURE ALTITUDE

10

40 10 15 & BELOW ISA DEV (°C) 65 70

15

00 00

5

30

35

0 0 HEAD 100 (KTS) 50 0 REF LINE 50 0 50 100 150 200 5 10 15 20 25 30 35 40 45 50 (MIN) 55

40

FU EN EL G BU IN R E (K FA N F G IL RO ) UR M E

10

25

00

75

00 00

20

00

60

65

70

TIME FROM ENGINE FAILURE

TAIL 100

WIND

250 (NM)

300

GROUND DISTANCE FROM ENGINE FAILURE

Anti-Ice Adjustment

ANTI-ICE CONFIGURATION ENGINE ONLY ENGINE AND WING 0 1.2 6.0 2 1.2 5.9 4 1.3 5.8 6 1.3 5.6 LEVEL OFF WEIGHT (1000 KG) PRESSURE ALTITUDE (1000 FT) 8 10 12 1.3 1.3 1.3 5.4 5.2 5.0 14 1.2 4.9 16 1.2 4.8

Copyright © The Boeing Company. See title page for details.

November 1, 2006

D632A008-ZZ022

4.2.13

NON-STANDARD CONFIGURATION Gear Down, Planning

Flight Planning and Performance Manual

737-800/CFM56-7B26 JAA/JAROPS Category C Brakes

GEAR DOWN

Long Range Cruise Trip Fuel and Time

Based on VREF40 + 70 climb and descent

8 7 6 (HOURS) 5 4 3 2 1 0

P S RE RE TI AL DE (1 FT )

10 14 20

0 00

24

TU

TRIP TIME

SU

28

32

REF LINE

20 10 0 -10 ISA DEV (°C)

14

10

28

24

24

20

UD E

(10

00

FT )

20

SU

RE

PRESSURE ALTITUDE (1000 FT)

AL TIT

10

28

16

PR

12

28

8

HEAD 100 (KTS) 50 0 50 REF LINE

REF LINE

4

40 50 60 70 LANDING WEIGHT (1000 KG)

0

WIND

TAIL 100

0

500 TRIP DISTANCE

1000 1500 (NAUTICAL GROUND MILES)

2000

Copyright © The Boeing Company. See title page for details.

4.2.14

D632A008-ZZ022

November 1, 2006

FUEL REQUIRED (1000 KG)

ES

737-800/CFM56-7B26 JAA/JAROPS Category C Brakes

NON-STANDARD CONFIGURATION Gear Down, All Engine

Flight Planning and Performance Manual

4.3 NON-STANDARD CONFIGURATION-Gear Down, All Engine

Gear Down, All Engine

GEAR DOWN

PRESSURE ISA + 15°C 11500 14600 17600 20500 23500 26300 29000 31300 33500 36000

Long Range Cruise Altitude Capability

Max Cruise Thrust, 100 ft/min residual rate of climb

WEIGHT (1000 KG) 85 80 75 70 65 60 55 50 45 40 ISA + 10°C & BELOW 14600 17400 20300 22800 25400 27800 30200 32300 34500 36900 ISA + 20°C 8500 11700 14900 17800 20900 24400 27300 30100 32400 34900

Copyright © The Boeing Company. See title page for details.

November 1, 2006

D632A008-ZZ022

4.3.1

NON-STANDARD CONFIGURATION Gear Down, All Engine

Flight Planning and Performance Manual

737-800/CFM56-7B26 JAA/JAROPS Category C Brakes

GEAR DOWN

Gear Down, All Engine

Long Range Cruise Table

40000 FT to 35000 FT

PRESS ALT (1000 FT) (STD TAT) %N1 MAX TAT 40 KIAS MACH FF/ENG KTAS %N1 MAX TAT 39 KIAS MACH FF/ENG KTAS %N1 MAX TAT 38 KIAS MACH FF/ENG KTAS %N1 MAX TAT 37 KIAS (-42) MACH FF/ENG KTAS %N1 MAX TAT 36 KIAS (-43) MACH FF/ENG KTAS %N1 MAX TAT 35 KIAS (-40) MACH FF/ENG KTAS WEIGHT (1000 KG) 85 80 75 70 65 60 55 50 45 40

93.6 -28 191 .578 1309 333

92.5 -28 181 .573 1160 329 90.3 -23 182 .564 1134 323 88.6 -17 183 .554 1125 319

Max TAT not shown where %N1 can be set in ISA + 30°C conditions. Increase/decrease %N1 required by 1% per 5°C above/below standard TAT. Increase/decrease fuel flow 3% per 10°C above/below standard TAT. Increase/decrease KTAS by 1 knot per 1°C above/below standard TAT.

Max Cruise %N1

PRESS ALT (1000 FT) 37 36 35 -65 88.2 88.1 88.0 -60 89.2 89.1 89.0 -55 90.2 90.1 90.0 -50 91.1 91.0 91.0 -45 92.1 91.9 91.9 -40 93.0 92.8 92.8 TAT (°C) -35 -30 93.9 94.1 93.7 94.0 93.7 94.5 -25 93.3 93.2 93.8 -20 92.5 92.4 92.9 -15 91.5 91.4 91.9 -10 90.5 90.5 91.1 -5 89.5 89.5 90.1 0 88.3 88.4 89.0

With engine anti-ice on, decrease limit %N1 by 0.9. With engine and wing anti-ice on, decrease limit %N1 by 3.4.

Copyright © The Boeing Company. See title page for details.

4.3.2

D632A008-ZZ022

November 1, 2006

737-800/CFM56-7B26 JAA/JAROPS Category C Brakes

NON-STANDARD CONFIGURATION Gear Down, All Engine

Flight Planning and Performance Manual

GEAR DOWN

Gear Down, All Engine

Long Range Cruise Table

34000 FT to 29000 FT

PRESS ALT (1000 FT) (STD TAT) %N1 MAX TAT 34 KIAS (-39) MACH FF/ENG KTAS %N1 MAX TAT 33 KIAS (-36) MACH FF/ENG KTAS %N1 MAX TAT 32 KIAS (-35) MACH FF/ENG KTAS %N1 MAX TAT 31 KIAS (-33) MACH FF/ENG KTAS %N1 MAX TAT 30 KIAS (-31) MACH FF/ENG KTAS %N1 MAX TAT 29 KIAS (-29) MACH FF/ENG KTAS WEIGHT (1000 KG) 85 80 75 70 65 60 55 50 45 92.0 -21 192 .568 1285 329 90.1 -15 193 .559 1271 325 88.6 -9 194 .550 1266 321 87.4 -4 195 .541 1265 317 86.4 196 .530 1262 313 85.5 196 .520 1259 308 40 87.2 -12 184 .545 1121 316 86.1 185 .535 1119 311 85.1 185 .524 1117 306 84.2 185 .513 1115 301 83.2 185 .502 1113 296 82.3 185 .491 1112 291

95.7 -22 220 .580 1756 343

95.4 -21 211 .581 1610 341 93.7 -14 212 .571 1582 337 91.9 -9 213 .562 1564 333

94.7 -25 201 .580 1461 337 93.0 -18 202 .571 1435 333 91.1 -11 203 .561 1418 329 89.7 -6 204 .552 1412 325 88.5 -2 205 .544 1409 322

Max TAT not shown where %N1 can be set in ISA + 30°C conditions. Increase/decrease %N1 required by 1% per 5°C above/below standard TAT. Increase/decrease fuel flow 3% per 10°C above/below standard TAT. Increase/decrease KTAS by 1 knot per 1°C above/below standard TAT.

Max Cruise %N1

PRESS ALT (1000 FT) 34 33 32 31 30 29 -65 88.0 88.0 88.0 88.0 87.8 87.5 -60 89.0 89.0 89.0 89.0 88.7 88.5 -55 90.0 89.9 89.9 89.9 89.7 89.5 -50 90.9 90.9 90.9 90.9 90.7 90.4 -45 91.9 91.8 91.8 91.8 91.6 91.4 -40 92.8 92.8 92.8 92.7 92.5 92.3 TAT (°C) -35 -30 93.7 94.6 93.7 94.6 93.7 94.6 93.7 94.6 93.5 94.4 93.2 94.1 -25 94.3 94.9 95.4 95.5 95.3 95.0 -20 93.5 94.0 94.6 95.2 95.6 95.9 -15 92.5 93.1 93.8 94.3 94.7 95.2 -10 91.6 92.1 92.6 93.2 93.7 94.3 -5 90.6 91.1 91.7 92.2 92.6 93.1 0 89.5 90.1 90.6 91.2 91.6 92.1

With engine anti-ice on, decrease limit %N1 by 1.1. With engine and wing anti-ice on, decrease limit %N1 by 3.4.

Copyright © The Boeing Company. See title page for details.

November 1, 2006

D632A008-ZZ022

4.3.3

NON-STANDARD CONFIGURATION Gear Down, All Engine

Flight Planning and Performance Manual

737-800/CFM56-7B26 JAA/JAROPS Category C Brakes

GEAR DOWN

Gear Down, All Engine

Long Range Cruise Table

28000 FT to 23000 FT

PRESS ALT (1000 FT) (STD TAT) %N1 MAXTAT 28 KIAS (-27) MACH FF/ENG KTAS %N1 MAXTAT 27 KIAS (-26) MACH FF/ENG KTAS %N1 MAXTAT 26 KIAS (-24) MACH FF/ENG KTAS %N1 MAXTAT 25 KIAS (-22) MACH FF/ENG KTAS %N1 MAXTAT 24 KIAS (-20) MACH FF/ENG KTAS %N1 MAXTAT 23 KIAS (-18) MACH FF/ENG KTAS WEIGHT (1000 KG) 85 80 75 70 65 60 94.0 -12 221 .571 1727 339 92.3 -7 222 .562 1709 335 90.9 -2 223 .553 1701 331 89.8 2 224 .544 1697 328 88.9 6 225 .535 1697 324 88.0 9 225 .525 1696 319 55 90.4 -4 214 .553 1556 329 89.3 0 215 .545 1552 325 88.3 4 216 .535 1550 321 87.4 9 216 .525 1546 316 86.5 216 .515 1544 311 85.6 216 .504 1542 306 50 87.4 3 206 .534 1406 317 86.6 206 .523 1403 312 85.7 206 .513 1398 307 84.8 206 .502 1394 302 83.8 206 .492 1393 297 83.0 206 .482 1392 292 45 84.6 196 .508 1256 302 83.7 196 .498 1253 297 82.8 196 .487 1250 292 81.9 196 .477 1247 287 81.0 196 .468 1245 283 80.1 196 .458 1245 278 40 81.4 185 .481 1110 286 80.5 185 .471 1108 281 79.6 185 .461 1105 276 78.8 185 .452 1102 272 77.9 185 .443 1101 268 77.0 185 .434 1102 263

94.0 -7 239 .566 2014 342 92.6 -3 240 .557 2002 338

94.0 -10 230 .569 1871 341 92.6 -5 231 .560 1854 337 91.3 -1 232 .551 1847 333 90.2 3 233 .543 1847 330

Max TAT not shown where %N1 can be set in ISA + 30°C conditions. Increase/decrease %N1 required by 1% per 5°C above/below standard TAT. Increase/decrease fuel flow 3% per 10°C above/below standard TAT. Increase/decrease KTAS by 1 knot per 1°C above/below standard TAT.

Max Cruise %N1

PRESS ALT (1000 FT) 28 27 26 25 24 23 -55 88.9 88.3 87.6 87.0 86.5 86.1 -50 89.9 89.3 88.6 88.0 87.4 87.1 -45 90.8 90.2 89.6 89.0 88.4 88.0 -40 91.7 91.1 90.5 89.9 89.3 88.9 -35 92.6 92.0 91.4 90.9 90.3 89.9 -30 93.5 93.0 92.3 91.8 91.2 90.8 TAT (°C) -25 -20 94.4 95.3 93.9 94.8 93.2 94.1 92.7 93.6 92.1 93.0 91.7 92.6 -15 95.6 95.6 95.0 94.5 93.9 93.5 -10 94.6 95.0 95.5 95.4 94.8 94.4 -5 93.6 94.0 94.5 94.9 94.8 94.9 0 92.5 92.9 93.4 93.9 93.8 93.8 5 91.5 91.9 92.4 92.8 92.8 92.8 10 90.3 90.9 91.3 91.8 91.9 92.0

With engine anti-ice on, decrease limit %N1 by 1.2. With engine and wing anti-ice on, decrease limit %N1 by 3.1.

Copyright © The Boeing Company. See title page for details.

4.3.4

D632A008-ZZ022

November 1, 2006

737-800/CFM56-7B26 JAA/JAROPS Category C Brakes

NON-STANDARD CONFIGURATION Gear Down, All Engine

Flight Planning and Performance Manual

GEAR DOWN

Gear Down, All Engine

Long Range Cruise Table

22000 FT to 17000 FT

PRESS ALT (1000 FT) (STD TAT) %N1 MAXTAT 22 KIAS (-17) MACH FF/ENG KTAS %N1 MAXTAT 21 KIAS (-15) MACH FF/ENG KTAS %N1 MAXTAT 20 KIAS (-13) MACH FF/ENG KTAS %N1 MAXTAT 19 KIAS (-11) MACH FF/ENG KTAS %N1 MAXTAT 18 KIAS (-9) MACH FF/ENG KTAS %N1 MAXTAT 17 KIAS (-8) MACH FF/ENG KTAS WEIGHT (1000 KG) 85 80 75 70 91.4 1 241 .549 1999 335 90.4 5 242 .541 2004 331 89.6 8 243 .532 2006 327 88.7 12 243 .522 2007 322 87.8 16 243 .511 2007 317 86.9 20 243 .501 2007 312 65 89.3 7 234 .534 1850 325 88.4 10 234 .524 1851 321 87.5 14 234 .514 1850 316 86.6 18 234 .503 1849 310 85.7 22 234 .494 1851 306 84.9 234 .484 1853 301 60 87.1 13 225 .515 1695 314 86.2 225 .504 1694 308 85.3 225 .494 1695 304 84.4 225 .485 1696 299 83.6 225 .475 1698 294 82.7 225 .466 1701 290 55 84.7 216 .494 1542 301 83.8 216 .484 1543 296 82.9 216 .475 1544 292 82.0 216 .465 1546 287 81.2 216 .456 1549 283 80.3 216 .448 1553 278 50 82.1 206 .472 1393 288 81.2 206 .463 1395 283 80.3 206 .454 1397 279 79.5 206 .445 1401 274 78.6 206 .436 1405 270 77.8 207 .428 1410 266 45 79.3 196 .449 1247 274 78.4 196 .441 1251 270 77.6 196 .432 1255 265 76.7 196 .424 1260 261 75.8 196 .416 1266 257 75.0 196 .408 1272 253 40 76.1 185 .425 1107 259 75.3 185 .417 1114 255 74.5 185 .409 1120 251 73.7 185 .401 1126 247 72.9 186 .393 1132 243 72.1 186 .386 1138 240

92.4 2 257 .551 2311 340 91.5 6 258 .543 2317 336 90.7 9 259 .534 2323 332

92.6 0 248 .554 2154 339 91.4 3 250 .546 2155 336 90.6 7 251 .538 2162 332 89.8 10 251 .528 2165 327 88.9 14 251 .518 2166 322

Max TAT not shown where %N1 can be set in ISA + 30°C conditions. Increase/decrease %N1 required by 1% per 5°C above/below standard TAT. Increase/decrease fuel flow 3% per 10°C above/below standard TAT. Increase/decrease KTAS by 1 knot per 1°C above/below standard TAT.

Max Cruise %N1

PRESS ALT (1000 FT) 22 21 20 19 18 17 -45 87.3 86.9 86.4 85.7 85.2 84.5 -40 88.2 87.8 87.4 86.6 86.1 85.4 -35 89.2 88.7 88.3 87.5 87.0 86.3 -30 90.1 89.6 89.2 88.4 87.9 87.2 -25 91.0 90.5 90.1 89.3 88.8 88.1 -20 91.9 91.4 91.0 90.2 89.7 89.0 TAT (°C) -15 -10 92.7 93.6 92.3 93.2 91.8 92.7 91.1 91.9 90.5 91.4 89.8 90.7 -5 94.5 94.0 93.6 92.8 92.2 91.5 0 93.8 93.9 94.2 93.6 93.1 92.4 5 92.8 92.9 93.0 93.1 93.2 93.2 10 92.0 92.0 92.1 92.2 92.3 92.3 15 91.0 91.1 91.2 91.3 91.4 91.5 20 89.9 90.0 90.2 90.3 90.4 90.5

With engine anti-ice on, decrease limit %N1 by 1.1. With engine and wing anti-ice on, decrease limit %N1 by 2.8.

Copyright © The Boeing Company. See title page for details.

November 1, 2006

D632A008-ZZ022

4.3.5

NON-STANDARD CONFIGURATION Gear Down, All Engine

Flight Planning and Performance Manual

737-800/CFM56-7B26 JAA/JAROPS Category C Brakes

GEAR DOWN

Gear Down, All Engine

Long Range Cruise Table

16000 FT to 11000 FT

PRESS ALT (1000 FT) (STD TAT) %N1 MAXTAT 16 KIAS (-6) MACH FF/ENG KTAS %N1 MAXTAT 15 KIAS (-4) MACH FF/ENG KTAS %N1 MAXTAT 14 KIAS (-2) MACH FF/ENG KTAS %N1 MAXTAT 13 KIAS (-1) MACH FF/ENG KTAS %N1 MAXTAT 12 KIAS (1) MACH FF/ENG KTAS %N1 MAXTAT 11 KIAS (3) MACH FF/ENG KTAS WEIGHT (1000 KG) 85 91.5 8 266 .538 2482 336 90.7 12 267 .529 2483 331 89.8 15 267 .519 2482 327 88.9 18 267 .509 2477 322 88.1 22 267 .500 2473 317 87.3 25 267 .491 2469 312 80 89.8 13 259 .524 2325 327 89.0 16 259 .514 2324 322 88.1 20 259 .504 2320 317 87.2 23 259 .495 2318 312 86.4 27 259 .486 2315 308 85.6 30 259 .477 2313 303 75 88.0 18 251 .508 2166 317 87.1 22 251 .498 2165 312 86.3 25 251 .489 2164 308 85.4 29 251 .480 2162 303 84.6 32 251 .471 2160 299 83.8 251 .463 2160 294 70 86.1 23 243 .492 2009 307 85.2 27 243 .483 2009 302 84.4 243 .474 2009 298 83.5 243 .465 2009 293 82.7 243 .456 2008 289 81.9 243 .448 2009 285 65 84.0 234 .475 1855 296 83.2 234 .466 1856 292 82.3 234 .457 1857 288 81.5 234 .449 1858 283 80.7 234 .441 1859 279 79.9 235 .433 1861 275 60 81.8 225 .457 1704 285 81.0 225 .449 1706 281 80.2 226 .441 1709 277 79.3 226 .432 1711 273 78.5 226 .425 1714 269 77.7 226 .417 1718 265 55 79.5 216 .439 1557 274 78.6 216 .431 1561 270 77.8 216 .423 1565 266 77.0 217 .415 1569 262 76.2 217 .408 1573 258 75.5 217 .400 1577 254 50 76.9 207 .420 1415 262 76.1 207 .412 1421 258 75.3 207 .405 1425 254 74.6 207 .397 1430 251 73.9 207 .390 1434 247 73.1 207 .383 1438 243 45 74.3 196 .400 1278 250 73.5 197 .392 1284 246 72.7 197 .385 1289 242 71.9 197 .378 1294 239 71.1 197 .371 1299 235 70.3 197 .364 1304 232 40 71.3 186 .378 1145 236 70.5 186 .371 1151 233 69.6 186 .365 1156 229 68.8 186 .358 1162 226 68.0 187 .352 1169 223 67.3 187 .346 1176 220

Max TAT not shown where %N1 can be set in ISA + 30°C conditions. Increase/decrease %N1 required by 1% per 5°C above/below standard TAT. Increase/decrease fuel flow 3% per 10°C above/below standard TAT. Increase/decrease KTAS by 1 knot per 1°C above/below standard TAT.

Max Cruise %N1

PRESS ALT (1000 FT) 16 15 14 13 12 11 -35 85.9 85.5 85.0 84.5 84.0 83.4 -30 86.8 86.4 85.9 85.4 84.8 84.3 -25 87.7 87.3 86.8 86.2 85.7 85.2 -20 88.5 88.1 87.6 87.1 86.5 86.0 -15 89.4 89.0 88.5 87.9 87.4 86.8 -10 90.2 89.8 89.3 88.8 88.2 87.7 TAT (°C) -5 0 91.1 91.9 90.6 91.5 90.1 90.9 89.6 90.4 89.0 89.8 88.5 89.3 5 92.7 92.3 91.8 91.2 90.6 90.1 10 92.5 92.6 92.6 92.0 91.4 90.8 15 91.6 91.6 91.6 91.7 91.7 91.6 20 90.7 90.8 90.8 90.8 90.8 90.7 25 89.8 89.9 90.0 90.0 90.0 89.9 30 88.8 89.0 89.1 89.1 89.1 89.1

With engine anti-ice on, decrease limit %N1 by 1.1. With engine and wing anti-ice on, decrease limit %N1 by 2.5.

Copyright © The Boeing Company. See title page for details.

4.3.6

D632A008-ZZ022

November 1, 2006

737-800/CFM56-7B26 JAA/JAROPS Category C Brakes

NON-STANDARD CONFIGURATION Gear Down, All Engine

Flight Planning and Performance Manual

GEAR DOWN

Gear Down, All Engine

Long Range Cruise Table

10000 FT to 5000 FT

PRESS ALT (1000 FT) (STD TAT) %N1 MAXTAT 10 KIAS (5) MACH FF/ENG KTAS %N1 MAXTAT 9 KIAS (6) MACH FF/ENG KTAS %N1 MAXTAT 8 KIAS (8) MACH FF/ENG KTAS %N1 MAXTAT 7 KIAS (10) MACH FF/ENG KTAS %N1 MAXTAT 6 KIAS (11) MACH FF/ENG KTAS %N1 MAXTAT 5 KIAS (13) MACH FF/ENG KTAS WEIGHT (1000 KG) 85 86.5 28 267 .482 2467 308 85.6 32 267 .473 2467 303 84.8 36 267 .465 2467 299 84.0 39 267 .456 2468 295 83.2 43 267 .448 2469 290 82.4 46 267 .441 2471 286 80 84.8 34 259 .468 2313 299 83.9 37 259 .460 2313 295 83.1 259 .452 2314 290 82.3 259 .444 2316 286 81.5 259 .436 2318 282 80.7 259 .428 2321 278 75 83.0 251 .454 2160 290 82.2 251 .446 2162 286 81.3 251 .438 2164 282 80.5 251 .430 2166 278 79.7 252 .423 2170 274 79.0 252 .416 2175 270 70 81.1 243 .440 2010 281 80.3 243 .432 2013 277 79.4 243 .424 2017 273 78.7 243 .417 2021 269 77.9 244 .410 2025 265 77.2 244 .402 2030 262 65 79.0 235 .425 1864 271 78.3 235 .417 1869 267 77.5 235 .410 1873 264 76.7 235 .403 1877 260 76.0 235 .395 1882 256 75.3 235 .389 1887 253 60 76.9 226 .409 1722 261 76.2 226 .402 1726 258 75.5 226 .395 1730 254 74.7 226 .388 1735 250 73.9 226 .381 1740 247 73.1 227 .374 1746 243 55 74.7 217 .393 1581 251 74.0 217 .386 1586 247 73.2 217 .379 1590 244 72.4 217 .372 1596 240 71.6 217 .366 1602 237 70.8 218 .360 1609 234 50 72.3 207 .376 1443 240 71.4 207 .369 1449 237 70.6 208 .363 1455 233 69.9 208 .357 1461 230 69.1 208 .350 1469 227 68.4 208 .345 1477 224 45 69.5 197 .358 1310 229 68.7 198 .352 1317 225 67.9 198 .346 1325 222 67.2 198 .340 1333 220 66.6 199 .335 1341 217 65.9 199 .329 1351 214 40 66.6 187 .340 1184 217 65.9 188 .334 1191 214 65.2 188 .329 1200 211 64.5 188 .323 1208 209 63.9 189 .318 1216 206 63.2 189 .313 1226 204

Max TAT not shown where %N1 can be set in ISA + 30°C conditions. Increase/decrease %N1 required by 1% per 5°C above/below standard TAT. Increase/decrease fuel flow 3% per 10°C above/below standard TAT. Increase/decrease KTAS by 1 knot per 1°C above/below standard TAT.

Max Cruise %N1

PRESS ALT (1000 FT) 10 9 8 7 6 5 -25 84.6 84.1 83.6 83.1 82.6 82.1 -20 85.4 84.9 84.4 83.9 83.4 82.9 -15 86.2 85.8 85.3 84.8 84.2 83.7 -10 87.1 86.6 86.1 85.6 85.0 84.5 -5 87.9 87.4 86.9 86.4 85.8 85.3 0 88.7 88.2 87.7 87.2 86.6 86.1 TAT (°C) 5 10 89.5 90.2 89.0 89.7 88.4 89.2 87.9 88.7 87.4 88.1 86.9 87.6 15 91.0 90.5 90.0 89.4 88.9 88.3 20 90.7 90.8 90.7 90.2 89.6 89.1 25 89.9 90.0 90.1 90.2 90.3 89.8 30 89.1 89.2 89.3 89.4 89.5 89.4 35 88.2 88.3 88.5 88.6 88.6 88.6 40 87.3 87.4 87.6 87.7 87.9 87.8

With engine anti-ice on, decrease limit %N1 by 1.0. With engine and wing anti-ice on, decrease limit %N1 by 2.3.

Copyright © The Boeing Company. See title page for details.

November 1, 2006

D632A008-ZZ022

4.3.7

NON-STANDARD CONFIGURATION Gear Down, All Engine

Flight Planning and Performance Manual

737-800/CFM56-7B26 JAA/JAROPS Category C Brakes

GEAR DOWN

Gear Down, All Engine

Long Range Cruise Enroute Fuel and Time

Based on VREF40 + 70 descent

8 7 (HOURS) 6 5 4 3

PR ES RE SU AL T TI UD E ( 0 10 0 F T)

10 14

20 24

28

TIME REQUIRED

2 1 0 20 10 0 -10 ISA DEV (°C) REF LINE 24

14

10

20

TI

TU

DE

(1

00

0

16

RE

AL

12 PRESSURE 10 ALTITUDE (1000 FT) 28 8

4 REF LINE

0 40 HEAD 100 (KTS) 50 0 WIND 50 REF LINE 50 60 70 80 WEIGHT AT CHECK POINT (1000 KG)

TAIL 100

0

200

400 600 800 1000 1200 1400 1600 1800 DISTANCE FROM CHECK POINT (NAUTICAL GROUND MILES)

Copyright © The Boeing Company. See title page for details.

4.3.8

D632A008-ZZ022

November 1, 2006

FUEL REQUIRED (1000 KG)

20 24 28

PR

ES

SU

FT

)

737-800/CFM56-7B26 JAA/JAROPS Category C Brakes

NON-STANDARD CONFIGURATION Gear Down, All Engine

Flight Planning and Performance Manual

GEAR DOWN

Gear Down, All Engine

Descent

VREF40 + 70

PRESSURE ALTITUDE (FT) 41000 39000 37000 35000 33000 31000 29000 27000 25000 23000 21000 19000 17000 15000 10000 5000 1500 TIME (MIN) 20 20 19 18 18 17 16 15 15 14 13 12 11 11 8 6 4 FUEL (KG) 270 270 260 260 250 250 240 240 230 220 220 210 200 190 170 130 110 DISTANCE (NM) 88 84 79 75 71 67 63 59 55 51 47 43 39 35 25 16 9

Allowances for a straight-in approach are included.

Holding

Flaps Up

PRESSURE ALTITUDE (FT) %N1 35000 KIAS FF/ENG %N1 30000 KIAS FF/ENG %N1 25000 KIAS FF/ENG %N1 20000 KIAS FF/ENG %N1 15000 KIAS FF/ENG %N1 10000 KIAS FF/ENG %N1 5000 KIAS FF/ENG %N1 1500 KIAS FF/ENG WEIGHT (1000 KG) 80 75 70 65 60 55 50 45 92.6 185 1320 85.1 185 1250 80.5 185 1230 76.0 185 1240 71.8 185 1270 67.6 185 1290 63.7 185 1310 60.8 185 1330 40 87.7 178 1140 82.2 178 1120 77.7 178 1110 73.4 178 1130 69.1 178 1150 65.0 178 1170 61.0 178 1200 58.2 178 1220

90.8 225 2170 86.1 225 2160 81.8 225 2140 77.5 225 2150 74.8 225 2160

89.0 220 2030 84.4 220 2020 80.0 220 2010 76.0 220 2030 73.1 220 2040

93.1 216 1940 87.1 216 1890 82.5 216 1890 78.2 216 1890 74.3 216 1900 71.3 216 1920

90.2 211 1780 85.1 211 1750 80.7 211 1760 76.4 211 1770 72.4 211 1780 69.5 211 1800

95.7 204 1740 87.7 204 1630 83.1 204 1620 78.6 204 1630 74.5 204 1640 70.3 204 1660 67.5 204 1680

91.6 198 1550 85.5 198 1490 80.9 198 1490 76.4 198 1500 72.4 198 1520 68.2 198 1540 65.5 198 1570

87.9 192 1390 83.0 192 1360 78.5 192 1360 74.2 192 1380 70.0 192 1400 66.0 192 1430 63.3 192 1450

This table includes 5% additional fuel for holding in a racetrack pattern.

Copyright © The Boeing Company. See title page for details.

November 1, 2006

D632A008-ZZ022

4.3.9

NON-STANDARD CONFIGURATION Gear Down, All Engine

Flight Planning and Performance Manual

737-800/CFM56-7B26 JAA/JAROPS Category C Brakes

Intentionally Blank

Copyright © The Boeing Company. See title page for details.

4.3.10

D632A008-ZZ022

November 1, 2006

737-800/CFM56-7B26 JAA/JAROPS Category C Brakes

NON-STANDARD CONFIGURATION Gear Down, Engine Inoperative

Flight Planning and Performance Manual

4.4 NON-STANDARD CONFIGURATION-Gear Down, Engine Inoperative

GEAR DOWN ENGINE INOP

MAX CONTINUOUS THRUST

Gear Down, Engine Inoperative

Driftdown/LRC Cruise Range Capability

Includes APU fuel burn

TIME FROM START OF DRIFTDOWN (HOURS) 4

3

W EIG

S HT

2

AR ST T DR

IFT

W DO

N

20 FUEL FROM START OF DRIFTDOWN (1000 KG)

1

AL

L

0

AR ST

T

D

T RIF

W DO

N

W

EIG

HT

(1

0

00

) KG

80 75 70 65 60 55 50 45

40

16

12

8

4

0 HEAD 100 WIND (KTS) 50 0 50 0 200 400 600 800 DISTANCE (NAUTICAL GROUND MILES) 1000 REF LINE

TAIL 100

Copyright © The Boeing Company. See title page for details.

November 1, 2006

D632A008-ZZ022

4.4.1

NON-STANDARD CONFIGURATION Gear Down, Engine Inoperative

Flight Planning and Performance Manual

737-800/CFM56-7B26 JAA/JAROPS Category C Brakes

GEAR DOWN ENGINE INOP

MAX CONTINUOUS THRUST

Gear Down, Engine Inoperative

Long Range Cruise Altitude Capability

100 ft/min residual rate of climb

WEIGHT (1000 KG) 75 70 65 60 55 50 45 40 ISA + 10°C & BELOW 700 3800 6800 10000 12700 15600 18700 21800 PRESSURE ALTITUDE (FT) ISA + 15°C 1600 5200 8400 11600 14800 17800 20900 ISA + 20°C

2600 6200 9800 13700 17000 20000

Copyright © The Boeing Company. See title page for details.

4.4.2

D632A008-ZZ022

November 1, 2006

737-800/CFM56-7B26 JAA/JAROPS Category C Brakes

NON-STANDARD CONFIGURATION Gear Down, Engine Inoperative

Flight Planning and Performance Manual

GEAR DOWN ENGINE INOP

MAX CONTINUOUS THRUST

Gear Down, Engine Inoperative

Long Range Cruise Diversion Fuel and Time

Based on VREF40 + 70 descent and includes APU fuel burn

5

6

4 (HOURS)

10 14

3

TIME REQUIRED

(1 TI T E UD

0 00

FT

)

2

1 REF LINE

14 10

PR

E

6

U SS

RE

AL

14

12

RE

AL

TI T

8

PR

PRESSURE 6 ALTITUDE (1000 FT) 14

6

4

2 REF LINE

0 40 HEAD 100 (KTS) 50 0 WIND 50 REF LINE 50 60 70 80 WEIGHT AT CHECK POINT (1000 KG)

TAIL 100

0

200

400 600 800 DISTANCE FROM CHECK POINT (NAUTICAL GROUND MILES)

1000

Copyright © The Boeing Company. See title page for details.

November 1, 2006

D632A008-ZZ022

FUEL REQUIRED (1000 KG)

ES

SU

UD

E

(1

20 10 0 -10 ISA DEV (°C)

00

0

FT

0

10

)

4.4.3

NON-STANDARD CONFIGURATION Gear Down, Engine Inoperative

Flight Planning and Performance Manual

737-800/CFM56-7B26 JAA/JAROPS Category C Brakes

GEAR DOWN ENGINE INOP

MAX CONTINUOUS THRUST

Gear Down, Engine Inoperative

Long Range Cruise Table

23000 FT to 18000 FT

PRESS ALT (1000 FT) (STD TAT) %N1 MAXTAT KIAS 23 MACH FF/ENG KTAS %N1 MAXTAT 22 KIAS (-20) MACH FF/ENG KTAS %N1 MAXTAT 21 KIAS (-19) MACH FF/ENG KTAS %N1 MAXTAT 20 KIAS (-16) MACH FF/ENG KTAS %N1 MAXTAT 19 KIAS (-15) MACH FF/ENG KTAS %N1 MAXTAT 18 KIAS (-13) MACH FF/ENG KTAS WEIGHT (1000 KG) 80 75 70 65 60 55 50 45 40

100.0 -6 188 .415 2548 255 97.7 1 189 .408 2489 252 95.6 8 189 .401 2443 248

97.2 -5 178 .409 2207 249 95.1 2 179 .402 2160 246 93.1 10 179 .395 2123 242 91.5 179 .387 2107 239 90.3 179 .380 2104 235

Max TAT not shown where %N1 can be set in ISA + 30°C conditions. Increase/decrease %N1 required by 1% per 5°C above/below standard TAT. Increase/decrease fuel flow 3% per 10°C above/below standard TAT. Increase/decrease KTAS by 1 knot per 1°C above/below standard TAT.

Max Continuous %N1

PRESS ALT (1000 FT) 23 22 21 20 19 18 -50 92.9 92.7 92.5 92.6 92.2 91.7 -45 93.9 93.7 93.5 93.6 93.2 92.7 -40 94.8 94.6 94.5 94.6 94.1 93.7 -35 95.8 95.6 95.5 95.6 95.1 94.7 -30 96.7 96.5 96.4 96.6 96.1 95.6 -25 97.6 97.4 97.4 97.5 97.0 96.6 TAT (°C) -20 -15 98.5 99.4 98.3 99.2 98.3 99.2 98.4 99.3 98.0 98.9 97.5 98.4 -10 99.6 100.1 100.0 100.2 99.8 99.3 -5 98.8 99.3 99.9 100.6 100.6 100.2 0 97.7 98.2 98.8 99.6 100.0 100.1 5 96.9 97.4 97.9 98.6 99.0 99.2 10 95.9 96.5 97.0 97.6 98.0 98.3 15 94.8 95.3 96.0 96.7 97.1 97.4

With engine anti-ice on, decrease limit %N1 by 1.2. With engine and wing anti-ice on, decrease limit %N1 by 4.3.

Copyright © The Boeing Company. See title page for details.

4.4.4

D632A008-ZZ022

November 1, 2006

737-800/CFM56-7B26 JAA/JAROPS Category C Brakes

NON-STANDARD CONFIGURATION Gear Down, Engine Inoperative

Flight Planning and Performance Manual

GEAR DOWN ENGINE INOP

MAX CONTINUOUS THRUST

Gear Down, Engine Inoperative

Long Range Cruise Table

17000 FT to 12000 FT

PRESS ALT (1000 FT) (STD TAT) %N1 MAXTAT 17 KIAS (-11) MACH FF/ENG KTAS %N1 MAXTAT 16 KIAS (-9) MACH FF/ENG KTAS %N1 MAXTAT 15 KIAS (-7) MACH FF/ENG KTAS %N1 MAXTAT 14 KIAS (-5) MACH FF/ENG KTAS %N1 MAXTAT 13 KIAS (-3) MACH FF/ENG KTAS %N1 MAXTAT 12 KIAS (-2) MACH FF/ENG KTAS WEIGHT (1000 KG) 80 75 70 65 60 55 50 99.5 -4 198 .412 2824 256 97.2 7 199 .405 2766 253 95.1 16 199 .398 2722 249 93.6 20 200 .391 2696 246 92.3 24 200 .384 2684 242 91.4 28 200 .377 2678 239 45 93.5 15 189 .393 2411 245 92.1 190 .386 2399 241 90.9 190 .380 2396 238 90.0 190 .373 2394 235 89.1 191 .367 2393 231 88.2 191 .361 2393 229 40 89.3 180 .374 2106 232 88.4 180 .367 2109 229 87.5 181 .361 2113 226 86.6 181 .355 2117 223 85.8 182 .349 2122 220 85.1 182 .344 2130 218

98.4 6 208 .407 3081 256 96.4 13 209 .400 3027 253 94.7 19 209 .393 2989 249

Max TAT not shown where %N1 can be set in ISA + 30°C conditions. Increase/decrease %N1 required by 1% per 5°C above/below standard TAT. Increase/decrease fuel flow 3% per 10°C above/below standard TAT. Increase/decrease KTAS by 1 knot per 1°C above/below standard TAT.

Max Continuous %N1

PRESS ALT (1000 FT) 17 16 15 14 13 12 -40 93.3 92.8 92.2 91.6 91.0 90.5 -35 94.2 93.7 93.1 92.5 92.0 91.4 -30 95.2 94.6 94.0 93.5 92.9 92.4 -25 96.1 95.5 94.9 94.4 93.8 93.3 -20 97.0 96.5 95.8 95.3 94.7 94.2 -15 97.9 97.3 96.7 96.1 95.6 95.0 TAT (°C) -10 -5 98.8 99.6 98.2 99.1 97.6 98.4 97.0 97.8 96.4 97.3 95.9 96.8 0 100.2 99.9 99.2 98.7 98.1 97.6 5 99.2 99.2 99.2 99.2 98.9 98.4 10 98.6 98.7 98.6 98.4 98.4 98.5 15 97.5 97.7 97.7 97.6 97.5 97.5 20 96.8 96.9 97.0 96.7 96.6 96.6 25 95.7 96.0 96.1 96.0 95.9 95.8

With engine anti-ice on, decrease limit %N1 by 1.2. With engine and wing anti-ice on, decrease limit %N1 by 3.8.

Copyright © The Boeing Company. See title page for details.

November 1, 2006

D632A008-ZZ022

4.4.5

NON-STANDARD CONFIGURATION Gear Down, Engine Inoperative

Flight Planning and Performance Manual

737-800/CFM56-7B26 JAA/JAROPS Category C Brakes

GEAR DOWN ENGINE INOP

MAX CONTINUOUS THRUST

Gear Down, Engine Inoperative

Long Range Cruise Table

11000 FT to 6000 FT

PRESS ALT (1000 FT) (STD TAT) %N1 MAXTAT 11 KIAS (1) MACH FF/ENG KTAS %N1 MAXTAT 10 KIAS (2) MACH FF/ENG KTAS %N1 MAXTAT 9 KIAS (4) MACH FF/ENG KTAS %N1 MAXTAT 8 KIAS (6) MACH FF/ENG KTAS %N1 MAXTAT 7 KIAS (8) MACH FF/ENG KTAS %N1 MAXTAT 6 KIAS (10) MACH FF/ENG KTAS WEIGHT (1000 KG) 80 75 70 65 60 97.3 13 218 .402 3326 256 95.6 19 218 .395 3282 252 94.3 23 218 .388 3263 249 93.3 27 219 .382 3255 245 92.4 31 219 .375 3252 242 91.6 36 219 .369 3250 239 55 93.5 23 209 .387 2971 246 92.4 27 210 .380 2964 243 91.6 31 210 .374 2961 239 90.7 35 210 .368 2960 236 89.8 211 .362 2961 233 89.0 212 .356 2966 231 50 90.5 201 .371 2674 236 89.6 201 .365 2674 233 88.7 202 .359 2676 230 87.9 202 .353 2682 227 87.2 203 .348 2691 225 86.4 204 .343 2702 222 45 87.4 192 .355 2396 226 86.6 192 .349 2403 223 85.9 193 .344 2412 220 85.2 194 .339 2424 218 84.4 195 .334 2437 215 83.8 195 .329 2451 213 40 84.3 183 .339 2139 215 83.6 184 .333 2151 213 82.9 184 .329 2164 211 82.2 185 .324 2179 208 81.5 186 .320 2196 206 80.9 187 .315 2214 204

96.3 19 227 .395 3575 254 95.0 24 227 .389 3556 251 94.0 28 227 .382 3548 248

Max TAT not shown where %N1 can be set in ISA + 30°C conditions. Increase/decrease %N1 required by 1% per 5°C above/below standard TAT. Increase/decrease fuel flow 3% per 10°C above/below standard TAT. Increase/decrease KTAS by 1 knot per 1°C above/below standard TAT.

Max Continuous %N1

PRESS ALT (1000 FT) 11 10 9 8 7 6 -25 92.8 92.3 91.8 91.3 90.6 90.1 -20 93.7 93.2 92.7 92.2 91.5 91.0 -15 94.6 94.1 93.5 93.1 92.4 91.9 -10 95.4 94.9 94.4 93.9 93.3 92.7 -5 96.3 95.8 95.3 94.8 94.1 93.6 0 97.1 96.6 96.1 95.6 95.0 94.4 TAT (°C) 5 10 98.0 98.6 97.5 98.3 96.9 97.7 96.4 97.3 95.8 96.6 95.2 96.0 15 97.6 97.8 97.9 98.0 97.4 96.8 20 96.6 96.7 96.9 97.2 97.4 97.6 25 95.8 95.9 96.0 96.2 96.4 96.7 30 95.1 95.1 95.3 95.5 95.6 95.8 35 94.2 94.2 94.4 94.6 94.9 95.1 40 93.2 93.2 93.5 93.7 94.0 94.3

With engine anti-ice on, decrease limit %N1 by 1.0. With engine and wing anti-ice on, decrease limit %N1 by 3.5.

Copyright © The Boeing Company. See title page for details.

4.4.6

D632A008-ZZ022

November 1, 2006

737-800/CFM56-7B26 JAA/JAROPS Category C Brakes

NON-STANDARD CONFIGURATION Gear Down, Engine Inoperative

Flight Planning and Performance Manual

GEAR DOWN ENGINE INOP

MAX CONTINUOUS THRUST

Gear Down, Engine Inoperative

Holding

Flaps Up

PRESSURE ALTITUDE (FT) %N1 15000 KIAS FF/ENG %N1 10000 KIAS FF/ENG %N1 5000 KIAS FF/ENG %N1 1500 KIAS FF/ENG WEIGHT (1000 KG) 80 75 70 65 60 55 98.4 198 3110 91.0 198 2940 86.4 198 2920 83.5 198 2920 50 93.6 192 2730 88.3 192 2670 83.9 192 2660 80.9 192 2670 45 90.2 185 2450 85.5 185 2420 81.2 185 2420 78.3 185 2440 40 87.1 178 2180 82.6 178 2170 78.3 178 2190 75.6 178 2210

94.1 225 4240

95.5 220 4010 92.1 220 3960

93.3 216 3730 90.0 216 3680

97.0 211 3560 91.1 211 3450 88.0 211 3430

93.6 204 3230 88.8 204 3180 85.8 204 3170

This table includes 5% additional fuel for holding in a racetrack pattern.

Copyright © The Boeing Company. See title page for details.

November 1, 2006

D632A008-ZZ022

4.4.7

NON-STANDARD CONFIGURATION Gear Down, Engine Inoperative

Flight Planning and Performance Manual

737-800/CFM56-7B26 JAA/JAROPS Category C Brakes

Intentionally Blank

Copyright © The Boeing Company. See title page for details.

4.4.8

D632A008-ZZ022

November 1, 2006

737-800/CFM56-7B26 JAA/JAROPS Category C Brakes

NON-STANDARD CONFIGURATION Alternate Mode EEC

Flight Planning and Performance Manual

4.5 NON-STANDARD CONFIGURATION-Alternate Mode EEC

Alternate Mode EEC

ALTERNATE MODE EEC

ALTERNATE MODE EEC LIMIT WEIGHT (1000 KG) NORMAL MODE PERFORMANCE LIMIT WEIGHT (1000 KG) 56 60 64 68 72 53.3 57.0 60.8 64.2 68.4 52.4 56.1 60.0 63.6 67.3 52.6 56.3 60.1 63.7 67.4

Alternate Mode EEC Limit Weight

PERFORMANCE LIMIT FIELD CLIMB OBSTACLE 44 41.8 41.1 41.3 48 45.6 44.9 45.1 52 49.5 48.6 48.8 76 72.2 71.1 71.1 80 75.9 74.3 74.7 84 79.8 78.6 78.6

Alternate Mode EEC Takeoff Speed Adjustment

TAKEOFF SPEEDS DRY V1 WET V1 VR V2 TAKEOFF SPEED ADJUSTMENT (KTS) +1 +2 +1 0

Alternate Mode EEC Max Takeoff %N1

Based on engine bleeds for packs on, engine and wing anti-ice on or off

OAT °C 60 55 50 45 40 35 30 25 20 15 10 5 0 -5 -10 -15 -20 -25 -30 -35 -40 -45 -50 -55 °F 140 131 122 113 104 95 86 77 68 59 50 41 32 23 14 5 -4 -13 -22 -31 -40 -49 -58 -67 -2000 92.6 93.2 93.8 94.5 95.2 95.7 95.4 94.6 93.8 93.0 92.3 91.5 90.7 89.8 89.0 88.2 87.4 86.5 85.7 84.8 83.9 83.1 82.2 81.3 0 93.6 94.3 95.0 95.7 96.4 97.2 97.7 97.3 96.6 95.8 95.0 94.2 93.4 92.6 91.8 91.0 90.2 89.4 88.5 87.7 86.8 86.0 86.0 86.0 1000 93.7 94.4 95.1 95.8 96.5 97.3 98.0 97.9 97.1 96.4 95.6 94.8 94.1 93.3 92.5 91.7 90.8 90.0 89.2 88.3 87.5 86.6 85.7 84.9 2000 93.8 94.5 95.2 95.9 96.6 97.4 98.2 98.3 97.7 97.0 96.2 95.4 94.7 93.9 93.1 92.3 91.5 90.7 89.8 89.0 88.1 87.3 86.4 85.6 AIRPORT PRESSURE ALTITUDE (FT) 3000 4000 5000 93.9 94.0 94.1 94.6 94.7 94.9 95.4 95.5 95.6 96.1 96.2 96.3 96.7 96.8 97.0 97.5 97.6 97.7 98.1 98.3 98.2 98.3 98.5 98.5 98.0 98.3 98.5 97.3 97.6 97.9 96.5 96.8 97.2 95.8 96.1 96.4 95.0 95.3 95.7 94.2 94.5 94.9 93.4 93.7 94.1 92.6 93.0 93.4 91.8 92.2 92.6 91.0 91.4 91.8 90.2 90.6 91.0 89.4 89.7 90.2 88.5 88.9 89.3 87.7 88.1 88.5 86.8 87.2 87.7 86.0 86.4 86.8 AIRPORT PRESSURE ALTITUDE (FT) 3000 4000 5000 0.9 1.0 1.0 6000 94.0 94.7 95.5 96.2 96.8 97.6 98.2 98.5 98.6 98.3 97.5 96.8 96.0 95.3 94.5 93.7 93.0 92.2 91.4 90.6 89.7 88.9 88.1 87.2 7000 93.7 94.4 95.2 95.9 96.6 97.3 98.0 98.5 98.7 98.7 97.9 97.2 96.4 95.7 94.9 94.1 93.4 92.6 91.8 90.9 90.1 89.3 88.5 87.6 8000 93.6 94.1 94.9 95.6 96.3 97.0 97.8 98.3 98.6 98.8 98.3 97.6 96.8 96.1 95.3 94.5 93.7 93.0 92.2 91.3 90.5 89.7 88.8 88.0 9000 93.5 93.7 94.4 95.3 96.2 96.9 97.7 98.3 98.6 98.8 98.8 98.1 97.3 96.5 95.8 95.0 94.2 93.4 92.6 91.8 90.9 90.1 89.3 88.4

%N1 Adjustments for Engine Bleed

BLEED CONFIGURATION PACKS OFF -2000 0.7 0 0.8 1000 0.9 2000 0.9 6000 1.0 7000 1.0 8000 1.0 9000 1.0

Copyright © The Boeing Company. See title page for details.

November 1, 2006

D632A008-ZZ022

4.5.1

NON-STANDARD CONFIGURATION Alternate Mode EEC

Flight Planning and Performance Manual

737-800/CFM56-7B26 JAA/JAROPS Category C Brakes

Intentionally Blank

Copyright © The Boeing Company. See title page for details.

4.5.2

D632A008-ZZ022

November 1, 2006

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