Read Microsoft Word - AEROED-747-400 System Course Criteria.doc text version

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Course Outline

1. INTRODUCTION TO B-747-400 SYSTEMS INTRODUCTION COURSE.

2.

AIRCRAFT DATA. A. Chapter 06 Aircraft Dimensions. Principal Dimensions Aircraft Section Numbers Forward Fuselage Diagram Aft Fuselage Diagram Fuselage Cross Section Drain Locations Wing Structure Horizontal Stabilizer Vertical Stabilizer Engine Nacelle & Strut

3.

CHAPTER 24 ELECTRICAL POWER A. Electrical Power Sources. Engine Generators (IDG) IDG oil servicing External/APU power Engine power DC power Standby power Load distribution B747-400 CMC/EICAS Course Criteria

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Indicating B. Electrical System Control Panel. Drive Disconnect Generator control Buss tie External power 1 & 2 APU generator 1 & 2 Battery Left & right utility Bus Standby power

AC Bus Power Distribution AC busses 1, 2, 3, 4 F/O transfer bus AC F/O XFR) Capt transfer bus (AC CAPT XFR) AC standby bus (AC STBY) Ground handling bus (AC GH) Ground service bus (AC GS)

DC Bus Power Distribution 1. DC 1, 2, 3, 4 2. DC ground handling (DC GH) 3. APU hot battery (APU HOT BAT) 4. Main hot battery (MN HOT BAT) 5. Main battery (MN BAT) 6. APU battery (APU BAT) E. Major Components. Cockpit Main Equipment Center. Access. B747-400 CMC/EICAS Course Criteria 01/19/05 2

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Power Centers. Left Right Split System Breaker (SSB). 4. CHAPTER 49 APU A. Purpose. Ground electrical power. Ground pneumatic power. Description. Controls Indications Location. Access. APU servicing oil & filters Starter motor brushes for wear

B.

C.

Operation. Specifications. Fire Procedures Start and Stop procedures Component locations Installation. 1. Views: 2. Front. 3. Side. 4. Top.

D.

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E.

Engine Gas Path and Accessories. 1. Compressor. 2. Pneumatic. 3. Cooling.

5.

CHAPTERS 71 ­ 80 ENGINE SYSTEMS. A. B. C. Engine Specifications. Engine Ground Clearance. Engine Cowling 1. Inlet cowl 2. Fan cowl 3. Core cowl 4. Fan duct cowl & thrust reverser Engine Stations & General Locations

D.

E.

Main Gearbox 1. Front view 2. Aft view Engine Vents & Drains Engine Fuel System 1. Engine fuel pump 2. Fuel metering unit 3. Fuel distribution components 4. Fuel supply line 5. Fuel flow transmitter 6. Fuel distribution valve & strainer B747-400 CMC/EICAS Course Criteria

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7. Fuel tubes and injectors Engine Controls & Indication Fuel control Electronic Engine Control (EEC) EEC speed transducer (N1) EEC Alternator (N2 speed transducer) EEC pressure sensors EEC Temperature sensors I. Engine Control System Summary System control System operation Command modes Interfaces Thrust management Thrust lever assembly Fuel condition motor Engine fire & emergency shutdown

J.

Engine Air System Accessory cooling Engine external accessories Engine bearings Turbine cooling Compressor control systems Compressor bleed control Compressor stator vane control HPC secondary flow control

Engine Ignition System Electrical power supply B747-400 CMC/EICAS Course Criteria 01/19/05 5

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Ignition exciters High tension distribution Ignitor plug cables Ignitors Engine ignition & start control panel Engine start system operation & interface Starter servicing Start valve Engine Indication System Engine pressure ratio (EPR) Engine tachometer (N1 & N2) Exhaust gas temperature (EGT) Airborne vibration monitoring (AVM) Central maintenance computer (CMC)

Engine Oil System Engine oil distribution Engine oil cooling Engine oil strainers Engine oil scavenge Engine oil indication Oil quantity transmitter Oil sight gauge Oil pressure transmitter Low oil pressure Oil filter differential EEC oil temperature No. 3 bearing oil temperature Magnetic chip detectors Engine Exhaust System B747-400 CMC/EICAS Course Criteria 01/19/05 6

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Engine exhaust system operation Stowed Deployed Engine exhaust indication Engine exhaust system control Thrust levers & interlock actuators Hydraulic actuators Locking Non locking Unlock & deploy & auto restow sensors Directional control valve Isolation valve Thrust reverser deactivation Manual deployment

6.

ATA CHAPTER 26 FIRE PROTECTION A. Fire Protection Systems Overview Engines APU Wheel wells Pneumatic system Cargo compartments Crew rest Engine Overheat & Fire Protection 1. Controls 2. Detection a. Detectors 3. Indication 4. Extinguishing a. Fire handle switch B747-400 CMC/EICAS Course Criteria

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b. Fire extinguisher bottle c. EICAS messages C APU Overheat & Fire Protection 1. Controls a. APU fire shutdown module 2. Detection a. Detectors 3. Indication 4. Extinguishing a. Fire handle switch b. Fire extinguisher bottle c. EICAS messages

D.

Cargo Smoke Detection & Fire Protection Smoke detection system Controls & indication Forward cargo Aft & bulk cargo Venturi ejector Detectors EICAS messages Fire extinguishing system Controls & indication Components Forward aft & bulk cargo extinguisher bottles Discharge manifold Pressure regulator Discharge nozzle Line pressure switrch Filter dryer EICAS messages B747-400 CMC/EICAS Course Criteria

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Wheel Well Fire Detection 1. System overview 2. Detectors 3. EICAS indication Pneumatic Wing Leading edge overheat System Overview Thermal switch detectors EICAS messages

Smoke Detection Lavatory & Crew Rest 1. Lavatory smoke detectors a. Operation b. Indication c. Fire protection 2. Crew rest smoke detectors a. Operation b. Indication c. EICAS messages 3. Portable fire extinguishers a. Halon b. Water

7.

ATA CHAPTER 36 PNEUMATICS.

A. System Uses Overview Air conditioning Pressurization Anti-ice Engine starting Leading edge flap drive B747-400 CMC/EICAS Course Criteria

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Air driven hydraulic pumps Water tank pressurization Hydraulic reservoir pressurization Cargo compartment heating Total air temp probe Cargo smoke detection

B.

Controls. Engine bleed APU bleed Wing isolation valves Fault indication lights Distribution. Ducts. Wings. Body. APU Cross over Starter Truck Connections. Pylon Valves ( PRSOV ). APU Bleed Load Control Valve. Isolation Valve. Check Valves Wing Isolation Valves. Operation. 1. Air system control and test unit (ASCTU) a. HPSOV controller b. PRV controller c. High pressure shutoff valve ( 15 th ) HPSOV B747-400 CMC/EICAS Course Criteria 10

C.

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d. e. f. g. E.

Pressure regulating valve (PRV) Low stage ( 8th ) Pressure relief. Pylon valve (PRSOV).

Bleed Air Temperature Control. 1. ASCTU control 2. Heat exchanger ( Pre-Cooler ) 3. Fan Air valve 4. Temperature sensor Pressure Control. 1. Pylon Valve (PRSOV) a. Four Functions. b. Shut off. i. Automatic. ii. Manual. c. Pressure Regulator. d. Temperature Regulator. e. Reverse Flow Shut off.

F.

Indications EICAS messages Synoptic display CMC maintenance display 8. ATA CHAPTER 21 AIRCONDITIONING A. System Overview Air conditioning packages Air distribution Temperature control Cargo compartment heating B747-400 CMC/EICAS Course Criteria 11

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Supplemental heating Humidifier

B.

System Controls Pack selector switches Equipment cooling switch Passenger temp selector switch Flight deck temp control switch Trim air valve switch Zone reset switch Upper & lower recirculation fan switch Aft cargo compartment heat switch Humidifier switch Pack reset switch

Air-Conditioning Package Pack control diagram Operation Back up operation Pack air flow Air cycle machine Turbine bypass valve Compressor bypass check valve Water collector Water separator Pack cooling Ram air inlet Ram air exit Door actuators Cooling air check valves Heat exchanger

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Pack Temperature Sensors Compressor discharge temp Compressor discharge overtemp Pack discharge temp Pack discharge overtemp Pack Temperature Control 1. Block Diagram a. Normal b. Backup c. High flow d. Over-temperature 2. System fault light a. Pack trip b. Out of sequence c. Cabin overpressure d. Cargo compartment fire 3. Cabin air flow a. sensor b. signal conditioner 4. EICAS indication a. Synoptic page b. Maintenance page c. EICAS messages

Air Distribution Distribution system Components Recirculation fans Air filters B747-400 CMC/EICAS Course Criteria 13

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Check valves Access EICAS displays Trim air Trim air PRSOV Trim air valves Indication Zone temperature sensors Location Sensor filters Duct temperature sensors Normal temperature sensor Over-temperature sensor Zone & duct temperature indication Flight Deck Humidifier Controls Components EICAS messages

Supplemental Heating Flight deck Windshield air valve Foot heaters Shoulder heaters Flight deck crew rest area Cabin Door area heaters Door 5 crew rest area heat Control Heater Fan B747-400 CMC/EICAS Course Criteria 14

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Air filter Check valve Temperature sensor Cargo Compartment Heating 1. Forward cargo heat components a. Distribution ducts b. Heater c. Temperature sensors d. EICAS messages 2. Aft cargo heat 3. System overview 4. Control a. Temperature selector b. Valves c. Heating ducts d. EICAS messages

Equipment Cooling 1. System overview a. Forward b. Aft 2. Aft equipment cooling a. Galley & lavatory b. Aft equipment center c. EICAS messages 3. Forward equipment cooling 4. Operation a. Normal b. Standby c. Override 5. Equipment cooling racks B747-400 CMC/EICAS Course Criteria 15

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a. Flow control 6. Fans & check Valves 7. Inboard valve 8. Skin temperature switch 9. Inboard exhaust valve 10. Ground exhaust valve 11. Overheat sensors 12. Smoke detectors 13. Smoke override valve 14. Air flow detectors 15. E6/E9 valve 16. EICAS messages

Pressurization System 1. System overview 2. Controls & indications a. Outflow valve position indication b. Landing altitude select switch c. Auto select switch d. Left & right manual switch e. Outflow valves open/close toggle switch 3. Controlers a. 2 Cabin pressure controllers b. 2 Interface control units 4. Outflow valves a. Position indication 5. Modes of operation a. Auto modes i. Ground ii. Takeoff iii. Cruise iv. Descent B747-400 CMC/EICAS Course Criteria 16

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v. Landing b. Manual mode 6. Cabin pressure relief system 7. Operation a. Valve installation b. Valve doors c. Indication 8. Negative pressure relief doors 9. Operation a. Indication 10. Altitude warning& indication 11. EICAS indication

K.

Pressurization System (contd) 12. Synoptic 13. ECS block 14. Maintenance page

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ATA CHAPTER 29 HYDRAULIC POWER A. System Overview 1. Four main systems 2. Auxiliary system 3. Systems interface with a. Landing Gear. b. Flight Controls. Controls & Indication 1. Engine driven pump switch 2. Rotary demand pump switches 3. Pressure indication (lights) 4. System fault lights B747-400 CMC/EICAS Course Criteria 17

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5. Hydraulic interface module (HYDIM) 6. Hydraulic quantity interface module (HYQUIM) C. Main Hydraulic System 1. Four independent systems. 2. Two pumps per system. a. Engine driven pump (EDP) b. Demand pump (ADP) 3. Brake system electric pump 4. Central servicing location. a. Pressure fill b. Hand Pump (suction)

C.

Main Hydraulic System Ccontd) c. Reservoir quantities 5. Return Filter Module. 6. Reservoir Installation. 7. Supply Shutoff Valve (firewall). 8. Pumps. a. Engine Driven EDP. b. Air Driven ADP. c. Electric A C Motor Driven AC Pump. 9. System Pressure Module. 10. Case Drain Module. 11. Hydraulic Oil Cooling a. Heat Exchangers 12. EICAS indication a. EICAS messages b. EICAS synoptic display c. EICAS maintenance page ATA CHAPTER 32 LANDING GEAR B747-400 CMC/EICAS Course Criteria 18

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A.

Landing Gear System Main gear Main gear doors Nose gear Nose gear doors Wheels & brakes Steering Landing gear indication system Landing gear extension & retraction

B.

Main Gear Body Truck positioning actuator Seals & servicing Ground locks Wing Truck positioning actuator Mechanical truck tilt lock Seals & servicing Ground locks Nose Seals & servicing Ground locks Steering bypass pin Main Gear Doors 1. Body a. Operation b. Manual release 2. Wing a. Operation B747-400 CMC/EICAS Course Criteria 19

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b. Manual release 3. Nose a. Operation b. Manual release D. Landing Gear Control 1. Normal operation 2. Landing gear lever a. Wing gear selector valve b. Body & nose gear selector valves

D.

Landing Gear Control (contd) 3. Up & down lock operated sequence a. Body b. Wing c. Nose 4. Alternate landing gear extension a. Body b. Wing c. Nose Landing Gear Indication 1. Main EICAS display a. Normal b. Expanded 2. Gear synoptic display 3. EICAS messages Landing Gear Brakes System overview Tires & wheels Brakes B747-400 CMC/EICAS Course Criteria 20

E.

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Antiskid system Auto brake system Torque limiting system Main gear Tires Wheel & wheel bearings Axle Nose gear Tires Wheel & wheel bearings Wheel snubber

G.

Tire pressure indication Body Wheel interface unit Transducer Wing Wheel interface unit Transducer Nose Wheel interface unit Transducer Tire pressure indication Tire pressure monitoring unit Synoptic display EICAS maintenance display Hydraulic Brakes 1. System overview a. Normal/Alternate brake system b. Parking brake system c. Brake temperature system B747-400 CMC/EICAS Course Criteria 21

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d. Antiskid system e. Auto-brake system f. Torque limiting system 2. System diagram 3. Operation a. Normal b. Alternate c. Hydraulic source selector valve d. Accumulator isolation valve e. De-spin brake f. Pressure switches

H.

Hydraulic Brakes (contd) 4. Brake source indication 5. Parking brake a. Bus rod mechanism b. Indication switch c. Cable d. Park brake module e. Brake 6. Brake unit 7. Brake system accumulators a. Normal brake accumulator b. Wing & body anti-skid accumulators c. Servicing d. Brake pressure transducers Brake Temperature Monitoring 1. Temperature sensors 2. Brake temp monitoring unit 3. EICAS display

I.

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Antiskid System 1. Normal wheel control 2. Alternate wheel control 3. Locked wheel protection 4. Hydroplane/Touchdown protection 5. Antiskid valves 6. Wheel speed transducers 7. Brake system control unit (BSCU) 8. Brake deactivation procedure

K.

Auto Brake System Auto brake selector module Brake pedal position switch BSCU Auto brake pressure control module Auto brake shuttle valves Fault annunciation EICAS indication Brake Torque Limiting System 1. Brake torque sensors 2. Torque limiter card 3. Indication 4. EICAS Messages 5. EICAS maintenance page Steering System Nose gear Operation Directional control Control inputs Body gear steering arm switch B747-400 CMC/EICAS Course Criteria 23

L.

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Tiller & cable rum Rudder pedals Metering valve Body gear

M. Steering System (contd) Operation Body gear steering electronics control unit Body gear steering control modules Steering actuators and lock switches Steering quadrant and arming switch Command transducer Steering Indications EICAS messages 11. ATA CHAPTER 27 FLIGHT CONTROLS A. System Overview 1. Primary 2. Secondary Hydraulic Power Distribution 1. System # 1 2. System # 2 3. System # 3 4. System # 4

B.

Flight Control Hydraulic Power Isolation Wings System # 1 System # 2 System # 3 B747-400 CMC/EICAS Course Criteria 24

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system # 4

D.

Flight Control Hydraulic Power Isolation (contd) Empenage. System # 1 System # 2 System # 3 System # 4 Flight Control Electronic System Flight control electronic power supply (FCE) Flap control units (FCU) Stabilizer trim rudder ratio changer modules (SRM) Yaw damper modules (YDM) FCE air data computer inputs Auto-flight inputs Speed stability trim Yaw damper Lateral Control System Overview Component location Flight deck Main equipment center Wing gear wheel well Wings Control. Mechanical Trim, center and feel Lost motion quadrant Central lateral control package (CLCP) Input bus rod & load limiter B747-400 CMC/EICAS Course Criteria 25

D.

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E.

Lateral Control (contd) Aileron programmer (s); left and right Backdrive rod (Rt. programmer) to lost motion quadrant Input bus rod and load limiter (between programmers) Cable input to four aileron power control units (PCU) Outboard aileron lockout Position indication (EICAS) Flight spoilers Position indication (EICAS) Spoiler mixers CLCP inputs Cable inputs to spoiler power actuators Ground spoiler control valve Speed brake sequencer Trailing Edge Flaps 1. Component location a. Flight deck b. Main equipment center c. Wing gear wheel well 2. Controls a. Primary mode b. Alternate mode 3. Flap control units (FCU) 4. Flap control lever 5. Trailing edge flap drive system a. Operation i. Up ii. Down

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F.

Trailing Edge Flaps (contd) 6. Flap load relief 7. Flap indication a. Position transmitters b. Main EICAS indication i. Normal display ii. Expanded display c. Maintenance page display Leading Edge Flaps Component location Flight deck Main equipment center Wing gear wheel well Controls Primary mode Alternate mode Flap control units (FCU) Primary control pneumatic Primary control electric Priority Tests Flap control lever Kruger flaps Offset gearbox Rotary actuator Variable camber flaps Linkage Rotary actuator

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G.

Leading Edge Flaps (contd) Position indication Normal display Expanded display Maintenance page display Horizontal Stabilizer System 1. System overview a. Horizontal stabilizer trim control b. Stabilizer trim indication 2. Control a. Manual trim switches b. Alternate trim switches 3. Interface a. Flight control computers (FCC) b. Digital air data computers (DADC) c. Stabilizer trim/rudder ratio module (SRM) d. Stabilizer trim control module (STCM) 4. Stabilizer hydraulic control a. Hydraulic system # 2 b. Hydraulic system # 3 5. SRM module a. Auto-trim actuation b. Trim rate control c. Auto shutdown d. Trim limit change e. Stabilizer rate control f. Fault annunciation

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H.

Horizontal Stabilizer System (contd) 6. Stabilizer trim switches a. Column cut-out switches b. Trim limit switches 7. Speed stability trim a. Half rate auto-trim b. Full rate auto-trim c. Fault annunciation 8. Horizontal stabilizer indication system a. Interfaces i. FCU ii. MAWEA iii. FCC iv. SRM b. Greenband indicator c. Nose gear pressure switch 9. EICAS indication Elevator System System overview Elevator control system Stall warning Elevator position indication Control system Control columns Elevator feel computer FCCs Elevator feel unit Auto-pilot actuators

I.

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I.

Elevator System (contd) Elevator hydraulic power Hydraulic system #1 Hydraulic system #2 Hydraulic system #3 Hydraulic system #4 Stall warning Elevator position indication Position transmitters EICAS display EICAS messages Maintenance page display Rudder System 1. System Overview a. Rudder trim control system b. Hydraulic supply shutoff valves c. Rudder position indication 2. Control system a. Rudder pedals b. Trim centering & feel mechanism c. Roll-out power control package (PCP) d. Rudder ratio changers e. Yaw damper servos (SRM) f. Power control modules (PCM) 3. Hydraulic power distribution & shutoff a. Hydraulic system #1 b. Hydraulic system #2 c. Hydraulic system #3 d. Hydraulic system #4

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J.

Rudder System (contd) 4. Rudder trim control 5. Upper & lower power control modules 6. Rudder position indications system a. Position transmitters 7. Indication a. EICAS displays b. EICAS messages c. EICAS maintenance page

12.

ATA CAHPTER 30 ICE & RAIN PROTECTION A. System Overview Protection provided for Wings leading edge Engine nacelles Flight deck windows Pitot static probes Total air temp probes Angle of attack sensor Water lines & drains Controls Wing anti-ice switch Nacelle anti-ice switch Window heat switches Windshield wiper switch Windshield washer switches

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B.

Wing Anti-Ice System Control Valves Indications Tests EICAS messages Nacelle Anti-Ice System Control Valves Overheat & pressure switches Indications Tests EICAS messages Pitot Static Probes 1. Operation 2. Indication 3. Tests 4. EICAS messages Total Air Temperature Probes Operation Indication Tests EICAS messages

C.

D.

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F.

Angle Of Attack Sensors 1. Operation 2. Indication 3. Tests 4. EICAS messages Window Heat 1. Controls 2. Operation 3. Indication 4. Tests 5. EICAS messages Windshield Wipers 1. Control a. Wiper motor/converter 2. Windshield parking mechanism Water & Drain Line Heaters 1. Electrically heated tape 2. Temperature controller Drain Masts Ground operation Air operation

G.

H.

I.

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13.

ATA CHAPTER 28 FUEL A. System Overview Fuel storage tanks System controls Fuel quantity indication Fueling Engine feed APU feed Reserve & main tank transfer Horizontal stabilizer fuel transfer Scavenge Jettison Fuel Storage Tanks 1. Main tanks 2. Reserve tanks 3. Horizontal stabilizer tank (HST) 4. Access to all tanks 5. Fuel sump drain valves (all tanks) 6. Fuel tank venting a. Float valves b. Fuel vent drain valves 7. Vent & surge tank (wings & HST) a. Flame arrester b. Drain check valves c. Pressure relief valves (negative & positive)

B.

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C.

Fuel System Control Fuel management panel Fuel jettison panel Refuel control panel Fuel transfer switch De-fuel panel EICAS displays Fuel Indication System 1. Fuel quantity indication processor (FQIS) 2. Fuel system card file 3. Remote electronics unit (REU) 4. Tank sensors 5. Fuel measuring sticks 6. EICAS displays a. Synoptic b. Maintenance pages Fueling Control panel Operation Indication Refueling station Refuel valves De-fuel valves Wing tanks Main Reserve

D.

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E.

Fueling (contd) Center tank & HST Isolation valves Fueling valves Tank fuel valves & controllers Over-wing fill ports Engine Fuel Feed System 1. System Overview a. Pumps b. Manifolds c. Fuel flow control 2. Main tank boost pumps 3. Water scavenge ejector pump 4. Cross-flow compensator 5. Cross-feed valves 6. engine fuel shutoff valve APU Fuel Feed System 1. Control 2. Boost pumps a. AC pump b. DC pump 3. Control pressure switch 4. Fuel lines Reserve & Main Tank Transfer 1. Control 2. Tank interconnection valves a. Reserve tanks b. Main tanks B747-400 CMC/EICAS Course Criteria 36

F.

G.

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I.

HST Fuel Transfer System 1. Control a. Transfer pumps b. Isolation valves c. Transfer fuel line d. Center wing tank isolation valves e. Center wing tank secondary refuel valves f. Refuel override valves (center wing tank) 2. Indication Fuel Jettison System Control Jettison nozzle valves Override/Jettison pumps Jettison transfer valves Main tanks Reserve tanks HST tank Fueling & jettison manifold EICAS indication EICAS messages EICAS maintenance page De-Fueling System 1. Control a. De-fuel valve 2. Reserve tanks 3. Main tanks 4. Center wing tank 5. HST 6. Indication B747-400 CMC/EICAS Course Criteria 37

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14.

ATA CHAPTER 52 DOORS A. Main Cabin Doors Location No. 1 through 5 Lh No. 1 through 5 Rh Indication Synoptic display EICAS messages Control Handles (inner and outer) Mode selector lever Safety practices Assume door is armed Work or access stand in place Open using interior controls Mode selector "Manual" Rotate handle full travel; door is in 30 deg "Cocked Position" Verify: Sear pin fully retracted Trigger in contact with hinge arm Girt bar cleared from floor fittings Push door open Open using exterior handle Pull out ("butterfly") handle Feel slight resistance; indicates "manual mode" Rotate 45 deg. Lower and upper gates fold inward Door moves to 30 deg "cocked position" Push door open

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A.

Main Cabin Doors (contd) Maintenance repair practices Safety pin bottle Before Leaving; arming lever in Manual Mode Door number 3 drags on floor Heavier escape slide Fuselage flexes when heavily loaded Close door before loading for flight Flight Deck Door 1. Control a. Operation b. Door latch assembly

B.

Emergency Exit doors 1. Flight deck overhead door a. Operation 2. Upper deck cabin door a. Open using interior control i. Mode selection ii. Internal arm/disarm lever b. Latch system c. Lift mechanism d. Lift system 3. Open using exterior control a. External arm/disarm lever b. External control switch 4. Fight lock actuator 5. Escape slide pack 6. EICAS messages 7. EICAS synoptic display B747-400 CMC/EICAS Course Criteria 39

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Cargo Doors Location right side Forward Aft Indication Synoptic display Pilot's glare shield Fault lights external control panels Latch cam witness marks Modes of operation Electrical Ground handling buss No. 1 external power No. 1 APU generator Manual Normal operation; (electrical) Master latch lock mechanism Switch on external control panel Interior switch on forward door frame Manual operation. (a brief discussion on operation in manual) Closing Hold switch to close Green light "ON" Master latch lock handle flush with skin. Vent doors closed Green Light "OFF" All door edges flush with skin Verify witness marks Bulk Cargo Door 1. Opening & closing a. Hold open latch B747-400 CMC/EICAS Course Criteria 40

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15.

ATA CHAPTER 35 OXYGEN SYSTEMS A. Systems Overview Diluter demand system (flight crew) Continuous flow (passenger) Portable bottles (walk around) Diluter Demand System 1. Crew oxygen cylinders a. Pressure reducer b. Pressure transducer c. Thermal compensator 2. Overboard discharge port indicator 3. Pressure regulator a. Operation 4. Mask regulator assembly a. Operation 5. Pressure indication a. EICAS display b. EICAS messages

B.

Continuous Flow Passenger Oxygen 1. Passenger oxygen cylinders a. Flow control units 2. Distribution manifolds 3. Oxygen voltage averaging unit 4. Passenger oxygen control switch a. Operation 5. Pressure indication a. EICAS display b. EICAS messages B747-400 CMC/EICAS Course Criteria 41

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Portable Oxygen System Bottles Locations (General) 16. ATA CHAPTER 38 WATER & WASTE A. Potable Water 1. System provides water for: a. Galleys b. Lavatories c. Humidifier 2. Water tanks a. Servicing b. Fill & overflow valve c. Drain Valves 3. Water tank pressurization a. Air compressor b. Air compressor interlock switch 4. Water quantity indication a. Water quantity transmitter & probe b. Indicators Lavatory Water System System schematic Water supply Water heater Wash basin Water filter

B.

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B.

Lavatory Water System (contd) Drain Masts Foreward Mid Aft Summary Toilet Waste System 1. System Schematic 2. Toilet Assembly a. Toilet shroud & flush switch b. Flush control unit c. Rinse water/anti-siphon valve d. Flush valve 3. Toilet flush control circuit a. Normal cycle b. jam cycle 4. Waste tanks a. Tank drain lines b. Liquid separator c. Vacuum blower d. Altitude pressure switch 5. Waste tank level sensing a. Quantity indication b. Lights c. Sensor fouled indication 6. Drain line heating blanket 7. Waste water service panel a. Servicing b. Rinse fitting & filter c. Pre-charge valve B747-400 CMC/EICAS Course Criteria 43

C.

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