D.
References
(1)
AMM 24-22-00/201, Manual Control
EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. ú
73-34-00
ALL ú ú N01 Page 501 ú Feb 10/97
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
////////////////////////A / PW4000 SERIES /747-400 / ENGINES /MAINTENANCE MANUAL ////////////////////////
MAIN FUEL
FUEL FLOW
SUPPLY HOSE
TRANSMITTER
(REF)
(REF)
SEEA
HOUSING FUEL FILTER SEE B
(REF) MAIN GEARBOX A
BRACKET
SEE C ADAPTER PACKING DS1585 CONNECTOR ELECTRICAL BOLT (2 LOCATIONS) BOLT (2 LOCATIONS) PORT "HI" PRESSURE
(2 LOCATIONS) WASHER
HOUSING FILTER FUEL DOWEL PIN B S1585 PRESSURE SWITCH DIFFERENTIAL FUEL FILTER ADAPTER C PORT "LO" PRESSURE
Figure 501 Pressure Adapter Installation
EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. ú
73-34-00
ALL ú ú N02 Page 502 ú Jun 10/90
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
(2)
AMM 31-61-00/501 Integrated Display System
(3)
AMM 45-10-00/201, Central Maintenance Computer System
(4)
AMM 71-11-04/201, Fan Cowl Panels
(5)
AMM 71-11-06/201, Core Cowl Panels
(6)
AMM 73-34-01/401, Fuel Filter Differential Pressure Switch
(7)
AMM 78-31-00/201, Thrust Reverser System
(8)
IPC 73-11-02 Fig. 5, 73-34-01 Fig. 5
(9)
WDM 73-34-12
(10)
SSM 73-34-02
E.
Access
(1)
Location Zone
412 Engine 1 - Main Gearbox Fwd Face 5 o'clock
422 Engine 2 - Main Gearbox Fwd Face 5 o'clock
432 Engine 3 - Main Gearbox Fwd Face 5 o'clock
442 Engine 4 - Main Gearbox Fwd Face 5 o'clock
(2)
Access Panel
416 Right Thrust Reverser Half - Engine 1
426 Right Thrust Reverser Half - Engine 2
436 Right Thrust Reverser Half - Engine 3
446 Right Thrust Reverser Half - Engine 4
F.
Preconditions
S 865-031-N00
(1)
These conditions are necessary for this task:
(a)
Electrical Power on (AMM 24-22-00/201).
(b)
Integrated Display System (IDS) serviceable (AMM 31-61-00/501).
(c)
Central Maintenance Computer (CMC) serviceable (AMM 45-10-00/501).
G.
Prepare for the System Test
S 865-002-N00
(1)
Supply electrical power (AMM 24-22-00/201).
S 865-003-N00
(2)
Make sure the applicable FUEL CONTROL switch is in the CUTOFF position.
S 865-004-N00
(3)
Push the STAT button on the EICAS display select panel.
(a)
Make sure the status page shows on the auxiliary EICAS.
(b)
Make sure the applicable FUEL SPAR VLV ENG 1, 2, 3, or 4 status message is not on.
___
EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. ú
73-34-00
ALL ú ú N02 Page 503 ú Feb 10/97
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
////////////////////////A / PW4000 SERIES /747-400 / ENGINES/MAINTENANCE MANUAL ////////////////////////
S 865-005-N00
WARNING: FAILURE TO OPEN APPLICABLE ENGINE IGNITION CIRCUIT BREAKERS
_______ PRIOR TO POSITIONING FUEL CONTROL SWITCH TO "RUN" WILL RESULT IN AUTOMATIC FIRING OF IGNITER PLUGS IF/WHEN FLAPS ARE OUT OF ZERO DETENT, NACELLE ANTI-ICE IS ON, CON IGNITION SWITCH IS SET TO "ON", OR ENGINE START SWITCH IS PULLED TO "ON". WITH UNBURNED FUEL IN COMBUSTION CHAMBER, INTERNAL ENGINE OR TAILPIPE FIRE MAY RESULT CAUSING INJURY TO PERSONNEL OR ENGINE DAMAGE.
中國航空網(wǎng) www.k6050.com
航空翻譯 www.aviation.cn
本文鏈接地址：747-400 AMM 飛機維護(hù)手冊 發(fā)動機燃油和控制 2(96)
