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时间:2011-04-16 10:09来源:蓝天飞行翻译 作者:航空
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D00250 Petrolatum White, VV-P-236

 D.  
References

 (1)  
AMM 24-22-00/201, Manual Control


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 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BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.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 

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 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BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.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.


___
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 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.
 
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