(2)
G00009 Compound, Corrosion Inhibiting - BMS 3-23 Type II

 (3)
C00803 Primer - BMS 10-11, Type I

 C.  
References

 (1)
AMM 71-11-06/201, Core Cowl Panel

 (2)
AMM 71-11-07/401, Core Cowl Panel Latches

 (3)
AMM 78-31-00/201, Thrust Reverser System

 (4)
AMM 78-31-04/501, Fan Duct Tension Latches

 (5)
IPC 71-11-07 Fig. 1

 D.  
Access

 (1)  
Location Zone
 417 and 418 Core Cowl Panel - Engine 1
 427 and 428 Core Cowl Panel - Engine 2
 437 and 448 Core Cowl Panel - Engine 3
 447 and 448 Core Cowl Panel - Engine 4

 E.  
Procedure

 EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. ú

 71-11-07
 ALL  ú ú N01 Page 501 ú Jun 18/00
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
////////////////////////A / PW4000 SERIES /747-400 / ENGINES/MAINTENANCE MANUAL ////////////////////////
S 045-022-N00

 WARNING:_______ DO THE THRUST REVERSER DEACTIVATION PROCEDURE TO PREVENT THE
 OPERATION OF THE THRUST REVERSER.  THE ACCIDENTAL OPERATION OF
 THE THRUST REVERSER CAN CAUSE INJURIES TO PERSONS OR DAMAGE TO

 EQUIPMENT.
 (1)  
Do this procedure: Thrust Reverser Deactivation for Ground Maintenance (AMM 78-31-00/201).

 S 015-003-N00

 (2)  
Open the core cowl panels (AMM 71-11-06/201).

 S 215-025-N00
 CAUTION: MAKE SURE YOU CORRECTLY ADJUST THE LATCHES ON THE CORE COWL
_______ PANELS. THE LATCHES CAN RELEASE IF THEY ARE NOT CORRECTLY ADJUSTED. IF THE LATCHES RELEASE WHEN THE AIRPLANE IS IN THE AIR, DAMAGE TO THE CORE COWL PANEL OR THE ENGINE CAN OCCUR.
 (3)  
Make sure the keeper eyebolts do not turn and the retention pins are not broken off.

 S 425-005-N00

 (4)  
If the keeper eyebolt turns, immediately replace the broken or damaged keepers and latches (AMM 71-11-07/401).

 S 415-006-N00

 (5)  
Close and latch the thrust reverser (AMM 78-31-00/201).

 S 415-023-N00

 (6)  
Close and latch the core cowl panels (AMM 71-11-06/201).

 S 825-007-N00

 (7)  
Make sure the clearance between the core cowl panels is 0.125 inch

 (3.2 mm) at each latch location.
 (a)  If the clearance is not in the limits, adjust the clearance with the steps that follow: 1) Open all four latches for the core cowl panel. 2) Remove the shims (4 locations) from the middle two latch
 pads. 3) Remove the shims from the forward and aft keepers. 4) Apply the modeling clay [approx 0.25 inch (6.4 mm) thick]
 to all shim locations. 5) Apply the corrosion inhibiting compound to the shim mating surfaces.
 EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. ú

 71-11-07
 ALL  ú ú N01 Page 502 ú Jun 18/00
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
SEE D
SEE A
FWD 
SEE  C 
SEE  B 
A 

SHEAR PLATE SHEAR PLATESHIM AND SHIM SHIM AND SHIM
SHEAR SHEARPLATE PLATE
BOLT
BOLT
FORWARD MIDDLE LATCH LOCATION
AFT MIDDLE LATCH LOCATION B
C
Core Cowl Panel Latch Shim Installation Figure 501 (Sheet 1)
EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. ú

 71-11-07
 ALL  ú ú N01 Page 503 ú Oct 10/91
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
////////////////////////A / PW4000 SERIES /747-400 / ENGINES /MAINTENANCE MANUAL ////////////////////////
SEE  E 
D  FWD 
SEE  E 

SHIM
PLATEBOLT
E

Core Cowl Panel Latch Shim Installation
Figure 501 (Sheet 2)

EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. ú
　
中國航空網 m.k6050.com
航空翻譯 www.aviation.cn
本文鏈接地址：747-400 AMM 飛機維護手冊 動力裝置 POWER PLANT 2(82)