(2)
AMM 27-51-01/501, Inboard Flap

 (3)
AMM 27-51-01/601, Inboard Flap

 (4)
AMM 27-51-02/401, Inboard Foreflap

 (5)
AMM 27-51-44/401, Inboard Flap Track Fairing Support

 (6)
AMM 29-11-00/201, Main Hydraulic Supply System

 (7)
AMM 57-52-01/401, Flap to Fuselage, Seals

 (8)
AIPC 27-51-01, Fig. 1

 F.
Access

 (1)  
Location Zone
 577 Inboard Midflap, LH
 677 Inboard Flap Midflap, RH

 (2)  
Access Panel 577ET Midflap Inboard Trailing Edge Flap Carriage, LH 577BT Midflap Inboard Trailing Edge Flap Carriage, LH 677ET Midflap Inboard Trailing Edge Flap Carriage, RH 677BT Midflap Inboard Trailing Edge Flap Carriage, RH

 EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. ú

 27-51-01
 ALL  ú ú 01 Page 415 ú Feb 18/01
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A
747-400 MAINTENANCE MANUAL
 G. Prepare for Installation
 S 824-031
 (1)  
Make sure that the flap-to-fuselage seal material is tight. If the material is not tight, adjust it (AMM 57-52-01/401).

 S 224-032

 (2)  
If you will install used parts, or if used parts are suspected then you can do this inspection procedure (AMM 27-51-01/601).

 S 824-033

 (3)  
If a replacement flap or midflap will be installed, adjust the carriage shims:

 (a)  
Remove midflap access panels 577ET and 577BT (on the left side) or 677ET and 677BT (on the right side) above the aft end of each carriage spindle (Fig. 401).

 (b)  
Remove the bolts (23), washers (24 and 27), and nuts (28) which attach the support fitting (25). Remove the fitting.

 CAUTION: INSTALL SOFT SHIMS THAT HAVE LAMINATIONS AGAINST THE
_______ STRUCTURE WHEN MORE SHIMS ARE NECESSARY. FASTENERS WILL BECOME LOOSE IF SOFT SHIMS ARE INSTALLED AGAINST THE NUT.
 (c)  Install the shims (26) between the carriage bearing support fitting and midflap frame.
 NOTE: Use the new shims that are supplied with the
____ replacement midflap. Do not use the old shims from the removed midflap.
 Install the new shims at the same thickness as the old shims that were removed. If the shim thickness dimension cannot be found, or if the flap or midflap is new, do not install the shims (the nominal thickness is
 0.00 inch). If more shims must be installed, install the shims below the nut to keep a correct bolt grip length.
 (d)  
Apply a layer of BMS 5-95 sealant to the bolts.

 (e)  
Install the support fitting with bolts, washers, nuts, and shims.

 (f)  
Tighten the nut (28) to 300-500 inch-pounds (34-56 N-m).

 (g)  
Apply a layer of BMS 5-95 sealant to the heads of the bolts and the nuts.

 (h)  
Install the access panels.

 EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. ú

 27-51-01
 ALL  ú ú 01 Page 416 ú Feb 18/01
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A
747-400 MAINTENANCE MANUAL
 S 034-035
 (4)  
Install the fail-safe link, if it is not installed (Detail E, Fig. 401):

 (a)  
Remove the midflap access panels 577ET and 577BT (on the left side) or 677ET and 677BT (on the right side) above the aft end of each carriage spindle (Fig. 401).

 (b)  
Remove the nut (22) and washer (21) which attach the fail-safe pin (20) to the midflap frame.

 (c)  
Install the fail-safe link on the pin.

 (d)  
Install the pin in the frame.

 (e)  
Attach the pin (20) with a washer (21) and a nut (22). 1) At the outboard track locations, tighten the nut to 290-410 pound-inches (33-46 N-m).

 2)  At the inboard track locations, tighten the nut to 660-780 pound-inches (75-88 N-m).

 (f)  
Install the fail-safe link on the main carriage with the bolt (32) and washer (31) with the head of the bolt forward.
　
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 飛行操縱 FLIGHT CONTROLS 4(71)