27-51-46
 ALL  ú ú 01 Page 411 ú Jun 18/01
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A
747-400 MAINTENANCE MANUAL
 ~.............................................................................. | AMM | | AIPC | ................. ............................ | FIG | ITEM | NOMENCLATURE | SUBJECT | FIG | ITEM | ................................................................................ | | 16 | Bolt | | | | | | 17 | Plate Assembly | | | | | | 18 | Lock Cap | | | | | | 19 | Shim | | | | | | 20 | Filler | | | | | | 21 | Fitting Assy (Track No. 4 and 5) | 27-51-01 | 10 | 230 | | | | Fitting Assy (Track No. 3 and 6) | 27-51-01 | 10 | 235 | | | 22 | Nut | | | | | | 23 | Washer | | | | | | 24 | Bolt | 27-51-04 | 10 | | 2......…........…...................................…..........….....….........1
 D. References
 (1)
AMM 12-21-20/301, Trailing Edge Flap System

 (2)
AMM 27-51-41/601, Ball Screw

 (3)
OHM 57-52-35, Inboard Trailing Edge Midflap Assembly

 (4)
OHM 57-52-55, Outboard Trailing Edge Midflap Assembly

 (5)
SB 747-57A2310, Actuator Attach Fitting Inspection and Replacement

 E.
Access

 (1)  
Location Zones 567 Outboard Flap Track Fairing, Outboard Flap, LH, (Track No. 1) 565 Inboard Flap Track Fairing, Outboard Flap, LH, (Track No. 2) 563 Outboard Flap Track Fairing, Inboard Flap, LH, (Track No. 3) 561 Inboard Flap Track Fairing, Inboard Flap, LH, (Track No. 4) 661 Inboard Flap Track Fairing, Inboard Flap, RH, (Track No. 5) 663 Outboard Flap Track Fairing, Inboard Flap, RH, (Track No. 6) 665 Inboard Flap Track Fairing, Outboard Flap, RH, (Track No. 7)

 667  Outboard Flap Track Fairing, Outboard Flap, RH, (Track No. 8)
 F. Prepare for the Installation
 S 224-015
 (1) Do this task: "Ball Screw Inspection" (AMM 27-51-41/601).
 EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. ú

 27-51-46
 ALL  ú ú 01 Page 412 ú Jun 18/01
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A
747-400
MAINTENANCE MANUAL

 S 624-016
 (2)  
Apply a layer of corrosion preventive compound on the ball screw and the universal joint.

 S 494-017

 (3)  
Install the ball and screw support tool.

 S 284-032

 (4)  
Do this Task: Actuator Attach Fitting, "Part 1 - Inspection" (SB 747-57A2310).

 G.  
Install the Actuator Attach Fitting

 S 424-018
 (1)  
Install the actuator attach fitting (Fig. 402):

 (a)  
ON THE OUTBOARD FLAPS; install the fitting assembly (15) into the housing assembly (14) (Fig. 402, View C): 1) Install the fitting assembly (15) into the housing

 assembly (14) with laminated shims (13), bearing (12) and nut (11). Use a restraining tool and torque the nut to 480 - 600 pound-inches (54 - 68 N-m).
 NOTE: You may need to back the nut off within the torque
____ range to install the cotter pin.
 2)  Check that the gap between the upper surface of the bushing on the top of the fitting assembly and the bearing (12) is
 0.010 to 0.005 inch (0.254 - 0.127 mm).
 3)  Adjust the gap as necessary by adding or removing shims (13).
 NOTE: This is an itterative process to get the correct
____
 gap.

 4) Install the cotter pin (10). 5) Lubricate the attach fitting assembly at the zerk fitting with BMS 3-33 grease. Wipe off excess grease. 6) Install the cover (9) with the bolts (24).
 (b)  ON THE INBOARD FLAPS; install the fitting assembly (21) into the support fitting (Fig. 402, View D): 1) Install the gimbal assembly (21) into the fitting assembly
 with filler (20), shims (19), lock cap (18), plate assembly (17), nuts (22), washers (23) and bolts (16). Torque the nuts (22), 90 - 125 pound-inches (10 - 14 N-m).
 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 飛行操縱 FLIGHT CONTROLS 6(9)