(c)
Attach tags to identify the disconnected cable ends.
(d)
Disconnect the output control rod (7) of the autopilot actuator from the trim and feel mechanism (1).
(e)
Disconnect the output shaft (13) of the aileron trim actuator (16) from the trim and feel mechanism (1).
(f)
Disconnect the output control rod (12) of the CLCP-right autopilot from trim and feel mechanism (1).
(g)
Remove four bolts (14) from the trim and feel mechanism (1).
(h)
Remove the trim and feel mechanism (1) from the rigging beam of the wheel well.
(i)
Remove the cable ends (25 and 31) from the trim and feel mechanism quadrant (24).
TASK 27-11-06-402-035
5. Aileron Trim and Feel Mechanism Installation____________________________________________
A. Special Tools and Equipment
(1)
G12001-50 Rig Pin Kit
(2)
MIT65B04001-41 Control Wheel Straightedge
(3)
4MIT65B80307-1 Protractor (Recommended)
(4)
F52485-500 Protractor (Optional)
EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. ú
27-11-06
ALL ú ú 04 Page 212 ú Jun 18/01
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A
747-400
MAINTENANCE MANUAL
(5)
3MIT65B80307-1 Control Wheel Adapter
B.
Consumable Materials
(1)
C00528 Corrosion Preventive Compound - MIL-C-16173, grade 2
C.
Parts ~.............................................................................. | AMM | | AIPC | ................. ............................ | FIG | ITEM | NOMENCLATURE | SUBJECT | FIG | ITEM | ................................................................................ | 201 | 1 | Trim and Feel | 27-11-06 | 02 | 1J | | | 3 | Bolt | | | 30 | | | 4 | Washer | | | 35 | | | 5 | Nut | | | 40 | | | 8 | Bolt | 27-11-08 | 01 | 120 | | | 9 | Washer | | | 125 | | | 10 | Nut | | | 130 | | | 11 | Pin | | | 35 | | | 14 | Bolt | 27-11-06 | 02 | 160 | | | 15 | Washer | | | 155 | | | 27 | Bolt | 27-11-55 | 01 | 20 | | | 28 | Washer | | | 30 | | | 29 | Nut | | | 35 | | | 30 | Pin | | | 40 | 2......…........…...................................…...........….....…........1
D.
References
(1)
24-22-00/201, Manual Control
(2)
29-11-00/201, Main Hydraulic Supply System
(3)
32-00-30/201, Landing Gear Door Locks
(4)
SSM 27-11-01
(5)
WDM 27-11-11
E.
Access
(1)
Location Zone
135 Wing Landing Gear Well, LH
136 Wing Landing Gear Well, RH
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27-11-06
ALL ú
ú 04 Page 213
ú Feb 15/98
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A
747-400 MAINTENANCE MANUAL
F. Procedure
S 422-036
(1)
Install the aileron trim and feel mechanism (Fig. 201):
(a)
Install the trim and feel mechanism (1) on the rigging beam of the wheel well with four bolts (14) and washers (15).
(b)
Install the cable ends (25 and 31) on the trim and feel mechanism quadrant (24).
(c)
Install the cotter pins.
(d)
Lubricate with corrosion preventive compound the left body cable AA (31) and AB (25), the full length of travel along pulleys, grommets, fairleads and quadrants.
(e)
Connect the turnbuckles.
(f)
Tighten the cables to the specified tension range (Fig. 202).
(g)
Make sure you can easily install rig pin A/S-2.
(h)
Connect the output control rod (12) to the trim and feel mechanism (1) with the nut (29), bolt (27), and washer (28).
(i)
Install the cotter pin (6).
(j)
If it is necessary, adjust the force rod until you can easily install the bolt.
(k)
Connect the output control rod (7) to the trim and feel mechanism (1) with the bolt (8), washer (9), and nut (10).
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本文鏈接地址：747-400 AMM 飛機維護手冊 飛行操縱 FLIGHT CONTROLS 1(105)
