(2)
Rigging Pins Kit - F70207-3, -52, -61, or -84:
(3)
thru (8) deleted
(9)
Feeler gage set - capacity of at least 0.30 inch
(10)
Corrosion Preventive Compound - MIL-C-11796, Class 3
Ref No. F70207-( ) Diameter (inches) Length (inches) Function
A/S-1 -13 0.309-0.311 2.35 ±0.06 Transfer mechanism
A/S-1A -11 0.309-0.311 6.7 ±0.25 Transfer mechanism
A/S-3 -8 0.309-0.311 3.7 ±0.25 Spoiler control quadrant lower lever
A.S-4 -11 0.309-0.311 6.7 ±0.25 Aileron bus drum
A/S-8 -23 0.246-0.248 3.7 ±0.25 Spoiler actuator quadrant left wing
A/S-9 -23 0.246-0.248 3.7 ±0.25 Spoiler actuator quadrant (left wing)
A/S-10 -23 0.246-0.248 3.7 ±0.25 Spoiler actuator quadrant (right wing)
A/S-11 -23 0.246-0.248 3.7 ±0.25 Spoiler actuator quadrant (right wing)
A/S-14 -11 0.309-0.311 6.7 ±0.25 Spoiler mixer
S/B-2 -13 0.309-0.311 2.35 ±0.06 Speed brake input quadrant
27-61-0 Feb 20/88 Page 504
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.
(11)
Control Surface Protractor - 4MIT65B80307-1 (preferred), F52485-500 (optional) (2 required)
NOTE: One protractor with stand, (item (12), following) is for measuring angular position of spoiler panels. Protractor may be hand-held on spoiler instead of using stand. One protractor with mount (item (13), following) is for measuring angular position of control wheel.
(12)
Control Surface Protractor Stand Assembly - F71292-17 (optional)
(13)
Aileron Control Wheel Protractor Mount - F72790
(14)
Control Wheel Straightedge - SE27-0001
(15)
Sealant - BMS 5-95 (Ref 20-30-11)
C. Adjust Spoiler Control System
(1)
Remove system A and B hydraulic power (Ref 27-61-0 MP).
(2)
Adjust Right Aileron Control Cables (AA and AB).
(a)
Open nose compartment access door.
(b)
Insert aileron rigging pin No. A/S-1 and A/S-1A in transfer mechanism at base of first officer's control column (Fig. 502).
NOTE: Rigging pin A/S-1 must be fully put into transfer mechanism and held to keep it from falling out.
(c)
Check that rigging pin No. A/S-3 fits freely through rigging pin hole in lower lever at spoiler control quadrant (Fig. 503).
(d)
Check that tension in right aileron control cables AA and AB is within value required for ambient temperature. See temperature-tension chart in Fig. 501 for required cable tension. Check that tension in cables AA and AB is balanced.
(e)
If a new AA or AB cable is installed:
1) Tension cables to twice the value required for ambient temperature. See temperature-tension chart in Fig. 501.
NOTE: Turnbuckles are located in lower nose compartment.
500
Feb 01/95 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 27-61-0 Page 505
G29446G29226
Transfer Mechanism Rigging Pin Location 500
27-61-0 Figure 502 Aug 15/69
Page 506
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.
500 Spoiler Mixer and Ratio Changer Linkage
May 01/00 Figure 503 27-61-0
Page 507
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.
2) Remove rigging pins No. A/S-1, A/S-1A and A/S-3.
3) Cycle aileron control system 20 times to maximum travel limits.
(f) If checks in steps (c) and (d) are not met or if step (e) was accomplished, use turnbuckles to adjust cable tension as follows: 1) Install rigging pins A/S-1 and A/S-1A in transfer mechanism. (See figure 502.) 2) Adjust cables AA and AB so that rigging pin A/S-3 can be freely inserted in 中國航空網(wǎng) www.k6050.com 航空翻譯 www.aviation.cn 本文鏈接地址：737 AMM 飛機維護手冊 飛行操縱 FLIGHT CONTROLS 3(90)
