(e)  
Aileron Bus Cables ABSA and ABSB

1)  With rigging pin A/S-4 installed, the left and right ailerons shall be in neutral position as defined in Fig. 506. If discrepancies exist, adjust the cables in both wings as described in par. C.(6).
(5)  Following replacement or reinstallation of an aileron, aileron tab, or aileron tab control rod it is necessary to perform a flight test to determine and correct asymmetrical flight control forces as described in par. 3.
B.  Equipment and Materials
(1)  
Cable Tensiometer - 0 to 200 pound range

(2)  
Protractor - Aileron Tab Alignment - F80222-1 which consists of a -2 protractor assembly (Ref 27-09-700 MP).

500 
27-11-0 Page 508  BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.  May 01/99 

(4) Rigging Pins Kit - F70207-84, or -98:
REF NO.  F70207-( )  DIAMETER (INCHES)  LENGTH (INCHES)  FUNCTION 
A/S-1 A/S-1AA/S-3 A/S-4 A/S-13 -13  -19 -8 -11  -8  0.309-0.311 0.309-0.311 0.309-0.311 0.309-0.311 0.309-0.311  2.35 士0.06 8.25 士0.25 3.7 士0.25 6.7 士0.25 3.7 士0.25  AILERON TRANSFER MECHANISM AILERON TRANSFER MECHANISM SPOILER CONTROL QUADRANT LOWER LEVER AILERON BUS DRUM AILERON TRIM GEARBOX 

C.  Adjust Aileron and Aileron Trim Control System
NOTE:  If trim is adjusted with both aileron power control units depressurized, the drag of the unpowered aileron system will allow the system to remain out of center. This will force the trim and centering mechanism cam follower out of the cam detent. Then, when hydraulic power is applied, the control wheels and ailerons will rapidly move to the newly trimmed position.
(1)  Adjust aileron trim cables ATA and ATB.
(a)  
Set aileron trim control knob in zero trim position (Fig. 502).

(b)  
Check that rigging pin A/S-13 can be inserted without binding through both walls of aileron trim mechanism gearbox. If rigging pin cannot be inserted freely, accomplish the following steps: 1) Disconnect coupler from trim shaft by removing nuts, washers and bolts. 2) Rotate trim shaft to permit insertion of rigging pin A/S-13. 3) Reconnect trim shaft and coupler. 4) Remove rigging pin A/S-13.

(c)  
Check that cable tension on cables ATA and ATB is within limits (Fig. 501).

(d)  
If cable tension is not within limits, adjust cables ATA and ATB as follows:

1)  Ensure trim knob indicator is in zero trim position. Tape trim knob to the cockpit control stand (Fig. 502).
Aug 01/96 27-11-0 Page 509
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.

2) Insert rigging pin A/S-13.
3) Adjust cables to tension specified (Fig. 501).
4) Remove tape from trim knob.
5) Remove rigging pn A/S-13.
6) Rotate aileron trim knob through maximum travel for several cycles.
7) Check that cable tension is within range specified (Fig. 501) and tension in

cables ATA and ATB is balanced. 8) Install rigging pin A/S-13 and check that trim knob indicator is in zero trim position. 9) Install turnbuckle locking clips.
(2)  Adjust aileron control bus cables ACBA and ACBB.
(a)  
Open lower nose compartment access door 1103.

(b)  
Position captain's and first officer's aileron control wheels in neutral by placing a straightedge across upper ends of each control wheel (Fig. 501). One end of first officer's control wheel may be out of contact with the straightedge by a maximum of 0.20 inch.

(c)  
Check that cable tension in ACBA and ACBB cables is within limits specified  (Fig. 501) as follows: 1) Remove bolts securing aileron bus control cable shield clamps to support

brackets and remove shields (Fig. 503).
2) Check cable tension with cable tensiometer.
3) Reinstall cable shields and clamps.

(d)  
If conditions of steps (b) or (c) cannot be obtained, proceed as follows:

1)  If installed, remove bolts securing aileron bus control cable shield clamps to support brackets and remove shields.
506 
27-11-0 Page 510  BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.  Aug 15/69 

2) Insert rigging pin A/S-1A in base of first officer's aileron control wheel.
NOTE:  Rigging pin A/S-1 must be fully put into transfer mechanism and held to keep it from falling out.
3)  Adjust cables ACBA and ACBB to meet conditions in step (d), and tension
specified (Fig. 501). 4) Remove rigging pin A/S-1A. Pin should withdraw freely. 5) Center control wheels and check that control wheels upper ends contact
straightedge. One end of first officer's control wheel may be out of contact with
　
中國航空網 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 1(58)