(2)
Place flap control lever in FLAP UP position to raise trailing edge flaps.
(3)
Remove systems A and B hydraulic power (Ref 27-61-0).
B. Remove electrical power if no longer required.
500
27-61-61 Page 406 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. Aug 01/75
FLIGHT SPOILER ACTUATOR QUADRANT - ADJUSTMENT/TEST
1. General
A. This test checks the operation of flight spoiler quadrants 2, 3, 6 and 7. However, only the quadrants actually changed require testing. When testing the spoilers on the right wing the full travel position of the applicable left wing spoiler must be determined. If any of the test checks in this section are not within limits, adjust the applicable flight spoiler (Ref 27-61-51 R/I).
2. Flight Spoiler Actuator Quadrant Test
A. Equipment and Materials
(1)
Control Surface Protractor - 4MIT65B80307-1 (preferred) F52485-500 (optional) (2 required)
(2)
Control Surface Protractor Stand Assembly - F71292-17 (optional)
(3)
Aileron Control Wheel Protractor Mount - F72790
(4)
Rigging Pins Kit - F70207-3, -52, -61, or -84:
Ref No. F70207-( ) Diameter (inches) Length (inches) Function
A/S-4 -11 0.309-0.311 6.7 +0.25 Aileron bus drum
B. Prepare for Test
(1)
Provide electrical power.
(2)
Provide systems A and B hydraulic power (Ref 27-61-0 MP).
(3)
Install protractor mount and protractor on captain's aileron control wheel.
(4)
Place speed brake control lever in DOWN position.
(5)
Set aileron in neutral. Aileron is in neutral when rigging pin A/S-4 can be freely inserted and removed. Remove rigging pin.
(6)
Install protractor stand and protractor on spoiler No. 6.
NOTE: Protractor may be hand-held on spoiler instead of using stand.
(7)
Set protractors to zero.
C. Test Spoiler Actuator Quadrant
(1)
Rotate captain's aileron control wheel clockwise and check that spoiler No. 6 begins to rise at 9 +1 degrees clockwise rotation from zero position.
(2)
Rotate captain's aileron control wheel 87 degrees clockwise and check that:
(a)
Spoiler No. 6 is 38 + 2 degrees up from zero position.
(b)
Spoiler No. 2 is full down.
(3)
From wheel position in previous step, return control wheel counterclockwise and check that spoiler No. 6 starts down when wheel is positioned at 70 degrees minimum clockwise from zero.
(4)
From wheel position in previous step, rotate control wheel counterclockwise and check that all spoilers are full down when the wheel is positioned at 4 ± 2 degrees clockwise from zero.
(5)
Rotate control wheel counterclockwise and check that spoiler No. 2 begins to rise at 9 + 1 degrees counterclockwise from zero position.
(6)
Continue rotating control wheel to 87 degrees counterclockwise and check that:
(a)
Spoiler No. 2 is 38 + 2 degrees up from zero position.
(b)
Spoiler No. 6 is full down.
(7)
From wheel position in previous step, return control wheel clockwise and check that spoiler No. 2 starts down when wheel is positioned at 70 degrees minimum counterclockwise from zero.
(8)
From wheel position in previous step, rotate control wheel clockwise and check that all spoilers are full down when the wheel is positioned at 4 + 2 degrees counterclockwise from zero.
500
Feb 01/95 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 27-61-61 Page 501
D. Restore Airplane to Normal
(1)
Remove systems A and B hydraulic power (Ref 27-61-0).
(2)
Remove protractor and protractor mount from captain's control wheel.
(3)
Remove protractor and protractor stand from spoiler.
(4)
Remove electrical power if no longer required.
500
27-61-61 Page 502 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. Feb 01/95
FLIGHT SPOILER ACTUATOR QUADRANT - APPROVED REPAIRS
1. General
A. Shear rivets provide a means by which normal operation of essential flight systems can be maintained in the event of failure or jamming of related or interconnect secondary systems (Ref 27-09-500).
2. Equipment and Materials
中国航空网 www.aero.cn
航空翻译 www.aviation.cn
本文链接地址：737 AMM 飞机维护手册 飞行操纵 FLIGHT CONTROLS 3(111)
