(g)
Tighten checknut on input lever adjusting screw within 30 to 40 pound-inch torque range and install lockwire.
(8)
Set control surface protractor to zero by:
(a)
Turn captain's control wheel counterclockwise from neutral to ensure that flight spoilers No. 6 and 7 are fully retracted.
(b)
Position protractor and protractor stand on flight spoiler, and set protractor to zero.
500
Feb 20/84 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 27-61-51 Page 407
NOTE: Protractor may be hand-held on spoiler instead of using stand.
(9)
Rotate captain's control wheel clockwise 50 + 5 degrees and return toward neutral.
(10)
Check that flight spoilers No. 6 and 7 are fully retracted when the captain's control wheel is 4 + 2 degrees clockwise from neutral. Check that spoiler-to-flap clearance remains at 0.03
+ 0.10/-0.00 inch.
(11)
If check in step (10) is not within limits:
(a)
Lower trailing edge flaps by placing flap control lever in FLAP DOWN detent.
(b)
Hold captain's control wheel at 9 + 1 degrees clockwise from neutral.
(c)
Break lockwire on input lever adjusting screw and loosen checknut.
(d)
Using adjusting screw set No. 6 and 7 actuators so that spoiler panels begin to rise from zero (fully retracted) position.
(e)
Raise trailing edge flaps by placing flap control lever in FLAP UP detent.
(f)
Release captain's control wheel and perform steps (9) and (10). Spoilers must operate within these limits.
(g)
Tighten checknut on input lever adjusting screw to 30-40 pound-inches and install lockwire.
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U. Check spoiler actuator at full travel.
(1)
Place speed brake control lever in UP position.
(2)
Set captain's aileron control wheel at zero and check that applicable spoiler is within following limits:
(a)
Spoiler No. 2 is 39 + 3 degrees up from zero.
(b)
Spoiler No. 6 is within + 2 degrees of spoiler No. 2 in step (a), with a minimum of 36 degrees up from zero.
(c)
Spoiler No. 3 fairs with spoiler No. 2 within + 0.25 inch.
(d)
Spoiler No. 7 fairs with spoiler No. 6 within + 0.25 inch.
(3)
Place speed brake control lever in DOWN position.
V. Check spoiler actuator pick-up position.
(1)
Rotate captain's aileron control wheel counterclockwise and check that spoiler No. 2 begins to rise at 9 + 1 degrees counterclockwise from zero.
(2)
Rotate captain's aileron control wheel clockwise and check that spoiler No. 6 begins to rise at 9 + 1 degrees clockwise from zero.
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W. Return airplane to normal.
(1)
Remove systems A and B hydraulic power. Refer to 27-61-0.
(2)
Remove protractor and protractor mount from captain's control wheel.
(3)
Remove protractors and stands from spoilers.
(4)
Remove electrical power if no longer required.
(5)
Check hydraulic reservoirs and service if required. Refer to Chapter 29, Hydraulic power.
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FLIGHT SPOILER ACTUATOR - INSPECTION/CHECK
1. General
A. This data consists of illustrations and wear limits charts. There will be no procedure given in this section for gaining access to, or removing and replacing the component after inspection for wear. Refer to Component, Removal/Installation for this information.
2. Flight Spoiler Actuator Wear Limits
G35560 G35581G36763
500 Flight Spoiler Actuator Wear Limits
Feb 20/85 Figure 601 (Sheet 1) 27-61-51
Page 601
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.
Flight Spoiler Actuator Wear Limits 500
27-61-51 Figure 601 (Sheet 2) Aug 15/71
Page 602
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.
501 Flight Spoiler Actuator Wear Limits
Nov 01/74 Figure 601 (Sheet 3) 27-61-51
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