(a)
Set aileron in neutral. Aileron is in neutral when rigging pin A/S-4 can be freely inserted. Remove rigging pin.
(b)
Place speed brake control lever in UP position.
(c)
Set captain's control wheel at zero and check that: 1) Spoiler No. 2 is 39 ± 3 degrees up from zero. Record value. 2) Spoiler No. 7 is within ± 2 degrees of spoiler No. 2 with a minimum of 36
degrees up from zero.
3) Spoiler No. 3 fairs with spoiler No. 2 within ± 0.25 inch.
4) Spoiler No. 6 fairs with spoiler No. 7 within ± 0.25 inch.
(d)
Set captain's control wheel 87 degrees counterclockwise from zero and check that: 1) Spoiler No. 2 is 39 ±3 degrees up from zero. Record value. 2) Spoiler No. 7 is partially raised.
(e)
Set captain's control wheel at 87 degrees clockwise from zero and check that: 1) Spoiler No. 7 is 39 ±3 degrees up from zero. Record value. 2) Spoiler No. 2 is partially raised.
(5)
Test Spoiler Response Time
(a)
Rapidly move speed brake control lever from DOWN to UP and check that flight spoilers actuate from full down to full up in less than 1 second.
(b)
Rapidly move the speed brake control lever from UP to DOWN and check that flight spoilers actuate from full up to full down in less than 1 second.
(6)
Test Autopilot Authority (Ref 27-11-0)
500
27-61-0 Page 520 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. Feb 01/95
500
Oct 20/89 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 27-61-0 Page 521
NOTE: The autopilot authority test for ailerons also tests autopilot authority for spoilers.
E. Restore Airplane to Normal
(1)
Remove system 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 stands from flight spoilers No. 2 and 7.
(4)
Remove electrical power if no longer required.
500
27-61-0 Page 522 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. Oct 20/89
G29575
500 Speed Brake Control Cable Locations and Cable Tension
Aug 15/69 Figure 507 27-61-0
Page 523
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FLIGHT SPOILERS - REMOVAL/INSTALLATION
1. General
A. For interchangeability of graphite/composite flight spoilers with aluminum/fiberglass flight
spoilers, refer AMM 27-09-800/201. 1A. Equipment and Materials
A. Flight Spoiler Ground Lock Assy - F80017-33 (Preferred), F80017-23 (Optional)
(Use on airplanes with chamfered clevis)
B. Flight Spoiler Ground Lock Set - C27047-16 (Use on airplanes with rounded clevis)
C. Corrosion Preventive Compound - MIL-C-11796, Class 3 (AMM 20-30-21/201)
2. Prepare for Removal
A. Provide electrical power.
B. Provide system A and B hydraulic power (AMM 27-61-0/201).
C. Place FLT CONTROLS A switch on forward overhead panel to ON to pressurize trailing edge flaps.
D. Place flap control lever in FLAP DOWN position to extend trailing edge flaps.
E. Place speed brake control lever in UP position to raise spoilers.
F. Remove system A and B hydraulic power (AMM 27-61-0/201).
G. Install spoiler ground lock on actuator for spoiler being removed.
3. Remove Flight Spoiler
A. Remove bolt attaching spoiler actuator rod end to spoiler (Fig. 401).
B. Disconnect bonding jumpers from spoiler. Jumpers are located adjacent to inboard and outboard hinge locations.
C. Remove four hinge bolts.
D. Remove spoiler from airplane.
NOTE: Flight spoiler weighs approximately 16 pounds.
E. Remove bearings at inboard and outboard hinge locations.
May 01/00 27-61-11 Page 401 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.
G29593
Flight Spoiler Installation 500
27-61-11 Figure 401 Jun 20/86
Page 402
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.
4. Install Flight Spoiler
NOTE: If a used bolt or bearing is being installed, check for allowable wear (Ref 27-61-51, I/C).
A. Position bearings in spoiler at inboard and outboard hinge locations.
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