(d)
Turn actuator piston rod to obtain proper spoiler to flap clearance. Each quarter turn will change spoiler to flap clearance by approximately 0.12 inch.
CAUTION: TURNING PISTON ROD WHEN ACTUATOR IS PRESSURIZED WILL DAMAGE ACTUATOR.
(e)
Engage locking key with piston rod.
(f)
Coat rod end threads with corrosion preventive compound.
(g)
Tighten rod end checknut to 350-400 pound-inches.
(h)
Lockwire checknut to locking key.
(i)
Apply a bead of sealant to the rod end checknut.
(j)
Provide system A and B hydraulic power.
(k)
Lower spoilers or raise flaps, as applicable.
(l)
Check spoiler to flap clearance per step (1).
(m)
Test flight spoiler.
D. Restore Airplane to Normal
(1)
Remove system A and B hydraulic power.
(2)
Remove electrical power if no longer required.
2. Flight Spoiler Test
A. Equipment and Materials
(1)
Control Surface Protractor - 4MIT65B80307-1 (preferred), F52485-500 (optional)
(2)
Control Surface Protractor Stand Assembly - F71292-17
B. Prepare Flight Spoiler for Test
(1)
Provide electrical power.
(2)
Provide system A and B hydraulic power (Ref 27-61-0, Maintenance Practices).
(3)
Install protractor and protractor mount on captain's control wheel. Set protractor to zero.
500
Feb 01/95 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 27-61-11 Page 503
C. Test Flight Spoiler
NOTE: This test presents check of full travel limits for all flight spoilers; however, only spoiler, which has been replaced, need be tested.
(1)
Place speed brake control lever to UP position.
(2)
Place captain's control wheel in neutral position and check that:
(a)
Spoiler No. 2 is 39 (+ 3) degrees up from zero. Record value.
(b)
Spoiler No. 3 fairs with spoiler No. 2 within + 0.25 inch.
(c)
Spoiler No. 6 is within + 2 degrees of spoiler No. 2 in step (a) with a minimum of 36 degrees up from zero.
(d)
Spoiler No. 7 fairs with spoiler No. 6 within + 0.25 inch.
(3)
Place speed brake control lever in DOWN position to lower spoilers.
D. Restore Airplane to Normal
(1)
Remove electrical power if not required.
(2)
Remove system A and B hydraulic power. Refer to 27-61-0.
(3)
Remove protractor and protractor mount from captain's control wheel.
500
27-61-11 Page 504 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. Feb 15/73
FLIGHT SPOILER - 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 Wear Limits
G33713 G34950
501 Flight Spoiler Wear Limits
Feb 20/85 Figure 601 (Sheet 1) 27-61-11
Page 601
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.
INDEX NO. PART NAME DIM DESIGN LIMITS WEAR LIMITS REPLACE WORN PART REPAIR WORN PART REPAIR INSTR.
DIAMETER MAX WEAR DIM. MAX DIAM CLEAR-ANCE
MIN MAX
1 BEARING ID 0.4995 0.5000 0.5025 0.0030 X
BOLT OD 0.4985 0.4995 0.4965 X
2 BEARING ID 0.5000 0.5015 0.5045 0.0050 X
BOLT OD 0.4985 0.4995 0.4950 X
3 BEARING ID 0.3120 0.3125 0.3150 0.0030 X
BOLT OD 0.3110 0.3120 0.3090 X
4 BEARING ID 0.3125 0.3140 0.3170 0.0050 X
BOLT OD 0.3110 0.3120 0.3090 X
Flight Spoiler Wear Limits 501
27-61-11 Figure 601 (Sheet 2) Feb 20/84
Page 602
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.
SPOILER MIXER - REMOVAL/INSTALLATION
1. Equipment and Materials
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