G29322
Wing Spoiler Cable Turnbuckles 500
27-61-0 Figure 505 Jun 20/85
Page 512
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.
(6) Adjust Spoiler to Flap Clearance
(a)
Provide electrical power to airplane.
(b)
Provide system A and B hydraulic power (Ref 27-61-0 MP).
(c)
Place speed brake control lever in FLIGHT DETENT position to raise all spoiler panels.
NOTE: Raising spoilers will ensure that trailing edge flaps do not strike spoilers during retraction.
(d)
With hydraulic power on, retract the flaps to the up position by placing the flap control lever in the FLAP UP detent.
(e)
Remove system A and B hydraulic power (Ref 27-61-0 MP).
(f)
Place speed brake control lever in DOWN position.
(g)
Using hand pressure on upper surface of spoiler panel, push down until actuator piston bottoms.
(h)
Check that spoiler to flap clearance for flight spoilers No.2, 3, 6, and 7 is 0.03 +0.10/-0.00 inch. Measure at point of minimum clearance (Fig. 506).
NOTE: Minimum spoiler panel gap measured along panel span at trailing edge need only be sufficient to ensure that panel has clearance with flap.
500
May 01/00 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 27-61-0 Page 513
A89646
Flight Spoiler Panel Adjustment 500
27-61-0 Figure 506 Oct 20/92
Page 514
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.
(i) If spoiler to flap clearance is not within limits: 1) Provide system A and B hydraulic power (Ref 27-61-0, Maintenance Practices). 2) Provide access to spoiler actuator by either lowering flaps and opening
applicable trailing edge panel or by placing speed brake control lever in UP position to raise spoilers. Depressurize hydraulic systems A and B (Ref 27-61-0, Maintenance Practices).
WARNING: DO NOT PUT ANY PART OF BODY BETWEEN SPOILER AND WING UNLESS HYDRAULIC POWER IS REMOVED. SERIOUS INJURY CAN RESULT.
3) Break lockwire and loosen checknut on actuator rod end.
4) Disengage locking key from piston rod.
5) Turn actuator piston rod to obtain proper spoiler to flap clearance. Each quarter
turn will change spoiler to flap clearance by approximately 0.10 inch.
CAUTION: TURNING PISTON ROD WHEN ACTUATOR IS PRESSURED WILL DAMAGE ACTUATOR.
6) Engage locking key with piston rod.
7) Coat rod end threads with corrosion preventive compound.
8) Tighten rod end checknut to 350-400 pound-inches.
9) Lockwire checknut to locking key.
10) 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)
Rotate captain's control wheel clockwise to ensure that flight spoilers No. 2 and 3 are full down.
(m)
Remove system A and B hydraulic power (Ref 27-61-0).
(n)
Check that spoiler to flap clearance for flight spoilers No. 2 and 3 is 0.03 +0.10/-0.00 inch.
(o)
Rotate captain's control wheel counterclockwise to ensure that flight spoilers 6 and 7 are full down.
(p)
Remove system A and B hydraulic power (Ref 27-61-0).
(q)
Check that spoiler to flap clearance for flight spoilers No. 6 and 7 is 0.03 +0.10/-0.00 inch.
(r)
If spoiler to flap clearances are not within limits, repeat step (i).
500
Feb 01/95 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 27-61-0 Page 515
(7) Adjust Spoiler Actuator Input Lever
(a)
Provide system A and B hydraulic power (Ref 27-61-0).
(b)
Turn captain's control wheel clockwise from neutral to ensure that flight spoilers No. 2 and 3 are fully retracted.
(c)
Install protractor mount and protractor on captain's aileron control wheel.
(d)
Place straightedge across both aileron control wheels and set protractor on captain's control wheel to zero with control wheels in this position. Remove straightedge.
(e)
Install control surface protractor stand and protractor on flight spoiler No. 2. Set protractor to zero.
NOTE: Protractor may be hand-held on spoiler instead of using stand.
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