(f)
After two minutes, remove system A hydraulic power (Ref AMM 27-51-0 MP).
(2)
Check that angular clearance between upstops on ball nut (13) and jackscrew is 90 to 135 degrees (3/8 turn -45 degrees) turn of jackscrew. If clearance is not within limits (Ref AMM 27-51-01 A/T).
500
27-51-12 Page 408 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. Feb 01/75
(2a) Check adjustment of aftflap actuating mechanism boom cables as follows:
(a)
Provide hydraulic system A power (Ref AMM 27-51-0 MP).
(b)
Position flap control lever to FLAP DOWN to fully extend trailing edge flaps.
(c)
Remove system A hydraulic power (Ref AMM 27-51-0 MP).
(d)
Disconnect two pushrods from aftflap.
(e)
Disconnect boom assembly at forward end if not previously disconnected.
(f)
Provide hydraulic system A power (Ref AMM 27-51-0 MP).
(g)
Partially retract flaps sufficiently to allow movement of boom assembly aft to rigging position.
(h)
Move boom assembly aft to rigging position.
(i)
Insert rigging pins F-5 and F-6.
(j)
Check that cable tension is 100 +10 pounds.
NOTE: Cables should be adjusted to 100-pound tension at temperature of approximately 70oF. As temperature decreases, tension should be decreased and as temperature increases, tension should be increased. However, the 10-pound tolerance should not be exceeded.
(k)
If cable tension is incorrect, adjust inboard trailing flap assembly
(Ref AMM 27-51-12 A/T).
(l)
If cable tension is correct, remove rigging pins F-5 and F-6.
(m)
Provide hydraulic system A power (Ref AMM 27-51-0 MP).
(n)
Extend trailing edge flaps and move boom assembly forward to forward attach point.
NOTE: Before moving trailing edge flaps, check that rigging pins F-5 and F-6 are removed.
(o)
Temporarily attach boom assembly at forward end.
(p)
Connect pushrods to aftflap.
(q)
Retract trailing edge flaps.
(r)
Disconnect boom assembly at forward attach point.
(s)
After two minutes, remove hydraulic system A power (Ref AMM 27-51-0 MP).
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27-51-12
Page 408A/408B
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.
(3)
With rigging pins F-5 and F-6 installed to trap boom roller, connect forward end of boom
(1) to inboard fairing support fitting. Adjust boom end fitting as necessary to make connection. Install bolt with corrosion preventive compound with head on inboard side. Tighten checknut on end fitting and lockwire.
(4)
Remove rigging pins F-5 and F-6 from boom.
(5)
Provide hydraulic system A power (AMM 27-51-0/201).
(6)
Move flap control lever to FLAP DOWN (40-unit) detent and back to FLAP UP detent. Carefully check operation of flap for any indication of interference or rough operation.
(7)
Remove hydraulic system A power (AMM 27-51-0/201).
(8)
Remove plug screws and attach inboard flap rigging tool at location marked by black arrows at WBL 147.2 or hand position inboard flap rigging beam to black stripes located at WBL 147.2 on front and rear spar (Section A-A, Fig. 402). Check that flap trailing edge is within士 0.25 inch of theoretical wing chord plane (WCP) and is symmetrical with opposite inboard flap trailing edge within 0.10 inch. If you have made trim corrections with the inboard TE flaps, the limits can be more than 0.25 inch. Measurements to be made with aftflap dead-weight rollers contacting. If adjustment is required, proceed as follows:
(a)
Remove forward roller assemblies from each flap carriage.
(b)
Loosen nut on each roller assembly enough to allow rotation of eccentric bushing.
(c)
Rotate bushings as necessary to fair flap trailing edge with wing chord plane. Rotate all bushings on a flap to the same position. Tighten nuts as bushings are adjusted. Tighten nuts to 200-500 pound-inches and install cotter pins.
(d)
With all bushings adjusted, reinstall carriage front rollers. Lockwire bolts.
(e)
Recheck position of flap trailing edge in relation to wing chord plane.
(f)
Remove inboard flap rigging tool and install plug screws if required.
(9)
Provide system A hydraulic power (Ref 27-51-0), extend flaps to FLAP DOWN (40-unit) position and check the following:
NOTE: Rotating bushings one notch will shift flap trailing edge approximately 0.10 inch.
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