502 Leading Edge Slats Main Track Wear Limits
Oct 20/83 Figure 602 (Sheet 1) 27-81-21
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BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.
Leading Edge Slats Main Tracks Wear Limits 501
27-81-21 Figure 602 (Sheet 2) Aug 15/73
Page 604
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.
502 Leading Edge Slats Main Tracks Wear Limits
Jun 20/90 Figure 602 (Sheet 3) 27-81-21
Page 605
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G43147
Leading Edge Slat Torsion Tube Wear Limits 501
27-81-21 Figure 603 Aug 15/73
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BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.
LEADING EDGE FLAP ACTUATORS - REMOVAL/INSTALLATION
1. General
A. A container will be required to catch hydraulic fluid when disconnecting hydraulic lines from leading edge flap actuators.
2. Equipment and Materials
A. Leading Edge Flap Actuator Locks - F80048-89, -90 (Preferred) or -84 (Optional)
B. Corrosion Preventive Compound - MIL-C-11796 class 3 (Ref 20-30-21)
C. Protractor Assembly - 4MIT65B80307-1 (preferred), F52485-500 (optional)
3. Remove Leading Edge Flap Actuator
A. Provide system A hydraulic power (AMM 27-81-0/201).
B. Position flap control lever to 1-unit detent to extend leading edge flaps.
C. Depressurize hydraulic systems (AMM 27-81-0/201).
D. Install lock on adjacent leading edge flap actuator.
E. Remove bolt attaching leading edge flap actuator to leading edge flap (Fig. 401).
F. Remove lockwire and disconnect hydraulic lines from support bracket. Install plugs in hydraulic lines and cap all ports.
G. Remove bolt attaching actuator to support fitting and remove actuator.
4. Install Leading Edge Flap Actuator
A. If existing bearings, bushings, or bolts are being installed, check for allowable wear
(AMM 27-81-31/601).
B. Align leading edge flap actuator with support fitting and install clamp-up bushing and bolt with washer on each side (Fig. 401). Install locknut and tighten 300 to 450 pound-inches.
C. Ensure that hydraulic reservoirs are depressurized and remove plugs from hydraulic lines and caps from ports.
D. Connect hydraulic lines to support bracket. Lockwire nuts.
May 01/00 27-81-31 Page 401 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.
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Leading Edge Flap Actuator Installation 500
27-81-31 Figure 401 Nov 15/67
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BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.
E. Apply a thin film of corrosion preventive compound to actuator rod-end attachment bolt and washers then align actuator rod-end with leading edge flap and install bolt with a washer under bolthead. Place washer under nut and tighten nut 660 to 780 pound-inches, aligning cotter pin hole in bolt with slot in nut. Install cotter pin.
F. Remove leading edge flap actuator lock (Ref 27-81-0 MP).
G. Provide system A hydraulic power (Ref 27-81-0 MP).
H. Retract leading edge flap using hydraulic pressure.
I. Attach adjustable angle protractor to flap and set to zero angle. Mark protractor location on flap for future use. On inboard flap, attach protractor to outboard end of flap. On outboard flap, attach protractor to inboard end of flap.
J. Extend leading edge flap with hydraulic pressure.
K. Attach protractor at same location as that for retracted position. Check that flap angle for extended position is 96 to 97 degrees. If not, disconnect actuator from flap panel. Adjust flap actuator rod end to attain required extend angle. Lockwire and seal. Connect actuator to flap panel, tighten nut 660 to 780 pound-inches and install cotter pin.
NOTE: Maximum adjustment of rod end is limited to two full turns.
L. Remove system A hydraulic power (Ref 27-81-0 MP).
M. Pressurize system A hydraulic power (Ref 27-81-0 MP).
N. Cycle leading edge flaps and slats several times to bleed air from system.
O. Examine hydraulic fittings on actuator for leakage.
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P. Test leading edge flap standby hydraulic system as follows:
(1)
Connect electrical power and check that power is available on No. 1 and 2 generator buses.
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