(i)
Place alternate flaps arming switch to ARM position.
(j)
Check that standby hydraulic system low pressure light is off.
(k)
Observe leading edge flaps and slats for 60 seconds. Verify that flaps and slats do not extend.
(l)
Place alternate flaps arming switch in OFF position.
NOTE: Leading edge flaps may slowly extend due to gravity.
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(12) Check for leading edge flap droop.
(a)
Pressurize hydraulic system A.
(b)
Place flap control lever in FLAP UP position to fully retract leading edge devices.
(c)
Depressurize hydraulic system A. Bleed off hydraulic pressure to zero psi.
(d)
After a one-minute wait, measure gap between lower surface of flap trailing edge and adjacent wing skin lower surface at outboard end of inboard flap and inboard end of outboard flap.
(e)
Check that gap does not exceed 2.0 inches for new or overhauled actuators or 4.0 inches for inservice units.
C. Restore Airplane to Normal Configuration
(1)
Remove system A hydraulic power (Ref 29-11-0 MP).
(2)
Close hydraulic ground interconnect valve.
(3)
Lockwire alternate flap master arming switch.
(4)
Determine if there is any further need for electrical power on airplane. If not, disconnect power.
(5)
Install all access panels.
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LEADING EDGE FLAPS - REMOVAL/INSTALLATION
1. General
A. The following procedure applies to the inboard and outboard leading edge flaps. If both flaps are being replaced, the inboard flap should be installed and adjusted first.
2. Equipment and Materials
A. Leading Edge Flap Lock - F80048-84 (preferred), -36 (optional)
B. Corrosion Preventive Compound - MIL-C-11796, Class 3 or MIL-C-16173, Grade 2 (Ref 20-30-21)
C. Aerodynamic Smoother - BMS 5-79, Class B (Ref 20-30-11)
D. Chemical and Solvent Resistant Finish - BMS 10-11, type 1 (Ref 20-30-41)
E. Protractor Assembly - 4MIT65B80307-1 (preferred), F52485-500 (optional)
3. Remove Leading Edge Flap (Fig. 401)
A. Provide system A hydraulic power (Ref 27-81-0 MP).
B. Extend leading edge flaps.
C. Remove system A hydraulic power (Ref 27-81-0 MP).
D. Install leading edge flap actuator lock on actuator of flap adjacent to flap being removed.
WARNING: INSTALL LEADING EDGE FLAP ACTUATOR LOCK WHEN FLAP IS IN EXTENDED POSITION. FLAPS ARE FAST ACTING AND CAN CAUSE SERIOUS INJURY TO PERSONNEL.
E. At all flap nose operating linkages except inboard linkage of inboard flap, disconnect flap nose links from lugs in wing leading edge.
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G42416
Leading Edge Flap Installation 521
27-81-12 Figure 401 Feb 15/73
Page 402
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521 Leading Edge Flap Installation
Feb 15/73 Figure 401 (Sheet 2) 27-81-12
Page 403
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G44219G44231
Leading Edge Flap Installation 521
27-81-12 Figure 401 (Sheet 3) Sep 20/81
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504 Leading Edge Flap Installation
Jan 20/83 Figure 401 (Sheet 4) 27-81-12
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F. At inboard linkage of inboard flap, if existing flap nose rod can be used, disconnect rod from operating crank on flap panel and leave installed in wing (Details A and B, Fig. 401). If existing flap nose rod cannot be used, remove landing light lens on wing leading edge for access and disconnect flap nose rod from lug in wing.
G. Disconnect flap actuator from flap panel.
H. Disconnect bonding jumpers.
I. At inboard hinge of inboard flap, if existing hinge fitting can be used, disconnect hinge fitting from flap panel by removing two bolts and leave hinge fitting installed in wing. If existing hinge fitting cannot be used, remove landing light lens from wing leading edge and forward wing to body fairing for access and remove hinge bolt (detail B).
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