(9)
Set landing gear control lever in UP position.
(10)
Operate test bench to slowly retract gear.
CAUTION: MAKE SURE THAT STRUT DOORS CLEAR WING PANELS BEFORE RETRACTING GEAR COMPLETELY.
(11)
Loosen the four strut door support clamps (1, 4, 9, 11).
(12)
Hold outer door in place and adjust center door so that outer door overlaps center door
0.50 + 0.10 inch and there is a gap of 0.20 + 0.15/-0.05 inch between center door and aft wing skin panels.
NOTE: When installing a new door assembly, the center and inner doors may require edge-trimming to meet the gap requirements.
If drag and shock strut door support clamps (1, 4, 9, 11) were moved during door removal, place clamps at distances shown in Fig. 401.
(13)
Tighten strut door support clamps.
(a) Mark index stripe on clamp (9) and shock strut outer cylinder per Fig. 401 (Sheet 2A).
(14)
Shim shock strut supports (8 and 10) and adjust drag strut door support link until center door fairs with wing profile within + 0.06 inch.
(15)
Extend gear and connect outer and inner door control rods.
(16)
Retract gear and check fit of inner and outer doors. Outer door should fair with wing profile within + 0.06 inch. Inner door should fair with body fairing within + 0.06 inch.
(17)
Extend gear.
NOTE: When performing Step (18), refer to 32-13-21 to check adjustment of wing door.
(18)
Adjust inner (7) and wing door control rods as necessary to meet conditions of Step (16).
(19)
Repeat Steps (16) thru (18) until tolerances are met.
(20)
Determine whether there is further need for electrical and hydraulic power on the airplane; if not, shut down sources.
(21)
Install ground lock assemblies (Ref 32-00-01) on gear.
(22)
Lower airplane and remove jacks.
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4. Shock Strut Inner Door - Removal/Installation
A. Remove Shock Strut Inner Door
(1)
Check that assemblies (Ref 32-00-01) ground locks are installed.
(2)
Disconnect inner door control rod assembly (7, Fig. 401).
(3)
Support inner door and remove hinge bolts.
B. Install Shock Strut Inner Door
(1)
Place door in mounting position (Fig. 401).
(2)
Apply a film of grease to hinge bolts and install hinge bolts, washers, nuts, and cotter pins.
(3)
Connect inner door control rod assembly (7).
(4)
Jack airplane until all tires are clear of ground (Ref Chapter 7, Jacking Airplane).
(5)
Check that electrical power is available.
(6)
Connect external hydraulic test bench. Do not pressurize hydraulic system A.
(7)
Remove ground lock assemblies (Ref 32-00-01) on landing gear being repaired.
(8)
Set landing gear control lever to UP position.
(9)
Operate test bench to regulate hydraulic pressure and flow to slowly retract gear.
(10)
Check fit of inner door.
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NOTE: When installing a new inner door, the door may require edge-trimming to meet the gap requirements.
(a)
Door should fair with body fairing within + 0.06 inch.
(b)
Gap between forward edge of door and body fairing should be 0.20 +0.05/-0.14 inch.
(c)
Gap between aft edge of door and body fairing should be 0.35 +0.15/-0.05 inch.
(11)
Rig inner door with forward inboard corner 0.17 +0.03/-0.00 inch inside body contour. This will allow door to fair when wing is deflected in flight.
NOTE: Door must be rigged with landing gear control lever in neutral and with flaps up.
(12)
Extend gear and adjust inner door control rod (7).
(13)
Repeat steps (9) thru (12) until tolerances are met.
(14)
Determine whether there is further need for electrical and hydraulic power on airplane; if not, shut down sources.
(15)
Install ground lock assemblies (Ref 32-00-01).
(16)
Lower airplane and remove jacks.
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MAIN GEAR SHOCK STRUT DOORS - INSPECTION/CHECK
1. General
A. This data consists of illustrations and wear limit charts. No procedure is given in this section for access to permit inspection. Refer to Main Gear Shock Strut Doors – Removal/Installation for record procedure.
NOTE: The shock strut doors may be removed and installed as an assembly or the inner door may be removed and installed separately.
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