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S 424-011
(4)
Install the bolt, the spacer, the washers, the nut, and the cotter pin to connect the springs and the spools to the spring retainer (View A-A).
E.
Put the Airplane Back to Its Usual Condition.
S 094-012
(1)
Remove the spring extender from the springs.
S 094-016
(2)
Remove the downlocks on the nose and main landing gear
(AMM 32-00-20/201).
S 844-013
(3)
Remove the DO-NOT-OPERATE tag from the control lever for the landing gear. Return the lever to DN.
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MAIN GEAR DOWNLOCK SPRINGS - INSPECTION/CHECK
_____________________________________________
1. General_______
A. This procedure has only an illustration, and a wear limit table which shows the data for wear limits. There are no procedures for access, removal, or installation of the parts. Refer to the Main Gear Downlock Springs - Removal/Installation for the procedures to do these tasks.
TASK 32-11-22-206-002
2. Wear Limits for the Downlock Springs of the Main Landing Gear (Fig. 601)_____________________________________________________________
A. Wear Limits for the Downlock Springs
S 226-001
(1) Refer to Fig. 601 for the inspection points and the wear limits table.
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MAINTENANCE MANUAL
DOWNLOCK SPRINGS SHOCK STRUT
SEE A
DRAG STRUT
FWD
STRUT SIDE
DOWNLOCK
LINK
B
A B
DOWNLOCK SPRING
(2 LOCATIONS)
A
A
1.
BUSHING/SPACER
2.
BUSHING/SPACER 2. BUSHING/SPACER
2. BUSHING/SPACER 2. BUSHING/SPACER 3. BUSHING/SPACER 3. BUSHING/SPACER
A-A B-B
Main Landing Gear Downlock Springs Wear Limits
Figure 601 (Sheet 1)
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NO. INDEX PART NAME DIM. DESIGN LIMITS WEAR LIMITS WORN PART REPLACE PART WORN REPAIR INSTR REPAIR
DIAMETER PER-MITTED WEAR DIM. MAX ANCE CLEAR-DIAM
MIN MAX
1 BUSHING ID 0.5000 0.5010 0.5034 0.0039 X
SPACER OD 0.4985 0.4995 0.4971 X
2 BUSHING ID 0.5005 0.5015 0.5039 0.0044 X
SPACER OD 0.4985 0.4995 0.4961 X
3 BUSHING ID 0.5000 0.5007 0.5039 0.0036 X
SPACER OD 0.4985 0.4995 0.4971 X
Main Landing Gear Downlock Springs Wear Limits
Figure 601 (Sheet 2)
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MAIN GEAR SHOCK STRUT SEALS - MAINTENANCE PRACTICES
___________________________________________________
1. General_______
A. This procedure contains four tasks. The first task does a check of the strut for serviceability. The other tasks replace the seals on the shock strut of the main landing gear. Task two replaces the seals with the spare seals. Two sets of spare seals are in the gland nut of the shock strut. Task three replaces the active seals and the spare seals. Task three is used when the two sets of spare seals have been used. Task four is an optional procedure that replaces the active seals and the spare seals from the top of the inner cylinder.
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