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AIRPLANE MAINTENANCE MANUAL
Item No. Part No. Nomenclature Manufacturers Dimension Service Dimension Service Tol. Remarks
16 78722-002 Bearing Assembly, ID .562
Rod End .564
17 67926-026 Trunnion housing, side ID .7530 ID .7530
67926-027 brace attachment .7550 .7550
18 67026-010 Bushing, trunnion ID .499 ID .498 .004 Install using
.500 .502 Loctite 601.
19 402-974 Bolt, trunnion/side OD .5616+.0000
(NAS 464 P9A-46) brace attaching -.0009
20 67926-026 Trunnion housing, ID .4410 ID .4410
67926-027 torquelink attachment .4430 .4440
21 67026-007 (2) Bearing, trunnion **ID .314 ID .315 Press fit.
.313 Install using Loctite 601.
22 67012-000 Torquelink ID .312+.001 ID .312+.002 .002 Line ream.
-.000 -.000
23 67012-000 Torquelink ID .3760 ID .3770 .0025
.3745 .3745
24 31796-000 (2) Bushing, Torquelink **ID .252 ID .253 .002 Press fit.
.251 .251
25 67037-004 Strut Assembly ID .4385 ID .4395 .0025
.4370 .4370
26 67026-007 (2) Bearing, strut **ID .314 ID .315 .002 Press fit.
.313 .313
27 67012-000 Torquelink ID .312+.001 ID .312+.002 .002 Line ream.
-.000 -.000
** Line ream to this dimension after installation of new part.
Figure 32-2. Main Gear Service Tolerances (Sheet 3 of 3)
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AIRPLANE MAINTENANCE MANUAL
3. Inspect the gear downlock spring for the following:
A. Excessive wear or corrosion, especially around the hook portion of the spring. A spring should be rejected if wear or corrosion exceeds one-quarter the diameter of the spring. Clean away all corrosion and repaint.
B. Check the spring for load tensions below minimum allowable tolerance. The minimum tension of the spring is 48 pounds pull at 7.9 inches. Measurement is taken from the inner side of each hook.
4.
Check the general condition of each limit switch and its actuator, and wiring for fraying, poor connections or conditions that may lead to failures.
5.
Check side brace link through center travel by attaching the upper and lower links, setting them on a surface table, and ascertaining that when the stop surfaces of the two links touch, linkage is not less than .062 nor more than .125 of an inch through center. Should the distance exceed the required through center travel and bolt and bushings are tight, replace one or both links.
6.
With side brace links assembled and checked, ascertain that when stop surfaces of the two links contact. the clearance between each downlock hook and the flat of the downlock pin is not less than
0.010 of an inch. Should clearance be less than that required, the hook only may be filed not to exceed a gap of more than 0.025 of an inch. The maximum allowable clearance between each hook and the downlock pin that are service worn is 0.055 of an inch. Should clearance be more than
0.055 of an inch, replace the pin, check clearance and then if still beyond tolerance, replace hooks. The gap between each hook should be equal.
7.
Repair of the landing gear is limited to reconditioning of parts such as replacing components, bearings and bushings, smoothing out minor nicks and scratches and repainting areas where paint has chipped or peeled.
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AIRPLANE MAINTENANCE MANUAL
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INSTALLATION OF MAIN LANDING GEAR. (Refer to Figure 32-3.)
— Note —
When assembling components of the landing gear, lubricate bearings, bushings, and friction surfaces with proper lubricant as described in Chapter 12.
1.
Insert a gear support bearing in each support fitting and secure with snap rings. Check bearing for excess end play, shim as necessary with shim washers (P/N 62833-044).
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