(g)
Install the cotter pin.
S 434-016
(15)
Connect the electrical wire harness (11) to the lower torsion link (10).
(a)
Loosen the wire harness and install on torsion links.
(16)
Install the nose wheels (AMM 32-45-21/401).
S 824-014
(17)
Adjust the safety sensor on the nose landing gear (AMM 32-09-02/501).
S 414-015
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737-300/400/500MAINTENANCE MANUAL
S 094-013
(18)
Remove the jack from the axle of the nose landing gear.
S 584-012
(19)
Lower the nose of the airplane and remove the jacks (AMM 07-11-11/201).
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A
737-300/400/500MAINTENANCE MANUAL
NOSE LANDING GEAR TORSION LINKS - INSPECTION/CHECK
__________________________________________________
1. General
_______
A. This procedure only has illustration and a wear limits table which shows the data for wear limits. There are no procedures for the access, the removal, or the installation of the parts. Refer to the Nose Landing Gear Torsion Links - Removal/Installation for procedures to do these tasks.
TASK 32-21-31-206-001
2. Wear Limits for the Torsion Links of the Nose Landing Gear (Fig. 601)
__________________________________________________________
A. Wear Limits for the Torsion Links
S 226-002
(1) Refer to Fig. 601 for the inspection points and the wear limits table.
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737-300/400/500
MAINTENANCE MANUAL
1. BUSHING/PIN
(2 LOCATIONS) A
6.
A
STEERING FWD
COLLAR LUG
C
B
PIN
B
C
UPPER
TORSION
LINK
2. BUSHING PIN APEX
(2 LOCATIONS) BOLT 8.
A-A 8.
3. BUSHING/BOLT
(5 LOCATIONS)
LOWER TORSION
LINK
4. BUSHING PIN
(2 LOCATIONS)
7.
B-B
PIN
SHOCK STRUT 5. BUSHING/PIN
INNER CYLINDER (2 LOCATIONS)
LUG
C-C
Nose Landing Gear Torsion Links Installation
Figure 601 (Sheet 1)
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A 737-300/400/500MAINTENANCE MANUAL
INDEX NO. PART NAME DIM. DESIGN LIMITS WEAR LIMITS REPLACE WORN PART WORN PART REPAIR REPAIR INSTR
DIAMETER MITTED WEAR DIM. PER- CLEAR-ANCE MAX DIA
MIN MAX
1 BUSHING ID 1.2500 1.2510 1.260 0.010 X
PIN OD 1.2490 1.2498 1.245 X 1
2 BUSHING ID 1.2500 1.2510 1.260 0.010 X
PIN OD 1.2490 1.2498 1.245 X 1
3 BUSHING ID 0.6250 0.6259 0.634 0.010 X
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