NOTE:  A solution of 15 to 20% isopropyl alcohol in distilled water may be applied to tool, used to form fillet, to prevent sealant from sticking to tool. Water alcohol solution is to be kept free of contamination by dispensing from polyethylene squirt bottles.

(c)  
Form fillet a minimum of 0.08 inch thick at junction of gland nut and shock strut surfaces extending 1/8 to 1/4 inch out on gland nut surface and up shock strut surface.

NOTE:  A surface skin will form on sealant a few minutes after exposure. Forming of fillet should be done immediately after sealant is applied.
(49) Install bolt (10) to connect upper and lower torsion links.
D.  Restore Airplane to Normal Configuration
(1)  
On airplanes with nose gear taxi light, connect taxi light electrical harness wiring at the light and lockwire plug.

(2)  
On airplanes with taxi light, install clamps on electrical wiring at points from which removed.

(3)  
Wipe exposed portion of inner cylinder with hydraulic fluid.

(4)  
Service shock strut first with hydraulic oil then dry air or nitrogen per decal on nose gear shock strut (Ref Chapter 12).

(5)  
Lower airplane nose and check for leaks at gland nut.

(6)  
Remove airplane jacks.

(7)  
Remove tag showing seal status from shock strut.

(8)  
Install nose gear wheel well doors (Ref 32-22-11 R/I).

(9)  
Adjust nose wheel steering system (Ref 32-51-0 A/T).

500 
Oct 20/93  BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.  32-21-11 Page 813 

NOSE GEAR DRAG BRACE - REMOVAL/INSTALLATION
1.  Equipment and Materials
A.  Ground Lock Assemblies (Ref 32-00-01)
B.  Corrosion Preventive Compound - MIL-C-11796, Class 3 (Ref 20-30-21)
C.  Grease - MIL-G-21164 or MIL-G-23827 optional to BMS 3-33 (Ref 20-30-21)
D.  Naptha - PD-680 solvent (Ref 20-30-31)
2.  Remove Nose Gear Drag Brace Assembly (Fig. 401)
A.  Install ground lock assemblies (Ref 32-00-01).
B.  Jack nose of airplane until nose gear wheels are off the ground (Ref Chapter 7, Airplane Jacking). Do not deflate shock strut.
WARNING:  THE NOSE GEAR SHOCK STRUT MUST BE FULLY EXTENDED BEFORE DRAG BRACE IS DISCONNECTED AS UNEXPECTED MOVEMENT OF A PARTIALLY COMPRESSED SHOCK STRUT COULD INJURE PERSONNEL.
C.  Disconnect drag brace from door mechanism link (16) on each drag brace trunnion arm (17).
D.  Remove bolt to disconnect nose gear actuator (1) from upper drag brace link (2).
E.  Remove bolt (11) to disconnect drag brace and lock link assembly (8) and remove spacer bushing (7, 9) from each lock link (8) fork arm.
F.  Remove drag brace pin (6) to separate upper and lower links.
G.  Remove bolt at lower end of drag brace lower link to detach lower link from shock strut  (Fig. 401, detail C).
H.  Remove aft access panel on right and left bulkheads o f nose gear wheel well.
I.  Remove cotter pin and loosen nut (20) on each drag brace (21) pin outboard the right and left wheel well bulkheads.
NOTE:  Loosen each nut on each drag brace pin and leave each loosened nut on pin as an aid for removing pin.
May 01/03 32-21-21 Page 401 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.

J.  Remove drag brace pin antirotation bolt (18) from each drag brace pin.
K.  Pull bottom of gear forward to relieve gear weight from drag brace pins to make pin removal less difficult.
L.  Support drag brace and remove pins by pulling them outboard.
NOTE:  The partially removed nut is to be used for removal of each pin to avoid damage to pin threads.
M.  Lower drag brace to clear lower end of actuator and remove from area.
3.  Prepare to Install Nose Gear Drag Brace
A.  Check distance between nose gear drag brace bearings in wheel well structure (Ref 32-21-61), Nose Gear Drag Brace Bearing – Removal/Installation.
4.  Install Nose Gear Drag Brace Assembly
A.  Clean drag brace pins, washers, and nuts with naphtha and lubricate pin threads and washer faces with grease.
B.  Mark a reference line through center of each drag brace pin antirotation bolt (18) hole to threaded end of each pin (21).
C.  Connect Actuator to Drag Brace
(1)  
Position drag brace upper link (2) for installation by sliding upper link into forked terminal on lower end of actuator (1) (Fig. 401, View 1).

(2)  
Slide a nylon hydraulic washer (5, 13) on each side of swivel (14) between swivel and actuator forked terminal.
　
中國航空網 m.k6050.com
航空翻譯 www.aviation.cn
本文鏈接地址：737 AMM 飛機維護手冊 起落架 LANDING GEAR(68)