I. Remove actuator by pulling up, sliding rod end (9) from swivel bearing in drag brace upper link.
J. Plug hydraulic lines.
K. Remove union (6) and restrictor (19) from actuator.
L. Remove and discard O-rings from union and restrictor.
3. Install Nose Gear Actuator
A. Clean and apply thin coat of grease to bolt shanks and all mating surfaces of actuator and parts used to install nose gear actuator (8).
B. Install new O-rings in union (6) and restrictor (19). Install union in actuator upper port and restrictor in bottom port of actuator.
C. Fill actuator with Skydrol 500 hydraulic fluid.
(1)
With actuator piston (18) extended, fill through restrictor (19) until piston is fully retracted.
(2)
Cap union and restrictor.
D. Position actuator in clamp (7), if installed, with actuating rod end (9) down, with restrictor (19) on the right, and sliding hydraulic lines (5) and (20) into respective union and restrictor at top and bottom of actuator.
NOTE: Do steps D and E simultaneously.
E. Slide actuating rod end onto swivel bearing (14) in the drag brace upper link (13).
F. Insert nylon washers (12) and (15) between actuator rod end and swivel bearing on each side of swivel bearing.
G. Install lubricated close tolerance, short thread bolt (10) with countersunk, high strength washer
(11) under bolt head with countersink towards bolt head.
H. Install high strength, plain washer (17) and castellated nut (16).
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32-33-11 Page 402 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. Oct 20/84
500 Nose Gear Actuator Installation
Oct 20/84 Figure 401 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 32-33-11 Page 403
I. Tighten nut (16) 1500 to 1800 pound-inches torque.
NOTE: If cotter pin cannot be installed within specified torque range, meet torque requirements by either interchanging nuts or adding one flat washer under the countersunk washer (11), on the opposite side of countersink. Use both methods if necessary.
J. Install cotter pin.
K. Slide fork of terminal fitting (2) of actuator, onto connective fitting (24) in top of wheel well.
L. Install nylon washer (1) and (23) between fork arm of terminal fitting (2) on actuator and connective fitting in top of wheel well, on each side of connective fitting.
M. Install lubricated, close tolerance, short thread bolt (4) with countersunk, high strength washer
(3) under bolthead with countersink towards bolthead.
N. Install plain washer (22) and castellated nut (21).
O. Tighten nut 1500 to 1800 pound-inches torque.
NOTE: If cotter pin cannot be installed within specified torque range, meet torque requirements by either interchanging nuts or adding one flat washer under the countersunk washer, on the opposite side of countersink. Use both methods if necessary.
P. Install cotter pin.
Q. If installed, tighten bolt on clamp (7).
R. Remove plugs from lines and caps from actuator.
S. Connect hydraulic lines (5, 20) to respective bottom and top connective fittings on actuator.
4. Bleed Nose Gear Actuator (Airplane On Jacks)
A. Connect variable volume test bench and pressurize hydraulic system A to 100 psi maximum.
B. Jack airplane nose (Ref Chapter 7). Lower tail support jack as nose is raised.
C. Check that gear ground lock assemblies are installed in nose and main gear (Ref 32-00-01).
WARNING: CHECK THAT GROUND LOCK ASSEMBLIES ARE INSTALLED IN ALL LANDING GEAR TO PREVENT INADVERTENT OPERATION OF GEAR. INJURY TO PERSONNEL AND/OR DAMAGE TO EQUIPMENT COULD RESULT IF GEAR RETRACTS.
D. Actuate override trigger and move landing gear control handle to UP position.
E. Remove lockwire and open bleed plug, which is located on the aft side of the actuator, top head end.
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32-33-11 Page 404 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. Jun 20/91
F. Close bleed plug when fluid flow indicates air is bled from system.
G. Install NC32 monel lockwire, to lock wire bleed plug to actuator, using double twist method.
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