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B.  The airplane system may be used for a straight retraction test after replacement of hydraulic components. Gear operating times and hydraulic pressure will be near normal when the airplane hydraulic system is used.
2.  Equipment and Materials
A.  Hydraulic Test Bench, Skydrol 500 Hydraulic Fluid, capable of delivering 10 gpm at 3000 psi
B.  Gear Ground Lock Assemblies (Ref 32-00-01)
C.  Stop Watch
3.  Prepare to Test Extension and Retraction
A.  Check shutoff valves for open position.
B.  Jack airplane for nose gear retraction test (Ref Chapter 7, Jacking).
C.  Ground airplane from vicinity of main gear.
D.  Connect electrical power.
E.  Remove gear ground lock assembly from nose gear (Ref 32-00-01).
WARNING:  CHECK THAT GROUND LOCK ASSEMBLIES ARE INSTALLED IN MAIN LANDING GEAR TO PREVENT INADVERTENT OPERATION OF GEAR. INJURY TO PERSONNEL AND/OR EQUIPMENT COULD RESULT IF GEAR RETRACTS.
F.  Check that nose gear is fully extended and locked, with control lever in OFF position.
G.  If it is desired to operate nose gear using external hydraulic power, connect hydraulic test bench to airplane and pressurize hydraulic system (Ref Chapter 29).
CAUTION:  DO NOT TURN STEERING WHEEL WITH NOSE GEAR SHOCK STRUT FULLY EXTENDED, BECAUSE OF POSSIBLE DAMAGE TO CENTERING CAMS IN SHOCK STRUT.
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H. If it is desired to operate nose gear using airplane hydraulic system, proceed as follows:
(1)  
Close A and B flight control and spoiler shutoff valves.

(2)  
Open hydraulic interconnect valve circuit breaker.

(3)  
Manually open hydraulic interconnect valve.

(4)  
Turn on both B system hydraulic pumps.

CAUTION:  PUMPS MAY BE DAMAGED IF ATTEMPTS ARE MADE TO VARY RETRACTION SPEED WHEN AIRPLANE SYSTEM IS IN USE FOR TEST.
I.  Advance both throttles to a position greater than 17 degrees.
4.  Test Landing Gear
WARNING:  CLEAR NOSE WHEEL WELL AREA OF EQUIPMENT AND PERSONNEL BEFORE OPERATING GEAR.
A.  Operate override trigger and move control lever to UP position and note gear retraction time.
NOTE:  Check that all red warning lights are on during gear transit.
B.  Check that nose gear is up and locked and wheel well doors are closed within 6 seconds from the time control lever enters UP detent.
NOTE:  Gear retraction time is defined as the time period between when control handle is placed in UP position and when red warning lights go off.
C.  Check that red warning lights are off.
D.  Place control lever in OFF position for approximately 15 seconds.
E.  Make sure that the warning light remains off and that the landing gear remains locked.
F.  Place the control lever in the down position.
G.  Check that nose gear extension time does not exceed 6 seconds.
NOTE:  Gear extension time is defined as the time period between when control handle is placed in DN position and when green indicator lights come on.
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H. Ensure all green indicator lights are on.
I. Close interconnect valve.
J. Install nose gear ground lock assembly (Ref 32-00-01).
K. Determine if electrical or hydraulic power is still required on airplane. If not, disconnect sources.
L. Lower airplane and remove jacks (Ref Chapter 7, Jacking Airplane).
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NOSE GEAR ACTUATOR - REMOVAL/INSTALLATION
1.  Equipment and Materials
A.  Gear Ground Lockpins (Ref 32-00-01)
B.  Tail Support Jack
C.  Grease,  MIL-G-21164 or MIL-G-23827 optional to BMS 3-33
D.  Naphtha, PD-680 or equivalent solvent
E.  Lockwire MS20995NC 32 (monel)
F.  Skydrol 500
G.  Variable volume test bench for Skydrol 500 hydraulic fluid capable of delivering 10 gpm at 3000 psi
2.  Remove Nose Gear Actuator (Fig. 401)
A.  Install gear ground lockpin on nose and each main landing gear (Ref 32-00-01).
B.  Depressurize hydraulic system A (Ref Chapter 29).
C.  If installed, remove bolt holding hydraulic down-line clamp (7) around nose gear actuator (8).
D.  Unscrew tubing nuts from union (6) and restrictor (19).
E.  Remove bolt (4) from terminal fitting (2) at top of actuator.
F.  Remove bolt (10) from actuating rod end (9) at bottom of actuator.
　
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