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B.  The airplane system may be used for a straight retraction test after replacement of hydraulic components. Gear operating times will be normal if gears are retracted two at a time when the airplane hydraulic system B is used.
C.  Procedure is for main gear only. Nose gear extension/retraction is accomplished separately (Ref 32-33-0 A/T).
D.  The times for gear retraction in the operational test depend on the hydraulic flow rate.  The retraction times given in this procedure are based on a minimum flowrate of 19 gpm at a hydraulic system pressure of 3000 +/-150 psi.  Hydraulic pressure can be supplied by a hydraulic test bench or the engine driven pumps to give this minimum flow rate.
E.  The electric motor driven pump (EMDP) can be used for the component replacement test.  When you use the EMDP, operate only one landing gear at a time.  The EMDP provides a hydraulic flow rate of approximately 6 gpm.  This lower rate causes slower landing gear operation, especially if you operate more than one gear at the same time.  Do not use the EMDP to measure extension/retraction times.
2.  Equipment and Materials
A.  One variable volume test bench for hydraulic fluid. Capacity 20 gallons per minute at 3000 psi. Pressure adjustable from 0 to 3000 psi. Test bench filters must be capable of a nominal filtration of 5 micron and of 15 micron absolute.
B.  Stop watch
C.  Ground Lock Assemblies (Ref 32-00-01)
3.  Prepare to Test Extension and Retraction
A.  Jack airplane for gear retraction (Ref Chapter 7, Jacking Airplane).
B.  Ground the airplane (Ref 20-40-11 Static Grounding).
C.  Set trailing edge flap control valve out of null by opening both standby pump circuit breakers, setting flap master switch to ARM, and setting flap lever at the 30-detent position.
D.  Close both flight control and spoiler shutoff valves.
E.  Connect external electrical power.
Sep 01/02 32-32-0 Page 501 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.

F.  Remove ground lock assemblies from main gear (Ref 32-00-01).
G.  Check that landing gear is fully extended and locked with control level in OFF position.
CAUTION:  DO NOT TURN STEERING WHEEL WITH NOSE GEAR SHOCK STRUT FULLY EXTENDED. CENTERING CAMS IN SHOCK STRUT MAY BE DAMAGED.
H.  Pressurize hydraulic system A (Ref 29-11-0 MP).
I.  Advance both throttles to a position greater than 17 degrees.
J.  Close and latch main landing gear tire burst screens.
WARNING:  FAILURE TO CLOSE AND LATCH TIRE BURST SCREEN WILL DAMAGE EQUIPMENT AND MAY INJURE PERSONNEL.
4.  Test Main Landing Gear Extension and Retraction
A.  Place landing gear control lever in UP position and note gear retraction time.
WARNING:  RAPID ACTION OF GEAR AND DOORS MAY INJURE PERSONNEL OR DAMAGE EQUIPMENT.
B.  Check that main gears are up and locked and doors closed within 8.5 seconds from time control handle enters UP detent until landing gear red warning lights go off.
C.  Check that all gear lights are off.
D.  Place control lever in OFF position for 15 seconds then move to DN position.
E.  Check that main gear are fully extended and locked within 7.5 seconds from time the control lever enters DN detent until gear green indicator lights come on.
5.  Restore Airplane To Normal
A.  Depressurize hydraulic system A (Ref 29-11-0 MP).
B.  Install main gear ground lock assemblies (Ref 32-00-01).
C.  Determine if electrical power, hydraulic or pneumatic supply is still required. If not, disconnect source.
D.  Lower airplane and remove jacks (Ref Chapter 7, Jacking Airplane).
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MAIN GEAR ACTUATOR ASSEMBLY - REMOVAL/INSTALLATION
1. General
A.  The main gear actuator assembly includes actuator, actuator walking beam, and beam hanger. The entire assembly must be removed to change any individual component.
2.  Equipment and Materials
A.  Ground Lock Assembly - F72735 (Ref 32-00-01)
B.  Grease - Aero Shell 07 (Ref 20-30-21)
C.  Corrosion Inhibitor - Mastinox 6856K (Ref 20-30-21)
D.  Primer - BMS 10-11, Type I
3.  Prepare to Remove Main Gear Actuator Assembly
A.  Check that landing gear ground lock assemblies are installed in all gear and depressurize hydraulic system (Ref 32-00-01).
B.  Remove hydraulic access panels 8401 left or 8501 right.
C.  Disconnect outer wing door pushrod (10, Fig. 401) from trunnion link (9).
D.  Disconnect bonding cable (11) from structure.
　
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