(2)
Depressurize system B (Ref 29-12-0).
(3)
Depressurize all hydraulic system reservoirs (Ref 29-09-300).
(4)
Drain A, B, and standby reservoirs
(5)
Disconnect and drain suction, pressure, and case return lines at both engine-driven hydraulic pumps by disconnecting the hoses at pumps. Plug or cap open ports and lines.
(6)
Jack airplane for retraction (Ref Chapter 7, Jacking Airplane).
(7)
Using one of the following steps, provide fluid flow path to the waste container.
(a)
Disconnect return hoses from system A and B reservoirs. Lengthen as necessary and route hoses to empty containers.
(b)
Disconnect a pump supply hose from a system B pump and lengthen this hose as necessary to reach the waste container.
(c)
Disconnect a system B pump supply hose at the disconnect on the reservoir and connect a suitable length hose from disconnect on reservoir to waste container.
(8)
Connect hydraulic ground test bench to No. 1 engine driven hydraulic pump pressure line. Operate any flight control until approximately 2 gallons of fluid have been flushed into container.
(9)
Connect test bench to No. 1 engine pump case drain line. Operate test bench until approximately 2 gallons of fluid have been flushed into container.
(10)
Repeat steps (8) and (9) for No. 2 engine pump lines.
(11)
Using one of the following steps, provide hydraulic fluid source.
(a)
To connect ground test bench pressure source, disconnect pressure hose from No. 1 or 2 system B pump. Lengthen as necessary and route to outlet of ground test bench. Route inlet of ground test bench into barrel of new oil.
(b)
To use system B pumps as pressure source, disconnect both system B pump supply hoses at the reservoir disconnects and then lengthen hoses as required to reach into the barrel of new oil.
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Nov 01/74 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 29-00 Page 201
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29-00 Page 202 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. Feb 01/75
CAUTION: DO NOT OPERATE SYSTEM B PUMPS MORE THAN 2 MINUTES UNLESS THE NO. 2 FUEL TANK CONTAINS AT LEAST 250 GALLONS OF FUEL. IF PUMPS ARE OPERATED 2 MINUTES WITHOUT FUEL IN TANK, ALLOW RESERVOIR TO RETURN TO AMBIENT TEMPERATURE BEFORE RESUMING TEST.
(12)
If test bench is used as fluid source, flush system B pump pressure and case drain lines by connecting test bench to each line and operating until approximately 2 gallons of fluid has been flushed from each line into container.
(13)
Provide electrical power and check that the following circuit breakers are closed:
(a)
All flight control circuit breakers
(b)
Hydraulic System B circuit breakers (if system B pumps are being used as pressure source)
(c)
Standby System circuit breakers
(14)
On the forward overhead panel, check that FLT CONTROL A and B switches are in the OFF position.
(15)
Open ground interconnect valve circuit breaker, then manually open valve. Energize fluid source. Perform the following operations in sequence to assure complete changing of fluid.
WARNING: ENSURE THAT ALL PERSONNEL AND MAINTENANCE EQUIPMENT ARE CLEAR OF ALL FLIGHT CONTROLS BEFORE OPERATION TO PREVENT INJURY TO PERSONNEL AND DAMAGE TO THE AIRPLANE.
(16)
Retract and extend main and nose gear through two full cycles (Ref Chapter 32, Landing Gear).
(17)
Shut off fluid source.
(18)
Remove airplane from jacks (Ref Chapter 7, Jacking Airplane).
(19)
Turn on fluid source.
(20)
Cycle nose wheel steering through two full cycles. Refer to Chapter 32, Landing Gear.
(21)
Position FLT CONTROL A and B and SPOILER A and B switches to ON.
(22)
Operate elevators through seven full stroke cycles from DOWN to UP to DOWN. Return control column to normal position.
(23)
Operate rudders through two full stroke cycles from LEFT to RIGHT to LEFT. Return rudder pedal to normal.
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