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 B.  Leakage in the standby hydraulic system will be reflected in the loss of hydraulic fluid from System B hydraulic reservoir.
 C.  Leakage at the Power Transfer Unit pump and associated plumbing will be reflected in the loss of hydraulic fluid from system B reservoir. Leakage of the Power Transfer Unit motor and associated plumbing will be reflected in the loss of fluid from System A.
 D.  Illumination of any pump low pressure warning light during operation of a system and a confirmation of loss of pressure on the affected pump should be followed by a check of the corresponding pump pressure filter and case drain return filter. Contaminated filter elements indicate a defective pump. A pump need not be operated again following warning light illumination unless filter check shows no sign of contamination and trouble is suspected outside the pump. If additional information is required on the pump low pressure warning lights, refer to 29-34-01.
 E.  Transfer of hydraulic fluid between hydraulic systems A and B is caused by improper operation of system controls or worn equipment. See trouble shooting steps below for correct operation or replacment of parts.
 F.  When trouble shooting, it is not necessary to perform a check of both systems. Only the system (A or B) where the trouble is present needs to be checked. By feeling for hot tubing or actuators or listening for fluid leakage, faulty components can be isolated within a subsystem which has excessive internal leakage. Whenever possible, standard tools for detecting heat, vibration or sound should be used. Before checking for internal leakage by these methods, cycle the components to be checked to ensure that personnel will not be injured or equipment damaged when the component moves.
 G.  When trouble shooting, the hydraulic system should stabilize between 2800 and 3200 psi with flight control and spoiler switches ON and 2900 to 3200 with flight control and spoiler switches OFF.
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BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A
737-300/400/500MAINTENANCE MANUAL
 H.  If either engine No. 1 or 2 fire switches are positioned to FIRE with the corresponding engine-driven pump operating, proceed with the following steps:
 (1)  
If a supply shutoff valve was closed for less than 5 minutes, no maintenance is required and shutoff periods are not accumulative.

 (2)  
If supply shutoff valve was closed for longer than 5 minutes, ensure that pump has operated at least one minute with supply fluid available before checking filter elements so that metal contamination, possibly generated during fluid shutoff, has reached the filter.

 (a)  
Check case drain filter element for metal contamination (Ref 29-15-91, MP).

 (b)  
Check pressure filter for metal contamination (AMM 29-15-71/201).

 (c)  
If no metal is found in either filter, install new filters and continue to run pump. Recheck filters in 200 hrs.

 (d)  
If metal is found, remove applicable pump for overhaul and flush lines between the pump and filters (Ref I/C).

 

 2.  Prepare for Trouble Shooting____________________________
 A.  Service hydraulic reservoir(s) (AMM 12-12-00/301).
 NOTE: Standby system is serviced along with System B.
____
 B.  Pressurize hydraulic reservoir(s) (AMM 29-09-00/201).
 C.  Provide electrical power (AMM 24-22-00/201).
 D.  Check that parking brake is set.
 E.  When trouble shooting engine-driven pumps, pressurize system by operating or motoring engine (AMM 71-00-00/201).
 F.  When trouble shooting using an electric pump, position applicable ELEC hydraulic pump switch (P5) ON.
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 ALL  ú ú 02 Page 102 ú Nov 12/01
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A 737-300/400/500MAINTENANCE MANUAL
 3. Hydraulic System A or B Trouble Shooting Chart
______________________________________________
 NOTE: Hydraulic pump high and low pressure adjustments are made on a test
　
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