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MAINTENANCE MANUAL
S 434-032
(2)
Install the new O-ring(s) on the check valve or the differential pressure indicator.
S 424-033
(3)
Install the check valve or the differential pressure indicator on the filter module.
S 434-034
(4)
Tighten the check valve or the differential pressure indicator to 50-75 pound-inches.
S 434-035
(5)
Safety the check valve or the differential pressure indicator with a lockwire.
H.
Put the Airplane Back to Its Usual Condition
S 864-036
(1)
Push the indicator button on the differential pressure indicator until it aligns with the adjacent surface.
S 864-037
(2)
Remove the DO-NOT-CLOSE tags and close these circuit breakers on the overhead panel, P11:
(a) 11D31, HYDRAULIC PTU CONT
S 864-038
(3)
Supply electrical power (AMM 24-22-00/201).
S 864-039
(4)
Pressurize the right hydraulic system (AMM 29-11-00/201).
S 864-040
(5)
Put the manual control switch for the PTU on the pilot's right side panel, P61, to the ON position.
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(6) S 794-042Make sure there are no leaks at the filter module.
(7) S 864-043Put the manual control switch for the PTU to the OFF position.
S 114-044
CAUTION: QUICKLY CLEAN THE INSTALLATION AREA OF ALL HYDRAULIC FLUID.
_______ HYDRAULIC FLUID CAN CAUSE DAMAGE TO THE AIRPLANE EQUIPMENT.
(8)
Clean all hydraulic fluid from the installation area (AMM 12-25-01/301).
S 614-045
(9)
Fill the reservoir in the left hydraulic system (AMM 12-12-01/301).
S 094-046 WARNING: USE THE PROCEDURE IN AMM 32-00-15/201 TO REMOVE THE DOOR LOCKS.
_______ THE DOORS OPEN AND CLOSE QUICKLY AND CAN CAUSE INJURY TO PERSONS OR DAMAGE TO EQUIPMENT.
(10)
Remove door locks from the landing gear doors and close the doors (AMM 32-00-15/201).
S 864-047
(11)
Remove hydraulic power if it is not necessary (AMM 29-11-00/201). S 864-048
(12)
Remove electrical power if it is not necessary (AMM 24-22-00/201).
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HYDRAULIC PRESSURE INDICATING SYSTEM - DESCRIPTION AND OPERATION
________________________________________________________________
1. General_______
A. A hydraulic pressure indicating system is provided for each main hydraulic system. This system provides indication of fluid pressure and low pressure warning for each hydraulic system. Low pressure warning lights are on the hydraulic control panel in the flight compartment. A pressure indicating light for the RAT is on the engine start/RAT control panel in the flight compartment. The EICAS display contains a digital readout of hydraulic system pressure. This display also provides low pressure warning messages. The pressure indicating system inputs to the EICAS computer are powered by 28 volts dc from circuit breakers on overhead panel P11. The low pressure warning lights are powered by 28 volts dc from master dim and test circuit breakers on panel P11.
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