(4)
If the voltage between pin 1 and 2 of connector D10070 is out of this range, do the steps that follow:
(a)
Manually hold the main rudder PCU upper control rod at location A (Fig. 611) and pull aft with a force of approximately 30 lbs to 40 lbs until it touches the stop and hold.
(b)
Verify the voltage between pin 1 and pin 2 of connector D10070 on the E2 shelf is between 2.37 VDC to 3.13 VDC.
(c)
Release the main rudder PCU control rod.
(5)
If the voltage between pin 1 and pin 2 of connector D10070 on the E2 shelf is within the range, then continue with the next step.
(6)
Push the DOWN key on the YDC keypad.
(a) Make sure the display shows the following:
1) OFF (Where XXXX is a number)
(7)
Verify the voltage between pin 1 and pin 2 of connector D10070 on the E2 shelf
(stanchion station 351) is less than 1.87 VDC.
(8)
If the voltage between pin 1 and 2 of connector D10070 is out of this range, do the steps that follow:
(a)
Manually hold the main rudder PCU upper control rod at location A (Fig. 611) and pull aft with a force of approximately 30 lbs to 40 lbs until it touches the stop and hold.
(b)
Verify the voltage between pin 1 and pin 2 of connector D10070 on the E2 shelf is less than 1.87 VDC.
(c)
Release the main rudder PCU control rod.
(9)
If the voltage between pin 1 and pin 2 of connector D10070 on the E2 shelf is within the range, then continue with the next step.
(10)
Release the right rudder pedal.
XXXX psi (IGNORE THE NUMBER FOR THIS TEST) NOTE: You have completed the test of system A in the retract direction.
597
29-00 Page 638 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. May 01/03
I. Put the Airplane Back to Its Usual Condition
(1)
Release the pressure from the rudder hydraulic system (AMM 27-21-0/201).
(2)
If electrical power is not needed, remove electrical power (AMM 24-22-0/201).
(3)
Close the trailing edge access door, 9510.
(4)
Close the access panels 9512 and 9514.
(5)
Close the electrical equipment compartment access door 1201.
(6)
Put the FLT CONTROL A and B switches, on the P5-3 panel, to the ON position.
597
May 01/03 29-00 Page 639
EFFECTIVITY
AIRPLANES WITH THE ENHANCED RUDDER CONTROL SYSTEM (RSEP) (POST-SB 27-1252)
W26796
Main Rudder PCU Internal Leakage Test 597
29-00 Figure 611 May 01/03
Page 640
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.
HYDRAULIC FLUID - INSPECTION/CHECK
1. General
A. The operational environment of the hydraulic fluid will affect the service life of the fluid. A sample of the fluid should be removed from the airplane at intervals in accordance with the operator's experience and analyzed for the fluid properties shown in Fig. 601. If the fluid properties exceed any one of the fluid in service limits, an amount of fluid should be replaced in order to bring the fluid properties within service limits. The amount of fluid replaced is left to the discretion of the operator.
2. Hydraulic Fluid Sampling Procedure
A. General
(1)
The following is the recommended procedure for obtaining hydraulic fluid samples. Fluid samples must be taken in bottles cleaned per the following procedure or fluid samples may be invalid.
(2)
Duplicate fluid samples should be obtained from each test source selected. One sample from each source should be obtained in a 1- pint polyethylene bottle and the other should be in a 1- or 2- oz glass bottle.
B. Equipment and Materials
(1)
Polyethylene bottle with polyethylene sealed screw cap - 1-pint capacity
(2)
Glass bottle with polyethylene sealed screw cap - 1- or 2-ounce capacity
(3)
Isopropyl alcohol - approximately 1 pint
(4)
Petroleum ether - approximately 1 pint
(5)
Distilled deionized water - approximately 1 pint
(6)
Millipore NR filter and Trichloroethylene or the solvent
(7)
Filter - Gelman Type GA-6 Membrane, or equivalent
(8)
Clean polyethylene bags for storing bottles
(9)
Nitric acid 20% by volume - approximately 1 pint
502
Feb 15/77 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 29-09-111 Page 601
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