(2)
Connect air source to air bleed valve and open valve one to two turns.
(3)
Pressurize reservoirs 40 to 47 psi. Maintain constant pressure until test requirements are complete.
(4)
Remove air source, tighten air bleed valve body and install dust cap.
(5)
Lockwire air bleed valve.
C. Pressurize reservoirs with ground air charging (test) valve.
(1)
Gain access to charging valve on pressurization manifold in wheel well.
(2)
Remove dust cap and connect air source to connector.
NOTE: Check valve in charging valve will prevent loss of air while connection in being made.
(3)
Open air source. Pressure regulators will maintain system pressure until tests are complete.
(4)
Remove air source and install dust cap.
505
Jun 20/90 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 29-09-300 Page 201
3. Depressurize Hydraulic Reservoirs
A. Gain access to reservoir air bleed valve on air manifold in wheel well.
B. Hold container below bleed valve to catch trapped fluid.
C. Bleed air from system by removing cap from valve and loosening release nut one or two turns.
D. Tighten release nut on valve and reinstall cap.
E. Lockwire bleed valve.
4. Drain Air Manifold Sump Tube and Drain Fitting (Not on all airplanes)
A. Gain access to sump tube and drain fitting on air manifold in wheel well.
B. Ensure that engines are not operating and external air source is not connected to air manifold. Depressurize reservoir per Par. 3.
WARNING: DO NOT OPEN DRAIN FITTING IF AIR MANIFOLD IS PRESSURIZED. PERSONNEL INJURY COULD RESULT.
C. Hold container below drain fitting to catch drained water.
D. Remove cap from drain fitting and drain sump tube.
E. Invert drain cap and insert the raised portion of cap into opening now exposed in bottom of drain body. Press cap into drain body with hand pressure to open a spring-loaded seal and allow any collected liquid in the sump to exit.
F. Install cap.
510
29-09-300 Page 202 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. Oct 20/87
HYDRAULIC RESERVOIR PRESSURIZATION SYSTEM - ADJUSTMENT/TEST
1. General
A. This procedure is used to test the pressure regulator for proper operation and correct setting and to test for leakage along the lines and fittings from the engine bleed to the reservoir pressurization system. No adjustment is allowed on the regulator. A defective regulator should be replaced by a new regulator.
2. Equipment and Materials
A. Regulated source of high pressure nitrogen or clean, dry air, 0 to 200 psi
B. Pressure gage - 0- to 200-psi range (2 required)
C. Pneumatic shutoff valve (2 required)
3. Test Air Pressure Regulator
A. Depressurize hydraulic reservoirs (Ref 29-09-300 MP).
B. On airplanes with sump tube and drain fitting, remove sump drain cap and install blanking cap to seal opening.
C. On No. 1 engine-to-wing fairing area, open access panel No. 5226 on outboard side of fairing.
D. Disconnect reservoir pressurization engine bleed line hose from fitting and connect a nitrogen or dry air source to reservoir side of fitting together with a 200-psi gage and shutoff valve.
E. On No. 2 engine-to-wing fairing area, open access panel No. 5126 on outboard side of fairing.
590
Jun 20/90 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 29-09-300 Page 501
F86149
Hydraulic Reservoir Pressurization System Test 536
29-09-300 Figure 401 Jun 20/93
Page 502
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.
F. Disconnect reservoir pressurization engine bleed line hose and connect a 200-psi test gage to reservoir side of fitting.
G. Slowly pressurize engine No. 1 line to 200 psi. Close shutoff valve at source and check that reservoir pressure stabilizes between 40-47 psi.
H. Decrease pressure to zero psi.
I. Disconnect and cap inlet tube to air pressure regulator.
J. Slowly increase pressure to 200 psi and close shutoff valve. Check that pressure in No. 1 engine bleed air line does not drop more than 5 psi over a 5-minute period. Check that check valve in No. 2 engine bleed line does not leak.
中國航空網 www.k6050.com
航空翻譯 www.aviation.cn
本文鏈接地址：737 AMM 飛機維護手冊 液壓 HYDRAULIC POWER(31)
