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Engine-Driven Hydraulic Pump Installation 531
29-11-32 Figure 401 (Sheet 1) Feb 15/73
Page 402
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.
532 Engine - Driven Hydraulic Pump Installation
Feb 20/90 Figure 401 (Sheet 2) 29-11-32
Page 403
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.
D. Disconnect pump electrical connector.
E. Disconnect hydraulic lines at engine disconnect panel.
F. Disconnect hydraulic lines from pump.
G. Remove QAD clamp and remove pump.
4. Prepare for Installation (Fig. 401)
A. Flush return line, supply line and pressure line below engine disconnect panel.
B. Lubricate O-ring s and threaded fittings with assembly lube or hydraulic fluid.
C. Install O-ring and reducer in supply line port.
D. Install O-ring and union in pressure, and return line ports.
E. On airplanes with shaft seal drain line,
(1)
Remove shaft seal drain plug from pump mounting flange and install O-ring and drain fitting in opening. Lockwire fitting.
(2)
Check that pump shaft seal drain line is clean. Flush line if necessary.
F. Fill pump with hydraulic fluid to remove air from pump.
532
29-11-32 Page 404 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. Feb 20/90
5. Install System Engine-Driven Hydraulic Pump (Fig. 401)
A. Install O-ring in pump mounting flange.
B. Apply grease to splines of pump shaft.
C. Engage pump shaft with engine drive shaft.
D. Install QAD clamp and tighten to torque specified on clamp.
E. Connect hydraulic lines to pump.
F. Connect hydraulic lines at engine disconnect panel.
(1)
Tighten case drain line 270 \\\ pound-inches.
(2)
Tighten pressure line 500 ±25 pound-inches.
(3)
Tighten supply line 1200 ±60 pound-inches.
G. Secure hydraulic lines to engine with clamps.
H. On airplanes with shaft seal drain line, connect shaft seal drain line to shaft seal drain fitting.
I. Connect electrical connector.
J. Connect air source to system A reservoir changing valve (Ref\29-09-300\MP [Pressurize System A Hydraulic Reservoir]).
K. Loosen hydraulic supply line at pump inlet and apply air pressure to reservoir charging valve. Bleed supply line until air is removed, then tighten supply line.
NOTE: Use suitable container to catch hydraulic fluid.
L. Remove air source from reservoir.
M. Pressurize hydraulic system A by motoring engine (Ref 71-09-100, Operating Procedure).
N. Check that hydraulic pressure stabilizes between 2900 and 3100 psi with flight control switches OFF and ground interconnect valve CLOSED.
P. Position engine pump switch to depressurize mode and allow system to bleed down.
Q. Position pump switch to normal and check that pressure stabilizes between 2900 and 3100 psi.
R. Shut down engine.
S. Check pump, lines and connections for leaks.
T. Close engine cowl.
584
Feb 20/90 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 29-11-32 Page 405
SYSTEM A ENGINE-DRIVEN HYDRAULIC PUMP - ADJUSTMENT/TEST
1. System A Engine-Driven Hydraulic Pump Test
A. General
(1) The following test procedure should be performed when the engine-driven hydraulic pump has been replaced or when the pump is suspected of malfunctioning. This test is typical for either engine pump.
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