(3)
Install upper mounting bolt with head aft. Place washer under bolt head, under nut and either side of module. Tighten nut finger-tight and install new cotter pin.
C. Position module in airplane and install upper and lower mounting bolts with heads forward and a washer under each nut.
D. Install center mounting bolt with head aft. Place filler and spacer between module and structure and install washer under nut.
E. Remove protective caps and plugs from module and hydraulic lines. Be prepared to catch spilled fluid.
F. Lubricate fittings with assembly lube or hydraulic fluid. Attach eight hydraulic lines to module.
G. Provide elevator systems A and B hydraulic power. Refer to 27-31-0.
H. Exercise control column and rudder pedals to bleed hydraulic lines.
I. Visually check hydraulic connections to module for signs of leakage.
J. Test module. Refer to Isolation Valves Hydraulic Module - Adjustment/Test.
6. Restore Airplane to Normal Configuration
A. Restore airplane to normal hydraulic configuration. Refer to 27-31-0.
B. Close aft compartment access door.
C. Service hydraulic reservoirs, if required. Refer to Chapter 12, Hydraulic Servicing.
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Feb 15/73 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 27-31-201 Page 403
ISOLATION VALVES HYDRAULIC MODULE - ADJUSTMENT/TEST
1. Hydraulic Module Test
A. General
(1) The following procedure provides instructions for testing the six manual isolation valves. If testing the module, perform the entire test. If testing an individual valve, perform the steps applicable to that valve only.
B. Equipment and Materials
(1) Scale - 0 to 6 inches, graduated in tenths and hundredths of an inch
C. Prepare for Test
(1)
Provide elevator systems A and B hydraulic power (Ref 27-31-0 MP).
(2)
Open aft compartment access door 3701 and remove tail cone access panel 3802 (Ref Chapter 12, Access Doors and Panels).
(3)
Remove lower mounting bolt securing locking bar to module. Pivot locking bar upward to gain access to valve handles.
D. Test Hydraulic Module
(1)
Close isolation valve No. 1 (Fig. 501).
(2)
Close isolation valve No. 4.
(3)
Open isolation valve No. 1. Check that feel actuator body moves forward 1.0 to 1.73 inches.
NOTE: Feel actuator body movement may, at times, take 10 to 15 minutes to occur during this test.
504
Oct 20/88 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 27-31-201 Page 501
G25978
Isolation Valves Hydraulic Module Test 500
27-31-201 Figure 501 Aug 15/72
Page 502
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.
(4)
Close isolation valve No. 1.
(5)
Open isolation valve No. 4. Check that feel actuator body moves aft 1.0 to 1.73 inches.
(6)
Open isolation valve No. 1.
(7)
Rotate control columns aft until stops are contacted and hold or tie in this position.
(8)
Close isolation valve No. 3. Check that left elevator tab moves down.
(9)
Open isolation valve No. 3. Check that left tab moves up to fair with left elevator.
(10)
Close isolation valve No. 6. Check that right elevator tab moves down.
(11)
Open isolation valve No. 6. Check that right tab moves up to fair with right elevator.
(12)
Test isolation valve No. 2.
NOTE: Isolation valve No. 2 supplies hydraulic system A power to rudder.
(a)
Position flight controls hydraulic system B switch to OFF and system A switch to ON.
(b)
Close isolation valves No. 2 and 5.
(c)
Cycle rudder pedals and check rudder is not powered.
NOTE: Non-hydraulically powered rudder will move.
(d)
Open isolation valve No. 2.
(e)
Move rudder pedals and check rudder is powered.
(f)
Open isolation valve No. 5.
(13) Test isolation valve No. 5.
NOTE: Isolation valve No. 5 supplies hydraulic system B power to rudder.
(a)
Position flight controls hydraulic system A switch to OFF and system B switch to ON.
(b)
Close isolation valves No. 2 and 5.
(c)
Move rudder pedals and check that rudder does not move.
(d)
Open isolation valve No. 5.
(e)
Move rudder pedals and check that rudder is powered.
(f)
Open isolation valve No. 2.
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