TCH.1C-27J-2-29JG
2-17.2 INSTALLATION (refer to figure
(refer to figure
) , (refer to figure
)
and (refer to figure
10.Position the engine driven pump (56) on the gear box.
Torque tighten the supply flex hose nut to 470 thru
550 in lb (5.4 thru 6.3 m kg) (AGE NO. 00054).
11.Apply grease to engine driven pump shaft.
12.Install the engine driven pump (56) with new gasket
(24) on the engine gear box flange using six flat
washers (54) and six nuts (53). Tighten to 265 in lb
thru 300 in lb (3.1 m kg thru 3.5 m kg) (AGE NO.
00054).
13.Connect the clamps (21, 48, 24, 46, 35, 39, 43 and
44) using screws (19, 22, 37 and 41), flat washers
(20, 23, 38 and 42) and new self locking nuts (47, 40
and 45) (LCM NO. 00106).
14.Connect the plate (29) and the clamps (30, 36, 31 and
34) using screws (25 and 27), flat washers (26 and
28) and new self locking nuts (33 and 32) (LCM NO.
00106).
15.Connect the external electrical supply to the aircraft
(refer to manual
) .
16.Close the HYDRAULICS SOV ENG 1 (61DE) (1)
(HYDRAULICS SOV ENG 2 (34DE) (2)) circuit
breaker, located on the Overhead Circuit Breakers
Panel (271VE) in position B 1 (B 2).
(Cont'd)
29-10-15
2-117