(3) Put the cross beam between the engine and the pylon and let it on the engine case.
F 『 EEFF : ALL E Page 42071-22-11
E E Aug 01/05 E E ECES E
F 『
E C F M E
E E
E 56-5B E
E E
(4) Install the pins into the lateral link ends, turbine case side.
(Ref. Fig. 401/TASK 71-22-11-991-300)
(a) Put the bushing (45), shoulder bushing (80), and bushing (25) on the engine.
(b) Install the shear pin (15), anti-rotation bracket (40), and bracket (20) to the engine flange.
(c) Put the shear bolt (10) into the shear pin (15).
(5) Lift the cross beam.
(Ref. Fig. 404/TASK 71-22-11-991-304)
(a) Lift the cross beam parallel to the pylon attach fitting, engage the alignment pins (280).
(b) Hold the cross beam and turn the lateral links (150) and install the anti-rotation brackets (100) on the pins (90) engage the pins into the link ends.
(c) Install the bolts (80), and retaining pins (70).
(6) Install the pin into the center link end, turbine case side.
(Ref. Fig. 401/TASK 71-22-11-991-300)
CAUTION : INSTALL THE BUSHING (80) WITH ITS SHOULDER AT THE INTERIOR
_______
OF THE ENGINE RANGE.
(a) Put the bushing (45), shoulder bushing (80), and bushing (25) on the engine.
(b) Install the shear pin (15), anti-rotation bracket (40), and bracket (20) to the engine flange.
(c) Put the shear bolt (10) into the shear pin (15).
(7) Install the pin into the center link end, cross beam side.
(Ref. Fig. 404/TASK 71-22-11-991-304)
(a) Install the anti-rotation brackets (100), pins (90), bolts (80), and retaining pins (70).
(8) Simulteanously remove slack in the aft cables so as to have the cross beam touch the pylon attach fitting. To get this apply a 400 daN (900 lbf) force.
F 『 EEFF : ALL E Page 42171-22-11
E E Feb 01/98 E E ECES E
F 『
E C F M E
E E
E 56-5B E
E E
(9) Install the cross beam and pylon attach fittings.
(Ref. Fig. 403/TASK 71-22-11-991-303)
CAUTION : INSTALL THE BARREL NUT WITH THE ROUNDED SIDE UP. IF NOT,
_______
DAMAGE TO THE NUT CAN OCCUR.
(a) Install the nuts (155) with the retainer (150) on the aft engine mount holes, the bolts (135) and the washers (140).
R (b) TORQUE the aft mount bolts (135) to between 480 and 580 lbf.ft
R (65.07 and 78.63 m.daN) and safety with lockwire 0.032 in. (0.8
R mm) dia (Material No. CP8001), or safety cable 0.032 in. (0.8 mm)
R dia. (Material No. CP8006).
(10) Torque and safety pins of the three links end, turbine case side (Ref. Fig. 401/TASK 71-22-11-991-300)
(a) Install the slotted spanner.
CAUTION : USE OF THE SPANNER WRENCHES AS A TORQUE WRENCH ADAPTOR
_______ WILL CHANGE THE TORQUE VALUE WHICH IS REALLY APPLIED.
NOTE : To find the correct TORQUE value when spanner wrenches are
____ used refer to the formula in standard practices (Ref. TASK 20-21-11-911-001).
1 Install the slotted spanner nuts (75) on shear pin (15).
_ TORQUE the nut (75) to 80 lbf.ft (10.84 m.daN) minimum. Use a WRENCH SET - AFT ENGINE MOUNT (98D71203004000) to adapt the torque wrench to the spanner nut (75).
NOTE : Install the nut (75) with the counter bore side turned
____ to the shear pin (15).
(b) Install the slotted spanner nut (65) on the shear bolt (10). TORQUE the nut (65) to 35 lbf.ft (4.74 m.daN) minimum. Use WRENCH SET - AFT ENGINE MOUNT (RSE1098-1) to adapt the torque wrench to the spanner nut (65).
NOTE : It is recommended that you position the flat side of the
____
nut (65) forward.
(c) Install the outer retainers (60) and (70) on the bracket (40) with washers (35) below bolts (30) and washers (50) below nuts (55).
F 『 EEFF : ALL E Page 42271-22-11
E E May 01/01 E E ECES E E 56-5B E E E
F 『
E C F M E
E E
(d) If the holes in the anti-rotation bracket (40) do not line up with holes in brackets (60) and (70), increase the torque on nuts
(65) and (75) as necessary to line up the holes. Do not TORQUE nut (75) more than to 95 lbf.ft (12.88 m.daN) or nut (65) more than to 42 lbf.ft (5.69 m.daN).
(e) TORQUE the nuts (55) to between 24 and 27 lbf.in (0.27 and 0.30 m.daN).
(f) Install the retaining pin (5) through the shear pin (15).
(11) Torque and safety pins of the three links end, cross beam side.
中國航空網 www.k6050.com
航空翻譯 www.aviation.cn
本文鏈接地址：A320飛機維護手冊 AMM 動力裝置 POWER PLANT 2(6)
