747-400 AMM 飞机维护手册 发动机 ENGINE 1(117)

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 h) Make a record of the part number and tang location of all counterweights.
 NOTE: After the fan is indexed, the tang at the____ 12 o'clock position is the No. 1 tang. The tangs are numbered 1 through 19 in the clockwise direction.
 5)  Input their weight (PBS class number) and location (tang number) into the PBS-4100 computer.
 NOTE: The PBS class number must be input as a negative____ (-) number.
 6) 7) 8)  Remove all of the counterweights on the fan.Install the inlet cone (AMM 72-31-01/401).Do a Check Run as given later in this procedure.

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BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
////////////////////////A / PW4000 SERIES /747-400 / ENGINES/MAINTENANCE MANUAL ////////////////////////
(i) If counterweights are not installed, do these steps:
 1)  Install counter-weights No. 1 (CW1) trial weights to the
 fan balance ring (See Table 503 and Figure 503).

 NOTE: Use assembled phase angle and sensitivity data
____
 to find the CW1 trial weight location.

 2) Temporarily install the correction weights in the fan with cotter pins (See Table 501). 3) If necessary, install correction weights in the turbine by one of these two methods (See Table 502 and Figure 505):
 NOTE: Low turbine plane counterweights are installed
____
 to the 6th-stage turbine blades.

 There are 128 6th-stage turbine blades. With the fan indexed, the No. 1 turbine will be the blade at 12 o'clock position. The blades are numbered 1 through 128 in the clockwise direction.
 A clip-on counterweight (50N401) is provided for the LPT 6th-stage blade shroud. Use as necessary with a maximum number of 10 clip-on weights per engine.
 a)  Attach the counterweights with a PWA 86302 Hydraulic Bender and a PWA 76855 Hydraulic Pump.
 CAUTION: DO NOT BEND THE COUNTER-WEIGHT TABS WHEN YOU HOLD
_______ THE COUNTER-WEIGHT IN THE MECHANICAL BENDER. IF YOU BEND THE TABS, YOU WILL NOT BE ABLE TO INSTALL THE COUNTERWEIGHT ON THE 6TH-STAGE TURBINE BLADE.
 b)  Attach the counter-weights with a PWS 102335 Mechanical Bender:
 1.  
Put the counter-weight on the counter-weight holder

_ of the PWA 102335 Mechanical Bender.

 2.  
Operate the quick grip handle to lightly hold the

_ counter-weight. Do not squeeze the quick grip handle too much so that you bend the counter-weight tabs.

 3.
Put the PWA 102335 Mechanical Bender with the

_ counter-weight on the airfoil section of the designated 6th-stage turbine blade(s).

 4.
With the counter-weight still installed in the

_ bender, slide the counter-weight along the airfoil onto the blade outer shroud.
 NOTE: Make sure the counter-weight hook goes
____ around the leading edge of the blade.
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BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
5.
To attach the counter-weight to the blade, operate

_ the quick grip handle until it hits the bar stop to bend the tab.

 6.
Release the quick grip handle and remove the PWA

_
 102335 Mechanical Bender from the engine. 4) Install the inlet cone (AMM 72-31-01/401). 5) Do a Check Run as given later in this procedure.
 ~............................................................................... | TABLE 501 | | TRIM BALANCE COUNTERWEIGHTS FOR THE FAN PLANE | ................................................................................. |CLS| CNTRWGHT PN 534493 |CNTRWGHT PN 534495 | CNTRWGHT PN 1B4294 | ................................................................................. | 1 |2.0 oz.in (1440 g.mm)|4.9 oz-in (3528 g.mm) | 12.8 oz-in (9216 g.mm) | ................................................................................. | 2 |2.4 oz.in (1728 g.mm)|5.3 oz-in (3816 g.mm) | | ................................................................................. | 3 |2.8 oz.in (2016 g.mm)|5.7 oz-in (4104 g.mm) | | ................................................................................. | 4 | |6.1 oz-in (4392 g.mm) | | ................................................................................. | 5 | |6.5 oz-in (4680 g.mm) | | 2...….....................…......................…..............................1
　
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