(a) Tighten the screws to 50-75 pound-inches (5.6-8.4 newton meters).
SUBTASK 72-31-00-945-027-G00
(6) Remove the protective mats from the internal inlet cowl.
M. Do a check of the correction for the imbalance of the engine (Run number 3).
SUBTASK 72-31-00-865-032-G00
(1) Do the steps in the Operate the Engine paragraph.
NOTE: Operate the engine at the same N1 speed (rpm) that was used for the initial engine
run.
SUBTASK 72-31-00-865-037-G00
(2) Look at the engine vibration indication on the lower EICAS display.
(a) The guideline is 2.5 units (on the display). No sudden changes of 1.0 units or more are
permitted (PAGEBLOCK 71-00-00/201).
(b) If the vibration amplitude is less than the guideline, the trim balance procedure is
complete.
1) Do the steps to put the Airplane Back to its Usual Condition.
(c) If the vibration is more than the guideline, continue with the procedure.
SUBTASK 72-31-00-975-034-G00
(3) Repeat the steps (that you used to find W2) to Find the Balance Correction Weight for W3.
NOTE: Always use the initial run data (Uo and Ao) when you make a plot with the latest run
data (Ux and Ax).
SUBTASK 72-31-00-435-035-G00
(4) Repeat the steps to Install the correction balance screws.
SUBTASK 72-31-00-975-036-G00
(5) Repeat the steps to do a check of the corection for the imbalance of the engine.
SUBTASK 72-31-00-725-009-G00
(6) If this procedure cannot balance the engine, do the Low Pressure Turbine (LPT) Trim Balance
Procedure (PAGEBLOCK 72-52-00/501).
N. Put the Airplane Back to Its Usual Condition
SUBTASK 72-31-00-015-017-G00
(1) Open the fan cowl panels (PAGEBLOCK 71-11-04/201).
SUBTASK 72-31-00-015-019-G00
(2) Open the core cowl panels (PAGEBLOCK 71-11-06/201).
SUBTASK 72-31-00-435-037-G00
(3) Disconnect the wires from the accelerometer and the N1 speed sensors.
SUBTASK 72-31-00-435-038-G00
(4) Remove the wires from the engine.
SUBTASK 72-31-00-425-039-G00
WARNING
PUT THE ACCESS PANEL TO THE HEAT EXCHANGER IN ITS POSITION. IF
IT IS MISSING, INJURY TO PERSONS OR DAMAGE TO THE ENGINE COULD
OCCUR.
(5) Install the access panel on the aft firewall of the accessory compartment.
767
AIRCRAFT MAINTENANCE MANUAL
CF6-80A SERIES ENGINES
72-31-00
NoC
Page 507
D633T1B7 Aug 22/2017
ECCN 9E991 BOEING PROPRIETARY - Copyright © Unpublished Work - See title page for details
EFFECTIVITY
ABX 001-007, 011, 012, 016-019, 021, 022, 025, 101,
109, 114, 115, 314-999
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