A
757
MAINTENANCE MANUAL
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PW2000 SERIES
/
/
/
ENGINES
////////////////////////
International Lease Finance Corporation
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DATE
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¦71-00-00
CONT.
¦71-00-00
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¦CHAPTER 71 TAB
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JUN 20/97
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MAY 20/98
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¦POWER PLANT
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¦EFFECTIVE PAGES
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¦SEE LAST PAGE OF LIST FOR
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R = REVISED, A = ADDED OR D = DELETED
F = FOLDOUT PAGE
23
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D633N123
CHAPTER
71
EFFECTIVE PAGES
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PAGE
1
CONTINUED
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A
757
MAINTENANCE MANUAL
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/
PW2000 SERIES
/
/
/
ENGINES
////////////////////////
International Lease Finance Corporation
~¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼ ¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼ ¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼
¦ PAGE
DATE
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DATE
CODE
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¦71-00-00
CONT.
¦71-00-00
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¦71-00-00
CONT.
¦
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DELETED
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JUN 20/91
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MAY 28/03
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JUN 20/91
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R = REVISED, A = ADDED OR D = DELETED
F = FOLDOUT PAGE
23
SEP 28/03
D633N123
CHAPTER
71
EFFECTIVE PAGES
P
PAGE
2
CONTINUED
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A
757
MAINTENANCE MANUAL
////////////////////////
/
PW2000 SERIES
/
/
/
ENGINES
////////////////////////
International Lease Finance Corporation
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CONT.
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CONT.
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F = FOLDOUT PAGE
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International Lease Finance Corporation
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F = FOLDOUT PAGE
23
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A
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MAINTENANCE MANUAL
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ENGINES
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International Lease Finance Corporation
~¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼ ¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼ ¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼
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R = REVISED, A = ADDED OR D = DELETED
F = FOLDOUT PAGE
23
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LAST PAGE
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
////////////////////////
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ENGINES
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A
757
MAINTENANCE MANUAL
CHAPTER 71 - POWER PLANT
TABLE OF CONTENTS
_________________
Chapter
Section
Subject
_______
Subject
_______
___________
POWER
PLANT
Description and Operation
General
Component Details
Cowling
Drains
Engine Mounts
Power Plant
Page
____
Effectivity
___________
71-00-00
1
1
1
2
3
2
1
ALL
71-CONTENTS
PILF
Page 1
Dec 20/96
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
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A
757
MAINTENANCE MANUAL
CHAPTER 71 - POWER PLANT
TABLE OF CONTENTS
_________________
Chapter
Section
Subject
_______
Subject
_______
Maintenance Practices
Engine Ground Safety Precautions
Air Intake
Airplane Skidding Prevention
for High Power Operation
Engine Cool Down
Engine Ignition
Engine Noise
Exhaust Characteristics
Fuel and Lubricating Oils
General
X-Rays
Power Plant Operation (Cold
Weather)
Power Plant Operation
(Dry-Motor)
Power Plant Operation (Normal)
Power Plant Operation
(Wet-Motor)
Power Plant Operation Limits
Cowling Limits
Electronic Engine Control
Limits
Engine Operation Limits
Ignition Ground Use Limits
Leakage Limits
Oil Consumption Limits
Overspeed Limits
Overtemperature Limits and
Inspection Requirements
Precautionary Procedures
Start Procedure After An
Emergency Engine Shutdown
Starter Operation Limits
Thrust Reverser Guidelines
Vibration Guidelines
Page
____
201
202
205
202
Effectivity
___________
ALL
211
212
212
211
214
202
214
269
259
241
264
215
238
239
216
227
227
228
219
221
230
239
215
236
227
71-CONTENTS
PILF
Page 2
May 28/01
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A
757
MAINTENANCE MANUAL
CHAPTER 71 - POWER PLANT
TABLE OF CONTENTS
_________________
Chapter
Section
Subject
_______
Subject
_______
Adjustment/Test
Power Plant Test Reference Table
System Test - Power Plant
Test No. 1 - Engine-Driven
(Hydraulic) Pump (EDP) Test
Test No. 10 - Replacement Engine
Test (Untested)
Test No. 11 - Oil Pressure Test
Test No. 12 - Replacement Engine
Test (Pretested)
Test No. 13 - Intercompressor
2.5 Bleed Actuator Test
Test No. 14 - Stator Vane
Actuator Test
Test No. 15 - Fuel Control
Replacement Test
Test No. 16 - Not Used
Test No. 17 - Thrust Lever Angle
(TLA) Resolver Test
Test No. 18 - Low Pressure Rotor
Trim Balance
Test No. 18A - Engine Trim
Balance With The Universal AVM
Test No. 19 - PT2 System Leak
Test
Test No. 2 - Engine Motoring
(Dry) Leak Test
Test No. 2A - Engine Motoring
(Wet) Leak Test
Test No. 20 - Static Leak Test
Test No. 3 - Minimum Idle Test
Test No. 3A - Idle Leak Test for
the Oil and Fuel Systems
Test No. 4 - Integrated Drive
Generator (IDG) Test
Test No. 5 - Main Gearbox
Replacement Test
Test No. 6 - 14th-Stage Bleed
System Test
Test No. 7 - Electronic Engine
Control (EEC) Static Test
Test No. 8 - Vibration Survey
Test No. 9 - Performance Test
Page
____
501
502
507
512
Effectivity
___________
ALL
580J
582A
582F
582S
582V
582Z
584C
584D
584F
586I
588
515
517
588E
519
520
524
528
546
550
551
555
71-CONTENTS
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MAINTENANCE MANUAL
CHAPTER 71 - POWER PLANT
TABLE OF CONTENTS
_________________
Chapter
Section
Subject
_______
Subject
_______
ú
Inspection/Check
POWER PLANT
Maintenance Practices
Engine Depreservation
Engine Preservation
POWER PLANT
Removal/Installation
POWER PLANT (ACOUSTIC PANEL)
Maintenance Practices
Acoustic Panel Lining Repair
Limits
POWER PLANT (ENGINE
INTERMIX/SUBSTITUTION)
Maintenance Practices
Replace One or Two PW2040
Engines with PW2037 Engines
Replace One PW2037 Engine
With One PW2037(M) Engine
Replace One PW2037(M) Engine
With One PW2037 Engine
Replace PW2037 Engines with
PW2040 Engines
POWER PLANT
POWER PLANT (TRIM CHECK TABLES)
Maintenance Practices
[*] PW2040 ENGINES
ú
Effectivity
___________
601
ALL
201
210
201
ALL
401
ALL
201
201
ALL
201
201
ALL
71-00-03
71-00-02
71-00-04
71-00-07
211
208
205
71-01-00
71-01-02
Maintenance Practices
[*] PW2037/PW2037(M) ENGINES
_______
COWLING
ENGINE COWLING
Description and Operation
General
Component Details
Core Cowl Panels
Fan Cowl Panels
Fan Duct Cowl and Thrust
Reverser
Inlet Cowl
Operation
Functional Description
Page
____
201
CONFIG
1 [*]
201
CONFIG
2 [*]
71-10-00
71-11-00
1
1
1
3
1
3
ALL
1
3
3
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MAINTENANCE MANUAL
CHAPTER 71 - POWER PLANT
TABLE OF CONTENTS
_________________
Chapter
Section
Subject
_______
Subject
_______
Component Location
Component Index
Component Location
Maintenance Practices
Aerodynamic Smoothness
Adjustment
BLANKET - FAN COWL PANEL
INSULATION
Approved Repairs
COWL - INLET
Removal/Installation
DOOR - INLET COWL PRESSURE
RELIEF
Removal/Installation
Adjustment/Test
Aerodynamic Smoothness Check
Latch Test
DOORS - COWL PANEL PRESSURE
RELIEF
Removal/Installation
Adjustment/Test
Aerodynamic Smoothness Check
Latch Test
DUCT - INLET COWL THERMAL
ANTI-ICE (TAI)
Removal/Installation
LATCH - CORE COWL PANEL
Removal/Installation
Adjustment/Test
LATCH - FAN COWL PANEL
Removal/Installation
Adjustment/Test
PANEL - CORE COWL
Maintenance Practices
Close the Core Cowl Panels
Open the Core Cowl Panels
Removal/Installation
PANEL - FAN COWL
Maintenance Practices
Close the Fan Cowl Panel
Open the Fan Cowl Panels
Removal/Installation
Page
____
Effectivity
___________
101
ALL
201
201
ALL
801
ALL
401
ALL
401
501
505
501
ALL
ALL
401
501
505
501
ALL
ALL
401
ALL
401
501
ALL
ALL
401
501
ALL
ALL
201
205
201
401
ALL
201
206
201
401
ALL
71-11-12
71-11-01
71-11-03
71-11-08
71-11-09
71-11-07
71-11-05
71-11-06
ALL
71-11-04
ALL
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CHAPTER 71 - POWER PLANT
TABLE OF CONTENTS
_________________
Chapter
Section
Subject
_______
Subject
_______
ROD - HOLD OPEN
Maintenance Practices
Cleaning
Inspection
Page
____
Effectivity
___________
71-11-10
______
MOUNTS
ENGINE MOUNTS
Description and Operation
General
Component Details
Aft Lower Engine Mount
Forward Lower Engine Mount
Component Location
Component Index
Component Location
Maintenance Practices
Inspection/Check
ISOLATOR - FORWARD ENGINE MOUNT
Removal/Installation
MOUNT - AFT LOWER ENGINE
Removal/Installation
MOUNT - FORWARD LOWER ENGINE
Removal/Installation
71-20-00
71-21-00
__________________
ELECTRICAL
HARNESS
ENGINE WIRE HARNESS
Adjustment/Test
Inspection/Check
Approved Repairs
71-50-00
71-51-00
_____________
ENGINE
DRAINS
ENGINE VENTS AND DRAINS
Description and Operation
General
Component Details
Drains
Vents
Component Location
Component Index
Component Location
Maintenance Practices
Clear the Strut Drain Line
Inspection/Check
71-70-00
71-71-00
201
204
201
ALL
1
1
1
1
1
101
ALL
201
601
ALL
ALL
401
ALL
401
ALL
401
ALL
501
601
801
ALL
ALL
ALL
1
1
1
1
1
101
ALL
201
201
601
ALL
ALL
71-21-03
71-21-02
71-21-01
ALL
ALL
71-CONTENTS
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ELECTRONIC PROPULSION CONTROL SYSTEM (EPCS)
___________________________________________
COMPONENT
ACTUATOR - (FIM 75-24-00/101)
TURBINE COOLING AIR VALVE, M11127
ACTUATOR - (FIM 75-31-00/101)
STATOR VANE, M10507
ACTUATOR - (FIM 75-32-00/101)
INTERCOMPRESSOR BLEED VALVE, M10508
ACTUATOR - (FIM 78-31-00/101)
T/R HYDRAULIC ACTUATOR
ALTERNATOR - (FIM 73-21-00/101)
ELECTRONIC ENGINE CONTROL, M10510
CIRCUIT BREAKER EICAS CMPTR L, C4078
EICAS CMPTR R, C4079
EICAS DISPLAY SELECT, C4094
EICAS DISPLAY SW, C4189
EICAS LOWER DISPLAY, C4082
EICAS UPPER DISPLAY, C4081
LEFT ENGINE EEC PRI ACCESS 1, C4306
LEFT ENGINE EEC SEC ACCESS 1, C4302
RIGHT ENGINE EEC PRI ACCESS 1, C4307
RIGHT ENGINE EEC SEC ACCESS 1, C4303
T/R PRI CONT, C4338
T/R PRI CONT, C4339
T/R SEC CONT, C4304
T/R SEC CONT, C4305
COMPUTER - (FIM 31-41-00/101)
L EICAS, M10181
R EICAS, M10182
COMPUTER - (FIM 34-12-00/101)
L AIR DATA, M100
R AIR DATA, M101
CONTROL - (FIM 73-21-00/101)
ELECTRONIC ENGINE, M10501
MODULE - HIGH VOLTAGE ISOLATION
M10594,M10595
M10596,M10597
M10600 THRU M10603
M10606 THRU M10609
M10629 THRU M10634
M10637 THRU M10642
PLUG - (FIM 73-21-00/101)
EEC DATA ENTRY
PROBE - (FIM 34-12-00/101)
TOTAL AIR TEMPERATURE, TS5001
PROBE - (FIM 73-21-00/101)
FUEL TEMPERATURE, TS5230
INLET PRESSURE/TEMPERATURE, B10081
OIL TEMPERATURE, TS5231
TCA THERMOCOUPLE, TS5304
T3.5 THERMOCOUPLE, TS5305
PROBE - (FIM 77-11-00/101)
EXHAUST GAS PRESSURE, P4.9
PROBE - (FIM 77-21-00/101)
EXHAUST GAS TEMPERATURE, T4.9, TB234
FIG.
102 QTY
SHT
1
2
2
2
2
2
2
2
AMM
REFERENCE
ACCESS/AREA
1
1
1
1
1
1
1
1
1
1
1
1
1
1
FLT COMPT, P11
11J2
11J29
11J32
11J31
11J30
11J3
11L2
11L5
11L29
11L32
11K6
11K32
11K7
11K33
2
2
4
4
6
6
119BL, MAIN EQUIP CTR
E4-2
E3-4
E5-1
E5-2
P36
P36
H86255
Electronic Propulsion Control System (EPCS) - Component Index
Figure 101 (Sheet 1)
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ú
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71-EPCS MESSAGE INDEX
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COMPONENT
FIG.
102 QTY
SHT
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AMM
REFERENCE
ACCESS/AREA
RELAY - (FIM 31-01-36/101)
EEC CHANNEL SELECT, K10528
FIRE WARNING, K10519
FIRE WARNING, K10520
THRUST LEVER INTERLOCK, K10466
THRUST LEVER INTERLOCK, K10465
RELAY - (FIM 31-01-37/101)
EEC CHANNEL SELECT, K10530
FIRE WARNING, K10521
FIRE WARNING, K10522
THRUST LEVER INTERLOCK, K10471
THRUST LEVER INTERLOCK, K10470
RESOLVER - (FIM 73-21-00/101)
THRUST LEVER ANGLE, M10491
TRANSDUCER - (FIM 73-21-00/101)
N1 SPEED, TS5221
UNIT - (FIM 73-21-00/101)
FUEL CONTROL, M10506
UNIT - L PROPULSION DISCRETE INTERFACE,
M10552
UNIT - R PROPULSION DISCRETE INTERFACE,
M10553
VALVE - (FIM 75-24-00/101)
HPT-ACC, V10084
LPT-ACC, V10085
VALVE - (FIM 75-32-00/101)
14TH-STAGE BLEED CONVERTER, V10087
VALVE - (FIM 78-34-00/101)
DIRECTIONAL CONTROL LEFT, V10112
DIRECTIONAL CONTROL RIGHT, V10120
VALVE - (FIM 79-21-00/101)
AIR/OIL HEAT EXCHANGER, V10086
FUEL/OIL HEAT EXCHANGER, M10509
H86276
Electronic Propulsion Control System (EPCS) - Component Index
Figure 101 (Sheet 2)
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ú
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FAULT ISOLATION/MAINT MANUAL
P11 PANEL
EICAS DISPLAY
UNITS (REFERENCE)
SEE
A
P61 PANEL
EICAS
MAINTENANCE
PANEL (REFERENCE)
SEE
B
FLIGHT COMPARTMENT
TAT + 12c
1.50
1.8
L HYD SYS PRESS
L YAW DAMPER
RUDDER RATIO
1.50
1.28
1.4
1.8
1.4
1.0
1.28
1.0
EPR
54.2
54.2
N1
428
428
UPPER EICAS
DISPLAY
UNIT
EICAS MAINT
DISPLAY SELECT
STATUS
EPCS
____
P SVA/EEC
P N1/EEC
S PDIU
FCU/EEC
PAGE 1
PRI
SEC
21.3
-0.93
-12
104.2
-12
9.2
101.5
21.3
-0.93
-12
104.2
-12
9.2
101.5
OIL T YEL
TLR
SVA
BVA
N2C
T2
P2/PS
RVA
ECS
MSG
ELEC
HYD
CONF
MCDP
ENG
EXCD
PRI
SEC
54.2
1.24
102
73.2
12
9.2
-12.7
54.2
1.24
102
73.2
12
9.2
-12.7
AUTO EVENT
LOWER EICAS
DISPLAY
UNIT
EGT RED
MAN
PERF
APU
TEST
S DCV/EEC
P FOX/EEC
EVENT
READ
AUTO
EGT
REC
ERASE
EPCS
EPCS SWITCH
(REFERENCE)
EICAS MAINTENANCE PANEL (REFERENCE)
B
EICAS DISPLAY UNITS (REFERENCE)
A
H86300
Electronic Propulsion Control System (EPCS) - Component Location
Figure 102 (Sheet 1)
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HIGH VOLTAGE ISOLATION
MODULES, M10594, M10595
(E4-2)
HIGH VOLTAGE ISOLATION
MODULES, M10600 THRU M10603
(E5-1)
HIGH VOLTAGE ISOLATION
MODULES, M10596, M10597
(E3-4)
P36 PANEL
HIGH VOLTAGE ISOLATION
MODULES, M10606 THRU M10609
(E5-2)
HIGH VOLTAGE ISOLATION
MODULES, M10629 THRU M10634,
M10636 THRU M10642
H86308
Electronic Propulsion Control System (EPCS) - Component Location
Figure 102 (Sheet 2)
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POWER PLANT - DESCRIPTION AND OPERATION
_______________________________________
1.
2.
General
_______
A. The 757 airplanes are supplied with power by two PW2037 or two PW2040
turbofan engines.
B. The power plants are held in the strut mounted nacelles. One power plant
is installed below each wing.
C. Each power plant supplies the airplane with hydraulic, pneumatic, and
electrical power and also propulsion.
D. An engine which is fully assembled, and includes the inlet cowl, weighs
approximately 8452 pounds.
Component Details
_________________
A. Power Plant (Fig. 1)
89529
Split Compressor and Turbine Arrangement
Figure 1
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(1)
B.
C.
The PW2037 and the PW2040 engines are a two-spool, axial-flow
turbofan engine with a high bypass ratio.
(2) The shaft center of the two rotor assemblies is the same. The low
pressure (N1) compressor has five stages and is driven by a
five-stage turbine. The high pressure (N2) compressor has twelve
stages and is driven by a two-stage turbine (Ref 72-00-00/001).
(3) All engine parameters are controlled by the electronic engine
control (EEC). The EEC gives a signal to the fuel control to adjust
the fuel flow and servo fuel pressure (Ref 73-21-00/001).
(4) The ignition of the fuel is done by two different systems. The
systems will automatically supply and control ignition as necessary
(Ref 74-31-00/001).
(5) Engine cooling air is used to decrease the clearance to a minimum
between the rotor blades and the engine case. This is done to
increase fuel efficiency (Ref 75-24-00/001).
(6) This engine includes a modulating 2.5 bleed valve
(Ref 75-32-00/001).
(7) Power levels set by the flight crew are sent to the engine from a
transducer in the flight compartment (Ref 76-11-00/001).
(8) Many engine parameter transmitters are installed on the engine and
send data to the Engine Indicating and Crew Alerting System (EICAS)
(Ref 77-00-00/001).
(9) A thrust reverser with a translating sleeve uses fan air to slow
down the airplane (Ref 78-30-00/001).
(10) An oil system on the engine is used for lubrication and to decrease
the internal engine components (Ref 79-00-00/001).
(11) The engine starting system is used to turn the N2 rotor
(Ref 80-11-00/001).
(12) A integrated drive generator is installed on the main gearbox and
supplies electrical power to many airplane systems
(Ref 24-11-00/001).
(13) Fire detection systems are added to the basic engine to supply the
flight crew with an indication of an engine fire (Ref 26-11-00/001).
(14) A hydraulic pump is installed on the main gearbox and supplies
hydraulic power to the airplane (Ref 29-11-00/001).
(15) Bleed air from the engine is used to supply pneumatic power
(Ref 36-10-00/0) and to operate the air conditioning packs
(Ref 21-51-00/001).
Cowling (Fig. 2)
(1) The engine cowling and turbine exhaust system make an
aerodynamically smooth surface on the engine and prevents damage to
the components installed on the engine.
(2) The cowling includes an inlet cowl, left and right fan cowl panels,
and left and right core cowl panels. The left and right fan duct
cowl and thrust reverser and turbine exhaust sleeve are the nacelle.
Refer to 71-11-00/001, Engine Cowling, 78-11-00/001, Turbine Exhaust
and 78-31-00/001, Thrust Reverser for a description of each
component.
Engine Mounts
(1) Each engine is attached to the airplane wing strut by two engine
mounts.
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(2)
D.
The engine mounts hold the engine and remove the engine thrust
loads. The engine mounts remove vertical and side loads and loads
in the axial and radial directions when the temperature increases
(Ref 71-21-00/001).
Drains
(1) The engine drain system collects drain fluids and lets the drain
fluids from the engine and strut fall overboard. The drain fluids
are released through openings in the cowling (Ref 71-71-00/001).
STRUT
TURBINE
EXHAUST SLEEVE
CORE COWL PANELS
FAN DUCT COWL AND
THRUST REVERSER
FAN COWL PANELS
INLET COWL
89528
Cowling
Figure 2
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MAINTENANCE MANUAL
START DUCT
ENGINE DRIVEN
HYDRAULIC PUMP
FUEL
STARTER
DISTRIBUTION
VALVE
FUEL PUMP AND
FUEL CONTROL
MAIN
GEARBOX
ELECTRONIC
ENGINE CONTROL
INTEGRATED
DRIVE GENERATOR
OIL TANK
89564
Major Power Plant Components
Figure 3
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POWER PLANT - MAINTENANCE PRACTICES (OPERATING PROCEDURE)
_________________________________________________________
1.
General
_______
A. This section contains the items that follow: the safety precautions for
an engine on the ground, the limits of operation for the power plant, the
procedures to motor the engine, and the procedure to operate the engine
in cold weather.
B. Many engine indications show on the Engine Indication and Crew Alerting
System (EICAS) display when the engine is in operation. You can look at
more engine indications when you operate the bottom EICAS display.
NOTE:
____
C.
D.
E.
If the
on the
engine
again,
bottom EICAS display does not show, push the ENGINE switch
pilot's display select panel to operate the secondary
parameter indications. When you push the ENGINE switch
it will remove the bottom EICAS display out of view.
The Power Plant Operation (Normal) is the regular procedure to operate
the engine.
The procedure to motor the engine is when you turn the engine with the
starter but you do not supply ignition. The Dry-Motor procedure supplies
the fuel to the fuel pump as a lubricant, but not to the engine
combustion chamber. The Wet-Motor procedure supplies the fuel to the
fuel pump and lets the fuel go into the combustion chamber. Thus, you
must only use the Wet-Motor procedure when it is necessary.
The Power Plant Operation (Cold Weather) is the procedure to operate the
engine with the conditions of snow, ice and temperatures below 32° F
(0° C).
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MAINTENANCE MANUAL
ENGINE GROUND SAFETY PRECAUTIONS
________________________________
2.
TASK 71-00-00-862-079-P00
Engine Ground Safety Precautions
________________________________
A. General
(1) It is necessary during the operation of airplanes, which are
supplied with power by jet engines, to prevent injury to persons and
damage to property. You must not only stay away from the engine
inlet, but also the exhaust nozzle where hot exhaust gases come out
at high speeds. Also, the speed of the air that comes out of the
fan, especially at high thrust positions, is sufficient to cause
injury. When the thrust reverser is in the reverse thrust position,
the fan air comes out forward and not rearward.
(2) You must wear eye and ear protection when you do the work by the
airplane while the engines are in operation.
(3) Use the aerostands or platforms with the protection railings to
prevent injury when you do the work on the engines.
(4) Use the general safety items, which follow, when it is necessary for
the task to prevent an accident.
B. Airplane Skidding Prevention for High Power Operation (Fig. 201)
(1)
S 712-136-P00
To keep the risk of an airplane skid to a minimum during a high
power operation, make sure the ramp and tires are free from
contamination.
NOTE:
____
(2)
A wet ramp surface is permitted. But, you cannot have
standing water, frost, ice, oil, sand or other contamination.
S 982-116-P00
Apply the parking brake.
(a) Make sure the indicator light of the PARK BRAKE, on the P10
panel, comes on.
(3)
S 982-117-P00
Put the nose landing gear in the forward direction.
(4)
S 412-124-P00
Install ground locks on the nose and main landing gear.
(5)
S 412-125-P00
Put chocks 6 to 12 inches (15 to 30 cm) in front and aft of the nose
and all main landing gear tires.
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________________________________
S 862-140-P00
CAUTION:
_______
(6)
DO NOT OPERATE THE AIRPLANE HYDRAULIC SYSTEMS UNLESS THE FUEL
QUANTITY IS SUFFICIENT TO GO ABOVE THE HEAT EXCHANGERS FOR THE
HYDRAULIC FLUID. IF YOU OPERATE THE AIRPLANE HYDRAULIC SYSTEMS
WITHOUT SUFFICIENT FUEL, YOU CAN CAUSE DAMAGE TO THE AIRPLANE
HYDRAULIC SYSTEMS.
Make sure there is a minimum of 600 gallons (4,020 pounds/1,827
kilograms) of fuel in each main (wing) tank to fully cover the heat
exchangers.
NOTE:
____
(a)
(7)
The total fuel load for the airplane must be a minimum of
1,200 gallons (8,040 pounds/3,654 kilograms) for the heat
exchangers. If you will operate the engines on the ground,
you must add more fuel to each tank for the amount of time
you will operate the engines.
If it is necessary, do the servicing procedure for the fuel
tanks (AMM 12-11-01/301).
S 862-142-P00
For engine operations more than the idle speed, use the table that
follows to put the airplane in the correct weight configuration.
(a) Make sure the airplane weighs more than the minimum gross
weight for the applicable power level.
(b) If it is necessary, do the servicing procedure for the fuel
tanks (AMM 12-11-01/301).
(c) To prevent airplane skids when you operate one engine at high
power, make sure you operate the opposite engine at the
specified power level for the airplane CG (center of gravity).
NOTE:
____
Figure 201 gives the relationship between temperature,
EPR and percent of engine RPM for engine operations in
the N1 mode. This is for reference only. Do not use
this cross reference chart to set the power level.
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________________________________
~¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼
¦
PW2037 ENGINES
¦
»¼¼¼¼¼¼¼¼¼¼¼¼ ¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼ ¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼ ¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼«
¦ 1st Engine ¦ 2nd Engine
¦ Minimum Loading ¦
Minimum Gross
¦
¦
Power
¦
Power
¦ (Fuel or other) ¦
Weight
¦
¦
¦
¦
*[2]
¦
¦
»¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼«
¦ 1.24 EPR ¦
1.2 EPR
¦
8,040 lbs
¦
129,000 lbs
¦
¦
¦
¦
(3,654 kg)
¦
(58,500 kg)
¦
¦
¦
¦
¦
*[4]
¦
»¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼«
¦
TAKEOFF ¦ 1.0 to 1.2
¦
24,000 lbs
¦
145,000 lbs
¦
¦
¦ EPR *[1]
¦
(10,900 kg)
¦
(65,800 kg)
¦
»¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼«
¦
TAKEOFF ¦
TAKEOFF
¦
62,000 lbs
¦
183,000 lbs
¦
¦
¦
¦
(28,100 kg)
¦
(83,000 kg)
¦
²¼¼¼¼¼¼¼¼¼¼¼¼…¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼…¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼…¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¹
~¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼
¦
PW2040 ENGINES
¦
»¼¼¼¼¼¼¼¼¼¼¼¼ ¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼ ¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼ ¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼«
¦ 1st Engine ¦ 2nd Engine
¦ Minimum Loading ¦
Minimum Gross
¦
¦
Power
¦
Power
¦ (Fuel or other) ¦
Weight
¦
¦
¦
¦
*[2]
¦
¦
»¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼«
¦
1.24 EPR ¦
1.2 EPR
¦
8,040 lbs
¦
129,000 lbs
¦
¦
¦
¦
(3,654 kg)
¦
(58,500 kg)
¦
¦
¦
¦
¦
*[4]
¦
»¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼«
¦
TAKEOFF ¦ 1.0 to 1.2
¦
42,000 lbs
¦
163,000 lbs
¦
¦
¦
EPR *[1]
¦
(19,100 kg)
¦
(73,900 kg)
¦
»¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼«
¦
TAKEOFF ¦
TAKEOFF
¦
83,000 lbs
¦
204,000 lbs
¦
¦
¦
¦
(37,600 kg)
¦
(92,500 kg)
¦
¦
¦
¦
*[3]
¦
¦
²¼¼¼¼¼¼¼¼¼¼¼¼…¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼…¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼…¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¹
*[1] When you operate only one engine at high power, make sure that
a pneumatic source (operate the other engine at 1.2 EPR or
less, or operate the APU) is available to motor the engine if
there is a compressor surge (stall) or a fire in the gaspath.
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ENGINE GROUND SAFETY PRECAUTIONS
________________________________
*[2] The values of the minimum fuel load are calculated from an
airplane weight of 121,000 lbs (54,900 kg). This weight
includes an empty airplane with the interior, fuel not used,
oil, oxygen, escape slide, fixed galley stucture, 65% of the
galley structure which you can remove, other equipment, and a
two person crew. If a better estimate of the airplane weight
is available before the maintenance engine operation, you can
calculate the minimum fuel load if you subtract the actual
airplane weight from the minimum gross weight. If a better
weight estimate is not available, use the minimum fuel loads
shown in the table.
*[3] The maximum fuel load is approximately 75,000 lbs (34,000 kg).
Since this maximum fuel load is less than the necessary minimum
load for two engines which operate at takeoff power, you must
add other loads also.
*[4] At the 129,000 lbs gross weight, the intermediate thrust level
settings for the testing of one engine operating at a reduced
thrust level from full rated takeoff level is provided in the
table. This is with the second engine operating to provide the
minimum hydraulic system requirement. The intermediate thrust
level for the PW2000 engine is at a point of the scavanger
valve closure.
C.
Air Intake (Fig. 202, 202A, 203, and 203A)
S 912-007-P00
WARNING:
_______
(1)
ALL PERSONS MUST STAY AWAY FROM THE HAZARD AREAS IN THE FRONT
AND THE REAR OF THE POWER PLANT. YOU MUST STAY OUT OF THE
ENGINE SAFETY BARRIER, IF USED, DURING THE GROUND OPERATIONS.
THE ENGINE CAN CAUSE SUFFICIENT SUCTION AT THE INLET TO PULL A
PERSON INTO THE INLET AND CAUSE INJURY. THUS, WHEN YOU GO NEAR
A JET ENGINE, YOU MUST FOLLOW THE PRECAUTIONS TO STAY AWAY FROM
THE INLET AIRFLOW. THE SUCTION NEAR THE INLET CAN ALSO PULL IN
HATS, GLASSES, LOOSE CLOTHES AND WIPE-RAGS FROM POCKETS. YOU
MUST ATTACH OR REMOVE LOOSE OBJECTS BEFORE YOU DO THE WORK
AROUND THE ENGINE. IF YOU DO NOT FOLLOW THESE INSTRUCTIONS,
YOU CAN CAUSE INJURY TO PERSONS OR DAMAGE TO EQUIPMENT.
When you operate the engine, the mass airflow will pull unwanted
materials into the engine. Thus, you must clean and examine the
engine compartment, air inlet, and work area to make sure there are
no unwanted materials before the engine operation.
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757-200/PW2000 ENGINE
N1 SPEEDS AT MINIMUM A/P GROSS WT. OF 129,000 LBS
120
100
80
AMBIENT TEMPERATURE - DEGREE F
SECOND ENGINE, EPR = 1.20
60
40
FIRST ENGINE, EPR = 1.24
20
0
-20
-40
-60
88
84
80
76
72
68
64
60
L.P. ROTOR SPEED - N1 - PERCENTS
NOTE:
____ N1 VALUES ARE FOR CROSS REFERENCE ONLY
DO NOT USE FOR POWER SETTING PURPOSE.
L-91998
C99141
N1 Rotor Speed Cross Reference Chart
Figure 201
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1
SEE A
175 FEET
EXHAUST HAZARD AREA
WARNING:
_______
IF THE WIND IS MORE THAN 25 KNOTS,
INCREASE THE DISTANCE OF THE INLET
AREA BY 20%. IF THERE IS SNOW, ICE,
WATER, OIL OR OTHER CONTAMINATION ON
THE RAMP, IT IS NECESSARY TO CLEAN THE
RAMP.
WHEN THE ENGINE IS OPERATED, THE
PERSONS ON THE RAMP MUST NOT STAND
IN THE HARZARD AREAS SHOWN. IT
IS NECESSARY FOR THE PERSONS ON
THE GROUND TO TELL THE PERSONS
IN THE CONTROL CABIN WHEN
PROBLEMS OCCUR.
5 FEET
ENTRY
CORRIDOR
IF YOU DO NOT OBEY THESE
INSTRUCTIONS YOU CAN
CAUSE INJURY TO PERSONS.
9 FOOT RADIUS
ENTRY
CORRIDOR
45`
INLET HAZARD AREA
1
THE DOTTED LINE IS THE HAZARD AREA
FOR A ONE ENGINE OPERATION
A
127979
Minimum Idle/High Idle - Power Hazard Area
Figure 202
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SEE A
400 FEET
EXHAUST HAZARD AREA
WARNING:
_______
IF THE WIND IS MORE THAN 25 KNOTS,
INCREASE THE DISTANCE OF THE INLET
AREA BY 20%. IF THERE IS SNOW, ICE,
WATER, OIL OR OTHER CONTAMINATION ON
THE RAMP, IT IS NECESSARY TO CLEAN THE
RAMP.
7 FEET
WHEN THE ENGINE IS OPERATED, THE
PERSONS ON THE RAMP MUST NOT STAND
IN THE HARZARD AREAS SHOWN. IT
IS NECESSARY FOR THE PERSONS ON
THE GROUND TO TELL THE PERSONS
IN THE CONTROL CABIN WHEN
PROBLEMS OCCUR.
IF YOU DO NOT OBEY THESE
INSTRUCTIONS YOU CAN
CAUSE INJURY TO PERSONS.
16 FOOT RADIUS
45`
INLET HAZARD AREA
A
229519
Breakaway Thrust - Power Hazard Area
Figure 202A
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SEE A
1900 FEET
EXHAUST HAZARD AREA
WARNING:
_______
IF THE WIND IS MORE THAN 25 KNOTS,
INCREASE THE DISTANCE OF THE INLET
AREA BY 20%. IF THERE IS SNOW, ICE,
WATER, OIL OR OTHER CONTAMINATION ON
THE RAMP, IT IS NECESSARY TO CLEAN THE
RAMP.
7 FEET
WHEN THE ENGINE IS OPERATED, THE
PERSONS ON THE RAMP MUST NOT STAND
IN THE HARZARD AREAS SHOWN. IT
IS NECESSARY FOR THE PERSONS ON
THE GROUND TO TELL THE PERSONS
IN THE CONTROL CABIN WHEN
PROBLEMS OCCUR.
IF YOU DO NOT OBEY THESE
INSTRUCTIONS YOU CAN
CAUSE INJURY TO PERSONS.
45`
16 FOOT RADIUS
INLET HAZARD AREA
A
127982
Takeoff Thrust - Power Hazard Area
Figure 203
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30 FEET
45`
75 FOOT RADIUS
_______
WARNING:
IF THERE IS SNOW, ICE, WATER, OIL
OR OTHER CONTAMINATION ON THE RAMP,
IT IS NECESSARY TO CLEAN THE RAMP.
WHEN THE ENGINE IS OPERATED, THE
PERSONS ON THE RAMP MUST NOT STAND
IN THE HARZARD AREAS SHOWN. IT
IS NECESSARY FOR THE PERSONS ON
THE GROUND TO TELL THE PERSONS
IN THE CONTROL CABIN WHEN
PROBLEMS OCCUR.
CAUTION:
_______
FOR THE MAINTENANCE, THE LIMIT OF
THE ENGINE OPERATION IN REVERSE
THRUST IS MINIMUM IDLE POWER.
IF YOU DO NOT OBEY THESE
INSTRUCTIONS YOU CAN
CAUSE INJURY TO PERSONS.
216819
Reverse Minimum Idle - Power Hazard Area
Figure 203A
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________________________________
D.
Exhaust Characteristics (Fig. 202, 202A, 203, and 203A)
(1)
(2)
S 862-081-P00
Velocity
(a) At high engine speeds, the air which flows out of the fan and
the engine exhaust can blow loose dirt, stones, sand and other
material at a distance of more than one hundred feet. Thus,
you must use caution when you park the aircraft for a high
speed operation to prevent injury to persons or damage to
property or other aircraft. A blast fence is recommended if
you are to operate the engines at high power in an area where
there is not sufficient space available. It is necessary to
have a sufficient space to decrease the speed of the fan and
exhaust blast.
S 862-082-P00
Temperature
(a) You can find high temperature more than one hundred feet from
the exhaust nozzle in the correct wind conditions. By the
engine, the exhaust temperature can cause sufficient
deterioration of bituminous pavement. Thus, concrete aprons
are recommended for areas of a high speed operation. It is
possible for a jet engine, when started, to set fire to the
fuel that has collected in the turbine exhaust area. This will
cause long flames to blow out of the exhaust nozzle. You must
monitor this possible dangerous condition and keep all
flammable materials away.
S 862-083-P00
Toxicity
(a) The tests have shown that the quantity of the carbon monoxide
in the exhaust is low. But, there are other gases which smell
bad and can cause an effect to your body. If you are near
these gases, this can cause injury to your eyes. But more
important, this can cause you not to breathe correctly.
Because of these two results, you must not get near the gases,
specially in small spaces where the concentration is high.
Engine Cool Down
(3)
E.
(1)
S 912-110-P00
You must not touch the heat exchanger and tubes, which are near the
heat exchanger, in less than 1.5 hours from the time you do the
engine shutdown. It is possible the temperatures are more than
400°F (204°C).
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________________________________
S 862-084-P00
After the engine operation, you must make sure that the turbine
exhaust sleeve and plug have decreased in temperature before you do
work in these areas. You can do the work on most other parts
without the risk of injury.
Engine Noise (Fig. 204)
(2)
F.
S 862-128-P00
WARNING:
_______
YOU MUST WEAR EAR PROTECTION EQUIPMENT WHILE YOU DO THE WORK IN
THE NOISE HAZARD AREAS OF THE ENGINE. IF YOU DO NOT OBEY THESE
INSTRUCTIONS, YOU CAN CAUSE DAMAGE TO YOUR EARS.
(1)
G.
The jet engines usually cause temporary, or permanent, damage to
your ears. All persons must obey the noise hazard areas of the
engine. Short times to very high noise can cause damage to the ears
and all persons must use some type of protection. The noise can
cause damage to the ear mechanism which will cause you not to be
stable or move correctly. Thus, you are recommended to use the
cup-type ear protection.
Engine Ignition
S 012-133-P00
WARNING:
_______
(1)
THE ENGINE IGNITION SYSTEM IS USUALLY HIGH IN ENERGY. THIS
TYPE OF THE SYSTEM IS SUCH AS TO MAKE THE SYSTEM A DANGEROUS
SOURCE OF ELECTRICAL SHOCK UNLESS YOU USE PRECAUTIONS. IF YOU
DO NOT OBEY THESE INSTRUCTIONS, YOU CAN CAUSE INJURY TO
PERSONS, OR POSSIBLY KILL.
Do not disconnect the ignition system components unless you first
remove the input leads from the ignition exciter.
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* _______
WARNING:
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WITH EAR PROTECTION,
A LONG EXPOSURE CAN
POSSIBLY CAUSE EAR
DAMAGE.
X
EAR PR0TECTION IS NECESSARY IN
THIS AREA WHEN THE EXPOSURE
TIME IS MORE THAN THE VALUE
SHOWN IN THE CHART BELOW
* PERMITTED DAILY NOISE EXPOSURE
ONE ENGINE OPERATION
8.0
GROUND
IDLE
7.0
EXPOSURE TIME (HOURS)
6.0
BREAKAWAY
TAKEOFF
5.0
4.0
3.0
2.0
1.0
0.0
0
200
400
600
800
1000
1200
127983
RADIUS X (FEET)
Engine Noise Hazard Areas
Figure 204
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________________________________
H.
Fuel and Lubricating Oils
S 912-129-P00
All fuel, oils and hydraulic fluids can dry the skin.
all precautions to not get these fluids on your skin.
X-Rays
(1)
I.
You must use
S 912-016-P00
CAUTION:
_______
(1)
THE ELECTRONIC ENGINE CONTROL (EEC) CAN BE DAMAGED BY CONTINUED
USE OF X-RAYS. THE EEC MUST BE REMOVED PRIOR TO THE USE OF
X-RAYS.
It is possible to use X-rays for a diagnostic inspection of the
important parts inside the engine. The X-rays can damage the
electronic engine control (EEC). Remove the EEC before you do an
inspection with X-rays.
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POWER PLANT OPERATION LIMITS
____________________________
3.
TASK 71-00-00-862-086-P00
Power Plant Operation Limits
____________________________
A. Starter Operation Limits
(1)
(2)
S 862-087-P00
Each starter is supplied with low pressure air to start and motor
the engine. This air is supplied through the pneumatic manifold
from an engine in operation, supply units for the ground low
pressure air, or the auxiliary power unit (APU) installed on the
airplane.
S 712-127-P00
The engine starter limits for operation are as follows:
(a) The normal duty cycle and cooling requirements are as follows:
NOTE:
____
The amount of time before the starter can be used again
after an aborted start is a minimum of 30 seconds.
1)
(b)
(c)
The starter can be operated continuously for not more than
2 minutes.
a) If the engine start is not completed, do not use the
starter again until the N2 rotor speed decreases to
zero.
2) A second continuous starter operation for not more than 2
minutes is permitted.
a) If the second engine start is not completed, do not use
the starter again until the N2 rotor speed decreases to
zero.
3) A third continuous starter operation for not more than 2
minutes is permitted.
a) If the engine start is not completed, let the starter
become cool for 15 minutes before it is used again.
The extended starter duty cycles and cooling requirements, with
fuel and ignition off, are as follows:
1) For extended operation, continuous starter operation for
not more than 4 minutes is permitted.
a) Let the starter become cool for 15 minutes before it is
used again.
The starter re-engagement limits are as follows:
1) Starter re-engagement is recommended at 0% N2 rpm.
2) Starter re-engagement is not permitted above 20% N2 rpm,
except in the case of a fire or an EGT exceedance
condition.
NOTE:
____
If possible, let the engine come to a complete stop
before you re-engage the starter.
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CAUTION:
_______
YOU MUST NOT ENGAGE THE STARTER AT 30% OR MORE. IF
YOU DO ENGAGE THE STARTER, YOU CAN CAUSE DAMAGE TO
THE STARTER OR GEARBOX.
3)
B.
Starter re-engagement up to 30% is permitted to clear a
fire or after an EGT exceedance condition.
Engine Operation Limits (Figs. 205 and 206)
(1)
(2)
S 862-088-P00
The engine operation conditions and limits are shown in Fig. 205.
The relative wind data which is recommended for the engine
maintenance operation is shown in Fig. 206. More data about the
effect of the tailwinds on the engine ground operations are in the
steps that follow.
S 982-089-P00
You can get the levels of engine operation as follows when you put
the thrust lever to the specified EPR:
(a) TAKEOFF
1) This is the maximum thrust you are permitted to use and has
a time limit of 5 minutes. You can only use this thrust
for the takeoff.
(b) MAXIMUM CONTINUOUS
1) This is the maximum thrust you can use continuously. Its
primary function is for an emergency at the decision of the
pilot.
(c) MAXIMUM CLIMB
1) This is the maximum approved thrust for a climb operation.
(d) MAXIMUM CRUISE
1) This is the maximum approved thrust for a cruise operation.
(e) IDLE
1) This is not a thrust level, but a position of the thrust
lever when it is fully rearward.
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CONDITION OF THE
OPERATION 1
TIME LIMIT
(MINUTES)
MAXIMUM
EXHAUST GAS
TEMP (EGT)
(T4.9)`C
GRD/AIR START
1-1/2 2
485-545 3
MIN IDLE
CONTINUOUS
460-490 8
4
OIL PRESSURE
PSID
MINIMUM 6
OIL TEMP
`C 7
N/A
N/A
5
70
163
5
645
80
163
MAXIMUM CONTINUOUS
CONTINUOUS
615
80
163
MAXIMUM CLIMB
CONTINUOUS
615
80
163
MAXIMUM CRUISE
CONTINUOUS
615
80
163
5
645
80
163
TAKEOFF
MAXIMUM REVERSE
1
THE MAXIMUM PERMITTED SPEED OF OPERATION OF THE ROTOR:
Ñ N1 100.5% (4575 RPM)
Ñ N2 100.0% (12250 RPM).
2
THE ENGINE IS NOT PERMITTED TO OPERATE MORE THAN 90 SECONDS FROM THE TIME OF FUEL ON
(THE FUEL CONTROL SWITCH IS SET TO THE RUN POSITION) TO MIN IDLE.
3
DECREASING FROM 545`C TO 485`C OVER A 30 SECOND PERIOD OF TIME
4
IF THE N2 ACCELERATION BECOMES SLOW BETWEEN 30 AND 40% N2 AND THE EGT INCREASES QUICKLY THROUGH
425`C, STOP THE START BEFORE THE EGT IS 545`C (FIM 71-06-00/101, FIG. 102, 103, AND 104).
5
MORE DETAILED EGT LIMITS ARE SHOWN IN THESE PROCEDURES: HOT START (ENGINE OVERTEMPERATURE LIMITS
FOR GROUND START AND ENGINE OPERATION BELOW IDLE SPEEDS)(FIM 71-06-00/101, FIG. 104); AND ENGINE
OVERTEMPERATURE INSPECTION REQUIREMENTS (ALL RUN CONDITIONS EXCEPT FOR GROUND STARTING AND ENGINE
OPERATION BELOW IDLE SPEEDS)(FIM 71-05-00/101, FIG. 110).
6
THE OIL PRESSURE DURING A SATISFACTORY ENGINE OPERATION IS 80 TO 305 PSID, BUT NOT AT IDLE WHERE
70 PSID MINIMUM IS PERMITTED. THE OIL DIFFERENTIAL PRESSURE IS THE MANIFOLD OIL PRESSURE LESS
THE SCAVENGE OIL PRESSURE OF THE NO. 4 BEARING. THE PSID VALUES OF THE OIL PRESSURE ARE SHOWN
ON THE EICAS AS PSI VALUES. THE OIL PRESSURES WHICH ARE NOT BETWEEN THE LIMITS ARE NOT SAFE
AND IT IS NECESSARY TO STOP THE ENGINE OPERATION.
7
IF, DURING AN ENGINE OPERATION WITH STABLE CONDITIONS, THE OIL TEMPERATURE IS MORE THAN THE
MAXIMUM OIL TEMPERATURE OF 163`C (325`F) FOR MORE THAN 20 MINUTES, BUT THE OIL TEMPERATURE DOES
GO MORE THAN THE OVERSHOOT LIMIT OF 177`C (350`F), YOU CAN KEEP THE ENGINE IN OPERATION ONLY IF
YOU FIND THE CAUSE OF THE OVERTEMPERATURE AND CORRECT IT. DURING AN OPERATION WITHOUT STABLE
CONDITIONS FROM HIGH POWER (HIGH OIL TEMPERATURE AND LOW FUEL FLOW), YOU CAN GET THE MAXIMUM
OVERSHOOT LIMIT OF 177`C (350`F). THIS IS SATISFACTORY IF THE OIL TEMPERATURE GOES
BELOW 163`C (325`F) IN LESS THAN 20 MINUTES OF THE IDLE OPERATION.
IF THE OIL TEMPERATURE IS MORE THAN 162`C (325`F) FOR MORE THAN 20 MINUTES OR MORE THAN 177`C
(350`F), DO THE HIGH OIL TEMPERATURE INSPECTION (AMM 72-00-00/601). YOU CAN CONTINUE THE ENGINE
IN OPERATION ONLY AFTER YOU DO THE INSPECTION, FIND THE CAUSE OF THE OVERTEMPERATURE, AND
CORRECT THE CAUSE.
IF THE ENGINE OIL TEMPERATURE EXCEEDS 219`C (425`F), REPLACE THE ENGINE (AMM 71-00-02/401).
8
THE IDLE EGT VALUE OF 460`C IS FOR THE ENGINE THAT DOES USE THE AIR BLEED OR POWER EXTRACTION.
126923
Engine Start and Operation Limits
Figure 205
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60`
60`
60`
1
NOTE:
____ THE APU CAN BE OPERATED DURING ALL
RELATIVE WIND ANGLES.
RELATIVE WIND
RECOMMENDED (25 KNOTS MAXIMUM
WIND VELOCITY) 1
PERMITTED (15 KNOTS MAXIMUM
WIND VELOCITY) 1
2
NOT PERMITTED
1
THE WIND VELOCITY IS FOR STABLE
WIND CONDITIONS. DECREASE THE MAXIMUM
WIND LIMIT 5 KNOTS WHEN YOU HAVE GUSTS
OF WIND
2
STOP THE OPERATION OF THE ENGINE
MAINTENANCE IF THE EPR OR N1 DOES NOT
BECOME STABLE OR IF THE INLET NOISE
SUDDENLY CHANGES TO A BLOW TORCH TYPE
OF A SOUND (CAUSED BY SEPARATION OF THE
AIR AT THE COWL LIP). DECREASE THE
POWER TO IDLE AND EXAMINE THE RELATIVE
WIND DIRECTION AND SPEED. STOP THE
ENGINE AND CHANGE THE POSITION OF THE
AIRPLANE TO POINT IN THE DIRECTION OF
THE WIND, IF IT IS NECESSARY, BEFORE
YOU COMPLETE THE ENGINE MAINTENANCE
127990
Recommended Relative Wind Direction During an Engine Operation
Figure 206
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S 862-090-P00
Tailwinds, or components of the wind from the tail, have a bad
effect on the ground operation of the engines.
(a) During a start, and at idle or a low level of power, you can
get a high EGT.
(b) At a high level of power, a compressor surge can occur in high
crosswinds, or tailwind conditions.
(c) A compressor surge is identified when the air noise suddenly
increases when separation occurs on the inlet cowl lip.
(d) The compressor surge is shown by the EPR gage when it suddenly
becomes not stable.
(e) You must quickly (1-2 seconds) move the thrust lever rearward,
from a high power to "IDLE", to not get a compressor surge.
1) Monitor the EGT.
2) Make sure the EGT and the fuel flow decrease.
(f) The relative wind data which is recommended for an engine
maintenance operation is shown in Fig. 206.
Overspeed Limits
(3)
C.
(1)
(2)
S 972-091-P00
If N1 speed was between 100.5% and 102.0%, do the Overtemperature
Limits and Inspection Requirements procedure as specified.
(a) Before you do more of the operation, make sure the rotors turn
freely.
(b) Visually examine the inlet, 2.5 bleed valve, and exhaust area
for unwanted material.
1) If there is no damage and the ground operation is
satisfactory after you correct the cause of the overspeed,
continue the engine in operation.
2) If there is damage, you must do more inspection (include
the gaspath borescope inspection) and do the applicable
correction.
S 712-092-P00
If N1 is more than 102.0%, you must do the steps that follow:
(a) Use the Power Plant Operation (Normal) procedure to do the
engine shutdown as quickly as it is possible.
(b) Do a full engine inspection (AMM 72-00-00/601).
(c) Before you remove an engine for an overspeed indication, you
must make sure the tachometer indicating system operates
correctly (AMM 77-12-00/501).
NOTE:
____
You must erase the memory in the maintenance mode of
EICAS after the cause of the overspeed is corrected.
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(3)
S 712-111-P00
If the N2 speed is between 100.0% N2 rpm and 103.0% N2 rpm, do the
inspection procedure as specified.
NOTE:
____
(a)
(b)
(c)
(4)
(5)
The inspection procedure is not necessary for a transient
N2 overspeed of 100.7% N2 rpm or less which occurs for less
than five seconds.
Before you do more of the operation, make sure the rotors turn
freely.
Visually examine the inlet, 14th-stage bleed valve and exhaust
area for unwanted material.
1) If there is no damage and the ground operation is
satisfactory after you correct the cause of the overspeed,
continue the engine in operation.
2) If there is damage, you must do more inspection (include
the gaspath borescope inspection) and do the applicable
correction.
Remove and repair the overspeed limiting function in the engine
accessory components that follow:
1) Electronic engine control (EEC).
2) Fuel control (examine only if the overspeed is more than
101.0% N2 rpm).
S 712-112-P00
If the N2 speed is more than 103.0% N2 rpm, you must do the steps
that follow:
(a) Use the Power Plant Operation (Normal) procedure to do the
engine shutdown as quickly as it is possible.
(b) Remove the engine.
1) Remove the high pressure compressor and do a complete
overhaul inspection.
2) Inspect the high pressure turbine blades and disks for
growth.
3) Do a fluorescent penetrant inspection of the high pressure
turbine blades and disks.
(c) Before you remove an engine for an overspeed indication, make
sure the tachometer indicating system operates correctly
(AMM 77-12-00/501).
S 982-105-P00
Set the overspeed indications.
(a) Push the MAX IND RESET switch on the forward electronic control
panel, P9.
(b) After you find the cause of the problem, erase the ENG EXCD
page from the EICAS memory.
1) Push the ENG EXCD switch on the EICAS maintenance panel at
the P61 panel.
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2) Push and hold the ERASE switch for three seconds.
After you find the cause of the problem, erase the PERF/APU
page from the EICAS memory.
1) Push the PERF/APU switch on the EICAS maintenance panel at
the P61 panel.
2) Push the AUTO-EVENT READ switch.
3) Push and hold the ERASE switch for three seconds.
Overtemperature Limits and Inspection Requirements (Fig. 205)
(c)
D.
(1)
(2)
(3)
S 862-157-P00
During an engine operation, an overtemperature condition occurs when
the fuel flow rate, high compressor rpm, or exhaust gas temperature
increases in large quantities over a short period of time.
S 992-153-P00
The maximum exhaust gas temperature limit is shown on this chart:
Engine Start and Operation Limits (AMM 71-00-00, Fig. 205).
S 992-176-P00
More detailed EGT limits data are shown on these charts:
(a) Engine Overtemperature Limits (For Ground Start And Engine
Operation Below Idle Speeds) (FIM 71-06-00, Fig. 104).
(b) Engine Overtemperature Inspection Requirements (All Run
Conditions Except For Ground Starting And Engine Operation
Below Idle Speeds) (FIM 71-05-00, Fig. 110).
S 862-151-P00
CAUTION:
_______
(4)
IF THE ENGINE HAS AN OVERTEMPERATURE CONDITION BECAUSE OF A
COMPRESSOR STALL, YOU MUST DO THE EMERGENCY ENGINE SHUTDOWN
PROCEDURE. IF YOU DO NOT DO THIS, CONTINUED ENGINE OPERATION
CAN CAUSE DAMAGE TO THE ENGINE.
If the engine has a compressor stall, do this task in the
Precautionary Procedures: Compressor Stall (AMM 71-00-00/201).
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128005
Not Used
Figure 207
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127994
Not Used
Figure 208
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S 862-158-P00
CAUTION:
_______
(5)
(6)
IF THERE IS NO COMPRESSOR STALL, YOU MUST NOT DO THE EMERGENCY
ENGINE SHUTDOWN PROCEDURE WHEN THERE IS AN OVERTEMPERATURE
CONDITION, UNLESS THE CONTINUED OPERATION WILL CAUSE MORE
DAMAGE. IF YOU DO A QUICK ENGINE SHUTDOWN, THE ENGINE WILL NOT
HAVE TIME TO COOL DOWN, AND THE HIGH TEMPERATURE WILL CAUSE
DAMAGE TO THE ENGINE.
If there is no compressor stall, but you think an overtemperature
condition will occur, or has occurred, you must do the steps that
follow.
(a) Move the forward thrust lever fully rearward to the applicable
minimum engine rpm.
(b) Let the engine operate at the applicable minimum rpm for a
minimum of five minutes to cool down the engine.
(c) Do this task: Engine Shutdown Procedure
(AMM 71-00-00/201).
S 972-149-P00
When the overtemperature occurs, the EICAS keeps a record of these
results on the EICAS EXCD page:
(a) Maximum EGT during the event.
(b) Length of time the EGT was more than the limit.
1) The length of overtemperature time is measured from the
yellow line limit under this condition:
a) During the engine operation at idle rpm or above, when
the maximum EGT is more than the yellow line limit, but
less than the red line limit.
2) The length of overtemperature time is measured from the red
line limit under each of these conditions:
a) During the engine start.
b) During the engine operation below idle rpm.
c) During the engine operation at, or above, idle rpm when
the maximum EGT is more than the red line limit.
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(7)
S 862-150-P00
The logic the EICAS uses to set an EGT exceedance during an engine
start is different than the logic used to set an EGT exceedance
during normal engine operation (after the engine start is complete).
NOTE:
____
The engine start is defined as: up to three minutes after
the fuel control switch is put into the RUN position, or
until the engine reaches 53% N2 rpm, whichever comes first.
NOTE:
____
True EGT exceedance events usually do not cause the EGT
indication to immediately "spike" to the maximum (red)
temperature range. Instead, EGT exceedances usually are
progressive events. Usually, if no corrective action is
taken, the EGT indication increases through the amber range
to the red range on the temperature dial. The logic for this
progressive change in the color of the EICAS EGT indication
is shown below.
(a)
(b)
(8)
During the engine start, an EGT exceedance changes the EICAS
EGT dial from white to red at 485 degrees C.
1) Although the maximum EGT limit begins at 545 degrees C and
decreases to 485 degrees C (over a 30-second period of
time), the EICAS EGT dial is set to turn from white to red
at the lower limit of 485 degrees C.
2) There is no amber EGT exceedance during the engine start.
After the engine start, during normal engine operation, the
EICAS EGT dial will turn from white to amber or red when the
conditions are as follows:
1) When the EGT is 615-630 degrees C for more than five
seconds, the EICAS EGT dial changes to amber.
2) When the EGT is 630-645 degrees C (no time delay is
necessary), the EICAS EGT dial changes to amber, or stays
amber if it already shows that color.
3) When the EGT is 645-660 degrees C for 0 to 5 seconds, the
EICAS EGT dial changes to amber, or stays amber if it
already shows that color.
4) When the EGT continues to be 645-660 degrees C for more
than five seconds, the EICAS EGT dial changes to red.
5) When the EGT is 660 degrees C or higher (no time delay is
necessary), the EICAS EGT dial changes to red, or stays red
if it already shows that color.
S 972-155-P00
You must record the EICAS EXCD data from all overtemperature
conditions, and keep this data with the permanent engine maintenance
records.
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S 212-156-P00
CAUTION:
_______
(9)
DO NOT START THE ENGINE AGAIN UNTIL YOU DO THE APPLICABLE
ENGINE INSPECTION. YOU MUST MAKE SURE THE TWO ROTORS TURN
CORRECTLY AND THERE IS NO DAMAGE TO THE ENGINE. IF YOU DO NOT
DO THIS, YOU CAN CAUSE DAMAGE TO THE ENGINE.
Look at the EICAS EXCD data for the overtemperature condition to
find the necessary inspection that you must do before you can start
the engine again.
(a) If the overtemperature event occured during the engine start,
or engine operation below idle rpm, do this procedure:
Hot Start (FIM 71-06-00, Fig. 104).
(b) If the overtemperature event occured during the engine
operation at, or above, idle rpm, do this procedure:
Engine Overtemperature Inspection Requirements
(FIM 71-05-00, Fig. 110).
S 212-120-P00
(10) Make sure the outer inter-turbine duct segments are not disengaged.
(a) Monitor the EGT to see if it increases by a large quantity of
approximately 20 degrees or more during a short time (from one
flight to the subsequent one).
(b) If the EGT increases by a large quantity, use a borescope to
see if the outer inter-turbine duct segments are disengaged
(AMM 72-00-00/601).
S 862-160-P00
(11) Erase the overtemperature indications.
(a) Push the MAX IND RESET switch on the forward electronic control
panel, P9.
(b) After the cause of the overtemperature is found, erase the ENG
EXCD page from the EICAS memory.
1) Push the ENG EXCD switch on the EICAS maintenance panel at
the P61 panel.
2) Push and hold the ERASE switch for 3 seconds.
(c) After the cause of the overtemperature is found, erase the
PERF/APU page from the EICAS memory.
1) Push the PERF/APU switch on the EICAS maintenance panel at
the P61 panel.
2) Push the AUTO-EVENT READ switch.
3) Push and hold the ERASE switch for 3 seconds.
S 862-154-P00
(12) If you did the emergency engine shutdown, but the EICAS EXCD data
shows that you did not go above the applicable EGT limits, do this
task to restart the engine: Start Procedure After An Emergency
Engine Shutdown (AMM 71-00-00/201).
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E.
S 212-159-P00
(13) It is permitted to ferry an airplane (with an engine which has had
an overtemperature condition) back to the maintenance base if you
obey the conditions that follow.
(a) Do this procedure: Overtemperature Visual Inspection
(AMM 72-00-00/601).
(b) Do this procedure: Overtemperature Hot Section Inspection
(AMM 72-00-00/601).
(c) If you find that the overtemperature condition was caused by a
line replaceable unit (LRU), you must replace the applicable
LRU.
(d) These conditions are permitted for only one of the two engines
on the airplane.
Leakage Limits
(1)
(2)
S 792-097-P00
The permitted leakage from the engine vents and drains during an
engine operation and after an engine shutdown, with the necessary
correction, is given in AMM 71-71-00/601, Engine Vents and Drains Inspection/Check.
S 792-098-P00
Fuel Leakage in the cowling is not permitted.
WARNING:
_______
(a)
(b)
(c)
(d)
(e)
F.
Ignition
KEEP OUT OF THE ENGINE HAZARD AREAS SHOWN IN FIGS. 201 AND
202 WHEN YOU EXAMINE THE NACELLE. IF YOU DO NOT KEEP OUT
OF THE ENGINE HAZARD AREAS, INJURY TO PERSONS OR DAMAGE TO
EQUIPMENT CAN OCCUR.
You can see the fuel leakage in the cowling during an engine
start, in the light of the day and in artificial light.
The fuel leakage is a fog-like spray off the bottom of the aft
lip of the turbine exhaust sleeve.
If you look at the aft part of the nacelle during an engine
start, you can see the fuel leakage.
If you see signs of a fuel leakage, you must stop the engine
start, or do the engine shutdown procedure if the engine is
started.
Do not start or operate the engine until the cause of the fuel
leakage is found and corrected.
Ground Use Limits
S 982-099-P00
Keep the ignition off during all maintenance ground operations after
the engine is started. This will keep a possible overtemperature
condition to a minimum if there is a compressor surge (stall).
Vibration Guidelines
(1)
G.
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S 712-134-P00
CAUTION:
_______
(1)
USE THIS VIBRATION GUIDELINE ONLY FOR THE GROUND TEST OF THE
ENGINES DURING THE MAINTENANCE. THE VIBRATION GUIDELINE IS NOT
FOR THE FLIGHT OPERATIONS.
Make sure the mean vibration indication is not more than the
permitted levels, as shown in Fig. 208A
NOTE:
____
H.
Make sure you check the vibration 30 seconds after the engine
becomes stable. This applies to all permitted engine speeds.
Oil Consumption Limits
(1)
S 972-144-P00
The maximum oil consumption that is permitted for an engine in
operation is an average of 0.6 quart (0.57 liter) in one hour,
calculated as an average over the last 25 hours of operation.
NOTE:
____
(2)
Divide the number of quarts (liters) of oil the engine has
used in the last 25 hours by the number 25. This will give
you the average number of quarts (liters) of oil that the
engine used for each hour of engine operation.
S 972-145-P00
If the oil consumption increases suddenly, or starts to increase
continuously, do the troubleshooting procedure for High Oil
Consumption (FIM 71-05-00/101).
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N1 INCHES PER SECOND (IPS)
1.75
1.0
.87
N1 VIBRATION INDICATION (AVM UNITS)
N1 ACCEPTANCE LEVEL
2.0
1.0
10
20
30
40
50
60
70
80
90
100
80
85
90
95
100
%N1
N2 INCHES PER SECOND (IPS)
1.75
1.0
.87
N2 VIBRATION INDICATION (AVM UNITS)
N2 ACCEPTANCE LEVEL
2.0
1.0
50
55
60
65
70
75
%N2
NOTE: THE CONVERSION FORMULA FROM AVM UNITS TO IPS IS :
____
3.1416 (277.885)(AVM UNITS)
IPS : ___________________________
1000
153055
N1 and N2 Vibration Acceptance Levels
Figure 208A
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I.
Precautionary Procedures
S 712-131-P00
CAUTION:
_______
(1)
DO NOT MOVE THE THRUST LEVER FORWARD ON AN ENGINE THAT HAS A
SURGE (STALL). YOU MUST ALWAYS MOVE THE THRUST LEVER REARWARD.
IF YOU DO NOT DO THIS, YOU CAN CAUSE DAMAGE TO THE ENGINE.
Compressor Surge
NOTE:
____
(a)
(b)
(c)
(d)
(e)
(f)
(g)
(h)
(2)
During an engine operation, it is possible to have a
compressor surge when you operate at high power in high
speeds of crosswinds, or tailwind conditions. If such an
incident occurs, keep one hand on the thrust lever and the
other hand on the FUEL CONTROL switch to make it easier for a
fast engine shutdown.
If a compressor surge (stall) occurs, quickly (in less than 1-2
seconds) move the thrust lever rearward to idle to make sure
the compressor surge (stall) stops.
1) Monitor the EGT.
2) Make sure the EGT and the fuel flow decreases.
Make sure the engine becomes stable.
Examine for fault messages on the EICAS and for the wind
conditions.
When there are satisfactory conditions, slowly move the thrust
lever forward to find out if the compressor surge (stall) will
occur again.
Monitor the that N2% rpm to make sure it follows the thrust
lever movement.
If the compressor surge (stall) does not stop and the EGT
increases, set the FUEL CONTROL switch to the CUTOFF position.
After the N2 rpm decreases to 20% or less, do the steps that
follow:
1) Engage the starter.
2) Motor the EGT until it is less than 180°C.
If the EGT was less than the limits, you can start the engine
again as specified for the start procedure after an emergency
engine shutdown.
S 912-103-P00
Starting Precautions
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CAUTION:
_______
(a)
Failure to Light Up
1) If the engine does not light up in 20 seconds or less
(30 to 35 seconds if it is the initial start after an
engine replacement or a maintenance on the engine fuel
system system) after the FUEL CONTROL switch is moved to
RUN, immediately put the FUEL CONTROL switch into CUTOFF.
2) Continue to motor the engine for a minimum of 30 seconds
(engage the starter at 20% N2 rpm or less, if it is
necessary) to remove the fuel from the engine or until the
EGT is less than 180°C.
3) Use the Power Plant Operation (Normal) procedure to do the
engine shutdown.
4) Examine the engine.
5) Correct the problem before you try to start the engine.
CAUTION:
_______
(b)
IF THE ENGINE DOES NOT LIGHT UP IN 20 SECONDS OR LESS
(30 TO 35 SECONDS IF IT IS THE INITIAL START AFTER AN
ENGINE REPLACEMENT OR A MAINTENANCE OF THE ENGINE FUEL
SYSTEM) AFTER THE FUEL CONTROL SWITCH IS MOVED TO RUN,
IMMEDIATELY PUT THE FUEL CONTROL SWITCH INTO CUTOFF. IF
YOU DO NOT OBEY THESE INSTRUCTIONS, AN ENGINE GROUND FIRE
OR A FLAME WHICH COMES OUT THE EXHAUST CAN OCCUR.
IF AN INSTANTANEOUS LIGHT UP OCCURS (LIGHT UP OCCURS IN 1
TO 2 SECONDS AFTER YOU PUT THE FUEL CONTROL SWITCH TO THE
RUN POSITION), IMMEDIATELY PUT THE FUEL CONTROL SWITCH
INTO THE CUTOFF POSITION. IF YOU DO NOT OBEY THESE
INSTRUCTIONS, YOU CAN CAUSE DAMAGE TO THE ENGINE.
Instantaneous Light Up
1) If an instantaneous light up occurs, immediately put the
FUEL CONTROL switch into CUTOFF.
2) Continue to motor the engine for a minimum of 30 seconds
(engage the starter at 20 percent N2 rpm or less, if it is
necessary) to remove the fuel from the engine or until the
EGT is less than 180°C.
3) Use the Power Plant Operation (Normal) procedure to do the
engine shutdown.
4) Examine the engine.
5) Correct the problem before you try to start the engine
again.
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CAUTION:
_______
(c)
IF THE N2 ACCELERATION IS NOT STABLE AFTER LIGHT UP AND
BEFORE 40% N2 AND THE EGT QUICKLY INCREASES THROUGH 425°C,
IMMEDIATELY PUT THE FUEL CONTROL SWITCH INTO THE CUTOFF
POSITION. IF YOU DO NOT OBEY THESE INSTRUCTIONS, YOU CAN
CAUSE DAMAGE TO THE ENGINE.
Sluggish N2 Acceleration
1) If the N2 acceleration is not stable after light up and
before 40% N2 and the EGT quickly increases through 425°C,
immediately put the FUEL CONTROL switch to the CUTOFF
position.
a) Continue to motor the engine until the EGT starts to
decrease.
2) Put the FUEL CONTROL switch to the RUN position to start
the engine again at maximum motor speed (25-35% N2).
CAUTION:
_______
(e)
AT THE CUTOUT SPEED OF THE
HIGHER, IMMEDIATELY PUT THE
CUTOFF POSITION. IF YOU DO
YOU CAN CAUSE DAMAGE TO THE
Compressor Stall
1) If a compressor stall occurs at the cutout speed of the
starter valve (51-52% N2) or higher, immediately put the
FUEL CONTROL switch into the CUTOFF position.
2) Continue to motor the engine for a minimum of 30 seconds
(engage the starter at 20% N2 rpm or less) or until the EGT
is less than 180°C.
3) Stop the engine.
4) Examine the engine (FIM 71-05-00 Fig. 103, Surge Occurred
Audible Stall).
5) If it is applicable, correct the problem before you start
the engine again.
CAUTION:
_______
(d)
IF A COMPRESSOR STALL OCCURS
STARTER VALVE (51-52% N2) OR
FUEL CONTROL SWITCH INTO THE
NOT OBEY THESE INSTRUCTIONS,
ENGINE.
IF THERE IS NO INDICATION THAT N1 STARTS TO TURN WHILE THE
EGT STARTS TO INCREASE, IMMEDIATELY PUT THE FUEL CONTROL
SWITCH INTO THE CUTOFF POSITION. IF YOU DO NOT OBEY THESE
INSTRUCTIONS, YOU CAN CAUSE DAMAGE TO THE ENGINE.
No indication that N1 starts to turn.
1) If a crewman on the ground does not see an indication that
the N1 turns as the EGT starts to increase, put the FUEL
CONTROL switch to the CUTOFF position.
a) Continue to motor engine for a maximum of three
minutes.
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b)
c)
d)
Turn the ENGINE START switch to the OFF position.
If the N1 does turn during the three minutes and the
EGT is less than 180°C, continue with the start
procedure.
If the N1 does not turn in three minutes, turn the
ENGINE START switch to the OFF position.
WARNING:
_______
MAKE SURE THE N1 AND N2 ROTORS ARE FULLY STOPPED
BEFORE YOU TRY TO MANUALLY TURN THE FAN. IF THE
N1 AND N2 ROTORS ARE NOT FULLY STOPPED, YOU CAN
CAUSE INJURY TO PERSONS.
WARNING:
_______
MAKE SURE THE PERSONS IN THE CONTROL CABIN AND
THE PERSONS WHO MANUALLY TURN THE FAN CAN SPEAK
TO EACH OTHER. IF YOU DO NOT OBEY THESE
INSTRUCTIONS DURING THE START, YOU CAN CAUSE
INJURY TO PERSONS.
e)
f)
g)
h)
After the engine has stopped, manually turn the fan one
or two turns counterclockwise.
Try to start the engine with the Power Plant Operation
(Normal) procedure.
If the N1 rotor is locked, manually turn the fan one or
two turns counterclockwise again (only do this one
time).
Try again to start the engine with the start (normal)
procedure.
NOTE:
____
If the N1 does not turn after three times
(initial plus two subsequent starts), do not try
to start again. Let the engine decrease in
temperature until the rotor moves freely. If
the rotor stays locked, find the cause and
correct it.
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CAUTION:
_______
(f)
Fuel or Ignition Interruption
1) If the fuel or ignition is stopped, immediately put the
FUEL CONTROL switch to the CUTOFF position. Continue to
motor the engine for a minimum of 30 seconds (engage the
starter at 20 percent N2 rpm or less, if it is necessary)
or until the EGT is less than 180°C.
2) Put the FUEL CONTROL switch to the RUN position to start
the engine again at the maximum speed you can motor (25-35%
N2).
CAUTION:
_______
(g)
IF THE FUEL OR IGNITION IS STOPPED, IMMEDIATELY PUT THE
FUEL CONTROL SWITCH TO THE CUTOFF POSITION. IF YOU DO NOT
OBEY THIS INSTRUCTION, YOU CAN CAUSE DAMAGE TO THE ENGINE.
IF THE ENGINE ACCELERATION TO IDLE IS VERY SLOW,
IMMEDIATELY PUT THE FUEL CONTROL SWITCH TO THE CUTOFF
POSITION. IF YOU DO NOT OBEY THIS INSTRUCTION, YOU CAN
CAUSE DAMAGE TO THE ENGINE.
Slow Engine Acceleration
1) If the engine acceleration to idle is very slow (goes near
90 seconds from the time you put the FUEL CONTROL switch to
the RUN position), put the FUEL CONTROL switch to the
CUTOFF position.
2) Continue to motor the engine for a minimum of 30 seconds
(engage the starter at 20% N2 rpm or less, if it is
necessary) or until EGT is less than 180°C.
3) Make sure the 2.5 and 14th-stage bleed valves are open
during the engine start or while the engine is stopped.
4) Examine the IDG for sufficient servicing
(AMM 12-13-03/301).
a) If the IDG has too much oil, change the IDG oil
(AMM 12-13-03/301).
5) Put the FUEL CONTROL switch to the RUN position to start
the engine again at the maximum speed you can motor (25-35%
N2).
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CAUTION:
_______
(h)
FOR A NEW ENGINE OR AN ENGINE WITH AN HPC WHICH WAS
REPAIRED, DO THE BOWED ROTOR PROCEDURE FOR ALL GROUND
OPERATION BEFORE THE FIRST FLIGHT. IF YOU DO NOT OBEY THE
BOWED ROTOR PROCEDURE, THE PERFORMANCE OF THE ENGINE CAN
DECREASE.
Bowed Rotor Procedure
1) Equipment
a) Motor Drive - SWE 18928K20
Rotating Kit, B. K. Sweeney
Manufacturing Co., Denver, CO
80216
NOTE:
____
2)
3)
4)
5)
This procedure is necessary when a new engine or an engine
with an HPC which was repaired is operated before the first
flight.
Its function is to prevent thermal distortions of the HPC
which can cause the rubstrips to not wear equally and the
engine performance can decrease.
You can use two basic procedures:
a) First, the Engine Cool Down procedure operates the
engine at the minimum idle for an extended time before
you do the engine shutdown procedure.
b) Second, the Engine Manual Rotation procedure
continuously or regularly turns the high pressure (HP)
rotor after you do the engine shutdown procedure.
This procedure is necessary if the engine was operated at a
power more than 1.15 EPR and the Engine Cool Down procedure
was not used.
NOTE:
____
6)
The Motor Drive is only
used with the Bowed Rotor
Procedure to give a
continuous manual turn of
the high pressure rotor.
If you start the engine again in less than 30
minutes or after more than six hours from the engine
shutdown, no special procedures are necessary.
Engine Cool Down Procedure
a) Before you do the engine shutdown, extend the time to
decrease the temperature of the engine at the minimum
idle to two times the time the engine was at the power
more than 1.15 EPR.
1
_
A minimum of five minutes and a maximum of 10
minutes is necessary.
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b)
7)
If the engine cool down procedure is used, you can
start the engine after the engine shutdown with no time
limit.
Engine Manual Rotation Procedure (Fig. 208B)
a) Remove the nuts which attach the crank drive cover to
the gearbox.
b) Remove the crank drive cover.
c) Use the torque wrench to make sure the HP rotor moves
freely.
1 If more than 75 pound-feet (101.7 newton-meters) are
_
necessary to turn the HP rotor, the rotor does not
move freely.
2 If the HP rotor does not move freely, examine the
_
movement each 30 minutes until it does move freely.
3 Turn the HP rotor 180 degrees.
_
d) When the HP rotor moves freely, install the motor drive
for a continuous turn or the hand crank to turn it
regularly.
NOTE:
____
If the HP rotor did not move freely, do not try
to start the engine for a minimum of 1 hour from
the time the HP rotor moved freely.
1
_
J.
If you turn it regularly, turn the HP rotor 180
degrees each 30 minutes until you try to start the
engine.
e) When you prepare to start the engine, remove the motor
drive or the hand crank.
f) Examine the HP rotor to make sure it moves freely in 15
minutes of the start.
g) If the HP rotor moves freely, do the steps that follow:
1 Lubricate the new packing with oil.
_
2 Lubricate the nuts with oil.
_
3 Install the crank drive cover with a new packing,
_
nuts and washers.
4 Tighten the nuts to 75-85 pound-inches
_
(8.474-9.604 newton-meters).
Thrust Reverser Guidelines
(1)
S 712-109-P00
You must use caution during an operation of the thrust reverser when
it is stopped with the engine in operation.
(a) Make sure the area around the engine is clean and there is no
unwanted material which can cause foreign object damage (FOD).
(b) For the maintenance, the limit for the engine operation in
reverse thrust is minimum idle power.
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SEE
A
NUT
WASHER
MANUAL CRANK
PAD COVER
A
A
A
PREFORMED
PACKING
COVER
CRANK DRIVE
1
A-A
1
TURN THE CRANK DRIVE 1/3 OF A TURN (120`-130`)
TO GET 180` OF A TURN OF THE HP ROTOR
252250
Bowed Rotor
Figure 208B
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K.
Cowling Limits
(1)
S 912-106-P00
The engine operation is usually done with all cowling closed and
locked.
S 712-006-P00
WARNING:
_______
(2)
IF YOU OPEN THE FAN COWL PANELS, YOU MUST NOT OPERATE THE
ENGINE AT MORE THAN IDLE RPM, OR OPERATE THE ENGINE IN REVERSE
THRUST. YOU MUST NOT OPERATE THE ENGINE WITH OPEN FAN COWL
PANELS IF THE WIND SPEED IS MORE THAN 20 KNOTS, OR IF THE WIND
GUSTS ARE MORE THAN 30 KNOTS. ALSO, YOU MUST INSTALL THE TWO
HOLD-OPEN RODS ON EACH FAN COWL PANEL THAT IS OPEN. IF YOU DO
NOT OBEY THESE INSTRUCTIONS, DAMAGE TO THE ENGINE OR FAN COWL
PANELS, AND INJURY TO PERSONS CAN OCCUR.
You can operate the engine with the fan cowl panels in the open or
closed position, but if you operate with them open, you must obey
the instructions that follow:
(a)
(b)
Make sure the airplane is static (not towed or taxied).
Make sure fire extinguishing equipment is available.
NOTE:
____
(c)
(d)
(e)
The airplane fire detection and extinguishing functions
are reduced when the fan cowls are open.
Do not operate the engine with the open fan cowl panels if the
wind speed is more than 20 knots.
Do not operate the engine with the open fan cowl panels if the
wind gusts are more than 30 knots.
Do not operate the engine in reverse thrust.
NOTE:
____
You must operate the engine in forward thrust only.
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(f)
(g)
Do not operate the engine at more than idle RPM with the fan
cowl panels open.
Each fan cowl panel has two hold-open rods. You must install
the two hold-open rods on each open fan cowl panel to safely
keep it in the open position.
NOTE:
____
L.
Make sure each hold-open rod is fully extended and
locked.
Electronic Engine Control Limits
S 712-107-P00
The EEC gives the takeoff EPR at the full forward position of the
thrust levers.
Start Procedure After An Emergency Engine Shutdown
(1)
M.
NOTE:
____
An emergency engine shutdown is an engine shutdown from the power
levels more than the minimum idle because of a compressor surge or
other emergency conditions. This procedure is only for an engine,
which is started after an emergency engine shutdown, for a ground
test of the engine during maintenance.
S 912-132-P00
CAUTION:
_______
YOU MUST OBEY THE INSTRUCTIONS FOR THE START PROCEDURE AFTER AN
EMERGENCY ENGINE SHUTDOWN. IF YOU DO NOT OBEY THESE
INSTRUCTIONS, YOU CAN CAUSE DAMAGE TO THE TIP SEALS OF THE
TURBINE BLADES.
THIS PROCEDURE IS NOT FOR FLIGHT OPERATIONS. THIS PROCEDURE IS
FOR AN ENGINE, WHICH IS STARTED AFTER AN EMERGENCY ENGINE
SHUTDOWN, FOR A GROUND TEST OF THE ENGINES DURING MAINTENANCE.
THE FUNCTION OF THIS PROCEDURE IS TO KEEP THE DAMAGE TO THE TIP
SEALS A MINIMUM.
(1)
If the EGT was not more than the limits and the two rotors move
freely, you can start the engine again with the applicable step that
follows:
(a) If you can start the engine in a time not more than 15 minutes
from time of the engine shutdown:
1) Start the engine with the Power Plant (Normal) Operation
procedure.
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2)
(b)
(2)
Stay at the minimum idle rpm for a minimum of 15 minutes
before you increase the speed to a higher power.
If you cannot start the engine in 15 minutes from the time of
the engine shutdown:
1) Stop for a minimum of 50 minutes from the time of the
engine shutdown before you try to start the engine again.
2) After the 50-minutes, make sure the two rotors turn freely.
3) If the two rotors turn freely, motor the engine for
approximately two minutes to permit the engine to become
cool.
4) After you motor the engine, permit the engine to become
cool for five minutes before you motor again.
5) After the five minutes, do the steps that follow:
a) Motor the engine for two more minutes.
b) Try to start the engine again with the Power Plant
Operation (Normal) procedure.
6) Stay at the minimum idle rpm for a minimum of 15 minutes
before you increase the speed to a higher power.
S 112-018-P00
Clean the engine gaspath after the fire extinguishing agents are
used (AMM 72-00-00/701).
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______________________________
4.
TASK 71-00-00-862-001-P00
Power Plant Operation (Normal)
______________________________
A. General
(1) This procedure contains the instructions necessary to operate the
engine during the permitted conditions.
(2) You can use this procedure to examine the operation of the engine or
the related systems when the engine operation is necessary.
(3) During cold weather, it is possible you must prepare the engine,
increase the temperature for example, before you try to start it.
(4) Use the Power Plant Operation (Cold Weather) procedure to operate
the engine in cold weather.
(5) It is important to have a clean engine compartment because the large
quantity of mass airflow can pull unwanted material into the engine.
(a) You must fully clean and examine the area after you are done
with the work.
(b) Make sure there is no dirt, oil, or grease in the inlet area.
(c) Remove all parts which are not used, for example, nuts,
washers, and pieces of lockwire.
(6) To prevent corrosion in the compressor stages and damage to the fan,
you are recommended to install the applicable covers on the engine
inlet and exhaust when it is possible.
(7) When the temperature is less than 0°C (32°F) or there is sufficient
wind to turn the engine, it is important to immediately install the
covers on the engine.
(8) AIRPLANES PRE-SB 73-0029;
Personnel must stay clear of the engine inlet and exhaust hazard
areas when electrical power transfer occurs during the engine start,
as the air/ground relays can cause the engine(s) to temporarily
increase to approach idle rpm, then decrease back to minimum idle
rpm.
B. Equipment
(1) Service interphone equipment
(2) Engine inlet cover
(3) Engine exhaust covers (fan and turbine)
(4) 2037 Engine Safety Barrier - A71042-1
C. References
(1) AMM 10-11-01/201, Normal Parking
(2) AMM 12-11-01/301, Fuel Tank
(3) AMM 12-12-01/301, Hydraulic Systems
(4) AMM 12-13-01/301, Engine
(5) AMM 12-13-02/301, Engine Starter (oil servicing)
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(6)
(7)
(8)
(9)
(10)
(11)
(12)
D.
AMM
AMM
AMM
AMM
AMM
AMM
AMM
24-22-00/201,
26-21-00/501,
29-11-00/201,
32-00-20/201,
36-00-00/201,
54-52-01/601,
71-00-00/201,
(13) AMM 71-01-02/201,
(14) AMM 71-11-04/201,
(15) AMM 71-11-06/201,
(16) AMM 74-21-01/601,
(17) AMM 78-31-00/201,
Prepare for the Engine
(1)
(2)
(3)
Electrical Power - Control
Engine Fire Extinguishing System - Adjustment/Test
Main Hydraulic Systems
Landing Gear Downlocks
Pneumatic - General
Strut Forward Fairing
Powerplant - Maintenance Practices (Engine Ground
Safety Precautions)
Engine Trim (Trim Tables)
Fan Cowl Panels
Core Cowl Panels
Exciter to Igniter Plug Cable
Thrust Reverser System
Operation
S 862-173-P00
Do this task: Engine Ground Safety Precautions
(AMM 71-00-00/201).
S 862-002-P00
Make sure the airplane is parked in a clean area with the wheels on
areas that do not have oil, grease, or other wet materials
(AMM 10-11-01/201).
S 492-003-P00
Make sure the landing gear downlocks are installed
(AMM 32-00-20/201).
S 912-004-P00
CAUTION:
_______
(4)
MAKE SURE THE WHEEL CHOCKS ARE INSTALLED WHEN YOU OPERATE ONE
OR BOTH ENGINES AT TAKEOFF POWER. IF YOU DO NOT INSTALL THE
WHEEL CHOCKS WHEN YOU OPERATE THE ENGINES AT TAKEOFF POWER, THE
AIRPLANE CAN JUMP THE CHOCKS AND MOVE EVEN THOUGH FULL BRAKE
PRESSURE IS APPLIED. THIS CAN CAUSE DAMAGE TO THE AIRPLANE.
Put chocks 6 to 12 inches (15 to 30 cm) in front and aft of the nose
and all main landing gear tires.
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S 862-005-P00
CAUTION:
_______
(5)
(6)
MAKE SURE YOU HAVE THE NECESSARY CONDITIONS FOR THE MINIMUM
GROSS WEIGHT, NOSE WHEEL POSITION, AND GROUND/TIRE SURFACE TO
PREVENT AN AIRPLANE SKID DURING AN ENGINE OPERATION AT HIGH
POWER. IF YOU DO NOT HAVE THE NECESSARY CONDITIONS, AN
AIRPLANE SKID CAN OCCUR AT HIGH POWER AND DAMAGE TO THE
AIRPLANE CAN OCCUR.
For an engine operation at high power, you must have the necessary
conditions of the minimum gross weight, nose wheel position, and
ground/tire surface (Ref Airplane Skidding Prevention for High Power
Operation).
S 862-006-P00
For the operation of each engine:
(a) Remove the engine inlet and exhaust covers, if they are
installed.
(b) Remove the covers for the pitot probes, if they are installed.
(c) Attach the engine safety barrier at the inlet area, if it is
necessary.
(d) Examine the air inlet, fan and turbine exhaust areas, wing
leading edge immediately above the engine, and the ground area
around the engine for unwanted material.
CAUTION:
_______
(e)
DO NOT OPERATE THE AIRPLANE HYDRAULIC SYSTEMS UNLESS THE
FUEL QUANTITY IS SUFFICIENT TO GO ABOVE THE HEAT
EXCHANGERS FOR THE HYDRAULIC FLUID. IF YOU OPERATE THE
AIRPLANE HYDRAULIC SYSTEMS WITHOUT SUFFICIENT FUEL, YOU
CAN CAUSE DAMAGE TO THE AIRPLANE HYDRAULIC SYSTEMS.
Make sure there is a minimum of 600 gallons (4,020 pounds/1,823
kilograms) of fuel in each main (wing) tank to fully cover the
heat exchangers.
NOTE:
____
The total fuel load for the airplane must be a minimum
of 1,200 gallons (8,040 pounds/3,647 kilograms) for the
heat exchangers. If you will operate the engines on the
ground, you must add more fuel to each tank for the
amount of time you will operate the engines.
1)
(f)
If it is necessary, do the servicing procedure for the fuel
tanks (AMM 12-11-01/301).
2) Make sure the fuel tank sumps are free of water.
Examine the hydraulic fluid reservoir for sufficient servicing
(you can see the fluid in the sight gages on the reservoirs).
1) If servicing is necessary, do the servicing procedure for
the hydraulic fluid reservoirs (AMM 12-12-01/301).
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CAUTION:
_______
(g)
(h)
(i)
(j)
(k)
(l)
(m)
(7)
(8)
BEFORE YOU OPEN THE OIL TANK CAP, PERMIT A MINIMUM OF FIVE
MINUTES AFTER THE ENGINE SHUTDOWN TO LET THE PRESSURE IN
THE OIL TANK BLEED OFF. A FAST FLOW OF HOT OIL CAN OCCUR
AND CAUSE INJURY TO YOU.
Examine the engine oil tank for sufficient servicing
(AMM 12-13-01/301).
1) Before you install the oil tank cap, examine the packing to
make sure there is no damage or deterioration.
Examine the engine starter for sufficient servicing.
1) If servicing is necessary, do the servicing procedure for
the engine starter (AMM 12-13-02/301).
Examine the IDG for sufficient servicing.
1) If servicing is necessary, do the servicing procedure for
the IDG (AMM 12-13-03/301).
Make sure the forward fairing is installed correctly
(AMM 54-52-01/601).
Make sure the fan duct cowl and the thrust reverser is closed
and latched (AMM 78-31-00/201).
Make sure the fan cowl panels are closed and latched
(AMM 71-11-04/201).
Make sure the core cowl panels are closed and latched
(AMM 71-11-06/201).
S 862-162-P00
Make sure you have the conditions that follow (Fig. 209):
(a) The forward thrust lever is at idle.
(b) The reverse thrust lever is in the forward position.
(c) The FUEL CONTROL switch is in the CUTOFF position.
(d) On the aft electronic control panel, P8, make sure the fire
handles are fully in.
S 862-007-P00
Make sure the control surfaces and the controls agree.
S 862-008-P00
CAUTION:
_______
(9)
KEEP THE LEFT AND RIGHT HYDRAULIC SYSTEMS PRESSURIZED DURING
THE OPERATION OF THE TEST. IF YOU DO NOT KEEP THE HYDRAULIC
SYSTEM PRESSURIZED, THE PERFORMANCE OF THE AIRPLANE CONTROL CAN
DECREASE.
Supply hydraulic power (AMM 29-11-00/201).
S 862-009-P00
(10) Make sure the towing lever on the steering metering valve is in the
NORMAL position.
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SEE
A
FLIGHT COMPARTMENT
FORWARD
THRUST
LEVERS
REVERSE
THRUST
LEVERS
CONTROL
STAND
2
SEE
B
1
ENG
VALVE a
REV
ISLN a
SPAR
VALVE a
L
FUEL CONTROL
ENG
VALVE a
SPAR
VALVE a
FUEL
CONTROL
SWITCHES
R
RUN
CUTOFF
L ENG
LIM PROT a
A
R ENG
LIM PROT a
B
1
AIRPLANES WITHOUT THRUST REVERSER SYNC LOCKS
2
AIRPLANES WITH THRUST REVERSER SYNC LOCKS
127997
Engine Fire Emergency Shutdown
Figure 209
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S 862-010-P00
(11) Put the parking brake ON.
S 862-011-P00
(12) Supply electrical power (AMM 24-22-00/201).
S 862-012-P00
(13) Make sure the six EICAS circuit breakers are closed.
S 862-161-P00
WARNING:
_______
MAKE SURE YOU OPEN THE CIRCUIT BREAKERS FOR THE WEATHER RADAR
SYSTEM BEFORE YOU OPERATE THE ENGINE. IF YOU DO NOT, YOU CAN
CAUSE SERIOUS INJURY OR DEATH TO PERSONS AND DAMAGE TO
EQUIPMENT.
(14) Open
P11,
(a)
(b)
these circuit breakers on the overhead circuit breaker panel,
and attach the DO-NOT-CLOSE tags:
11F2, WEATHER RADAR LEFT
11F34, WEATHER RADAR RIGHT
S 862-013-P00
(15) For the left engine, make sure this circuit breaker on the overhead
circuit breaker panel, P11, is closed:
(a) 11K9, LEFT ENGINE OIL PRESS
S 862-014-P00
(16) For the right engine, make sure this circuit breaker on the overhead
circuit breaker panel, P11, is closed:
(a) 11K35, RIGHT ENGINE OIL PRESS
E.
S 862-015-P00
(17) Supply pneumatic power (AMM 36-00-00/201).
Operate the Engine
(1)
S 862-016-P00
Do the prestart procedure.
(a) Prepare the check sheet to make a record of the engine data
during the start and the ground operations.
(b) Make sure the LIM PROT light is not on.
(c) With the trim table section (AMM 71-01-02/201) or the value
calculated by the thrust management computer, find the takeoff
EPR target for the ambient temperature and the true barometric
pressure.
(d) On the pilot's overhead panel, P5, make sure the components
that follow are in the specified position:
1) Isolation Valve - Open
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2)
3)
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Applicable Engine (Bleed) Valve Light - Switch in (OFF
light is on)
Pack Valves - Packoff (2)
WARNING:
_______
4)
Applicable Boost Pump Switches - ON
NOTE:
____
(e)
(f)
(h)
(i)
Continuously monitor the fuel quantity and the low
pressure light indication for the applicable main
fuel tank(s) when you operate the boost pumps.
Immediately put the applicable fuel pump switch(es)
in the OFF position if the LOW PRESSURE light comes
on and stays on.
5) Crossfeed Valve - Closed
6) Wing Anti-Ice Switch - Off
7) Engine Anti-Ice Switches - Off
Do the operational test of the engine fire detection system
(AMM 26-11-00/501).
Do the operational test of the fire extinguishing system
(AMM 26-21-00/501).
CAUTION:
_______
(g)
DO NOT OPERATE THE FUEL BOOST PUMP IF THE LOW
PRESSURE LIGHT COMES ON AND STAYS ON. FUEL VAPORS IN
THE TANK MAY IGNITE AND CAUSE A FIRE OR EXPLOSION.
WHEN YOU RUN THE ENGINE, GROUND OPERATIONS DATA WILL
RECORD OVER THE OLDEST FLIGHT LEG DATA ON THE RECORDER.
IF YOU DO NOT WANT TO ERASE THE DATA FROM THE OLDEST
FLIGHT LEG, YOU MUST OPEN THE CIRCUIT BREAKERS FOR THE
RECORDER BEFORE YOU START THE ENGINE. FAILURE TO DO THIS
WILL CAUSE THE OLDEST FLIGHT LEG DATA TO BE ERASED.
If you do not want to record ground run data over the oldest
flight leg data on the flight recorder, open these circuit
breakers on the overhead circuit breaker panel, P11, and attach
the DO-NOT-CLOSE tags:
1) 11J7, FLIGHT RECORDER AC
2) 11J8, FLIGHT RECORDER DC
For the left engine, make sure these circuit breakers on the
P11 panel are closed:
1) 11D7, ENGINE STBY IGNITION LEFT 1
2) 11D8, ENGINE STBY IGNITION LEFT 2
3) 11D19, ENGINE START CONT LEFT
4) 11L1, LEFT ENGINE IGNITION 1
5) 11L35, SEC D ENGINE START CONT L
For the right engine, make sure these circuit breakers on the
P11 panel are closed:
1) 11D9, ENGINE STBY IGNITION RIGHT 1
2) 11D10, ENGINE STBY IGNITION RIGHT 2
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(j)
3) 11D20, ENGINE START CONT RIGHT
4) 11L28, RIGHT ENGINE IGN 1
For the left engine, make sure this circuit breaker on the P11
panel is closed:
1) 11R14, ENG PROBE HTR LEFT
For the right engine, make sure this circuit breaker on the P11
panel is closed:
1) 11R23, ENG PROBE HTR RIGHT
Make sure these circuit breakers on the main power distribution
panel, P6, are closed:
1) 6L15, PITOT HEAT CAPT MAIN
2) 6L16, PITOT HEAT L AUX
3) 6L21, PITOT HEAT R AUX
4) 6L22, PITOT HEAT F/O MAIN
(k)
(l)
(2)
S 862-017-P00
Start the engine (ground low pressure or APU air source).
NOTE:
____
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(a)
During the start procedure, monitor the aft part of the
nacelle for signs of fuel leakage as specified in the Leakage
Limits in the cowling.
On the pilot's overhead panel, P5, make sure the components
that follow are in the specified positions.
WARNING:
_______
1)
DO NOT OPERATE THE FUEL BOOST PUMP IF THE LOW
PRESSURE LIGHT COMES ON AND STAYS ON. FUEL VAPORS IN
THE TANK MAY IGNITE AND CAUSE A FIRE OR EXPLOSION.
For the fuel tank on the same side as the engine which will
be started, put all the boost pump switches in the ON
position.
NOTE:
____
Continuously monitor the fuel quantity and the low
pressure light indication for the applicable main
fuel tank(s) when you operate the boost pumps.
Immediately put the applicable fuel pump switch(es)
in the OFF position if the LOW PRESSURE light comes
on and stays on.
a)
2)
3)
Make sure the two applicable low fuel pressure lights
go off.
If you use the ground low pressure air source to start the
engine:
a) Close the APU VALVE.
If the APU is used for the air source:
a) Open the APU VALVE.
b) Close the isolation valve for the engine which is not
started.
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4)
Put the ignition start switch to 1 or 2 for a one igniter
start, or to BOTH for a two igniter start (Fig. 210).
NOTE:
____
You can use one or two igniters for ground starts.
Use the opposite ignition system in subsequent one
igniter starts.
CAUTION:
_______
(b)
MAKE SURE THE ENGINE START SWITCH DOES NOT RELEASE FROM
GND UNTIL YOU GET 51-52% N2 RPM. FAILURE OF THE ENGINE
START SWITCH TO STAY IN THE GND POSITION UNTIL 51-52% N2
RPM CAN CAUSE A HOT START WITH SUBSEQUENT ENGINE DAMAGE.
YOU MUST USE THE STARTER OPERATION LIMITS OR YOU CAN CAUSE
DAMAGE TO THE STARTER.
Put the applicable ENGINE START switch in the GND position
(Fig. 210).
1) Make sure the start VALVE light goes on and then goes off.
2) Turn the ENGINE START switch to the OFF position if you do
not see an indication that the N2 turns in 10 seconds or
less.
NOTE:
____
CAUTION:
_______
(c)
The EICAS must show N2 before you put the fuel
switch to the RUN position.
USE THE ENGINE STARTING PRECAUTIONS IN THE PRECAUTIONARY
PROCEDURES. IF YOU DO NOT USE THESE PRECAUTIONS, YOU CAN
CAUSE DAMAGE TO THE ENGINE.
When the N2 rpm indication shows that the engine is at the
maximum motoring speed (but not less than 18% N2 rpm), put the
fuel control switch to the RUN position.
1) Monitor the N1, N2, and the EGT indications while the light
up occurs.
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SEE A
P11 PANEL
P5 PANEL
FLIGHT COMPARTMENT
RAM AIR TURB
PRESS g
UNLKDa
ENG START
BOTH
1
2
L
VALVE
GND
R
VALVE
a
AUTO OFF
GND
a
AUTO OFF
CONT
CONT
FLT
FLT
A
127998
Engine Start and Ignition Module
Figure 210
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______________________________
2)
(d)
If the person on the ground makes sure the N1 turns, you
can continue to do the start procedure although the EGT
increases with no N1 indication on the RPM indications.
3) If the person on the ground does not see the N1 turn as the
EGT increases, immediately do the procedure when there is
no indication that the N1 turns (Refer to the Starting
Precautions of the Precautionary Procedures).
Look at the specified engine indications (on EICAS) while the
engine lights up and the speed increases to idle.
NOTE:
____
1)
2)
3)
4)
5)
6)
7)
The EICAS will not show the EPR and the EGT values until
12-13% N2. This is not unusual.
Light up - the EGT increases in 20 seconds or less (30 to
35 seconds if it is the initial start after an engine
replacement or maintenance on the engine fuel system).
Engine Oil Pressure - increases
The Warning Light for Low Oil Pressure goes off at a
minimum of 80 psi.
Fuel Flow at Light up - Usually 400 pph to 550 pph
EGT - less than 485°C
Push the ELEC/HYD switch on the EICAS maintenance panel.
Make sure there is a small IDG RISE indication (6°C).
NOTE:
____
(e)
A small IDG RISE indication is a sign that the IDG
oil cooling system operates correctly.
Make sure the ENGINE START switch moves to the AUTO position at
51-52% N2 rpm.
NOTE:
____
1)
2)
3)
4)
When the ENGINE START switch releases, it suddenly
causes the engine to get back the pneumatic duct
pressure.
Make sure the start VALVE light goes on and then goes off.
If the ENGINE START switch does not move to the AUTO
position at 51-52% N2, manually turn the ENGINE START
switch to the AUTO position.
Make sure the start VALVE light goes on and then goes off.
If the start VALVE light does not go off, do the following:
a) Put the L(R) ENGINE BLEED AIR switch to the OFF
position.
b) Close the ISOLATION VALVE.
c) Put the APU BLEED AIR switch to the OFF position.
d) Put the FUEL CONTROL switch in the CUTOFF postion.
e) Disconnect GROUND AIR source (if in use).
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______________________________
(f)
Let the speed of the engine increase to minimum idle (Use the
Trim Tables, AMM 71-01-02, Fig. 202).
NOTE:
____
After the FUEL CONTROL switch is put to the RUN
position, you are permitted no more than 90 seconds to
increase the engine speed to the minimum idle. If a
hung start occurs, stop the start procedure, and find
and correct the cause for no acceleration.
1)
(g)
Permit the engine to become stable at the rpm for the
minimum idle.
Make sure you have these approximate specified indications:
1) EPR - 1.00-1.01
2) N1 rpm - 19-21%
3) Fuel Flow - 890 pph
4) EGT - less than 460°C (10.0 service bleed closed)
less than 490°C (10.0 service bleed open)
5) N2 rpm - use the Trim Tables (AMM 71-01-02, Fig. 202)
6) Oil Quantity - 13-15 quarts
NOTE:
____
(h)
(i)
(j)
(k)
(l)
(3)
The oil quantity indication decreases when you start
the engine. This condition occurs because the oil
is removed from the oil tank and into the empty
spaces above the oil tank level. The oil quantity
indication will go to the usual indication after the
engine is stopped.
7) Oil Temperature - less than 163°C
8) Oil Pressure - 70 psi minimum.
9) Engine Vibration - see Fig. 208A
Make sure the pressure of the hydraulic system becomes stable
between 2850 and 3075 psi.
Remove pneumatic power if it is not necessary
(AMM 36-00-00/201).
Remove electrical power if it is not necessary
(AMM 24-22-00/201).
Remove hydraulic power if it is not necessary
(AMM 29-11-00/201).
If the APU was used for an air source during the start, put the
APU VALVE switch to the closed position.
S 862-018-P00
Start the engine (pneumatic cross start - engine bleed air).
(a) Operate the engine which is used as a pneumatic source at idle.
(b) Make sure you do the steps from above to Prepare the Engine for
Operation.
(c) Do the prestart procedure:
1) Prepare the check sheet to make a record of the engine data
during a start and a ground operation.
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______________________________
ú
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On the pilot's overhead panel, P5, make sure the components
that follow are in the specified positions.
a) Isolation Valve - Open
b) Applicable engine (Bleed) Valve Light - Switch in (OFF
light is on)
c) Pack Valves - Packoff (2)
d) Crossfeed Valve - Closed
WARNING:
_______
e)
Boost Pump Switches - ON
NOTE:
____
(d)
(e)
(f)
(g)
(h)
(i)
DO NOT OPERATE THE FUEL BOOST PUMP IF THE LOW
PRESSURE LIGHT COMES ON AND STAYS ON. FUEL
VAPORS IN THE TANK MAY IGNITE AND CAUSE A FIRE OR
EXPLOSION.
Continuously monitor the fuel quantity and the
low pressure light indication for the applicable
main fuel tank(s) when you operate the boost
pumps. Immediately put the switch(es) in the
OFF position if the LOW PRESSURE light comes on
and stays on.
f) APU Valve - Closed
g) Wing Anti-Ice Switch - Off
h) Engine Anti-Ice Switches - Off
For the left engine, make sure these circuit breakers on the
overhead circuit breaker panel, P11, are closed.
1) 11D7, ENGINE STBY IGNITION LEFT 1
2) 11D8, ENGINE STBY IGNITION LEFT 2
3) 11D19, ENGINE START CONT LEFT
4) 11L1, LEFT ENGINE IGNITION 1
5) 11L35, SEC D ENGINE START CONT L
For the right engine, make sure these circuit breakers on the
overhead circuit breaker panel, P11, are closed:
1) 11D9, ENGINE STBY IGNITION RIGHT 1
2) 11D10, ENGINE STBY IGNITION RIGHT 2
3) 11D20, ENGINE START CONT RIGHT
4) 11L28, RIGHT ENGINE IGN 1
Make sure the six EICAS circuit breakers on the overhead
circuit breaker panel, P11, are closed.
For the left engine, make sure this circuit breaker on the
overhead circuit breaker panel, P11, is closed:
1) 11K9, LEFT ENGINE OIL PRESS
For the right engine, make sure this circuit breaker on the
overhead circuit breaker panel, P11, is closed:
1) 11K35, RIGHT ENGINE OIL PRESS
Increase the power on the engine in operation until you get 70%
N2 rpm (the duct pressure must stay between a minimum of 30-40
psi).
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(j)
(k)
(4)
Continue to do the start procedure with the ground low pressure
or the APU air source.
Decrease the engine used for the pneumatic cross start to
minimum power after the starter valve releases on the engine
which is started.
S 712-118-P00
Engine Manual Start
WARNING:
_______
THE MANUAL OVERRIDE FOR THE STARTER CONTROL VALVE IS IN
THE INLET HAZARD AREA OF THE IDLE POWER ENGINE. WHEN YOU
DO THE MANUAL ENGINE START, STAY FAR AFT AS PERMITTED FOR
EASY OPERATION OF THE MANUAL OVERRIDE. (YOU ARE PERMITTED
TO PUT YOUR ARMS IN THE INLET HAZARD AREA, BUT YOU CANNOT
PUT YOUR BODY IN THE INLET HAZARD AREA.)
WARNING:
_______
WHEN YOU MANUALLY OPERATE THE STARTER CONTROL VALVE, YOU
MUST WEAR COVERS ON YOUR HANDS AND ARMS. THE HEAT AND AIR
FLOW FROM THE STARTER CONTROL VALVE CAN CAUSE INJURY TO
PERSONS.
CAUTION:
_______
YOU MUST HAVE AIR PRESSURE IN THE INLET DUCT IF YOU
MANUALLY OPERATE THE STARTER CONTROL VALVE. IF YOU DO NOT
HAVE AIR PRESSURE, YOU CAN CAUSE DAMAGE TO THE STARTER
CONTROL VALVE.
(a)
If the electrical circuit for the starter control valve does
not operate, use the manual override to operate the starter
control valve.
1) Make sure the persons in the control cabin can hear the
persons on the ground.
2) Install a 3/8 inch square drive with an 18 inch extension
through the access port in the fan cowl.
NOTE:
____
3)
4)
Make sure the fan cowl is closed.
Engage the 3/8 inch square drive in the override receptacle
on the starter control valve.
Do the Power Plant Operation (Normal) procedure but use the
steps that follow when it is applicable:
a) When the engine start switch for the starter control
valve, which does not operate, is put in the GND
position, tell the person on the ground to open the
starter control valve.
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______________________________
CAUTION:
_______
b)
When you get to 50-52% N2 RPM, tell the persons on the
ground to close the starter control valve.
Make sure the engine start switch goes back to the AUTO
position.
c)
(5)
(6)
MAKE SURE THE MANUAL OVERRIDE RELEASES AT 50-52%
N2 RPM. IF THE MANUAL OVERRIDE IS NOT RELEASED
AT 50-52% N2 RPM, IT IS POSSIBLE THE STARTER HAS
DAMAGE.
S 862-019-P00
Operate the engine and the related systems.
(a) If you operate the engine at high power, open these circuit
breakers on the overhead circuit breaker panel, P11, and attach
DO-NOT-CLOSE tags to disconnect the the Aural Warning Speakers:
1) 11B16, AURAL WARN SPKR LEFT
2) 11H35, AURAL WARN SPKR RIGHT
S 862-020-P00
Engine Shutdown Procedure
(a) Do the Power Plant Operation (Normal) procedure.
1) Move the forward thrust lever rearward to operate at
minimum power.
CAUTION:
_______
2)
Permit the engine to become cool for a minimum of five
minutes.
CAUTION:
_______
3)
DO NOT DO THE ENGINE SHUTDOWN WITHOUT SUFFICIENT AIR
TO DECREASE THE TEMPERATURE OF THE ENGINE. IF YOU DO
NOT ADD SUFFICIENT AIR, YOU CAN CAUSE DAMAGE TO THE
TURBINE WHEEL.
FOR A NEW ENGINE OR AN ENGINE WITH AN HPC WHICH WAS
REPAIRED, DO THE BOWED ROTOR PROCEDURE FOR ALL GROUND
OPERATION BEFORE THE FIRST FLIGHT. IF YOU DO NOT
OBEY THE BOWED ROTOR PROCEDURE, THE PERFORMANCE OF
THE ENGINE CAN DECREASE.
For an engine which is new or has an HPC which was
repaired, do the Bowed Rotor procedure for all ground
operation before the first flight.
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POWER PLANT OPERATION (NORMAL)
______________________________
CAUTION:
_______
4)
5)
6)
7)
8)
DO NOT DO THE ENGINE SHUTDOWN WHEN THERE IS AN
INTERNAL ENGINE FIRE UNLESS YOU SUPPLY PNEUMATIC
POWER TO MOTOR THE ENGINE WITH THE STARTER. IF YOU
DO NOT SUPPLY PNEUMATIC POWER, YOU CAN CAUSE DAMAGE
TO THE ENGINE.
Supply pneumatic power (AMM 36-00-00/201).
Make sure the PACK VALVES are OFF.
Make sure the ISOLATION VALVES are open.
Supply electrical power from the source other than the
engine which the test is done on (AMM 24-22-00/201).
Put the FUEL CONTROL switch in the CUTOFF position.
CAUTION:
_______
IF YOU DO NOT IMMEDIATELY SEE THE INDICATIONS OF
AN ENGINE SHUTDOWN, YOU MUST FIND THE CAUSE AND
CORRECT IT BEFORE THE SUBSEQUENT START. FAILURE
TO CORRECT THE CAUSE OF THE INCORRECT ENGINE
SHUTDOWN CAN CAUSE AN ENGINE OVERTEMPERATURE OR A
FLAME OUT THE EXHAUST ON THE SUBSEQUENT START.
a)
(b)
Examine the N1, N2, EGT and fuel flow for a fast
indication of the engine shutdown.
b) Make sure the engine decreases in speed freely and none
of the engine parts rub together.
c) When the speed decreases, examine the engine for signs
of an internal fire or tailpipe fire.
d) If an internal fire or tailpipe fire occurs, do the
steps for an internal fire during an engine shutdown
(refer to the engine shutdown procedure).
9) Put the FWD and AFT BOOST PUMP switches in the OFF
position.
a) Make sure that the two low fuel PRESS warning lights go
on.
10) Put the L ENG ELEC HYD PUMP and R ENG ELEC HYD PUMP
switches to the off position.
11) Look at the EICAS for fault messages.
Internal engine fire during an engine shutdown.
1) Put the FUEL CONTROL switch to the CUTOFF position.
2) Engage the starter at a speed of 30% N2 rpm or less, use a
lower speed if it is possible, as recommended in the
starter operation limits.
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POWER PLANT OPERATION (NORMAL)
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CAUTION:
_______
DO NOT USE THE FIRE EXTINGUISHING AGENTS ON A FIRE IN
THE INTERNAL OR TURBINE EXHAUST AREAS UNLESS THE FIRE
IS NOT CONTROLLED WHEN YOU MOTOR THE ENGINE. THE HOT
SECTION OF THE ENGINE IS RESISTANT TO VERY HIGH
TEMPERATURE. USUALLY, A FIRE IN THE INTERNAL OR
TURBINE EXHAUST AREA IS PERMITTED TO BURN UNTIL YOU
CAN MOTOR THE ENGINE. THE DAMAGE TO THE ENGINE FROM
A FIRE IS USUALLY LESS THAN THE DAMAGE CAUSED BY THE
FIRE EXTINGUISHING AGENTS.
3)
F.
Motor the engine to remove all signs of the internal fire
or exhaust sleeve fire without the starter time limits.
4) After you remove the fire, complete the engine shutdown
procedure.
(c) Emergency engine shutdown (Engine Fire Warning).
1) Move the forward thrust lever rearward to operate at
minimum power.
2) Immediately put the FUEL CONTROL switch in the CUTOFF
position.
3) On the aft electronic control panel, P8, pull the
applicable fire handle.
4) Turn the applicable fire handle to release the fire
extinguishing agents.
5) Monitor the master caution warning lights at the pilots'
glare shield and the sound of the fire warning bells.
6) Put the FWD and AFT BOOST PUMP switches to the OFF
position.
7) Examine the cable for the Exciter to Igniter Plug
(AMM 74-21-01/601).
Put the airplane back to its initial condition
(1)
(2)
S 862-021-P00
On the pilot's overhead panel, P5, put the components that follow in
the specified position:
(a) Isolation Valve - Open
(b) Applicable Engine (Bleed) Valve Light - Switch in (OFF light is
on)
(c) Pack Valves - Packoff
(d) Boost Pump Switches - Off
(e) Crossfeed Valve - Closed
(f) Engine Anti-Ice Switch - Off
(g) Wing Anti-Ice Switch - Off
S 212-022-P00
Examine the EICAS for auto events, which are on the record, during
the engine operation.
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(3)
(4)
S 862-042-P00
If the circuit breakers for the Aural Warning Speakers are open,
remove the DO-NOT-CLOSE tags and close these circuit breakers on the
P11 panel:
(a) 11B16, AURAL WARN SPKR LEFT
(b) 11H35, AURAL WARN SPKR RIGHT
S 862-023-P00
If it is necessary, remove the DO-NOT-CLOSE tags and close these
circuit breakers on the P11 panel:
(a) 11F2, WEATHER RADAR LEFT
(b) 11F34, WEATHER RADAR RIGHT
(c) 11J7, FLIGHT RECORDER AC
(d) 11J8, FLIGHT RECORDER DC
(5)
S 862-024-P00
Remove pneumatic power if it is not necessary (AMM 36-00-00/201).
(6)
S 862-025-P00
Remove electrical power if it is not necessary (AMM 24-22-00/201).
(7)
S 942-026-P00
Remove the engine safety barrier from the inlet area, if it was used
and is not necessary.
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POWER PLANT OPERATION (DRY-MOTOR)
_________________________________
5.
TASK 71-00-00-862-027-P00
Power Plant Operation (Dry-Motor)
_________________________________
A. General
(1) Use the dry motor procedure for all tests, which it is necessary, to
motor unless a wet motor procedure is necessary.
B. References
(1) AMM 24-22-00/201, Electrical Power - Control
(2) AMM 36-00-00/201, Pressurize/Depressurize Pneumatic System
(3) AMM 71-00-00/201, Powerplant - Maintenance Practices (Engine Ground
Safety Precautions)
C. Equipment
(1) Service interphone equipment.
D. Prepare to Motor the Engine
(1)
(2)
S 862-174-P00
Do this task: Engine Ground Safety Precautions
(AMM 71-00-00/201).
(a) Make sure the wheel chocks and the ground locks are installed.
S 862-029-P00
To motor the engine:
(a) Remove the engine inlet and exhaust covers, if they are
installed.
(b) Examine the areas around the air inlet, fan and turbine
exhaust, wing leading edge immediately above the engine, and
the ground for signs of unwanted material.
(c) Make sure you have the conditions that follow:
1) The forward thrust lever is in the position for minimum
power.
2) The reverse thrust lever is in the forward thrust position.
3) The FUEL CONTROL switch is in the CUTOFF position.
(d) On the aft electronic control panel, P8, make sure the fire
handle is fully in.
(3)
S 862-030-P00
Supply electrical power (AMM 24-22-00/201).
(4)
S 862-031-P00
Supply pneumatic power (AMM 36-00-00/201).
(5)
S 862-032-P00
Use the electric pump in the right hydraulic system for a pressure
source to put the parking brake in the ON position.
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POWER PLANT OPERATION (DRY-MOTOR)
_________________________________
E.
Motor the Engine
(1)
S 862-033-P00
Do the pre-motor procedure.
(a) On the pilot's overhead panel, P5, make sure the components
that follow are in the specified position:
1) Isolation Valve - Open
2) Applicable Engine (Bleed) Valve Light - OFF light is on
3) Pack Valves - Packoff
4) Crossfeed Valves - Closed
5) Engine Anti-Ice Switch - Off
6) Wing Anti-Ice Switch - Off
CAUTION:
_______
(b)
(c)
(d)
(e)
(f)
(g)
DO NOT KEEP THE CIRCUIT BREAKERS FOR THE IGNITION CLOSED.
IF YOU KEEP THE CIRCUIT BREAKERS CLOSED, ACCIDENTAL LIGHT
UP CAN OCCUR WHEN YOU WET MOTOR THE ENGINE.
For the left engine, open these circuit breakers on the
overhead circuit breaker panel, P11, and install DO-NOT-CLOSE
tags:
1) 11D7, ENGINE STBY IGNITION LEFT 1
2) 11D8, ENGINE STBY IGNITION LEFT 2
3) 11L1, LEFT ENGINE IGNITION 1
For the right engine, open these circuit breakers on the
overhead circuit breaker panel, P11, and install DO-NOT-CLOSE
tags:
1) 11D9, ENGINE STBY IGNITION RIGHT 1
2) 11D10, ENGINE STBY IGNITION RIGHT 2
3) 11L28, RIGHT ENGINE IGN 1
Make sure the six EICAS circuit breakers on the P11 panel are
closed.
For the left engine, make sure these circuit breakers on the
P11 panel are closed:
1) 11D19, ENGINE START CONT LEFT
2) 11K9, LEFT ENGINE OIL PRESS
3) 11L35, SEC D ENGINE START CONT L
For the right engine, make sure these circuit breakers on the
P11 panel are closed:
1) 11D20, ENGINE START CONT RIGHT
2) 11K35, RIGHT ENGINE OIL PRESS
Open the spar valve.
NOTE:
____
1)
You must open the spar fuel valve when you motor the
engine to supply a lubricant to the engine fuel pump.
Supply electrical power (AMM 24-22-00/201).
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2)
(h)
(2)
For the left engine, make sure these circuit breakers on
the P6 panel are closed:
a) 6C1, FUEL COND CONT L
b) 6E1, FUEL VALVES L SPAR
3) For the right engine, make sure these circuit breakers on
the P6 panel are closed:
a) 6C2, FUEL COND CONT R
b) 6E2, FUEL VALVES L SPAR
4) Make sure the FUEL CONTROL switch is in the CUTOFF
position.
5) Make sure the two ENG VALVE and SPAR VALVE lights are not
on.
6) For the left engine, open this circuit breaker on the main
power distribution panel, P6, and install a DO-NOT-CLOSE
tag:
a) 6C1, FUEL COND CONT L
7) For the right engine, open this circuit breaker on the main
power distribution panel, P6, and install a DO-NOT-CLOSE
tag:
a) 6C2, FUEL COND CONT R
8) Put the FUEL CONTROL switch to the RUN position.
a) Make sure the SPAR VALVE light goes on then goes off.
9) For the left engine, open this circuit breaker on the main
power distribution panel, P6, and install a DO-NOT-CLOSE
tag:
a) 6E1, FUEL VALVES L SPAR
10) For the right engine, open this circuit breaker on the main
power distribution panel, P6, and install a DO-NOT-CLOSE
tag:
a) 6E2, FUEL VALVES R SPAR
11) Put the FUEL CONTROL switch to the CUTOFF position.
12) For the left engine, remove the DO-NOT-CLOSE tag and close
this circuit breaker on the P6 panel:
a) 6C1, FUEL COND CONT L
13) For the right engine, remove the DO-NOT-CLOSE tag and close
this circuit breaker on the P6 panel:
a) 6C2, FUEL COND CONT R
14) Make sure the ENG VALVE light is not on.
Apply the boost pump pressure.
1) Put the FWD and AFT BOOST PUMP switches for the tank on the
applicable side in the ON position.
2) Make sure the two warning lights for low fuel pressure go
off.
S 862-034-P00
Dry motor the engine.
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POWER PLANT OPERATION (DRY-MOTOR)
_________________________________
CAUTION:
_______
(a)
YOU MUST MAKE SURE TO USE THE STARTER OPERATION LIMITS.
IF YOU DO NOT OBEY THE LIMITS, YOU CAN CAUSE DAMAGE TO THE
STARTER.
Put the applicable ENGINE START switch in the GND position
(Fig. 208).
NOTE:
____
(b)
When the engine start switch is put in the GND position,
the engine start VALVE light on the pilot's overhead
panel, P5, must go on then go off. Also, the DUCT
PRESSURE indicator on the P5 panel will show a fast
decrease and will slowly, but not fully, get back to the
initial pressure.
Make sure the engine motors at a speed of 25 to 35% N2 rpm.
1) Make sure there is a positive oil pressure and the N1
turns.
CAUTION:
_______
YOU MUST FIND AND CORRECT THE CAUSE FOR THE FLOW
INDICATION OR THE FOG BEFORE THE SUBSEQUENT START.
IF YOU DO NOT CORRECT THE CAUSE OF FLOW INDICATION OR
THE FOG, YOU CAN CAUSE AN ENGINE OVERTEMPERATURE OR A
FLAME OUT THE EXHAUST ON THE SUBSEQUENT START.
2)
F.
If the fuel flow indication or a fuel fog occurs for the
left engine, remove the DO-NOT-CLOSE tag and close this
circuit breaker on the P6 panel:
a) 6E1, FUEL VALVES L SPAR
3) If the fuel flow indication or the fuel fog occurs for the
right engine, remove the DO-NOT-CLOSE tag and close this
circuit breaker on the P6 panel:
a) 6E2, FUEL VALVES R SPAR
(c) Continue to motor with the starter operation limits.
(d) Do the checks that are necessary.
(e) Put the ENGINE START switch to the OFF position.
1) Make sure the engine starter VALVE light goes on then goes
off.
Put the Airplane Back to its Usual Condition
(1)
(2)
S 862-063-P00
Put the FWD and AFT BOOST PUMP switches back to the OFF position.
S 862-064-P00
For the left engine, remove the DO-NOT-CLOSE tag and close this
circuit breaker on the P6 panel:
(a) 6E1, FUEL VALVES L SPAR
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(3)
(4)
(5)
(6)
(7)
(8)
(9)
S 862-065-P00
For the right engine, remove the DO-NOT-CLOSE tag and close this
circuit breaker on the P6 panel:
(a) 6E2, FUEL VALVES R SPAR
S 862-066-P00
Make sure the SPAR VALVE light goes off.
S 862-067-P00
On the pilot's overhead panel, P5, make sure the components that
follow are in the specified position:
(a) Isolation Valve - Open
(b) Applicable Engine (Bleed) Valve Light - Switch in (OFF light is
on)
(c) Pack Valves - Packoff
(d) Boost Pump Switches - Off
(e) Crossfeed Valves - Closed
(f) Engine Anti-Ice Switches - Off
(g) Wing Anti-Ice Switch - Off
S 862-068-P00
Remove the DO-NOT-CLOSE tags and close these circuit breakers on the
P11 panel:
(a) 11B16, AURAL WARN SPKR LEFT
(b) 11H35, AURAL WARN SPKR RIGHT
S 862-069-P00
For the left engine, remove the DO-NOT-CLOSE tags and close these
circuit breakers on the P11 panel:
(a) 11D7, ENGINE STBY IGNITION LEFT 1
(b) 11D8, ENGINE STBY IGNITION LEFT 2
(c) 11L1, LEFT ENGINE IGNITION 1
S 862-070-P00
For the right engine, remove the DO-NOT-CLOSE tags and close these
circuit breakers on the P11 panel:
(a) 11D9, ENGINE STBY IGNITION RIGHT 1
(b) 11D10, ENGINE STBY IGNITION RIGHT 2
(c) 11L28, RIGHT ENGINE IGN 1
S 862-071-P00
Remove pneumatic power if it is not necessary (AMM 36-00-00/201).
S 862-072-P00
(10) Remove electrical power if it is not necessary (AMM 24-22-00/201).
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POWER PLANT OPERATION (WET-MOTOR)
_________________________________
6.
TASK 71-00-00-862-035-P00
Power Plant Operation (Wet-Motor)
_________________________________
A. References
(1) AMM 24-22-00/201, Electrical Power - Control
(2) AMM 36-00-00/201, Pressurize/Depressurize Pneumatic System
(3) AMM 71-00-00/201, Powerplant - Maintenance Practices (Engine Ground
Safety Precautions)
B. Equipment
(1) Service interphone equipment.
C. Prepare to Motor the Engine
(1)
(2)
S 862-175-P00
Do this task: Engine Ground Safety Precautions
(AMM 71-00-00/201).
(a) Make sure the wheel chocks and the ground locks are installed.
S 862-074-P00
To motor the engine:
(a) Remove the engine inlet and exhaust covers, if they are
installed.
(b) Examine the areas around the air inlet, fan and turbine
exhaust, wing leading edge immediately above the engine, and
the ground for signs of unwanted material.
(c) Make sure you have the conditions that follow:
1) The forward thrust lever is in the position for minimum
power.
2) The reverse thrust lever is in the forward thrust position.
3) The FUEL CONTROL switch is in the CUTOFF position.
(d) On the aft electronic control panel, P8, make sure the fire
handle is fully in.
(3)
S 862-075-P00
Supply electrical power (AMM 24-22-00/201).
(4)
S 862-076-P00
Supply pneumatic power (AMM 36-00-00/201).
S 862-077-P00
Use the electric pump in the right hydraulic system for a pressure
source to put the parking brake in the ON position.
Motor the Engine
(5)
D.
(1)
S 862-078-P00
Do the pre-motor procedure.
(a) On the pilot's overhead panel, P5, make sure the components
that follow are in the specified position:
1) Isolation Valve - Open
2) Applicable Engine (Bleed) Valve Light - OFF light is on
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3)
4)
5)
6)
Pack Valves - Packoff
Crossfeed Valves - Closed
Engine Anti-Ice Switch - Off
Wing Anti-Ice Switch - Off
CAUTION:
_______
(b)
(c)
(d)
(e)
(f)
(g)
DO NOT KEEP THE CIRCUIT BREAKERS FOR THE IGNITION CLOSED.
IF YOU KEEP THE CIRCUIT BREAKERS CLOSED, ACCIDENTAL LIGHT
UP CAN OCCUR WHEN YOU WET MOTOR THE ENGINE.
For the left engine, open these circuit breakers on the
overhead circuit breaker panel, P11, and install DO-NOT-CLOSE
tags:
1) 11D7, ENGINE STBY IGNITION LEFT 1
2) 11D8, ENGINE STBY IGNITION LEFT 2
3) 11L1, LEFT ENGINE IGNITION 1
For the right engine, open these circuit breakers on the
overhead circuit breaker panel, P11, and install DO-NOT-CLOSE
tags:
1) 11D9, ENGINE STBY IGNITION RIGHT 1
2) 11D10, ENGINE STBY IGNITION RIGHT 2
3) 11L28, RIGHT ENGINE IGN 1
Make sure the six EICAS circuit breakers on the P11 panel are
closed.
For the left engine, make sure these circuit breakers on the
P11 panel are closed:
1) 11D19, ENGINE START CONT LEFT
2) 11K9, LEFT ENGINE OIL PRESS
3) 11L35, SEC D ENGINE START CONT L
For the right engine, make sure these circuit breakers on the
P11 panel are closed:
1) 11D20, ENGINE START CONT RIGHT
2) 11K35, RIGHT ENGINE OIL PRESS
Open the spar valve.
NOTE:
____
1)
2)
3)
You must open the spar fuel valve when you motor the
engine to supply a lubricant to the engine fuel pump.
For the left engine, make sure these circuit breakers on
the P6 panel are closed:
a) 6C1, FUEL COND CONT L
b) 6E1, FUEL VALVES L SPAR
For the right engine, make sure these circuit breakers on
the P6 panel are closed:
a) 6C2, FUEL COND CONT R
b) 6E2, FUEL VALVES L SPAR
Make sure the FUEL CONTROL switch is in the CUTOFF
position.
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4)
5)
6)
7)
8)
9)
10)
11)
12)
13)
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Make sure the two ENG VALVE and SPAR VALVE lights are not
on.
For the left engine, open this circuit breaker on the main
power distribution panel, P6, and install a DO-NOT-CLOSE
tag:
a) 6C1, FUEL COND CONT L
For the right engine, open this circuit breaker on the main
power distribution panel, P6, and install a DO-NOT-CLOSE
tag:
a) 6C2, FUEL COND CONT R
Put the FUEL CONTROL switch to the RUN position.
a) Make sure the SPAR VALVE light goes on then goes off.
For the left engine, open this circuit breaker on the main
power distribution panel, P6, and install a DO-NOT-CLOSE
tag:
a) 6E1, FUEL VALVES L SPAR
For the right engine, open this circuit breaker on the main
power distribution panel, P6, and install a DO-NOT-CLOSE
tag:
a) 6E2, FUEL VALVES R SPAR
Put the FUEL CONTROL switch to the CUTOFF position.
For the left engine, remove the DO-NOT-CLOSE tag and close
this circuit breaker on the P6 panel:
a) 6C1, FUEL COND CONT L
For the right engine, remove the DO-NOT-CLOSE tag and close
this circuit breaker on the P6 panel:
a) 6C2, FUEL COND CONT R
Make sure the ENG VALVE light is not on.
WARNING:
_______
(h)
DO NOT OPERATE THE FUEL BOOST PUMP IF THE LOW PRESSURE
LIGHT COMES ON AND STAYS ON. FUEL VAPORS IN THE TANK MAY
IGNITE AND CAUSE A FIRE OR EXPLOSION.
Apply the boost pump pressure.
NOTE:
____
1)
2)
Continuously monitor the fuel quantity and the low
pressure light indication for the applicable main fuel
tank(s) when you operate the boost pumps. Immediately
put the applicable fuel pump switch(es) in the OFF
position if the LOW PRESSURE light comes on and stays
on.
Put the FWD and AFT BOOST PUMP switches for the tank on the
applicable side in the ON position.
Make sure the two warning lights for low fuel pressure go
off.
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(2)
S 862-036-P00
Wet motor the engine (Wet motor permits the fuel into the engine
combustion chamber. Do not do this step unless you were told to wet
motor for the tests which are done.).
CAUTION:
_______
(a)
YOU MUST MAKE SURE TO USE THE STARTER OPERATION LIMITS.
IF YOU DO NOT OBEY THE LIMITS, YOU CAN CAUSE DAMAGE TO THE
STARTER.
Put the applicable ENGINE START switch in the GND position
(Fig. 208).
NOTE:
____
(b)
(c)
(d)
(e)
(f)
When the engine start switch is put in the GND position,
the engine start VALVE light on the pilot's overhead
panel, P5, must go on then go off. Also, the DUCT
PRESSURE indicator on the P5 panel will show a fast
decrease and will slowly, but not fully, get back to the
initial pressure.
Make sure to motor the engine at a speed of 25 to 35% N2 rpm.
1) Make sure there is a positive oil pressure and the N1
turns.
Put the FUEL CONTROL switch to the RUN position.
Continue to motor with the starter operation limits.
Do the checks that are necessary or until a fuel fog occurs, as
it is applicable.
Put the FUEL CONTROL switch back to the CUTOFF position.
1) Make sure the ENG VALVE indicator light goes on
momentarily.
CAUTION:
_______
FIND AND CORRECT THE CAUSE FOR THE FUEL FOG, WHICH STAYS
FOR AN EXTENDED TIME, BEFORE THE SUBSEQUENT START. IF YOU
DO NOT CORRECT THE CAUSE OF THE FUEL FOG, YOU CAN CAUSE AN
ENGINE OVERTEMPERATURE OR A FLAME OUT THE EXHAUST ON THE
SUBSEQUENT START.
(g)
E.
Dry motor the engine with the FUEL CONTROL switch in the CUTOFF
position to remove the fuel which has collected in the gaspath.
1) Continue to dry motor the engine until the fuel fog goes
out of view.
(h) Turn the ENGINE START switch to the OFF position.
1) Make sure the start VALVE goes on then goes off.
Put the Airplane Back to its Usual Condition
(1)
S 862-037-P00
Put the FWD and AFT BOOST PUMP switches back to the OFF position.
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(2)
(3)
(4)
(5)
(6)
(7)
S 862-038-P00
For the left engine, remove the DO-NOT-CLOSE tag and close this
circuit breaker on the P6 panel:
(a) 6E1, FUEL VALVES L SPAR
S 862-039-P00
For the right engine, remove the DO-NOT-CLOSE tag and close this
circuit breaker on the P6 panel:
(a) 6E2, FUEL VALVES R SPAR
S 862-040-P00
Make sure the SPAR VALVE light goes off.
S 862-041-P00
On the pilot's overhead panel, P5, make sure the components that
follow are in the specified position:
(a) Isolation Valve - Open
(b) Applicable Engine (Bleed) Valve Light - Switch in (OFF light is
on)
(c) Pack Valves - Packoff
(d) Boost Pump Switches - Off
(e) Crossfeed Valves - Closed
(f) Engine Anti-Ice Switches - Off
(g) Wing Anti-Ice Switch - Off
S 862-043-P00
For the left engine, remove the DO-NOT-CLOSE tags and close these
circuit breakers on the P11 panel:
(a) 11D7, ENGINE STBY IGNITION LEFT 1
(b) 11D8, ENGINE STBY IGNITION LEFT 2
(c) 11L1, LEFT ENGINE IGNITION 1
S 862-044-P00
For the right engine, remove the DO-NOT-CLOSE tags and close these
circuit breakers on the P11 panel:
(a) 11D9, ENGINE STBY IGNITION RIGHT 1
(b) 11D10, ENGINE STBY IGNITION RIGHT 2
(c) 11L28, RIGHT ENGINE IGN 1
(8)
S 862-045-P00
Remove pneumatic power if it is not necessary (AMM 36-00-00/201).
(9)
S 862-046-P00
Remove electrical power if it is not necessary (AMM 24-22-00/201).
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POWER PLANT OPERATION (COLD WEATHER)
____________________________________
7.
TASK 71-00-00-862-047-P00
Power Plant Operation (Cold Weather)
____________________________________
A. General
(1) This procedure gives the instructions for engine operation during
cold weather conditions.
(2) These instructions add the data, the techniques, and more procedures
to the normal engine operation procedure.
(3) Engine icing can occur during engine operation when the following
conditions are present:
(a) Ambient air temperature is less than 50° F (10° C).
(b) Visible moisture is present.
NOTE:
____
(4)
During cold weather operation, you can prevent damage to the engine
if you use the inlet covers, thrust reverser plugs, and exhaust
covers.
(a) Before you start the engine, make sure the rotors are not
locked.
(b) Before you start the engine, all snow and ice must be removed
from the engine inlet.
(c) During very cold weather operations, the covers will slow the
heat loss from the engine.
NOTE:
____
(5)
Visible moisture is defined as clouds or fog with less
than one mile visibility. Visible moisture also
includes rain, snow, sleet, ice crystals, water, ice, or
snow on the ground.
The covers also prevent the engine oil temperature from
decreasing too fast.
Ice that collects in the engine inlet is one of the dangerous
conditions during cold weather engine operation.
(a) Snow blown into the engine can become ice if it melts and then
freezes again.
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(b)
(c)
(6)
Ice can lock the rotor blades to the stator case.
If there is a layer of ice on the rotor blades, the engine
rotors will not be balanced.
Ice can collect on engine parts (i.e. stators, guide vanes, fan
blades, spinner, etc.) during the engine operation.
NOTE:
____
This is caused by the large quantity of air that is moved by
suction into the engine.
(a)
(7)
This condition is dangerous when you operate the engine at high
power and static conditions on the ground.
(b) The suction decreases the air pressure which decreases the air
temperature.
(c) This condition and condensation make ice when there are water
drops on the fan blades, guide vanes, and spinner.
After the engine is shutdown, you must immediately install the inlet
cover and the thrust reverser plugs.
NOTE:
____
This will prevent wind-blown snow or rain from entering the
engines. In very cold conditions, it will also help to keep
the heat in the engine.
(8)
It is recommended that the airplane is pointed into the wind when it
is parked for a long period of time.
(9) During heavy snowstorms, you must always shut down the engine in the
forward thrust position.
(a) This will prevent ice layers on the cascade vanes, the blocker
doors, and linkages of the thrust reverser.
(10) It is usually not necessary to increase the temperature of the
engine before you start the engine.
NOTE:
____
(a)
(b)
(c)
Reliable starts can usually be done with the normal start
procedures.
You must increase the temperature of the engine to release
rotors locked with snow and ice.
You must remove all the snow and ice from these areas:
1) The engine inlet panels.
2) The fan cowl panels.
3) The external surfaces and joints of the thrust reverser.
4) The acoustic panels of the inlet cowl.
5) The fan and turbine exhaust ducts.
You must increase the temperature of the engine if the engine
oil temperature is colder than -40° F (-40° C).
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(11) When it is very cold, the high viscosity oil in the thrust reverser
opening system can cause the thrust reverser to close very slowly.
NOTE:
____
The oil may also cause a hydraulic lock in the check valve of
the quick disconnect for the hand pump. If the thrust
reverser closes very slowly, apply hot air to the opening
actuators and tubes and at the quick disconnect for the hand
pump. To clear a hydraulic lock, pump the thrust reverser
open a small amount and then try to close it again. Continue
to apply hot air, to warm the opening system, and open and
close the thrust reverser small amounts until the reverser is
completely closed.
(12) Additional procedures are necessary for very cold weather operations
that are colder than -22° F (-30° C).
NOTE:
____
B.
C.
Do the Through Flight procedure for short periods or the
Return to Service After Cold Soak procedure for overnight or
extended periods.
Equipment
(1) Heater Assembly - Diesel Fueled, Portable,
400,000 BTU, Model 4600-46 (recommended),
or equivalent,
Engineered Air Systems, Inc.,
St. Louis, MO 63132
(2) YMP350 Heater Assembly (alternative), or equivalent
(3) Service interphone equipment
(4) Engine inlet cover
(5) Thrust Reverser Plug
(6) Turbine Exhaust Cover
(7) Modified Turbine Exhaust Cover - This is a modified turbine exhaust
cover with two 10 inch (250 mm) holes for the YMP350 heater hoses.)
(8) Wooden stick - applicable for a N1 rotor which
you manually turn
References
(1) AMM 12-11-03/301, Fuel Sump Draining
(2) AMM 12-33-01/301, Cold Weather Maintenance
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POWER PLANT OPERATION (COLD WEATHER)
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D.
(3) AMM 24-22-00/201, Electrical Power
(4) AMM 36-00-00/201, Pneumatic - General
(5) AMM 71-00-00/201, Power Plant
(6) AMM 72-00-00/601, Icing Build-up on the 1st LPC Stator Inspection
Prepare the Power Plant for Operation
(1)
S 862-048-P00
Prepare for normal engine operation and add these steps:
(a) Remove all snow and ice from the engine inlet and the acoustic
panels of the inlet cowl, the thrust reverser exhaust, and the
turbine exhaust areas.
WARNING:
_______
(b)
(c)
(d)
MAKE SURE THAT YOU FOLLOW THE PROCEDURES TO TURN THE LOW
PRESSURE (N1) AND THE HIGH PRESSURE (N2) ROTOR SYSTEM.
FAILURE TO FOLLOW AMM 71-00-00/201 COULD CAUSE INJURY TO
PERSONS AND DAMAGE TO EQUIPMENT.
Make sure the N1 rotor can turn freely in the counterclockwise
direction as seen from the front (AMM 71-00-00/201).
1) Turn the fan blades with a wood stick or a rod that is made
of material that will not cause damage to the fan blades.
Make sure the N2 rotor can turn freely (AMM 71-00-00/201).
If the N1 or N2 rotors cannot turn, do these steps to increase
the temperature of the engine:
1) Install the inlet cover.
2) Install the plugs for the thrust reverser.
3) Install the modified turbine exhaust cover.
4) Attach two heater hoses to the heater.
5) Install the two heater hoses through the modified turbine
exhaust cover.
6) Operate the hot air source heater to supply hot air.
NOTE:
____
The temperature of the hot air must not be
more than 175° F (80° C).
7)
8)
9)
10)
Apply hot air until the rotors turn freely.
Stop the operation of the hot air source heater.
Disconnect the heater hoses.
Remove the modified turbine exhaust cover from the turbine
exhaust.
11) Install the turbine exhaust cover.
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POWER PLANT OPERATION (COLD WEATHER)
____________________________________
CAUTION:
_______
(e)
(f)
If you find it difficult to open the fan cowl panels or the
thrust reverser because of snow or ice, apply hot air to the
external surfaces as necessary.
1) Blow the melted snow or ice from the external joints before
you open the cowl panels.
Drain the water from all fuel sumps in the fuel system
(AMM 12-11-03/301).
NOTE:
____
1)
(2)
THE ENGINE INLET MUST BE COMPLETELY CLEAN OF ICE AND
SNOW. THE ENGINE ANTI-ICE SYSTEM CAN MELT THE ICE
AND SNOW AT THE HEATED AREA, BUT THE WATER CAN FREEZE
AGAIN ON THE INLET ACOUSTIC PANELS AND ON THE ENGINE
PARTS.
If the fuel flows freely from the drains in the tank
sumps, the fuel system has no ice.
If there is ice in the fuel system, blow hot air from an
explosion-proof hot air source (250° F (121° C) maximum) at
the drain area (AMM 12-33-01/301).
S 842-008-P00
Do the applicable steps for very cold conditions:
(a) Through Flight At Temperatures Colder Than -22° F (-30° C)
NOTE:
____
1)
Through flight conditions are defined as follows:
The cabin temperatures are kept warmer than 32° F
(0° C ).
The engine oil temperatures must be warmer than -40° F
(-40° C) while the airplane is on the ground.
The airplane must be monitored during this time.
If the EICAS engine oil temperature indication is -40° F
(-40° C) or warmer, do these steps:
a) Make sure that you follow the procedure for airplane
cold weather maintenance (AMM 12-33-01/301).
NOTE:
____
b)
To see the oil temperature on EICAS with the
engines not operating, turn on the EEC Ground
Test Power.
Remove the inlet covers, thrust reverser plugs, and
turbine exhaust covers from the engines.
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POWER PLANT OPERATION (COLD WEATHER)
____________________________________
CAUTION:
_______
THE EICAS ENGINE OIL TEMPERATURE VALUE MUST BE
WARMER THAN -40° F (-40° C) WHEN YOU START THE
ENGINE FOR THROUGH FLIGHTS. IF THE ENGINE OIL
TEMPERATURE IS COLDER THAN -40° F (-40° C) AND
YOU START THE ENGINE, DAMAGE TO THE ENGINE
BEARINGS AND LUBE PUMP CAN OCCUR.
IF THE OIL TEMPERATURE IS LESS THAN -40° F
(-40° C) DO THE RETURN TO SERVICE AFTER COLD
SOAK PROCEDURE.
c)
Start the engine using the cold weather procedures.
NOTE:
____
d)
During engine starts at cold temperatures, high
oil pressure can occur, and the indicated oil
quantity can decrease. As the oil temperature
increases with the engine operation at idle
thrust, the oil pressure will decrease and the
indicated oil quantity will go to the usual
condition.
Operate the engine at idle until the oil temperature is
equal to or warmer than 32° F (0° C).
NOTE:
____
1.
_
The oil must be at this temperature before you
move the thrust levers forward and accelerate
the engine from idle power.
Operate cold engines at idle power or taxi power
until the oil temperature is more than 122° F
(50° C).
NOTE:
____
The oil must be at this temperature before
you go to takeoff power.
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____________________________________
2.
_
If you use this procedure to re-warm the engine,
make sure the engine operates at idle power for a
minimum of 10 minutes before the engine is shut
down.
NOTE:
____
e)
f)
g)
h)
(b)
Return
NOTE:
____
1)
2)
Measure the 10 minutes from the time that
the engine oil temperature reaches 32° F
(0° C). These 10 minutes are the minimum
time for the engine temperature to become
stable. You can increase the time periods
between engine operations to re-warm the
engine if you increase the engine run time
to more than 10 minutes or use a higher
power level than idle power.
Do the procedure to shutdown the engine
(AMM 71-00-00/201).
Install the inlet covers.
Install the thrust reverser plugs.
Install the turbine exhaust cover when the engine
exhaust is sufficiently cool to prevent damage to the
cover.
The Airplane To Service After a Cold Soak
A cold soak is defined as follows:
The outside temperature is less than 5° F (-15° C).
The airplane has remained overnight, or for an extended
period.
The airplane has not been monitored during this time.
Make sure you follow the procedure for airplane cold
weather maintenance (AMM 12-33-01/301).
If the engine oil temperature is colder than -40° F
(-40° C), do these steps:
NOTE:
____
If engine oil temperatures are colder than
-40° F (-40° C), you must warm the engine bearings
and the engine oil to prevent engine damage. The
procedure to warm the engine bearings is slow.
To view oil temperatures on EICAS with the engines
not operating, turn on the EEC ground test power.
If the engine oil temperature is colder than -58° F
(-50° C), the EICAS indication will not be
displayed.
a)
Increase the temperature of the engine with a hot air
source heater.
1. Remove the turbine exhaust cover.
_
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POWER PLANT OPERATION (COLD WEATHER)
____________________________________
2.
_
3.
_
4.
_
5.
_
_
6.
7.
_
Install a modified turbine exhaust cover on the
turbine exhaust.
Install two heater hoses through the modified
exhaust cover holes.
Install a heater hose through the oil service
access door.
Position the heater hose such that the air blows
down across the oil tank towards the gearbox.
Attach the heater hoses to the heater.
Operate the hot air source heaters to supply hot
air.
NOTE:
____
The temperature of the hot air must not be
more than 175° F (80° C).
8.
_
3)
Apply hot air to the engine core through the
turbine exhaust, and to the fan compartment through
the oil service access door.
b) As an alternate procedure, move the airplane to a warm
airplane hangar to increase the temperature of the
engine oil to 32° F (0° C) or more.
When the engine oil temperature is warmer than 32° F
(0° C), do these steps:
a) If the engine temperature is increased with hot air
from a heater, do these steps:
1. Stop the operation of the hot air source heater.
_
2. Disconnect the heater hoses.
_
3. Remove the modified turbine exhaust cover.
_
4. Install the turbine exhaust cover.
_
b) If the airplane is in a hangar, move the airplane to
the outside ramp.
c) Supply electrical power (AMM 24-22-00/201).
d) Remove the inlet and exhaust covers and the thrust
reverser plugs from the engines.
e) Start the engine using the cold weather procedures.
NOTE:
____
During engine starts at cold temperatures, high
oil pressure can occur, and the indicated oil
quantity can decrease. As the oil temperature
increases with the engine operation at idle
thrust, the oil pressure will decrease and the
indicated oil quantity will go to the usual
condition.
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____________________________________
f)
Operate the engine at idle until the oil temperature is
equal to or warmer than 32° F (0° C).
NOTE:
____
1.
_
2.
_
The oil must be at this temperature before you
move the thrust levers forward and accelerate
the engine from the idle power setting.
Operate cold engines at idle power or taxi power
until the oil temperature is more than 122° F
(50° C) before you go to takeoff power.
If you use this procedure to re-warm the engine,
make sure the engine operates at idle power for a
minimum of 10 minutes before the engine is shut
down.
NOTE:
____
g)
h)
i)
j)
E.
Measure the 10 minutes from the time that
the engine oil temperature reaches 32° F
(0° C). These 10 minutes are the minimum
time for the engine temperature to become
stable. You can increase the time periods
between engine operations to re-warm the
engine if you increase the engine run time
to more than 10 minutes or use a higher
power level than idle power.
Shutdown the engine.
Install the inlet covers.
Install the thrust reverser plugs.
Install the turbine exhaust cover when the engine
exhaust is sufficiently cool to prevent damage to the
cover.
Operate the Engine
(1)
S 862-049-P00
Do the procedure to prepare the engine for normal operation.
(a) Make sure that you follow the procedures for temperatures
colder than -22° F (-30° C).
1) Through Flight At Temperatures Colder Than -22° F (-30° C).
2) Return the Airplane to Service After a Cold Soak.
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POWER PLANT OPERATION (COLD WEATHER)
____________________________________
(2)
S 212-138-P00
Do the Visual Check For Low Pressure Compressor (LPC) Ice (Fig 211).
NOTE:
____
It is recommended that you do the Visual Check For LPC Ice
before you start the engine for continuous ground operations
in icing conditions. If you do this check, it will not be
necessary to do the subsequent engine run-ups as frequently
as when you do not do this check.
NOTE:
____
Icing conditions on the ground are when the operation of
the engine anti-ice system is necessary, and the outside air
temperature (OAT) is 37° F (3° C) or less.
(a)
While the engine is not in operation, do a visual check for ice
on the LPC blades, stators, splitter and spinner.
NOTE:
____
1)
2)
3)
4)
5)
The visual check of the LPC for ice can be done easier
on a windmilling engine. You can look through the fan
blades while they slowly turn to see the LPC blades,
stators and splitter.
Go to a position on the ground in front of the engine, to
the right of the engine centerline (so you can look back
between the fan blades to see the stators and the
splitter).
Use sufficient light to see the LPC blades, stators,
splitter and spinner.
Carefully examine the leading edge of the LPC blades and
stators, the lip of the splitter, and the face of the
spinner for ice.
If you do not find ice on the LPC blades, stators, splitter
or spinner, you can start the engine (AMM 71-00-00/201).
If you find ice on the LPC blades, stators, splitter or
spinner, do the steps that follow to remove it.
a) If the total ground operating time since the last
engine run-up above 50% N1 is less than 30 minutes, you
can start the engine and increase the RPM above 50% N1
to loosen and remove the ice.
b) If the total ground operating time since the last
engine run-up above 50% N1 is more than 30 minutes, you
must melt the ice off the LPC before you can start the
engine.
c) Use a hot air heater to blow hot air across the ice on
the LPC.
NOTE:
____
The temperature of the hot air must not be more
than 175° F (80° C).
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SPINNER
VIEW THE BLADES, STATORS
AND SPLITTER BY LOOKING
BETWEEN THE FAN BLADES,
IN THIS DIRECTION.
LOOK FOR ICE ON
THE SPLITTER LIP,
AND ON THE LEADING
EDGE OF THE STATORS
G03626
Visual Check for LPC Ice
Figure 211
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POWER PLANT OPERATION (COLD WEATHER)
____________________________________
d)
e)
Remove all the melted ice chunks and water from the LPC
and the engine inlet so they will not cause damage when
you operate the engine again.
You must fully remove all the ice on the first stage of
the LPC before you can start the engine for ground
operations or dispatch.
S 712-015-P00
CAUTION:
_______
DO NOT OPERATE AN ENGINE WHICH HAS BEEN AT LOW TEMPERATURES, IF
THE ENGINE DOES NOT ACCELERATE CORRECTLY TO IDLE POWER.
IMMEDIATELY SHUTDOWN THE ENGINE IF THE INDICATIONS ARE LESS
THAN NORMAL.
IF THE AIRPLANE IS PARKED ON ICE OR PACKED SNOW, START THE
ENGINES WITH THE AUXILIARY POWER UNIT (APU) OR SUPPLY AIR FROM
THE GROUND CARTS. ENGINE THRUST IS NOT SYMMETRIC DURING CROSS
BLEED STARTS AND CAN CAUSE THE AIRPLANE TO MOVE IN A CIRCLE.
ICE CHOCKS AND A HIGH GROSS WEIGHT CAN MINIMIZE AIRPLANE
MOVEMENT.
(3)
Start the engine with the instructions for normal engine operation
and add these steps:
(a) The fuel temperature must be greater than -40° F (-40° C) or
7.2° F (3° C) above its freezing point, whichever is greater.
(b) Supply pneumatic power from the APU or two or three ground air
carts (AMM 36-00-00/201).
1) Do not use the cross bleed start procedure.
(c) If there is no drop in pressure on the DUCT PRESSURE indicator,
on the pilots overhead panel P5, during the start, examine the
starter control valve for a frozen solenoid.
1) Use the manual starter valve override handle on the starter
control valve during the engine start to release the valve.
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POWER PLANT OPERATION (COLD WEATHER)
____________________________________
2)
(d)
(e)
(f)
Apply hot air from an explosion-proof hot air source to
release the strut valve or the high pressure bleed valve
(250° F (121° C) maximum).
If an engine start with one igniter causes a problem, use two
igniters during the next start attempt.
If an engine accelerates slowly after lightup and a hung start
occurs, do the engine shutdown procedure.
If the engine is slow to start or will not accelerate to idle
power (hung start), do the engine shutdown procedure and find
the cause.
CAUTION:
_______
IF THERE IS NO OIL PRESSURE INDICATION (EICAS RED
BAND) WHEN THE ENGINE HAS ACCELERATED TO MINIMUM IDLE
OR THE OIL PRESSURE DECREASES TO ZERO DURING ENGINE
OPERATION, DO THE PROCEDURE TO SHUTDOWN THE ENGINE
AND FIND THE CAUSE OF THE PROBLEM.
WHEN THE ENGINE IS STARTED DURING VERY COLD
CONDITIONS THE OIL PRESSURE INDICATION CAN GO HIGHER
THAN NORMAL BECAUSE OF HIGH OIL VISCOSITY. THE OIL
PRESSURE WILL DECREASE AS THE OIL TEMPERATURE
INCREASES. IF THE OIL PRESSURE DOES NOT DECREASE
AFTER THE OIL TEMPERATURE BECOMES STABLE, DO THE
PROCEDURE TO SHUTDOWN THE ENGINE AND FIND THE CAUSE
OF THE PROBLEM.
(g)
Operate the engine at idle until the oil temperature is equal
to or warmer than 32° F (0° F).
NOTE:
____
1)
The oil must be at this temperature before you move the
thrust levers forward and accelerate the engine from
idle power.
Operate cold engines at idle power or taxi power until the
oil temperature is greater than 122° F (50° C).
NOTE:
____
The oil must be at this temperature before you go to
takeoff power.
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POWER PLANT OPERATION (COLD WEATHER)
____________________________________
2)
If you use this procedure to re-warm the engine, make sure
the engine operates at idle power for a minimum of 10
minutes before the engine is shutdown.
NOTE:
____
CAUTION:
_______
(h)
Measure the 10 minutes from the time that the
engine oil temperature reaches 32° F (0° C). These
10 minutes are the minimum time for the engine
temperature to become stable. You can increase the
time periods between engine operations to re-warm
the engine if you increase the engine run time to
more than 10 minutes or use a higher power level
than idle power.
DO NOT TURN ON THE ENGINE ANTI-ICE SYSTEM IF THE ENGINE
INLET IS NOT COMPLETELY CLEAN OF ICE. AT TEMPERATURES
COLDER THAN FREEZING, THE ANTI-ICE SYSTEM HAS SUFFICIENT
HEAT TO MELT THE ICE AT THE INLET. THE ICE AND WATER WILL
MOVE INTO THE ENGINE AND FREEZE AGAIN ON THE INLET
ACOUSTIC PANELS AND ENGINE PARTS.
While the engine operates on the ground at idle power during
icing conditions, turn on the engine anti-ice system.
1) Push the applicable engine anti-ice switch to the ON
position on the Wing and Anti-ice Control Panel.
a) L ENG ANTI-ICE
b) R ENG ANTI-ICE
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POWER PLANT OPERATION (COLD WEATHER)
____________________________________
(4)
S 712-137-P00
Do these steps for Continuous Ground Operations In Icing Conditions.
NOTE:
____
(a)
Icing conditions on the ground are when the operation of
the engine anti-ice system is necessary, and the outside air
temperature (OAT) is 37° F (3° C) or less.
Momentarily increase the engine RPM to a mimimum of 50% N1 to
remove the ice from the LPC.
NOTE:
____
1)
When you operate the engine on the ground in icing
conditions, you must do the engine run-ups in the time
limits that follow.
If you completed the Visual Check For LPC Ice procedure
before you started the engine, do the engine run-up no more
than 30 minutes after the engine start time.
NOTE:
____
2)
You must do the engine run-up again each time
you have 30 more minutes of continuous engine ground
operations (if you completed the Visual Check For
LPC Ice procedure before you started the engine).
The time limit of 30 minutes includes the time you
use to taxi to and from the engine run-up area, and
the ground holding time.
If you DID NOT complete the Visual Check For LPC Ice before
you started the engine, do the engine run-up no more than
15 minutes after the engine start time.
NOTE:
____
You must do the engine run-up again each time
you have 15 more minutes of continuous engine ground
operations (if you DID NOT do the Visual Check For
LPC Ice procedure before you started the engine).
The time limit of 15 minutes includes the time you
use to taxi to and from the engine run-up area, and
the ground holding time.
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POWER PLANT OPERATION (COLD WEATHER)
____________________________________
(b)
You must continue to do the engine run-ups at the intervals
specified above for all the time you operate the engine on the
ground in icing conditions.
NOTE:
____
(c)
The 15 minute or the 30 minute time limits include the
time you use to taxi the airplane in or out, and the
ground holding time.
If you do not do the engine run-ups in the time limits shown
above, you must do the steps that follow:
1) Taxi the airplane to the engine shutdown area, but do not
increase the engine RPM above 40% N1 while you taxi.
NOTE:
____
2)
3)
(5)
This will keep the ice from causing damage to the
engine if it comes off the LPC while you taxi the
airplane.
Do the Engine Shutdown Procedure (AMM 71-00-00/201).
Do the Visual Check For LPC Ice (AMM 71-00-00/201).
S 712-010-P00
If you must do the Power Plant Tests in AMM 71-00-00/501, you must
turn off the engine anti-ice system.
NOTE:
____
Good data from the power plant tests requires engine
operation with no electrical load on the IDG and no bleed air
off-takes.
(a)
F.
Push the applicable engine anti-ice switch to the OFF posistion
on the Wing and Engine Anti-Ice Control Panel.
1) L ENG ANTI-ICE
2) R ENG ANTI-ICE
(b) Shutdown the engine.
1) Do the engine shutdown as specified for normal engine
operation.
a) Make sure the thrust reverser is retracted (the forward
thrust position).
Put the Airplane in Its Usual Condition
(1)
S 842-011-P00
Do the steps to put the airplane back to the usual condition with
the procedure for normal engine operation.
(2)
S 842-012-P00
Install the inlet cover.
(3)
S 842-013-P00
Install the thrust reverser plugs.
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POWER PLANT OPERATION (COLD WEATHER)
____________________________________
(4)
S 842-014-P00
Install the turbine exhaust cover when the engine is sufficiently
cool to prevent damage to the cover.
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POWER PLANT - ADJUSTMENT/TEST
_____________________________
1.
General
_______
A. The tests in this section apply to PW2000 series engines. The tests give
the necessary steps to make sure the engine operates correctly after a
component is replaced or repaired.
B. The tests have a number for identification. The table that follows shows
the test numbers and titles.
~¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼
¦
Power Plant Tests List
¦
»¼¼¼¼¼¼¼¼¼¼¼¼¼ ¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼«
¦ Test Number ¦
Title of Test
¦
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¦
1.
¦ Engine Driven (Hydraulic) Pump (EDP) Test
¦
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¦
2.
¦ Engine Motoring (Dry) Leak Test
¦
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¦
2A.
¦ Engine Motoring (Wet) Leak Test
¦
»¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼«
¦
3.
¦ Minimum Idle Test
¦
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¦
3A.
¦ Idle Leak Test for the Oil and Fuel Systems
¦
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¦
4.
¦ Integrated Drive Generator (IDG) Test
¦
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¦
5.
¦ Main Gearbox Replacement Test
¦
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¦
6.
¦ Fourteenth-Stage Bleed System Test
¦
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¦
7.
¦ Electronic Engine Control (EEC) Static Test
¦
»¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼«
¦
8.
¦ Vibration Survey
¦
»¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼«
¦
9.
¦ Performance Test
¦
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¦
10.
¦ Engine Replacement Test (Untested)
¦
»¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼«
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~¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼
¦
Power Plant Tests List
¦
»¼¼¼¼¼¼¼¼¼¼¼¼¼ ¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼«
¦ Test Number ¦
Title of Test
¦
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¦
11.
¦ Oil Pressure Test
¦
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¦
12.
¦ Engine Replacement Test (Pre-Tested)
¦
»¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼«
¦
13.
¦ Intercompressor 2.5 Bleed Actuator Test
¦
»¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼«
¦
14.
¦ Stator Vane Actuator Test
¦
»¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼«
¦
15.
¦ Fuel Control Replacement Test
¦
»¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼«
¦
16.
¦ Test No. 16 Not Used
¦
»¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼«
¦
17.
¦ Thrust Lever Angle (TLA) Resolver Test
¦
»¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼«
¦
18.
¦ Low Pressure Rotor Trim Balance
¦
»¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼«
ú¦
¦ 757-300 AIRPLANES;
¦
¦
18A.
¦ Engine Trim Balance With The Vibro-Meter Universal
¦
¦
¦ Airborne Vibration Monitor (AVM) (P/N S362A001-9)
¦
»¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼«
¦
19.
¦ PT2 System Leak Test
¦
»¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼«
¦
20.
¦ Static Leak Test
¦
²¼¼¼¼¼¼¼¼¼¼¼¼¼…¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¹
2.
TASK 71-00-00-715-361-P00
Power Plant Test Reference Table
________________________________
A. General
(1) The Power Plant Test Reference Table that follows shows the
necessary tests after a component is repaired or replaced. The
table also shows components that are not removed or installed
on-the-wing for conditions where a test cell is not available.
EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùùû
ú
ALL
ú
ú
ú
71-00-00
P01.1
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
Page 502
Sep 28/03
A
757
MAINTENANCE MANUAL
////////////////////////
/
PW2000 SERIES
/
/
/
ENGINES
////////////////////////
~¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼
¦
Power Plant Test Reference Table
¦
»¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼ ¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼«
¦
Component Repaired or Replaced
¦ Necessary Test ¦
»¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼«
¦
BASIC ENGINE COMPONENTS
¦
¦
»¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼«
¦ COMPRESSOR SECTION
¦
¦
¦
FAN SECTION
¦
¦
¦
»¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼«
¦
¦
¦
Fan Blade Assembly
¦
8 & 18
¦
¦
¦ or 18A *[1]
¦
¦
»¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼«
¦
¦
¦
*[1] Engines with the Universal AVM P/N S362A001-9 only
¦
¦
¦
»¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼«
¦
¦
¦ LOW PRESSURE COMPRESSOR SECTION
¦
¦
¦
»¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼«
¦
¦
¦
Low Pressure Compressor Group
¦
9
¦
¦
»¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼«
¦
¦
¦ HIGH PRESSURE COMPRESSOR SECTION
¦
¦
¦
»¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼«
¦
¦
¦
High Pressure Compressor Group
¦
9
¦
¦
»¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼«
¦
¦
¦ COMBUSTION SECTION
¦
¦
¦
»¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼«
¦
¦
¦
Diffuser and Combustor Group
¦
9
¦
¦
»¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼«
¦
¦
¦ TURBINE SECTION
¦
¦
¦
»¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼«
¦
¦
¦
Turbine Nozzle Group
¦
9
¦
¦
»¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼«
¦
¦
¦
High Pressure Turbine Group
¦
9
¦
¦
»¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼«
¦
¦
¦
Low Pressure Turbine Assembly
¦
9
¦
¦
»¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼«
¦
¦
¦ ACCESSORY DRIVES
¦
¦
¦
»¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼«
¦
¦
¦
Accessory Drive Seals
¦
2
¦
¦
»¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼«
¦
¦
¦
Angle Gearbox Lower Cover
¦
2
¦
¦
»¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼«
¦
¦
¦
Main Gearbox Assembly
¦
5
¦
¦
»¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼«
¦
¦
¦
Deoiler Housing
¦
3A
¦
¦
»¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼«
¦
¦
¦
Manual Crank Pad Cover
¦
3A
¦
¦
»¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼«
¦
¦
EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùùû
ú
ALL
ú
ú
ú
71-00-00
P01
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
Page 503
Sep 28/02
A
757
MAINTENANCE MANUAL
////////////////////////
/
PW2000 SERIES
/
/
/
ENGINES
////////////////////////
~¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼
¦
Power Plant Test Reference Table
¦
»¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼ ¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼«
¦
Component Repaired or Replaced
¦ Necessary Test ¦
»¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼«
¦
BASIC ENGINE COMPONENTS
¦
¦
»¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼«
¦ ENGINE BLEED AND AIR CONTROL SYSTEM
¦
¦
¦
»¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼«
¦
¦
¦
HP Turbine Cooling Air Valve
¦
2A
¦
¦
»¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼«
¦
¦
¦
LP Turbine Cooling Air Valve
¦
2A
¦
¦
»¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼«
¦
¦
¦
Fourteenth-Stage Bleed Valve
¦
6
¦
¦
»¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼«
¦
¦
¦
Fourteenth-Stage Bleed Converter Valve
¦
6
¦
¦
»¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼«
¦
¦
¦
Intercompressor (2.5) Bleed Actuator
¦
13
¦
¦
»¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼«
¦
¦
¦
Turbine Cooling Air Valve (TCAV) Actuator
¦
2A&3 *[1] ¦
¦
»¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼«
¦
¦
¦
*[1] The TCA Actuator is on BG 11 engines.
¦
¦
¦
»¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼«
¦
¦
¦ ENGINE COMPRESSOR STATOR VANE CONTROL SYSTEM
¦
¦
¦
»¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼«
¦
¦
¦
Stator Vane Actuator
¦
14
¦
¦
»¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼«
¦
¦
¦ ENGINE IGNITION SYSTEM (74-00-00)
¦
¦
¦
»¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼«
¦
¦
¦
Exciter-to-Igniter Plug Cable, or
¦AMM 74-00-00/501¦
¦
¦ /501
¦
»¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼«
¦
¦
¦
¦ Ignition Exciters, or
¦AUDIBLE TEST
¦
¦
Igniter Plugs
¦
¦
¦
»¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼«
¦
¦
EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùùû
ú
ALL
ú
ú
ú
71-00-00
P02
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
Page 504
May 20/98
A
757
MAINTENANCE MANUAL
////////////////////////
/
PW2000 SERIES
/
/
/
ENGINES
////////////////////////
~¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼
¦
Power Plant Test Reference Table
¦
»¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼ ¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼«
¦
Component Repaired or Replaced
¦ Necessary Test ¦
»¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼«
¦
BASIC ENGINE COMPONENTS
¦
¦
»¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼«
¦ ENGINE FUEL SYSTEM COMPONENTS (73-00-00)
¦
¦
¦
»¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼«
¦
¦
¦
Fuel Control
¦
15
¦
¦
»¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼«
¦
¦
¦
Fuel Control Filter
¦
2A
¦
¦
»¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼«
¦
¦
¦
Fuel Distribution Valve
¦
2A
¦
¦
»¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼«
¦
¦
¦
Fuel Distribution Valve Filter
¦
2A
¦
¦
»¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼«
¦
¦
¦
Fuel Flow Transmitter
¦
3A
¦
¦
»¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼«
¦
¦
¦
Fuel Injector and Support Assemblies
¦
2A
¦
¦
»¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼«
¦
¦
¦
Fuel Pump
¦
2A or 3A ¦
¦
»¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼«
¦
¦
¦
Fuel Pump Filter
¦
2
¦
¦
»¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼«
¦
¦
¦
Fuel Pump Filter Differential Pressure Switch
¦
2
¦
¦
»¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼«
¦
¦
¦
Fuel Pump/Fuel Control Coupling Clamp
¦
2A
¦
¦
»¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼«
¦
¦
¦
Main Fuel Supply Line
¦
2A
¦
¦
»¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼«
¦
¦
¦
Electronic Engine Control (EEC)
¦
7
¦
¦
»¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼«
¦
¦
¦
EEC Alternator (N2 Transducer)
¦
3
¦
¦
»¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼«
¦
¦
¦
EEC Speed Transducer (N1)
¦
3
¦
¦
»¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼«
¦
¦
¦
EEC Inlet Total Pressure/Temperature (PT2/TT2) Probe
¦
3
¦
¦
»¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼«
¦
¦
¦
EEC Fuel Temperature Thermocouple Probe
¦
3
¦
¦
»¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼«
¦
¦
¦
EEC Oil Temperature Thermocouple Probe
¦
3
¦
¦
»¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼«
¦
¦
¦
EEC Data Entry Plug
¦
7
¦
¦
»¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼«
¦
¦
¦
EEC Wiring Harness
¦
7
¦
¦
»¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼«
¦
¦
¦
Propulsion Discrete Interface Unit (PDIU)
¦
7
¦
¦
»¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼«
¦
¦
¦
Thrust Lever Angle (TLA) Resolver
¦
17
¦
¦
»¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼«
¦
¦
EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùùû
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ALL
ú
ú
ú
71-00-00
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/
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/
/
/
ENGINES
////////////////////////
~¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼
¦
Power Plant Test Reference Table
¦
»¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼ ¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼«
¦
Component Repaired or Replaced
¦ Necessary Test ¦
»¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼«
¦
BASIC ENGINE COMPONENTS
¦
¦
»¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼«
¦ ENGINE OIL SYSTEM COMPONENTS (79-00-00)
¦
¦
¦
»¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼«
¦
¦
¦
Engine Oil Tank
¦
3A
¦
¦
»¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼«
¦
¦
¦
Prismalite Oil Level Indicator
¦
3A
¦
¦
»¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼«
¦
¦
¦
Main Oil Filter
¦
3A
¦
¦
»¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼«
¦
¦
¦
Last Chance Oil Filters
¦
3A
¦
¦
»¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼«
¦
¦
¦
Lubrication and Scavenge Oil Pump
¦
11
¦
¦
»¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼«
¦
¦
¦
No. 4 Bearing Scavenge Valve
¦
3A
¦
¦
»¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼«
¦
¦
¦
No. 4 Bearing Scavenge Manifold
¦
3A
¦
¦
»¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼«
¦
¦
¦
Fuel/Oil Heat Exchanger
¦
3A
¦
¦
»¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼«
¦
¦
¦
Fuel/Oil Heat Exchanger Bypass Valve
¦
3A
¦
¦
»¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼«
¦
¦
¦
Air/Oil Heat Exchanger
¦
3A
¦
¦
»¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼«
¦
¦
¦
Air/Oil Heat Exchanger Valve
¦
3A
¦
¦
»¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼«
¦
¦
¦
Gearbox Oil Scavenge Pump Assembly
¦
3A
¦
¦
»¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼«
¦
¦
¦
Oil Tank Pressurization Valve
¦
3A
¦
¦
»¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼«
¦
¦
¦
Gearbox Strainer Element Assembly
¦
3A
¦
¦
»¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼«
¦
¦
¦
Gearbox Oil Suction Strainer Assembly
¦
3A
¦
¦
»¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼«
¦
¦
¦
Oil Quantity Transmitter
¦
3A
¦
¦
»¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼«
¦
¦
¦
Oil Pressure Transmitter
¦
11
¦
¦
»¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼«
¦
¦
¦
Low Oil Pressure Switch
¦
3A
¦
¦
»¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼«
¦
¦
¦
Oil Filter Differential Pressure Switch
¦
3A
¦
¦
»¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼«
¦
¦
EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùùû
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ALL
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71-00-00
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~¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼
¦
Power Plant Test Reference Table
¦
»¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼ ¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼«
¦
Component Repaired or Replaced
¦ Necessary Test ¦
»¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼«
¦
BASIC ENGINE COMPONENTS
¦
¦
»¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼«
¦ ENGINE INDICATING SYSTEM (77-00-00)
¦
¦
¦
»¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼«
¦
¦
¦
EGT (T4.9) Thermocouple Box and Cable
¦
3
¦
¦
»¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼«
¦
¦
¦
EGT (T4.9) Thermocouple Probes
¦
3
¦
¦
»¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼«
¦
¦
¦
P4.9 Pneumatic Line
¦
3
¦
¦
»¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼«
¦
¦
¦ ENGINE STARTING SYSTEM (80-11-00)
¦
¦
¦
»¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼«
¦
¦
¦
Starter
¦ Dry Motor
¦
»¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼«
¦
¦
¦
¦
Starter Control Valve
¦ Engine
¦
¦
¦ (AMM 71-00-00/ ¦
¦
¦ 201)
¦
¦
»¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼«
¦
¦
¦ POWER PLANT
¦
¦
¦
»¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼«
¦
¦
¦
Engine Replacement (Engine untested in test cell)
¦
10
¦
¦
»¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼«
¦
¦
¦
Engine Replacement (Engine pretested in test cell)
¦
12
¦
¦
»¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼«
¦
¦
¦ MISCELLANEOUS AIRPLANE SYSTEM
¦
¦
¦
»¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼«
¦
¦
¦
Integrated Drive Generator
¦
4
¦
¦
»¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼«
¦
¦
¦
Integrated Drive Generator Fuel/Oil Heat Exchanger
¦
3A
¦
¦
»¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼«
¦
¦
¦
Integrated Drive Generator Air/Oil Heat Exchanger
¦
3A
¦
¦
»¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼«
¦
¦
¦
Integrated Drive Generator Scavenge Filter
¦
2
¦
¦
»¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼«
¦
¦
¦
Engine-Driven Pump (EDP)
¦
1
¦
²¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼…¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¹
3.
TASK 71-00-00-735-363-P00
System Test - Power Plant
A. General
(1) You must correct all EPCS messages which show on the EICAS EPCS page
before you do the tests that follow.
EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùùû
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(2)
B.
If it is necessary to do Test No. 9 - Performance Test when you
replace a component, monitor the pressure ratio of the turbine
cooling air [PS3I/PS3.1]. You must monitor the pressure ratio when
you initially do a test on the engine at the powers more than idle.
This will make sure the correct quantity of turbine cooling air is
supplied to the turbine.
(a) If the pressure ratio is more than the maximum limit, the
turbine cooling air flow is too low (Fig. 506).
(b) If the pressure ratio is less than the minimum limit, there is
too much turbine cooling air flow. This condition could change
the performance of the engine. It can possibly cause bearing
skid as a result of the changes in the bearing thrust loads
(Fig. 506).
Precaution Procedures and Limits
S 735-368-P00
CAUTION:
_______
(1)
DO NOT MOVE THE THRUST LEVER FORWARD, OR DO NOT KEEP IT IN THE
SAME POSITION, ON AN ENGINE THAT HAD A SURGE (STALL). IF YOU
DO NOT MOVE THE THRUST LEVER REARWARD, YOU CAN CAUSE DAMAGE TO
THE ENGINE.
Compressor Surge (Stall)
NOTE:
____
(a)
(b)
During an engine operation at power more than 1.2 EPR,
keep one hand on the thrust lever and the other hand on the
fuel control switch. This will make it easier to stop the
engine if the compressor surge (stall), with overtemperature
which occurs quickly, shows.
If a compressor surge (stall) occurs, you must do the steps
that follow:
1) Quickly (in less than one second) move the thrust lever
rearward to operate the engine at minimum power.
2) Put the fuel control switch to the CUTOFF position.
3) Motor the engine until the EGT is less than 180°C.
If the EGT was not more than the limits after an emergency
engine shutdown, start the engine with the steps that follow:
EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùùû
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MAINTENANCE MANUAL
S 915-369-P00
CAUTION:
_______
(2)
MAKE SURE TO USE THE CORRECT START PROCEDURE AFTER AN EMERGENCY
ENGINE SHUTDOWN. DAMAGE TO THE TURBINE BLADE TIP SEALS CAN
OCCUR.
Start procedure after an emergency engine shutdown.
NOTE:
____
An emergency engine shutdown is when you stop the engine from
power levels more than minimum idle. Because of the
compressor surge (stall) or other emergency conditions, you
are not permitted to do the usual procedure to stop the
engine.
This does not apply to flight operations.
(a)
(3)
(4)
Refer to the procedure of operation for the power plant
(AMM 71-00-00/201).
S 735-365-P00
Ignition Ground Use Limits
(a) Keep the ignition off during all maintenance ground operations
after the engine is started. Do this to decrease the risk of
overtemperature when you have a compressor surge (stall).
S 735-366-P00
Wind Direction
(a) Tailwinds can cause bad results during ground operation of the
engines. This condition can cause a high EGT during a start,
idle, or low power. At a power of 1.2 EPR and more, a
compressor surge (stall) can occur.
(b) The data for the recommended wind direction during engine
ground tests is shown in Fig. 501.
EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùùû
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60`
60`
60`
1
THE WIND VELOCITY IS FOR STABLE
WIND CONDITIONS. DECREASE THE MAXIMUM
WIND LIMIT 5 KNOTS WHEN YOU HAVE GUSTS
OF WIND
2
STOP THE OPERATION OF THE ENGINE
MAINTENANCE IF THE EPR OR N1 DOES NOT
BECOME STABLE OR IF THE INLET NOISE
SUDDENLY CHANGES TO A BLOW TORCH TYPE
OF A SOUND (CAUSED BY SEPARATION OF THE
AIR AT THE COWL LIP). DECREASE THE
POWER TO IDLE AND EXAMINE THE RELATIVE
WIND DIRECTION AND SPEED. STOP THE
ENGINE AND CHANGE THE POSITION OF THE
AIRPLANE TO POINT IN THE DIRECTION OF
TH WIND, IF IT IS NECESSARY, BEFORE
YOU COMPLETE THE ENGINE MAINTENANCE
3
YOU CAN OPERATE THE APU DURING THE
OPERATION ON THE GROUND
RELATIVE WIND
RECOMMENDED (25 KNOTS MAXIMUM
WIND VELOCITY) 1
3
PERMITTED 1
2
3
NOT PERMITTED 3
152082
Recommended Relative Wind Direction During an Engine Operation
Figure 501
EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùùû
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C.
////////////////////////
/
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////////////////////////
Engine Test Data Symbols
(1)
S 995-367-P00
These symbols are given to some engine data at internal and external
locations on the engine. These are shown below:
AMB
TT2
PT2
PS2
PT2.5
PS3.1
PS3I
TT4.9
PT4.9
EPR
TLR
FF
N1
N2
N2C
EGT
OAT
BVA
SVA
Ambient Temperature (T) or Pressure (P)
Compressor Inlet Total Temperature
Compressor Inlet Total Pressure
Compressor Inlet Static Pressure
Low Pressure Compressor Discharge Total Pressure
Burner Case Static Pressure
Turbine Cooling Air Static Pressure
Turbine Discharge Total Temperature
Turbine Discharge Total Pressure
Engine Pressure Ratio
Thrust Lever Resolver
Fuel Flow
Low Pressure Compressor Rotor Angular Speed
High Pressure Compressor Rotor Angular Speed
High Pressure Compressor Rotor Angular Speed
Corrected To Low Pressure Compressor Pressure
Exhaust Gas Temperature
Outside Air Temperature
Bleed Valve Angle
Stator Vane Angle
EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùùû
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////////////////////////
TEST NO. 1 - ENGINE-DRIVEN (HYDRAULIC) PUMP (EDP) TEST
______________________________________________________
4.
TASK 71-00-00-715-018-P00
Test No. 1 - Engine-Driven (Hydraulic) Pump (EDP) Test
______________________________________________________
A. General
(1) This test examines the output pressure during an engine operation at
idle. This is done to make sure the performance of the
engine-driven pump is satisfactory.
B. References
(1) AMM 29-11-00/201, Main Hydraulic System
(2) AMM 71-00-00/201, Power Plant - General
(3) AMM 71-11-04/201, Fan Cowl Panels
(4) AMM 71-11-06/201, Core Cowl Panels
(5) AMM 78-31-00/201, Thrust Reverser System
C. Access
(1) Location Zones
211/212
Flight Compartment
411/421
Engine
D.
Do the Engine-Driven (Hydraulic) Pump Test.
(1)
(2)
S 865-019-P00
Pressurize the right hydraulic system with the electric motor pump
(AMM 29-11-00/201).
S 865-020-P00
Put the parking brake in the ON position.
S 865-021-P00
WARNING:
_______
(3)
(4)
(5)
(6)
USE AMM 71-00-00/201 TO OPERATE THE POWER PLANT. IF YOU DO NOT
USE THIS PROCEDURE, YOU CAN CAUSE DAMAGE TO EQUIPMENT OR INJURY
TO PERSONS.
Use the Power Plant Operation (Normal) procedure to start the engine
(AMM 71-00-00/201).
S 865-022-P00
Push the ELEC/HYD display select switch on the P61 panel.
S 865-023-P00
For left engine-driven pump, do the steps that follow:
(a) Make sure the HYD PUMPS L ENG switch, on the P5 Panel, is in
the ON position.
(b) Make sure the L HYD PRESS is 3000 |150 psi.
S 865-024-P00
For the right engine-driven pump, do the steps that follow:
(a) Put the HYD PUMPS R ELEC switch on the panel P5 to the OFF
position.
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TEST NO. 1 - ENGINE-DRIVEN (HYDRAULIC) PUMP (EDP) TEST
______________________________________________________
(b)
(c)
(d)
(7)
(8)
(9)
Make sure the HYD PUMPS R ENG switch, on the P5 Panel, is in
the ON position.
Make sure the R HYD PRESS is 3000 |150 psi.
Put the HYD PUMPS R ELEC switch on the P5 panel to the ON
position.
S 215-025-P00
Look at the ECS/MSG and EPCS pages on the bottom EICAS display for
messages.
(a) Correct all messages.
S 865-026-P00
Use the Power Plant Operation (Normal) procedure to do the engine
shutdown (AMM 71-00-00/201).
S 015-027-P00
Open the fan cowl panels (AMM 71-11-04/201).
S 045-379-P00
WARNING:
_______
DO THE THRUST REVERSER DEACTIVATION PROCEDURE TO PREVENT THE
OPERATION OF THE THRUST REVERSER. THE ACCIDENTAL OPERATION OF
THE THRUST REVERSER CAN CAUSE INJURY TO PERSONS OR DAMAGE TO
EQUIPMENT.
(10) Do this procedure: Thrust Reverser Deactivation for Ground
Maintenance (AMM 78-31-00/201).
S 015-030-P00
(11) Open the core cowl panels (AMM 71-11-06/201).
S 015-370-P00
WARNING:
_______
OBEY THE INSTRUCTIONS IN AMM 78-31-00/201 WHEN YOU OPEN THE
THRUST REVERSERS. IF YOU DO NOT OBEY THE INSTRUCTIONS, INJURY
TO PERSONS OR DAMAGE TO EQUIPMENT COULD OCCUR.
(12) Open the thrust reversers (AMM 78-31-00/201).
S 215-031-P00
(13) Examine the engine for leaks.
E.
S 365-032-P00
(14) Repair the leaks as it is necessary.
Put the airplane back to its initial condition
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TEST NO. 1 - ENGINE-DRIVEN (HYDRAULIC) PUMP (EDP) TEST
______________________________________________________
S 415-033-P00
WARNING:
_______
OBEY THE INSTRUCTIONS IN AMM 78-31-00/201 WHEN YOU CLOSE THE
THRUST REVERSERS. IF YOU DO NOT OBEY THE INSTRUCTIONS, INJURY
TO PERSONS OR DAMAGE TO EQUIPMENT COULD OCCUR.
(1)
Close the thrust reversers (AMM 78-31-00/201).
(2)
S 415-034-P00
Close the core cowl panels (AMM 71-11-06/201).
(3)
S 415-035-P00
Close the fan cowl panels (AMM 71-11-04/201).
(4)
S 445-036-P00
Do the activation procedure for the thrust reversers
(AMM 78-31-00/201).
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TEST NO. 2 - ENGINE MOTORING (DRY) LEAK TEST
____________________________________________
5.
TASK 71-00-00-215-037-P00
Test No. 2 - Engine Motoring (Dry) Leak Test
____________________________________________
A. General
(1) This test is a leak check for the oil system components and the fuel
system components upstream from the fuel control. Motor the engine
to supply power to the EEC and to examine the EPCS messages on the
EICAS.
B. References
(1) AMM 71-00-00/201, Power Plant - General
(2) AMM 71-11-04/201, Fan Cowl Panels
(3) AMM 71-11-06/201, Core Cowl Panels
(4) AMM 78-31-00/201, Thrust Reverser System
C. Access
(1) Location Zones
211/212
Flight Compartment
411/421
Engine
D.
Do the Engine Motoring Leak Test.
(1)
(2)
S 865-038-P00
Make sure the EEC MAINT POWER switch on the P61 panel is in the NORM
position.
S 015-040-P00
Open the fan cowl panels (AMM 71-11-04/201).
S 045-041-P00
WARNING:
_______
(3)
(4)
DO THE THRUST REVERSER DEACTIVATION PROCEDURE TO PREVENT THE
OPERATION OF THE THRUST REVERSER. THE ACCIDENTAL OPERATION OF
THE THRUST REVERSER CAN CAUSE INJURY TO PERSONS OR DAMAGE TO
EQUIPMENT.
Do this procedure: Thrust Reverser Deactivation for Ground
Maintenance (AMM 78-31-00/201).
S 015-042-P00
Open the core cowl panels (AMM 71-11-06/201).
S 015-043-P00
WARNING:
_______
(5)
OBEY THE INSTRUCTIONS IN AMM 78-31-00 WHEN YOU OPEN THE THRUST
REVERSERS. IF YOU DO NOT OBEY THE INSTRUCTIONS, INJURY TO
PERSONS OR DAMAGE TO EQUIPMENT COULD OCCUR.
Open the thrust reversers (AMM 78-31-00/201).
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TEST NO. 2 - ENGINE MOTORING (DRY) LEAK TEST
____________________________________________
S 865-044-P00
WARNING:
_______
(6)
(7)
(8)
(9)
E.
USE AMM 71-00-00/201 TO OPERATE THE POWER PLANT. IF YOU DO NOT
USE THIS PROCEDURE, YOU CAN CAUSE DAMAGE TO THE EQUIPMENT OR
INJURY TO PERSONS.
Use the Power Plant Dry-Motor procedure to motor the engine
(AMM 71-00-00/201).
S 865-045-P00
If you replaced the starter control valve, make sure the start valve
light goes off.
S 215-046-P00
Look at the EPCS page on the bottom EICAS display for EPCS messages.
(a) If EPCS messages show, do the corrections which are necessary
for the applicable EPCS message.
S 215-047-P00
Examine the engine for leaks.
(a) If you find a leak, repair the leak.
S 215-048-P00
(10) Do the engine motoring leak test again if you find leaks.
Put the airplane back to its initial condition
S 415-049-P00
WARNING:
_______
OBEY THE INSTRUCTIONS IN AMM 78-31-00/201 WHEN YOU CLOSE THE
THRUST REVERSERS. IF YOU DO NOT OBEY THE INSTRUCTIONS, INJURY
TO PERSONS OR DAMAGE TO EQUIPMENT COULD OCCUR.
(1)
Close the thrust reversers (AMM 78-31-00/201).
(2)
S 415-050-P00
Close the core cowl panels (AMM 71-11-06/201).
(3)
S 415-051-P00
Close the fan cowl panels (AMM 71-11-04/201).
(4)
S 445-052-P00
Do the activation procedure for the thrust reversers
(AMM 78-31-00/201).
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TEST NO. 2A - ENGINE MOTORING (WET) LEAK TEST
_____________________________________________
6.
TASK 71-00-00-215-053-P00
Test No. 2A - Engine Motoring (Wet) Leak Test
_____________________________________________
A. General
(1) This test is used to examine the components downstream of the fuel
control. These components are the fuel system components and the
components operated by the fuel pressure.
B. References
(1) AMM 71-00-00/201, Power Plant - General
(2) AMM 71-11-04/201, Fan Cowl Panels
(3) AMM 71-11-06/201, Core Cowl Panels
(4) AMM 78-31-00/201, Thrust Reverser System
C. Access
(1) Location Zones
411/421
Engine
D.
Do the Engine Motoring Leak Test.
(1)
S 015-054-P00
Open the fan cowl panels (AMM 71-11-04/201).
S 045-055-P00
WARNING:
_______
(2)
(3)
DO THE THRUST REVERSER DEACTIVATION PROCEDURE TO PREVENT THE
OPERATION OF THE THRUST REVERSER. THE ACCIDENTAL OPERATION OF
THE THRUST REVERSER CAN CAUSE INJURY TO PERSONS OR DAMAGE TO
EQUIPMENT.
Do this procedure: Thrust Reverser Deactivation for Ground
Maintenance (AMM 78-31-00/201).
S 015-056-P00
Open the core cowl panels (AMM 71-11-06/201).
S 015-057-P00
WARNING:
_______
(4)
OBEY THE INSTRUCTIONS IN AMM 78-31-00 WHEN YOU OPEN THE THRUST
REVERSERS. IF YOU DO NOT OBEY THE INSTRUCTIONS, INJURY TO
PERSONS OR DAMAGE TO EQUIPMENT COULD OCCUR.
Open the thrust reversers (AMM 78-31-00/201).
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TEST NO. 2A - ENGINE MOTORING (WET) LEAK TEST
_____________________________________________
S 865-058-P00
WARNING:
_______
(5)
USE AMM 71-00-00/201 TO OPERATE THE POWER PLANT. IF YOU DO NOT
USE THIS PROCEDURE, YOU CAN CAUSE DAMAGE TO EQUIPMENT OR INJURY
TO PERSONS.
Use the Power Plant Wet-Motor procedure to motor the engine
(AMM 71-00-00/201).
S 215-059-P00
Examine the engine for leaks.
(a) If you find a leak, repair the leak.
Put the airplane back to its initial condition
(6)
E.
S 415-371-P00
WARNING:
_______
OBEY THE INSTRUCTIONS IN AMM 78-31-00 WHEN YOU CLOSE THE THRUST
REVERSERS. IF YOU DO NOT OBEY THE INSTRUCTIONS, INJURY TO
PERSONS OR DAMAGE TO EQUIPMENT COULD OCCUR.
(1)
Close the thrust reversers (AMM 78-31-00/201).
(2)
S 415-060-P00
Close the core cowl panels (AMM 71-11-06/201).
(3)
S 415-061-P00
Close the fan cowl panels (AMM 71-11-04/201).
(4)
S 445-062-P00
Do the activation procedure for the thrust reversers
(AMM 78-31-00/201).
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TEST NO. 3 - MINIMUM IDLE TEST
______________________________
7.
TASK 71-00-00-715-063-P00
Test No. 3 - Minimum Idle Test
______________________________
A. General
(1) This test examines the operation of the engine from start up until
the engine becomes stable at idle.
B. References
(1) AMM 71-00-00/201, Power Plant - General
C. Access
(1) Location Zones
211/212
Flight Compartment
D.
Do the Minimum Idle Test
S 865-064-P00
WARNING:
_______
(1)
(2)
(3)
USE AMM 71-00-00/201 TO OPERATE THE POWER PLANT. IF YOU DO NOT
USE THIS PROCEDURE, YOU CAN CAUSE DAMAGE TO EQUIPMENT OR INJURY
TO PERSONS.
Use the Power Plant Operation (Normal) procedure to start the engine
(AMM 71-00-00/201).
(a) Permit the engine to become stable at idle for five minutes.
(b) Make sure there are satisfactory engine indications.
S 215-065-P00
Look at the ECS/MSG and EPCS pages on the bottom EICAS display for
messages.
(a) If messages show, do the corrections which are necessary for
the applicable message.
S 865-066-P00
Use the Power Plant Operation (Normal) procedure to do the engine
shutdown (AMM 71-00-00/201).
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TEST NO. 3A - IDLE LEAK TEST FOR THE OIL AND FUEL SYSTEMS
_________________________________________________________
8.
TASK 71-00-00-795-408-P00
Test No. 3A - Idle Leak Test for the Oil and Fuel Systems
_________________________________________________________
A. General
(1) This test is used to examine the engine for oil and fuel leaks after
you operate the engine at the minimum idle.
(2) You can operate the engine with the fan cowl panels in the open or
closed position for this test. If you operate the engine with the
fan cowl panels open, you must obey the instructions that follow:
(a) You must use inlet screens on the engine during engine
operation with the fan cowls open.
(b) Make sure the airplane is static (not towed or taxied).
(c) Make sure fire extinguishing equipment is available..
NOTE:
____
(d)
(e)
(f)
Do not operate the engine with open fan cowl panels if the wind
speed is more than 20 knots.
Do not operate the engine with open fan cowl panels if the wind
gusts are more than 30 knots.
Do not operate the engine in reverse thrust.
NOTE:
____
(g)
(h)
C.
You must operate the engine in forward thrust only.
Do not operate the engine at more than idle RPM with the fan
cowl panels open.
Each fan cowl panel has two hold-open rods. You must install
the two hold-open rods on each open fan cowl panel to safely
keep it in the open position.
NOTE:
____
B.
The airplane fire detection and extinguishing functions
are reduced when the fan cowls are open.
Make sure each hold-open rod is fully extended and
locked.
References
(1) AMM 71-00-00/201, Power Plant - General
(2) AMM 71-11-04/201, Fan Cowl Panels
(3) AMM 71-11-06/201, Core Cowl Panels
(4) AMM 78-31-00/201, Thrust Reverser System
Access
(1) Location Zones
211/212
Flight Compartment
411/421
Engine
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TEST NO. 3A - IDLE LEAK TEST FOR THE OIL AND FUEL SYSTEMS
_________________________________________________________
(2)
D.
Access Panels
413AL/414AR
415AL/416AR
417AL/418AR
423AL/424AR
425AL/426AR
427AL/428AR
Fan Cowl Panels, Left Engine
Thrust Reversers, Left Engine
Core Cowl Panels, Left Engine
Fan Cowl Panels, Right Engine
Thrust Reversers, Right Engine
Core Cowl Panels, Right Engine
Do the Idle Leak Test for the Oil and Fuel Systems.
S 015-430-P00
WARNING:
_______
(1)
IF YOU OPEN THE FAN COWL PANELS, YOU MUST NOT OPERATE THE
ENGINE AT MORE THAN IDLE RPM, OR OPERATE THE ENGINE IN REVERSE
THRUST. YOU MUST NOT OPERATE THE ENGINE WITH OPEN FAN COWL
PANELS IF THE WIND SPEED IS MORE THAN 20 KNOTS, OR IF THE WIND
GUSTS ARE MORE THAN 30 KNOTS. ALSO, YOU MUST INSTALL THE TWO
HOLD-OPEN RODS ON EACH FAN COWL PANEL THAT IS OPEN. IF YOU DO
NOT OBEY THESE INSTRUCTIONS, DAMAGE TO THE ENGINE OR FAN COWL
PANELS, AND INJURY TO PERSONS CAN OCCUR.
If it is necessary, open the fan cowl panels (AMM 71-11-04/201).
S 865-407-P00
WARNING:
_______
(2)
(3)
(4)
USE AMM 71-00-00/201 TO OPERATE THE POWER PLANT. IF YOU DO NOT
USE THIS PROCEDURE, YOU CAN CAUSE INJURIES TO PERSONS OR DAMAGE
TO EQUIPMENT.
Use the Power Plant Operation (Normal) procedure to start the engine
(AMM 71-00-00/201).
(a) Permit the engine to become stable at idle until you get an oil
temperature of 149 degrees F (65 degrees C), then permit the
engine to idle for one additional minute.
(b) Make sure there are satisfactory engine indications.
S 865-409-P00
Use the Power Plant Operation (Normal) procedure to do the engine
shutdown (AMM 71-00-00/201).
S 015-410-P00
Do the steps that follow to open the applicable engine cowls:
(a) If you kept the fan cowl panels closed during the engine
operation, open the fan cowl panels (AMM 71-11-04/201).
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TEST NO. 3A - IDLE LEAK TEST FOR THE OIL AND FUEL SYSTEMS
_________________________________________________________
WARNING:
_______
(b)
Do this procedure: Thrust Reverser Deactivation for Ground
Maintenance (AMM 78-31-00/201).
Open the core cowl panels (AMM 71-11-06/201).
(c)
WARNING:
_______
(d)
(5)
(7)
OBEY THE INSTRUCTIONS IN AMM 78-31-00/201 WHEN YOU OPEN
THE THRUST REVERSERS. IF YOU DO NOT OBEY THE
INSTRUCTIONS, YOU CAN CAUSE INJURIES TO PERSONS OR DAMAGE
TO EQUIPMENT.
Open the thrust reversers (AMM 78-31-00/201).
S 795-411-P00
Examine the engine for oil leaks.
NOTE:
____
(6)
DO THE THRUST REVERSER DEACTIVATION PROCEDURE TO PREVENT
THE OPERATION OF THE THRUST REVERSERS. THE ACCIDENTAL
OPERATION OF THE THRUST REVERSERS CAN CAUSE INJURIES TO
PERSONS OR DAMAGE TO EQUIPMENT.
If there is oil on the tube connections or the oil filter
cover, clean the oil off and operate the engine again. If
there is more oil on the tube connections or the oil filter
cover, the engine has an oil leak.
S 365-412-P00
If the engine has an oil leak, repair the leak and do this test
again.
S 795-451-P00
Examine the engine for fuel leaks.
NOTE:
____
If there is fuel on the tube connections or the fuel system
components, clean it off and operate the engine again. If
there is more fuel on the tube connections or the fuel system
components, the engine has a fuel leak.
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TEST NO. 3A - IDLE LEAK TEST FOR THE OIL AND FUEL SYSTEMS
_________________________________________________________
S 365-452-P00
If the engine has a fuel leak, repair the leak and do this test
again.
Put the Airplane Back to its Usual Condition.
(8)
E.
S 415-413-P00
WARNING:
_______
OBEY THE INSTRUCTIONS IN AMM 78-31-00/201 WHEN YOU CLOSE THE
THRUST REVERSERS. IF YOU DO NOT OBEY THE INSTRUCTIONS, YOU CAN
CAUSE INJURIES TO PERSONS OR DAMAGE TO EQUIPMENT.
(1)
Close the thrust reversers (AMM 78-31-00/201).
(2)
S 015-414-P00
Close the core cowl panels (AMM 71-11-06/201).
(3)
S 445-415-P00
Do the thrust reverser activation procedure (AMM 78-31-00/201).
(4)
S 415-416-P00
Close the fan cowl panels (AMM 71-11-04/201).
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TEST NO. 4 - INTEGRATED DRIVE GENERATOR (IDG) TEST
__________________________________________________
9.
TASK 71-00-00-715-067-P00
Test No. 4 - Integrated Drive Generator (IDG) Test
__________________________________________________
A. General
(1) This test examines the performance of the IDG and the operation of
the IDG drive disconnect.
B. References
(1) AMM 24-22-00/201, Electrical Power - Control
(2) AMM 49-11-00/201, Auxiliary Power Unit
(3) AMM 71-00-00/201, Power Plant - General
(4) AMM 71-11-04/201, Fan Cowl Panels
(5) AMM 71-11-06/210, Core Cowl Panels
(6) AMM 78-31-00/201, Thrust Reverser System
C. Access
(1) Location Zones
211/212
Flight Compartment
411/421
Engine
D.
Do the Integrated Drive Generator (IDG) test.
(1)
S 865-068-P00
Supply electrical power, from a ground power or an APU generator,
during the test (AMM 24-22-00/201).
S 865-069-P00
WARNING:
_______
(2)
(3)
(4)
(5)
USE AMM 71-00-00/201 TO OPERATE THE POWER PLANT. IF YOU DO NOT
USE THIS PROCEDURE, YOU CAN CAUSE DAMAGE TO EQUIPMENT OR INJURY
TO PERSONS.
Use the Power Plant Operation (Normal) procedure to start the engine
(AMM 71-00-00/201).
S 865-070-P00
Set the applicable L(R) GEN CONT switch on the P5 panel to the OFF
position.
(a) Make sure the OFF light goes on.
S 865-071-P00
Put the applicable L(R) GEN CONT switch on the P5 panel to the ON
position.
(a) Make sure the OFF light goes off.
S 865-072-P00
Push the ELEC/HYD display select switch on the P61 panel.
(a) Make sure the indications that follow show for the applicable
L(R) generator:
1) AC-V = 115 |5
2) FREQ = 400 |5
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TEST NO. 4 - INTEGRATED DRIVE GENERATOR (IDG) TEST
__________________________________________________
(6)
S 865-073-P00
Do the IDG disconnect check.
CAUTION:
_______
DO NOT OPERATE THE GEN DRIVE DISC SWITCH FOR MORE THAN
THREE SECONDS. PERMIT A MINIMUM OF 60 SECONDS BETWEEN
OPERATIONS.
CAUTION:
_______
DO NOT OPERATE THE GEN DRIVE DISC SWITCH UNLESS THE ENGINE
IS AT OR ABOVE IDLE N2 RPM. DO NOT DISCONNECT THE IDG
WITH THE ENGINE BELOW IDLE. THIS CAN CAUSE DAMAGE TO THE
DISCONNECT DOG TEETH.
(a)
(b)
(7)
(8)
While you operate the engine at minimum idle N2 rpm or more,
push the applicable L(R) GEN DRIVE DISC switch on the P5 panel.
Make sure the applicable L(R) DRIVE light and L(R) GEN CONT OFF
lights go on to make sure the IDG is disconnected.
S 865-074-P00
Use the Power Plant Operation (Normal) procedure to do the engine
shutdown (AMM 71-00-00/201).
S 015-075-P00
Open the fan cowl panels (AMM 71-11-04/201).
S 045-076-P00
WARNING:
_______
(9)
DO THE THRUST REVERSER DEACTIVATION PROCEDURE TO PREVENT THE
OPERATION OF THE THRUST REVERSER. THE ACCIDENTAL OPERATION OF
THE THRUST REVERSER CAN CAUSE INJURY TO PERSONS OR DAMAGE TO
EQUIPMENT.
Do this procedure: Thrust Reverser Deactivation for Ground
Maintenance (AMM 78-31-00/201).
S 015-362-P00
(10) Open the core cowl panels (AMM 71-11-06/201).
S 015-372-P00
WARNING:
_______
OBEY THE INSTRUCTIONS IN AMM 78-31-00 WHEN YOU OPEN THE THRUST
REVERSERS. IF YOU DO NOT OBEY THE INSTRUCTIONS, INJURY TO
PERSONS OR DAMAGE TO EQUIPMENT COULD OCCUR.
(11) Open the thrust reversers (AMM 78-31-00/201).
S 215-078-P00
(12) Examine the engine for leaks.
(a) If you find a leak, repair the leak.
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TEST NO. 4 - INTEGRATED DRIVE GENERATOR (IDG) TEST
__________________________________________________
S 865-079-P00
(13) Make sure the N2 rotor is stable.
S 865-080-P00
(14) Pull the IDG disconnect reset ring until you feel the solenoid pin
go into position.
S 415-081-P00
WARNING:
_______
OBEY THE INSTRUCTIONS IN AMM 78-31-00 WHEN YOU OPEN THE THRUST
REVERSERS. IF YOU DO NOT OBEY THE INSTRUCTIONS, INJURY TO
PERSONS OR DAMAGE TO EQUIPMENT COULD OCCUR.
(15) Close the thrust reversers (AMM 78-31-00/201).
S 415-082-P00
(16) Close the core cowl panels (AMM 71-11-06/201).
S 415-386-P00
(17) Close the fan cowl panels (AMM 71-11-04/201).
S 445-387-P00
(18) Do the activation procedure for the thrust reversers
(AMM 78-31-00/201).
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SEE A
INTEGRATED DRIVE
GENERATOR (IDG)
IDG DISCONNECT
RESET RING
A
117496
IDG Reset
Figure 502
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TEST NO. 5 - MAIN GEARBOX REPLACEMENT TEST
__________________________________________
TASK 71-00-00-725-084-P00
10. Test
__________________________________________
No. 5 - Main Gearbox Replacement Test
A. General
(1) This procedure gives the minimum steps necessary to do a test after
the replacement of the main gearbox. The procedure examines the
gearbox-mounted components, leaks, and vibration.
NOTE:
____
B.
The leak checks include a recommended Vacuum Leak Test.
You can do the Test No. 20 - Static Leak Test as an optional
procedure. Do only one of the tests to examine the oil
system for leaks.
Equipment
(1)
C.
D.
Adapter, Ejector Inlet Breather Tube PWA 81903, Pratt & Whitney
(2) CTE 7075 - Cart
(3) Plate, Cover - PWA 81821, Pratt and Whitney
(4) Pint Bottle of Water - Commercially Available
(5) Hose - 2 Feet long, 3/8 Inch Diameter for Slip
Fitting Drain Tubes
(6) Air Supply - Pneumatic unit which supplies air
at 10 psig (69 kPa) maximum regulated pressure
and 300°F (149°C) maximum temperature (air at
or near room temperature is recommended).
Consumable Materials
(1) G02151 Solution - Leak Check - PMC 9569 Fluid
References
(1) AMM 12-11-01/301, Fuel Tank - Pressure Fueling (Replenishing)
(2) AMM 12-12-01/301, Hydraulic System (Replenishing)
(3) AMM 12-13-01/301, Engine - Oil Servicing
(4) AMM 12-13-02/301, Engine Starter (Oil Servicing)
(5) AMM 12-13-03/301, Integrated Drive Generator (Oil Servicing)
(6) AMM 24-22-00/201, Electrical Power - Control
(7) AMM 29-11-00/201, Main Hydraulic System
(8) AMM 36-00-00/201, Pneumatic - General
(9) AMM 49-11-00/201, Auxiliary Power Unit
(10) AMM 71-00-00/201, Power Plant - General
(11) AMM 71-11-04/201, Fan Cowl Panels
(12) AMM 71-11-06/201, Core Cowl Panels
(13) AMM 78-31-00/201, Thrust Reverser System
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TEST NO. 5 - MAIN GEARBOX REPLACEMENT TEST
__________________________________________
E.
Access
(1) Location Zones
211
Flight Compartment
212
Flight Compartment
413
L Power Plant Fan Cowl Panel
414
L Power Plant Fan Cowl Panel
415
L Power Plant Fan Reverser
416
L Power Plant Fan Reverser
423
R Power Plant Fan Cowl Panel
424
R Power Plant Fan Cowl Panel
425
R Power Plant Fan Reverser
426
R Power Plant Fan Reverser
(2)
F.
Access Panels
413AL
Fan
414AR
Fan
415AL
Fan
416AR
Fan
423AL
Fan
424AR
Fan
425AL
Fan
426AR
Fan
Cowl Panel (Left)
Cowl Panel (Right)
Reverser (Left)
Reverser (Right)
Cowl Panel (Left)
Cowl Panel (Right)
Reverser (Left)
Reverser (Right)
Prepare to do a Test of the Main Gearbox
S 865-085-P00
CAUTION:
_______
(1)
(2)
(3)
DO NOT OPERATE THE AIRPLANE HYDRAULIC SYSTEMS UNLESS THE FUEL
QUANTITY IS SUFFICIENT TO GO ABOVE THE HYDRAULIC FLUID HEAT
EXCHANGERS. THE AIRPLANE HYDRAULIC SYSTEMS COULD BECOME TOO
HOT AND DAMAGE COULD OCCUR.
Make sure the fuel tanks have a minimum of 9000 (4085 kilograms)
pounds of fuel (AMM 12-11-01/301).
(a) Make sure the tank sumps are free of water.
S 215-086-P00
Examine the hydraulic fluid reservoir for a sufficient quantity (you
can see the hydraulic fluid in the sight gages on the reservoirs).
(a) If it is necessary, do the servicing procedure for the
hydraulic reservoirs (AMM 12-12-01/301).
S 215-087-P00
Examine the engine oil tank for sufficient servicing (the oil level
is at the lip of the filler neck).
(a) If it is necessary, do the servicing procedure for the engine
oil tank (AMM 12-13-01/301).
1) Before you install the oil tank cap, make sure the packing
is free of damage and has no deterioration.
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__________________________________________
S 215-088-P00
Examine the engine starter for sufficient servicing.
(a) If it is necessary, do the servicing procedure for the engine
starter (AMM 12-13-02/301).
(4)
S 215-089-P00
Examine the IDG for sufficient servicing.
(a) If it is necessary, do the servicing procedure for the IDG
(AMM 12-13-03/301).
(5)
S 865-090-P00
Pressurize the right hydraulic system with the electric motor pump
(AMM 29-11-00/201).
(6)
(7)
S 865-091-P00
Put the parking brake in the ON position.
(8)
S 015-092-P00
Open the fan cowl panels (AMM 71-11-04/201).
S 045-093-P00
WARNING:
_______
(9)
DO THE THRUST REVERSER DEACTIVATION PROCEDURE TO PREVENT THE
OPERATION OF THE THRUST REVERSER. THE ACCIDENTAL OPERATION OF
THE THRUST REVERSER CAN CAUSE INJURY TO PERSONS OR DAMAGE TO
EQUIPMENT.
Do this procedure: Thrust Reverser Deactivation for Ground
Maintenance (AMM 78-31-00/201).
S 015-094-P00
(10) Open the core cowl panels (AMM 71-11-06/201).
S 015-095-P00
WARNING:
_______
G.
OBEY THE INSTRUCTIONS IN AMM 78-31-00 WHEN YOU OPEN THE THRUST
REVERSERS. IF YOU DO NOT OBEY THE INSTRUCTIONS, INJURY TO
PERSONS OR DAMAGE TO EQUIPMENT COULD OCCUR.
(11) Open the thrust reversers (AMM 78-31-00/201).
Do the Leak Test - Vacuum Method (Recommended) (Fig. 502A)
NOTE:
____
This test is recommended, or you can do the Test No. 20 - Static
Leak Test, as an optional procedure. Do only one of these tests
to examine the oil system for leaks.
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SEE
C
SEE
SEE
A
B
BOLT (3 LOCATIONS)
NUT (3 LOCATIONS)
INSERT
PLUG
PACKING
DEOILER
BRACKET
DEOILER
OUTLET
ELBOW
PACKING
EJECTOR INLET
BREATHER TUBE
FWD
MAIN GEARBOX
A
597893
Oil System Leak Test
Figure 502A (Sheet 1)
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IDG PAD
SEAL DRAIN
FUEL PUMP PAD
SEAL DRAIN
FWD
HYDRAULIC PUMP
PAD SEAL DRAIN
EEC ALTERNATOR
PAD SEAL DRAIN
B
DEOILER
OUTLET
ELBOW
DEOILER
FWD
USE THE PWA 81903
ADAPTER TO
PRESSURIZE THE SYSTEM
THROUGH THIS CONNECTOR
EJECTOR INLET
BREATHER TUBE
C
L-95370
629900
Oil System Leak Test
Figure 502A (Sheet 2)
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TEST NO. 5 - MAIN GEARBOX REPLACEMENT TEST
__________________________________________
(1)
S 725-097-P00
To do the leak check, do the steps that follow:
(a) Put the PWA 81903 adapter on the open end of the ejector inlet
breather tube.
(b) Put the clamp detail of the PWA 81903 adapter on the rear face
of the ejector inlet breather tube.
(c) Install the retaining bolts through the PWA 81903 adapter and
into the clamp detail.
NOTE:
____
If it is necessary, use more adapters to adapt to the
pressure source. You must attach a pressure gage to the
.4375 - 20-inch threaded connector. The pressure source
is attached to the 1.0625 - 12-inch threaded air inlet
connector.
(d)
(e)
(f)
H.
Attach the line from CTE 7075 cart to the PWA 81903 adapter.
Apply a pressure of -20 inches (-508.000 mm) hg for the test.
Make sure the airflow leakage into the engine compartments
(No. 1, 2, 3, 4, and 5 plus gearbox) is not more than a maximum
of 50 pounds/hour (22.68 kg/hour) removed from the overboard
breather.
(g) When you complete the test satisfactorily, do the steps that
follow:
1) Remove the line from the PWA 81903 adapter.
2) Remove the PWA 81903 adapter and all other adapters, if
applicable, from the main gearbox.
Put the Airplane Back To Its Initial Condition
S 415-098-P00
WARNING:
_______
OBEY THE INSTRUCTIONS IN AMM 78-31-00 WHEN YOU CLOSE THE THRUST
REVERSERS. IF YOU DO NOT OBEY THE INSTRUCTIONS, INJURY TO
PERSONS OR DAMAGE TO EQUIPMENT COULD OCCUR.
(1)
Close the thrust reversers (AMM 78-31-00/201).
(2)
S 415-099-P00
Close the core cowl panels (AMM 71-11-06/201).
(3)
S 415-100-P00
Close the fan cowl panels (AMM 71-11-04/201).
(4)
S 445-101-P00
Do the activation procedure for the thrust reversers
(AMM 78-31-00/201).
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TEST NO. 5 - MAIN GEARBOX REPLACEMENT TEST
__________________________________________
I.
Do the Wet Motor Leak Test
(1)
S 015-112-P00
Open the fan cowl panels (AMM 71-11-04/201).
S 045-113-P00
WARNING:
_______
(2)
(3)
DO THE THRUST REVERSER DEACTIVATION PROCEDURE TO PREVENT THE
OPERATION OF THE THRUST REVERSER. THE ACCIDENTAL OPERATION OF
THE THRUST REVERSER CAN CAUSE INJURY TO PERSONS OR DAMAGE TO
EQUIPMENT.
Do this procedure: Thrust Reverser Deactivation for Ground
Maintenance (AMM 78-31-00/201).
S 015-114-P00
Open the core cowl panels (AMM 71-11-06/201).
S 015-115-P00
WARNING:
_______
(4)
OBEY THE INSTRUCTIONS IN AMM 78-31-00 WHEN YOU OPEN THE THRUST
REVERSERS. IF YOU DO NOT OBEY THE INSTRUCTIONS, INJURY TO
PERSONS OR DAMAGE TO EQUIPMENT COULD OCCUR.
Open the thrust reversers (AMM 78-31-00/201).
S 865-116-P00
WARNING:
_______
(5)
(6)
USE AMM 71-00-00/201 TO OPERATE THE POWER PLANT. IF YOU DO NOT
USE THIS PROCEDURE, YOU CAN CAUSE DAMAGE TO EQUIPMENT AND
INJURY TO PERSONS.
Use the Power Plant Wet-Motor procedure to motor the engine
(AMM 71-00-00/201).
S 215-117-P00
Examine the engine for leaks.
(a) If you find a leak, repair the leak.
(b) If leaks are found, do the test again.
S 415-118-P00
WARNING:
_______
(7)
OBEY THE INSTRUCTIONS IN AMM 78-31-00 WHEN YOU CLOSE THE THRUST
REVERSERS. IF YOU DO NOT OBEY THE INSTRUCTIONS, INJURY TO
PERSONS OR DAMAGE TO EQUIPMENT COULD OCCUR.
Close the thrust reversers (AMM 78-31-00/201).
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__________________________________________
(8)
S 415-119-P00
Close the core cowl panels (AMM 71-11-06/201).
(9)
S 415-120-P00
Close the fan cowl panels (AMM 71-11-04/201).
S 445-121-P00
(10) Do the activation procedure for the thrust reversers
(AMM 78-31-00/201).
S 865-122-P00
WARNING:
_______
USE AMM 71-00-00/201 TO OPERATE THE POWER PLANT. IF YOU DO NOT
USE THIS PROCEDURE, YOU CAN CAUSE DAMAGE TO EQUIPMENT OR INJURY
TO PERSONS.
(11) Use the Power Plant Operation (Normal) procedure to start the engine
(AMM 71-00-00/201).
S 715-123-P00
(12) Do the Engine Operation Checks
(a) Make sure the engine indications are satisfactory.
(b) Look at the ECS/MSG and EPCS pages on the lower EICAS display
for messages.
1) If messages show, do the corrections which are necessary
for the applicable message.
WARNING:
_______
USE AMM 71-00-00/201 TO OPERATE THE POWER PLANT. IF YOU
DO NOT USE THIS PROCEDURE, YOU CAN CAUSE DAMAGE TO
EQUIPMENT OR INJURY TO PERSONS.
CAUTION:
_______
MAKE SURE TO START THE OTHER ENGINE OR THE APU. TO
PREPARE FOR AN EMERGENCY ENGINE SHUTDOWN, YOU MUST OPERATE
THE OTHER ENGINE OR THE APU FOR PNEUMATIC POWER. IF THE
PNEUMATIC POWER IS NOT AVAILABLE DURING AN EMERGENCY
ENGINE SHUTDOWN, YOU CAN CAUSE DAMAGE TO THE ENGINE.
(c)
Do the Power Plant Operation (Normal) procedure to start the
other engine (AMM 71-00-00/201) or do the APU operation
(AMM 49-11-00/201) procedure.
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__________________________________________
(d)
(e)
(f)
(g)
Remove the ground pneumatic power, if it was supplied
(AMM 36-00-00/201).
Examine the Integrated Drive Generator.
1) Supply a different electrical power source, the ground
power or the APU generator (AMM 24-22-00/201).
2) Put the applicable L(R) GEN CONT switch on the P5 panel to
the OFF position.
3) Put the applicable L(R) GEN CONT switch on the P5 panel to
the ON position.
4) Push the ELEC/HYD display select switch on the P61 panel.
5) Make sure the indications that follow show for the
applicable L(R) generator:
a) AC-V = 115 |5
b) FREQ = 400 |5
Examine the engine-driven (hydraulic) pump.
1) For the left engine-driven pump, do the steps that follow:
a) Put the HYD PUMPS L ENG pump switch on the P5 panel to
the ON position.
b) Make sure the L HYD PRESS is 3000 |150 psi.
c) Put the HYD PUMPS L ENG pump switch on the P5 panel to
the OFF position.
2) For the right engine-driven pump, do the steps that follow:
a) Put the HYD PUMPS R ELEC pump switch on the P5 panel to
the OFF position.
b) Put the HYD PUMPS R ENG pump switch on the P5 panel to
the ON position.
c) Make sure the R HYD PRESS is 3000 |150 psi.
d) Put the HYD PUMPS R ENG pump switch on the P5 panel to
the OFF position.
e) Put the HYD PUMPS R ELEC pump switch on the P5 panel to
the ON position.
Examine the oil pump pressure.
1) With the indications from the PERF/APU page on the bottom
EICAS display, examine the manifold and scavenge oil
pressure with the steps that follow:
a) Oil Temperature - TEMP
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TEST NO. 5 - MAIN GEARBOX REPLACEMENT TEST
__________________________________________
2)
b) Oil Pressure Delta P - DIFF
c) Engine Speed, N2 - N2
d) No. 4 Restrictor Pressure - SCAV
Examine the manifold and scavenge oil pressure.
a) Make sure the oil temperature is more than 95°C.
b) Slowly increase the speed of the engine until the No. 4
restrictor valve closes (i.e., SCAV is the same as or
more than 75 psi [517.1 kpa]).
c) Permit the engine to become stable for three minutes.
d) Make a record of the N2 speed, the DIFF oil pressure,
and the SCAV oil pressure.
e) Make sure the SCAV oil pressure does not go above the
maximum pressure limits (Fig. 503).
f) If the SCAV oil pressure goes above the maximum oil
pressure limits, look at the ECS/MSG and EPCS pages on
the bottom EICAS display for messages.
g) If messages show, do the corrections which are
necessary for the applicable message.
h) Move the thrust lever rearward to operate at minimum
power.
i) Examine the manifold oil pressure.
NOTE:
____
The manifold oil pressure is equivalent to the
SCAV oil pressure plus the DIFF oil pressure.
1
_
3)
Add the SCAV oil pressure and the DIFF oil
pressure.
2
_
Make sure the manifold oil pressure which was
calculated is not more than the maximum pressure
limits (Fig. 504).
If the manifold oil pressure is above the maximum limits,
adjust the oil pressure.
a) Use the Power Plant Operation (Normal) procedure to do
the engine shutdown (AMM 71-00-00/201).
NOTE:
____
The adjustment of oil pressure is not possible
while the engine is in operation.
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NO. 4 BEARING SCAVENGE VALVE PRESSURE - PSIG
160
150
140
MAXIMUM
130
120
110
100
90
80
70
60
50
40
30
MAXIMUM
NOTE:
____
20
10
0
7000
(57)
8000
(65)
9000
(73.5)
BELOW 10,000 RPM, NO. 4 SCAVENGE
MAXIMUM LIMIT IS ADJUSTED TO DETECT
DISTRESSED CARBON SEALS; CURVE DOES
NOT EQUAL MANIFOLD OIL PRESSURE
(MOP) MINUS ~ MAIN OIL PRESSURE.
10000
(81.5)
11000
(90)
12000
(98)
OBSERVED HIGH ROTOR SPEED (N2) - RPM (%)
KEY DATA POINTS
N2 (RPM)
Pscav (PSIG)
7000
20
9300
22
1000
40
10300
110
11950
160
12500
160
116079
No. 4 Restrictor Oil Pressure SCAV Vs. N2 Rotor Speed
Figure 503
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305
MANIFOLD OIL PRESSURE PSIG (KPa)
300
(2068.4)
200
(1379.0)
170
UPPER LIMIT
160
TRIM BAND
LOWER LIMIT
110
100
(689.5)
80
20
60
57
70
N2 SPEED
75
80 82
90
98 100
PERCENT
116080
Oil Pressure Adjustment Band
Figure 504
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TEST NO. 5 - MAIN GEARBOX REPLACEMENT TEST
__________________________________________
b)
Open the fan cowl panels (AMM 71-11-04/201).
WARNING:
_______
c)
d)
Do this procedure: Thrust Reverser Deactivation for
Ground Maintenance (AMM 78-31-00/201).
Open the core cowl panels (AMM 71-11-06/201).
WARNING:
_______
e)
f)
DO THE THRUST REVERSER DEACTIVATION PROCEDURE TO
PREVENT THE OPERATION OF THE THRUST REVERSER.
THE ACCIDENTAL OPERATION OF THE THRUST REVERSER
CAN CAUSE INJURY TO PERSONS OR DAMAGE TO
EQUIPMENT.
OBEY THE INSTRUCTIONS IN AMM 78-31-00 WHEN YOU
OPEN THE THRUST REVERSERS. IF YOU DO NOT OBEY
THE INSTRUCTIONS, INJURY TO PERSONS OR DAMAGE TO
EQUIPMENT COULD OCCUR.
Open the thrust reversers (AMM 78-31-00/201).
ENGINES WITH OIL PUMPS THAT HAVE BARRIER SCREENS;
Remove and examine the barrier screen.
NOTE:
____
It is necessary to make sure the barrier screen
does not have contamination before you do the
pressure adjustment.
1
_
g)
h)
i)
If the barrier screen is broken, remove and clean
the trim (needle) valve.
Remove the dust cover for the oil pressure trim valve
(found on the lubrication and scavenge oil pump)
(Fig. 505).
While you hold the trim (needle) valve, loosen the
jamnut.
Turn the trim (needle) valve counterclockwise to
decrease the pressure or clockwise to increase the
pressure.
NOTE:
____
At minimum power, do not permit the oil pressure
to go below the bottom of the trim band. But,
at minimum power, you can go more than the trim
band to put the oil pressure in the pressure
limits at the high power point. The high side
of the trim band is only an aid.
One full turn of the trim (needle) valve will
change the oil pressure by 15-30 psi
(103.4-206.8 kPa).
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SEE A
LUBRICATION AND
SCAVENGE OIL PUMP
A
BARRIER
SCREEN
A
A
2
A
1
A
DUST COVER
TRIM (NEEDLE) VALVE
JAMNUT
BODY NUT
1
LUBRICATION AND SCAVENGE OIL PUMP
WITHOUT THE BARRIER SCREEN.
2
LUBRICATION AND SCAVENGE OIL PUMP
WITH THE BARRIER SCREEN.
A-A
116081
Oil Pressure Adjustment
Figure 505
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TEST NO. 5 - MAIN GEARBOX REPLACEMENT TEST
__________________________________________
j)
k)
Tighten the jamnut to 60-80 pound-inches (6.779-9.039
newton-meters).
Install the dust cover.
1
_
Tighten the dust cover with your fingers.
WARNING:
_______
OBEY THE INSTRUCTIONS IN AMM 78-31-00 WHEN YOU
CLOSE THE THRUST REVERSERS. IF YOU DO NOT OBEY
THE INSTRUCTIONS, INJURY TO PERSONS OR DAMAGE TO
EQUIPMENT COULD OCCUR.
l)
m)
n)
o)
(h)
Close the thrust reversers (AMM 78-31-00/201).
Close the core cowl panels (AMM 71-11-06/201).
Close the fan cowl panels (AMM 71-11-04/201).
Do the activation procedure for the thrust reversers
(AMM 78-31-00/201).
p) Use the Power Plant Operation (Normal) procedure to do
the engine shutdown (AMM 71-00-00/201).
q) Examine the oil pump pressure again until the manifold
oil pressure is in the pressure limits.
Examine the vibration of the engine.
1) Push the PERF/APU switch on the right sidewall panel P61 to
monitor the N1 and N2 engine vibration.
2) Slowly move the thrust lever forward at a constant rate.
a) Increase the speed of the engine from idle to takeoff
power in 90-120 seconds.
NOTE:
____
b)
c)
You must keep the acceleration at a sufficiently
slow rate to find a high vibration level.
During the acceleration, look at the engine VIB
indication for N1 and N2 on the bottom EICAS display.
During the temporary operation, N1 and N2 engine
vibration must have one or more high vibration
conditions at some speeds between idle and takeoff.
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TEST NO. 5 - MAIN GEARBOX REPLACEMENT TEST
__________________________________________
d)
(i)
(j)
Make a record of %N1 and %N2 RPM indications at which
the N1 and N2 high vibration levels occur.
3) Slowly move the thrust lever rearward to the RPM at which
each high level of vibration occurred.
a) Permit the engine to become stable for 30 seconds at
the specified RPM at which the high vibration level
occurred.
b) Make a record of the average N1 and N2 vibrations and
the related %N1 or %N2 speeds.
4) The average of the vibration indication is less than the
permitted levels 30 seconds after the engine becomes stable
(Fig. 505A).
a) If the average of the vibration is more than the
permitted levels, repair as it is necessary.
b) If a repair was necessary, do the test again.
5) Move the thrust lever rearward to decrease the engine to
operate at minimum power.
Look at the ECS/MSG and EPCS pages on the bottom EICAS display
for messages.
1) If messages show, do the corrections which are necessary
for the applicable message.
Do the IDG disconnect check.
CAUTION:
_______
DO NOT OPERATE THE GEN DRIVE DISC SWITCH FOR MORE
THAN THREE SECONDS. PERMIT A MINIMUM OF 60 SECONDS
BETWEEN OPERATIONS.
CAUTION:
_______
DO NOT OPERATE THE GEN DRIVE DISC SWITCH UNLESS THE
ENGINE IS AT OR ABOVE IDLE N2 RPM. DO NOT DISCONNECT
THE IDG WITH THE ENGINE BELOW IDLE. THIS CAN CAUSE
DAMAGE TO THE DISCONNECT DOG TEETH.
1)
While you operate the engine at the minimum idle N2 RPM or
more, push the applicable L(R) GEN DRIVE DISC switch on the
panel P5.
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N1 INCHES PER SECOND (IPS)
1.75
1.0
.87
N1 VIBRATION INDICATION (AVM UNITS)
N1 ACCEPTANCE LEVEL
2.0
1.0
10
20
30
40
50
60
70
80
90
100
80
85
90
95
100
%N1
N2 INCHES PER SECOND (IPS)
1.75
1.0
.87
N2 VIBRATION INDICATION (AVM UNITS)
N2 ACCEPTANCE LEVEL
2.0
1.0
50
55
60
65
70
75
%N2
NOTE: THE CONVERSION FORMULA FROM AVM UNITS TO IPS IS :
____
3.1416 (277.885)(AVM UNITS)
IPS : ___________________________
1000
188211
N1 and N2 Vibration Acceptance Levels
Figure 505A
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TEST NO. 5 - MAIN GEARBOX REPLACEMENT TEST
__________________________________________
2)
3)
4)
Make sure the applicable L(R) DRIVE light and L(R) GEN CONT
OFF lights go on to make sure the IDG is disconnected.
Use the Power Plant Operation (Normal) procedure to do the
engine shutdown (AMM 71-00-00/201).
Open the fan cowl panels (AMM 71-11-04/201).
WARNING:
_______
5)
6)
Do this procedure: Thrust Reverser Deactivation for Ground
Maintenance (AMM 78-31-00/201).
Open the core cowl panels (AMM 71-11-06/201).
WARNING:
_______
7)
8)
9)
OBEY THE INSTRUCTIONS IN AMM 78-31-00 WHEN YOU OPEN
THE THRUST REVERSERS. IF YOU DO NOT OBEY THE
INSTRUCTIONS, INJURY TO PERSONS OR DAMAGE TO
EQUIPMENT COULD OCCUR.
Open the thrust reversers (AMM 78-31-00/201).
Make sure the N2 rotor is stopped.
Pull out the IDG disconnect reset ring until you feel the
solenoid pin go into position (Fig. 502).
WARNING:
_______
10)
11)
12)
13)
DO THE THRUST REVERSER DEACTIVATION PROCEDURE TO
PREVENT THE OPERATION OF THE THRUST REVERSER.
ACCIDENTAL OPERATION OF THE THRUST REVERSER CAN CAUSE
INJURY TO PERSONS OR DAMAGE TO EQUIPMENT.
OBEY THE INSTRUCTIONS IN AMM 78-31-00 WHEN YOU CLOSE
THE THRUST REVERSERS. IF YOU DO NOT OBEY THE
INSTRUCTIONS, INJURY TO PERSONS OR DAMAGE TO
EQUIPMENT COULD OCCUR.
Close the thrust reversers (AMM 78-31-00/201).
Close the core cowl panels (AMM 71-11-06/201).
Close the fan cowl panels (AMM 71-11-04/201).
Do the activation procedure for the thrust reversers
(AMM 78-31-00/201).
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TEST NO. 6 - 14TH-STAGE BLEED SYSTEM TEST
_________________________________________
TASK 71-00-00-715-001-P00
11. Test
_________________________________________
No. 6 - 14th-Stage Bleed System Test
A. General
ú
(1) This test examines the operation of the 14th-stage bleed system and
ú
uses reverse thrust to make sure the 14th-stage bleed valve operates
ú
correctly. It is only necessary to operate the engine at idle speed
ú
in this procedure.
(2) If the 14th-stage bleed system fails to open the valve, the
stability of the engine can decrease. If the 14th-stage bleed
system fails to close the valve, the EGT, the fuel consumption, and
the engine noise levels will increase.
B. References
(1) AMM 31-41-00/201, EICAS
(2) AMM 71-00-00/201, Power Plant - General
(3) AMM 71-11-04/201, Fan Cowl Panels
(4) AMM 71-11-06/201, Core Cowl Panels
(5) AMM 78-31-00/201, Thrust Reverser System
C. Access
(1) Location Zones
211/212
Flight Compartment
411/421
Engine
ú
ú
D.
Do the 14th-Stage Bleed System Test.
S 865-388-P00
WARNING:
_______
(1)
USE AMM 71-00-00/201 TO OPERATE THE POWER PLANT. IF YOU DO NOT
USE THIS PROCEDURE, YOU CAN CAUSE DAMAGE TO EQUIPMENT OR INJURY
TO PERSONS.
Use the Power Plant Operation (Normal) procedure to start the engine
(AMM 71-00-00/201).
(a) Permit the engine to become stable at idle for five minutes.
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TEST NO. 6 - 14TH-STAGE BLEED SYSTEM TEST
_________________________________________
(b)
(2)
Make sure there are satisfactory engine indications.
S 215-389-P00
Look for the EICAS message L(R) REV ISLN VAL on the top EICAS
display and on the MAINTENANCE display.
NOTE:
____
(3)
(4)
(5)
(6)
This procedure will make the L(R) REV ISLN VAL message show
on EICAS. If the message is not shown at this time, you can
erase the message when you complete this test.
S 865-390-P00
For the left engine, open this circuit breaker on the overhead
circuit breaker panel, P11, and attach a DO-NOT-CLOSE tag:
(a) 11D12, L ENG THRUST REVERSER CONT/SCAV PRESS
S 865-391-P00
For the right engine, open this circuit breaker on the overhead
circuit breaker panel, P11, and attach a DO-NOT-CLOSE tag:
(a) 11B30, R ENG THRUST REVERSER CONT/SCAV PRESS
S 975-392-P00
Make a record of the EGT from the EICAS display.
S 715-393-P00
Move the reverse thrust lever up and aft to the reverse idle
position.
NOTE:
____
(a)
The EEC will open the 14th-stage bleed valve when the
engine is at reverse thrust.
Make sure the EGT is 25°C to 50°C more than the EGT at the
forward idle.
NOTE:
____
If the EGT does not increase, the 14th-stage bleed
system does not operate correctly.
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TEST NO. 6 - 14TH-STAGE BLEED SYSTEM TEST
_________________________________________
(7)
(8)
(9)
S 715-394-P00
Move the reverse thrust lever forward and down to the forward idle
position.
(a) After the engine becomes stable, make sure the EGT decreases to
the EGT from the record +/- 4°C.
S 865-455-P00
For the left engine, remove the DO-NOT-CLOSE tag and close this
circuit breaker on the overhead circuit breaker panel, P11:
(a) 11D12, L ENG THRUST REVERSER CONT/SCAV PRESS
S 865-456-P00
For the right engine, remove the DO-NOT-CLOSE tag and close this
circuit breaker on the overhead circuit breaker panel, P11:
(a) 11B30, R ENG THRUST REVERSER CONT/SCAV PRESS
S 865-395-P00
(10) Use the Power Plant Operation (Normal) procedure to do the engine
shutdown (AMM 71-00-00/201).
S 865-396-P00
(11) If the EICAS message L(R) ISLN VAL was not shown before this test,
do the maintenance message erase procedure (AMM 31-41-00/201).
S 015-397-P00
(12) Open the fan cowl panels (AMM 71-11-04/201).
S 045-399-P00
WARNING:
_______
DO THE THRUST REVERSER DEACTIVATION PROCEDURE TO PREVENT THE
OPERATION OF THE THRUST REVERSER. THE ACCIDENTAL OPERATION OF
THE THRUST REVERSER CAN CAUSE INJURIES TO PERSONS OR DAMAGE TO
EQUIPMENT.
(13) Do this procedure: Thrust Reverser Deactivation for Ground
Maintenance (AMM 78-31-00/201).
S 015-400-P00
(14) Open the core cowl panels (AMM 71-11-06/201).
S 015-401-P00
WARNING:
_______
OBEY THE INSTRUCTIONS IN AMM 78-31-00 WHEN YOU OPEN THE THRUST
REVERSERS. IF YOU DO NOT OBEY THE INSTRUCTIONS, INJURIES TO
PERSONS OR DAMAGE TO EQUIPMENT CAN OCCUR.
(15) Open the thrust reversers (AMM 78-31-00/201).
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TEST NO. 6 - 14TH-STAGE BLEED SYSTEM TEST
_________________________________________
S 795-402-P00
(16) Examine the engine for leaks.
(a) If it is necessary, repair the leaks.
S 415-403-P00
WARNING:
_______
OBEY THE INSTRUCTIONS IN AMM 78-31-00 WHEN YOU CLOSE THE THRUST
REVERSERS. IF YOU DO NOT OBEY THE INSTRUCTIONS, INJURIES TO
PERSONS OR DAMAGE TO EQUIPMENT CAN OCCUR.
(17) Close the thrust reversers (AMM 78-31-00/201).
S 415-404-P00
(18) Close the core cowl panels (AMM 71-11-06/201).
S 415-405-P00
(19) Close the fan cowl panels (AMM 71-11-04/201).
S 445-406-P00
(20) Do the activation procedure for the thrust reversers
(AMM 78-31-00/201).
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TEST NO. 7 - ELECTRONIC ENGINE CONTROL (EEC) STATIC TEST
________________________________________________________
TASK 71-00-00-715-124-P00
12. Test
______________________________________________________
No. 7 Electronic Engine Control (EEC) Static Test
A. General
(1) This procedure makes sure of the correct operation of the EEC, and
the interface between the EEC and components, when the engine is not
in operation. The EEC does the internal self-tests, and gives test
failure data to the EPCS page on the EICAS. The EEC also compares
output-to-feedback signals to make sure of the correct interface
operation.
B. References
(1) AMM 24-22-00/201, Electrical Power - Control
C. Access
(1) Location Zones
211/212
Flight Compartment
D.
Do the EEC Static Test
(1)
(2)
(3)
(4)
(5)
S 865-125-P00
Supply electrical power (AMM 24-22-00/201).
S 865-126-P00
Supply power to the EEC.
(a) For the left engine, make sure this circuit breaker on the
overhead circuit breaker panel, P11, is closed:
1) 11L4, LEFT ENGINE ELECTRONIC ENGINE CONTROL ALTN PWR
(b) For the right engine, make sure this circuit breaker on the
overhead circuit breaker panel, P11, is closed:
1) 11L31, RIGHT ENGINE ELECTRONIC ENGINE CONTROL ALTN PWR
(c) Put the EEC MAINT POWER switch on the P61 panel in the ALTN
position.
S 215-127-P00
Look at the EPCS page on the bottom EICAS display for EPCS messages.
(a) If messages show, do the corrections which are necessary for
the applicable message.
S 865-129-P00
Put the EEC MAINT POWER switch on the P61 panel in the NORM
position.
S 865-130-P00
Remove electrical power (AMM 24-22-00/201).
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TEST NO. 8 - VIBRATION SURVEY
_____________________________
TASK 71-00-00-735-131-P00
13. Test
_____________________________
No. 8 - Vibration Survey
A. General
(1) Use this test to make sure the engine vibration stays in the
permitted levels after you replace or repair some components/module.
B. References
(1) AMM 71-00-00/201, Power Plant - General
C. Access
(1) Location Zones
211/212
Flight Compartment
D.
Do the Vibration Survey.
(1)
S 865-132-P00
Make sure this circuit breaker on the overhead circuit breaker
panel, P11, is closed:
(a) 11K2, VIB MONITOR L/R
S 865-133-P00
WARNING:
_______
(2)
USE AMM 71-00-00/201 TO OPERATE THE POWER PLANT. IF YOU DO NOT
USE THIS PROCEDURE, YOU CAN CAUSE DAMAGE TO EQUIPMENT OR INJURY
TO PERSONS.
Use the Power Plant Operation (Normal) procedure to start the engine
(AMM 71-00-00/201).
(a) Permit the engine to become stable at idle N2 RPM for five
minutes.
(b) Make sure there are satisfactory engine indications.
(3)
S 865-134-P00
Slowly move the thrust lever forward and increase the speed of the
engine to 1.33 EPR for a minimum of three minutes.
(4)
S 865-135-P00
Move the thrust lever rearward and put the engine back to idle N2
RPM for a minimum of 6 minutes.
NOTE:
____
(5)
These steps will let the engine temperature become stable so
you can do the vibration survey. Do not do the vibration
survey on an engine that does not have a stable temperature.
S 865-136-P00
Push the PERF/APU switch on the right sidewall panel, P61, to
monitor the N1 and N2 engine vibration.
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TEST NO. 8 - VIBRATION SURVEY
_____________________________
(6)
(7)
S 865-138-P00
Slowly move the thrust lever forward at a constant rate.
S 865-139-P00
Increase the speed of the engine from idle to takeoff power in
90-120 seconds.
NOTE:
____
(a)
(b)
(8)
You must keep the acceleration at a sufficiently slow rate to
find a high vibration level.
During the acceleration, look at the engine VIB indication for
N1 and N2 on the bottom EICAS display.
During the temporary operation, N1 and N2 engine vibration must
have one or more of the highest vibration conditions at some
speeds between idle and takeoff.
1) Make a record of %N1 and %N2 indications at which the
highest N1 and N2 vibration levels occur.
S 865-140-P00
Move the thrust lever rearward to the speed at which each high
vibration level occurred.
(a) Permit the engine to become stable for 30 seconds at the
specified speed at which the highest vibration level occurred.
(b) Make a record of the average N1 and N2 vibrations and the
related %N1 or %N2 speeds.
1) AIRPLANES WITH AVM P/N S362A001-9 AND SUBSEQUENT;
To get imbalance data, use this alternate acceleration
procedure with the takeoff power speed for the current
conditions:
CAUTION:
_______
2)
DO NOT EXCEED THE TAKEOFF POWER SPEED FOR THE CURRENT
CONDITIONS, ENGINE DAMAGE CAN OCCUR.
Pause for 30 seconds at each of the ideal dwell fan speeds
|1% N1. Do not use fan speeds which exceeds the takeoff
power speed.
NOTE:
____
If conditions do no allow the engine to run 30
seconds at the ideal speed, then use a lower speed
in the speed range. If conditions do not allow the
engine to run 30 seconds in the speed range, then
skip that particular speed range.
NOTE:
____
The AVM gathers imbalance data when the engine
runs at a constant speed within test ranges during
ground runs and flights.
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TEST NO. 8 - VIBRATION SURVEY
_____________________________
~¼¼¼¼¼¼¼ ¼¼¼¼¼¼¼¼¼¼¼¼¼¼ ¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼
¦ SPEED ¦ IDEAL DWELL ¦
¦
¦ RANGE ¦ SPEED (% N1) ¦ SPEED RANGE (% N1) ¦
»¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼«
¦
1
¦
94.0
¦
100.0 - 88.1
¦
¦
2
¦
86.5
¦
88.0 - 85.0
¦
¦
3
¦
83.0
¦
84.9 - 81.1
¦
¦
4
¦
78.0
¦
81.0 - 75.0
¦
¦
5
¦
72.5
¦
74.9 - 70.0
¦
¦
6
¦
65.0
¦
69.9 - 60.0
¦
²¼¼¼¼¼¼¼…¼¼¼¼¼¼¼¼¼¼¼¼¼¼…¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¹
3)
(c)
(9)
During the acceleration, monitor the applicable engine
vibration indications.
4) Record the N1% and the N2% where the maximum vibrations
occur (if more than one).
5) Let the engine become stable at the takeoff power speed for
a minimum of 15 seconds.
Operate the engine at stable idle N2 rpm for five minutes to
let the temperature decrease and become stable before the
engine is shutdown.
S 865-141-P00
Use the Power Plant Operation (Normal) procedure to do the engine
shutdown (AMM 71-00-00/201).
S 735-142-P00
(10) You must have an average of the vibration indication less than the
permitted level 30 seconds after the engine becomes stable
(Fig. 505A).
(a) If the average vibration indication is more than the permitted
level, do Test No. 18 - Low Pressure Rotor Trim Balance or Test
No. 18A Engine Trim Balance with the Universal Airborne
Vibration Monitor (AVM) (P/N S362A001-9).
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TEST NO. 8 - VIBRATION SURVEY
_____________________________
S 865-144-P00
(11) Put the airplane back to its initial condition.
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TEST NO. 9 - PERFORMANCE TEST
_____________________________
TASK 71-00-00-725-145-P00
14. Test
_____________________________
No. 9 - Performance Test
A. General
(1) Replacement of an engine module can cause an unsatisfactory effect
on these: The performance of the engine, the engine EGT margin, the
compressor surge margin, the rotor speeds, the turbine cooling, and
the bearing thrust load. This test is necessary as shown in the
Power Plant Test Reference Table to keep the engine performance and
safety.
(2) You can use the EICAS displays of EPR, %N1, %N2 and EGT for the
performance test if all systems operate correctly.
(3) This test is the only necessary engine check made to show engine
component defects. It is necessary to use accurate leak-free
instruments to measure the engine pressures.
(4) For the engine limits of operation, the procedures, the safety
precautions, and other related data refer to AMM 71-00-00/201.
(5) Samples are found at the end of this test (Fig. 516) to help when
you calculate the engine data.
B. Equipment
(1) Pressure Equipment - Performance Test, B71034
which has the equipment that follows:
(2) PT2.5 Gage - 0-60 psi |0.066% accuracy,
P/N 62A-2A-0060, Pennwalt Corp., Wallace &
Tiernan Div., 25 Main St., Belleville, NJ 07109
(3) PS3I Gage - 0-500 psi |0.1% accuracy,
P/N 62B-2A-0500, Pennwalt Corp.
(4) PS3.1 Gage - 0-500 psi |0.066% accuracy,
P/N 62A-2A-0500, Pennwalt Corp.
(5) Adapter - P/N 0103-4-4C, Parker Hannifin Corp.,
Hose Products Div., 30240 Lakeland Blvd.,
Wickliffe, Ohio, 44092
(6) Adapter - 1 is necessary, P/N 0103-4-5C,
Parker Hannifin Corp.
(7) Adapter - 2 are necessary, P/N 0503-6-4C,
Parker Hannifin Corp.
(8) Tee - P/N 033T-4-4C, Parker Hannifin Corp.
(9) Hose Identification Clamp - 7 are necessary,
P/N FSC, Parker Hannifin Corp.
(10) Hose - 2 are necessary, 12-foot length,
P/N 9090606-4-4-4C-144, Parker Hannifin Corp.
(PS 3.1)
(11) Hose - 2 are necessary, 120-foot length,
P/N 9090606-5-5-5C-1440, Parker Hannifin Corp.
(PT 2.5 and PS 3I)
(12) Hose - 1 is necessary, 120-foot length,
P/N 9090606-4-4-4C-1440, Parker Hannifin
Corp. (PS3.1)
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TEST NO. 9 - PERFORMANCE TEST
_____________________________
C.
D.
E.
F.
(13) Adapter - 1 is necessary, P/N 0103-2-5C,
Parker Hannifin Corp.
(14) Hygrometer - Sling Psychrometer with charts, or
the equivalent, commercially available
(15) Probe, PT2.5 - PWA 80678, Pratt & Whitney, East
Hartford, CT
Consumable Materials
(1) Petrolatum, White - PMC 9609
(2) Seal - MS9386-028
References
(1) AMM 24-22-00/201, Electrical Power - Control
(2) AMM 29-11-00/201, Main Hydraulic Systems
(3) AMM 36-00-00/201, Pneumatic - General
(4) AMM 49-11-00/201, Auxiliary Power Unit
(5) AMM 71-00-00/201, Power Plant - General
(6) AMM 71-01-02/201, Engine Trim (Trim Check Tables)
(7) AMM 71-11-04/201, Fan Cowl Panels
(8) AMM 71-11-06/201, Core Cowl Panels
(9) AMM 78-31-00/201, Thrust Reverser System
Access
(1) Location Zones
211/212
Flight Compartment
411/421
Engine
Prepare to Do a Test of the Engine Performance.
(1)
S 015-146-P00
Open the fan cowl panels (AMM 71-11-04/201).
S 045-147-P00
WARNING:
_______
(2)
(3)
DO THE THRUST REVERSER DEACTIVATION PROCEDURE TO PREVENT THE
OPERATION OF THE THRUST REVERSER. THE ACCIDENTAL OPERATION OF
THE THRUST REVERSER CAN CAUSE INJURY TO PERSONS OR DAMAGE TO
EQUIPMENT.
Do this procedure: Thrust Reverser Deactivation for Ground
Maintenance (AMM 78-31-00/201).
S 015-148-P00
Open the core cowl panels (AMM 71-11-06/201).
S 015-149-P00
WARNING:
_______
(4)
OBEY THE INSTRUCTIONS IN AMM 78-31-00 WHEN YOU OPEN THE THRUST
REVERSERS. IF YOU DO NOT OBEY THE INSTRUCTIONS, INJURY TO
PERSONS OR DAMAGE TO EQUIPMENT COULD OCCUR.
Open the thrust reversers (AMM 78-31-00/201).
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TEST NO. 9 - PERFORMANCE TEST
_____________________________
(5)
S 485-150-P00
Install the equipment to monitor the pressure (Fig. 506).
(a) Remove the PT2.5 plug.
(b) Loosen the oil pressure sense lines necessary to install the
PT2.5 probe.
(c) Install the PT2.5 probe.
1) Remove the used seals from the PT2.5 plug.
a) Discard the used seals.
2) Lubricate the new seals with petrolatum.
3) Install the seals on the PT2.5 plug.
(d) Remove the cap from PS3I port.
(e) Remove the plugs from the PS3.1 ports.
(f) Connect the 120-foot hoses to the PT2.5 probe and to the PS3I
ports.
(g) Connect the 12-foot hoses to the PS3.1 ports and to the Tee.
(h) Connect the 120-foot hose to the Tee.
1) Attach the hoses together as it is necessary to help close
the cowl easier.
(i) Connect the PT2.5, PS3I and PS3.1 gages.
(j) Put the PT2.5, PS3I and PS3.1 gages in the flight compartment.
S 415-151-P00
WARNING:
_______
OBEY THE INSTRUCTIONS IN AMM 78-31-00 WHEN YOU CLOSE THE THRUST
REVERSERS. IF YOU DO NOT OBEY THE INSTRUCTIONS, INJURY TO
PERSONS OR DAMAGE TO EQUIPMENT COULD OCCUR.
(6)
Close the thrust reversers (AMM 78-31-00/201).
(7)
S 415-152-P00
Close the core cowl panels (AMM 71-11-06/201).
(8)
S 415-153-P00
Close the fan cowl panels (AMM 71-11-04/201).
(9)
S 445-154-P00
Do the activation procedure for the thrust reversers
(AMM 78-31-00/201).
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PS3I
SEE A
PS3.1
ACTIVE CLEARANCE
CONTROL VALVE
(REF)
BOLT
OIL PRESSURE
SENSE LINES
PT2.5 PLUG
A
116087
PT2.5, PS3.1 and PS3I Test Port Locations
Figure 506
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TEST NO. 9 - PERFORMANCE TEST
_____________________________
S 975-377-P00
CAUTION:
_______
TO PREVENT ERRORS, DO NOT USE THE TOTAL AIR TEMPERATURE OF THE
AIRPLANE FOR THE AMBIENT AIR TEMPERATURE. MAKE SURE TO GET THE
LOCAL BAROMETRIC PRESSURE (NOT CORRECTED TO SEA LEVEL) FROM THE
CONTROL TOWER.
CAUTION:
_______
DO NOT USE A MERCURY THERMOMETER ON THE AIRPLANE. IF THE
THERMOMETER BREAKS, THE MERCURY CAN CAUSE DAMAGE TO THE
EQUIPMENT.
(10) Get these ambient weather conditions:
(a) Get the ambient temperature (outside air temperature, OAT) in
the shade at the airplane nose gear.
1) Make a record of the OAT.
(b) Get the true local barometric pressure.
1) Make a record of the true local barometric pressure.
(c) Get the specific humidity.
1) Make a record of the specific humidity.
S 865-359-P00
CAUTION:
_______
MAKE SURE THE LEFT AND RIGHT HYDRAULIC SYSTEMS ARE PRESSURIZED
DURING THE OPERATION OF THE TEST. IF YOU DO NOT KEEP THE
HYDRAULIC SYSTEM PRESSURIZED, YOU POSSIBLY CANNOT CONTROL THE
AIRPLANE.
(11) Pressurize the left and right hydraulic systems (Ref 29-11-00).
(a) The engine can freeze when there is visible moisture and the
OAT is less than 46°F (8°C).
NOTE:
____
G.
Visible moisture is rain, snow, or fog (you can see 1
mile [1.6 kilometer] or less).
S 865-157-P00
(12) Supply electrical power, if it is not supplied (AMM 24-22-00/201).
Do a Test of the Engine Performance
S 865-158-P00
WARNING:
_______
(1)
USE AMM 71-00-00/201 TO OPERATE THE POWER PLANT. IF YOU DO NOT
USE THIS PROCEDURE, YOU CAN CAUSE DAMAGE TO EQUIPMENT OR INJURY
TO PERSONS.
Use the Power Plant Operation (Normal) procedure to start the engine
(AMM 71-00-00/201).
(a) Permit the engine to operate at minimum power for five minutes.
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TEST NO. 9 - PERFORMANCE TEST
_____________________________
(2)
(3)
S 215-159-P00
Monitor the vibration indications during the five minutes at the
stable idle and while you decrease and increase the engine speed.
S 215-160-P00
Make sure the indications of the operation are in the limits of the
operation (AMM 71-00-00/201).
(a) Make a record of the %N1, %N2, the ambient temperature, the oil
pressure and the oil temperature.
(b) Make sure the primary and secondary channel conditions are in
the limits of operation.
S 865-161-P00
WARNING:
_______
USE AMM 71-00-00/201 TO OPERATE THE POWER PLANT. IF YOU DO NOT
USE THIS PROCEDURE, YOU CAN CAUSE DAMAGE TO EQUIPMENT OR INJURY
TO PERSONS.
CAUTION:
_______
MAKE SURE TO START THE OTHER ENGINE OR THE APU. TO PREPARE FOR
AN EMERGENCY ENGINE SHUTDOWN, YOU MUST OPERATE THE OTHER ENGINE
OR THE APU FOR PNEUMATIC POWER. IF THE PNEUMATIC POWER IS NOT
AVAILABLE DURING AN EMERGENCY ENGINE SHUTDOWN, YOU CAN CAUSE
DAMAGE TO THE ENGINE.
(4)
(5)
(6)
Use the Power Plant Operation (Normal) procedure to start the other
engine (AMM 71-00-00/201) or do the APU Operation
(AMM 49-11-00/201).
S 865-162-P00
Remove ground pneumatic power, if it is supplied (AMM 36-00-00/201).
S 865-163-P00
Make sure these systems are in the off position for the engine which
gets this test:
NOTE:
____
(a)
(b)
(c)
(7)
These systems must be off during the test because the test
limits are for no load and no bleed air conditions.
Engine bleed air.
Engine and wing anti-ice unless it is necessary.
Integrated Drive Generator (IDG).
S 865-164-P00
If you do the test in frozen conditions, supply air to the nacelle
anti-ice system for the engine of this test as follows:
(a) If the two engines are in operation, put the valves that follow
in the specified position:
1) PRSOV for the engine which the test is done on - closed
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TEST NO. 9 - PERFORMANCE TEST
_____________________________
(b)
2) PRSOV for the other engine - open
3) Isolation Valve - open
4) Nacelle anti-ice valves for the two engines
If the APU is in operation, put the valves that
specified position:
1) PRSOV for the engine which the test is done
2) APU Valve - open
3) Isolation Valve - open, if the test is done
engine - closed, if the test is done on the
4) Nacelle anti-ice valve - open
- open
follow in the
on - closed
on the right
left engine
S 735-165-P00
CAUTION:
_______
MONITOR THE PRESSURE RATIO OF THE TURBINE COOLING AIR WHEN THE
ENGINE IS OPERATED ABOVE IDLE SPEED. THIS IS NECESSARY TO MAKE
SURE THERE IS SUFFICIENT COOLING AIR SUPPLIED TO THE TURBINE.
IF THE PRESSURE RATIO IS MORE THAN THE SPECIFIED LIMITS, THIS
CAN CAUSE UNSATISFACTORY PERFORMANCE OF THE ENGINE. IF THE
PRESSURE RATIO IS LESS THAN THE SPECIFIED LIMITS, THIS CAN
CAUSE DAMAGE TO THE ENGINE.
(8)
Do Test No. 8 at this time if it is necessary.
(9)
S 865-166-P00
Move the thrust lever forward to get 1.31 EPR.
(a) Permit the engine to become stable for five minutes.
S 865-167-P00
(10) Push the EVENT RECORD switch on the pilot's display select panel on
the P9 panel to make a record of the engine conditions.
(a) Make a record of the PT2.5, PS3I and PS3.1.
S 225-168-P00
(11) Make sure the corrected pressure ratio of the turbine cooling air
you calculated is in the specified limits.
(a) Look at the records of the engine which the test is done on for
the part numbers of the components that follow:
1) 1st-stage turbine blade
2) Tangential On Board Injection (TOBI) duct
(b) Use the records of the engine to find the applicable Turbine
Cooling Air Check Curve (Fig. 507).
(c) Calculate the corrected turbine cooling air pressure ratio:
(d)
= PS3I + PAMB
----------PS3.1 + PAMB
Make a graph of corrected pressure ratio of the turbine cooling
air and the monitored N2 (RPM) on the Turbine Cooling Air Check
Curve.
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TEST NO. 9 - PERFORMANCE TEST
_____________________________
(e)
Make sure the point is in the limits.
NOTE:
____
N2 (RPM) = % N2 X 12250 RPM.
S 225-169-P00
(12) Make sure the stroke of the stator vane actuator (SVA) is in the
limits.
(a) Use the applicable trim table section (AMM 71-01-02/201) to
find the takeoff power (EPR units) for the ambient temperature
and true barometric pressure.
NOTE:
____
(b)
(c)
(d)
(e)
(f)
If you have not operated the engine in less than 30
minutes, you must examine the weather conditions at
least each 30 minutes. Use the ambient temperature and
true local barometric pressure at the time of the test.
Push the EPCS DISPLAY SELECT switch on the P61 panel.
Move the thrust lever to the full forward position.
1) Permit the engine to become stable.
2) Make sure you get the takeoff EPR.
Make a record of the %N1, SVA, N2C and EGT.
Put the thrust lever back to the idle position.
Make sure the SVA agrees with the Stator Vane Actuator Schedule
Check Data (Fig. 508).
S 865-170-P00
(13) Do the acceleration/deceleration checks as follows:
(a) Use the applicable trim check table (AMM 71-01-02/201) to find
the targets that follow at the local ambient conditions:
1) 95% TAKEOFF THRUST (EPR)
2) 90% THRUST CHANGE DECEL (EPR)
3) APP IDLE (%N2)
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0.820
0.800
0.780
MAXIMUM
____________
PS3I
+ PAMB
PS3.1 + PAMB
0.760
0.740
0.720
0.700
MINIMUM
0.680
0.660
0.640
0.620
0.600
7500
(61.2)
8000
(65.3)
8500
(69.4)
9000
(73.5)
9500
(77.6)
10000
(81.6)
10500
(85.7)
11000
(89.8)
11500
(93.9)
12000
(98.0)
N2 MONITORED - RPM
(%N2)
CPE CURVE 2313
NOTE:
____
THIS CURVE APPLIES TO ENGINES WITH ALL 1ST-STAGE
TURBINE BLADES P/N 1B4921 AND 1B1271 AND THE
TANGENTIAL ON BOARD INJECTION (T0BI) DUCTS
P/N 1B2571,1B3290,1B3568,1B3569,1B4464, OR 1B5206.
SEE PW SB 72-259 FOR THE SPECIFIED INTERCHANGEABLE
DATA AS RELATED TO THE 1ST-STAGE TURBINE BLADES,
TOBI, AND OTHER PARTS OR CONDITIONS.
L-92967
1285
871405
Turbine Cooling Air Check Curve
Figure 507 (Sheet 1)
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0.820
0.800
0.780
MAXIMUM
____________
PS3I
+ PAMB
PS3.1 + PAMB
0.760
0.740
0.720
0.700
MINIMUM
0.680
0.660
0.640
0.620
0.600
7500
(61.2)
8000
(65.3)
8500
(69.4)
9000
(73.5)
9500
(77.6)
10000
(81.6)
10500
(85.7)
11000
(89.8)
11500
(93.9)
12000
(98.0)
N2 MONITORED - RPM
(%N2)
CPE CURVE 2313
L-92967
1285
871420
Turbine Cooling Air Check Curve
Figure 507 (Sheet 2)
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STATOR VANE ACTUATOR SCHEDULE CHECK
EPCS %N2C
EPCS SVA STROKE
MIN
MAX
96.0
2.22
2.27
96.2
2.23
2.28
96.4
2.24
2.29
96.6
2.25
2.30
96.8
2.26
2.31
97.0
2.27
2.32
97.2
2.28
2.33
97.4
2.29
2.34
97.6
2.30
2.35
97.8
2.31
2.36
98.0
2.32
2.37
98.2
2.33
2.38
98.4
2.34
2.39
98.6
2.35
2.40
98.8
2.36
2.41
99.0
2.37
2.42
99.2
2.38
2.43
99.4
2.39
2.44
99.6
2.40
2.45
99.8
2.41
2.46
100.0
2.42
2.47
100.2
2.43
2.48
100.4
2.44
2.49
100.6
2.45
2.50
100.8
2.46
2.51
101.0
2.47
2.52
700120
Stator Vane Actuator Schedule Check Data
Figure 508
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TEST NO. 9 - PERFORMANCE TEST
_____________________________
(b)
(c)
(d)
(e)
(f)
(g)
(h)
4) MIN IDLE (%N2)
Make sure the engine becomes stable at idle for two minutes.
Make sure the white box is around the PRI on the EICAS EPCS
page.
Pull the THRUST REF SET switch on the forward electronics
panel, P9.
Set the REF EPR target bug on the EICAS to 95% TAKEOFF THRUST
(EPR) target.
1) Do not push in the THRUST REF SET switch.
To prevent the activation of probe heaters, open these circuit
breakers that follow:
1) Open these circuit breakers on the main power distribution
panel, P6, and attach DO-NOT-CLOSE tags:
a) 6L15, PITOT HEAT CAPT MAIN
b) 6L16, PITOT HEAT L AUX
c) 6L17, L AOA HEAT
d) 6L21, PITOT HEAT R AUX
e) 6L22, PITOT HEAT F/O MAIN
f) 6L23, R AOA HEAT
g) 6L24, TAT PROBE HEAT
2) Open these circuit breakers on the right miscellaneous
electrical equipment panel, P37, and attach DO-NOT-CLOSE
tags:
a) 37F4, HEATER F/O AUX HI
b) 37F7, HEATER DRAIN MST AIR
3) Open this circuit breaker on the miscellaneous equipment
panel, P70, and attach DO-NOT-CLOSE tag:
a) 70A6, CAPT AUX HTR HI
Push the PERF/APU DISPLAY SELECT switch on the P61 panel.
Set the approach idle as follows:
1) For the left engine, open these circuit breakers on the
overhead circuit breaker panel, P11, in sequence and attach
DO-NOT-CLOSE tags:
a) 11C14, FSEU 2 PWR
b) 11S15, AIR/GND SYS 1
c) 11C30, LANDING GEAR POS SYS 1
2) For the right engine, open these circuit breakers on the
overhead circuit breaker panel, P11, in sequence and attach
DO-NOT-CLOSE tags:
a) 11G21, FSEU 3 PWR
b) 11S19, AIR/GND SYS 2
c) 11S23, LANDING GEAR POS SYS 2
d) ILF 501 POST-SB 78-28 AND ILF 502-999;
11C19, LANDING GEAR POS SYS 2 ALTN
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TEST NO. 9 - PERFORMANCE TEST
_____________________________
3)
(i)
Make sure the idle speed increases to |0.5% or less of the
APR IDLE (%N2) target.
a) Permit the engine to become stable for 60 seconds.
Quickly increase the speed of the engine and measure the time
as follows:
1) In less than one second, move the applicable thrust lever
to the full forward position.
CAUTION:
_______
YOU MUST RETARD THE POWER LEVERS BEFORE THE EGT IS
MORE THAN THE MAXIMUM EGT. THE EEC ONLY HAS A LIMIT
ON THE EPR AND THE ENGINE SPEED. THE EEC DOES NOT
PREVENT THE OVERTEMPERATURE AND DOES NOT HAVE A LIMIT
FOR THE TEMPERATURE (EGT). THE DETERIORATION OF THE
ENGINE OR BLEED SYSTEM CAN CAUSE AN EGT WHICH IS MORE
THAN THE MAXIMUM EGT BEFORE THE EPR (OR ROTOR SPEED)
DECREASES. IF YOU DO NOT RETARD THE POWER LEVERS,
YOU CAN CAUSE DAMAGE TO THE ENGINE.
2)
(j)
(k)
Measure the time of acceleration from approach idle to the
95% TAKEOFF THRUST (EPR) target.
3) Make sure the acceleration time is 5.8 seconds or less.
4) Make sure the engine does not go above the TAKEOFF (EPR)
target.
5) Permit the engine to become stable for 15-20 seconds.
Set the minimum idle as follows:
1) For the left engine, remove the DO-NOT-CLOSE tags and close
these circuit breakers on the P11 panel in sequence:
a) 11S15, AIR/GND SYS 1
b) 11C14, FSEU 2 PWR
c) 11C30, LANDING GEAR POS SYS 1
2) For the right engine, remove the DO-NOT-CLOSE tags and
close these circuit breakers on the P11 panel in sequence:
a) 11S17, AIR/GND SYS 2
b) 11G21, FSEU 3 PWR
c) 11S23, LANDING GEAR POS SYS 2
d) ILF 501 POST-SB 78-28 AND ILF 502-999;
11C19, LANDING GEAR POS SYS 2 ALTN
Quickly move the thrust lever rearward to decrease the speed of
the engine and measure the time as follows:
1) In less than one second, move the applicable thrust lever
to the idle position.
2) Measure the time of deceleration from TAKEOFF (EPR) to the
90% THRUST CHANGE DECEL (EPR) targets.
a) Make sure the time of deceleration is 7.1 seconds or
less.
3) Make sure the engine becomes stable at the MIN IDLE target.
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TEST NO. 9 - PERFORMANCE TEST
_____________________________
(l)
(m)
(n)
(o)
Close the circuit breakers for the probe heaters.
1) Remove the DO-NOT-CLOSE tags and close these circuit
breakers on the P6 panel:
a) 6L15, PITOT HEAT CAPT MAIN
b) 6L16, PITOT HEAT L AUX
c) 6L17, L AOA HEAT
d) 6L21, PITOT HEAT R AUX
e) 6L22, PITOT HEAT F/O MAIN
f) 6L23, R AOA HEAT
g) 6L24, TAT PROBE HEAT
2) Remove the DO-NOT-CLOSE tags and close these circuit
breakers on the P37 panel:
a) 37F4, HEATER F/O AUX HI
b) 37F7, HEATERS DRAIN MST AIR
3) Remove the DO-NOT-CLOSE tag and close this circuit breaker
on the P70 panel:
a) 70A6, CAPT AUX HTR HI
Push in the THRUST REF SET switch on the P9 panel.
Look at the EPCS page on the bottom EICAS display for EPCS
messages.
1) If EPCS messages show, do the corrections which are
necessary for the applicable EPCS message.
Operate the engine at idle five minutes to let the temperature
decrease and become stable before the engine shutdown.
S 865-171-P00
(14) Use the Power Plant Operation (Normal) procedure to do the engine
shutdown (AMM 71-00-00/201).
S 865-172-P00
(15) Push the PERF/APU switch on the P61 panel.
S 865-173-P00
(16) Push the MAN-EVENT READ switch on the P61 panel.
(a) Make a record of the full set of engine indications from the
PERF/APU page on the EICAS.
S 865-174-P00
(17) Push the EPCS DISPLAY SELECT switch on the P61 panel.
S 865-175-P00
(18) Push the MAN-EVENT READ switch on the P61 panel.
(a) Make a record of the engine conditions from the EPCS page on
the bottom EICAS display.
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TEST NO. 9 - PERFORMANCE TEST
_____________________________
S 225-176-P00
(19) Correct the records when the engine became stable with the steps
that follow:
(a) Calculate the pressure ratio as follows:
1) Low pressure compressor pressure ratio
=
PT2.5 + PAMB
-----------------0.06
PAMB X (æT2)
+
Delta PT2.5
-----------------0.06
PAMB + (æT2)
where,
æT2 = TT2°C + 273.16
-------------288.16
Delta PT 2.5
-----------------0.06
PAMB X (æT2)
2)
is found from Fig. 514
sheet 3 and applied only
when %N2 is less than
89% (10900 rpm).
Overall compressor pressure ratio
=
PS3.1 + PAMB
-----------PAMB
where,
Delta PS3.1
----------PAMB
+
Delta PS3.1
----------PAMB
is found from Fig. 514 sheet 1
and applied only when %N2
is less than 89% (10900 rpm).
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TEST NO. 9 - PERFORMANCE TEST
_____________________________
S 975-360-P00
(20) High pressure compressor ratio
= corrected overall compressor pressure ratio
-----------------------------------------------corrected low pressure compressor pressure ratio
(a) Calculate the corrected N1 (rpm):
CN1 =
N1(rpm)
----------≥æT2 X KHN1
+
Delta N1
----------≥æT2 X KHN1
where,
N1(rpm) = %N1 X 4550 rpm
æT2 = TT2°C + 273.16
-------------288.16
KHN1 is found from Fig. 515
Delta N1
----------≥æT2 x KHN1
(b)
is found from Fig. 514 sheet 4
and applied only when %N2
is less than 89% (10900 rpm).
Calculate the corrected EGT (°C):
= EGT + 273.26
- 273.16 + Delta T4.9
-------------------------------------0.955
0.955
(æT2)
X KHT4.9
(æT2)
X KHT4.9
where,
æT2 = TT2°C + 273.16
-------------288.16
KHT4.9 is found from Fig. 515
Delta T4.9
-------------------0.955
(≥æT2)
X KHT4.9
is found from Fig. 514
sheet 2 and applied
only when %N2 is less than 89%
(10900 rpm)
S 225-177-P00
(21) Make a graph of the data as follows:
(a) Make a graph of the corrected N2 (rpm) and the monitored EPR on
the N2 Rotor Speed Limit Curve (Fig. 509).
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TEST NO. 9 - PERFORMANCE TEST
_____________________________
(b)
(c)
(d)
(e)
Make a graph of the corrected N1 (rpm) and the monitored EPR on
the N1 Rotor Speed Limit Curve (Fig. 510).
Make a graph of the corrected EGT and the monitored EPR on the
Corrected EGT Limit Curve (Fig. 511).
Make a graph of the pressure ratio for the low pressure
compressor and the EPR on the LPC Limit Curve (Fig. 512).
Make a graph of the pressure ratio for the high pressure
compressor and the EPR on the HPC Limit Curve (Fig. 513).
S 225-178-P00
(22) Make sure the points on the graph on the applicable charts are
satisfactory with the steps that follow:
(a) On the MAXIMUM and MINIMUM limit curves, make sure the points
on the graph are in the limits.
(b) On the charts with only the MAXIMUM limit curves, make sure the
points are not above the maximum limits.
S 015-179-P00
(23) Open the fan cowl panels (AMM 71-11-04/201).
S 045-180-P00
WARNING:
_______
DO THE THRUST REVERSER DEACTIVATION PROCEDURE TO PREVENT THE
OPERATION OF THE THRUST REVERSER. THE ACCIDENTAL OPERATION OF
THE THRUST REVERSER CAN CAUSE INJURY TO PERSONS OR DAMAGE TO
EQUIPMENT.
(24) Do this procedure: Thrust Reverser Deactivation for Ground
Maintenance (AMM 78-31-00/201).
S 015-181-P00
(25) Open the core cowl panels (AMM 71-11-06/201).
S 015-182-P00
WARNING:
_______
OBEY THE INSTRUCTIONS IN AMM 78-31-00 WHEN YOU OPEN THE THRUST
REVERSERS. IF YOU DO NOT OBEY THE INSTRUCTIONS, INJURY TO
PERSONS OR DAMAGE TO EQUIPMENT COULD OCCUR.
(26) Open the thrust reversers (AMM 78-31-00/201).
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11800
11700
11600
MAXIMUM
CORRECTED N2 - RPM (CN2)
11500
11400
11300
11200
11100
11000
1.30
1.32
1.34
1.36
1.38
1.40
1.42
1.44
EPR
L-92000
871430
N2 Rotor Speed Limit Curve
Figure 509 (Sheet 1)
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11600
11300
11400
11500
CORRECTED N2 - RPM
11700
11800
11900
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1.30
1.34
1.38
1.42
1.46
1.50
1.54
EPR
CPE CURVE NO. 2525-2
L-93744
871434
N2 Rotor Speed Limit Curve
Figure 509 (Sheet 2)
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4150
4100
4050
CORRECTED N1 - RPM (CN1)
4000
MAXIMUM
3950
3900
3850
3800
3750
3700
1.30
1.32
1.34
1.36
1.38
1.40
1.42
1.44
EPR
L-91998
871437
N1 Rotor Speed Limit Curve
Figure 510 (Sheet 1)
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4100
4000
3700
3800
3900
CORRECTED N1 - RPM
4200
4300
4400
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1.30
1.34
1.38
1.42
1.46
1.50
1.54
EPR
CPF CURVE NO. 2525-1
L-93745
871441
N1 Rotor Speed Limit Curve
Figure 510 (Sheet 2)
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590
NOTE:
____ LINES REPRESENT EQUIVALENT 0` MARGIN
ON-WING AT 38` C (100` F) TAMB.
580
570
CORRECTED EGT - `C
560
MAXIMUM LIMIT FOR
ENGINE WITHOUT HOT
SECTION REFURBISHMENT
550
MAXIMUM LIMIT FOR
ENGINE WITH HOT
SECTION REFURBISHMENT
(TURBINE CLEARANCES RESTORED)
540
530
520
510
500
1.30
1.32
1.34
1.36
1.38
1.40
1.42
1.44
EPR
CPE CURVE 2200
4-12-85
L-92975
871460
Corrected EGT Limit Curve
Figure 511 (Sheet 1)
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560
MAXIMUM LIMIT FOR
ENGINES WITHOUT HOT
SECTION REFURBISHMENT
540
CORRECTED EGT - `C
580
600
NOTE:
____ LINES REPRESENT EQUIVALENT 0 MARGIN
ON-WING AT 38` C (100` F) TAMB.
500
520
MAXIMUM LIMIT FOR
ENGINES WITH HOT
SECTION REFURBISHMENT
(TURBINE CLEARANCES RESTORED)
1.28
1.32
1.36
1.40
1.44
1.48
1.52
EPR
L-93752
CPE CURVE 2526-1
871467
Corrected EGT Limit Curve
Figure 511 (Sheet 2)
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CORRECTED LOW PRESSURE COMPRESSOR PRESSURE RATIO
2.5
2.4
2.3
2.2
MAXIMUM
2.1
MINIMUM
2.0
1.9
1.8
1.7
1.16
1.20
1.24
1.28
1.32
1.36
1.40
1.44
EPR
L-91763
152102
LPC Limit Curve
Figure 512
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CORRECTED HIGH PRESSURE COMPRESSOR PRESSURE RATIO
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11.6
11.2
10.8
MAXIMUM
10.4
10.0
MINIMUM
9.6
9.2
8.8
8.4
1.16
1.20
1.24
1.28
1.32
1.36
1.40
1.44
EPR
L-91764
116105
HPC Limit Curve
Figure 513
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.06
.05
DELTA PS3.1/PAMB
.04
.03
.02
.01
0
1.08
1.16
1.24
1.32
1.40
1.48
1.56
EPR
L-91768
117501
LPT ACC Correction Curves
Figure 514 (Sheet 1)
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DELTA T4.9/[(òT2)
0.955
x KHT4.9]
1
0
-1
-2
-3
-4
-5
-6
-7
1.00
1.08
1.16
1.24
1.32
1.40
1.48
1.56
EPR
L-91770
301108
LPT ACC Correction Curves
Figure 514 (Sheet 2)
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.06
.05
DELTA PT2.5/[PAMB x (òT2)
-0.06
]
.04
.03
.02
.01
0
1.00
1.08
1.16
1.24
1.32
1.40
1.56
1.48
EPR
L-91771
301109
LPT ACC Correction Curves
Figure 514 (Sheet 3)
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24
20
DELTA N1/[(\òT2) x (KHN1)]
16
12
8
4
0
0.96
1.04
1.12
1.20
1.28
1.36
1.44
1.52
EPR
L-91773
301111
LPT ACC Correction Curves
Figure 514 (Sheet 4)
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1.006
1.005
KH N1
1.004
1.003
1.002
1.001
1.000
1.004
KH N2
1.003
1.002
1.001
1.000
KH T4.9
1.000
.999
.998
.997
0
.005
.010
.015
.020
.025
SPECIFIC HUMIDITY
LBS MOISTURE/LB DRY AIR
L-91755
188552
Humidity Correction Factors
Figure 515
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SAMPLE DATA FOR USE IN EXAMPLES
TRUE LOCAL BAROMETRIC PRESSURE (P
). . . . . . . . . . 29.94 INCHES Hg ABSOLUTE
BAR
AMBIENT TEMPERATURE ( T AMB) . . . . . . . . . . . . . . . `F
AMBIENT PRESSURE (P AMB ). . . . . . . . . . . . . . . . . 14.597 PSIG
SPECIFIC HUMIDITY. . . . . . . . . . . . . . . . . . . . 0.010 LB MOISTURE/LB DRY AIR
EPR. . . . . . . . . . . . . . . . . . . . . . . . . . . 1.31
PS3I . . . . . . . . . . . . . . . . . . . . . . . . . . 194.94 PSIG
PS3.1. . . . . . . . . . . . . . . . . . . . . . . . . . 305.2 PSIG
%N1. . . . . . . . . . . . . . . . . . . . . . . . . . . 83.8%
%N2. . . . . . . . . . . . . . . . . . . . . . . . . . . 93.3%
PT2. . . . . . . . . . . . . . . . . . . . . . . . . . . 14.6 PSIG
TT2. . . . . . . . . . . . . . . . . . . . . . . . . . . 28`C
PT2.5 (BVA). . . . . . . . . . . . . . . . . . . . . . . 17 PSIG
EGT. . . . . . . . . . . . . . . . . . . . . . . . . . . 536`C
1)
EXAMINE THE %N2. IF %N2 IS MORE THAN OR THE SAME AS 89% THEN DELTA CURVES (FIG. 511) DO NOT
APPLY. SINCE THE %N2 IS 93.3%, MORE THAN 89%, IGNORE FIG. 511 CORRECTIONS.
2)
CALCULATE N2 (RPM)
N2 (RPM) = %N2 x 12250 RPM
= 93.3% x 12250
= 11429 RPM
3)
CALCULATE òT2
òT2
=
______________
TT2`C
+ 273.16
288.16
=
28`C +273.16
______________
288.16
= 1.045
4)
FIND THE CORRECTION FACTORS FROM FIG. 512 AT THE SPECIFIC HUMIDITY
KHN1
KHN2
KHT4.9
= 1.0023
= 1.0016
= 0.9992
5)
NOT USED
6)
CALCULATE THE CORRECTED TURBINE COOLING AIR PRESSURE RATIO
=
____________
PS3I + PAMB
PS3.1 + PAMB
=
_______________
194.94
+ 14.597
305.2 + 14.597
= 0.655
188223
Sample Calculations
Figure 516 (Sheet 1)
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CALCULATE THE VALUE AND MAKE SURE THE PLOTTED POINT IS IN THE LIMITS ON THE TURBINE COOLING AIR
CHECK CURVE (FIG. 505)
____
CN2
\òT2
=
11136
_____
\1.05
= 10868
NOTE:
____
8)
THE VALUE ABOVE IS IN THE LIMITS.
CALCULATE THE LOW PRESSURE COMPRESSOR PRESSURE RATIO
=
_________________
PT2.5
+ PAMB
PAMB x (òT2) -0.06
+
DELTA
_________________
PT2.5
PAMB x (òT2) -0.06
=
____________________
16.70
+ 14.597
14.597 x (1.05) -0.06
+
0
= 2.15
NOTE:
____
9)
__________________
DELTA PT2.5
PAMB x (òT2) -0.06
=
0 PER STEP 1
CALCULATE THE OVERALL COMPRESSOR PRESSURE RATIO
=
PS3.1 + PAMB
____________
PAMB
=
305.2 + 14.597
______________
14.597
DELTA PS3.1
___________
PAMB
+
= 21.91
NOTE:
____
10)
DELTA PS3.1
___________
PAMB
=
0 PER STEP 1
CALCULATE THE HIGH PRESSURE COMPRESSOR RATIO
=
______________________________________
OVERALL
COMPRESSOR PRESSURE RATIO
LOW PRESSURE COMPRESSOR PRESSURE RATIO
=
21.91
_____
2.15
= 10.19
11)
CALCULATE N1 (RPM)
N1 (RPM) = %N1 x 4550 RPM
= 83.8% x 4550 RPM
= 3813 RPM
12)
CALCULATE THE CORRECTED N1 (RPM)
CN1
=
___________
N1
(RPM)
\òT2 x KHN1
=
______________
3813
RPM
+
\1.05 x 1.0023
+
___________
DELTA
N1
\òT2 x KHN1
0
= 3713
NOTE:
____
___________
DELTA
N1
\òt2 x KHN1
= 0 FOR STEP 1
301112
Sample Calculations
Figure 516 (Sheet 2)
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CALCULATE CORRECTED EGT
CEGT
=
___________________
EGT
+273.16
0.955
x KHT4.9
(òT2)
- 273.16
+
___________________
DELTA T4.9
0.955
x KHT4.9
(òT2)
=
____________________
536
+273.16
0.955
(1.05)
x 0.9992
- 273.16
+ 0
= 500`C
NOTE:
____
14)
DELTA T4.9
___________________
(òT2) 0.955 x KHT4.9
=
0 PER STEP 1
CALCULATE PT4.9
PT4.9
= EPR x PT2
= 1.31 x 14.6 PSIG
= 19.1 PSIG
301113
Sample Calculations
Figure 516 (Sheet 3)
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TEST NO. 9 - PERFORMANCE TEST
_____________________________
H.
S 215-183-P00
(27) Examine the engine and the engine mounted components for signs of
fuel, oil, and hydraulic leaks.
(a) If you find a leak, repair the leak.
(b) If leaks are found, do the test again.
Put the airplane back to its initial condition
(1)
S 085-184-P00
Remove the pressure monitoring equipment, if it is not necessary.
(2)
S 435-185-P00
Install the PS3I cap.
(3)
S 435-186-P00
Install the PS3.1 plugs.
(4)
(5)
S 435-187-P00
Install the PT2.5 plug as follows:
(a) Install the PT2.5 plug into the PT2.5 port with the nut.
1) Tighten the nut to 85-95 pound-inches.
S 215-188-P00
If the oil pressure sense lines were changed for the installation or
removal of the PT2.5 probe, do the Test No. 2 - Engine Motoring
(Dry) Leak Test.
(6)
S 865-189-P00
If the other engine was operated, use the Power Plant Operation
(Normal) procedure to do the engine shutdown (AMM 71-00-00/201).
(7)
S 865-190-P00
If the APU was operated, use the APU operation procedure to do the
APU shutdown (AMM 49-11-00/201).
S 415-191-P00
WARNING:
_______
OBEY THE INSTRUCTIONS IN AMM 78-31-00 WHEN YOU CLOSE THE THRUST
REVERSERS. IF YOU DO NOT OBEY THE INSTRUCTIONS, INJURY TO
PERSONS OR DAMAGE TO EQUIPMENT COULD OCCUR.
(8)
Close the thrust reversers (AMM 78-31-00/201).
(9)
S 415-192-P00
Close the core cowl panels (AMM 71-11-06/201).
S 415-193-P00
(10) Close the fan cowl panels (AMM 71-11-04/201).
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TEST NO. 9 - PERFORMANCE TEST
_____________________________
S 445-194-P00
(11) Do the activation procedure for the thrust reversers
(AMM 78-31-00/201).
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MAINTENANCE MANUAL
TEST NO. 10 - REPLACEMENT ENGINE TEST (UNTESTED)
________________________________________________
TASK 71-00-00-725-195-P00
15. Test
________________________________________________
No. 10 - Replacement Engine Test (Untested)
A. General
(1) This procedure gives the minimum test necessary for a new installed
engine. This procedure is for an engine which did not have a test
in a test cell before it was installed. This includes the
engine/airplane interface checks, schedule checks, electrical and
hydraulic system checks, and leak checks.
(2) If the replacement engine had a test in a test cell, use Test No. 12
- Replacement Engine Test (Pretested).
B. Equipment
(1)
C.
D.
E.
Controlled air pressure (or nitrogen) supply
capable of 60 psig
References
(1) AMM 12-11-01/301, Fuel Tank - Pressure Fueling (Replenishing)
(2) AMM 12-12-01/301, Hydraulic System (Replenishing)
(3) AMM 12-13-01/301, Engine (Oil Servicing)
(4) AMM 12-13-02/301, Engine Starter (Oil Servicing)
(5) AMM 12-13-03/301, Integrated Drive Generator (Oil Servicing)
(6) AMM 24-11-02/201, Scavenge Filter
(7) AMM 24-22-00/201, Electrical Power - Control
(8) AMM 26-21-00/501, Engine Fire Extinguishing System
(9) AMM 29-11-00/201, Main Hydraulic System
(10) AMM 49-11-00/201, Auxiliary Power Unit
(11) AMM 71-00-00/201, Power Plant - General
(12) AMM 71-01-02/201, Power Plant (Trim Check Tables)
(13) AMM 71-11-04/201, Fan Cowl Panels
(14) AMM 71-11-06/201, Core Cowl Panels
(15) AMM 71-71-00/601, Engine Vents and Drains
(16) AMM 73-11-02/401, Fuel Pump Filter
(17) AMM 73-11-04/401, Fuel Distribution Valve Filter
(18) AMM 73-21-02/401, Fuel Control Filter
(19) AMM 78-31-00/201, Thrust Reverser System
(20) AMM 79-21-05/401, Main Oil Filter
(21) AMM 79-21-10/601, Magnetic Chip Detectors
Access
(1) Location Zones
211/212
Flight Compartment
411/421
Engine
Prepare to Do the Engine Replacement Test
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MAINTENANCE MANUAL
TEST NO. 10 - REPLACEMENT ENGINE TEST (UNTESTED)
________________________________________________
S 865-449-P00
CAUTION:
_______
(1)
DO NOT OPERATE THE AIRPLANE HYDRAULIC SYSTEMS UNLESS THE FUEL
QUANTITY IS SUFFICIENT TO GO ABOVE THE HEAT EXCHANGERS FOR THE
HYDRAULIC FLUID. IF YOU OPERATE THE AIRPLANE HYDRAULIC SYSTEMS
WITHOUT SUFFICIENT FUEL, YOU CAN CAUSE DAMAGE TO THE AIRPLANE
HYDRAULIC SYSTEMS.
Make sure there is a minimum of 600 gallons (4,020 pounds/1,827
kilograms) of fuel in each main (wing) tank to fully cover the heat
exchangers.
NOTE:
____
(a)
(b)
(2)
(3)
(4)
(5)
(6)
The total fuel load for the airplane must be a minimum of
1,200 gallons (8,040 pounds/3,654 kilograms) to cover the
heat exchangers. For this test, you must add more fuel to
this amount. This will make sure you have sufficient fuel to
operate the engines, and keep fuel above the heat exchangers.
If it is necessary, do the servicing procedure for the fuel
tanks (AMM 12-11-01/301).
Make sure the fuel tank sumps are free of water.
S 215-197-P00
Examine the hydraulic fluid reservoir for a sufficient quantity (you
can see the hydraulic fluid in the sight gages on the reservoirs).
(a) If it is necessary, do the servicing procedure for the
hydraulic reservoirs (AMM 12-12-01/301).
S 215-198-P00
Examine the engine oil tank for sufficient servicing (the oil level
is at the lip of the filler neck).
(a) If it is necessary, do the servicing procedure for the engine
oil tank (AMM 12-13-01/301).
1) Before you install the oil tank cap, make sure the packing
is free of damage and has no deterioration.
S 215-199-P00
Examine the engine starter for sufficient servicing.
(a) If it is necessary, do the servicing procedure for the engine
starter (AMM 12-13-02/301).
S 215-200-P00
Examine the IDG for sufficient servicing.
(a) If it is necessary, do the servicing procedure for the IDG
(AMM 12-13-03/301).
S 865-201-P00
Supply electrical power (AMM 24-22-00/201).
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MAINTENANCE MANUAL
TEST NO. 10 - REPLACEMENT ENGINE TEST (UNTESTED)
________________________________________________
(7)
(8)
(9)
F.
S 725-381-P00
Do a functional test of the EEC Data Entry Plug
(a) Put the EEC MAINT POWER switch, on the P61
position.
(b) Select the CONF/MCDP page on the EICAS.
(c) Make sure the same EEC PW20XX is shown for
(d) Put the EEC MAINT POWER switch, on the P61
position.
using these steps:
panel, in the ALTN
both engines.
panel, in the NORM
S 865-202-P00
Pressurize the right hydraulic system with the electric motor pump
(AMM 29-11-00/201).
S 865-203-P00
Put the parking brake in the ON position.
S 865-204-P00
(10) Use the APU Operation procedure to start the APU (AMM 49-11-00/201).
Pre-engine operation checks
(1)
S 725-205-P00
Do the pneumatic leak check.
(a) Open the fan cowl panels (AMM 71-11-04/201).
WARNING:
_______
(b)
(c)
DO THE THRUST REVERSER DEACTIVATION PROCEDURE TO PREVENT
THE OPERATION OF THE THRUST REVERSER. THE ACCIDENTAL
OPERATION OF THE THRUST REVERSER CAN CAUSE INJURY TO
PERSONS OR DAMAGE TO EQUIPMENT.
Do this procedure: Thrust Reverser Deactivation for Ground
Maintenance (AMM 78-31-00/201).
Open the core cowl panels (AMM 71-11-06/201).
WARNING:
_______
OBEY THE INSTRUCTIONS IN AMM 78-31-00 WHEN YOU OPEN THE
THRUST REVERSERS. IF YOU DO NOT OBEY THE INSTRUCTIONS,
INJURY TO PERSONS AND DAMAGE TO EQUIPMENT COULD OCCUR.
(d)
(e)
Open the thrust reversers (AMM 78-31-00/201).
Make sure the high pressure shutoff valve (HPSOV) is fully
closed (Fig. 517).
(f)
On the pilot's overhead panel P5, put the switches in the
position that follow:
1) L(R) ENG (BLEED) valve - OFF
2) ISLN valve - OPEN
3) WING ANTI-ICE valve - CLOSED
4) L(R) PACK valve - PACK OFF
5) FWD CARGO HEAT valves - CLOSED
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MAINTENANCE MANUAL
SEE
A
14TH-STAGE
BLEED DUCT
SEE
B
HIGH PRESSURE
SHUTOFF VALVE
(HPSOV)
10TH-STAGE
BLEED DUCT
(REF)
A
OPEN
MANUAL
OVERRIDE
NUT
CLOSE
VISUAL
POSITION
INDICATOR
B
201125
High Pressure Shutoff Valve
Figure 517
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MAINTENANCE MANUAL
TEST NO. 10 - REPLACEMENT ENGINE TEST (UNTESTED)
________________________________________________
(g)
(h)
6) L(R) ENG ANTI-ICE valve - CLOSED
7) L(R) ENG START switch - OFF
8) APU valve - CLOSED
Manually open the Pressure Regulating and Shutoff Valve (PRSOV)
as follows (Fig. 518):
1) Pull the ON/OFF solenoid pin on the PRSOV Regulator to the
extended position.
2) Remove the inlet pressure sense line at the PRSOV
(Fig. 518)
a) Install a cap on all open sense lines or fittings to
keep out unwanted material and prevent air leakage.
3) Install the clean air (or nitrogen) source, capable of up
to 60 PSIG, pressure gauge, and regulator to the inlet
pressure sense line.
Open the APU valve.
1) Make sure the duct pressure is between 35-45 psi.
2) On the P11 overhead panel, open this circut breaker and
install a DO-NOT-CLOSE tag:
a) 11Q22, APU BLEED PWR
3) Slowly apply 50-60 PSIG to the PRSOV inlet pressure sense
line.
4) Make sure the PRSOV opens.
WARNING:
_______
(i)
(j)
(k)
DO NOT PUT YOUR HAND IN FAST AIR LEAKAGE FROM THE DUCT.
THE PNEUMATIC AIR IS AT HIGH PRESSURE AND CAN CAUSE
INJURIES TO PERSONS.
Do a check for air leakage of all the duct joints at the
airplane to engine interface.
1) Feel for the air leakage at 12 inches or more from the duct
joint.
2) If you cannot get access to all the joints, listen for an
air leakage at the nearest access.
a) If you think there is an air leakage, get access as
necessary and feel for air leakage at 12 inches or more
from the duct.
3) Small air leakage is satisfactory.
4) Adjust the joints or couplings, or replace the duct to
correct the air leakage.
Close the APU valve as follows:
1) On the P11 overhead panel, remove the DO-NOT-CLOSE tag and
close this circut breaker:
a) 11Q22, APU BLEED PWR
2) On the P5 Bleed Air Control Panel, move the APU Bleed
Switch to OFF.
Close the PRSOV as follows:
1) Decrease the pressure from the clean air source (or
nitrogen) to zero PSIG.
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MAINTENANCE MANUAL
PRESSURE REGULATING
AND SHUTOFF VALVE (PRSOV)
TEST EQUIPMENT
SEE
A
INLET PRESSURE SENSE
LINE (DISCONNECTED)
PRSOV
PRSOV POSITION
INDICATOR
SEE
B
INLET PRESSURE SENSE LINE
FITTING, UNION (MS-6)
MANUAL
OVERRIDE
NUT
TEST LINE TO THE
INLET PRESSURE
SENSE LINE
SUPPLY
PRESSURE
GAGE (Ps)
OPEN
CLOSE
VISUAL
POSITION
INDICATOR
REGULATOR
CLEAN AIR OR
NITROGEN SUPPLY
PRESSURE
PRSOV POSITION INDICATOR
PRSOV TEST EQUIPMENT
B
A
301114
Pressure Regulating and Shutoff Valve
Figure 518
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MAINTENANCE MANUAL
TEST NO. 10 - REPLACEMENT ENGINE TEST (UNTESTED)
________________________________________________
2)
3)
Remove the air source (or nitrogen) from the inlet pressure
sense line.
Connect the inlet pressure sense line to the PRSOV.
(2)
S 715-206-P00
Do a test of the engine fire detection system
(AMM 26-11-00/501).
(a) Make sure you have all fire indications during the test.
(b) Look at the EICAS STATUS page.
1) Make sure no fire or high temperature items show.
S 865-207-P00
WARNING:
_______
(3)
USE AMM 71-00-00/201 TO OPERATE THE POWER PLANT. IF YOU DO NOT
USE THIS PROCEDURE, YOU CAN CAUSE DAMAGE TO EQUIPMENT OR INJURY
TO PERSONS.
Use the Power Plant Wet-Motor procedure to motor the engine
(AMM 71-00-00/201).
NOTE:
____
(a)
(b)
Keep the fan cowl, thrust reverser, and core cowl panels
open when you motor the engine. This will make it easier to
do the leak check.
If you find a leak, repair the leak.
If leaks were found, do the test again.
S 865-208-P00
WARNING:
_______
USE AMM 71-00-00/201 TO OPERATE THE POWER PLANT. IF YOU DO NOT
USE THIS PROCEDURE, YOU CAN CAUSE DAMAGE TO EQUIPMENT OR INJURY
TO PERSONS.
CAUTION:
_______
BEFORE YOU DO THE IGNITION SYSTEM TEST, DO THE DRY-MOTOR
PROCEDURE TO REMOVE ALL FUEL FROM THE ENGINE. THE FUEL IN THE
ENGINE FROM THE WET-MOTOR PROCEDURE CAN CAUSE AN ENGINE FIRE OR
A TURBINE EXHAUST AREA FIRE.
(4)
Use the Power Plant Dry-Motor procedure to motor the engine
(AMM 71-00-00/201).
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MAINTENANCE MANUAL
TEST NO. 10 - REPLACEMENT ENGINE TEST (UNTESTED)
________________________________________________
(5)
S 715-209-P00
Do the Ignition System Audible Test.
CAUTION:
_______
(a)
(b)
(c)
(d)
(e)
(f)
(g)
MAKE SURE YOU OPEN THE START CONT CIRCUIT BREAKER. IF THE
CIRCUIT BREAKER IS NOT OPEN, THE ENGINE WILL MOTOR WHEN
THE START SWITCH IS IN THE GND POSITION AND THE AIRPLANE
PNEUMATIC SYSTEM PRESSURIZED.
For the left engine, open this circuit breaker on the overhead
circuit breaker panel, P11, and install DO-NOT-CLOSE tag:
1) 11D19, ENGINE START CONT LEFT
For the right engine, open this circuit breaker on the overhead
circuit breaker panel, P11, and attach DO-NOT-CLOSE tag:
1) 11D20, ENGINE START CONT RIGHT
For the left engine, open these circuit breakers on the main
power distribution panel, P6, and install DO-NOT-CLOSE tags:
1) 6C1, FUEL COND CONT L
2) 6E1, FUEL VALVES L SPAR
For the right engine, open these circuit breakers on the main
power distribution panel, P6, and install DO-NOT-CLOSE tags:
1) 6C2, FUEL COND CONT R
2) 6E2, FUEL VALVES R SPAR
For the left engine, make sure these circuit breakers on the
overhead circuit breaker panel, P11, are closed:
1) 11D7, ENGINE STBY IGNITION LEFT 1
2) 11D8, ENGINE STBY IGNITION LEFT 2
3) 11L1, LEFT ENGINE IGN 1
For the right engine, make sure these circuit breakers on the
overhead circuit breaker panel, P11, are closed:
1) 11D9, ENGINE STBY IGNITION RIGHT 1
2) 11D10, ENGINE STBY IGNITION RIGHT 2
3) 11L28, RIGHT ENGINE IGN 1
Put the ignition select switch on the overhead panel, P5, to 1.
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MAINTENANCE MANUAL
TEST NO. 10 - REPLACEMENT ENGINE TEST (UNTESTED)
________________________________________________
(h)
(i)
(j)
(k)
(l)
(m)
(n)
(o)
(p)
(q)
(r)
(s)
(t)
(u)
(v)
(w)
(x)
(y)
(z)
Put the applicable L(R) engine start switch on the overhead
panel, P5, to the GND position.
Listen to make sure the igniter plug fires.
Put the engine start switch on the overhead panel P5 to the OFF
position.
Put the applicable engine ANTI-ICE switch on the overhead
panel, P5, to the ON position.
Put the engine start switch on the overhead panel, P5, to the
AUTO position.
Listen to make sure the igniter plug fires.
Put the engine ANTI-ICE switch on the overhead panel, P5, to
the OFF position.
Make sure the igniter plug does not fire.
Put the engine start switch on the overhead panel, P5, to the
CONT position.
Make sure the igniter plug fires.
Put the engine start switch on the overhead panel, P5, to the
FLT position.
Make sure the two igniter plugs fire.
Put the engine start switch on the overhead panel P5 to the OFF
position.
Put the ignition select switch to 2.
Do the Ignition System Audible Test again.
For the left engine, remove the DO-NOT-CLOSE tag and close this
circuit breaker on the P11 panel:
1) 11D19, ENGINE START CONT LEFT
For the right engine, remove the DO-NOT-CLOSE tag and close
this circuit breaker on the P11 panel:
1) 11D20, ENGINE START CONT RIGHT
For the left engine, remove the DO-NOT-CLOSE tags and close
these circuit breakers on the P6 panel:
1) 6C1, FUEL COND CONT L
2) 6E1, FUEL VALVES L SPAR
For the right engine, remove the DO-NOT-CLOSE tags and close
these circuit breakers on the P6 panel:
1) 6C2, FUEL COND CONT R
2) 6E2, FUEL VALVES R SPAR
WARNING:
_______
(aa)
(ab)
(ac)
(ad)
OBEY THE INSTRUCTIONS IN AMM 78-31-00 WHEN YOU CLOSE THE
THRUST REVERSERS. IF YOU DO NOT OBEY THE INSTRUCTIONS,
INJURY TO PERSONS OR DAMAGE TO EQUIPMENT COULD OCCUR.
Close the thrust reversers (AMM 78-31-00/201).
Close the core cowl panels (AMM 71-11-06/201).
Close the fan cowl panels (AMM 71-11-04/201).
Do the activation procedure of the thrust reversers
(AMM 78-31-00/201).
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MAINTENANCE MANUAL
TEST NO. 10 - REPLACEMENT ENGINE TEST (UNTESTED)
________________________________________________
G.
Prepare for the engine operation checks.
NOTE:
____
You must know the EEC part number for this test. Make a note of
the EEC part number prior to starting the engine.
S 865-210-P00
WARNING:
_______
(1)
(2)
USE AMM 71-00-00/201 TO OPERATE THE POWER PLANT. IF YOU DO NOT
USE THIS PROCEDURE, YOU CAN CAUSE DAMAGE TO EQUIPMENT OR INJURY
TO PERSONS.
Use the Power Plant Operation (Normal) procedure to start the engine
(AMM 71-00-00/201).
S 865-211-P00
Make sure the systems that follow are off for the engine the test is
done on, unless specified differently.
NOTE:
____
(a)
(b)
(c)
(3)
(4)
You must keep the systems off during the test. The test
limits are for the no load, no bleed air conditions.
Engine bleed air
Engine and wing anti-ice unless they are necessary
Integrated Drive Generator (IDG)
S 865-212-P00
If you do the test in conditions below 32°F (0°C), supply air to the
nacelle anti-ice system for the engine of this test as follows:
(a) Make sure the pressure regulating and shutoff valve (PRSOV) is
closed.
(b) Open the APU valve.
(c) If you do the test on the right engine, open the Isolation
valve.
(d) Open the applicable L(R) ENG ANTI-ICE valve.
S 215-213-P00
Make sure there are satisfactory engine indications.
S 215-214-P00
Look at the ECS/MSG and EPCS pages on the bottom EICAS display for
EPCS messages.
(a) If EPCS messages show, do the corrections which are necessary
for the applicable EPCS message.
Do the engine operation checks
(5)
H.
(1)
S 715-215-P00
Do the engine-driven (hydraulic) pump check.
(a) Push the ELEC/HYD display select switch on the P61 panel.
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MAINTENANCE MANUAL
TEST NO. 10 - REPLACEMENT ENGINE TEST (UNTESTED)
________________________________________________
(b)
(c)
(2)
(3)
If you do the test on the left engine, examine the left
engine-driven pump as follows:
1) Put the HYD PUMPS L ENG pump switch on the P5 panel to the
ON position.
2) Make sure the L HYD PRESS is 3000 |150 psi.
3) Put the HYD PUMPS L ENG pump switch on the P5 panel to the
OFF position.
If you do the test on the right engine, examine the right
engine-driven pump as follows:
1) Put the HYD PUMPS R ELEC pump switch on the P5 panel to the
OFF position.
2) Put the HYD PUMPS R ENG pump switch on the P5 panel to the
ON position.
3) Make sure the R HYD PRESS is 3000 |150 psi.
4) Put the HYD PUMPS R ENG pump switch on the P5 panel to the
OFF position.
5) Put the HYD PUMPS R ELEC pump switch on the P5 panel to the
ON position.
S 715-216-P00
Examine the Integrated Drive Generator (IDG)
(a) Put the applicable L(R) GEN CONT switch on the P5 panel to the
ON position.
(b) Make sure the LOAD is divided between the APU GEN and the
applicable L(R) IDG.
(c) Put the applicable L(R) GEN CONT switch on the P5 panel to the
OFF position.
(d) Make sure the LOAD moves to the APU GEN.
S 715-217-P00
Examine the Pressure Regulating and Shutoff Valve (PRSOV)
(a) On the P5 panel, put the items that follow in the specified
position:
1) APU valve - closed (flowbar is off)
2) BLEED AIR L(R) ENG Valve - open (flowbar is on)
3) ISOLATION VALVE - closed (flowbar is off)
4) Air Conditioning L(R) Pack Selector Switch - AUTO
5) L(R) RECIRC FAN - ON
6) L(R) Temp Select Switch - AUTO
7) TRIM AIR VALVE - ON
(b) Push the PERF/APU display select switch on the P61 panel.
(c) Make sure the applicable L(R) DUCT PR shows 14 |1 psi.
(d) On the P5 panel, put the items that follow in the specified
position:
1) TRIM AIR VALVE - OFF
2) L(R) Temp Select Switch - OFF
3) L(R) RECIRC FAN - OFF
4) Air Conditioning L(R) Pack Selector Switch - OFF
5) BLEED AIR L(R) ENG Valve - closed (flowbar is off)
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MAINTENANCE MANUAL
TEST NO. 10 - REPLACEMENT ENGINE TEST (UNTESTED)
________________________________________________
6)
(4)
APU Valve - open (flowbar is on)
S 715-219-P00
Do the approach idle, snap ACCEL/DECEL, SVA schedule, and 14th-Stage
Bleed System checks.
(a) With the applicable trim check table (AMM 71-01-02/201), find
the targets that follow for the local weather:
1) MIN IDLE %N2
2) APP IDLE %N2
3) TAKEOFF (EPR)
4) 95% TAKEOFF THRUST (EPR)
5) 90% THRUST CHANGE DECEL (EPR)
(b) Push the EPCS display select switch on the P61 panel.
1) Make sure the white box is around the PRI.
(c) Push the PERF/APU display select switch on the P61 panel.
(d) Pull the THRUST REF SET switch on the forward electronics
panel, P9.
(e) Set the REF EPR target bug on the EICAS to the 95% TAKEOFF
THRUST (EPR) target.
1) Do not push in the THRUST REF SET switch.
(f) To prevent the activation of the probe heaters, open the
circuit breakers that follow:
1) Open these circuit breakers on the main power distribution
panel, P6, and attach DO-NOT-CLOSE tags:
a) 6L15, PITOT HEAT CAPT MAIN
b) 6L16, PITOT HEAT L AUX
c) 6L17, L AOA HEAT
d) 6L21, PITOT HEAT R AUX
e) 6L22, PITOT HEAT F/O MAIN
f) 6L23, R AOA HEAT
g) 6L24, TAT PROBE HEAT
2) Open these circuit breakers on the right miscellaneous
electrical equipment panel, P37, and attach DO-NOT-CLOSE
tags:
a) 37F4, HEATER F/O AUX HI
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MAINTENANCE MANUAL
TEST NO. 10 - REPLACEMENT ENGINE TEST (UNTESTED)
________________________________________________
b) 37F7, HEATER DRAIN MST AIR
Open the circuit breakers on the miscellaneous electrical
equipment panel, P70, and attach DO-NOT-CLOSE tag:
a) 70A6, CAPT AUX HTR HI
For the left engine, open these circuit breakers on the
overhead circuit breaker panel, P11, in sequence and attach
DO-NOT-CLOSE tags:
1) 11C14, FSEU 2 PWR
2) 11S15, AIR/GND SYS 1
3) 11C30, LANDING GEAR POS SYS 1
For the right engine, open these circuit breakers on the
overhead circuit breaker panel, P11, in sequence and attach
DO-NOT-CLOSE tags:
1) 11G21, FSEU 3 PWR
2) 11S19, AIR/GND SYS 2
3) 11S23, LANDING GEAR POS SYS 2
4) ILF 501 POST-SB 78-28 AND ILF 502-999;
11C19, LANDING GEAR POS SYS 2 ALTN
Make sure the engine speed increases to the APP IDLE %N2
target.
For the left engine, remove the DO-NOT-CLOSE tag and close this
circuit breaker on the P11 panel:
1) 11S15, AIR/GND SYS 1
For the right engine, remove the DO-NOT-CLOSE tag and close
this circuit breaker on the P11 panel:
1) 11S19, AIR/GND SYS 2
For the left engine, open this circuit breaker on the overhead
circuit breaker panel P11 and attach DO-NOT-CLOSE tag:
1) 11S15, AIR/GND SYS 1
For the right engine, open this circuit breaker on the overhead
circuit breaker panel P11 and attach DO-NOT-CLOSE tag:
1) 11S19, AIR/GND SYS 2
Permit the engine to become stable at approach idle for 60
seconds.
3)
(g)
(h)
(i)
(j)
(k)
(l)
(m)
(n)
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MAINTENANCE MANUAL
TEST NO. 10 - REPLACEMENT ENGINE TEST (UNTESTED)
________________________________________________
(o)
Quickly move the thrust lever forward to increase the speed of
the engine and measure the time as follows:
1) In less than one second, move the applicable thrust lever
to the full forward position.
CAUTION:
_______
YOU MUST RETARD THE POWER LEVERS BEFORE THE EGT IS
MORE THAN THE MAXIMUM EGT. THE EEC ONLY HAS A LIMIT
ON THE EPR AND THE ENGINE SPEED. THE EEC DOES NOT
PREVENT THE OVERTEMPERATURE AND DOES NOT HAVE A LIMIT
FOR THE TEMPERATURE (EGT). THE DETERIORATION OF THE
ENGINE OR BLEED SYSTEM CAN CAUSE AN EGT WHICH IS MORE
THAN THE MAXIMUM EGT BEFORE THE EPR (OR ROTOR SPEED)
DECREASES. IF YOU DO NOT RETARD THE POWER LEVERS,
YOU CAN CAUSE DAMAGE TO THE ENGINE.
2)
(p)
(q)
(r)
(s)
Measure the time of acceleration from approach idle to the
95% TAKEOFF THRUST (EPR) target.
3) Make sure the acceleration time is 5.8 seconds or less.
4) Make sure the engine does not go above the TAKEOFF (EPR)
target.
5) Permit the engine to become stable for 15-20 seconds.
Push the EVENT RECORD switch on the forward electronics panel,
P9, to make a record of the engine conditions.
For the left engine, remove the DO-NOT-CLOSE tag and close
these circuit breakers on the P11 panel in sequence:
1) 11S15, AIR/GND SYS 1
2) 11C14, FSEU 2 PWR
3) 11C30, LANDING GEAR POS SYS 1
For the right engine, remove the DO-NOT-CLOSE tags and close
these circuit breakers on the P11 panel in sequence:
1) 11S19, AIR/GND SYS 2
2) 11G21, FSEU 3 PWR
3) 11S23, LANDING GEAR POS SYS 2
4) ILF 501 POST-SB 78-28 AND ILF 502-999;
11C19, LANDING GEAR POS SYS 2 ALTN
Quickly move the thrust lever rearward to decrease the speed of
the engine and measure the time as follows:
1) In less than one second, move the applicable thrust lever
to the idle position.
2) Measure the time of deceleration from TAKEOFF (EPR) to the
90% THRUST CHANGE DECEL (EPR) targets.
a) Make sure the time of deceleration is 7.1 seconds or
less.
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MAINTENANCE MANUAL
TEST NO. 10 - REPLACEMENT ENGINE TEST (UNTESTED)
________________________________________________
(t)
ENGINES WITH EEC PART NUMBERS 783600-13-068 OR 783600-14-068;
Do Test No. 6 - 14th Stage Bleed System Test
(AMM 71-00-00/501).
NOTE:
____
(u)
This procedure is applicable for engines with these EEC
part numbers: Hamilton Standard P/N 783600-13-068 and
783600-14-068, (Pratt & Whittney P/N 1B6597 and 1B6598).
These EEC's contain SCN 24C software.
ENGINES WITHOUT EEC PART NUMBERS 783600-113-068 OR
783600-14-068;
Do the step which follows to monitor the operation of the
14th-stage converter valve.
NOTE:
____
This step is applicable for engines without these EEC
part numbers: Hamilton Standard P/N 783600-13-068, and
783600-14-068. This step is applicable for EEC's
without SCN 24C.
1)
(v)
(w)
(x)
(y)
Make sure the conditions that follow show approximately 80
seconds after the thrust lever is at the minimum idle stop:
a) The EGT decreases between 30°C to 50°C.
b) The engine becomes stable at the MIN IDLE %N2 target.
Push the MAN-EVENT READ switch on the P61 panel.
1) Make a record of the engine conditions from the PERF/APU
page on the bottom EICAS display.
Push the EPCS display select switch on the P61 panel.
Push the MAN-EVENT READ switch on the P61 panel.
1) Make a record of the takeoff values for the N2C and the SVA
from the EPCS page on the bottom EICAS display.
Make sure the SVA is in the limits shown in Fig. 508.
(z)
Remove the DO-NOT-CLOSE tags and close these circuit breakers
on the P6 panel:
1) 6L15, PITOT HEAT CAPT MAIN
2) 6L16, PITOT HEAT L AUX
3) 6L17, L AOA HEAT
4) 6L21, PITOT HEAT R AUX
5) 6L22, PITOT HEAT F/O MAIN
6) 6L23, R AOA HEAT
7) 6L24, TAT PROBE HEAT
(aa) Remove the DO-NOT-CLOSE tags and close these circuit breakers
on the P37 panel:
1) 37F4, HEATER F/O AUX HI
2) 37F7, HEATER DRAIN MST AIR
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MAINTENANCE MANUAL
TEST NO. 10 - REPLACEMENT ENGINE TEST (UNTESTED)
________________________________________________
(ab) Remove the DO-NOT-CLOSE tag and close this circuit breaker on
the P70 panel:
1) 70A6, CAP AUX HTR HI
(ac) Push in the THRUST REF SET switch on the P9 panel.
(5)
S 715-220-P00
Do the thrust reverser check.
(a) Slowly move the thrust reverser lever to the DEPLOY position.
(b) Make sure the REV indication shows on the top EICAS display.
(c) Make a record of the time the REV indication is amber in color.
NOTE:
____
The REV indication is amber in color when the thrust
reverser moves. When there is a green REV indication,
the thrust reverser is fully deployed.
1)
(d)
(e)
(f)
(g)
(6)
(7)
Make sure the amber REV indication is not on for more than
2.0 seconds.
Make sure the RVA on the EPCS page reads 100% |2%.
Slowly move the thrust reverser lever to the stow position.
Make sure the REV indication changes from green to amber in
color (the thrust reverser has movement).
1) Make sure the REV indication goes off from the top EICAS
display.
2) Make a record of the time the REV indication is amber in
color.
3) Make sure the amber REV indication is not on for more than
5.0 seconds.
Make sure the RVA reads 0 |2%.
S 215-221-P00
Look at the ECS/MSG and EPCS pages on the bottom EICAS display for
messages.
(a) If messages show, do the corrections which are necessary for
the applicable message.
S 865-222-P00
Do the IDG disconnect check.
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MAINTENANCE MANUAL
TEST NO. 10 - REPLACEMENT ENGINE TEST (UNTESTED)
________________________________________________
CAUTION:
_______
DO NOT OPERATE THE GEN DRIVE DISC SWITCH FOR MORE THAN
THREE SECONDS. PERMIT A MINIMUM OF 60 SECONDS BETWEEN
OPERATIONS.
CAUTION:
_______
DO NOT OPERATE THE GEN DRIVE DISC SWITCH UNLESS THE ENGINE
IS AT OR ABOVE IDLE N2 RPM. DO NOT DISCONNECT THE IDG
WITH THE ENGINE BELOW IDLE. THIS CAN CAUSE DAMAGE TO THE
DISCONNECT DOG TEETH.
(a)
I.
While you operate the engine at the minimum idle N2 RPM or
more, push the applicable L(R) GEN DRIVE DISC switch on the P5
panel.
1) Make sure the applicable L(R) DRIVE light and L(R) GEN CONT
OFF lights go on to make sure the IDG is disconnected.
(b) Use the Power Plant Operation (Normal) procedure to do the
engine shutdown (AMM 71-00-00/201).
(c) Use the APU Operation procedure to do the APU shutdown
(AMM 49-11-00/201).
Do the post-engine operation checks.
(1)
S 015-223-P00
Open the fan cowl panels (AMM 71-11-04/201).
S 045-224-P00
WARNING:
_______
(2)
(3)
DO THE THRUST REVERSER DEACTIVATION PROCEDURE TO PREVENT THE
OPERATION OF THE THRUST REVERSER. THE ACCIDENTAL OPERATION OF
THE THRUST REVERSER CAN CAUSE INJURY TO PERSONS OR DAMAGE TO
EQUIPMENT.
Do this procedure: Thrust Reverser Deactivation for Ground
Maintenance (AMM 78-31-00/201).
S 015-225-P00
Open the core cowl panels (AMM 71-11-06/201).
S 015-226-P00
WARNING:
_______
(4)
OBEY THE INSTRUCTIONS IN AMM 78-31-00 WHEN YOU OPEN THE THRUST
REVERSERS. IF YOU DO NOT OBEY THE INSTRUCTIONS, INJURY TO
PERSONS OR DAMAGE TO EQUIPMENT COULD OCCUR.
Open the thrust reversers (AMM 78-31-00/201).
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MAINTENANCE MANUAL
TEST NO. 10 - REPLACEMENT ENGINE TEST (UNTESTED)
________________________________________________
(5)
(6)
(7)
(8)
(9)
S 215-227-P00
Do a full leak check of the fuel, oil, and hydraulic connections
(AMM 71-71-00/601).
(a) No fuel, oil or hydraulic fluid is permitted, but this does not
include the approved leakage from the engine vents and drains.
S 215-228-P00
Make sure the N2 rotor is stopped.
S 825-229-P00
Pull out the IDG disconnect reset ring until you feel the solenoid
pin go into position (Fig. 502).
S 215-230-P00
Examine the engine fuel system screens and filters.
(a) Replace the fuel pump filter (AMM 73-11-02/401).
(b) Clean the fuel control filter (AMM 73-21-02/701).
(c) If the fuel control filter was very dirty, replace the fuel
distribution valve filter (AMM 73-11-04/401).
S 215-231-P00
Examine the oil system filters and the magnetic chip detectors.
(a) Replace the main oil filter (AMM 79-21-05/401).
(b) Clean the magnetic chip detectors (AMM 79-21-10/701).
(c) Examine the IDG scavenge filter (AMM 24-11-02/201).
WARNING:
_______
(d)
BEFORE YOU OPEN THE OIL TANK CAP, PERMIT A MINIMUM OF FIVE
MINUTES AFTER THE ENGINE STOPS TO LET THE PRESSURE IN THE
OIL TANK BLEED OFF. A FAST FLOW OF HOT OIL CAN OCCUR AND
CAUSE INJURY TO YOU.
Examine the engine oil tank for sufficient servicing (the oil
level is at the lip of the filler neck).
1) If it is necessary, do the servicing procedure for the
engine oil tank (AMM 12-13-01/301).
S 415-232-P00
WARNING:
_______
OBEY THE INSTRUCTIONS IN AMM 78-31-00 WHEN YOU CLOSE THE THRUST
REVERSERS. IF YOU DO NOT OBEY THE INSTRUCTIONS, INJURY TO
PERSONS OR DAMAGE TO EQUIPMENT COULD OCCUR.
(10) Close the thrust reversers (AMM 78-31-00/201).
S 415-233-P00
(11) Close the core cowl panels (AMM 71-11-06/201).
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TEST NO. 10 - REPLACEMENT ENGINE TEST (UNTESTED)
________________________________________________
S 415-234-P00
(12) Close the fan cowl panels (AMM 71-11-04/201).
S 445-235-P00
(13) Do the activation procedure for the thrust reversers
(AMM 78-31-00/201).
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TEST NO. 11 - OIL PRESSURE TEST
_______________________________
TASK 71-00-00-735-236-P00
16. Test
_______________________________
No. 11 - Oil Pressure Test
A. General
(1) This test examines the engine scavenge (SCAV) and manifold oil
pressures to make sure they are in the limits. This procedure also
includes the necessary steps to adjust the manifold oil pressure if
the pressures are more than the limits.
B. References
(1) AMM 71-00-00/201, Power Plant - General
(2) AMM 71-11-04/201, Fan Cowl Panels
(3) AMM 71-11-06/201, Core Cowl Panels
(4) AMM 78-31-00/201, Thrust Reverser System
C. Access
(1) Location Zones
211/212
Flight Compartment
411/421
Engine
D.
Do a Test of the Engine Oil Pressure (Fig. 518A and 518B)
S 865-237-P00
WARNING:
_______
(1)
(2)
(3)
USE AMM 71-00-00/201 TO OPERATE THE POWER PLANT. IF YOU DO NOT
USE THIS PROCEDURE, YOU CAN CAUSE DAMAGE TO EQUIPMENT OR INJURY
TO PERSONS.
Use the Power Plant Operation (Normal) procedure to start the engine
(AMM 71-00-00/201).
(a) Permit the N2 RPM to become stable at idle.
(b) Make sure there are satisfactory engine indications.
S 225-238-P00
Use the items that follow from the PERF/APU page to examine and
adjust the manifold and scavenge oil pressure.
(a) Oil Temperature - TEMP
(b) Oil Pressure Delta P - DIFF
(c) Engine Speed, N2 - N2
(d) No. 4 Restrictor Pressure - SCAV
S 225-239-P00
Examine the manifold and scavenge oil pressure as follows:
(a) Operate the engine at minimum idle until the oil temperature is
more than 95° C.
(b) Slowly move the thrust lever forward to increase the speed of
the engine until the No. 4 scavenge valve closes (i.e., SCAV is
the same as or more than 75 psi [517.1 kpa]).
(c) Permit the engine to become stable for three minutes.
(d) Make a record of the N2 speed, DIFF oil pressure, and SCAV oil
pressure.
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MAINTENANCE MANUAL
NO. 4 BEARING SCAVENGE VALVE PRESSURE - PSIG
160
150
140
MAXIMUM
130
120
110
100
90
80
70
60
50
40
30
MAXIMUM
NOTE:
____
20
10
0
7000
(57)
8000
(65)
9000
(73.5)
BELOW 10,000 RPM, NO. 4 SCAVENGE
MAXIMUM LIMIT IS ADJUSTED TO DETECT
DISTRESSED CARBON SEALS; CURVE DOES
NOT EQUAL MANIFOLD OIL PRESSURE
(MOP) MINUS ~ MAIN OIL PRESSURE.
10000
(81.5)
11000
(90)
12000
(98)
OBSERVED HIGH ROTOR SPEED (N2) - RPM (%)
KEY DATA POINTS
N2 (RPM)
Pscav (PSIG)
7000
20
9300
22
1000
40
10300
110
11950
160
12500
160
M20708
No. 4 Restrictor Oil Pressure SCAV Vs. N2 Rotor Speed
Figure 518A
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305
MANIFOLD OIL PRESSURE PSIG (KPa)
300
(2068.4)
200
(1379.0)
170
UPPER LIMIT
160
TRIM BAND
LOWER LIMIT
110
100
(689.5)
80
20
60
57
70
N2 SPEED
75
80 82
90
98 100
PERCENT
M20709
Oil Pressure Adjustment Band
Figure 518B
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TEST NO. 11 - OIL PRESSURE TEST
_______________________________
(e)
ú
(f)
(g)
(h)
(i)
Make sure the SCAV oil pressure is not more than the maximum
pressure limits (Fig. 518A).
Look at the STATUS and ECS/MSG pages on the bottom EICAS
display for messages.
1) If messages show, do the corrections which are necessary
for the applicable message.
Operate the engine at idle for five minutes to let the
temperature of the engine decrease and become stable before the
engine shutdown.
Use the Power Plant Operation (Normal) procedure to do the
engine shutdown (AMM 71-00-00/201).
Open the fan cowl panels (AMM 71-11-04/201).
WARNING:
_______
(j)
(k)
DO THE THRUST REVERSER DEACTIVATION PROCEDURE TO PREVENT
THE OPERATION OF THE THRUST REVERSER. THE ACCIDENTAL
OPERATION OF THE THRUST REVERSER CAN CAUSE INJURY TO
PERSONS OR DAMAGE TO EQUIPMENT.
Do this procedure: Thrust Reverser Deactivation for Ground
Maintenance (AMM 78-31-00/201).
Open the core cowl panels (AMM 71-11-06/201).
WARNING:
_______
(l)
(m)
(n)
OBEY THE INSTRUCTIONS IN AMM 78-31-00 WHEN YOU OPEN THE
THRUST REVERSERS. IF YOU DO NOT OBEY THE INSTRUCTIONS,
INJURY TO PERSONS OR DAMAGE TO EQUIPMENT COULD OCCUR.
Open the thrust reversers (AMM 78-31-00/201).
Examine the engine for leaks.
1) If you find a leak, repair the leak.
Examine the manifold oil pressure as follows:
NOTE:
____
1)
2)
ú
The manifold oil pressure is the same as the SCAV oil
pressure added to the DIFF oil pressure.
Add the SCAV oil pressure and the DIFF oil pressure.
Make sure the manifold oil pressure which was calculated is
in the limits (Fig. 518B).
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TEST NO. 11 - OIL PRESSURE TEST
_______________________________
(4)
S 825-240-P00
Adjust the manifold and scavenge oil pressure, if it is necessary.
NOTE:
____
(a)
The adjustment of the manifold and scavenge oil pressure is
not possible when you operate the engine.
ENGINES WITH OIL PUMPS THAT HAVE BARRIER SCREENS;
Remove and examine the barrier screen.
NOTE:
____
It is necessary to make sure the barrier screen does
not have contamination before you do the pressure
adjustment.
1)
(b)
(c)
(d)
If the barrier screen is broken, remove and clean the trim
(needle) valve.
Remove the dust cover on the oil pressure trim valve (found on
the lubrication and scavenge oil pump) (Fig. 505).
Loosen the jamnut while you hold the trim (needle) valve
stable.
Turn the trim (needle) valve counterclockwise to decrease the
oil pressure or clockwise to increase the oil pressure.
NOTE:
____
At minimum power, do not permit the oil pressure to go
below the bottom of the trim band. But, at minimum
power, you can go above the trim band to put the oil
pressure in the pressure limits at the high power point.
One full turn of the trim (needle) valve will change the
oil pressure by 10-20 psi (68.9-137.9 kPa).
(e)
(f)
Tighten the jamnut to 60-80 pound-inches (6.779-9.039
newton-meters).
Install the dust cover.
1) Tighten the dust cover with your fingers.
2) Install lockwire to the dust cover.
WARNING:
_______
(g)
(h)
(i)
(j)
(k)
OBEY THE INSTRUCTIONS IN AMM 78-31-00 WHEN YOU CLOSE THE
THRUST REVERSERS. IF YOU DO NOT OBEY THE INSTRUCTIONS,
INJURY TO PERSONS OR DAMAGE TO EQUIPMENT COULD OCCUR.
Close the thrust reversers (AMM 78-31-00/201).
Close the core cowl panels (AMM 71-11-06/201).
Close the fan cowl panels (AMM 71-11-04/201).
Do the activation procedure for the thrust reversers
(AMM 78-31-00/201).
Do the steps from above until the manifold and scavenge oil
pressure is in limits.
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TEST NO. 12 - REPLACEMENT ENGINE TEST (PRE-TESTED)
__________________________________________________
TASK 71-00-00-725-241-P00
17. Test
_________________________________________________
No. 12 - Replacement Engine Test (Pretested)
A. General
(1) This procedure gives the minimum tests necessary for a new installed
engine. This procedure is for an engine which did a test in a test
cell before it was installed. This includes the engine/airplane
interface checks, electrical and hydraulic system checks, and leak
checks.
(2) If the replacement engine is not a pretested engine, you must use
Test No. 10 - Replacement Engine Test (Untested).
B. Equipment
(1)
C.
D.
E.
Controlled air pressure (or nitrogen) supply
capable of 60 psig
References
(1) AMM 12-11-01/301, Fuel Tank - Pressure Fueling (Replenishing)
(2) AMM 12-12-01/301, Hydraulic System (Replenishing)
(3) AMM 12-13-01/301, Engine - Oil Servicing
(4) AMM 12-13-02/301, Engine Starter (Oil Servicing)
(5) AMM 12-13-03/301, Integrated Drive Generator (Oil Servicing)
(6) AMM 24-22-00/201, Electrical Power - Control
(7) AMM 26-21-00/501, Engine Fire Extinguishing System
(8) AMM 29-11-00/201, Main Hydraulic System
(9) AMM 49-11-00/201, Auxiliary Power Unit
(10) AMM 71-00-00/201, Power Plant - General
(11) AMM 71-01-02/201, Power Plant (Trim Check Tables)
(12) AMM 71-11-04/201, Fan Cowl Panels
(13) AMM 71-11-06/201, Core Cowl Panels
(14) AMM 78-31-00/201, Thrust Reverser System
Access
(1) Location Zones
211/212
Flight Compartment
411/421
Engine
Prepare to Do the Test of the Engine
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TEST NO. 12 - REPLACEMENT ENGINE TEST (PRE-TESTED)
__________________________________________________
S 865-450-P00
CAUTION:
_______
(1)
DO NOT OPERATE THE AIRPLANE HYDRAULIC SYSTEMS UNLESS THE FUEL
QUANTITY IS SUFFICIENT TO GO ABOVE THE HEAT EXCHANGERS FOR THE
HYDRAULIC FLUID. IF YOU OPERATE THE AIRPLANE HYDRAULIC SYSTEMS
WITHOUT SUFFICIENT FUEL, YOU CAN CAUSE DAMAGE TO THE AIRPLANE
HYDRAULIC SYSTEMS.
Make sure there is a minimum of 600 gallons (4,020 pounds/1,827
kilograms) of fuel in each main (wing) tank to fully cover the heat
exchangers.
NOTE:
____
(a)
(b)
(2)
(3)
(4)
(5)
(6)
The total fuel load for the airplane must be a minimum of
1,200 gallons (8,040 pounds/3,654 kilograms) to cover the
heat exchangers. For this test, you must add more fuel to
this amount. This will make sure you have sufficient fuel to
operate the engines, and keep fuel above the heat exchangers.
If it is necessary, do the servicing procedure for the fuel
tanks (AMM 12-11-01/301).
Make sure the fuel tank sumps are free of water.
S 215-243-P00
Examine the hydraulic fluid reservoir for a sufficient quantity (you
can see the hydraulic fluid in the sight gages on the reservoirs).
(a) If it is necessary, do the servicing procedure for the
hydraulic reservoirs (AMM 12-12-01/301).
S 215-244-P00
Examine the engine oil tank for sufficient servicing (the oil level
is at the lip of the filler neck).
(a) If it is necessary, do the servicing procedure for the engine
oil tank (AMM 12-13-01/301).
1) Before you install the oil tank cap, make sure the packing
is free of damage and has no deterioration.
S 215-245-P00
Examine the engine starter for sufficient servicing.
(a) If it is necessary, do the servicing procedure for the engine
starter (AMM 12-13-02/301).
S 215-246-P00
Examine the IDG for sufficient servicing.
(a) If it is necessary, do the servicing procedure for the IDG
(AMM 12-13-03/301).
S 865-247-P00
Supply electrical power (AMM 24-22-00/201).
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TEST NO. 12 - REPLACEMENT ENGINE TEST (PRE-TESTED)
__________________________________________________
(7)
(8)
(9)
F.
S 725-447-P00
Do a functional test of the EEC Data Entry Plug
(a) Put the EEC MAINT POWER switch, on the P61
position.
(b) Select the CONF/MCDP page on the EICAS.
(c) Make sure the same EEC PW20XX is shown for
(d) Put the EEC MAINT POWER switch, on the P61
position.
using these steps:
panel, in the ALTN
both engines.
panel, in the NORM
S 865-248-P00
Pressurize the right hydraulic system with the electric motor pump
(AMM 29-11-00/201).
S 865-249-P00
Put the parking brake in the ON position.
S 865-250-P00
(10) Use the APU Operation procedure to start the APU (AMM 49-11-00/201).
Do the pre-engine operation checks
(1)
S 715-251-P00
Do the pneumatic leak check.
(a) Open the fan cowl panels (AMM 71-11-04/201).
WARNING:
_______
(b)
(c)
Do the Deactivation Procedure for Ground Maintenance
(AMM 78-31-00/201).
Open the core cowl panels (AMM 71-11-06/201).
WARNING:
_______
(d)
(e)
(f)
DO THE THRUST REVERSER DEACTIVATION PROCEDURE TO PREVENT
THE OPERATION OF THE THRUST REVERSER. THE ACCIDENTAL
OPERATION OF THE THRUST REVERSER CAN CAUSE INJURY TO
PERSONS AND DAMAGE TO EQUIPMENT.
OBEY THE INSTRUCTIONS IN THE PROCEDURE TO WHEN YOU OPEN
THE THRUST REVERSERS. IF YOU DO NOT OBEY THE
INSTRUCTIONS, INJURY TO PERSONS AND DAMAGE TO EQUIPMENT
COULD OCCUR.
Open the thrust reversers (AMM 78-31-00/201).
Make sure the high pressure shutoff valve (HPSOV) is fully
closed (Fig. 517).
On the pilot's overhead panel P5, put the switches in the
position that follow:
1) L(R) ENG (BLEED) Valve - OFF
2) ISLN Valve - OPEN
3) WING ANTI-ICE Valve - CLOSED
4) L(R) PACK Valve - PACK OFF
5) L(R) ENG ANTI-ICE Valve - CLOSED
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TEST NO. 12 - REPLACEMENT ENGINE TEST (PRE-TESTED)
__________________________________________________
(g)
(h)
6) L(R) ENG START Switch - OFF
7) APU Valve - CLOSED
Manually open the Pressure Regulating and Shutoff Valve (PRSOV)
as follows (Fig. 518):
1) Pull the ON/OFF solenoid pin on the PRSOV Regulator to the
extended position.
2) Remove the inlet pressure sense line at the PRSOV
(Fig. 518)
a) Install a cap on all open sense lines or fittings to
keep out unwanted material and prevent air leakage.
3) Install the clean air (or nitrogen) source, capable of up
to 60 PSIG, pressure gauge, and regulator to the inlet
pressure sense line.
Open the APU valve.
1) Make sure the duct pressure is between 35-45 psi.
2) On the P11 overhead panel, open this circut breaker and
install a DO-NOT-CLOSE tag:
a) 11Q22, APU BLEED PWR
3) Slowly apply 50-60 PSIG to the PRSOV inlet pressure sense
line.
4) Make sure the PRSOV opens.
WARNING:
_______
(i)
(j)
(k)
DO NOT PUT YOUR HAND IN FAST AIR LEAKAGE FROM THE DUCT.
THE PNEUMATIC AIR IS AT HIGH PRESSURE AND CAN CAUSE
INJURIES TO PERSONS.
Do a check for air leakage of all the duct joints at the
airplane to engine interface.
1) Feel for the air leakage at 12 inches or more from the duct
joint.
2) If you cannot get access to all the joints, listen for air
leakage at the nearest access.
a) If you think there is air leakage, get access as
necessary and feel for air leakage at 12 inches or more
from the duct.
3) Small air leakage is satisfactory.
4) Adjust the joints or couplings, or replace the duct to
correct the air leakage.
Close the APU valve as follows:
1) On the P11 overhead panel, remove the DO-NOT-CLOSE tag and
close this circut breaker:
a) 11Q22, APU BLEED PWR
2) On the P5 Bleed Air Control Panel, move the APU Bleed
Switch to the OFF position.
Close the PRSOV as follows:
1) Decrease the pressure from the clean air source (or
nitrogen) to zero PSIG.
2) Remove the air source (or nitrogen) from the inlet pressure
sense line.
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TEST NO. 12 - REPLACEMENT ENGINE TEST (PRE-TESTED)
__________________________________________________
3)
(2)
Connect the inlet pressure sense line to the PRSOV.
S 715-252-P00
Do the operational test for the engine fire and overheat detection
system (AMM 26-11-00/501).
(a) Make sure you have all fire indications during the test.
(b) Look at the STATUS page on the bottom EICAS display.
1) Make sure no fire or high temperature items show.
S 865-253-P00
WARNING:
_______
(3)
USE AMM 71-00-00/201 TO OPERATE THE POWER PLANT. IF YOU DO NOT
USE THIS PROCEDURE, YOU CAN CAUSE DAMAGE TO EQUIPMENT AND
INJURY TO PERSONS.
Use the Power Plant Wet-Motor procedure to motor the engine
(AMM 71-00-00/201).
NOTE:
____
(a)
(b)
Keep the fan cowl, thrust reverser, and core cowl panels
open when you motor the engine. This will make it easier to
do the leak check.
If you find a leak, repair the leak.
If leaks are found, do the test again.
S 415-254-P00
WARNING:
_______
OBEY THE INSTRUCTIONS IN THE PROCEDURE WHEN YOU CLOSE THE
THRUST REVERSERS. IF YOU DO NOT OBEY THE INSTRUCTIONS, INJURY
TO PERSONS AND DAMAGE TO EQUIPMENT COULD OCCUR.
(4)
Close the thrust reversers (AMM 78-31-00/201).
(5)
S 415-255-P00
Close the core cowl panels (AMM 71-11-06/201).
(6)
S 415-256-P00
Close the fan cowl panels (AMM 71-11-04/201).
S 445-257-P00
Do the activation procedure for the thrust reversers
(AMM 78-31-00/201).
Prepare for the engine operation checks.
(7)
G.
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TEST NO. 12 - REPLACEMENT ENGINE TEST (PRE-TESTED)
__________________________________________________
S 865-258-P00
WARNING:
_______
(1)
(2)
USE AMM 71-00-00/201 TO OPERATE THE POWER PLANT. IF YOU DO NOT
USE THIS PROCEDURE, YOU CAN CAUSE DAMAGE TO EQUIPMENT AND
INJURY TO PERSONS.
Use the Power Plant Operation (Normal) procedure to start the engine
(AMM 71-00-00/201).
S 865-259-P00
Make sure the systems that follow are off for the engine the test is
done on, unless specified differently.
NOTE:
____
(a)
(b)
(c)
(3)
(4)
You must keep the systems off during the test because the
test limits are for the no load, no bleed air conditions.
Engine bleed air
Engine and wing anti-ice, unless it is necessary
Integrated Drive Generator (IDG)
S 865-260-P00
If you do the test in frozen conditions, supply air to the nacelle
anti-ice system for the engine of this test as follows:
(a) Make sure the pressure regulating and shutoff valve (PRSOV) is
closed.
(b) Open the APU valve.
(c) If you do the test on the right engine, open the Isolation
valve.
(d) Open the applicable L(R) ENG ANTI-ICE valve.
S 865-261-P00
Make sure there are satisfactory engine indications.
S 215-262-P00
Look at the ECS/MSG and EPCS pages on the bottom EICAS display for
messages.
(a) If messages show, do the corrections which are necessary for
the applicable message.
Do the engine operation checks
(5)
H.
(1)
S 865-263-P00
Push the ELEC/HYD display select switch on the P61 panel.
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TEST NO. 12 - REPLACEMENT ENGINE TEST (PRE-TESTED)
__________________________________________________
(2)
(3)
(4)
S 735-264-P00
Do the engine-driven (hydraulic) pump check.
(a) If you do the test on the left engine, examine the left
engine-driven pump as follows:
1) Put the HYD PUMPS L ENG pump switch on the P5 panel to the
DEPRESS position.
2) Let the hydraulic system pressure decrease.
3) Make sure the engine-driven pump PRESS indicator light
comes on.
4) Put the L HYD PUMPS ENG pump switch to the ON position.
5) Make sure the L HYD PRESS is 3000 |150 psi.
6) Make sure the engine-driven pump PRESS indicator light goes
off.
(b) If you do the test on the right engine, examine the right
engine-driven pump as follows:
1) Put the HYD PUMPS R ELEC pump switch on the P5 panel to the
DEPRESS position.
2) Let the hydraulic system pressure decrease.
3) Make sure the engine-driven pump PRESS indicator light
comes on.
4) Put the HYD PUMPS R ENG pump switch on the P5 panel to the
ON position.
5) Make sure the HYD PRESS is 3000 |150 psi.
6) Make sure the engine-driven pump PRESS indicator light goes
off.
S 715-265-P00
Examine the Integrated Drive Generator (IDG)
(a) Put the applicable L(R) GEN CONT switch on the P5 panel to the
ON position.
(b) Make sure the LOAD is divided between the APU GEN and the
applicable L(R) IDG.
(c) Put the applicable L(R) GEN CONT switch on the P5 panel to the
OFF position.
(d) Make sure the LOAD moves to the APU GEN.
S 715-266-P00
Examine the Pressure Regulating and Shutoff Valve (PRSOV)
(a) On the P5 panel, put the items that follow in the specified
position:
1) APU Valve - closed (flowbar is off)
2) BLEED AIR L(R) ENG Valve - open (flowbar is on)
3) ISOLATION VALVE - closed (flowbar is off)
4) Air Conditioning L(R) PACK selector switch - AUTO
5) L(R) RECIRC FAN - ON
6) L(R) Temp Select Switch - AUTO
7) TRIM AIR Valve - ON
(b) Push the PERF/APU display select switch on the P61 panel.
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TEST NO. 12 - REPLACEMENT ENGINE TEST (PRE-TESTED)
__________________________________________________
(c)
(d)
(5)
Make sure the applicable L(R) DUCT PR shows 14 |1 psi.
On the P5 panel, put the items that follow in the specified
position:
1) TRIM AIR VALVE - OFF
2) L(R) Temp Select Switch - OFF
3) L(R) RECIRC FAN - OFF
4) Air Conditioning L(R) PACK Selector Switch - OFF
5) BLEED AIR L(R) ENG Valve - closed (flowbar is off)
6) APU Valve - open (flowbar is on)
S 735-267-P00
Do the snap ACCEL check.
(a) With the applicable trim check table (AMM 71-01-02/201), find
the targets that follow for the local conditions of the
weather:
1) MIN IDLE %N2
2) APP IDLE %N2
3) TAKEOFF (EPR)
4) 95% TAKEOFF THRUST (EPR)
(b) Push the EPCS display select switch on the P61 panel.
1) Make sure the white box is around the PRI.
(c) Push the PERF/APU display select switch on the P61 panel.
(d) Pull the THRUST REF SET switch on forward electronics panel,
P9.
(e) Set the REF EPR target bug on the EICAS to the 95% TAKEOFF
THRUST (EPR) target.
1) Do not push in the THRUST REF SET switch.
(f) To prevent the activation of the probe heaters, open the
circuit breakers that follow:
1) Open these circuit breakers on the main power distribution
panel, P6, and attach DO-NOT-CLOSE tags:
a) 6L15, PITOT HEAT CAPT MAIN
b) 6L16, PITOT HEAT L AUX
c) 6L17, L AOA HEAT
d) 6L21, PITOT HEAT R AUX
e) 6L22, PITOT HEAT F/O MAIN
f) 6L23, R AOA HEAT
g) 6L24, TAT PROBE HEAT
2) Open these circuit breakers on the right miscellaneous
electrical equipment panel, P37, and attach DO-NOT-CLOSE
tags:
a) 37F4, HEAT F/O AUX HI
b) 37F7, HEATER DRAIN INST AIR
3) Open this circuit breaker on the miscellaneous electrical
equipment panel, P70, and attach DO-NOT-CLOSE tag:
a) 70A6, CAPT AUX HTR HI
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TEST NO. 12 - REPLACEMENT ENGINE TEST (PRE-TESTED)
__________________________________________________
(g)
(h)
(i)
(j)
(k)
For the left engine, open this circuit breaker on the overhead
circuit breaker panel, P11, in sequence and attach DO-NOT-CLOSE
tag:
1) 11C14, FSEU 2 PWR
2) 11S15, AIR/GND SYS 1
3) 11C30, LANDING GEAR POS SYS 1
For the right engine, open this circuit breaker on the overhead
circuit breaker panel, P11, in sequence and attach DO-NOT-CLOSE
tag:
1) 11G21, FSEU 3 PWR
2) 11S19, AIR/GND SYS 2
3) 11S23, LANDING GEAR POS SYS 2
4) ILF 501 POST-SB 78-28 AND ILF 502-999;
11C19, LANDING GEAR POS SYS 2 ALTN
Make sure the engine speed increases to the APP IDLE %N2
target.
Permit the engine to become stable at approach idle for 60
seconds.
Quickly move the thrust lever forward to increase the speed of
the engine and measure the time as follows:
1) In less than one second, move the applicable thrust lever
to the full forward position.
CAUTION:
_______
2)
YOU MUST RETARD THE POWER LEVERS BEFORE THE EGT IS
MORE THAN THE MAXIMUM EGT. THE EEC ONLY HAS A LIMIT
ON THE EPR AND THE ENGINE SPEED. THE EEC DOES NOT
PREVENT THE OVERTEMPERATURE AND DOES NOT HAVE A LIMIT
FOR THE TEMPERATURE (EGT). THE DETERIORATION OF THE
ENGINE OR BLEED SYSTEM CAN CAUSE AN EGT WHICH IS MORE
THAN THE MAXIMUM EGT BEFORE THE EPR (OR ROTOR SPEED)
DECREASES. IF YOU DO NOT RETARD THE POWER LEVERS,
YOU CAN CAUSE DAMAGE TO THE ENGINE.
Measure the time of acceleration from approach idle to the
95% TAKEOFF THRUST (EPR) target.
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TEST NO. 12 - REPLACEMENT ENGINE TEST (PRE-TESTED)
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3)
4)
(l)
(m)
(n)
(o)
(p)
Make sure the acceleration time is 5.8 seconds or less.
Make sure the engine does not go above the TAKEOFF (EPR)
target.
5) Permit the engine to become stable for 15-20 seconds.
Push the EVENT RECORD switch on the forward electronics panel
P9 to make a record of the engine conditions.
For the left engine, remove the DO-NOT-CLOSE tag and close this
circuit breaker on the P11 panel:
1) 11C14, FSEU 2 PWR
2) 11S15, AIR/GND SYS 1
3) 11C30, LANDING GEAR POS SYS 1
For the right engine, remove the DO-NOT-CLOSE tag and close
this circuit breaker on the P11 panel:
1) 11G21, FSEU 3 PWR
2) 11S19, AIR/GND SYS 2
3) 11S23, LANDING GEAR POS SYS 2
4) ILF 501 POST-SB 78-28 AND ILF 502-999;
11C19, LANDING GEAR POS SYS 2 ALTN
Move the thrust lever rearward to the minimum idle stop.
1) Make sure the engine becomes stable at the MIN IDLE (%N2)
target.
Close the circuit breakers for the probe heaters.
1) Remove the DO-NOT-CLOSE tags and close these circuit
breakers on the P6 panel:
a) 6L15, PITOT HEAT CAPT MAIN
b) 6L16, PITOT HEAT L AUX
c) 6L17, L AOA HEAT
d) 6L21, PITOT HEAT R AUX
e) 6L22, PITOT HEAT F/O MAIN
f) 6L23, R AOA HEAT
g) 6L24, TAT PROBE HEAT
2) Remove the DO-NOT-CLOSE tags and close these circuit
breakers on the P37 panel:
a) 37F4, HEATER F/O AUX HI
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TEST NO. 12 - REPLACEMENT ENGINE TEST (PRE-TESTED)
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b) 37F7, HEATER DRAIN MST AIR
Remove the DO-NOT-CLOSE tag and close this circuit breaker
on the P70 panel:
a) 70A6, CAPT AUX HTR HI
Push in the THRUST REF SET switch on the P9 panel.
3)
(q)
(6)
S 735-268-P00
Do the thrust reverser check.
(a) Slowly move the thrust reverser lever to the DEPLOY position.
(b) Make sure the REV indication shows on the top EICAS display.
(c) Make a record of the time the REV indication is amber in color.
NOTE:
____
The amber REV indication shows when the thrust
reverser moves. When the green REV indication shows,
the thrust reverser is fully deployed.
1)
(d)
(e)
(f)
(g)
(7)
Make sure the amber REV indication is not on for more than
2.0 seconds.
Make sure the RVA on the EPCS page reads 100% |2%.
Slowly move the thrust reverser lever to the stow position.
Make sure the REV indication changes from green to amber in
color (the thrust reverser has movement).
1) Make sure the REV indication goes off from the top EICAS
display.
2) Make a record of the time the REV indication is amber in
color.
3) Make sure the amber REV indication is not on for more than
5.0 seconds.
Make sure the RVA reads 0 |2%.
S 215-269-P00
Look at the ECS/MSG and EPCS pages on the bottom EICAS display for
messages.
(a) If messages show, do the corrections which are necessary for
the applicable message.
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TEST NO. 12 - REPLACEMENT ENGINE TEST (PRE-TESTED)
__________________________________________________
(8)
S 735-270-P00
Do the IDG disconnect check.
CAUTION:
_______
DO NOT OPERATE THE GEN DRIVE DISC SWITCH FOR MORE THAN
THREE SECONDS. PERMIT A MINIMUM OF 60 SECONDS BETWEEN
OPERATIONS.
CAUTION:
_______
DO NOT OPERATE THE GEN DRIVE DISC SWITCH UNLESS THE ENGINE
IS AT OR ABOVE IDLE N2 RPM. DO NOT DISCONNECT THE IDG
WITH THE ENGINE BELOW IDLE. THIS CAN CAUSE DAMAGE TO THE
DISCONNECT DOG TEETH.
(a)
I.
While you operate the engine at the minimum idle N2 RPM or
more, push the applicable L(R) GEN DRIVE DISC switch on the P5
panel.
1) Make sure the applicable L(R) DRIVE light and L(R) GEN CONT
OFF lights go on to make sure the IDG is disconnected.
(b) Use the Power Plant Operation (Normal) procedure to do the
engine shutdown (AMM 71-00-00/201).
(c) Use the APU Operation procedure to do the APU shutdown
(AMM 49-11-00/201).
Do the post-engine operation checks.
(1)
S 015-271-P00
Open the fan cowl panels (AMM 71-11-04/201).
S 045-272-P00
WARNING:
_______
(2)
(3)
DO THE THRUST REVERSER DEACTIVATION PROCEDURE TO PREVENT THE
OPERATION OF THE THRUST REVERSER. THE ACCIDENTAL OPERATION OF
THE THRUST REVERSER CAN CAUSE INJURY TO PERSONS OR DAMAGE TO
EQUIPMENT.
Do this procedure: Thrust Reverser Deactivation for Ground
Maintenance (AMM 78-31-00/201).
S 015-273-P00
Open the core cowl panels (AMM 71-11-06/201).
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TEST NO. 12 - REPLACEMENT ENGINE TEST (PRE-TESTED)
__________________________________________________
S 015-373-P00
WARNING:
_______
OBEY THE INSTRUCTIONS IN THE PROCEDURE WHEN YOU OPEN THE THRUST
REVERSERS. IF YOU DO NOT OBEY THE INSTRUCTIONS, INJURY TO
PERSONS AND DAMAGE TO EQUIPMENT COULD OCCUR.
(4)
Open the thrust reversers (AMM 78-31-00/201).
(5)
S 215-275-P00
Make sure the N2 rotor is stopped.
(6)
S 865-276-P00
Pull out the IDG disconnect reset ring until you feel the solenoid
pin go into position (Fig. 502).
S 415-374-P00
WARNING:
_______
OBEY THE INSTRUCTIONS IN THE PROCEDURE WHEN YOU CLOSE THE
THRUST REVERSERS. IF YOU DO NOT OBEY THE INSTRUCTIONS, INJURY
TO PERSONS AND DAMAGE TO EQUIPMENT COULD OCCUR.
(7)
Close the thrust reversers (AMM 78-31-00/201).
(8)
S 415-278-P00
Close the core cowl panels (AMM 71-11-06/201).
(9)
S 415-279-P00
Close the fan cowl panels (AMM 71-11-04/201).
S 445-280-P00
(10) Do the activation procedure for the thrust reversers
(AMM 78-31-00/201).
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TEST NO. 13 - INTERCOMPRESSOR 2.5 BLEED ACTUATOR TEST
_____________________________________________________
TASK 71-00-00-735-281-P00
18. Test
_____________________________________________________
No. 13 - Intercompressor 2.5 Bleed Actuator Test
A. General
(1) This test examines the operation of the intercompressor 2.5 bleed
actuator.
B. References
(1) AMM 71-00-00/201, Power Plant - General
(2) AMM 71-01-02/201, Power Plant (Trim Check Tables)
(3) AMM 71-11-04/201, Fan Cowl Panels
(4) AMM 71-11-06/201, Core Cowl Panels
(5) AMM 78-31-00/201, Thrust Reverser System
C. Access
(1) Location Zones
211/212
Flight Compartment
411/421
Engine
D.
Do the Intercompressor 2.5 Bleed Actuator Check.
S 865-282-P00
WARNING:
_______
(1)
(2)
USE AMM 71-00-00/201 TO OPERATE THE POWER PLANT. IF YOU DO NOT
USE THIS PROCEDURE, YOU CAN CAUSE DAMAGE TO EQUIPMENT OR INJURY
TO PERSONS.
Use the Power Plant Operation (Normal) procedure to start the engine
(AMM 71-00-00/201).
(a) Permit the engine to become stable at idle for five minutes.
S 215-283-P00
Look at the EPCS page for the messages shown below, and do the
necessary corrections for the messages that you find.
(a) P(S) 2.5 BLEED/EEC
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TEST NO. 13 - INTERCOMPRESSOR 2.5 BLEED ACTUATOR TEST
_____________________________________________________
(b)
(c)
(3)
P(S) T2 OR ADC/EEC
T2 OR TAT
S 215-454-P00
Push the EPCS display select switch on the P61 panel and make sure
the BVA is 100 |10%.
NOTE:
____
If the BVA is not 100 |10%, it may not be adjusted correctly.
(4)
S 865-468-P00
Increase the engine power to 1.35 EPR and let it become stable for a
minimum of 10 seconds.
(5)
S 215-469-P00
Push the EPCS display select switch on the P61 panel and make sure
the BVA is 0 |2%.
NOTE:
____
(6)
(7)
(8)
If the BVA is not 0 |2%, it may not be adjusted correctly.
S 215-471-P00
Look at the EPCS page for the message shown below, and do the
necessary corrective action if you find the message.
(a) P(S) 2.5 BLEED/EEC
S 865-285-P00
Use the Power Plant Operation (Normal) to do the engine shutdown
(AMM 71-00-00/201).
S 015-286-P00
Open the fan cowl panels (AMM 71-11-04/201).
S 045-287-P00
WARNING:
_______
(9)
DO THE THRUST REVERSER DEACTIVATION PROCEDURE TO PREVENT THE
OPERATION OF THE THRUST REVERSER. THE ACCIDENTAL OPERATION OF
THE THRUST REVERSER CAN CAUSE INJURY TO PERSONS OR DAMAGE TO
EQUIPMENT.
Do this procedure: Thrust Reverser Deactivation for Ground
Maintenance (AMM 78-31-00/201).
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TEST NO. 13 - INTERCOMPRESSOR 2.5 BLEED ACTUATOR TEST
_____________________________________________________
S 015-288-P00
(10) Open the core cowl panels (AMM 71-11-06/201).
S 015-289-P00
WARNING:
_______
OBEY THE INSTRUCTIONS IN AMM 78-31-00 WHEN YOU OPEN THE THRUST
REVERSERS. IF YOU DO NOT OBEY THE INSTRUCTIONS, INJURY TO
PERSONS OR DAMAGE TO EQUIPMENT COULD OCCUR.
(11) Open the thrust reversers (AMM 78-31-00/201).
S 215-290-P00
(12) Examine the engine for leaks.
(a) If you find a leak, repair the leak.
S 415-291-P00
WARNING:
_______
OBEY THE INSTRUCTIONS IN AMM 78-31-00 WHEN YOU CLOSE THE THRUST
REVERSERS. IF YOU DO NOT OBEY THE INSTRUCTIONS, INJURY TO
PERSONS OR DAMAGE TO EQUIPMENT COULD OCCUR.
(13) Close the thrust reversers (AMM 78-31-00/201).
S 415-292-P00
(14) Close the core cowl panels (AMM 71-11-06/201).
S 415-293-P00
(15) Close the fan cowl panels (AMM 71-11-04/201).
S 445-294-P00
(16) Do the activation procedure for the thrust reversers
(AMM 78-31-00/201).
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TEST NO. 14 - STATOR VANE ACTUATOR TEST
_______________________________________
TASK 71-00-00-735-295-P00
19. Test
_______________________________________
No. 14 - Stator Vane Actuator Test
A. General
(1) This test examines the operation of the Stator Vane Actuator (SVA).
The SVA travels full stroke during engine start-up and shut-down.
The Electronic Engine Control (EEC) has test logic in place to check
the stroke and feedback signal from the SVA.
B. References
(1) AMM 49-11-00/201, Pneumatics - General
(2) AMM 49-11-00/201, Auxiliary Power Unit
(3) AMM 71-00-00/201, Power Plant - General
(4) AMM 71-01-02/201, Power Plant (Trim Check Tables)
(5) AMM 71-11-04/201, Fan Cowl Panels
(6) AMM 71-11-06/201, Core Cowl Panels
(7) AMM 78-31-00/201, Thrust Reverser System
C. Access
(1) Location Zones
211/212
Flight Compartment
411/421
Engine
D.
Do the Stator Vane Actuator checks.
S 865-296-P00
WARNING:
_______
(1)
USE AMM 71-00-00/201 TO OPERATE THE POWER PLANT. IF YOU DO NOT
USE THIS PROCEDURE, YOU CAN CAUSE DAMAGE TO EQUIPMENT OR INJURY
TO PERSONS.
Use the Power Plant Operation (Normal) procedure to start the engine
(AMM 71-00-00/201).
S 865-297-P00
CAUTION:
_______
(2)
(3)
MAKE SURE TO START THE OTHER ENGINE OR THE APU. TO PREPARE FOR
AN EMERGENCY ENGINE SHUTDOWN, YOU MUST OPERATE THE OTHER ENGINE
OR THE APU FOR PNEUMATIC POWER. IF THE PNEUMATIC POWER IS NOT
AVAILABLE DURING AN EMERGENCY ENGINE SHUTDOWN, YOU CAN CAUSE
DAMAGE TO THE ENGINE.
Use the Power Plant Operation (Normal) procedure to start the other
engine (AMM 71-00-00/201) or do the APU Operation
(AMM 49-11-00/201).
S 865-298-P00
Remove pneumatic ground power, if it is supplied (AMM 36-00-00/201).
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TEST NO. 14 - STATOR VANE ACTUATOR TEST
_______________________________________
(4)
S 865-299-P00
Make sure these systems are in the off position for the engine which
gets this test:
NOTE:
____
(a)
(b)
(c)
(5)
(6)
These systems must be off during the test because the test
limits are for no load and no bleed air conditions.
Engine bleed air
Engine and wing anti-ice unless it is necessary
Integrated Drive Generator (IDG)
S 865-300-P00
If you do the test in frozen conditions, supply air to the nacelle
anti-ice system for the engine of this test as follows:
(a) If the two engines are in operation, put the valves that follow
in the specified position:
1) PRSOV for the engine which the test is done on - closed
2) PRSOV for the other engine - open
3) Isolation Valve - open
4) Nacelle anti-ice valves for the two engines - open
(b) If the APU is in operation, put the valves that follow in the
specified position:
1) PRSOV for the engine which the test is done on - closed
2) APU Valve - open
3) Isolation Valve - open, if the test is done on the right
engine - closed, if the test is done on the left engine
4) Nacelle anti-ice valve - open
S 865-301-P00
To prevent the activation of probe heaters, open these circuit
breakers that follow:
(a) Open these circuit breakers on the main power distribution
panel, P6, and attach DO-NOT-CLOSE tags:
1) 6L15, PITOT HEAT CAPT MAIN
2) 6L16, PITOT HEAT L AUX
3) 6L17, L AOA HEAT
4) 6L21, PITOT HEAT R AUX
5) 6L22, PITOT HEAT F/O MAIN
6) 6L23, R AOA HEAT
7) 6L24, TAT PROBE HEAT
(b) Open these circuit breakers on the right miscellaneous
electrical equipment panel, P37, and attach DO-NOT-CLOSE tags:
1) 37F4, HEATER F/O AUX HI
2) 37F7, HEATER DRAIN MST AIR
(c) Open this circuit breaker on the miscellaneous equipment panel,
P70, and attach DO-NOT-CLOSE tag:
1) 70A6, CAPT AUX HTR HI
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TEST NO. 14 - STATOR VANE ACTUATOR TEST
_______________________________________
(7)
(8)
(9)
S 735-303-P00
With the applicable trim check table (AMM 71-01-02/201), find the
targets that follow for the local conditions of the weather:
(a) MIN IDLE %N2
S 865-312-P00
Close the circuit breakers for the probe heaters.
(a) Remove the DO-NOT-CLOSE tags and close this circuit breaker on
the P6 panel:
1) 6L15, PITOT HEAT CAPT MAIN
2) 6L16, PITOT HEAT L AUX
3) 6L17, L AOA HEAT
4) 6L21, PITOT HEAT R AUX
5) 6L22, PITOT HEAT F/O MAIN
6) 6L23, R AOA HEAT
7) 6L24, TAT PROBE HEAT
(b) Remove the DO-NOT-CLOSE tags and close these circuit breakers
on the P37 panel:
1) 37F4, HEATER F/O AUX HI
2) 37F7, HEATER DRAIN MST AIR
(c) Remove the DO-NOT-CLOSE tag and close this circuit breaker on
the P70 panel:
1) 70A6, CAPT AUX HTR HI
S 865-316-P00
Use the Power Plant Operation (Normal) procedure to do the engine
shutdown (AMM 71-00-00/201).
S 865-317-P00
(10) If the other engine was operated, use the Power Plant Operation
(Normal) procedure to do the engine shutdown (AMM 71-00-00/201).
S 865-318-P00
(11) If the APU was operated, use the APU Operation procedure to do the
APU shutdown (AMM 49-11-00/201).
S 985-380-P00
(12) Push the EPCS display select switch on the P61 panel.
(a) Make sure there are no EPCS messages displayed.
(b) If any EPCS messages are displayed preform the corrective
action indicated.
S 015-319-P00
(13) Open the fan cowl panels (AMM 71-11-04/201).
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TEST NO. 14 - STATOR VANE ACTUATOR TEST
_______________________________________
S 045-320-P00
WARNING:
_______
DO THE THRUST REVERSER DEACTIVATION PROCEDURE TO PREVENT THE
OPERATION OF THE THRUST REVERSER. THE ACCIDENTAL OPERATION OF
THE THRUST REVERSER CAN CAUSE INJURY TO PERSONS OR DAMAGE TO
EQUIPMENT.
(14) Do this procedure: Thrust Reverser Deactivation for Ground
Maintenance (AMM 78-31-00/201).
S 015-321-P00
(15) Open the core cowl panels (AMM 71-11-06/201).
S 015-322-P00
WARNING:
_______
OBEY THE INSTRUCTIONS IN AMM 78-31-00 WHEN YOU OPEN THE THRUST
REVERSERS. IF YOU DO NOT OBEY THE INSTRUCTIONS, INJURY TO
PERSONS OR DAMAGE TO EQUIPMENT COULD OCCUR.
(16) Open the thrust reversers (AMM 78-31-00/201).
S 215-323-P00
(17) Examine the engine for leaks.
(a) If you find a leak, repair the leak.
S 415-324-P00
WARNING:
_______
OBEY THE INSTRUCTIONS IN AMM 78-31-00 WHEN YOU CLOSE THE THRUST
REVERSERS. IF YOU DO NOT OBEY THE INSTRUCTIONS, INJURY TO
PERSONS OR DAMAGE TO EQUIPMENT COULD OCCUR.
(18) Close the thrust reversers (AMM 78-31-00/201).
S 415-325-P00
(19) Close the core cowl panels (AMM 71-11-06/201).
S 415-326-P00
(20) Close the fan cowl panels (AMM 71-11-04/201).
S 445-327-P00
(21) Do the activation procedure for the thrust reversers
(AMM 78-31-00/201).
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TEST NO. 15 - FUEL CONTROL REPLACEMENT TEST
___________________________________________
TASK 71-00-00-735-328-P00
20. Test
___________________________________________
No. 15 - Fuel Control Replacement Test
A. General
(1) This test examines the installation of the fuel control with a wet
motor leak check and an acceleration check measured in time.
B. References
(1) AMM 71-00-00/201, Power Plant - General
(2) AMM 71-01-02/201, Power Plant (Trim Check Tables)
(3) AMM 71-11-04/201, Fan Cowl Panels
(4) AMM 71-11-06/201, Core Cowl Panels
(5) AMM 78-31-00/201, Thrust Reverser System
C. Access
(1) Location Zones
211/212
Flight Compartment
411/421
Engine
D.
Do the Test of the Fuel Control Replacement
(1)
S 015-329-P00
Open the fan cowl panels (AMM 71-11-04/201).
S 045-330-P00
WARNING:
_______
(2)
(3)
DO THE THRUST REVERSER DEACTIVATION PROCEDURE TO PREVENT THE
OPERATION OF THE THRUST REVERSER. THE ACCIDENTAL OPERATION OF
THE THRUST REVERSER CAN CAUSE INJURY TO PERSONS OR DAMAGE TO
EQUIPMENT.
Do this procedure: Thrust Reverser Deactivation for Ground
Maintenance (AMM 78-31-00/201).
S 015-331-P00
Open the core cowl panels (AMM 71-11-06/201).
S 015-375-P00
WARNING:
_______
OBEY THE INSTRUCTIONS IN AMM 78-31-00 WHEN YOU OPEN THE
THRUST REVERSERS. IF YOU DO NOT OBEY THE INSTRUCTIONS,
INJURY TO PERSONS OR DAMAGE TO EQUIPMENT COULD OCCUR.
(4)
Open the thrust reversers (AMM 78-31-00/201).
(5)
S 865-333-P00
Use the Power Plant Wet-Motor procedure to motor the engine
(AMM 71-00-00/201).
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TEST NO. 15 - FUEL CONTROL REPLACEMENT TEST
___________________________________________
(6)
S 215-334-P00
Examine the engine for leaks.
(a) If you find a leak, repair the leak.
(b) After you repair the leaks, examine the engine again.
S 415-335-P00
WARNING:
_______
OBEY THE INSTRUCTIONS IN AMM 78-31-00 WHEN YOU CLOSE THE THRUST
REVERSERS. IF YOU DO NOT OBEY THE INSTRUCTIONS, INJURY TO
PERSONS OR DAMAGE TO EQUIPMENT COULD OCCUR.
(7)
Close the thrust reversers (AMM 78-31-00/201).
(8)
S 415-336-P00
Close the core cowl panels (AMM 71-11-06/201).
(9)
S 415-337-P00
Close the fan cowl panels (AMM 71-11-04/201).
S 445-338-P00
(10) Do the activation procedure for the thrust reversers
(AMM 78-31-00/201).
S 865-339-P00
WARNING:
_______
USE AMM 71-00-00/201 TO OPERATE THE POWER PLANT. IF YOU DO NOT
USE THIS PROCEDURE, YOU CAN CAUSE DAMAGE TO EQUIPMENT OR INJURY
TO PERSONS.
(11) Use the Power Plant Operation (Normal) procedure to start the engine
(AMM 71-00-00/201).
S 735-340-P00
(12) With the applicable trim check table (AMM 71-01-02/201), find the
targets that follow for the local ambient conditions:
(a) MIN IDLE %N2
(b) APP IDLE %N2
(c) TAKEOFF (EPR)
(d) 95% TAKEOFF THRUST (EPR)
(e) 90% THRUST CHANGE DECEL (EPR)
S 865-341-P00
(13) To prevent the activation of probe heaters, open these circuit
breakers that follow:
(a) Open these circuit breakers on the main power distribution
panel, P6, and attach DO-NOT-CLOSE tags:
1) 6L15, PITOT HEAT CAPT MAIN
2) 6L16, PITOT HEAT L AUX
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TEST NO. 15 - FUEL CONTROL REPLACEMENT TEST
___________________________________________
(b)
(c)
3) 6L17, L AOA HEAT
4) 6L21, PITOT HEAT R AUX
5) 6L22, PITOT HEAT F/O MAIN
6) 6L23, R AOA HEAT
7) 6L24, TAT PROBE HEAT
Open these circuit breakers on the right miscellaneous
electrical equipment panel, P37, and attach DO-NOT-CLOSE tags:
1) 37F4, HEATER F/O AUX HI
2) 37F7, HEATER DRAIN MST AIR
Open this circuit breaker on the miscellaneous equipment panel,
P70, and attach DO-NOT-CLOSE tag:
1) 70A6, CAPT AUX HTR HI
S 865-343-P00
(14) Pull the THRUST REF SET switch on the forward electronics panel, P9.
S 865-344-P00
(15) Set the REF EPR target bug on the EICAS to 95% TAKEOFF THRUST (EPR)
target.
(a) Do not push in the THRUST REF SET switch.
S 865-345-P00
(16) For the left engine, open these circuit breakers on the overhead
circuit breaker panel, P11, in sequence and attach DO-NOT-CLOSE
tags:
(a) 11C14, FSEU 2 PWR
(b) 11S15, AIR/GND SYS 1
(c) 11C30, LANDING GEAR POS SYS 1
S 865-346-P00
(17) For the right engine, open these circuit breakers on the overhead
circuit breaker panel, P11, in sequence and attach DO-NOT-CLOSE
tags:
(a) 11G21, FSEU 3 PWR
(b) 11S19, AIR/GND SYS 2
(c) 11S23, LANDING GEAR POS SYS 2
(d) ILF 501 POST-SB 78-28 AND ILF 502-999;
11C19, LANDING GEAR POS SYS 2 ALTN
S 865-347-P00
(18) Permit the engine to become stable at approach idle for 60 seconds.
S 865-348-P00
(19) Quickly move the thrust lever forward to increase the speed of the
engine and measure the time as follows:
(a) In less than one second, move the applicable thrust lever to
the full forward position.
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TEST NO. 15 - FUEL CONTROL REPLACEMENT TEST
___________________________________________
CAUTION:
_______
(b)
(c)
(d)
YOU MUST RETARD THE POWER LEVERS BEFORE THE EGT IS MORE
THAN THE MAXIMUM EGT. THE EEC ONLY HAS A LIMIT ON THE EPR
AND THE ENGINE SPEED. THE EEC DOES NOT PREVENT THE
OVERTEMPERATURE AND DOES NOT HAVE A LIMIT FOR THE
TEMPERATURE (EGT). THE DETERIORATION OF THE ENGINE OR
BLEED SYSTEM CAN CAUSE AN EGT WHICH IS MORE THAN THE
MAXIMUM EGT BEFORE THE EPR (OR ROTOR SPEED) DECREASES. IF
YOU DO NOT RETARD THE POWER LEVERS, YOU CAN CAUSE DAMAGE
TO THE ENGINE.
Measure the time of acceleration from approach idle to the 95%
TAKEOFF THRUST (EPR) target.
Make sure the acceleration time is 5.8 seconds or less.
Make sure the engine does not go above the TAKEOFF (EPR)
target.
S 865-349-P00
(20) For the left engine, remove the DO-NOT-CLOSE tags and close these
circuit breakers on the P11 panel in sequence:
(a) 11S15, AIR/GND SYS 1
(b) 11C14, FSEU 2 PWR
(c) 11C30, LANDING GEAR POS SYS 1
S 865-350-P00
(21) For the right engine, remove the DO-NOT-CLOSE tags and close these
circuit breakers on the P11 panel in sequence:
(a) 11S19, AIR/GND SYS 2
(b) 11G21, FSEU 3 PWR
(c) 11S23, LANDING GEAR POS SYS 2
(d) ILF 501 POST-SB 78-28 AND ILF 502-999;
11C19, LANDING GEAR POS SYS 2 ALTN
S 865-351-P00
(22) Quickly move the thrust lever rearward to decrease the speed of the
engine and measure the time as follows:
(a) In less than one second, move the applicable thrust lever to
the idle position.
(b) Measure the time of deceleration from TAKEOFF (EPR) to the 90%
THRUST CHANGE DECEL (EPR) targets.
1) Make sure the time of deceleration is 7.1 seconds or less.
(c) Make sure the engine becomes stable at the MIN IDLE target.
(d) Look at the ECS/MSG and EPCS pages on the bottom EICAS display
for messages.
1) If messages show, do the corrections which are necessary
for the applicable messages.
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TEST NO. 15 - FUEL CONTROL REPLACEMENT TEST
___________________________________________
S 865-353-P00
(23) Close the circuit breakers for the probe heaters.
(a) Remove the DO-NOT-CLOSE tags and close these circuit breakers
on the P6 panel:
1) 6L15, PITOT HEAT CAPT MAIN
2) 6L16, PITOT HEAT L AUX
3) 6L17, L AOA HEAT
4) 6L21, PITOT HEAT R AUX
5) 6L22, PITOT HEAT F/O MAIN
6) 6L23, R AOA HEAT
7) 6L24, TAT PROBE HEAT
(b) Remove the DO-NOT-CLOSE tags and close these circuit breakers
on the P37 panel:
1) 37F4, HEATER F/O AUX HI
2) 37F7, HEATER DRAIN MST AIR
(c) Remove the DO-NOT-CLOSE tag and close this circuit breaker on
the P70 panel:
1) 70A6, CAPT AUX HTR HI
S 865-354-P00
(24) Push in the THRUST REF SET switch on the P9 panel.
S 865-355-P00
(25) Use the Power Plant Operation (Normal) procedure to do the engine
shutdown (AMM 71-00-00/201).
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TEST NO. 16 - NOT USED
______________________
TASK 71-00-00-835-356-P00
21. Test
______________________
No. 16 - Not Used
A.
General
(1) Not Used.
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TEST NO. 17 - THRUST LEVER ANGLE (TLA) RESOLVER TEST
____________________________________________________
TASK 71-00-00-735-371-P00
22. Test
____________________________________________________
No. 17 - Thrust Lever Angle (TLA) Resolver Test
A. General
(1) This test examines the installation of the TLA Resolver.
B. References
(1) AMM 24-22-00/201, Electrical Power - Control
(2) AMM 76-11-00/501, Engine Control System
C. Do the Thrust Lever Angle Resolver Test
(1)
(2)
(3)
(4)
(5)
(6)
S 865-372-P00
Supply electrical power (AMM 24-22-00/201).
S 865-373-P00
Supply power to the EECs as follows:
(a) For the left engine, make sure this circuit breaker on the
overhead circuit breaker panel, P11, is closed:
1) 11L4, LEFT ENGINE ELECTRONIC ENGINE CONTROL ALTN PWR
(b) For the right engine, make sure this circuit breaker on the
overhead circuit breaker panel, P11, is closed:
1) 11L31, RIGHT ENGINE ELECTRONIC ENGINE CONTROL ALTN PWR
(c) Put the EEC MAINT POWER switch on the P61 panel in the ALTN
position.
S 865-374-P00
Push the EPCS display select switch on the P61 panel.
S 215-375-P00
Look at the EPCS page on the bottom EICAS display for EPCS messages.
(a) If EPCS messages show, do the corrections which are necessary
for the applicable EPCS message.
S 735-376-P00
Examine the TLA resolver rigging as follows:
(a) Make sure the thrust levers touch the idle stops.
(b) Make sure TLR on the EPCS page reads 38 - 40° for
right TLA resolvers.
(c) Move the thrust levers to the full forward thrust
(d) Make sure TLR on the EPCS page reads 80.5 - 82.5°
and right TLA resolvers.
(e) Move the thrust levers back to the idle stops.
(f) If the angles are not in the ranges given, adjust
rods (AMM 76-11-00/501).
the left and
stops.
for the left
the control
S 865-377-P00
Put the EEC MAINT POWER switch on the P61 panel in the NORM
position.
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TEST NO. 17 - THRUST LEVER ANGLE (TLA) RESOLVER TEST
____________________________________________________
(7)
S 865-379-P00
Remove electrical power (AMM 24-22-00/201).
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MAINTENANCE MANUAL
TEST NO. 18 - LOW PRESSURE ROTOR TRIM BALANCE
_____________________________________________
TASK 71-00-00-725-380-P00
23. Test
_____________________________________________
No. 18 - Low Pressure Rotor Trim Balance
A. General
(1) This procedure includes instructions for two procedures which trim
balance the low pressure compressor (LPC) and/or the low pressure
turbine (LPT):
(a) The Sommervaille Trim Balance procedure uses the Endevco
Analyzer (or equivalent) which has three parts:
1) Part one operates the engine to find the quantity and %N1
rpm for the maximum B and P flange vibration.
2) Part two adds a trial weight to some point called 0-degree
point on the fan or turbine plane and operates the engine
to examine the effect. This is done again with the weight
moved to 120- and 240-degree positions, from the 0-degree
position, on the fan.
3) Part three makes two polar graphs of the data from parts
one and two. An estimate is made from the location and the
quantity of the balance weight necessary.
(b) The Phase angle Trim Balance uses the Mechanical Technology
Incorporated PBS 4000/4100 balancing system. This system
automatically calculates the best balance solution.
(2) Trim Balance Limits:
(a) The maximum permitted correction weight added during a single
trim balance is 30 oz-in. (21600 g.-mm). The total vector sum
of all the weights installed is not more than 50 oz-in.
(36000 g.-mm).
1) The maximum permitted vibration levels (one value),
transient or stable condition, at all thrust levels are as
follows:
LOCATION
________
OVERALL (20-220 Hz)
___________________
LOW ROTOR
_________
HP
________
ROTOR *[1]
Fan Case
Flange B
(Vertical)
|0.0020 in.
|0.0015 in.
0-9200 N¿ 1.0 in./sec
9200-T/O .5 in./sec
Turbine
Exhaust Case
Flange P
(Vertical)
|0.0020 in.
|0.0015 in.
Same as "B" Flange
*[1] You cannot correct the HP rotor vibration with the use of this procedure
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MAINTENANCE MANUAL
TEST NO. 18 - LOW PRESSURE ROTOR TRIM BALANCE
_____________________________________________
B.
C.
Equipment
(1) Trim Balance Set - B72001 has the parts that
follow:
(a) B flange Accelerometer Assembly - B72001-3
1) Accelerometer - Endevco model
6222C-100 Endevco, 30700 RANCHO VIEJO
RD., SAN JUAN CAPISTRANO, CA 92675
2) Cable Assembly - Endevco 6917B-1400
3) Accelerometer bracket - B72001-6
(b) P flange Accelerometer Assembly - B72001-4
1) Accelerometer - Endevco model 6233C-50
2) Cable Assembly - Endevco 6917B-1400
3) Hose Assembly - Resistoflex
R50200CC-8-2400 Resistoflex Corp.,
Woodland Rd., Roseland, NJ 07068
4) Accelerometer cooling bracket B72001-7
5) "Y" Adapter - B72001-11
(c) Clamps - QS 100M 20H, Breeze Corp.,
700 Liberty Ave., Union, NJ 07083
(2) Riveter - PWA 81550
(3) Balance Weights - P&W P/N 534495
(4) Balance Weights - P&W P/N 534493
(5) Counterweights - P&W P/N 1B5812
(6) Special Equipment for the Manual Trim Balance
Procedure
(a) Trim Balance Analyzer - Endevco Model
68301-2
(7) Special Equipment for the Automatic Trim
Balance Procedure
(a) PBS 4000/4100 Portable Balancing Unit Mechanical Technology Inc., 968
Albany-Shaker Road, Latham, NY 12110
(b) Engine Data Diskette for PW2000 Series
Engine - Mechanical Technology Inc.
(c) Charge Amplifier System - Mechanical
Technology Inc. part number 40CA-B757,
Mechanical Technology Inc.
1) Charge Amplifier, two are necessary
2) Cable Adapter, two are necessary
3) "Y" Cable Adapter, one is necessary
(d) N1 Signal Breakout Box - B72001-19
(e) Bender, Hydraulic - P&W P/N 82001
(f) Pump, Hydraulic - P&W P/N 76855 (used with PWA 82001)
Consumable Materials
(1) D00137 Engine Oil - PWA 521
(2) Dye, Layout and Identification - PMC 4039
(3) G00144 Lockwire - P&W P/N 586822
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MAINTENANCE MANUAL
TEST NO. 18 - LOW PRESSURE ROTOR TRIM BALANCE
_____________________________________________
D.
E.
References
(1) AMM 71-00-00/201, Power Plant - General
(2) AMM 71-11-04/201, Fan Cowl Panels
(3) AMM 71-11-06/201, Core Cowl Panels
(4) AMM 72-31-01/401, Compressor Inlet Cone
(5) AMM 77-41-01/401, Standby Engine Indicator
(6) AMM 78-11-01/401, Turbine Exhaust Sleeve
(7) AMM 78-11-02/401, Turbine Exhaust Plug
(8) AMM 78-31-00/201, Thrust Reverser System
Access
(1) Location Zones
211
Flight Compartment
212
Flight Compartment
411
L Engine
421
R Engine
(2)
F.
Access Panels
413AL/423AL
414AR/424AR
415AL/425AL
416AR/426AR
417AL/427AL
418AR/428AR
Fan Cowl Panel (Left)
Fan Cowl Panel (Right)
Fan Reverser (Left)
Fan Reverser (Right)
Core Cowl Panel (Left)
Core Cowl Panel (Right)
Manual Trim Balance
(1)
(2)
S 945-376-P00
Names used in the procedure:
(a) VB, VP - Maximum B and P flange vibration before you add the
trial weights.
(b) VB0, VB120, VB240; VP0, VP120, VP240 - Vibration levels at B
and P flanges with the trial weight at 0-, 120-, or 240-degree
fan blade locations.
(c) TB, TP - The result for the B and the P flanges which is not
balanced.
(d) Mo - Moment weight of the added trial weight.
(e) M - Moment weight of the necessary balance weight.
(f) Stable Vibration - All vibrations where the highest value does
not change more than one quarter unit after 30 seconds of
stable engine operation.
S 485-381-P00
Install the Trim Balance Equipment (Fig. 519)
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MAINTENANCE MANUAL
'B' FLANGE
ACCELEROMETER
AND BRACKET
'P' FLANGE
ACCELEROMETER
BRACKET
N1 SIGNAL
BREAKOUT
CABLE
TUBE
DISCONNECT
BRACKET
STARTER VENT
IDG SERVICE
ACCESS DOOR
120 FOOT
ELECTRICAL
CABLE
N1 SIGNAL
ENDEVCO
ANALYZER
PPS
4000/4100
319983
Trim Balance Equipment
Figure 519
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MAINTENANCE MANUAL
TEST NO. 18 - LOW PRESSURE ROTOR TRIM BALANCE
_____________________________________________
WARNING:
_______
(a)
(b)
(c)
Do the deactivation procedure for the thrust reverser for
ground maintenance (AMM 78-31-00/201).
Open the left fan cowl panels (AMM 71-11-04/201).
Open the left core cowl panel (AMM 71-11-06/201).
WARNING:
_______
(d)
(e)
(f)
OBEY THE INSTRUCTIONS IN THE PROCEDURE TO OPEN THE THRUST
REVERSERS. IF YOU DO NOT OBEY THE INSTRUCTIONS, INJURY TO
PERSONS OR DAMAGE TO EQUIPMENT CAN OCCUR.
Open the left thrust reverser (AMM 78-31-00/201).
Install the B flange accelerometer as follows:
1) Remove the bolt and nut from the holes No. 11 and 12 on the
B flange.
a) Keep the bolts and the nuts.
2) Install the B flange accelerometer on the bracket.
3) Install the bracket on the B flange at the empty bolt hole
with the tool bolt and nut.
Install the P flange accelerometer as follows:
1) Remove the bolt and nut from the two adjacent holes on the
P flange nearest to the top as the external equipment will
permit.
a) Keep the nuts and the bolts.
2) Install the P flange accelerometer.
3) Open the starter Vent/IDG service access door on the right
fan cowl panel.
4) Pull a sufficient quantity of electrical cable to the B
flange accelerometer through the opened access door.
5) Connect the electrical cable to the B flange accelerometer
leads.
6) Remove the aft cover from the tube disconnect bracket.
a) Keep the cover, bolts, and nuts.
7) Pull a sufficient quantity of the electrical cable through
the open access door to the P flange accelerometer.
8) Connect the electrical cable to the P flange accelerometer.
WARNING:
_______
(g)
(h)
DO THE DEACTIVATION PROCEDURE TO PREVENT THE OPERATION OF
THE THRUST REVERSER. THE ACCIDENTAL OPERATION OF THE
THRUST REVERSER CAN CAUSE INJURY TO PERSONS OR DAMAGE TO
EQUIPMENT.
OBEY THE INSTRUCTIONS IN THE PROCEDURE TO CLOSE THE THRUST
REVERSERS. IF YOU DO NOT OBEY THE INSTRUCTIONS, INJURY TO
PERSONS OR DAMAGE TO EQUIPMENT CAN OCCUR.
Close the left thrust reversers (AMM 78-31-00/201).
Close the left core cowl panels (AMM 71-11-06/201).
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MAINTENANCE MANUAL
TEST NO. 18 - LOW PRESSURE ROTOR TRIM BALANCE
_____________________________________________
(i)
(j)
(k)
(l)
(m)
(n)
(3)
Do the activation procedure for the thrust reverser
(AMM 78-31-00/201).
Close the left fan cowl panels (AMM 71-11-04/201).
Attach the electrical cables to the starter Vent/IDG service
access door with the tie wraps.
Do the routing of the cables with the steps that follow:
1) Put the cable up the side of the fan cowl and along the top
of the wing.
2) Continue along the wing and put the cable through the
emergency exit door to the cabin equipment.
Connect the electrical cable ends to the Analyzer as it is
shown.
Connect the Analyzer to a 110v 400 Hz power.
S 725-446-P00
Do the Sommervaille Trim Balance procedure for the Fan Plane with
the steps that follow:
WARNING:
_______
(a)
USE AMM 71-00-00/201 TO OPERATE THE POWER PLANT. IF YOU
DO NOT USE THIS PROCEDURE, YOU CAN CAUSE DAMAGE TO
EQUIPMENT OR INJURY TO PERSONS.
Use the Power Plant Operation (Normal) procedure to start the
engine (AMM 71-00-00/201).
1) Permit the engine to become stable at idle for three
minutes.
2) Push the PERF/APU button on the EICAS MAINT panel P61.
3) Make sure the indications of operation are in the limits.
4) Slowly increase the speed of the engine to approximately
1.32 EPR and stabilize for three minutes.
5) Slowly decrease the speed of the engine to idle and
stabilize for six minutes.
NOTE:
____
You must only do a vibration survey or trim balance
survey on a thermally stabilized engine.
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MAINTENANCE MANUAL
TEST NO. 18 - LOW PRESSURE ROTOR TRIM BALANCE
_____________________________________________
6)
(b)
Do a slow increase in engine speed (90-120 seconds) from
idle to takeoff.
7) Record Peak B and Peak P vibration (amplitude and N1 speed)
at takeoff.
8) Decrease the speed of the engine to idle.
9) Operate the engine at idle for five minutes to permit the
engine to become cool.
10) Use the Power Plant Operation (Normal) procedure to do the
engine shutdown (AMM 71-00-00/201).
Install the balance weight as follows:
1) Remove the inlet cone segment of the front compressor
(AMM 72-31-01/401).
2) With a dye, make a mark on the three balance flange
sections at the 0-, 120- and 240-degree positions as 0°,
120° and 240°.
NOTE:
____
3)
There are 5 balance flange sections without
marks between the balance flange sections 0- and
120-, 120- and 240-, and 240- and 0-degree.
4)
Install the 14.9 oz-in. (10728 g.-mm) balance weight (Ref
Balance Weight Class Table) with the cotter pin in the
center on the 0° balance flange section.
Install the inlet cone segment of the front compressor
(AMM 72-31-01/401).
~¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼
¦
TRIM BALANCE WEIGHTS
¦
¦
(Fan balance ring radius is 10.336 inches)
¦
»¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼ ¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼ ¼¼¼¼¼¼¼¼¼¼¼¼¼«
¦
P/N 534495
¦
P/N 534493
¦ P/N 1B4294 ¦
»¼¼¼¼¼¼¼¼¼ ¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼ ¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼«
¦ Class 1 ¦ 3.7 oz-in. ¦ Class 1 ¦ 1.5 oz-in. ¦ 10.0 oz.in.¦
»¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼«
¦ Class 2 ¦ 4.0 oz-in. ¦ Class 2 ¦ 1.7 oz-in. ¦
¦
»¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼«
¦ Class 3 ¦ 4.3 oz-in. ¦ Class 3 ¦ 2.0 oz-in. ¦
¦
»¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼«
¦ Class 4 ¦ 4.6 oz-in. ¦
¦
¦
¦
»¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼«
¦ Class 5 ¦ 4.9 oz-in. ¦
¦
¦
¦
²¼¼¼¼¼¼¼¼¼…¼¼¼¼¼¼¼¼¼¼¼¼…¼¼¼¼¼¼¼¼¼…¼¼¼¼¼¼¼¼¼¼¼¼…¼¼¼¼¼¼¼¼¼¼¼¼¼¹
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MAINTENANCE MANUAL
SEE B
0`
FAN CASE
SEE A
COMPRESSOR
INLET CONE
240`
120`
A
0`
TRIM BALANCE WEIGHT
P/N 534495 CL5
TRIM BALANCE WEIGHT
P/N 1B4294
240`
120`
BALANCE WEIGHT INSTALLATION
BALANCE FLANGE MARKING
METHOD 1
B
319984
Balance Weight Installation
Figure 520
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MAINTENANCE MANUAL
TEST NO. 18 - LOW PRESSURE ROTOR TRIM BALANCE
_____________________________________________
WARNING:
_______
5)
6)
7)
Use the Power Plant Operation (Normal) procedure to start
the engine (AMM 71-00-00/201).
Permit the engine to become stable at idle for three
minutes.
Make sure the indications of operation are in the limits.
NOTE:
____
8)
10)
11)
12)
13)
14)
A higher vibration can occur at a different %N1 rpm.
You must measure the vibration data used to find the
balance weight at the same %N1 rpm at which the
AS-IS data was taken.
Slowly increase the speed of the engine to approximately
1.32 EPR and stabilize for three minutes.
NOTE:
____
9)
USE AMM 71-00-00/201 TO OPERATE THE POWER PLANT. IF
DO NOT USE THIS PROCEDURE, YOU CAN CAUSE DAMAGE TO
EQUIPMENT OR INJURY TO PERSONS.
You must only do a vibration survey or trim balance
survey on a thermally stabilized engine.
Slowly decrease the speed of the engine to idle and
stabilize for six minutes.
Do a slow increase in engine speed to the same N1 speeds
taken during the AS-IS (No weights installed).
Record Peak B and Peak P vibration (amplitude and N1
speed).
Decrease the speed of the engine to operate at minimum
power.
Operate the engine at minimum power for five minutes to
permit the engine to become cool.
Use the Power Plant Operation (Normal) procedure to do the
engine shutdown (AMM 71-00-00/201).
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MAINTENANCE MANUAL
TEST NO. 18 - LOW PRESSURE ROTOR TRIM BALANCE
_____________________________________________
(c)
15) Use Method 1, 2 or 3 to move the weight from the 0-degree
to the 120-degree position.
16) Measure the vibration level VB120 and VP120 at %N1 rpm used
for VB and VP.
17) Make a record of the vibration levels VB120 and VP120.
18) Use Method 1, 2 or 3 to move the weight from the 120-degree
to the 240-degree position.
19) Measure the vibration level VB240 and VP240 at %N1 rpm used
for VB and VP.
Find the location and quantity of the balance moment necessary
as follows (Part 3):
NOTE:
____
1)
2)
3)
4)
5)
6)
7)
8)
9)
There is no accurate procedure to find the location
or quantity of the balance moment. The steps that
follow are given to supply a point to start. If the
results are not satisfactory from the first trial, you
must do more trial and error adjustments.
On a piece of polar graph paper, make a circle at the
center with a radius the same as VB (Fig. 521).
a) Identify the circle with the label VB.
Identify the points where the 0-, 120-, and 240-degree
lines go across the circle.
Make a circle with a radius the same as VBO with the center
at the intersection of the 0-degree line and the circle VB.
a) Identify the circle with the label VB0.
Make a circle with the radius the same as VB120 with the
center at the intersection of the 120-degree line and the
circle VB.
a) Identify the circle with the label VB120.
Make a circle with the radius the same as VB240 with the
center at the intersection of the 240-degree line and the
circle VB.
a) Identify the circle with the label VB240.
Make a line from the center of the graph to the center of
the triangle made by the circles VBO, VB120, and VB240.
a) Identify the line with the label TB.
Measure the length of the line TB.
a) Make a record of the length of the line TB.
Do the steps again to find TP for the P flange.
a) Identify the data with the labels VP, VP0, VP120, VP240
and TP.
Compare the direction of the lines TB and TP.
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MAINTENANCE MANUAL
210`
150`
200`
160`
190`
170`
170`
190`
180`
160`
200`
150`
210`
220`
140`
140`
220`
230`
130`
130`
230`
240`
120`
120`
240`
VB120
VB240
250`
110`
110`
250`
260`
100`
100`
260`
270`
90`
90`
270`
VB
.1
.2
.3
.4
.5
.6
TB = .15
80`
280`
.7
80`
280`
290`
70`
70`
290`
VBO
300`
60`
BALANCE MOMENT REQUIRED: MB =
310`
50`
60`
300`
MoVB
____
TB
50`
310`
FOR THIS EXAMPLE: Mo = 15 OZ. IN.
VB = .25 (AS - IS)
TB = .15 (MEASURED FROM
VECTOR ABOVE)
MB =
320`
40`
330`
30`
340`
20`
(15)(.25)
_________
.15
= 25 OZ.IN. (LOCATED AT 0 DEGREES)
350`
10`
0
10`
350`
40`
320`
20`
340`
30`
330`
319985
Fan and Low Pressure Compressor Trim Balance
Figure 521
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MAINTENANCE MANUAL
TEST NO. 18 - LOW PRESSURE ROTOR TRIM BALANCE
_____________________________________________
10) If the lines TB and TP are less than 90-degrees apart, find
the quantity and direction of the balance moment as
follows:
a) Calculate the quantity as follows:
M =
MB+MP
----2
Where MB = MO x VB and MP = MO x VP
------------TB
TP
11) Identify the
lines TB and
12) If the lines
the quantity
NOTE:
____
a)
direction with half of the angle between the
TP.
TB and TP are more than 90-degrees apart, find
and direction as follows:
If the lines TB and TP are more than 90-degrees
apart, you can only decrease one of the two
vibration levels VB or VP. And it is possible the
other will increase. The result is best if you
decrease the larger vibration below the limits. But
do not cause the smaller vibration to increase more
than the limits. The vibration level for the B
flange is more sensitive than the P flange vibration
level when the weight is added.
Calculate the quantity as follows:
M = 1/2 MB if MB is more than MP
M = 1/2 MP if MP is more than MB
Where MB = MO x VB and MP = MO x VP
------------TB
TP
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MAINTENANCE MANUAL
TEST NO. 18 - LOW PRESSURE ROTOR TRIM BALANCE
_____________________________________________
b)
(d)
Give the direction of the balance moment M.
1
_
The balance moment M is between lines TB and TP and
1/4 rotation from the larger to the smaller.
Install the balance weights.
1) With the Balance Weight Class Table, find the weights
necessary to supply the balance moment M.
2) Remove the inlet cone segment of the front compressor
(AMM 72-31-01/401).
3) With a riveter, attach the weights to the flange section
nearest the specified direction.
NOTE:
____
If the lines TB and TP are less than 90-degrees
apart, move the balance weight to the higher
quantity line. If the lines TB and TP are more than
90 degrees apart, move the balance weight to the
lower quantity line.
a)
(e)
Flare the rivet(s) to 0.125 inch (3.175 mm) in
diameter.
4) Install the inlet cone segment of the front compressor
(AMM 72-31-01/401).
Examine the vibration levels of the engine.
WARNING:
_______
1)
2)
3)
4)
5)
Use the Power Plant Operation (Normal) procedure to start
the engine (AMM 71-00-00/201).
Permit the engine to become stable for three minutes.
Make sure the indications of operation are in the limits.
Slowly increase the speed of the engine to approximately
1.32 EPR and stabilize for 3 minutes.
Slowly decrease the speed of the engine to idle and
stabilize for 6 minutes.
NOTE:
____
6)
USE AMM 71-00-00/201 TO OPERATE THE POWER PLANT. IF
YOU DO NOT USE THIS PROCEDURE, YOU CAN CAUSE DAMAGE
TO EQUIPMENT OR INJURY TO PERSONS.
You must only do a vibration survey or trim balance
survey on a thermally stabilized engine.
Do the vibration survey as shown in Engine Test No. 8.
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MAINTENANCE MANUAL
TEST NO. 18 - LOW PRESSURE ROTOR TRIM BALANCE
_____________________________________________
7)
Decrease the speed of the engine to operate at minimum
power.
8) Operate the engine for five minutes to permit the engine to
become cool.
9) Use the Power Plant Operation (Normal) procedure to do the
engine shutdown (AMM 71-00-00/201).
10) If the vibration levels stay unsatisfactory, you must do
more trial and error adjustment to balance the fan.
NOTE:
____
(4)
You must obey the limits to the quantity of the
balance moment which was added.
S 725-383-P00
Do the trim balance procedure for the low pressure turbine (LPT).
(a) Conditions for the calibration weights for the LPT plane are as
follows:
1) 30 Inches (762.0 mm) of P/N 586822 lockwire wound around
the 7th stage LPT blade will give 4 oz-in (2880.0 g.mm) of
balance weight.
2) Engines with PW SB 72-268 have permanently installed
adjustable counterweignts at the rear hub. This is to
allow for trim balance at the LPT plane without the removal
of the exhaust case.
3) Engines with PW SB 72-466 have P/N 1B5812 clip-on
counterweights on the 7th stage blades.
a) The P/N 1B5812 clip-on counterweights have 2.92 oz-in
(2102 g.mm) of balance weight each.
b) Do not install more than 10 clip-on counterweights on
an engine at one time.
4) ENGINES PRE-PW-SB 72-268 OR PRE-PW-SB 72-466;
Can be trim balanced at the LPT plane with clip-on
counterweights as an alternative to lockwire.
5) Engines with adjustable counterweights install by
PW SB 72-268 can be trim balanced with P/N 1B5812 clip-on
counterweights if it is necessary.
a) It is recommended that the adjustable counterweights be
removed from the engine (see PW SB 72-466) before the
clip-on counterweights are used. This is at the 7th
stage blade tips.
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MAINTENANCE MANUAL
TEST NO. 18 - LOW PRESSURE ROTOR TRIM BALANCE
_____________________________________________
b)
(b)
(c)
It is permitted to position the adjustable the
counterweights to zero static moment (180 degrees
apart).
c) Then, do the trim balance procedure with the P/N 1B5812
clip-on counterweights for engines with PW SB 72-466.
d) When you try to do the trim balance:
1. And you cannot disassemble the rear compartment to
_
remove or zero out the adjustable counterweights,
it is also permitted to keep the adjustable
counterweights set at their current positions.
2. Continue with trim balance using the 1M5812 clip-on
_
counterweights at the 7th stage blades.
e) But, with a large amount of initial imbalance, a trim
balance solution is not always possible. When this
occurs:
1. The adjustable weights should either be removed or
_
set to zero moment weight.
2. Then, another attempt to trim balance the engine
_
can be made using procedures for Engines with
PW SB 72-466.
Find the location of the maximum LPT imbalance with the
directions on the PBS 4000/4100 Video Display and in the PBS
4000/4100 Operation Manual.
ENGINES WITH P/N 1B5812 CLIP-ON COUNTERWEIGHTS;
You can balance the low pressure turbine (LPT) as follows
(Fig. 522):
NOTE:
____
(d)
If the trim balance on the fan plane is incorrect,
it is possible you have to trim balance the low turbine.
You cannot always find the correct balance plane (fan or
LPT) from the vibration survey. But, usually, the high
values in the 2000 rpm N1 range can show the LPT plane
is not balanced. High values in the 3600 rpm N1 range
can show the fan or the LPT plane is not balanced.
Remove all P/N 1B5812 counterweights if they were installed
before.
1) Remove the installation jaw from the PWA 82001 Bender.
a) Install the removal jaw and the stop to the bender.
2) Move the hydraulic lever to the PUSH position.
a) Operate the hydraulic handle until the jaw moves
forward as far as it will go.
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MAINTENANCE MANUAL
TEST NO. 18 - LOW PRESSURE ROTOR TRIM BALANCE
_____________________________________________
3)
Carefully insert the bender through the 7th stage blades.
NOTE:
____
Use a flashlight and an inspection mirror attached
to a pole to help you put the tool into position.
You will have to twist and turn the bender to get it
through the blades.
4)
(e)
Put the bender into position until the stop is against the
rear face of the 7th stage blades.
a) Unbend the counterweight with the jaw until it contacts
the stop.
5) Push the bender forward to remove the counterweight from
the blade.
6) Remove the bender with the counterweight from between the
blades.
7) Move the hydraulic bender to the PUSH position.
a) Operate the hydraulic handle to remove the
counterweight from the jaw of the bender.
Install the trial balance counterweights on the 7th stage
turbine blade as follows:
1) Install the P/N 1B5812 counterweight.
a) Put the counterweight in the PWA 82001 bender.
b) Move the hydraulic lever to the PUSH position.
CAUTION:
_______
c)
d)
DO NOT OPERATE THE HYDRAULIC HANDLE MORE THAN
NECESSARY. IF YOU DO NOT OBEY THIS INSTRUCTION,
YOU WILL BEND THE COUNTERWEIGHT.
Operate the hydraulic handle until the jaw touches and
holds the counterweight.
Carefully put the bender with the counterweight through
the 7th stage blade.
NOTE:
____
Use a flashlight and an inspection mirror
attached to a pole to help you put the tool into
position.
You will have to twist and turn the bender to
get it through the blades.
e)
Position the counterweight leading edge holder on the
7th stage blade leading edge.
NOTE:
____
f)
Make sure the counterweight body is against the
handle.
Operate the hydraulic handle until the counterweight
shroud hook bends over the blade shroud.
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BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
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MAINTENANCE MANUAL
TEST NO. 18 - LOW PRESSURE ROTOR TRIM BALANCE
_____________________________________________
g)
h)
Move the hydraulic handle to the PULL position.
Operate the hydraulic handle to retract the jaw.
NOTE:
____
2)
Put 21.954 inches (557.632 millimeters) of P/N 586822
lockwire around the 7th stage turbine blade to be used as a
trial weight.
NOTE:
____
(5)
Carefully twist and turn the bender back through
the blades to remove it from the engine.
The lockwire will provide 2.92 ounce-inches
(2102 gram-millimeters) of imbalance and is the same
weight as one P/N 1B5812 counterweight.
S 715-383-P00
You can balance the low pressure turbine (LPT) as follows
(Fig. 522):
NOTE:
____
If the trim balance on the fan plane is incorrect, it is
possible you have to trim balance the low turbine. You
cannot always find the correct balance plane (fan or LPT)
from the vibration survey. But, usually, the high values in
the 2000 rpm N1 range can show the LPT plane is not balanced.
High values in the 3600 rmp N1 range can show the fan or the
LPT plane is not balanced.
NOTE:
____
If it is not possible to get access to the adjustable
counterweights, P/N 1B5812 clip-on counterweights as shown in
PW SB 72-466 can be used. See step (4) (a) for the
conditions.
(a)
(b)
(c)
(d)
(e)
(f)
(g)
Remove the turbine exhaust sleeve (AMM 78-11-01/401).
Remove the turbine exhaust plug (AMM 78-11-02/401).
Remove the No. 5 bearing cover.
1) Remove the bolts which attaches the heat shield halves and
the No. 5 bearing cover to the flange at the center of the
exhaust case.
2) With the PWA 80522 Knocker Puller, remove the No. 5 bearing
cover.
a) Discard the packing.
Remove the No. 5 bearing retaining ring and the keywasher.
Remove the retaining ring of the counterweight lockring
assembly.
Remove the rear counterweight lockring assembly.
Align the slots on the ID of the hub with the tabs on the front
counterweight lockring assembly.
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BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
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MAINTENANCE MANUAL
SEE A
HEAT SHIELD
BOLT
(12 LOCATIONS)
PACKING
PREFORM
HEAT SHIELD
NO. 5 BEARING
COVER
NO. 5 BEARING
RETAINING RING
FWD
LPT REAR HUB
SEE B
A
NO. 5 BEARING
RETAINING RING
KEYWASHER
FWD
REAR COUNTERWEIGHT
LOCKRING ASSEMBLY
FRONT COUNTERWEIGHT
LOCKRING ASSEMBLY
RETAINING RING
B
L-95079
L-95080
319995
Low Pressure Turbine Trim Balance
Figure 522
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ENGINES WITH PW SB 72-268
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MAINTENANCE MANUAL
TEST NO. 18 - LOW PRESSURE ROTOR TRIM BALANCE
_____________________________________________
(h)
(i)
Make a mark at the location of the maximum imbalance on the
rear face of the LPT hub.
1) This point was found in the step before.
Use the correct relocation angle from the Counterweight
Relocation Angle Table.
~¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼
¦
COUNTERWEIGHT RELOCATION ANGLE TABLE
¦
»¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼ ¼¼¼¼¼¼¼¼¼ ¼¼¼¼¼¼¼¼¼ ¼¼¼¼¼¼¼¼¼ ¼¼¼¼¼¼¼¼¼ ¼¼¼¼¼¼¼¼ ¼¼¼¼¼¼¼¼¼¼«
¦ Angle Between
¦
¦
¦
¦
¦
¦
¦
¦ Counterweights ¦
0°
¦
36°
¦
71°
¦ 108°
¦ 144° ¦
180°
¦
»¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼«
¦ Static Moment
¦ 19.63 ¦ 18.67 ¦ 15.88 ¦ 11.54 ¦ 6.07 ¦
0
¦
¦ oz-in. (g-mm)
¦ (14134) ¦ (13442) ¦ (11434) ¦ (8309) ¦ (4370) ¦
¦
²¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼…¼¼¼¼¼¼¼¼¼…¼¼¼¼¼¼¼¼¼…¼¼¼¼¼¼¼¼¼…¼¼¼¼¼¼¼¼¼…¼¼¼¼¼¼¼¼…¼¼¼¼¼¼¼¼¼¼¹
(j)
(k)
(l)
(m)
(n)
(o)
(p)
(q)
(r)
(s)
Assemble the counterweight lockring assemblies to the necessary
relocation angle.
Make a mark on the two lockrings at the center of the
relocation angle.
Move the counterweight lockring assemblies apart.
Align the tabs on one of the counterweight lockring assemblies
with the slots on the ID of the LPT hub.
Make sure the counterweight points forward.
Push the counterweight lockring assembly forward to the
shoulder on the slot of the circumference of the ID.
Turn the counterweight lockring assembly until the mark on the
lockring is 180° from the maximum imbalance mark on the rear
face of the LPT hub.
Put a center mark on the remaining counterweight lockring
assembly.
1) Put the center mark 180 degrees from the maximum imbalance
on the rear face of the LPT hub.
Install the counterweight lockring assembly with the
counterweight to the rear.
Push the rear counterweight lockring assembly forward. This is
to align the tabs and slots in the counterweight lockring
assemblies.
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MAINTENANCE MANUAL
TEST NO. 18 - LOW PRESSURE ROTOR TRIM BALANCE
_____________________________________________
(t)
Install the rear counterweight assembly against the front
counterweight lockring assembly.
1) Install the retaining ring of the counterweight lockring
assembly.
a) Install it in the ID groove made by the front and rear
counterweight lockrings.
2) Install the keywasher while you align the tabs to the slots
on the No. 5 bearing retaining nut and the LPT hub.
3) Install the No. 5 bearing retaining ring.
4) Lubricate the new packing for the No. 5 bearing cover with
engine oil.
5) Install the packing on the No. 5 bearing cover.
6) Install the No. 5 bearing cover on the flange at the center
of the exhaust case while you align the holes.
7) Lubricate the threads of the bolts, which attach the No. 5
bearing cover, with engine oil.
8) Install the two heat shield halves above the No. 5 bearing
cover with the bolts.
a) Tighten the bolts to 85-95 pound-inches (9.604-10.734
newton-meters).
9) Install the turbine exhaust plug (AMM 78-31-02/401).
10) Install the turbine exhaust sleeve (AMM 78-31-01/401).
WARNING:
_______
(u)
(v)
(w)
(x)
(y)
(z)
(aa)
(ab)
(ac)
(ad)
(ae)
USE AMM 71-00-00/201 TO OPERATE THE POWER PLANT. IF YOU
DO NOT USE THIS PROCEDURE, YOU CAN CAUSE DAMAGE TO
EQUIPMENT OR INJURY TO PERSONS.
Use the Power Plant Operation (Normal) procedure to start the
engine (AMM 71-00-00/201).
Permit the engine to become stable for three minutes.
Push the PERF/APU display select switch on the right sidewall
panel, P61.
Set the switch of the test equipment to monitor the P flange
accelerometer.
Slowly increase the speed of the engine to 75% N1.
Slowly increase the speed of the engine to takeoff power.
1) Look for the high values in the P flange vibration levels.
Slowly increase the speed of the engine to %N1 rpm at which the
maximum value of the P flange vibration level occurred.
Permit the engine to become stable until you get a stable
vibration indication.
Make a record of the P flange vibration, VP, and the %N1 rpm at
which it was taken.
Decrease the speed of the engine to operate at minimum power.
1) Permit the engine to become stable for five minutes.
Use the Power Plant Operation procedure to do the engine
shutdown (AMM 71-00-00/201).
1) Permit the engine to become cool.
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MAINTENANCE MANUAL
TEST NO. 18 - LOW PRESSURE ROTOR TRIM BALANCE
_____________________________________________
(af) ENGINES WITH P/N 1B5812 CLIP-ON COUNTERWEIGHTS;
Do the steps that follow:
1) If the vibration is in the specified limits, do the steps
that follow:
a) Remove the lockwire, when it is installed, from the 7th
stage blades and attach permanent counterweights P/N
1B5812.
b) The maximum number of counterweights permitted is 10.
2) If the vibration is not in the specified limits, do the
steps that follow:
a) Continue to test the engine with until the vibration is
in the specified limits.
b) Replace the lockwire, when it is installed, with
permanent counterweights.
c) The maximum number of counterweights permitted is 10.
(ag) ENGINES POST-PW-SB 72-268;
Do the steps that follow:
NOTE:
____
1)
2)
If it is not possible to get access to the adjustable
counterweights, P/N 1B5812 clip-on counterweights as
shown in PW SB 72-466 can be used. See step (4) (a) for
the conditions.
Get access to the counterweights.
Put the rear counterweight lockring in a position where it
is between 0 and 180 degrees from the front counterweight.
NOTE:
____
3)
The counterweights have six possible separation
angles [See the Counterweight Relocation Angle
Table]. You must keep the same angle during all
three trial operations.
Make a mark at the center of the angle between the
counterweights on the two counterweight lockrings.
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MAINTENANCE MANUAL
TEST NO. 18 - LOW PRESSURE ROTOR TRIM BALANCE
_____________________________________________
4)
5)
6)
Make a mark on the LPT hub at the location of the mark at
the center on the counterweight lockrings.
a) Identify the mark with the label location No. 1.
Make a mark at two more locations on the LPT hub at
120-degree separations.
a) Identify the marks with the labels location No. 2 and
No. 3.
Prepare the engine for the subsequent balance procedure.
WARNING:
_______
7)
8)
9)
10)
11)
12)
13)
14)
15)
16)
USE AMM 71-00-00/201 TO OPERATE THE POWER PLANT. IF
YOU DO NOT USE THIS PROCEDURE, YOU CAN CAUSE DAMAGE
TO EQUIPMENT OR INJURY TO PERSONS.
Use the Power Plant Operation (Normal) procedure to start
the engine (AMM 71-00-00/201).
a) Permit the engine to become stable at idle for three
minutes.
Slowly decrease the speed of the engine to %N1 rpm at which
the record of VP was made.
Permit the engine to become stable until you get a stable
vibration indication.
Make a record of the P flange vibration, VP1.
Decrease the speed of the engine to operate at minimum
power.
Permit the engine to become stable for five minutes.
Use the Power Plant Operation (Normal) procedure to do the
engine shutdown (AMM 71-00-00/201).
After you permit the engine to become cool, get access to
the counterweights.
Remove the rear counterweight lockring.
Turn the front counterweight lockring until the mark at the
center of the counterweight separation angle aligns with
the location No. 2 mark.
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MAINTENANCE MANUAL
TEST NO. 18 - LOW PRESSURE ROTOR TRIM BALANCE
_____________________________________________
17) Install the rear counterweight lockring while you align the
mark at the center of the counterweight relocation angle
with the location No. 2 mark.
18) Push the rear counterweight lockring forward to align the
tabs and the slots on the two counterweight lockrings.
19) Install the rear counterweight lockring against the front
counterweight lockring.
20) Prepare the engine for the subsequent balance procedure.
21) Record VP2.
22) Relocate the counterweight angle center point to location
No. 3.
23) Record VP3.
24) Find the necessary position of the counterweights which
makes the best balance as follows:
a) On a piece of polar graph paper, make a circle at the
center with a radius the same as VP.
b) Identify the circle with the label VP.
c) Make a mark on the circle VP where 0-, 120-, and
240-degree lines go across it.
d) Make circles with the center at the 0-, 120-, and
240-degree points with the radii the same as VP1, VP2,
and VP3.
e) Identify the circles with the labels VP1, VP2, and VP3.
f) Draw a line from the center to the center of the
triangle made by the three circles VP1, VP2, and VP3.
g) Identify the line with the label TP.
h) The necessary angular position of the static moment is
specified by the angle of TP.
i) The necessary static moment (M) is specified as
follows:
M = MO x VP
------TP
Where TP = length of vector TP
MO = Static moment used in the trial runs
specified by the table that follows.
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MAINTENANCE MANUAL
TEST NO. 18 - LOW PRESSURE ROTOR TRIM BALANCE
_____________________________________________
25) After you permit the engine to become cool, get access to
the counterweights.
26) Remove the rear counterweight lockring.
27) Align the slots on the ID of the LPT hub with the tabs on
the front counterweight lockring.
28) Remove the front counterweight lockring.
29) Make a mark at the angular position of the necessary
balance moment on the LPT hub.
30) Choose the counterweight relocation angle from the
Counterweight Relocation Angle Table
a) The table will give you the static moment to the
nearest calculated value for the necessary static
moment M.
31) Before you install the counterweight lockrings, assemble
them with the counterweights at the relocation angle found
from the step before.
32) Make a mark on the two counterweight lockrings at the
center of the relocation angle.
33) Move the counterweight lockrings apart.
34) Install one counterweight lockring, with the counterweight
which points forward.
a) Align the tabs with the slots on the ID of the LPT hub.
b) Push the counterweight lockring forward to the shoulder
of the circumferential slot.
35) Turn the installed counterweight lockring until the mark at
the center of the counterweight relocation angle aligns
with the mark on the LPT hub.
36) The mark on the LPT hub shows the necessary angular
position of the balance moment.
37) Install the other counterweight lockring, the counterweight
which points rearward.
a) Align the marks at the center of the counterweight
separation angle and on the forward counterweight
lockring.
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MAINTENANCE MANUAL
TEST NO. 18 - LOW PRESSURE ROTOR TRIM BALANCE
_____________________________________________
38) Align the tabs and the slots of the counterweight
lockrings.
39) Push the rear counterweight lockring forward until it is
against the forward counterweight lockring.
40) Install the retaining ring of the counterweight lockring in
the groove made by the front and the rear counterweight
lockrings.
41) Align the tabs on the key washer with the slots on the
No. 5 bearing retaining nut and the LPT hub.
42) Install the No. 5 bearing retaining ring.
43) Lubricate the new packing for the No. 5 bearing cover with
engine oil.
44) Install the packing on the No. 5 bearing cover.
45) Lubricate the threads of the bolts, which attach the No. 5
bearing cover, with engine oil.
46) Install the No. 5 bearing cover on the flange at the center
of the exhaust case with the bolts.
a) Make sure to align the holes.
b) Tighten the bolts to 85-95 pound-inches (9.604-10.734
newton-meters).
47) Install the turbine exhaust plug (AMM 78-11-02/401).
48) Install the turbine exhaust sleeve (AMM 78-11-01/401).
(ah) Examine the engine vibration from the steps before.
(ai) If the vibration levels are satisfactory, remove the test
equipment from the engine as follows:
WARNING:
_______
DO THE DEACTIVATION PROCEDURE TO PREVENT THE OPERATION OF
THE THRUST REVERSER. THE ACCIDENTAL OPERATION OF THE
THRUST REVERSER CAN CAUSE INJURY TO YOU OR DAMAGE TO
EQUIPMENT.
(aj) Do the deactivation procedure for the thrust reverser for
ground maintenance (AMM 78-31-00/201).
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MAINTENANCE MANUAL
TEST NO. 18 - LOW PRESSURE ROTOR TRIM BALANCE
_____________________________________________
(ak) Open the fan cowl panels (AMM 71-11-04/201).
(al) Open the core cowl panels (AMM 71-11-06/201).
WARNING:
_______
OBEY THE INSTRUCTIONS IN THE PROCEDURE TO OPEN THE THRUST
REVERSERS. IF YOU DO NOT OBEY THE INSTRUCTIONS, INJURY TO
PERSONS OR DAMAGE TO EQUIPMENT COULD OCCUR.
(am) Open the thrust reversers (AMM 78-31-00/201).
(an) Remove the clamps which attach the electrical cable and cooling
air lines of the trim balance equipment.
(ao) Disconnect the electrical cable from the B flange
accelerometer.
(ap) Remove the B flange accelerometer from the engine.
(aq) Disconnect the cooling air line from the P flange cooling
bracket.
(ar) Disconnect the electrical cable from the P flange
accelerometer.
(as) Remove the P flange accelerometer from the engine.
(at) Install the removed cover on the tube disconnect bracket.
1) Attach the cover with the bolts and the nuts.
(au) Replace the tool bolts, which attach the B flange accelerometer
bracket, with the B flange bolts and nuts.
1) Make sure you lubricate the threads of the B flange bolts
with engine oil.
2) Tighten the B flange bolts to 75-85 pound-inches
(8.474-9.604 newton-meters).
(av) Replace the tool bolts, which attach the P flange cooling
bracket, with the P flange bolts and nuts.
1) Make sure you lubricate the threads of the P flange bolts
with engine oil.
2) Tighten the P flange bolts to 85-95 pound-inches
(9.604-10.734 newton-meters).
(aw) Close the starter vent/IDG service access door.
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TEST NO. 18 - LOW PRESSURE ROTOR TRIM BALANCE
_____________________________________________
WARNING:
_______
OBEY THE INSTRUCTIONS IN THE PROCEDURE TO CLOSE THE THRUST
REVERSERS. IF YOU DO NOT OBEY THE INSTRUCTIONS, INJURY TO
PERSONS OR DAMAGE TO EQUIPMENT COULD OCCUR.
(ax)
(ay)
(az)
(ba)
G.
Close the thrust reverser (AMM 78-31-00/201).
Close the core cowl panels (AMM 71-11-06/201).
Close the fan cowl panels (AMM 71-11-04/201).
Do the activation procedure for the thrust reversers
(AMM 78-31-00/201).
Automatic Trim Balance
NOTE:
____
(1)
The PBS 4000/4100 system uses a consistent phase location to show
the position of the necessary balance weights. On PW2000 series
engines, this location is given by a different size tooth on the
gear used by the N1 speed transducer. The angular position of
this different size tooth is identified by a dimple on the front
lip of the drive shaft for the low pressure rotor. Hole No. 1 of
the balance flange, as used by the PBS 4000/4100 system, is then
specified as the nearest hole to the dimple. The other balance
flange holes are given one number after the other from No. 1 in
the direction it turns.
S 485-384-P00
Install the Trim Balance Equipment (Fig. 523)
WARNING:
_______
(a)
(b)
(c)
Do the deactivation procedure for the thrust reverser for
Ground Maintenance (AMM 78-31-00/201).
Open the left fan cowl panels (AMM 71-11-04/201).
Open the left core cowl panels (AMM 71-11-06/201).
WARNING:
_______
(d)
(e)
(f)
DO THE DEACTIVATION PROCEDURE TO PREVENT THE OPERATION OF
THE THRUST REVERSER. THE ACCIDENTAL OPERATION OF THE
THRUST REVERSER CAN CAUSE INJURY TO YOU OR DAMAGE TO
EQUIPMENT.
OBEY THE INSTRUCTIONS IN THE PROCEDURE TOP OPEN THE THRUST
REVERSERS. IF YOU DO NOT OBEY THE INSTRUCTIONS, INJURY TO
PERSONS OR DAMAGE TO EQUIPMENT COULD OCCUR.
Open the left thrust reversers (AMM 78-31-00/201).
Install the B flange accelerometer as follows:
1) Remove the bolt and nut from the holes No. 11 and 12 on the
B flange.
a) Keep the nuts and the bolts.
Install the B flange accelerometer on the bracket.
1) Install the bracket on the B flange at the empty bolt hole
with the tool bolt and nut.
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'B' FLANGE
ACCELEROMETER
AND BRACKET
'P' FLANGE
ACCELEROMETER BRACKET
N1 SIGNAL
BREAKOUT
CABLE
TUBE
DISCONNECT
BRACKET
STARTER VENT
IDG SERVICE
ACCESS DOOR
120 FOOT
ELECTRICAL
CABLE
10 FOOT ADAPTER
CABLES
CHARGE
AMP
10 FOOT "Y"
ADAPTER CABLES
MTI
PBS 4000
UNIT
320014
Optional Trim Balance Equipment
Figure 523
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TEST NO. 18 - LOW PRESSURE ROTOR TRIM BALANCE
_____________________________________________
(g)
(h)
Install the P flange accelerometer as follows:
1) Remove the bolt and nut from the two adjacent holes on the
P flange nearest to the top as the external equipment will
permit.
a) Keep the bolts and the nuts.
2) Install the P flange accelerometer.
Install the electrical cables as follows:
1) Open the starter Vent/IDG service access door on the right
fan cowl panel.
2) Pull a sufficient quantity of electrical cable through the
opened access door to the B flange accelerometer.
3) Connect the electrical cable to the B flange accelerometer
leads.
4) Remove the aft cover from the tube disconnect bracket.
a) Keep the cover, bolts, and nuts.
5) Pull a sufficient quantity of the electrical cable through
the open access door to the P flange accelerometer.
6) Connect the electrical cable to the P flange accelerometer.
WARNING:
_______
(i)
(j)
(k)
(l)
(m)
OBEY THE INSTRUCTIONS IN THE PROCEDURE TO CLOSE THE THRUST
REVERSERS. IF YOU DO NOT OBEY THE INSTRUCTIONS, INJURY TO
PERSONS OR DAMAGE TO EQUIPMENT COULD OCCUR.
Close the left thrust reverser (AMM 78-31-00/201).
Close the left core cowl panels (AMM 71-11-06/201).
Close the left fan cowl panels (AMM 71-11-04/201).
Do the activation procedure for the thrust reversers
(AMM 78-31-00/201).
Do the routing of the cables with the steps that follow:
1) Put the cable up the side of the fan cowl and along the top
of the wing.
2) Continue along the wing and put the cable through the
emergency exit door to the cabin equipment.
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TEST NO. 18 - LOW PRESSURE ROTOR TRIM BALANCE
_____________________________________________
(n)
(o)
(p)
(q)
(r)
(s)
(t)
(2)
Connect the electrical cables to the electrical cable adapters.
Connect the electrical cable adapters to the charge amplifiers.
Connect the Y-cable adapter to the charge amplifiers.
Connect the Y-cable adapter to the PBS 4000 Unit.
Remove the Standby Engine Indicator (AMM 77-41-01/401).
Install the N1 Signal breakout box in the location of the
Standby Engine Indicator.
Connect the PBS 4000/4100 Unit to the 110v ac 400 Hz airplane
power.
S 725-385-P00
Do the Trim Balance Procedure on the Low Pressure Compressor and Low
Turbine.
(a) Make sure the engine data diskette is not in the PBS 4000/4100
Unit.
(b) Make sure the N/REV/1/REV switch on the PBS 4000/4100 Unit is
in the N/REV position.
(c) Set the power switch on the PBS 4000/4100 Unit to the ON
position.
(d) Install the engine data diskette when the system tells you.
(e) Use the Main Menu function No. 6 to make sure the indications
that follow are set as it is shown:
1) TACHOMETER RATIO - 1.0
2) 100% SPEED ON TACHOMETER #1-4550
3) CHAN #1 SENSOR SENSITIVITY - 1 unit/volt
4) CHAN #2 SENSOR SENSITIVITY - 2 units/volt
5) CHANNEL #1 FULL SCALE VOLTAGE RANGE - 2 Volts
6) CHANNEL #2 FULL SCALE VOLTAGE RANGE - 2 Volts
7) CHANNEL #1 SENSOR TYPE - Velocity
8) CHANNEL #2 SENSOR TYPE - Velocity
(f) Set the main menu function in the sequence that follows and do
the alternatives which are applicable:
NOTE:
____
1)
The procedures that follow are necessary:
To start and stop the Power Plant, AMM 71-00-00/201.
To remove and install the compressor inlet cone,
AMM 72-31-01/401.
To install the trial balance weights, Ref Manual Trim
Balance Procedure.
Function No. 1 - Enter Engine ID
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TEST NO. 18 - LOW PRESSURE ROTOR TRIM BALANCE
_____________________________________________
(g)
2) Function No. 2 - Vibration Survey
3) Function No. 4 - Frequency Spectrum
4) Function No. 3 - Balance Engine
5) Function No. 2 - Vibration Survey
After you get the satisfactory vibration levels, do Function
No. 7 Update Influence Coefficient file.
1) If the vibration levels are satisfactory, remove the test
equipment from the engine as follows:
WARNING:
_______
a)
b)
c)
Do the deactivation procedure for the thrust reverser
for ground maintenance (AMM 78-31-00/201).
Open the left fan cowl panels (AMM 71-11-04/201).
Open the left core cowl panels (AMM 71-11-06/201).
WARNING:
_______
d)
e)
f)
g)
h)
i)
DO THE DEACTIVATION PROCEDURE TO PREVENT THE
OPERATION OF THE THRUST REVERSER. THE ACCIDENTAL
OPERATION OF THE THRUST REVERSER CAN CAUSE INJURY
TO PERSONS OR DAMAGE TO EQUIPMENT.
OBEY THE INSTRUCTIONS IN THE PROCEDURE TO OPEN
THE THRUST REVERSERS. IF YOU DO NOT OBEY THE
INSTRUCTIONS, INJURY TO PERSONS OR DAMAGE TO
EQUIPMENT COULD OCCUR.
Open the left thrust reversers (AMM 78-31-00/201).
Remove the clamps which attach the electrical cable and
cooling air lines for the trim balance equipment.
Disconnect the electrical cable from the B flange
accelerometer.
Remove the B flange accelerometer from the engine.
Disconnect the cooling air line from the cooling
bracket for the P flange.
Disconnect the electrical cable from the P flange
accelerometer.
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TEST NO. 18 - LOW PRESSURE ROTOR TRIM BALANCE
_____________________________________________
j)
k)
l)
m)
n)
Remove the P flange accelerometer from the engine.
Install the removed cover on the tube disconnect
bracket with bolts and nuts which were kept.
Replace the tool bolts which attach the bracket with
the P flange bolts.
1
_
Make sure to lubricate the threads of the P flange
bolts with engine oil.
2
_
Tighten the P flange bolts to 75-85 pound-inches
(8.474-9.604 newton-meters).
Replace the tool bolts, which attach the cooling
bracket, with the P flange bolts.
1
_
Lubricate the threads of the P flange bolts with
engine oil.
2
_
Tighten the P flange bolts to 85-95 pound-inches
(9.604-10.734 newton-meters).
Close the starter vent/IDG service access door.
WARNING:
_______
OBEY THE INSTRUCTIONS IN THE PROCEDURE TO CLOSE
THE THRUST REVERSER. IF YOU DO NOT OBEY THE
INSTRUCTIONS, INJURY TO PERSONS OR DAMAGE TO
EQUIPMENT COULD OCCUR.
o)
p)
q)
r)
(h)
(i)
Close the left thrust reversers (AMM 78-31-00/201).
Close the left core cowl panels (AMM 71-11-06/201).
Close the left fan cowl panels (AMM 71-11-04/201).
Do the activation procedure for the thrust reversers
(AMM 78-31-00/201).
Remove the N1 Signal breakout box from the Standby Engine
Indicator position.
Install the Standby Engine Indicator (AMM 77-41-01/401).
TASK 71-00-00-725-462-P00
24. Test
________________________________________________________________________
No. 18A - Engine Trim Balance with the Universal Airborne Vibration
Monitor (AVM) (P/N S362A001-9 and Subsequent)
_____________________________________________
A. General
ú
(1) ON 757-300 AIRPLANES ONLY;
This procedure does a trim balance of the engine using the
Vibro-Meter Universal Airborne Vibration Monitor (AVM) S362A001-9.
(a) Using vibration data recorded during flight and on ground runs,
this system calculates the best balance solution for:
1) The Fan only, 1-plane solution.
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TEST NO. 18 - LOW PRESSURE ROTOR TRIM BALANCE
_____________________________________________
ú
2)
(2)
(3)
(4)
Both fan and low pressure turbine (LPT), a 2-plane
solution.
The trim balance procedures should decrease the vibration levels of
the fan and LPT.
This trim balance procedure uses the imbalance data from one of the
last 6 flights or ground runs.
(a) The imbalance data is recorded by the AVM from the
accelerometer mounted on the fan case for the fan. Imbalance
data for the LPT is available only on the 757-300 and is
recorded from the sensor mounted in the engine strut.
From the front panel display of the AVM you can get this data:
(a) The current imbalance data.
(b) The balance weights configuration currently installed on the
engine fan.
(c) The results of a calculation of a 1-plane balance (fan only) or
a 2-plane balance (fan and LPT).
1) The results are given as raw data and a specific
solution.
NOTE:
____
B.
C.
The specific solution will give the balance
weight part number that must be attached at each
location to balance the fan for a 1-plane solution.
For a 2-plane solution of the fan and LPT the
specific solution will give the balance weight and
location and the counterweight and turbine blade
number.
This is a distributed weight solution that takes
into account there are only a limited number of
weights and locations to attach the balance weights
to the fan and counterweights to the LPT
References
(1) AMM 71-00-00/201, Power Plant - General
(2) AMM 72-31-01/401, Compressor Inlet Cone
(3) AMM 78-11-01/401, Turbine Exhaust Sleeve
Equipment
(1) Mat - Protective, 3/8 Inch Minimum Thickness, Minimum 42 Inches by
60 Inches With Warning Streamers (commercially available)
(2) Riveter - PWA 81550
(3) Balance Weights - P&W P/N 534495C1
P&W P/N 534495C2
P&W P/N 534495C3
P&W P/N 534495C4
P&W P/N 534495C5
P&W P/N 1B4294
(4) Counterweights - P&W P/N 1B5812
(5) Bender, Mechanical - P&W P/N PWA102978
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MAINTENANCE MANUAL
TEST NO. 18 - LOW PRESSURE ROTOR TRIM BALANCE
_____________________________________________
D.
E.
Consumable Material
(1) G02061 Marker-Felt tip
Access
(1) Location Zones
411 Left Engine
421 Right Engine
(2)
F.
Access Panel
119
Main Equipment center
120
Main Equipment center
Prepare for the Trim Balance Procedure
S 865-464-P00
Make sure that this circuit breaker is closed:
(a) Circuit Breaker Panel, P11:
1) 11K2, VIB MONITOR L/R
Trim Balance Procedure
(1)
G.
(1)
(2)
S 845-472-P00
Remove the inlet cone segment of the front compressor
(fan nose cone) (AMM 72-31-01/401).
S 985-474-P00
Find the dimple on the front end of the low pressure compressor
shaft. This represents the radial marking for zero degrees.
The location on the balance flange radially out from the dimple is
location 1.
NOTE:
____
(a)
If the radial from the dimple points to a space between
two locations, location 1 is the first location clockwise
from the radial.
The locations are counted clockwise when facing aft and
looking at the engine.
Record the part number and location of any balance weights that
you find.
NOTE:
____
If the engine has any balance weights with P/N 534493CL1
534493CL2 or 534493CL3 installed, it is recommended that
you to remove these weights and run a Vibration Survey
(AMM 71-00-00/501).
NOTE:
____
If there are 2 weights installed on the same location,
it is recommeded that you move one of them to an
adjecent location.
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SEE
B
FAN CASE
SEE
A
COMPRESSOR
INLET CONE
A
0`
TRIM BALANCE WEIGHT
LOCATION 1
FAN BALANCE WEIGHT
FLANGE LOCATION
B
N00307
Fan Balance Weight Flange Location
Figure 523A
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TEST NO. 18 - LOW PRESSURE ROTOR TRIM BALANCE
_____________________________________________
(3)
S 745-465-P00
Do these steps to get to the 1-plane or 2-plane balance menu on the
AVM front panel:
(a) Push and release one of the four buttons to show SELF TEST? on
the front panel display.
NOTE:
____
(b)
(c)
(d)
The front panel display will turn off if the buttons are
not pushed for five minutes or if an engine starts
running.
Push and release the NO button three times until the BALANCE?
option shows.
Push and release the YES button to go to the balance menu.
This causes the BALANCE ENGINE 1? screen to show.
To get the balance data for engine 1, push and release the YES
button. This causes the IMBAL DATA READ? screen to show.
1) To get the balance data for engine 2, do these steps:
a) From the BALANCE ENGINE 1? screen push and release the
NO button. This causes the BAL ENGINE 2? screen to
show.
b) Push and release the YES button. This causes the IMBAL
DATA READ? screen to show.
NOTE:
____
The Enigne 2 balance procedure is the same as
Engine 1 except the Ex code on all of the
screens will read E2 instead of E1.
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TEST NO. 18 - LOW PRESSURE ROTOR TRIM BALANCE
_____________________________________________
(4)
S 745-466-P00
Do these steps at the IMBAL DATA READ? menu to read the balance
data:
NOTE:
____
It is recommended to look at the imbalance data for other
flights or trim balance runs.
NOTE:
____
The AVM gathers data from six N1% speed ranges for each
engine and stores this data from the previous six flights or
engine ground runs. A balance calculation can be performed
on the data from any of these six flights or engine ground
runs. This calculation can be performed as long as the
flight or ground run has imbalance data recorded in one or
more of the N1% speed ranges. Better balances are obtained
when the flight or ground run has captured data in several
N1% speed ranges, and when the data has been obtained in
flight rather than a ground run.
(a)
(b)
Push and release the YES button.
DISPLAY? screen to show.
This causes the X FLIGHTS
NOTE:
____
The X refers to the total number of flights in memory,
and can be 1 through 6.
NOTE:
____
If NO IMBAL DATA shows, there is no stored balance data
in the AVM. The fan trim balance cannot be performed
until after a flight or ground trim run is performed.
(AMM 71-00-00/501 Vibration Survey)
Push and release the YES button.
screen to show.
NOTE:
____
1)
This causes the FLIGHT X?
The X refers to the flight number, and can be 0 through
5, where 0 is the last flight. Use the UP and DOWN
ARROW buttons to make a selection of the flight that you
want to see the imbalance history on.
If you push and release the NO button, the BALANCE 1 PLANE
COMPUTE? screen will show.
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TEST NO. 18 - LOW PRESSURE ROTOR TRIM BALANCE
_____________________________________________
(c)
Push and release the YES button to show the highest imbalance
data for the selected flight that was recorded (TABLE 503).
NOTE:
____
The definitions of the screen are given below.
NOTE:
____
There are six separate imbalance data screens for each
flight.
NOTE:
____
Use the UP and DOWN ARROW buttons to get each of the
five other imbalance data screens that were recorded
during each flight.
NOTE:
____
If no data was recorded for a particular screen then the
screen will appear as:
E1 --.-%
-.--/---:--/---
Use the UP and DOWN ARROW buttons to view the next imbalance
data screen.
NOTE:
____
Each data screen contains vibration information at a
different engine N1 speed. Typically, the six screens
show vibration information for 100-88.1% N1, 88.0-85.0%
N1, 84.9-81.1% N1, 81.0-75.0% N1, 74.9-70.0% N1, and
69.0-60.0% N1.
~¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼
¦
AVM FRONT PANEL DISPLAY
¦
¦
TABLE 503
¦
»¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼«
¦
E
1
x x . x %
¦
¦
¦
¦
n
.
n n / y y y
¦
¦
¦
¦
m
.
m m / z z z
¦
¦
¦
²¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¹
1)
2)
3)
xxx - N1 rotor speed in percent
nnn - the fan displacement in mils DA
mmm - the LPT displacement in mils DA
NOTE:
____
4)
5)
DA is double amplitude
yyy - the phase angle for the fan in degrees
zzz - the phase angle for the LPT in degrees
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TEST NO. 18 - LOW PRESSURE ROTOR TRIM BALANCE
_____________________________________________
(d)
From the FLIGHT X ? screen, push and release the NO button.
This causes the WEIGHTS CONFIG.? screen to show.
(5)
S 745-476-P00
From the IMBAL DATA READ? or FLIGHT x? screen, push and release the
NO button. This causes the WEIGHTS CONFIG.? screen to show.
(6)
S 745-492-P00
From the WEIGHTS CONFIG.? screen, push and release the YES button.
This causes the READ ACTUAL CONFIG.? screen to show.
(7)
S 745-493-P00
From the READ ACTUAL CONFIG.? screen, push and release the YES
button. This will display the balance weight part number and
location of the balance weights on the fan.
(a) Use the UP and Down arrows to look at the balance weight part
numbers stored in the AVM for each each location. Be sure to
look all 18 locations. Compare the information stored in the
AVM with the balance weight part number and location you
recorded when you removed the fan nose cone.
NOTE:
____
(b)
If no balance weights are recorded in the AVM the
display will read:
E1 FAN NO WGTS INST.
If the location numbers and balance weight part numbers agree
with what you recorded then, push and release the NO button 2
times to go to the BALANCE 1 PLANE? menu.
1) If the location numbers and balance weight part numbers DO
NOT agree with what you recorded then:
a) Push and release the NO button to display the RESET
ACTUAL CONFIG? screen.
b) Push and release the YES button, this will cause the
SAVE NEW CONFIG.? screen to display.
c) Push and release the YES button. This will cause the
the AVM to erase all stored weight data for the engine
and will cause the MODIFY ACTUAL CONFIG.? screen to
display.
d) Push and release the YES button this will cause the
TABLE 504 screen to display:
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MAINTENANCE MANUAL
TEST NO. 18 - LOW PRESSURE ROTOR TRIM BALANCE
_____________________________________________
~¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼
¦
AVM FRONT PANEL DISPLAY
¦
¦
TABLE 504
¦
»¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼«
¦
L O C . X X
¦
¦
¦
¦
N
O
W G H T
¦
¦
¦
¦
M
O
D
I F Y
?
¦
¦
¦
²¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¹
e)
Use the UP and DOWN ARROWS to move between the 18
locations. Push and release the YES button at the
locations where you want to modify the balance weight
part number TABLE 505 screen will display.
~¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼
¦
AVM FRONT PANEL DISPLAY
¦
¦
TABLE 505
¦
»¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼«
¦
L O C .
X X
¦
¦
¦
¦
N O
W G H T
¦
¦
¦
¦
S
A V E
?
¦
¦
¦
²¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¹
f)
g)
Use the UP and DOWN arrows to change the NO WGHT
display to the balance weight part number you recorded
earlier.
NOTE:
____
When the right balance weight part number
shows on the second line of the front panel
display, push and release the YES button. This
will return you to the display as shown in TABLE
504 and the next location.
NOTE:
____
Balance weight P/N 534493CL1, 534493CL2 and
534493CL3 are NOT used by the AVM and cannot be
recorded.
At the TABLE 504 screen push and release the NO button
when you are done changing the balance weight part
numbers to match your recorded data.
The BALANCE 1 PLANE COMPUTE? will display.
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MAINTENANCE MANUAL
TEST NO. 18 - LOW PRESSURE ROTOR TRIM BALANCE
_____________________________________________
(8)
S 745-467-P00
Do these steps at the BALANCE 1 PLANE COMPUTE? menu to calculate a
1-plane (fan only) balance solution:
NOTE:
____
This menu will do a 1-plane (fan only) trim balance
calculation.
NOTE:
____
If you want to do a 2-plane (fan and LPT) balance
solution push and release the NO button. The 2-PLANE
BALANCE? display will show, then go to the 2-plane balance
procedure.
(a)
To do a 1-plane (fan) balance solution Push and release the YES
button, then Push and release the NO button. The display will
read xxxxxxxx SPECIFIC COEFFS.?
NOTE:
____
(b)
(c)
(d)
Push and release the Yes button. The display will temporarily
read COMPUTE IN PROGRESS.
After the computation is completed the Display Panel will read:
NO BALANCE DATA or X FLIGHTS DISPLAY?. Where x is the number
of flights or ground runs from 1 to 6.
1) If the display reads NO BALANCE DATA, push and release the
NO button 2 times to go to the Engine 2 balance menu.
Push and release the YES button. The display will read
FLIGHT 0.
NOTE:
(e)
(f)
xxxxxxxxx is the Specific Coeff. Set Identification.
FLIGHT 0 is the last flight or ground run. Use the
UP and DOWN ARROW buttons to get to the data recorded
for each of the other 5 flights or ground runs.
Push and release the YES button to get the balance data for the
flight or ground run you have selected (TABLE 506).
NOTE:
____
This is a raw data solution. The data for all of
the flights or ground runs should be looked to determine
which flight (Fx) should be used for the specific
balance solution.
NOTE:
____
The definitions of the screen are given below.
To go back and select another flight or ground run from a
solution screen, push and release the No button.
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MAINTENANCE MANUAL
TEST NO. 18 - LOW PRESSURE ROTOR TRIM BALANCE
_____________________________________________
~¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼
¦
AVM FRONT PANEL DISPLAY
¦
¦
TABLE 506
¦
»¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼«
¦
n
n
n n / y y y
¦
¦
¦
¦
¦
¦
¦
¦
x / 6
Fx
?
¦
¦
¦
²¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¹
(g)
1) nnnn - Fan balance weight solution (oz-in).
2) yyy - the Fan balance weight position in degrees.
3) x/6 - the number of speed ranges with valid data (0 to 6).
4) Fx - the flight number (0 to 5, where 0 is the last fight).
From the balance solution screen of the flight you want to use
for the specific solution, push and release the YES button.
The display will temporarily read BALANCE IN PROGRESS.
1) When the AVM has completed the balance solution one of the
following messages show:
SOLUTION FOUND DISPLAY?
WEIGHT LIMIT EXCEEDED
NO CHANGE REQUIRED
NO BAL. DATA ACQUIRED
NO SOLUTION FOUND
NOTE:
____
(h)
If the displayed message is not SOLUTION FOUND,
go back to the raw balance solutions and try another
flight or ground run to see if a solution can be
found before doing other trouble shooting.
From the SOLUTION FOUND DISPLAY? screen push and release the
YES buton. This will cause the solution screens to show.
1) The solution screens give the balance weight part number to
install and the location on the fan to install the weight.
NOTE:
____
The solution screens will also give location and
balance weight part number of existing weights to
remove from the fan.
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MAINTENANCE MANUAL
TEST NO. 18 - LOW PRESSURE ROTOR TRIM BALANCE
_____________________________________________
~¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼
¦
AVM FRONT PANEL DISPLAY
¦
¦
TABLE 507
¦
»¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼«
¦
E x L O C . X X
¦
¦
¦
¦
I N S T A L L *[1]
¦
¦
¦
¦
x x x x x x x X
¦
¦
¦
²¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¹
2)
3)
4)
5)
Ex - Engine E1 or E2.
LOC. XX - Location 01 through 18
*[1] This instruction may say REMOVE if the
configuration stored in the AVM indicates a
balance weight is already installed at this
location.
x x x x x x x x - Part number of the balance weight
~¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼
¦
TRIM BALANCE WEIGHTS
¦
»¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼ ¼¼¼¼¼¼¼¼¼¼¼¼¼¼«
¦
P/N 534495
¦ P/N 1B4294 ¦
»¼¼¼¼¼¼¼¼¼¼¼ ¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼«
¦ 534495C1 ¦ 3.7 oz-in. ¦ 10.0 oz-in. ¦
»¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼«
¦
¦ 534495C2 ¦ 4.0 oz-in. ¦
¦
»¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼«
¦
¦ 534495C3 ¦ 4.3 oz-in. ¦
¦
»¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼«
¦
¦ 534495C4 ¦ 4.6 oz-in. ¦
¦
»¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼«
¦
¦ 534495C5 ¦ 4.9 oz-in. ¦
¦
²¼¼¼¼¼¼¼¼¼¼¼…¼¼¼¼¼¼¼¼¼¼¼¼…¼¼¼¼¼¼¼¼¼¼¼¼¼¼¹
(i)
(9)
Push and release the DOWN ARROW to show each screen in the
solution. Be sure that you look at all of the screens of the
solution. Record the weight part number and location for each
weight listed in the specific balance solution.
S 745-477-P00
If you are satisfied you have recorded all of the balance weight
part numbers and locations, then at the DISPLAY SOLUTION AGAIN?
screen push and release the NO button.
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MAINTENANCE MANUAL
TEST NO. 18 - LOW PRESSURE ROTOR TRIM BALANCE
_____________________________________________
S 745-478-P00
(10) At the SAVE NEW CONFIG.? screen push and release the YES button.
The RESET SPECIFIC COEFFS.? screen will display.
NOTE:
____
Push and release the NO button if you DO NOT want to save
the new balance soultion. This is a fail safe step, from
here you can start over again.
S 745-479-P00
(11) If you want to save the new weight part numbers and locations push
and release the YES button.
S 745-499-P00
(12) If you are not going to balance Engine 2, push and release the NO
button 2 times. The TURN OFF DISPLAY? screen will show. Push and
release the NO button to turn off the display or the display will
automatically turn off after 5 minutes of no activity.
S 025-496-P00
(13) Do the following steps to install balance weights on the fan.
NOTE:
(a)
(b)
(c)
The maximum correction at the fan shall not exceed a total
vector sum of 30 oz-in. The maximum vector sum of all trim
balance weights and all previously installed weights on the
fan hub shall not exceed 50 oz-in.
Remove any balance weights from the fan balance flange that the
specific solution said to remove.
With a riveter attach the balance weights to the locations that
you recorded.
1) Flare the rivet(s) to 0.125 inch (3.175 mm) in diameter.
Install the inlet cone segment of the front compressor
(AMM 72-31-01/401).
S 745-483-P00
(14) Do these steps at the BALANCE 2 PLANES COMPUTE? menu to calculate a
2-plane (fan and LPT) balance solution:
(a) From the BALANCE 1 PLANE COMPUTE? push and release the NO
button. The display will read BALANCE 2 PLANES COMPUTE?.
(b) To do a 2-plane (fan and LPT) balance solution push and relaese
the YES button, then Push and release the NO button. The
display will read xxxxxxxx SPECIFIC COEFFS.?
NOTE:
____
(c)
xxxxxxxx is the Specific Coeffients Set Identifer.
Push and release the YES button.
read COMPUTE IN PROGRESS.
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The display will temporarily
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MAINTENANCE MANUAL
TEST NO. 18 - LOW PRESSURE ROTOR TRIM BALANCE
_____________________________________________
(d)
(e)
After the computation is completed the Display Panel will read:
NO BALANCE DATA or X FLIGHTS DISPLAY?.
1) If the display reads NO BALANCE DATA, push and release the
NO button 2 times to go to the Engine 2 balance menu.
Push and release the YES button. The display will read
Flight 0.
NOTE:
____
(f)
(g)
Flight 0 is the last flight or ground run. Use the
UP and DOWN ARROW buttons to get to the data recorded
for each of the other 5 flights or ground runs.
Push and release the YES button to get the balance data for the
flight or ground run you have selected (TABLE 508).
NOTE:
____
This is a raw data solution. The data for all of
the recorded flights or ground runs should be looked at
to determine which flight (Fx) you want to use for the
specific balance solution.
NOTE:
____
The definitions of the screen are given below.
To go back and select another flight or ground run from a
solution screen, push and release the No button.
~¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼
¦
AVM FRONT PANEL DISPLAY
¦
¦
TABLE 508
¦
»¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼«
¦
n n n n / y y y
¦
¦
¦
¦
m m m m / z z z
¦
¦
¦
¦
x / 6
Fx
?
¦
¦
¦
²¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¹
1)
2)
3)
4)
5)
6)
nnnn - Fan balance weight solution (oz-in).
yyy - The Fan balance weight position in degrees.
mmmm - Low Pressure Turbine solution (oz-in).
zzz - Te Low Pressure Turbine counterweight position in
degrees.
x/6 - the number of speed ranges with valid data (0 to 6).
Fx - the flight number (0 to 5, where 0 is the last fight).
EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùùû
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MAINTENANCE MANUAL
TEST NO. 18 - LOW PRESSURE ROTOR TRIM BALANCE
_____________________________________________
(h)
From the balance solution screen of the flight you want to use
for the specific solution, push and release the YES button.
The display will temporarily read BALANCE IN PROGRESS.
1) When the AVM has completed the balance solution one of the
following messages show:
SOLUTION FOUND DISPLAY?
WEIGHT LIMIT EXCEEDED
NO CHANGE REQUIRED
NO BAL. DATA ACQUIRED
NO SOLUTION FOUND
NOTE:
____
(i)
If the displayed message is not SOLUTION FOUND,
go back to the raw balance solutions and try another
flight or ground run to see if a solution can be
found before doing other trouble shooting.
From the SOLUTION FOUND DISPLAY? screen push and release the
YES buton. The will cause the solution screens to show.
1) The solution screens give the balance weight part number to
install and the location on the fan and LPT to install the
weight.
NOTE:
____
The solution screens will also give location and
balance weight part number of existing weights to
remove from the fan.
~¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼
¦
AVM FRONT PANEL DISPLAY
¦
¦
TABLE 509
¦
»¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼«
¦
E x L O C . X X
¦
¦
¦
¦
I N S T A L L *[1]
¦
¦
¦
¦
x x x x x x x X
¦
¦
¦
²¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¹
2)
3)
4)
5)
Ex LOC.
BLD
*[1]
Engine E1 of E2.
XX - Location 01 through 18 on the fan
XX - Blade number on the LPT
This instruction may say REMOVE if the
configuration stored in the AVM has a
balance weight already installed at this
location on the fan. Weights installed on
the low pressure turbine (LPT) are not
removed.
x x x x x x x x - Part number of the balance weight
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MAINTENANCE MANUAL
TEST NO. 18 - LOW PRESSURE ROTOR TRIM BALANCE
_____________________________________________
~¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼
¦
TRIM BALANCE WEIGHTS
¦
»¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼ ¼¼¼¼¼¼¼¼¼¼¼¼¼¼«
¦
P/N 534495
¦ P/N 1B4294 ¦
»¼¼¼¼¼¼¼¼¼¼¼ ¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼«
¦ 534495C1 ¦ 3.7 oz-in. ¦ 10.0 oz-in. ¦
»¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼«
¦
¦ 534495C2 ¦ 4.0 oz-in. ¦
¦
»¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼«
¦
¦ 534495C3 ¦ 4.3 oz-in. ¦
¦
»¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼«
¦
¦ 534495C4 ¦ 4.6 oz-in. ¦
¦
»¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼«
¦
¦ 534495C5 ¦ 4.9 oz-in. ¦
¦
²¼¼¼¼¼¼¼¼¼¼¼…¼¼¼¼¼¼¼¼¼¼¼¼…¼¼¼¼¼¼¼¼¼¼¼¼¼¼¹
~¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼
¦
LPT CLIP ON
¦
¦
COUNTERWEIGHT
¦
»¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼«
¦
P/N 1B5812
¦
»¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼«
¦
2.29 oz-in
¦
²¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¹
(j)
Push and release the DOWN ARROW to show each screen in the
solution. Be sure that you look at all of the screens of the
solution. Record the weight part number and location for each
weight listed in the specific balance solution.
S 745-484-P00
(15) If you are satisfied that you have all of the balance weight part
numbers and locations recorded, at the DISPLAY SOLUTION AGAIN?
screen push and release the NO button.
S 745-485-P00
(16) At the SAVE NEW CONFIG.? screen push and release the YES button.
The RESET SPECIFIC COEFFS.? screen will display.
NOTE:
____
Push and release the NO button if you DO NOT want to save
the new balance soultion. This is a fail safe step, from
here you can start over again.
EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùùû
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MAINTENANCE MANUAL
TEST NO. 18 - LOW PRESSURE ROTOR TRIM BALANCE
_____________________________________________
S 745-491-P00
(17) If you want to save the specific coefficients push and release the
YES button.
NOTE:
____
The low pressure turbine (LPT) counterweight part numbers
are not saved in the AVM.
S 745-500-P00
(18) If you are not going to balance Engine 2, push and release the NO
button 2 times. The TURN OFF DISPLAY? screen will show. Push and
release the NO button to turn off the display or the display will
automatically turn off after 5 minutes of no activity.
S 745-497-P00
(19) Do the following steps to install balance weights on the fan and
counterweights on the LPT:
(a) If the specific balance solution includes balance weights to be
put on the LPT do the following steps:
1) Remove the Turbine Exhaust Sleeve (AMM 78-11-01/401).
2) Rotate the fan until the dimple on the fan shaft is
straight up at the 12 o'clock position.
3) After the fan is rotated the low pressure turbine blade
pointing straight up is the number one blade.
a) Mark this blade with the felt tip marker.
b) The turbine blades are numbered counter-clockwise when
looking at the rear of the engine facing forward.
4) Do the following steps to install a P/N 1B5812 clip
on counterweight to each of the turbine blades that
you recorded from the specific 2-plane balance
solution:
a) Use the felt tip marker to mark the turbine blades
where a counterweight will be attached.
b) Rotate the LPT until the blade you want to put a
counterweight on is pointing straight down to the 6
o'clock position.
NOTE:
____
If a blade already has a counterweight clipped
on it, clip the new counterweight to the next
closest blade.
NOTE:
____
No more than a total of 10 counterweights may be
installed on the low pressure turbine.
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MAINTENANCE MANUAL
TEST NO. 18 - LOW PRESSURE ROTOR TRIM BALANCE
_____________________________________________
CAUTION:
_______
c)
d)
DO NOT OPERATE THE MECHANICAL HANDLE MORE THAN
NECESSARY. IF YOU DO NOT OBEY THIS INSTRUCTION
YOU WILL BEND THE COUNTERWEIGHT.
Operate the mechanical bender until the jaw touches and
holds the counterweight.
Carefully put the bender with the counterweight through
the LPT blades.
NOTE:
____
Use a flash light and an inspection mirror
attached to a pole to help you put the tool into
position.
You will have to twist and turn the bender to
get it through the blades.
e)
Position the counterweight leading edge holder on the
LPT blade leading edge.
NOTE:
____
f)
g)
Once the counter weight is in position release
the grip of the mechanical bender on the
counterweight and allow it to drop into place
covering the shroud.
Operate the mechanical bender until the counterweight
shroud hook bends over the blade shroud.
Release the handle of the mechanical bender to retract
the jaw.
NOTE:
____
You will have to twist and turn the bender back
Through the blades to remove it from the engine.
S 025-498-P00
(20) Do the following steps to install balance weights on the fan.
NOTE:
____
(a)
(b)
The maximum correction at the fan shall not exceed a total
vector sum of 30 oz-in. The maximum vector sum of all trim
balance weights and all previously installed weights on the
fan hub shall not exceed 50 oz-in.
Remove any balance weights from the fan balance flange that the
specific solution said to remove.
With a riveter attach the balance weights to the fan locations
that you recorded.
1) Flare the rivet(s) to 0.125 inch (3.175 mm) in diameter.
EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùùû
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TEST NO. 18 - LOW PRESSURE ROTOR TRIM BALANCE
_____________________________________________
S 945-489-P00
(21) Install the inlet cone segment of the front compressor
(AMM 72-31-01/401).
S 945-490-P00
(22) Install the Turbine Exhaust Sleeve (AMM 78-11-01/401).
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TEST NO. 19 - PT2 SYSTEM LEAK TEST
__________________________________
TASK 71-00-00-795-417-P00
25. Test
__________________________________
No. 19 - PT2 System Leak Test
A. General
(1) This procedure does a pressurization and leak check for the PT2
system. The PT2 system is pressurized at the PT2/TT2 probe (on the
internal side of the inlet cowl) to the EEC.
(2) Leaks in the PT2 system are not permitted. It is necessary to
repair all the leaks you find in the PT2 system.
B. Equipment
(1) Regulator (for air pressure), with an isolation
shutoff valve
(2) Pressure Gage, with a range of 10 PSIG
(68.9 KPa) and an accuracy of | 10%
(3) Tygon Flexible Tubing, 0.250 inch (6.350) ID or
equivalent
(4) Ground Pneumatic Cart, to supply clean dry air
at 10 PSIG (68.9 KPa)
C. Consumable Materials
(1) G02151 Fluid, Leak Check (bubble type) PMC 9569
D. References
(1) 71-11-04/201, Fan Cowl Panels
E. Access
(1) Location Zones
211/212
Control Cabin
411
Left Engine
421
Right Engine
(2)
Access Panels
413AL
Fan Cowl Panel, Left Engine
423AL
Fan Cowl Panel, Right Engine
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TEST NO. 19 - PT2 SYSTEM LEAK TEST
__________________________________
F.
Prepare for the PT2 System Leak Test.
(1)
(2)
(3)
G.
S 865-418-P00
Attach a DO-NOT-OPERATE tag to the L(R) ENGINE START switch on the
pilot's overhead panel, P5.
S 865-419-P00
For the left engine, open these circuit breakers on the overhead
circuit breaker panel, P11, and attach DO-NOT-CLOSE tags:
(a) 11R14, ENG PROBE HTR LEFT
(b) 11R16, PROBE HEAT IND ENG LEFT
S 865-420-P00
For the right engine, open these circuit breakers on the overhead
circuit breaker panel, P11, and attach DO-NOT-CLOSE tags:
(a) 11R23, ENG PROBE HTR RIGHT
(b) 11R24, PROBE HEAT IND ENG RIGHT
S 015-421-P00
(4) Open the left fan cowl panel (Ref 71-11-04/201).
Do the PT2 System Leak Test.
(1)
(2)
S 485-422-P00
Connect the air pressure source to the PT2/TT2 probe as shown, but
do not pressurize the system (Fig. 524):
S 795-423-P00
Pressurize the PT2 system to look for leaks as follows:
CAUTION:
_______
(a)
DO NOT PRESSURIZE THE PT2 SYSTEM MORE THAN 15 PSIG
(1.3.4KPa). MAKE SURE THE PRESSURE REGULATOR IS SET LOW
BEFORE YOU PRESSURIZE THE PT2 SYSTEM. A HIGH PRESSURE CAN
CAUSE DAMAGE TO THE EEC.
Pressurize the PT2 system at a rate of | 2.0 PSIG (13.8 KPa)
per minute to a maximum pressure of 10 PSIG (68.9 KPa).
1) Hold the flexible tube to keep it attached to the PT2/TT2
probe.
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SEE
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A
EEC (REF)
PT2 TUBE
ELECTRICAL
CONNECTORS
FWD
A
PT2 SENSE
LINE
SEE
B
SCREW AND
WASHER
BOLT AND
WASHER
(6 LOCATIONS)
PT2/TT2
PROBE
SEE
NUT AND
WASHER
C
BONDING
JUMPER
FWD
PT2/TT2 PROBE
(SHOWN REMOVED FROM THE INLET COWL)
B
985774
PT2 System Leak Test
Figure 524 (Sheet 1)
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INLET COWL
PT2 INLET PORT
EEC INLET TOTAL
PRESSURE/TEMPERATURE
PT2/TT2 PROBE
TYGON 0.250 INCH
(6.350 mm)FLEXIBLE
TUBING OR
EQUIVALENT
REGULATED 10 PSIG (69.9 KPA)
AIR SUPPLY
SHUT OFF
VALVE
PRESSURE
GAUGE
C
L-A4354
985782
PT2 System Leak Cheak
Figure 524 (Sheet 2)
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TEST NO. 19 - PT2 SYSTEM LEAK TEST
__________________________________
(b)
(c)
(d)
When the system is pressurized, close the shutoff valve to
isolate the PT2 system.
Monitor the pressure gage.
If the pressure decreases, use the leak check fluid to find the
leak.
S 795-424-P00
If you find leaks in the PT2 system, repair the leaks and do the
test again.
Put the Airplane Back to its Usual Condition.
(3)
H.
(1)
S 085-425-P00
Remove the air pressure source from the PT2 probe inlet.
(2)
S 415-426-P00
Close the left fan cowl panel (AMM 71-11-04/201).
(3)
(4)
(5)
S 865-427-P00
For the left engine, remove the DO-NOT-CLOSE tags and close these
circuit breakers on the P11 panel:
(a) 11R14, ENG PROBE HTR LEFT
(b) 11R16, PROBE HEAT IND ENG LEFT
S 865-428-P00
For the right engine, remove the DO-NOT-CLOSE tags and close these
circuit breakers on the P11 panel:
(a) 11R23, ENG PROBE HTR RIGHT
(b) 11R24, PROBE HEAT IND ENG RIGHT
S 865-429-P00
Remove the DO-NOT-OPERATE tag from the L(R) ENGINE START switch on
the P5 panel.
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TEST NO. 20 - STATIC LEAK TEST
______________________________
TASK 71-00-00-715-442-P00
26. Test
______________________________
No. 20 - Static Leak Test
A. General
(1) This procedure gives the minimum steps necessary to do a static leak
test after the replacement of the main gearbox.
B. Equipment
(1) Plate, Block Off - PWA 80821, Pratt and Whitney
(2) Adapter, Gearbox - PWA 81405, Pratt and Whitney
(3) Adapter, Ejector Inlet Breather Tube PWA 81903, Pratt & Whitney
(4) CTE 7075 - Cart
(5) Plate, Cover - PWA 81821, Pratt and Whitney
(6) Pint Bottle of Water - Commercially Available
(7) Hose - 2 Feet long, 3/8 Inch Diameter for Slip
Fitting Drain Tubes
(8) Air Supply - Pneumatic unit which supplies air
at 10 psig (69 kPa) maximum regulated pressure
and 300°F (149°C) maximum temperature (air at
or near room temperature is recommended).
C. Consumable Materials
(1) Solution - Leak Check - PMC 9569 Fluid
D. References
(1) AMM 71-00-00/201, Power Plant - General
(2) AMM 71-11-04/201, Fan Cowl Panels
(3) AMM 71-11-06/201, Core Cowl Panels
(4) AMM 78-31-00/201, Thrust Reverser System
E. Access
(1) Location Zones
413
L Power Plant Fan Cowl Panel
414
L Power Plant Fan Cowl Panel
415
L Power Plant Fan Reverser
416
L Power Plant Fan Reverser
423
R Power Plant Fan Cowl Panel
424
R Power Plant Fan Cowl Panel
425
R Power Plant Fan Reverser
426
R Power Plant Fan Reverser
(2)
Access Panels
413AL
Fan
414AR
Fan
415AL
Fan
416AR
Fan
423AL
Fan
424AR
Fan
425AL
Fan
426AR
Fan
Cowl Panel (Left)
Cowl Panel (Right)
Reverser (Left)
Reverser (Right)
Cowl Panel (Left)
Cowl Panel (Right)
Reverser (Left)
Reverser (Right)
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TEST NO. 20 - STATIC LEAK TEST
______________________________
F.
Do the Leak Test - Static Leak Method (Optional) (Fig. 502A)
NOTE:
____
You can apply a pressure to the main gearbox with one of the two
different procedures. The block-off plate procedure uses the PWA
80821 block-off plate to seal the deoiler outlet while you apply a
pressure at a gearbox plug. The leak check tooling procedure uses
the PWA 81903 adapter to apply a pressure at the ejector inlet
breather tube.
S 045-433-P00
WARNING:
_______
(1)
DO THE DEACTIVATION PROCEDURE TO PREVENT THE OPERATION OF THE
THRUST REVERSER. THE ACCIDENTAL OPERATION OF THE THRUST
REVERSER CAN CAUSE INJURY TO YOU OR DAMAGE TO EQUIPMENT.
Do the deactivation procedure for the thrust reverser for ground
maintenance (AMM 78-31-00/201).
(2)
S 015-432-P00
Open the fan cowl panels (AMM 71-11-04/201).
(3)
S 015-434-P00
Open the core cowl panels (AMM 71-11-06/201).
S 015-435-P00
WARNING:
_______
(4)
(5)
OBEY THE INSTRUCTIONS IN THE PROCEDURE TO OPEN THE THRUST
REVERSERS. IF YOU DO NOT OBEY THE INSTRUCTIONS, INJURY TO
PERSONS OR DAMAGE TO EQUIPMENT COULD OCCUR.
Open the thrust reversers (AMM 78-31-00/201).
S 725-436-P00
If you do the block-off plate procedure, do the steps that follow:
(a) Remove a bolt that attaches the deoiler outlet elbow and the
inlet breather ejector tube.
(b) Loosen the remaining bolts which attach the deoiler outlet
elbow to the ejector inlet breather tube.
(c) Install the block-off plate between the flange of the deoiler
outlet elbow and the ejector inlet breather tube.
(d) Install the bolt to attach the PWA 80821 block-off plate.
(e) Remove the plug and the insert from the top right corner of
gearbox (above the deoiler gear shaft assembly).
1) Discard the packing.
(f) Install the PWA 81405 gearbox adapter (Hansen fitting) into the
opening.
(g) Connect the air supply to the PWA 81405 gearbox adapter.
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TEST NO. 20 - STATIC LEAK TEST
______________________________
CAUTION:
_______
(h)
DO NOT SUPPLY MORE THAN 7 PSIG (48 KPa) PRESSURE OR 300°F
(149°C) TEMPERATURE AIR IN THE MAIN GEARBOX. DO NOT MOTOR
THE ENGINE DURING THE TEST. IF YOU MOTOR THE ENGINE WHILE
THE OIL SYSTEM IS PRESSURIZED, YOU CAN CAUSE OIL
CONTAMINATION OF THE COMPRESSORS AND GASPATH.
Supply dry air at a pressure of 5-7 psig (34-48 kPa) in the
main gearbox.
NOTE:
____
The pressures less than 5 psig (34 kPa) are not
sufficient to give accurate results.
1)
(i)
Make sure the air pressure is less than 7 psig (48 kPa) in
the main gearbox.
2) Make sure the air temperature is less than 300°F (149°C) in
the main gearbox.
Examine all seal drain outlet tubes in the engine vent and
drain system.
1) Connect a hose to each seal drain outlet tube at the drain
collector.
2) Put the hoses in the pint bottle of water one at a time.
a) All seal drain outlet tubes that cause continuous air
bubbles in the water are not permitted.
NOTE:
____
(j)
(k)
(l)
(m)
(n)
(o)
(p)
You can have some leakage, but it is possible to
count the number of air bubbles.
Use the leak check or a soap and water solution to examine for
leaks at these locations:
1) All oil lines from the oil pump to the main gearbox and to
the bearings.
2) All the gearbox housing covers and connections.
3) All the connections to the deoiler.
4) All the gearbox pad seals that do not have overboard
drains.
5) All the main gearbox, angle gearbox, and lay shaft
connections.
Remove the air pressure from the main gearbox.
If you find a leak, repair the leak.
Do the test again if leaks are found.
If the test is completed satisfactorily, do the steps that
follow:
1) Remove the air supply lines.
2) Remove the PWA 81405 gearbox adapter.
3) Remove the PWA 81821 cover plate.
4) Discard the packing.
Lubricate the new packing for the insert.
Install the packing on the insert.
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TEST NO. 20 - STATIC LEAK TEST
______________________________
(q)
(r)
(s)
(t)
(u)
(v)
(w)
(x)
(y)
(z)
(6)
Lubricate the threads of the insert with engine oil.
Install the insert in the opening at the top right corner of
the main gearbox.
1) Tighten the insert to 53-71 pound-inches (5.988-8.021
newton-meters).
Lubricate the new packing for the plug.
Install the packing on the plug.
Lubricate the threads of the plug with engine oil.
Install the plug into the insert in the top right corner of the
main gearbox.
1) While you hold the insert, tighten the plug to 35-53
pound-inches (3.954-5.988 newton-meters).
2) Install the lockwire on the plug.
Lubricate the new packing for the deoiler outlet elbow with
engine oil.
Put the packing in the face of the deoiler outlet elbow.
Lubricate the threads of the bolts, which attach the deoiler
outlet elbow and the ejector inlet breather tube, with engine
oil.
Attach the ejector inlet breather tube to the deoiler outlet
elbow with the bolts and nuts.
1) Tighten the bolts to 85-95 pound-inches (9.604-10.734
newton-meters).
S 725-437-P00
If you do the leak check tooling procedure, do the steps that
follow:
(a) Put the PWA 81903 adapter on the open end of the ejector inlet
breather tube.
(b) Put the clamp detail of the PWA 81903 adapter on the rear face
of the ejector inlet breather tube.
(c) Install the retaining bolts through the PWA 81903 adapter and
into the clamp detail.
NOTE:
____
(d)
If it is necessary, use more adapters to adapt to the
pressure source. You must attach a pressure gage to the
.4375 - 20-inch threaded connector. The pressure source
is attached to the 1.0625 - 12-inch threaded air inlet
connector.
Attach the line from CTE 7075 cart to the PWA 81903 adapter.
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TEST NO. 20 - STATIC LEAK TEST
______________________________
CAUTION:
_______
(e)
DO NOT SUPPLY MORE THAN 7 PSIG (48 KPa) PRESSURE OR 300°F
(149°C) TEMPERATURE AIR IN THE MAIN GEARBOX. DO NOT MOTOR
THE ENGINE DURING THE TEST. IF YOU MOTOR THE ENGINE WHILE
THE OIL SYSTEM IS PRESSURIZED, YOU CAN CAUSE OIL
CONTAMINATION OF THE COMPRESSORS AND GASPATH.
Supply dry air at a pressure of 5-7 psig (34-48 kPa) in the
main gearbox.
NOTE:
____
The pressures less than 5 psig (34 kPa) are not
sufficient to give accurate results.
1)
(f)
Make sure the air pressure is less than 7 psig (48 kPa) in
the main gearbox.
2) Make sure the air temperature is less than 300°F (149°C) in
the main gearbox.
Examine all seal drain outlet tubes in the engine vent and
drain system.
1) Connect a hose to each seal drain outlet tube at the drain
collector.
2) Put the hoses in the pint bottle of water one at a time.
a) All seal drain outlet tubes that cause continuous air
bubbles in the water are not permitted.
NOTE:
____
You can have some leakage, but it is possible to
count the number of air bubbles.
(g)
G.
Use the leak check or a soap and water solution to examine for
leaks at these locations:
1) All oil lines from the oil pump to the main gearbox and to
the bearings.
2) All the connections to the deoiler.
3) All the gearbox housing covers and connections.
4) All the gearbox pad seals that do not have overboard
drains.
5) All the main gearbox, angle gearbox, and lay shaft
connections.
(h) Remove the air pressure from the main gearbox.
(i) When you complete the test satisfactorily, do the steps that
follow:
1) Remove the line which is connected to the PWA 81903
adapter.
2) Remove the PWA 81903 adapter and all other adapters, if
applicable, from the main gearbox.
Put the airplane back to its initial condition
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TEST NO. 20 - STATIC LEAK TEST
______________________________
S 415-438-P00
WARNING:
_______
OBEY THE INSTRUCTIONS IN THE PROCEDURE TO CLOSE THE THRUST
REVERSERS. IF YOU DO NOT OBEY THE INSTRUCTIONS, INJURY TO
PERSONS OR DAMAGE TO EQUIPMENT COULD OCCUR.
(1)
Close the thrust reversers (AMM 78-31-00/201).
(2)
S 415-439-P00
Close the core cowl panels (AMM 71-11-06/201).
(3)
S 415-440-P00
Close the fan cowl panels (AMM 71-11-04/201).
(4)
S 445-441-P00
Do the activation procedure for the thrust reversers
(AMM 78-31-00/201).
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POWER PLANT - INSPECTION/CHECK
______________________________
1.
2.
General
_______
A. There are two tasks in this procedure to make a visual inspection of the
power plant (referred to as the engine). The first task is an inspection
of the engine cowls and of the engine mounts. The second task is a
visual inspection of the engine and strut drains.
TASK 71-00-00-216-001-P00
Examine the Engine Cowls and the Engine Mounts
______________________________________________
A. References
(1) 71-11-04/201, Fan Cowl Panels
(2) 71-11-06/201, Core Cowl Panels
(3) 78-31-00/201, Thrust Reverser System
B. Access
(1) Location Zones
410
Left Engine
420
Right Engine
(2)
C.
Access Panels
413AL/414AR
415AL/416AR
417AL/418AR
423AL/424AR
425AL/426AR
427AL/428AR
Fan Cowl Panel, Left Engine
Thrust Reverser, Left Engine
Core Cowl Panel, Left Engine
Fan Cowl Panel, Right Engine
Thrust Reverser, Right Engine
Core Cowl Panel, Right Engine
Procedure
(1)
(2)
S 216-002-P00
Examine the external side of the inlet cowl, the fan cowl panels,
and the core cowl panels for damage.
S 016-003-P00
Open the fan cowl panels (Ref 71-11-04).
S 046-004-P00
WARNING:
_______
(3)
DO THE THRUST REVERSER DEACTIVATION PROCEDURE TO PREVENT THE
OPERATION OF THE THRUST REVERSER. THE ACCIDENTAL OPERATION OF
THE THRUST REVERSER CAN CAUSE INJURIES TO PERSONS OR DAMAGE TO
EQUIPMENT.
Do this procedure: Thrust Reverser Deactivation for Ground
Maintenance (Ref 78-31-00).
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S 016-005-P00
Open the core cowl panels (Ref 71-11-06).
S 016-006-P00
WARNING:
_______
(5)
(6)
(7)
(8)
(9)
OBEY THE INSTRUCTIONS IN AMM 78-31-00/201 WHEN YOU OPEN THE
THRUST REVERSER. IF YOU DO NOT OBEY THE INSTRUCTIONS, YOU CAN
CAUSE INJURIES TO PERSONS OR DAMAGE TO EQUIPMENT.
Open the thrust reversers (Ref 78-31-00).
S 216-007-P00
Do these steps to examine the inlet cowl:
(a) Examine the inlet cowl flange and the fan case flange for
damage.
(b) Make sure the mounting bolts on the inlet cowl are tight and do
not have damage.
(c) Make sure the pressure relief doors on the inlet cowl are
closed.
(d) Examine the pressure relief doors for loose parts or for
damage.
S 216-008-P00
Do these steps to examine the fan cowl panel:
(a) Examine the latches on the fan cowl panels for loose parts or
for damage.
(b) Examine the cowl area adjacent to the latches for damage.
(c) Examine the pressure relief door for loose parts and for
damage.
(d) Examine the hinges and the adjacent cowl structure for damage.
(e) Make sure the hinges are not loose.
S 216-009-P00
Do these steps to examine the core cowl panels:
(a) Examine the latches on the core cowl panel for loose parts or
for damage.
(b) Examine the cowl area adjacent to the latches for damage.
(c) Examine the hinges and the adjacent structure for damage.
(d) Make sure the hinges are tight.
(e) Examine the internal surface of the core cowl panels for
damage.
(f) Examine the pressure relief doors for loose parts and for
damage.
S 216-010-P00
Do these steps to examine the engine mounts:
(a) Examine these parts of the forward mount that you can see:
1) Make sure the thrust links are tight and do not have
damage.
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2)
D.
Make sure the mounting bolts are tight and do not have
damage.
3) Make sure the center attachment to the compressor
intermediate case is tight and does not have damage.
4) Make sure the platform fitting is tight and does not have
damage.
(b) Examine these parts of the aft mount that you can see:
1) Make sure the mounting bolts are tight and do not have
damage.
2) Make sure the aft mount hanger is tight and does not have
damage.
3) Make sure the tangential and the center links are tight and
do not have damage.
Put the Airplane Back to its Usual Condition.
S 416-011-P00
WARNING:
_______
3.
OBEY THE INSTRUCTIONS IN AMM 78-31-00/201 WHEN YOU CLOSE THE
THRUST REVERSERS. IF YOU DO NOT OBEY THE INSTRUCTIONS, YOU CAN
CAUSE INJURIES TO PERSONS OR DAMAGE TO EQUIPMENT.
(1)
Close the thrust reversers (Ref 78-31-00).
(2)
S 416-012-P00
Close the core cowl panels (Ref 71-11-06).
(3)
S 446-013-P00
Do the thrust reverser activation procedure (Ref 78-31-00).
(4)
S 416-014-P00
Close the fan cowl panels (Ref 71-11-04).
TASK 71-00-00-216-015-P00
Examine the Engine and Strut Drain Systems
__________________________________________
A. References
(1) 54-53-01/401, Strut Pressure Relief and Access Doors
(2) 71-11-04/201, Fan Cowl Panels
(3) 71-11-06/201, Core Cowl Panels
(4) 78-31-00/201, Thrust Reverser System
B. Access
(1) Location Zones
410
Left Engine
420
Right Engine
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(2)
C.
Access Panels
413AL/414AR
415AL/416AR
417AL/418AR
423AL/424AR
425AL/426AR
427AL/428AR
433AL
443AL
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Fan Cowl Panel, Left Engine
Thrust Reverser, Left Engine
Core Cowl Panel, Left Engine
Fan Cowl Panel, Right Engine
Thrust Reverser, Right Engine
Core Cowl Panel, Right Engine
Strut Access Door, Left Engine
Strut Access Door, Right Engine
Procedure
(1)
S 016-016-P00
Open the fan cowl panels (Ref 71-11-04).
S 046-017-P00
WARNING:
_______
(2)
(3)
DO THE THRUST REVERSER DEACTIVATION PROCEDURE TO PREVENT THE
OPERATION OF THE THRUST REVERSER. THE ACCIDENTAL OPERATION OF
THE THRUST REVERSER CAN CAUSE INJURIES TO PERSONS OR DAMAGE TO
EQUIPMENT.
Do this procedure: Thrust Reverser Deactivation for Ground
Maintenance (Ref 78-31-00).
S 016-018-P00
Open the core cowl panels (Ref 71-11-06).
S 016-019-P00
WARNING:
_______
OBEY THE INSTRUCTIONS IN AMM 78-31-00/201 WHEN YOU OPEN THE
THRUST REVERSER. IF YOU DO NOT OBEY THE INSTRUCTIONS, YOU CAN
CAUSE INJURIES TO PERSONS OR DAMAGE TO EQUIPMENT.
(4)
Open the thrust reversers (Ref 78-31-00).
(5)
S 216-020-P00
Examine the engine and strut drain lines for damage, and for the
correct installation.
(6)
S 216-021-P00
Do these steps to examine the strut drain line for a blockage
(Fig. 601):
(a) Remove the strut access panel at the forward end of the strut
(Ref 54-53-01).
(b) Make sure the inlet to the strut drain line does not have a
blockage.
(c) Install the strut access panel (Ref 54-53-01).
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ACCESS PANEL,
433AL (443AL)
STRUT DRAIN
INLET 1
FORWARD LOWER
ENGINE MOUNT
STRUT DRAIN LINE
1
PART OF THE STRUT IS REMOVED TO SHOW
THE STRUT DRAIN LINE
197726
Strut Drain Inlet
Figure 601
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S 216-022-P00
Examine the engine and strut drain lines for signs of leakage
(AMM 71-71-00/601).
Put the Airplane Back to its Usual Condition.
(7)
D.
S 416-023-P00
WARNING:
_______
OBEY THE INSTRUCTIONS IN AMM 78-31-00/201 WHEN YOU CLOSE THE
THRUST REVERSER. IF YOU DO NOT OBEY THE INSTRUCTIONS, YOU CAN
CAUSE INJURIES TO PERSONS OR DAMAGE TO EQUIPMENT.
(1)
Close the thrust reversers (Ref 78-31-00).
(2)
S 416-024-P00
Close the core cowl panels (Ref 71-11-06).
(3)
S 446-025-P00
Do the activation procedure for the thrust reversers (Ref 78-31-00).
(4)
S 416-026-P00
Close the fan cowl panels (Ref 71-11-04).
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POWER PLANT - REMOVAL/INSTALLATION
__________________________________
1.
General
_______
A. This procedure has four tasks to remove and install the power plant
(referred to as the engine). These tasks are shown below in the sequence
that they occur in this procedure:
(1) Prepare the airplane for the power plant removal
(2) Power plant removal with the bootstrap equipment
(3) Power plant installation with the bootstrap equipment
(4) Put the airplane back to its initial condition after the power plant
installation.
B. It is necessary to have platforms or stands to get access to the items
that you will disconnect. Almost all of the items that you will
disconnect are 8-1/2 to 10 feet above the ground.
C. The engine weighs approximately 8500 pounds (3855.5 kilograms). This
weight does not include the equipment to remove and install the engine.
You must be very careful when you remove, install, or move the engine.
If you are not careful, you can cause injuries to yourself or other
personnel, or cause damage to the engine and equipment.
D. Be careful not to apply too much of a load on the strut when you lift the
engine. It is necessary to use load cells to monitor the lift force on
the engine.
E. The bootstrap equipment uses a lever hoist at each of the four support
arms. The lever hoists permit you to adjust the pitch and the roll of
the engine. You operate the two front or the aft lever hoists to adjust
the pitch of the engine. You operate one of the front lever hoists to
adjust the roll of the engine.
F. It is necessary make the airplane level to |3 degrees pitch and roll when
you use the bootstrap equipment (AMM 08-21-00/201).
G. Before you remove the engine, find the center of gravity (c.g.) of the
airplane (AMM 07-11-05/201). It can be necessary to use a tail jack to
support the tail of the airplane when an engine is removed.
H. When you remove the engine, it is necessary to immediately install caps
on all of the tubes, ducts, and electrical connectors after you
disconnect them. Do not remove the caps during the installation until
you connect the tubes, ducts or electrical connectors.
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I.
2.
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After you complete the engine installation, examine the engine, the inlet
cowl, and the area around the engine for tools or loose objects. It is
necessary to operate the engine after you install it. If there are loose
objects around the engine, the objects can get pulled into the engine,
which can cause damage to the engine.
TASK 71-00-02-844-001-P00
Prepare the Airplane for the Power Plant Removal
________________________________________________
A. General
(1) This task puts the airplane in the correct configuration for the
engine removal. This task also has the steps to disconnect the
fuel, hydraulic, pneumatic, and electrical systems at the strut.
B. Equipment
(1) Bootstrap Equipment - B71022-172
(2) Thrust Reverser/Core Cowl Hold-Open Equipment B71020-53.
(3) Container - 5-gallon quantity for fuel
(4) Container - 1-gallon quantity for hydraulic
fluid
(5) Protective pads
C. References
(1) AMM 07-11-05/201, Jacking for Airplane Support with Engines Removed
(2) AMM 08-21-00/201, Leveling
(3) AMM 20-41-00/201, Static Grounding
(4) AMM 24-22-00/201, Electrical Power - Control
(5) AMM 27-81-00/201, Leading Edge Slat System
(6) AMM 29-11-00/201, Main Hydraulic Systems
(7) AMM 71-11-04/401, Fan Cowl Panels
(8) AMM 71-11-06/201, Core Cowl Panels
(9) AMM 71-11-06/401, Core Cowl Panels
(10) AMM 71-21-00/601, Engine Mounts
(11) AMM 78-31-00/201, Thrust Reverser System
D. Access
(1) Location Zones
410
Left Engine Nacelle
420
Right Engine Nacelle
(2)
Access Panels
413AL/414AR
415AL/416AR
417AL/418AR
423AL/424AR
425AL/426AR
427AL/428AR
436CL/436CR
437AL/437AR
446CL/446CR
447AL/447AR
Fan Cowl Panels, Left Engine
Thrust Reversers, Left Engine
Core Cowl Panels, Left Engine
Fan Cowl Panels, Right Engine
Thrust Reversers, Right Engine
Core Cowl Panels, Right Engine
Core Cowl Skirt Fairing, Left Engine
Aft Segment of Underwing Fairing, Left Engine
Core Cowl Skirt Fairing, Right Engine
Aft Segment of Underwing Fairing, Right Engine
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E.
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Put the Airplane in the Correct Configuration for the Engine Removal.
(1)
(2)
(3)
(4)
(5)
S 864-002-P00
Ground the airplane to an approved grounding lug (AMM 20-41-00/201).
S 864-003-P00
Make sure the airplane is level to |3 degrees pitch and roll
(AMM 08-21-00/201).
S 864-004-P00
Find if it is necessay to install a tail jack to the airplane with
the engine(s) removed (AMM 07-11-05/201).
(a) If it is necessary, install the tailjack (AMM 07-11-05/201).
S 864-005-P00
Make sure the forward thrust levers are fully aft (the idle
position) and attach a DO-NOT-OPERATE tag.
S 864-006-P00
Supply electrical power (AMM 24-22-00/201).
S 864-007-P00
WARNING:
_______
(6)
(7)
MAKE SURE THE SPAR VALVE IS CLOSED BEFORE YOU REMOVE THE
ENGINE. IF THE SPAR VALVE IS OPEN, THE FUEL CAN DRAIN AND
CAUSE INJURIES TO PERSONS.
Do these steps to make sure the applicable engine and spar valves
are closed:
(a) For the left engine, make sure these circuit breakers on the
main power distribution panel, P6, are closed:
1) 6C1, FUEL COND CONT L
2) 6E1, FUEL VALVES L SPAR
(b) For the right engine, make sure these circuit breakers on the
main power distribution panel, P6, are closed:
1) 6C2, FUEL COND CONT R
2) 6E2, FUEL VALVES R SPAR
(c) Put the FUEL CONTROL switch on the control stand to the CUTOFF
position and attach a DO-NOT-OPERATE tag.
(d) Make sure the ENG VALVE and the SPAR VALVE lights on the
control stand are not on.
S 864-008-P00
Do these steps to keep the applicable engine and spar valves closed:
(a) For the left engine, open these circuit breakers on the P6
panel and attach DO-NOT-CLOSE tags:
1) 6C1, FUEL COND CONT L
2) 6E1, FUEL VALVES L SPAR
(b) For the right engine, open these circuit breakers on the P6
panel and attach DO-NOT-CLOSE tags:
1) 6C2, FUEL COND CONT R
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2)
(8)
6E2, FUEL VALVES R SPAR
S 864-009-P00
Do these steps to close the supply shutoff valve for the engine
driven pump (EDP):
(a) For the left engine, make sure this circuit breaker on the
overhead circuit breaker panel, P11, is closed:
1) 11D28, HYDRAULIC ENG PUMP SUPPLY LEFT
(b) For the right engine, make sure this circuit breaker on the
overhead circuit breaker panel, P11, is closed:
1) 11D29, HYDRAULIC ENG PUMP SUPPLY RIGHT
(c) Make sure the fire handle switch for the applicable engine on
the aft electronic control panel, P8, is to the normal
position.
(d) Push the manual override switch below the fire handle switch.
CAUTION:
_______
(e)
(f)
(9)
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DO NOT TURN THE FIRE HANDLE SWITCH AFTER YOU PULL IT.
YOU TURN THE FIRE HANDLE SWITCH, THE FIRE BOTTLE WILL
RELEASE ITS CONTENTS.
IF
Pull the applicable fire handle switch on the P8 panel.
Make sure the indication for the EDP supply shutoff valve moves
to the CLOSE position.
S 864-010-P00
Retract the leading edge slats (AMM 27-81-00/201).
S 864-011-P00
(10) Remove the pressure from the applicable (left or the right)
hydraulic system (AMM 29-11-00/201).
S 044-012-P00
WARNING:
_______
DO THE THRUST REVERSER DEACTIVATION TO PREVENT THE OPERATION OF
THE THRUST REVERSERS. THE ACCIDENTAL OPERATION OF THE THRUST
REVERSERS CAN CAUSE INJURIES TO PERSONS OR DAMAGE TO EQUIPMENT.
(11) Do this procedure: Thrust Reverser Deactivation for Ground
Maintenance (AMM 78-31-00/201).
S 844-013-P00
(12) Put the protective pads on the exhaust sleeve (one on each side).
S 014-014-P00
(13) Remove the bolts (3B) and the aft skirt fairings (4) from each side
of the strut (Fig. 401):
S 014-015-P00
(14) Remove the bolts (5A) and the aft skirt fairing brackets (5B) from
each side of the strut (Fig. 402).
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MAINTENANCE MANUAL
1A. BOLT
(2 LOCATIONS ON EACH SIDE)
SEE
B
SEE
INBD
A
1C. BOLT
(10 LOCATIONS ON THE OUTBOARD SIDE)
(7 LOCATIONS ON THE INBOARD SIDE)
1D. AFT SEGMENT OF THE
UNDERWING FAIRING
(ONE ON EACH SIDE)
2. BOLT
(ONE ON EACH SIDE)
4. AFT SKIRT FAIRING
(ONE ON EACH SIDE)
A
3B. BOLT
(3 LOCATIONS
ON EACH SIDE)
3A. BOLT
(10 LOCATIONS ON EACH SIDE)
5. BOLT
(4 LOCATIONS ON EACH COWL)
6. WASHER
(4 LOCATIONS ON EACH COWL)
7. CORE COWL PANEL
HOLD-OPEN PAD
(2 LOCATIONS ON
EACH COWL)
CORE
COWL PANEL
BOLT STORAGE
HOLES
8. SCREW
(4 LOCATIONS
ON EACH COWL)
B
107637
Preparation for Engine Removal
Figure 401
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MAINTENANCE MANUAL
SEE
SEE
A
B
INBD
INBD
3. BOLT
(2 LOCATIONS)
2. INBOARD
BRACE
1A. CABLE
4. BRACKET
6. AFT
INBOARD ARM
BOLT
5. SHORT BRACE
5B. AFT SKIRT
FAIRING
BRACKET
FWD
5A. BOLT (2 LOCATIONS)
9. OUTBOARD
BRACE
A
10. NUT
1B. STRUT
THRU-ROD
2. CABLE
8. BOLT
(2 LOCATIONS)
7. BRACKET
11. AFT
OUTBOARD
ARM
12. BOLT
CORE COWL
PANEL
13. SHORT BRACE
FWD
B
108563
Aft Bootstrap Equipment Installation
Figure 402
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S 494-016-P00
(15) If you will use the bootstrap equipment to remove the engine, do
these steps to install the aft bootstrap components:
NOTE:
____
(a)
(b)
(c)
(d)
(e)
(f)
(g)
(h)
It is easier to install the aft bootstrap components before
you open the core cowl panels. The hold-open equipment for
the core cowl panels also attach to the aft bootstrap
components.
Remove the bolts (1C) and the aft segment of the underwing
fairing (1D) from each side of the strut (Fig. 401).
Remove the bolts for the ground support equipment (GSE) from
the strut (Fig. 401).
1) Remove two forward bolts (1A) from each side of the strut.
2) Remove the aft bolt (2) from each side of the strut.
3) Keep the bolts (1A and 2) for the installation procedure.
Install the thru-rod (1B) through the strut and put the aft
inboard arm (6) in its position on the inboard side of the
strut (Fig. 402).
1) Install the bolt that attaches the aft inboard arm (6) to
the strut.
2) Tighten the bolt to 175-265 pound-inches (19.78-29.95
newton meters).
Put the aft outboard arm (11) in its position on the strut
(Fig. 402).
1) Install the nut (10) to the thru-rod (1B).
2) Install the bolt (12) to attach the bottom of the aft
outboard arm to the strut.
3) Tighten the bolt (12) to 175-265 pound-inches (19.78-29.95
newton meters).
4) Tighten the nut (10) to 200-250 pound-inches (22.60-28.25
newton meters).
Attach the brackets (4 and 7) to each side of the strut with
the bolts (3 and 8) (Fig. 402).
1) Tighten the bolts (3 and 8) to 175-265 pound-inches
(19.78-29.95 newton meters).
Install the short braces (5 and 13) (Fig. 402).
Install the inboard brace (2) and the outboard brace (9)
(Fig. 402).
Put the cable (2) in the pulley on the aft outboard arm (11).
S 494-017-P00
(16) If you will keep the core cowl panels on the airplane during the
engine removal, do these steps:
(a) Remove screws (8) from each core cowl panel (Fig. 401).
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(b)
Attach the hold-open pads (7) to the core cowl panels with the
bolts (5) and the washers (6) (Fig. 401).
NOTE:
____
(c)
(d)
(e)
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The bolts (5) are kept in the storage holes on the
hold-open pads.
Keep the screws (8) for the installation procedure in the
storage holes of the hold-open pads.
Attach the hold-open arms (1 and 3) to the hold-open pads on
the core cowl panels (Fig. 403).
Open the core cowl panels, but do not attach the hold-open rods
to the engine (AMM 71-11-06/201).
1) Attach the hold-open arms (1 and 3) to the aft brackets on
the strut (Fig. 403).
S 014-018-P00
(17) If you will not keep the core cowl panels on the airplane during the
engine removal, remove the core cowl panels (AMM 71-11-06/401).
S 014-019-P00
(18) Remove the fan cowl panels (AMM 71-11-04/401).
S 014-020-P00
WARNING:
_______
OBEY THE INSTRUCTIONS IN AMM 78-31-00/201 WHEN YOU OPEN THE
THRUST REVERSERS. IF YOU DO NOT OBEY THE INSTRUCTIONS, YOU CAN
CAUSE INJURIES TO PERSONS OR DAMAGE TO EQUIPMENT.
(19) Open the thrust reversers (AMM 78-31-00/201).
S 494-024-P00
(20) Do these steps to install the hold-open equipment for the thrust
reversers (Fig. 404):
(a) Put the actuator lock around the actuator rod as shown.
(b) Turn the adjustment handle until the actuator lock cannot move.
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MAINTENANCE MANUAL
SEE A
1. AFT
HOLD-OPEN
ARM
3. FORWARD
HOLD-OPEN ARM
2. CABLE
CORE COWL
PANEL
A
107731
Core Cowl Hold-Open Equipment
Figure 403
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MAINTENANCE MANUAL
A
A
THRUST
REVERSER
(REF)
STRUT
(REF)
ACTUATOR (REF)
(2 LOCATIONS) 1
MOUNTING BRACKET
FOR THE T/R COWL
OPENING ACTUATOR
(REF)
ACTUATOR
LOCK
(2 LOCATIONS)
A-A
1
ACCESS TO THE THRUST REVERSER HYDRAULIC
COWL OPENING ACTUATOR IS UNDER THE
THRUST REVERSER
300744
Thrust Reverser Hold-Open Equipment
Figure 404
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(c)
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Remove the hold-open rods from the engine and put them in the
stow brackets on the thrust reversers.
S 844-025-P00
(21) Put protective pads on the engine and the cowls to prevent damage
from the engine removal equipment.
F.
S 224-128-P00
(22) Do a check of the vibration isolator clearances on the forward and
aft engine mounts (AMM 71-21-00/601).
Disconnect the Fuel, Hydraulic, Pneumatic, and Electrical Systems at the
Strut.
S 864-026-P00
WARNING:
_______
(1)
(2)
REMOVE THE ELECTRICAL POWER WHEN YOU DISCONNECT THE FUEL,
HYDRAULIC, AND ELECTRICAL SYSTEMS AT THE STRUT. IF YOU DO NOT
REMOVE THE ELECTRICAL POWER, YOU CAN CAUSE INJURIES TO PERSONS
OR DAMAGE TO EQUIPMENT.
Remove electrical power (AMM 24-22-00/201).
S 034-027-P00
Do these steps to disconnect the main fuel supply line on the right
side of the strut (Fig. 405):
(a) Release the pressure from the fuel supply line (1).
1) Put a container below the fuel pump filter.
2) Loosen the retaining bolt (8) for the fuel filter
cover (7).
3) Move the fuel filter cover (7) to loosen the seal.
4) Let the pressure release from the fuel supply line.
5) When pressure is released, tighten the retaining bolt (8)
for the fuel filter cover (7) to 150-200 pound-inches
(16.95-22.60 newton meters).
(b) Put the container below the connection for the fuel supply
line (1) on the right side of the strut.
(c) Turn the coupling sleeve counterclockwise to loosen the threads
of the hose nut.
NOTE:
____
The coupling sleeve moves in the direction of the rigid
fuel line when you turn the sleeve counterclockwise.
This causes the teeth on the locknut to disengage, which
permits you to loosen the hose nut.
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3. HYDRAULIC PUMP
CASE DRAIN HOSE
SEE
A
4. PACKING
SEE
C
5. HYDRAULIC
SUPPLY
INLET HOSE
2. HYDRAULIC
PRESSURE
OUTLET HOSE
5A. PACKING
5B. PACKING
1. ENGINE MAIN FUEL
SUPPLY LINE
(FLEXIBLE)
SEE
B
FWD
5C. PACKING
A
7. FUEL PUMP
FILTER COVER
1. ENGINE MAIN
FUEL SUPPLY LINE
(FLEXIBLE)
COUPLING
SLEEVE
PIN (EXAMPLE)
(3 LOCATIONS)
RETAINER
RING
HOSE NUT
PACKING
GROOVE
HOSE FITTING
4. PACKING
LOCKNUT
FWD
9. FUEL PUMP
6. MAIN FUEL
SUPPLY LINE
(RIGID)
8. RETAINING
BOLT
B
C
108116
Fuel System Drain
Figure 405
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(d)
Disconnect the flexible fuel line (1) from the rigid fuel
line (6).
1) Let the fuel drain from the fuel line.
2) Remove and discard the packing (4) from the rigid fuel
line (6).
CAUTION:
_______
(e)
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MAKE SURE YOU PUT CAPS ON THE FLEXIBLE FUEL LINE AND ON
THE RIGID FUEL LINE. YOU CAN GET CONTAMINATION IN THE
FUEL IF YOU DO NOT INSTALL CAPS ON THE FUEL LINES, WHICH
CAN CAUSE DAMAGE TO THE ENGINE.
Install caps on the flexible fuel line (1) and on the rigid
fuel line (6).
S 034-028-P00
CAUTION:
_______
(3)
MAKE SURE YOU DISCONNECT THE V-BAND HINGE FROM THE STRUT.
YOU DO NOT DISCONNECT THE V-BAND HINGE, YOU WILL CAUSE
STRUCTURAL DAMAGE TO THE AIRPLANE.
IF
Disconnect the V-band hinge (12) from each side of the engine
(Fig. 406).
(a) Remove the nut (11), the washer (10), the bolt (8) and the
pin (9) to disconnect the V-band hinge (12).
S 034-029-P00
CAUTION:
_______
DO NOT PUT KINKS IN THE HYDRAULIC LINES. THE KINKS CAN
DECREASE THE FLUID FLOW, WHICH CAN CAUSE DAMAGE TO THE ENGINE
DRIVEN PUMP (EDP) OR LOW PRESSURE IN THE AIRPLANE HYDRAULIC
SYSTEM.
CAUTION:
_______
MAKE SURE YOU PUT CAPS ON THE HYDRAULIC LINES AFTER YOU
DISCONNECT THE LINES. THE HYDRAULIC FLUID CAN GET
CONTAMINATION IF YOU DO NOT PUT CAPS ON THE HYDRAULIC LINES,
WHICH CAN CAUSE DAMAGE TO THE HYDRAULIC SYSTEM.
CAUTION:
_______
IMMEDIATELY CLEAN UP ALL THE HYDRAULIC FLUID THAT SPILLS.
SPILLED HYDRAULIC FLUID CAN CAUSE CORROSION DAMAGE TO THE
AIRPLANE OR TO THE ENGINE.
(4)
THE
Do these steps to disconnect the hydraulic lines at the right side
of the strut (Fig. 405):
(a) Disconnect the hydraulic supply line (5) and drain the fluid
into the container.
1) Remove and discard the packing (5B) from the hydraulic
supply line (5).
2) Put caps on the hydraulic supply line (5) and on the
adjacent line on the engine.
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SEE
A
2. HYDRAULIC
PUMP CASE
DRAIN HOSE
3. HYDRAULIC
SUPPLY
INLET HOSE
4. COUPLING
1. MAIN FUEL
SUPPLY LINE
13. HYDRAULIC
PRESSURE
OUTLET
HOSE
5. NUT
6. SEAL
12. FAN DUCT VEE
BAND HINGE
(RIGHT SIDE
SHOWN, LEFT
SIDE IS ALMOST
THE SAME
7. START
DUCT
11. NUT
FWD
8. BOLT
10. WASHER
9. PIN
A
107737
Right Side Fan Case Disconnects
Figure 406
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(b)
(c)
(5)
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Disconnect the hydraulic pressure line (2) and drain the fluid
into the container.
1) Remove and discard the packing (5C) from the hydraulic
pressure line (2).
2) Put caps on the hydraulic pressure line (2) and on the
adjacent line on the engine.
Disconnect the hydraulic pump case drain (3) and drain the
fluid into the container.
1) Remove and discard the packing (5A) from the hydraulic pump
case drain line (3).
2) Put caps on the hydraulic pump case drain line (3) and on
the adjacent line on the engine.
S 034-030-P00
Remove the coupling (4) for the starter duct (7) (Fig. 406).
(a) Wrap a protective pad around the starter duct (7).
(b) Safety the starter duct (7) to surrounding structure to prevent
damage.
S 034-031-P00
CAUTION:
_______
(6)
(7)
(8)
IMMEDIATELY PUT CAPS ON THE ELECTRICAL CONNECTORS AFTER YOU
DISCONNECT THEM. THE ELECTRICAL CONNECTORS CAN GET
CONTAMINATION, WHICH CAN CAUSE DAMAGE TO THE CONNECTORS.
Do these steps to disconnect the electrical connectors:
(a) Disconnect the electrical connectors (1 thru 9) from the left
side of the strut (Fig. 407).
1) Put caps on all of the electrical connectors.
(b) Disconnect the electrical connectors (4 thru 6) from the right
side of the strut (Fig. 408).
1) Put caps on all of the electrical connectors.
S 864-032-P00
If it is necessary for other maintenance, supply electrical power
(AMM 24-22-00/201).
S 034-033-P00
Do these steps to remove the top section of the 14th-stage bleed
duct (13) on the right side of the engine (Fig. 408):
(a) Remove the coupling (2) that attaches the 14th-stage bleed duct
to the precooler.
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SEE A
ELECTRICAL CONNECTORS 1
1. 2. 3. 4. 5. 6. 7. 8. 9.
FWD
EEC
A
ELECTRICAL CONNECTOR IDENTIFICATION
1
2
INDEX
NUMBER
CONNECTOR
NUMBER
TORQUE WRENCH
SETTING
(POUND-INCHES)
REQUIRED TORQUE
POUND-INCHES
LEFT STRUT
RIGHT STRUT
1
2
3
4
5
6
7
8
9
D1092P
D1090P
P1022
D1072P
D1078P
D1074P
D1070P
D1088P
D1080P
NOT APPLICABLE
72-77
21-26
72-77
85-90
72-77
85-90
72-77
85-90
2
83-88
24-29
83-88
99-104
83-88
99-104
83-88
99-104
D1092J
D1090J
D1022J
D1072J
D1078J
D1074J
D1070J
D1088J
D1080J
D1292J
D1290J
D1222J
D1272J
D1278J
D1274J
D1270J
D1288J
D1280J
MATING RECEPTACLE
TIGHTEN ELECTRICAL CONNECTOR
HAND TIGHT PLUS 1/8 TURN
107744
Electrical Connector Installation
Figure 407
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SEE A
3. SEAL
PRECOOLER
1. NUT
4. ELECTRICAL
CONNECTOR,
D1084P
5. ELECTRICAL
CONNECTOR,
D1082P
2. COUPLING
6. ELECTRICAL
CONNECTOR,
D1064P
7. 10TH-STAGE
BLEED DUCT
SEE C
8. SEAL
9. COUPLING
11. NUT
FWD
10. 14TH-STAGE
BLEED DUCT
SEE B
A
107777
Pneumatic Duct Installation
Figure 408 (Sheet 1)
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12. PRECOOLER
14. COUPLING
15. SEAL
13. 14TH-STAGE
BLEED DUCT
16. NUT
17. HIGH PRESSURE
SHUTOFF VALVE
(HPSOV)
10TH-STAGE
BLEED DUCT
(REF)
SEE
D
B
TO
PRECOOLER
18. 10TH-STAGE
BLEED DUCT
26. BOLT
25. WASHER
24. 14TH-STAGE
SUPPORT
ROD
23. WASHER
20. SEAL
22. NUT
19. COUPLING
HPSOV
(REF)
HPSOV
(REF)
21. NUT
FWD
D
C
141101
Pneumatic Duct Installation
Figure 408 (Sheet 2)
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(b)
(c)
(d)
(9)
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Remove the coupling (14) that attaches the 14th-stage bleed
duct to the high pressure shutoff valve (HPSOV).
Remove the nut (22), the washers (23 and 25), and the bolt (26)
to remove the 14th-stage bleed duct from the support rod (24).
Put caps on the precooler and the HPSOV where the 14th-stage
bleed duct was removed.
S 034-034-P00
Do these steps to remove the top section of the 10th-stage bleed
duct (18) on the right side of the engine (Fig. 408):
(a) Remove the coupling (9) that attaches the 10th-stage bleed duct
to the precooler.
(b) Remove the coupling (19) and the 10th-stage bleed duct (18).
(c) Put caps on the precooler and the open end of the check valve
where the 10th-stage bleed duct was removed.
S 034-035-P00
CAUTION:
_______
MAKE SURE YOU PUT A CAP ON THE STRUT DRAIN LINE WHEN YOU
DISCONNECT THE DRAIN. IF YOU DO NOT PUT A CAP ON THE DRAIN
LINE, THE DRAIN CAN HAVE A BLOCKAGE.
(10) Disconnect the strut drain line (4) from the left side of the strut
(Fig. 409).
(a) Put caps on the two connectors for the strut drain line.
3.
TASK 71-00-02-004-036-P00
Power Plant Removal with the Bootstrap Equipment
________________________________________________
A. General
(1) This task has the steps to install the bootstrap equipment, and to
remove the engine with the bootstrap equipment.
B. Equipment
(1) Bootstrap Equipment - B71022-172
(2) Tool Set, Engine Change - B71024-17
(3) Thrust Reverser/Core Cowl Hold-Open Equipment B71020-53.
(4) Use one of the three cradle systems that
follow:
(a) From Stang Hydronics, Inc.,
1) Transportation Stand - 110505-1
2) Cradle - 110506-101
(b) From PF Industries, Inc.,
1) Shipping Buck, Cradle, and Adapters PF71-2037-1
(c) From Advanced Ground Systems Engineering
(AGSE) Corp.,
1) Transportation Stand - AM-2510
2) Cradle - AM-2472
(5) Protective pads
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C.
D.
References
(1) AMM 71-11-06/201, Core Cowl Panels
(2) AMM 78-31-00/201, Thrust Reverser System
Access
(1) Location Zones
410
Left Engine Nacelle
420
Right Engine Nacelle
(2)
E.
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Access Panels
413AL/414AR
415AL/416AR
417AL/418AR
423AL/424AR
425AL/426AR
427AL/428AR
Fan Cowl Panels, Left Engine
Thrust Reversers, Left Engine
Core Cowl Panels, Left Engine
Fan Cowl Panels, Right Engine
Thrust Reversers, Right Engine
Core Cowl Panels, Right Engine
Install the Bootstrap Equipment.
NOTE:
____
(1)
(2)
The aft bootstrap components were installed in the task to
prepare the airplane for the power plant removal.
S 494-037-P00
Do these steps to install the forward bootstrap components
(Fig. 409):
(a) Put the upper forward support (2) in its position at the
forward end of the strut and hold it there.
(b) Install the lower forward support (3) below the upper forward
support (2).
1) Make sure the guide roller (1) is locked and in the correct
position.
(c) Attach the inboard and the outboard support arms (5) to the
upper forward support (2) with the pin (6).
S 494-038-P00
Do these steps to install the forward and the aft handling adapters
(Fig. 410 or 410A):
(a) Attach the forward handling adapter base to the engine with the
bolts.
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B
1. GUIDE
ROLLER
2. UPPER
FORWARD
SUPPORT
3. LOWER
FORWARD
SUPPORT
4. STRUT
DRAIN
LINE
A
107766
Forward Bootstrap Equipment Installation
Figure 409 (Sheet 1)
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6. LOCK
PIN
5. SUPPORT
ARM
FWD
B
107617
Forward Bootstrap Equipment Installation
Figure 409 (Sheet 2)
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BOLT
(8 LOCATIONS)
SEE B
SAFETY
PIN
SEE A
FORWARD HANDLING
ADAPTER BRACKET
PIN
ENGINE
CASE
FORWARD HANDLING
ADAPTER BASE
A
PIN
SAFETY PIN
AFT HANDLING
ADAPTER
ENGINE
CASE
B
108117
Stang Hydronics Handling Adapter Installation
Figure 410 (Sheet 1)
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C
INBD
FWD
SEE
D
FWD HANDLING
ADAPTER
AFT
HANDLING
ADAPTER
LATCH BOLT
FWD HANDLING
ADAPTER BASE
SAFETY
PIN
TEE PIN
CLAMP BLOCK
CRADLE
CRADLE
C
D
117419
Stang Hydronics Handling Adapter Installation
Figure 410 (Sheet 2)
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BOLT
(8 LOCATIONS)
FORWARD HANDLING
ADAPTER BASE
SAFETY
PIN
SEE
B
ENGINE
CASE
SEE
A
FORWARD HANDLING
ADAPTER BRACKET
PIN
A
PIN
ENGINE
CASE
AFT HANDLING
ADAPTER
SAFETY
PIN
B
178520
PF Industries Handling Adapter Installation
Figure 410A (Sheet 1)
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SEE C
SEE D
INBD
FWD HANDLING
ADAPTER BASE
FWD
AFT HANDLING
ADAPTER
SAFETY
PIN
SAFETY PIN
PIN
CRADLE
CRADLE
C
D
178531
PF Industries Handling Adapter Installation
Figure 410A (Sheet 2)
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SEE B
SEE A
A
B
F26567
Advanced Ground Systems Engineering Handling Adapter Installation
Figure 410B (Sheet 1)
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SEE
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C
INBD
FWD
SEE
D
AFT
HANDLING
ADAPTER
FWD HANDLING
ADAPTER
FWD HANDLING
ADAPTER BASE
SAFETY
PIN
TEE PIN
CRADLE
CRADLE
C
D
F26643
Advanced Ground Systems Engineering Handling Adapter Installation
Figure 410B (Sheet 2)
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(b)
Remove the forward and the aft handling adapters from the
cradle.
Attach the forward handling adapters to the forward handling
adapter bases with the pins and the safety pins.
Attach the aft handling adapters to the engine case with the
pins and the safety pins.
(c)
(d)
(3)
(4)
S 494-039-P00
Do these steps to install the dynamometers to the bootstrap
equipment:
(a) Install a dynamometer to the cable at the aft inboard arm.
(b) Install a dynamometer to each forward support arm (inboard side
and outboard side).
S 494-040-P00
Do these steps to install the hoists to the bootstrap equipment
(Fig. 411 or 411A).
NOTE:
____
(a)
(b)
(c)
(5)
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If you remove the engine when the airplane is on the jacks,
make sure the length of the chains is sufficient before you
install the hoists.
Use shackles to attach the forward hoists (1 and 9) to the
dynamometers on the inboard and outboard sides.
Use shackles to attach the aft inboard hoist (3) to the
dynamometer on the inboard end of the cable.
Use a shackle to attach the aft outboard hoist (6) to the
outboard end of the cable.
S 494-041-P00
Attach the cradle (10) to the hoists (Fig. 411 or 411A).
(a) Move the transportation stand (shipping buck), with the cradle
attached, below the engine from the aft side.
(b) Remove all the rails or tow bars that are on the transportation
stand (shipping buck) and the cradle.
(c) Attach the aft lower arm (7) to the cradle (10) with the pin
(Fig. 411 or 411A).
(d) Attach the hoist cables to the cradle.
1) Attach the forward hoist cables to the forward shackles on
the cradle.
2) Attach the aft hoist cables to the aft lower arms (7) with
the pins.
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5. CABLE
4. DYNAMOMETER
3. AFT INBOARD
HOIST
2. DYNAMOMETER
6. AFT
OUTBOARD
HOIST
1. HOIST
7. AFT LOWER
ARM
8. DYNAMOMETER
9. HOIST
INBD
10. CRADLE
11. SHACKLE
FWD
107625
Stang Hydronics Cradle Installation
Figure 411
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5. CABLE
4. DYNAMOMETER
3. AFT INBOARD
HOIST
2. DYNAMOMETER
1. FWD INBOARD
HOIST
6. AFT
OUTBOARD
HOIST
7. AFT LOWER
ARM
8. DYNAMOMETER
9. HOIST
10. CRADLE
11. SHACKLE
178711
PF Industries Cradle Installation
Figure 411A
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5. CABLE
4. DYNAMOMETER
3. AFT INBOARD
HOIST
2. DYNAMOMETER
6. AFT
OUTBOARD
HOIST
1. HOIST
7. AFT LOWER
ARM
8. DYNAMOMETER
11. SHACKLE
9. HOIST
INBD
10. CRADLE
FWD
F26563
Advanced Ground Systems Emgineering Cradle Installation
Figure 411B
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S 494-042-P00
WARNING:
_______
(6)
ONLY APPROVED PERSONS MUST OPERATE THE LEVER HOISTS. A LEVER
HOIST WITH A LIGHT LOAD CAN RELEASE THE LOAD IF THE CONTROL
LEVER IS NOT IN THE CORRECT POSITION. IF THE LEVER HOIST
RELEASES, IT CAN CAUSE INJURIES TO PERSONS OR DAMAGE TO THE
ENGINE.
Lift the cradle, with the transportation stand (shipping buck)
attached, a maximum of one inch (25.4 mm) to put the transportation
stand (shipping buck) in the correct position.
(a) Let the transportation stand (shipping buck) move to its free
position.
(b) Lower the transportation stand (shipping buck) to the ground.
S 494-043-P00
Disconnect the cradle from the transportation stand (shipping buck).
(a) Remove the clamps or pins that attach the cradle to the
transportation stand (shipping buck).
Remove the Engine with the Bootstrap Equipment.
(7)
F.
(1)
S 494-044-P00
Make sure the thru-rod nut (10) for the aft outboard arm is tight
to 200-250 pound-inches (22.60-28.25 newton meters) (Fig. 402).
(2)
S 494-045-P00
Lift the cradle from the transportation stand (shipping buck) to the
engine.
NOTE:
____
(a)
(b)
Use the forward hoists to adjust the roll of the cradle.
Use the forward and the aft hoists to adjust the pitch of the
cradle.
If it is necessary, help the cradle into the handling adapters
on the engine.
Attach the cradle to the handling adapters (Fig. 410 or 410A):
1) Install the pin and the safety pin through the forward
handling adapters on each side of the engine.
2) If the cradle has clamp blocks, turn the clamp block and
tighten the latch bolt for the aft handling adapters.
3) If the cradle does not have clamp blocks, install the pin
and the safety pin through the aft handling adapters.
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S 024-046-P00
WARNING:
_______
(3)
(4)
MONITOR THE LOAD ON ALL OF THE DYNAMOMETERS. DO NOT APPLY MORE
THAN 6,500 POUNDS TO THE FORWARD INBOARD DYNAMOMETER OR 5,200
POUNDS TO THE FORWARD OUTBOARD DYNAMOMETER. DO NOT APPLY MORE
THAN 1,200 POUNDS TO THE AFT DYNAMOMETER. IF YOU APPLY TOO
MUCH OF A LOAD, YOU CAN CAUSE DAMAGE TO THE BOOTSTRAP
EQUIPMENT, TO THE STRUT, OR TO THE ENGINE.
Do these steps to put the weight of the engine on the bootstrap
equipment:
(a) Operate the aft hoists until the dynamometer shows 900 pounds.
(b) Operate the forward hoists until the inboard dynamometer shows
5,300 pounds and the outboard dynamometer shows 4,300 pounds.
S 034-047-P00
Do the steps that follow to disconnect the engine mounts (Fig. 412):
(a) Use the B71024-17 Tool Set to loosen all of the tension bolts
in the forward and the aft mounts one-half turn.
NOTE:
____
The SN 24B breaker bar is used for bolt breakaway. The
-18 wrench assembly and the S711A flex-head ratchet are
used for bolt run off for the forward mount bolts. The
S711A flex-head ratchet is used for bolt run off for the
aft mount bolts.
1)
(b)
Make sure the loads on the dynamometers are in the
specified limits.
2) Make sure there is no clearance between the mounts and the
strut.
3) If there is clearance between the strut and the mount, lift
the engine until the clearance is gone.
a) Make sure the loads on the dynamometers stay in the
specified limits.
Loosen all of the tension bolts one-half turn again.
NOTE:
____
1)
(c)
(5)
When you loosen the tension bolts one full turn, the
bootstrap equipment supports the weight of the engine.
Make sure
specified
2) Make sure
mounts.
Remove all of
the loads on the dynamometers stay in the
limits.
there is no clearance between the strut and the
the tension bolts.
S 024-048-P00
Do these steps to lower the engine to the transportation stand
(shipping buck) (Fig. 413 or 414):
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SPREADER HINGE
(2 LOCATIONS)
2
RETAINER
(2 LOCATIONS)
BARREL NUT
(4 LOCATIONS)
SEE
B
SEE
1
A
RETAINER
(4 LOCATIONS)
BARREL NUT
(4 LOCATIONS)
SHEAR PIN
AFT ENGINE
MOUNT
FWD
A
A
WASHER
(4 LOCATIONS)
TENSION BOLT
(4 LOCATIONS)
A
1
AFT MOUNT WITH FOUR RETAINERS AND
FOUR BARREL NUTS.
2
AFT MOUNT WITH TWO BARREL NUT ASSEMBLIES.
EACH ASSEMBLY HAS TWO BARREL NUTS, ONE
SPREADER HINGE, AND ONE RETAINER.
AREA WHERE CLEARANCE
IS PERMITTED
A-A
634023
Engine Mount Bolt Installation
Figure 412 (Sheet 1)
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TENSION BOLT
(4 LOCATIONS)
WASHER
(4 LOCATIONS)
SHEAR PIN
B
B
BARREL NUT
(4 LOCATIONS)
FWD
FORWARD
ENGINE
MOUNT
RETAINER
(4 LOCATIONS)
B
C
C
SHIM (PART OF
TOOL SET B-71024)
AREA WHERE
CLEARANCE IS
PERMITTED
FORWARD
ENGINE
MOUNT
B-B
FWD
C-C
107640
Engine Mount Bolt Installation
Figure 412 (Sheet 2)
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INBD
CRADLE
FWD
TRANSPORTATION
STAND
1. ENGINE
SEE A
BOLT
(8 LOCATIONS)
PIN
(4 LOCATIONS)
CLAMP JAW
A
108118
Stang Hydronics Cradle to Transportation Stand Installation
Figure 413
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INBD
FWD
1. ENGINE
SHIPPING
BUCK
CRADLE
SEE
A
PIN
(4 LOCATIONS)
CRADLE
SHIPPING
BUCK
A
178720
PF Industries Cradle to Shipping Buck Installation
Figure 414
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WARNING:
_______
(a)
(b)
(c)
(d)
(e)
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KEEP YOUR HANDS AND TOOLS AWAY FROM THE ENGINE MOUNTS WHEN
YOU LOWER THE ENGINE. THE ENGINE AND THE STRUT CAN MOVE
SUDDENLY WHEN THE SHEAR PINS DISENGAGE. THIS CAN CAUSE
INJURIES TO PERSONS OR DAMAGE TO EQUIPMENT.
Slowly lower the forward and the aft hoists at an equal rate
until the shear pins are clear of the strut.
Lower the engine 3 to 4 inches.
Operate the forward hoists to roll the cradle until it is
level.
Continue to lower the engine and the cradle to the
transportation stand (shipping buck).
Install the pins and clamps to attach the cradle to the
transportation stand (shipping buck):
S 034-049-P00
Use tape to attach the upper fitting of the aft engine mount to the
lower fitting to prevent damage during transportation.
(6)
S 094-050-P00
Disconnect the forward and the aft chains from the cradle.
(7)
S 024-051-P00
Move the transportation stand (shipping buck) forward until the
engine is clear of the strut.
Remove the Forward Bootstrap Equipment and Close the Engine Cowls.
(8)
G.
NOTE:
____
If you will not install an engine for more than 24 hours or if
the wind velocity is more than the limits for the hold-open
equipment, it is necessary to close the engine cowls. The forward
bootstrap components must be removed before you can close the
thrust reversers.
(1)
S 094-052-P00
Remove the four hoists from the bootstrap equipment.
(2)
S 094-053-P00
Remove the three dynamometers from the bootstrap equipment.
(3)
S 094-054-P00
Do these steps to remove the forward bootstrap components
(Fig. 409):
(a) Remove pins (6) and the inboard and the outboard support
arms (5).
(b) Remove the lower forward support (3) and the upper forward
support (2).
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S 094-055-P00
Do these steps to remove the hold-open equipment for the thrust
reversers (Fig. 404):
WARNING:
_______
FULLY OPEN THE THRUST REVERSERS BEFORE YOU REMOVE THE
HOLD-OPEN EQUIPMENT. THE THRUST REVERSER WILL CLOSE IF
THE OPENING SYSTEM FOR THE THRUST REVERSERS IS NOT
PRESSURIZED. THIS CAN CAUSE INJURIES TO PERSONS OR DAMAGE
TO EQUIPMENT.
WARNING:
_______
OBEY THE INSTRUCTIONS IN AMM 78-31-00/201 WHEN YOU OPEN
THE THRUST REVERSERS. IF YOU DO NOT OBEY THE
INSTRUCTIONS, YOU CAN CAUSE INJURIES TO PERSONS OR DAMAGE
TO EQUIPMENT.
(a)
(b)
(c)
Fully open the thrust reversers (AMM 78-31-00/201).
Loosen the adjustment handle on the actuator lock.
Remove the actuator lock.
S 414-124-P00
WARNING:
_______
(5)
(6)
OBEY THE INSTRUCTIONS IN AMM 78-31-00/201 WHEN YOU CLOSE THE
THRUST REVERSERS. IF YOU DO NOT OBEY THE INSTRUCTIONS, YOU CAN
CAUSE INJURIES TO PERSONS OR DAMAGE TO EQUIPMENT.
Close the thrust reversers (AMM 78-31-00/201).
S 494-057-P00
If the core cowl panels were not removed from the airplane, remove
the hold-open equipment for the core cowl panels:
(a) Hold the core cowl panel open and remove the hold-open
arms (1 and 3) from the bracket on the strut (Fig. 403).
(b) Close the core cowl panels (AMM 71-11-06/201).
(c) Remove the bolts (5), the washers (6) and hold-open
pads (7) from the core cowl panels (Fig. 401).
1) Remove the screws (8) from the storage holes on the
hold-open pads.
2) Install the screws (8) in the core cowl panels.
3) Install the bolts (5) with the washers (6) in the bolt
storage holes on the hold-open pads.
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TASK 71-00-02-404-058-P00
Power Plant Installation with the Bootstrap Equipment
_____________________________________________________
A. General
(1) This task installs the engine with the bootstrap equipment. This
task also has the steps to remove the bootstrap equipment after the
engine installation.
B. Equipment
(1) Bootstrap Equipment - B71022-172
(2) Tool Set - B71024
(3) Thrust Reverser/Core Cowl Hold-Open Equipment B71020-74.
(4) Use one of the three cradle systems that
follow:
(a) From Stang Hydronics, Inc.,
1) Transportation Stand - 110505-1
2) Cradle - 110506-101
(b) From PF Industries, Inc.,
1) Shipping Buck, Cradle, and Adapters PF71-2037-1
(c) From Advanced Ground Systems Engineering
(AGSE) Corp.,
1) Transportation Stand - AM-2510
2) Cradle - AM-2472
C. Consumable Materials
(1) D00010 Antiseize Compound - Bostick Never-Seez
D.
E.
References
(1) AMM 71-21-00/601, Engine Mounts
(2) AMM 71-21-01/401, Foward Lower Engine Mount
(3) AMM 71-21-02/401, Aft Lower Engine Mount
Access
(1) Location Zones
410
Left Engine Nacelle
420
Right Engine Nacelle
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(2)
F.
Access Panels
413AL/414AR
415AL/416AR
417AL/418AR
423AL/424AR
425AL/426AR
427AL/428AR
S 234-060-P00
Get new engine mount bolts and vertical tension bolts, or do the
steps that follow to examine the bolts that were used before to
attach the engine.
NOTE:
____
The steps that follow are applicable to the vertical tension
bolts and the engine mount bolts.
(a)
Visually examine the engine mount bolts and the vertical
tension bolts for damage.
Do a Dye Penetrant Inspection of the engine mount bolts and the
vertical tension bolts (AMM 71-21-00/601).
(b)
(2)
(3)
(4)
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Fan Cowl Panels, Left Engine
Thrust Reversers, Left Engine
Core Cowl Panels, Left Engine
Fan Cowl Panels, Right Engine
Thrust Reversers, Right Engine
Core Cowl Panels, Right Engine
Prepare the Engine for the Installation Procedure.
(1)
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S 224-061-P00
Do the check of the wear limits for the forward and the aft engine
mounts (AMM 71-21-00/601).
S 214-062-P00
Examine the forward engine mount (AMM 71-21-01/401) and the aft
engine mount (AMM 71-21-02/401) for heat damage (discoloration),
cracks, corrosion, wear, loose fasteners, worn bearings, or a sign
of damage to the adjacent structure.
S 214-118-P00
ENGINES WITH A ZEE BRACKET ALONG THE FIRESEAL ON THE LOWER SIDE OF
THE STRUT;
Examine the zee bracket for bending or other damage.
NOTE:
____
The zee bracket is installed on engines manufactured before
1998, and is located along the fireseal that mates with the
top of the engine fan case (NAC WL 141.84). If there is no
zee bracket along the fireseal, you can ignore this step.
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(5)
S 214-119-P00
Examine the engine D-flange for damage from the 11:00 to the 1:00
0'clock postion, aft of the thrust reverser vee.
(6)
S 844-063-P00
Make sure all the steps to Prepare the Airplane for the Power Plant
Removal are completed.
(7)
S 494-064-P00
If it is necessary, do the steps to install the bootstrap equipment
in the Power Plant Removal procedure.
(8)
S 014-065-P00
If it is necessary, open the core cowl panels and the thrust
reversers, and install the applicable hold-open equipment (refer to
the steps to Prepare the Airplane for the Power Plant Removal).
NOTE:
____
G.
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You must remove the fan cowl panels when you install the
engine.
Install the Engine with the Bootstrap Equipment.
S 644-114-P00
CAUTION:
_______
(1)
(2)
ONLY INSTALL NEW MOUNT BOLTS OR MOUNT BOLTS THAT HAD A DYE
PENETRANT INSPECTION. IF THE MOUNT BOLTS ARE NOT SATISFACTORY,
THE BOLTS CAN HAVE FAILURES, WHICH CAN CAUSE DAMAGE TO THE
AIRPLANE OR THE ENGINE.
Apply the antiseize compound to the shank and the threads of all the
tension bolts (four locations on the forward mount and four
locations on the aft mount).
S 644-068-P00
Apply antiseize compound to the shear pins on the forward and aft
engine mounts (Fig. 412).
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(3)
(4)
(5)
(6)
(7)
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S 214-069-P00
Make sure the top surfaces of the engine mounts and the adjacent
surfaces on the strut do not have grease, oil, or other unwanted
material.
S 494-070-P00
Put the transportation stand (shipping buck) with the engine in its
position below the strut.
S 494-071-P00
Attach the bootstrap equipment to the cradle (Fig. 411).
(a) Attach the forward hoist chains to the forward shackles on the
cradle.
(b) If it is necessary, attach the aft lower arms (7) to the cradle
with the pins (Fig. 411).
(c) Attach the aft hoist chains to the aft lower arms on the
cradle.
S 494-072-P00
Install the shim from the tool set to hold the aft end of the
forward engine mount (Fig. 412).
S 494-073-P00
Do these steps to align the engine and the transportation stand
(shipping buck) with the strut (Fig. 413 or 414):
(a) Make sure the cradle is attached to the transportation stand
(shipping buck).
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WARNING:
_______
DO NOT LIFT THE ENGINE WITH THE TRANSPORTATION STAND
(SHIPPING BUCK) MORE THAN ONE INCH FROM THE GROUND. THE
ADDED WEIGHT OF THE TRANSPORTATION STAND (SHIPPING BUCK)
INCREASES THE RISK OF A BOOTSTRAP FAILURE. IF A FAILURE
OCCURS WITH THE ENGINE MORE THAN ONE INCH FROM THE GROUND,
YOU CAN CAUSE INJURIES TO PERSONS OR DAMAGE TO THE ENGINE.
WARNING:
_______
MONITOR THE LOAD ON ALL OF THE DYNAMOMETERS. DO NOT APPLY
MORE THAN 6,500 POUNDS TO THE FORWARD INBOARD DYNAMOMETER
OR 5,200 POUNDS TO THE FORWARD OUTBOARD DYNAMOMETER. DO
NOT APPLY MORE THAN 1,200 POUNDS TO THE AFT DYNAMOMETER.
IF YOU APPLY TOO MUCH OF A LOAD, YOU CAN CAUSE DAMAGE TO
THE BOOTSTRAP EQUIPMENT, TO THE STRUT, OR TO THE ENGINE.
(b)
Lift the engine and the transportation stand (shipping buck) a
maximum of one inch to put the engine in the correct position.
NOTE:
____
It is not necessary for the wheels of the transportation
stand (shipping buck) to be fully off the ground. The
engine will correctly align when the wheels still touch
the ground.
1)
(c)
(d)
(8)
(9)
Let the engine and the transportation stand (shipping buck)
move to their free position.
Lower the engine and the transportation stand (shipping buck)
until they are fully on the ground.
Loosen the bolts or remove the pins to disconnect the cradle
from the transportation stand (shipping buck).
S 494-074-P00
Make sure the nut (10) on the thru-rod is tight to 200-250
inch-pounds (16.6-20.8 foot-pounds or 22.60-28.25 newton-meters)
(Fig. 402).
S 434-075-P00
Remove the tape that attaches the upper fitting to the lower fitting
on the aft engine mount.
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S 424-076-P00
(10) Do these steps to lift the engine to the strut:
CAUTION:
_______
(a)
(b)
(c)
LIFT THE ENGINE WITHOUT A PITCH OR ROLL UNTIL THE ENGINE
IS CLEAR OF THE TRANSPORTATION STAND (SHIPPING BUCK). IF
YOU DO NOT LIFT THE ENGINE WITHOUT A PITCH OR A ROLL, THE
CRADLE OR ENGINE CAN HIT THE TRANSPORTATION STAND
(SHIPPING BUCK). THIS CAN CAUSE DAMAGE TO THE BOOTSTRAP
EQUIPMENT OR TO THE ENGINE.
Lift the engine until it is clear of the transportation stand
(shipping buck).
Continue to lift the engine until there is approximately six
inches between the mounts and the strut.
Adjust the pitch and the roll of the engine until the surfaces
of the mounts align with the strut.
NOTE:
____
(d)
It is necessary adjust the roll of the engine
approximately 5 degrees. Use the forward hoists to
adjust the roll of the engine. Use the aft hoists to
adjust the pitch of the engine.
Do these steps to engage the shear pins:
NOTE:
____
1)
2)
3)
The mounts can move a small quantity until the
mounts are attached to the strut.
Adjust the pitch and the roll of the engine as necessary
while you continue to lift the engine.
Make sure the shim holds the aft end of the forward mount
in the correct position.
Engage the forward shear pins at the same time as the aft
shear pins, or engage the shear pins on either mount a
maximum of 0.10 inch before the shear pins on the other
mount.
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WARNING:
_______
4)
5)
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MONITOR THE LOAD ON ALL OF THE DYNAMOMETERS. DO NOT
APPLY MORE THAN 6,500 POUNDS TO THE FORWARD INBOARD
DYNAMOMETER OR 5,200 POUNDS TO THE FORWARD OUTBOARD
DYNAMOMETER. DO NOT APPLY MORE THAN 1,200 POUNDS TO
THE AFT DYNAMOMETER. IF YOU APPLY TOO MUCH OF A
LOAD, YOU CAN CAUSE DAMAGE TO THE BOOTSTRAP
EQUIPMENT, TO THE STRUT, OR TO THE ENGINE.
Lift the engine until there is a clearance of 0.00-0.060
inch between the strut and the top surfaces of the mounts.
Make sure the loads on the hoists are approximately as
follows:
a) 5,300 pounds on the forward inboard dynamometer.
b) 4,300 pounds on the forward outboard dynamometer.
c) 900 pounds on the aft dynamometer.
S 424-077-P00
(11) Do the steps that follow to attach the engine to the strut
(Fig. 412):
(a) If you will use torque wrench adapters, make sure you set the
torque wrench correctly before you tighten the mount bolts
(AMM 20-11-00/201).
(b) Install the tension bolts, the washers, the barrel nuts, and
the retainers in the forward mount.
1) Use the B71024-17 Tool Set to tighten the bolts evenly to
1935-2365 inch-pounds (161-197 foot-pounds or 218.7-267.2
newton-meters).
NOTE:
____
(c)
(d)
The forward engine mount installation uses
B71024-4, -6, and -7 to tighten the bolts. When
tightening the bolt, the -4 extension must be kept
perpendicular to the -6 torqometer. The -18 wrench
assembly and the S711A flex-head ratchet are used
for bolt run-on.
Remove the shim from the forward mount.
Install the tension bolts, the washers, the barrel nuts, the
spreader hinges, and the retainers in the aft mount.
1) Use the B71024-17 Tool Set to tighten the bolts evenly to
1935-2365 inch-pounds (161-197 foot-pounds or 218.7-267.2
newton-meters).
NOTE:
____
The aft engine mount installation uses B71024-2
or -3, -6, and -7 to tighten the bolts. When
tightening the aft engine mount bolts, the -6
torqometer must be kept axially, in line with the -7
extension assembly. The S711A flex-head ratchet is
used for bolt run-on.
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(e)
(f)
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Do these steps to do a check of the self-locking capability of
the barrel nuts for the forward and aft engine mounts
(Fig. 412).
1) One at a time, loosen the tension bolts and re-tighten
them.
2) As you re-tighten each tension bolt, make sure the barrel
nut run-on torque is a minimum of 50 inch-pounds (4
foot-pounds or 5.6 newton-meters).
a) Replace all of the barrel nuts with a run-on torque
that is less than 50 inch-pounds (4 foot-pounds or 5.6
newton-meters).
3) After you have done a check of the run-on torque,
re-tighten each tension bolt to 1935-2365 inch-pounds
(161-197 foot-pounds or 218.7-267.2 newton-meters).
Repeat the above procedure for the seven remaining tension
bolts on the forward and aft mounts.
S 424-116-P00
(12) Lower the hoists to hold only the weight of the cradle, not the
weight of the engine.
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S 214-115-P00
CAUTION:
_______
MAKE SURE THERE IS NO CLEARANCE BETWEEN THE TOP PLATE OF THE
AFT ENGINE MOUNT AND THE LOWER SPAR WEB AS SHOWN ON FIG. 412.
IF THERE IS CLEARANCE IN THESE AREAS, THE TENSION BOLTS FOR THE
AFT ENGINE MOUNT WILL NOT RECEIVE THE CORRECT PRELOAD ON
INSTALLATION. WITH CLEARANCE IN THESE AREAS, DAMAGE CAN OCCUR
TO THE TENSION BOLTS.
(13) Make sure there is no clearance between the top plate of the aft
mount and the lower spar web of the strut, as shown in Fig. 412.
NOTE:
____
H.
The area where clearance is permitted in shown in the shaded
area on Fig. 412.
Remove the Bootstrap Equipment from the Engine.
NOTE:
____
(1)
The aft bootstrap components are removed in the procedure to
put the airplane back to its usual condition. The hold-open
equipment for the core cowl panels attach to the aft bootstrap
components.
S 094-078-P00
Remove the cradle from the engine (Fig. 410 or 410A):
(a) Remove the pins that attach the forward handling adapters to
the cradle.
(b) Remove the pins or release the clamp blocks that attach the aft
handling adapters.
CAUTION:
_______
(c)
(d)
(e)
(f)
BE CAREFUL WHEN YOU LOWER THE CRADLE. THE CRADLE CAN MOVE
IN THE INBOARD DIRECTION WHEN THE CRADLE IS CLEAR OF THE
ADAPTERS. IF THE CRADLE HITS THE ENGINE, IT CAN CAUSE
DAMAGE TO THE ENGINE.
Lower the cradle to the transportation stand (shipping buck).
Install the clamps or pins to attach the cradle to the
transportation stand (shipping buck) (Fig. 413 or 414).
Disconnect the hoist chains from the cradle.
Move the transportation stand (shipping buck) clear of the
engine.
(2)
S 094-079-P00
Remove the four hoists from the bootstrap equipment.
(3)
S 094-080-P00
Remove the three dynamometers from the bootstrap equipment.
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5.
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S 094-081-P00
Do these steps to remove the forward bootstrap components
(Fig. 409):
(a) Remove pins (6) and the inboard and the outboard support
arms (5).
(b) Remove the lower forward support (3) and the upper forward
support (2).
TASK 71-00-02-844-082-P00
Put the Airplane Back to Its Initial Condition After the Power Plant
____________________________________________________________________
____________
Installation
A. General
(1) This task has the steps to connect the fuel, hydraulic, pneumatic,
and electrical systems at the strut after the engine installation.
This task also has the steps to put the airplane back to its usual
condition.
B. Equipment
(1) Bootstrap Equipment - B71022-172
(2) Thrust Reverser/Core Cowl Hold-Open Equipment B71020-74.
(3) Protective pads
(4) Use one of the strap wrenches that follow:
(a) Balmer - 76-101
(b) Daniels - Model 601:
Daniels Mfg. Corp.; Orlando FL
(c) Glenair - TG-70:
Glenair Inc., Glendale, CA
C. Parts
~¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼ ¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼ ¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼
¦
AMM
¦
¦
AIPC
¦
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»¼¼¼¼¼¼¼¼¼¼ ¼¼¼¼¼¼ ¼¼¼¼¼¼¼¼«
¦ FIG ¦ ITEM
¦
NOMENCLATURE
¦ SUBJECT ¦ FIG ¦ ITEM ¦
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¦ 401 ¦
1A
¦ Bolt
¦ 71-11-06 ¦ 05 ¦ 460
¦
¦
¦
1C
¦ Bolt (Outboard)
¦ 54-52-01 ¦ 07 ¦
40
¦
¦
¦
¦ Bolt (Inboard)
¦
¦
¦
95
¦
¦
¦
1D
¦ Underwing Fairing (Outboard, Left ¦
¦
¦
45
¦
¦
¦
¦ Engine)
¦
¦
¦
¦
¦
¦
¦ Underwing Fairing (Inboard, Left ¦
¦
¦ 100
¦
¦
¦
¦ Engine)
¦
¦
¦
¦
¦
¦
¦ Underwing Fairing (Outboard, Right¦
¦
¦
50
¦
¦
¦
¦ Engine)
¦
¦
¦
¦
¦
¦
¦ Underwing Fairing (Inboard, Right ¦
¦
¦ 105
¦
¦
¦
¦ Engine)
¦
¦
¦
¦
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~¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼ ¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼ ¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼
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AMM
¦
¦
AIPC
¦
»¼¼¼¼¼ ¼¼¼¼¼¼¼¼¼«
»¼¼¼¼¼¼¼¼¼¼ ¼¼¼¼¼¼ ¼¼¼¼¼¼¼¼«
¦ FIG ¦ ITEM
¦
NOMENCLATURE
¦ SUBJECT ¦ FIG ¦ ITEM ¦
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¦
¦
2
¦ Bolt
¦ 71-11-06 ¦ 05 ¦ 465
¦
¦
¦
3A
¦ Bolt
¦ 54-52-54 ¦ 01 ¦
95
¦
¦
¦
3B
¦ Bolt
¦
¦
¦
90
¦
¦
¦
4
¦ Aft Skirt Fairing (Left Side)
¦
¦
¦
80
¦
¦
¦
¦ Aft Skirt Fairing (Right Side)
¦
¦
¦
85
¦
¦
¦
8
¦ Screw
¦ 71-11-06 ¦ 05 ¦
40
¦
¦ 402 ¦
5A
¦ Bolt
¦ 54-52-54 ¦ 01 ¦ 205
¦
¦
¦
5B
¦ Aft Skirt Fairing Bracket
¦
¦
¦ 210
¦
¦ 405 ¦
4
¦ Packing
¦ 73-11-51 ¦ 01 ¦
30
¦
¦
¦
5A
¦ Packing
¦ 29-11-63 ¦ 01 ¦ 112
¦
¦
¦
5B
¦ Packing
¦
¦
¦ 113 or¦
¦
¦
¦
¦
¦
¦ 114
¦
¦
¦
5C
¦ Packing
¦
¦
¦ 133
¦
¦ 406 ¦
4
¦ Coupling
¦ 80-11-01 ¦ 02 ¦ 105
¦
¦
¦
6
¦ Seal
¦
¦
¦ 115
¦
¦
¦
8
¦ Bolt
¦ 71-00-56 ¦ 01 ¦ 435
¦
¦
¦
9
¦ Pin
¦
¦
¦ 455
¦
¦
¦
10
¦ Washer
¦
¦
¦ 445
¦
¦
¦
11
¦ Nut
¦
¦
¦ 450
¦
¦ 408 ¦
2
¦ Coupling
¦ 36-11-07 ¦ 01 ¦
50
¦
¦
¦
3
¦ Seal
¦
¦
¦
55
¦
¦
¦
8
¦ Seal
¦
¦
¦
55
¦
¦
¦
9
¦ Coupling
¦
¦
¦
50
¦
¦
¦
13
¦ 14th Stage Bleed Duct
¦
¦
¦ 115
¦
¦
¦
14
¦ Coupling
¦
¦
¦
70
¦
¦
¦
15
¦ Seal
¦
¦
¦
75
¦
¦
¦
18
¦ 10th Stage Bleed Duct
¦
¦
¦
90
¦
¦
¦
19
¦ Coupling
¦
¦
¦
60
¦
¦
¦
20
¦ Seal
¦
¦
¦
65
¦
¦
¦
22
¦ Nut
¦
¦
¦
20
¦
¦
¦
23
¦ Washer
¦
¦
¦
15
¦
¦
¦
25
¦ Washer
¦
¦
¦
10
¦
¦
¦
26
¦ Bolt
¦
¦
¦
5
¦
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D.
References
(1) AMM 07-11-05/201,
(2) AMM 24-22-00/201,
(3) AMM 29-11-00/201,
(4) AMM 71-00-00/501,
(5) AMM 71-00-03/201,
(6) AMM 71-11-04/401,
(7) AMM 71-11-05/501,
(8) AMM 71-11-06/201,
(9) AMM 71-11-06/401,
Jacking for Airplane Support with Engines Removed
Electrical Power - Control
Main Hydraulic Systems
Power Plant
Engine Preservation/Depreservation
Fan Cowl Panels
Fan Cowl Panel Latches
Core Cowl Panels
Core Cowl Panels
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E.
(10) AMM 71-11-07/501, Core Cowl Panel Latches
(11) AMM 78-31-00/201, Thrust Reverser System
(12) AMM 78-31-02/501, Fan Duct V-Grove Latch Bands
(13) AMM 78-31-04/501, Fan Duct Tension Latches
Access
(1) Location Zones
410
Left Engine Nacelle
420
Right Engine Nacelle
(2)
F.
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Access Panels
413AL/414AR
415AL/416AR
417AL/418AR
423AL/424AR
425AL/426AR
427AL/428AR
436CL/436CR
437AL/437AR
446CL/446CR
447AL/447AR
Fan Cowl Panels, Left Engine
Thrust Reversers, Left Engine
Core Cowl Panels, Left Engine
Fan Cowl Panels, Right Engine
Thrust Reversers, Right Engine
Core Cowl Panels, Right Engine
Core Cowl Skirt Fairing, Left Engine
Aft Segment of Underwing Fairing, Left Engine
Core Cowl Skirt Fairing, Right Engine
Aft Segment of Underwing Fairing, Right Engine
Connect the Fuel, Hydraulic, Pneumatic, and Electrical Systems at the
Strut.
(1)
(2)
S 434-083-P00
Remove the caps and connect the strut drain line (4) at the left
side of the strut (Fig. 409).
S 434-084-P00
Do these steps to install the 10th-stage bleed duct at the right
side of the strut (Fig. 408):
(a) Remove all of the caps from the ducts.
(b) Install new seals (8 and 20) on the two ends of the duct (18).
(c) Install the duct (18) with the two couplings (9 and 19).
(d) Tighten the coupling nuts (11 and 21) to 110-125 pound-inches
(12.43-14.13 newton meters).
S 414-123-P00
CAUTION:
_______
(3)
IT IS NECESSARY TO ALIGN THE TEETH ON THE 14TH-STAGE BLEED DUCT
CORRECTLY WITH THE GROOVES ON THE HIGH PRESSURE SHUTOFF VALVE
(HPSOV). THE 14TH-STAGE BLEED DUCT CAN LEAK IF IT IS NOT
ALIGNED. DAMAGE CAN ALSO OCCUR TO THE HPSOV, THE 14TH-STAGE
BLEED DUCT, OR THE DUCT SEAL.
Do these steps to install the 14th-stage bleed duct at the right
side of the strut (Fig. 408):
(a) Remove the caps from the precooler (12) and the HPSOV (17).
(b) Install new seals (3 and 15) on the 14th-stage bleed duct (13).
(c) Install the 14th-stage bleed duct (13) with the couplings (2
and 14), but do not tighten the couplings at this time.
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(d)
(e)
(f)
(4)
(5)
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Attach the 14-stage bleed duct to the support rod (24) with the
bolt (26), the washers (25 and 23), and the nut (22).
1) Install the bolt (26) from the top side (the head of the
bolt up).
Tighten the coupling nut (1) to 110-125 pound-inches
(12.43-14.13 newton meters).
Tighten the coupling nut (16) to 105-120 pound-inches
(11.87-13.56 newton meters).
S 424-121-P00
Do these steps to connect the starter duct (7) at the right side of
the strut (Fig. 406):
(a) Remove all items used to safety and protect the starter
duct (7).
(b) Remove the caps from the starter duct (7).
(c) Install a new seal (6) on the starter duct.
(d) Connect the starter duct with the coupling (4).
(e) Tighten the coupling nut (5) to 85-100 pound-inches (9.61-11.30
newton meters).
S 434-087-P00
Attach the V-band hinge (12) on each side of the engine with the
pin (9), the bolt (8), the washer (10), and the nut (11) (Fig. 406).
S 864-088-P00
WARNING:
_______
(6)
REMOVE THE
HYDRAULIC,
NOT REMOVE
PERSONS OR
ELECTRICAL POWER WHEN YOU CONNECT THE FUEL, THE
AND THE ELECTRICAL SYSTEMS AT THE STRUT. IF YOU DO
THE ELECTRICAL POWER, YOU CAN CAUSE INJURIES TO
DAMAGE TO EQUIPMENT.
If it is necessary, remove electrical power (AMM 24-22-00/201).
S 434-089-P00
CAUTION:
_______
(7)
SET THE TORQUE WRENCH TO THE SPECIFIED TORQUE VALUE TO GET THE
NECESSARY TORQUE. AN INCORRECT TORQUE VALUE CAN CAUSE DAMAGE
TO THE CONNECTOR AND UNSATISFACTORY LIGHTNING PROTECTION FOR
THE ELECTRICAL CIRCUITS.
Do these steps to connect the electrical connectors at the right
side of the strut (Fig. 408):
(a) Remove the caps from the electrical connectors (4 thru 6) and
from the connectors on the strut.
(b) Connect the electrical connectors (4 thru 6).
(c) Tighten the electrical connectors (4 and 5) as follows:
1) Make sure the torque wrench is set to 72-77 pound-inches
(8.14-8.70 newton meters).
2) Use the torque wrench and the strap wrench to tighten the
electrical connectors (4 and 5) to 83-88 pound-inches
(9.38-9.94 newton meters).
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(d)
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Tighten the electrical connector (6) as follows:
1) Make sure the torque wrench is set to 40-45 pound-inches
(4.52-5.09 newton meters).
2) Use the torque wrench and the strap wrench to tighten the
electrical connector (6) to 45-50 pound-inches (5.09-5.65
newton meters).
S 434-090-P00
CAUTION:
_______
(8)
SET THE TORQUE WRENCH TO THE SPECIFIED TORQUE VALUE TO GET THE
NECESSARY TORQUE. AN INCORRECT TORQUE VALUE CAN CAUSE DAMAGE
TO THE CONNECTOR AND UNSATISFACTORY LIGHTNING PROTECTION FOR
THE ELECTRICAL CIRCUITS.
Do these steps to connect the electrical connectors on the left side
of the strut (Fig. 407):
(a) Remove the caps from the electrical connectors (1 thru 9) and
from the connectors on the strut.
(b) Connect the electrical connectors (1 thru 9).
(c) Tighten the electrical connector (1) as follows:
1) Tighten the electrical connector (1) with your hand.
2) Use the strap wrench to tighten the electrical
connector (1) 1/8 turn.
(d) Tighten the electrical connectors (2, 4, 6, and 8) as follows:
1) Make sure the torque wrench is set to 72-77 pound-inches
(8.14-8.70 newton meters).
2) Use the torque wrench and the strap wrench to tighten the
electrical connectors (2, 4, 6, and 8) to 83-88
pound-inches (9.38-9.94 newton meters).
(e) Tighten the electrical connector (3) as follows:
1) Make sure the torque wrench is set to 21-26 pound inches
(2.37-2.94 newton meters).
2) Use the torque wrench and the strap wrench to tighten the
electrical connector (3) to 24-29 pound-inches (2.71-2.38
newton meters).
(f) Tighten the electrical connectors (5, 7, and 9) as follows:
1) Make sure the torque wrench is set to 85-90 pound-inches
(9.61-10.17 newton meters).
2) Use the torque wrench and the strap wrench to tighten the
electrical connectors (5, 7, and 9) to 99-104 pound-inches
(11.19-11.75 newton meters).
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S 434-091-P00
CAUTION:
_______
DO NOT PUT KINKS IN THE HYDRAULIC LINES. THE KINKS CAN
DECREASE THE FLUID FLOW, WHICH CAN CAUSE DAMAGE TO THE ENGINE
DRIVEN PUMP (EDP) OR LOW PRESSURE IN THE AIRPLANE HYDRAULIC
SYSTEM.
CAUTION:
_______
IMMEDIATELY CLEAN UP ALL THE HYDRAULIC FLUID THAT SPILLS.
SPILLED HYDRAULIC FLUID CAN CAUSE CORROSION DAMAGE TO THE
AIRPLANE OR TO THE ENGINE.
CAUTION:
_______
IN THE STEPS THAT FOLLOW, INSTALL NEW PACKINGS ON THE FITTINGS
WHERE YOU WILL CONNECT THE HYDRAULIC HOSES. IF A NEW PACKING
IS NOT INSTALLED CORRECTLY, LEAKAGE OF HYDRAULIC FLUID CAN
OCCUR. THIS CAN CAUSE CORROSION DAMAGE TO THE AIRPLANE OR TO
THE ENGINE.
(9)
THE
Do these steps to connect the hydraulic lines at the right side of
the strut (Fig. 405):
(a) Remove the caps from the hydraulic pump case drain hose (3) and
from the adjacent fitting on the engine.
(b) Install a new packing (5A) on the fitting where you will attach
the hydraulic pump case drain hose (3).
(c) Connect the hydraulic pump case drain hose (3) to the fitting.
1) Tighten the coupling nut on the hose fitting to 430-470
pound-inches (48.58-53.10 newton meters).
(d) Remove the caps from the hydraulic pressure outlet hose (2) and
from the adjacent fitting on the engine.
(e) Install a new packing (5C) on the fitting where you will attach
the hydraulic pressure outlet hose (2).
(f) Connect the hydraulic pressure outlet hose (2) to the fitting.
1) Tighten the coupling nut on the hose fitting to 1140-1260
pound-inches (128.79-142.35 newton meters).
(g) Remove the caps from the hydraulic supply inlet hose (5) and
from the adjacent fitting on the engine.
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Install a new packing (5B) on the fitting where you will attach
the hydraulic supply inlet hose (5).
Connect the hydraulic supply inlet hose (5) to the fitting.
1) Tighten the coupling nut on the hose fitting to 1520-1680
pound-inches (171.73-189.80 newton meters)
S 434-092-P00
(10) Do these steps to connect the main fuel supply line at the right
side of the strut (Fig. 405):
(a) Remove the caps from the flexible fuel line (1) and from the
rigid fuel line (6) on the engine.
CAUTION:
_______
(b)
(c)
Lubricate a new packing (4) with the petrolatum and install the
packing in the internal groove of the rigid fuel line (6).
Make sure the retainer ring is installed on the hose fitting.
CAUTION:
_______
(d)
MAKE SURE THE PACKING IS CORRECTLY INSTALLED IN THE
INTERNAL PACKING GROOVE OF THE RIGID FUEL LINE (6). IF
THE PACKING IS NOT INSTALLED CORRECTLY, THE FUEL LINE CAN
LEAK.
DO NOT USE TOOLS TO TIGHTEN THE COUPLING ON THE FUEL
SUPPLY LINE. IF YOU TIGHTEN THE COUPLING TOO TIGHT, YOU
CAN CAUSE DAMAGE TO THE COUPLING AND THE FUEL LINE CAN
LEAK.
Connect the flexible fuel line (1) to the rigid fuel line (6).
1) Tighten the coupling with your hand.
NOTE:
____
G.
The three pins in the coupling sleeve will turn
the hose nut.
2) Make sure the hose nut teeth engage the locknut teeth.
Put the Airplane Back to its Usual Condition.
(1)
(2)
(3)
S 864-093-P00
Supply electrical power (AMM 24-22-00/201).
S 864-094-P00
Open the supply shutoff valve for the engine driven pump (EDP).
(a) Push the fire switch handle on the aft electronic control
panel, P8.
(b) Make sure the indication for the EDP supply shutoff valve moves
to the OPEN position.
S 794-095-P00
Examine the engine fuel system for leaks:
(a) For the left engine, remove the DO-NOT-CLOSE tag and close this
circuit breaker on the main power distribution panel, P6:
1) 6E1, FUEL VALVES L SPAR
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(b)
(c)
(d)
(e)
(f)
(g)
(h)
(i)
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For the right engine, remove the DO-NOT-CLOSE tag and close
this circuit breaker on the main power distribution panel, P6:
1) 6E2, FUEL VALVES R SPAR
Put the applicable FUEL CONTROL switch to the RUN position.
Put the FWD and the AFT BOOST PUMP switches for the applicable
fuel tank to the ON position.
Examine the engine fuel system for leaks.
Put the FWD and the AFT BOOST PUMP switches to the OFF
position.
Put the applicable FUEL CONTROL switch to the CUTOFF position.
For the left engine, remove the DO-NOT-CLOSE tag and close this
circuit breaker on the P6 panel:
1) 6C1, FUEL COND CONT L
For the right engine, remove the DO-NOT-CLOSE tag and close
this circuit breaker on the P6 panel:
1) 6C2, FUEL COND CONT R
(4)
S 634-096-P00
If the engine preservation was completed on the spare engine, do the
engine depreservation (AMM 71-00-03/201).
(5)
S 864-098-P00
If it is not necessary for other maintenance, remove electrical
power (AMM 24-22-00/201).
(6)
(7)
S 094-099-P00
Remove all of the protective pads from the engine nacelle.
S 094-100-P00
Do these steps to remove the hold-open equipment for the thrust
reversers (Fig. 404):
(a) Connect the hold-open rods for the thrust reversers to the
brackets on the engine case.
WARNING:
_______
FULLY OPEN THE THRUST REVERSERS BEFORE YOU REMOVE THE
HOLD-OPEN EQUIPMENT. THE THRUST REVERSER WILL CLOSE IF
THE OPENING SYSTEM FOR THE THRUST REVERSERS IS NOT
PRESSURIZED. THIS CAN CAUSE INJURIES TO PERSONS OR DAMAGE
TO EQUIPMENT.
WARNING:
_______
OBEY THE INSTRUCTIONS IN AMM 78-31-00/201 WHEN YOU OPEN
THE THRUST REVERSERS. IF YOU DO NOT OBEY THE
INSTRUCTIONS, YOU CAN CAUSE INJURIES TO PERSONS OR DAMAGE
TO EQUIPMENT.
(b)
(c)
(d)
Fully open the thrust reversers (AMM 78-31-00/201).
Loosen the adjustment handle on the actuator lock.
Remove the actuator lock.
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S 414-101-P00
WARNING:
_______
OBEY THE INSTRUCTIONS IN AMM 78-31-00/201 WHEN YOU CLOSE THE
THRUST REVERSERS. IF YOU DO NOT OBEY THE INSTRUCTIONS, YOU CAN
CAUSE INJURIES TO PERSONS OR DAMAGE TO EQUIPMENT.
(8)
Close the thrust reversers (AMM 78-31-00/201).
(9)
S 824-102-P00
Adjust the V-groove latch bands (AMM 78-31-02/501).
S 824-103-P00
(10) Adjust the tension latches on the thrust reversers
(AMM 78-31-04/501).
S 094-104-P00
(11) If the core cowl panels were not removed, do these steps to remove
the hold-open equipment for the core cowl panels:
(a) Hold the core cowl panel open and remove the hold-open
arms (1 and 3) from the bracket on the strut (Fig. 403).
(b) Close the core cowl panels (AMM 71-11-06/201).
(c) Remove the bolts (5), the washers (6) and hold-open
pads (7) from the core cowl panels (Fig. 401).
1) Remove the screws (8) from the storage holes on the
hold-open pads.
2) Install the screws (8) in the core cowl panels.
3) Install the bolts (5) with the washers (6) in the bolt
storage holes on the hold-open pads.
S 094-105-P00
(12) If you used the bootstrap equipment to install the engine, do these
steps to remove the aft bootstrap components (Fig. 402):
(a) Lift the cable (2) off the pulley on the aft outboard arm (11).
(b) Remove the inboard brace (2) and the outboard brace (9) from
each side of the strut.
(c) Remove the short braces (5 and 13) from each side of the strut.
(d) Remove the aft outboard arm (11) as follows:
1) Loosen the thru-rod nut (10) on the outboard side.
2) Remove the bolt (12) that attaches the outboard arm to the
strut.
3) Remove the thru-rod nut (10) and the aft outboard arm (11).
(e) Remove the aft inboard arm (6) as follows:
1) Remove the bolt that attaches the aft inboard arm to the
strut.
2) Remove the aft inboard arm with the strut thru-rod.
(f) Remove the brackets (4 and 7) from each side of the strut.
(g) Install the bolts (1A and 2) on each side of the strut
(Fig. 401).
(h) Install the aft segment of the underwing fairing (1D) with the
bolts (1C) on each side of the strut (Fig. 401).
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S 414-106-P00
(13) Do these steps to install the aft skirt fairing on the strut:
(a) Install the brackets (5B) for the aft skirt fairing with the
bolts (5A) (Fig. 402).
(b) Install the aft skirt fairing (4) with the bolts (3B and 3A)
(Fig. 401).
S 414-107-P00
(14) If the core cowl panels were removed, install the core cowl panels
(AMM 71-11-06/401).
S 824-108-P00
(15) Adjust the latches for the core cowl panels (AMM 71-11-07/501).
S 414-109-P00
(16) Install the fan cowl panels (AMM 71-11-04/401).
S 824-110-P00
(17) Adjust the latches for the fan cowl panels (AMM 71-11-05/501).
S 864-111-P00
(18) If it is necessary, remove the tailjack (AMM 07-11-05/201).
S 444-112-P00
(19) Do the thrust reverser activation procedure (AMM 78-31-00/201).
S 724-113-P00
(20) Do the test for the power plant that is shown in the Power Plant
Test Reference Table (AMM 71-00-00/501).
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POWER PLANT - MAINTENANCE PRACTICES (PRESERVATION AND DEPRESERVATION)
_____________________________________________________________________
1.
2.
General
_______
A. This procedure contains two tasks. One task is the preservation of an
engine. The other task is the depreservation of an engine.
B. The procedure for the preservation of an installed engine is different
because of two conditions. The conditions are the length of time with no
operation and the weather.
C. If an engine is not scheduled for operation for more than 90 days, it is
necessary to do the dry motor procedure during the preservation.
TASK 71-00-03-622-001-P00
Engine Preservation
___________________
A. Equipment
(1) Fuel System Preservation Adapter Set - B71035
(2) Preservation Cart - CTE 3160
(3) 5-gallon container for fuel (2 are necessary)
B. Consumable Materials
(1) D00124 Flushing Oil - PMC 9852
C. References
(1) 12-13-01/301, Engine - Oil Servicing
(2) 24-22-00/201, Electrical Power - Control
(3) 29-11-05/401, Engine-Driven Pump (EDP)
(4) 71-00-00/201, Power Plant (Operating Instructions)
(5) 71-11-04/201, Fan Cowl Panels
(6) 71-11-06/201, Core Cowl Panels
(7) 72-61-02/401, Accessory Drive Seals
(8) 73-11-02/401, Fuel Pump Filter
(9) 73-21-02/401, Fuel Control Filter
(10) 78-31-00/201, Thrust Reverser System
(11) 79-11-00/301, Engine Oil Storage
D. Access
(1) Location Zones
413
L Power Plant Fan Cowl Panel
414
L Power Plant Fan Cowl Panel
415
L Power Plant Fan Reverser
416
L Power Plant Fan Reverser
423
R Power Plant Fan Cowl Panel
424
R Power Plant Fan Cowl Panel
425
R Power Plant Fan Reverser
426
R Power Plant Fan Reverser
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(2)
E.
Access Panels
413AL
Fan
414AR
Fan
415AL
Fan
416AR
Fan
423AL
Fan
424AR
Fan
425AL
Fan
426AR
Fan
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Cowl Panel (Left)
Cowl Panel (Right)
Reverser (Left)
Reverser (Right)
Cowl Panel (Left)
Cowl Panel (Right)
Reverser (Left)
Reverser (Right)
Engine Preservation
S 622-013-P00
CAUTION:
_______
DO NOT APPLY AN OIL FOR PRESERVATION INTO THE ENGINE GASPATH.
THE OIL WILL POSSIBLY CAUSE DIRT PARTICLES ON THE BLADES AND
VANES WHICH WILL DECREASE THE ENGINE PERFORMANCE.
THE HYDRAULIC FLUID CAN DANGEROUSLY CAUSE CORROSION IN THE MAIN
GEARBOX HOUSING DURING LONG LENGTHS OF TIME BETWEEN ENGINE
OPERATIONS. WITH A TRICHLORETHYLENE SOAKED CLOTH, IMMEDIATELY
CLEAN OFF THE HYDRAULIC FLUID WHICH GETS ON THE MAIN GEARBOX
HOUSING.
(1)
Method I (up to 30 days) - You can keep the installed engines out of
operation up to 30 days if you do the conditions that follow:
(a) The engine was operated in seven days or less.
(b) The engine is not open to the conditions of the weather.
1) The engine is kept in a hangar, or an equivalent building,
or it has a tarp or plastic caps put on, and closed on all
sides.
NOTE:
____
(c)
(d)
(2)
A cap for the bottom is optional.
You can keep the oil system full or you can drain it
(Ref 79-11-00).
After the engine is kept out of operation for 30 days, do the
steps that follow:
1) Fill the oil system (Ref 12-13-01).
2) Operate the engine to remove the condensation and to put
oil through the system.
a) See the Periodic Engine Run-Up procedure.
3) If the oil is not drained, do an oil analysis which is
included in the Periodic Engine Run-Up.
4) Do Method I again for each 30 days the engine is not
operated.
S 622-003-P00
Method II (up to 90 days) - You can keep an installed engine out of
operation up to 90 days if you do the conditions that follow:
(a) The engine was operated in seven days or less.
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(b)
(c)
(d)
(e)
(3)
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The oil system was drained (Ref 79-11-00).
The complete nacelle/engine, or all nacelle/engine openings,
also the inlet and exhaust are sealed off.
1) Also, the engine is installed in a shipping bag or the
equivalent.
After the engine is kept out of operation for 90 days, do the
steps that follow:
1) Fill the oil system (Ref 12-13-01).
2) Operate the engine with the steps from the Periodic Engine
Run-Up.
a) This step is done to remove the condensation and to put
oil through the oil system.
3) Do the applicable preservation procedure if the engine is
to continue out of operation.
4) You can keep the engines done by the Method II preservation
out of operation up to 180 days if they are kept from wet
conditions.
Method III preservation has no limit to the time without
operation, if you do the steps that follow:
1) The preservation of the engine was done by Method II.
2) The preservation of the engine oil system and the engine
fuel system was done by Method III.
3) The engines are kept in an air-conditioned location.
S 622-004-P00
Method III (more than 90 days) - You can keep the installed engines
out of operation for more than 90 days if you do the steps that
follow:
(a) Fuel System Preservation
NOTE:
____
1)
2)
3)
It is not necessary to supply electrical power to the
EEC or the fuel control during the preservation.
If it is necessary, supply electrical power (Ref 24-22-00).
For the left engine, make sure these circuit breakers on
the main power distribution panel, P6, are closed:
a) 6C1, FUEL COND CONT L
b) 6E1, FUEL VALVES L SPAR
For the right engine, make sure these circuit breakers on
the main power distribution panel, P6, are closed:
a) 6C2, FUEL COND CONT R
b) 6E2, FUEL VALVES R SPAR
c) Make sure the applicable FUEL CONTROL switch is in the
cutoff position.
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d)
Make sure the applicable ENG VALVE and SPAR VALVE panel
lights on the control stand are off.
NOTE:
____
4)
5)
6)
8)
During the fuel system preservation, you must
keep the applicable spar fuel valve closed or
the fuel will drain at the strut quick
disconnect coupling. The fuel pump is
lubricated when you flush the oil supplied from
the preservation cart.
For the left engine, open these circuit breakers on the
main power distribution panel, P6, and attach DO-NOT-CLOSE
tags:
a) 6C1, FUEL COND CONT L
b) 6E1, FUEL VALVES L SPAR
For the right engine, open these circuit breakers on the
main power distribution panel, P6, and attach DO-NOT-CLOSE
tags:
a) 6C2, FUEL COND CONT R
b) 6E2, FUEL VALVES R SPAR
Open the left fan cowl panel (Ref 71-11-04).
WARNING:
_______
7)
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DO THE THRUST REVERSER DEACTIVATION PROCEDURE TO
PREVENT THE OPERATION OF THE THRUST REVERSER. THE
ACCIDENTAL OPERATION OF THE THRUST REVERSER CAN CAUSE
INJURY TO PERSONS OR DAMAGE TO EQUIPMENT.
Do this procedure: Thrust Reverser Deactivation for Ground
Maintnenance (Ref 78-31-00).
Open the left core cowl panel (Ref 71-11-06).
WARNING:
_______
OBEY THE INSTRUCTIONS IN AMM 78-31-00/201 WHEN YOU
OPEN THE THRUST REVERSER. IF YOU DO NOT OBEY THE
INSTRUCTIONS, INJURY TO PERSONS OR DAMAGE TO
EQUIPMENT COULD OCCUR.
9) Open the left thrust reverser (Ref 78-31-00).
10) Remove the fuel pump filter (Ref 73-11-02).
a) Examine the fuel pump filter for contamination.
b) If it is necessary, replace the fuel pump filter.
11) Remove the fuel control filter (Ref 73-21-02).
a) Examine the fuel control filter for contamination.
b) If it is necessary, replace the fuel control filter.
12) Remove the water drain plug for the fuel control.
NOTE:
____
The port for the water drain plug is identified as
the H2O DP.
a) Discard the packing from the water drain plug.
13) Install a MS 9193-06 drain fitting, or the equivalent, in
the port for the water drain plug.
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14) Connect one end of a hose to the drain fitting.
15) Put the other end of the hose into a container with a
minimum capacity of five gallons (19 liters).
16) Install the PWA 29486 Adapter to the inlet pad of the fuel
pump with the four bolts.
17) Connect the CTE 3160 Preservation Cart to the quick
disconnect coupling on the PWA 29486 Adapter.
NOTE:
____
The preservation cart must supply PMC 9852 flushing
oil at an inlet pressure of 5-25 psig (34.5-172.4
kPa) and at a minimum temperature of 60° F (16° C).
Be careful not to get unwanted material into the
fuel system.
The equipment must have filters and strainers of no
larger mesh than 40 microns.
18) Add
a)
b)
c)
d)
19)
20)
21)
22)
23)
24)
25)
the flushing oil to the engine as follows:
Set the ignition switch in the OFF position.
Close the fuel control valve.
Close the fuel supply or the spar shutoff valve.
Apply pressure to the main fuel inlet until
approximately two U.S. gallons (8 liters) of liquid
drains from the port.
Disconnect the CTE 3160 preservation cart from the rigid
main fuel supply line.
a) Permit the remaining fluid to drain from the engine
into the container.
Install a cap on the main fuel supply line.
Remove the drain fitting from the port.
Lubricate the packing for the water drain plug with STP.
Install the packing on the water drain plug.
Install the water drain plug, without a lubricant on the
threads, in the port.
a) Tighten the water drain plug to 70-80 pound-inches
(7.9-9.0 newton meters).
Attach the preservation identifier for the fuel system to
the fuel control.
NOTE:
____
WARNING:
_______
The preservation identifier shows the preservation
used and the date of the preservation.
OBEY THE INSTRUCTIONS IN AMM 78-31-00/201 WHEN YOU
CLOSE THE THRUST REVERSER. IF YOU DO NOT OBEY THE
INSTRUCTIONS, INJURY TO PERSONS OR DAMAGE TO
EQUIPMENT COULD OCCUR.
26) Close the left thrust reverser (Ref 78-31-00).
27) Close the left core cowl panel (Ref 71-11-06).
28) Close the left fan cowl panel (Ref 71-11-04).
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(b)
29) Do the activation procedure for the thrust reversers
(Ref 78-31-00).
30) For the left engine, remove the DO-NOT-CLOSE tags and close
these circuit breakers on the P6 panel:
a) 6C1, FUEL COND CONT L
b) 6E1, FUEL VALVES L SPAR
31) For the right engine, remove the DO-NOT-CLOSE tags and
close these circuit breakers on the P6 panel:
a) 6C2, FUEL COND CONT R
b) CE2, FUEL VALVES R SPAR
Oil System Preservation
NOTE:
____
1)
The oil system preservation is necessary for engines out
of operation for more than 90 days.
Put the applicable container below the drain plugs of the
oil tank and the main gearbox.
NOTE:
____
The oil tank capacity is 28 quarts.
gearbox capacity is 6 quarts.
The main
2)
3)
4)
5)
Remove the drain plug from the bottom of the oil tank.
Remove the drain plug from the bottom of the main gearbox.
Remove the main oil filter (Ref 79-21-05).
Clean the magnetic chip detectors (Ref 79-21-10).
a) Do not install the magnetic chip detectors.
6) Let the engine oil drain until the engine oil falls in
drops (approximately one-half hour).
7) Install a new main oil filter (Ref 79-21-05).
8) Install the magnetic chip detectors (Ref 79-21-10).
9) Install the drain plugs in the oil tank and the main
gearbox.
a) Tighten the drain plug in the oil tank to 200-225
pound-inches (22.596-25.421 newton meters).
b) Tighten the drain plug in the main gearbox to 35-40
pound-inches (3.954-4.519 newton meters).
10) Fill the oil tank with new engine oil (Ref 12-13-01).
WARNING:
_______
USE AMM 71-00-00/201 TO OPERATE THE POWER PLANT. IF
YOU DO NOT USE THIS PROCEDURE, YOU CAN CAUSE DAMAGE
TO EQUIPMENT OR INJURY TO PERSONS.
11) Use the Power Plant Dry-Motor procedure to motor the engine
until the oil pressure increases (Ref 71-00-00).
12) Use the Power Plant Dry-Motor procedure to do the engine
shutdown (Ref 71-00-00).
13) Operate the engine as follows:
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WARNING:
_______
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USE AMM 71-00-00/201 TO OPERATE THE POWER PLANT.
IF YOU DO NOT USE THIS PROCEDURE, YOU CAN CAUSE
DAMAGE TO EQUIPMENT OR INJURY TO PERSONS.
a)
(c)
(d)
(e)
(f)
(g)
Use the Power Plant Operation (Normal) procedure to
start the engine (Ref 71-00-00).
b) Set the power lever to minimum idle.
c) Permit the engine to become stable at minimum idle for
five minutes.
d) Set the power lever for 1.13-1.14 EPR.
e) After the main oil temperature is 220° F (104° C),
operate the engine for five more minutes.
f) Set the power lever to minimum idle.
g) Permit the engine to become stable at minimum idle for
five minutes.
h) Use the Power Plant Operation (Normal) procedure to do
the engine shutdown (Ref 71-00-00).
Put a container below the drain plugs of the oil tank and the
main gearbox.
Remove the drain plugs from the oil tank and the main gearbox.
1) Let the engine oil drain for approximately one-half hour
until the it falls in drops.
Install the drain plug in the main gearbox with the steps that
follow:
1) Lubricate the new packing for the drain plug with engine
oil.
2) Install the packing on the drain plug.
3) Lubricate the threads of the drain plug with engine oil.
4) Install the drain plug in the insert in the main gearbox.
a) Tighten the drain plug to 35-40 pound-inches
(3.954-4.519 newton meters).
b) While you hold the insert, install the lockwire to the
drain plug.
Install the drain plug in the oil tank with the steps that
follow:
1) Lubricate the new packing for the drain plug with engine
oil.
2) Install the packing on the drain plug.
3) Lubricate the threads of the drain plug with engine oil.
4) Install the drain plug in the oil tank.
a) Tighten the drain plug to 200-225 pound-inches
(22.597-25.422 newton meters).
For the preservation of the internal section of the main
gearbox at the locations of the accessory gearbox cover, do the
steps that follow:
1) Remove the accessory gearbox covers from the pads on the
main gearbox where the components are not installed.
2) Apply engine oil to the open surfaces from which the covers
were removed.
3) Lubricate the threads of the bolts with engine oil.
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4)
(h)
(i)
(j)
Install the covers to the main gearbox with the bolts and
the nuts.
a) Tighten the bolts to 275-300 pound-inches (31-34 newton
meters).
Put a tag on the oil tank cap with the preservation date.
Examine the indications of the humidity.
1) Examine the engine each 90 days if the engine is not kept
below some type of cover.
2) Examine the engine each 180 days if the engine is kept
below some type of cover.
If the relative humidity is more than 40 percent, do the steps
that follow:
1) Fill the oil tank (Ref 12-13-01).
WARNING:
_______
USE AMM 71-00-00/201 TO OPERATE THE POWER PLANT. IF
YOU DO NOT USE THIS PROCEDURE, YOU CAN CAUSE DAMAGE
TO EQUIPMENT OR INJURY TO PERSONS.
2)
(k)
(l)
Use the Power Plant Dry-Motor procedure to motor the engine
until the oil pressure increases (Ref 71-00-00).
3) Continue to motor the engine for five minutes.
a) Permit the oil to flow through the engine.
b) Obey the limits for a continuous starter operation.
4) Use the Power Plant Dry-Motor procedure to do the engine
shutdown (Ref 71-00-00).
5) Make an analysis of the engine oil for water and acid
contamination.
6) If the contamination found is more than the limits, operate
the engine with the steps in the Periodic Engine Run-Up.
7) Do the preservation procedure again.
a) Use the specified procedure for the length of time the
engine is kept out of operation.
Seal off all of the nacelle/engine, or all nacelle/engine
openings (the inlet and exhaust included).
Keep the relative humidity below 40 percent in the
nacelle/engine with the steps that follow:
1) Apply 26-52 pounds (12-24 kg) of dehydrating agent equally
between the inlet, exhaust, and the engine components.
NOTE:
____
The weather controls the quantity. You must hang
the dehydrating agent to keep the dehydrating agent
and the engine parts apart.
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2)
Put the humidity indications in the inlet and the exhaust
at a location where you can see them.
NOTE:
____
(m)
(4)
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It is recommended you examine the relative humidity
of the engine each 90 days (if not kept below cover)
or each 180 days (if kept below cover). If the
relative humidity increases to more than 40 percent,
you must do the steps to examine the engine oil for
water and acid contamination.
You are permitted to keep the engines out of operation if the
Method III preservation is completed in 40 percent relative
humidity:
1) You can keep the engine in storage for 90 days more if you
put it below a tarp or equivalent cover.
2) You can keep the engine in storage for 180 days more if you
keep it in a hangar or equivalent structure, where it has
protection from wet weather.
S 862-005-P00
Periodic Engine Run-Up
NOTE:
____
You must operate the engine for a sufficient quantity of time
and power to dry the condensation in the oil system.
WARNING:
_______
(a)
(b)
(c)
(d)
(e)
(f)
USE AMM 71-00-00/201 TO OPERATE THE POWER PLANT. IF YOU
DO NOT USE THIS PROCEDURE, YOU CAN CAUSE DAMAGE TO
EQUIPMENT OR INJURY TO PERSONS.
Use the Power Plant Operation (Normal) procedure to start the
engine (Ref 71-00-00).
Permit the engine to become stable at minimum idle for five
minutes.
Move the thrust lever forward to 1.13-1.14 EPR.
1) Permit the engine to become stable for five minutes.
2) Make sure the oil temperature is 104° C (220° F) or more.
Move the thrust lever rearward to minimum idle to permit the
engine to become cool.
1) Operate the engine at minimum idle for five minutes.
Use the Power Plant Operation (Normal) procedure to do the
engine shutdown (Ref 71-00-00).
Make an analysis of the engine oil for water as follows:
1) Open the fan cowl panels (Ref 71-11-04).
2) Get a 4 oz (100 ml) sample of the engine oil.
3) Do the Karl Fisher ASTMD-1744 Water Analysis to find out
how much water is in the engine oil.
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4)
If more than 800 parts/million (ppm) by weight or volume of
water is found, change the engine oil (Ref 79-11-00).
NOTE:
____
(g)
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800 ppm is the maximum quantity of water permitted
in the PWA 521 engine oils.
Make an analysis of the engine oil for acid as follows:
1) Get a 4 oz (100 ml) sample of the engine oil.
2) Get a 4 oz (100 ml) sample of new engine oil.
3) Do the ASTMD-664 Total Acid Number (TAN) (titrated to PH
11.0) analysis to compare the TAN of the new engine oil and
the used engine oil.
NOTE:
____
There is a difference in the TAN for PWA 521 engine
oils because of the different types.
4)
(h)
If the TAN for the used engine oil is more than 0.2 above
the TAN of the new engine oil, change the engine oil
(Ref 79-11-00).
5) Close the fan cowl panels (Ref 71-11-04).
If the water or acid was more than the limits, do the steps
that follow to make sure the new engine oil is in all of the
oil system.
WARNING:
_______
1)
2)
3)
4)
5)
6)
7)
3.
USE AMM 71-00-00/201 TO OPERATE THE POWER PLANT. IF
YOU DO NOT USE THIS PROCEDURE, YOU CAN CAUSE DAMAGE
TO EQUIPMENT OR INJURY TO PERSONS.
Use the Power Plant Operation (Normal) procedure to start
the engine (Ref 71-00-00).
Permit the engine to become stable at minimum idle for five
minutes.
Move the thrust lever forward to 1.13-1.14 EPR.
a) Permit the engine to become stable for five minutes.
Make sure the engine oil temperature is 104° C (220° F) or
more.
Move the thrust lever rearward to minimum idle.
Operate the engine at minimum idle for five minutes to
permit the engine to become cool.
Use the Power Plant Operation (Normal) procedure to do the
engine shutdown (Ref 71-00-00).
TASK 71-00-03-632-006-P00
Engine Depreservation
_____________________
A. References
(1) 12-13-01/301, Engine - Oil Servicing
(2) 29-11-05/401, Hydraulic Pump
(3) 72-61-02/401, Accessory Drive Seals
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B.
Access
(1) Location Zones
413
L Power
414
L Power
415
L Power
416
L Power
423
R Power
424
R Power
425
R Power
426
R Power
(2)
C.
Access Panels
413AL
Fan
414AR
Fan
415AL
Fan
416AR
Fan
423AL
Fan
424AR
Fan
425AL
Fan
426AR
Fan
Plant
Plant
Plant
Plant
Plant
Plant
Plant
Plant
Fan
Fan
Fan
Fan
Fan
Fan
Fan
Fan
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Cowl Panel
Cowl Panel
Reverser
Reverser
Cowl Panel
Cowl Panel
Reverser
Reverser
Cowl Panel (Left)
Cowl Panel (Right)
Reverser (Left)
Reverser (Right)
Cowl Panel (Left)
Cowl Panel (Right)
Reverser (Left)
Reverser (Right)
Procedure
(1)
(2)
(3)
(4)
(5)
S 212-007-P00
Examine the main gearbox housing for corrosion caused by a leak of
the hydraulic fluid.
S 962-008-P00
If you find corrosion, do the steps that follow:
(a) Remove the hydraulic pump (Ref 29-11-05).
(b) Look for hydraulic fluid in the empty space in the main
gearbox.
(c) If you find hydraulic fluid, replace the EDP Drive Oil Seal
(Ref 72-61-02).
S 632-009-P00
Depreservation procedure for the Method I preservation.
(a) No depreservation is necessary.
(b) If it is necessary, do the servicing procedure for the oil
system (Ref 12-13-01).
S 632-010-P00
Depreservation procedure for Method II preservation.
(a) Remove the covers from the inlet, exhaust, and the
nacelle/engine.
(b) Do the servicing procedure for the oil system (Ref 12-13-01).
S 632-011-P00
Depreservation procedure for Method III preservation.
(a) Remove the indications for the humidity and the blockage used
to seal the engine openings from the ambient humidity.
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(b)
(c)
(d)
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Remove the dehydrating agent in the tailpipe and the fan case.
Do the servicing procedure for the oil system (Ref 12-13-01).
No special fuel system depreservation is necessary.
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POWER PLANT - MAINTENANCE PRACTICES (ACOUSTIC PANEL REPAIR LIMITS)
__________________________________________________________________
1.
2.
General
_______
A. This procedure has the data to make sure the noise certification standard
for the engine nacelle is not more than the specified limits. You use
the area (in square inches) of the repaired acoustic linings to calculate
the noise certification standard.
B. It is necessary to make sure the engine nacelle is in the limit for the
noise certification standard when the acoustic lining is repaired or
replaced. The acoustic lining is installed on the inlet cowl, the fan
case, the thrust recverser, and the turbine exhaust sleeeve.
TASK 71-00-04-222-001-P00
Acoustic Panel Lining Repair Limits
___________________________________
A. Access
(1) Location Zones
410
Left Engine Nacelle
420
Right Engine Nacelle
B.
Procedure
(1)
(2)
S 222-002-P00
Refer to the maintenance records or measure the area of the repaired
acoustic lining for these parts (in square inches):
(a) The inlet cowl (IC)
(b) The engine fan case (EFC)
(c) The thrust reverser (TR)
(d) The turbine exhaust sleeve (TES).
S 222-003-P00
Use the areas from the step above in the equation that follows to
find the noise certification standard:
NOTE:
____
The denominators in this equation are the maximum areas
of the acoustic lining that can be repaired for one of the
engine cowls if no other cowls have repairs.
~¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼
¦ NOISE CERTIFICATION STANDARD = (IC) + (EFC) + (TR) + (TES)
¦
¦
--------------¦
¦
504
792
648
1944
¦
²¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¹
(a) Make sure the noise certification standard is less than
1.00 square inch.
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(b)
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This step is an example to do a check of the noise
certification standard:
NOTE:
____
The noise certification standard for this example is
permitted because it is less than 1.00 inch.
- (IC)
= 150 square inches
- (EFC) =
- (TR)
50 square inches
= 110 square inches
- (TES) = 100 square inches
~¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼
¦ 150 + 50 + 110 + 100 = 0.582
¦
¦ ---------¦
¦ 504
792
648
1944
¦
²¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¹
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POWER PLANT - MAINTENANCE PRACTICES (ENGINE INTERMIX/SUBSTITUTION)
__________________________________________________________________
1.
General
_______
A. This procedure has instructions for the interchangeability of the engine
configurations. The three different engine configurations are as
follows:
(1) Two PW2040 engines
(2) Two PW2037 engines.
(3) One PW2037(M) engine and one PW2037 engine
(a) A PW2037(M) engine is a PW2040 engine that was changed to the
thrust rating of a PW2037 engine. You cannot change the thrust
rating of a PW2037 engine to the thrust rating of a PW2040
engine.
B. Use the table that follows to find the correct paragraph for the
applicable engine configuration:
~¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼ ¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼
¦
ENGINE CONFIGURATION
¦
USE
¦
»¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼ ¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼«
PARAGRAPH
¦
¦
CHANGE FROM
¦
CHANGE TO
¦
NO.
¦
»¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼«
¦ 2 PW2040 ENGINES
¦ 1 PW2037 and 1 PW2037(M)
¦
2
¦
»¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼«
¦ 2 PW2040 ENGINES
¦ 2 PW2037 ENGINES
¦
2
¦
»¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼«
¦ 2 PW2037 ENGINES
¦ 2 PW2040 ENGINES
¦
3
¦
»¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼«
¦ 1 PW2037 and 1 PW2037(M)
¦ 2 PW2040 ENGINES
¦
3
¦
»¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼«
¦ 1 PW2037 and 1 PW2037(M)
¦ 2 PW2037 ENGINES
¦
4
¦
»¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼«
¦ 2 PW2037 ENGINES
¦ 1 PW2037 and 1 PW2037(M)
¦
5
¦
²¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼…¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼…¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¹
2.
TASK 71-00-07-962-001-P00
Replace One or Two PW2040 Engines With PW2037 Engines
_____________________________________________________
A. General
(1) This task gives instructions for replacing the following
combinations of engines:
(a) Changing from (2) PW2040 engines to (2) PW2037 engines.
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(b)
B.
C.
Changing from (2) PW2040 engines to (1) PW2037 and (1)
PW2037(M).
Changing from (2) PW2040 engines to (2) PW2037(M) engines.
(c)
References
(1) AMM 24-22-00/201, Electrical Power - Control
(2) AMM 34-61-03/201, Flight Management Computer Program Pins
(3) AMM 71-00-00/501, Power Plant - General
(4) AMM 71-00-02/401, Power Plant
(5) AMM 71-21-01/401, Forward Lower Engine Mount
(6) AMM 71-21-02/401, Aft Lower Engine Mount
(7) AMM 73-21-08/401, EEC Data Entry Plug
(8) PPBU 71-00-02, Powerplant Buildup Manual
(9) WDM 22-32-14
(10) WDM 34-61-14
(11) WDM 34-61-24
Access
(1) Location Zones
119/120
Main Equipment Center
411
Left Engine
421
Right Engine
(2)
D.
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Access Panels
119BL
Main Equipment Center
Procedure
(1)
S 212-002-P00
Make sure the buildup of the replacement PW2037 engine is the same
configuration as the removed PW2040 engine (PPBU 71-00-02).
NOTE:
____
(a)
Use the quick engine change (QEC) kit to make sure the
replacement engine has the correct configuration.
If the replacement PW2037 engine does not have the
configuration for the applicable airplane, make sure these
parts are correct:
CAUTION:
_______
1)
MAKE SURE THE CORRECT ENGINE MOUNTS ARE INSTALLED ON
THE ENGINE. THE VIBRATION ISOLATED AND THE
NONISOLATED MOUNTS ARE NOT INTERCHANGEABLE. IF YOU
DO NOT INSTALL THE CORRECT MOUNTS, YOU CAN CAUSE
DAMAGE TO THE ENGINE AND THE AIRPLANE.
Make sure the engine mounts are vibration isolated mounts
(AMM 71-21-01/401 and 71-21-02/401).
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3)
Make sure the hydraulic pump is an approved part for the
Boeing 757-200 (refer to the pump nameplate)
Make sure the Electronic Engine Control (EEC) is a Hamilton
Standard P/N 783600-XX-YYY, or P/N 815770-X-YYY, as
applicable (refer to the nameplate on the EEC).
NOTE:
____
4)
The P/N will change for Pressure Burner Sensor Range
and EEC software revision (-X(X)-YYY).
Make sure the fuel flow transmitter has the same part
number as the one on the engine you will replace.
(2)
S 962-003-P00
Replace the PW2040 engine with the PW2037 engine (AMM 71-00-02/401).
(3)
S 862-004-P00
Remove electrical power if it is supplied (AMM 24-22-00).
(4)
S 962-008-P00
If you replace only one PW2040 engine with a PW2037 engine, do these
steps to change the remaining PW2040 engine to a PW2037(M) engine:
NOTE:
____
(a)
For information on the data entry plug (DEP) and the engine
nameplate, refer to PW SB 72-244.
Change the data entry plug from a PW2040 DEP to a PW2037 DEP:
1) Remove the PW2040 DEP (AMM 73-21-08/401).
2) Make a note of the last two numbers of the PW2040 DEP.
CAUTION:
_______
3)
4)
MAKE SURE THE LAST TWO NUMBERS OF THE DATA ENTRY PLUG
(DEP) FOR THE PW2037 ARE THE SAME AS THE LAST TWO
NUMBERS OF THE PW2040 DEP. IF THE LAST TWO DIGITS
ARE NOT THE SAME, THE EEC WILL NOT OPERATE
CORRECLTLY.
Get a PW2037 DEP with the same last two numbers as the
PW2040 DEP.
Install the PW2037 DEP (AMM 73-21-08/401).
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(b)
(5)
(6)
(7)
Change the engine nameplate from a PW2040 to a PW2037(M):
1) Remove and discard the nameplate with the PW2040
identification.
2) Install a nameplate with the PW2037(M) identification.
S 012-005-P00
Open the access door to the main equipment center.
S 962-044-P00
Change the engine program pins for flight management computers
(FMC's) to get the airframe/engine identification for PW2037 engines
(AMM 34-61-03/201, WDM 34-61-14, and WDM 34-61-24).
S 962-050-P00
Change the engine program pins for the thrust management computer
(TMC) to get the airframe/engine identification for PW2037 engines
(WDM 22-32-14).
(8)
S 412-045-P00
Close the access door to the main equipment center.
(9)
S 862-046-P00
Supply electrical power (AMM 24-22-00/201).
S 212-047-P00
(10) Do a check of the EICAS CONF/MCDP display.
(a) Put the EEC MAINT POWER swith on the right sidewall panel, P61,
to the ALTN position.
(b) Select the EPCS page on the EICAS.
(c) Make sure the P(S) DEP/EEC message is not displayed for the
left or right engine.
(d) Select the CONF/MCDP page on the EICAS.
(e) Make sure EEC PW2037 is displayed for the left and right
engines.
(f) Put the EEC MAINT POWER switch on the P61 panel to the NORM
position.
S 722-012-P00
(11) Do the test for the power plant that is shown in the Power-Plant
Test-Reference Table (AMM 71-00-00/501).
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TASK 71-00-07-962-013-P00
Replace PW2037 Engines with PW2040 Engines
__________________________________________
A. General
(1) This task gives instructions for replacing the following
combinations of engines:
(a) Changing from (2) PW2037 or (2) PW2037(M) engines to (2) PW2040
engines.
(b) Changing from (1) PW2037 and (1) PW2037(M) engine by replacing
the PW2037 with a PW2040 engine and modifying the PW2037(M).
B. References
C.
(1) AMM 24-22-00/201, Electrical Power - Control
(2) AMM 34-61-03/201, Flight Management Computer Program Pins
(3) AMM 71-00-00/501, Power Plant - General
(4) AMM 71-00-02/401, Power Plant
(5) AMM 71-21-01/401, Forward Lower Engine Mount
(6) AMM 71-21-02/401, Aft Lower Engine Mount
(7) AMM 73-21-08/401, EEC Data Entry Plug
(8) PPBU 71-00-02, Powerplant Buildup Manual
(9) WDM 22-32-14
(10) WDM 34-61-14
(11) WDM 34-61-24
Access
(1) Location Zones
119/120
Main Equipment Center
411
Left Engine
421
Right Engine
(2)
D.
Access Panels
119BL
Main Equipment Center
Procedure
(1)
S 212-014-P00
Make sure the buildup of the replacement PW2040 engine is the same
configuration as the removed PW2037 engine (PPBU 71-00-02).
NOTE:
____
(a)
Use the quick engine change (QEC) kit to make sure the
replacement engines have the correct configuration.
If the replacement PW2040 engine does not have the correct
configuration for the airplane, make sure these parts are
correct:
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CAUTION:
_______
1)
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MAKE SURE THE CORRECT ENGINE MOUNTS ARE INSTALLED ON
THE ENGINE. THE VIBRATION ISOLATED AND THE
NONISOLATED MOUNTS ARE NOT INTERCHANGEABLE. IF YOU
DO NOT INSTALL THE CORRECT MOUNTS, YOU CAN CAUSE
DAMAGE TO THE ENGINE AND THE AIRPLANE.
2)
Make sure the engine mounts are vibration isolated mounts
(AMM 71-21-01/401 and 71-21-02/401).
Make sure the hydraulic pump is an approved part for the
Boeing 757-200 (refer to the pump nameplate).
Make sure the Electronic Engine Control (EEC) is a Hamilton
Standard P/N 783600-XX-YYY, or P/N 815770-X-YYY, as
applicable (refer to the nameplate on the EEC).
3)
NOTE:
____
4)
The P/N will change for Pressure Burner Sensor Range
and EEC software revision (-X(X)-YYY).
Make sure the fuel flow transmitter has the same part
number as the one on the engine you will replace.
(2)
S 962-015-P00
Replace the PW2037 engine with the PW2040 engine (AMM 71-00-02/401).
(3)
S 862-016-P00
Remove electrical power if it is supplied (AMM 24-22-00/201).
(4)
S 902-059-P00
If you only replace one PW2037 engine with a PW2040 engine and the
other engine is a PW2037(M), do these steps to change the PW2037(M)
engine to a PW2040 engine:
NOTE:
____
(a)
For information on the data entry plug (DEP) and the engine
nameplate, refer to PW SB 72-245.
Change the data entry plug from a PW2037 DEP to a PW2040 DEP:
1) Remove the PW2037 DEP (AMM 73-21-08/401).
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2)
Make a note of the last two numbers of the PW2037 DEP.
CAUTION:
_______
MAKE SURE THE LAST TWO NUMBERS OF THE DATA ENTRY PLUG
(DEP) FOR THE PW2040 ARE THE SAME AS THE LAST TWO
NUMBERS OF THE PW2037 DEP. IF THE LAST TWO DIGITS
ARE NOT THE SAME, THE EEC WILL NOT OPERATE
CORRECLTLY.
3)
(b)
(5)
(6)
(7)
Get a PW2040 DEP with the same last two numbers as the
PW2037 DEP.
4) Install the PW2040 DEP (Ref 73-21-08/401).
Change the engine nameplate from a PW2037(M) to a PW2040.
1) Remove and discard the nameplate with the PW2037(M)
identification.
2) Install a nameplate with the PW2040 identification.
S 012-017-P00
Open the access door to the main equipment center.
S 962-048-P00
Change the engine program pins for the flight management computers
(FMC's) to get the airframe/engine identification for PW2040 engines
(AMM 34-61-03/201, WDM 34-61-14, and WDM 34-61-24).
S 962-049-P00
Change the engine program pins for the thrust management computer
(TMC) to get the airframe/engine identification for PW2040 engines
(WDM 22-32-14).
(8)
S 412-052-P00
Close the access door to the main equipment center.
(9)
S 862-021-P00
Supply electrical power (AMM 24-22-00/201).
S 212-051-P00
(10) Do a check of the EICAS CONF/MCDP display.
(a) Put the EEC MAINT POWER swith on the right sidewall panel, P61,
to the ALTN position.
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(b)
(c)
(d)
(e)
(f)
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Select the EPCS page on the EICAS.
Make sure the P(S) DEP/EEC message is not displayed for the
left or right engine.
Select the CONF/MCDP page on the EICAS.
If both PW2037 engines were replaced, make sure EEC PW2040 is
displayed.
Put the EEC MAINT POWER switch on the P61 panel to the NORM
position.
S 722-024-P00
(11) Do the test for the power plant that is shown in the Power-Plant
Test-Reference Table (AMM 71-00-00/501).
4.
TASK 71-00-07-962-025-P00
Replace One PW2037(M) Engine With One PW2037 Engine
___________________________________________________
A. General
(1) This task gives instruction for replacing the following combination
of engines:
(a) Changing (1) PW2037(M) engine with (1) PW2037 engine (for a
final combination of (2) PW2037 engines).
B. References
C.
(1) AMM 24-22-00/201, Electrical Power - Control
(2) AMM 34-61-03/201, Flight Management Computer Program Pins
(3) AMM 71-00-00/501, Power Plant - General
(4) AMM 71-00-02/401, Power Plant
(5) AMM 71-21-01/401, Forward Lower Engine Mount
(6) AMM 71-21-02/401, Aft Lower Engine Mount
(7) PPBU 71-00-02, Powerplant Buildup Manual
(8) WDM 22-32-14
(9) WDM 34-61-14
(10) WDM 34-61-24
Access
(1) Location Zones
119/120
Main Equipment Center
411
Left Engine
421
Right Engine
(2)
Access Panels
119BL
Main Equipment Center
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D.
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Procedure
(1)
S 212-026-P00
Make sure the buildup of the replacement PW2037 engine is the same
configuration as the removed PW2037(M) engine (PPBU 71-00-02).
NOTE:
____
(a)
Use the quick engine change (QEC) kit to make sure the
replacement engine has the correct configuration.
If the replacement PW2037 engine does not have the correct
configuration for the airplane, make sure these parts are
correct:
CAUTION:
_______
1)
2)
3)
Make sure the engine mounts are vibration isolated mounts
(AMM 71-21-01/401 and 71-21-02/401).
Make sure the hydraulic pump is an approved part for the
Boeing 757-200 (refer to the pump nameplate).
Make sure the Electronic Engine Control (EEC) is a Hamilton
Standard P/N 783600-XX-YYY, or P/N 815770-X-YYY, as
applicable (refer to the nameplate on the EEC).
NOTE:
____
4)
(2)
MAKE SURE THE CORRECT ENGINE MOUNTS ARE INSTALLED ON
THE ENGINE. THE VIBRATION ISOLATED AND THE
NONISOLATED MOUNTS ARE NOT INTERCHANGEABLE. IF YOU
DO NOT INSTALL THE CORRECT MOUNTS, YOU CAN CAUSE
DAMAGE TO THE ENGINE AND THE AIRPLANE.
The P/N will change for Pressure Burner Sensor Range
and EEC software revision (-X(X)-YYY).
Make sure the fuel flow transmitter has the same part
number as the one on the engine you will replace.
S 862-027-P00
Remove electrical power if it is supplied (AMM 24-22-00/201).
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(3)
(4)
(5)
(6)
S 962-028-P00
Replace the applicable PW2037(M) engine with a PW2037 engine
(AMM 71-00-02/401).
S 012-029-P00
Open the access door to the main equipment center.
S 212-030-P00
Make sure the engine program pins for the FMCs (flight management
computers) have the airframe/engine identification for PW2037
engines (AMM 34-61-03/201, WDM 34-61-14, and WDM 34-61-24):
S 212-031-P00
Make sure the engine program pins for the TMC (thrust management
computer) have the airframe/engine identification for PW2037 engines
(WDM 22-32-14):
(7)
S 412-032-P00
Close the access door to the main equipment center.
(8)
S 862-058-P00
Supply electrical power (AMM 24-22-00/201).
(9)
S 212-053-P00
Do a check of the EICAS CONF/MCDP display.
(a) Put the EEC MAINT POWER switch on the right sidewall panel,
P61, to the ALTN position.
(b) Select the EPCS page on the EICAS.
(c) Make sure P(S) DEP/EEC is not displayed for the left or right
engine.
(d) Select the CONF/MCDP page on the EICAS.
(e) Make sure EEC PW2037 is displayed for the left and right
engines.
(f) Put the EEC MAINT POWER switch on the P61 panel to the NORM
position.
S 722-033-P00
(10) Do the test for the power plant that is shown in the Power-Plant
Test-Reference Table (AMM 71-00-00/501).
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TASK 71-00-07-962-034-P00
Replace One PW2037 Engine With One PW2037(M) Engine
___________________________________________________
A. General
(1) This task gives instructions for replacing the following
combinations of engines:
(a) Changing from (2) PW2037 engines to (1) PW2037 and (1)
PW2037(M) engine.
(b) Change (1) PW2037 with (1) PW2040 engine and modify the PW2040
to a PW2037(M).
B. References
C.
(1) AMM 24-22-00/201, Electrical Power - Control
(2) AMM 34-61-03/201, Flight Management Computer Program Pins
(3) AMM 71-00-00/501, Power Plant - General
(4) AMM 71-00-02/401, Power Plant
(5) AMM 71-21-01/401, Forward Lower Engine Mount
(6) AMM 71-21-02/401, Aft Lower Engine Mount
(7) AMM 73-21-08/401, EEC Data Entry Plug
(8) PPBU 71-00-02, Powerplant Buildup Manual
(9) WDM 22-32-14
(10) WDM 34-61-14
(11) WDM 34-61-24
Access
(1) Location Zones
119/120
Main Equipment Center
411
Left Engine
421
Right Engine
(2)
D.
Access Panels
119BL
Main Equipment Center
Procedure
(1)
S 212-035-P00
Make sure the buildup of the replacement PW2037(M) engine is the
same configuration as the removed PW2037 engine (PPBU 71-00-02).
NOTE:
____
(a)
Use the quick engine change (QEC) kit to make sure the
replacement engine has the correct configuration.
If the replacement PW2037(M) engine does not have the correct
configuration for the airplane, make sure these parts are
correct:
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CAUTION:
_______
1)
MAKE SURE THE CORRECT ENGINE MOUNTS ARE INSTALLED ON
THE ENGINE. THE VIBRATION ISOLATED AND THE
NONISOLATED MOUNTS ARE NOT INTERCHANGEABLE. IF YOU
DO NOT INSTALL THE CORRECT MOUNTS, YOU CAN CAUSE
DAMAGE TO THE ENGINE AND THE AIRPLANE.
Make sure the engine mounts are vibration isolated mounts
(AMM 71-21-01/401 and 71-21-02/401).
Make sure the hydraulic pump is an approved part for the
Boeing 757-200 (refer to the pump nameplate).
Make sure the Electronic Engine Control (EEC) is a Hamilton
Standard P/N 783600-XX-YYY, or P/N 815770-X-YYY, as
applicable (refer to the nameplate on the EEC).
2)
3)
NOTE:
____
4)
(2)
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The P/N will change for Pressure Burner Sensor Range
and EEC software revision (-X(X)-YYY).
Make sure the fuel flow transmitter has the same part
number as the one on the engine you will replace.
S 862-036-P00
Remove electrical power if it is supplied (AMM 24-22-00/201).
(3)
S 962-037-P00
Replace the applicable PW2037 engine with a PW2037(M) engine
(AMM 71-00-02/401).
(4)
S 962-041-P00
If you installed a PW2040 engine, do these steps to change the
PW2040 engine to a PW2037(M) engine:
NOTE:
____
(a)
For information on the data entry plug (DEP) and the engine
nameplate, refer to PW SB 72-244.
Change the data entry plug from a PW2040 DEP to a PW2037 DEP:
1) Remove the PW2040 DEP (AMM 73-21-08/401).
2) Make a note of the last two numbers of the PW2040 DEP.
CAUTION:
_______
MAKE SURE THE LAST TWO NUMBERS OF THE DATA ENTRY PLUG
(DEP) FOR THE PW2037 ARE THE SAME AS THE LAST TWO
NUMBERS OF THE PW2040 DEP. IF THE LAST TWO DIGITS
ARE NOT THE SAME, THE EEC WILL NOT OPERATE
CORRECLTLY.
3)
(b)
Get a PW2037 DEP with the same last two numbers as the
PW2040 DEP.
4) Install the PW2037 DEP (AMM 73-21-08/401).
Change the engine nameplate from a PW2040 to a PW2037(M):
1) Remove and discard the nameplate with the PW2040
identification.
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2)
(5)
(6)
(7)
Install a nameplate with the PW2037(M) identification.
S 012-038-P00
Open the access door to the main equipment center.
S 212-054-P00
Make sure the engine program pins for the flight management
computers (FMC's) have the airframe/engine identification for PW2037
engines (AMM 34-61-03/201, WDM 34-61-14, and WDM 34-61-24):
S 212-055-P00
Make sure the engine program pins for the thrust management computer
(TMC) have the airframe/engine identification for PW2037 engines
(WDM 22-32-14):
(8)
S 412-042-P00
Close the access door to the main equipment center.
(9)
S 862-056-P00
Supply electrical power (AMM 24-22-00/201).
S 212-057-P00
(10) Do a check of the EICAS CONF/MCDP display.
(a) Put the EEC MAINT POWER swith on the right sidewall panel, P61,
to the ALTN position.
(b) Select the EPCS page on the EICAS.
(c) Make sure the P(S) DEP/EEC message is not displayed for the
left or right engine.
(d) Select the CONF/MCDP page on the EICAS.
(e) Make sure EEC PW2037 is displayed.
(f) Put the EEC MAINT POWER switch on the P61 panel to the NORM
position.
S 722-043-P00
(11) Do the test for the power plant that is shown in the Power-Plant
Test-Reference Table (AMM 71-00-00/501).
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POWER PLANT - MAINTENANCE PRACTICES (TRIM CHECK TABLES)
_______________________________________________________
1.
2.
General
_______
A. This procedure has the necessary data for the tests that do a check of
the engine trim (AMM 71-00-00/501).
B. There is an example to show you how to use the Trim Tables on Fig. 201.
Do not use the values on Fig. 201 for the trim data. The correct values
for the trim data are shown on Fig. 202.
C. The Trim Tables have the trim data for barometric pressures of 22.0 to
31.0 inches of mercury absolute and ambient temperatures of -40°F to
124°F (-40°C to 51°C).
TASK 71-01-02-972-001-P01
Find the Trim Targets (Fig. 202)
_____________________
A. Procedure
(1)
S 972-002-P01
Use the ambient temperature and the barometric pressure to find the
trim targets that follow on Figure 202:
NOTE:
____
If the ambient temperature and the barometric pressure are
not shown on the tables, find the data by interpolation.
(a)
(b)
MIN IDLE (% N2)
APP IDLE (% N2)
(c)
(d)
(e)
TAKEOFF (EPR)
95% TAKEOFF THRUST (EPR)
90% THRUST CHANGE DECEL (EPR)
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EXAMPLE TRIM CHECK PROBLEM
__________________________
______
ASSUME:
1. AMBIENT TEMPERATURE:
2. BAROMETRIC PRESSURE:
OAT = 12`F
= 29.0 INCHES OF MERCURY
SELECT TRIM TARGETS FOR THE FOLLOWING:
_____________________________________
3. TAKEOFF (EPR) IS
1.50 +0.01/-0.00 EPR
4. 95% TAKEOFF THRUST (EPR)
IS 1.46 EPR
5. 90% THRUST CHANGE
DECELERATION (EPR)
IS 1.04 EPR
1. MINIMUM IDLE (%N2) IS 57.7 (+1.5/-0.5)%N2
2. APPROACH IDLE (%N2) IS 67.6 |0.5 %N2
BAROMETER, INCHES OF MERCURY
OAT `F
(`C)
TRIM TARGETS
12
(-11)
MIN IDLE (%N2)
APP IDLE (%N2)
TAKEOFF (EPR)
95% TAKEOFF THRUST (EPR)
90% THRUST CHANGE DECEL (EPR)
57.6
67.5
1.45
1.42
1.03
57.6
67.5
1.48
1.45
1.03
57.7
67.6
1.50
1.46
1.04
58.0
67.7
1.51
1.47
1.04
58.3
67.8
1.53
1.48
1.04
58.6
67.9
1.54
1.50
1.04
58.9
68.0
1.56
1.51
1.04
59.5
68.3
1.57
1.52
1.04
60.2
68.8
1.59
1.53
1.04
60.9
69.0
1.61
1.54
1.04
16
(-9)
MIN IDLE (%N2)
APP IDLE (%N2)
TAKEOFF (EPR)
95% TAKEOFF THRUST (EPR)
90% THRUST CHANGE DECEL (EPR)
57.9
67.8
1.45
1.42
1.03
57.9
67.8
1.48
1.45
1.03
58.0
67.9
1.50
1.46
1.04
58.2
68.0
1.51
1.47
1.04
58.5
68.1
1.53
1.48
1.04
58.8
68.2
1.54
1.50
1.04
59.2
68.3
1.56
1.51
1.04
59.8
68.6
1.57
1.52
1.04
60.4
68.9
1.59
1.53
1.04
61.2
69.3
1.61
1.54
1.04
20
(-7)
MIN IDLE (%N2)
APP IDLE (%N2)
TAKEOFF (EPR)
95% TAKEOFF THRUST (EPR)
90% THRUST CHANGE DECEL (EPR)
58.1
68.1
1.45
1.42
1.03
58.1
68.1
1.48
1.45
1.03
58.2
68.2
1.50
1.46
1.04
58.5
68.3
1.51
1.47
1.04
58.8
68.3
1.53
1.48
1.04
59.1
68.5
1.54
1.50
1.04
59.4
68.6
1.56
1.51
1.04
60.0
68.9
1.57
1.52
1.04
60.7
69.2
1.59
1.53
1.04
61.4
69.6
1.61
1.54
1.04
58.4
58.7
68.5
59.0
61.0
61.7
69.8
31.0 30.0 29.0 28.0 27.0 26.0 25.0 24.0 23.0 22.0
246738
Trim Table Usage
Figure 201
EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùùû
PW2040 ENGINES
ú
ú
ú
ú
71-01-02
P01
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
CONFIG
1
Page 202
May 28/99
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/
PW2000 SERIES
/
/
/
ENGINES
////////////////////////
A
757
MAINTENANCE MANUAL
BAROMETER, INCHES OF MERCURY
OAT `F
(`C)
TRIM TARGETS
-40
(-40)
MIN IDLE (%N2)
APP IDLE (%N2)
TAKEOFF (EPR)
95% TAKEOFF THRUST (EPR)
90% THRUST CHANGE DECEL (EPR)
54.3
63.7
1.45
1.42
1.03
54.3
63.7
1.48
1.44
1.03
54.4
63.8
1.50
1.46
1.04
54.7
63.8
1.51
1.47
1.04
55.0
63.9
1.53
1.48
1.04
55.3
64.0
1.54
1.50
1.04
55.6
64.1
1.56
1.51
1.04
56.1
64.4
1.57
1.52
1.04
56.8
64.7
1.59
1.53
1.04
57.4
65.1
1.61
1.54
1.04
-36
(-38)
MIN IDLE (%N2)
APP IDLE (%N2)
TAKEOFF (EPR)
95% TAKEOFF THRUST (EPR)
90% THRUST CHANGE DECEL (EPR)
54.6
64.0
1.45
1.42
1.03
54.6
64.0
1.48
1.44
1.03
54.7
64.1
1.50
1.46
1.04
55.0
64.2
1.51
1.47
1.04
55.2
64.2
1.53
1.48
1.04
55.5
64.3
1.54
1.50
1.04
55.9
64.4
1.56
1.51
1.04
56.4
64.7
1.57
1.52
1.04
57.0
65.0
1.59
1.53
1.04
57.7
65.4
1.61
1.54
1.04
-32
(-36)
MIN IDLE (%N2)
APP IDLE (%N2)
TAKEOFF (EPR)
95% TAKEOFF THRUST (EPR)
90% THRUST CHANGE DECEL (EPR)
54.9
64.3
1.45
1.42
1.03
54.9
64.3
1.48
1.44
1.03
54.9
64.4
1.50
1.46
1.04
55.2
64.5
1.51
1.47
1.04
55.5
64.5
1.53
1.48
1.04
55.8
64.6
1.54
1.50
1.04
56.1
64.7
1.56
1.51
1.04
56.7
65.0
1.57
1.52
1.04
57.3
65.3
1.59
1.53
1.04
58.0
65.7
1.61
1.54
1.04
-28
(-33)
MIN IDLE (%N2)
APP IDLE (%N2)
TAKEOFF (EPR)
95% TAKEOFF THRUST (EPR)
90% THRUST CHANGE DECEL (EPR)
55.1
64.6
1.45
1.42
1.03
55.1
64.6
1.48
1.44
1.03
55.2
64.7
1.50
1.46
1.04
55.5
64.8
1.51
1.47
1.04
55.8
64.8
1.53
1.48
1.04
56.1
64.9
1.54
1.50
1.04
56.4
65.0
1.56
1.51
1.04
56.9
65.3
1.57
1.52
1.04
57.6
65.6
1.59
1.53
1.04
58.3
66.0
1.61
1.54
1.04
-24
(-31)
MIN IDLE (%N2)
APP IDLE (%N2)
TAKEOFF (EPR)
95% TAKEOFF THRUST (EPR)
90% THRUST CHANGE DECEL (EPR)
55.4
64.9
1.45
1.42
1.03
55.4
64.9
1.48
1.44
1.03
55.5
65.0
1.50
1.46
1.04
55.7
65.1
1.51
1.47
1.04
56.0
65.1
1.53
1.48
1.04
56.3
65.2
1.54
1.50
1.04
56.7
65.3
1.56
1.51
1.04
57.2
65.6
1.57
1.52
1.04
57.8
66.0
1.59
1.53
1.04
58.5
66.3
1.61
1.54
1.04
-20
(-29)
MIN IDLE (%N2)
APP IDLE (%N2)
TAKEOFF (EPR)
95% TAKEOFF THRUST (EPR)
90% THRUST CHANGE DECEL (EPR)
55.6
65.2
1.45
1.42
1.03
55.6
65.2
1.48
1.44
1.03
55.7
65.3
1.50
1.46
1.04
56.0
65.4
1.51
1.47
1.04
56.3
65.4
1.53
1.48
1.04
56.6
65.5
1.54
1.50
1.04
56.9
65.6
1.56
1.51
1.04
57.5
65.9
1.57
1.52
1.04
58.1
66.3
1.59
1.53
1.04
58.8
66.6
1.61
1.54
1.04
31.0 30.0 29.0 28.0 27.0 26.0 25.0 24.0 23.0 22.0
TOLERANCES:
MI N IDLE (%N2) - (+1.5/-0.5)
APP IDLE (%N2) - |0.5
TAKEOFF (EPR) - (+0.01/-0.00)
246747
Trim Table
Figure 202 (Sheet 1)
EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùùû
PW2040 ENGINES
ú
ú
ú
ú
71-01-02
P01
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
CONFIG
1
Page 203
May 28/99
////////////////////////
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PW2000 SERIES
/
/
/
ENGINES
////////////////////////
A
757
MAINTENANCE MANUAL
BAROMETER, INCHES OF MERCURY
OAT `F
(`C)
TRIM TARGETS
-16
(-27)
MIN IDLE (%N2)
APP IDLE (%N2)
TAKEOFF (EPR)
95% TAKEOFF THRUST (EPR)
90% THRUST CHANGE DECEL (EPR)
55.9
65.5
0
1.45
1.42
1.03
55.9
65.5
1.48
1.44
1.03
56.0
65.6
1.50
1.46
1.04
56.2
65.6
1.51
1.47
1.04
56.5
65.7
1.53
1.48
1.04
56.8
65.8
1.54
1.50
1.04
57.2
65.9
1.56
1.51
1.04
57.7
66.2
1.57
1.52
1.04
58.4
66.6
1.59
1.53
1.04
59.1
66.9
1.61
1.54
1.04
-12
(-24)
MIN IDLE (%N2)
APP IDLE (%N2)
TAKEOFF (EPR)
95% TAKEOFF THRUST (EPR)
90% THRUST CHANGE DECEL (EPR)
56.1
65.8
1.45
1.42
1.03
56.1
65.8
1.48
1.44
1.03
56.2
65.9
1.50
1.46
1.04
56.5
65.9
1.51
1.47
1.04
56.8
66.0
1.53
1.48
1.04
57.1
66.1
1.54
1.50
1.04
57.4
66.2
1.56
1.51
1.04
58.0
66.5
1.57
1.52
1.04
58.6
66.9
1.59
1.53
1.04
59.3
67.2
1.61
1.54
1.04
-8
(-22)
MIN IDLE (%N2)
APP IDLE (%N2)
TAKEOFF (EPR)
95% TAKEOFF THRUST (EPR)
90% THRUST CHANGE DECEL (EPR)
56.4
66.1
1.45
1.42
1.03
56.4
66.1
1.48
1.44
1.03
56.5
66.1
1.50
1.46
1.04
56.7
66.2
1.51
1.47
1.04
57.0
66.3
1.53
1.48
1.04
57.3
66.4
1.54
1.50
1.04
57.7
66.5
1.56
1.51
1.04
58.2
66.8
1.57
1.52
1.04
58.9
67.2
1.59
1.53
1.04
59.6
67.5
1.61
1.54
1.04
-4
(-20)
MIN IDLE (%N2)
APP IDLE (%N2)
TAKEOFF (EPR)
95% TAKEOFF THRUST (EPR)
90% THRUST CHANGE DECEL (EPR)
56.6
66.4
1.45
1.42
1.03
56.6
66.4
1.48
1.44
1.03
56.7
66.4
1.50
1.46
1.04
57.0
66.5
1.51
1.47
1.04
57.3
66.6
1.53
1.48
1.04
57.6
66.7
1.54
1.50
1.04
57.9
66.8
1.56
1.51
1.04
58.5
67.1
1.57
1.52
1.04
59.2
67.4
1.59
1.53
1.04
59.9
67.8
1.61
1.54
1.04
0
(-18)
MIN IDLE (%N2)
APP IDLE (%N2)
TAKEOFF (EPR)
95% TAKEOFF THRUST (EPR)
90% THRUST CHANGE DECEL (EPR)
56.9
66.6
1.45
1.42
1.03
56.9
66.6
1.48
1.45
1.03
57.0
66.7
1.50
1.46
1.04
57.2
66.8
1.51
1.47
1.04
57.5
66.9
1.53
1.48
1.04
57.8
67.0
1.54
1.50
1.04
58.2
67.1
1.56
1.51
1.04
58.8
67.4
1.57
1.52
1.04
59.4
67.7
1.59
1.53
1.04
60.1
68.1
1.61
1.54
1.04
4
(-16)
MIN IDLE (%N2)
APP IDLE (%N2)
TAKEOFF (EPR)
95% TAKEOFF THRUST (EPR)
90% THRUST CHANGE DECEL (EPR)
57.1
66.9
1.45
1.42
1.03
57.1
66.9
1.48
1.45
1.03
57.2
67.0
1.50
1.46
1.04
57.5
67.1
1.51
1.47
1.04
57.8
67.2
1.53
1.48
1.04
58.1
67.3
1.54
1.50
1.04
58.4
67.4
1.56
1.51
1.04
59.0
67.7
1.57
1.52
1.04
59.7
68.0
1.59
1.53
1.04
60.4
68.4
1.61
1.54
1.04
31.0 30.0 29.0 28.0 27.0 26.0 25.0 24.0 23.0 22.0
TOLERANCES:
MI N IDLE (%N2) - (+1.5/-0.5)
APP IDLE (%N2) - |0.5
TAKEOFF (EPR) - (+0.01/-0.00)
246753
Trim Table
Figure 202 (Sheet 2)
EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùùû
PW2040 ENGINES
ú
ú
ú
ú
71-01-02
P01
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
CONFIG
1
Page 204
May 28/99
////////////////////////
/
PW2000 SERIES
/
/
/
ENGINES
////////////////////////
A
757
MAINTENANCE MANUAL
BAROMETER, INCHES OF MERCURY
OAT `F
(`C)
TRIM TARGETS
31.0 30.0 29.0 28.0 27.0 26.0 25.0 24.0 23.0 22.0
8
(-13)
MIN IDLE (%N2)
APP IDLE (%N2)
TAKEOFF (EPR)
95% TAKEOFF THRUST (EPR)
90% THRUST CHANGE DECEL (EPR)
57.4
67.2
1.45
1.42
1.03
57.4
67.2
1.48
1.45
1.03
57.5
67.3
1.50
1.46
1.04
57.7
67.4
1.51
1.47
1.04
58.0
67.5
1.53
1.48
1.04
58.4
67.6
1.54
1.50
1.04
58.7
67.7
1.56
1.51
1.04
59.3
68.0
1.57
1.52
1.04
59.9
68.3
1.59
1.53
1.04
60.6
68.7
1.61
1.54
1.04
12
(-11)
MIN IDLE (%N2)
APP IDLE (%N2)
TAKEOFF (EPR)
95% TAKEOFF THRUST (EPR)
90% THRUST CHANGE DECEL (EPR)
57.6
67.5
1.45
1.42
1.03
57.6
67.5
1.48
1.45
1.03
57.7
67.6
1.50
1.46
1.04
58.0
67.7
1.51
1.47
1.04
58.3
67.8
1.53
1.48
1.04
58.6
67.9
1.54
1.50
1.04
58.9
68.0
1.56
1.51
1.04
59.5
68.3
1.57
1.52
1.04
60.2
68.5
1.59
1.53
1.04
60.9
69.0
1.61
1.54
1.04
16
(-9)
MIN IDLE (%N2)
APP IDLE (%N2)
TAKEOFF (EPR)
95% TAKEOFF THRUST (EPR)
90% THRUST CHANGE DECEL (EPR)
57.9
67.8
1.45
1.42
1.03
57.9
67.8
1.48
1.45
1.03
58.0
67.9
1.50
1.46
1.04
58.2
68.0
1.51
1.47
1.04
58.5
68.1
1.53
1.48
1.04
58.8
68.2
1.54
1.50
1.04
59.2
68.3
1.56
1.51
1.04
59.8
68.6
1.57
1.52
1.04
60.4
68.9
1.59
1.53
1.04
61.2
69.3
1.61
1.54
1.04
20
(-7)
MIN IDLE (%N2)
APP IDLE (%N2)
TAKEOFF (EPR)
95% TAKEOFF THRUST (EPR)
90% THRUST CHANGE DECEL (EPR)
58.1
68.1
1.45
1.42
1.03
58.1
68.1
1.48
1.45
1.03
58.2
68.2
1.50
1.46
1.04
58.5
68.3
1.51
1.47
1.04
58.8
68.3
1.53
1.48
1.04
59.1
68.5
1.54
1.50
1.04
59.4
68.6
1.56
1.51
1.04
60.0
68.9
1.57
1.52
1.04
60.7
69.2
1.59
1.53
1.04
61.4
69.6
1.61
1.54
1.04
24
(-4)
MIN IDLE (%N2)
APP IDLE (%N2)
TAKEOFF (EPR)
95% TAKEOFF THRUST (EPR)
90% THRUST CHANGE DECEL (EPR)
58.3
68.4
1.45
1.42
1.03
58.3
68.4
1.48
1.45
1.03
58.4
68.4
1.50
1.46
1.04
58.7
68.5
1.51
1.47
1.04
59.0
68.6
1.53
1.48
1.04
59.3
68.7
1.54
1.50
1.04
59.7
68.9
1.56
1.51
1.04
60.3
69.1
1.57
1.52
1.04
61.0
69.5
1.59
1.53
1.04
61.7
69.8
1.61
1.54
1.04
28
(-2)
MIN IDLE (%N2)
APP IDLE (%N2)
TAKEOFF (EPR)
95% TAKEOFF THRUST (EPR)
90% THRUST CHANGE DECEL (EPR)
58.6
68.6
1.45
1.42
1.03
58.6
68.6
1.48
1.45
1.03
58.7
68.7
1.50
1.46
1.04
59.0
68.8
1.51
1.47
1.04
59.3
68.9
1.53
1.48
1.04
59.6
69.0
1.54
1.50
1.04
59.9
69.1
1.56
1.51
1.04
60.5
69.4
1.57
1.52
1.04
61.2
69.8
1.59
1.53
1.04
61.9
70.1
1.61
1.54
1.04
TOLERANCES:
MI N IDLE (%N2) - (+1.5/-0.5)
APP IDLE (%N2) - |0.5
TAKEOFF (EPR) - (+0.01/-0.00)
246757
Trim Table
Figure 202 (Sheet 3)
EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùùû
PW2040 ENGINES
ú
ú
ú
ú
71-01-02
P01
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
CONFIG
1
Page 205
May 28/99
////////////////////////
/
PW2000 SERIES
/
/
/
ENGINES
////////////////////////
A
757
MAINTENANCE MANUAL
BAROMETER, INCHES OF MERCURY
OAT `F
(`C)
TRIM TARGETS
31.0 30.0 29.0 28.0 27.0 26.0 25.0 24.0 23.0 22.0
32
(2)
MIN IDLE (%N2)
APP IDLE (%N2)
TAKEOFF (EPR)
95% TAKEOFF THRUST (EPR)
90% THRUST CHANGE DECEL (EPR)
58.8
68.9
1.45
1.42
1.03
58.8
68.9
1.48
1.45
1.03
58.9
69.0
1.50
1.46
1.04
59.2
69.1
1.51
1.47
1.04
59.5
69.2
1.53
1.48
1.04
59.8
69.3
1.54
1.50
1.04
60.2
69.4
1.56
1.51
1.04
60.8
69.7
1.57
1.52
1.04
61.5
70.1
1.59
1.53
1.04
62.2
70.4
1.61
1.54
1.04
36
(0)
MIN IDLE (%N2)
APP IDLE (%N2)
TAKEOFF (EPR)
95% TAKEOFF THRUST (EPR)
90% THRUST CHANGE DECEL (EPR)
59.1
69.2
1.45
1.42
1.03
59.1
69.2
1.48
1.45
1.03
59.2
69.3
1.50
1.46
1.04
59.4
69.4
1.51
1.47
1.04
59.7
69.5
1.53
1.48
1.04
60.1
69.6
1.54
1.50
1.04
60.4
69.7
1.56
1.51
1.04
61.0
70.0
1.57
1.52
1.04
61.7
70.3
1.59
1.53
1.04
62.4
70.7
1.61
1.54
1.04
40
(4)
MIN IDLE (%N2)
APP IDLE (%N2)
TAKEOFF (EPR)
95% TAKEOFF THRUST (EPR)
90% THRUST CHANGE DECEL (EPR)
59.3
69.5
1.45
1.42
1.03
59.3
69.5
1.48
1.45
1.03
59.4
69.6
1.50
1.46
1.04
59.7
69.7
1.51
1.47
1.04
60.0
69.8
1.53
1.48
1.04
60.3
69.9
1.54
1.50
1.04
60.7
70.0
1.56
1.51
1.04
61.3
70.3
1.57
1.52
1.04
61.9
70.6
1.59
1.53
1.04
62.7
71.0
1.61
1.54
1.04
44
(7)
MIN IDLE (%N2)
APP IDLE (%N2)
TAKEOFF (EPR)
95% TAKEOFF THRUST (EPR)
90% THRUST CHANGE DECEL (EPR)
59.5
69.8
1.45
1.42
1.03
59.5
69.8
1.48
1.45
1.03
59.6
69.8
1.50
1.46
1.04
59.9
69.9
1.51
1.47
1.04
60.2
70.0
1.53
1.48
1.04
60.6
70.1
1.54
1.50
1.04
60.9
70.3
1.56
1.51
1.04
61.5
70.6
1.57
1.52
1.04
62.2
70.9
1.59
1.53
1.04
62.9
71.3
1.61
1.54
1.04
48
(9)
MIN IDLE (%N2)
APP IDLE (%N2)
TAKEOFF (EPR)
95% TAKEOFF THRUST (EPR)
90% THRUST CHANGE DECEL (EPR)
59.8
70.0
1.45
1.42
1.03
59.8
70.0
1.48
1.45
1.03
59.9
70.1
1.50
1.46
1.04
60.2
70.2
1.51
1.47
1.04
60.5
70.3
1.53
1.48
1.04
60.8
70.4
1.54
1.50
1.04
61.2
70.5
1.56
1.51
1.04
61.8
70.8
1.57
1.52
1.04
62.4
71.2
1.59
1.53
1.04
63.2
71.6
1.61
1.54
1.04
52
(11)
MIN IDLE (%N2)
APP IDLE (%N2)
TAKEOFF (EPR)
95% TAKEOFF THRUST (EPR)
90% THRUST CHANGE DECEL (EPR)
60.0
70.3
1.45
1.42
1.03
60.0
70.3
1.48
1.45
1.03
60.1
70.4
1.50
1.46
1.04
60.4
70.5
1.51
1.47
1.04
60.7
70.6
1.53
1.48
1.04
61.0
70.7
1.54
1.50
1.04
61.4
70.8
1.56
1.51
1.04
62.0
71.1
1.57
1.52
1.04
62.7
71.5
1.59
1.53
1.04
63.4
71.8
1.61
1.54
1.04
TOLERANCES:
MI N IDLE (%N2) - (+1.5/-0.5)
APP IDLE (%N2) - |0.5
TAKEOFF (EPR) - (+0.01/-0.00)
246764
Trim Table
Figure 202 (Sheet 4)
EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùùû
PW2040 ENGINES
ú
ú
ú
ú
71-01-02
P02
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
CONFIG
1
Page 206
May 28/03
////////////////////////
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PW2000 SERIES
/
/
/
ENGINES
////////////////////////
A
757
MAINTENANCE MANUAL
BAROMETER, INCHES OF MERCURY
OAT `F
(`C)
TRIM TARGETS
31.0 30.0 29.0 28.0 27.0 26.0 25.0 24.0 23.0 22.0
MIN IDLE (%N2)
APP IDLE (%N2)
TAKEOFF (EPR)
95% TAKEOFF THRUST (EPR)
90% THRUST CHANGE DECEL (EPR)
60.2
70.6
1.45
1.42
1.03
60.2
70.6
1.48
1.45
1.03
60.3
70.7
1.50
1.46
1.04
60.6
70.8
1.51
1.47
1.04
60.9
70.9
1.53
1.48
1.04
61.3
71.0
1.54
1.50
1.04
61.6
71.1
1.56
1.51
1.04
62.2
71.4
1.57
1.52
1.04
62.9
71.8
1.59
1.53
1.04
63.7
72.1
1.61
1.54
1.04
MIN IDLE (%N2)
APP IDLE (%N2)
TAKEOFF (EPR)
95% TAKEOFF THRUST (EPR)
90% THRUST CHANGE DECEL (EPR)
60.5
70.9
1.45
1.42
1.03
60.5
70.9
1.48
1.45
1.03
60.6
70.9
1.50
1.46
1.04
60.9
71.0
1.51
1.47
1.04
61.2
71.1
1.53
1.48
1.04
61.5
71.3
1.54
1.50
1.04
61.9
71.4
1.56
1.51
1.04
62.5
71.7
1.57
1.52
1.04
63.2
72.0
1.59
1.53
1.04
63.9
72.4
1.60
1.54
1.04
MIN IDLE (%N2)
APP IDLE (%N2)
TAKEOFF (EPR)
95% TAKEOFF THRUST (EPR)
90% THRUST CHANGE DECEL (EPR)
60.7
71.1
1.45
1.42
1.03
60.7
71.1
1.48
1.45
1.03
60.8
71.2
1.50
1.46
1.04
61.1
71.3
1.51
1.47
1.04
61.4
71.4
1.53
1.48
1.04
61.7
71.5
1.54
1.50
1.04
62.1
71.6
1.56
1.51
1.04
62.7
72.0
1.57
1.52
1.04
63.4
72.3
1.58
1.53
1.04
64.2
72.7
1.58
1.53
1.04
68
(20)
MIN IDLE (%N2)
APP IDLE (%N2)
TAKEOFF (EPR)
95% TAKEOFF THRUST (EPR)
90% THRUST CHANGE DECEL (EPR)
60.9
71.4
1.45
1.42
1.03
60.9
71.4
1.48
1.45
1.03
61.0
71.5
1.50
1.46
1.04
61.3
71.6
1.51
1.47
1.04
61.6
71.7
1.53
1.48
1.04
62.0
71.8
1.54
1.50
1.04
62.3
71.9
1.56
1.51
1.04
63.0
72.2
1.56
1.51
1.04
63.7
72.6
1.56
1.51
1.04
64.4
73.0
1.56
1.51
1.04
72
(22)
MIN IDLE (%N2)
APP IDLE (%N2)
TAKEOFF (EPR)
95% TAKEOFF THRUST (EPR)
90% THRUST CHANGE DECEL (EPR)
61.2
71.7
1.45
1.42
1.03
61.2
71.7
1.48
1.45
1.03
61.3
71.8
1.50
1.46
1.04
61.6
71.9
1.51
1.47
1.04
61.9
72.0
1.53
1.48
1.04
62.2
72.1
1.54
1.50
1.04
62.6
72.2
1.55
1.50
1.04
63.2
72.5
1.55
1.50
1.04
63.9
72.9
1.55
1.50
1.04
64.7
73.3
1.55
1.50
1.04
76
(24)
MIN IDLE (%N2)
APP IDLE (%N2)
TAKEOFF (EPR)
95% TAKEOFF THRUST (EPR)
90% THRUST CHANGE DECEL (EPR)
61.4
71.9
1.45
1.42
1.03
61.4
71.9
1.48
1.45
1.03
61.5
72.0
1.50
1.46
1.04
61.8
72.1
1.51
1.47
1.04
62.1
72.2
1.53
1.48
1.04
62.4
72.3
1.53
1.49
1.04
62.8
72.5
1.53
1.49
1.04
63.4
72.8
1.53
1.49
1.04
64.1
73.1
1.53
1.49
1.04
64.9
73.5
1.53
1.49
1.04
56
(13)
60
(16)
64
(18)
TOLERANCES:
MI N IDLE (%N2) - (+1.5/-0.5)
APP IDLE (%N2) - |0.5
TAKEOFF (EPR) - (+0.01/-0.00)
246769
Trim Table
Figure 202 (Sheet 5)
EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùùû
PW2040 ENGINES
ú
ú
ú
ú
71-01-02
P01
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
CONFIG
1
Page 207
May 28/99
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PW2000 SERIES
/
/
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ENGINES
////////////////////////
A
757
MAINTENANCE MANUAL
BAROMETER, INCHES OF MERCURY
OAT `F
(`C)
TRIM TARGETS
31.0 30.0 29.0 28.0 27.0 26.0 25.0 24.0 23.0 22.0
MIN IDLE (%N2)
APP IDLE (%N2)
TAKEOFF (EPR)
95% TAKEOFF THRUST (EPR)
90% THRUST CHANGE DECEL (EPR)
61.6
72.2
1.45
1.42
1.03
61.6
72.2
1.48
1.45
1.03
61.7
72.3
1.50
1.46
1.04
62.0
72.4
1.51
1.47
1.04
62.3
72.5
1.51
1.47
1.04
62.7
72.6
1.51
1.47
1.04
63.1
72.7
1.51
1.47
1.04
63.7
73.0
1.51
1.47
1.04
64.4
73.4
1.51
1.47
1.04
65.2
73.8
1.51
1.47
1.04
84
(29)
MIN IDLE (%N2)
APP IDLE (%N2)
TAKEOFF (EPR)
95% TAKEOFF THRUST (EPR)
90% THRUST CHANGE DECEL (EPR)
61.8
72.5
1.45
1.42
1.03
61.8
72.5
1.48
1.45
1.03
62.0
72.6
1.50
1.46
1.04
62.3
72.7
1.50
1.46
1.04
62.6
72.8
1.50
1.46
1.04
62.9
72.9
1.50
1.46
1.04
63.3
73.0
1.50
1.46
1.04
63.9
73.3
1.50
1.46
1.04
64.6
73.7
1.50
1.46
1.04
65.4
74.0
1.50
1.46
1.04
88
(31)
MIN IDLE (%N2)
APP IDLE (%N2)
TAKEOFF (EPR)
95% TAKEOFF THRUST (EPR)
90% THRUST CHANGE DECEL (EPR)
62.1
72.7
1.45
1.42
1.03
62.1
72.7
1.48
1.44
1.03
62.2
72.8
1.48
1.44
1.03
62.5
72.9
1.48
1.44
1.04
62.8
73.0
1.48
1.44
1.04
63.1
73.1
1.48
1.44
1.04
63.5
73.3
1.48
1.44
1.04
64.1
73.6
1.48
1.44
1.04
64.9
73.9
1.48
1.44
1.04
65.6
74.3
1.48
1.44
1.04
92
(33)
MIN IDLE (%N2)
APP IDLE (%N2)
TAKEOFF (EPR)
95% TAKEOFF THRUST (EPR)
90% THRUST CHANGE DECEL (EPR)
62.3
73.0
1.45
1.42
1.03
62.3
73.0
1.46
1.43
1.03
62.4
73.1
1.46
1.43
1.03
62.7
73.2
1.46
1.43
1.03
63.0
73.3
1.46
1.43
1.04
63.4
73.4
1.46
1.43
1.04
63.7
73.5
1.46
1.43
1.04
64.4
73.9
1.46
1.43
1.04
65.1
74.2
1.46
1.43
1.04
65.9
74.6
1.46
1.43
1.04
96
(36)
MIN IDLE (%N2)
APP IDLE (%N2)
TAKEOFF (EPR)
95% TAKEOFF THRUST (EPR)
90% THRUST CHANGE DECEL (EPR)
62.5
73.3
1.44
1.41
1.03
62.5
73.3
1.44
1.41
1.03
62.6
73.4
1.44
1.41
1.03
62.9
73.5
1.44
1.41
1.03
63.3
73.6
1.44
1.41
1.03
63.6
73.7
1.44
1.41
1.04
64.0
73.8
1.44
1.41
1.04
64.6
74.1
1.44
1.41
1.04
65.3
74.5
1.44
1.41
1.04
66.1
74.9
1.44
1.41
1.04
100
(37.8)
MIN IDLE (%N2)
APP IDLE (%N2)
TAKEOFF (EPR)
95% TAKEOFF THRUST (EPR)
90% THRUST CHANGE DECEL (EPR)
62.8
73.5
1.43
1.40
1.03
62.8
73.5
1.43
1.40
1.03
62.9
73.6
1.43
1.40
1.03
63.2
73.7
1.43
1.40
1.03
63.5
73.8
1.43
1.40
1.03
63.8
73.9
1.43
1.40
1.03
64.2
74.1
1.43
1.40
1.04
64.8
74.4
1.43
1.40
1.04
65.6
74.7
1.43
1.40
1.04
66.3
75.1
1.43
1.40
1.04
80
(27)
TOLERANCES:
MI N IDLE (%N2) - (+1.5/-0.5)
APP IDLE (%N2) - |0.5
TAKEOFF (EPR) - (+0.01/-0.00)
246799
Trim Table
Figure 202 (Sheet 6)
EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùùû
PW2040 ENGINES
ú
ú
ú
ú
71-01-02
P01
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
CONFIG
1
Page 208
May 28/99
////////////////////////
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/
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ENGINES
////////////////////////
A
757
MAINTENANCE MANUAL
BAROMETER, INCHES OF MERCURY
OAT `F
(`C)
TRIM TARGETS
104
(40)
MIN IDLE (%N2)
APP IDLE (%N2)
TAKEOFF (EPR)
95% TAKEOFF THRUST (EPR)
90% THRUST CHANGE DECEL (EPR)
63.0
73.8
1.41
1.38
1.03
63.0
73.8
1.41
1.38
1.03
63.1
73.9
1.41
1.38
1.03
63.4
74.0
1.41
1.38
1.03
63.7
74.1
1.41
1.38
1.03
64.1
74.2
1.41
1.38
1.03
64.4
74.3
1.41
1.38
1.03
65.1
74.6
1.41
1.38
1.04
65.8
75.0
1.41
1.38
1.04
66.6
75.4
1.41
1.38
1.04
108
(42)
MIN IDLE (%N2)
APP IDLE (%N2)
TAKEOFF (EPR)
95% TAKEOFF THRUST (EPR)
90% THRUST CHANGE DECEL (EPR)
63.2
74.1
1.39
1.36
1.03
63.2
74.1
1.39
1.36
1.03
63.3
74.2
1.39
1.36
1.03
63.6
74.3
1.39
1.36
1.03
63.9
74.4
1.39
1.36
1.03
64.3
74.5
1.39
1.36
1.03
64.7
74.6
1.39
1.36
1.03
65.3
74.9
1.39
1.36
1.03
66.6
75.3
1.39
1.36
1.04
66.8
75.7
1.39
1.36
1.04
112
(44)
MIN IDLE (%N2)
APP IDLE (%N2)
TAKEOFF (EPR)
95% TAKEOFF THRUST (EPR)
90% THRUST CHANGE DECEL (EPR)
63.4
74.3
1.37
1.35
1.03
63.4
74.3
1.37
1.35
1.03
63.5
74.4
1.37
1.35
1.03
63.8
74.5
1.37
1.35
1.03
64.2
74.6
1.37
1.35
1.03
64.5
74.7
1.37
1.35
1.03
64.9
74.9
1.37
1.35
1.03
65.5
75.2
1.37
1.35
1.03
66.3
75.5
1.37
1.35
1.03
67.0
75.9
1.37
1.35
1.04
MIN IDLE (%N2)
APP IDLE (%N2)
TAKEOFF (EPR)
95% TAKEOFF THRUST (EPR)
90% THRUST CHANGE DECEL (EPR)
63.6
74.6
1.36
1.33
1.03
63.6
74.6
1.36
1.33
1.03
63.8
74.7
1.36
1.33
1.03
64.1
74.8
1.36
1.33
1.03
64.4
74.9
1.36
1.33
1.03
64.7
75.0
1.36
1.33
1.03
65.1
75.1
1.36
1.33
1.03
65.8
75.4
1.36
1.33
1.03
66.5
75.8
1.36
1.33
1.03
67.3
76.2
1.36
1.33
1.03
MIN IDLE (%N2)
APP IDLE (%N2)
TAKEOFF (EPR)
95% TAKEOFF THRUST (EPR)
90% THRUST CHANGE DECEL (EPR)
63.9
74.8
1.34
1.32
1.03
63.9
74.8
1.34
1.32
1.03
64.0
74.9
1.34
1.32
1.03
64.3
75.0
1.34
1.32
1.03
64.6
75.1
1.34
1.32
1.03
65.0
75.3
1.34
1.32
1.03
65.3
75.4
1.34
1.32
1.03
66.6
75.7
1.34
1.32
1.03
66.7
76.1
1.34
1.32
1.03
67.5
76.5
1.34
1.32
1.03
MIN IDLE (%N2)
APP IDLE (%N2)
TAKEOFF (EPR)
95% TAKEOFF THRUST (EPR)
90% THRUST CHANGE DECEL (EPR)
64.1
75.1
1.32
1.30
1.03
64.1
75.1
1.32
1.30
1.03
64.2
75.2
1.32
1.30
1.03
64.5
75.3
1.32
1.30
1.03
64.8
75.4
1.32
1.30
1.03
65.2
75.5
1.32
1.30
1.03
65.6
75.6
1.32
1.30
1.03
66.2
76.0
1.32
1.30
1.03
67.0
76.3
1.32
1.30
1.03
67.7
76.7
1.32
1.30
1.03
116
(47)
120
(49)
124
(51)
31.0 30.0 29.0 28.0 27.0 26.0 25.0 24.0 23.0 22.0
TOLERANCES:
MI N IDLE (%N2) - (+1.5/-0.5)
APP IDLE (%N2) - |0.5
TAKEOFF (EPR) - (+0.01/-0.00)
246805
Trim Table
Figure 202 (Sheet 7)
EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùùû
PW2040 ENGINES
ú
ú
ú
ú
71-01-02
P01
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
CONFIG
1
Page 209
May 28/99
A
757
MAINTENANCE MANUAL
////////////////////////
/
PW2000 SERIES
/
/
/
ENGINES
////////////////////////
POWER PLANT - MAINTENANCE PRACTICES (TRIM CHECK TABLES)
_______________________________________________________
1.
2.
General
_______
A. This procedure has the necessary data for the tests that do a check of
the engine trim (AMM 71-00-00/501).
B. There is an example to show you how to use the Trim Tables on Fig. 201.
Do not use the values on Fig. 201 for the trim data. The correct values
for the trim data are shown on Fig. 202.
C. The Trim Tables have the trim data for barometric pressures of 22.0 to
31.0 inches of mercury absolute and ambient temperatures of -40°F to
124°F (-40°C to 51°C).
TASK 71-01-02-972-001-P02
Find the Trim Targets (Fig. 202)
_____________________
A. Procedure
(1)
S 972-002-P02
Use the ambient temperature and the barometric pressure to find the
trim targets that follow on Figure 202:
NOTE:
____
If the ambient temperature and the barometric pressure are
not shown on the tables, find the data by interpolation.
(a)
(b)
MIN IDLE (% N2)
APP IDLE (% N2)
(c)
(d)
(e)
TAKEOFF (EPR)
95% TAKEOFF THRUST (EPR)
90% THRUST CHANGE DECEL (EPR)
EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùùû
PW2037/PW2037(M) ENGINES
ú
ú
ú
ú
71-01-02
P01
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
CONFIG
2
Page 201
May 28/99
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ENGINES
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A
757
MAINTENANCE MANUAL
EXAMPLE TRIM CHECK PROBLEM
__________________________
ASSUME:
______
1. AMBIENT TEMPERATURE:
2. BAROMETRIC PRESSURE:
OAT = 12`F
= 29.0 INCHES OF MERCURY
SELECT TRIM TARGETS FOR THE FOLLOWING:
_____________________________________
3. TAKEOFF (EPR) IS
1.44 +0.01/-0.00 EPR
4. 95% TAKEOFF THRUST (EPR)
IS 1.41 EPR
5. 90% THRUST CHANGE
DECELERATION (EPR)
IS 1.03 EPR
1. MINIMUM IDLE (%N2) IS 57.7 (+1.5/-0.5)%N2
2. APPROACH IDLE (%N2) IS 67.6 |0.5 %N2
OAT `F
(`C)
12
(-11)
16
(-9)
20
(-7)
BAROMETER, INCHES OF MERCURY
TRIM TARGETS
31.0 30.0 29.0 28.0 27.0 26.0 25.0 24.0 23.0 22.0
MIN IDLE (%N2)
APP IDLE (%N2)
TAKEOFF (EPR)
95% TAKEOFF THRUST (EPR)
90% THRUST CHANGE DECEL (EPR)
57.6
67.5
1.41
1.39
1.03
57.6
67.5
1.42
1.39
1.03
57.7
67.6
1.44
1.41
1.03
58.0
67.7
1.46
1.43
1.03
58.3
67.8
1.48
1.45
1.03
58.6
67.9
1.50
1.46
1.03
58.9
68.0
1.52
1.48
1.04
59.5
68.3
1.54
1.50
1.04
60.2
68.8
1.56
1.51
1.04
60.9
69.0
1.58
1.52
1.04
MIN IDLE (%N2)
APP IDLE (%N2)
TAKEOFF (EPR)
95% TAKEOFF THRUST (EPR)
90% THRUST CHANGE DECEL (EPR)
57.9
67.8
1.41
1.39
1.03
57.9
67.8
1.42
1.39
1.03
58.0
67.9
1.44
1.41
1.03
58.2
68.0
1.46
1.43
1.03
58.5
68.1
1.48
1.45
1.03
58.8
68.2
1.50
1.46
1.03
59.2
68.3
1.52
1.48
1.04
59.8
68.6
1.54
1.50
1.04
60.4
68.9
1.56
1.51
1.04
61.2
69.3
1.58
1.52
1.04
MIN IDLE (%N2)
APP IDLE (%N2)
TAKEOFF (EPR)
95% TAKEOFF THRUST (EPR)
90% THRUST CHANGE DECEL (EPR)
58.1
68.1
1.41
1.39
1.03
58.1
68.1
1.42
1.39
1.03
58.2
68.2
1.44
1.41
1.03
58.5
68.3
1.46
1.43
1.03
58.8
68.3
1.48
1.45
1.03
59.1
68.5
1.50
1.46
1.03
59.4
68.6
1.52
1.48
1.04
60.0
68.9
1.54
1.50
1.04
60.7
69.2
1.56
1.51
1.04
61.4
69.6
1.58
1.52
1.04
58.4
58.7
68.5
59.0
61.0
61.7
69.8
194961
Trim Table Usage
Figure 201
EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùùû
PW2037/PW2037(M) ENGINES
ú
ú
ú
ú
71-01-02
P01
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
CONFIG
2
Page 202
May 28/99
////////////////////////
/
PW2000 SERIES
/
/
/
ENGINES
////////////////////////
A
757
MAINTENANCE MANUAL
BAROMETER, INCHES OF MERCURY
OAT `F
(`C)
TRIM TARGETS
31.0 30.0 29.0 28.0 27.0 26.0 25.0 24.0 23.0 22.0
-40
(-40)
MIN IDLE (%N2)
APP IDLE (%N2)
TAKEOFF (EPR)
95% TAKEOFF THRUST (EPR)
90% THRUST CHANGE DECEL (EPR)
54.3
63.7
1.41
1.39
1.03
54.3
63.7
1.42
1.39
1.03
54.4
63.8
1.44
1.41
1.03
54.7
63.8
1.46
1.43
1.03
55.0
63.9
1.48
1.45
1.03
55.3
64.0
1.50
1.46
1.03
55.6
64.1
1.52
1.48
1.04
56.1
64.4
1.54
1.50
1.04
56.8
64.7
1.56
1.51
1.04
57.4
65.1
1.58
1.52
1.04
-36
(-38)
MIN IDLE (%N2)
APP IDLE (%N2)
TAKEOFF (EPR)
95% TAKEOFF THRUST (EPR)
90% THRUST CHANGE DECEL (EPR)
54.6
64.0
1.41
1.39
1.03
54.6
64.0
1.42
1.39
1.03
54.7
64.1
1.44
1.41
1.03
55.0
64.2
1.46
1.43
1.03
55.2
64.2
1.48
1.45
1.03
55.5
64.3
1.50
1.46
1.03
55.9
64.4
1.52
1.48
1.04
56.4
64.7
1.54
1.50
1.04
57.0
65.0
1.56
1.51
1.04
57.7
65.4
1.58
1.52
1.04
-32
(-36)
MIN IDLE (%N2)
APP IDLE (%N2)
TAKEOFF (EPR)
95% TAKEOFF THRUST (EPR)
90% THRUST CHANGE DECEL (EPR)
54.9
64.3
1.41
1.39
1.03
54.9
64.3
1.42
1.39
1.03
54.9
64.4
1.44
1.41
1.03
55.2
64.5
1.46
1.43
1.03
55.5
64.5
1.48
1.45
1.03
55.8
64.6
1.50
1.46
1.03
56.1
64.7
1.52
1.48
1.04
56.7
65.0
1.54
1.50
1.04
57.3
65.3
1.56
1.51
1.04
58.0
65.7
1.58
1.52
1.04
-28
(-33)
MIN IDLE (%N2)
APP IDLE (%N2)
TAKEOFF (EPR)
95% TAKEOFF THRUST (EPR)
90% THRUST CHANGE DECEL (EPR)
55.1
64.6
1.41
1.39
1.03
55.1
64.6
1.42
1.39
1.03
55.2
64.7
1.44
1.41
1.03
55.5
64.8
1.46
1.43
1.03
55.8
64.8
1.48
1.45
1.03
56.1
64.9
1.50
1.46
1.03
56.4
65.0
1.52
1.48
1.04
56.9
65.3
1.54
1.50
1.04
57.6
65.6
1.56
1.51
1.04
58.3
66.0
1.58
1.52
1.04
-24
(-31)
MIN IDLE (%N2)
APP IDLE (%N2)
TAKEOFF (EPR)
95% TAKEOFF THRUST (EPR)
90% THRUST CHANGE DECEL (EPR)
55.4
64.9
1.41
1.39
1.03
55.4
64.9
1.42
1.39
1.03
55.5
65.0
1.44
1.41
1.03
55.7
65.1
1.46
1.43
1.03
56.0
65.1
1.48
1.45
1.03
56.3
65.2
1.50
1.46
1.03
56.7
65.3
1.52
1.48
1.04
57.2
65.6
1.54
1.50
1.04
57.8
66.0
1.56
1.51
1.04
58.5
66.3
1.58
1.52
1.04
-20
(-29)
MIN IDLE (%N2)
APP IDLE (%N2)
TAKEOFF (EPR)
95% TAKEOFF THRUST (EPR)
90% THRUST CHANGE DECEL (EPR)
55.6
65.2
1.41
1.39
1.03
55.6
65.2
1.42
1.39
1.03
55.7
65.3
1.44
1.41
1.03
56.0
65.4
1.46
1.43
1.03
56.3
65.4
1.48
1.45
1.03
56.6
65.5
1.50
1.46
1.03
56.9
65.6
1.52
1.48
1.04
57.5
65.9
1.54
1.50
1.04
58.1
66.3
1.56
1.51
1.04
58.8
66.6
1.58
1.52
1.04
TOLERANCES:
MI N IDLE (%N2) - (+1.5/-0.5)
APP IDLE (%N2) - |0.5
TAKEOFF (EPR) - (+0.01/-0.00)
194865
Trim Table
Figure 202 (Sheet 1)
EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùùû
PW2037/PW2037(M) ENGINES
ú
ú
ú
ú
71-01-02
P01
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
CONFIG
2
Page 203
May 28/99
////////////////////////
/
PW2000 SERIES
/
/
/
ENGINES
////////////////////////
A
757
MAINTENANCE MANUAL
BAROMETER, INCHES OF MERCURY
OAT `F
(`C)
TRIM TARGETS
-16
(-27)
MIN IDLE (%N2)
APP IDLE (%N2)
TAKEOFF (EPR)
95% TAKEOFF THRUST (EPR)
90% THRUST CHANGE DECEL (EPR)
55.9
65.5
1.41
1.39
1.03
55.9
65.5
1.42
1.39
1.03
56.0
65.6
1.44
1.41
1.03
56.2
65.6
1.46
1.43
1.03
56.5
65.7
1.48
1.45
1.03
56.8
65.8
1.50
1.46
1.03
57.2
65.9
1.52
1.48
1.04
57.7
66.2
1.54
1.50
1.04
58.4
66.6
1.56
1.51
1.04
59.1
66.9
1.58
1.52
1.04
-12
(-24)
MIN IDLE (%N2)
APP IDLE (%N2)
TAKEOFF (EPR)
95% TAKEOFF THRUST (EPR)
90% THRUST CHANGE DECEL (EPR)
56.1
65.8
1.41
1.39
1.03
56.1
65.8
1.42
1.39
1.03
56.2
65.9
1.44
1.41
1.03
56.5
65.9
1.46
1.43
1.03
56.8
66.0
1.48
1.45
1.03
57.1
66.1
1.50
1.46
1.03
57.4
66.2
1.52
1.48
1.04
58.0
66.5
1.54
1.50
1.04
58.6
66.9
1.56
1.51
1.04
59.3
67.2
1.58
1.52
1.04
-8
(-22)
MIN IDLE (%N2)
APP IDLE (%N2)
TAKEOFF (EPR)
95% TAKEOFF THRUST (EPR)
90% THRUST CHANGE DECEL (EPR)
56.4
66.1
1.41
1.39
1.03
56.4
66.1
1.42
1.39
1.03
56.5
66.1
1.44
1.41
1.03
56.7
66.2
1.46
1.43
1.03
57.0
66.3
1.48
1.45
1.03
57.3
66.4
1.50
1.46
1.03
57.7
66.5
1.52
1.48
1.04
58.2
66.8
1.54
1.50
1.04
58.9
67.2
1.56
1.51
1.04
59.6
67.5
1.58
1.52
1.04
-4
(-20)
MIN IDLE (%N2)
APP IDLE (%N2)
TAKEOFF (EPR)
95% TAKEOFF THRUST (EPR)
90% THRUST CHANGE DECEL (EPR)
56.6
66.4
1.41
1.39
1.03
56.6
66.4
1.42
1.39
1.03
56.7
66.4
1.44
1.41
1.03
57.0
66.5
1.46
1.43
1.03
57.3
66.6
1.48
1.45
1.03
57.6
66.7
1.50
1.46
1.03
57.9
66.8
1.52
1.48
1.04
58.5
67.1
1.54
1.50
1.04
59.2
67.4
1.56
1.51
1.04
59.9
67.8
1.58
1.52
1.04
0
(-18)
MIN IDLE (%N2)
APP IDLE (%N2)
TAKEOFF (EPR)
95% TAKEOFF THRUST (EPR)
90% THRUST CHANGE DECEL (EPR)
56.9
66.6
1.41
1.39
1.03
56.9
66.6
1.42
1.39
1.03
57.0
66.7
1.44
1.41
1.03
57.2
66.8
1.46
1.43
1.03
57.5
66.9
1.48
1.45
1.03
57.8
67.0
1.50
1.46
1.03
58.2
67.1
1.52
1.48
1.04
58.8
67.4
1.54
1.50
1.04
59.4
67.7
1.56
1.51
1.04
60.1
68.1
1.58
1.52
1.04
4
(-16)
MIN IDLE (%N2)
APP IDLE (%N2)
TAKEOFF (EPR)
95% TAKEOFF THRUST (EPR)
90% THRUST CHANGE DECEL (EPR)
57.1
66.9
1.41
1.39
1.03
57.1
66.9
1.42
1.39
1.03
57.2
67.0
1.44
1.41
1.03
57.5
67.1
1.46
1.43
1.03
57.8
67.2
1.48
1.45
1.03
58.1
67.3
1.50
1.46
1.03
58.4
67.4
1.52
1.48
1.04
59.0
67.7
1.54
1.50
1.04
59.7
68.0
1.56
1.51
1.04
60.4
68.4
1.58
1.52
1.04
31.0 30.0 29.0 28.0 27.0 26.0 25.0 24.0 23.0 22.0
TOLERANCES:
MI N IDLE (%N2) - (+1.5/-0.5)
APP IDLE (%N2) - |0.5
TAKEOFF (EPR) - (+0.01/-0.00)
194866
Trim Table
Figure 202 (Sheet 2)
EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùùû
PW2037/PW2037(M) ENGINES
ú
ú
ú
ú
71-01-02
P01
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
CONFIG
2
Page 204
May 28/99
////////////////////////
/
PW2000 SERIES
/
/
/
ENGINES
////////////////////////
A
757
MAINTENANCE MANUAL
BAROMETER, INCHES OF MERCURY
OAT `F
(`C)
TRIM TARGETS
8
(-13)
MIN IDLE (%N2)
APP IDLE (%N2)
TAKEOFF (EPR)
95% TAKEOFF THRUST (EPR)
90% THRUST CHANGE DECEL (EPR)
57.4
67.2
1.41
1.39
1.03
57.4
67.2
1.42
1.39
1.03
57.5
67.3
1.44
1.41
1.03
57.7
67.4
1.46
1.43
1.03
58.0
67.5
1.48
1.45
1.03
58.4
67.6
1.50
1.46
1.03
58.7
67.7
1.52
1.48
1.04
59.3
68.0
1.54
1.50
1.04
59.9
68.3
1.56
1.51
1.04
60.6
68.7
1.58
1.52
1.04
12
(-11)
MIN IDLE (%N2)
APP IDLE (%N2)
TAKEOFF (EPR)
95% TAKEOFF THRUST (EPR)
90% THRUST CHANGE DECEL (EPR)
57.6
67.5
1.41
1.39
1.03
57.6
67.5
1.42
1.39
1.03
57.7
67.6
1.44
1.41
1.03
58.0
67.7
1.46
1.43
1.03
58.3
67.8
1.48
1.45
1.03
58.6
67.9
1.50
1.46
1.03
58.9
68.0
1.52
1.48
1.04
59.5
68.3
1.54
1.50
1.04
60.2
68.5
1.56
1.51
1.04
60.9
69.0
1.58
1.52
1.04
16
(-9)
MIN IDLE (%N2)
APP IDLE (%N2)
TAKEOFF (EPR)
95% TAKEOFF THRUST (EPR)
90% THRUST CHANGE DECEL (EPR)
57.9
67.8
1.41
1.39
1.03
57.9
67.8
1.42
1.39
1.03
58.0
67.9
1.44
1.41
1.03
58.2
68.0
1.46
1.43
1.03
58.5
68.1
1.48
1.45
1.03
58.8
68.2
1.50
1.46
1.03
59.2
68.3
1.52
1.48
1.04
59.8
68.6
1.54
1.50
1.04
60.4
68.9
1.56
1.51
1.04
61.2
69.3
1.58
1.52
1.04
20
(-7)
MIN IDLE (%N2)
APP IDLE (%N2)
TAKEOFF (EPR)
95% TAKEOFF THRUST (EPR)
90% THRUST CHANGE DECEL (EPR)
58.1
68.1
1.41
1.39
1.03
58.1
68.1
1.42
1.39
1.03
58.2
68.2
1.44
1.41
1.03
58.5
68.3
1.46
1.43
1.03
58.8
68.3
1.48
1.45
1.03
59.1
68.5
1.50
1.46
1.03
59.4
68.6
1.52
1.48
1.04
60.0
68.9
1.54
1.50
1.04
60.7
69.2
1.56
1.51
1.04
61.4
69.6
1.58
1.52
1.04
24
(-4)
MIN IDLE (%N2)
APP IDLE (%N2)
TAKEOFF (EPR)
95% TAKEOFF THRUST (EPR)
90% THRUST CHANGE DECEL (EPR)
58.3
68.4
1.41
1.39
1.03
58.3
68.4
1.42
1.39
1.03
58.4
68.4
1.44
1.41
1.03
58.7
68.5
1.46
1.43
1.03
59.0
68.6
1.48
1.45
1.03
59.3
68.7
1.50
1.46
1.03
59.7
68.9
1.52
1.48
1.04
60.3
69.1
1.54
1.50
1.04
61.0
69.5
1.56
1.51
1.04
61.7
69.8
1.58
1.52
1.04
28
(-2)
MIN IDLE (%N2)
APP IDLE (%N2)
TAKEOFF (EPR)
95% TAKEOFF THRUST (EPR)
90% THRUST CHANGE DECEL (EPR)
58.6
68.6
1.41
1.39
1.03
58.6
68.6
1.42
1.39
1.03
58.7
68.7
1.44
1.41
1.03
59.0
68.8
1.46
1.43
1.03
59.3
68.9
1.48
1.45
1.03
59.6
69.0
1.50
1.46
1.03
59.9
69.1
1.52
1.48
1.04
60.5
69.4
1.54
1.50
1.04
61.2
69.8
1.56
1.51
1.04
61.9
70.1
1.58
1.52
1.04
31.0 30.0 29.0 28.0 27.0 26.0 25.0 24.0 23.0 22.0
TOLERANCES:
MI N IDLE (%N2) - (+1.5/-0.5)
APP IDLE (%N2) - |0.5
TAKEOFF (EPR) - (+0.01/-0.00)
194870
Trim Table
Figure 202 (Sheet 3)
EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùùû
PW2037/PW2037(M) ENGINES
ú
ú
ú
ú
71-01-02
P01
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
CONFIG
2
Page 205
May 28/99
////////////////////////
/
PW2000 SERIES
/
/
/
ENGINES
////////////////////////
A
757
MAINTENANCE MANUAL
BAROMETER, INCHES OF MERCURY
OAT `F
(`C)
TRIM TARGETS
32
(0)
MIN IDLE (%N2)
APP IDLE (%N2)
TAKEOFF (EPR)
95% TAKEOFF THRUST (EPR)
90% THRUST CHANGE DECEL (EPR)
58.8
68.9
1.41
1.39
1.03
58.8
68.9
1.42
1.39
1.03
58.9
69.0
1.44
1.41
1.03
59.2
69.1
1.46
1.43
1.03
59.5
69.2
1.48
1.45
1.03
59.8
69.3
1.50
1.46
1.03
60.2
69.4
1.52
1.48
1.04
60.8
69.7
1.54
1.50
1.04
61.5
70.1
1.56
1.51
1.04
62.2
70.4
1.58
1.52
1.04
36
(2)
MIN IDLE (%N2)
APP IDLE (%N2)
TAKEOFF (EPR)
95% TAKEOFF THRUST (EPR)
90% THRUST CHANGE DECEL (EPR)
59.1
69.2
1.41
1.39
1.03
59.1
69.2
1.42
1.39
1.03
59.2
69.3
1.44
1.41
1.03
59.4
69.4
1.46
1.43
1.03
59.7
69.5
1.48
1.45
1.03
60.1
69.6
1.50
1.46
1.03
60.4
69.7
1.52
1.48
1.04
61.0
70.0
1.54
1.50
1.04
61.7
70.3
1.56
1.51
1.04
62.4
70.7
1.58
1.52
1.04
40
(4)
MIN IDLE (%N2)
APP IDLE (%N2)
TAKEOFF (EPR)
95% TAKEOFF THRUST (EPR)
90% THRUST CHANGE DECEL (EPR)
59.3
69.5
1.41
1.39
1.03
59.3
69.5
1.42
1.39
1.03
59.4
69.6
1.44
1.41
1.03
59.7
69.7
1.46
1.43
1.03
60.0
69.8
1.48
1.45
1.03
60.3
69.9
1.50
1.46
1.03
60.7
70.0
1.52
1.48
1.04
61.3
70.3
1.54
1.50
1.04
61.9
70.6
1.56
1.51
1.04
62.7
71.0
1.58
1.52
1.04
44
(7)
MIN IDLE (%N2)
APP IDLE (%N2)
TAKEOFF (EPR)
95% TAKEOFF THRUST (EPR)
90% THRUST CHANGE DECEL (EPR)
59.5
69.8
1.41
1.39
1.03
59.5
69.8
1.42
1.39
1.03
59.6
69.8
1.44
1.41
1.03
59.9
69.9
1.46
1.43
1.03
60.2
70.0
1.48
1.45
1.03
60.6
70.1
1.50
1.46
1.03
60.9
70.3
1.52
1.48
1.04
61.5
70.6
1.54
1.50
1.04
62.2
70.9
1.56
1.51
1.04
62.9
71.3
1.58
1.52
1.04
48
(9)
MIN IDLE (%N2)
APP IDLE (%N2)
TAKEOFF (EPR)
95% TAKEOFF THRUST (EPR)
90% THRUST CHANGE DECEL (EPR)
59.8
70.0
1.41
1.39
1.03
59.8
70.0
1.42
1.39
1.03
59.9
70.1
1.44
1.41
1.03
60.2
70.2
1.46
1.43
1.03
60.5
70.3
1.48
1.45
1.03
60.8
70.4
1.50
1.46
1.03
61.2
70.5
1.52
1.48
1.04
61.8
70.8
1.54
1.50
1.04
62.4
71.2
1.56
1.51
1.04
63.2
71.6
1.58
1.52
1.04
52
(11)
MIN IDLE (%N2)
APP IDLE (%N2)
TAKEOFF (EPR)
95% TAKEOFF THRUST (EPR)
90% THRUST CHANGE DECEL (EPR)
60.0
70.3
1.41
1.39
1.03
60.0
70.3
1.42
1.39
1.03
60.1
70.4
1.44
1.41
1.03
60.4
70.5
1.46
1.43
1.03
60.7
70.6
1.48
1.45
1.03
61.0
70.7
1.50
1.46
1.03
61.4
70.8
1.52
1.48
1.04
62.0
71.1
1.54
1.50
1.04
62.7
71.5
1.56
1.51
1.04
63.4
71.8
1.57
1.52
1.04
31.0 30.0 29.0 28.0 27.0 26.0 25.0 24.0 23.0 22.0
TOLERANCES:
MI N IDLE (%N2) - (+1.5/-0.5)
APP IDLE (%N2) - |0.5
TAKEOFF (EPR) - (+0.01/-0.00)
194871
Trim Table
Figure 202 (Sheet 4)
EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùùû
PW2037/PW2037(M) ENGINES
ú
ú
ú
ú
71-01-02
P01
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
CONFIG
2
Page 206
May 28/99
////////////////////////
/
PW2000 SERIES
/
/
/
ENGINES
////////////////////////
A
757
MAINTENANCE MANUAL
BAROMETER, INCHES OF MERCURY
OAT `F
(`C)
TRIM TARGETS
31.0 30.0 29.0 28.0 27.0 26.0 25.0 24.0 23.0 22.0
MIN IDLE (%N2)
APP IDLE (%N2)
TAKEOFF (EPR)
95% TAKEOFF THRUST (EPR)
90% THRUST CHANGE DECEL (EPR)
60.2
70.6
1.41
1.39
1.03
60.2
70.6
1.42
1.39
1.03
60.3
70.7
1.44
1.41
1.03
60.6
70.8
1.46
1.43
1.03
60.9
70.9
1.48
1.45
1.03
61.3
71.0
1.50
1.46
1.03
61.6
71.1
1.52
1.48
1.04
62.2
71.4
1.54
1.50
1.04
62.9
71.8
1.56
1.51
1.04
63.7
72.1
1.57
1.52
1.04
MIN IDLE (%N2)
APP IDLE (%N2)
TAKEOFF (EPR)
95% TAKEOFF THRUST (EPR)
90% THRUST CHANGE DECEL (EPR)
60.5
70.9
1.41
1.39
1.03
60.5
70.9
1.42
1.39
1.03
60.6
70.9
1.44
1.41
1.03
60.9
71.0
1.46
1.43
1.03
61.2
71.1
1.48
1.45
1.03
61.5
71.3
1.50
1.46
1.03
61.9
71.4
1.52
1.48
1.04
62.5
71.7
1.54
1.50
1.04
63.2
72.0
1.56
1.51
1.04
63.9
72.4
1.56
1.51
1.04
MIN IDLE (%N2)
APP IDLE (%N2)
TAKEOFF (EPR)
95% TAKEOFF THRUST (EPR)
90% THRUST CHANGE DECEL (EPR)
60.7
71.1
1.41
1.39
1.03
60.7
71.1
1.42
1.39
1.03
60.8
71.2
1.44
1.41
1.03
61.1
71.3
1.46
1.43
1.03
61.4
71.4
1.48
1.45
1.03
61.7
71.5
1.50
1.46
1.03
62.1
71.6
1.52
1.48
1.04
62.7
72.0
1.54
1.50
1.04
63.4
72.3
1.55
1.50
1.04
64.2
72.7
1.55
1.50
1.04
68
(20)
MIN IDLE (%N2)
APP IDLE (%N2)
TAKEOFF (EPR)
95% TAKEOFF THRUST (EPR)
90% THRUST CHANGE DECEL (EPR)
60.9
71.4
1.41
1.39
1.03
60.9
71.4
1.42
1.39
1.03
61.0
71.5
1.44
1.41
1.03
61.3
71.6
1.46
1.43
1.03
61.6
71.7
1.48
1.45
1.03
62.0
71.8
1.50
1.46
1.03
62.3
71.9
1.52
1.48
1.04
63.0
72.2
1.53
1.49
1.04
63.7
72.6
1.53
1.49
1.04
64.4
73.0
1.53
1.49
1.04
72
(22)
MIN IDLE (%N2)
APP IDLE (%N2)
TAKEOFF (EPR)
95% TAKEOFF THRUST (EPR)
90% THRUST CHANGE DECEL (EPR)
61.2
71.7
1.41
1.39
1.03
61.2
71.7
1.42
1.39
1.03
61.3
71.8
1.44
1.41
1.03
61.6
71.9
1.46
1.43
1.03
61.9
72.0
1.48
1.45
1.03
62.2
72.1
1.50
1.46
1.03
62.6
72.2
1.52
1.48
1.04
63.2
72.5
1.52
1.48
1.04
63.9
72.9
1.52
1.48
1.04
64.7
73.3
1.52
1.48
1.04
MIN IDLE (%N2)
APP IDLE (%N2)
TAKEOFF (EPR)
95% TAKEOFF THRUST (EPR)
90% THRUST CHANGE DECEL (EPR)
61.4
71.9
1.41
1.39
1.03
61.4
71.9
1.42
1.39
1.03
61.5
72.0
1.44
1.41
1.03
61.8
72.1
1.46
1.43
1.03
62.1
72.2
1.48
1.45
1.03
62.4
72.3
1.49
1.46
1.03
62.8
72.5
1.50
1.46
1.03
63.4
72.8
1.50
1.46
1.04
64.1
73.1
1.50
1.46
1.04
64.9
73.5
1.50
1.46
1.04
56
(13)
60
(16)
64
(18)
76
(24)
TOLERANCES:
MI N IDLE (%N2) - (+1.5/-0.5)
APP IDLE (%N2) - |0.5
TAKEOFF (EPR) - (+0.01/-0.00)
194873
Trim Table
Figure 202 (Sheet 5)
EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùùû
PW2037/PW2037(M) ENGINES
ú
ú
ú
ú
71-01-02
P01
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
CONFIG
2
Page 207
May 28/99
////////////////////////
/
PW2000 SERIES
/
/
/
ENGINES
////////////////////////
A
757
MAINTENANCE MANUAL
BAROMETER, INCHES OF MERCURY
OAT `F
(`C)
TRIM TARGETS
80
(27)
MIN IDLE (%N2)
APP IDLE (%N2)
TAKEOFF (EPR)
95% TAKEOFF THRUST (EPR)
90% THRUST CHANGE DECEL (EPR)
61.6
72.2
1.41
1.39
1.03
61.6
72.2
1.42
1.39
1.03
61.7
72.3
1.44
1.41
1.03
62.0
72.4
1.46
1.43
1.03
62.3
72.5
1.47
1.44
1.03
62.7
72.6
1.48
1.44
1.03
63.1
72.7
1.49
1.45
1.03
63.7
73.0
1.49
1.45
1.03
64.4
73.4
1.49
1.45
1.04
65.2
73.8
1.49
1.45
1.04
84
(29)
MIN IDLE (%N2)
APP IDLE (%N2)
TAKEOFF (EPR)
95% TAKEOFF THRUST (EPR)
90% THRUST CHANGE DECEL (EPR)
61.8
72.5
1.41
1.39
1.03
61.8
72.5
1.42
1.39
1.03
62.0
72.6
1.44
1.41
1.03
62.3
72.7
1.45
1.42
1.03
62.6
72.8
1.46
1.42
1.03
62.9
72.9
1.47
1.43
1.03
63.3
73.0
1.47
1.44
1.03
63.9
73.3
1.47
1.44
1.04
64.6
73.7
1.47
1.44
1.04
65.4
74.0
1.47
1.44
1.03
88
(31)
MIN IDLE (%N2)
APP IDLE (%N2)
TAKEOFF (EPR)
95% TAKEOFF THRUST (EPR)
90% THRUST CHANGE DECEL (EPR)
62.1
72.7
1.41
1.39
1.03
62.1
72.7
1.42
1.39
1.03
62.2
72.8
1.43
1.40
1.03
62.5
72.9
1.44
1.41
1.03
62.8
73.0
1.45
1.41
1.03
63.1
73.1
1.45
1.42
1.03
63.5
73.3
1.46
1.43
1.03
64.1
73.6
1.46
1.43
1.04
64.9
73.9
1.46
1.43
1.03
65.6
74.3
1.46
1.43
1.03
92
(33)
MIN IDLE (%N2)
APP IDLE (%N2)
TAKEOFF (EPR)
95% TAKEOFF THRUST (EPR)
90% THRUST CHANGE DECEL (EPR)
62.3
73.0
1.41
1.38
1.03
62.3
73.0
1.41
1.38
1.03
62.4
73.1
1.42
1.39
1.03
62.7
73.2
1.43
1.40
1.03
63.0
73.3
1.43
1.40
1.03
63.4
73.4
1.44
1.41
1.03
63.7
73.5
1.45
1.42
1.03
64.4
73.9
1.45
1.42
1.03
65.1
74.2
1.45
1.42
1.03
65.9
74.6
1.45
1.42
1.03
96
(36)
MIN IDLE (%N2)
APP IDLE (%N2)
TAKEOFF (EPR)
95% TAKEOFF THRUST (EPR)
90% THRUST CHANGE DECEL (EPR)
62.5
73.3
1.40
1.37
1.03
62.5
73.3
1.40
1.37
1.03
62.6
73.4
1.41
1.38
1.03
62.9
73.5
1.42
1.39
1.03
63.3
73.6
1.42
1.40
1.03
63.6
73.7
1.43
1.40
1.03
64.0
73.8
1.44
1.40
1.03
64.6
74.1
1.44
1.40
1.03
65.3
74.5
1.44
1.40
1.03
66.1
74.9
1.44
1.40
1.03
MIN IDLE (%N2)
APP IDLE (%N2)
TAKEOFF (EPR)
95% TAKEOFF THRUST (EPR)
90% THRUST CHANGE DECEL (EPR)
62.8
73.5
1.39
1.36
1.03
62.8
73.5
1.39
1.36
1.03
62.9
73.6
1.40
1.37
1.03
63.2
73.7
1.41
1.38
1.03
63.5
73.8
1.41
1.38
1.03
63.8
73.9
1.42
1.39
1.03
64.2
74.1
1.42
1.39
1.03
64.8
74.4
1.42
1.39
1.03
65.6
74.7
1.42
1.39
1.03
66.3
75.1
1.42
1.39
1.03
100
(37.8)
31.0 30.0 29.0 28.0 27.0 26.0 25.0 24.0 23.0 22.0
TOLERANCES:
MI N IDLE (%N2) - (+1.5/-0.5)
APP IDLE (%N2) - |0.5
TAKEOFF (EPR) - (+0.01/-0.00)
194874
Trim Table
Figure 202 (Sheet 6)
EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùùû
PW2037/PW2037(M) ENGINES
ú
ú
ú
ú
71-01-02
P01
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
CONFIG
2
Page 208
May 28/99
////////////////////////
/
PW2000 SERIES
/
/
/
ENGINES
////////////////////////
A
757
MAINTENANCE MANUAL
BAROMETER, INCHES OF MERCURY
OAT `F
(`C)
TRIM TARGETS
104
(40)
MIN IDLE (%N2)
APP IDLE (%N2)
TAKEOFF (EPR)
95% TAKEOFF THRUST (EPR)
90% THRUST CHANGE DECEL (EPR)
63.0
73.8
1.38
1.35
1.03
63.0
73.8
1.38
1.36
1.03
63.1
73.9
1.39
1.36
1.03
63.4
74.0
1.40
1.37
1.03
63.7
74.1
1.40
1.37
1.03
64.1
74.2
1.40
1.37
1.03
64.4
74.3
1.40
1.37
1.03
65.1
74.6
1.40
1.37
1.03
65.8
75.0
1.40
1.37
1.03
66.6
75.4
1.40
1.37
1.03
108
(42)
MIN IDLE (%N2)
APP IDLE (%N2)
TAKEOFF (EPR)
95% TAKEOFF THRUST (EPR)
90% THRUST CHANGE DECEL (EPR)
63.2
74.1
1.37
1.35
1.03
63.2
74.1
1.37
1.35
1.03
63.3
74.2
1.38
1.35
1.03
63.6
74.3
1.38
1.36
1.03
63.9
74.4
1.38
1.36
1.03
64.3
74.5
1.38
1.36
1.03
64.7
74.6
1.38
1.36
1.03
65.3
74.9
1.38
1.36
1.03
66.6
75.3
1.38
1.36
1.03
66.8
75.7
1.38
1.36
1.03
112
(44)
MIN IDLE (%N2)
APP IDLE (%N2)
TAKEOFF (EPR)
95% TAKEOFF THRUST (EPR)
90% THRUST CHANGE DECEL (EPR)
63.4
74.3
1.36
1.34
1.03
63.4
74.3
1.36
1.34
1.03
63.5
74.4
1.37
1.34
1.03
63.8
74.5
1.37
1.34
1.03
64.2
74.6
1.37
1.34
1.03
64.5
74.7
1.37
1.34
1.03
64.9
74.9
1.37
1.34
1.03
65.5
75.2
1.37
1.34
1.03
66.3
75.5
1.37
1.34
1.03
67.0
75.9
1.37
1.34
1.03
116
(47)
MIN IDLE (%N2)
APP IDLE (%N2)
TAKEOFF (EPR)
95% TAKEOFF THRUST (EPR)
90% THRUST CHANGE DECEL (EPR)
63.6
74.6
1.35
1.33
1.03
63.6
74.6
1.35
1.33
1.03
63.8
74.7
1.35
1.33
1.03
64.1
74.8
1.35
1.33
1.03
64.4
74.9
1.35
1.33
1.03
64.7
75.0
1.35
1.33
1.03
65.1
75.1
1.35
1.33
1.03
65.8
75.4
1.35
1.33
1.03
66.5
75.8
1.35
1.33
1.03
67.3
76.2
1.35
1.33
1.03
120
(49)
MIN IDLE (%N2)
APP IDLE (%N2)
TAKEOFF (EPR)
95% TAKEOFF THRUST (EPR)
90% THRUST CHANGE DECEL (EPR)
63.9
74.8
1.34
1.31
1.02
63.9
74.8
1.34
1.31
1.02
64.0
74.9
1.34
1.31
1.02
64.3
75.0
1.34
1.31
1.02
64.6
75.1
1.34
1.31
1.02
65.0
75.3
1.34
1.31
1.02
65.3
75.4
1.34
1.31
1.02
66.6
75.7
1.34
1.31
1.02
66.7
76.1
1.34
1.31
1.02
67.5
76.5
1.34
1.31
1.02
124
(51)
MIN IDLE (%N2)
APP IDLE (%N2)
TAKEOFF (EPR)
95% TAKEOFF THRUST (EPR)
90% THRUST CHANGE DECEL (EPR)
64.1
75.1
1.32
1.30
1.02
64.1
75.1
1.32
1.30
1.02
64.2
75.2
1.32
1.30
1.02
64.5
75.3
1.32
1.30
1.02
64.8
75.4
1.32
1.30
1.02
65.2
75.5
1.32
1.30
1.02
65.6
75.6
1.32
1.30
1.02
66.2
76.0
1.32
1.30
1.02
67.0
76.3
1.32
1.30
1.02
67.7
76.7
1.32
1.30
1.02
31.0 30.0 29.0 28.0 27.0 26.0 25.0 24.0 23.0 22.0
TOLERANCES:
MI N IDLE (%N2) - (+1.5/-0.5)
APP IDLE (%N2) - |0.5
TAKEOFF (EPR) - (+0.01/-0.00)
194876
Trim Table
Figure 202 (Sheet 7)
EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùùû
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CONFIG
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ENGINE COWLING - DESCRIPTION AND OPERATION
__________________________________________
1.
2.
General
_______
A. The engine cowling is an aerodynamically smooth surface on the engine and
prevents damage to the components on the engine.
B. You can get access to the engine components through the fan cowl panels,
the core cowl panels and the fan duct cowl and thrust reverser. Also,
you can get access to some components through the access doors in the
cowling.
C. The fan duct cowl and thrust reverser is part of the nacelle. This is
part of the exhaust system and is in 78-31-00, Thrust Reverser System.
Component Details (Fig.1)
_________________
A. Inlet Cowl
(1) The inlet cowl is installed on the forward flange of the fan case
and is an entry for air to go into the engine with minimum drag.
(2) The inlet cowl is an aluminum structure with a honeycomb core
acoustical lining and Kevlar-graphite external panels.
(3) The inlet cowl weighs approximately 411 pounds.
(4) The thermal anti-icing (TAI) duct supplies warm engine bleed air to
a spray duct manifold to prevent ice on the inlet cowl. The
manifold is installed fully around the lip of the inlet cowl
(Ref 30-21-00/001).
(5) The total pressure/total temperature (PT2/TT2) probe is installed on
the inner face of the inlet cowl. You can get access through an
access door in the outer skin of the inlet cowl.
(6) A pressure relief door is installed on the aft lower section of the
inlet cowl.
B. Fan Cowl Panels
(1) The fan cowl panels are installed on the strut with three hinges on
each panel. The fan cowl panels are latched together near the
center at the bottom left with three tension latches.
(2) The fan cowl panels are a composite structure of nomex honeycomb and
kevlar-graphite panels with an aluminum frame.
(3) The left fan cowl panel weighs approximately 96 pounds and the right
fan cowl panel weighs approximately 81 pounds.
(4) Two hold-open rods, kept on the inner side of each fan cowl panel,
hold the fan cowl panels in the open position. You can release the
lower end of the hold-open rod from the stowed position and attach
it to a receiver bracket. The two hold-open rods must be fully
extended to hold each fan cowl panel which is locked in the open
position.
(5) A pressure relief door on the left fan cowl panel opens to release
pressure if failure of the thermal anti-ice or start duct occurs.
(6) The right fan cowl panel has an access door in it to manually close
the thermal anti-ice (TAI) valve.
EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùùû
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MAINTENANCE MANUAL
HOLD-OPEN RODS
FAN COWL PANELS
CORE COWL PANELS
14TH-STAGE BLEED
TURBINE
EXHAUST SLEEVE (REF)
INLET COWL
INLET COWL PRESSURE
RELIEF DOOR
FAN COWL PRESSURE
RELIEF DOOR
CORE COWL PRESSURE
RELIEF DOOR
FAN DUCT COWL AND
THRUST REVERSER (REF)
CORE COWL PRESSURE
RELIEF DOOR
CORE COWL LATCHES
(3 LOCATIONS)
TAI VALVE
ACCESS DOOR
HOLD-OPEN ROD
DEOILER
EXHAUST
VENT
FAN COWL
LATCHES
(3 LOCATIONS)
ACCESS HOLE FOR
THE IDG OIL LEVEL
SIGHT GAGE
HOLD-OPEN RODS
START CONTROL VALVE
MANUAL OVERRIDE ACCESS
STARTER VENT/IDG
SERVICE ACCESS DOOR
89577
Engine Cowling
Figure 1
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(7)
3.
A starter vent and IDG service access door is installed near the
bottom of the right fan cowl panel.
(8) There is an opening on the bottom edge of the left fan cowl panel to
examine the IDG oil level and not open the cowling.
(9) A port in the lower section of the right fan cowl panel gives access
to the starter control valve for manual override without the cowling
open.
C. Fan Duct Cowl and Thrust Reverser
(1) The right fan duct cowl and thrust reverser has an opening for the
engine deoiler exhaust vent.
D. Core Cowl Panels
(1) The core cowl panels are installed on the strut with three hinges on
each panel. The core cowl panels are latched together at the bottom
with three tension latches.
(2) The core cowl panels are made of aluminum.
(3) Each core cowl panel weighs approximately 76 pounds.
(4) A hold-open rod, kept on the inner side of each panel, holds the
core cowl panels in the open position. You can release the lower
end of the hold-open rod from the stowed position and attach it to a
receiver bracket. One hold-open rod must be fully extended to hold
each core cowl panel which is locked in the open position.
(5) There is a pressure relief door on each core cowl panel. These
pressure relief doors open to release pressure if failure of the
pneumatic duct occurs.
(6) The left core cowl panel has an exhaust vent for the engine
14th-stage bleed.
_________
Operation
A. Functional Description
(1) To open the fan cowl and core cowl panels to get access to the
engine components, unlatch the tension latches, push the cowl open
and hold the cowl with the hold-open rods.
(2) You must open the fan cowl and core cowl panels before you open the
fan duct cowl and thrust reverser.
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ENGINE COWLING
______________
FIG.
102
SHT QTY
COMPONENT
ACCESS - LEFT ENGINE START CONTROL VALVE
MANUAL OVERRIDE
ACCESS - RIGHT ENGINE START CONTROL VALVE
MANUAL OVERRIDE
COWL - LEFT ENGINE INLET
COWL - RIGHT ENGINE INLET
DOOR - LEFT ENGINE CORE COWL PRESSURE RELIEF
DOOR - RIGHT ENGINE CORE COWL PRESSURE RELIEF
DOOR - LEFT ENGINE FAN COWL PRESSURE RELIEF
DOOR - RIGHT ENGINE FAN COWL PRESSURE RELIEF
DOOR - LEFT ENGINE INLET COWL PRESSURE RELIEF
DOOR - RIGHT ENGINE INLET COWL PRESSURE
RELIEF
DOOR - LEFT ENGINE STARTER VENT/IDG SERVICE
ACCESS
DOOR - RIGHT ENGINE STARTER VENT/IDG SERVICE
ACCESS
DOOR - LEFT ENGINE TAI VALVE ACCESS
DOOR - RIGHT ENGINE TAI VALVE ACCESS
LATCH - LEFT ENGINE CORE COWL
LATCH - RIGHT ENGINE CORE COWL
LATCH - LEFT ENGINE FAN COWL
LATCH - RIGHT ENGINE FAN COWL
PANEL - LEFT ENGINE CORE COWL
PANEL - RIGHT ENGINE CORE COWL
PANEL - LEFT ENGINE FAN COWL
PANEL - RIGHT ENGINE FAN COWL
ROD - LEFT ENGINE CORE COWL HOLD-OPEN
ROD - RIGHT ENGINE CORE COWL HOLD-OPEN
ROD - LEFT ENGINE FAN COWL HOLD-OPEN
ROD - RIGHT ENGINE FAN COWL HOLD-OPEN
ACCESS/AREA
REFERENCE
--
1
414AR, FAN COWL
71-00-00
--
1
424AR, FAN COWL
71-00-00
---------
1
1
2
2
1
1
1
1
417AL,418AR, CORE COWL
427AL,428AR, CORE COWL
413AL, FAN COWL
423AL, FAN COWL
71-11-01
71-11-01
71-11-08
71-11-08
71-11-08
71-11-08
71-11-03
71-11-03
--
1
413CL,423CL, FAN COWL
71-11-00
--
1
424AR, FAN COWL
71-11-00
---------------
1
1
3
3
3
3
2
2
2
2
2
2
4
4
414AR, FAN COWL
424AR, FAN COWL
417AL,418AR, CORE COWL
427AL,428AR, CORE COWL
413AL,414AR, FAN COWL
423AL,424AR, FAN COWL
417AL,418AR, CORE COWL
427AL,428AR, CORE COWL
413AL,414AR, FAN COWL
423AL,424AR, FAN COWL
417AL,418AR, CORE COWL
427AL,428AR, CORE COWL
413AL,414AR, FAN COWL
423AL,424AR, FAN COWL
71-11-00
71-11-00
71-11-07
71-11-07
71-11-05
71-11-05
71-11-06
71-11-06
71-11-04
71-11-04
71-11-06
71-11-06
71-11-04
71-11-04
97885
Engine Cowling - Component Index
Figure 101
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FAN COWL
HOLD-OPEN
RODS
FAN COWL
PANELS
CORE COWL
PRESSURE
RELIEF DOOR
CORE COWL
PANELS
INLET COWL
FAN COWL PRESSURE
RELIEF DOOR
CORE COWL
HOLD-OPEN
ROD
START CONTROL
VALVE MANUAL
OVERRIDE ACCESS
TAI VALVE
ACCESS DOOR
FAN COWL
HOLD-OPEN
RODS
CORE COWL PRESSURE
RELIEF DOOR
INLET COWL PRESSURE
RELIEF DOOR
CORE COWL
LATCH
CORE COWL
HOLD-OPEN
ROD
FAN COWL
LATCH
STARTER VENT/IDG SERVICE
SERVICE ACCESS DOOR
97770
Engine Cowling - Component Location
Figure 102
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ENGINE COWLING - MAINTENANCE PRACTICES
______________________________________
1.
2.
General
_______
A. The cowling access doors and panels are in the areas where aerodynamic
smoothness is important. After removal and installation, it is necessary
to adjust the panels and doors to get the correct aerodynamic smoothness
tolerances.
B. All of the dimensions shown are in inches.
TASK 71-11-00-822-001-P00
Aerodynamic Smoothness Adjustment
_________________________________
A. Access
(1) Location Zones
410
L Power Plant
420
R Power Plant
B.
Procedure (Fig. 201)
(1)
S 222-002-P00
Examine the aerodynamic smoothness of the surfaces shown in
Fig. 201.
(a) If necessary, trim, shim, or form the surfaces.
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Jan 28/02
SMOOTHLY ALIGNED
FLAG NOTES
NOTE:
____ ALL DIMENSIONS ARE IN INCHES
UNLESS SPECIFIED DIFFERENTLY.
APPROX.
10 UNITS
DEFINED AREAS
AIRFLOW
1
AIRFLOW
CRITICAL
1 UNIT
(+) POSITIVE STEP
HIGH DEGREE OF
AERODYNAMIC
SMOOTHNESS IS
NECESSARY
NON-CRITICAL
SHAPE OF THE SHAVE FAIR
IF THE BUTT JOINTS OF THE TRANSVERSE SKIN IS NOT ALIGNED BY LESS THAN
THE SPECIFIED VALUE, IT IS NECESSARY TO SHAVE THE UNWANTED MATERIAL.
YOU MUST SHAVE THE UNWANTED MATERIAL LESS THAN THE SPECIFIED VALUE.
THE SHAPE OF THE FAIR IS AS SHOWN ABOVE.
(-) NEGATIVE STEP
2
IF THE SURFACES ARE NOT ALIGNED BY LESS THAN +0.010, IT IS
NECESSARY TO SHAVE THE SURFACE AT A 10 TO 1 RATIO (SEE THE
SHAPE OF THE SHAVE FAIR DIAGRAM.)
3
THE SOUND PANEL JOINTS, PARALLEL AND PERPENDICULAR TO THE AIRFLOW,
IS SPECIFIED NOT TO BE MORE THAN 10% OF THE PANEL CIRCUMFERENTIAL
LENGTH. THIS DOES NOT INCLUDE THE +0.060 MAXIMUM PERMITTED LOCALLY
BETWEEN THE FASTENERS AND AT THE CORNERS
4
USE WITH P/N'S 314N3227-1, -2
5
USE WITH P/N'S 314N3227-45, -46
6
USE WITH 315N3317 ASSEMBLY
7
USE WITH 315N3449 ASSEMBLY
8
THE MAXIMUM TOLERANCE GAP, WHICH
IS THE ADDITION OF THE FORWARD
AND AFT GAPS, IS LESS THAN 0.18
9
A MAXIMUM ALLOWABLE GAP OF 0.400
ON 15% OF PERIPHERY AND A MAXIMUM
ALLOWABLE NEGATIVE STEP OF 0.140
ON 5% OF PERIPHERY IS FUNCTIONALLY
ACCEPTABLE.
PROBE
ACCESS
DOOR
J
J
AA CC
H-H
FWD
THE WAVE DEPTH
IS CONCAVE
OR CONVEX
A
.20
.15
AA CC EE
NON-CRITICAL
CRITICAL
.05
0
10
20
30
40
50
60
70
L-L
13.48
INCH
INTERNAL
CRITICAL
AREA
.10
THE SKIN SMOOTHNESS IN THE CRITICAL AND NON-CRITICAL
AREAS OVER THE CONTINUOUS SKIN IS LESS THAN THE
LIMITS SHOWN AT THE RIGHT. (FOR THE STRAIGHT
OR CURVED AREAS)
M V-V
M
Y-Y
A N
WAVE DEPTH TO LENGTH RATIO
ALL SKINS
1
WAVE DEPTH TO LENGTH RATIO
AT FASTENERS
1.0 MAX DIA. DISHING AT FASTENERS
CRITICAL
SEE SKIN
SMOOTHNESS
DIAGRAM ABOVE
0.0050
INLET
COWL
R
XX
F1
P
GG
D1-D1
CORE COWL
0.10
C
B
REMOVABLE PANELS
HINGED PANELS
FIXED SKINS
3
TRANSVERSE (NORMAL TO AIRSTREAM)
BUTT JOINT GAPS
FIXED SKINS
REMOVABLE & HINGED PANELS
0.00 TO +0.03
+0.01 TO +0.07
FIXED SKINS
REMOVABLE & HINGED PANELS
-0.020 TO +0.020 -0.030 TO +0.030
FIXED SKINS
-0.020 TO +0.020 -0.030 TO +0.030
REMOVABLE & HINGED PANELS
-0.025 TO +0.025 -0.040 TO +0.040
0.060
0.080
0.040
0.060
0.080
0.040
B
0.00 TO +0.06
+0.005 TO +0.105
INLET
LIP
INLET OUTER
SKIN PANEL
FLUSHNESS
LONGITUDINAL JOINT FLUSHNESS
5
TRANSVERSE JOINT FLUSHNESS
Aerodynamic Smoothness
Figure 201 (Sheet 1)
K55304
71-11-00
Page 202
Jan 28/02
LONGITUDINAL (STREAMWISE) BUTT
JOINT-MAX. GAPS
-0.025 TO +0.025 -0.040 TO +0.040
AIRFLOW
INLET
COWL
A-A
(EXAMPLE, 2 LOCATIONS - 180` APART)
B-B
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GAPS
0.16
0.04
0.14
0.02
D
C
PRIMARY EXHAUST
NOZZEL
THE INNER SURFACE OF THE TRACK
FAIRING AND THE CLOSEOUT FITTING
OF THE TRACK SUPPORT BEAM ARE
CRITICAL AREAS
15.00 INCH
INTERNAL
CRITICAL AREA
D
0.0100
E1
11.73 INCH
INTERNAL
CRITICAL AREA
C1-C1
TT-TT XX
FAN DUCT COWL
AND THRUST
REVERSER
FAN
COWL
SEE SKIN
SMOOTHNESS
DIAGRAM ABOVE
2
4
AFT STRUT
FAIRING
A1 A1
B1-B1
VV VV
X
R GG
N
NON-CRITICAL
SS-SS F1
X
U
U
STREAMWISE WAVE LENGTH - INCHES
LOCATION
RR
DD
E1
80
NECESSARY TOLERANCES FOR AERODYNAMIC SMOOTHNESS (UNLESS SPECIFIED DIFFERENTLY)
FF FF
RR
P
CONDITION
DD
EE
757
MAINTENANCE MANUAL
WAVE DEPTH -INCHES
WAVE LENGTH
A
SKIN SMOOTHNESS
OUTER BODY SKIN SURFACE
(FOR STRAIGHT OR
CURVED AREAS)
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___________________
GENERAL
INFORMATION
E
E
0.10
0.02
F
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BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
AIRFLOW
0.38
0.20
K-K
G-G
1
OF
INTERFACE
OF
INTERFACE
AIRFLOW
INLET
INNER
ACOUSTIC
PANEL
ATTACH
RING
PT2/TT2
PROBE
ACCESS DOOR
I
Aerodynamic Smoothness
Figure 201 (Sheet 2)
FAN COWL
SUPPORT BEAM
+0.05
-0.05 OVER 90% MIN
SUPPORT BEAM
+0.08
-0.08 OVER 10% MAX
SUPPORT BEAM
0.15
GAP
0.05
INLET PT2/TT2
ELECTRONIC PROBE
INLET OUTER
SKIN PANEL
1
I
+0.015
-0.025
G
INLET INNER
ACOUSTIC PANEL
L-L
0.028 AVG MAX
+0.050
1
-0.100
H-H
D-D
ENGINE
CONTAINMENT RING
AIRFLOW
INLET PT2/TT2
PROBE
G
INLET INNER
ACOUSTIC PANEL
INLET
COWL
AIRFLOW
E-E
1
AIRFLOW
0.031 AVG MAX
I-I
+0.02
-0.02
+0.080
1
-0.040
INLET OUTER
SKIN PANEL
AIRFLOW
3
+0.01
-0.03
1
0.09
0.03
M-M
0.132 AVG MAX
0.16
0.01
FAN COWL
PANEL
PT2/TT2
PROBE
ACCESS DOOR
0.06
INLET INNER
ACOUSTIC PANEL
INLET LIP
O
AIRFLOW
INLET
COWL
AIRFLOW
INLET
COWL
K
0.28
K
N-N
O
J-J
0.36
0.20
F-F
+0.02
3
-0.02
SPLICE
PLATE
FAN COWL
SUPPORT BEAM
INLET INNER
ACOUSTIC
PANEL
0.38
0.18
FAN COWL
PANEL
0.28
0.36
0.20
0.06
0.09
0.03
PRESSURE RELIEF/
TAI VENT DOOR
0.28
INLET
INNER
ACOUSTIC
PANEL
757
MAINTENANCE MANUAL
INLET
COWL
0.29
INLET INNER
ACOUSTIC PANEL
C-C
AIRFLOW
0.13
0.03
(EXAMPLE, 3 LOCATIONS - 120` APART)
INLET INNER
ACOUSTIC PANEL
F
INLET
LIP
A
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71-11-00
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140907
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S
S
O-O
T
INBD
FAN COWL PANEL
FAN COWL RECEPTACLE
FITTING
PRESSURE RELIEF/
TAI VENT DOOR
0.06
U-U
+0.03
-0.03
FAN COWL
PANEL
PRESSURE RELIEF
LATCH
0.09
0.03
W
V-V
OIL FILLER ACCESS/
PRESSURE RELIEF DOOR
0.22
Q
AIRFLOW
FAN COWL PANEL
AIRFLOW
0.25
0.19
(3 LOCATIONS)
0.150
0.120
0.090
(2 LOCATIONS)
AIRFLOW
W
+0.030
-0.030
Q
+0.03
1
-0.03
AIRFLOW
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BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
FAN COWL
PANEL
AIRFLOW
9
0.280
0.085
X-X
AIRFLOW
9
FAN COWL
PANEL
THRUST REVERSER
SLEEVE
FAN COWL PANEL
0.270
0.070
0.17
0.02
0.06
0.00
30` (REF)
STARTER VENT IDG
ACCESS DOOR
+0.050
1
-0.085
FAN COWL
PANEL
T-T
0.88R
Aerodynamic Smoothness
Figure 201 (Sheet 3)
FAN COWL
PANEL
Q-Q
FAN COWL
LATCH FITTING
+0.025
-0.025
IDG OIL LEVEL
VIEW PORT
0.180
0.000 8
(2 LOCATIONS)
W-W
PRESSURE
RELIEF
LATCH
0.265
0.060
STARTER VENT IDG
ACCESS DOOR
FAN COWL PANEL
FAN COWL
LATCH FITTING
OIL FILLER
ACCESS/PRESSURE
RELIEF DOOR
S-S
FAN COWL
PANEL
P-P
0.09
0.03
(EXAMPLE,
3 LOCATIONS)
0.06
FAN COWL PANEL
757
MAINTENANCE MANUAL
INBD
0.09
GAP
0.03
OIL FILLER ACCESS/
PRESSURE RELIEF DOOR
(EXAMPLE, 3 LOCATIONS)
R-R
+0.06
IN THE AREA MORE THAN 3.00 INCHES FROM THE SHEAR PIN
-0.06
+0.03
IN THE AREA LESS THAN 3.00 INCHES FROM THE SHEAR PIN
-0.03
T
FAN COWL
PANEL
FAN COWL LATCH
FITTING
AIRFLOW
INLET COWL
+0.03
1
-0.03
A
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K55338
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CC-CC
0.28
0.36
0.20
THRUST REVERSER ACCESS
FAIRING HINGE BEAM
AIRFLOW
THRUST REVERSER
SLEEVE
THRUST REVERSER
HINGE BEAM
0.20 0.320
0.010
THRUST
REVERSER
SLEEVE
INBD
7
+0.060
-0.060
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DD-DD
THRUST REVERSER
ACCESS FAIRING
HINGE BEAM
THRUST
REVERSER
SLEEVE
+0.120 OVER 25% MAX
-0.120 OF INTERFACE
0.24
FAN COWL
HINGE FITTING
FAN COWL
0.28 0.36
0.20
+0.060 OVER 75% MIN
-0.060 OF INTERFACE
FORWARD FAIRING
FAN COWL
PANEL
THRUST REVERSER
HINGE BEAM
0.30 0.335
0.200
Z-Z
0.25 0.31
0.06
0.040 AVG MAX
6
+0.025
-0.035
0.09
0.06
0.03
Aerodynamic Smoothness
Figure 201 (Sheet 4)
Y-Y
Z
Z
+0.03
1
-0.03
TAI VALVE
ACCESS DOOR
0.330
AVG
0.150
0.33
0.15
+0.090
-0.090
FF-FF
AIRFLOW
0.04 AVG MAX
+0.09
1
-0.09
INBD
+0.020
1
-0.020
INBD
ACTUATOR ACCESS
PANEL
0.105
GAP
0.005
THRUST REVERSER
STRUT FAIRING
(EXAMPLE, 3 LOCATIONS/SIDE)
EE-EE
THRUST REVERSER
SLEEVE
FAN COWL
SUPPORT BEAM
0.22
0.08
AA-AA
0.15
757
MAINTENANCE MANUAL
FAN COWL
PANEL
+0.050
-0.050
TAI VALVE
ACCESS DOOR
FAN COWL
PANEL
FORWARD FAIRING
A
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71-11-00
Page 205
Jan 28/02
140884
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HH
II-II
0.15
0.10
0.04
+0.06
-0.06 1
JJ
FORWARD ACCESS
DOOR
GG-GG
THRUST REVERSER
SLEEVE
0.26
0.06
AFT ACCESS
DOOR
0.16
THRUST REVERSER
SLEEVE
II II
JJ
FORWARD ACCESS
DOOR
JJ-JJ
KK KK
NN
MM
+0.060
-0.060
THRUST REVERSER
SLEEVE
AFT ACCESS
DOOR
THRUST REVERSER
SLEEVE
+0.06
-0.06
0.22 0.37
0.06
FORWARD
ACCESS
DOOR
0.41 0.485
0.310
NN
OO
LL
QQ
PP PP MM QQ
OO
LL
THRUST REVERSER
SLEEVE
0.26
0.06
TRACK SUPPORT
BEAM CLOSEOUT
FITTING
0.16
THRUST
REVERSER
SLEEVE
OO-OO
+0.06
-0.06
0.08
0.15
0.04
P01
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
0.46
0.26
LL-LL
AFT ACCESS
DOOR
Aerodynamic Smoothness
Figure 201 (Sheet 5)
0.36
0.10
THRUST
REVERSER
SLEEVE
0.16
0.26
0.06
HH-HH
TRACK SUPPORT BEAM
CLOSEOUT FITTING
THRUST REVERSER
SLEEVE
0.26
0.06
0.26
0.04
0.16
+0.060
-0.060
FORWARD ACCESS
BOND PANEL
+0.06
-0.06
AFT ACCESS
DOOR
THRUST REVERSER
SLEEVE
+0.060
1
-0.060
KK-KK
FORWARD ACCESS
DOOR
AIRFLOW
TRACK SUPPORT
BEAM CLOSEOUT
FITTING
+0.06
-0.06
MM-MM
+0.06
-0.06
FORWARD ACCESS
BOND PANEL
757
MAINTENANCE MANUAL
NN-NN
+0.06
-0.06
AIRFLOW
AIRFLOW
FORWARD
ACCESS
BOND PANEL
FAN COWL
PANEL
HH
FORWARD ACCESS
BOND PANEL
A
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Page 206
Jan 28/02
140769
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UU
P01
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
PRESSURE RELIEF
LATCH
0.09
0.03
UU
WW-WW
AIRFLOW
0.06
0.02
0.26
0.04
QQ-QQ
FORWARD
ACCESS PANEL
0.10
+0.06
-0.06
FORWARD
ACCESS PANEL
AIRFLOW
G1
CORE
COWL
PANEL
CORE COWL
DE-OILER
EXHAUST DUCT
TRACK SUPPORT
BEAM CLOSEOUT
FITTING
AFT ACCESS
DOOR
Aerodynamic Smoothness
Figure 201 (Sheet 6)
TT-TT
PP-PP
+0.060
1
-0.060
CORE
COWL
PANEL
CORE
COWL
PANEL
UU-UU
+0.03
1
-0.03
YY
CORE COWL
LATCH FITTING
RR-RR
INBD
AIRFLOW
WW
WW
SS-SS
0.06
+0.040
-0.040
YY
CORE
COWL
PANEL
CORE COWL
RECEPTACLE
FITTING
+0.06
IN THE AREA MORE THAN 3.0 INCHES FROM THE SHEAR PIN
-0.06
+0.03
IN THE AREA LESS THAN 3.0 INCHES FROM THE SHEAR PIN
-0.03
VV-VV
0.100
GAP
0.030
CORE COWL
PANEL
PRESSURE RELIEF
LATCH
0.48 0.58 4
0.38
0.43
0.33
5
0.23
0.025 AVG MAX
+0.080
1
-0.035
0.06R 0.07R
0.05R
(LEFT SIDE SHOWN, RIGHT SIDE OPPOSITE)
CORE COWL
AIRFLOW
FAN DUCT
INNER WALL
PRESSURE RELIEF
DOOR INSTL
THRUST REVERSER
STRUT FAIRING
0.140
0.120
(EXAMPLE, 3 LOCATIONS)
XX-XX
CORE COWL
DE-OILER
EXHAUST DUCT
0.330
AVG
0.140
0.35
0.12
0.080 AVG MAX
+0.09
-0.09
0.18
CORE COWL
SKIRT FAIRING
0.130
CORE
COWL
PANEL
757
MAINTENANCE MANUAL
G1
PRESSURE
RELIEF
DOOR
CORE
COWL
PANEL
FORWARD ACCESS
DOOR
0.15
0.08
0.04
A
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0.21
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P01
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
Aerodynamic Smoothness
Figure 201 (Sheet 7)
+0.80
-0.80
PRESSURE
RELIEF
DOOR
CORE
COWL
PANEL
G1-G1
ZZ-ZZ
D1-D1
+0.03
1
-0.03
AIRFLOW
INBD
CORE
COWL
PANEL
PRESSURE RELIEF
LATCH
0.56
(COLD POSITION)
0.44
AIRFLOW
0.50
PRIMARY EXHAUST
NOZZLE
A1-A1
AIRFLOW
CORE COWL
PANEL
PRIMARY EXHAUST
NOZZLE
PRIMARY EXHAUST
NOZZLE
CORE COWL
PANEL
LATCH HANDLE
+0.045
-0.045
0.32
(COLD POSITION)
0.20
AIRFLOW
E1-E1
THE TOTAL HEIGHT DIFFERENCE
0.020 FOR ALL WELDED SEAMS
0.000 IN THE CRITICAL AREA OF
THE SLEEVE ASSEMBLY
0.26
TURBINE
EXHAUST
CASE
B1-B1
0.20
+0.06
1
-0.06
PRIMARY
EXHAUST
PLUG
757
MAINTENANCE MANUAL
F1-F1
PRIMARY
EXHAUST
NOZZLE
+0.06
-0.06
+0.03
-0.03
(DIFFERENCE BETWEEN
THRUST REVERSER
HALVES)
YY-YY
LATCH
HANDLE
C1-C1
ZZ
ZZ
FAN DUCT COWL
+0.06
1
-0.06
AIRFLOW
0.140
0.000
TURBINE
EXHAUST CASE
0.27
0.14
CORE COWL
PANEL
CORE COWL
PANEL
A
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INLET COWL - REMOVAL/INSTALLATION
_________________________________
1.
2.
General
_______
A. There are two tasks in this procedure. The first task is the removal of
the inlet cowl. The second task is the installation of the inlet cowl.
B. It is necessary to have a crane to complete this procedure. A
dynamometer is also necessary unless the crane has an adjustable load
limit. The dynamometer is necessary to prevent damage to the cowl by
large loads that lift the cowl when it is attached to the engine.
C. The inlet cowl sling has three hoists, adjustable straps, and a sling
link. These parts permit the cowl to be moved vertically, and to be
moved about the longitudinal and lateral axes.
D. When the inlet cowl is removed, it can be put on a platform with the
front side up or down. If the inlet cowl is put with the front side up,
carefully support the cowl to prevent damage to the thermal anti-ice
(TAI) duct.
TASK 71-11-01-004-001-P00
Remove the Inlet Cowl
_____________________
A. Equipment
(1) Inlet Cowl Sling - A71005-33
(2) Dynamometer - 0-1000 pound capacity,
| 2% accuracy, Part Number AP30006-0027
W. C. Dillon Co. Inc., Van Nuys, CA
(not necessary if the crane has an adjustable
load limit)
(3) Ratchet Hoist (3 are necessary),
Part Number L4H150, Ingersoll Rand,
Shippensberg, PA
B. Consumable Materials
(1) D00015 Grease - Corrosion Resistant BMS 3-24
C. References
(1) 71-11-04/201, Fan Cowl Panels
D. Access
(1) Location Zones
412
Inlet Cowl, Left Engine
422
Inlet Cowl, Right Engine
(2)
Access Panels
413AL
Fan
414AR
Fan
423AL
Fan
424AR
Fan
Cowl
Cowl
Cowl
Cowl
Panel,
Panel,
Panel,
Panel,
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Left Engine
Left Engine
Right Engine
Right Engine
71-11-01
P01
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Page 401
Dec 20/91
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E.
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Procedure
(1)
(2)
(3)
(4)
S 864-002-P00
For the left engine, open this circuit breaker on the overhead
circuit breaker panel, P11, and attach a DO-NOT-CLOSE tag:
(a) 11R14, ENG PROBE HTR LEFT
S 864-003-P00
For the right engine, open this circuit breaker on the overhead
circuit breaker panel, P11, and attach a DO-NOT-CLOSE tag:
(a) 11R23, ENG PROBE HTR RIGHT
S 014-004-P00
Open the fan cowl panels (Ref 71-11-04).
S 034-005-P00
Do these steps to disconnect the thermal anti-icing (TAI) duct
(Fig. 401):
(a) Make a note of the position of the coupling for the correct
installation.
(b) Remove the V-band coupling (2) and the seal (1) from the duct.
CAUTION:
_______
(c)
(5)
(6)
PUT CAPS ON ALL OF THE OPEN ENDS OF THE TAI DUCT
IMMEDIATELY AFTER YOU DISCONNECT THE DUCT. IF DIRT GETS
IN THE TAI DUCT, A BLOCKAGE CAN OCCUR.
Put caps on the open ends of the TAI duct.
S 034-006-P00
Disconnect the PT2 tube from the inlet cowl (Fig. 402):
(a) Put caps on the PT2 tube and on the inlet cowl.
S 034-007-P00
Do these steps to disconnect the electrical connectors from the
PT2/TT2 probe (14) (Fig. 402).
(a) Remove the bolts (2, 13) that attach the access panel (1) to
the inlet cowl.
(b) Remove the access panel (1).
(c) Disconnect the electrical connectors (15, 16) from the PT2/TT2
probe (14).
(d) If you will not install the same inlet cowl, do these steps:
1) Lubricate all of the bolt surfaces (2, 13) with the grease.
2) Put the access panel (1) in its position on the inlet cowl.
3) Install the CRES (marked B30LR) bolts (13) at the forward
and the aft positions.
4) Install the titanium (marked B30NN) bolts (2).
(e) Remove the bolts (3) that attach the bracket (4) to the inlet
cowl.
(f) Move the bracket (4), the plate (5), and the seal (6) aft.
(g) Pull the electrical harness out of the inlet cowl.
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71-11-01
P01
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
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Mar 20/91
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A
757
MAINTENANCE MANUAL
SEE
ALIGNMENT
MARKS
A
1. SEAL
2. COUPLING
3. NUT
FWD
A
97763
TAI Duct Installation
Figure 401
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71-11-01
P01
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
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Jun 20/91
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A
757
MAINTENANCE MANUAL
SEE
A
3. BOLT
(4 LOCATIONS)
2. BOLT
(6 LOCATIONS)
1. ACCESS
PANEL
SEE
B
13. BOLT
(2 LOCATIONS)
12. WASHER
(24 LOCATIONS)
11. NUT
(24 LOCATIONS)
6. SEAL
10. INLET COWL
5. PLATE
4. BRACKET
7. BOLT
(24 LOCATIONS)
8. WASHER
(24 LOCATIONS)
9. SPACER
(24 LOCATIONS)
PT2 LINE
A
97741
Inlet Cowl Installation
Figure 402 (Sheet 1)
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71-11-01
P01
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Page 404
Jun 20/91
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MAINTENANCE MANUAL
14. PT2/TT2
PROBE
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YFPB-P71-00-0082
15. ELECTRICAL
CONNECTOR
16. ELECTRICAL
CONNECTOR
B
97767
Inlet Cowl Installation
Figure 402 (Sheet 2)
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71-11-01
P02
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
Page 405
Mar 15/87
A
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MAINTENANCE MANUAL
(7)
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S 494-008-P00
Do these steps to install the inlet cowl sling (Fig. 403):
WARNING:
_______
(a)
MAKE SURE YOU KNOW HOW TO USE A RATCHET HOIST BEFORE YOU
APPLY A LOAD TO THE HOIST. A RATCHET HOIST WITH A LIGHT
LOAD ON IT CAN RELEASE IF IT IS PUT INTO A NEUTRAL (OR
FREE) POSITION. IF THE RATCHET HOIST RELEASES, INJURIES
TO PERSONS OR DAMAGE TO EQUIPMENT CAN OCCUR.
If the crane has an adjustable load limit, adjust the limit to
balance the weight of the inlet cowl and the sling equipment.
NOTE:
____
(b)
(c)
(d)
(e)
If the crane does not have an adjustable load limit, install a
dynamometer on the crane hook.
Install the sling equipment on the crane hook (or to the
dynamometer if it is installed).
Put the crane, with the sling equipment, in its position above
the inlet cowl.
Install the spindles in the receptacles on the inlet cowl at
the three and the nine o'clock positions (4 locations).
1) If you will put the inlet cowl on a platform with the front
side up, attach the strap (without a hoist) to the forward
receptacle.
2) If you will put the inlet cowl on a platform with the front
side down, connect the strap (without a hoist) to the aft
receptacle.
3) Install the three spindles with the hoists to the inlet
cowl.
WARNING:
_______
(f)
Refer to the placard on the sling equipment for the
weight of the inlet cowl and sling equipment.
MAKE SURE THE SPINDLES ARE TIGHT. IF THE SPINDLES BECOME
LOOSE WHILE YOU LIFT THE COWL, INJURIES TO PERSONS OR
DAMAGE TO EQUIPMENT CAN OCCUR.
Make sure the spindles are tight.
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71-11-01
P01
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Mar 20/92
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A
757
MAINTENANCE MANUAL
DYNAMOMETER
SEE
INLET COWL
SLING LINK
B
INLET COWL
SEE
A
INLET COWL
SLING LINK
HOIST
SHACKLE
RECEPTACLE
STRAP
STRAP AND
SPINDLE
SPINDLE
RING
HOIST RECEPTACLE
(4 LOCATIONS)
ADJUSTMENT HOIST
(3 LOCATIONS)
A
B
97742
Inlet Cowl Sling Installation
Figure 403
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71-11-01
P01
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
Page 407
Mar 20/92
A
757
MAINTENANCE MANUAL
WARNING:
_______
(g)
(h)
ADJUST THE CRANE TO BALANCE THE WEIGHT OF THE INLET COWL
AND THE SLING EQUIPMENT. IF YOU APPLY TOO MUCH FORCE ON
THE INLET COWL, YOU CAN CAUSE INJURIES TO PERSONS OR
DAMAGE TO EQUIPMENT.
Adjust the crane and the sling straps until the straps are
tight.
Make sure the load on the inlet cowl is not more than the
weight of the inlet cowl and the sling equipment.
NOTE:
____
(8)
Refer to the placard on the sling equipment for the
weight of the inlet cowl and sling equipment.
S 024-009-P00
Do these steps to remove the inlet cowl (Fig. 402):
(a) Remove all of the mount bolts (7) but two (at approximately the
three o'clock and the nine o'clock positions).
(b) Slowly loosen the last two bolts (7) and make sure the crane is
in the correct position.
(c) Remove the last tow bolts.
CAUTION:
_______
(d)
(9)
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HOLD THE INLET COWL STABLE WHEN YOU DISENGAGE THE
ALIGNMENT PINS. THE INLET COWL CAN TURN WHEN THE
ALIGNMENT PINS DISENGAGE, WHICH CAN CAUSE DAMAGE TO THE
COWL OR TO THE ENGINE.
Move the inlet cowl forward to disengage the alignment pins.
S 024-010-P00
Put the inlet cowl on a platform or on sandbags.
(a) Put the inlet cowl in its position above a platform or
sandbags.
(b) Adjust the hoists to turn the inlet cowl until the front side
is up or down.
CAUTION:
_______
(c)
(d)
WHEN YOU LOWER THE INLET COWL, MAKE SURE THE TAI DUCT GOES
IN AN OPENING ON THE PLATFORM (OR SANDBAGS). IF THE
WEIGHT OF THE INLET COWL IS ON THE TAI DUCT, DAMAGE TO THE
COWL WILL OCCUR.
If you put the inlet cowl on the platform with the front side
up, make sure the TAI duct goes in an opening on the platform.
Lower the inlet cowl on the platform.
S 094-011-P00
(10) If you will not install the same inlet cowl, remove the sling
equipment.
(a) Lower the crane to remove the tension from the sling.
(b) Remove the spindles from the inlet cowl.
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71-11-01
P01
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
Page 408
Mar 20/92
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MAINTENANCE MANUAL
(c)
(d)
3.
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Lower the sling to the ground away from the inlet cowl.
Remove the sling from the crane hook.
TASK 71-11-01-404-012-P00
Install the Inlet Cowl
______________________
A. Equipment
(1) Inlet Cowl Sling - A71005-33
(2) Dynamometer - 0-1000 pound capacity,
|2% accuracy, Part Number AP30006-0027,
W. C. Dillon Co. Inc., Van Nuys, CA
(not necessary if the crane has an adjustable
load limit)
(3) Ratchet Hoist (3 are necessary),
Part Number L4H150, Ingersoll Rand,
Shippensberg, PA
B. Consumable Materials
(1) D00015 Grease - Corrosion Resistant BMS 3-24
C. Parts
~¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼ ¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼ ¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼
¦
AMM
¦
¦
AIPC
¦
»¼¼¼¼¼ ¼¼¼¼¼¼¼¼¼«
»¼¼¼¼¼¼¼¼¼¼ ¼¼¼¼¼¼ ¼¼¼¼¼¼¼¼«
¦ FIG¦
ITEM ¦
NOMENCLATURE
¦ SUBJECT ¦ FIG ¦
ITEM ¦
»¼¼¼¼¼î¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼î¼¼¼¼¼¼¼¼«
¦ 401¦
1
¦ Seal
¦ 30-21-01¦
02 ¦
105 ¦
¦
¦
2
¦ Coupling
¦
¦
¦
100 ¦
¦ 402¦
1
¦ Door Assy - Access
¦ 71-11-01¦
01 ¦
36 ¦
¦
¦
2
¦ Bolt
¦
¦
¦
40 ¦
¦
¦
3
¦ Bolt
¦
¦
¦
237 ¦
¦
¦
7
¦ Bolt
¦
¦
¦
26 ¦
¦
¦
8
¦ Washer
¦
¦
¦
28 ¦
¦
¦
9
¦ Spacer
¦
¦
¦
31 ¦
¦
¦
10
¦ Inlet Assy
¦
¦
¦
34 ¦
¦
¦
11
¦ Nut
¦
¦
¦
32 ¦
¦
¦
12
¦ Washer
¦
¦
¦
30 ¦
¦
¦
13
¦ Bolt
¦
¦
¦
38 ¦
²¼¼¼¼¼…¼¼¼¼¼¼¼¼¼…¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼…¼¼¼¼¼¼¼¼¼¼…¼¼¼¼¼¼…¼¼¼¼¼¼¼¼¹
D.
E.
References
(1) 71-00-04/201, Power Plant
(2) 71-11-04/201, Fan Cowl Panels
Access
(1) Location Zones
412
Inlet Cowl, Left Engine
422
Inlet Cowl, Right Engine
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71-11-01
P01
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(2)
F.
Access Panels
413AL
Fan
414AR
Fan
423AL
Fan
424AR
Fan
Cowl
Cowl
Cowl
Cowl
Panel,
Panel,
Panel,
Panel,
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Left Engine
Left Engine
Right Engine
Right Engine
Procedure
(1)
(2)
(3)
S 224-013-P00
Do a check of the repair limits for the acoustic panels
(Ref 71-00-04).
S 214-014-P00
Make sure the alignment pins, washers, and nuts, are installed on
the inlet cowl (at the flange Ao) at the three and the nine o'clock
positions.
S 494-015-P00
If it was removed, install the inlet cowl sling (Fig. 403):
WARNING:
_______
(a)
MAKE SURE YOU KNOW HOW TO USE A RATCHET HOIST BEFORE YOU
APPLY A LOAD TO THE HOIST. A RATCHET HOIST WITH A LIGHT
LOAD ON IT CAN RELEASE IF IT IS PUT INTO A NEUTRAL (OR
FREE) POSITION. IF THE RATCHET HOIST RELEASES, INJURIES
TO PERSONS OR DAMAGE TO EQUIPMENT CAN OCCUR.
If the crane has an adjustable load limit, adjust the limit to
balance the weight of the inlet cowl and the sling equipment.
NOTE:
____
(b)
(c)
If the crane does not have an adjustable load limit, install a
dynamometer on the crane hook.
Install the spindles in the receptacles on the inlet cowl (4
locations).
1) If the inlet cowl has the front side up, connect the strap
without the hoist to the forward receptacle.
2) If the inlet cowl has the front side down, connect the
strap without the hoist to the aft receptacle.
3) Install the three spindles with the hoists to the inlet
cowl.
WARNING:
_______
(d)
Refer to the placard on the sling equipment for the
weight of the inlet cowl and sling equipment.
MAKE SURE THE SPINDLES ARE TIGHT. IF THE SPINDLES BECOME
LOOSE WHILE YOU LIFT THE COWL, INJURIES TO PERSONS OR
DAMAGE TO EQUIPMENT CAN OCCUR.
Make sure the spindles are tight.
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(4)
(5)
(6)
(7)
(8)
(9)
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S 424-016-P00
Do these steps to install the inlet cowl (8) to the engine
(Fig. 402):
(a) Remove the straps that attach the inlet cowl to the platform.
(b) Adjust the crane and the hoists until the straps are tight.
(c) Lift the inlet cowl with the crane until there is sufficient
clearance to turn the cowl.
(d) Adjust hoists to turn the inlet cowl until it is vertical.
(e) Align the inlet cowl with the alignment pins on the engine
flange.
(f) Move the inlet cowl (10) aft to engage the alignment pins.
(g) Install the washers (8) and the spacers (9) on the bolts (7).
(h) Install the bolts (7), the washers (8), the spacers (9), and
the nuts (11) to attach the inlet cowl to the engine.
1) Tighten the nuts (11) on the bolts (7) to a torque of
300-500 pound-inches (33.9-56.5 newton-meters).
S 094-017-P00
Disconnect the sling equipment from the inlet cowl.
(a) Lower the crane to remove the tension from the straps.
(b) Remove the spindles from the inlet cowl.
(c) Move the crane and the sling equipment away from the engine.
(d) Remove the sling equipment from the crane.
S 434-018-P00
Remove the caps from the PT2 tube and connect the tube to the inlet
cowl (Fig. 403):
S 434-019-P00
Do these steps to connect the electrical connectors to the PT2/TT2
probe (14) (Fig. 402):
(a) Remove the access panel (1), if it is installed.
(b) Put the electrical harness into the inlet cowl.
(c) Attach the electrical connectors (13,14) to the PT2/TT2
probe (14).
(d) Attach the seal (6), the plate (5), and the bracket (4) to the
inlet cowl with the bolts (3).
S 414-020-P00
Do these steps to install the access panel (1) (Fig. 402):
(a) Put the access panel (1) in its position on the inlet cowl.
(b) Lubricate all of the surfaces of the bolts (2,13) with the
grease.
(c) Install the CRES (marked B30LR) bolts (13) at the forward and
the aft positions.
(d) Install the titanium (marked B30NN) bolts (2).
S 434-021-P00
Do these steps to connect TAI duct to the inlet cowl (Fig. 401):
(a) Remove the caps from the TAI ducts.
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(b)
(c)
(d)
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Examine the seal (1) for scratches, cuts, pits or unwanted
material.
1) If it is necessary, replace the seal (1).
Put the seal (1) in its position between the ducts.
Connect the ducts with the coupling (2).
1) Make sure the coupling is installed correctly.
NOTE:
____
2)
A note of the correct installation was made
during the removal of the inlet cowl.
Tighten the nut (3) on the coupling (2) to 85-100
pound-inches (9.61-11.30 newton meters).
S 214-022-P00
CAUTION:
_______
KEEP TOOLS AND OTHER OBJECTS OUT OF THE INLET COWL. IF OBJECTS
ARE IN THE INLET COWL WHEN THE ENGINE STARTS, DAMAGE TO THE
ENGINE WILL OCCUR.
(10) Make sure that no tools or other objects are in the inlet cowl.
S 414-023-P00
(11) Close the fan cowl panels (Ref 71-11-04).
S 864-024-P00
(12) For the left engine, remove the DO-NOT-CLOSE tag and close this
circuit breaker on the overhead circuit breaker panel, P11:
(a) 11R14, ENG PROBE HTR LEFT
S 864-025-P00
(13) For the right engine, remove the DO-NOT-CLOSE tag and close this
circuit breaker on the overhead circuit breaker panel, P11:
(a) 11R23, ENG PROBE HTR RIGHT
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INLET COWL PRESSURE RELIEF DOOR - REMOVAL/INSTALLATION
______________________________________________________
1.
2.
General
_______
A. There are two tasks in this procedure. The first task is the removal
procedure for the pressure relief door on the inlet cowl. The second
task is the installation procedure for the pressure relief door on the
inlet cowl.
B. The pressure relief door is on the bottom side of the inlet cowl. This
door will release the pressure in the inlet cowl if the thermal anti-ice
(TAI) duct has a failure. This door attaches to the inlet cowl with two
latches and two hinges.
TASK 71-11-03-004-001-P00
Pressure Relief Door Removal (Fig. 401)
____________________________
A. Access
(1) Location Zones
412
Inlet Cowl, Left Engine
422
Inlet Cowl, Right Engine
B.
Procedure
(1)
3.
S 034-002-P00
Put a screwdriver into the latches and apply a force to the
screwdriver to release the latches (2 locations).
(2)
S 034-003-P00
Use a punch to remove the two roll pins from each of the hinges.
(3)
S 034-004-P00
Remove the two bolts from each of the hinges.
(4)
S 024-005-P00
Remove the door from the inlet cowl.
TASK 71-11-03-404-006-P00
Pressure Relief Door Installation (Fig. 401)
_________________________________
A. Consumable Materials
(1) C00259 Primer - BMS 10-11 Type 1
(2) D00015 Grease - BMS 3-24
B. References
(1) 71-11-03/501, Inlet Cowl Pressure Relief Door
C. Access
(1) Location Zones
412
Inlet Cowl, Left Engine
422
Inlet Cowl, Right Engine
D.
Procedure
(1)
S 214-007-P00
Examine the bushing to see if it is worn.
(a) If it is necessary, replace the bushing.
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SEE A
SEE B
SEE B
NUT
(2 LOCATIONS)
HINGE
SUPPORT
INLET COWL
PRESSURE
RELIEF DOOR
WASHER
(2 LOCATIONS)
LATCH
(2 LOCATIONS)
ROLL PIN
(2 LOCATIONS)
A
BUSHING
HINGE
WASHER
(SPACER)
SHIM
DOOR
BOLT
(2 LOCATIONS)
B
117561
Inlet Cowl Pressure Relief Door Installation
Figure 401
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(2)
(3)
S 424-008-P00
Do these steps to attach the pressure relief door to the inlet cowl:
(a) Install the washer and the hinge into the hinge support.
(b) Apply the grease to the threads of the bolts.
(c) Attach the door to the hinges with the bolts, the washers, the
shim, and the nuts.
1) Tighten the nuts.
S 824-009-P00
Adjust the pressure relief door (Ref 71-11-03/501).
(4)
S 434-010-P00
If you did not apply the primer to the shims, remove the door.
(a) Apply the primer to the shims.
(5)
S 434-011-P00
Attach the pressure relief door to the inlet cowl, but do not
tighten the nuts at this time.
(6)
S 434-012-P00
Install the roll pins until they are smooth with the external
surface of the door.
NOTE:
____
(a)
There are more than two holes in the hinge fittings for
the roll pins. These holes are for subsequent adjustment.
Do not drill new holes for the roll pins until it is
necessary.
Cut the internal end of the roll pin until it is smooth with
the hinge fitting.
(7)
S 434-013-P00
Tighten the nuts.
(8)
S 434-014-P00
Close the pressure relief door.
(9)
S 434-015-P00
Apply the primer to the end of the roll pins on the external side of
the door.
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INLET COWL PRESSURE RELIEF DOOR - ADJUSTMENT/TEST
_________________________________________________
1.
2.
General
_______
A. There are two tasks in this procedure. The first task does a latch test
of the pressure relief door on the inlet cowl. The second task does a
check of the aerodynamic smoothness of the pressure relief door on the
inlet cowl.
(1) The latch test makes sure the latches will release with the correct
force.
(2) The check of the aerodynamic smoothness makes sure the pressure
relief door has the correct tolerances.
TASK 71-11-03-725-001-P00
Latch Test for the Inlet Cowl Pressure Relief Door
__________________________________________________
A. Equipment
(1) Adapter - Load Test - Pressure Relief Door
Latch - B71044-10
B. Access
(1) Location Zones
412
Inlet Cowl, Left Engine
422
Inlet Cowl, Right Engine
C.
Do the Test of the Latches on the Pressure Relief Door (Fig. 501).
(1)
(2)
S 015-016-P00
Open the latches on the pressure relief door.
(a) Put the blade of a straight-slot screwdriver into the latch
slot (1).
(b) Move the screwdriver handle to the side to turn the latch (1)
to the open position.
S 485-003-P00
Install the load-test-adapter-tool for the latch on the pressure
relief door.
(a) Remove the two latch mounting bolts (3) that are nearest to the
edge of the pressure relief door.
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COWL PANEL
INSIDE
(REF)
DOOR
SEE
A
3. BOLTS
LATCH
B
SEE
INLET COWL
PRESSURE
RELIEF DOOR
B
SEE
A
B
1. LATCH
(2 lOCATIONS)
5. PIVOT
SUPPORT
ASSEMBLY
5. PIVOT
SUPPORT
ASSEMBLY
DOOR FRAME
(REF)
2. ADAPTER
ASSEMBLY
2. ADAPTER
ASSEMBLY
TORQUE WRENCH
AND 13/16 SOCKET
DOOR SIDE
(REF)
7. PIVOT
BOLT
6. RING PIN
SEE
C
6. RING PIN
STRUCTURE SIDE
(REF)
4. ADAPTER BOLT
WASHER
NUT
(2 LOCATIONS)
DOOR LATCH
(REF)
C
B71044-10 LOAD TEST TOOL INSTALLATION
D00326
Inlet Cowl Pressure Relief Door Latch Test
Figure 501
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(b)
Temporarily fasten the adapter assembly (2) to the door with
the bolts (4) that are supplied with the adapter assembly.
1) Put the adapter bolts (4) into the bolt holes that the
latch bolts (3) were removed from.
2) Tighten the nuts on the bolts (4) with your fingers.
Attach the arm of the pivot support assembly (5) to the adapter
assembly (2) with the ring pin (6).
Put the base of the pivot support assembly (5) flush on the
surface of the pressure relief door.
(c)
(d)
NOTE:
____
(3)
Make sure that the handle of the torque wrench is parallel
with the surface of the pressure relief door.
S 415-018-P00
Close the latch (1) that you will examine on the pressure relief
door.
(a) Put the blade of a straight-slot screwdriver into the slot on
the latch (1) that you will examine.
(b) Move the screwdriver handle until the latch (1) is in the fully
open position, and close the pressure relief door.
(c) Move the screwdriver in the opposite direction to lock the
latch (1).
(d) Do not lock the opposite latch.
NOTE:
____
(5)
The axis of the main tube of the pivot support
assembly (5) must be vertical, or 90-degrees, to the
surface of the pressure relief door. The arm of the
pivot support assembly (5), that connects to the adapter
assembly (2), also must be 90-degrees to the surface of
the pressure relief door. When you put the tool in this
correct position and turn the torque wrench, force will
be applied correctly at the centerline of the latch.
S 485-013-P00
Attach the torque wrench to the pivot bolt (7) of the pivot support
assembly (5).
NOTE:
____
(4)
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The opposite latch must stay unlocked during the test.
S 725-004-P00
Do the test of the latches on the pressure relief door.
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CAUTION:
_______
(a)
(b)
(c)
(d)
PUT A FOLDED SHOP CLOTH OR RUBBER MAT BETWEEN THE TORQUE
WRENCH HANDLE AND THE PRESSURE RELIEF DOOR (BEFORE YOU
TURN THE HANDLE TO OPEN THE LATCH). THIS WILL PREVENT
INJURY TO YOUR HAND WHEN YOU SUDDENLY RELEASE THE LATCH.
ALSO, IT WILL PREVENT SCRATCHES TO THE SURFACE OF THE
PRESSURE RELIEF DOOR CAUSED BY THE TORQUE WRENCH HANDLE.
IF YOU DO NOT DO THIS, INJURIES TO PERSONS OR DAMAGE TO
EQUIPMENT CAN OCCUR.
Put a folded shop cloth or rubber mat between the torque wrench
handle and the pressure relief door.
With the handle of the torque wrench parallel to the surface of
the pressure relief door, turn the handle down smoothly.
As you turn the handle down, make a record of the torque when
the latch on the pressure relief door opens.
The latch is serviceable if the torque used to open it is
94.0-130.0 pound-inches (10.6-14.7 newton-meters).
NOTE:
____
(6)
(7)
(8)
(9)
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The force necessary to open the latch is 47-65 pounds
(21.3-29.5 kilograms). But, the arm of the pivot
support assembly which pulls up on the latch decreases
the applied force by a factor of two. This makes it
necessary to increase the force you apply by a factor of
two. Thus, the latch must unlock when the torque wrench
shows 94.0-130.0 pound-inches (10.6-14.7 newton-meters).
S 025-014-P00
If the force to release the latch (1) is not in the specified
limits, replace the latch.
S 085-015-P00
Remove the load-test-adapter-tool from the pressure relief door.
(a) Remove the pivot support assembly (5) from the pressure relief
door.
(b) Remove the adapter assembly (2) from the pressure relief door.
(c) Install the mounting bolts, washers and nuts (3) on the latch,
and tighten the nuts (3).
S 725-005-P00
Do these steps again to do a test of the other latch on the pressure
relief door.
S 415-006-P00
When you have completed the tests for the two latches on the
pressure relief door, do these steps:
(a) Put the blade of a straight-slot screwdriver into the slot of
one of the latches (1) on the pressure relief door.
(b) Move the screwdriver handle until the latch (1) is in the fully
open position, and close the pressure relief door.
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(c)
(d)
3.
Move the screwdriver in the opposite direction to lock the
latch (1).
Do these steps again to close the opposite latch (1) on the
pressure relief door.
TASK 71-11-03-225-007-P00
Aerodynamic Smoothness Check of the Inlet Cowl Pressure Relief Door
___________________________________________________________________
A. Consumable Materials
(1) C00259 Primer - BMS 10-11 Type 1
B. References
(1) 71-11-00/201, Aerodynamic Smoothness
(2) 71-11-03/401, Inlet Cowl Pressure Relief Door
C. Access
(1) Location Zones
412
Inlet Cowl, Left Engine
422
Inlet Cowl, Right Engine
D.
Procedure
(1)
(2)
(3)
(4)
S 215-008-P00
Make sure the pressure relief door is fully closed.
S 225-009-P00
Make sure the pressure relief door is in the limits for the
aerodynamic smoothness (Ref 71-11-00/201).
(a) Do a check of the clearance at the sides of the door.
(b) Make sure the surface of the door is smooth with the inlet
cowl.
S 225-010-P00
If the vent is not in the limits for the aerodynamic smoothness, do
these steps to adjust the door:
(a) Adjust the side clearance of the door.
1) Make sure the door does not move when the door is fully
closed.
2) Remove or install washers as necessary between the hinges
and the bushings (Ref 71-11-03/401).
(b) Adjust the surface height of the door (smoothness).
1) Remove the pressure relief door (Ref 71-11-03/401).
2) Remove the laminations of the shim (or install a new shim)
to make the door smooth with the inlet cowl.
3) Apply the primer to the shim.
4) Attach the door to the inlet cowl (Ref 71-11-03/401).
(c) Do a check of the aerodynamic smoothness again
(Ref 71-11-00/201).
S 425-011-P00
Complete the installation of the pressure relief door
(Ref 71-11-03/401).
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FAN COWL PANEL - MAINTENANCE PRACTICES (OPEN/CLOSE)
___________________________________________________
1.
2.
General
_______
A. There are two tasks in this procedure. The first task opens the fan cowl
panels. The second task closes the fan cowl panels. These two task are
used for the inboard and the outboard fan cowl panels.
B. The hold-open rods extend to hold the fan cowl panels in the open
position. The top end of each hold-open rod is attached to the fan cowl
panel. If you move the lock collar, it releases the lower end of a
hold-open rod from its stow point on the fan cowl panel. While you open
the fan cowl panels, the hold-open rods extend. You must fully extend
the hold-open rods to keep them in the locked position.
C. It is important to make sure that the two hold-open rods are locked open.
If you do not do this, a fan cowl panel can fall and cause injury to
persons.
TASK 71-11-04-012-016-P00
Open the Fan Cowl Panels
________________________
A. Access
(1) Location Zones
413
L Power
414
L Power
423
R Power
424
R Power
(2)
B.
Access Panels
413AL
Fan
414AR
Fan
423AL
Fan
424AR
Fan
Plant
Plant
Plant
Plant
Cowl
Cowl
Cowl
Cowl
Fan
Fan
Fan
Fan
Panel
Panel
Panel
Panel
Cowl
Cowl
Cowl
Cowl
Panel
Panel
Panel
Panel
(Left)
(Right)
(Left)
(Right)
Procedure (Fig. 201)
S 012-017-P00
WARNING:
_______
USE CAUTION WHEN YOU OPEN THE FAN COWL PANELS IN LARGE WINDS OR
IN GUSTS OF WIND. IF YOU DO NOT USE CAUTION, INJURY TO PERSONS
OR DAMAGE TO EQUIPMENT CAN OCCUR.
DO NOT HOLD THE FAN COWL PANELS OPEN WITH THE HOLD-OPEN RODS IF
THE WIND VELOCITY IS MORE THAN 60 KNOTS. THE HOLD-OPEN RODS
CAN HAVE A FAILURE IN LARGE WINDS WHICH CAN CAUSE INJURY TO
PERSONS OR DAMAGE TO EQUIPMENT.
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SEE
SEE
SEE
B
A
C
HOLD OPEN
ROD
BRACKET
HOLD OPEN
ROD
BRACKET
A
B
97737
Fan Cowl Panel Opening
Figure 201 (Sheet 1)
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LOCK COLLARS
BOTH SIDES OF
THE ENGINE
SEE
D
LOCK COLLARS
BOTH SIDES OF
THE ENGINE
SEE
D
BRACKET
BRACKET
LEFT SIDE OF ENGINE
C
E80475
Fan Cowl Panel Opening
Figure 201 (Sheet 2)
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PIN RETAINER
LOCK PIN HOLE
LOCK COLLAR
LOCK PIN
D
735104
Fan Cowl Panel Opening
Figure 201 (Sheet 3)
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(1)
(2)
(3)
Do the steps that follow to open the latches on the fan cowl panels:
(a) Open the forward latch.
1) Push the trigger to release the handle.
2) Pull the handle down to release the latch.
(b) Use the same steps to open the other latches from the front of
the fan cowl panel to the rear.
S 012-018-P00
Manually lift up and hold the weight of the fan cowl panel.
S 012-021-P00
Move the lower ends of each hold-open rod from the fan cowl panel to
the engine as follows.
(a) Turn the lock collars on the hold-open rod, in the direction
shown, to the unlocked position.
(b) Lift up on the unmarked (with no label) collar at the lower end
of the hold-open rod to release it from the bracket on the fan
cowl panel.
(c) Install the end of each hold-open rod into the applicable
bracket.
NOTE:
____
(d)
One bracket is on the inlet cowl.
is on a flange on the fan case.
A second bracket
Move the end of the other hold-open rod.
S 012-005-P00
WARNING:
_______
(4)
MAKE SURE THE HOLD-OPEN RODS ARE FULLY EXTENDED AND LOCKED WHEN
THE FAN COWL PANEL IS OPENED. THE HOLD-OPEN RODS ARE NOT
LOCKED WHEN YOU CAN SEE THE RED BAND WITH THE WORD "UNLOCKED"
ON THE SLEEVE. IF THE HOLD-OPEN ROD IS NOT CORRECTLY LOCKED,
INJURY TO PERSONS OR DAMAGE TO EQUIPMENT CAN OCCUR.
Open the fan cowl panel to fully extend the hold-open rods.
NOTE:
____
(a)
(b)
The right fan cowl panel weighs approximately 81 pounds.
left fan cowl panel weighs approximately 96 pounds.
The
Move the lock collar to the locked position.
Make sure you cannot see the red band and the word UNLOCKED on
the lock collar.
(5)
S 012-008-P00
Remove the lock pin from the pin retainer.
(6)
S 412-009-P00
Install the lock pin through the lock pin hole.
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3.
TASK 71-11-04-412-022-P00
Close the Fan Cowl Panel
________________________
A. References
(1) 71-11-05/501, Fan Cowl Panel
B. Access
(1) Location Zones
413
L Power Plant Fan
414
L Power Plant Fan
423
R Power Plant Fan
424
R Power Plant Fan
(2)
C.
Access Panels
413AL
Fan
414AR
Fan
423AL
Fan
424AR
Fan
Cowl
Cowl
Cowl
Cowl
Panel
Panel
Panel
Panel
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Latch
Cowl
Cowl
Cowl
Cowl
Panel
Panel
Panel
Panel
(Left)
(Right)
(Left)
(Right)
Procedure (Fig. 201)
S 412-011-P00
WARNING:
_______
HOLD THE FAN COWL PANELS OPEN WHEN YOU REMOVE THE HOLD-OPEN
RODS. THE RIGHT FAN COWL PANEL WEIGHS APPROXIMATELY 81 POUNDS.
THE LEFT COWL PANEL WEIGHS APPROXIMATELY 96 POUNDS. IF THE FAN
COWL PANEL FALLS, YOU CAN CAUSE INJURY TO PERSONS OR DAMAGE TO
EQUIPMENT.
WARNING:
_______
USE CAUTION WHEN YOU CLOSE THE FAN COWL PANELS IN LARGE WINDS
OR IN GUSTS OF WIND. IF YOU DO NOT USE CAUTION, INJURY TO
PERSONS OR DAMAGE TO EQUIPMENT CAN OCCUR.
DO NOT HOLD THE FAN COWL PANELS OPEN WITH THE HOLD-OPEN RODS IF
THE WIND VELOCITY IS MORE THAN 60 KNOTS. THE HOLD-OPEN RODS
CAN HAVE A FAILURE IN LARGE WINDS WHICH CAN CAUSE INJURY TO
PERSONS OR DAMAGE TO EQUIPMENT.
(1)
Hold the fan cowl panel open and do the steps that follow to close
the fan cowl panel:
(a) Remove the lock pin from the lock pin hole.
(b) Install the lock pin in the pin retainer.
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(c)
D.
Move the lower ends of each hold-open rod from the engine to
the fan cowl panel as follows.
1) Turn the lock collars on the hold-open rod (not in the
direction shown) to the unlocked position.
2) Lift up on the unmarked (with no label) collar at the lower
end of the hold-open rod to release it from the bracket on
the engine.
3) Install the end of each hold-open rod into the applicable
bracket on the fan cowel panel.
4) Move the end of the other hold-open rod to the fan cowl
panel.
(d) Lower the fan cowl panel.
Put the Airplane Back to Its Usual Condition.
(1)
S 412-012-P00
Close the fan cowl panels.
(2)
S 412-013-P00
Close the latches on the fan cowl panels.
(3)
S 822-014-P00
Adjust the latches (Ref 71-11-05).
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FAN COWL PANELS - REMOVAL/INSTALLATION
______________________________________
1.
2.
General
_______
A. This procedure has two tasks. The first task removes the fan cowl
panels. The second task installs the fan cowl panels.
B. The fan cowl panels are the cowl panels which are the most forward and
can open.
C. This procedure is used for the inboard and the outboard fan cowl panels.
TASK 71-11-04-024-018-P00
Remove the Fan Cowl Panel
_________________________
A. References
(1) 71-11-04/201, Fan Cowl Panels
B. Access
(1) Location Zones
413
L Power Plant Fan Cowl
414
L Power Plant Fan Cowl
423
R Power Plant Fan Cowl
424
R Power Plant Fan Cowl
(2)
C.
Access Panels
413AL
Fan
414AR
Fan
423AL
Fan
424AR
Fan
Cowl
Cowl
Cowl
Cowl
Panel
Panel
Panel
Panel
Panel
Panel
Panel
Panel
(Left)
(Right)
(Left)
(Right)
Prepare to Remove the Fan Cowl Panel
S 014-019-P00
WARNING:
_______
USE CAUTION WHEN YOU OPEN THE FAN COWL PANELS IN LARGE WINDS OR
IN GUSTS OF WIND. IF YOU DO NOT USE CAUTION, INJURY TO PERSONS
OR DAMAGE TO EQUIPMENT CAN OCCUR.
DO NOT HOLD THE FAN COWL PANELS OPEN WITH THE HOLD-OPEN RODS IF
THE WIND VELOCITY IS MORE THAN 60 KNOTS. THE HOLD-OPEN RODS
CAN HAVE A FAILURE IN LARGE WINDS WHICH CAN CAUSE INJURY TO
PERSONS OR DAMAGE TO EQUIPMENT.
(1)
Open the fan cowl panels (Ref 71-11-04).
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MAINTENANCE MANUAL
SEE
A
1. FAN COWL
PANEL
HINGE (3 LOCATIONS)
2. WASHER
3. NUT
4. BOLT
ROLL PIN
FWD
A
97740
Fan Cowl Panel Installation
Figure 401
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D.
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Remove the Fan Cowl Panel (Fig. 401)
S 014-003-P00
WARNING:
_______
(1)
Manually hold the fan cowl panel (1).
(2)
S 034-004-P00
Disengage the hold-open rods.
(3)
S 434-005-P00
Put the hold-open rods in the receivers on the fan cowl panel.
(4)
S 024-006-P00
Remove the bolt (4) from the hinges of the fan cowl panel.
(5)
S 024-007-P00
Move the hinges off the roll pin to remove the fan cowl panel (1).
(6)
3.
HOLD THE FAN COWL PANEL OPEN WHEN YOU REMOVE THE COWL. THE
RIGHT FAN COWL PANEL WEIGHS APPROXIMATELY 81 POUNDS. THE LEFT
FAN COWL PANEL WEIGHS APPROXIMATELY 96 POUNDS. IF THE FAN COWL
PANEL FALLS, INJURY TO PERSONS OR DAMAGE TO EQUIPMENT CAN
OCCUR.
S 554-008-P00
Put the fan cowl panel on a storage platform.
(a) Attach the fan cowl panel with two straps.
TASK 71-11-04-424-016-P00
Install the Fan Cowl Panel
__________________________
A. Consumable Materials
(1) D00014 Grease - MIL-G-21164 Molybdenum
disulphide
B. Parts
~¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼ ¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼ ¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼
¦
AMM
¦
¦
AIPC
¦
»¼¼¼¼¼ ¼¼¼¼¼¼¼¼¼«
»¼¼¼¼¼¼¼¼¼¼ ¼¼¼¼¼¼ ¼¼¼¼¼¼¼¼«
¦ FIG¦
ITEM ¦
NOMENCLATURE
¦ SUBJECT ¦ FIG ¦
ITEM ¦
»¼¼¼¼¼î¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼î¼¼¼¼¼¼¼¼«
¦ 401¦
1
¦ Cowl Assy - (LH Side)
¦ 71-11-04¦
05 ¦
14 ¦
¦
¦
¦ Cowl Assy - (RH Side)
¦
¦
¦
16 ¦
¦
¦
2
¦ Washer
¦
¦
¦
6 ¦
¦
¦
3
¦ Nut
¦
¦
¦
8 ¦
¦
¦
4
¦ Bolt
¦
¦
¦
4 ¦
²¼¼¼¼¼…¼¼¼¼¼¼¼¼¼…¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼…¼¼¼¼¼¼¼¼¼¼…¼¼¼¼¼¼…¼¼¼¼¼¼¼¼¹
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C.
D.
References
(1) 71-11-04/201, Fan Cowl Panels
(2) 71-11-05/501, Fan Cowl Panel Latch
Access
(1) Location Zones
413
L Power Plant Fan Cowl Panel
414
L Power Plant Fan Cowl Panel
423
R Power Plant Fan Cowl Panel
424
R Power Plant Fan Cowl Panel
(2)
E.
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Access Panels
413AL
Fan
414AR
Fan
423AL
Fan
424AR
Fan
Cowl
Cowl
Cowl
Cowl
Panel
Panel
Panel
Panel
(Left)
(Right)
(Left)
(Right)
Procedure (Fig. 401)
S 424-010-P00
WARNING:
_______
(1)
(2)
(3)
HOLD THE FAN COWL PANEL OPEN WHEN YOU REMOVE THE COWL. THE
RIGHT FAN COWL PANEL WEIGHS APPROXIMATELY 81 POUNDS. THE LEFT
FAN COWL PANEL WEIGHS APPROXIMATELY 96 POUNDS. IF THE FAN COWL
PANEL FALLS, INJURY TO PERSONS OR DAMAGE TO EQUIPMENT CAN
OCCUR.
Put the hinges of the fan cowl panel on the roll pins.
S 824-011-P00
Turn the fan cowl panel (1) to approximately 55 degrees of the open
position.
(a) Adjust the fan cowl panel (1) to align the holes.
S 644-012-P00
Apply a thin layer of grease to the shank of the bolt (4).
NOTE:
____
Do not apply grease to the threads of the bolt.
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S 424-013-P00
Install the bolt (4), washer (2), and nut (3) in the hinges
(3 locations).
Put the Airplane Back to Its Usual Condition
(4)
F.
(1)
S 414-014-P00
Close the fan cowl panels (Ref 71-11-04).
(2)
S 824-015-P00
Adjust the latches of the fan cowl panel (Ref 71-11-05).
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FAN COWL PANEL LATCH - REMOVAL/INSTALLATION
___________________________________________
1.
2.
General
_______
A. There are two tasks in this procedure. The first task is the removal of
latches on the fan cowl panel. The second task is the installation of
the latches on the fan cowl panel.
TASK 71-11-05-004-001-P00
Fan Cowl Panel Latch Removal (Fig. 401)
____________________________
A. References
(1) 71-11-04/201, Fan Cowl Panel
B. Access
(1) Location Zones
413
Fan Cowl Panel, Left Engine
423
Fan Cowl Panel, Right Engine
(2)
C.
3.
Access Panels
413AL
Fan Cowl Panel, Left Engine
423AL
Fan Cowl Panel, Right Engine
Procedure
(1)
S 014-002-P00
Open the left fan cowl panel (Ref 71-11-04/201).
(2)
S 034-003-P00
Remove the bolt from the latch.
(3)
S 024-004-P00
Remove the latch from the fan cowl panel.
TASK 71-11-05-404-005-P00
Install Fan Cowl Panel Latch (Fig. 401)
____________________________
A. Consumable Materials
(1) A00779 Sealant - BMS 5-26 Type II
B. References
(1) 71-11-04/201, Fan Cowl Panels
(2) 71-11-05/501, Fan Cowl Panel Latch
C. Access
(1) Location Zones
413
Fan Cowl Panel, Left Engine
423
Fan Cowl Panel, Right Engine
(2)
Access Panels
413AL
Fan Cowl Panel, Left Engine
423AL
Fan Cowl Panel, Right Engine
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MAINTENANCE MANUAL
SEE
A
WASHER
NUT
FAN COWL
PANEL
BOLT
FWD
LATCH
(3 LOCATIONS)
A
97733
Fan Cowl Panel Latch Installation
Figure 401
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Procedure
(1)
(2)
S 424-006-P00
Put the latch handle in its position smooth with the surface of the
fan cowl panel, and align the bolt hole.
(a) Install the bolt, the washers, and the nut to attach the latch
to the fan cowl panel.
S 224-007-P00
Make sure there is a maximum of 0.02 inch (0.508 mm) between the
bushing and the latch.
S 824-008-P00
CAUTION:
_______
MAKE SURE YOU ADJUST THE LATCHES CORRECTLY. THE ENGINE MOVES
WHEN IT OPERATES. HEAT ALSO CAUSES THE ENGINE TO BECOME
LARGER. IF YOU DO NOT ADJUST THE LATCHES, DAMAGE CAN OCCUR TO
THE ENGINE OR TO THE FAN COWL PANELS.
(3)
Adjust the latches for the fan cowl panels (Ref 71-11-05/501).
(4)
S 434-009-P00
Apply the sealant with a thickness of 0.06 inch (1.524 mm) to the
end of bolt and the nut.
(5)
S 414-010-P00
Close the left fan cowl panel (Ref 71-11-04/201).
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FAN COWL PANEL LATCH - ADJUSTMENT/TEST
______________________________________
1.
2.
General
_______
A. This procedure has a task to adjust the latches on the fan cowl panels.
It is necessary to adjust the latches to make sure the latches have the
correct tension on them. It is also necessary to adjust the latches to
make sure the aerodynamic smoothness is in the specified limits.
B. It is necessary to adjust the latches on the fan cowl panels when one of
these components is replaced: a thrust reverser, a fan cowl panel, or a
latch on the fan cowl panels.
C. It is necessary to install and adjust the thrust reversers before you
adjust the latches on the fan cowl panels. It is also necessary to
install the inlet cowl before you adjust the latches on the fan cowl
panels.
TASK 71-11-05-825-011-P00
Adjust the Fan Cowl Panel Latches
_________________________________
A. Equipment
(1) Hex Wrench - 4 millimeter or 5/32 inch
standard long series
(2) Scale - Push/pull, with a 0-60 pound range
B. Consumable Materials
(1) G02020 Clay - Modeling
(2) D00139 Lubricant - Silicone Spray, WD-40
(3) A00307 Primer - BAC 5710 Type 51
C. References
(1) 71-11-04/201, Fan Cowl Panels
(2) 78-31-00/201, Thrust Reverser System
D. Access
(1) Location Zones
413/414
Fan Cowl Panels, Left Engine
423/424
Fan Cowl Panels, Right Engine
(2)
Access Panels
413AL/414AR
423AL/424AR
Fan Cowl Panels, Left Engine
Fan Cowl Panels, Right Engine
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Procedure
(1)
S 215-002-P00
Make sure the thrust reversers are closed and latched
(Ref 78-31-00/201).
(2)
S 215-003-P00
Make sure the fan cowl panels are closed and latched
(Ref 71-11-04/201).
S 825-000-P00
CAUTION:
_______
(3)
(4)
MAKE SURE YOU CORRECTLY ADJUST THE LATCHES ON THE FAN
COWL PANELS. IF YOU OPERATE THE AIRPLANE WHEN THE LATCHES
ARE NOT ADJUSTED CORRECTLY, THE LATCHES CAN RELEASE. IF
THE LATCHES RELEASE, DAMAGE CAN OCCUR TO THE FAN COWL
PANELS, THE ENGINE, OR THE AIRPLANE.
Make sure the fan cowl panels and the latches are in the limits for
the aerodynamic smoothness (Fig. 501).
(a) Do a check of the clearance between the two fan cowl panels.
(b) Do a check of the clearance between the latches and the
adjacent fan cowl panel.
(c) Make sure the surfaces of the two fan cowl panels are smooth
(the step height).
S 225-005-P00
If the fan cowl panels are not in the limits for aerodynamic
smoothness, do these steps to adjust the latches (Fig. 502):
(a) Open the right fan cowl panel (Ref 71-11-04/201).
(b) Make sure the keeper eyebolt does not turn.
1) If the keeper eyebolt turns, replace the anti-rotation
stops and the keepers that have damage.
(c) Remove the shims (6 locations) from the right fan cowl panel:
1) Remove the shims on the aft side of the keepers
(3 locations).
2) Remove the shear pins to remove the shims at the forward
side of the keepers.
3) Install the shear pins with the nuts.
(d) Apply the modeling clay to the shim locations on the keepers.
(e) Apply the lubricant to the adjacent surface for the shims on
the left fan cowl panel.
(f) Close and latch the fan cowl panels (Ref 71-11-04/201).
(g) Do the steps that follow to adjust the clearance between the
fan cowl panels:
1) Push the latch trigger to open the latch handles to
approximately 15 degrees.
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SKIN CLEARANCE
(COWL)
SEE A
1
SKIN CLEARANCE
(LATCHES)
2
FWD
A
AERODYNAMIC
SMOOTHNESS
3
1
0.03-0.15 INCH FROM THE
COWL TO THE OTHER COWL
2
0.15-0.27 INCH FROM THE
LATCH EDGE TO THE COWL
3
|0.03 INCH IN THE AREA
3.00 INCHES FROM THE SHEAR PINS.
|0.06 INCH WHEN THERE IS MORE
THAN 3.00 INCHES FROM THE
SHEAR PINS.
127739
Fan Cowl Panel Clearance and Aerodynamic-Smoothness
Figure 501
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SEE
SEE
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A
BOLT
(4 LOCATIONS)
B
BOLT
WASHER
SHEAR PIN
NUT
(4 LOCATIONS)
SHEAR PIN
NUT
KEEPER
KEEPER
SHIM
KEEPER
BOLT
WASHER
NUT
(4 LOCATIONS)
SHEAR PIN
NUT
SHIM
SHIM
SHIM
SHIM
NUT
NUT
(4 LOCATIONS)
WASHER
(4 LOCATIONS)
SEE D
FAN COWL PANEL - KEEPER SIDE
ON FAN COWL PANELS WITH SB 71-20
A
BOLT
WASHER
SHEAR PIN
NUT
(4 LOCATIONS)
SHEAR PIN
NUT
KEEPER
SHIM
KEEPER
BOLT
(4 LOCATIONS)
KEEPER
BOLT
WASHER
NUT
(4 LOCATIONS)
SHEAR PIN
NUT
SHIM
SHIM
SHIM
SHIM
FWD
NUT
NUT
(4 LOCATIONS)
WASHER
(4 LOCATIONS)
SEE C
FAN COWL PANEL - KEEPER SIDE
ON FAN COWL PANELS WITHOUT SB 71-20
1
IF THE TANG IS GONE IT IS NECESSARY TO REPLACE THE KEEPER
A
97760
Fan Cowl Panel Latch Adjustment
Figure 502 (Sheet 1)
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LATCH
(3 LOCATIONS)
FWD
SHEAR PIN SEAT
(3 LOCATIONS)
FAN COWL PANEL - LATCH SIDE
B
LATCH HOOK
TANG 1
HEX WRENCH
KEEPER ADJUSTMENT ON FAN
COWL PANELS WITHOUT SB 71-20
LATCH HOOK
C
KEEPER ANTI-ROTATION STOP
HEX WRENCH
KEEPER ADJUSTMENT ON FAN
COWL PANELS WITH SB 71-20
D
276902
Fan Cowl Panel Latch Adjustment
Figure 502 (Sheet 2)
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2)
Turn the adjustment star with the hex wrench until the
clearance between the cowls is in the specified limits.
NOTE:
____
(h)
(i)
(j)
(k)
(l)
(m)
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The direction to turn the adjustment star is
shown on the keeper. Increase the load to decrease
the clearance between the cowls.
Open the right fan cowl panel (Ref 71-11-04/201).
Measure the thickness of the modeling clay at each of the shim
locations.
Remove the laminations from the shims (or install new shims)
until the shims are the same thickness as the modeling clay at
each shim location.
Remove the modeling clay from the shim locations.
Apply the primer to each of the shims.
Do these steps to install the shims:
1) Remove the three shear pins from the keepers.
2) Install the shims, the shear pins, and the nuts at the
forward side of the keepers.
3) Install the shims at the three locations on the aft side of
the keepers.
S 725-006-P00
CAUTION:
_______
(5)
DO NOT APPLY MORE THAN A 55 POUND FORCE TO THE LATCH HANDLES.
IF YOU APPLY A LARGE FORCE, YOU CAN CAUSE DAMAGE TO THE LATCH.
Use the scale on each latch handle to do a check of the force
necessary to close the latch.
(a) If the force necessary to close the latch is not 45-55 pounds,
do these steps to adjust the latch:
1) Push the latch trigger to open the latch handles to
approximately 15 degrees.
2) Turn the adjustment star with the hex wrench to increase or
decrease the force necessary to close the latches.
NOTE:
____
(6)
(7)
The direction to turn the adjustment star is
shown on the keeper.
S 415-007-P00
Close the fan cowl panels (Ref 71-11-04/201).
S 215-008-P00
Make sure the latches are smooth with the external surface of the
fan cowl panel.
(a) If the latch handles are not smooth with the fan cowl panels,
do these steps:
1) Open the right fan cowl panel (Ref 71-11-04/201).
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2)
3)
4)
5)
6)
(8)
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Loosen the bolts that attach the keeper to the right fan
cowl panel.
Move the keeper up or down to make the two fan cowl panels
smooth.
Tighten the bolts that attach the keeper to the right fan
cowl panel.
Close the fan cowl panels (Ref 71-11-04/201).
Make sure the latch handles are smooth with the fan cowl
panel.
S 725-009-P00
Do a check of the force necessary to close the latches again.
(a) Make sure the force to close the latches is 45-55 pounds.
(b) If it is necessary, adjust the latch tension again.
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CORE COWL PANELS (OPEN/CLOSE) - MAINTENANCE PRACTICES
_____________________________________________________
1.
2.
General
_______
A. There are two task in this procedure. The first task opens the core cowl
panels. The second task closes the core cowl panels. These two tasks
are for the inboard and the outboard core cowl panels.
B. The hold-open rods extend to hold the core cowl panels in the open
position. The top end of each hold-open rod is attached to the core cowl
panel. If you move the lock collar, it releases the lower end of a
hold-open rod from its stow point on the core cowl panel. While the core
cowl panels are opened, the hold-open rods extend. You must fully extend
the hold-open rod before you install the bottom end into the receiver
bracket on the engine flange. When the hold-open rod is fully extended
it will stay locked in its position.
C. It is important to make sure that the hold-open rod is locked open. If
you do not do this, a core cowl panel can fall and cause injury to
persons.
TASK 71-11-06-002-017-P00
Open the Core Cowl Panels
_________________________
A. References
(1) AMM 78-31-00/201, Thrust
B. Access
(1) Location Zones
415
L Power Plant
416
L Power Plant
417
L Power Plant
418
L Power Plant
425
R Power Plant
426
R Power Plant
427
R Power Plant
428
R Power Plant
(2)
Reverser System
Fan Reverser
Fan Reverser
Core Cowl
Core Cowl
Fan Reverser
Fan Reverser
Core Cowl
Core Cowl
Access Panels
415AL
Fan Reverser (Left)
416AR
Fan Reverser (Right)
417AL
Core Cowl (Left)
418AR
Core Cowl (Right)
425AL
Fan Reverser (Left)
426AR
Fan Reverser (Right)
427AL
Core Cowl (Left)
428AR
Core Cowl (Right)
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MAINTENANCE MANUAL
SEE
A
SEE B
HOLD OPEN ROD
BRACKET
ENGINE FLANGE
FWD
A
97748
Core Cowl Panel Opening
Figure 201 (Sheet 1)
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LOCK COLLAR
COLLAR TYPE LOCK
WITHOUT SAFETY PIN
B
LOCK COLLAR
PIN RETAINER
LOCK PIN
LOCK PIN HOLE
COLLAR TYPE LOCK
WITH SAFETY PIN
B
LOCK RELEASE
LEVER
LEVER TYPE LOCK
B
230802
Core Cowl Panel Opening
Figure 201 (Sheet 2)
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C.
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Prepare to Open the Core Cowl Panels
S 042-002-P00
WARNING:
_______
DO THE THRUST REVERSER DEACTIVATION PROCEDURE TO PREVENT THE
OPERATION OF THE THRUST REVERSER. THE ACCIDENTAL OPERATION OF
THE THRUST REVERSER CAN CAUSE INJURY TO PERSONS OR DAMAGE TO
EQUIPMENT.
(1)
D.
Do this procedure: Thrust Reverser Deactivation for Ground
Maintenance (AMM 78-31-00/201).
Open the Core Cowl Panels (Fig. 201)
S 012-021-P00
WARNING:
_______
USE CAUTION WHEN YOU OPEN THE CORE COWL PANELS IN LARGE WINDS
OR IN GUSTS OF WIND. IF YOU DO NOT USE CAUTION, INJURY TO
PERSONS OR DAMAGE TO EQUIPMENT CAN OCCUR.
WARNING:
_______
DO NOT HOLD THE CORE COWL PANELS OPEN WITH THE HOLD-OPEN RODS
IF THE WIND VELOCITY IS MORE THAN 60 KNOTS. THE HOLD-OPEN RODS
CAN HAVE A FAILURE IN LARGE WINDS WHICH CAN CAUSE INJURY TO
PERSONS OR DAMAGE TO EQUIPMENT.
(1)
(2)
Do the steps that follow to open the latches on the core cowl
panels:
(a) Open the forward latch.
1) Push the trigger to release the handle.
2) Pull the handle down to release the latch.
(b) Use the same steps to open the other latches from the front of
the core cowl panel to the rear.
S 012-005-P00
Extend the hold-open rods with the collar type locks as follows:
(a) Turn and move the lock collar to the bottom end of the
hold-open rod.
(b) Remove the bottom end of the hold-open rod from the stow point.
(c) Open the core cowl panel.
WARNING:
_______
(d)
(e)
MAKE SURE THE HOLD-OPEN RODS ARE FULLY EXTENDED AND LOCKED
WHEN THE FAN COWL PANEL IS OPENED. THE HOLD-OPEN RODS ARE
NOT LOCKED WHEN YOU CAN SEE THE RED BAND WITH THE WORD
"UNLOCKED" ON THE SLEEVE. IF THE HOLD-OPEN ROD IS NOT
CORRECTLY LOCKED, INJURY TO PERSONS OR DAMAGE TO EQUIPMENT
CAN OCCUR.
Fully extend the hold-open rod to the locked position.
1) Make sure you cannot see the red band.
For the hold-open rods with safety lock pins, do the steps that
follow:
1) Remove the safety lock pin from the pin retainer.
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2)
(3)
(d)
(e)
3.
Install the safety lock pin in the lock pin hole.
S 012-006-P00
Extend the hold-open rods with the lever type locks with the steps
that follow:
(a) Push the lock release lever.
(b) Remove the bottom end of the hold-open rod from the stow point.
(c) Open the core cowl panel.
WARNING:
_______
(4)
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MAKE SURE THE HOLD-OPEN RODS ARE FULLY EXTENDED AND LOCKED
WHEN THE FAN COWL PANEL IS OPENED. THE HOLD-OPEN RODS ARE
NOT LOCKED WHEN YOU CAN SEE THE RED BAND WITH THE WORD
"UNLOCKED" ON THE SLEEVE. IF THE HOLD-OPEN ROD IS NOT
CORRECTLY LOCKED, INJURY TO PERSONS OR DAMAGE TO EQUIPMENT
CAN OCCUR.
Fully extend the hold-open rod to the locked position.
Release the lock release lever.
1) Make sure you cannot see the red band.
S 412-007-P00
Engage the hold-open rod with the bracket on the engine.
TASK 71-11-06-402-016-P00
Close the Core Cowl Panels
__________________________
A. References
(1) AMM 71-11-07/501, Core Cowl Panel Latches
(2) AMM 78-31-00/201, Thrust Reverser System
B. Access
(1) Location Zones
415
L Power Plant Fan Reverser
416
L Power Plant Fan Reverser
417
L Power Plant Core Cowl
418
L Power Plant Core Cowl
425
R Power Plant Fan Reverser
426
R Power Plant Fan Reverser
427
R Power Plant Core Cowl
428
R Power Plant Core Cowl
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(2)
C.
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Access Panels
415AL
Fan Reverser (Left)
416AR
Fan Reverser (Right)
417AL
Core Cowl (Left)
418AR
Core Cowl (Right)
425AL
Fan Reverser (Left)
426AR
Fan Reverser (Right)
427AL
Core Cowl (Left)
428AR
Core Cowl (Right)
Procedure (Fig. 201)
S 412-019-P00
WARNING:
_______
USE CAUTION WHEN YOU CLOSE THE CORE COWL PANELS IN LARGE WINDS
OR GUSTS OF WIND. IF YOU DO NOT USE CAUTION, AN INJURY TO
PERSONS OR DAMAGE TO EQUIPMENT CAN OCCUR.
WARNING:
_______
DO NOT HOLD THE CORE COWL PANELS OPEN WITH THE HOLD-OPEN RODS
IF THE WIND VELOCITY IS MORE THAN 60 KNOTS. THE HOLD-OPEN ROD
CAN HAVE A FAILURE IN LARGE WINDS WHICH CAN CAUSE AN INJURY TO
PERSONS OR DAMAGE TO EQUIPMENT.
(1)
Retract and put back the hold-open rods with the collar type locks
with the steps that follow:
WARNING:
_______
(a)
(b)
(c)
(d)
(e)
(f)
(g)
(2)
HOLD THE CORE COWL PANEL OPEN WHEN YOU REMOVE THE
HOLD-OPEN ROD FROM THE ENGINE. THE CORE COWL PANELS WEIGH
76 POUNDS EACH. IF THE CORE COWL PANEL FALLS, AN INJURY
TO PERSONS CAN OCCUR.
Manually hold the core cowl panel open.
For the hold-open rods with the safety lock pin, do the steps
that follow:
1) Remove the safety lock pin from the lock pin hole.
2) Install the safety lock pin in the pin retainer.
Turn and move the lock collar to the top end of the hold-open
rod.
Pull the hold-open rod from the bracket on the engine flange.
Retract the hold-open rod.
Lower the core cowl panel.
Install the hold-open rod in the receiver on the core cowl
panel.
S 412-011-P00
Retract and put back the hold-open rods with the lever type locks
with the steps that follow:
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WARNING:
_______
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HOLD THE CORE COWL PANEL OPEN WHEN YOU REMOVE THE
HOLD-OPEN ROD FROM THE ENGINE. THE CORE COWL PANELS WEIGH
76 POUNDS EACH. IF THE CORE COWL PANEL FALLS, AN INJURY
TO PERSONS CAN OCCUR.
(a)
(b)
(c)
(d)
(e)
(f)
D.
Manually hold the core cowl panel open.
Push the lock release lever.
Pull the hold-open rod from the bracket on the engine flange.
Retract the hold-open rod.
Lower the core cowl panel.
Install the hold-open rod in the receiver on the core cowl
panel.
Put the Airplane Back to Its Usual Condition.
(1)
S 412-012-P00
Close the core cowl panels.
(2)
S 412-013-P00
Close the latches on the core cowl panels.
(3)
S 822-014-P00
Adjust the latches if they are not smooth with the core cowl panel
(AMM 71-11-07/501).
(4)
S 442-015-P00
Do the activation procedure for the thrust reversers
(AMM 78-31-00/201).
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CORE COWL PANELS - REMOVAL/INSTALLATION
_______________________________________
1.
2.
General
_______
A. This procedure has two tasks. The first task removes the core cowl
panel. The second task installs the core cowl panel. These two tasks
are for the inboard and the outboard core cowl panels.
B. The core cowl panel is the cowl panel which is the most aft that you can
open.
C. There are two procedures to remove and install the core cowl panels. One
procedure uses a lift sling and boom hoist. The second procedure does
not use special equipment.
TASK 71-11-06-004-037-P00
Remove the Core Cowl Panel
__________________________
A. Equipment
(1) Sling - Core Cowl - A71016
(2) Boom Hoist - General (8' Lift, 400 lb cap.) - A20001-79
(3) Ladder - Two necessary for removal procedure without special
equipment
B. References
(1) AMM 71-11-04/201, Fan Cowl Panels
(2) AMM 71-11-06/201, Core Cowl Panels
(3) AMM 78-31-00/201, Thrust Reverser System
C. Access
(1) Location Zones
410
Left Engine Nacelle
420
Right Engine Nacelle
(2)
D.
Access Panels
415AL/416AR
417AL/418AR
425AL/426AR
427AL/428AR
Thrust Reverser,
Core Cowl Panel,
Thrust Reverser,
Core Cowl Panel,
Left Engine
Left Engine
Right Engine
Right Engine
Prepare to Remove the Core Cowl Panel
(1)
S 014-002-P00
Open the fan cowl panels (AMM 71-11-04/201).
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S 044-035-P00
WARNING:
_______
DO THE THRUST REVERSER DEACTIVATION PROCEDURE TO PREVENT THE
OPERATION OF THE THRUST REVERSER. THE ACCIDENTAL OPERATION OF
THE THRUST REVERSER CAN CAUSE INJURIES TO PERSONS OR DAMAGE TO
EQUIPMENT.
(2)
E.
Do this procedure: Thrust Reverser Deactivation for Ground
Maintenance (AMM 78-31-00/201).
Remove the Core Cowl Panels with the Lift Sling (Fig. 401)
S 494-066-P00
WARNING:
_______
USE CAUTION WHEN YOU OPEN THE CORE COWL PANELS IN LARGE WINDS
OR IN GUSTS OF WIND. IF YOU DO NOT USE CAUTION, INJURY TO
PERSONS OR DAMAGE TO EQUIPMENT CAN OCCUR.
WARNING:
_______
DO NOT HOLD THE CORE COWL PANELS OPEN WITH THE HOLD-OPEN RODS
IF THE WIND VELOCITY IS MORE THAN 60 KNOTS. THE HOLD-OPEN RODS
CAN HAVE A FAILURE IN LARGE WINDS WHICH CAN CAUSE INJURY TO
PERSONS OR DAMAGE TO EQUIPMENT.
(1)
Attach the arm assembly to the boom hoist.
(2)
S 494-005-P00
Remove the screws (1, 2) from the core cowl panel.
(3)
S 494-006-P00
Remove the bolts from the storage holes on the lift pads.
(4)
S 494-007-P00
Move the lift sling in position adjacent to the core cowl panel.
(5)
S 494-008-P00
Install the forward and aft lift pads in the nutplates of the core
cowl panel with the bolts included with the lift sling.
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ARM
LIFT SLING
BOOM HOIST
1
IPC NOMENCLATURE: COWL ASSY - (LH SIDE), OR
COWL ASSY - (RH SIDE), AS APPLICABLE
97750
Lift Sling Installation
Figure 401 (Sheet 1)
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SEE
A
SEE
B
BOOM HOIST
CORE COWL
PANEL
1
BOLT STORAGE
HOLE (2 LOCATIONS)
BOLT
(2 LOCATIONS)
LIFT PAD
BOLT
(2 LOCATIONS)
LIFT PAD
1. SCREW
(2 LOCATIONS)
BOLT
STORAGE
HOLES
2. SCREW
(2 LOCATIONS)
NUT PLATE
(2 LOCATIONS)
NUT PLATE
(2 LOCATIONS)
A
B
117816
Lift Sling Installation
Figure 401 (Sheet 2)
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MAINTENANCE MANUAL
SEE
A
1. WASHER
(3 LOCATIONS)
4. CORE COWL
PANEL
2. NUT
(3 LOCATIONS)
CORE COWL
PANEL HINGE
3. BOLT
(3 LOCATIONS)
A
97756
Core Cowl Panel Installation
Figure 402
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WARNING:
_______
(a)
(6)
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MAKE SURE THE BOLTS THAT ATTACH THE LIFT SLING TO THE CORE
COWL PANEL ARE TIGHT. THE CORE COWL PANELS WEIGH 76
POUNDS EACH. IF THE CORE COWL PANEL FALLS, AN INJURY TO
PERSONS OR DAMAGE TO EQUIPMENT CAN OCCUR.
Make sure the bolts are tightened in the fittings on the core
cowl panel.
S 014-009-P00
Open the core cowl panel (AMM 71-11-06/201).
S 014-010-P00
WARNING:
_______
OBEY THE INSTRUCTIONS IN AMM 78-31-00/201 WHEN YOU OPEN THE
THRUST REVERSERS. IF YOU DO NOT OBEY THE INSTRUCTIONS,
INJURIES TO PERSONS OR DAMAGE TO EQUIPMENT CAN OCCUR.
(7)
Open the thrust reversers (AMM 78-31-00/201).
(8)
S 494-011-P00
Attach the lift sling to the arm assembly on the boom hoist.
(9)
S 494-012-P00
Hold the weight of the core cowl panel on the boom hoist.
S 024-013-P00
(10) Disconnect and stow the hold-open rod.
S 024-014-P00
(11) Remove the bolts (3) from the hinges of the core cowl panel
(Fig. 402).
S 024-015-P00
(12) Remove the core cowl panel (4).
S 024-016-P00
(13) Move the core cowl panel away from the engine.
S 024-017-P00
(14) Lower the core cowl panel (4) to the storage rack.
S 094-018-P00
(15) If you do not install the same core cowl panel, do the steps that
follow (Fig. 401).
(a) Remove the lift sling.
(b) Install the screws (1, 2) into the core cowl panel.
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F.
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Remove the Core Cowl Panel without the Lift Sling
S 014-067-P00
WARNING:
_______
USE CAUTION WHEN YOU OPEN THE CORE COWL PANELS IN LARGE WINDS
OR IN GUSTS OF WIND. IF YOU DO NOT USE CAUTION, INJURY TO
PERSONS OR DAMAGE TO EQUIPMENT CAN OCCUR.
WARNING:
_______
DO NOT HOLD THE CORE COWL PANELS OPEN WITH THE HOLD-OPEN RODS
IF THE WIND VELOCITY IS MORE THAN 60 KNOTS. THE HOLD-OPEN RODS
CAN HAVE A FAILURE IN LARGE WINDS WHICH CAN CAUSE INJURY TO
PERSONS OR DAMAGE TO EQUIPMENT.
(1)
Open the core cowl panels (AMM 71-11-06/201).
(2)
S 944-042-P00
Put two ladders in a position so you have access to the top of the
forward and rear supports of the core cowl panel.
(3)
S 034-049-P00
While you manually hold the bottom of the core cowl panel in the
open position, disconnect and stow the hold-open rod.
S 024-051-P00
WARNING:
_______
MAKE SURE YOU HOLD THE CORE COWL PANEL TIGHTLY WHEN YOU REMOVE
THE SAFETY PINS. THE CORE COWL PANEL WEIGHS 76 POUNDS. IF THE
CORE COWL PANELS FALLS, INJURY TO PERSONS OR DAMAGE TO
EQUIPMENT CAN OCCUR.
WARNING:
_______
BE CAREFUL WHEN YOU MOVE THE CORE COWL PANEL DOWN THE LADDERS.
IF YOU ARE NOT CAREFUL, YOU CAN FALL OFF THE LADDER AND CAUSE
INJURY TO PERSONS OR DAMAGE TO EQUIPMENT.
(4)
While you tightly hold the core cowl panel on the top and bottom,
remove the bolts (3), washers (1) and nuts (2) which attach the core
cowl panel.
(a) Remove the bolt (3) from the center hinge first, then remove
the bolts (3) from the forward and rear hinges.
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(b)
3.
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Put the core cowl panel on a storage rack.
TASK 71-11-06-404-036-P00
Install the Core Cowl Panel
___________________________
A. Equipment
(1) Sling - Core Cowl - A71016
(2) Boom Hoist - General (8' Lift, 400 lb cap.) - A20001-79
(3) Ladders - Two necessary for installation procedure without special
equipment
B. Consumable Materials
(1) D00014 Grease - MIL-G-21164 Molybdenum disulphide
C. Parts
~¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼ ¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼ ¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼
¦
AMM
¦
¦
AIPC
¦
»¼¼¼¼¼ ¼¼¼¼¼¼¼¼¼«
»¼¼¼¼¼¼¼¼¼¼ ¼¼¼¼¼¼ ¼¼¼¼¼¼¼¼«
¦ FIG ¦ ITEM
¦
NOMENCLATURE
¦ SUBJECT ¦ FIG ¦ ITEM ¦
»¼¼¼¼¼î¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼î¼¼¼¼¼¼¼¼«
¦ 401 ¦
1
¦ Screw
¦ 71-11-06 ¦ 05 ¦
40
¦
¦
¦
2
¦ Screw
¦
¦
¦
40
¦
¦ 402 ¦
1
¦ Washer
¦
¦
¦
4
¦
¦
¦
2
¦ Nut
¦
¦
¦
6
¦
¦
¦
3
¦ Bolt
¦
¦
¦
2
¦
¦
¦
4
¦ Cowl Assy - (LH)
¦
¦
¦
15
¦
¦
¦
4
¦ Cowl Assy - (RH)
¦
¦
¦
17
¦
²¼¼¼¼¼…¼¼¼¼¼¼¼¼¼…¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼…¼¼¼¼¼¼¼¼¼¼…¼¼¼¼¼¼…¼¼¼¼¼¼¼¼¹
D.
E.
References
(1) AMM 71-11-04/201, Fan Cowl Panels
(2) AMM 71-11-06/201, Core Cowl Panels
(3) AMM 71-11-07/501, Core Cowl Panel Latch
(4) AMM 78-31-00/201, Thrust Reverser System
Access
(1) Location Zones
410
Left Engine Nacelle
420
Right Engine Nacelle
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(2)
F.
Access Panels
415AL/416AR
417AL/418AR
425AL/426AR
427AL/428AR
Thrust Reverser,
Core Cowl Panel,
Thrust Reverser,
Core Cowl Panel,
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Left Engine
Left Engine
Right Engine
Right Engine
Install the Core Cowl Panel with the Lift Sling (Fig. 401)
S 494-039-P00
WARNING:
_______
USE CAUTION WHEN YOU CLOSE THE CORE COWL PANELS IN LARGE WINDS
OR GUSTS OF WIND. IF YOU DO NOT USE CAUTION, AN INJURY TO
PERSONS OR DAMAGE TO EQUIPMENT CAN OCCUR.
WARNING:
_______
DO NOT HOLD THE CORE COWL PANELS OPEN WITH THE HOLD-OPEN RODS
IF THE WIND VELOCITY IS MORE THAN 60 KNOTS. THE HOLD-OPEN ROD
CAN HAVE A FAILURE IN LARGE WINDS WHICH CAN CAUSE AN INJURY TO
PERSONS OR DAMAGE TO EQUIPMENT.
(1)
If the lift sling is not installed, do the steps that follow
(Fig. 401):
(a) Remove the screws (1, 2) from the core cowl panel.
(b) Move the lift sling in position adjacent to the core cowl
panel.
(c) Install the forward and the aft lift pads on the core cowl
panel with the bolts included with the sling.
WARNING:
_______
(d)
(2)
MAKE SURE
PANEL ARE
EACH. IF
OR DAMAGE
THE BOLTS THAT ATTACH THE SLING TO THE CORE COWL
TIGHT. THE CORE COWL PANELS WEIGH 76 POUNDS
THE CORE COWL PANEL FALLS, AN INJURY TO PERSONS
TO EQUIPMENT CAN OCCUR.
Make sure the bolts are tightened in the fittings on the core
cowl panel.
S 424-021-P00
Lift the core cowl panel (4) to align the hinges with the fittings
on the strut.
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(3)
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S 644-022-P00
Apply a thin layer of grease to the shank of the bolt (3).
NOTE:
____
Do not apply grease to the threads of the bolts.
(4)
S 424-023-P00
Install the bolts (3), washers (1), and nuts (2) in the hinges.
(5)
S 424-024-P00
Engage the hold-open rod (AMM 71-11-06/401).
(6)
S 094-025-P00
Disconnect the lift sling from the boom hoist.
(7)
S 094-026-P00
Move the boom hoist away from the engine.
S 414-027-P00
WARNING:
_______
OBEY THE INSTRUCTIONS IN AMM 78-31-00/201 WHEN YOU CLOSE THE
THRUST REVERSERS. IF YOU DO NOT OBEY THE INSTRUCTIONS,
INJURIES TO PERSONS OR DAMAGE TO EQUIPMENT CAN OCCUR.
(8)
Close the thrust reversers (AMM 78-31-00/201).
(9)
S 414-028-P00
Close the core cowl panels (AMM 71-11-06/201).
S 414-029-P00
(10) Close the fan cowl panels (AMM 71-11-04/201).
S 444-030-P00
(11) Do the activation procedure for the thrust reversers
(AMM 78-31-00/201).
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S 094-031-P00
(12) Remove the bolts from the lift pads.
S 494-032-P00
(13) Install the bolts in the storage holes on the lift pads.
S 434-033-P00
(14) Install the screws (1, 2) in the core cowl panel.
G.
S 824-034-P00
(15) Adjust the latches for the core cowl panel (AMM 71-11-07/501).
Install the Core Cowl Panel without the Lift Sling
S 644-068-P00
WARNING:
_______
USE CAUTION WHEN YOU CLOSE THE CORE COWL PANELS IN LARGE WINDS
OR GUSTS OF WIND. IF YOU DO NOT USE CAUTION, AN INJURY TO
PERSONS OR DAMAGE TO EQUIPMENT CAN OCCUR.
WARNING:
_______
DO NOT HOLD THE CORE COWL PANELS OPEN WITH THE HOLD-OPEN RODS
IF THE WIND VELOCITY IS MORE THAN 60 KNOTS. THE HOLD-OPEN ROD
CAN HAVE A FAILURE IN LARGE WINDS WHICH CAN CAUSE AN INJURY TO
PERSONS OR DAMAGE TO EQUIPMENT.
(1)
Apply a thin layer of grease to the shank of the bolts (3).
NOTE:
____
Do not apply grease to the threads of the bolts.
S 424-061-P00
WARNING:
_______
(2)
BE CAREFUL WHEN YOU LIFT THE CORE COWL PANEL. THE CORE COWL
PANEL WEIGHS 76 POUNDS. IF YOU ARE NOT CAREFUL, YOU CAN FALL
AND CAUSE INJURY TO PERSONS OR DAMAGE TO EQUIPMENT.
While you tightly hold the core cowl panel, move the core cowl panel
up the ladders and hold in the open position.
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(3)
(4)
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S 434-055-P00
Install the bolts (3), washers (1) and nuts (2) in the forward and
rear hinges first, then install the bolt (3), washer (1) and nut (2)
in the center hinge.
(a) Tighten the bolts (3).
S 434-054-P00
Connect the hold-open rod to the engine.
S 414-062-P00
WARNING:
_______
OBEY THE INSTRUCTIONS IN AMM 78-31-00/201 WHEN YOU CLOSE THE
THRUST REVERSERS. IF YOU DO NOT OBEY THE INSTRUCTIONS,
INJURIES TO PERSONS OR DAMAGE TO EQUIPMENT CAN OCCUR.
(5)
Close the thrust reversers (AMM 78-31-00/201).
(6)
S 414-063-P00
Close the core cowl panels (AMM 71-11-06/201).
(7)
S 414-064-P00
Close the fan cowl panels (AMM 71-11-04/201).
(8)
(9)
S 444-065-P00
Do the activation procedure for the thrust reversers
(AMM 78-31-00/201).
S 824-060-P00
Adjust the latches for the core cowl panels (AMM 71-11-07/501).
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CORE COWL PANEL LATCH - REMOVAL/INSTALLATION
____________________________________________
1.
2.
General
_______
A. There are two tasks in this procedure. The first task is the removal of
the latches on the core cowl panel. The second task is the installation
of the latches on the core cowl panel.
TASK 71-11-07-004-001-P00
Core Cowl Panel Latch Removal (Fig. 401)
_____________________________
A. References
(1) 71-11-06/201, Core Cowl Panels
(2) 78-31-00/201, Thrust Reverser System
B. Access
(1) Location Zones
410
Left Engine Nacelle
420
Right Engine Nacelle
(2)
C.
Access Panels
415AL/416AR
417AL/418AR
425AL/426AR
427AL/428AR
Thrust Reverser,
Core Cowl Panel,
Thrust Reverser,
Core Cowl Panel,
Left Engine
Left Engine
Right Engine
Right Engine
Procedure
S 044-002-P00
WARNING:
_______
(1)
3.
DO THE THRUST REVERSER DEACTIVATION PROCEDURE TO PREVENT THE
OPERATION OF THE THRUST REVERSER. THE ACCIDENTAL OPERATION OF
THE THRUST REVERSER CAN CAUSE INJURIES TO PERSONS OR DAMAGE TO
EQUIPMENT.
Do this procedure: Thrust Reverser Deactivation for Ground
Maintenance (Ref 78-31-00/201).
(2)
S 014-003-P00
Open the left core cowl panel (Ref 71-11-06/201).
(3)
S 034-004-P00
Remove the bolt that attaches the latch to the core cowl panel.
(4)
S 024-005-P00
Remove the latch from the core cowl panel.
TASK 71-11-07-404-006-P00
Core Cowl Panel Latch Installation (Fig. 401)
__________________________________
A. Consumable Materials
(1) A00160 Sealant - BMS 5-63
B. References
(1) 71-11-06/201, Core Cowl Panels
(2) 78-31-00/201, Thrust Reverser System
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SEE A
WASHER (2 LOCATIONS)
NUT
BOLT
CORE COWL PANEL LATCH
(3 LOCATIONS)
A
97765
Core Cowl Panel Latch Installation
Figure 401
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C.
(3) 71-11-07/501, Core Cowl Panel Latch
Access
(1) Location Zones
410
Left Engine Nacelle
420
Right Engine Nacelle
(2)
D.
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Access Panels
415AL/416AR
417AL/418AR
425AL/426AR
427AL/428AR
Thrust Reverser,
Core Cowl Panel,
Thrust Reverser,
Core Cowl Panel,
Left Engine
Left Engine
Right Engine
Right Engine
Procedure
(1)
S 424-007-P00
Put the latch handle in its position smooth with the surface of the
core cowl panel, and align the bolt hole.
(a) Install the bolt, the washers, and the nut to attach the latch
to the core cowl panel.
S 824-008-P00
CAUTION:
_______
MAKE SURE YOU ADJUST THE LATCHES CORRECTLY. THE ENGINE MOVES
WHEN IT OPERATES. HEAT ALSO CAUSES THE ENGINE TO BECOME
LARGER. IF YOU DO NOT ADJUST THE LATCHES, DAMAGE CAN OCCUR TO
THE ENGINE OR THE CORE COWL PANELS.
(2)
Adjust the latches on the core cowl panels (Ref 71-11-07/501).
(3)
S 434-009-P00
Apply the sealant with a thickness of 0.06 inch (1.524 mm) to the
end of the bolt and the nut.
(4)
S 414-010-P00
Close the core cowl panels (Ref 71-11-06/201).
(5)
S 444-011-P00
Do the thrust reverser activation procedure (Ref 78-31-00/201).
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CORE COWL PANEL LATCH - ADJUSTMENT/TEST
_______________________________________
1.
2.
General
_______
A. This procedure has a task to adjust the latches on the core cowl panels.
It is necessary to adjust the latches to make sure the latches have the
correct tension on them. It is also necessary to adjust the latches to
make sure the aerodynamic smoothness is in the specified limits.
B. It is necessary to adjust the latches on the core cowl panels when one of
these components is replaced: A thrust reverser, a core cowl panel, or a
latch on the core cowl panels.
C. It is necessary to install and adjust the thrust reverser before you
adjust the latches on the core cowl panels.
TASK 71-11-07-825-001-P00
Adjust the Core Cowl Panel Latches
__________________________________
A. Equipment
(1) Hex Wrench - 4 millimeter or 5/32 inch,
standard long series
(2) Scale - Push/pull, with a 0-60 pound range
B. Consumable Materials
(1) G02020 Clay - Modeling
(2) D00139 Lubricant - Silicone spray, WD-40
(3) A00307 Primer - BAC 5710 Type 51
C. References
(1) 71-11-06/201, Core Cowl Panels
(2) 78-31-00/201, Thrust Reverser System
D. Access
(1) Location Zones
410
Left Engine Nacelle
420
Right Engine Nacelle
(2)
Access Panels
415AL/416AR
417AL/418AR
425AL/426AR
427AL/428AR
Thrust Reverser,
Core Cowl Panel,
Thrust Reverser,
Core Cowl Panel,
EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùùû
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Left Engine
Left Engine
Right Engine
Right Engine
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E.
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Procedure
(1)
S 215-011-P00
Make sure the thrust reversers are closed and latched
(Ref 78-31-00/201).
S 045-002-P00
WARNING:
_______
(2)
DO THE THRUST REVERSER DEACTIVATION TO PREVENT THE OPERATION OF
THE THRUST REVERSERS. THE ACCIDENTAL OPERATION OF THE THRUST
REVERSERS CAN CAUSE INJURIES TO PERSONS OR DAMAGE TO EQUIPMENT.
Do this procedure: Thrust Reverser Deactivation for Ground
Maintenance (Ref 78-31-00/201).
S 215-012-P00
CAUTION:
_______
(3)
(4)
(5)
MAKE SURE YOU CORRECTLY ADJUST THE LATCHES ON THE CORE COWL
PANELS. IF YOU OPERATE THE AIRPLANE WHEN THE LATCHES ARE NOT
ADJUSTED CORRECTLY, THE LATCHES CAN RELEASE. IF THE LATCHES
RELEASE, DAMAGE CAN OCCUR TO THE CORE COWL PANELS, THE ENGINE,
OR THE AIRPLANE.
Make sure the core cowl panels are closed and latched
(Ref 71-11-06/201).
S 225-004-P00
Make sure the core cowl panels and the latches are in the limits for
the aerodynamic smoothness (Fig. 501).
(a) Do a check of the clearance between the two core cowl panels.
(b) Make sure the surfaces of the two core cowl panels are smooth
(the step height).
S 225-005-P00
If the core cowl panels are not in the limits for the aerodynamic
smoothness, do these steps to adjust the latches (Fig. 502):
(a) Open the core cowl panels (Ref 71-11-06/201).
(b) Make sure the keeper eyebolts do not turn.
1) If the keeper eyebolts turn, replace the anti-rotation
stops and the keepers that have damage.
(c) Do these steps to remove the shims (4 locations) from the core
cowl panels:
1) Remove the two shims at the center latch on the left core
cowl panel.
2) Remove the two shims at the forward and the aft keepers on
the right core cowl panel.
a) Remove the bearing pad and the shim at the forward and
the aft keepers.
b) Install the bearing pads at the forward and the aft
keepers.
(d) Apply the modeling clay at the four shim locations.
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MAINTENANCE MANUAL
SEE A
SKIN CLEARANCES
(COWL)
1
FWD
AERODYNAMIC
SMOOTHNESS
A
2
1
0.06-0.18 INCH FROM THE
COWL TO THE OTHER COWL
2
|0.03 INCH IN AN AREA 3.0
INCHES FROM THE SHEAR PINS.
|0.06 INCH WHEN THERE IS
MORE THAN 3.0 INCHES FROM
THE SHEAR PINS.
97766
Core Cowl Panel Clearance and Aero-Smoothness
Figure 501
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SEE
SEE
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A
B
BOLT
(4 LOCATIONS)
BOLT
(4 LOCATIONS)
BEARING PAD/
ANTI-ROTATION STOP
BEARING PAD/
ANTI-ROTATION STOP
SHIM
BOLT
(4 LOCATIONS)
KEEPER
KEEPER
SHEAR PIN
WASHER
(4 LOCATIONS)
SHEAR PIN
SHIM
KEEPER
SHEAR PIN
SEE
WASHER
(4 LOCATIONS)
NUT
SEE
(4 LOCATIONS)
D
SEE
NUT
(4 LOCATIONS)
E
WASHER
(4 LOCATIONS)
CORE COWL PANEL - KEEPER SIDE
ON CORE COWL PANELS WITH SB 71-20
BOLT
(4 LOCATIONS)
D
NUT
(4 LOCATIONS)
BOLT
(4 LOCATIONS)
A
BEARING PAD
BEARING PAD
SHIM
KEEPER
KEEPER
SHEAR PIN
BOLT
(4 LOCATIONS)
WASHER
(4 LOCATIONS)
SHEAR PIN
SHIM
KEEPER
SHEAR PIN
SEE
WASHER
(4 LOCATIONS)
NUT
SEE
(4 LOCATIONS)
C
SEE
NUT
(4 LOCATIONS)
NUT
(4 LOCATIONS)
C
CORE COWL PANEL - KEEPER SIDE
ON CORE COWL PANELS WITHOUT SB 71-20
1
IF THE TANG IS GONE IT IS
NECESSARY TO REPLACE THE KEEPER
WASHER
(4 LOCATIONS)
A
127723
Core Cowl Panel Latch Adjustment
Figure 502 (Sheet 1)
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MAINTENANCE MANUAL
LATCH
(3 LOCATIONS)
SHEAR PIN SEAT
(3 LOCATIONS)
SHIM
FWD
CORE COWL PANEL - LATCH SIDE
B
LATCH HOOK
TANG 1
HEX WRENCH
KEEPER ADJUSTMENT ON CORE
COWL PANELS WITHOUT SB 71-20
C
LATCH HOOK
LATCH HOOK
KEEPER
ANTI-ROTATION
STOP
KEEPER
ANTI-ROTATION
STOP
HEX WRENCH
HEX WRENCH
KEEPER ADJUSTMENT ON CORE
COWL PANELS WITH SB 71-20
KEEPER ADJUSTMENT ON CORE
COWL PANELS WITH SB 71-20
D
E
276907
Core Cowl Panel Latch Adjustment
Figure 502 (Sheet 2)
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MAINTENANCE MANUAL
(e)
(f)
(g)
Apply the lubricant to the adjacent surfaces for each of the
shim locations.
Close and latch the core cowl panels (Ref 71-11-06/201).
Do the steps that follow to adjust the clearance between the
core cowl panels:
1) Push the latch trigger to open the latch to approximately
15 degrees.
2) Turn the adjustment star with the hex wrench until the
clearance between the cowls is in the specified limits.
NOTE:
____
(h)
(i)
(j)
(k)
(l)
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The direction to turn the adjustment star is
shown on the keeper. Increase the load to decrease
the clearance between the cowls.
Open the core cowl panels (Ref 71-11-06/201).
Measure the thickness of modeling clay at each of the shim
locations.
Remove the laminations from the shims (or install new shims)
until the shims are the same thickness as the modeling clay at
each of the shim locations.
Apply the primer to each of the shims.
Install the bearing pads and the shims at the four locations
(Fig. 502).
S 725-006-P00
CAUTION:
_______
(6)
DO NOT APPLY MORE THAN A 55 POUND FORCE TO THE LATCH HANDLES.
IF YOU APPLY A LARGE FORCE, YOU CAN CAUSE DAMAGE TO THE LATCH.
Use the scale on each latch handle to do a check of the force
necessary to close the latch.
(a) If the force necessary to close the latch is not 45-55 pounds,
do these steps to adjust the latch.
1) Push the latch trigger to open the latch handles to
approximately 15 degrees.
2) Turn the adjustment star with the hex wrench to increase or
decrease the force necessary to close the latches.
NOTE:
____
(7)
(8)
The direction to turn the adjustment star is
shown on the keeper.
S 415-007-P00
Close the core cowl panels (Ref 71-11-06/201).
S 215-008-P00
Make sure the latches are smooth with the external surface of the
core cowl panel.
(a) If the latch handles are not smooth with the core cowl panel,
do these steps:
1) Open the right core cowl panel (Ref 71-11-06/201).
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2)
3)
4)
5)
6)
(9)
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Loosen the bolts that attach the keeper to the right core
cowl panel.
Move the keeper up or down to make the two core cowl panels
smooth.
Tighten the bolts that attach the keeper to the right core
cowl panel.
Close the core cowl panels (Ref 71-11-06/201).
Make sure the latch handles are smooth with the core cowl
panel.
S 725-009-P00
Do a check of the force necessary to close the latches again.
(a) Make sure the force to close the latches is 45-55 pounds.
(b) If it is necessary, adjust the latch tension again.
S 445-010-P00
(10) Do the thrust reverser activation (Ref 78-31-00/201).
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COWL PANEL PRESSURE RELIEF DOORS - REMOVAL/INSTALLATION
_______________________________________________________
1.
2.
General
_______
A. This procedure includes the removal and the installation of the pressure
relief doors in the fan cowl panels and the core cowl panels. The fan
cowl panels have one pressure relief door and the core cowl panels have
two pressure relief doors.
TASK 71-11-08-004-001-P00
Remove the Cowl Panel Pressure Relief Doors
___________________________________________
NOTE:
____
A.
B.
This procedure is for the doors of the fan cowl panel and the core
cowl panel.
References
(1) 78-31-00/201, Thrust Reverser System
Access
(1) Location Zones
413
L Power Plant Fan Cowl Panel
417
L Power Plant Core Cowl
418
L Power Plant Core Cowl
(2)
C.
Access Panels
413AL
Fan Cowl Panel (Left)
417AL
Core Cowl (Left)
418AL
Core Cowl (Right)
Prepare to Remove the Pressure Relief Door of the Cowl Panel
S 044-002-P00
WARNING:
_______
(1)
DO THE THRUST REVERSER DEACTIVATION PROCEDURE TO PREVENT THE
OPERATION OF THE THRUST REVERSER. THE ACCIDENTAL OPERATION OF
THE THRUST REVERSER CAN CAUSE INJURY TO YOU OR DAMAGE TO
EQUIPMENT.
Do this procedure: Thrust Reverser Deactivation for Ground
Maintenance (Ref 78-31-00).
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MAINTENANCE MANUAL
FAN COWL
PRESSURE
RELIEF DOOR
CORE COWL PRESSURE
RELIEF DOOR
(1 LOCATION EACH CORE COWL)
SEE
SEE
SEE
A
B
A
SEE
BOLT
(2 LOCATIONS)
C
TAPERED
SPACER
ROLL PIN
(2 LOCATIONS)
1
SHIM
WASHER
(2 LOCATIONS)
DOOR
2
A
HINGE
NUT
(2 LOCATIONS)
WASHER
BOLT
BUSHING
WASHER
SEE
C
NUT
RUBBER
STOP
C
1
B
2
1
GAP CLEARANCE
0.03-0.09 INCH
2
SMOOTHNESS
|0.03 INCH
117568
Cowl Panel Pressure Relief Door Installation
Figure 401
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D.
Remove the Pressure Relief Door of the Cowl Panel
S 014-003-P00
Install a screwdriver into the latch slot (2 locations).
(1)
(2)
S 014-004-P00
Apply a force to the screwdriver to release the pressure relief
door.
(3)
S 034-006-P00
Remove the bolt and nut which attach the rubber stop to the hinge
support.
S 034-007-P00
Remove the rubber stop.
(4)
(5)
S 034-008-P00
Remove the bolts from the hinge assemblies on the pressure relief
door.
(6)
S 034-009-P00
With a drift, lightly hit the roll pins until you can remove the
pressure relief door.
(7)
S 024-010-P00
Remove the pressure relief door.
(8)
S 034-011-P00
Remove the hinges and the washers from the bushings.
S 034-012-P00
If it is necessary to remove the shims and the spacer, fully remove
the roll pins.
(9)
3.
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TASK 71-11-08-404-013-P00
Install the Cowl Panel Pressure Relief Doors
____________________________________________
NOTE:
____
A.
B.
This procedure is for the doors of the fan cowl panel and the core
cowl panel.
Consumable Materials
(1) D00015 Grease - Corrosion Preventive BMS 3-24
(2) C00259 Primer - BMS 10-11 Type I
(3) A00307 Primer - DeSotos Hi-Temperature
polyurethane, BAC 5710 - Type 51
References
(1) 71-11-08/501, Cowl Panel Pressure Relief Doors
(2) 78-31-00/201, Thrust Reverser System
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C.
Access
(1) Location Zones
413
L Power Plant Fan Cowl Panel
417
L Power Plant Core Cowl
418
L Power Plant Core Cowl
(2)
D.
Access Panels
413AL
Fan Cowl Panel (Left)
417AL
Core Cowl (Left)
418AL
Core Cowl (Right)
Procedure
(1)
(2)
S 214-014-P00
Examine the bushings for worn areas.
(a) If it is necessary, replace the bushing.
S 434-015-P00
Install the washer and the hinge in the bushing.
(a) Install the necessary number of washers to keep the clearance
between the skins.
(b) Make sure there is no free play from one side to the other
side.
(3)
S 644-016-P00
Apply grease to the bolts.
(4)
S 424-017-P00
Install the bolts, nuts, and washers in the hinges.
(5)
S 424-018-P00
Close the pressure relief door.
(6)
S 214-019-P00
Make sure there is a smooth surface between the pressure relief door
and the cowl panel.
(a) If you do not have a smooth surface, remove the shim
laminations, as it is necessary, to get a smooth surface.
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(7)
(8)
(9)
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S 034-020-P00
Remove the shims after you find the necessary thickness.
S 394-021-P00
Apply the applicable primer to the shims.
(a) Apply the type 1 primer to the shims on the pressure relief
door of the fan cowl panel.
(b) Apply the DeSotos Hi-Temperature primer to the shims on the
pressure relief door of the core cowl panel.
S 434-022-P00
Install the shims to the applicable pressure relief door.
(a) Do not tighten the nuts.
S 434-023-P00
(10) Install the roll pins until they are flat with the external surface.
NOTE:
____
More roll pin holes are given in the hinge fittings for
an adjustment or a replacement. Do not drill through until
it is necessary.
S 354-024-P00
(11) Cut the roll pin until it is flat against the internal surface.
S 434-025-P00
(12) Tighten the nuts.
S 394-026-P00
(13) Apply the wet primer to the end of the roll pins at the external
surface.
S 824-027-P00
(14) Adjust the latches and the hinges on the pressure relief door
(Ref 71-11-08).
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E.
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Put the airplane back to its initial condition
(1)
S 444-028-P00
Do the activation procedure for the thrust reverser (Ref 78-31-00).
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COWL PANEL PRESSURE RELIEF DOORS - ADJUSTMENT/TEST
__________________________________________________
1.
2.
General
_______
A. There are two tasks in this procedure for the pressure relief doors on
the fan cowl panels and on the core cowl panels. The first task does a
latch test of the pressure relief doors. The second task does a check of
the aerodynamic smoothness of the pressure relief doors.
TASK 71-11-08-725-001-P00
Latch Test for the Pressure Relief Doors on the Fan and Core Cowl Panels
________________________________________________________________________
A. Equipment
(1) Adapter - Load Test - Pressure Relief Door
Latch - B71044-10
B. References
(1) 71-11-08/401, Cowl Panel Pressure Relief Doors
(2) 78-31-00/201, Thrust Reverser System
C. Access
(1) Location Zones
410
Left Engine Nacelle
420
Right Engine Nacelle
(2)
D.
Access Panels
413AL/414AR
415AL/416AR
417AL/418AR
423AL/424AR
425AL/426AR
427AL/428AR
Fan Cowl Panel, Left Engine
Thrust Reverser, Left Engine
Core Cowl Panel, Left Engine
Fan Cowl Panel, Right Engine
Thrust Reverser, Right Engine
Core Cowl Panel, Right Engine
Do the Test of the Latches on the Pressure Relief Doors (Fig. 501).
S 045-002-P00
WARNING:
_______
(1)
DO THE THRUST REVERSER DEACTIVATION TO PREVENT THE OPERATION OF
THE THRUST REVERSER. THE ACCIDENTAL OPERATION OF THE THRUST
REVERSER CAN CAUSE INJURIES TO PERSONS OR DAMAGE TO EQUIPMENT.
Do this procedure: Thrust Reverser Deactivation for Ground
Maintenance (AMM 78-31-00/201).
NOTE:
____
This is only necessary if you will use this procedure for
the pressure relief doors on the core cowl panels.
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MAINTENANCE MANUAL
PRESSURE RELIEF DOOR
FAN COWL
PRESSURE
RELIEF DOOR
SEE
1. LATCHES
CORE COWL
PRESSURE RELIEF
DOOR
A
SEE
SEE
B
A
A
DOOR
COWL PANEL
INSIDE (REF)
3. BOLTS
WASHERS
NUTS
5. PIVOT
SUPPORT
ASSEMBLY
5. PIVOT
SUPPORT
ASSEMBLY
LATCH
B
2. ADAPTER
ASSEMBLY
2. ADAPTER
ASSEMBLY
TORQUE WRENCH
AND 13/16 SOCKET
DOOR SIDE
(REF)
SEE
DOOR FRAME
(REF)
7. PIVOT
BOLT
C
6. RING PIN
STRUCTURE SIDE
(REF)
4. ADAPTER BOLT
WASHER
NUT
(2 LOCATIONS)
DOOR LATCH
(REF)
B71044-10 LOAD TEST TOOL INSTALLATION
C
G76899
Cowl Pressure Relief Door Latch Test
Figure 501
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(2)
(3)
S 015-017-P00
Open the latches on the pressure relief door.
(a) Put the blade of a straight-slot screwdriver into the latch
slot (1).
(b) Move the screwdriver handle to the side to turn the latch (1)
to the open position.
S 485-018-P00
Install the load-test-adapter-tool for the latch on the pressure
relief door.
(a) Remove the two latch mounting bolts (3) that are nearest to the
edge of the pressure relief door.
(b) Temporarily fasten the adapter assembly (2) to the door with
the bolts (4) that are supplied with the adapter assembly.
1) Put the adapter bolts (4) into the bolt holes that the
latch bolts (3) were removed from.
2) Tighten the nuts on the bolts (4) with your fingers.
(c) Attach the arm of the pivot support assembly (5) to the adapter
assembly (2) with the ring pin (6).
(d) Put the base of the pivot support assembly (5) flush on the
surface of the pressure relief door.
NOTE:
____
(4)
The axis of the main tube of the pivot support
assembly (5) must be vertical, or 90-degrees, to the
surface of the pressure relief door. The arm of the
pivot support assembly (5), that connects to the adapter
assembly (2), also must be 90-degrees to the surface of
the pressure relief door. When you put the tool in this
correct position and turn the torque wrench, force will
be applied correctly at the centerline of the latch.
S 485-019-P00
Attach the torque wrench to the pivot bolt (7) of the pivot support
assembly (5).
NOTE:
____
(5)
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Make sure that the handle of the torque wrench is parallel
with the surface of the pressure relief door.
S 415-020-P00
Close the latch (1) that you will examine on the pressure relief
door.
(a) Put the blade of a straight-slot screwdriver into the slot on
the latch (1) that you will examine.
(b) Move the screwdriver handle until the latch (1) is in the fully
open position, and close the pressure relief door.
(c) Move the screwdriver in the opposite direction to lock the
latch (1).
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(d)
Do not lock the opposite latch.
NOTE:
____
(6)
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The opposite latch must stay unlocked during the test.
S 725-021-P00
Do the test of the latches on the pressure relief door.
CAUTION:
_______
(a)
(b)
(c)
(d)
PUT A FOLDED SHOP CLOTH OR RUBBER MAT BETWEEN THE TORQUE
WRENCH HANDLE AND THE PRESSURE RELIEF DOOR (BEFORE YOU
TURN THE HANDLE TO OPEN THE LATCH). THIS WILL PREVENT
INJURY TO YOUR HAND WHEN YOU SUDDENLY RELEASE THE LATCH.
ALSO, IT WILL PREVENT SCRATCHES TO THE SURFACE OF THE
PRESSURE RELIEF DOOR CAUSED BY THE TORQUE WRENCH HANDLE.
IF YOU DO NOT DO THIS, INJURIES TO PERSONS OR DAMAGE TO
EQUIPMENT CAN OCCUR.
Put a folded shop cloth or rubber mat between the torque wrench
handle and the pressure relief door.
With the handle of the torque wrench parallel to the surface of
the pressure relief door, turn the handle down smoothly.
As you turn the handle down, make a record of the torque when
the latch on the pressure relief door opens.
For the fan cowl panel, the latch on the pressure relief door
is serviceable if the torque used to open it is 162.0-198.0
pound-inches (18.3-22.4 newton-meters).
NOTE:
____
(e)
The force necessary to open the latch is 81-99 pounds
(36.7-45.0 kilograms). But, the arm of the pivot
support assembly which pulls up on the latch decreases
the applied force by a factor of two. This makes it
necessary to increase the force you apply by a factor of
two. Thus, the latch must unlock when the torque wrench
shows 162.0-198.0 pound-inches (18.3-22.4 newton-meters).
For the core cowl panel, the latch on the pressure relief door
is serviceable if the torque used to open it is 80-100
pound-inches (9.0-11.3 newton-meters).
NOTE:
____
The force necessary to open the latch is 40-50 pounds
(18.0-22.7 kilograms). But, the arm of the pivot
support assembly which pulls up on the latch decreases
the applied force by a factor of two. This makes it
necessary to increase the force you apply by a factor of
two. Thus, the latch must unlock when the torque wrench
shows 80-100 pound-inches (9.0-11.3 newton-meters).
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(7)
(8)
(9)
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S 025-022-P00
If the force to release the latch (1) is not in the specified
limits, replace the latch.
S 085-023-P00
Remove the load-test-adapter-tool from the pressure relief door.
(a) Remove the pivot support assembly (5) from the pressure relief
door.
(b) Remove the adapter assembly (2) from the pressure relief door.
(c) Install the mounting bolts, washers and nuts (3) on the latch,
and tighten the nuts (3).
S 725-024-P00
Do these steps again to do a test of the other latch on the pressure
relief door.
S 415-025-P00
(10) When you have completed the tests for the two latches on the
pressure relief door, do these steps:
(a) Put the blade of a straight-slot screwdriver into the slot of
one of the latches (1) on the pressure relief door.
(b) Move the screwdriver handle until the latch (1) is in the fully
open position, and close the pressure relief door.
(c) Move the screwdriver in the opposite direction to lock the
latch (1).
(d) Do these steps again to close the opposite latch (1) on the
pressure relief door.
S 445-008-P00
(11) If it is necessary, do this procedure: Thrust Reverser Activation
After Ground Maintenance (AMM 78-31-00/201).
3.
TASK 71-11-08-225-009-P00
Aerodynamic Smoothness Check for the Pressure Relief Doors on the Fan Cowl
__________________________________________________________________________
and the Core Cowl Panels
________________________
A. Consumable Materials
(1) D00015 Grease - Corrosion Preventive, BMS 3-24
B. References
(1) 71-11-00/201, Aerodynamic Smoothness
(2) 71-11-08/401, Cowl Panel Pressure Relief Doors
(3) 78-31-00/201, Thrust Reverser System
C. Access
(1) Location Zones
410
Left Engine Nacelle
420
Right Engine Nacelle
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(2)
D.
Access Panels
413AL/414AR
415AL/416AR
417AL/418AR
423AL/424AR
425AL/426AR
427AL/428AR
Fan Cowl Panel, Left Engine
Thrust Reverser, Left Engine
Core Cowl Panel, Left Engine
Fan Cowl Panel, Right Engine
Thrust Reverser, Right Engine
Core Cowl Panel, Right Engine
Procedure
S 045-010-P00
WARNING:
_______
(1)
DO THE THRUST REVERSER DEACTIVATION PROCEDURE TO PREVENT THE
OPERATION OF THE THRUST REVERSERS. THE ACCIDENTAL OPERATION OF
THE THRUST REVERSERS CAN CAUSE INJURIES TO PERSONS OR DAMAGE TO
EQUIPMENT.
Do this procedure: Thrust Reverser Deactivation for Ground
Maintenance (Ref 78-31-00/201).
NOTE:
____
(2)
(3)
(4)
This is only necessary if you will use this procedure for
the pressure relief doors on the core cowl panels.
S 215-011-P00
Make sure the pressure relief door is fully closed.
S 225-012-P00
Make sure the pressure relief doors are in the limits for the
aerodynamic smoothness (Ref 71-11-00/201).
(a) Do a check of the clearance at the sides of the door.
(b) Make sure the surface of the door is smooth with the surface of
the cowl.
S 225-013-P00
If the door is not in the limits for the aerodynamic smoothness, do
these steps to adjust the door:
(a) Adjust the side clearance of the door.
1) Make sure the door does not move when the door is fully
closed.
2) Remove or install washers as necessary between the hinges
and the bushings (Ref 71-11-08/401).
(b) Adjust the surface height of the door (smoothness).
1) Remove the pressure relief door (Ref 71-11-08/401).
2) Remove the laminations of the shim (or install a new shim)
to make the door smooth with the cowl surface.
3) Apply the primer to the shim.
4) Attach the door to the inlet cowl (Ref 71-11-08/401).
(c) Do a check of the aerodynamic smoothness again
(Ref 71-11-00/201).
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(5)
S 425-014-P00
Complete the installation of the pressure relief door
(Ref 71-11-08/401).
(6)
S 445-015-P00
If it is necessary, do the thrust reverser activation procedure
(Ref 78-31-00/201).
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INLET COWL THERMAL ANTI-ICE (TAI) DUCT - REMOVAL/INSTALLATION
_____________________________________________________________
1.
2.
General
_______
A. There are two tasks in this procedure. The first task is the removal of
the thermal anti-ice (TAI) duct. The second task is the installation of
the TAI duct.
B. It is not necessary to remove the lower skin on the inlet cowl to remove
the TAI duct. You must remove the lower skin on the inlet cowl to
replace the duct seal in the inlet cowl.
TASK 71-11-09-004-001-P00
Inlet Cowl TAI Duct Removal (Fig. 401)
___________________________
A. References
(1) 30-21-03/401, Thermal Anti-Ice (TAI) Valve
(2) 71-11-01/401, Inlet Cowl
(3) 71-11-04/201, Fan Cowl Panels
B. Access
(1) Location Zones
412/422
Inlet Cowl
414
Fan Cowl Panel, Left Engine
424
Fan Cowl Panel, Right Engine
(2)
C.
Access Panels
414AR
Fan Cowl Panel, Left Engine
424AR
Fan Cowl Panel, Right Engine
Procedure
(1)
(2)
(3)
(4)
(5)
S 024-002-P00
If it is necessary, remove the inlet cowl (Ref 71-11-01/401).
S 034-003-P00
If you will keep the inlet cowl on the engine, do these steps:
(a) Open the right fan cowl panel (Ref 71-11-04/201).
(b) Remove the TAI valve (Ref 30-21-03/401).
S 034-004-P00
Remove the bolts, the spacers, and the shims that hold the retainer
to the inlet cowl.
S 034-010-P00
If it is necessary to replace the seal, do these steps:
(a) Remove the bolts that attach the lower skin on the inlet cowl.
(b) Remove the lower skin from the inlet cowl.
(c) Move the TAI duct aft until it is clear of the seal.
(d) Remove the seal.
S 024-006-P00
Move the TAI duct aft through the aft bulkhead of the inlet cowl.
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TAI VALVE
FAN COWL
INLET COWL
SEE A
SEE B
SEE B
BOLT
BOLT
(4 LOCATIONS)
SHIM
(2 LOCATIONS)
SPACER
(2 LOCATIONS)
INLET COWL
LOWER SKIN
A
BOLT
RETAINER
INLET COWL THERMAL
ANTI-ICE (TAI) DUCT
FWD
B
INLET
COWL
SEAL
139894
Inlet Duct Installation
Figure 401
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TASK 71-11-09-404-007-P00
Inlet Cowl TAI Duct Installation (Fig. 401)
________________________________
A. References
(1) 30-21-03/401, Thermal Anti-Ice (TAI) Valve
(2) 71-11-01/401, Inlet Cowl
(3) 71-11-04/201, Fan Cowl Panels
B. Access
(1) Location Zones
412/422
Inlet Cowl
414
Fan Cowl Panel, Left Engine
424
Fan Cowl Panel, Right Engine
(2)
C.
Location Zones
414AR
Fan Cowl Panel, Left Engine
424AR
Fan Cowl Panel, Right Engine
Procedure
(1)
(2)
S 424-008-P00
Install the TAI duct through the aft bulkhead of the inlet cowl.
S 434-009-P00
If the seal was removed, do these steps:
(a) Install a new seal on the inlet cowl.
(b) Move the TAI duct forward into the seal housing.
(c) Install the lower skin on the inlet cowl with the bolts.
(3)
S 434-011-P00
Install the bolts, the spacers, and the shims to attach the TAI
duct.
(4)
S 424-012-P00
If the inlet cowl was removed from the engine, install the inlet
cowl (Ref 71-11-01/401).
(5)
S 434-013-P00
If you did not remove the inlet cowl from the engine, do these
steps:
(a) Install the TAI valve (Ref 30-21-03/401).
(b) Close the right fan cowl panel (Ref 71-11-04/201).
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HOLD OPEN ROD - MAINTENANCE PRACTICES
_____________________________________
1.
2.
General
_______
A. This procedure has two tasks. The first task is an inspection of the
hold-open rods for the fan cowl panels, the thrust reversers, and the
core cowl panels. The second task is used to clean the hold-open rods
for the engine cowls.
B. The hold-open rods hold the cowl open when you do maintenance on the
engine. The rods attach to a bracket on the engine when the cowls are
open. When the cowls are closed, the rod attaches to a stow bracket on
the cowl.
C. The hold-open rods must lock when they are fully extended. If the lock
mechanism on the rods does not operate correctly, injuries to persons can
occur by a cowl that closes.
TASK 71-11-10-712-001-P00
Do an Inspection of the Hold-Open Rods for the Engine Cowls (Fig. 201)
___________________________________________________________
A. References
(1) AMM 71-11-04/201, Fan Cowl Panel
(2) AMM 71-11-06/201, Core Cowl Panel
(3) AMM 78-31-00/201, Thrust Reverser System
B. Access
(1) Location Zones
411
Left Engine
421
Right Engine
(2)
C.
Access Panels
413AL/414AR
415AL/416AR
417AL/428AR
423AL/424AR
425AL/426AR
427AL/428AR
Fan Cowl Panels, Left Engine
Thrust Reversers, Left Engine
Core Cowl Panels, Left Engine
Fan Cowl Panels, Right Engine
Thrust Reversers, Right Engine
Core Cowl Panels, Right Engine
Prepare for the Inspection of the Hold-Open Rods.
(1)
S 012-002-P00
Open the fan cowl panels (AMM 71-11-04/201).
NOTE:
____
You open the fan cowl panels to get access to the hold-open
rods on the fan cowls and the thrust reversers. It is not
necessary to open the thrust reversers for this inspection.
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LOCK COLLAR
PIN RETAINER
LOCK PIN
LOCK PIN HOLE
COLLAR TYPE LOCK
WITH SAFETY PIN
RED
WARNING
BAND
LOCK
RELEASE
LEVER
LOCK
RELEASE
COLLAR
LEVER TYPE LOCK
(CORE COWL ONLY)
COLLAR TYPE LOCK
230806
Hold-Open Rod
Figure 201
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S 042-016-P00
WARNING:
_______
(2)
D.
DO THE THRUST REVERSER DEACTIVATION PROCEDURE TO PREVENT THE
OPERATION OF THE THRUST REVERSERS. THE ACCIDENTAL OPERATION OF
THE THRUST REVERSERS CAN CAUSE INJURIES TO PERSONS OR DAMAGE TO
EQUIPMENT.
Do this procedure: Thrust Reverser Deactivation for Ground
Maintenance (AMM 78-31-00/201).
S 012-003-P00
(3) Open the core cowl panels (AMM 71-11-06/201).
Do the Inspection of the Hold-Open Rods.
(1)
(2)
S 012-004-P00
Hold the fan cowl panels and the core cowls open from the external
side.
S 712-005-P00
Do these steps to examine the hold-open rods on all of the engine
cowls:
(a) Disconnect and connect the rods to the stow bracket to make
sure they operate correctly.
(b) Make sure the end of the rod that is permanently attached to
the cowl moves freely.
(c) Visually examine the rods for damage.
(d) Extend the rods to make sure they operate smoothly.
(e) Make sure the lock releases correctly when the rod fully
extends (Fig. 201).
(f) Operate the lock release three times to make sure the lock does
not have contamination.
1) If you think there is contamination, do the task to clean
the hold-open rods.
(g) For the hold-open rods with safety lock pins, do the steps that
follow:
1) Visually examine the pin retainer for damage.
2) Visually examine the safety lock pin for damage.
3) Make sure the safety lock pins can be installed correctly.
4) Make sure the safety lock pin can be installed in the lock
pin hole of the hold open rod correctly.
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S 212-018-P00
Examine the bracket, which is used to connect the hold-open rod to
the core cowl panel, for signs of wear.
(a) If the rod end nut, which attaches the hold-open rod to the
bracket, is loose and there are signs of wear on the bracket,
replace the bracket.
(b) Make sure the rod end nut is tightened to 160-240 pound-inches
(18.1-27.1 newton-meters).
Put the Airplane Back to its Usual Condition.
(3)
E.
3.
(1)
S 412-006-P00
Close the core cowl panels (AMM 71-11-06/201).
(2)
S 442-007-P00
Do the thrust reverser activation procedure (AMM 78-31-00/201).
(3)
S 412-008-P00
Close the fan cowl panels (AMM 71-11-04/201).
TASK 71-11-10-112-009-P00
Clean the Hold-Open Rods for the Engine Cowls (Fig. 201)
_____________________________________________
A. Consumable Materials
(1) B00069 Solvent - Triclorethane
B. Access
(1) Location Zones
411
Left Engine
421
Right Engine
(2)
C.
Access Panels
413AL/414AR
415AL/416AR
417AL/428AR
423AL/424AR
425AL/426AR
427AL/428AR
Fan Cowl Panels, Left Engine
Thrust Reversers, Left Engine
Core Cowl Panels, Left Engine
Fan Cowl Panels, Right Engine
Thrust Reversers, Right Engine
Core Cowl Panels, Right Engine
Procedure
(1)
S 212-010-P00
Make sure the rods are fully extended and locked.
(2)
S 112-011-P00
Apply a large quantity of the solvent to the rods and the lock
devices.
(3)
S 712-012-P00
Extend and retract the rods to make sure the rods operate correctly
and smoothly.
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(4)
S 712-013-P00
Operate the lock devices to make sure the locks operate correctly
and smoothly.
(5)
S 112-014-P00
Before the solvent evaporates, dry the rods and the lock devices
with a clean cloth.
(6)
S 112-015-P00
Do not lubricate the rods or the lock devices.
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FAN COWL PANEL INSULATION BLANKET - APPROVED REPAIRS
____________________________________________________
1.
General
_______
A. This procedure has the instructions to repair the insulation blanket on
the fan cowl panels. This procedure also has the steps to repair the
aluminized cover on the insulation blanket. The list that follows shows
all of the repairs in this procedure:
(1) Insulation Core Damage Repair (Paragraph 2) - Use this repair when
the aluminized cover has damage, and the insulation core material
has damage, is gone, or has contamination.
(2) Insulation Cover Penetration Repair (Paragraph 3) - Use this repair
when the aluminized cover has damage, but the insulation core
material does not have contamination and has only a small quantity
of damage.
(3) Aluminized Cover Abrasion Repair (Paragraph 4) - Use this repair
when the aluminized cover has damage, but the damage does not go
through the aluminized cover.
(4) Repair the Aluminized Cover That Is Not There (Paragraph 5) - Use
this repair when the aluminized cover is gone.
(5) Repair the Insulation That Is Not Attached (Paragraph 6) - Use this
repair when the insulation blanket is not attached, but does not
have damage.
(6) Insulation Blanket Foil Delamination Repair (Paragraph 7) - Use this
repair when the blanket foil on the insulation has delamination.
(7) Insulation Blanket Foil Delamination Repair (Adjacent to the
Starter) (Paragraph 8) - Use this repair when the insulation blanket
that is adjacent to the starter has delamination. This delamination
is caused by the starter exhaust air.
(8) Interim Repair (Paragraph 9) - This repair is a temporary repair of
the insulation. A permanent repair is necessary as quickly as it is
possible.
B. The steps that follow give the limits for the insulation blanket on the
fan cowl panels:
(1) Damage or contamination to the insulation core material is not
permitted. Repair this damage when you find it.
(2) Damage to the aluminized cover on the insulation is permitted if
there is not damage to the insulation core material. You must
repair the damage to the aluminized cover as quickly as possible to
prevent damage to the insulation core material.
(3) You can complete the Interim Repair for all damage to the insulation
blanket on the fan cowl panels.
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TASK 71-11-12-358-001-P00
Insulation Core Damage Repair (Fig. 801)
_____________________________
A. Consumable Materials
(1) Insulation Core Material - MIN-K,
Hi-Temp Insulation Inc.; Camarillo, CA 93010
(2) G00723 Insulation Tape - flexible MIN-K with
1/8-inch thickness, Hi-Temp Insulation Inc.
(3) A01015 Patch Material - HT-2100, Glass fabric
with the aluminized cover on one side and
silicon coating on the other side, Hi-Temp
Insulation Inc.
PRIMER (DC 1200)
AND ADHESIVE
(RTV 560)
ALUMINIZED
COVER
SEALING
FABRIC
INSULATION
EXAMPLE OF THE INSULATION BLANKET CONSTRUCTION
E42539
Insulation Blanket
Figure 801
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CATALYST
CONCENTRATION
PARTS PER 100
CATALYST
A
CATALYST
B
NO. OF DROPS OF
CATALYST AS LISTED
CONCENTRATION
2
POT LIFE
HOURS
PER
LB
PER
100
g
PER
LB
1
1
0.1
0.1
5
23
4
21
0.25
0.25
15
69
12
62
0.5
0.5
25
115
20
105
CATALYST
A
FULL CURE
HOURS
3
3
CATALYST A CATALYST B
1
1
PER
100
g
TACK FREE
HOURS
CATALYST
B
1
CATALYST
A
1
1
4 - 6
0.5
10 - 12
2 - 3-1/2
0.25
5 - 7
1 - 1-1/2
0.1
1-1/2 2-1/2
1
CATALYST A = THARMOLYTE-12 (DIBUTYL TIN DILAURATE)
CATALYST B = NUOCURE 2B (TIN OCTOATE)
2
FROM A CONVENTIONAL MEDICINE DROPPER.
3
AT 77`F AND 50% RELATIVE HUMIDITY.
4
THE TACK FREE TIME IS NOT APPLICABLE TO THE TIN OCTOATE CATALYST.
3
CATALYST
B
CATALYST
A
1
1
4
CATALYST
B
1
36 - 40
1
26 - 30
3/4
16 - 24
1/2
205498
Catalyst Concentrations vs Cure Time Measuring Guide
Figure 802
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(4)
B.
C.
Adhesive - Either of the ones that follow:
(a) A00102 Adhesive - RTV 560, General
Electric Company, Silicone Products
Division; Waterford, NY 12188
(b) A00578 Adhesive - RTV 60, General Electric
Company, Silicone Products Division,
Waterford, NY 12188
(5) Catalyst - Either of the ones that follow:
(a) A00309 Catalyst A - Dibutyl Tin Dilaurate,
M&T Chemical Corp.; Pico Rivera, CA 90660
(b) A00308 Catalyst B - Tin Octoate,
Tenncco Chemical Inc., Organics & Polymers
Division; Elizabeth, NJ 07201
(6) A00054 Adhesive Primer - Dow Corning 1200,
Dow-Corning Corp; Midland, Michigan 48641
(7) B00602 Solvent - Methyl Ethyl Ketone (MEK),
TT-M-261
(8) G02167 Scotchbrite - Abrasive pads
References
(1) 71-11-04/201, Fan Cowl Panel
Access
(1) Location Zones
413/414
Fan Cowl Panels, Left Engine
423/424
Fan Cowl Panels, Right Engine
(2)
D.
Access Panels
413AL/414AR
423AL/424AR
Fan Cowl Panels, Left Engine
Fan Cowl Panels, Right Engine
Procedure
(1)
(2)
S 018-002-P00
Open the fan cowl panels (Ref 71-11-04/201).
S 358-003-P00
Cut and remove the insulation core material, the cloth cover, or the
aluminized cover that has damage.
NOTE:
____
(a)
Do not remove the bottom cover that attaches to the
structure.
(3)
Make sure you remove all of the unwanted material.
S 358-004-P00
Cut a sufficeint quantity of the insulation tape to go on the
removed insulation material.
NOTE:
____
You can remove more insulation material to make it easier
to repair.
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(5)
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S 378-005-P00
Cut a piece of the patch material to install on the repair area.
(a) Cut the patch material with a minimum overlap of 1.5 inches
around the circumference.
S 358-006-P00
Use a scotchbrite pad to make the top aluminized cover around the
repair area rough.
S 118-007-P00
WARNING:
_______
(6)
(7)
(8)
DO NOT GET METHYL
ON YOUR SKIN. DO
PROTECTIVE SPLASH
AWAY FROM SPARKS,
FLAMMABLE SOLVENT
Use a cloth and the MEK to clean the repair area, the top aluminized
cover around the repair area, and the patch material.
S 358-008-P00
Apply the adhesive primer to all nonsilicone (the surfaces that are
not red) that you will apply the adhesive (this includes all the
faces of the insulation tape, the aluminized cover around the repair
area, and the repair area).
(a) Let the primer dry for a minimum of 30 minutes at 75 |10°F.
(b) The maximum time for the primer to dry is 2 hours at a relative
humidity of 50% or higher or 4 hours at a relative humidity of
30-49%.
(c) If the primer dries for more than the specified time, remove
the primer with the MEK and apply the primer again.
S 358-009-P00
Mix the adhesive base compound and the catalyst (Fig. 802).
NOTE:
____
(9)
ETHYL KETONE (MEK) IN YOUR MOUTH OR EYES, OR
NOT BREATHE THE FUMES FROM MEK. PUT ON A
GOGGLE AND GLOVES WHEN YOU USE MEK. KEEP MEK
FLAME, AND HEAT. MEK IS A POISONOUS AND
WHICH CAN CAUSE INJURY OR DAMAGE.
Use the catalyst concentration that will give a pot life
and a cure that is sufficient to complete the repair.
S 358-010-P00
Apply the adhesive compound with a thickness of approximately
0.01-0.02 inch to these surfaces: All the faces of the insulation
tape, the aluminized cover around the repair area, the repair area,
and the silicon surface of the patch material.
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////////////////////////
S 358-011-P00
(10) Apply the adhesive below all of the aluminized cover around the
repair area that is loose.
S 358-012-P00
(11) Put the insulation tape into the patch area and apply the patch on
the repair area.
(a) Apply a pressure of 2-5 psi and let the adhesive bond
permanently.
S 418-013-P00
(12) Close the fan cowl panels (Ref 71-11-04/201).
3.
TASK 71-11-12-358-014-P00
Insulation Cover Penetration Repair (Fig. 801)
___________________________________
A. Consumable Materials
(1) Insulation Core Material - MIN-K,
Hi-Temp Insulation Inc.; Camarillo, CA 93010
(2) A01015 Patch Material - Glass fabric with the
aluminized cover on one side and silicon coated
on the other side, Hi-Temp Insulation Inc.
(3) Adhesive - Either of the ones that follow:
(a) A00102 Adhesive - RTV 560, General
Electric Company, Silicone Products
Division; Waterford, NY 12188
(b) A00578 Adhesive - RTV 60, General Electric
Company, Silicone Products Division,
Waterford, NY 12188
(4) Catalyst - Either of the ones that follow:
(a) A00309 Catalyst A - Dibutyl Tin Dilaurate,
M&T Chemical Corp.; Pico Rivera, CA 90660
(b) A00308 Catalyst B - Tin Octoate,
Tenncco Chemical Inc., Organics & Polymers
Division; Elizabeth, NJ 07201
(5) A00521 Adhesive Primer - Dow Corning 1200,
Dow-Corning Corp; Midland, Michigan 48641
(6) B00378 Solvent - Methyl Ethyl Ketone (MEK),
TT-M-261
(7) G02167 Scotchbrite - Abrasive pads
B. References
(1) 71-11-04/201, Fan Cowl Panel
C. Access
(1) Location Zones
413/414
Fan Cowl Panels, Left Engine
423/424
Fan Cowl Panels, Right Engine
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71-11-12
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(2)
D.
Access Panels
413AL/414AR
423AL/424AR
////////////////////////
/
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/
/
/
ENGINES
////////////////////////
Fan Cowl Panels, Left Engine
Fan Cowl Panels, Right Engine
Procedure
(1)
S 018-015-P00
Open the fan cowl panels (Ref 71-11-04/201).
(2)
S 358-016-P00
Replace the insulation core material that is gone.
(3)
(4)
S 358-017-P00
Cut a piece of the patch material to install over the repair.
(a) Cut the patch material with a minimum overlap of 1.5 inches
around the circumference.
S 358-018-P00
Use a scotchbrite pad to make the top aluminized cover around the
repair area rough.
S 118-019-P00
WARNING:
_______
(5)
(6)
(7)
DO NOT GET METHYL
ON YOUR SKIN. DO
PROTECTIVE SPLASH
AWAY FROM SPARKS,
FLAMMABLE SOLVENT
Use a cloth and the MEK to clean the aluminized cover around the
repair area.
S 358-020-P00
Apply the adhesive primer to the repair area.
(a) Let the primer dry for a minimum of 30 minutes at 75 |10°F.
(b) The maximum time for the primer to dry is 2 hours at a relative
humidity of 50% or higher or 4 hours at a relative humidity of
30-49%.
(c) If the primer dries for more than the specified time, remove
the primer with the MEK and apply the primer again.
S 358-021-P00
Mix the adhesive base compound and the catalyst (Fig. 802).
NOTE:
____
(8)
ETHYL KETONE (MEK) IN YOUR MOUTH OR EYES, OR
NOT BREATHE THE FUMES FROM MEK. PUT ON A
GOGGLE AND GLOVES WHEN YOU USE MEK. KEEP MEK
FLAME, AND HEAT. MEK IS A POISONOUS AND
WHICH CAN CAUSE INJURY OR DAMAGE.
Use the catalyst concentration that will give a pot life
and a cure time that is sufficient to complete the repair.
S 358-022-P00
Apply the adhesive below all of the aluminized cover around the
repair area that is loose.
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(9)
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/
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S 358-023-P00
Apply the adhesive compound with a thickness of approximately
0.01-0.02 inch to the repair surface and to the silicone patch
material.
S 358-024-P00
(10) Put the patch on the repair area.
(a) Apply a pressure of 2-5 psi and let the adhesive bond
permanently.
S 418-025-P00
(11) Close the fan cowl panels (Ref 71-11-04/201).
4.
TASK 71-11-12-358-026-P00
Aluminized Cover Abrasion Repair (Fig. 801)
________________________________
A. Consumable Materials
(1) Adhesive - Either of the ones that follow:
(a) A00102 Adhesive - RTV 560, General
Electric Company, Silicone Products
Division; Waterford, NY 12188
(b) A00578 Adhesive - RTV 60, General Electric
Company, Silicone Products Division,
Waterford, NY 12188
(2) Catalyst - Either of the ones that follow:
(a) A00309 Catalyst A - Dibutyl Tin Dilaurate,
M&T Chemical Corp.; Pico Rivera, CA 90660
(b) A00308 Catalyst B - Tin Octoate,
Tenncco Chemical Inc., Organics & Polymers
Division; Elizabeth, NJ 07201
(3) A00521 Adhesive Primer - Dow Corning 1200,
Dow-Corning Corp; Midland, Michigan 48641
(4) B00378 Solvent - Methyl Ethyl Ketone (MEK),
TT-M-261
B. References
(1) 71-11-04/201, Fan Cowl Panel
C. Access
(1) Location Zones
413/414
Fan Cowl Panels, Left Engine
423/424
Fan Cowl Panels, Right Engine
(2)
D.
Access Panels
413AL/414AR
423AL/424AR
Fan Cowl Panels, Left Engine
Fan Cowl Panels, Right Engine
Procedure
(1)
S 018-027-P00
Open the fan cowl panels (Ref 71-11-04/201).
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71-11-12
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////////////////////////
/
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/
/
/
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////////////////////////
S 118-028-P00
WARNING:
_______
(2)
(3)
(4)
DO NOT GET METHYL
ON YOUR SKIN. DO
PROTECTIVE SPLASH
AWAY FROM SPARKS,
FLAMMABLE SOLVENT
Use a cloth and the MEK to clean the damaged surface.
S 358-029-P00
Apply the adhesive primer to the cleaned surface.
(a) Let the primer dry for a minimum of 30 minutes at 75 |10°F.
(b) The maximum time for the primer to dry is 2 hours at a relative
humidity of 50% or higher or 4 hours at a relative humidity of
30-49%.
(c) If the primer dries for more than the specified time, remove
the primer with the MEK and apply the primer again.
S 358-030-P00
Mix the adhesive base compound and the catalyst (Fig. 802).
NOTE:
____
(5)
(6)
5.
ETHYL KETONE (MEK) IN YOUR MOUTH OR EYES, OR
NOT BREATHE THE FUMES FROM MEK. PUT ON A
GOGGLE AND GLOVES WHEN YOU USE MEK. KEEP MEK
FLAME, AND HEAT. MEK IS A POISONOUS AND
WHICH CAN CAUSE INJURY OR DAMAGE.
Use the catalyst concentration that will give a pot life
and a cure time that is sufficient to complete the repair.
S 358-031-P00
Apply the adhesive compound to the damaged surface with a thickness
of approximately 0.01-0.02 inch.
(a) Let the adhesive cure.
S 418-032-P00
Close the fan cowl panels (Ref 71-11-04/201).
TASK 71-11-12-358-033-P00
Repair the Aluminized Cover That Is Not There (Fig. 801)
_____________________________________________
A. Consumable Materials
(1) Patch Material - Glass fabric with the
aluminized cover on one side and silicon coated
on the other side, Hi-Temp Insulation Inc.
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////////////////////////
/
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/
/
/
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////////////////////////
(2)
B.
C.
Adhesive - Either of the ones that follow:
(a) A00102 Adhesive - RTV 560, General
Electric Company, Silicone Products
Division; Waterford, NY 12188
(b) A00578 Adhesive - RTV 60, General Electric
Company, Silicone Products Division,
Waterford, NY 12188
(3) Catalyst - Either of the ones that follow:
(a) A00309 Catalyst A - Dibutyl Tin Dilaurate,
M&T Chemical Corp.; Pico Rivera, CA 90660
(b) A00308 Catalyst B - Tin Octoate,
Tenncco Chemical Inc., Organics & Polymers
Division; Elizabeth, NJ 07201
(4) A00521 Adhesive Primer - Dow Corning 1200,
Dow-Corning Corp; Midland, Michigan 48641
(5) B00378 Solvent - Methyl Ethyl Ketone (MEK),
TT-M-261
(6) G02167 Scotchbrite - Abrasive pads
References
(1) 71-11-04/201, Fan Cowl Panel
Access
(1) Location Zones
413/414
Fan Cowl Panels, Left Engine
423/424
Fan Cowl Panels, Right Engine
(2)
D.
Access Panels
413AL/414AR
423AL/424AR
Fan Cowl Panels, Left Engine
Fan Cowl Panels, Right Engine
Procedure
(1)
(2)
(3)
S 018-034-P00
Open the fan cowl panels (Ref 71-11-04/201).
S 358-035-P00
Cut a piece of the patch material to install over the repair.
(a) Cut the patch material with a minimum overlap of 1.5 inches
around the circumference.
S 358-036-P00
Use a scotchbrite pad to make the top aluminized cover around the
repair area rough.
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71-11-12
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////////////////////////
/
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/
/
/
ENGINES
////////////////////////
S 118-037-P00
WARNING:
_______
(4)
(5)
(6)
DO NOT GET METHYL
ON YOUR SKIN. DO
PROTECTIVE SPLASH
AWAY FROM SPARKS,
FLAMMABLE SOLVENT
Use a cloth and the MEK to clean the aluminized cover around the
repair area.
S 358-038-P00
Apply the adhesive primer to the repair area.
(a) Let the primer dry for a minimum of 30 minutes at 75 |10°F.
(b) The maximum time for the primer to dry is 2 hours at a relative
humidity of 50% or higher or 4 hours at a relative humidity of
30-49%.
(c) If the primer dries for more than the specified time, remove
the primer with the MEK and apply the primer again.
S 358-039-P00
Mix the adhesive base compound and the catalyst (Fig. 802).
NOTE:
____
(7)
(8)
(9)
ETHYL KETONE (MEK) IN YOUR MOUTH OR EYES, OR
NOT BREATHE THE FUMES FROM MEK. PUT ON A
GOGGLE AND GLOVES WHEN YOU USE MEK. KEEP MEK
FLAME, AND HEAT. MEK IS A POISONOUS AND
WHICH CAN CAUSE INJURY OR DAMAGE.
Use the catalyst concentration that will give a pot life
and a cure time that is sufficient to complete the repair.
S 358-040-P00
Apply the adhesive under all of the aluminized cover around the
repair area that is loose.
S 358-041-P00
Apply the adhesive compound with a thickness of approximately
0.01-0.02 inch to the repair surface and to the silicone patch
material.
S 358-042-P00
Put the patch over the repair area.
(a) Apply a pressure of 2-5 psi and let the adhesive cure.
S 418-043-P00
(10) Close the fan cowl panels (Ref 71-11-04/201).
6.
TASK 71-11-12-358-044-P00
Repair the Insulation That Is Not Attached (Fig. 801)
__________________________________________
A. Consumable Materials
(1) Adhesive - Either of the ones that follow:
(a) A00102 Adhesive - RTV 560, General
Electric Company, Silicone Products
Division; Waterford, NY 12188
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71-11-12
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/
/
/
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(b)
B.
C.
A00578 Adhesive - RTV 60, General Electric
Company, Silicone Products Division,
Waterford, NY 12188
(2) Catalyst - Either of the ones that follow:
(a) A00309 Catalyst A - Dibutyl Tin Dilaurate,
M&T Chemical Corp.; Pico Rivera, CA 90660
(b) A00308 Catalyst B - Tin Octoate,
Tenncco Chemical Inc., Organics & Polymers
Division; Elizabeth, NJ 07201
(3) A00521 Adhesive Primer - Dow Corning 1200,
Dow-Corning Corp; Midland, Michigan 48641
(4) B00378 Solvent - Methyl Ethyl Ketone (MEK),
TT-M-261
(5) G02167 Scotchbrite - Abrasive pads
References
(1) 71-11-04/201, Fan Cowl Panel
Access
(1) Location Zones
413/414
Fan Cowl Panels, Left Engine
423/424
Fan Cowl Panels, Right Engine
(2)
D.
Access Panels
413AL/414AR
423AL/424AR
Fan Cowl Panels, Left Engine
Fan Cowl Panels, Right Engine
Procedure
(1)
(2)
S 018-045-P00
Open the fan cowl panels (Ref 71-11-04/201).
S 358-046-P00
Use a scotchbrite pad to make the silicone surfaces that are not
attached rough.
S 118-047-P00
WARNING:
_______
(3)
(4)
DO NOT GET METHYL
ON YOUR SKIN. DO
PROTECTIVE SPLASH
AWAY FROM SPARKS,
FLAMMABLE SOLVENT
ETHYL KETONE (MEK) IN YOUR MOUTH OR EYES, OR
NOT BREATHE THE FUMES FROM MEK. PUT ON A
GOGGLE AND GLOVES WHEN YOU USE MEK. KEEP MEK
FLAME, AND HEAT. MEK IS A POISONOUS AND
WHICH CAN CAUSE INJURY OR DAMAGE.
Use a cloth and the MEK to clean the repair area.
S 358-048-P00
Where it is necessary, apply the adhesive primer to the nonsilicone
surfaces (the surfaces that are not red).
(a) Let the primer dry for a minimum of 30 minutes at 75 |10°F.
(b) The maximum time for the primer to dry is 2 hours at a relative
humidity of 50% or higher or 4 hours at a relative humidity of
30-49%.
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71-11-12
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Page 812
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MAINTENANCE MANUAL
(c)
(5)
If the primer dries for more than the specified time, remove
the primer with the MEK and apply the primer again.
S 358-049-P00
Mix the adhesive base compound and the catalyst (Fig. 802).
NOTE:
____
(6)
(7)
7.
////////////////////////
/
PW2000 SERIES
/
/
/
ENGINES
////////////////////////
Use the catalyst concentration that will give a pot life
and a cure time that is sufficient to complete the repair.
S 358-050-P00
Apply the adhesive compound with a thickness of 0.01-0.02 inch to
the loose insulation.
(a) Apply a pressure of 2-5 psi and let the adhesive bond
permanently.
S 418-051-P00
Close the fan cowl panels (Ref 71-11-04/201).
TASK 71-11-12-358-052-P00
Insulation Blanket Foil Delamination Repair (Fig. 801)
___________________________________________
A. Consumable Materials
(1) Adhesive - Either of the ones that follow:
(a) A00102 Adhesive - RTV 560, General
Electric Company, Silicone Products
Division; Waterford, NY 12188
(b) A00578 Adhesive - RTV 60, General Electric
Company, Silicone Products Division,
Waterford, NY 12188
(2) Catalyst - Either of the ones that follow:
(a) A00309 Catalyst A - Dibutyl Tin Dilaurate,
M&T Chemical Corp.; Pico Rivera, CA 90660
(b) A00308 Catalyst B - Tin Octoate,
Tenncco Chemical Inc., Organics & Polymers
Division; Elizabeth, NJ 07201
(3) A00521 Adhesive Primer - Dow Corning 1200,
Dow-Corning Corp; Midland, Michigan 48641
(4) B00378 Solvent - Methyl Ethyl Ketone (MEK),
TT-M-261
(5) G02167 Scotchbrite - Abrasive pads
B. References
(1) 71-11-04/201, Fan Cowl Panel
C. Access
(1) Location Zones
413/414
Fan Cowl Panels, Left Engine
423/424
Fan Cowl Panels, Right Engine
(2)
Access Panels
413AL/414AR
423AL/424AR
Fan Cowl Panels, Left Engine
Fan Cowl Panels, Right Engine
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71-11-12
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D.
////////////////////////
/
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/
/
/
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////////////////////////
Procedure
(1)
(2)
S 018-053-P00
Open the fan cowl panels (Ref 71-11-04/201).
S 358-054-P00
Use a scotchbrite pad on the external surface of the aluminized
cover that you will attach the loose cover to rough.
NOTE:
____
This step is for the aluminized cover that is below the
the overlap of a different aluminized cover.
S 118-055-P00
WARNING:
_______
(3)
(4)
(5)
DO NOT GET METHYL
ON YOUR SKIN. DO
PROTECTIVE SPLASH
AWAY FROM SPARKS,
FLAMMABLE SOLVENT
Use a cloth and the MEK to clean the repair area.
S 358-056-P00
Apply the adhesive primer to the repair area.
(a) Let the primer dry for a minimum of 30 minutes at 75 |10°F.
(b) The maximum time for the primer to dry is 2 hours at a relative
humidity of 50% or higher or 4 hours at a relative humidity of
30-49%.
(c) If the primer dries for more than the specified time, remove
the primer with the MEK and apply the primer again.
S 358-057-P00
Mix the adhesive base compound and the catalyst (Fig. 802).
NOTE:
____
(6)
(7)
(8)
ETHYL KETONE (MEK) IN YOUR MOUTH OR EYES, OR
NOT BREATHE THE FUMES FROM MEK. PUT ON A
GOGGLE AND GLOVES WHEN YOU USE MEK. KEEP MEK
FLAME, AND HEAT. MEK IS A POISONOUS AND
WHICH CAN CAUSE INJURY OR DAMAGE.
Use the catalyst concentration that will give a pot life
and a cure time that is sufficient to complete the repair.
S 358-058-P00
Apply the adhesive to the two surfaces to be attached.
S 358-059-P00
Attach the loose cover to the insulation blanket.
(a) Apply a pressure of 2-5 psi and let the adhesive bond
permanently.
S 418-060-P00
Close the fan cowl panels (Ref 71-11-04/201).
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71-11-12
P01
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8.
////////////////////////
/
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/
/
/
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////////////////////////
TASK 71-11-12-358-061-P00
Insulation Blanket Foil Delamination (Adjacent to Starter) Repair (Fig. 801)
_________________________________________________________________
A. Consumable Materials
(1) Patch Material - Glass fabric with the
aluminized cover on one side and silicon coated
on the other side, Hi-Temp Insulation Inc.
(2) Adhesive - Either of the ones that follow:
(a) A00102 Adhesive - RTV 560, General
Electric Company, Silicone Products
Division; Waterford, NY 12188
(b) A00578 Adhesive - RTV 60, General Electric
Company, Silicone Products Division,
Waterford, NY 12188
(3) Catalyst - Either of the ones that follow:
(a) A00309 Catalyst A - Dibutyl Tin Dilaurate,
M&T Chemical Corp.; Pico Rivera, CA 90660
(b) A00308 Catalyst B - Tin Octoate,
Tenncco Chemical Inc., Organics & Polymers
Division; Elizabeth, NJ 07201
(4) A00521 Adhesive Primer - Dow Corning 1200,
Dow-Corning Corp; Midland, Michigan 48641
(5) B00378 Solvent - Methyl Ethyl Ketone (MEK),
TT-M-261
(6) G02167 Scotchbrite - Abrasive pads
B. References
(1) 71-11-04/201, Fan Cowl Panel
C. Access
(1) Location Zones
413/414
Fan Cowl Panels, Left Engine
423/424
Fan Cowl Panels, Right Engine
(2)
D.
Access Panels
413AL/414AR
423AL/424AR
Fan Cowl Panels, Left Engine
Fan Cowl Panels, Right Engine
Procedure
(1)
S 018-062-P00
Open the fan cowl panels (Ref 71-11-04/201).
S 118-063-P00
WARNING:
_______
(2)
DO NOT GET METHYL
ON YOUR SKIN. DO
PROTECTIVE SPLASH
AWAY FROM SPARKS,
FLAMMABLE SOLVENT
ETHYL KETONE (MEK) IN YOUR MOUTH OR EYES, OR
NOT BREATHE THE FUMES FROM MEK. PUT ON A
GOGGLE AND GLOVES WHEN YOU USE MEK. KEEP MEK
FLAME, AND HEAT. MEK IS A POISONOUS AND
WHICH CAN CAUSE INJURY OR DAMAGE.
Use a cloth and the MEK to clean the repair area in and around the
insulation blanket well (Fig. 803).
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71-11-12
P01
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
Page 815
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////////////////////////
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/
/
/
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A
A
ALUMINIZED
COATING PATCH
INSULATION
BLANKET WELL
B
DRAIN HOLE
1.50 INCHES
(EXAMPLE)
1.50 INCHES
(EXAMPLE)
B
ALUMINIZED
PATCH BOND
IN PLACE
FAN COWL
SKIN
VIEW OF THE INNER SIDE OF THE RIGHT FAN COWL PANEL
A-A
INSULATION
BLANKET
B-B
299640
Insulation Blanket Foil Adjacent to Starter
Figure 803
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MAINTENANCE MANUAL
(3)
(4)
(5)
(6)
(7)
S 358-064-P00
Use a scotchbrite pad to make the inner surface of the insulation
blanket well and the area two inches around the well rough.
S 118-065-P00
Use a cloth and the MEK to clean the area again.
S 358-066-P00
Do these steps to prepare a piece of the patch material:
(a) Cut the patch material to extend approximately 1.5 inches out
of the insulation blanket well.
(b) Cut a wedge at each corner to prevent wrinkles when you fold
the edges of the patch material.
S 358-067-P00
Apply the adhesive primer to the repair area.
(a) Let the primer dry for a minimum of 30 minutes at 75 |10°F.
(b) The maximum time for the primer to dry is 2 hours at a relative
humidity of 50% or higher or 4 hours at a relative humidity of
30-49%.
(c) If the primer dries for more than the specified time, remove
the primer with the MEK and apply the primer again.
S 358-068-P00
Mix the adhesive base compound and the catalyst (Fig. 802).
NOTE:
____
(8)
(9)
////////////////////////
/
PW2000 SERIES
/
/
/
ENGINES
////////////////////////
Use the catalyst concentration that will give a pot life
and a cure time that is sufficient to complete the repair.
S 358-069-P00
Apply the adhesive compound with a thickness of approximately
0.01-0.02 inch to the insulation well and to the patch material
(Fig. 803).
S 358-070-P00
Install the patch material in its position.
(a) Apply a pressure of 2-5 psi and let the adhesive bond
permanently.
S 358-071-P00
(10) After the adhesive bonds permanently, cut and remove the patch
material from the drain hole.
S 418-072-P00
(11) Close the fan cowl panels (Ref 71-11-04/201).
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TASK 71-11-12-358-073-P00
Interim Repair (Fig. 801)
______________
A. Consumable Materials
(1) B00602 Solvent - Methyl Ethyl Ketone (MEK),
TT-M-261
(2) G00317 Aluminum Foil Tape (Speed Tape)
3M Y-436
B. References
(1) 71-11-04/201, Fan Cowl Panels
C. Access
(1) Location Zones
413/414
Fan Cowl Panels, Left Engine
423/424
Fan Cowl Panels, Right Engine
(2)
D.
Access Panels
413AL/414AR
423AL/424AR
Fan Cowl Panels, Left Engine
Fan Cowl Panels, Right Engine
Procedure
(1)
S 018-074-P00
Open the fan cowl panels (Ref 71-11-04/201).
S 118-075-P00
WARNING:
_______
DO NOT GET METHYL
ON YOUR SKIN. DO
PROTECTIVE SPLASH
AWAY FROM SPARKS,
FLAMMABLE SOLVENT
ETHYL KETONE (MEK) IN YOUR MOUTH OR EYES, OR
NOT BREATHE THE FUMES FROM MEK. PUT ON A
GOGGLE AND GLOVES WHEN YOU USE MEK. KEEP MEK
FLAME, AND HEAT. MEK IS A POISONOUS AND
WHICH CAN CAUSE INJURY OR DAMAGE.
(2)
Use a cloth and the MEK to clean the damaged area.
(3)
S 358-076-P00
Apply the aluminum foil tape (speed tape) to the damaged area.
(4)
S 418-077-P00
Close the fan cowl panels (Ref 71-11-04/201).
(5)
S 358-078-P00
Replace this interim repair with the applicable permanent repair as
quickly as possible.
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1.
2.
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ENGINE MOUNTS - DESCRIPTION AND OPERATION
_________________________________________
General
_______
A. The forward and aft lower engine mounts hold the engine and are attached
at six locations. The forward engine mount is attached to the rear
flange of the intermediate case at three locations. The aft engine mount
is attached to the double flange on the top of the turbine exhaust case
and at points approximately 35 degrees on the side of the centerline.
The lower engine mounts are made to remove the force of the engine thrust
and the vertical and side loads. The lower engine mounts can become
larger in the axial and radial directions when the temperature increases.
Component Details (Fig. 1)
_________________
A. Forward Lower Engine Mount
(1) The forward lower engine mount holds the engine at three locations:
a shear-pin fitting and two thrust links. The shear pin is
installed into a mating hole in the rear flange of the intermediate
case and held by four bolts. The two thrust links are attached to
the rear flange of the intermediate case on one side of the shear
pin fitting and to the aft end of the mount assembly. The forward
lower engine mount attaches to the strut with four vertical tension
bolts.
B. Aft Lower Engine Mounts
(1) The aft lower engine mount holds the engine at three points on the
double flange of the turbine exhaust case. The aft lower engine
mount includes two tangential links and a center link which attaches
to the same mount fitting. The mount fitting attaches to the strut
with four vertical tension bolts.
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MAINTENANCE MANUAL
SEE
A
SEE
B
FORWARD LOWER
ENGINE MOUNT
FWD
A
AFT LOWER
ENGINE MOUNT
FWD
B
624345
Engine Mounts
Figure 1
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ENGINE MOUNTS
_____________
FIG.
102
SHT QTY
COMPONENT
MOUNT
MOUNT
MOUNT
MOUNT
-
LEFT ENGINE AFT LOWER ENGINE
RIGHT ENGINE AFT LOWER ENGINE
LEFT ENGINE FORWARD LOWER ENGINE
RIGHT ENGINE FORWARD LOWER ENGINE
-----
1
1
1
1
ACCESS/AREA
417AL,418AR,
427AL,428AR,
415AL,416AR,
425AL,426AR,
REFERENCE
CORE COWL
CORE COWL
THRUST REVERSER
THRUST REVERSER
71-21-02
71-21-02
71-21-01
71-21-01
97887
Engine Mounts - Component Index
Figure 101
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FAULT ISOLATION/MAINT MANUAL
FORWARD LOWER
ENGINE MOUNT
SEE
A
CENTER
ATTACHMENT
(REF)
AFT LOWER
ENGINE MOUNT
SEE
B
EVENER
BAR (REF)
FORWARD LOWER
ENGINE MOUNT
THRUST
LINK (REF)
FWD
FORWARD LOWER ENGINE MOUNT
A
AFT LOWER
ENGINE MOUNT
SHEAR PIN
(REF)
TANGENTAL
LINK (REF)
FWD
AFT LOWER ENGINE MOUNT
B
623858
Engine Mounts - Component Location
Figure 102
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ENGINE MOUNT - MAINTENANCE PRACTICES
____________________________________
1.
General
_______
A. This procedure has two tasks, inspect the inner bolts of the engine
thrust link clevis mount and retouque both the inner and outter bolts if
any are loose.
B. Access
(1) Location Zones
410
Left Engine Nacelle
420
Right Engine Nacelle
C.
2.
Procedure:
(1) Examine the inner bolts of the engine thrust link clevis mount.
(a) Bolts with tamper-proof putty:
If the tamper-proof putty on the bolt head and putty on the
clevis mount are not aligned this indicates possible bolt
movement or loosening and is not acceptable.
(b) If loosening is incicated retorque both the inner and outer
clevis mount bolts (AMM 71-21-00/201).
(c) Bolts without tamper-proof putty:
Use an inspection merror and light source to visually inspect
bolts and washers for visible looseness.
(d) If loosening is indicated retorque both the inner and outer
clevis mount bolts (AMM 71-21-00/201).
TASK 71-21-00-422-038-P00
Thrust Link Clevis Mount Bolts Retorque - Special Procedure
____________________________________________________________
A. General
(1) This task is required after any evidence is seen of loosening of the
engine thrust link clevis mount bolts.
B. Access
(1) Location Zones
410
Left Engine Nacelle
420
Right Engine Nacelle
C.
Procedure
(1)
S 022-016-P00
Retorque the bolts which attach the engine thrust link clevis mount
at the location closest to the fan exit case to 190 - 215 in-lbs
(21.47 - 24.29 Nm).
(a) Continue to torque the 4 bolts in a repeated pattern until no
loss of torque occurs.
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MAINTENANCE MANUAL
SEE
A
FORWARD LOWER
ENGINE MOUNT
LEFT CLEVIS
MOUNT
SEE
LEFT THRUST
LINK
B
FWD
A
LEFT CLEVIS
MOUNT
LOCKWIRES
INNER BOLTS
SEE
TWO TURNS
C
BOLT AND
WASHER
(REF)
OUTER BLOTS
RETAINER
(2 LOCATIONS)
FWD
LEFT CLEVIS MOUNT
(RIGHT CLEVIS MOUNT IS OPPOSITE)
C
B
M65559
Engine Thrust Link Clevis Mounts
Figure 201
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(2)
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S 422-040-P00
Retorque the bolts which attach the engine thrust link clevis mount
at the location closest to the HPC case to 575 - 595 in-lbs
(64.96 - 673.22 Nm).
(a) Continue to torque the 4 bolts in a repeated pattern until no
loss of torque occurs.
S 412-039-P00
CAUTION:
_______
(3)
USE ONLY LOCK WIRE TO SAFETY THE CLEVIS BOLTS. ALTERNATIVE
SAFETY MEANS CAN CAUSE THE BOLTS TO LOOSEN AND CAN CAUSE DAMAGE
TO EQUIPMENT.
Satefy the clevis bolt as follows:
(a) Safety the clevis bolts in pairs with lockwire, see Figure 201.
(b) ENGINES WITH PW SB 72-576;
Install a retainer cover over each bolt on the outer edge of
the clevis, see firgure 201.
1) Put the ends of the retainer of a bolt at the upper or
lower edge of the clevis mount and the adjacent bolt
parallel and a short distance apart.
2) Make sure the retainers are in the position shown in figure
201.
3) Make sure the bolt and retainer lockwire holes are aligned.
4) Make sure that the retainers ends do not touch.
NOTE:
____
If the ends of the retainers pouch put them in
new positions until they look like the ones in the
figure.
5)
(c)
Wind lockwire around the ends of the retainers at two
loacations as shown in the figure. Twist the lockwire to
lock the ends of the retainer in position.
Clean inner bolt heads and inner clevis mount flange per SPOP
208.
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(d)
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At each inner clevis mount bolt:
1) Apply a bead of tamper proof putty, PMC 4459, 1/8 inch
minimum width.
a) The bead must extend across the side of each bolt head
and on to the clevis mount flange in one continuous
bead.
NOTE:
____
The appearance of the bead should be such
that any subsequent movement between the bolt
head and the clevis mount flange will be obvious
by visual inspection.
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ENGINE MOUNTS - INSPECTION/CHECK
________________________________
1.
2.
General
_______
A. This procedure has four tasks to examine the engine mounts. These tasks
are shown below in the sequence that they occur:
(1) Dye Penetrant Inspection for the Engine Mount Bolts and the Vertical
Tension Bolts.
(2) Wear Limits for the Engine Mounts.
(3) Vibration Isolator Clearance for the Forward Engine Mount.
(4) Vibration Isolator Clearance for the Aft Engine Mount.
B. You must examine the vertical tension bolts the same as you examine the
engine mount bolts in the procedure that follows.
TASK 71-21-00-236-011-P00
Dye Penetrant Inspection of the Engine Mount Bolts and Vertical Tension Bolts
_____________________________________________________________________________
A. Consumable Materials
(1) B00318 Solvent, Stoddard - ASTM D484-52
(2) E00015 Cloth - Lint-free, dry
(3) Penetrant Inspection Materials
B00398 SKC-W cleaner emulsifier
G02033 SKD-NF developer
G02036 SKL-HF penetrant
Magnaflux Corp., Chicago, Illinois or Turco WWI
penetrant and DY developer, Turco Products
Inc., Division of Purex Co., Wilmington, CA
B. References
(1) AMM 71-21-01/401, Forward Lower Engine Mount
(2) AMM 71-21-02/401, Aft Lower Engine Mount
C. Access
(1) Location Zones
410
Left Engine Nacelle
420
Right Engine Nacelle
D.
Do the Dye Penetrant Inspection of the Engine Mount Bolts and Vertical
Tension Bolts.
NOTE:
____
The procedure which follows is included for an available
procedure. All industry standard procedures of dye penetrant
inspection are permitted.
(1)
S 026-012-P00
Remove the engine mount bolts and vertical tension bolts from the
applicable engine mount (AMM 71-21-01/401 or AMM 71-21-02/401).
(2)
S 116-013-P00
Use a solvent to clean the dirt, oil and grease from the engine
mount bolts and vertical tension bolts.
(3)
S 116-014-P00
Blow dry the engine mount bolts and vertical tension bolts.
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(4)
(5)
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S 236-015-P00
If the SKL-HF (magnaflux) penetrant is used, do the steps that
follow:
(a) Apply the SKC-W Cleaner Emulsifier to the engine mount bolts
and vertical tension bolts.
(b) Wash the engine mount bolts and vertical tension bolts with
water.
S 236-016-P00
Apply the dye penetrant onto the engine mount bolts and vertical
tension bolts.
NOTE:
____
Use the SKL-HF (magnaflux) (used with the SKD-NF
developer) or the Turco WWI (used with the DY Check
developer).
(6)
S 236-017-P00
Permit the dye penetrant to set for approximately five to six
minutes.
(7)
S 236-018-P00
If the SKL-HF (magnaflux) Penetrant is used, apply the SKC-W Cleaner
Emulsifier, again, to the bolts which are examined.
(8)
S 236-019-P00
Apply clean water for a time of 30-45 seconds to wash the engine
mount bolts and vertical tension bolts.
(9)
S 236-020-P00
Blow air on the engine mount bolts and vertical tension bolts for
two to three minutes.
S 236-021-P00
(10) Apply the applicable dye developer to the engine mount bolts and
vertical tension bolts.
(a) Continue to blow air on the engine mount bolts and vertical
tension bolts to dry the dye developer slowly.
S 236-022-P00
(11) Examine the engine mount bolts and vertical tension bolts for
cracks.
S 236-023-P00
(12) If no signs of cracks are found, do the steps that follow:
(a) Flow clean water on the bolts for two to three minutes to wash
off the dye penetrant and dye developer.
(b) Dry the engine mount bolts and vertical tension bolts with air
or with a clean cloth.
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S 426-024-P00
(13) Install the engine mount bolts and vertical tension bolts in the
applicable engine mount (AMM 71-21-01/401 or AMM 71-21-02/401).
3.
TASK 71-21-00-226-025-P00
Wear Limits for the Engine Mounts (Fig. 601)
_________________________________
A. General
(1) This task makes sure the shear pins and the bolts that attach the
mounts to the engine are not too worn. It is necessary to remove
the engine mounts to do this task.
B. References
(1) AMM 54-51-01/601, Strut, Inspection Check
(2) SRM 54-51-90, Strut Fitting Repair
(3) AMM 71-21-01/401, Lower Forward Engine Mount
(4) AMM 71-21-02/401, Lower Aft Engine Mount
C. Access
(1) Location Zones
410
Left Engine Nacelle
420
Right Engine Nacelle
D.
Procedure
(1)
(2)
S 026-026-P00
Remove the forward engine mount (AMM 71-21-01/401) and the aft
engine mount (AMM 71-21-02/401).
S 226-027-P00
Measure the dimensions that follow:
(a) The diameter of the shear pins (1 and 4) and the internal
diameter of the shear pin bushings for the forward and the aft
mounts.
(b) The diameter of the thrust link bolts (2) and the internal
diameter of the thrust link bearing for the forward mount.
(c) The diameter of the center link bolts (3) and the internal
diameter of the center link bearings for the aft mount.
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1. SHEAR PIN
SEE
A
FORWARD LOWER
ENGINE MOUNT
2. BOLT
(2 PLACES)
THRUST LINK
ENGINE CASE
A
4. SHEAR PIN
SEE
AFT ENGINE
MOUNT
B
FWD
ENGINE
5. BOLT
CASE
(2 PLACES)
3. BOLT
TANGENTIAL LINK
(2 PLACES)
B
624358
Engine Mount Wear Limits
Figure 601 (Sheet 1)
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MAINTENANCE MANUAL
DESIGN LIMITS
INDEX
NO.
PART NAME
BUSHING
DIM.
ID
DIAMETER
MIN
MAX
1.2500
1.2515
WEAR LIMITS
PERMAX
MITTED
DIA
WEAR
CLEARDIM.
ANCE
REPLACE REPAIR
REPAIR
WORN
WORN
INSTR
PART
PART
X
1.2537
0.0057
1
SHEAR PIN
OD
1.2480
1.2585
1.2458
BEARING
ID
0.8745
0.8750
0.8769
X
1
X
1
X
1
X
1
X
1
X
0.008
2
BOLT
OD
0.8730
0.8740
0.8711
BEARING
ID
1.1245
1.1250
1.1271
3
4
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X
0.008
BOLT
OD
1.1230
1.1240
1.1209
BUSHING (AFT)
ID
0.7670
0.7680
0.7697
BUSHING (FWD)
ID
0.7495
0.7505
0.7522
X
0.024
X
0.0067
SHEAR PIN
OD
0.7455
0.7460
0.7438
BEARING
ID
1.1245
1.1250
1.1271
5
BOLT
1
X
0.008
OD
1.1230
1.1240
1.1209
STRIP CHROMIUM PLATE.
REPLACE WITH CHROMIUM.
POST-PLATE GRIND TO DESIGN LIMITS.
SINGLE PLATE THICKNESS MUST BE A MINIMUM OF 0.003 INCH AFTER GRINDING.
177444
Engine Mount Wear Limits
Figure 601 (Sheet 2)
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(d)
(3)
The diameter of the tangential link bolts (5) and the internal
diameter of the tangential link bearings for the aft mount.
S 226-028-P00
Make sure the dimensions from the steps above are in the specified
limits.
(a) Replace the parts that are not in the specified limits
(AMM 54-51-01/601 or SRM 54-51-90).
NOTE:
____
(4)
4.
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You can repair the shear pins (1 and 4), the thrust link
bolts (2), the center link bolts (3), and the tangential
link bolts (5).
S 426-029-P00
Install the forward engine mount (AMM 71-21-01/401) and the aft
engine mount (AMM 71-21-02/401).
TASK 71-21-00-226-030-P00
Vibration Isolator Clearance for the Forward Engine Mount (Fig. 602)
_________________________________________________________
A. General
(1) This task does a check of the vibration isolator clearance for the
forward engine mount. This task is done with the engine installed
on the airplane.
B.
C.
References
(1) AMM 71-11-04/201, Fan Cowl Panels
(2) AMM 71-11-06/201, Core Cowl Panels
(3) AMM 71-21-01/401, Lower Forward Engine Mount
(4) AMM 71-21-03/401, Forward Engine Mount Isolator
(5) AMM 78-31-00/201, Thrust Reverser System
Access
(1) Location Zones
411
Left Engine
421
Right Engine
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SEE A
FORWARD ENGINE
MOUNT ISOLATOR
SEE
B
1. FORWARD LOWER
ENGINE MOUNT
THRUST LINK
ENGINE CASE
A
C75015
Forward Engine Mount Isolator
Figure 602 (Sheet 1)
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SEE
C
+0.07 MAX
0.06
(EXAMPLE)
(REF)
-0.07 MAX
NOTE:
____ SCALE DRIFT INDICATOR
LINES FROM TOP OF LINES
FOR POSITIVE STEP AND
FROM BOTTOM OF LINES
FOR NEGATIVE STEP.
FWD
C
B
1
0.06 INCH MINIMUM
OUTBOARD SIDE
RULER
ELASTOMER
NOTE:
____
THE INNER COMPONENT OF
COMES OUT OF THE FRONT
WITH THE SCALE AGAINST
COMPONENT, MEASURE THE
THE ELASTOMER.
THE ISOLATOR
ENGINE MOUNT.
THE INNER
GAP ACROSS
1
ENGINES WITH SB 757-71-037
2
ENGINES WITHOUT SB 757-71-037
OUTBD
B
2
736009
Forward Engine Mount Isolator
Figure 602 (Sheet 2)
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MAINTENANCE MANUAL
(2)
D.
Access Panels
413AL/414AR
415AL/416AR
417AL/418AR
423AL/424AR
425AL/426AR
427AL/428AR
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Fan Cowl Panels, Left Engine
Thrust Reversers, Left Engine
Core Cowl Panels, Left Engine
Fan Cowl Panels, Right Engine
Thrust Reversers, Right Engine
Core Cowl Panels, Right Engine
Procedure
(1)
S 016-031-P00
Open the fan cowl panels (AMM 71-11-04/201).
S 046-032-P00
WARNING:
_______
(2)
(3)
DO THE THRUST REVERSER DEACTIVATION PROCEDURE TO PREVENT THE
OPERATION OF THE THRUST REVERSER. THE ACCIDENTAL OPERATION OF
THE THRUST REVERSER CAN CAUSE INJURIES TO PERSONS OR DAMAGE TO
EQUIPMENT.
Do this procedure: Thrust Reverser Deactivation for Ground
Maintenance (AMM 78-31-00/201).
S 016-033-P00
Open the core cowl panels (AMM 71-11-06/201).
S 016-034-P00
WARNING:
_______
(4)
(5)
(6)
OBEY THE INSTRUCTIONS IN AMM 78-31-00/201 WHEN YOU OPEN THE
THRUST REVERSERS. IF YOU DO NOT OBEY THE INSTRUCTIONS, YOU CAN
CAUSE INJURIES TO PERSONS OR DAMAGE TO EQUIPMENT.
Open the thrust reversers (AMM 78-31-00/201).
S 226-035-P00
ON ENGINES WITHOUT SB 757-71-0037;
measure the clearance between the inner and outer metal components
of the vibration isolator (across the top outboard elastomer).
(a) If the clearance is less than 0.06 inch, replace the vibration
isolator the next time the engine is removed
(AMM 71-21-03/401).
S 226-046-P00
ON ENGINES WITH SB 757-71-0037;
measure the clearance between the indicator lines located on the
sides of the inner and outer members of the vibration isolator.
NOTE:
____
Clearance measurements are taken from either the top of both
indicator lines or from the bottom of both indicator lines.
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(a)
E.
If the clearance is greater than 0.07 inch, replace the
vibration isolator the next time the engine is removed
(AMM 71-21-03/401).
(b) Examine the shim packs for worn, delaminated or missing shims.
1) If the shims are worn, delaminated, or missing, remove the
complete shim pack from the location that has damage.
2) Examine the cowling, compressor case and engine stator vane
system components for loose shims.
3) Replace the vibration isolator the next time the engine is
removed (AMM 71-21-03/401).
Put the airplane back to its initial condition.
S 416-036-P00
WARNING:
_______
5.
OBEY THE INSTRUCTIONS IN AMM 78-31-00/201 WHEN YOU CLOSE THE
THRUST REVERSERS. IF YOU DO NOT OBEY THE INSTRUCTIONS, YOU CAN
CAUSE INJURIES TO PERSONS OR DAMAGE TO EQUIPMENT.
(1)
Close the thrust reversers (AMM 78-31-00/201).
(2)
S 416-037-P00
Close the core cowl panels (AMM 71-11-06/201).
(3)
S 416-039-P00
Close the fan cowl panels (AMM 71-11-04/201).
TASK 71-21-00-226-040-P00
Vibration Isolator Clearance for the Aft Engine Mount (Fig. 603)
_____________________________________________________
A. General
(1) This task does a check of the vibration isolator clearance for the
aft engine mount. This task is done with the engine installed on
the airplane.
(2) The vibration isolator clearance is an indication of the condition
of the elastomer in the isolator. If the vibration isolator
clearance is more than 0.040 inch at the inboard stop, the isolator
can provide some noise control. It does not make a difference what
the clearance is at the outboard stop.
B. References
(1) AMM 71-21-02/401, Aft Lower Engine Mount
(2) AMM 78-31-00/201, Thrust Reverser System
C. Access
(1) Location Zones
410
Left Engine Nacelle
420
Right Engine Nacelle
D.
Procedure
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A
757
MAINTENANCE MANUAL
SEE
A
BOLT
(10 LOCATIONS
ON EACH SIDE)
AFT SKIRT FAIRING
(ONE ON EACH SIDE)
BOLT
(3 LOCATIONS
ON EACH SIDE)
A
SEE
B
OUTER
ELASTOMER
SKIN
TOP PLATE
THE CLEARANCE BETWEEN THE TORQUE
TUBE LUGS AND THE TOP PLATE DOWN
STOPS HAS A 0.040 INCH (1.106 mm)
MINIMUM ON THE INBOARD SIDE.
TORQUE TUBE
ASSEMBLY
FWD
B
962967
Aft Engine Mount Inspection
Figure 603
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MAINTENANCE MANUAL
S 046-041-P00
WARNING:
_______
(1)
(2)
(3)
DO THE DEACTIVATION PROCEDURE TO PREVENT THE OPERATION OF THE
THRUST REVERSERS. THE ACCIDENTAL OPERATION OF THE THRUST
REVERSERS CAN CAUSE INJURIES TO PERSONS AND DAMAGE TO
EQUIPMENT.
Do the deactivation procedure for the thrust reverser for ground
maintenance (AMM 78-31-00/201).
S 016-042-P00
Remove the aft skirt fairing above the inboard core cowl panel.
S 226-043-P00
Measure the clearance between the torque tube lug and the top plate
downstop on the inboard side of the aft mount.
(a) If the clearance is less than 0.040 inch, replace the aft mount
the next time the engine is removed (AMM 71-21-02/401).
NOTE:
____
(4)
(5)
After the mount has been removed, refer to the Lord
Bulletin No. SM-6410A.
S 416-044-P00
Install the aft skirt fairing on the inboard side of the engine.
S 446-045-P00
Do the activation procedure for the thrust reverser
(AMM 78-31-00/201).
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FORWARD LOWER ENGINE MOUNT - REMOVAL/INSTALLATION
_________________________________________________
1.
2.
General
_______
A. There are two tasks in this procedure. The first task is the removal of
the forward lower engine mount. The second task is the installation of
the forward lower engine mount.
B. The forward lower engine mount attaches to the intermediate case rear
flange with a shear pin fitting and two thrust links. You must remove
the engine before you remove the mount.
TASK 71-21-01-004-001-P00
Forward Lower Engine Mount Removal (Fig. 401)
__________________________________
A. References
(1) AMM 71-00-02/401, Power Plant
B. Access
(1) Location Zones
411
Left Engine
421
Right Engine
C.
Procedure
(1)
3.
S 024-002-P00
Remove the power plant (AMM 71-00-02/401).
(2)
S 034-003-P00
Remove the bolts (4) that attach the thrust links to the engine
case.
(3)
S 024-004-P00
Remove the bolts (2) and the washers (3) to remove the mount (1)
from the engine.
TASK 71-21-01-404-005-P00
Forward Lower Engine Mount Installation (Fig. 401)
_______________________________________
A. Consumable Materials
(1) D00010 Antiseize Compound - Bostick Never-Seez
B. Parts
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A
2. BOLT
(4 LOCATIONS)
3. WASHER
(4 LOCATIONS)
1. FORWARD LOWER
ENGINE MOUNT
4. BOLT
(2 LOCATIONS)
5. WASHER
(2 LOCATIONS)
6. WASHER
(2 LOCATIONS)
THRUST LINK
ENGINE CASE
7. NUT
(2 LOCATIONS)
A
M33864
Forward Lower Engine Mount Installation
Figure 401
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~¼¼¼¼¼¼¼¼¼¼¼¼¼¼ ¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼ ¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼
¦
AMM
¦
¦
AIPC
¦
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»¼¼¼¼¼¼¼¼¼¼¼¼ ¼¼¼¼¼¼¼¼ ¼¼¼¼¼¼¼¼«
¦ FIG ¦ ITEM ¦
NOMENCLATURE
¦ SUBJECT
¦ FIG
¦ ITEM ¦
»¼¼¼¼¼î¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼«
¦ 401 ¦
1
¦ Mount Assy
¦ 71-21-02 ¦
02
¦
280 ¦
¦
¦
2
¦ Bolt
¦
¦
¦
270, ¦
¦
¦
¦
¦
¦
¦
272 ¦
¦
¦
3
¦ Washer
¦
¦
¦
275 ¦
¦
¦
4
¦ Bolt
¦
¦
¦
250 ¦
¦
¦
5
¦ Washer
¦
¦
¦
255 ¦
¦
¦
6
¦ Washer
¦
¦
¦
260 ¦
¦
¦
7
¦ Nut
¦
¦
¦
265 ¦
²¼¼¼¼¼…¼¼¼¼¼¼¼¼…¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼…¼¼¼¼¼¼¼¼¼¼¼¼…¼¼¼¼¼¼¼¼…¼¼¼¼¼¼¼¼¹
C.
D.
E.
References
(1) AMM 71-00-02/401, Power Plant
Access
(1) Location Zones
411
Left Engine
421
Right Engine
Procedure
(1)
(2)
(3)
(4)
(5)
S 644-006-P00
Apply the antiseize compound to the bolts (2).
S 424-008-P00
Put the engine mount (1) in its position and align the bearing
housing with the bolt holes in the engine flange.
S 434-009-P00
Attach the engine mount (1) to the engine flange with the bolts (2)
and the washers (3).
(a) Tighten the bolts to 600-700 pound-inches (67.80-79.10
newton-meters).
(b) Install a lockwire to the bolts.
S 434-010-P00
Attach the thrust links to the engine flange with the bolts (4), the
washers (5), the washers (6), and the nuts (7).
(a) Make sure the run-on torque is 60-300 pound-inches (6.78-33.90
newton-meters).
1) If the run-on torque is not in the specified limits,
replace the nuts (7).
(b) Tighten the nuts to a finish torque of 660-980 pound-inches
(74.58-110.74 newton-meters).
S 424-011-P00
Install the power plant (AMM 71-00-02/401).
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AFT LOWER ENGINE MOUNT - REMOVAL/INSTALLATION
_____________________________________________
1.
2.
General
_______
A. There are two tasks in this procedure. The first task is the removal of
the aft lower engine mount. The second task is the installation of the
aft lower engine mount.
B. The aft lower engine mount attaches to the double flanges on the exhaust
case of the engine. You must remove the engine before you can remove the
aft lower engine mount.
TASK 71-21-02-004-001-P00
Aft Lower Engine Mount Removal (Fig. 401)
______________________________
A. References
(1) AMM 71-00-02/401, Power Plant
B. Access
(1) Location Zones
411
Left Engine
421
Right Engine
C.
Procedure
(1)
(2)
S 034-003-P00
Remove the bolt (1), the washers (2 and 7), and the nut (8) from the
mount.
(3)
S 034-004-P00
Remove the bolt (3), the washers (4 and 6), and the nut (9) from the
engine flange.
(4)
S 034-005-P00
Remove the bolts (16), the washers (17 and 12), and the nuts (11)
from the mount.
(5)
S 034-006-P00
Remove the bolts (15), the washers (14 and 13), and the nuts (10)
from the engine case.
(6)
3.
S 024-002-P00
Remove the power plant (AMM 71-00-02/401).
S 024-007-P00
Remove the aft lower engine mount (5).
TASK 71-21-02-404-008-P00
Aft Lower Engine Mount Installation (Fig. 401)
___________________________________
A. Consumable Materials
(1) D00010 Antiseize Compound - Bostick Never-Seez
B. Parts
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MAINTENANCE MANUAL
SEE
A
5. AFT ENGINE
MOUNT
8. NUT
FWD
7. WASHER
11. NUT
(2 LOCATIONS)
6. WASHER
3. BOLT
9. NUT
12. WASHER
(2 LOCATIONS)
14. WASHER
(2 LOCATIONS)
10. NUT
(2 LOCATIONS)
4. WASHER
2. WASHER
16. BOLT
(2 LOCATIONS)
1. BOLT
TANGENTIAL LINK
(2 LOCATIONS)
13. WASHER
(2 LOCATIONS)
17. WASHER
15. BOLT
(2 LOCATIONS)
(2 LOCATIONS)
A
624354
Aft Lower Engine Mount Installation
Figure 401
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~¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼ ¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼ ¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼
¦
AMM
¦
¦
AIPC
¦
»¼¼¼¼¼ ¼¼¼¼¼¼¼¼¼«
»¼¼¼¼¼¼¼¼¼¼ ¼¼¼¼¼¼ ¼¼¼¼¼¼¼¼«
¦ FIG ¦ ITEM
¦
NOMENCLATURE
¦ SUBJECT ¦ FIG ¦ ITEM ¦
»¼¼¼¼¼î¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼î¼¼¼¼¼¼¼¼«
¦ 401 ¦
1
¦ Bolt
¦ 71-21-02 ¦ 02 ¦
5
¦
¦
¦
2
¦ Washer
¦
¦
¦
15
¦
¦
¦
3
¦ Bolt
¦
¦
¦
10
¦
¦
¦
4
¦ Washer
¦
¦
¦
20
¦
¦
¦
5
¦ Mount Assy
¦
¦
¦
45
¦
¦
¦
6
¦ Washer
¦
¦
¦
30
¦
¦
¦
7
¦ Washer
¦
¦
¦
25
¦
¦
¦
8
¦ Nut
¦
¦
¦
35
¦
¦
¦
9
¦ Nut
¦
¦
¦
40
¦
¦
¦
10
¦ Nut
¦
¦
¦
40
¦
¦
¦
11
¦ Nut
¦
¦
¦
35
¦
¦
¦
12
¦ Washer
¦
¦
¦
25
¦
¦
¦
13
¦ Washer
¦
¦
¦
30
¦
¦
¦
14
¦ Washer
¦
¦
¦
20
¦
¦
¦
15
¦ Bolt
¦
¦
¦
10
¦
¦
¦
16
¦ Bolt
¦
¦
¦
5
¦
¦
¦
17
¦ Washer
¦
¦
¦
15
¦
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C.
D.
E.
References
(1) AMM 71-00-02/401, Power Plant
Access
(1) Location Zones
411
Left Engine
421
Right Engine
Procedure
(1)
S 644-009-P00
Apply the antiseize compound to the threads of the bolts
(1, 3, 15, and 16).
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(2)
S 424-011-P00
Put the aft engine mount (5) in its position between the flanges on
the engine case.
(3)
S 434-012-P00
Install the bolts (15) and the washers (14) through the tangential
links and the engine flanges.
NOTE:
____
(a)
(b)
Install the bolt from the aft side of the engine mount.
(4)
Install the washers (13) and the nuts (10) on the bolts (15).
Do one of these steps to tighten the bolts (15):
1) Recommended procedure - Tighten the nut (10) to 2600-3400
pound-inches (293.80-384.20 newton-meters), but do not turn
the bolt (15).
2) Optional procedure - Tighten the bolt (15) to 3060-3740
pound-inches (345.78-422.62 newton-meters).
S 434-013-P00
Install the bolt (3) and the washer (4) through the center link and
the engine flanges.
NOTE:
____
(a)
(b)
(5)
(6)
(7)
Install the bolt from the aft side of the engine mount.
Install the washer (6) and the nut (9) on the bolt (3).
Do one of these steps to tighten the bolt (3):
1) Recommended procedure - Tighten the nut (9) to 2600-3400
pound-inches (293.80-384.20 newton-meters), but do not turn
the bolt (3).
2) Optional procedure - Tighten the bolt (3) to 3060-3740
pound-inches (345.78-422.62 newton-meters).
S 434-014-P00
Install the bolt (16) with the washer (17) through the bolt (15).
(a) Install the washer (12) and the nut (11).
(b) Tighten the nut (11) to 90-125 pound-inches (10.17-14.13
newton-meters), but do not turn the bolt (16).
S 434-015-P00
Install the bolt (1) with the washer (2) through the bolt (3).
(a) Install the washer (7) and the nut (8) on the bolt (1).
(b) Tighten the nut (8) to 90-125 pound-inches (10.17-14.13
newton-meters), but do not turn the bolt (1).
S 424-016-P00
Install the power plant (AMM 71-00-02/401).
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757
MAINTENANCE MANUAL
1.
2.
FORWARD ENGINE MOUNT ISOLATOR - REMOVAL/INSTALLATION
____________________________________________________
General
_______
A. There are two tasks in this procedure. The first task is the removal of
the forward engine mount isolator. The second task is the installation
of the forward engine mount isolator.
B. The forward engine mount isolator attaches to the intermediate case rear
flange. You must remove the engine and the forward lower engine mount
before you remove the isolator.
TASK 71-21-03-024-012-P00
Removal of the Forward Engine Mount Isolator (Fig. 401)
_______________________________________________________
A. Equipment
(1) Spanner Wrench - F72959-41
B. References
(1) AMM 71-21-01/401, Foward Lower Engine Mount
(2) CMM 71-21-15/301, Disassembly
C. Access
(1) Location Zones
411
Left Engine
421
Right Engine
D.
Procedure
(1)
(2)
S 024-002-P00
Remove the forward lower engine mount (AMM 71-21-01/401).
S 034-003-P00
Remove the inner and outer collars from the forward engine mount
(CMM 71-21-15/301).
NOTE:
____
(3)
3.
The inner collar has counterclockwise (left) threads.
S 024-004-P00
Remove the isolator assembly from the forward engine mount
(CMM 71-21-15/301).
TASK 71-21-03-424-013-P00
Installation of the Forward Engine Mount Isolator (Fig. 401)
____________________________________________________________
A. Equipment
(1) F72959 - Spanner Wrench
B. References
(1) AMM 71-21-01/401, Forward Lower Engine Mount
(2) CMM 71-21-15/701, Assembly
C. Access
(1) Location Zones
411
Left Engine
421
Right Engine
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A
FORWARD ENGINE
MOUNT ISOLATOR
SEE
B
FORWARD LOWER
ENGINE MOUNT
THRUST LINK
ENGINE CASE
A
ISOLATOR
ASSEMBLY
FORWARD ENGINE
MOUNT BEAM
INNER
COLLAR
OUTER COLLAR
B
M33865
Forward Engine Mount Isolator Installation
Figure 401
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Procedure
(1)
(2)
S 214-014-P00
Examine the forward engine mount beam for signs of worn areas.
S 424-016-P00
If the engine mount beam is not damaged, install the isolator
assembly as follows (CMM 71-21-15/701):
(a) Install the isolator assembly on the forward engine mount beam
with the larger outer diameter installed toward the beam
shoulder.
(b) Make sure the inner and outer threads on the end of the beam
are clean.
(c) Do not apply antiseize compound to the beam threads.
(d) Install the outer collar on the mount beam. Do this until the
forward face of the outer collar is aft of the mount beam
forward end.
(e) Install the inner collar on the mount beam and tighten it to
200-500 pound-inches (22.60-56.50 newton meters) using the
spanner wrench.
NOTE:
____
(f)
(g)
Rotate the outer collar until it contacts the flange of the
inner collar.
Use the spanner wrench to tignten the outer collar to the inner
collar to a torque of 100-300 pound-inches (11.30-33.90 newton
meters).
NOTE:
(h)
(3)
The inner collar has counterclockwise (left) threads.
Make sure the lockwire holes in the two collars align.
Lockwire the two collars together using the double twist method
across the diameter of the collars.
S 424-015-P00
Install the forward lower engine mount (AMM 71-21-01/401).
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ENGINE WIRE HARNESS - ADJUSTMENT/TEST
_____________________________________
1.
2.
General
_______
A. This procedure gives the steps to do two tests. These these are for the
electrical harnesses on the power plant which do not have cables with the
external braid. One test is the circuit continuity test. The other test
is the wire insulation test. These test are followed by steps to connect
the connectors.
B. If you find damage on the engine wire harnesses, repair the harnesses
(AMM 71-51-00/801).
TASK 71-51-00-765-001-P00
Examine the Engine Wire Harnesses
_________________________________
A. Equipment
(1) Ohmmeter - Simpson 260 (or equivalent):
Simpson Electric Co., 853 Dundee Ave.,
Elgin, IL 60120-3090, USA
(2) Wrench - Glenair TG-70 (or equivalent):
Glenair Inc., 1211 Air Way,
Glendale, CA 91202, USA
(3) Wrench, Strap - Daniels BT - BS - 611 (or equivalent):
Daniels Manufacturing Corp., 6103 Anno Ave.,
Orlando, FL 32809-5033, USA
(4) Pliers, Connector Soft Jaw - Glenair TG-69 (or equivalent):
Glenair Inc., 1211 Air Way,
Glendale, CA 91202, USA
B. References
(1) AMM 24-22-00/201, Electrical Power - Control
(2) AMM 71-11-04/201, Fan Cowl Panels
(3) AMM 71-11-06/201, Core Cowl Panels
(4) AMM 78-31-00/201, Thrust Reverser System
C. Access
(1) Location Zones
211/212
Flight Compartment
411/421
Left and Right Engines
(2)
D.
Access Panels
413/414
415/416
417/418
423/424
425/426
427/428
Fan Cowl Panels, Left Engine
Thrust Reversers, Left Engine
Core Cowl Panels, Left Engine
Fan Cowl Panels, Right Engine
Thrust Reversers, Right Engine
Core Cowl Panels, Right Engine
Prepare to do the Engine Wire Harness - Adjustment/Test
(1)
S 015-002-P00
Open the fan cowl panels (AMM 71-11-04/201).
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S 045-003-P00
WARNING:
_______
(2)
(3)
DO THE DEACTIVATION PROCEDURE TO PREVENT THE OPERATION OF THE
THRUST REVERSERS. THE ACCIDENTAL OPERATION OF THE THRUST
REVERSERS CAN CAUSE INJURIES TO PERSONS AND DAMAGE TO
EQUIPMENT.
Do the deactivation procedure for the thrust reverser for ground
maintenance (AMM 78-31-00/201).
S 015-004-P00
Open the core cowl panels (AMM 71-11-06/201).
S 015-005-P00
WARNING:
_______
OBEY THE INSTRUCTIONS IN THE PROCEDURE TO OPEN THE THRUST
REVERSERS. IF YOU DO NOT OBEY THE INSTRUCTIONS, INJURIES TO
PERSONS AND DAMAGE TO EQUIPMENT CAN OCCUR.
(4)
Open the thrust reversers (AMM 78-31-00/201).
(5)
S 865-006-P00
Remove the electrical power (AMM 24-22-00/201).
S 865-007-P00
Make sure that the engine has been stopped for a minimum of 5
minutes.
Do the Wire Harness Circuit Continuity Test
(6)
E.
(1)
S 765-008-P00
Disconnect the two wire harness connectors which attach to the ends
of the circuit that you do a check.
NOTE:
____
(2)
(3)
Use a TG -70 or BT-BS-611 strap wrench, or equivalent
(Fig. 501). The rubber strap on the strap wrench will not
hold the backshell if you apply too much force.
S 485-009-P00
Attach an ohmmeter test lead to the connector contacts at each end
of the circuit.
S 765-010-P00
Measure the resistance of the circuit.
NOTE:
____
(a)
If the shield resistance value is necessary, attach the
ohmmeter leads to the connectors.
The circuit must have continuity.
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ADAPTER
BACKSHELL
MASTER KEY
CONNECTOR
BT-BS-611
STRAP WRENCH
BACKSHELL
CONNECTOR
TG-69 SOFT
NOSE PLIERS
TG-70
STRAP WRENCH
D00532
Backshell and Connector Tools
Figure 501
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F.
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S 085-011-P00
Remove the ohmmeter leads from the harness connectors.
Do the Wire Harness Wire Insulation Check.
S 765-013-P00
CAUTION:
_______
DO NOT USE A MEGOHMMETER FOR THE INSULATION RESISTANCE TEST OF
THE ON-WING WIRE REPAIR. THIS COULD RESULT IN INJURY TO
PERSONS OR DAMAGE TO THE AIRPLANE
CAUTION:
_______
YOU MUST DISCONNECT ALL THE CONNECTORS ON THE CIRCUIT WHICH YOU
WILL DO THE CHECK. IF YOU DO NOT DO THIS, YOU CAN CAUSE
UNSATISFACTORY RESISTANCE INDICATIONS AND POSSIBLE DAMAGE TO
THE CIRCUITS.
(1)
Disconnect the wire harness connectors which attach to the ends of
the circuits that you will test.
NOTE:
____
(2)
Use a TG-70 or BT-BS-611 strap wrench, or equivalent
(Fig. 501).
S 765-014-P00
Do the steps that follow to do a test of the insulation resistance:
(a) Put the ohmmeter at the 100K ohms scale.
(b) Attach a ohmmeter test lead to the connector contact (pin or
socket) of each of the wires that you will test.
(c) Connect the other test lead to the braided shield.
(d) Measure the resistance.
NOTE:
____
(e)
The circuit resistance must be infinity.
Do the procedure again for the other wires that you will test.
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(f) Remove the ohmmeter leads.
Connector/Receptacle Connection
(1)
S 415-021-P00
Connect the connectors to the receptacles.
(a) Align the master key on the connector with the master key-way
for the receptacle.
(b) Engage the connector to the receptacle with light hand
pressure.
(c) Connect and tighten the connector coupling nut in a clockwise
direction on the receptacle (Fig. 502 or 503).
NOTE:
____
(d)
Make sure the threads and contacts are correctly
engaged.
Push the connector into the receptacle while you move the
connector from one side to the other side.
CAUTION:
_______
(e)
(f)
DO NOT USE A METAL TOOL TO TIGHTEN OR TORQUE THE ALUMINUM
CONNECTORS. THIS MAY DAMAGE THE CONNECTORS.
Continue to tighten the coupling nut by hand until it is tight.
For connectors that have a self-locking coupling nut, make sure
the visual indicator band does not show (Fig. 503).
NOTE:
____
(g)
The visual indicator band on the receptacle is not a
stop line. The leading edge of the connector knurled
nut must go over the top of the indicator band. If you
see the band, the connector is not installed correctly.
If access to the receptacle is not easy, use a TG-70 or
BT-BS-611 strap wrench, or equivalent (Fig. 501).
For connectors that do not have a self-locking coupling nut, do
as follows:
1) Tighten the connector coupling nut to the receptacle until
the metal of the coupling nut touches the metal of the
connector.
NOTE:
____
Use a TG-70 or BT-BS-611 strap wrench, or
equivalent (Fig. 501). The rubber strap on the
strap wrench will not hold the backshell if you
apply too much force.
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BRAIDED SHIELD
CONICAL RING
BACKSHELL BODY
RED RUBBER TAPE
BACKSHELL
COUPLING NUT
STRAIN
RELIEF BODY
STRAIN RELIEF
CLAMP BARS
ALUMINUM BACKSHELL ASSEMBLY
LOCKWIRE
(4 LOCATIONS)
LOCKWIRE
(4 LOCATIONS)
LOCKWIRE INSTALLATION
D00558
Aluminum Backshell Assembly and Lockwire
Figure 502
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BACKSHELL
COUPLING NUT
BACKSHELL
BODY
HOSE
CLAMP
STRAIN RELIEF
CLAMP
(2 LOCATIONS)
RED RUBBER
TAPE
BRAIDED SHIELD
(2 LOCATIONS)
CONNECTOR
D00559
Stainless Steel Backshell Assembly
Figure 503
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For the connectors with the aluminum backshells, lockwire
the backshell, the strain-relief clamp assembly, and the
screws, as necessary (Fig. 502).
NOTE:
____
Lockwire is not required for the stainless steel
backshells and connector coupling nuts that are
self-locking.
3)
H.
Lockwire all the connector coupling nuts that are not
self-locking.
Put the Airplane Back to its Usual Condition.
S 415-017-P00
WARNING:
_______
OBEY THE INSTRUCTIONS IN THE PROCEDURE TO CLOSE THE THRUST
REVERSERS. IF YOU DO NOT OBEY THE INSTRUCTIONS, YOU CAN CAUSE
INJURIES TO PERSONS AND DAMAGE TO EQUIPMENT CAN OCCUR.
(1)
Close the thrust reversers (AMM 78-31-00/201).
(2)
S 415-018-P00
Close the core cowl panels (AMM 71-11-06/201).
(3)
S 445-019-P00
Close the fan cowl panels (AMM 71-11-04/201).
(4)
S 415-020-P00
Do the activation procedure for the thrust reversers
(AMM 78-31-00/201).
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ENGINE WIRE HARNESS - INSPECTION/CHECK
______________________________________
1.
2.
General
_______
A. This procedure has
this inspection is
B. If you find damage
(Ref 71-51-00/801,
a visual inspection of the engine wire harnesses, but
not for wire harnesses with externally braided cables.
on an engine wire harness, repair the harness
Wire Harness Repair).
TASK 71-51-00-216-001-P00
Make a Visual Inspection of the Engine Wire Harness
___________________________________________________
A. References
(1) 24-22-00/201, Electrical Power - Control
(2) 71-11-04/201, Fan Cowl Panels
(3) 71-11-06/201, Core Cowl Panels
(4) 78-31-00/201, Thrust Reverser System
B. Access
(1) Location Zones
211/212
Flight Compartment
411
Left Engine
421
Right Engine
(2)
C.
Access Panels
413AL/414AR
415AL/416AR
417AL/418AR
423AL/424AR
425AL/426AR
427AL/428AR
Fan Cowl Panels, Left Engine
Thrust Reversers, Left Engine
Core Cowl Panels, Left Engine
Fan Cowl Panels, Right Engine
Thrust Reversers, Right Engine
Core Cowl Panels, Right Engine
Prepare for Visual Inspection of the Engine Wire Harness.
(1)
S 016-002-P00
Open the fan cowl panels (Ref 71-11-04/201).
S 046-003-P00
WARNING:
_______
(2)
(3)
DO THE THRUST REVERSER DEACTIVATION TO PREVENT THE OPERATION OF
THE THRUST REVERSERS. THE ACCIDENTAL OPERATION OF THE THRUST
REVERSERS CAN CAUSE INJURIES TO PERSONS OR DAMAGE TO EQUIPMENT.
Do this procedure: Thrust Reverser Deactivation for Ground
Maintenance (Ref 78-31-00/201).
S 016-004-P00
Open the core cowl panels (Ref 71-11-06/201).
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S 016-005-P00
WARNING:
_______
D.
OBEY THE INSTRUCTIONS IN AMM 78-31-00/201 WHEN YOU OPEN THE
THRUST REVERSERS. IF YOU DO NOT OBEY THE INSTRUCTIONS, YOU CAN
CAUSE INJURIES TO PERSONS OR DAMAGE TO EQUIPMENT.
(4)
Open the thrust reversers (Ref 78-31-00/201).
(5)
S 866-006-P00
Make sure that the electrical power is removed (Ref 24-22-00/201).
S 866-007-P00
(6) Make sure the engine has been stopped for a minimum of 5 minutes.
Visually Examine the Engine Wire Harness.
(1)
S 216-008-P00
Do these steps to examine the harness cables and wires:
(a) Examine all the cables in the harness for damage to the outer
jacket and the braid.
(b) Examine all the harness wires that you can see for damage.
S 216-009-P00
Do these steps to examine the harness connectors:
(a) Examine the position of the connector coupling nut.
(b) If the coupling nut threads are not fully engaged on the
connector receptacle, do a check of the harness contacts (pins
or sockets):
1) Disconnect the harness connectors.
2) Make sure the contacts are straight, not damaged, and
correctly engaged in the connector face.
3) Connect the harness connectors.
Put the Airplane Back to its Usual Condition.
(2)
E.
S 416-010-P00
WARNING:
_______
OBEY THE INSTRUCTIONS IN AMM 78-31-00/201 WHEN YOU CLOSE THE
THRUST REVERSERS. IF YOU DO NOT OBEY THE INSTRUCTIONS, YOU CAN
CAUSE INJURIES TO PERSONS OR DAMAGE TO EQUIPMENT.
(1)
Close the thrust reversers (Ref 78-31-00/201).
(2)
S 416-011-P00
Close the core cowl panels (Ref 71-11-06/201).
(3)
S 446-012-P00
Do the thrust reverser activation procedure (Ref 78-31-00/201).
(4)
S 416-013-P00
Close the fan cowl panels (Ref 71-11-04/201).
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ENGINE WIRE HARNESS - APPROVED REPAIRS
______________________________________
1.
2.
General
_______
A. This procedure has three tasks for temporary repairs to the engine wire
harnesses. These tasks are shown below in the sequence that they occur
in this procedure:
(1) A cable splice
(2) A cable external jacket or braid repair
(3) A cable replacement.
B. The steps that follow identify the wire harness parts:
(1) Wire - A single electrical conductor with insulation around it.
(2) Cable - A group of wires contained in a metal shield and an
insulation jacket.
(3) Bundle - A group of cables attached to each other with lacing tape.
(4) Harness - A single bundle or two or more bundles with connectors
or terminals attached at the ends of the bundles.
C. Repair the connectors and connector contacts with the procedures in
Chapter 20 of the Standard Wiring Practices Manual.
TASK 71-51-00-358-001-P00
Cable Splice Repair
___________________
A. General
(1) This task repairs broken wires or wires with damage. The steps that
follow are the limits for the wire repairs:
(a) Replace the repaired cables when the harness is removed or
during the engine's next shop visit.
(b) Do not put a splice in a wire less than 6 inches (150 mm) from
the clamp on a connector backshell.
(c) Do not put a splice in a cable with a steel outer braid.
(d) Do not put a splice under a clamp or a drip loop.
(e) Do not put a splice where it can change the clamp positions or
the wire harness location.
(f) Do not put a splice in a fire detection circuit.
(g) Do not put a splice in generator feeders or cables with steel
outer braids.
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(h)
(2)
Splices must be moisture and abrasion resistant. Use a
moisture-resistant tape wrap covered with an abrasion-resistant
sleeve or tape when you do the repair.
This procedure is for a 2-wire cable with a braided shield. If you
put a splice in a 3-wire cable, put the third splice in the cable so
the insulation edges of the splices are all at least
1.3 inches (32 mm) away from each other. If you put a splice in a
1-wire cable without a braided shield, ignore the steps about the
shield.
(a) Do not put a splice in the two channels of a very important
circuit with fire-resistant wire. The circuits that follow are
very important circuits:
NOTE:
____
(3)
(4)
(5)
1) The fuel flow resolver
2) The fuel-flow-torque-motor
3) The overspeed solenoid
4) The EEC alternator
5) The air-oil-cooler-torque-motor
6) The air-oil-cooler-rotary-variable-transducer
7) All other circuits made with the fire-resistant wire.
(b) Do not put a splice in generator feeders or cables with steel
outer braids.
(c) If you put a splice in a circuit, replace the cable when the
harness is removed or the subsequent time the engine is in the
shop.
Refer to the Standard Wiring Practices Manual for repair of the
connectors and connector contacts.
Splices must be moisture and abrasion resistant. Use a moisture
resistant tape wrap covered with an abrasion resistant sleeve or
tape when you do the repair.
You must see the wire splice to do a visual inspection. Do not put
the wire splices under clamps or drip loops.
NOTE:
____
B.
This splice repair is not fire resistant. A splice
repair in a very important circuit will decrease the
serviceable condition of the circuit.
Where shields are used is very important and must be
continuous across all the wire splices.
Equipment
(1) Wire stripper, 16 to 20 gauge - Strip Master 45092 (or equivalent):
Ideal Industries, Inc., 1008 Becker Pl., Sycamore, IL 60178
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(2)
(3)
Wire splice crimp tools (use one of the crimp
tools that follow):
(a) STANDARD WIRES;
46673: AMPS Inc., 2800 Fulling Mill, P.O. Box 3608,
Harrisburg, PA 17105
or Y10MRE-S: Burndy Corp., Richards Ave., Norwalk, CT 06850
(b) THERMOCOUPLE WIRES;
46673: AMPS Inc., 2800 Fulling Mill,
P.O. Box 3608, Harrisburg, PA 17105
Replacement cable (Refer to the WDM wire diagrams and wire list for
the correct replacement cable).
NOTE:
____
(4)
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Use the same type of cable as the damaged cable. If the
same type of cable is not available, use the alternate cable
shown in Table 1. You must splice thermocouple circuits with
chromel and alumel wire and splices as applicable. The wire
type codes used in the wire list are identified in the
Standard Wiring Practices Manual D6-54446.
Cable ferrule crimp tools (use the tools shown in the table that
follows as necessary): Thomas and Betts Corp., 920 Route 202,
Raritan, NJ 08869-1420:
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TOOL DIE MS22520/5-43
¦
»¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼«
¦
BACS13S312CNP
¦
TOOL DIE MS22520/5-39
¦
²¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼…¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¹
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(5)
C.
Wire splices (use the splices that follow as
necessary):
(a) STANDARD WIRES;
BACT12C-20 (nickel plated copper)
(b) ALUMEL THERMOCOUPLE WIRES;
1-322325-0 (Alumel): AMPS Inc., 2800 Fulling Mill,
P.O. Box 3608, Harrisburg, PA 17105
(c) CHROMEL THERMOCOUPLE WIRES;
1-322325-1 (Chromel): AMPS Inc., 2800 Fulling Mill,
P.O. Box 3608, Harrisburg, PA 17105
Consumable Materials
(1) Braid, tubular - silver plated copper 0.25 inch (or an equivalent):
NEQ241636SP, New England Electric Wire Corp., 365 Main St., Lisbon,
New Hampshire 03585, USA
(2) G00042
Braid, Flat-Woven Fiberglass with a Teflon Coat - PN TG-25,
TG-40, E775-476, or E775-303: Gudebrod Inc., 262 King St.,
P.O. Box 357, Pottstown, PA 19464
(3) Tape, Lacing - BMS13-54 Grade D, Type 3p: or Gudebrod 718Z
(4) G00057 Tape, Teflon with an Acrylic Back - Scotch 63 or 65 (or an
equivalent): Minnesota Mining and Mfg. Co., 3M Ctr.,
St. Paul, MN 55101-1428
(5) G00152 Tape, Teflon Insulation - Scotch 4202
(6) G00055 Cable ferrules (use the ferrules shown
in the tables that follow as necessary):
~¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼
¦
INNER FERRULE
¦
»¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼ ¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼«
¦
APPLICATION
¦
PART NUMBER
¦
»¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼«
¦
Two 18 gauge wires
¦
BACS13S205BNP
¦
»¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼«
¦
Two 20 gauge wires
¦
BACS13S205BNP
¦
»¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼«
¦
Three 20 gauge wires
¦
BACS13S205BNP
¦
»¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼«
¦
Two 18 gauge wires
¦
BACS13S219BNP
¦
»¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼«
¦
Two 20 gauge wires
¦
BACS13S219BNP
¦
»¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼«
¦
Three 18 gauge wires
¦
BACS13S219BNP
¦
»¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼«
¦
Three 20 gauge wires
¦
BACS13S219BNP
¦
»¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼«
¦
Two 20 gauge wires
¦
BACS13S232BNP
¦
»¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼«
¦
Three 20 gauge wires
¦
BACS13S275BNP
¦
²¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼…¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¹
EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùùû
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~¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼
¦
OUTER FERRULE
¦
»¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼ ¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼«
¦
APPLICATION
¦
PART NUMBER
¦
»¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼«
¦
Two 18 gauge wires
¦
BACS13S312CNP
¦
»¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼«
¦
Two 20 gauge wires
¦
BACS13S312CNP
¦
»¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼«
¦
Three 20 gauge wires
¦
BACS13S312CNP
¦
»¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼«
¦
Two 18 gauge wires
¦
BACS13S327CNP
¦
»¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼«
¦
Two 20 gauge wires
¦
BACS13S327CNP
¦
»¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼«
¦
Three 18 gauge wires
¦
BACS13S327CNP
¦
»¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼«
¦
Three 20 gauge wires
¦
BACS13S327CNP
¦
»¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼«
¦
Two 20 gauge wires
¦
BACS13S348CNP
¦
»¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼«
¦
Three 20 gauge wires
¦
BACS13S375CNP
¦
²¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼…¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¹
D.
E.
References
(1) AMM 24-22-00/201, Electrical Power Control
(2) AMM 71-11-04/201, Fan Cowl Panels
(3) AMM 71-11-06/201, Core Cowl Panels
(4) AMM 71-51-00/501, Engine Wire Harness - Adjustment/Test
(5) AMM 78-31-00/201, Thrust Reverser System
(6) Standard Wiring Practices Manual D6-54446
Access
(1) Location Zones
411
Left Engine
421
Right Engine
EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùùû
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MAINTENANCE MANUAL
(2)
F.
Access Panels
413AL/414AR
415AL/416AR
417AL/418AR
423AL/424AR
425AL/426AR
427AL/428AR
////////////////////////
/
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/
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////////////////////////
Fan Cowl Panels, Left Engine
Thrust Reversers, Left Engine
Core Cowl Panels, Left Engine
Fan Cowl Panels, Right Engine
Thrust Reversers, Right Engine
Core Cowl Panels, Right Engine
Prepare to Do the Cable Splice Repair.
S 048-003-P00
WARNING:
_______
(1)
DO THE THRUST REVERSER DEACTIVATION PROCEDURE TO PREVENT THE
OPERATION OF THE THRUST REVERSERS. THE ACCIDENTAL OPERATION OF
THE THRUST REVERSERS CAN CAUSE INJURIES TO PERSONS OR DAMAGE TO
EQUIPMENT.
Do the deactivation procedure for the thrust reverser for ground
maintenance (AMM 78-31-00/201).
(2)
S 018-004-P00
Open the fan cowl panels (AMM 78-31-00/201).
(3)
S 018-080-P00
Open the core cowl panels (AMM 71-11-06/201).
S 018-005-P00
WARNING:
_______
OBEY THE INSTRUCTIONS IN THE PROCEDURE TO OPEN THE THRUST
REVERSER. IF YOU DO NOT OBEY THE INSTRUCTIONS, INJURIES TO
PERSONS AND DAMAGE TO EQUIPMENT CAN OCCUR .
(4)
Open the thrust reversers (AMM 78-31-00/201).
(5)
S 868-006-P00
Remove the electrical power (AMM 24-22-00/201).
(6)
S 868-007-P00
Make sure the engine has been stopped for a minimum of 5 minutes.
EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùùû
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(7)
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/
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////////////////////////
S 218-008-P00
Identify the type of replacement cable that is necessary for the
circuit you will repair.
NOTE:
____
Use a cable with the same wire gage, specifications, and
insulation color as the damaged engine cable. If the same
type cable is not available, use an alternate cable shown in
Table 801. You must splice thermocouple circuits with
chromel and alumel wire and splices as applicable.
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/
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~¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼
¦
Alternate Shielded and Unshielded Cables
¦
¦
Table 801
¦
»¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼«
¦ FIRST ALTERNATE CABLE: BMS 13-55 Cable, 16, 18, and 20 gage wires
¦
¦
¦
¦ ____
NOTE: Use the first alternate cable only if the initial cable is not
¦
¦
available.
¦
¦
¦
»¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼ ¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼«
¦ Type 1 or 2 for unshielded cables, ¦ Type 3 or 4 for shielded cables,
¦
¦ class and gage sisz as applicable ¦ class and gage size as applicable
¦
»¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼…¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼«
¦
Class 1 - single conductor cable
¦
»¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼«
¦
Class 2 - two conductor twisted cable
¦
»¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼«
¦
Class 3 - three conductor twisted cable
¦
»¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼«
¦
Class 4 - four conductor twisted cable
¦
»¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼«
¦ SECOND ALTERNATE CABLE: BMS 13¼31 Cable, 16, 18 and 20 gage wires
¦
¦
¦
¦ ____
NOTE: Use the second alternate cable only if the initial cable or first
¦
¦
alternate cable is not available. You cannot use the second alternate ¦
¦
cable in a fire detection circuit or the fuel shutoff circuit.
¦
¦
¦
»¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼ ¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼«
¦ Type 5 for unshielded cables,
¦ Type 7 for shielded cables,
¦
¦ class and gage size as applicable ¦ class and gage size as applicable
¦
»¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼…¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼«
¦
Class 1 - single conductor cable
¦
»¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼«
¦
Class 2 - two conductor twisted cable
¦
»¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼«
¦
Class 3 - three conductor twisted cable
¦
»¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼«
¦
Class 4 - four conductor twisted cable
¦
²¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¹
G.
Do the Cable Splice Repair.
(1)
S 018-097-P00
Remove the lacing tape and the harness clamps from the wire harness
to get sufficient access to the damaged cable.
EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùùû
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(2)
S 038-009-P00
Cut, remove, and discard the damaged part of the cable from the wire
harness.
NOTE:
____
(3)
////////////////////////
/
PW2000 SERIES
/
/
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Repair one cable at a time.
S 358-010-P00
Do these steps to prepare the two ends of the remaining engine cable
(Fig. 801):
(a) Clean the cable 12 inches (300 mm) from the ends.
(b) Cut and remove the insulation jacket 6 inches (150 mm) from the
end of the cable to show the braided shield.
(c) Cut and remove the braided shield back so that 0.75 inch
(19 mm) of the shield shows.
(d) Cut one wire 4 inches (100 mm) from the insulation jacket.
(e) Cut the other wire 2 inches (50 mm) from the end of the first
wire.
(4)
S 358-011-P00
Cut a piece of the replacement cable 12 inches (300 mm) longer than
the distance between the two ends of the remaining cable.
(5)
S 358-012-P00
Do the steps above to prepare one end of the replacement cable as
you did for the remaining engine cable.
NOTE:
____
(6)
Make sure the colors of the replacement cable wires are
the same as the engine cable wires. Cut the wires such that
the long engine wire aligns with the short replacement wire.
S 358-013-P00
Do these steps to install the replacement cable (Fig. 802):
(a) Install one outer termination ferrule on each end of the cable.
1) Move the ferrules away from the splice area.
(b) Cut a length of tubular braid to cover the splice area.
(c) With the tubular braid expanded, install it on one end of the
cable.
1) Move the braid away from the splice repair area.
(d) Install one inner termination ferrule on each end of the cable.
1) Move the ferrules away from the splice area.
(e) Make a splice each of the wires as follows (Fig. 801):
1) Use the wire stripper to remove sufficient insulation to
make it easy to put the conductor into the splice
correctly.
EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùùû
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////////////////////////
A
757
MAINTENANCE MANUAL
BRAIDED SHIELD
SEE
0.75 INCH
(19.05 mm)
WIRE INSULATION
A
CONDUCTOR
CABLE INSULATED
JACKET
PREPARE THE SPLICE
WIRE
INSULATION
SEE
SPLICE
B
CONDUCTOR
INSTALLATION OF THE WIRE SPLICE
A
0.125 INCH (3.175 mm)
MAXIMUM AFTER CRIMP
CRIMPED WIRE SPLICE
CONDUCTOR
INSULATION
CRIMPED WIRE SPLICE
B
C75008
Wire Splice
Figure 801
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MAINTENANCE MANUAL
2)
Put the wires into each end of the wire splice to make an
overlap.
NOTE:
____
3)
4)
The splice will not have sharp edges if you install
it correctly.
Wind two layers of the red rubber tape (Moxness 620-3/4)
directly around the splice with a 50% overlap on each turn
of the tape (Fig. 802).
NOTE:
____
6)
This is a parallel splice and not a butt splice.
The ends of the wire show at each end of the splice.
a) Use the correct crimp tool to attach the splice.
Pull on the splices to make sure they will not come off the
wires.
Remove all the sharp edges from the splices.
NOTE:
____
5)
////////////////////////
/
PW2000 SERIES
/
/
/
ENGINES
////////////////////////
Wind the second layer in the opposite direction
to the first layer. The tape wrap must be
sufficiently tight to give a moisture-resistant
seal.
Wind two layers of the electrical silicone tape (Scotch 92)
for abrasion protection with a 50% overlap on each turn of
the tape.
NOTE:
____
Wind the second layer in the opposite direction
to the first layer. The tape wrap must be
sufficiently tight to give a moisture-resistant
seal.
a)
7)
Extend the tape a minimum of one-half inch more than
each end of the inner tape.
For the repair of a 1-wire cable without a braided shield
do these steps (Fig. 803):
NOTE:
____
Do not do these steps if the cable has a braided
shield.
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MAINTENANCE MANUAL
0.50 INCH (12.7 mm)
MINIMUM
SEE
A
SEE
////////////////////////
/
PW2000 SERIES
/
/
/
ENGINES
////////////////////////
B
TWO LAYERS
OF MOISTURE
RESISTANT TAPE
TWO LAYERS WOUND
DIRECTLY OVER THE
SPLICE
A
B
685892
Moisture Resistant Tape Wrap
Figure 802
EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùùû
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////////////////////////
/
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/
/
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////////////////////////
END OF THE INNER TAPE WRAP
1.0 INCH (25.4 mm)
SEE
A
TWO LAYERS
CLOVE HITCH
SQUARE KNOT
LACING TAPE
A
C74971
Abrasion Resistant Tape Wrap and Lacing Tape
Figure 803
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8)
Wind the splice with tape to prevent abrasions (Fig. 803):
a) Wind two layers of electrical silicone tape (Scotch 62)
directly around the splice with 50 percent overlap on
each turn of the tape.
NOTE:
____
b)
c)
(h)
Tighten the clove hitch before you tighten
the square knot.
d) Cut the free ends to 0.25-0.50 inch (6-12 mm).
Make sure the metal strands of the braided shield are straight.
Put the inner ferrule near the end of the cable insulation and
fold the braid shield back over the ferrule (Fig. 804).
1) Make sure the metal strands of the braid shield have an
equal proportion around the ferrule.
Put one end of the tubular braid on the metal strands of the
shield (Fig. 804).
1) Move the outer ferrule on the tubular braid and the inner
ferrule.
2) Use the crimp tool to attach the outer ferrule on the inner
ferrule and braid shield (Fig. 805).
NOTE:
____
(i)
(j)
Wind the second layer in the opposite direction
of the first layer.
Extend the tape one inch beyond each end of the inner
tape.
With the lacing tape, make a clove hitch and a square
knot on each end of the tape.
NOTE:
____
(f)
(g)
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Make sure the braid shield stays between the inner
and the outer ferrules when you install the outer
ferrule.
Pull the tubular braid tight across the splice area.
Install the inner and outer ferrules on the other end as shown
in the steps above.
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WIRE SPLICE
OUTER FERRULE
SEE
TUBULAR BRAID
CABLE INSULATION
A
TUBULAR BRAID
WIRE SPLICE
INNER FERRULE
SEE
B
A
TUBULAR BRAID
INNER FERRULE
BRAIDED SHIELD
SEE
C
OUTER FERRULE
TUBULAR BRAID AND OUTER FERRULE INSTALLATION
B
BRAIDED SHIELD
INNER FERRULE
INNER FERRULE INSTALLATION
C
685893
Tubular Braid Installation
Figure 804
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MAKE SURE THE RADIUS SIDE
OF EACH DIE IS INSTALLED TO
THE CHANNEL SIDE OF THE TOOL
C74980
Crimp Tool for the Outer Ferrule
Figure 805
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(k)
Cut the unwanted braid near the outer end of the two outer
ferrules.
For abrasion protection wind two layers of the electrical
silicone tape (Scotch 62) directly around the splice
(Fig. 806).
(l)
NOTE:
____
1)
(7)
(a)
(b)
(9)
H.
Wind the second layer in the opposite direction to the
first layer. There must be a 50 percent overlap on each
turn of the tape. The tape wrap must be tight enough to
give a moisture resistant seal.
Extend the tape a minimum of one-half inch (13 mm) more
than each end of the inner tape.
S 768-086-P00
With lacing tape, make a clove hitch and a square knot on each end
of the tape (Fig. 803).
NOTE:
____
(8)
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Tighten the clove hitch before you tighten the
square knot.
Cut the free ends to 0.25-0.50 inch (6-12 mm).
Do the above procedure again to attach the other end of the
replacement cable to the remaining engine cable.
S 768-015-P00
Do the Engine Wire Harness Adjustment/Test for the cable you
repaired (AMM 71-51-00/501).
S 438-079-P00
Install the lacing tape to the repaired wire harness, as necessary.
S 438-017-P00
(10) Install all the clamps that you removed.
Put the Airplane Back to its Usual Condition.
S 418-018-P00
WARNING:
_______
OBEY THE INSTRUCTIONS IN THE PROCEDURE TO CLOSE THE THRUST
REVERSERS. IF YOU DO NOT OBEY THE INSTRUCTIONS, INJURIES TO
PERSONS AND DAMAGE TO EQUIPMENT CAN OCCUR.
(1)
Close the thrust reversers (AMM 78-31-00/201).
(2)
S 418-019-P00
Close the core cowl panels (AMM 71-11-06/201).
(3)
S 418-081-P00
Close the fan cowl panels (AMM 71-11-04/201).
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0.50 INCH (12.7 mm)
MINIMUM
BRAID SHIELD
FOLDED OVER THE
INNER FERRULE
WIRE SPLICE
(2 POSITIONS)
CABLE
INNER FERRULE
(2 POSITIONS)
OUTER FERRULE
(2 POSITIONS)
TUBULAR
BRAID
INSULATION TAPE
(3 LAYERS)
INSULATION TAPE
(2 SPIRAL LAYERS)
NOTE:
____
SHOWN WITHOUT THE
ACRYLIC TAPE INSTALLED.
989624
Two Conductor Shielded Cable Splice
Figure 806
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(4)
3.
S 448-020-P00
Do the activation procedure for the thrust reverser
(AMM 78-31-00/201).
TASK 71-51-00-358-022-P00
Cable Insulated Jacket and Braid Repair
_______________________________________
A. General
(1) This procedure has a repair for cables that have damage to the
braided shield or insulation jacket. If the braided shield and
insulated jacket are damaged more than the repair limits, cut the
wire and do the splice repair procedure. The limits for this repair
are shown as follows:
(a) The braided shield shows through the insulated jacket a maximum
of 50% around the cable.
(b) The insulation jacket shows the braided shield a maximum of
2 inches (51 mm) along the cable.
(c) A maximum of 20 percent of the metal strands of the braided
shield are damaged in one location.
B. Consumable Materials
(1) Tape, electrical silicone - Scotch 92,
Minnesota Mining and Mfg. Co., 6801 River Place
Blvd Austin TX 94023, USA
(2) G02119, Tape, electrical silicone - Scotch 62,
Minnesota Mining and Mfg. Co., 6801 River Place
Blvd Austin TX 94023, USA
(3) Tape, Lacing - BMS13-54 Grade D, Type 3: or Gudebrod 718Z
C. References
(1) AMM 24-22-00/201, Electrical Power - Control
(2) AMM 71-11-04/201, Fan Cowl Panels
(3) AMM 71-11-06/201, Core Cowl Panels
(4) AMM 78-31-00/201, Thrust Reverser System
(5) Standard Wiring Practices Manual D6-54446
D. Access
(1) Location Zones
411
Left Engine
421
Right Engine
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(2)
E.
Access Panels
413AL/414AR
415AL/416AR
417AL/418AR
423AL/424AR
425AL/426AR
427AL/428AR
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Fan Cowl Panels, Left Engine
Thrust Reversers, Left Engine
Core Cowl Panels, Left Engine
Fan Cowl Panels, Right Engine
Thrust Reversers, Right Engine
Core Cowl Panels, Right Engine
Prepare to Do the Cable Insulated Jacket or Braid Repair.
S 048-024-P00
WARNING:
_______
(1)
DO THE DEACTIVATION PROCEDURE TO PREVENT THE OPERATION OF THE
THRUST REVERSERS. THE ACCIDENTAL OPERATION OF THE THRUST
REVERSERS CAN CAUSE INJURIES TO PERSONS AND DAMAGE TO
EQUIPMENT.
Do the deactivation procedure for the thrust reversers for ground
maintenance (AMM 78-31-00/201).
(2)
S 018-082-P00
Open the fan cowl panels (AMM 71-11-04/201).
(3)
S 018-025-P00
Open the core cowl panels (AMM 71-11-06/201).
S 018-026-P00
WARNING:
_______
OBEY THE INSTRUCTIONS IN THE PROCEDURE TO OPEN THE THRUST
REVERSERS. IF YOU DO NOT OBEY THE INSTRUCTIONS, INJURIES TO
PERSONS AND DAMAGE TO EQUIPMENT CAN OCCUR.
(4)
Open the thrust reversers (AMM 78-31-00/201).
(5)
S 868-027-P00
Remove the electrical power (AMM 24-22-00/201).
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F.
S 868-028-P00
(6) Make sure the engine has been stopped for a minimum of 5 minutes.
Do the Cable Insulated Jacket or Braid Repair.
(1)
(2)
S 028-087-P00
Remove the lacing tape and the harness clamps from the wire harness
as necessary to get access to the damaged cable.
S 148-030-P00
Clean the cable to 3 inches (76 mm) on each side of the damage.
(3)
S 358-031-P00
Wind one layer or electrical silicone tape (Scotch 92) around the
cable with a 20 percent overlap on each turn of the tape.
(4)
S 358-032-P00
Extend the tape 1.0 inch (2.5 cm) more on each side of the worn area
of the insulated jacket.
(5)
(6)
G.
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S 358-064-P00
Install the insulation tape and silicone tape on the open braid:
(a) Wind one layer of electrical silicone tape (Scotch 62) over the
first layer of tape with a 20 percent overlap on each turn of
the tape.
1) Extend the tape 0.5 inch (13 mm) more on each side of the
first layer of tape.
S 438-034-P00
Install the lacing tape to the wire harness as necessary.
S 438-035-P00
(7) Install all the harness clamps that you removed.
Put the Airplane Back to its Usual Condition.
S 418-036-P00
WARNING:
_______
(1)
OBEY THE INSTRUCTIONS IN THE PROCEDURE TO CLOSE THE THRUST
REVERSERS. IF YOU DO NOT OBEY THE INSTRUCTIONS, INJURIES TO
PERSONS AND DAMAGE TO EQUIPMENT CAN OCCUR.
Close the thrust reversers (AMM 78-31-00/201).
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(2)
S 418-037-P00
Close the core cowl panels (AMM 71-11-06/201).
(3)
S 418-083-P00
Close the fan cowl panels (AMM 71-11-04/201).
(4)
4.
S 448-038-P00
Do the activation procedure for the thrust reverser
(AMM 78-31-00/201).
TASK 71-51-00-358-040-P00
Cable Replacement
_________________
A. General
(1) This task gives the steps to replace a damged or open circuit cable
with a new shielded or unshielded cable. The new cable will be
installed on the external side of the wire harness. For the
replacement cable, use the same type of cable as the damaged cable.
If the same type of cable is not available, use an alternate cable
shown in Table 1. You must splice thermocouple circuits with
chromel and alumel wires and splices as applicable.
B. Equipment
(1) Wrench - Glenair TG-70 (or equivalent): Glenair Inc., 1211 Air Way,
Glendale, CA 91201, USA
(2) Wrench, strap - Daniels BT-BS-611 (or equivalent): Daniels
Manufacturing Corp., 6103 Anno Ave., Orlando, FL 32809-5033, USA
(3) Pliers, connector soft jaw - Glenair TG-69 (or equivalent):
Glenair Inc., 1211 Air Way, Glendale, CA 91201, USA
(4) Kit, connector adapter - CM-S-837 (for MIL-C-26500 series
connectors) or CM-S-839T (for MIL-C-38999 series connectors) or
equivalent: Daniels Manufacturing Corp., 6103 Anno Ave.,
Orlando, FL 32809-5033, USA
(5) Contact insertion tool (16 gage) - MS27495A16,
Daniels Manufacturing Corp.
(6) Contact insertion tool (20 gage) - MS27495A20,
Daniels Manufacturing Corp.
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(7)
C.
Contact removal tool (16 gage) - MS27495R16,
Daniels Manufacturing Corp.
(8) Contact removal tool (20 gage) - MS27495R20,
Daniels Manufacturing Corp.
(9) Wire stripper, 16 to 20 gauge - Strip Master 45092 (or equivalent):
Ideal Industries, Inc., 1008 Becker Pl., Sycamore, IL 60178, USA
(10) Crimp tool frame (crimp contact), or
equivalent, - M22520/1-01,
Daniels Manufacturing Corp.
(11) Crimp tool positioner (crimp 16 gage contact),
or equivalent, - M22520/1-02,
Daniels Manufacturing Corp.
(12) Crimp tool positioner (crimp 20 gage contact),
or equivalent, - M22520/1-04,
Daniels Manufacturing Corp.
(13) Tool, retention test (16 gage) - HT210-16 or
equivalent,
Daniels Manufacturing Corp.
(14) Tool, retention test (20 gage) - HT210-20 or
equivalent,
Daniels Manufacturing Corp.
(15) Replacement socket tip (16 gage) - 68-016-01 or
equivalent,
Daniels Manufacturing Corp.
(16) Replacement socket tip (20 gage) - 68-020-01 or
equivalent,
Daniels Manufacturing Corp.
(17) Replacement pin tip (16 gage) - PN 67-016-02 or
equivalent,
Daniels Manufacturing Corp.
(18) Replacement pin tip (20 gage) - PN 67-020-02 or
equivalent,
Daniels Manufacturing Corp.
Consumable Materials
(1) Replacement cable (Refer to the WDM wire
diagrams and wire list for the correct
replacement cable).
NOTE:
____
The wire type codes used in the wire
list are identified in the Standard
Wiring Practices manual D6-54446.
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(2)
D.
E.
Tape, red rubber, self bonding - Moxness
620-3/4, Moxness Products Inc., 1914 Indiana
St., Racine, WI 53405-3649, USA
(3) Tape, Lacing - BMS13-54 Grade D, Type 3,
or Gudebrod 718Z
(4) Connector contacts - refer to the Standard
Wiring Practices Manual as follows for the
correct contacts to use for the connectors and
the wires that you have:
MIL-C-26500 Series Connector
SWPM 20-61-11
MIL-C-38999 Series Connector
SWPM 20-63-19
MIL-C-83723 Series Connector
SWPM 20-63-13
References
(1) AMM 24-22-00/201, Electrical Power - Control
(2) AMM 71-11-04/201, Fan Cowl Panels
(3) AMM 71-11-06/201, Core Cowl Panels
(4) AMM 71-51-00/501, Engine Wire Harness
(5) AMM 78-31-00/201, Thrust Reverser System
(6) Standard Wiring Practices Manual D6-54446
Access
(1) Location Zones
411
Left Engine
421
Right Engine
(2)
F.
Access Panels
413AL/414AR
415AL/416AR
417AL/418AR
423AL/424AR
425AL/426AR
427AL/428AR
Fan Cowl Panels, Left Engine
Thrust Reversers, Left Engine
Core Cowl Panels, Left Engine
Fan Cowl Panels, Right Engine
Thrust Reversers, Right Engine
Core Cowl Panels, Right Engine
Prepare to Do the Cable Replacement.
S 048-042-P00
WARNING:
_______
(1)
DO THE DEACTIVATION PROCEDURE TO PREVENT THE OPERATION OF THE
THRUST REVERSERS. THE ACCIDENTAL OPERATION OF THE THRUST
REVERSERS CAN CAUSE INJURIES TO PERSONS AND DAMAGE TO
EQUIPMENT.
Do the deactivation procedure for the thrust reversers for ground
maintenance (AMM 78-31-00/201).
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(2)
S 018-041-P00
Open the fan cowl panels (AMM 71-11-04/201).
(3)
S 018-043-P00
Open the core cowl panels (AMM 71-11-06/201).
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S 018-044-P00
WARNING:
_______
OBEY THE INSTRUCTIONS IN THE PROCEDURE TO OPEN THE THRUST
REVERSERS. IF YOU DO NOT OBEY THE INSTRUCTIONS, INJURIES TO
PERSONS AND DAMAGE TO EQUIPMENT CAN OCCUR.
(4)
Open the thrust reversers (AMM 78-31-00/201).
(5)
S 868-045-P00
Remove the electrical power (AMM 24-22-00/201).
(6)
S 868-046-P00
Make sure the engine has been stopped for a minimum of 5 minutes.
(7)
S 218-047-P00
Identify the type of replacement cable that is necessary for the
circuit that you will repair.
(a) Use a cable with the same wire gage, specifications, and
insulation colors as the damaged engine cable.
NOTE:
____
G.
If the same type cable is not available, use the
alternate cables shown in Table 1. You must splice
thermocouple circuits with chromel and alumel wire and
splices as applicable.
Do the Cable Replacement.
S 358-048-P00
WARNING:
_______
(1)
DO NOT USE HEAT GUNS, SOLDERING GUNS, AND SOLDERING IRONS FOR
THE ON-WING REPAIRS. THEY ARE NOT RESISTANT TO EXPLOSION AND
CAN CAUSE INJURY TO PERSONS OR DAMAGE TO EQUIPMENT.
Do these steps to install a new cable on the external side of the
harness:
(a) Find the two connectors that are attached to the ends of the
broken cable.
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(b)
Put the end of the new cable such that it is 6 inches (150 mm)
longer than the broken cable at one end.
Use the tape to attach the cable to the external side of the
connector.
Put the new cable along the wire harness.
Cut the other end of the cable 6 inches (150 mm) longer than
the broken cable at the second connector.
Use the tape to attach the cable to the external side of the
connector.
Put a label on each end of the new cable.
1) Write on each label the connector contact numbers of the
wires in the cable that you will replace.
Install the new cable in all the clamps that attach the wire
harness to the engine.
(c)
(d)
(e)
(f)
(g)
(h)
(2)
S 438-049-P00
Disconnect the two connectors for the cable with the damaged wire
(Fig. 807).
NOTE:
____
(3)
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Use the TG-70 or BT-BS-611 strap wrench or TG-69 pliers, or
equivalent.
S 358-050-P00
Do these steps to remove the wires of the damaged cable from each
connector:
(a) Remove the backshell and the strain relief clamp from each
connector (Fig. 808 or 809).
(b) If necessary, remove the lockwire on the backshell.
(c) For stainless steel backshells, do as follows:
1) Loosen the hose clamp on the backshell that attaches the
shielded cable to the backshell.
2) Move the hose clamp to the rear of the harness and away
from the repair area.
3) Fold the braided shields over the strain relief clamp to
make the shields straight.
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ADAPTER
BACKSHELL
MASTER KEY
CONNECTOR
BT-BS-611
STRAP WRENCH
BACKSHELL
TG-70
STRAP WRENCH
CONNECTOR
TG-69 SOFT
NOSE PLIERS
C74981
Backshell and Connector Tools for Removal/Installation
Figure 807
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BACKSHELL
COUPLING NUT
BACKSHELL
BODY
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HOSE
CLAMP
STRAIN RELIEF
CLAMP
(2 LOCATIONS)
RED RUBBER
TAPE
BRAIDED SHIELD
(2 LOCATIONS)
CONNECTOR
C74982
Stainless Steel Backshell Assembly
Figure 808
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BRAIDED SHIELD
CONICAL RING
BACKSHELL BODY
RED RUBBER TAPE
STRAIN
RELIEF BODY
BACKSHELL
COUPLING NUT
STRAIN RELIEF
CLAMP BARS
ALUMINUM BACKSHELL ASSEMBLY
LOCKWIRE
(4 LOCATIONS)
LOCKWIRE
(4 LOCATIONS)
LOCKWIRE INSTALLATION
C74983
Aluminum Backshell Assembly and Lockwire
Figure 809
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(d)
(e)
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Loosen the screws that attach the backshell strain relief
clamps to permit the clamp halves to move over the harness.
For aluminum backshells, do as follows:
1) Disconnect the strain-relief clamp assembly from the
backshell.
NOTE:
____
Use a TG-70 or BT-BS-611 strap wrench or TG-69
pliers, or equivalent.
2)
(f)
Move the strain-relief clamp assembly to the rear of the
harness and away from the repair area.
3) Remove the conical ring from the rear side of the backshell
and move the ring to the rear of the harness.
Install the correct size connector adapter on the connector
assembly (Fig. 807).
NOTE:
____
(g)
Hold the connector and adapter in your hand and disconnect the
backshell.
NOTE:
____
(h)
(4)
(5)
(6)
The connector adapter kit holds the connector
assembly and prevents movement of the connector when you
remove the backshell. Use the CM-S-837 or CM-S-839T
connector adapter kit, or equivalent.
Use a TG-70 or BT-BS-611 strap wrench or TG-69
pliers, or equivalent. You can also use a standard
crowfoot wrench for the stainless steel backshells.
Move the backshell to the rear of the harness and away from the
repair area.
S 038-068-P00
Remove the red rubber tape found below the strain relief clamps.
S 038-069-P00
Remove the contacts of the damaged wire from the two connectors.
(a) Use the correct contact removal tool for the wire gage of the
conductor and series connector (Fig. 810).
S 358-051-P00
Do these steps to prepare each end of the new cable:
(a) Put the new cable along the wires of the broken cable.
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GROMMET
EXPANDED COLLET
COLLET
CONTACT
REMOVAL TOOL
DIRECTION CONTACT MOVES
CONTACTS RELEASED FROM THE FRONT
GROMMET
COLLET
EXPANDED COLLET
CONTACT
DIRECTION CONTACT MOVES
REMOVAL TOOL
CONTACTS RELEASED FROM THE REAR
CONTACTS REMOVED
C74984
Connector Contact Removal
Figure 810
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(b)
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(c)
Cut the jacket of the new cable at the same location as the
jacket on the broken cable.
Cut the braided shield of the new cable at the same location as
the braided shield on the broken cable.
Pull the braided shield back around the cable as far back as
the braided shield on the broken cable.
Cut the new cable wires the same length as the wires of the
broken cables.
(d)
(e)
(7)
S 358-052-P00
Cut the damaged wires at each end of the broken cable where the
wires come out of the braided shield.
(8)
S 358-070-P00
Use the wire stripper to remove 0.276 inch (7 mm) of insulation from
each end of the new wire (Fig. 811).
S 358-071-P00
CAUTION:
_______
(9)
DO NOT RELEASE THE LATCH FOR THE CRIMP TOOL POSITIONER IF THE
TOOL FRAME HANDLE IS IN THE CLOSED POSITION. THE TOOL HANDLE
MUST BE OPEN WHEN THE POSITIONER IS INSTALLED, REMOVED, OR
RELEASED. INCORRECT USE CAN CAUSE DAMAGE TO THE POSITIONER AND
CRIMP TOOL.
Crimp the contacts on each end of the wire.
(a) Use the correct tool for the wire gage of the conductor and
series connector.
S 358-065-P00
(10) Install the contacts in the electrical connectors:
(a) Use the correct tool for the wire gage of the conductor and
series connectors (Fig. 812).
S 718-072-P00
(11) Do a check of each contact to make sure they are installed
correctly:
NOTE:
____
(a)
Each contact should be resistant to a force of
7 to 13 pounds (31.1 to 57.8 newtons).
Use the correct retention test tool, replacement pin, and
replacement socket tools.
1) Use the pin replacement tips when you do a test of the
socket contacts.
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DATA PLATE
CRIMP TOOL
POSITIONER
SELECTOR KNOB
A
A
POSITIONER
LOCK PLATE
CRIMP TOOL
FRAME
INDEX MARK
PUT CONTACT
INTO THIS SIDE
SEE
WIRE
A
PUT CONTACT
INTO THIS SIDE
CRIMP TOOL
POSITIONER
A-A
WIRE
INSULATION
0.276 INCH
(7.0 mm)
A
C74985
Wire Contact Installation
Figure 811
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CONTACTS
STRESS RELIEF CLAMP
AND COUPLING NUT
CONNECTOR
GROMMET
EXPANDED COLLET
COLLET
INSTALLED
CONTACT
INSERTION
TOOL
DIRECTION CONTACT MOVES
CONTACTS INSTALLED FROM THE FRONT
GROMMET
COLLET
EXPANDED COLLET
INSTALLED
CONTACT
DIRECTION CONTACT MOVES
INSERTION
TOOL
CONTACTS INSTALLED FROM THE REAR
C74986
Connector Contact Installation
Figure 812
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2)
CAUTION:
_______
(b)
(c)
(d)
(e)
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Use the socket replacement tips when you do a test of the
pin contacts.
BE CAREFUL WHEN YOU DO A CHECK OF THE CONTACTS. INCORRECT
USE OF THE RETENTION TEST TOOL CAN CAUSE DAMAGE TO THE
CONTACT, CONNECTOR GROMMET, OR TEST TOOL.
Put the 16 or 20 gage retention test tool and replacement pin
on the contact so they are in a straight line.
To get the most accurate results, keep this position when you
do a test on each contact.
Apply pressure to the tool until you see that a minimum of half
of the color-coded area is covered.
1) At this point, there is 10 pounds (44.5 newtons) of
pressure applied.
2) If the contact is still in the same condition and position,
the contact is satisfactory.
Repeat the above steps for the other contacts.
S 438-073-P00
(12) Prepare the harness for the backshell connection.
(a) Make sure the braided shield in the harness is straight.
CAUTION:
_______
(b)
(c)
DO NOT PUT TAPE AROUND THE BRAIDED SHIELDS. THIS COULD
CAUSE AN INCORRECT GROUND AND CAUSE DAMAGE TO THE
EQUIPMENT.
Wind the red rubber tape (Moxness 620-3/4) around the area of
the harness assembly where the two halves of the backshell
strain-relief clamp are installed (Fig. 808 or 809).
1) Use a sufficient amount of tape around the harness to hold
the harness tight between the clamps.
a) The two clamp bar surfaces must touch at the two screw
hole locations.
b) No movement of the harness in the clamp is permitted.
Fold the braided shield to the rear of the harness and over the
top of the red rubber tape.
1) For the aluminum backshell, put the braided shield equally
around the harness.
2) For the stainless steel backshell, make the braided shields
into two groups:
a) Put one group of the braided shields on the top of the
harness to align with the backshell strain-relief
clamp.
b) Put the other group 180 degrees from the first group.
S 438-074-P00
(13) Connect the backshell to the connector (Fig. 807):
(a) Hold the connector in your hand and move the backshell over the
harness and the folded braided shield.
(b) Connect the backshell coupling nut to the connector.
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(c)
(d)
Tighten the coupling nut by hand to engage the anti-rotation
teeth.
Install the correct size of connector adapter on the connector
assembly (Fig. 807).
NOTE:
____
(e)
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The connector adapter kit is used to hold the
connector assembly and prevent movement of the connector
when you install the backshell. Use the CM-S-837 or
CM-S-839T connector adapter kit, or equivalent.
Tighten the backshell coupling nut to the connector until the
metal surface of the coupling nut touches the metal surface of
the connector.
1) For the aluminum backshell, use a TG-70 or BT-BS-611 strap
wrench, or equivalent.
2) For the stainless steel backshell, use a standard crowfoot,
TG-70, or BT-BS-611 strap wrench, or equivalent.
NOTE:
____
The rubber strap on the strap wrench will not
hold the backshell if you apply too much force.
S 438-075-P00
(14) Install the backshell strain-relief clamp (Fig. 808 or 809).
(a) For connectors with aluminum backshells do as follows:
1) Put the braided shields equally around the conical seat of
the backshell.
2) Move the conical ring over the harness.
3) Put the conical ring into the rear of the backshell with
the braided shields located between the backshell and the
ring.
4) Seat the conical ring into the backshell.
5) If necessary, cut the braided shields that are not
necessary on the rear side of the conical seat.
6) Connect the nut for the strain relief clamp on the
backshell and tighten the nut by hand.
7) Tighten the strain-relief clamp assembly to the backshell
with a TG-70 or BT-BS-611 strap wrench, or equivalent.
NOTE:
____
The rubber strap on the strap wrench will not
hold the backshell if you apply too much force.
8)
Align the harness with each half of the strain-relief
clamp.
a) Make sure the harness is straight.
9) Tighten the strain-relief clamp screws equally to engage
the harness in the clamp correctly.
10) Continue to tighten the screws until the clamp bar surfaces
touch.
a) The harness must not move in the clamp.
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b)
(b)
If the harness is not tight in the clamp, repeat the
step to add the red rubber tape around the harness
assembly.
c) If the clamp bar surfaces do not touch, remove some of
the red rubber tape.
11) Torque the screws to 20 pound-inches (2.26 newton-meters).
For the connectors with the stainless steel backshells, do as
follows:
1) Align the harness in each half of the strain-relief clamp.
a) Make sure the harness is straight.
2) Make sure the two braided shield groups go between the red
rubber tape and the strain-relief clamp halves.
a) Do this for each side of the clamp halves.
3) Tighten the strain-relief clamp screws equally to engage
the harness in the clamp correctly.
a) Make sure the braided shields are straight.
4) Continue to tighten the screws until the clamp bars touch.
a) The harness must not move in the clamp.
b) If the harness is not tight in the clamp, repeat the
step to add the red rubber tape around the harness
assembly.
c) If the clamp bar surfaces do not touch, remove some of
the red rubber tape.
5) Torque the screws to 20 pound-inches (2.26 newton-meters).
6) Fold the two groups of the braided shield over the
strain-relief clamps and into the rear groove of the
backshell.
7) To hold the braided shield, install the hose clamp on the
rear backshell groove over the braided shields.
8) Tighten and torque the hose clamp screws to 20 pound-inches
(2.26 newton-meters).
9) If necessary, cut the front side of the braided shield to
the front of the clamp.
S 768-076-P00
(15) Do the adjustment/test procedure for the cable you repaired
(AMM 71-51-00/501).
S 438-077-P00
(16) Install the lacing tape to the repaired wire harness, as necessary.
S 438-078-P00
(17) Install all the clamps that you removed.
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~¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼
¦
Connector Backshell Torque Limits
¦
¦
Table 802
¦
»¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼ ¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼«
¦
¦
TORQUE
¦
¦
THREAD
»¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼ ¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼«
¦
DIAMETER
¦
pound-inches
¦
newton-meters
¦
¦
inches (mm)
»¼¼¼¼¼¼¼¼¼¼¼¼ ¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼ ¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼«
¦
¦
MIN
¦
MAX
¦
MIN
¦
MAX
¦
»¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼«
¦
0.50 (1.27)
¦
20
¦
26
¦
2.3
¦
2.9
¦
»¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼«
¦
0.56 (1.43)
¦
26
¦
32
¦
2.9
¦
3.6
¦
»¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼«
¦
0.63 (1.59)
¦
26
¦
32
¦
2.9
¦
3.6
¦
»¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼«
¦
0.69 (1.75)
¦
30
¦
36
¦
3.4
¦
4.1
¦
»¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼«
¦
0.75 (1.91)
¦
34
¦
40
¦
3.8
¦
4.5
¦
»¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼«
¦
0.81 (2.06)
¦
40
¦
46
¦
4.5
¦
5.2
¦
»¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼«
¦
0.88 (2.22)
¦
46
¦
50
¦
5.2
¦
5.7
¦
»¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼«
¦
0.94 (2.38)
¦
50
¦
55
¦
5.7
¦
6.2
¦
»¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼«
¦
1.00 (2.54)
¦
55
¦
60
¦
6.2
¦
6.8
¦
»¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼«
¦
1.06 (2.70)
¦
60
¦
65
¦
6.8
¦
7.3
¦
»¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼«
¦
1.13 (2.86)
¦
70
¦
75
¦
7.9
¦
8.5
¦
»¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼«
¦
1.19 (3.02)
¦
75
¦
80
¦
8.5
¦
9.0
¦
»¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼«
¦
1.25 (3.18)
¦
80
¦
85
¦
9.0
¦
9.6
¦
»¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼«
¦
1.31 (3.33)
¦
85
¦
90
¦
9.6
¦
10.2
¦
»¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼«
¦
1.38 (3.49)
¦
90
¦
95
¦
10.2
¦
10.7
¦
»¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼«
¦
1.44 (3.65)
¦
100
¦
110
¦
11.3
¦
12.4
¦
»¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼«
¦
1.50 (3.81)
¦
100
¦
110
¦
11.3
¦
12.4
¦
»¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼«
¦
1.63 (4.13)
¦
110
¦
120
¦
12.4
¦
13.6
¦
»¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼«
¦
1.75 (4.45)
¦
120
¦
130
¦
13.6
¦
14.7
¦
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~¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼
¦
Connector Backshell Torque Limits
¦
¦
Table 802
¦
»¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼ ¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼«
¦
¦
TORQUE
¦
¦
THREAD
»¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼ ¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼«
¦
DIAMETER
¦
pound-inches
¦
newton-meters
¦
¦
inches (mm)
»¼¼¼¼¼¼¼¼¼¼¼¼ ¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼ ¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼«
¦
¦
MIN
¦
MAX
¦
MIN
¦
MAX
¦
»¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼«
¦
1.88 (4.76)
¦
140
¦
150
¦
15.8
¦
16.9
¦
»¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼«
¦
2.00 (5.08)
¦
150
¦
160
¦
16.9
¦
18.1
¦
²¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼…¼¼¼¼¼¼¼¼¼¼¼¼…¼¼¼¼¼¼¼¼¼¼¼¼…¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼…¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¹
H.
Put the Airplane Back to its Usual Condition.
S 418-060-P00
WARNING:
_______
OBEY THE INSTRUCTIONS IN THE PROCEDURE TO CLOSE THE THRUST
REVERSERS. IF YOU DO NOT OBEY THE INSTRUCTIONS, INJURIES TO
PERSONS AND DAMAGE TO EQUIPMENT CAN OCCUR.
(1)
Close the thrust reversers (AMM 78-31-00/201).
(2)
S 418-061-P00
Close the core cowl panels (AMM 71-11-06/201).
(3)
S 418-063-P00
Close the fan cowl panels (AMM 71-11-04/201).
(4)
S 448-062-P00
Do the activation procedure for the thrust reverser
(AMM 78-31-00/201).
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5.
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TASK 71-51-00-358-084-P00
Repair the EEC Wiring Harness
_____________________________
A. General
(1) This section gives the steps to repair the EEC wire harnesses that
are damaged.
B. References
(1) AMM 71-11-04/201, Fan Cowl Panels
(2) AMM 71-51-00/801, Engine Wire Harness
C. Access
(1) Location Zone
411
Left Engine
421
Right Engine
(2)
Access Panels
413AL
Fan
414AR
Fan
423AL
Fan
424AR
Fan
Cowl
Cowl
Cowl
Cowl
Panel
Panel
Panel
Panel
(Left)
(Right)
(Left)
(Right)
D.
Prepare To Do the Repair:
E.
S 018-096-P00
(1) Open the fan cowl panels (AMM 71-11-04/201).
Repair the EEC Wire Harnesses.
S 358-086-P00
If the EEC wire harness is damaged, you can replace the wire
harness, or do one of these repairs if it is necessary
(AMM 71-51-00/801):
(a) A cable splice.
(b) A repair to the external jacket or braid.
(c) Cable replacement.
Put the Airplane Back To Its Usual Condition.
(1)
F.
(1)
6.
S 418-087-P00
Close the fan cowl panels (AMM 71-11-04/201).
TASK 71-51-00-358-088-P00
Approved Repairs For the Shield On the Thermocouple Ground Wire For the EEC
___________________________________________________________________________
Wiring Harness
______________
A. General
(1) This procedure gives the steps to repair the thermocouple ground
wire for EEC wire harnesses W5050, W5052, and W5058. The
thermocouple ground wires for the W5050, and W5052 wire harnesses
are at the EEC thermocouple probe for the fuel temperature, and the
EEC thermocouple probe for the oil temperature. The thermocouple
ground wire for the W5058 wire harness is at the EGT (T4.9)
thermocouple junction box.
B. References
(1) AMM 71-11-04/201, Fan Cowl Panels
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C.
(2) AMM 71-11-06/201, Core Cowl Panels
(3) AMM 78-31-00/201, Thrust Reverser System
Access
(1) Location Zone
411
Left Engine
421
Right Engine
(2)
D.
E.
F.
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Access Panels
413AL
Fan Cowl Panel (Left)
414AR
Fan Cowl Panel (Right)
415AL
Thrust Reverser (Left)
416AR
Thrust Reverser (Right)
417AL
Core Cowl Panel (Left)
418AR
Core Cowl Panel (Right)
423AL
Fan Cowl Panel (Left)
424AR
Fan Cowl Panel (Right)
425AL
Thrust Reverser (Left)
426AR
Thrust Reverser (Right)
427AL
Core Cowl Panel (Left)
428AR
Core Cowl Panel (Right)
Equipment
(1) Crimping Die - Thomas & Betts 11-10743
(2) Crimping Tool - Kell Strom Tool 9046119
(3) Crimping Tool - AMP Special Industries Model 49513
(4) Crimping Tool - Thomas & Betts Model WT-111-M
Consumable Materials
(1) F00170, Braid, P/N 10-180237-1
(2) G02286, Clamp, P/N 10-609688
(3) G02286, Clamp, P/N 10-609674
(4) G00661, Sleeve - Teflon, P/N 10-180063-7
(5) Tape - Insulation, P/N 10-180106-2
(6) G00861, Terminal - Grounding, P/N 10-92824-104
(7) Terminal - Grounding, P/N 10-609568
Prepare for the Repair (Fig. 813 and 814).
(1)
S 018-089-P00
Do these steps to prepare for the repair:
(a) AIRPLANES WITH WIRE HARNESS W5050 AND W5052;
Open the left fan cowl panel (AMM 71-11-04/201).
1) For the ground wire at the thermocouple probe for the EEC
fuel temperature, do these steps:
a) Remove the bolts that hold the thermocouple shield to
the cable support bracket.
b) Remove the shield from the engine.
2) Remove the bolts that hold the cable clamps and ground
wires to the cable support bracket.
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FUEL/OIL
HEAT EXCHANGER
SEE
SEE
A
B
SEE
C
FWD
A
FUEL/OIL HEAT
EXCHANGER
SEE
D
OIL TANK
FWD
B
C71662
Wiring Harness W5050 and W5052 Preparation for Repair
Figure 813 (Sheet 1)
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MAINTENANCE MANUAL
CABLE SUPPORT
BRACKET
NUT
(3 LOCATIONS)
EEC FUEL TEMPERATURE
THERMOCOUPLE PROBE
GROUND LEAD
GROUND LEAD
CLAMP
(3 LOCATIONS)
BOLT
(3 LOCATIONS)
WASHER
(2 LOCATIONS)
NUT
(2 LOCATIONS)
WASHER
(2 LOCATIONS)
NUT
(3 LOCATIONS)
NUT
(2 LOCATIONS)
THERMOCOUPLE
SHIELD
BOLT
(3 LOCATIONS)
C
CABLE
SUPPORT
BRACKET
BOLT
NUT
CLAMP
(2 LOCATIONS)
EEC OIL TEMPERATURE
THERMOCOUPLE PROBE
GROUND
LEAD
GROUND LEAD
WASHER
(2 LOCATIONS)
NUT
(2 LOCATIONS)
BOLT
NUT
WASHER
(2 LOCATIONS)
NUT
(2 LOCATIONS)
D
C71679
Wiring Harness W5050 and W5052 Preparation for Repair
Figure 813 (Sheet 2)
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MAINTENANCE MANUAL
SEE
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A
BOLT
NUT
NUT-AL
WASHER-AL
GROUND LEAD
NUT-CH
WASHER-CH
CLAMP
FWD
EGT (T4.9) THERMOCOUPLE JUNCTION BOX
A
C71700
Wiring Harness W5058 Preparation for Repair
Figure 814
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71-51-00
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3)
(b)
Remove the nuts that hold the thermocouple cables to the
probe.
a) Remove the thermocouple cables.
4) Move the identification label for the wire harness away
from the cable terminals.
a) Move the protection tubing away from the cable
terminals.
AIRPLANES WITH WIRE HARNESS W5058;
Do these steps:
WARNING:
_______
1)
2)
3)
4)
CAUTION:
_______
DO THE DEACTIVATION PROCEDURE TO PREVENT THE
OPERATION OF THE THRUST REVERSERS. THE ACCIDENTAL
OPERATION OF THE THRUST REVERSERS CAN CAUSE INJURIES
TO PERSONS AND DAMAGE TO EQUIPMENT.
Open the core cowl panels (AMM 71-11-06/201).
Remove the bolt that holds the cable clamp and the ground
lead at the EGT (T4.9) thermocouple junction box.
Remove the bolt that holds the thermocouple cable to the
junction box for the EGT (T4.9) thermocouple.
a) Remove the thermocouple cables.
Move the steel identification label for the wire harness
away from the cable terminals.
MAKE SURE THAT THE TAPE AND THE TERMINALS ARE NOT DAMAGED
DURING THE CLAMP REMOVAL. DAMAGED TAPE AND TERMINALS CAN
CAUSE THERMOCOUPLE SIGNAL DETERIORATION.
(c)
G.
Remove the dual clamp that goes around the thermocouple
terminal pair.
1) Discard the clamps.
Repair the EEC Wire Harness W5050, W5052, and the Shield For the W5058
Thermocouple Ground (Fig. 815 and 816).
(1)
S 358-090-P00
Do these steps to do the repair:
(a) Remove the outer cover of the thermocouple cable to open a 1/2
inch of the inner shield braid.
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BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
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MAINTENANCE MANUAL
GROUNDING
LEAD
OUTER JACKET
0.5 INCHES
(12.7 mm)
INNER
SHIELDING
BRAID
W5050
OR W5052
HARNESS
OUTER
JACKET
INNER
SHIELDING
BRAID
CONNECTOR
STRIPPING OUTER JACKET
APPLYING BRAID
GROUNDING
LEAD
TAPE
INNER
SHIELDING
BRAID
W5050
OR W5052
HARNESS
CONNECTOR
OUTER
JACKET
CLAMP
3.8-4.2 INCHES
(96.5-106.7 mm)
GROUNDING
TERMINAL
WRAPPING TAPE AND INSTALLING CLAMP
SLEEVE
CLAMP
TEFLON
SLEEVE
W5050
OR W5052
HARNESS
C71703
INSTALLING GROUNDING TERMINAL
EEC Wiring Harness W5050 and W5052 Thermocouple Grounding lead Shield Repair
Figure 815
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OUTER JACKET
GROUNDING
LEAD
W5058
HARNESS
0.5 INCH
(12.7 mm)
OUTER
JACKET
INNER
SHIELDING
BRAID
INNER
SHIELDING
BRAID
CONNECTOR
STRIPPING OUTER JACKET
APPLYING BRAID
TAPE
CONNECTOR
W5058
HARNESS
GROUNDING
LEAD
OUTER
JACKET
INNER
SHIELDING
BRAID
CLAMP
WRAPPING TAPE AND INSTALLING CLAMP
3.0-3.8 INCHES
(76.2-96.5 mm)
W5058
HARNESS
GROUNDING
TERMINAL
INSTALLING GROUNDING TERMINAL
C71705
EEC Wiring Harness W5058 Thermocouple Grounding Lead Shield Repair
Figure 816
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MAINTENANCE MANUAL
(b)
(c)
(d)
(e)
(f)
(g)
(h)
(i)
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Apply a braid to the shield.
1) Go around the cable three times in the direction shown
(Fig. 815 and 816).
AIRPLANES WITH WIRE HARNESS W5050 AND W5052;
Fold the braid along the cable away from the connectors as
shown (Fig. 815).
AIRPLANES WITH WIRE HARNESS W5058;
Fold the braid along the cable to the connectors as shown
(Fig. 816).
Apply five layers of tape around the braid as shown (Fig. 815
and 816).
AIRPLANES WITH WIRE HARNESSES W5050 AND W5052;
Do the steps that follow:
1) Put the clamp (10-609688) on the cable.
a) Put the rear tab on the repaired area as shown
(Fig. 815).
2) Move the ground wire to make it exit from the rear of the
clamp as shown (Fig. 815).
AIRPLANES WITH WIRING HARNESS W5058;
Do the steps that follow:
1) Put the clamp (10-609674) on the cable.
a) Put the rear tab on the center of the repaired area as
shown (Fig. 816).
2) Move the ground wire to make it exit from the front of the
rear tab of the clamp as shown (Fig. 816).
Crimp the clamp at the Alumel and Chromel connectors with the
crimping die (11-10743).
1) Crimp the rear clamp around the repaired area using the
crimping tool (9046119).
AIRPLANES WITH WIRE HARNESS W5050 AND W5052;
Do the steps that follow:
1) Install the teflon sleeve on the braided ground wire.
2) Crimp the ground terminal (10-92824-104) to the braided
ground wire so that the braided ground wire is the length
shown (Fig. 815).
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3)
H.
Move the teflon sleeve into the shield clamp on the braided
ground wire.
a) Crimp the teflon shield in its position as shown.
(j) AIRPLANES WITH WIRE HARNESS W5058;
Crimp the ground terminal (10-609568) to the braided ground
wire so that the braided ground wire is the length shown
(Fig. 816).
Put the Airplane Back To Its Usual Condition (Fig. 813 and 814).
(1)
S 418-091-P00
AIRPLANES WITH WIRE HARNESSES W5050 AND W5052;
Do these steps:
(a) Move the identification label for the wire harness and the
protection tubing to the cable terminals.
(b) Install the thermocouple cables to the thermocouple probe
terminals with the washers and nuts.
1) Tighten the alumel connections (larger nut) to 10-15
pound-inches (1.130-1695 newton meters).
2) Tighten the chromel connections (smaller nut) to 8-12
pound-inches (0.904-1.356 newton meters).
(c) For the ground wires at the EEC thermocouple probe, do these
steps:
1) Attach the thermocouple cable and the braided ground wires
to the cable support bracket in the two locations with the
clamps, bolts, and nuts.
2) Attach the thermocouple cable to the cable support bracket
with the clamp, bolt, and nut.
3) Attach the thermocouple shield to the cable support bracket
with bolts and nuts.
(d) For the ground wires at the EEC oil probe, do these steps:
1) Attach the thermocouple cable and the braided ground wire
to the cable support bracket with the clamp, bolt, and nut.
2) Attach the thermocouple cable to the cable support bracket
with the clamp, bolt, and nut.
3) Attach the braided ground wire to the cable support bracket
with the bolt and nut.
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(e)
(2)
(3)
(4)
Close the left fan cowl panel (AMM 71-11-04/201).
S 418-092-P00
AIRPLANES WITH WIRE HARNESS W5058;
Do these steps:
(a) Move the steel identification label back to the cable
connectors.
(b) Install the thermocouple cable leads to the terminals on the
EGT (T4.9) thermocouple junction box with the washers and nuts.
1) Tighten the alumel connections (larger nut) to 10-15
pound-inches (1.130-1695 newton meters).
2) Tighten the chromel connections (smaller nut) to 8-12
pound-inches (0.904-1.356 newton meters).
(c) Attach the thermocouple cable and the braided ground wire to
the bracket that is forward of the junction box for the EGT
(T4.9) thermocouple.
S 448-093-P00
Do the activation procedure for the thrust reverser
(AMM 78-31-00/201).
S 418-094-P00
Close the core cowl panels (AMM 71-11-06/201).
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MAINTENANCE MANUAL
ENGINE VENTS AND DRAINS - DESCRIPTION AND OPERATION
___________________________________________________
1.
2.
_______ (Fig. 1)
General
A. The engine drain system collects drain fluid and lets the drain fluids
fall overboard through a port in the access door on the lower fan cowl
panel.
B. The engine vents are used to bleed air overboard.
C. There are nine drains and two vents. The vents are the IDG thermal
relief vent and the deoiler overboard ejector tube vent. The drain
outlets are all in one group.
D. There are six fittings with caps on them in the drain system which are
used as fluid traps. You can use these fluid traps to help you isolate
the source of leakage when fluids from the drain mast are found.
Component Details
_________________
A. Drains (Fig. 2)
(1) Electronic Engine Control (EEC) Alternator Drain
(2) Hydraulic Pump Pad Seal Drain
(3) Fuel Pump Pad Seal Drain
(4) Starter Pad Seal Drain
(5) Oil Tank Scupper and Fuel/Oil Heat Exchanger Bypass Valve Drain
(a) Fuel/Oil Heat Exchanger Bypass Valve section of this drain has
a capped fitting which you can used as a fluid trap to isolate
the source of leakage.
(6) Fuel/Oil Heat Exchanger Drain
(7) Integrated Drive Generator (IDG) Pad Seal Drain
(8) Core Accessories Drain
(a) This drain line collects fluids from the components that
follow:
1) Intercompressor (2.5) Bleed Actuator
2) HP Compressor and HP Turbine Case Cooling Air Valve
3) LP Turbine Case Cooling Air Valve
4) Stator Vane Actuator
5) Air/Oil Heat Exchanger Valve
6) 14TH-Stage Bleed Converter Valve.
(b) All of the above components have a different fitting with a cap
on it, in the drain line but the stator vane actuator.
(c) When fluid drains from the core accessory drain line, you can
use fluid traps to help you isolate the source of the leakage.
(9) Strut Drain
B. Vents
(1) The Integrated Drive Generator (IDG) thermal relief vent releases
hot oil through the lower access door in the fan cowl panels.
(2) The deoiler breather vent releases clean air near the drain outlets.
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71-71-00
P03
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
Page 1
Jan 28/02
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P03
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
FLUID TRAP IS HORIZONTAL
LOWER
BIFURCATION
DISCONNECT
PANEL
STATOR VANE
ACTUATOR
FLUID
TRAP
INTERCOMPRESSOR
(2.5)BLEED
ACTUATOR
Fluid Drain System
Figure 1 (Sheet 1)
CORE ACCESSORIES DRAIN
FLUID
TRAP
AIR/OIL HEAT
EXCHANGER VALVE
LP TURBINE
CASE COOLING
AIR VALVE
HP COMPRESSOR AND
HP TURBINE CASE
COOLING AIR VALVE
FUEL/OIL
HEAT EXCHANGER
BYPASS VALVE
FLUID TRAP
FUEL/OIL
HEAT
EXCHANGER
IDG THERMAL
RELIEF VALVE
ENGINE
OIL TANK
IDG PAD
SEAL
STARTER
PAD SEAL
FUEL
PUMP
PAD
SEAL
MAIN GEARBOX
HYDRAULIC
PUMP
PAD SEAL
DEOILER
EEC
ALTERNATOR
PAD SEAL
DEOILER
FACE
SEAL
757
MAINTENANCE MANUAL
1
FLUID
TRAP
14TH-STAGE
BLEED CONVERTER
VALVE
FLUID
1
TRAP
STRUT
A
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71-71-00
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Jan 28/02
E32942
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P03
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
LOWER
BIFURCATION
DISCONNECT
PANEL
STATOR VANE
ACTUATOR
FLUID TRAP IS HORIZONTAL
FLUID
TRAP
FLUID
TRAP
INTERCOMPRESSOR
(2.5) BLEED
ACTUATOR
Fluid Drain System
Figure 1 (Sheet 2)
CORE ACCESSORIES DRAIN
FLUID
TRAP
AIR/OIL HEAT
EXCHANGER VALVE
LP TURBINE
CASE COOLING
AIR VALVE
HP COMPRESSOR AND
HP TURBINE CASE
COOLING AIR VALVE
FUEL/OIL
HEAT EXCHANGER
BYPASS VALVE
FLUID TRAP
FUEL/OIL
HEAT
EXCHANGER
IDG THERMAL
RELIEF VALVE
ENGINE
OIL TANK
IDG PAD
SEAL
STARTER
PAD SEAL
FUEL
PUMP
PAD
SEAL
MAIN GEARBOX
HYDRAULIC
PUMP
PAD SEAL
DEOILER
EEC
ALTERNATOR
PAD SEAL
DEOILER
FACE
SEAL
757
MAINTENANCE MANUAL
1
14TH-STAGE
BLEED
CONVERTER
VALVE
TURBINE COOLING AIR
VALVE ACTUATOR
FLUID
1
TRAP
STRUT
A
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SEE A
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SEE B
IDG THERMAL
RELIEF VALVE
DRAIN
IDG PAD
SEAL DRAIN
STARTER PAD
SEAL DRAIN
FUEL PUMP PAD
SEAL DRAIN
HYDRAULIC PUMP
PAD SEAL DRAIN
STRUT
DRAIN
FWD
CORE
ACCESSORIES
DRAIN
EEC ALTERNATOR
PAD SEAL DRAIN
OIL TANK
SCUPPER AND
FUEL/OIL
HEAT
EXCHANGER
DRAIN
A
108101
Engine Vents and Drains
Figure 2 (Sheet 1)
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DEOILER
OUTLET
ELBOW
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DEOILER
FWD
OVERBOARD
EJECTOR TUBE
B
L-95370
F68476
Engine Vents and Drains
Figure 2 (Sheet 2)
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ENGINE VENTS AND DRAINS
_______________________
COMPONENT
DRAIN - LEFT ENGINE CORE ACCESSORY
DRAIN - RIGHT ENGINE CORE ACCESSORY
DRAIN - LEFT ENGINE EEC ALTERNATOR PAD SEAL
DRAIN - RIGHT ENGINE EEC ALTERNATOR PAD SEAL
DRAIN - LEFT ENGINE FUEL PUMP PAD SEAL
DRAIN - RIGHT ENGINE FUEL PUMP PAD SEAL
DRAIN - LEFT ENGINE HYDRAULIC PUMP PAD SEAL
DRAIN - RIGHT ENGINE HYDRAULIC PUMP PAD SEAL
DRAIN - LEFT ENGINE IDG PAD SEAL
DRAIN - RIGHT ENGINE IDG PAD SEAL
DRAIN - LEFT ENGINE OIL TANK SCUPPER AND
FUEL/OIL HEAT EXCHANGER BYPASS VALVE
DRAIN - RIGHT ENGINE OIL TANK SCUPPER AND
FUEL/OIL HEAT EXCHANGER BYPASS VALVE
DRAIN - LEFT ENGINE STARTER PAD SEAL
DRAIN - RIGHT ENGINE STARTER PAD SEAL
DRAIN - LEFT ENGINE STRUT
DRAIN - RIGHT ENGINE STRUT
TRAP - LEFT ENGINE AIR/OIL HEAT EXCHANGER
VALVE DRAIN LINE FLUID
TRAP - RIGHT ENGINE AIR/OIL HEAT EXCHANGER
VALVE DRAIN LINE FLUID
TRAP - LEFT ENGINE FUEL/OIL HEAT EXCHANGER
BYPASS VALVE DRAIN LINE FLUID
TRAP - RIGHT ENGINE FUEL/OIL HEAT EXCHANGER
BYPASS VALVE DRAIN LINE FLUID
TRAP - LEFT ENGINE HP COMPRESSOR AND HP
TURBINE CASE COOLING AIR VALVE DRAIN LINE
FLUID
TRAP - RIGHT ENGINE HP COMPRESSOR AND HP
TURBINE CASE COOLING AIR VALVE DRAIN LINE
FLUID
TRAP - LEFT ENGINE INTERCOMPRESSOR (2.5)
BLEED ACTUATOR DRAIN LINE FLUID
TRAP - RIGHT ENGINE INTERCOMPRESSOR (2.5)
BLEED ACTUATOR DRAIN LINE FLUID
TRAP - LEFT ENGINE LP TURBINE CASE COOLING
AIR VALVE DRAIN LINE FLUID
TRAP - RIGHT ENGINE LP TURBINE CASE COOLING
AIR VALVE DRAIN LINE FLUID
TRAP - LEFT ENGINE 14TH STAGE BLEED
CONVERTER VALVE DRAIN LINE FLUID
TRAP - RIGHT ENGINE 14TH STAGE BLEED
CONVERTER VALVE DRAIN LINE FLUID
TRAP - LEFT ENGINE STATOR VANE ACTUATOR
DRAIN LINE FLUID
TRAP - RIGHT ENGINE STATOR VANE ACTUATOR
DRAIN LINE FLUID
VENT - LEFT ENGINE IDG THERMAL RELIEF
VENT - RIGHT ENGINE IDG THERMAL RELIEF
FIG.
102 QTY
SHT
AMM
REFERENCE
ACCESS/AREA
1
1
1
1
1
1
1
1
1
1
1
1
1
1
1
1
1
1
1
1
1
1
414AR,
424AR,
414AR,
424AR,
414AR,
424AR,
414AR,
424AR,
414AR,
424AR,
414AR,
COLLECTOR
COLLECTOR
COLLECTOR
COLLECTOR
COLLECTOR
COLLECTOR
COLLECTOR
COLLECTOR
COLLECTOR
COLLECTOR
COLLECTOR
71-71-00
71-71-00
71-71-00
71-71-00
71-71-00
71-71-00
71-71-00
71-71-00
71-71-00
71-71-00
71-71-00
1
1
414AR, DRAIN COLLECTOR
71-71-00
1
1
1
1
2
1
1
1
1
1
414AR,
424AR,
414AR,
424AR,
415AL,
DRAIN COLLECTOR
DRAIN COLLECTOR
DRAIN COLLECTOR
DRAIN COLLECTOR
THRUST REVERSER
71-71-00
71-71-00
71-71-00
71-71-00
71-71-00
2
1
425AL, THRUST REVERSER
71-71-00
2
1
414AR, DRAIN COLLECTOR
71-71-00
2
1
424AR, DRAIN COLLECTOR
71-71-00
3
1
415AL, THRUST REVERSER
71-71-00
3
1
425AL, THRUST REVERSER
71-71-00
4
1
415AL, THRUST REVERSER
71-71-00
4
1
425AL, THRUST REVERSER
71-71-00
3
1
415AL, THRUST REVERSER
71-71-00
3
1
425AL, THRUST REVERSER
71-71-00
2
1
416AR, THRUST REVERSER
71-71-00
2
1
426AR, THRUST REVERSER
71-71-00
4
1
416AR, THRUST REVERSER
71-71-00
4
1
426AR, THRUST REVERSER
71-71-00
1
1
1
1
414AR, DRAIN COLLECTOR
424AR, DRAIN COLLECTOR
71-71-00
71-71-00
DRAIN
DRAIN
DRAIN
DRAIN
DRAIN
DRAIN
DRAIN
DRAIN
DRAIN
DRAIN
DRAIN
97894
Engine Vents and Drains - Component Index
Figure 101
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DRAIN COLLECTOR
SEE
A
IDG THERMAL
RELIEF VENT
STRUT
DRAIN
CORE
ACCESSORIES
DRAIN
IDG PAD
SEAL DRAIN
STARTER PAD
SEAL DRAIN
FUEL PUMP PAD
SEAL DRAIN
MAIN
GEARBOX
(REF)
HYDRAULIC PUMP
PAD SEAL DRAIN
EEC ALTERNATOR
PAD SEAL DRAIN
OIL TANK SCUPPER
AND FUEL/OIL HEAT
HEAT EXCHANGER
FWD
DRAIN COLLECTOR
A
98274
Engine Vents and Drains - Component Location
Figure 102 (Sheet 1)
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FAULT ISOLATION/MAINT MANUAL
LEFT FAN
COWL PANEL,
413AL,423AL
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14TH-STAGE
BLEED
CONVERTER
VALVE
LEFT THRUST
REVERSER
415AL,425AL
SEE
B
AIR/OIL HEAT
EXCHANGER
SEE
C
ENGINE
OIL TANK
SEE
D
14TH-STAGE
BLEED
CONVERTER
VALVE
AIR/OIL HEAT
EXCHANGER VALVE
FLUID TRAP
B
FUEL/OIL HEAT
EXCHANGER
FLUID TRAP
AIR/OIL HEAT EXCHANGER
C
FLUID
TRAP
OIL TANK
OIL TANK
(REF)
D
276520
Engine Vents and Drains - Component Location
Figure 102 (Sheet 2)
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THRUST REVERSER,
415AR (LEFT ENGINE OUTBOARD),
HIGH PRESSURE
425AR (RIGHT ENGINE INBOARD)
COMPRESSOR AND
HIGH PRESSURE TURBINE
CASE COOLING AIR VALVE
SEE
F
LOW PRESSURE
TURBINE CASE
COOLING AIR
VALVE
SEE
E
THRUST REVERSER,
416AR (LEFT ENGINE INBOARD),
426AR (RIGHT ENGINE OUTBOARD)
HIGH PRESSURE COMPRESSOR
AND HIGH PRESSURE TURBINE
CASE COOLING AIR VALVE
FLUID
TRAP
LOW PRESSURE
TURBINE CASE
COOLING AIR
VALVE
FLUID TRAP
LOW PRESSURE TURBINE
CASE COOLING AIR VALVE
HIGH PRESSURE COMPRESSOR AND HIGH PRESSURE
TURBINE CASE COOLING AIR VALVE
E
F
276547
Engine Vents and Drains - Component Location
Figure 102 (Sheet 3)
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THRUST REVERSER,
416AR (LEFT ENGINE INBOARD),
426AR (RIGHT ENGINE OUTBOARD)
INTERCOMPRESSOR
(2.5) BLEED
ACTUATOR
SEE
H
THRUST REVERSER,
415AL (LEFT ENGINE OUTBOARD),
425AL (RIGHT ENGINE INBOARD)
STATOR VANE
ACTUATOR
SEE
G
INTERCOMPRESSOR
(2.5) BLEED
ACTUATOR (REF)
STATOR VANE
ACTUATOR (REF)
FLUID TRAP
FLUID TRAP
INTERCOMPRESSOR (2.5) BLEED ACTUATOR
H
STATOR VANE ACTUATOR
G
276568
Engine Vents and Drains - Component Location
Figure 102 (Sheet 4)
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THRUST REVERSER,
416AR (LEFT ENGINE INBOARD),
426AR (RIGHT ENGINE OUTBOARD)
TCAV
ACTUATOR
SEE
I
TCAV
ACTUATOR
STATOR VANE
ACTUATOR
(REF)
DRAIN FROM
TCAV
ACTUATOR
CORE DRAIN
ACCESSORIES
TCAV ACTUATOR
I
E33294
Engine Vents and Drains - Component Location
Figure 102 (Sheet 5)
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ENGINE VENTS AND DRAINS - MAINTENANCE PRACTICES
_______________________________________________
1.
TASK 71-71-00-172-001-P00
Clear the Strut Drain Line (Fig. 201)
__________________________
A. General
(1) This task has the instructions to make sure the strut drain is
clear. It is recommended that you clear the strut drain line when
you have access to the drain during other maintenance.
B. Equipment
(1) Compressed Air Source, regulated
with a hose and a nozzle
C. References
(1) 54-53-01/401, Strut Pressure Relief and Access Doors
(2) 71-11-04/201, Fan Cowl Panels
(3) 71-11-06/201, Core Cowl Panels
(4) 78-31-00/201, Thrust Reverser System
D. Access
(1) Location Zones
411
Left Engine
421
Right Engine
433
Left Strut
443
Right Strut
(2)
E.
Access Panels
413AL
Fan Cowl Panel, Left Engine
415AL
Thrust Reverser, Left Engine
417AL
Core Cowl Panel, Left Engine
433AL
Strut Access Panel, Left Strut
423AL
Fan Cowl Panel, Right Engine
425AL
Thrust Reverser, Right Engine
427AL
Core Cowl Panel, Right Engine
443AL
Strut Access Panel, Right Strut
Procedure
(1)
S 012-002-P00
Open the left fan cowl panel (Ref 71-11-04/201).
S 042-003-P00
WARNING:
_______
(2)
DO THE THRUST REVERSER DEACTIVATION PROCEDURE TO PREVENT THE
OPERATION OF THE THRUST REVERSERS. THE ACCIDENTAL OPERATION OF
THE THRUST REVERSERS CAN CAUSE INJURIES TO PERSONS OR DAMAGE TO
EQUIPMENT.
Do this procedure: Thrust Reverser Deactivation for Ground
Maintenance (Ref 78-31-00/201).
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SEE B
SEE A
STRUT
DRAIN
FWD
A
127740
Strut Drain
Figure 201 (Sheet 1)
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ACCESS PANEL,
433AL (443AL)
STRUT DRAIN
INLET 1
FORWARD LOWER
ENGINE MOUNT
STRUT DRAIN LINE
B
1
PART OF THE STRUT IS
REMOVED TO SHOW THE STRUT
DRAIN INLET
127857
Strut Drain
Figure 201 (Sheet 2)
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MAINTENANCE MANUAL
(3)
S 012-004-P00
Open the left core cowl panel (Ref 71-11-06/201).
S 012-005-P00
WARNING:
_______
OBEY THE INSTRUCTIONS IN AMM 78-31-00/201 WHEN YOU OPEN THE
THRUST REVERSER. IF YOU DO NOT OBEY THE INSTRUCTIONS, YOU CAN
CAUSE INJURIES TO PERSONS OR DAMAGE TO EQUIPMENT.
(4)
Open the left thrust reverser (Ref 78-31-00/201).
(5)
S 012-006-P00
Remove the strut access panel on the left, forward side of the strut
to get access to the strut drain inlet (Ref 54-53-01/401).
(6)
(7)
S 142-007-P00
Remove all of the unwanted material from the strut drain inlet.
S 172-008-P00
Supply air at a pressure of 20-30 psig at the strut drain exit in
the drain mast.
(a) Make sure the line is clear to the strut drain inlet.
S 142-009-P00
Remove all of the unwanted material from the strut drain inlet
again.
Put the Airplane Back to its Usual Condition.
(8)
F.
(1)
S 412-010-P00
Install the strut access panel (Ref 54-53-01/401).
S 412-011-P00
WARNING:
_______
OBEY THE INSTRUCTIONS IN AMM 78-31-00/201 WHEN YOU CLOSE THE
THRUST REVERSER. IF YOU DO NOT OBEY THE INSTRUCTIONS, YOU CAN
CAUSE INJURIES TO PERSONS OR DAMAGE TO EQUIPMENT.
(2)
Close the left thrust reverser (Ref 78-31-00/201).
(3)
S 412-012-P00
Close the left core cowl panel (Ref 71-11-06/201).
(4)
(5)
S 442-013-P00
Do the activation procedure for the thrust reverser
(Ref 78-31-00/201).
S 412-014-P00
Close the left fan cowl panel (Ref 71-11-04/201).
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ENGINE VENTS AND DRAINS - INSPECTION/CHECK
__________________________________________
1.
2.
General
_______
A. This procedure contains two tasks. The first task gives the instructions
to find out the leakage from the engine drains. The second task gives
the limits to examine the engine strut drain tubes and vents (referred to
as the drain tubes).
B. The table on the pages that follow gives the maximum leakage from the
engine components during the engine operation and after the engine
shutdown.
C. The drain outlets are in the fan cowl and thrust reverser and the exhaust
sleeve.
D. If one drain line is used for more than one component, a fluid trap is
included to help you isolate the source of the fluid leakage.
TASK 71-71-00-226-001-P00
Examine the Engine Drains
_________________________
A. References
(1) AMM 29-11-00/601, Main (Left, Right, and Center) Hydraulic Systems
(2) AMM 29-11-05/401, Engine Driven Hydraulic Pump
(3) AMM 72-61-02/401, Accessory Drive Seals
(4) AMM 73-11-01/401, Fuel Pump
(5) AMM 73-11-03/401, Fuel Distribution Valve
(6) AMM 75-24-01/401, LP Turbine Case Cooling Air Valve
(7) AMM 75-24-03/401, HP Compressor & HP Turbine Case Cooling Air Valve
(8) AMM 75-24-23/401, Turbine Cooling Air Valve (TCAV) Actuator
(9) AMM 75-31-01/401, Stator Vane Actuator
(10) AMM 75-32-01/401, Intercompressor (2.5) Bleed Actuator
(11) AMM 75-32-03/401, 14TH-Stage Bleed Converter Valve
(12) AMM 79-21-01/401, Fuel/Oil Heat Exchanger
(13) AMM 79-21-02/401, Fuel/Oil Heat Exchanger Bypass Valve
(14) AMM 79-21-08/401, Air/Oil Heat Exchanger Valve
B. Access
(1) Location Zones
413
L Power Plant Fan Cowl Panel
414
L Power Plant Fan Cowl Panel
415
L Power Plant Fan Reverser
416
L Power Plant Fan Reverser
423
R Power Plant Fan Cowl Panel
424
R Power Plant Fan Cowl Panel
425
R Power Plant Fan Reverser
426
R Power Plant Fan Reverser
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MAINTENANCE MANUAL
(2)
C.
Access Panels
413AL
Fan
414AR
Fan
415AL
Fan
416AR
Fan
423AL
Fan
424AR
Fan
425AL
Fan
426AR
Fan
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Cowl Panel (Left)
Cowl Panel (Right)
Reverser (Left)
Reverser (Right)
Cowl Panel (Left)
Cowl Panel (Right)
Reverser (Left)
Reverser (Right)
Examine the Engine Drains (Fig. 601)
S 226-002-P00
CAUTION:
_______
(1)
DO NOT INSTALL A PLUG OR CAP ON THE OVERBOARD SEAL DRAIN WHEN
THERE IS MORE LEAKAGE THAN THE LIMITS. IF YOU INSTALL A PLUG
OR CAP, THE FLUID WHICH DRAINS CAN COLLECT IN AN EMPTY SPACE IN
THE SEAL DRAIN. THIS CAN CAUSE MORE SEAL FAILURE AND
CONTAMINATION OF THE ENGINE OIL SYSTEM AND ACCESSORIES, OR LET
OUT FLAMMABLE FLUIDS OR FLUIDS WHICH CAUSE CORROSION INTO THE
COWLING.
Examine the drains for too much leakage.
(a) Use the leakage limits in the table that follows.
(b) If the leakage is more than the limits, do the steps in the
table that follows to correct the leakage.
~¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼ ¼¼¼¼¼¼¼¼ ¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼ ¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼
¦
¦
¦
PERMITTED LEAKAGE
¦
¦
¦
¦
»¼¼¼¼¼¼¼¼¼¼¼ ¼¼¼¼¼¼¼¼¼¼¼«
¦
¦
¦
¦
DURING ¦
AFTER
¦
CORRECTIVE
¦
¦ DRAIN/COMPONENT ¦ LIQUID ¦ OPERATION ¦ SHUTDOWN ¦
ACTION
¦
»¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼«
¦ Strut
¦ Is usually dry. The leakage
¦ Examine the drains in the ¦
¦
¦ shows that the leak is in the ¦ strut for leaks and repair¦
¦
¦ strut-contained system.
¦ the leaks as it is
¦
¦
¦
¦ necessary.
¦
»¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼«
¦ Stator Vane
¦ Fuel
¦ 1.0 cc/min¦ 1.0 cc/min¦ Replace the stator vane
¦
¦ Actuator *[1] ¦
¦(20 drops/ ¦(20 drops/ ¦ actuator
¦
¦
*[6] ¦
¦ min)
¦ min)
¦ (AMM 75-31-01/401).
¦
»¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼«
¦ Intercompressor ¦ Fuel
¦ 1.0 cc/min¦1.0 cc/min ¦ Replace the inter¦
¦ (2.5) Bleed
¦
¦(20 drops/ ¦(20 drops/ ¦ compressor (2.5) bleed
¦
¦ Actuator *[2] ¦
¦ min)
¦ min)
¦ actuator
¦
¦
*[6] ¦
¦
¦
¦ (AMM 75-32-01/401).
¦
»¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼«
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71-71-00
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~¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼ ¼¼¼¼¼¼¼¼ ¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼ ¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼
¦
¦
¦
PERMITTED LEAKAGE
¦
¦
¦
¦
»¼¼¼¼¼¼¼¼¼¼¼ ¼¼¼¼¼¼¼¼¼¼¼«
¦
¦
¦
¦
DURING ¦
AFTER
¦
CORRECTIVE
¦
¦ DRAIN/COMPONENT ¦ LIQUID ¦ OPERATION ¦ SHUTDOWN ¦
ACTION
¦
»¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼«
¦ Fuel/Oil Heat
¦ Oil
¦0.5 cc/min ¦0.5 cc/min ¦ Replace the fuel/oil heat ¦
¦ Exchanger
¦
¦(10 drops/ ¦(10 drops/ ¦ exchanger bypass valve
¦
¦ Bypass Valve
¦
¦ min)
¦ min)
¦ (AMM 79-21-02/401).
¦
¦ *[3]
¦
¦
¦
¦
¦
¦ *[6]
¦
¦
¦
¦
¦
»¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼«
¦ Fuel/Oil
¦ Fuel
¦ None
¦ None
¦ Replace the fuel/oil heat ¦
¦ Heat Exchanger ¦ and
¦
*[7]
¦
*[8]
¦ exchanger
¦
¦
¦ Oil
¦
*[9]
¦
*[9]
¦ (AMM 79-21-01/401).
¦
»¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼«
¦ HP Compressor
¦ Fuel
¦0.5 cc/min ¦0.5 cc/min ¦ Replace the HP compressor ¦
¦ and HP Turbine ¦
¦(10 drops/ ¦(10 drops/ ¦ and HP turbine case
¦
¦ Case Cooling
¦
¦ min)
¦ min)
¦ cooling air valve
¦
¦ Air Valve *[2] ¦
¦
¦
¦ (AMM 75-24-03/401).
¦
¦
*[6] ¦
¦
¦
¦
¦
»¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼«
¦ LP Turbine Case ¦ Fuel
¦0.5 cc/min ¦0.5 cc/min ¦ Replace the LP turbine
¦
¦ Cooling Air
¦
¦(10 drops/ ¦(10 drops/ ¦ case cooling air valve
¦
¦ Valve *[2]
¦
¦ min)
¦ min)
¦ (AMM 75-24-01/401).
¦
¦
*[6]
¦
¦
¦
¦
¦
»¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼«
¦ Turbine Cooling ¦ Fuel
¦0.5 cc/min ¦0.5 cc/min ¦ Replace the Turbine
¦
¦ Air Valve
¦
¦(10 drops/ ¦(10 drops/ ¦ Air Valve (TCAV) Actuator ¦
¦ (TCAV) Actuator¦
¦ min)
¦ min)
¦ (AMM 75-24-23/401).
¦
¦ *[2A]
¦
¦
¦
¦
¦
¦ *[6]
¦
¦
¦
¦
¦
»¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼«
¦ Air/Oil Heat
¦ Fuel
¦0.5 cc/min ¦0.5 cc/min ¦ Replace the air/oil heat ¦
¦ Exhanger Valve ¦
¦(10 drops/ ¦(10 drops/ ¦ exchanger valve
¦
¦ *[2]
¦
¦ min)
¦ min)
¦ (AMM 79-21-08/401).
¦
¦ *[6]
¦
¦
¦
¦
¦
»¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼«
¦ 14TH-Stage Bleed¦ Fuel
¦0.5 cc/min ¦0.5 cc/min ¦ Replace the 14TH-Stage
¦
¦ Converter Valve¦
¦(10 drops/ ¦(10 drops/ ¦ Bleed Converter Valve
¦
¦ *[2]
¦
¦ min)
¦ min)
¦ (AMM 75-32-03/401).
¦
¦ *[6]
¦
¦
¦
¦
¦
»¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼«
EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùùû
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ALL
ú
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71-71-00
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~¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼ ¼¼¼¼¼¼¼¼ ¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼ ¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼
¦
¦
¦
PERMITTED LEAKAGE
¦
¦
¦
¦
»¼¼¼¼¼¼¼¼¼¼¼ ¼¼¼¼¼¼¼¼¼¼¼«
¦
¦
¦
¦
DURING ¦
AFTER
¦
CORRECTIVE
¦
¦ DRAIN/COMPONENT ¦ LIQUID ¦ OPERATION ¦ SHUTDOWN ¦
ACTION
¦
»¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼«
¦ Engine Driven
¦ Oil
¦
*[4]
¦
*[4]
¦ Replace the hydraulic
¦
¦ Hydraulic Pump ¦
¦
¦
¦ pump drive seal
¦
¦
¦
¦
¦
¦ (AMM 72-61-02/401).
¦
¦
»¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼«
¦
¦ Hydrau-¦0.25 cc/min¦0.25 cc/min¦ Replace the engine driven ¦
¦
¦ lic
¦(5 drops/ ¦(5 drops/ ¦ hydraulic pump
¦
¦
¦ Fluid ¦
min)*[5]¦
min)*[5]¦ (AMM 29-11-05/401).
¦
»¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼«
¦ Starter
¦ Oil
¦
*[4]
¦
*[4]
¦ Replace the starter drive ¦
¦
¦
¦
¦
¦ seal (AMM 72-61-02/401). ¦
¦
¦
¦
¦
¦
¦
»¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼«
¦ Integrated Drive¦ Oil
¦
*[4]
¦
*[4]
¦ Replace the IDG drive
¦
¦ Generator (IDG)¦
¦
*[4A]
¦
*[4A]
¦ seal (AMM 72-61-02/401). ¦
¦
¦
¦
¦
¦
¦
»¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼«
¦ Electronic
¦ Oil
¦
*[4]
¦
*[4]
¦ Replace the EEC
¦
¦ Engine Control ¦
¦
¦
¦ alternator drive seal
¦
¦ (EEC)
¦
¦
¦
¦ (AMM 72-61-02/401).
¦
¦ Alternator
¦
¦
¦
¦
¦
»¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼«
¦ Fuel Pump
¦ Oil
¦
*[4]
¦
*[4]
¦ Replace the fuel pump
¦
¦
¦
¦
¦
¦ drive seal
¦
¦
¦
¦
¦
¦ (AMM 72-61-02/401).
¦
¦
¦
¦
¦
¦ If the oil leak continues,¦
¦
¦
¦
¦
¦ replace the fuel pump.
¦
¦
¦
¦
¦
¦ (AMM 73-11-01/401
¦
¦
»¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼«
¦
¦ Fuel
¦0.5 cc/min ¦0.5 cc/min ¦ Replace the fuel pump
¦
¦
¦ *[6]
¦(10 drops/ ¦(10 drops/ ¦ (AMM 73-11-01/401).
¦
¦
¦
¦ min)
¦ min)
¦
¦
»¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼«
¦ De-Oiler
¦ Oil
¦
*[4]
¦
*[4]
¦ Replace the De-Oiler
¦
¦ Overboard
¦
¦
¦
¦ drive seal
¦
¦ Ejector
¦
¦
¦
¦ (AMM 72-61-02/401).
¦
¦ Tube
¦
¦
¦
¦
¦
»¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼«
EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùùû
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ALL
ú
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71-71-00
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/
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~¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼ ¼¼¼¼¼¼¼¼ ¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼ ¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼
¦
¦
¦
PERMITTED LEAKAGE
¦
¦
¦
¦
»¼¼¼¼¼¼¼¼¼¼¼ ¼¼¼¼¼¼¼¼¼¼¼«
¦
¦
¦
¦
DURING ¦
AFTER
¦
CORRECTIVE
¦
¦ DRAIN/COMPONENT ¦ LIQUID ¦ OPERATION ¦ SHUTDOWN ¦
ACTION
¦
»¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼«
¦ Oil Scupper
¦ Oil
¦ None
¦ Servicing ¦ Examine the oil tank cap ¦
¦
¦
¦
¦ Spillage ¦ for the correct
¦
¦
¦
¦
¦ Only
¦ installation. Examine
¦
¦
¦
¦
¦
¦ the oil tank filler neck ¦
¦
¦
¦
¦
¦ for cracks. Do not let
¦
¦
¦
¦
¦
¦ the oil fall into the
¦
¦
¦
¦
¦
¦ engine during servicing. ¦
²¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼…¼¼¼¼¼¼¼¼…¼¼¼¼¼¼¼¼¼¼¼…¼¼¼¼¼¼¼¼¼¼¼…¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¹
*[1]
The core accessory drain is the drain for the stator vane actuator. There
are other items which drain through this line. Most of these components,
have a fuild trap. If fluid drains from this line and all of the fluid
traps are empty, check the stator vane actuator.
*[2]
You can see the liquid drain from the core accessory drain. A fluid trap
is included for this component to help you isolate the source of the fluid.
*[2A] You can see the liquid drain from the core accessory drain.
is not included for this component.
A fluid trap
*[3]
You can see the liquid drain from the oil tank scupper and the bypass
valve drain of the fuel/oil heat exchanger. A fluid trap is included for
this component to isolate the source of the fluid.
*[4]
A little leakage is permitted from the accessory gearbox seals as long as
the total oil consumption stays within the limits (AMM 71-00-00/201).
*[4A] If you think the leakage is from the IDG (because you must add the IDG oil
much more frequently than usual), then the maximum permitted leakage rate
is 2 drops of oil each 3 minutes.
*[5]
If the leakage from the hydraulic pump shaft is more than the usual
operation limits, see AMM 29-11-00 for the dispatch leakage limits.
EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùùû
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ALL
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*[6]
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Components that have seal leakage which is more than the maximum
limits are permitted to continue in operation if you obey the
conditions that follow:
1) Drain leakage (no limit on the number of drops) is not a continuous
stream after 30 seconds of engine operation.
2) A leakage check is done before each departure, until the
applicable component is replaced.
*[7]
If the fuel/oil heat exchanger fuel or oil leakage is 10 drops per minute
or less during engine operation, it can continue in service for 10 calendar
days or 100 hours of operation, whichever is greater from the time of
discovery.
*[8]
If the fuel/oil heat exchanger fuel or oil static leakage is 10 drops per
minute or less, it can continue in service for 10 calendar days or 100
hours of operation, whichever is greater from the time of discovery.
If the fuel/oil heat exchanger fuel or oil static leakage is more than 10
drops per minute, then you must run the engine for five minutes. If the
leakage rate decreases to 10 drops per minute or less during engine
operation, it can continue in service for 10 calendar days or 100 hours of
operation, whichever is greater from the time of discovery.
*[9]
3.
A leakage check is done before each departure, until the heat exchanger is
replaced.
TASK 71-71-00-226-003-P00
Engine Strut Drain Tubes Inspection
___________________________________
A. General
(1) This task gives the limits to examine the engine strut drain tubes
(referred to as the drain tubes).
B. References
(1) AMM 71-11-04/201, Fan Cowl Panels
EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùùû
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ALL
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71-71-00
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A
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MAINTENANCE MANUAL
SEE A
SEE B
IDG THERMAL
RELIEF VENT
STRUT
DRAIN
IDG PAD
SEAL DRAIN
STARTER PAD
SEAL DRAIN
FUEL PUMP PAD
SEAL DRAIN
HYDRAULIC PUMP
PAD SEAL DRAIN
FWD
CORE
ACCESSORIES
DRAIN
1
3
EEC ALTERNATOR
PAD SEAL DRAIN
OIL TANK
SCUPPER AND
FUEL/OIL
HEAT
EXCHANGER
DRAIN 2
A
1
THIS DRAIN IS FOR THESE COMPONENTS:
- THE INTERCOMPRESSOR (2.5) BLEED ACTUATOR 2
- THE HP COMPRESSOR AND HP TURBINE CASE COOLING AIR VALVE
- THE LP TURBINE CASE COOLING AIR VALVE 2
- THE STATOR VANE ACTUATOR 2
- THE AIR/OIL HEAT EXCHANGER VALVE 2
- THE 14TH-STAGE BLEED CONVERTER VALVE 2
2
2
THIS DRAIN HAS A FLUID TRAP TO FIND
THE SOURCE OF THE LEAK.
3
FLUID TRAP FOR THE 14TH-STAGE BLEED CONVERTER VALVE IS HORIZONTAL.
108109
Engine Drain Leakage Check
Figure 601 (Sheet 1)
EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùùû
AIRPLANES WITHOUT THE TCAV ACTUATOR
ú
ú
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71-71-00
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MAINTENANCE MANUAL
DEOILER
OUTLET
ELBOW
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/
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DEOILER
FWD
OVERBOARD
EJECTOR TUBE
B
L-95370
F67597
Engine Drain Leakage Check
Figure 601 (Sheet 2)
EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùùû
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MAINTENANCE MANUAL
SEE
A
SEE
B
IDG THERMAL
RELIEF VENT
STRUT
DRAIN
IDG PAD
SEAL DRAIN
STARTER PAD
SEAL DRAIN
FUEL PUMP PAD
SEAL DRAIN
HYDRAULIC PUMP
PAD SEAL DRAIN
FWD
CORE
ACCESSORIES
DRAIN
1
3
EEC ALTERNATOR
PAD SEAL DRAIN
OIL TANK
SCUPPER AND
FUEL/OIL
HEAT
EXCHANGER
DRAIN 2
A
1
THIS DRAIN IS FOR THESE COMPONENTS:
- THE INTERCOMPRESSOR (2.5) BLEED ACTUATOR 2
- THE HP COMPRESSOR AND HP TURBINE CASE COOLING AIR VALVE
- THE LP TURBINE CASE COOLING AIR VALVE 2
- THE STATOR VANE ACTUATOR 2
- THE AIR/OIL HEAT EXCHANGER VALVE 2
- THE 14TH-STAGE BLEED CONVERTER VALVE 2
- THE TURBINE COOLING AIR VALVE (TCAN) ACTUATOR 2
2
2
THIS DRAIN HAS A FLUID TRAP TO FIND
THE SOURCE OF THE LEAK.
3
FLUID TRAP FOR THE 14TH-STAGE BLEED CONVERTER VALVE IS HORIZONTAL.
E32928
Engine Drain Leakage Check
Figure 601A
EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùùû
AIRPLANES WITH THE TCAV ACTUATOR
ú
ú
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71-71-00
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MAINTENANCE MANUAL
C.
(2) AMM 71-11-06/201, Core Cowl Panels
(3) AMM 78-31-00/201, Thrust Reverser System
Access
(1) Location Zones
413
L Power Plant Fan Cowl Panel
414
L Power Plant Fan Cowl Panel
415
L Power Plant Fan Reverser
416
L Power Plant Fan Reverser
423
R Power Plant Fan Cowl Panel
424
R Power Plant Fan Cowl Panel
425
R Power Plant Fan Reverser
426
R Power Plant Fan Reverser
(2)
D.
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Access Panels
413AL
Fan
414AR
Fan
415AL
Fan
416AR
Fan
423AL
Fan
424AR
Fan
425AL
Fan
426AR
Fan
Cowl Panel (Left)
Cowl Panel (Right)
Reverser (Left)
Reverser (Right)
Cowl Panel (Left)
Cowl Panel (Right)
Reverser (Left)
Reverser (Right)
Prepare to Examine the Drain Tubes
S 046-005-P00
WARNING:
_______
(1)
DO THE DEACTIVATION PROCEDURE TO PREVENT THE OPERATION OF THE
THRUST REVERSER. THE ACCIDENTAL OPERATION OF THE THRUST
REVERSER CAN CAUSE INJURIES TO PERSONS AND DAMAGE TO EQUIPMENT.
Do the deactivation procedure for the thrust reverser for ground
maintenance (AMM 78-31-00/201).
(2)
S 016-004-P00
Open the fan cowl panels (AMM 71-11-04/201).
(3)
S 016-006-P00
Open the core cowl panels (AMM 71-11-06/201).
EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùùû
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ALL
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S 016-007-P00
WARNING:
_______
E.
OBEY THE INSTRUCTIONS IN THE PROCEDURE TO OPEN THE THRUST
REVERSERS. IF YOU DO NOT OBEY THE INSTRUCTIONS, INJURIES TO
PERSONS AND DAMAGE TO EQUIPMENT CAN OCCUR.
(4) Open the thrust reversers (AMM 78-31-00/201).
Examine the Drain Tubes
(1)
S 226-008-P00
Examine the drain tubes for cracks, dents, nicks, fretting, and
scoring.
(a) Cracks are not permitted.
(b) Dents are permitted for the limits that follow:
NOTE:
____
You must replace drain tubes that have dents which are
not in these limits.
1)
F.
If the dent has a larger area than depth, make this dent
smooth if it has these conditions:
a) The dent does not decrease the diameter of the tube
more than 10 percent at one point.
b) The dent is not less than one diameter or 0.500 inch
(12.7 mm) from the fitting at the end of the tube.
2) If the dent has a small area (the area is not more than
0.125 square inch (80.60 sq. mm)), make this dent smooth if
it has these conditions:
a) The dent has a round bottom.
b) The depth of the dent is not more than 0.015 inch
(0.381 mm) on the outside surface of a bend.
c) The depth of the dent is not more than 0.025 inch
(0.635 mm) on the remaining section of tube.
d) The dent is not less than one diameter or 0.500 inch
(12.725 mm) from the fitting at the end of the tube.
(c) Nicks are permitted with these limits:
1) The nick has a round bottom.
2) The depth of the nick is not more than 0.004 inch
(0.102 mm).
3) All burrs are removed.
(d) Fretting is permitted with these limits:
1) The depth of the fretting on the outside surface of a bend
must not be more than 0.007 inch (0.178 mm).
2) The depth of the fretting on the remaining sections of the
tube must not be more than 0.010 inch (0.254 mm).
(e) Make the scoring smooth with the area around it if it has these
limits:
1) The scoring must not be on the outside surface of a bend.
2) You must not remove more than 0.005 inch (0.127 mm) of the
metal.
Put the Airplane Back to Its Usual Condition
EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùùû
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MAINTENANCE MANUAL
S 416-009-P00
WARNING:
_______
OBEY THE INSTRUCTIONS IN THE PROCEDURE TO CLOSE THE THRUST
REVERSERS. IF YOU DO NOT OBEY THE INSTRUCTIONS, INJURIES TO
PERSONS AND DAMAGE TO EQUIPMENT CAN OCCUR.
(1)
Close the thrust reversers (AMM 78-31-00/201).
(2)
S 416-010-P00
Close the core cowl panels (AMM 71-11-06/201).
(3)
S 416-012-P00
Close the fan cowl panels (AMM 71-11-04/201).
(4)
S 446-011-P00
Do the activation procedure for the thrust reverser
(AMM 78-31-00/201).
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P01
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
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