• Author / Uploaded
• Mohamed Adam

Citation preview

PW41 00 . ENGINE AND NACELLE LINE AND BASE MAINTENANCE TRAINING GUIDE {A300/A31 0 INSTALLATIONS} " VOLUME 1 .

"

'.

:~

,'~

PART NO. 50A€j30. '.

.e .

.' . .

CUSTOM . e.R .' TRAINING .' : .

.

.

REVJSED·JUNE 1989

8. .

1

ABBREVIATIONS, TERMS AND SYMBOLS

1·1

FOR TRAINING PURPOSES ONLY 620 (wpPSTB2.57 06-22-89)

2

ABBREVIATIONS, TERMS AND SYMBOLS

, SEC

Secondary

SVA

Stator Vane Actuator

Tamb

Ambient Temperature

TAT

Total Air Temperature

TBD

To Be Determined

TBV

Thrust Balance Vent

TCC

Thrust Control Computer

TEC

Tt2.5

Low Pressure Compressor Exit Total Air Temperature

Tt3

High Pressure Compressor Exit Total Air Temperature

Tt4.95

Exhaust Gas Total Temperature (also referred to as Tt4.9 and Tt5)

TVBCA

Turbine Vane and Blade Cooling Air

Turbine Exhaust Case

US

United States

TNGV

Turbine Nozzle Guide Vane

VAC

Volts, Alternating Current

Toil

Temperature Engine Oil

VDC

Volts, Direct Current

T/R

Thrust Reverser

VIB

Vibration

TRA

Thrust Lever Resolver Angle

W

Rate of Flow (Expressed as Weight of Flow)

TRC

Thermatic Rotor Control Wa

Rate of Airflow

Waf

Rate of Fan Airflow

Wap

Rate of Primary Airflow

Wat

Rate of Total Airflow (Wat + Waf)

Wf

Rate· of Fuel Flow

TRP

Thrust Rating. Panel

Ts

Temperature Static

TSFC

Thrust Specific Fuel Consumption

Tt

Total Temperature

Tt2

Compressor Inlet Total Air Temperature

PW4l00-620 (06-15-89) FOR TRAINING PURPOSES ONLY

3

1-6

ABBREVIATIONS, TERMS AND SYMBOLS Wft

Fuel Flow Temperature

< >

Less Than Greater Than

A

Delta, Differential, Finite Difference

8

Theta, Relative Temperature Ratio Delta, Relative Pressure Ratio

=

Equal, Equivalent Approximately

%

Percent Above or Higher Below or Lower

:

--

Proportional To No Change

PW4l00-620 i"-e

20

25

30

/-------1

I

-

I

///~-P;

: N1 I

-

I

, II

END OF RESOLVER RANGE""'---I

I

I 5

/' . . . . r,;,y 1"'~

......

- - IIt-

I:

I Pec!AM.{' /:~"w . •"

~

L.:_

LRU CT 12717 6-89

FADEC I EEC FAULT ACCOMMODATION LOGIC 4-35

FOR TRAINING PURPOSES ONLY

102

FUEL AND CONTROL SYSTEM FULL AUTHORITY DIGITAL ELECTRONIC CONTROL SYSTEM (FADEC/EEC)

PNEUMATIC CONNECTORS: Description and Operation: • The connectors are identified on the FADEC/EEC housing. • Each connector supplies specified signal to both channels via transducers. Pt4.95 • The pneumatic input is via 2 combination Pt4.95/Tt4.95 probes located forward of 'T' flange at the 10:00 and 4:00 positions .on the turbine exhaust case. • A transducer located in the 'A' channel housing receives-the Pt4.95 signal, converts it to an electronic signal and sends it to the 'A'. and 'B' channel circuits. Pt2 • The pneumatic input is via the Pt2/Tt2 probe located in the inlet cowl at the 12:30 position. . • A transducer located in the 'A' channel housing receives the Pt2 signal, converts it to an electronic signal and sends it to the 'A' and 'B' channel circuits.

PW4100-620 (06-26-89) FOR TRAINING PURPOSES ONLY

103

Pb • The pneumatic input is via tubing from a static pressure port located on the diffuser case at the 1:30 position • • A transducer located in the 'B' channel housing receives the Pb signal, converts it to an electronic signal and sends it to the 'A' and 'B' channel circuits. Pamb • The pneumatic input is via two (2) screened static pressure ports located in the inlet cowl outer surface, at approximately the 5:00 and 7:00 ' pos.itions. The two (2) ports are connected to a common manifold, which is routed to the FADEC/EEC. • A transducer located in the 'B' channel housing receives the Pamb signal, converts it to an electronic signal and sends it to 'A' and 'B' channel circuits.

4-36

I

"PtS" (Pt4.9S)

"Pamb" CT 12026

4-89

FADEC/EEC PNEUMATIC CONNECTORS 4-37

FOR TRAINING PURPOSES ONLY

104

FUEL AND CONTROL SYSTEM FULL AUTHORITY DIGITAL ELECTRONIC CONTROL SYSTEM (FADEC/EEC)

ELECTRICAL CONNECTORS: 'A' channel: • J5 A/F - TRA feedback - TRA excitation - L ADC input - R ADC input - ARINC output - Fire discrete - Maintenance discrete input - Nl mode discrete input - Pt2/Tt2 probe heat discrete· - TCC digital output • J6 FMU - Nl sensor input - HPC secondary flow control air valve feedback (right) - TVBCA position .feedback (right) - SVA T/M power - ATRCC T/M power - wf T/M power - Wf resolver excitation - Wf resolver feedback - External reset discrete 2.5 BVA T/M output - Engine A/O HX valve T/M output

• J7 ENG - Tt2 sensor input - Tt3 sensor input -Tt4.95 sensor input - Thrust reverser RVDT excitation - Thrust reverser RVDT feedback - Oil temperature input - Fuel temperature input - SVA LVDT excitation - SVA LVDT feedback - ATRCC LVDT excitation ATRCC LVDT feedback - 2.5 BVA RVT excitation - 2.5 BVA RVT feedback - Engine A/O HX valve RVT excitation - Engine A/O HX valve RVT feedback

• J8 PWR - HPC secondary flow control air valve solenoid (right) TVBCA solenoid 28 VDC ground test Overspeed solenoid FADEC/EEC alternator power IDG AOC override solenoid Start bleed solenoid Stability bleed solenoid 28 VDC solenoid power input F/O cooler bypass valve solenoid • J9 EEC programming plug Discretes - Data entry plug

PW4l00-620 (06-26-89) FOR TRAINING PURPOSES ONLY

105

4-38

J9 •

J6 "Feu" (FMU)

J7 "gNG"

.

J8 "PWR"

CT 12027 4-89

FADEC/EEC "A" CHANNEL CONNECTORS 4-39

FOR TRAINING PURPOSES ONLY

106

FUEL AND CONTROL SYSTEM FULL AUTHORITY DIGITAL ELECTRONIC CONTROL SYSTEM (FADEC/EEC)

ELECTRICAL CONNECTORS - CONTINUED: I

BI Channel: • Jl A/F - Same as J5 except: • Nl indication output • J2 FCU (FMU) Same as J6 except: • No TVBCA feedback • HPC secondary flow control air valve feedback (left) • J3 ENG • Same as J7 • J4 PWR Same as J8 except: • HPC secondary flow control air valve solenoid (left)

PW4l00-620 (06-26-89) FOR TRAINING PURPOSES ONLY

107

4-40

J2 "Feu" (FMU)

CT 12028 4-89

FADEC/EEC

nsn CHANNEL CONNECTORS

FOR TRAINING PURPOSES ONLY

4-41

108

FUEL AND CONTROL SYSTEM FULL AUTHORITY DIGITAL ELECTRONIC CONTROL SYSTEM (FADEC/EEC)

ELECTRICAL HARNESSES Purpose: • The control wiring harnesses are used to connect engine components for electrical signal and power transmission. Description and Operation: • There are 6 harnesses. • The engine control harnesses are of open bundle construction. • Single-shielded conductors are employed for electromagnetic and lightning protection. • FADEC/EEC channels 'A' and 'B' are isolated from each other by separate harnesses and input/output on components where possible for increased safety margin.

PW4l00-620 (06-26-89) FOR TRAINING PURPOSES ONLY

109

4-42

~;::---W5

W6

ENGINE RIGHT

CT 12607 10·88

ELECtRICAL HARNESSES FOR TRAINING PURPOSES ONLY

4-45

110

FUEL AND CONTROL SYSTEM FULL AUTHORITY DIGITAL ELECTRONIC CONTROL SYSTEM (FADEC/EEC)

FADEC/EEC FUEL TEMPERATURE THERMOCOUPLE PROBE

FADEC/EEC OIL TEMPERATURE THERMOCOUPLE PROBE

Purpose:

Purpose:

• The FADEC/EEC fuel temperature thermocouple probe supplies the FADEC/EEC 'A' and 'B' channels with heated fuel temperature sense (filter outlet). Location:

• The FADEC/EEC oil temperature thermocouple probe supplies the FADEC/EEC 'A' and 'B' channels with scavenge oil temperature sense. Location:

• Mounted on the top right side of the fuel pump housing

• Mounted on the front, left face of main gearbox, below gearbox oil pressure 'IN' port

Description and operation: Description and Operation: • Dual element alumel-chromel thermocouple - Provides input for fuel heating and engine oil cooling. • Line replaceable unit

• Dual element alumel-chromel thermocouple - Provides input for engine oil cooling system control, oil temperature warning indication, and IDG oil cooling override. • Line replaceable unit

PW4l00-620

(06~26-89)

FOR TRAINING PURPOSES ONLY

111

4-46

/

FADEC/EEC FUEL TEMPERATURE THERMOCOUPLE PROBE PORT

THERMOCOUPLE PROSE

FADEC/ EEC OIL TEMpERATURE THERMOCOUPLE PROBE PORT

FADEC / EEC FUEL AND OIL TEMPERATURE

CT 12032 6-89

THERMOCOUPLE PROBES

4-47

FOR TRAINING PURPOSES ONLY

112

FUEL AND CONTROL SYSTEM FULL AUTHORITY DIGITAL ELECTRONIC CONTROL SYSTEM (FADEC/EEC)

FADEC/EEC THERMOCOUPLE PROBE (Tt3)

EGT (Tt4.95) THERMOCOUPLE JUNCTION BOX

Purpose:

Purpose:

• The FADEC/EEC thermocouple probe Supplies the FADEC/EEC 'A' and 'B' channels with station 3 (compressor discharge) temperature sense.

• The EGT thermocouple junction box supplies the FADEC/EEC 'A' and 'B' channels with an averaged exhaust gas temperature sense. Location:

Location: • Mounted on the diffuser case at 3: 0'0 position

• Mounted on the turbine exhaust case at 5:30 position Description and Operation:

Description and Operation: • Dual element alumel-chromel thermocouple

• The temperature sense is used only for input to the indication system. There is no EGT limiting function in the FADEC/EEC.

• FADEC/EEC utilizes Tt3 input for heat-soaked engine start logic

• Averaging junction box • Two average Tt4.95 senses are generated: - One for channel 'A' - One for channel 'B'

• Line replaceable unit

• Line replaceable unit

PW4l00-620 (06-26-89) FOR TRAINING PURPOSES ONLY

113

4-48

..-FJmEC I EEC THERMOCOUPLE PROBE (Tt3)

EGT (Tt4.95) THERMOCOUPLE JUNCTION BOX .

DUAL OUTPUTS

FADEC/EEC

FADEC / EEC THERMOCOUPLE PROBE (Tt3) AND EGT JUNCTION BOX FOR TRAINING PURPOSES ONLY

CT 12050

4-89

4-49

114

FUEL AND CONTROL SYSTEM FULL AUTHORITY DIGITAL ELECTRONIC CONTROL SYSTEM (FADEC/EEC)

EXHAUST GiS PRESSURE PROBE (Pt4.95)

EXHAUST GAS TEMPERATURE THERMOCOUPLE (Tt4.95) PROBE

Purpose: :

Purpose:

I

• The Pt4.95 probes supply the FADEC/EEC 'A' and 'B: channels with station 4.95 exhauxt gas pressure sense. Location: .

• The Tt4.95 probes supply the FADEC/EEC 'A' and 'B' channels with station 4.95 exhaust gas temperature sense. Location:

• Mounte4 in turbine exhaust case at 10:00 and 4:QO positions

• Mounted in turbine exhaust case at 1:00, 4:00, 6:30 and 10:00 positions

I

..

Description and Operation:

Descriptin and Operation: • The pr~bes are manifolded together to measure average pressure in the exhaust gas path.

• Probes provide temperature signals to thermocouple junction box where the signals are averaged.

• Line r~placeable unit

• Line replaceable unit

PW4l00-620 (06-26-89) FOR TRAINING PURPOSES ONLY

115

4-50

EXHAUST GAS TEMPERATURE· Tt4.95

EXHAUST GAS PRESSURE· Pt4.95

CT 12611 10-88

EXHAUST GAS PROBES FOR TRAINING PURPOSES ONLY

4-51

116

FUEL AND CONTROL SYSTEM FULL AUTHORITY DIGITAL ELECTRONIC CONTROL SYSTEM (FADEC/EEC)

FADEC/EEC ALTERNATOR Purpose: • The FADEC/EEC alternator supplies the FADEC/EEC 'A' and 'B' channels with power and N2 signal. It also supplies N2 signal to the aircraft systems. Location: • Mounted on the rear, upper middle of the main gearbox Description and Operation: • Permanent magnet alternator: Rotor - Stator

• Dual output connectors: Connector • FADEC/EEC 'A' channel power • FADEC/EEC 'A' channel N2 signal via a power winding • Aircraft N2 signal via a dedicated winding Connector • FADEC/EEC 'B' channel power • FADEC/EEC 'B' channel N2 signal via a power winding At 5 percent N2 the FADEC/EEC alternator output is sufficient to allow the FADEC/EEC to enable its control functions. • Line replaceable units: Stator - Rotor

• Stator cooled by fan air - Cooling air is discharged via both cables • Heatshield installed above FADEC/EEC alternator (mounts to main gearbox)

PW4l00-620 (06-26-89) FOR TRAINING PURPOSES ONLY

117

4-52

RETAINING NUT PIN (2 LOCATIONS) ~ DRIVE SHAFT

~ \~FLATS(2) \

""TEETH

LOCK ROTOR COOLING AIR

ELECTRICAL OUTPUTS AND COOLING AIR OUT ..

CT 12612 4-89

FADEC / EEC ALTERNATOR FOR TRAINING PURPOSES ONLY

4·53

118

FUEL AND CONTROL SYSTEM FULL AUTHORITY DIGITAL ELECTRONIC CONTROL SYSTEM (FADEC/EEC)

Nl SPEED TRANSDUCER Purpose: • The Nl speed transducer supplies the 'A' and 'B' channels with the Nl signal. Location: • Mounted to the rear of the intermediate case at 4:30 position Description and Operation: • Dual coil, magnetic transducer The magnetic transducers sense the frequency at which teeth (60) on the . LPC/LPT coupling pass by them. • Projects into No.1, 1.5, and 2 bearing compartment • Transducer tip is spring-loaded into a locating socket • Line replaceable unit

PW4l00-620 (06-26-89) FOR TRAINING PURPOSES ONLY

119

4-54

LPC/LPT COUPLING

NO.1.5 . ROLLER BEARING

DUAL COIL TRANSDUCER np

PACKING

(3 LOCATIONS) COIL TRANSDUCER TIP'

FADEC/EEC. ELECTRicAL CONNECTOR

HOLE

(4 LOCATIONS) CT 12613

FADEC I EEC SPEED TRANSDUCER (N1)

4-89

4-55

FOR TRAINING PURPOS.ES ONLY

120

FUEL AND CONTROL SYSTEM FULL AUTHORITY DIGITAL ELECTRONIC CONTROL SYSTEM (FADEC/EEC)

FADEC/EEC INLET PRESSURE/TEMPERATURE (Pt2/Tt2) PROBE Purpose: • The Pt2.Tt2 probe supplies the FADEC/EEC with the engine inlet temperature and pressure. Location: • Mounted in the inlet cowl at 1:00 position

• Electrically heated: Aircraft power via the right connector • 115 VAC • 475 watts maximum In flight the probe heat is continuous and is automatically controlled. - On the ground, during engine start with the flight deck switch set 'ON' • Line replaceable' unit

Description and Operation: • Temperature sensor: Dual element resistance sensor Electrica'l output to 'B' channel via the left connector and 'A' channel via the right connector • Pressure sensor: Total pressure probe Pneumatic output to 'A' channel transducer which generates an electronic signal to the 'A' and 'B' channel circuits

PW4100-620 (06-26-89) FOR TRAINING PURPOSES ONLY

121

4-56

Tt2 TO FADEC I EEC

Pt2 TO FADEC I EEC

(CHANNEL "e"

Tt2 TO FADEC I EEC CHANNEL "A" PLUS ANTI·ICING POWER TOPROeE

Tt2 AIRFLOW /,-,...-,11 DISCHARGE Pt2INLET PORT ~_..--_ .... ,---" Tt2 INLET PORT

Pt2/Tt2 PROBE

CT 12031 4-89

FOR TRAINING PURPOSES ONLY

4-57

122

FUEL AND CONTROL SYSTEM FULL AUTHORITY DIGITAL ELECTRONIC CONTROL SYSTEM (FADEC/EEC) STUDENT NOTE PAGE

PW4100-620 (06-26-89) FOR TRAINING PURPOSES ONLY

123

4-58

FUEL DISTRIBUTION SYSTEM

PW4100-620 (06-26-89) FOR TRAINING PURPOSES ONLY

124

4-59

FUEL AND CONTROL SYSTEM FUEL DISTRIBUTION SYSTEM

OVERALL SYSTEM DATA Purpose:

Components:

• The fuel and control system performs: - Thrust management and fuel scheduling/metering for all engine operating conditions. • It also provides: - Automatic fuel heating and oil co.oling Selected components and systems control ~ Required interfaces with aircraft systems

• Fuel distribution subsystem: - Fuel pump - Fuel bypass valve - Fuel/oil cooler and bypass valve - Fuel metering unit - Fuel flow transmitter (EBU component) - Fuel distribution valve - Fuel injector supply manifolds - Fuel injectors • Full Authority Digital Electronic Control (FADEC/EEC)

Subsystems: • Fuel distribution • Full Authority Digital Electronic Control· (FADEC/EEC)

PW4100-620 (06-26-89) FOR TRAINING PURPOSES ONLY

125

4-60

FUEL AND

~_,JNTROL

SYSTEM

FUEL DISTRIBUTION

SYST~

STUDENT NOTE PAGE

PW4100-620 (06-26-89) FOR TRAINING PURPOSES ONLY

126

4-63

FUEL AND CONTROL SYSTEM FUEL DISTRIBUTION SYSTEM

GENERAL Purpose: • The fuel distribution system provides ice-free fi1tered fuel at the pressure and flow rates necessary to me.et all engine operating requirements. Description and Operation:

• Any fuel that is not used as metered or servo supply flow becomes bypass return flow and is returned to pump interstage. • FMU bypass return flow joins boost stage outlet flow at low power or is selected to bypass the IDG section of the engine fuel/oil cooler at high power.

• Fuel at aircraft boost pump pressure flows to the engine fuel pump. It flows to the fuel bypass valve and across the boost stage, is directed out of the pump, through the fuel/oil cooler, and is returned to the pump. It flows across the fuel pump filter and on to the main stage. Main stage discharge flows to the ·fuel metering unit and becomes servo supply fuel, metered fuel or bypass return fuel. • The metered fuel flows from the fuel metering unit, through the fuel flow transmitter, to the fuel distribution 'valve where it is distributed to the fuel manifolds. From the fuel manifolds the fuel flows to the fuel injectors, where it is atomized for combustion. • Servo supply fuel is utilized in the fuel metering unit and in interface systems components as an actuation pressure.

PW4l00-620 (06-26-89) FOR TRAINING PURPOSES ONLY

127

4-64

FUEL TEMPERATURE SENSING PORT--.. MOUNT

FUEL FILTER AP SWITCH

FU~NC:;E....,

DRIVE SHAFT

~~~ INLET FROM AIRCRAFT FILTER COVER DRAIN PLLIG-../ FUEL FROM FUEL/OIL COOLER

RIGHT SIDE, BOOST STAGE FUEL TO lOG AND ENGINE/'o_~ FUEL OIL COOLER CORES FMU BYPASS FUEL TO,ENGINE

SEAL LEAKAGE DRAIN

MAIN 'STAGE FUEL TO FMU

INTERSTAGE PRESSURE TAP (FP8)

FUEL BYPASS VALVE

MAIN STAGE PRESSURE TAP (FP3) CT 12014

"- FUEL PUMP

4-89 4-67

FOR TRAINING PURPOSES ONLY

128

FUEL AND CONTROL SYSTEM FUEL DISTRIBUTION SYSTEM

FUEL BYPASS VALVE Purpose: • The fuel bypass valve prevents excessive engine fuel and oil temperatures during high power operation. Location: • Mounted to the left side of the fuel pump Description and Operation: • Two position hydraulically actuated valve Low engine power position • Less than 70 - 75 percent N2 • FMU bypass fuel and impeller stage discharge (Pout) is ported to the IDG and engine oil heat exchanger. • At low power, FMU bypass fuel and impeller stage discharge (Pout) will not collapse the bellows ·assembly being expanded by pump inlet pressure (pin). This causes the flapper nozzle to be blocked creating a relatively high flapper modulated pressure (Pml) to shuttle the valve to a non-bypass position.

PW4l00-620 (06-26-89) FOR TRAINING PURPOSES ONLY

129

High engine power position • Greater than 70 - 75 percent N2 • Impeller stage discharge continues to be ported to the IDG and engine oil heat exchangers while FMU bypass fuel is ported to the engine oil heat exchanger only. • At high power, FMU bypass and impeller discharge (Pout) pressure collapse the bellows assembly. This causes the flapper nozzle to open. Pml pressure drops and pf causes the valve to shuttle to the bypass position. The bellows assembly is maintained in the collapsed position by Pout. • Line replaceable unit

4-68

TO lOG AND ENGINE OIL HEAT EXCHANGER

FUEL METERING UNIT

LOW POWER MODE

TO ENGINE OIL HEAT

EXCHANGER)

BYPASS VALVE MOUNT PAD

J.';:.~N~k BYPASS VALVE TO ENGINE OIL HEAT EXCHANGER

CT 12015

.HIGH POWER MODE

·6-89

'-- FUEL BYPASS VALVE

POUT TO lOG AND ENGINE OIL HEAT EXCHANGER 4-69

FOR TRAINING PURPOSES ONLY

130

FUEL AND CONTROL SYSTEM FUEL DISTRIBUTION SYSTEM

FUEL/OIL COOLER AND BYPASS VALVE Purpose: • The fuel/oil cooler and bypass valve assemblies heat fuel pump filter inlet fuel to automatically prevent fuel system icing, cool engine and IDGS oil, and prevent excessive fuel temperature. Location: • Mounted on the HPC rear case at 8:00 position. Description and Operation: • Fuel/oil cooler: A single housing contains separa.te engine oil flow and IDGS oil flow heat exchanger cores that share a common internal fuel flow passage. • IDGS oil flow - continuous • Fuel flow - continuous Engine oil flow is controlled by the fuel/oil cooler bypass valve and is bypassed to prevent excessive fuel pump filter outlet fuel temperature.

PW4l00-620 (06-26-89) FOR TRAINING PURPOSES ONLY

131

• Fuel/oil cooler (continued): A pressure relief valve in the IDGS cooler core opens at 50 psid to allow fuel pump boost stagelDutput to bypass the IDGS core and flow only through the engine core in the event of IDGS cooler core blockage. Three (3) overboard ports drain internal fuel and/or oil leakage overboard. No leakage is permitted. • Fuel/oil cooler bypass valve: - The valve is FADEC/EEC controlled, solenoid operated, servo (engine pressure oil) actuated. - With no power to the solenoid the engine oil flows through the cooler core. - When the FADEC/EEC energizes the solenoid with 28 VDC aircraft power, it causes the engine oil to bypass the cooler core • • Line replaceable units: - Fuel/oil cooler Fuel/oil cooler bypass valve - Solenoid

4-70

. - - - ENGINE PRESSURE OIL OUT FITTING lOGS COOLER CORE PRESSURE RELIEF VALVE----.

FUEL/OIL COOLER

Pfr FROM ENGINE COMPO FUEL TO FUEL PUMP FILTER

*

..:----ByPASS VALVE

FAOECjEEC DB" CHANNEL CONNECTOR FADECjEEC nAn CHANNEL

FUEL FROM FUEL PUMP BYPASS VALVE FHc(

FUEL FROM FUEL

bY-f)';; PUMP BOOST ?t"/,~

r't>-'

STAGE

N'

jr//:1j'?"J . J

\

lOGS OIL FROM lOGS AIR/OIL \ HEAT EXCHANGER,/;

"" "

/7' I.)/) 157 a}'iJ "J

ENGINE OIL FROM ENGINE AIR/OIL HEAT EXCHANGER

(8, _ pO'S) ,:!I S

6~l>f2::r"c 6

P >

~C

,,'

!:a.£'l/ ' -"",/...,. ",~ ' \..,/~/e

"------

-'

r

c-/FUEL/OIL COOLER AND BYPASS VALVE FOR TRAINING PURPOSES ONLY

4-71

132

FUEL AND CONTROL SYSTEM FUEL DISTRIBUTION SYSTEM

FUEL METERING UNIT purpose: • The fuel metering unit implements FADEC/EEC fuel metering commands, implements flight deck fuel 'ON'/'OFF' swi tching commands, and provides servo. supply fuel (Pf) to the fuel bypass valve, and to selected compressor airflow control, turbine case cooling airflow control, and oil system components. Location: • Mounted on the front of the fuel pump Description and Operation: • Electronically controlled hydromechanical unit • FADEC/EEC controlled dual coil torque motor commands fuel metering valve position • Metering valve position is sent to the FADEC/EEC by a dual independent winding resolver.

PW4100-620 (06-26-89) FOR TRAINING PURPOSES ONLY

133

• Fuel 'ON'/'OFF' (condition) shaft positioned by the high pressure fuel shutoff valve actuator via the high pressure (HP) fuel shutoff valve control levers • Integral fuel filter: - 40 micron, wash type, servo filter - Not line maintenance replaceable • During engine starting and shutdown a minimum pressure of approximately 300 psig is maintained for control of engine systems actuators. • Overspeed solenoid valve: - At 116.4 percent Nl or 109 percent N2 the FADEC/EEC commands ~VDC (FADEC/EEC alternator supplied) to the overspeed solenoid valve, which when energized, causes the fuel metering valve to move to the minimum fuel flow stop. Not line maintenance replaceable • Line replaceable units: TRA resolvers and HP fuel shutoff valve actuator must be rigged No adjustments to the FMU are necessary or available.

4-72

OUNT STUDS (5 LOCATIONS)

FADEC/EEC"A"CHANNEL

FADEC I EEC "S" CHANNEL CONNECTOR (J1) - - - " ' f.{'-Iei

by_!'cv" vo!..,~

-4.'~

~~~~~~__ CONNECTOR (J2)

BYPASS FUEL TO FUEL PUMP

MAIN STAGE DISCHARGE FROM FUEL PUMP

METERED FUEL TO FUEL FLOW TRANSMITTER

CT 12019

.4-89

FUEL METERING UNIT FOR TRAINING PURPOSES ONLY

4-73

134

FUEL AND CONTROL SYSTEM FUEL DISTRIBUTION SYSTEM

FUEL METERING UNIT (JFC-131-1) - CONTINUED Inputs: • Fuel pump main stage discharge - Passage contains servo filter • Electrical: - FADEC/EEC 'A' channel - FADEC/EEC 'B' channel - Aircraft provided fuel 'ON'/'OFF' signal Outputs: • Metered fuel • Pf (fine filtered supply pressure) servo flow To selected compressor airflow control', turbine case cooling airflow control, fuel and oil system components • Bypass return fuel to fuel pump interstage • Electrical: - FADEC/EEC -, A' channel - FADEC/EEC 'B' channel

PW4100-620 (06-26-89) FOR TRAINING PURPOSES ONLY

135

4-74

FADEC/EEC"A" CHANNEL - , . \ CONNECTOR (J2) - - - -......

~~~~~~

'FADEC / EEC "B" CHANNEL CONNECTOR (J1) - - -.......

'r--FUEL "ON/OFF" (CONDITION) SHAFT

METERED FUEL TO FUEL FLOW TRANSMITTER

Pf TO ENGINE COMPON'ENTS

BYPASS FUEL TO FUEL PUMP MAIN STAGE FUEL FROM FUEL PUMP

REAR VIEW CT 12096

--FUEL METERING UNIT' INPUTS AND OUTPUTS

4-89

4-75

FOR TRAINING PURPOSES ONLY

136

FUEL AND CONTROL SYSTEM FUEL DISTRIBUTION SYSTEM

FUEL METERING UNIT (JFC-131-2) - CONTINUED Inputs: • Fuel pump main stage discharge - Passage contains servo filter • Electrical - EEC 'A' channel - EEC 'B' channel - Aircraft provided fuel 'ON·' j'OFF' signal Outputs: • Metered fuel • pf (fine filtered supply pressure) servo flow - To selected compressor airflow control, turbine case cooling airflow control, fuel and oil system components • Bypass return fuel to fuel pump interstage • Electrical - EEC 'A' channel - EEC 'B' channei - Airframe connector

PW4100-620 (06-26-89) FOR TRAINING PURPOSES ONLY

137

4-76

(-----U=r1=::J

AIRFRAME CONNECTORI

(J3)

•

• Pf PORT

LEFT SIDE

RIGHT SIDE

METERED FUEL. TO FUEL FLOW TRANSMITTER

/~oi!-ii fb I:::;~

AIRFRAME CONNECTOR

BYPASS FLOW PORT

FUEL INLET

REAR VIEW

CT 12655 6-89

FUEL METERING UNIT INPUTS AND OUTPUTS FOR TRAINING PURPOSES ONLY

4-77

138

FUEL AND CONTROL SYSTEM FUEL DISTRIBUTION SYSTEM

FUEL DISTRIBUTION VALVE Purpose: • The fuel distribution valve distributes metered fuel to the fuel injector supply manifolds. Location: • Mounted on the HPC rear case at 4:00 position Description and Operation: • Integral fuel filter housing: - 74 micron, metal screen filter - Filter bypass valve opens at 20 plus or minus 2 psid • Single fuel metering valve: ..:.. Spring loaded closed - Fuel pressure opened at 20 plus or minus ~ psi • 8 fuel outlet ports with transfer tubes • Line replaceable unit

PW4l00-620 (06-26-89) FOR TRAINING PURPOSES ONLY

139

4-78

;'6 ""llcrc~n

Hda([;i:. FUEL OUTLET PORTS (8 LOCATONS)

VALVE BODY

FUEL FLOW TRANSMITTER ADAPTER---'

METERED FUEL FROM FUEL FLOW TRANSMITTER

(--f8 LOCATIONS) "'(/'/61 ,/I f/?,c'l;a" aah/" ) ':'/

'

CT 12020

~FUEL DISTRIBUTION VALVE FOR TRAINING PURPOSES ONLY

10-88

4-79

140

FUEL AND CONTROL SYSTEM FUEL DISTRIBUTION SYSTEM

FUEL INJECTOR SUPPLY MANIFOLDS

FUEL INJECTORS

Purpose:

Purpose:

• The fuel injector supply manifolds route the fuel from the fuel distribution valve to the fuel injectors.

• The fuel injectors atomize fuel for combustion. Location:

Location: • Mounted on the diffuser case • Mounted on the diffuser case

Description and Operation:

Description and Operation: • 24 air blast fuel injectors • Single pipe manifolds • 8 manifolds: - Each manifold supplies fuel to three fuel injectors. - Manifold diameters vary to ensure even fuel distribution to the fuel injectors.

• Each fuel injector inlet fitting houses a filter and a flow orifice. • Line replaceable unit

• Manifold connectors at the fuel injectors and at the fuel distribution valve contain transfer tubes. • Line replaceable unit

PW4l00-620 (06-26-89) FOR TRAINING PURPOSES ONLY

",--,..

141

4-80

METERED FUEL FUEL INJECTOR SUPPLY MANIFOLD (~ LOCATIOtIISI-. I

PACKING----..

~

/'/ ,),r

HOLE (3 LOCATIONS)

..,--'HEATSHIELD

l~;:::::J

~~:E~==:::J DIFFUSER CASE

15TH STAGE AIR

FUEL INJECTOR AND SUPPORT (24 LOCATIONS)

FUEL INJECTOR SUPPLY MANIFOLDS AND FUEL INJECTOR FOR TRAINING PURPOSES ONLY

CT 12025

10·88

4-81

142

FUEL AND CON'l'HUL

:> 1· {Wi. M

STABILITY BLEED VALVE/SYSTEM

CT 12385 4-89

DECELlIMPENDING SURGE BLEED OPEN 5-19 R TRAINING PURPOSES ONLY

180

COMPRESSOR AIRFLOW CONTROL

~Y~TJ!iM

HPC NINTH STAGE (2.9) START/STABILITY BLEED SUBSYSTEM - COMPONENTS

START/STABILITY BLEED VALVE SOLENOID Purpose: • This solenoid controls the Ps3 pneumatic pressure to the start/stability (2.9) bleed valves. Location: • Mounted on the intermediate case rear face at 5:00 position Description and Operation: • Electrically operated, pneumatic solenoid valve assembly • Two solenoids mounted to a common valve housing Each solenoid has dual independent coils, one for channel 'A', one for channel· 'B' • FADEC/EEC controlled: - The aircraft system supplies 28VDC via the FADEC/EEC to the start and stability bleed valve solenoids. Initial start • The right solenoid is energized and Ps3 is blocked to both solenoid valves. Both bleed valves remain open (vented to nacelle area)

PW4l00-620 (06-26-89) FOR TRAINING PURPOSES ONLY

181

• 2 percent before idle and steady state - The right solenoid is de-energized • Ps3 is supplied to the start 2.9 bleed valve (right side) closing it. The left solenoid is energized, supplying Ps3 to the pneumatic relay valve, which closes the stability 2.9 bleed valve (left side) • Shutdown, decel, or surge detection • Both solenoids are de-energized • If the engine is shut down, both 2.9 bleed valves will be spring-loaded open as Ps3 equals Pamb • If the engine is decelerated below 81 percent N2 above 14,500 ft altitude-,or if a surge is detected by the FADEC/EEC, the stability 2.9 bleed valve (left side) will open for 180 seconds due to pneumatic relay valve shift to open position. The bleed valve re-closes if the engine is re-accelerated before the time limit expires • Line replaceable unit

5-20

LEFT SOLENOID

RIGHT SOLENOID DE-ENERGIZED

RIGHT VALVE CLOSE PRESSURE

RELAY VALVE VENTED OPEN

SHUTDOWN, DECEL OR SURGE DETECTION (WHEN SHUTDOWN, Ps3 = Pamb)

INTERMEDIATE CASE - REAR

DE-ENERGIZED

ENERGIZED (28 IInr'\--..

BRACKET RIGHT VALVE CLOSED PRESSURE RELAY VALVE CLOSE PRESSURE SIGNAL FADEC/EEC ELECTRICAL

2% N2 BEFORE IDLE AND STEADY STATE FADEC I EEC ELECTRICAL CONNECTOR

Z

FADEC I EEC CONNECTOH7, ELECTRICAL CONNECTOR ENERGIZED L,_~(28 VDC)

•

~-'f~i}' .

I

p.p~

'

{} {}

Y

..

2.5BLEED VALVE

PFR· SO VISUAL POSITION INDICATOR ON BOTTOM

FAN AIR

-1--------AiRfOIL HEAT EXCHANGER

FADEC/EEC ELECTRICAL· CONNECTOR

CT 12077 4-89

AIR/OILHEAT EXCHANGER - AIR SOURCE (TYPICAL)

'J~.~~.'

".;~:f:~ 266

'"

OIL SYSTEM PRESSURE SUBSYSTEM - COMPONENTS

ENGINE AIR/OIL HEAT EXCHANGER Purpose: • The engine air/oil heat exchanger cools engine oil. Location: • Mounted on the intermediate case tear bulkhead at 8:00 position Description and Operation: • Tube and fin heat exchanger • Single housing with fan air inlet and internal tube passages for. engine oil flow • Oil flow - continuous • Fan air flow (high power) or 2.5 air flow (low power) - controlled by the air/oil heat exchanger valve . . • Internal bypass:valve opens to bypass exchanger core at 60 psid • Line replaceable unit

PW4100-620 (06-21-89) FOR TRAINING PURPOSES ONLY

267

9-20

',~

OIL FROM FILTER

OIL TO FUEUOIL COOLER . BYPASS VALVE EXCHANGER BYPASS VALVE

COOLING AIR TO NACELLE AREA

PRESSURE

ENGINE AIR/OILHEATEXCHANGER FOR TRAINING PURPOSES ONLY

CT 12076 4-89

9-2

268

OIL SYSTEM PRESSURE SUBSYSTEM - COMPONENTS

FUEL/OIL COOLER BYPASS VALVE

• An internal oil pressure bypass valve opens at 50. psid, with cold oil, plugged core or stIcking valve, causing engine oil to bypass the cooler core

purpose: • The fuel/oil cooler bypass valve prevents excessive fuel temperature by controlling engine oil flow through the fuel/oil cooler. Location:

• Overboard drain leakage:

lQ cc/hr maximum

• Line replaceable unit Fuel/oil cooler bypass valve ~ Fuel/oil cooler bypass valve solenoid

• Mounted to the bottom of the fuel/oil cooler Descr ipt ion and Operat ion:· • FADEC/EEC controlled, solenoid operated, servo actuated, non-modulating valve • Temperature bypass valve Held in non-bypass (fail-safe) position by engine oil pressure Valve moves to bypass position when fuel pump filter outlet fuel temperature exceeds 127°C • The FADEC/EEC controls aircraft supplied power (28 VDC) to the dual coil solenoid 28 VDC sent to solenoid - bypass condition 28 VDC not sent to solenoid - non-bypass .. condition.

PW4100-620 (06-21-89) FOR TRAINING PURPOSES ONLY

269

9-22

~SOLENOID

,-""",~~~r~~~____

n

%

lOGS OIL FROM lOGS AIR/OIL HEAT EXCHANGER

11

\7

..

~

SERVO •. . RETURN OIL ENGINE TO TANK OIL IN

----

FADEC/EEC "S" CHANNEL CONNECTOR

FADEC/EEC "A" CHANNEL CONNECTOR

OVERBOARD DRAIN CT 12006 6-89

FUEL/OILCOOLER BYPASS VALVE

270

OIL SYSTEM PRESSURE SUBSYSTEM - COMPONENTS

FUEL/OIL COOLER

Description and Operation:

Purpose:

• Tube and baffle heat exchanger

• The purpose of the fuel/oil cooler is to cool engine and IDGS oil. I t also heats fuel pump filter inlet fuel automatically to prevent fuel system icing. Location: • Mounted on the HPC rear case at 8:00 position

• Single housing with common internal fuel passages .._ Two separate, individually replaceable, internal oil passage cores ~ Engine oil flow .,- IDGS oil flow • Fuel flow - continuous (However, a pressure relief valve in the fuel/oil cooler permits the fuel pump boost stage flow to bypass the IDGS core if IDGS core icing occurs at start) • IDGS oil flow - continuous, no bypass • Engine oil flow - controlled by the fuel/oil cooler bypass valve • Overboard drain leakage, zero leakage allowed - Engine fuel/oil cooler core - lDGS fuel/oil cooler core (2 locations) • Line replaceable unit

PW4100-620 (06-21-89) FOR TRAINING PURPOSES ONLY

271

9-24

,

''j.'" ~,~

',-

.. :::'.:' ~

~£i~

,''''~'.:f.::-:t (,' ''f>''?

•.

l~~

OIL TO NO.3 BEARING AND TRIM ORIFICE OIL TO NO.1, 1.5 AND 2 BEARINGS IDGS COOLER CORE PRESSURE RELIEF VAL

;~'~~:;

___-OIL TO AGB, MGB, FRONT HYDRAULIC PUMP DRIVE (AIRBUS) AND NO.4 BEARING LAST CHANCE OIL STRAINER

j~~:::~~=-'~~~~~- OIL PRESSURE TO OIL PRESSURE

~\O-_-"'"'

OVERBOARD DRAIN PORT----...

TRANSMITTER AND LOW OIL PRESSURE SWITCH .. ~

~ FUEL TO FUEL PUMP FILTER

OVERBOARD DRAIN lOGS OIL FROM FUEL/OIL COOLER BYPASS VALVE

OVERBOARD DRAIN

ENGINE OIL FROM FUEL/OIL COOLER BYPASS VALVE IDGS OIL TO IDG

. ;"::"?~-" ~)': .:\~::" :

.

CT 12005

10-88

FUEL/OIL COOLER -

- . .

_----- - ...... , 272

.

OIL. SYSTEM PRESSURE SUBSYSTEM - COMPONENTS

ENGINE OIL COOLING AND FUEL HEATING Purpose: ., The purpose 0 f eng i ne 0 il coo l i ng and f ue 1 heating is to maintain engine oil and fuel temperature wi thin limits. I t also controls fuel pump filter inlet fuel temperature to prevent pump filter icing and excessive fuel temperature effects during normal orwindmillingoperation. Description and Operation: • Hot oil flows to the engine air/oil heat exchanger and valve assembly. If the FADEC/EEC senses a fuel pump filter outlet fuel teinpera.ture greater than 121°C, it commands the -engine air/oil heat exchanger valve to start modulating open; This action permits fan or 2.5 air to flow across. the heat exchanger, cooling the oil, which in turn transmits less heat to the fuel • From the engine air/oil heat exchanger the· oil flows to the engine fuel/oil cooler bypass valve. If the FADEC/EEC senses a fuel pump filter fuel outlet temperature greater than 127°C, it commands the valve to the bypass position, causing the engine oil to bypass the engine fuel/oil cooler core

PW4100-620 (06-21-89) FOR TRAINING PURPOSES ONLY

273

9-26' .

,.:;''':!, ••:.

.,:~~~~:

(7

COMMANDS) SERVO RETURN TO TANK

VALVE FULL OPEN

.

¢

;;I

FAN AIR' ENGINE AIR! COOLING OR, -DOlL HEAT AAIR TO 2.5 , EXCHANGER~NACELLE' BLEED AIR ~ ~'. AND ,ALVE AREA

r.

.------I-li!1'1J .

(FADEC/EEC ' COMMANDS AND FEEDBACK)

CLOSED 'OR MODULATING

IL'J

FAN AIR

~

L-V

L±LMJ

I

1[

\_-, ENGINE AIR! OIL HEAT EXCHANGER LVE AND Vt

(FAOEC/EEC COMMANDS AND FEEDBACK)

HOT ENGINE OIL FROM OIL FILTER HOUSING

I

A

L-V

r

LEGEND

1

,

FUEL ENGINE OIL ........____'IDGS OIL

=~,

:=1

Tfuel> 127 oC OR Toil >160 oC

Tfuel

RETURN TO TANK

lOGS AIRIOIL

BOOST STAGE AND

EX~~~ER

B:J~~:ROM

I---lCL~~Es~~{:!il~;f~~ L..-----VA...JLVE

~

¢

ENGINE/AIR Pf FROM FMU FAN ---, OIL HEAT EXCHANGER AIR

SWITCH

¢

EXCHANGER VALVE.

POSITION SIGNAL TO FLIGHT DECK (BOEING)

I

?

-.I

"Q.

~T/M

FADEC I EEC COMMANDS AND Pf FEEDBACK FROM CLOSED FMU (Tfuef127 0 C)

AND~ALVE

¢

r

I

ENG OIL

L:::~p::PPS3

FUEL TEMPERATURE CONTROL SUMMARY FOR TRAINING PURPOSES ONLY

(Tfuel127 0 C)

CT 12729 4·89

10·21

306

IGNITION SYSTEM

UPON COMPLETION OF THIS LESSON, EACH STUDENT WILL BE ABLE TO:

1.

IDENTIFY THE MAJOR COMPONENTS OF THE TWO IGNITION SYSTEMS.

2.

STATE THE SAFETY PRECAUTIONS OF THE IGNITION SYSTEM.

11·1

FOR TRAINING PURPOSES ONLY 620 (WPPST8251

06-22~O)

307

IGNITION SYSTEM OVERALL SYSTEM DATA

GENERAL purpose: • The ignition system provides a high energy spark to ignite the fuel/air mixture. Components: • Ignition exciters • Exciter-to-igniter plug cables. • Igniter plugs Description and Operation: • The ignition system consists of two independent circuits • Each circuit is made up of an ignition exciter, exciter-to-igniter plug cable and an igniter plug • Power input is controlled by aircraft switching logic • The system is capable of continuous operation

PW4l00-620 (06-26-89) FOR TRAINING PURPOSES ONLY

308

11-2

IGNITION EXCITERS

FROM AIRCRAFT IGNITION SWITCHES 115 VAC, 400 Hz, 2 AMP MAX

CT 12100

6-88

IGNITION SYSTEM FOR TRAINING PURPOSES ONLY

309

~.

IGNITION SYSTEM COMPONENT LOCATION

ENGINE - RIGHT SIDE • Ignition Exciters: - Mounted on the right side of the main gearbox • Exciter-to-Igniter Plug Cables: Routed along the engine right side between the ignition exciters and the igniter plugs • Igniter Plugs:. Mounted in the diffuser case at 4:00 and 5:00 positions

PW4l00-620 (06-26-89) FOR TRAINING PURPOSES ONLY

310

11-4

;r~!

- -

EXCITER TO IGNITER PLUG CABLE (2 LOCATIONS)

l

:;~~:

-

~

~

;....

.

"'~~,"::

)

IJ;

.

It J

C

/

~

:l

......, ~

IGNITION EXCITERS

IGNITER PLUG (2 LOCATIONS)

CT 12091

6-88

IGNITION SYSTEM COMPONENTS-RIGHT SIDE FOR TRAINING PURPOSES ONLY

311

.

IGNITION SYSTEM COMPONENTS

IGNITION EXCITERS Purpose: • The ignition exciters convert aircraft electrical power to· the voltage required to achieve a high energy spark at the igniter plug. Location:

• Spark rate Minimum . • 1.0 spark per second MaxlmUrn • ~ sparks per second • Duty cycle - Continuous • Anti-shock mounting

• Mounted on the right side of the main gearbox

• Fan air cooled • Hermetically sealed, stainless steel inner case. The outer case is a replaceable (line maintenance) cooling jacket

Description and Operation: • Capacitor discharge exciters

• The upper exciter serves the 4:00 position igniter plug

• Input voltage· Normal • .115 VAC, 400 cycle Operating limits • 90 to 124 VAC • 360 to 440 cycles

• The lower exciter serves the 5:00 position igniter plug • Line replaceable unit

• Input current Maximum • 2.0 amperes • Stored energy 4 joules

PW4100-620(06-26-89} FOR TRAINING PURPOSES ONLY

312

11-6

INPUT CONNECTOR

COOLING AIR DISCHARGE

OUTPUT

r - - ANTI-SHOCK MOUNT

(6 LOCATIONS)

BRACKET

COOLING AIR DISCHARGE OUTPUT CONNECTOR COOLING AIR DISCHARGE

INPUT CONNECTOR

CT 12092

IGNITION EXCITERS FnR TRAINING PURPOSES ONLY

10-88

11-7

313

IGNITION SYSTEM COMPONENTS

EXCITER-To-IGNITER PLUG CABLES Purpose:

• Routed along the engine right side between the ignition exciters and the igniter plugs Description and Operation: • Fan air cooled coaxial cable • Sheet metal cooling shields ensure proper cooling air flow • Ceramic insulated terminals, with l'ubber bushings and sealing washers • The· cables are interchangeable • Line replaceable unit

PW4100-620 (06-26-89) FOR TRAINING PURPOSES ONLY

314

11-8

, .:-

,

:.~:'~~:'

"':2k~: ),-:"~~

:~'

.

.-\"'~"~:~ .~, ~';"

"

• Warning: Ignition system voltage 'is dangerously high. Ignition switch must be in, 'OFF' position before removal 'of any ignition components. A sufficient period of time (several minutes) shall elapse between operation of ignition system and removal of components; or immediately upon detaching cable from igniter, discharge current by grounding terminal. This is to ensure complete dissipation of energy from the system. Prerequisite Tasks:

• Using gage, determine Dimension B by inserting gage hook against rear inside diameter surface of outer combustion chamber and subtract gage reading from 2.200 inches. • Determine igniter plug guide ,configuration. (Shielded or Unshielded) • For engines incorporating the unshielded configuration, add .025 inch to Dimension B.

--

• For engines incorporating the shielded configuration, add .125 inch to Dimension B.

--

• Subtract Dimension B from Dimension A to determine Dimension C.

• Open appropriate circuit breakers and nacelle doors

• Select classified spacers to equal Dimension C plus or minus .010 inch.

• Remove igniter plug Uf}

• Use a maximum of two spacers and do not exce,ed 0.300 inch;

• Remove 'igniter boss and spacers, Key Steps: • Install new boss 'and keywasher to igniter. PW4I00-620 (06-26-89) FOR TRAINING PURPOSES ONLY

320

11-14

GAGE HOOK

""

SLEEVE (SHIELDED) IGNITER PLUG GUIDE SLEEVE

GAGE HOOK

t(UNSHIELDED)~~.~=t~~ IGNITER

PLUG~

t

IGNITER BOSS SPACERS

OUTER COMBUSTION CHAMBER

IGNITER PLUG GUIDE DEFUSER CASE

DIMENSION B

DIMENSION

J==!II!mJl

BASE PLUG,KEYWASHER, BOSS AND SPACERS REMOVED FOR DETERMINING DIMENSION B

t

DIMENSION KEYWASHER'l;:::=-::t

C

/

PWA 75509 IMMERSION GAGE

PLUG REMOVED-KEYWASHER AND BOSS INSTALLED FOR DETERMINING DIMENSION A

IGNITER PLUG DIMENSION CHECK FOR TRAINING PURPOSES ONLY

321

CT 12798 6-89

TAKE-OFF FEET (METERS)

34 MPH TO 720 FEET

60 (18)

40 (12)

20 (6)

o~___ ._ _ _~==i::.-== F METERS _ 30

FEET (METERS) .

60 (18)

40

- 0

0

15 50

-15

136 MPH

30 100

150

200 1

MIN IDLE

150°F 102 MPH 125°F

POWER

(12)

20 (6)

CT 12143 . 10-88

HAZARD AREA FOR TRAINING PURPOSES ONLY

322

ENGINE GROUND OPERATIONS

STARTING Starter Air: • APU, ground air cart or pneumatic cross start-engine bleed air· Precautions:

• Unsatisfactory Start (HP shuto.ff valve OFF) : - No EPR indication at 5 percent N2 - No oil pressure indication at fuel ON No rotation Hung start No EGT rise Impending HOT START Slow acceleration to idle

• Ground personnel observe hazard areas • Fire detection system operable Key Steps: • START I or START 2 push butt.ons in: Engine start page- right CRT Pack valves closed Fuel used - zeroed ARM (white) light off OPEN (blue) light on, starter shutoff valve opens. . . . . EPR will indicate at 5 percent N2 Button releases at 45-percentN2, OPEN light off at 45 percent N2 APU maintainsduct pressure Flight recorder on

• Observe: parameters during start • N2 rising • Starting fuel flow: 550-650 pph ( 249-295 kg/hr) • N1 rising • Oil pressure rising • EGT rising (not to exceed 535 DC) Start valve closes at 45 percent N2 Engine start selector =-OFF Parameters at idle • EPR - 1.01 • Nl - 23 percent • N2 -64 percent • Fuel IIow - 1400 pph ( 635 kg/hr) • oil pressure-=-70 psi mm• Oil temperature-= 50 DC min before advancing thrust lever.

• High pressure (HP) fuel shutoff valve 'ON' :

- Max motoring speed ( 15 percent N2 min} - Ignition sys.tem energIZed . - Fuel turned on

PW4l00-620 (06-26-89) FOR TRAINING PURPOSES ONLY

323

13-4

~,

>.

. _i .;';.:; ~,./,

S':

~{:',~{':

f,l;)DE

ENG

/

~~F"m-. ~ R

Nt

I YU

E

N

CONT REliGHT

ENGINE START PANEL

.~.~. w.

~. •

I

••

.•

I

START

FUEL SHUTOFF LEVERS· " ENGINE INDICATORS

324

• ~'..j;';c_~,

G

~~r~~

" ":'lJ1..,1'1; ENGINE

e

4)

CT 12146

START SYSTEM - FLIGHT DECK COMPONENTS PllppnC:I:C: nl\l! v

\~~j~~

I~I O~!K 1~lj e

ECAM SYSTEMS DISPLAY - RIGHT

TOI\I~II~Ir.

""'1~L .

II

/

!:no

Jf;

10-88

ENGINE GROUND OPERATIONS

SHUTDOWN Normal: • Stabi lize at idle ~- 5 minutes • HP shutoff valve - OFF Emergency: • Retard thrust lever to idle • HP shutoff valve - OFF • Motor engine until EGT goes below 180 DC Caution: • N2 must be below 20 percent before re-engaging starter ' , • If EGT exceeds start temperature'limit of

535,DC , duration of overtemperature in secondsand,peak temperature must be recorded in engine log for malntenance.

PW4100-620 160OC THAN77%N2 N2BETWEEN 70 AND 93% FOR 60 SEC TTAND94%

-OPENS IF IMPENDING ENGINE SURGE SENSED

MODULATING

.

MODULATING SCHEDULED _ OPEN L VALVE TOWARD FOR 3 MINUTES. CLOSED WlTHDECEL BELOW81%N2 ANDALT>14QOO FEET

RAPID

DECEL TO IDLE

ieSEL.Ec;TS N1 MODE ID~~ REVERSE !-SCHEDULES FUEL FLOW_ rnRU!!IT SLEEVES IN TRANSIT !-MAXREV=87%N

MODULATING

CLOSED

OPEN OPEN N2

FADEC GND TEST CHB CHA XXXX XXXX 270 XXXX XXXX 271 XXXX XXXX 272 XXXX XXXX 273 XXXX XXXX 274 1000 0000 350 0000 0010 351 0000 0000 352 0000 0000 353 0000 0000 354

.6. FL

-3

,-

FADEC GND TEST CHA CHB 1.S04 1.S04 EPRTO 14.429 PAMB PSI 14.429 14.430 14.430 P2 PSI 14.50 14.50 PB PSI 14.400 14.400 P5 PSI 14.7 14.7 T2·C 21.2 21.2 T3 ·C 25.1 2S.1 TF·C 24.8 24.8 TOIL ·C 37.0 TRA DEG. 37.0 100.1 100.1 SVA% 1.2 1.2 TCC% 100.0 100.0 AOC% 100.0 100.0 825% 0.5 O.S Rev % RIGHT ECAM

LEFT ECAM

ENG ,.--r!OEe---.

,-

-5

FADEC GND TEST CHB CHA XXXX XXXX EPRTO XXXX PAMB PSI XXXX XXXX XXXX P2 PSI XXXX XXXX PB PSI XXXX XXXX PS PSI XXXX ,XXXX T2 ·C XXXX XXXX T3·C XXXX XXXX TF·C XXXX XXXX TOIL ·C XXXX TRA DEG. XXXX XXXX XXXX SVA% XXXX XXXX TCC% XXXX XXXX AOC% XXXX XXXX B2S% XXXX XXXX Rev 0/0

472VU PANEL LEFT ECAM

RIGHT ECAM CT 12783

FADEC/EEC GROUND TEST OPERATION

6-89 14-23

FOR TRAINING PURPOSES ONLY

349

ENGINE FAULT ISOLATION

GENERAL PROCEDURE DISPATCH STATUS

Purpose: • Dispatch status releases an aircraft for service, after having resolved all fault messages. . Procedure: • Record dispa.tch status in aircraft log book

FOR TRAINING PURPOSES ONLY 620 WPPSTB322 (06-1U9)

14-24

350

STATUS FADEC GROUND TEST: DISPATCH DATE: _ _ __

AIRCRAFT. LOGBOOK

LEFT ECAM DISPLAV

.DISPATCH STATUS FOR TRAINING PURPOSES ONLY

CT12629 10-88 14-25

351

STATUS NONE

NONE

FLIGHT CREW OBSERVATION

MAINTENANCE CREW OBSERVATION

AIRCRAFT LOGBOOK

FADEC GND TEST CHA CHB OF41 ---- . OF01 270 7100 7100 271 _.". 0000 0000 .272 . 0000 - 0000 273 0100 0100 274

270 271 272 273 274

0000 . 0000 0000 0000 0000

350 351 352 353 354

0000 0000 0000 0000 0000

350 351 352 353 . 354

~FL

FADEC GND TEST CHB CHA XXXX . XXXX XXXX Xxxx XXXX XXXX XXXX XXXX XXXX XXXX 0000 0000 0000 0000 0200 ·5 BITE~LEFT

TEST·LEFT ECAM

0000 0000 0000 0000 0080 ·15 ECAM

CT12732 4-89

PRACTICE EXERCISE - 1 14-26

FOR TRAINING PURPOSES ONLY

352

CHANNEL LABEL

HEX DIGIT

SET

BIT

..m.

MEANING/CORRECTIVE ACTION

CT 12740T

PRACTICE EXERCISE WORKSHEET FOR TRAINING PURPOSES ONLY

14-27

620 WPPSTB322 (06-16--89-)

353

DURING THE STATIC GROUND TEST, THE FOLLOWING DISCRETE DATA BIT PATTERNS WILL BE TRANSMITTED BY THE FADEC AND DISPLAYED BY THE ECAM, . ~~

IN THE ABSENCE OF FAULTS.. BIT POSITION. OCTAL LABEL 29 28 27 26 25 24 23 22 21 20 19 18 17 16 15 14 270

0 0

X 1

1

1

1 0

X

o

X

271

X X X X X

0

0

1 0 0

0

0 X

X 0

0

272

0 0

0

0

0

0

0

0

0 0

0

0 0

0 0

0

273

0 0

0

0 0

0

X 0

0 0

0

0 0

0

0

0

274

0 0

0

0 0

0

0

X X 0

0

0 0

0

0

0

350

0 0

0

0 0

0

0

0

0

0

0 0

0 0

0

351

0 0

0

o

0

0

0

O. 00

0

0 0

0 0

0

352

0 0

0

0

0

0

0

o

0

o

0 0

0

353

0

0

0

0

0

0

00

0

0

0

0

0

0

0

0 0

0 1

-

0

0

0 0 0

0

0 0 0 ..

354

0

0

0

0

0

0

0

0

0 0

0 0 0

X = VARIABLE CONDITION. EITHER STATE (0 OR 1) COULD BE VALID.

CT12737 6-89

LABEL AND BIT PATTERN FOR TRAINING PURPOSES ONLY

14-28

354

STUDENT NOTE PAGE

FOR TRAINING PURPOSES ONLY

14-29

620 WPPSTB322 (06-16-89)

355

"CHANNEL A&B FAULT MESSAGE" AFTER TOUCHDOWN

STATUS ENG 1 FADEC CH.A FAULT ENG1 .. FADEC CH.B FAULT FUGHT CREW OBSERVATION

.

..-

.AIRCRAFT LOGBOOK ..

.

-- -- '-

.

CHA

MAINTENANCE CREW OBSERVATION

FADECGNDTEST CHB CHA

FADEC GND TEST . CHB

.

OF41 .QFQl 7100 7100 0000 0000 . 0000 0000 0100·· 0100 .

270 271 272 ·273 274

0000 0000· 0000 ·0000 0000

350 351 352 353 354

0000 .. 0000 0000 0000 0000 .. _-,.-

.

...

...

270 271 . 272 .273 274

XXXX XXXX XXXX XXXX

XXXX XXXX XXXX XXXX

350 351 352 353 354 AFL

0014 0040 0000 0000 0000 ·1

0014 0040 0000 0000 0000 ·1

XXXX

XXXX

BITE· LEFT ECAM

TEST· LEFT ECAM

CT12734 6-89

PRACTICE EXERCISE - 2 14-30

FOR TRAINING PURPOSES ONLY

356

CHANNEL LABEL

-

-

HEX DIGIT

-

BIT

SET

..IO-

MEANING/CORRECTIVE ACTION

---

CT12740T

PRACTICE EXERCISE WORKSHEET FOR TRAINING PURPOSES ONLY

14-31

620 WPPSTB322 (06-16-89)

357

STATUS NONE

NONE -

FLIGHT CREW OBSERVATION

AIRCRAFT LOGBOOK -

-

270 271 212 213 214

XXXX XXXX XXXX XXXX XXXX . XXXX XXXX XXXX XXXX XXXX

0014 0000 0020 0000 ·0000

350 351 352 353 354

0010 0000· 0020 0000 0000

0000 0000 0000 0000 0000

XXXX

XXX)(

-

MAINTENANCE CREW

OBSERVATION

FADEC GND TEST CHB CHA

FADEC-GND TEST CHA CHB 270 . OC01 OC41 1100· 1100 211 .212 0000 . 0000 _0000 0000 213 0:100 0100 214 0014 0000 0020 0000 ·0000

350 351 352 353 354

~FL

-

BITE-LEFT ECAM

TEST-LEFT ECAM_

CT12135 6-89

PRACTICE EXERCISE • 3 14·32

FOR TRAINING PURPOSES ONLY

358

CHANNEL LABEL

HEX DIGIT

fill

SET MEANING/CORRECTIVE ACTION

..IQ

CT 12740T

PRACTICE EXERCISE WORKSHEET FOR TRAINING PURPOSES ONLY

14-33

620 WPPSTB322 (06-16-89,

359

STATUS

FLIGHT CREW OBSERVATION

AIRCRAFT LOGBOOK --

:

FADEC GND TEST

FADEC GND TEST CHA

MAINTENANCE CREW OBSERVATION

CHB

270 271 .272 273 274

~

270 271 272 ,273 274

CHA

CHB

XXXX XXXX XXXX XXXX XXXX

XXXX XXXX XXXX XXXX XXXX

350 351 352 353 354

350 351 352 353 354

BITE-LEFT ECAM

TEST-LEFT ECAM

CT12736

6-89

PRACTICE EXERCISE 14-34

FOR TRAINING PURPOSES ONLY

360

CHANNEL LABEL

HEX DIGIT

IDI

SET

..TeL

MEANING/CORRECTIVE ACTION

CT12740T

PRACTICE EXERCISE WORKSHEET FOR TRAINING PURPOSES ONLY

14-35

620 WPP$TB322 (06-16-89)

361

STATUS

FLIGHT CREW

OB~ERVATION

AIRCRAFT LOGBOOK

FADEC GND TEST

FADEC GND TEST CHA

MAINTENANCE CREW OBSERVATION

CHB

270 271 .272 273 274

.270 271 272 ,273 274

350 351 352 353 .354

350 351 352 .353 354

CHA

CHB

XXXX XXXX XXXX XXXX XXXX

XXXX· XXXX XXXX

xxxx .. xxxx

BITE,LEFT ECAM

TEST-LEFT ECAM

CT12736 6-89

PRACTICE EXERCISE 14-36

Fro TRAINING PURPOSES ONLY

362

CHANNEL LABEL

.

-

HEX DIGIT

BIT

SET ..IQ.

MEANING/CORRECTIVE ACTION

--

-

CT12740T

PRACTICE EXERCISE WORKSHEET FOR TRAINING PURPOSES ONLY

14-37

620 WPPSl"B322 (06