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PRESENTATION ENGINE SYSTEM

CFM56-7B

Lesson Management Plan

ENGINE SYSTEM LEVEL 4

ENGINE SYSTEMS COURSE STRUCTURE - EEC

- Clearance Control • 75-21-00 HPTCC • 75-22-00 LPTCC

- Sensors

- Oil

- Intro

- Harnesses - Starting & Ignition • 80-00-00 Start system • 80-11-79 Starter • 74-00-00 Ignition - Power Management & Fuel Control - Fuel • 73-11-00 • 73-11-10 • 73-11-64 • 79-21-20 • 73-11-20 • 73-21-18 • 73-30-11 • 73-11-45 • 73-11-40

Fuel distribution Fuel pump IDG oil cooler Main oil / fuel heat exchanger Servo fuel heater Hydromechanical unit Fuel flow transmitter Fuel nozzle filter Fuel nozzle

- Geometry Control • 75-30-00 Variable geometry control system • 75-31-00 Variable bleed valve • 75-32-00 Variable stator vane • 75-26-00 Transient bleed valve

• 79-00-00 • 79-11-00 • 79-21-43 • 79-21-10 • 79-21-50 • 79-21-42 • 79-30-00 • 79-31-00 • 79-32-10 • 79-31-40 • 79-20-00

Oil general Oil tank Anti-leakage valve Lubrication unit Debris monitoring system (optional) Oil scavenge filter assembly Oil indicating components Oil quantity transmitter Oil pressure transmitter Oil temperature sensor Oil filter bypass switch

- Powerplant Drains - Thrust Reverser - Indicating • 77-00-00 Engine indicating system panels • 77-00-00 Common Display System - Vibration Monitoring • 77-31-00 Vibration monitoring and indicating - Condition Monitoring • 77-00-00 Aircraft condition monitoring system Page 1 Return

ENGINE SYSTEMS COURSE STRUCTURE - EEC

- Clearance Control • 75-21-00 HPTCC • 75-22-00 LPTCC

- Sensors

- Oil

- Intro

- Harnesses - Starting & Ignition • 80-00-00 Start system • 80-11-79 Starter • 74-00-00 Ignition - Power Management & Fuel Control - Fuel • 73-11-00 • 73-11-10 • 73-11-64 • 79-21-20 • 73-11-20 • 73-21-18 • 73-30-11 • 73-11-45 • 73-11-40

Fuel distribution Fuel pump IDG oil cooler Main oil / fuel heat exchanger Servo fuel heater Hydromechanical unit Fuel flow transmitter Fuel nozzle filter Fuel nozzle

- Geometry Control • 75-30-00 Variable geometry control system • 75-31-00 Variable bleed valve • 75-32-00 Variable stator vane • 75-26-00 Transient bleed valve

• 79-00-00 • 79-11-00 • 79-21-43 • 79-21-10 • 79-21-50 • 79-21-42 • 79-30-00 • 79-31-00 • 79-32-10 • 79-31-40 • 79-20-00

Oil general Oil tank Anti-leakage valve Lubrication unit Debris monitoring system (optional) Oil scavenge filter assembly Oil indicating components Oil quantity transmitter Oil pressure transmitter Oil temperature sensor Oil filter bypass switch

- Powerplant Drains - Thrust Reverser - Indicating • 77-00-00 Engine indicating system panels • 77-00-00 Common Display System - Vibration Monitoring • 77-31-00 Vibration monitoring and indicating - Condition Monitoring • 77-00-00 Aircraft condition monitoring system

TOC

NEXT DISPLAY : FADEC PURPOSE. Page 2

EXPLAIN :

MEANING OF FADEC.

PURPOSES :

FADEC SYSTEM.

GENERAL TERMS ONLY. COMPONENTS NEXT DISPLAY. POWER MANAGEMENT CONTROL

ACTIVE CLEARANCE CONTROL

FADEC STARTING / SHUTDOWN / IGNITION CONTROL

VARIABLE GEOMETRY CONTROL

FUEL CONTROL

THRUST REVERSER CONTROL

CTC-216-001-00

NEXT DISPLAY : FADEC COMPONENTS.

FADEC PURPOSE

TOC

Page 3

DESCRIBE :

ROLE - EEC.

CONTROL SIGNALS T3

T49.5 TCASE Ps3

P0

N1

ROLE - HMU.

N2

T25 T12 ANALOG DISCRETE SIGNALS

CTC-216-002-00

115V 400Hz

AIRCRAFT / EEC POWER SUPPLIES.

FEEDBACK SIGNALS

ARINC DATA BUSES

COMMUNICATION LINKS.

IGNITION

VBV VSV TBV EEC

ROLE - ALTERNATOR.

HPT LPT CC CC

ALTERNATOR

IDENTIFY / PURPOSES : WF METER

FUEL HYDROMECHANICAL UNIT (HMU)

THRUST REVERSER TRANSLATING SLEEVE LVDT

FUEL FLOW

SENSORS. VALVES & ACTUATORS.

T

P

OIL

OIL

P25

Ps13

T5

(PMUX OPTION)

(PMUX OPTION)

(PMUX OPTION)

EXPLAIN :

CONTROL LOOP PRINCIPLE. BRIEF - DETAILS LATER. EEC’S ROLE - T/R SYSTEM.

NEXT DISPLAY : FADEC INTERFACES.

FADEC COMPONENTS TOC

Page 4

CTC-216-003-00

PURPOSES : AIRCRAFT

ADIRU 1

FMC

THE CDS/DEU. COMMON DISPLAY SYSTEM / DISPLAY ELECTRONIC UNIT.

ADIRU 2

THE ADIRU. AIR DATA & INERTIAL REFERENCE UNIT.

EEC ENGINE 1

DESCRIBE :

CHANNEL A

THE 2 EEC CHANNELS PRINCIPLE. BRIEF - DETAILS LATER.

CHANNEL B

CDS/DEU2

CHANNEL B

CHANNEL A

CDS/DEU1

EEC ENGINE 2

NEXT DISPLAY : FADEC DESIGN.

FADEC INTERFACES TOC

Page 5

EXPLAIN :

BITE. BUILT IN TEST EQUIPMENT.

EXAMPLES :

SINGLE SENSORS. DUAL CONTROL SENSORS. SHARED SENSORS.

PURPOSE :

CCDL. CROSS CHANNEL DATA LINK.

DESCRIBE :

ACTIVE / STANDBY.

SINGLE SENSORS

EEC CHANNEL A DUAL CONTROL SENSORS C C D L

EEC CHANNEL A

EEC CHANNEL B

SHARED SENSORS

ACTIVE

STAND BY

SELECTION STRATEGY.

EEC

PURPOSE :

CHANNEL B

FAILSAFE CONTROL. GIVE EXAMPLE.

SINGLE SENSORS

CTC-216-004-00

NEXT DISPLAY : CLOSED LOOP CONTROL PHILOSOPHY.

FADEC DESIGN TOC

Page 6

CTC-216-005-00

DESCRIBE :

CLOSED LOOP CONTROL.

IMPORTANT SUBJECT. IF NECESSARY, USE FADEC COMPONENTS DISPLAY (P4) TO REINFORCE EXPLANATION.

CONTROL SENSORS

DEMAND CALCULATOR COMMAND

CONTROL LAW

FEEDBACK

+

-

DEMAND

EHSV

HMU

POSITION SENSOR

ACTUATOR

EEC

NEXT DISPLAY : INPUT PARAMETERS SELECTION.

CLOSED LOOP CONTROL PHILOSOPHY TOC

Page 7

CTC-216-259-00

VALIDATION TEST PROGRAM LOCAL VALUE

CHANNEL A

CCDL CROSS CHANNEL VALUE

VALIDATION TEST PROGRAM LOCAL VALUE

VALUE SELECTED : - AVERAGE OF BOTH VALUES OR - LOCAL VALUE OR - CROSS CHANNEL VALUE OR - MODEL OR - FAILSAFE

IDENTIFY :

NON-DUAL SENSORS.

EXPLAIN :

LOCAL / CROSS CHANNEL VALUES.

PURPOSE :

VALIDATION TESTS. MODEL VALUE.

DESCRIBE :

PARAMETERS SELECTION.

CHANNEL B

NEXT DISPLAY : TABLE OF CONTENTS.

INPUT PARAMETERS SELECTION TOC

Page 8

ENGINE SYSTEMS COURSE STRUCTURE - EEC

- Clearance Control • 75-21-00 HPTCC • 75-22-00 LPTCC

- Sensors

- Oil

- Intro

- Harnesses - Starting & Ignition • 80-00-00 Start system • 80-11-79 Starter • 74-00-00 Ignition - Power Management & Fuel Control - Fuel • 73-11-00 • 73-11-10 • 73-11-64 • 79-21-20 • 73-11-20 • 73-21-18 • 73-30-11 • 73-11-45 • 73-11-40

Fuel distribution Fuel pump IDG oil cooler Main oil / fuel heat exchanger Servo fuel heater Hydromechanical unit Fuel flow transmitter Fuel nozzle filter Fuel nozzle

- Geometry Control • 75-30-00 Variable geometry control system • 75-31-00 Variable bleed valve • 75-32-00 Variable stator vane • 75-26-00 Transient bleed valve

• 79-00-00 • 79-11-00 • 79-21-43 • 79-21-10 • 79-21-50 • 79-21-42 • 79-30-00 • 79-31-00 • 79-32-10 • 79-31-40 • 79-20-00

Oil general Oil tank Anti-leakage valve Lubrication unit Debris monitoring system (optional) Oil scavenge filter assembly Oil indicating components Oil quantity transmitter Oil pressure transmitter Oil temperature sensor Oil filter bypass switch

- Powerplant Drains - Thrust Reverser - Indicating • 77-00-00 Engine indicating system panels • 77-00-00 Common Display System - Vibration Monitoring • 77-31-00 Vibration monitoring and indicating - Condition Monitoring • 77-00-00 Aircraft condition monitoring system

TOC

NEXT DISPLAY : EEC LOCATION & COOLING. Page 9

COOLING DUCT

EEC.

DESCRIBE :

MOUNTING.

INLET

EEC

CTC-216-006-00

LOCATE :

COOLING SYSTEM.

FWD

COOLING AIR INLET

FAN INLET COWL

MOUNTING BOLT

COOLING AIR OUTLET

NEXT DISPLAY : EEC ARCHITECTURE.

ELECTRONIC ENGINE CONTROL TOC

Page 10

IDENTIFY/ DESCRIBE: ECA. ELECTRICAL CHASSIS ASSY

MOTHERBOARD ASSEMBLY

FRONT PANEL ASSEMBLY

AIR INLET

FPA. FRONT PANEL ASSY SIA. SIDE INTERFACE ASSY

ELECTRICAL CONNECTOR

PSS. PRESSURE SUBSYSTEM ELECTRICAL CONNECTOR

ACCESS TO CHAN.A & B CIRCUIT BOARDS. REAR COVER

PRESSURE TRANSDUCER PRESSURE SUB-SYSTEM

CTC-216-007-00

NEXT DISPLAY : ELECTRICAL CONNECTORS.

EEC ARCHITECTURE

TOC

Page 11

CTC-216-008-00

DESCRIBE:

CONNECTORS. KEYWAY ETC.

IDENTIFY:

CONNECTOR NUMBERING.

SIDE INTERFACE ASSEMBLY

FRONT PANEL ASSEMBLY

P11

J1

FUNCTION OF EACH CONNECTOR. ID PLUG LAST - LINK TO NEXT DISPLAY. J10

J3 J9

J7 J5

J2 J4

J8 J6

CHANNEL A CHANNEL B CONNECTOR CONNECTOR (ODD) (EVEN) J1 J3 J5 J7 J9 P11

J2 J4 J6 J8 J10 SHARED

FUNCTION

IGNITION POWER (115V) THRUST REVERSER HMU, N2, FUEL FLOW METER, OIL TEMP. N1, T12, EEC ALT., OIL & FUEL FILTER CLOGGED, OIL P. SENSOR, DMS (OPT.) T25, LPTACC, HPTACC, VSV, VBV, TBV, T3, T49.5, T5, TCC ENGINE IDENTIFICATION PLUG, TEST INTERFACE

NEXT DISPLAY : ID PLUG.

ELECTRICAL CONNECTORS TOC

Page 12

CTC-216-009-00

PURPOSE :

ID PLUG.

IDENTIFY:

METAL STRAP.

SAFETY WIRE

PUSH-PULL LINK

CODING CIRCUIT.

CODING CIRCUIT

PUSH-PULL LINKS. EXPLAINED LATER.

O-RING

SHEATHED CABLE

BOLTED ON THE FAN CASE

NEXT DISPLAY : BOEING APPLICATIONS.

IDENTIFICATION PLUG DESCRIPTION TOC

Page 13

737-600

CFM56-7B18 CFM56-7B20 & - 7B20/2 CFM56-7B22 & - 7B22/2

(19,500 lbs) (20,600 lbs) (22,700 lbs)

CFM56-7B20 & - 7B20/2 CFM56-7B22 & - 7B22/2 CFM56-7B24 & - 7B24/2

(20,600 lbs) (22,700 lbs) (24,200 lbs)

737-700

CFM56-7B24 & - 7B24/2 (24,200 lbs) CFM56-7B26 & - 7B26/B1 & - 7B26/2 (26,300 lbs) CFM56-7B27 & - 7B27/B1 & - 7B26/B3 & - 7B26/2 (27,300 lbs)

737-800

CFM56-7B24 & - 7B24/2 (24,200 lbs) CFM56-7B26 & - 7B26/B1 & - 7B26/2 (26,300 lbs) CFM56-7B27 & - 7B27/B1 & - 7B26/B3 & - 7B26/2 (27,300 lbs) CFM56-7B26 & - 7B26/B1 & - 7B26/2

PURPOSE / DESCRIBE :

FUSE LINKS.

IDENTIFY :

MIN & MAX THRUST RATINGS & APPLICATIONS.

EXPLAIN :

BUMP OPTION. PLUG TYPE.

737-900 737-BBJ

/

COMBI

(26,300 lbs)

C40A CFM56-7B26 & - 7B26/B1 & - 7B26/2

CTC-216-010-00

(26,300 lbs)

NEXT DISPLAY : PRINCIPLE SCHEMATIC PUSH-PULL CONTACTS.

CFM56-7B FOR BOEING APPLICATIONS

TOC

Page 14

CTC-216-011-00

PURPOSE / DESCRIBE :

PUSH-PULL LINKS.

IDENTIFY:

ENGINE CONFIGURATIONS. SAC WITH/WITHOUT BSV, DAC

O-RING

NEXT DISPLAY : N1 TRIM - PMUX.

PRINCIPLE SCHEMATIC PUSH-PULL CONTACT TOC

Page 15

N1

N1

N1 TRIM.

EXPLAIN:

PMUX.

96%

96%

CTC-216-012-00

PURPOSE / EXPLAIN :

ENG 2 TRIM DOWN

TRA

TRA

MTO/GA

TO/GA

26465 lbs

26300 lbs

N1

N1

96%

96.0

96.0

N1 %

N1 %

95.4%

TRA

TRA

TO/GA

26300 lbs

TO/GA

26300 lbs

ENG 1 UNCHANGED

96.0

96.0

N1 %

N1 %

NEXT DISPLAY : PRESSURE SUB-SYSTEM.

CODING CIRCUIT - N1 TRIM TOC

Page 16

CTC-216-013-00

PURPOSE :

PRESSURE SUB-SYSTEM.

IDENTIFY :

CONTROL PRESSURES.

MANIFOLD

OPTIONAL MONITORING PRESSURES. THE 2 TYPES OF PRESSURE MANIFOLDS. PMUX AND NON PMUX

UNUSED PORT

P25 (PMUX OPTION) P0 PS13 (PMUX OPTION)

UNUSED PORT

PS3

NEXT DISPLAY : EEC POWER SUPPLY.

PRESSURE SUB-SYSTEM TOC

Page 17

CTC-216-015-00

IDENTIFY :

REDUNDANT POWER SOURCES. AIRCRAFT TRANSFER BUSSES. 115VAC 400HZ

A/C 115 V AC 400 Hz

CHANNEL A

CONTROL ALTERNATOR.

CHANNEL B

J1

J2 EEC

J7

J8

CHANNEL A

CHANNEL B ALTERNATOR 96-134 VAC

NEXT DISPLAY : EEC POWER SUPPLY LOGIC.

EEC POWER SUPPLY TOC

Page 18

CTC-216-016-00

DESCRIBE : AIRFRAME 115- VAC TRANSFER BUS

ENGINE

POWER SUPPLY CIRCUIT N2 > 15%.

CHANNEL A

ENG ALTN POWER CH A

POWER SUPPLY CIRCUIT N2 < 12%.

EEC POWER CONNECT/DISCONNECT SOFTWARE CONTROL

115- VAC TRANSFER BUS

CHANNEL B

ENG ALTN POWER CH B

EEC POWER CONNECT/DISCONNECT SOFTWARE CONTROL

28- VDC BUS ENG RUN/POWER CONT ALTERNATE POWER RELAY

ELECTRONIC ENGINE CONTROL

EEC POWER CONNECT/DISCONNECT SOFTWARE CONTROL

CDS DEU No.1

EEC ALTERNATOR

EEC POWER CONNECT/DISCONNECT SOFTWARE CONTROL

CDS DEU No.2

NEXT DISPLAY : CONTROL ALTERNATOR.

EEC POWER SUPPLY LOGIC TOC

Page 19

CTC-216-017-00

LOCATE / DESCRIBE : ROTOR

CONTROL ALTERNATOR.

AGB GEARSHAFT

O-RING AGB

STATOR

J8 HARNESS CONNECTOR (CHANNEL B)

NUT

J7 HARNESS CONNECTOR (CHANNEL A)

NEXT DISPLAY : TABLE OF CONTENTS.

EEC CONTROL ALTERNATOR DESIGN TOC

Page 20

ENGINE SYSTEMS COURSE STRUCTURE - EEC

- Clearance Control • 75-21-00 HPTCC • 75-22-00 LPTCC

- Sensors

- Oil

- Intro

- Harnesses - Starting & Ignition • 80-00-00 Start system • 80-11-79 Starter • 74-00-00 Ignition - Power Management & Fuel Control - Fuel • 73-11-00 • 73-11-10 • 73-11-64 • 79-21-20 • 73-11-20 • 73-21-18 • 73-30-11 • 73-11-45 • 73-11-40

Fuel distribution Fuel pump IDG oil cooler Main oil / fuel heat exchanger Servo fuel heater Hydromechanical unit Fuel flow transmitter Fuel nozzle filter Fuel nozzle

- Geometry Control • 75-30-00 Variable geometry control system • 75-31-00 Variable bleed valve • 75-32-00 Variable stator vane • 75-26-00 Transient bleed valve

• 79-00-00 • 79-11-00 • 79-21-43 • 79-21-10 • 79-21-50 • 79-21-42 • 79-30-00 • 79-31-00 • 79-32-10 • 79-31-40 • 79-20-00

Oil general Oil tank Anti-leakage valve Lubrication unit Debris monitoring system (optional) Oil scavenge filter assembly Oil indicating components Oil quantity transmitter Oil pressure transmitter Oil temperature sensor Oil filter bypass switch

- Powerplant Drains - Thrust Reverser - Indicating • 77-00-00 Engine indicating system panels • 77-00-00 Common Display System - Vibration Monitoring • 77-31-00 Vibration monitoring and indicating - Condition Monitoring • 77-00-00 Aircraft condition monitoring system

TOC

NEXT DISPLAY : ENGINE SENSORS - AERODYNAMIC STATIONS. Page 21

CTC-216-044-00

ENGINE STATION IDENTIFICATION 0 FREE STREAM AMBIENT CONDITIONS

23 BOOSTER DISCHARGE

2 FAN INLET FRONT FRAME HUB SECTION

24 BOOSTER VARIABLE BLEED VALVE DISCHARGE

3 HP COMPRESSOR DISCHARGE

25 HP COMPRESSOR INLET

4 COMBUSTOR DISCHARGE

27 HP COMPRESSOR 5TH STG. BLEED EXT. STATION

5 LOW PRESSURE TURBINE DISCHARGE

41 HP TURBINE ROTOR INLET

8 PRIMARY EXHAUST NOZZLE THROAT

42 HP TURBINE DISCHARGE

9 PRIMARY EXHAUST NOZZLE DISCHARGE

48 LOW PRESSURE TURBINE INLET

12 FAN INLET FRONT FLANGE TIP SECTION 13 FAN OGV DISCHARGE 15 FAN FRAME DISCHARGE

IDENTIFY SOME SENSORS TO FAMILIARIZE STUDENTS WITH NAMES & LOCATIONS.

49 LOW PRESSURE TURBINE ROTOR INLET 55 LP TURBINE FRAME EXIT 495 EXHAUST GAS TEMPERATURE MEASURING PLANE

18 BYPASS EXHAUST NOZZLE THROAT

NEXT DISPLAY : ENGINE SENSORS.

ENGINE SENSORS TOC

Page 22

CTC-216-045-00

IDENTIFY / PURPOSE : SPEED SENSORS.

T5 T49.5 (EGT)

TEMPERATURE SENSORS. T3

RTD SENSORS. RESISTIVE THERMAL DEVICE.

PS13

THERMOCOUPLES. T12

PRESSURE SENSORS.

TCC

VIBRATION SENSORS.

FFCCV ACCELEROMETER

PO (TAKEN ON EEC ITSELF)

T3, PS3 N1 SPEED SENSOR PT25 (P25 AND T25) No.1 BRG VIB SENSOR N2 SPEED SENSOR (FWD FACE OF AGB)

NEXT DISPLAY : SPEED SENSOR DESIGN.

ENGINE SENSORS TOC

Page 23

REMINDER : SPEED SENSORS PURPOSE. MAGNETIC RING

MAGNET

SPEED SENSOR

IDENTIFY :

EEC & AVM CONNECTIONS.

DESCRIBE :

SPEED SENSORS FUNCTION.

N1 N2

COIL

CTC-216-046-00

CH A

EEC

CH B

A CH A CH B

EEC

B A/C A/C N1 SPEED SENSOR

AVM SIGNAL CONDITIONER

N2 SPEED SENSOR

NEXT DISPLAY : N1 SPEED SENSOR.

SPEED SENSOR DESIGN TOC

Page 24

LOCATE / DESCRIBE :

N1 SPEED SENSOR.

N1 SPEED SENSOR PROBE BODY

POLE PIECES

CTC-216-047-00

RECEPTACLE DAMPING RINGS

TENSION SPRING PROBE HOUSING

A/C

CH A CH B

NEXT DISPLAY : N2 SPEED SENSOR.

N1 SPEED SENSOR TOC

Page 25

LOCATE / DESCRIBE :

N2 SPEED SENSOR.

POLAR PIECES

A/C MAGNETIC HEAD

CTC-216-048-00

RIGID METAL TUBE

CH B

CH A

A/C

RECEPTACLE

2 EEC CONNECTORS

CH A DEU / AVM CONNECTORS

CH B SECURING FLANGE

NEXT DISPLAY : TEMP. SENSORS - RTD TYPE.

N2 SPEED SENSOR TOC

Page 26

DESCRIBE :

FUNCTION OF RTD’S.

EEC

CH A CH B

EEC

DUAL SENSING ELEMENTS

CTC-216-049-00

EXCITATION SOURCE PLATINUM RESISTOR

VI

S

VOLTAGE DROP f(T)

NEXT DISPLAY : T12 SENSOR.

RESISTIVE THERMAL DEVICE TOC

Page 27

CTC-216-050-00

IDENTIFY :AERODYNAMIC STATION 12 ON WALL CHART. T12 ACCESS PANEL

DESCRIBE :

T12 SENSOR.

INLET COWL T12 SENSOR

FWD

ELECTRICAL CONNECTORS

CHANNEL B CHANNEL A FLANGE DAMPER GROUND STUD

HOUSING

NEXT DISPLAY : P/T25 SENSOR.

T12 SENSOR TOC

Page 28

CTC-216-051-00

IDENTIFY :

AERODYNAMIC STATION 25 ON WALL CHART.

DESCRIBE :

P/T25 SENSOR.

DUST EXHAUST OUTLET AIR OUTLET AIRFLOW

PRESSURE TAPPING PORT EEC CONNECTOR CHANNEL A

AIR PRESSURE PORT P25 EEC CONNECTOR CHANNEL B

FWD

NEXT DISPLAY : TEMP. SENSORS - THERMOCOUPLE TYPE.

PT25 SENSOR TOC

Page 29

CTC-216-052-00

PURPOSE :

THERMOCOUPLES.

DESCRIBE :

THERMOCOUPLE PRINCIPLE.

A B

HOT JUNCTION

COLD JUNCTION

VOLTS PRIMARY AIRFLOW EEC

NEXT DISPLAY : T3 SENSOR.

THERMOCOUPLE PRINCIPLE TOC

Page 30

CTC-216-053-00

PURPOSE / LOCATE / DESCRIBE :

T3 SENSOR.

T3 SENSOR THERMOCOUPLE

CONNECTOR BOX

NEXT DISPLAY : EGT SENSING SYSTEM.

T3 TEMPERATURE SENSOR TOC

Page 31

IDENTIFY : TUBE

AERODYNAMIC STATION 49.5 ON WALL CHART.

PURPOSE / LOCATE :

EGT SENSING SYSTEM.

DESCRIBE :

WIRING HARNESS.

THERMOCOUPLE

JUNCTION BOX

WIRE HARNESS

DISTRIBUTION OF MEASUREMENTS TO EEC CHANNELS A AND B.

THERMOCOUPLE T49.5 THERMOCOUPLE HARNESS ENGINE TURBINE CASE (RIGHT SIDE) ENGINE TURBINE CASE (LEFT SIDE)

CTC-216-054-00

NEXT DISPLAY : T5 SENSOR.

EGT THERMOCOUPLES AND HARNESSES TOC

Page 32

PURPOSE / LOCATE / DESCRIBE :

T5 SENSOR.

FWD 3 O`CLOCK

T5 SENSOR ASSEMBLY

T5 SENSOR

CTC-216-055-00

NEXT DISPLAY : TCC SENSOR.

T5 TEMPERATURE SENSOR TOC

Page 33

CTC-216-061-00

PURPOSE / LOCATE / DESCRIBE :

TCC SENSOR.

B

THERMOCOUPLE PAD

VIEW B

FWD

GASKET

HOUSING

ELECTRICAL CONNECTION ELECTRICAL CONNECTOR

SENSING ELEMENT

NEXT DISPLAY : PRESSURE SENSORS - P0 AND PS3.

TCC SENSOR TOC

Page 34

CTC-216-059-00

PURPOSE / LOCATE :

P0 SENSOR. PS3 SENSOR.

FWD

PURPOSE :

PS3

EEC

WEEP HOLES. ‘WEEP’ = OLD ENGLISH WORD MEANING ‘PLEURER’.

CDP LINE

PS3 P0

NEXT DISPLAY : PS13 & P25.

P0 AND PS3 PRESSURE SENSORS TOC

Page 35

CTC-216-060-00

PURPOSE / LOCATE :

PS13 SENSOR. P25 SENSOR.

PS13

PS13

P25

PS13 TRANSDUCER

EEC CHANNEL A

P25 TRANSDUCER

EEC CHANNEL B

AIR PRESSURE TUBE

NEXT DISPLAY : VIBRATION SENSORS.

PS13 AND P25 SENSORS TOC

Page 36

FUNCTION :

TYPICAL VIBRATION SENSOR

VIBRATION SENSORS.

SPRING TO PRELOAD THE PIEZO ELECTRIC DISC MASS

PIEZO ELECTRIC DISCS

CTC-216-251-00

QUANTITY OF CURRENT PROPORTIONAL TO G LOAD

BASE ATTACHED TO ENGINE

NEXT DISPLAY : NO 1 BEARING ACCELEROMETER.

VIBRATION SENSORS TOC

Page 37

LOCATE / PURPOSE / DESCRIBE : FAN FRAME OUTER SURFACE

SELF-SEALING CONNECTOR

NO1 BEARING ACCELEROMETER.

SHOCK ABSORBERS

IDENTIFY / PURPOSE :

ELECTRICAL OUTPUT CONNECTOR

SHOCK ABSORBERS.

SENSITIVE AXIS

CABLE FORWARD STATIONARY AIR SEAL

VIBRATION SENSING ELEMENT

VIBRATION SENSOR (ACCELEROMETER)

AFT LOOKING FORWARD (ALF)

CTC-216-244-00

NEXT DISPLAY : FFCCV ACCELEROMETER.

NO.1 BEARING ACCELEROMETER

TOC

Page 38

LOCATE / PURPOSE / DESCRIBE : FFCCV ACCELEROMETER. SENSOR RECEPTACLE ELECTRICAL CONNECTOR FFCCV VIBRATION SENSOR FAN FRAME

FFCCV VIBRATION SENSOR FWD

CTC-216-245-00

NEXT DISPLAY : TABLE OF CONTENTS.

FAN FRAME COMPRESSOR CASE VERTICAL (FFCCV) ACCELEROMETER

TOC

Page 39

ENGINE SYSTEMS COURSE STRUCTURE - EEC

- Clearance Control • 75-21-00 HPTCC • 75-22-00 LPTCC

- Sensors

- Oil

- Intro

- Harnesses - Starting & Ignition • 80-00-00 Start system • 80-11-79 Starter • 74-00-00 Ignition - Power Management & Fuel Control - Fuel • 73-11-00 • 73-11-10 • 73-11-64 • 79-21-20 • 73-11-20 • 73-21-18 • 73-30-11 • 73-11-45 • 73-11-40

Fuel distribution Fuel pump IDG oil cooler Main oil / fuel heat exchanger Servo fuel heater Hydromechanical unit Fuel flow transmitter Fuel nozzle filter Fuel nozzle

- Geometry Control • 75-30-00 Variable geometry control system • 75-31-00 Variable bleed valve • 75-32-00 Variable stator vane • 75-26-00 Transient bleed valve

• 79-00-00 • 79-11-00 • 79-21-43 • 79-21-10 • 79-21-50 • 79-21-42 • 79-30-00 • 79-31-00 • 79-32-10 • 79-31-40 • 79-20-00

Oil general Oil tank Anti-leakage valve Lubrication unit Debris monitoring system (optional) Oil scavenge filter assembly Oil indicating components Oil quantity transmitter Oil pressure transmitter Oil temperature sensor Oil filter bypass switch

- Powerplant Drains - Thrust Reverser - Indicating • 77-00-00 Engine indicating system panels • 77-00-00 Common Display System - Vibration Monitoring • 77-31-00 Vibration monitoring and indicating - Condition Monitoring • 77-00-00 Aircraft condition monitoring system

TOC

NEXT DISPLAY : ENGINE WIRING HARNESSES. Page 40

IDENTIFY :

FAN SECTION HARNESS DESIGNATIONS. CORE ENGINE HARNESS DESIGNATIONS.

J5, J6, J7, J8, J9, & J10.

CTC-216-062-00

CJ9, CJ10.

NEXT DISPLAY : HARNESS INTERFACES.

ELECTRICAL ENGINE HARNESSES

TOC

Page 41

IDENTIFY: J5

CHANNEL A FUEL FLOW METER

N2 SENSOR

J7

EEC

HMU

J8

COMPONENTS - ‘CJ’ HARNESSES. RANDOM SELECTION.

N1 SENSOR

J6 CHANNEL B

OIL TEMP.

COMPONENTS - ‘J’ HARNESSES. RANDOM SELECTION.

T12 CH. B

CH. A EEC ALTERNATOR

J9

J10

OIL FILTER CLOGGED

T49,5 (S1) T49,5 (S2)

OIL PRESSURE SENSOR CJ9 FUEL FILTER CLOGGED

T49,5 (S3) T49,5 (S4) T5

JUNCTION

CHANNEL A

BOX T3

TBV

VBV

VSV

HPTACC

LPTACC

T25

DMS CHIPS DETECTORS (OPTIONAL)

TCC JUNCTION CJ10 BOX

CTC-216-063-00

CHANNEL B

NEXT DISPLAY : HOT SECTION HARNESSES.

HARNESSES INTERFACES

TOC

Page 42

CTC-216-064-00

DESCRIBE :

THE HARNESS. IDENTIFICATION.

CLAMPS

POLYAMIDE BRAID (EXCEPT AROUND VERY HOT PARTS)

SHIELDING BRAID

TEFLON BRAID

NEXT DISPLAY : FAN SECTION HARNESSES.

HOT SECTION HARNESSES TOC

Page 43

CTC-216-065-00

DESCRIBE :

HEAT SHRINK SLEEVE

THE HARNESS. IDENTIFICATION.

J7

PEENING HOLE

LOCKING RING

ADHESIVE COMPOUND

BUSH

ADAPTER STRANDS OF WIRE WIRES

OUTER SHEATH BRAID

NEXT DISPLAY : TABLE OF CONTENTS.

FAN SECTION HARNESSES TOC

Page 44

ENGINE SYSTEMS COURSE STRUCTURE - EEC

- Clearance Control • 75-21-00 HPTCC • 75-22-00 LPTCC

- Sensors

- Oil

- Intro

- Harnesses - Starting & Ignition • 80-00-00 Start system • 80-11-79 Starter • 74-00-00 Ignition - Power Management & Fuel Control - Fuel • 73-11-00 • 73-11-10 • 73-11-64 • 79-21-20 • 73-11-20 • 73-21-18 • 73-30-11 • 73-11-45 • 73-11-40

Fuel distribution Fuel pump IDG oil cooler Main oil / fuel heat exchanger Servo fuel heater Hydromechanical unit Fuel flow transmitter Fuel nozzle filter Fuel nozzle

- Geometry Control • 75-30-00 Variable geometry control system • 75-31-00 Variable bleed valve • 75-32-00 Variable stator vane • 75-26-00 Transient bleed valve

• 79-00-00 • 79-11-00 • 79-21-43 • 79-21-10 • 79-21-50 • 79-21-42 • 79-30-00 • 79-31-00 • 79-32-10 • 79-31-40 • 79-20-00

Oil general Oil tank Anti-leakage valve Lubrication unit Debris monitoring system (optional) Oil scavenge filter assembly Oil indicating components Oil quantity transmitter Oil pressure transmitter Oil temperature sensor Oil filter bypass switch

- Powerplant Drains - Thrust Reverser - Indicating • 77-00-00 Engine indicating system panels • 77-00-00 Common Display System - Vibration Monitoring • 77-31-00 Vibration monitoring and indicating - Condition Monitoring • 77-00-00 Aircraft condition monitoring system

TOC

NEXT DISPLAY : STARTING SYSTEM. Page 45

DESCRIBE : PRESSURIZED AIR FROM A/C AIR BLEED SYSTEM

CONTROL COMPONENTS. COCKPIT SWITCHES, CDS/DEU, EEC

UPPER AIR DUCT

IDENTIFY :

CDS/DEU START VALVE

PNEUMATIC POWER SOURCES. APU, GPU, RUNNING OPPOSITE ENGINE

SYSTEM COMPONENTS.

START VALVE LOWER AIR DUCT

STARTER

STARTER

CTC-216-297-00

NEXT DISPLAY : COCKPIT CONTROL INTERFACES.

START SYSTEM

TOC

Page 46

LOCATE / DESCRIBE : ENGINE START SWITCH

OFF

GRD

ENGINE START

CONT BOTH FLT IGN IGN L R

OFF

GRD

1

P5

ENGINE START SWITCHES. ENGINE START LEVERS.

CONT FLT

CDS - DEU. COMMON DISPLAY SYSTEM - DISPLAY ELECTRONIC UNIT.

2

IGNITION SELECTOR SWITCH

FLIGHT COMPARTMENT THRUST LEVERS

A/T LIM

TAT - 19C 96.0

CRZ

REVERSER UNLOCKED

0.0

10 8 TAI

6 4

10

0 2

0.0

8 6 4

N1

15

TAI

X-BLD START 8

0.0

10

0 6 4 2 12

8 N2

16.8

0 6 4 2 12

0.00

0.00

0

8 4

1

8500

50

18 EGT

10

8 FF/FU LB X 1000 CTR

2800 FUEL LB

0

START VLV OPEN

100 50 0 OIL P

200 100 0

OIL T

200 100 0 90

96 OIL Q%

A 3

8500

100 0

2 3 4 2 3 4 1 1 5 5 0 0 VIB

4

2

B 3

4

2 1 0

HYD P

4

2 1 0

FWD

RF 100 HYD Q% 100 RF

CDS DISPLAY UNIT

CTC-216-292-00

ENGINE START LEVERS

LOW OIL PRESS LOW OIL PRESS

0 2

CONTROL STAND

NEXT DISPLAY : START PROCEDURE SUMMARY.

START SYSTEM INTERFACES

TOC

Page 47

IDENTIFY : ENGINE START

OFF

1

GRD

CONT BOTH FLT IGN IGN L R

OFF

GRD

CONT FLT

TAT - 19C

5

2

50

ENGINE START SWITCHES (P5) 2

ENGINE START

OFF

GRD

CONT BOTH FLT IGN IGN L R

OFF

GRD

1

CONT FLT

6

100 50 0 OIL P

FF/FU LB X 1000

100 0

0 2

START LEVERS.

FUEL FLOW IN LIMITS 9

GROUND PERSONNEL : N1 TURNS CCW (FLA)

188

2

TAT - 19C

0.0

ENGINE START LEVERS

LOW OIL PRESS LOW OIL PRESS

0

50

TAI

100 0

50

100 0

11

10 OFF

EGT

GRD

START 10

UPPER CENTER DISPLAY UNIT (P2) CONTROL STAND

MOVED TO 20% N2 MINI

8 N2

4 X-BLD START

0.0

8 6 4

0 2

N2

START SEQUENCE.

IDENTIFY:

MONITORED PARAMETERS.

CONT FLT

55.0

0 6 4 2

2

BUT

EGT 10

DESCRIBE :

EGT

START VLV OPEN

EGT 10

16.8

8

0 2

6 4

START 10 8 N2

CTC-216-293-00

ENGINE START SWITCHES.

1.85

4

7 3

4

6

0

LOW OIL PRESS LOW OIL PRESS

1

6

N2

8

START VLV OPEN

IGNITION SELECTOR SWITCHES.

20.1

0 6 4 2

RECOMMENDED TO 25 % N2 OR MORE

12 MONITOR ALL ENGINE PARAMETERS UNTIL IDLE ENGINE SPEED

NEXT DISPLAY : START CONTROL.

ENGINE START PROCEDURE SUMMARY TOC

Page 48

DESCRIBE START CONTROL: GRD OFF CONT FLT

CONT. APU SYSTEM

FLT.

A/T LIM BOTH IGN IGN L R

TAT - 19C 96.0

CRZ

REVERSER UNLOCKED

ENGINE START GRD OFF CONT FLT

GRD OFF CONT FLT

0.0

10 8

DEU 1

TAI

6 4

10

0 2

0.0

8 6 4

N1

15

TAI

0.0

10 8

ENGINE START SWITCHES (P5)

DEU 2

10

0 6 4 2 12

8 N2

16.8

0 6 4 2 12

0.00

0.00

0

8 4

1

8500

50

18 EGT

2

8 FF/FU LB X 1000 CTR

2800 FUEL LB

0

START VLV OPEN

LOW OIL PRESS LOW OIL PRESS

0 2

X-BLD START

1

GRD.

100 50 0 OIL P

OIL T 96 OIL Q%

90

2 3 4 2 3 4 1 1 5 5 0 0 VIB A 3

8500

100 0

200 100 0

200 100 0

4

2

START VALVE

B 3

4

2 1 0

HYD P

4

2 1 0

RF 100 HYD Q% 100 RF

CDS DISPLAY UNIT

EEC

CTC-216-294-00

STARTER

NEXT DISPLAY : ON GROUND PROTECTION - HOT START.

START CONTROL

TOC

Page 49

IDENTIFY :

2 TYPES OF STARTING MODE.

IDENTIFY :

PROTECTIONS FEATURED BY: ENHANCED MANUAL MODE MANUAL MODE

DESCRIBE :

ENGINE HOT START PROTECTION. EEC ROLE - WARNING DISPLAY.

INFORM : PRIMARY ENGINE DISPLAY

CTC-216-241-00

CREW MUST MOVE START LEVER TO ‘CUT OFF’ TO UNLATCH IGNITION OFF.

NEXT DISPLAY : WET START & ROLLBACK PROTECTION.

ON GROUND STARTING PROTECTION - HOT START

TOC

Page 50

DESCRIBE :

WET START. EEC ROLE - CDU MESSAGE.

ROLLBACK & OVERTEMPERATURE. EEC ROLE - CDS MESSAGE.

INFORM :

CDU - ENGINE STARTING BITE

CTC-216-305-00

CREW MUST MOVE START LEVER TO ‘CUT OFF’ TO UNLATCH IGNITION OFF.

PRIMARY ENGINE DISPLAY

NEXT DISPLAY : IN-FLIGHT STARTING.

ON GROUND STARTING PROTECTION - WET START AND ROLLBACK

TOC

Page 51

DESCRIBE :

IN-FLIGHT STARTING PROCEDURE.

ENGINE START GRD

OFF

CONT FLT

GRD

BOTH IGN L

OFF

CONT FLT

IGN R

ENGINE START GRD

OFF

CONT FLT

1

GRD

BOTH IGN L

OFF

CONT FLT

IGN R

2

1

2

EGT X-BLD START

89.1

89.1 N2

UPPER CENTER DISPLAY UNIT (P2)

CTC-216-296-00

NEXT DISPLAY : IN-FLIGHT START PROTECTION.

IN FLIGHT STARTING

TOC

Page 52

EGT STARTING REDLINE (RED)

IDENTIFY :

EGT START REDLINE LIMIT ON EGT DISPLAY.

DESCRIBE :

LIMIT DIFFERENCE ACCORDING TO START CLASSIFICATION :

20

950°C FOR QWR. QUICK WINDMILL RELIGHT

15 TIME (SECS) REDLINE (RED) QWR

10

NORMAL

725°C FOR NORMAL IN-FLIGHT RELIGHT. 5 QWR 0

ALTITUDE, FT

0

CTC-216-306-00

10000

20000

30000

40000

50000

NEXT DISPLAY : TABLE OF CONTENTS.

IN FLIGHT STARTING PROTECTION

TOC

Page 53

ENGINE SYSTEMS COURSE STRUCTURE - EEC

- Clearance Control • 75-21-00 HPTCC • 75-22-00 LPTCC

- Sensors

- Oil

- Intro

- Harnesses - Starting & Ignition • 80-00-00 Start system • 80-11-79 Starter • 74-00-00 Ignition - Power Management & Fuel Control - Fuel • 73-11-00 • 73-11-10 • 73-11-64 • 79-21-20 • 73-11-20 • 73-21-18 • 73-30-11 • 73-11-45 • 73-11-40

Fuel distribution Fuel pump IDG oil cooler Main oil / fuel heat exchanger Servo fuel heater Hydromechanical unit Fuel flow transmitter Fuel nozzle filter Fuel nozzle

- Geometry Control • 75-30-00 Variable geometry control system • 75-31-00 Variable bleed valve • 75-32-00 Variable stator vane • 75-26-00 Transient bleed valve

• 79-00-00 • 79-11-00 • 79-21-43 • 79-21-10 • 79-21-50 • 79-21-42 • 79-30-00 • 79-31-00 • 79-32-10 • 79-31-40 • 79-20-00

Oil general Oil tank Anti-leakage valve Lubrication unit Debris monitoring system (optional) Oil scavenge filter assembly Oil indicating components Oil quantity transmitter Oil pressure transmitter Oil temperature sensor Oil filter bypass switch

- Powerplant Drains - Thrust Reverser - Indicating • 77-00-00 Engine indicating system panels • 77-00-00 Common Display System - Vibration Monitoring • 77-31-00 Vibration monitoring and indicating - Condition Monitoring • 77-00-00 Aircraft condition monitoring system

TOC

NEXT DISPLAY : STARTER. Page 54

PURPOSE / LOCATE / DESCRIBE :

SAFETY CABLE MAGNETIC PLUG HOUSING

AIR STARTER.

HORIZONTAL DRIVE SHAFT

DESCRIBE :

SERVICING.

PACKING MAGNETIC PLUG

TEDECO SERVICING TOOL LOWER PNEUMATIC DUCT ASSEMBLY

COUPLING

ADAPTER COUPLING

OUTPUT SHAFT ENGINE ACCESSORY GEARBOX (AGB)

STARTER

FWD DRAIN/FILL PORT (MAGNETIC PLUG) CTC-216-162-00

NEXT DISPLAY : STARTER OPERATION.

STARTER

TOC

Page 55

CTC-216-164-00

IDENTIFY : DESCRIBE : A = TURBINE B = REDUCTION GEAR SET C = CLUTCH D = OUTPUT SHAFT

MAIN ELEMENTS. GENERAL OPERATION. BRIEF - DETAILS NEXT DISPLAY.

EXHAUST

AIR PRESSURE FROM A/C AIR SYSTEM

A

B

C

D

NEXT DISPLAY : AIR STARTER DETAILS.

AIR STARTER OPERATION

TOC

Page 56

DESCRIBE : STATOR INLET ASSEMBLY

CONTAINMENT RING

DETAILED OPERATION.

DIFFUSER ASSEMBLY

CUTTER RING

PLANETARY GEAR RING GEAR

SPRAG CLUTCH OUTPUT SHAFT WITH DECOUPLER ASSEMBLY

TENSION BAR

FILTER DISC TURBINE WHEEL

CTC-216-165-00

PUMP ASSEMBLY INTERMEDIATE HOUSING ASSEMBLY

SUN GEAR

NEXT DISPLAY : TABLE OF CONTENTS.

STARTER TOC

Page 57

ENGINE SYSTEMS COURSE STRUCTURE - EEC

- Clearance Control • 75-21-00 HPTCC • 75-22-00 LPTCC

- Sensors

- Oil

- Intro

- Harnesses - Starting & Ignition • 80-00-00 Start system • 80-11-79 Starter • 74-00-00 Ignition - Power Management & Fuel Control - Fuel • 73-11-00 • 73-11-10 • 73-11-64 • 79-21-20 • 73-11-20 • 73-21-18 • 73-30-11 • 73-11-45 • 73-11-40

Fuel distribution Fuel pump IDG oil cooler Main oil / fuel heat exchanger Servo fuel heater Hydromechanical unit Fuel flow transmitter Fuel nozzle filter Fuel nozzle

- Geometry Control • 75-30-00 Variable geometry control system • 75-31-00 Variable bleed valve • 75-32-00 Variable stator vane • 75-26-00 Transient bleed valve

• 79-00-00 • 79-11-00 • 79-21-43 • 79-21-10 • 79-21-50 • 79-21-42 • 79-30-00 • 79-31-00 • 79-32-10 • 79-31-40 • 79-20-00

Oil general Oil tank Anti-leakage valve Lubrication unit Debris monitoring system (optional) Oil scavenge filter assembly Oil indicating components Oil quantity transmitter Oil pressure transmitter Oil temperature sensor Oil filter bypass switch

- Powerplant Drains - Thrust Reverser - Indicating • 77-00-00 Engine indicating system panels • 77-00-00 Common Display System - Vibration Monitoring • 77-31-00 Vibration monitoring and indicating - Condition Monitoring • 77-00-00 Aircraft condition monitoring system

TOC

NEXT DISPLAY : IGNITION SYSTEM. Page 58

CTC-216-171-00

IGNITER (2)

2 IGNITION LEAD ASSEMBLIES

PURPOSE :

IGNITION SYSTEM.

IDENTIFY :

MAIN COMPONENTS.

DESCRIBE :

FUNCTION - MAIN COMPONENTS. BRIEF.

2 EXCITERS

NEXT DISPLAY : IGNITION EXCITERS.

IGNITION GENERAL TOC

Page 59

CTC-216-173-00

PURPOSE / LOCATE / DESCRIBE : IGNITION EXCITERS.

UPPER IGNITION EXCITER

IDENTIFY : ENGINE RIGHT SIDE

IDENTIFY :

IGNITION 2

INPUT & OUTPUT VOLTAGES.

POSSIBLE HAZARDS.

TO RIGHT IGNITER

TO LEFT IGNITER

IGNITION 1

SHOCKMOUNT LOWER IGNITION EXCITER

GROUND STRAP

NEXT DISPLAY : IGNITION LEADS.

IGNITION EXCITERS TOC

Page 60

BOOSTER AIR INTRODUCTION

NON-COOLED SECTION IGNITION EXCITER SIDE

LOCATE / DESCRIBE :

IGNITION LEAD ASSEMBLY.

IDENTIFY :

COOLING AIR FLOWPATH.

AIR INLET ADAPTER

COOLED SECTION

CTC-216-176-00

BRAIDED CONDUIT

BOOSTER AIR

ELBOW ASSEMBLY IGNITER PLUG SIDE

COOLING AIR EXIT 6 O'CLOCK STRUT

IGNITION LEADS

NEXT DISPLAY : IGNITER PLUG.

IGNITION LEAD TOC

Page 61

IDENTIFY :

PLUG COMPONENTS.

DESCRIBE :

OPERATION PRINCIPLE.

SHROUD CLAMP COMBUSTION CASE

COOLING SHROUD

BASIC MAINTENANCE PRACTICES. COUPLING NUT IGNITER BUSHING

IGNITION LEAD ASSEMBLY

ELECTRODE IGNITER PLUG

CAPTIVE WASHER OUTER SILICONE SEAL

CTC-216-177-00

COOLING SHROUD

NEXT DISPLAY : IGNITION CONTROL.

IGNITER PLUG

TOC

Page 62

IDENTIFY :

POWER SUPPLIES.

IDENTIFY :

CONTROL COMPONENTS.

DESCRIBE :

THEIR INTERACTION DURING STARTING.

(AUTO) OFF

GRD

CTC-216-172-00

ENGINE START

CONT BOTH FLT IGN IGN L R

OFF

GRD

ENGINE

A/C

CONT FLT

MONITOR 1

IGNITION 2

EEC Ch. B B

2

START SWITCHES FLIGHT COMPARTMENT

115VAC STANDBY BUS

J2

J2

UPPER IGNITION EXCITER

CH. A RIGHT IGNITER CH. B IGNITION 1

EEC Ch. A MONITOR

115VAC TRANSFER BUS

START LEVERS

J1

A

J1

LOWER IGNITION EXCITER

CH. A LEFT IGNITER CH. B

CONTROL STAND

NEXT DISPLAY : IGNITION / START CONTROL.

IGNITION SYSTEM TOC

Page 63

IDENTIFY :

IGNITER SELECTOR POSITIONS.

START LEVERS OFF

GRD

ENGINE START

CONT BOTH FLT IGN IGN R L

OFF

GRD

CONT FLT

START SWITCH POSITIONS.

LEFT IGNITER

RIGHT IGNITER 1

2

CONTROL STAND OFF

GRD

ENGINE START

CONT BOTH FLT IGN IGN L R

OFF

GRD

CONT FLT

2

ENGINE 1 & 2, LEFT IGNITER SELECTION OFF

ENGINE START

CONT BOTH FLT IGN IGN R L

OFF

GRD

CONT FLT

2

ENGINE 1 & 2 CRUISE, NO IGNITION (UNLESS FLAMEOUT) OFF

ENGINE START

CONT BOTH FLT IGN IGN L R

1

OFF

GRD

RIGHT IGNITER

CONT FLT

LEFT IGNITER 2

ENGINE 1 & 2 FLIGHT, BOTH IGNITERS OPERATE

CTC-216-300-00

RIGHT IGNITER

LEFT IGNITER

1

GRD

IGNITER ACTIVATION ACCORDING TO START SWITCH POSITION.

LEFT IGNITER

1

GRD

DESCRIBE :

ENGINE 1 RIGHT IGNITER SELECTION, START LEVER UP

RIGHT IGNITER

NEXT DISPLAY : ABNORMAL OPERATION & AUTO IGNITION.

IGNITION/START CONTROL

TOC

Page 64

ENGINE START GRD

OFF

CONT FLT

IGN L

ENGINE START GRD

BOTH

OFF

CONT

GRD

AUTO CONT

FLT

IGN R

1

REMIND STUDENTS OF START SWITCH POSITION WHEN THE ENGINE IS RUNNING.

FLT

2

GRD

BOTH IGN L

AUTO CONT FLT

IGN R

1

AUTOMATIC IGNITION OPTION NOT INSTALLED: IDENTIFY PARAMETERS FOR AUTOMATIC IGNITION.

2

AUTOMATIC IGNITION OPTION INSTALLED: TRA

N2 N2 DECEL

EEC

50%