U.S%20ARMY

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U.S ARMY CH-47D CHINOOK T55-GA-714A (ECP D 218)
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FUEL SUPPLY
HYD PRESS
HYD RTN
REVERSIONARY
ACCESSORY
P3
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No. 4 TURBINE
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RTN TO TANK
TO FWD COMP
TO REAR COMP
OIL IN
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CHIP DETECTOR
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PTIT
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PRESSURIZING VALVE
FLOW DIVIDER
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OVERSPEED SOLENOID VALVE
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WATER WASH LINE AIR
WATER WASH LINE FLUID
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FADEC SYSTEM INTRODUCTION
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HYDROMECHANICAL FUEL CONTROL

• Marginal Starting During Hot Restarts and
• Cold Temperature Operations

• Slow Engine Acceleration Rates

• Compressor Stalls or Surges

• Mismatching of Engine Torque Under
• Heavy Load Conditions

• Rotor Speed Droop During Transient Maneuvers

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HYDROMECHANICAL FUEL CONTROL

• Lack of Safety Features or Mode Failure
  Protection

• Lack of Built-In Test or Self-Diagnostics

• Inability to Record Engine Faults, History,
• and Limit Exceedence Values

• High Pilot and Maintenance Workload

• Require a Large Spares Inventory

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FADEC ADVANTAGES

• Simplified Hands-Off Engine Starting

• Improved Engine Acceleration/Deceleration Control

• Power Assurance/Overspeed Test

• Independent Electronic Engine Overspeed
  Protection

• Engine Compressor Surge Detection And Avoidance

• Control System Self-Test, Self-Diagnosis
• And Fault Identification

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FADEC ADVANTAGES

• Engine History, Start/Component Cycle
• And Limit Exceedence Recording

• Load Anticipation (Minimizing Rotor Droop)

• Accurate Torque Matching And Limiting Functions

• Automatic Switch-Over to an Independent
• Back-Up Control System

• Engine Over-Temperature Avoidance

• No Field Level, System Adjustments

• On-Condition Maintenance

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PRIMARY MODE FUNCTIONS

• Twin Engine Load Sharing

• Electronic Power Turbine Speed Governing

• Transient Load Anticipation Using Rotor Speed
  And Thrust Rate

• Transient Torque Smoothing Using Power Turbine
  Rates

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PRIMARY MODE FUNCTIONS

• Contingency Power To Meet Aircraft Demands

• Automatic Engine Starting, Sequencing Ignition,
  Start Fuel, And Stabilized Engine Operation At
  Idle

• Acceleration And Deceleration Using Closed Loop
  NDOT Control

• Engine Temperature And Temperature Rate Limiting

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PRIMARY MODE FUNCTIONS

• Compressor Bleed Valve Control (For Both
  Transient And Steady State Surge Margin)

• Surge Detection/Surge Recovery

• Fuel Flow Limiting

• Engine Fail Detection

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PRIMARY MODE FUNCTIONS

• Engine Power Assurance Test

• Engine History/Fault Recording

• Automatic Switch Over To The Reversionary
  Channel In The Event Of Primary Channel Hard Fault

• Data Bus For Decu To Decu Cross
• Communication

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REVERSIONARY MODE FUNCTIONS

• Automatic Start Sequencing Including
• Over Temperature Protection

• Pilot Controlled Start Fuel Enrichment/De-Enrichm
  ent,
• If Required Through ECL Modulation

• Proportional Power Turbine Governing And
  Automatic
• Power Modulation Response To Thrust Rate Changes

• Engine 1 (2) Increase/Decrease Switch To Input
  Power
• Turbine Changes For Accurate Load Matching Of The
• Engines

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REVERSIONARY MODE FUNCTIONS

• Full Contingency Power Capability

• Over Temperature Protection Throughout The
  Engine Operational Range

• Engine Shutdown In Response To The ECL

• Tracking Of The Primary Channels Operation
  Allowing A Smooth Switch- Over When The
  Reversionary Channel Is Selected, Or The Primary
  Channel Fails

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FADEC SYSTEM COMPONENTS
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REFER TO HMA COLOR HANDOUT
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ENGINE P3 LINE
AMBIENT AIR
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P3 FROM HMA
P3 TO DECU
SIGHT GAUGE
CHECK VALVE
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T1
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FADEC SYSTEM OPERATION
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PRIMARY SYSTEM INTERFACE
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PRIMARY SYSTEM INTERFACE
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PRIMARY SYSTEM INTERFACE
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PRIMARY SYSTEM OPERARIONS
ENGINE STARTING
ENGINE SHUTDOWN
POWER AVAILABLE
ACCELERATION AND DECELERATION
SURGE RECOVERY
STEADY STATE FLIGHT CONDITIONS
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PRIMARY SYSTEM OPERARIONS
TRANSIENT FLIGHT CONDITIONS
TEMPERATURE LIMITING
TEMPERATURE LIMITING
POWER TURBINE OVERSPEED LIMITING
POWER ASSURANCE TEST
FAULT CODE RECORDING
ENGINE HISTORY RECORDING
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REFER TO APPENDIX B1
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PRIMARY SYSTEM
Ground Starting, Primary Mode (Normal Operation,
No Faults)
1. SET THE ECL TO GND
2. HOLD ENG START SWITCH UNTIL N1 10

• PRIMARY CHANNEL WILL AUTOMATICALLY CONTROL
• THE START SEQUENCING

1. STARTER
2. FUEL FLOW TO START FUEL NOZZLES
3. IGNITION
4. FUEL FLOW TO MAIN FUEL NOZZLES
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PRIMARY SYSTEM
Ground Starting, Primary Mode (Normal Operation,
No Faults)

• TEMPERATURE LIMITING (AFTER LIGHTOFF PTIT 760C)

REDUCES FUEL FLOW TO 100 PPH MINIMUM

• OVERTEMPERATURE DURING START (ABORT)

• FUEL SHUTOFF IF PTIT gt 815.5ºC

• ENG FAIL INDICATION

• ECL TO STOP RESETTING THE START MODE

• AIR STARTS PROCEDURES ARE THE SAME
• AS FOR A GROUND START

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PRIMARY MODE
ENGINE SHUTDOWN
ECL MOVED TO GND TO ALLOW NORMAL ENGINE COOL DOWN
ECL TO STOP
PRIMARY SYSTEM CLOSES THE METERING VALVE TO THE
40 PPH POSITION
REVERSIONARY MODE WILL EFFECT COMPLETE SHUTOFF OF
FUEL WHEN THE ECL IS MOVED TO STOP
THE SHUTOFF FEATURE IS THE ONLY FUNCTION OF
THE REVERSIONARY MODE THAT IMPACTS THE PRIMARY
MODE.
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PRIMARY SYSTEM
POWER AVAILABLE
GROUND IDLE

• ECL AT GND

• IDLE SPEED ADJUSTED FOR ENGINE INLET
• TEMPERATURE

N1 50 - COLD DAY (-65F) 55 - STD DAY
(59F) 59 - HOT DAY (135F)
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PRIMARY SYSTEM
POWER AVAILABLE
GROUND TO FLIGHT TRANSITION

• ECL MOVED TO FLT POSITION

FADEC WILL ACCELERATE ENGINE TO NP GOVERNOR SET
SPEED (ROTOR RPM SELECTED BY THE NR SWITCH ON
THE FADEC CONTROL PANEL)
ECL FLT POSITION SETS NG GOVERNOR TO EMERGENCY
POWER SPEED LIMIT
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REVERSIONARY CONTROL
TRANSFER TO REVERSIONARY
REVERSIONARY CHANNEL (REV 1(2) OFF)
WHEN IN PRIMARY, THE REVERSIONAR CONTROL TRACKS N1
PILOT SELECTS REVERSIONARY OR PRIMARY CHANNEL
FAILURE COCKPIT DISPLAY - FADEC 1 (2) ON NORMAL
TRANSITION TO REVERSIONARY WILL BE SMOOTH,
NORMALLY NOT REQUIRING PILOT ACTION
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REVERSIONARY CONTROL
TRANSFER TO REVERSIONARY
IF THE REVERSIONARY CHANNEL IS HARD FAULTED (REV
1 (2) ON)
PRIMARY SYSTEM FAILS TO FIXED FUEL FLOW (FAILED
FIXED)
IF PILOT SELECTS REVERSIONARY, SYSTEM
CONTROL FAILS FIXED TO REVERSIONARY SETTING
COCKPIT CONTROLS AND INDICATIONS 1. COCKPIT
DISPLAY FADEC 1 (2) AND REV 1( 2)
INDICATION ON 2. THE EFFECTED ENGINE DOES NOT
RESPOND TO CONTROL CHANGES 3. INDICATED
TORQUE SPLITS
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REVERSIONARY SYSTEM INTERFACE
CONTROL REVERSIONARY MODE
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REVERSIONARY SYSTEM
ENGINE STARTING
ENGINE SHUTDOWN
CORE ENGINE SPEED GOVERNOR
PROPORTIONAL POWER TURBINE GOVERNOR
WF/P3DOT ACCELERATION AND DECELERATION
TEMPERATURE RATE OF CHANGE LIMITING
TEMPERATURE LIMITING
HYDROMECHANICAL BLEED BAND CONTROL
INC/DEC TRIM FUNCTION
FAULT CODE REPORTING
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REFER TO APPENDIX B2
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REVERSIONARY MODE
ECL ENRICHMENT IF ENGINE TENDS TO STAGNATE HAS
NOT BEEN REQUIRED IN DEVELOPMENT ENGINE
TESTS (-65º TO 135º F STARTS)
760º C TEMPERATURE LIMIT FUEL CUTBACK TO 130 PPH
MIN FLOW
AIR START SAME PROCEDURE AS GROUND STARTS
WINDMILL SPEEDS WHERE N1 gt 10 WILL START AS ECL
IS MOVED FROM STOP
SHUTDOWN ECL SET TO GND FOR ENGINE COOL DOWN ECL
SET TO STOP REVERSIONARY WILL IMMEDIATELY OPEN
WINDMILL BYPASS FOR FUEL SHUTOFF
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PAT Power Assurance Test Ref. Pg 8-9 0f the TM
55-1529-240-10
Perform First Flight of the Day May be deferred
to the Hover Check
a. NR Switch 100
b. ENG 1 ECL - Adjust
c. Thrust Control Lever - Raise until TRQ reads
60 to 80. Stabilize for 30 seconds
d. Test switch ENG 2 - PWR ASSURANCE. Check DECU
display compare displayed value with PAT Trigger
Value.
e. ENG 1 ECL - FLT
f. Repeat check with ENG 2 COND lever
g. THRUST CONT lever - Adjust
4. RRPM - Set as required
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PAT Power Assurance Test Ref. Pg 2-55 0f the TM
55-1529-240-MTF
Perform First Flight of the Day
a. NR Switch 100
b. ENG 1 ECL - Adjust
c. Thrust Control Lever - Raise until TRQ reads
60 to 80. Stabilize for 30 seconds
d. Test switch ENG 2 - PWR ASSURANCE. Check DECU
display (FE) An A means that the engine is
operating at a cooler temperature than a
baseline spec engine. An F means that the engine
is operating at a warmer temperature than a
baseline spec engine. . Record Results.
d. THRUST CONT lever - Adjust
d. ENG 1 ECL - FLT
e. Repeat check with ENG 2 ENG COND lever
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PAC Power Assurance Check Ref. Pg 2-76.1 0f the
TM 55-1529-240-MTF Ref. Section IV
Power Assurance Check Maximum Power Chart Power
Assurance Check Maximum Continuous Power
Chart Power Assurance Check engine Temperature
Limits Chart Power Assurance Check N1 Gas
Generator Speed Power Assurance Check Altitude
Bands Chart
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MONITORING FAULT CHECKS
Power-Up Prestart Checks Pressure Sensors Bleed
Valve Solenoid Primary Reversionary Change-Over
Solenoid Primary Switch-Over (Watchdog Timer)
Circuitry Programmable Read Only Memory
(Prom) Electronically Erasable Programmable Read
Only Memory (Eeprom)
CONTINUOUS FAULT CHECKS
Airframe Engine Interface Sensors Electromechani
cal Components Power Supplies
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FAULT STORAGE AND READOUT
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REVERSIONARY FAULTS
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Tom Mietus [phone] thomas.r.mietus_at_bo
eing.com Date 10/18/99 Course PILOTS
POWERPLANT COURSE (ECP D 218)
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BOEING CUSTOMER TRAINING