Title: U.S%20ARMY
1(No Transcript)
2U.S ARMY CH-47D CHINOOK T55-GA-714A (ECP D 218)
3(No Transcript)
4(No Transcript)
5FUEL SUPPLY
HYD PRESS
HYD RTN
REVERSIONARY
ACCESSORY
P3
6(No Transcript)
7(No Transcript)
8(No Transcript)
9(No Transcript)
10(No Transcript)
11(No Transcript)
12(No Transcript)
13No. 4 TURBINE
14(No Transcript)
15(No Transcript)
16(No Transcript)
17(No Transcript)
18(No Transcript)
19(No Transcript)
20(No Transcript)
21RTN TO TANK
TO FWD COMP
TO REAR COMP
OIL IN
22(No Transcript)
23CHIP DETECTOR
24(No Transcript)
25PTIT
26(No Transcript)
27(No Transcript)
28PRESSURIZING VALVE
FLOW DIVIDER
29(No Transcript)
30(No Transcript)
31(No Transcript)
32(No Transcript)
33OVERSPEED SOLENOID VALVE
34(No Transcript)
35(No Transcript)
36WATER WASH LINE AIR
WATER WASH LINE FLUID
37(No Transcript)
38(No Transcript)
39(No Transcript)
40(No Transcript)
41(No Transcript)
42(No Transcript)
43(No Transcript)
44(No Transcript)
45(No Transcript)
46(No Transcript)
47FADEC SYSTEM INTRODUCTION
48(No Transcript)
49HYDROMECHANICAL 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
50HYDROMECHANICAL 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
51FADEC 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
52FADEC 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
53PRIMARY MODE FUNCTIONS
- Electronic Power Turbine Speed Governing
- Transient Load Anticipation Using Rotor Speed
And Thrust Rate
- Transient Torque Smoothing Using Power Turbine
Rates
54PRIMARY 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
55PRIMARY MODE FUNCTIONS
- Compressor Bleed Valve Control (For Both
Transient And Steady State Surge Margin)
- Surge Detection/Surge Recovery
56PRIMARY 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
57REVERSIONARY 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
58REVERSIONARY 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
59FADEC SYSTEM COMPONENTS
60(No Transcript)
61(No Transcript)
62(No Transcript)
63(No Transcript)
64(No Transcript)
65(No Transcript)
66(No Transcript)
67(No Transcript)
68(No Transcript)
69REFER TO HMA COLOR HANDOUT
70(No Transcript)
71(No Transcript)
72(No Transcript)
73(No Transcript)
74(No Transcript)
75(No Transcript)
76ENGINE P3 LINE
AMBIENT AIR
77P3 FROM HMA
P3 TO DECU
SIGHT GAUGE
CHECK VALVE
78(No Transcript)
79(No Transcript)
80(No Transcript)
81(No Transcript)
82T1
83(No Transcript)
84(No Transcript)
85(No Transcript)
86(No Transcript)
87(No Transcript)
88(No Transcript)
89(No Transcript)
90FADEC SYSTEM OPERATION
91PRIMARY SYSTEM INTERFACE
92PRIMARY SYSTEM INTERFACE
93PRIMARY SYSTEM INTERFACE
94(No Transcript)
95(No Transcript)
96PRIMARY SYSTEM OPERARIONS
ENGINE STARTING
ENGINE SHUTDOWN
POWER AVAILABLE
ACCELERATION AND DECELERATION
SURGE RECOVERY
STEADY STATE FLIGHT CONDITIONS
97PRIMARY SYSTEM OPERARIONS
TRANSIENT FLIGHT CONDITIONS
TEMPERATURE LIMITING
TEMPERATURE LIMITING
POWER TURBINE OVERSPEED LIMITING
POWER ASSURANCE TEST
FAULT CODE RECORDING
ENGINE HISTORY RECORDING
98(No Transcript)
99(No Transcript)
100REFER TO APPENDIX B1
101(No Transcript)
102(No Transcript)
103PRIMARY 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
104PRIMARY 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
- ECL TO STOP RESETTING THE START MODE
- AIR STARTS PROCEDURES ARE THE SAME
- AS FOR A GROUND START
105PRIMARY 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.
106PRIMARY SYSTEM
POWER AVAILABLE
GROUND IDLE
- IDLE SPEED ADJUSTED FOR ENGINE INLET
- TEMPERATURE
N1 50 - COLD DAY (-65F) 55 - STD DAY
(59F) 59 - HOT DAY (135F)
107PRIMARY 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
108(No Transcript)
109REVERSIONARY 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
110REVERSIONARY 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
111(No Transcript)
112REVERSIONARY SYSTEM INTERFACE
CONTROL REVERSIONARY MODE
113(No Transcript)
114REVERSIONARY 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
115(No Transcript)
116(No Transcript)
117REFER TO APPENDIX B2
118(No Transcript)
119(No Transcript)
120(No Transcript)
121(No Transcript)
122REVERSIONARY 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
123(No Transcript)
124(No Transcript)
125(No Transcript)
126(No Transcript)
127PAT 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
128PAT 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
129PAC 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
130MONITORING 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
131(No Transcript)
132(No Transcript)
133FAULT STORAGE AND READOUT
134REVERSIONARY FAULTS
135(No Transcript)
136 Tom Mietus (610) 591-4148 thomas.r.mietus_at_bo
eing.com Date 10/18/99 Course PILOTS
POWERPLANT COURSE (ECP D 218)
137BOEING CUSTOMER TRAINING