CFM56-3 Line Maintenance Course
|
|
- Julie Townsend
- 6 years ago
- Views:
Transcription
1 CFM56-3 Line Maintenance Course Volume II Document: CFM3LMV2 Revised: January 96 Published by: CFMI Customer Training Programs GE Aircraft Engines Customer Technical Education Center 123 Merchant Street Cincinnati, Ohio ALL INTRO Page 1
2 THIS PAGE INTENTIONALLY LEFT BLANK ALL INTRO Page 2
3 This CFMI publication is for Training Purposes Only. The information is accurate at the time of compilation; however, no update service will be furnished to maintain accuracy. For authorized maintenance practices and specifications, consult pertinent maintenance publications. The information (including technical data) contained in this document is the property of CFM International (GE and SNECMA). It is disclosed in confidence, and the technical data therein is exported under a U.S. Government license. Therefore, None of the information may be disclosed to other than the recipient. In addition, the technical data therein and the direct product of those data, may not be diverted, transferred, re-exported or disclosed in any manner not provided for by the license without prior written approval of both the U.S. Government and CFM International. Copyright 1995 CFM International ALL INTRO Page 3
4 THIS PAGE INTENTIONALLY LEFT BLANK ALL INTRO Page 4
5 TABLE OF CONTENTS Section Topic Revision Page Numbers Intro Table of Contents...5 Intro Abbreviations and Acronyms Power Assurance Check Examples Trim Table Examples Systems Review Exercise Diagnostic Run Data Examples ALL INTRO Page 5
6 ABBREVIATIONS AND ACRONYMS ALL INTRO Page 6
7 AC ACARS AD ADC ADEPT ADIRS AGB AIDS ALF AOG APU ARINC ARP ATA AVM BITE BSI BTU C CAD CBP CCW CDP CESM CFM CFMI CIP Alternating Current Aircraft Communication Addressing and Reporting System Airworthiness Directive Air Data Computer Airline Data Engine Performance Trend Air Data and Inertial Reference System Accessory Gearbox Aircraft Integrated Data System Aft Looking Forward Aircraft On Ground Auxiliary Power Unit Aeronautical Radio Inc. Aero Recommended Practice Air Transport Association Aircraft Vibration Monitoring Built In Test Equipment Borescope Inspection British Thermal Unit Celsius/Centigrade (degrees) Computer Assisted Design Compressor Bleed Pressure Counter Clockwise Compressor Discharge Pressure Commercial Engine Service Memorandum Commercial Fan Motor Commercial Fan Motor International Compressor Inlet Pressure CIT cm.g CODEP CRT CSD CSI CSN CTEC CW DC DGAC DOD EBU ECAM EFH EFIS EGT EICAS EIS EMF ESN F F/I FAA FADEC FAR Compressor Inlet Temperature centimeter grams Common Deposition Cathode Ray Tube Constant Speed Drive Cycles Since Installation Cycles Since New Customer Technical Education Center Clockwise Direct Current Direction Generale de l Aviation Civile Domestic Object Damage Engine Buildup Unit Electronic Centralized Aircraft Monitoring Engine Flight Hours Electronic Flight Instrument System Engine Gas Temperature Engine Indicating and Crew Alerting System Electronic Instrument System ElectroMotive Force Engine Serial Number Fahrenheit (Degrees) Flight Idle Federal Aviation Administration Full Authority Digital Engine Control Federal Aviation Regulation ALL INTRO Page 7
8 FEIM FFCCV FIT FLA FMV FN FOD FPI g.in G/I GEAE GEM GPH GPM Field Engineering Investigation Memo Fan Frame Compressor Case Vertical Fan Inlet Temperature Forward Looking Aft Fuel Metering Valve Net Thrust Foreign Object Damage Fluorescent Penetrant Inspection gram inches Ground Idle General Electric Aircraft Engines Ground-based Engine Monitoring Gallons Per Hour Gallons Per Minute ID IDG IFSD IGB IGV in. IPB IPC ips K KIAS kpa Kv Inside Diameter Integrated Drive Generator In-flight Shutdown Inlet Gearbox Inlet Guide Vane inches Illustrated Parts Breakdown Illustrated Parts Catalog Inches Per Second Kelvin (Degrees) One Thousand Indicated Air Speed in Knots Kilo Paschal Kilovolts HC HCF HP HPC HPCR HPT HPTCC HPTCCV HPTN HPTR Hz I/O IAS Hydro-Carbons High Cycle Fatigue High Pressure High Pressure Compressor High Pressure Compressor Rotor High Pressure Turbine High Pressure Turbine Clearance Control High Pressure Turbine Clearance Control Valve High Pressure Turbine Nozzle High Pressure Turbine Rotor Hertz Input/Output Indicated Air Speed L/E lbs. LCD LCF LP LPC LPT LPTN LPTR LRU LVDT ma MCD MCL Leading Edge Pounds, Weight Liquid Crystal Display Low Cycle Fatigue Low Pressure Low Pressure Compressor Low Pressure Turbine Low Pressure Turbine Nozzle Low Pressure Turbine Rotor Line Replaceable Unit Linear Variable Differential Transducer Milliamperes (Current) Magnetic Chip Detector Maximum Climb ALL INTRO Page 8
9 MCR Maximum Cruise MCT Maximum Continuous MEC Main Engine Control mils D.A. Mils Double Amplitude mm Millimeters MN Mach Number MPA Maximum Power Assurance MTBF Mean Time Between Failures MTBO Mean Time Between Overhaul MTBR Mean Time Between Removals mv Millivolts mvdc Millivolts Direct Current N1 Actual Fan Speed N1* Desired Fan Speed N1K Corrected Fan Speed N2 Actual Core Speed N2* Desired Core Speed N2K Corrected Core Speed NLR Speed Low Pressure Rotor Pcr Pf PIREPS PLA PMC PPH PPH PRSOV Ps Ps12 Ps13 Ps3 psi psia psid Pt2.5 QAD Qty. Case Regulated Pressure Heated Servo Pressure Pilot Reports Power Lever Angle Power Management Control Pounds Per Hour Pounds Per Hour Pressure Regulating Shutoff Valve Pump Supply Pressure Fan Inlet Static Air Pressure Fan Outlet Static Air Pressure Compressor Discharge Pressure Pounds Per Square Inch Pounds Per Square Inch Absolute Pounds Per Square Inch Differential High Pressure Compressor Inlet Total Air Pressure Quick Attach Detach Quantity OAT OD OGV OVBD Outside Air Temperature Outside Diameter Outlet Guide Vane Overboard R RPM RTV RVDT Rankin (degrees) Revolutions Per Minute Room Temperature Vulcanizing Rotary Variable Differential Transducer P6 - Pb P7 - Pb Pb Pc CIT Signal Pressure Differential FIT Signal Pressure Differential Bypass Pressure Regulated Servo Pressure S/B S/R SER sfc Service Bulletin Service Request Service Evaluation Request Specific Fuel Consumption ALL INTRO Page 9
10 SG SGA SLS SLSD SN SNECMA STP SVR Specific Gravity Specific Gravity Adjustment Sea Level Standard Sea Level Standard Day Serial Number Societe d Etude et de Construction de Moteurs d Aviation Standard Temperature and Pressure Shop Visit Rate T/E Trailing Edge T/O Takeoff T/R Thrust Reverser T12 Fan Inlet Total Air Temperature (Electrical) T2.0 Fan Inlet Temperature (Hydromechanical) T2.5 High Pressure Compressor Inlet Air Temperature T4.95 Exhaust Gas Temperature TAI Thermal Anti-Ice TAT Total Air Temperature TBC Thermal Barrier Coating The Boeing Company TBD To Be Determined TBO Time Between Overhaul TC1 Turbine Clearance Control (5th Stage Signal) TC2 Turbine Clearance Control (9th Stage Signal) TC3 Turbine Clearance Control (Timer Signal) TCCV Turbine Clearance Control Valve TEMPER TGB TMC TRF Ts5 Ts9 TSI TSN TSO UER USAF USN VBV VDC VIB VMC VSV Wf YTD Turbine Engine Modular Performance Estimating Routine Transfer Gearbox Torque Motor Current Turbine Rear Frame Turbine Clearance Control (5th Stage Signal with Timer) Turbine Clearance Control (9th Stage Signal with Timer) Time Since Installation Time Since New Time Since Overhaul Unscheduled Engine Removal United States Air Force United States Navy Variable Bleed Valve Volts Direct Current Vibration Visual Meteorological Condition Variable Stator Vane Fuel Flow Year to Date ALL INTRO Page 10
11 THIS PAGE LEFT INTENTIONALLY BLANK ALL INTRO Page 11
12 POWER ASSURANCE CHECK EXAMPLES ALL Page 1
13 POWER ASSURANCE CHECK EXAMPLE #1 Engine Conditions 23.5K Pounds Thrust. Ambient Temperature (OAT) = 90 F (32 C) Use MPA Fan Speed (for this example 85% N 1 ) Procedure Record the following from the MPA Test 85% N 1 Fan Speed: - OAT -N 1 target - For 23.5K pounds thrust, EGT maximum - For CFM56-3C-1 engines, maximum 23.5K Page 2
14 OAT = 90 F N 1 TARGET = 87.3% FOR 23.5K POUNDS THRUST, EGT MAXIMUM = 799 C FOR CFM56-3C-1 ENGINES, MAXIMUM = 97.6% POWER ASSURANCE CHECK EXAMPLE #1 23.5K Page 3
15 POWER ASSURANCE CHECK EXAMPLE #1 Procedure Set N 1 target, after the engine operation is stable for four minutes and record N 1, and EGT. 23.5K Page 4
16 N 1 = 87.0% = 95.5% EGT = 785 C POWER ASSURANCE CHECK EXAMPLE #1 23.5K Page 5
17 POWER ASSURANCE CHECK EXAMPLE #1 Procedure Adjust the recorded parameters to the N 1 target: Use the N 1 difference: (N 1 target - N 1 record) For each 0.1% N 1 positive difference (N 1 target > N 1 record) adjust as follows: - add 1.0 C to the EGT record. - add 0.045% to the record. For each 0.1% N 1 negative difference (N 1 target < N 1 record) adjust as follows: - subtract 1.0 C to the EGT record. - subtract 0.045% to the record. 23.5K Page 6
18 N 1 TARGET - N 1 RECORD = DIFFERENCE = = 0.3% ADJUSTMENT = RECORDED + (0.3/0.1) (0.045) = (3 X.0045) = = 95.6% EGT ADJUSTMENT = EGT RECORDED + (0.3/0.1) (1) = (3 X 1) = = 788 C. POWER ASSURANCE CHECK EXAMPLE #1 23.5K Page 7
19 POWER ASSURANCE CHECK EXAMPLE #1 Procedure EGT adjustment for the HPTCC timer: - The EGT limits include the effects of the timer at this thrust rating. - No more adjustment is necessary. EGT adjustment for the altitude: - No adjustment is necessary for the altitude at this thrust rating. adjustment for the thrust rating: - No adjustment is necessary at this thrust rating. Compare the adjusted parameters to the determined limits. Record the margin and the EGT margin. 23.5K Page 8
20 MAXIMUM = 97.6% EGT MAXIMUM = 799 C MARGIN EGT MARGIN = MAXIMUM - ADJUSTMENT = = 2.0% = EGT MAXIMUM - EGT RECORD = = 11 C. POWER ASSURANCE CHECK EXAMPLE #1 23.5K Page 9
21 POWER ASSURANCE CHECK EXAMPLE #2 Engine Conditions CFM56-3C-1 22K Pounds Thrust Ambient Temperature (OAT) = 90 F (32 C) Use MPA Fan Speed (for this example 85% N 1 ) Procedure Record the following from the MPA Test 85% N 1 Fan Speed: - OAT -N 1 target - For 22K pounds thrust, EGT maximum - For CFM56-3C-1 engines, maximum 22K Page 10
22 OAT = 90 F N 1 TARGET = 87.3% FOR 22K POUNDS THRUST, EGT MAXIMUM = 803 C FOR CFM56-3C-1 ENGINES, MAXIMUM = 97.6% POWER ASSURANCE CHECK EXAMPLE #2 22K Page 11
23 POWER ASSURANCE CHECK EXAMPLE #2 Procedure Set N 1 target, after the engine operation is stable for four minutes and record N 1, and EGT. 22K Page 12
24 N 1 = 87.0% = 95.5% EGT = 785 C POWER ASSURANCE CHECK EXAMPLE #2 22K Page 13
25 POWER ASSURANCE CHECK EXAMPLE #2 Procedure Adjust the recorded parameters to the N 1 target: Use the N 1 difference: (N 1 target - N 1 record) For each 0.1% N 1 positive difference (N 1 target > N 1 record) adjust as follows: - add 1.0 C to the EGT record. - add 0.045% to the record. For each 0.1% N 1 negative difference (N 1 target < N 1 record) adjust as follows: - subtract 1.0 C to the EGT record. - subtract 0.045% to the record. 22K Page 14
26 N 1 TARGET-N 1 RECORD = DIFFERENCE = = 0.3% ADJUSTMENT = RECORDED + (0.3/0.1) (0.045) = (3 X.0045) = = 95.6% EGT ADJUSTMENT = EGT RECORDED + (0.3/0.1) (1) = (3 X 1) = = 788 C. POWER ASSURANCE CHECK EXAMPLE #2 22K Page 15
27 POWER ASSURANCE CHECK EXAMPLE #2 Procedure EGT adjustment for the HPTCC timer: - Increase the EGT margin by 17 C. - If the timer is deactivated in service, do not increase the EGT margin. EGT adjustment for the altitude: - No adjustment is necessary for the altitude at this thrust rating. adjustment for the thrust rating: - No adjustment is necessary at this thrust rating. Compare the adjusted parameters to the determined limits. Record the margin and the EGT margin. 22K Page 16
28 MAXIMUM = 97.6% EGT MAXIMUM = 803 C MARGIN EGT MARGIN = MAXIMUM - ADJUSTMENT = = 2.0% = EGT MAXIMUM - EGT RECORD = = 15 C = 15 C + 17 C (TIMER ADJUSTMENT) = 32 C POWER ASSURANCE CHECK EXAMPLE #2 22K Page 17
29 POWER ASSURANCE CHECK EXAMPLE #3 Engine Conditions CFM56-3C-1 20K Pounds Thrust Ambient Temperature (OAT) = 90 F (32 C) Use MPA Fan Speed (for this example 85% N 1 ) Procedure Record the following from the MPA Test 85% N 1 Fan Speed: - OAT -N 1 target - For 20K pounds thrust, EGT maximum - For CFM56-3C-1 engines, maximum 20K Page 18
30 OAT = 90 F N 1 target = 87.3% For 20K pounds thrust, EGT maximum = 848 C For CFM56-3C-1 engines, maximum = 97.6% POWER ASSURANCE CHECK EXAMPLE #3 20K Page 19
31 POWER ASSURANCE CHECK EXAMPLE #3 Procedure Set N 1 target, after the engine operation is stable for four minutes make a record of N 1, and EGT. 20K Page 20
32 N 1 = 87.0% = 95.5% EGT = 785 C POWER ASSURANCE CHECK EXAMPLE #3 20K Page 21
33 POWER ASSURANCE CHECK EXAMPLE #3 Procedure Adjust the recorded parameters to the N 1 target: Use the N 1 difference: (N 1 target - N 1 record) For each 0.1% N 1 positive difference (N 1 target > N 1 record) adjust as follows: - add 1.0 C to the EGT record. - add 0.045% to the record. For each 0.1% N 1 negative difference (N 1 target < N 1 record) adjust as follows: - subtract 1.0 C to the EGT record. - subtract 0.045% to the record. 20K Page 22
34 N 1 TARGET - N 1 RECORD = DIFFERENCE = = 0.3% EGT ADJUSTMENT = EGT RECORDED + (0.3/0.1) (1) = (3 X 1) = = 788 C. ADJUSTMENT = RECORDED + (0.3/0.1) (0.045) = (3 X.0045) = = 95.6% POWER ASSURANCE CHECK EXAMPLE #3 20K Page 23
35 POWER ASSURANCE CHECK EXAMPLE #3 Procedure EGT adjustment for the HPTCC timer: - Increase the EGT margin by 17 C. - If the timer is deactivated in service, do not increase the EGT margin. EGT adjustment for the altitude: - There is an altitude effect for this thrust rating. - The MPA tables are for sea level. - For 4,000 feet and above operation, decrease the EGT margin by 44 C. adjustment for the thrust rating: - Increase the margin by 0.6%. Compare the adjusted parameters to the determined limits. Record the margin and the EGT margin. 20K Page 24
36 MAXIMUM = 97.6% EGT MAXIMUM = 848 C MARGIN EGT MARGIN = MAXIMUM - ADJUSTMENT = = 2.0% = 2.0% + 0.6% (THRUST RATING) = 2.6% = EGT MAXIMUM - EGT RECORD = = 60 C = 60 C + 17 C (TCC TIMER) = 77 C = 77 C - 44 C (ALTITUDE) = 33 C (4000 FEET AND ABOVE) POWER ASSURANCE CHECK EXAMPLE #3 20K Page 25
37 POWER ASSURANCE CHECK EXAMPLE #4 Engine Conditions CFM56-3C K Pounds Thrust) Ambient Temperature (OAT) = 90 F (32 C) Use MPA Fan Speed (for this example 85% N 1 ) Procedure Record the following from the MPA Test 85% N 1 Fan Speed: - OAT -N 1 target - For 18.5K pounds thrust, EGT maximum - For CFM56-3C-1 engines, maximum 18.5K Page 26
38 OAT = 90 F N 1 TARGET = 87.3% FOR 18.5K POUNDS THRUST, EGT MAXIMUM = 874 C FOR CFM56-3C-1 ENGINES, MAXIMUM = 97.6% POWER ASSURANCE CHECK EXAMPLE #4 18.5K Page 27
39 POWER ASSURANCE CHECK EXAMPLE #4 Procedure Set N 1 target, after the engine operation is stable for four minutes and record N 1, and EGT. 18.5K Page 28
40 N 1 = 87.0% = 95.5% EGT = 785 C POWER ASSURANCE CHECK EXAMPLE #4 18.5K Page 29
41 POWER ASSURANCE CHECK EXAMPLE #4 Procedure Adjust the recorded parameters to the N 1 target: Use the N 1 difference: (N 1 target - N 1 record) For each 0.1% N 1 positive difference (N 1 target > N 1 record) adjust as follows: - add 1.0 C to the EGT record. - add 0.045% to the record. For each 0.1% N 1 negative difference (N 1 target < N 1 record) adjust as follows: - subtract 1.0 C to the EGT record. - subtract 0.045% to the record. 18.5K Page 30
42 N 1 TARGET - N 1 RECORD = DIFFERENCE = = 0.3% ADJUSTMENT = RECORDED + (0.3/0.1) (0.045) = (3 X.0045) = = 95.6% EGT ADJUSTMENT = EGT RECORDED + (0.3/0.1) (1) = (3 X 1) = = 788 C. POWER ASSURANCE CHECK EXAMPLE #4 18.5K Page 31
43 POWER ASSURANCE CHECK EXAMPLE #4 Procedure EGT adjustment for the HPTCC timer: - Increase the EGT margin by 17 C. - If the timer is deactivated in service, do not increase the EGT margin. EGT adjustment for the altitude: - There is an altitude effect for this thrust rating. - The MPA tables are for sea level. - For 4,000 feet and above operation, decrease the EGT margin by 44 C. adjustment for the thrust rating: - Increase the margin by 1.3%. Compare the adjusted parameters to the determined limits. Record the margin and the EGT margin. 18.5K Page 32
44 MAXIMUM = 97.6% EGT MAXIMUM = 874 C MARGIN EGT MARGIN = MAXIMUM - ADJUSTMENT = = 2.0% = 2.0% + 1.3% (THRUST RATING) = 3.3% = EGT MAXIMUM - EGT RECORD = = 86 C = 86 C + 17 C (TCC TIMER) = 103 C = 103 C - 44 C (ALTITUDE) = 59 C (4000 FEET AND ABOVE) POWER ASSURANCE CHECK EXAMPLE #4 18.5K Page 33
45 POWER ASSURANCE CHECK EXAMPLE #5 Engine Conditions CFM56-3B-2 22K Pounds Thrust Ambient Temperature (OAT) = 90 F (32 C) Use MPA Fan Speed (for this example 85% N 1 ) Procedure From the MPA Test Table (85% N 1 Fan Speed): - OAT -N 1 target - For 22K pounds thrust, EGT maximum - For CFM56-3B-2 engines, maximum 22K Page 34
46 OAT = 90 F N 1 TARGET = 87.3% FOR 22K POUNDS THRUST, EGT MAXIMUM = 803 C FOR CFM56-3B-2 ENGINES, MAXIMUM = 97.9% POWER ASSURANCE CHECK EXAMPLE #5 22K Page 35
47 POWER ASSURANCE CHECK EXAMPLE #5 Procedure Set N 1 target, after the engine operation is stable for four minutes and record N 1, and EGT. 22K Page 36
48 N 1 = 87.0% = 95.5% EGT = 780 C POWER ASSURANCE CHECK EXAMPLE #5 22K Page 37
49 POWER ASSURANCE CHECK EXAMPLE #5 Procedure Adjust the recorded parameters to the N 1 target: Use the N 1 difference: (N 1 target - N 1 record) For each 0.1% N 1 positive difference (N 1 target > N 1 record) adjust as follows: - add 1.0 C to the EGT record. - add 0.045% to the record. For each 0.1% N 1 negative difference (N 1 target < N 1 record) adjust as follows: - subtract 1.0 C to the EGT record. - subtract 0.045% to the record. 22K Page 38
50 N 1 TARGET - N 1 RECORD = DIFFERENCE = = 0.3% ADJUSTMENT = RECORDED + (0.3/0.1) (0.045) = (3 X.0045) = = 95.6% EGT ADJUSTMENT = EGT RECORDED + (0.3/0.1) (1) = (3 X 1) = = 783 C. POWER ASSURANCE CHECK EXAMPLE #5 22K Page 39
51 POWER ASSURANCE CHECK EXAMPLE #5 Procedure EGT adjustment for the HPTCC timer: - Increase the EGT margin by 17 C. - If the timer is deactivated in service, do not increase the EGT margin. EGT adjustment for the altitude: - No adjustment is necessary for the altitude at this thrust rating. adjustment for the thrust rating: - No adjustment is necessary at this thrust rating. Compare the adjusted parameters to the determined limits. Record the margin and the EGT margin. 22K Page 40
52 MAXIMUM = 97.6% EGT MAXIMUM = 803 C MARGIN EGT MARGIN = MAXIMUM - ADJUSTMENT = = 2.3% = EGT MAXIMUM - EGT RECORD = = 20 C = 20 C + 17 C (TCC TIMER) = 37 C POWER ASSURANCE CHECK EXAMPLE #5 22K Page 41
53 POWER ASSURANCE CHECK EXAMPLE #6 Engine Conditions CFM56-3B-2 20K Pounds Thrust Ambient Temperature (OAT) = 90 F (32 C) Use MPA Fan Speed (for this example 85% N 1 ) Procedure From the MPA Test Table (85% N 1 Fan Speed): - OAT -N 1 target - For 20K pounds thrust, EGT maximum - For CFM56-3B-2 engines, maximum 20K Page 42
54 OAT = 90 F N 1 TARGET = 87.3% FOR 20K POUNDS THRUST, EGT MAXIMUM = 848 C FOR CFM56-3B-2 ENGINES, MAXIMUM = 97.9% POWER ASSURANCE CHECK EXAMPLE #6 20K Page 43
55 POWER ASSURANCE CHECK EXAMPLE #6 Procedure Set N 1 target, after the engine operation is stable for four minutes and record N 1, and EGT. 20K Page 44
56 N 1 = 87.0% = 95.5% EGT = 785 C POWER ASSURANCE CHECK EXAMPLE #6 20K Page 45
57 POWER ASSURANCE CHECK EXAMPLE #6 Procedure Adjust the recorded parameters to the N 1 target: Use the N 1 difference: (N 1 target - N 1 record) For each 0.1% N 1 positive difference (N 1 target > N 1 record) adjust as follows: - add 1.0 C to the EGT record. - add 0.045% to the record. For each 0.1% N 1 negative difference (N 1 target < N 1 record) adjust as follows: - subtract 1.0 C to the EGT record. - subtract 0.045% to the record. 20K Page 46
58 N 1 TARGET - N 1 RECORD = DIFFERENCE = = 0.3% ADJUSTMENT = RECORDED + (0.3/0.1) (0.045) = (3 X.0045) = = 95.6% EGT ADJUSTMENT = EGT RECORDED + (0.3/0.1) (1) = (3 X 1) = = 788 C. POWER ASSURANCE CHECK EXAMPLE #6 20K Page 47
59 POWER ASSURANCE CHECK EXAMPLE #6 Procedure EGT adjustment for the HPTCC timer: - Increase the EGT margin by 17 C. - If the timer is deactivated in service, do not increase the EGT margin. EGT adjustment for the altitude: - There is an altitude effect for this thrust rating. - The MPA tables are for sea level. - If the route structure of the airplane includes an airport at 4,000 feet and above, decrease the EGT margin by 44 C. adjustment for the thrust rating: - Increase the margin by 0.6%. Compare the adjusted parameters to the determined limits. Record the margin and the EGT margin. 20K Page 48
60 MAXIMUM = 97.9% EGT MAXIMUM = 874 C MARGIN EGT MARGIN = MAXIMUM - ADJUSTMENT = = 2.3% = 2.3% + 0.6% (THRUST RATING) = 2.9% = EGT MAXIMUM - EGT RECORD = = 60 C = 60 C + 17 C (TCC TIMER) = 77 C = 77 C - 44 C (ALTITUDE) = 33 C (4000 FEET AND ABOVE) POWER ASSURANCE CHECK EXAMPLE #6 20K Page 49
61 POWER ASSURANCE CHECK EXAMPLE #7 Engine Conditions CFM56-3-B1 20K Pounds Thrust Ambient Temperature (OAT) = 90 F (32 C) Use MPA Fan Speed (for this example 85% N 1 ) Procedure From the MPA Test Table (85% N 1 Fan Speed): - OAT -N 1 target - For 20K pounds thrust, EGT maximum - For CFM56-3-B1 engines, maximum 20K Page 50
62 OAT = 90 F N 1 TARGET = 87.3% FOR 20K POUNDS THRUST, EGT MAXIMUM = 848 C FOR CFM56-3-B1 ENGINES, MAXIMUM = 98.6% POWER ASSURANCE CHECK EXAMPLE #7 20K Page 51
63 POWER ASSURANCE CHECK EXAMPLE #7 Procedure Set N 1 target, after the engine operation is stable for four minutes and record N 1, and EGT. 20K Page 52
64 N 1 = 87.0% = 95.5% EGT = 780 C POWER ASSURANCE CHECK EXAMPLE #7 20K Page 53
65 POWER ASSURANCE CHECK EXAMPLE #7 Procedure Adjust the recorded parameters to the N 1 target: Use the N 1 difference: (N 1 target - N 1 record) For each 0.1% N 1 positive difference (N 1 target > N 1 record) adjust as follows: - add 1.0 C to the EGT record. - add 0.045% to the record. For each 0.1% N 1 negative difference (N 1 target < N 1 record) adjust as follows: - subtract 1.0 C to the EGT record. - subtract 0.045% to the record. 20K Page 54
66 N 1 TARGET - N 1 RECORD = DIFFERENCE = = 0.3% ADJUSTMENT = RECORDED + (0.3/0.1) (0.045) = (3 X.0045) = = 95.6% EGT ADJUSTMENT = EGT RECORDED + (0.3/0.1) (1) = (3 X 1) = = 783 C. POWER ASSURANCE CHECK EXAMPLE #7 20K Page 55
67 POWER ASSURANCE CHECK EXAMPLE #7 Procedure EGT adjustment for the HPTCC timer: - The timer is not available, no adjustment is necessary. EGT adjustment for the altitude: - There is an altitude effect for this thrust rating. - The MPA tables are for sea level. - If the route structure of the airplane includes an airport at 4,000 feet and above, decrease the EGT margin by 44 C. adjustment for the thrust rating: - No adjustment is necessary at this thrust rating. Compare the adjusted parameters to the determined limits. Record the margin and the EGT margin. 20K Page 56
68 MAXIMUM = 98.6% EGT MAXIMUM = 848 C MARGIN EGT MARGIN = MAXIMUM - ADJUSTMENT = = 3.0% = EGT MAXIMUM - EGT RECORD = = 65 C = 65 C - 44 C (ALTITUDE) = 21 C (4000 FEET AND ABOVE) POWER ASSURANCE CHECK EXAMPLE #7 20K Page 57
69 POWER ASSURANCE CHECK EXAMPLE #8 Engine Conditions CFM56-3-B1 18.5K Pounds Thrust Ambient Temperature (OAT) = 90 F (32 C) Use MPA Fan Speed (for this example 85% N 1 ) Procedure From the MPA Test Table (85% N 1 Fan Speed): - OAT -N 1 target - For 18.5K pounds thrust, EGT maximum - For CFM56-3-B1 engines, maximum 18.5K Page 58
70 OAT = 90 F N 1 TARGET = 87.3% FOR 18.5K POUNDS THRUST, EGT MAXIMUM = 874 C FOR CFM56-3-B1 ENGINES, MAXIMUM = 98.6% POWER ASSURANCE CHECK EXAMPLE #8 18.5K Page 59
71 POWER ASSURANCE CHECK EXAMPLE #8 Procedure Set N 1 target, after the engine operation is stable for four minutes and record N 1, and EGT. 18.5K Page 60
72 N 1 = 87.0% = 95.5% EGT = 780 C POWER ASSURANCE CHECK EXAMPLE #8 18.5K Page 61
73 POWER ASSURANCE CHECK EXAMPLE #8 Procedure Adjust the recorded parameters to the N 1 target: Use the N 1 difference: (N 1 target - N 1 record) For each 0.1% N 1 positive difference (N 1 target > N 1 record) adjust as follows: - add 1.0 C to the EGT record. - add 0.045% to the record. For each 0.1% N 1 negative difference (N 1 target < N 1 record) adjust as follows: - subtract 1.0 C to the EGT record. - subtract 0.045% to the record. 18.5K Page 62
74 N 1 TARGET - N 1 RECORD = DIFFERENCE = = 0.3% ADJUSTMENT = RECORDED + (0.3/0.1) (0.045) = (3 X.0045) = = 95.6% EGT ADJUSTMENT = EGT RECORDED + (0.3/0.1) (1) = (3 X 1) = = 783 C. POWER ASSURANCE CHECK EXAMPLE #8 18.5K Page 63
75 POWER ASSURANCE CHECK EXAMPLE #8 Procedure EGT adjustment for the HPTCC timer: - The timer is not available, no adjustment is necessary. EGT adjustment for the altitude: - There is an altitude effect for this thrust rating. - The MPA tables are for sea level. - If the route structure of the airplane includes an airport at 4,000 feet and above, decrease the EGT margin by 44 C. adjustment for the thrust rating: - Increase the margin by 0.7%. Compare the adjusted parameters to the determined limits. Record the margin and the EGT margin. 18.5K Page 64
76 MAXIMUM = 98.6% EGT MAXIMUM = 874 C MARGIN EGT MARGIN = MAXIMUM - ADJUSTMENT = = 3.0% = 3.0% + 0.7% (THRUST RATING) = 3.7% = EGT MAXIMUM - EGT RECORD = = 91 C = 91 C - 44 C (ALTITUDE) = 47 C (4000 FEET AND ABOVE) POWER ASSURANCE CHECK EXAMPLE #8 18.5K Page 65
77 THIS PAGE INTENTIONALLY LEFT BLANK 18.5K Page 66
78 TRIM TABLE EXAMPLES ALL Page 1
79 TRIM TABLE USAGE Description The CFM56-3 trim tables provide the following information: - Low Idle (% ) - High Idle (% ) - Part Power PMC OFF (% ) - Part Power PMC ON (%N 1 ) - Static Take Off PMC ON/OFF (%N 1 ) - Accel Check Target (%N 1 ) ALL Page 2
80 CFM56-3 TRIM TABLE ALL Page 3
81 TRIM TABLE USAGE Description The Boeing /400/500 maintenance manual has 10 different trim table configurations. To determine which trim table configuration to use the following information should be obtained: - Engine model - Engine thrust rating - PMC/MEC part numbers - Incorporation of SB With this information it can then be determined which trim table configuration is required by comparing the above data with the effectivity block. ALL Page 4
82 CFM56-3 TRIM TABLE BLOCK ALL Page 5
83 TRIM TABLE USAGE Description Before using the trim tables record the following: - Ambient temperature (OAT) - Barometric pressure Do not use the flight deck temperature indicator as ambient temperature (OAT). Use a thermometer in the shade of the nose wheel well to obtain the required temperature. To determine local barometric pressure convert the altimeter setting from the airport tower using the appropriate maintenance manual chart. See example below. ALL Page 6
84 EXAMPLE: ALTIMETER SETTING FROM TOWER IS IN. HG FIELD ELEVATION IS 2000 FT LOCAL BAROMETRIC PRESSURE IS IN. HG ALTIMETER SETTING CONVERSION TO LOCAL BAROMETRIC PRESSURE ALL Page 7
85 THIS PAGE INTENTIONALLY LEFT BLANK ALL Page 8
86 SYSTEMS REVIEW - PMC/MEC EXERCISE ALL Page 1
87 MEC REVIEW EXERCISE General Following the instructors guidance have your team complete the MEC System Exercise. ALL Page 2
88 MEC SYSTEM EXERCISE ALL Page 3
89 PMC REVIEW EXERCISE General Following the instructors guidance have your team complete the PMC System Exercise. ALL Page 4
90 PMC SYSTEM EXERCISE ALL Page 5
91 THIS PAGE INTENTIONALLY LEFT BLANK ALL Page 6
92 DIAGNOSTIC TOOLS - GROUND RUN EXERCISE ALL Page 1
93 GROUND RUNS - EXAMPLE 1 Pilot Report "Two-knob throttle stagger, No. 1 throttle leading." (This is a CFM56-3C engine, operated at 22,000 lbs. thrust.) Ground Run Data From the pilot report, there is no indication of whether the stagger occurs during one phase of flight, or all phases of flight. Therefore, we choose to run an idle check (for speed differences at idle) and a part power trim check. If the N 1 K/ K can be assessed at the part power stop, an MPA run will not be run since high EGT is not an issue. Observations _ ALL _ Findings Page 2
94 AMBIENT CONDITIONS: TEMPERATURE: 22 C PRESSURE: 29.0" Hg IDLE DATA: ENGINE NO. 1 ENGINE NO. 2 N 1 : : EGT: FUEL FLOW (W f ): TARGET (FROM TRIM TABLE): 61.7 (+3/-1%) PART POWER TRIM DATA: PMC OFF PMC ON ENGINE NO. 1 ENGINE NO. 2 ENGINE NO. 1 ENGINE NO. 2 N 1 : N 1 : : : EGT: - - EGT: - - FUEL FLOW (W f ) : - - FUEL FLOW (W f ): - - TARGET (FROM TRIM TABLE): 92.8 (±.5) N 1 TARGET (FROM TRIM TABLE): 74.8 (±.1.5) ALL EXAMPLE NO. 1 DATA Page 3
95 GROUND RUNS - EXAMPLE 2 Pilot Report "No. 2 EGT hit 936 C for three seconds on T/O. N 1 exceeded T/O target by 2.5%. Throttle retarded. Throttle stagger during flight, No. 1 leading." (This is a CFM56-3B-2 engine.) Ground Run Data Since the problem does not seem to be related to idle speed, or low speed engine health, it is not necessary to perform/record the low idle data. Because there is a question regarding the T/O EGT health of the engine, it is decided that an MPA check is needed - which can also be used to assess N 1 K/ K for VSV/VBV system anomalies. A part power trim check is also deemed necessary, as it will isolate whether a problem in the MEC or PMC systems is causing the high EGT (via improper N 1 or scheduling). Observations: Findings: _ ALL Page 4
96 AMBIENT CONDITIONS: TEMPERATURE: 24 C PRESSURE: 29.5" Hg PART POWER TRIM DATA: PMC OFF PMC ON ENGINE NO. 1 ENGINE NO. 2 ENGINE NO. 1 ENGINE NO. 2_ N 1 : N 1 : : : EGT: - - EGT: - - FUEL FLOW (W f ): - - FUEL FLOW (W f ): - - TARGET (FROM TRIM TABLE): 93.0 (±.5) N 1 TARGET (FROM TRIM TABLE): 74.8 (±.1.5) MPA DATA: ENGINE NO. 1 ENGINE NO. 2 N 1 : : EGT: FUEL FLOW (W f ) : - - PMC ON/OFF: ON ON MPA TARGET: MAX EGT: (FROM MM TABLE) MAX : (FROM MM TABLE) 777 C 96.8% ALL EXAMPLE NO. 2 DATA Page 5
97 GROUND RUNS - EXAMPLE 3 Pilot Report "No. 1 engine very slow to start - start aborted. Next start successful, but slow. No. 1 engine very slow on T/O throttle set from idle. Throttle stagger, No. 1 forward." (This is a CFM56-3B2 engine). Ground Run Data The No. 1 engine has about 1,000 cycles since previous shop visit, with a few previous reports of slow acceleration, but no reports of high T/O EGT. Because of the write-ups for slow start/acceleration, a low idle check is scheduled. To check the MEC/PMC scheduling systems, a part power trim run is planned, and an MPA is performed to assess N 1 K/ K and T/O EGT health. Additionally, an acceleration check from low idle to 40% N 1 is planned to assess how slow/fast the engines are accelerating. Observations: Findings: _ ALL Page 6
98 AMBIENT CONDITIONS: TEMPERATURE: 8 C PRESSURE: 28.5" Hg IDLE DATA: ENGINE NO. 1 ENGINE NO. 2 N 1 : : EGT: FUEL FLOW (W f ): TARGET (FROM TRIM TABLE): 60.3 (+3/-1%) (NOTE: MAINTENANCE REPORTED NO. 1 START TIME WAS TWO MINUTES, WHILE NO. 2 START TIME WAS 75 SECONDS. BOTH ENGINES HAD BEEN SHUT DOWN FOR FOUR HOURS) PART POWER TRIM DATA: PMC OFF PMC ON ENGINE NO. 1 ENGINE NO. 2 ENGINE NO. 1 ENGINE NO.2 N 1 : N 1 : : : EGT: - - EGT: - - FUEL FLOW (W f ): - - FUEL FLOW (W f ): - - TARGET (FROM TRIM TABLE): 90.6 (±.5) N 1 TARGET (FROM TRIM TABLE): 73.3 (±1.5) MPA DATA: ENGINE NO. 1 ENGINE NO. 2 N 1 : : EGT: FUEL FLOW (W f ): - - PMC ON/OFF: ON ON MPA TARGET: MAXIMUM EGT: (FROM MM TABLE) 725 C MAXIMUM : (FROM MM TABLE) 94.4% ACCELERATION TIMES FROM IDLE TO 40% N 1 : NO. 1 ENGINE 13.2 SECONDS NO. 2 ENGINE 8.8 SECONDS ALL EXAMPLE NO. 3 DATA Page 7
99 GROUND RUNS - EXAMPLE 4 Pilot Report "Throttle stagger in cruise, No. 1 throttle lagging. No. 1 has higher RPM on descent." (This is a CFM56-3C1 engine operated at 23.5K thrust ). Ground Run Data Because of the reference to descent idle, a high idle speed check is performed, as well as low idle (to see if both idles are affected). A part power trim run will identify whether the MEC and PMC systems are scheduling properly. If any of the part power trim run data shows matched N 1 's or matched 's, then an N 1 K/ K assessment can be made at part power. If matched speeds are not available, an MPA run can be made to assess N 1 K/ K. Observations: ALL Findings: Page 8
100 AMBIENT CONDITIONS: TEMPERATURE: 34 C PRESSURE: 29.0" Hg LOW IDLE DATA: HIGH IDLE DATA: ENGINE NO. 1 ENGINE NO. 2 ENGINE NO. 1 ENGINE NO. 2 N 1 : N 1 : : : EGT: - - EGT: - - FUEL FLOW (W f ): - - FUEL FLOW (W f ): - - TARGET (FROM TRIM TABLE): 63.0 (+3/-1%) TARGET (FROM TRIM TABLE): 73.7 (±.7%) PART POWER TRIM DATA: PMC OFF PMC ON ENGINE NO. 1 ENGINE NO. 2 ENGINE NO. 1 ENGINE NO.2 N 1 : N 1 : : : EGT: - - EGT: - - FUEL FLOW (W f ): - - FUEL FLOW (W f ): - - TARGET (FROM TRIM TABLE): 94.5 (±.5) N 1 TARGET (FROM TRIM TABLE): 76.4 (±.1.5) ALL EXAMPLE NO. 4 DATA Page 9
101 THIS PAGE INTENTIONALLY LEFT BLANK ALL Page 10
COMPONENT IDENTIFICATION
This CFMI publication is for Training Purpose Only. The information is accurate at the time of compilation; however, no update service will be furnished to maintain accuracy. For authorized maintenance
More informationCFM REGULATION THE POWER OF FLIGHT
CFM56-3 3 REGULATION 1 CFM56-3 2 Speed Governing System Fuel Limiting System VBV VSV N1 Vs P Idling System HPTCCV N1 Vs Z N1 Vs T Main Tasks Additional Tasks Corrections MEC PMC CFM 56-3 ENGINE OPERATIONAL
More informationTCDS NUMBER E37NE. REVISION: 13* DATE: May 1, 2014 CFM INTERNATIONAL, S.A. MODELS:
TCDS NUMBER E37NE U.S. DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION TYPE CERTIFICATE DATA SHEET E37NE REVISION: 13* DATE: May 1, 2014 CFM INTERNATIONAL, S.A. MODELS: CFM56-5B1 CFM56-5B1/P
More informationTYPE-CERTIFICATE DATA SHEET
Issue: 02 & LEAP-1C series engines Date: 11 March 2016 TYPE-CERTIFICATE DATA SHEET No. E.110 for Engine & LEAP-1C series engines Type Certificate Holder SA SA 2, boulevard du Général Martial Valin 75015
More informationTYPE CERTIFICATE DATA SHEET
TYPE CERTIFICATE DATA SHEET For Models: No. IM.E.102 for Engine GEnx Series Engines Type Certificate Holder GE Aviation One Neumann Way Cincinnati Ohio 45215 United States of America GEnx 1B GEnx 2B GEnx
More informationTCDS NUMBER E00078NE U.S. DEPARTMENT OF TRANSPORTATION REVISION: 3 DATE: April 12, 2011
TCDS NUMBER E00078NE U.S. DEPARTMENT OF TRANSPORTATION REVISION: 3 DATE: April 12, 2011 FEDERAL AVIATION ADMINISTRATION GENERAL ELECTRIC COMPANY MODELS: TYPE CERTIFICATE DATA SHEET E00078NE GEnx-1B54 GEnx-1B58
More informationTYPE-CERTIFICATE DATA SHEET
TYPE-CERTIFICATE DATA SHEET No. E.003 for Type Certificate Holder CFM International SA 2, boulevard du Général Martial Valin F-75724 Paris Cedex 15 France For Models: CFM56-5B SAC CFM56-5B DAC CFM56-5C
More informationTYPE-CERTIFICATE DATA SHEET
TYPE-CERTIFICATE DATA SHEET For Models: No. IM.E.102 for Engine GEnx Series Engines Type Certificate Holder GE Aviation One Neumann Way Cincinnati - Ohio 45215 United States of America GEnx-1B GEnx-2B
More informationEuropean Aviation Safety Agency
European Aviation Safety Agency EASA TYPE CERTIFICATE DATA SHEET Number: IM.E.021 Issue: 05 Date: 03 January 2013 Type: General Electric Company CF34-10E Series Engines Variants CF34-10E2A1 CF34-10E5 CF34-10E5A1
More informationEuropean Aviation Safety Agency
European Aviation Safety Agency EASA TYPE CERTIFICATE DATA SHEET Number : IM.E.026 Issue : 03 Date : 04 January 2013 Type : Engine Alliance LLC GP7200 series engines Variants: GP7270 GP7277 List of Effective
More informationTYPE CERTIFICATE DATA SHEET
TYPE CERTIFICATE DATA SHEET No. IM.E.096 for PW800 Series Engines Type Certificate Holder 1000 Marie Victorin Longueuil, Quebec J4G1A1 Canada For : TE.CERT.00052 001 European Aviation Safety Agency, 2016.
More informationTYPE-CERTIFICATE DATA SHEET
TYPE-CERTIFICATE DATA SHEET EASA.E.042 for RB211 Trent 700 series engines Type Certificate Holder 62 Buckingham Gate Westminster London SW1E 6AT United Kingdom For Models: RB211 Trent 768-60 RB211 Trent
More informationTYPE-CERTIFICATE DATA SHEET
TYPE-CERTIFICATE DATA SHEET No. IM.E.054 for Engine GE Honda Aero Engines Series Engine Type Certificate Holder 9050 Centre Pointe Dr Suite 200 West Chester, OH 45069 Unites States of America For s: TE.CERT.00052-001
More informationGENERAL The Honeywell model TFE731-40AR turbofan engine is a lightweight, two-spool, geared-stage, front-fan, jet engine.
ENGINE GENERAL The Honeywell model TFE731-40AR turbofan engine is a lightweight, two-spool, geared-stage, front-fan, jet engine. The cross section of the engine is shown in Figure 7-71-1, page VII-71-3.
More informationAn agency of the European Union
TYPE-CERTIFICATE DATA SHEET No. E.115 for Engine LEAP-1B series engines Type Certificate Holder SA SA 2, boulevard du Général Martial Valin 75015 Paris France For Models: LEAP-1B21 LEAP-1B23 LEAP-1B25
More informationPremier Aircraft LLC. Differences Manual
Premier Aircraft LLC Differences Manual UPGRADE DIFFERENCES Page 2 NOTICE This document is intended to provide an overview of the modifications to Falcon 50 airplanes when Premier Aircraft LLC STC ST01951LA
More informationTYPE-CERTIFICATE DATA SHEET
TYPE-CERTIFICATE DATA SHEET No. IM.E.093 for PW1100G-JM Series Engines Type Certificate Holder 400 Main Street East Hartford, CT 06118 United States of America For Models: PW1133G-JM PW1133GA-JM PW1130G-JM
More informationEuropean Aviation Safety Agency
European Aviation Safety Agency EASA TYPE-CERTIFICATE DATA SHEET Number : E.036 Issue : 04 Date : 10 September 2013 Type : Rolls-Royce plc Trent 1000 series engines Models Trent 1000-A Trent 1000-A2 Trent
More informationTYPE-CERTIFICATE DATA SHEET
TYPE-CERTIFICATE DATA SHEET EASA.E.036 For Models: for Trent 1000 series engines Certificate Holder Rolls-Royce plc 62 Buckingham Gate London SW1E 6AT United Kingdom Trent 1000-A Trent 1000-A2 Trent 1000-AE3
More informationTYPE-CERTIFICATE DATA SHEET
TYPE-CERTIFICATE DATA SHEET No. EASA E.047 for RB211 Trent 800 series engines Type Certificate Holder 62 Buckingham Gate Westminster London SW1E 6AT United Kingdom For Models: RB211 Trent 895-17 RB211
More informationTYPE-CERTIFICATE DATA SHEET
TYPE-CERTIFICATE DATA SHEET EASA.E.060 for RB211 Trent 500 Series Engines Type Certificate Holder 62 Buckingham Gate Westminster London SW1E 6AT United Kingdom For Models: RB211 Trent 553-61 RB211 Trent
More informationV2527E-A5 ENGINE MINI-PACK
V2527E-A5 ENGINE MINI-PACK Engine Serial Number: Total Time / Total Cycles: V10136 47,579:58 / 23,093 Time/Cycles Since Last 5,994 / 11,562 Shop Visit LHT 2012 Time/Cycles Since Last 5,994 / 11,562 Performance
More informationTHOMSON AIRWAYS LIMITED DISCREPANCY SHEET
IPC REF FIG ITEM DESCRIPTION FROM 72.35.01 01 085/220 ROTATING FAIRINGS 72.31.11 01 280 LP BLADES (22 OFF) 73.11.07 01 645/725 MAIN FUEL INLET TUBE 29.11.03 02 100 HYD. SUPPLY,RIGID TUBE 29.11.03 02 200
More informationTYPE-CERTIFICATE DATA SHEET
TYPE-CERTIFICATE DATA SHEET No. IM.E.016 issue 10 for FJ44/FJ33 Series Engines Certificate Holder Williams International Co. Walled Lake Michigan 48390-0200 USA For Models: FJ44-1A FJ44-1AP FJ44-2A FJ44-2C
More informationDASSAULT AVIATION Proprietary Data
FALCON 7X 02-70-05 CODDE 1 PAGE 1 / 6 GENERAL ACRONYMS LIST ACOC AGB APU A/T ATSV BOV CAS CB CL CMC CR DC DCU ECS EEC FADEC FBW FCU FF FOHE FSOV HP HPC HPT IGV ITT LP LPC LPT LRU MV N1 N2 PDU PLA PMA PMU
More informationDEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION TYPE CERTIFICATE DATA SHEET NO. 1E8
DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION 1E8 Revision 18 PRATT & WHITNEY AIRCRAFT TURBO WASP JT3D-1 JT3D-3 JT3D-1A JT3D-3B JT3D-1-MC6 JT3D-3C JT3D-1A-MC6 JT3D-7 JT3D-1-MC7 JT3D-7A JT3D-1A-MC7
More informationEuropean Aviation Safety Agency
European Aviation Safety Agency EASA TYPE-CERTIFICATE DATA SHEET Number : IM.E.016 Issue : 07 Date : 21 May 2014 Type : Williams International Co. FJ44 Series Engines s FJ44-1A FJ44-1AP FJ44-2A FJ44-2C
More informationENGINE GROUND RUNNING
B737 600/700/800/900 (CFM 56) ENGINE GROUND RUNNING Guide and Reference Sheets This publication is for TRAINING PURPOSES ONLY. This information is accurate at the time of completion. No update service
More informationChromalloy. Borescope and Test Report. Prepared for. Triumph Air Repair A Triumph Group Company
A Triumph Group Company Borescope and Test Report Prepared for Chromalloy Customer P.O.#: S2669 A.P.U. Model #: GTCP331-200ER A.P.U. Serial #: P-2796 A.P.U. Part #: 3800298-1 Triumph SRO #: S000013678
More informationTYPE-CERTIFICATE DATA SHEET
C28 series TYPE-CERTIFICATE DATA SHEET No. IM.E.109 for C28 series engines (see Note 1) Type Certificate Holder Rolls-Royce Corporation 450 South Meridian Street Indianapolis, Indiana 46225-1103 USA For
More informationMTU Maintenance Dallas, Inc. Integrated Management System. MM 03D-03 Capability List Manual
Chapter 0 Page 2 of 15 Revision: Initial Date: 01NOV2012 0.1 Table of Contents 0 Title Page... 1 0.1 Table of Contents... 2 0.2 List of Effective Pages... 3 0.3 Record of Revision... 4 0.4 Record of Temporary
More informationAn agency of the European Union
TYPE-CERTIFICATE DATA SHEET No. E.110 for Engine LEAP-1A & LEAP-1C series engines Type Certificate Holder SA SA 2, boulevard du Général Martial Valin 75015 Paris France For Models: LEAP-1A23 LEAP-1A24
More informationSystems of Commercial Turbofan Engines
Systems of Commercial Turbofan Engines Andreas Linke-Diesinger Systems of Commercial Turbofan Engines An Introduction to Systems Functions 123 Andreas Linke-Diesinger Lufthansa Technik AG Propulsion Systems
More informationEuropean Aviation Safety Agency
European Aviation Safety Agency EASA TYPE-CERTIFICATE DATA SHEET Number : IM.E.020 Issue : 1 Date : 08 June 2005 Type : Pratt and Whitney PW6000 series engines Variants PW6122A PW6124A List of effective
More informationDEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION. TYPE CERTIFICATE DATA SHEET No. A50NM
DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION A50NM Dassault Aviation Falcon 2000 December 19, 1995 TYPE CERTIFICATE DATA SHEET No. A50NM This data sheet which is part of Type Certificate
More informationLiberty Aerospace, Inc. Section 1 SECTION 1 GENERAL TABLE OF CONTENTS
Liberty Aerospace, Inc. Section 1 SECTION 1 TABLE OF CONTENTS Introduction... 1-3 Airplane Three Views... 1-4 Descriptive Data... 1-5 Engine... 1-5 Propeller... 1-5 Fuel... 1-5 Oil... 1-5 Maximum Certificated
More informationDEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION TYPE CERTIFICATE DATA SHEET NO. A33EU
DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION A33EU Revision 2 DASSAULT-BREGUET Falcon 10 September 3, 1987 TYPE CERTIFICATE DATA SHEET NO. A33EU This data sheet which is a part of Type
More informationEngine Finance Rountable Managing an engine. Stephane Garson, General Manager Marketing. 1 st May 2008, New York
Engine Finance Rountable Managing an engine Stephane Garson, General Manager Marketing 1 st May 2008, New York Two Strong Aerospace Leaders Behind CFM CFM International is a Joint Company of Snecma & General
More informationDEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION
DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION E4WE Revision 34 HONEYWELL (AlliedSignal, Garrett, AiResearch) TPE331-3 TPE331-8 TPE331-10N TPE331-11U TPE331-3U TPE331-8A TPE331-10P TPE331-11UA
More informationTYPE CERTIFICATE DATA SHEET
TYPE CERTIFICATE DATA SHEET No. EASA E.076 for Engine Series Type Certificate Holder 10 12, rue Didier Daurat 18021 Bourges Cedex France For Models: TE.CERT.00052 001 European Aviation Safety Agency, 2016.
More informationCanadair Regional Jet 100/200 - Auxiliary Power Unit
1. INTRODUCTION The auxiliary power unit (APU) is installed within a fireproof titanium enclosure in the aft equipment compartment. The APU is a fully automated gas turbine power plant which drives an
More informationTYPE-CERTIFICATE DATA SHEET
TYPE-CERTIFICATE DATA SHEET No. E.062 for Type Certificate Holder Rolls-Royce plc 62 Buckingham Gate London SW1E 6AT United Kingdom For Models: RB211-22B-02, RB211-524-02, RB211-524B-02, RB211-524B-B-02,
More informationLMS100 Gas Turbine System
GE Energy LMS100 Gas Turbine System A flexible growth platform to meet changing energy needs. The LMS100 game changing technology from frame and aero gas turbines LMS100 CFM TECH56 CAPPs Combustor LM6000
More informationTYPE-CERTIFICATE DATA SHEET
TYPE-CERTIFICATE DATA SHEET No. IM.E.053 for CF34-8 series engines Certificate Holder General Electric Aircraft Engines GE Aviation 1000 Western Avenue Lynn, Massachusetts 01910 USA For Models: CF34-8C1
More informationTYPE-CERTIFICATE DATA SHEET
TYPE-CERTIFICATE DATA SHEET No. IM.E.044 for AE 3007 Series Type Certificate Holder Rolls-Royce Corporation P.O. Box 420 Indianapolis, Indiana 46206-0420 United States of America For Models: AE 3007C AE
More informationDEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION TYPE CERTIFICATE DATA SHEET NO. T00009LA
DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION T00009LA Revision 2 Marsh Aviation Company S-2F3AT November 18, 2002 TYPE CERTIFICATE DATA SHEET NO. T00009LA This data sheet, which is a part
More informationTYPE-CERTIFICATE DATA SHEET
TYPE-CERTIFICATE DATA SHEET No. E.073 for Arriel 1 series engines Type Certificate Holder 64510 Bordes France For Models: Arriel 1A Arriel 1A1 Arriel 1A2 Arriel 1B Arriel 1C Arriel 1C1 Arriel 1C2 Arriel
More informationNational Transportation Safety Board Washington, D.C
E PLURIBUS UNUM NATIONAL TRA SAFE T Y N S PORTATION B OAR D National Transportation Safety Board Washington, D.C. 20594 Safety Recommendation Date: April 29, 2004 In reply refer to: A-04-34 and -35 Honorable
More informationATA 49 AUXILIARY POWER UNIT
F900EX EASY 02-49-00 CODDE 1 PAGE 1 / 2 TABLE OF CONTENTS 02-49 02-49-00 TABLE OF CONTENTS 02-49-05 GENERAL Introduction Sources APU location 02-49-10 DESCRIPTION Introduction Description Operating principle
More informationTYPE-CERTIFICATE DATA SHEET
TYPE-CERTIFICATE DATA SHEET EASA.E.034 for SaM146 series engines Type Certificate Holder 2, Boulevard du Général Martial Valin 75015 Paris France For Models: SaM146-1S17 SaM146-1S17C SaM146-1S18 SaM146-1S18C
More informationTYPE-CERTIFICATE DATA SHEET
TYPE-CERTIFICATE DATA SHEET No. E. 103 Issue 2 for ARDIDEN 3 series engines Type Certificate Holder Avenue Joseph Szydlowski 64510 Bordes France For Models: ARDIDEN 3G ARDIDEN 3C TE.CERT.00052-001 European
More informationEuropean Aviation Safety Agency
European Aviation Safety Agency EASA TYPE-CERTIFICATE DATA SHEET Number : IM.E.043 Issue : 02 Date : 07 January 2013 Type : Pratt & Whitney PW4000-100 Series Engines Variants PW4164 PW4164C PW4164C/B PW4164-1D
More informationInstallation of the Altitude-Compensating Fuel Pump on IO-240-B Series Engines.
TELEDYNE CONTINENTAL AIRCRAFT ENGINE SERVICE INFORMATION LETTER Contains Useful Information Pertaining to Your Aircraft Engine Category 5 SIL 04-1 Technical Portions are FAA Approved SUBJECT: PURPOSE:
More informationAIR TRACTOR, INC. OLNEY, TEXAS
TABLE OF CONTENTS LOG OF REVISIONS... 2 DESCRIPTION... 4 SECTION 1 LIMITATIONS... 5 SECTION 2 NORMAL PROCEDURES... 8 SECTION 3 EMERGENCY PROCEDURES... 8 SECTION 4 MANUFACTURER'S SECTION - PERFORMANCE...
More informationDASSAULT AVIATION Proprietary Data
F2000EX EASY 02-70-00 CODDE 1 PAGE 1 / 2 TABLE OF CONTENTS 02-70 02-70-00 TABLE OF CONTENTS 02-70-05 GENERAL Introduction Sources Engine location 02-70-10 DESCRIPTION Introduction Major components Operating
More informationBoeing /-200/-200A Limitations
Boeing 727-100/-200/-200A Limitations The information provided in this document is to be used during simulated flight only and is not intended to be used in real life. Attention VA's - you may post this
More informationCessna Citation Model Stats
Cessna Citation Model Stats Cessna Citation Sovereign - Dimensions Length 63 ft 6 in (19.35 m) Height 20 ft 4 in (6.20 m) Wingspan 72 ft 4 in (22.04 m) Wing Wing Area Wing Sweep Wheelbase Tread 516 sq
More informationTYPE-CERTIFICATE DATA SHEET
SF340A, 340B TYPE-CERTIFICATE DATA SHEET No. EASA.A.068 for SF340A, 340B Type Certificate Holder: Saab AB 581 88 Linköping SWEDEN For Models: SF340A, 340B TE.CERT.00051-001 European Aviation Safety Agency,
More informationEuropean Aviation Safety Agency
European Aviation Safety Agency EASA TYPE-CERTIFICATE DATA SHEET Number : IM.E.052 Issue : 01 Date : 22 June 2011 Type : Rolls-Royce Corporation Model 250 Series II engines Models 250-C18 250-C18A 250-C20
More informationCHAPTER 4 AIRWORTHINESS LIMITATIONS
Section Title CHAPTER 4 AIRWORTHINESS LIMITATIONS 4-10 Airworthiness Limitations..................................... 4.1 4-20 Additional Limitations....................................... 4.3 4-21 Parts
More informationNATIONAL TRANSPORTATION SAFETY BOARD Office of Aviation Safety Washington, D.C POWERPLANT GROUP CHAIRMAN S FACTUAL REPORT
NATIONAL TRANSPORTATION SAFETY BOARD Office of Aviation Safety Washington, D.C. 20594 June 9, 2008 May 11, 2009 POWERPLANT GROUP CHAIRMAN S FACTUAL REPORT NTSB No: DCA-09-MA-021 A. ACCIDENT Location: Denver
More informationTYPE-CERTIFICATE DATA SHEET
TYPE-CERTIFICATE DATA SHEET No. E.018 for BR700-710 engines Certificate Holder Rolls-Royce Deutschland Ltd & Co KG Eschenweg 11, Dahlewitz 15827 Blankenfelde-Mahlow Germany EASA Design Organisation Approval
More informationFull Authority Digital Electronic Control (FADEC)
Eng.10 Engines-Description and Operation General The aircraft is equipped with three GE CF6-80C2 engines or three P&W PW4460 or PW4462 engines. Each engine has dual rotors, a Low Pressure Compressor (LPC)
More informationPreservation. A.1. Preservation for a Period of up to 30 Days. Pág. 2. Memoria ** ON A/C , , TASK
Annex Pág. 2 Memoria A Preservation A.1. Preservation for a Period of up to 30 Days ** ON A/C 001-010, 012-099, 201-299 TASK 72-00-00-600-001 Preservation for a Period of up to 30 Days 1. Reason for the
More informationEuropean Aviation Safety Agency
TCDS No.: EASA.IM.A.212 Learjet M60 Page 1 of 15 European Aviation Safety Agency EASA TYPE CERTIFICATE DATA SHEET No. EASA.IM.A.212 for LEARJET Model 60 Type Certificate Holder: Learjet Inc. One Learjet
More informationAIRWORTHINESS DIRECTIVE
EASA AIRWORTHINESS DIRECTIVE AD No.: 2015-0133 Date: 08 July 2015 Note: This Airworthiness Directive (AD) is issued by EASA, acting in accordance with Regulation (EC) No 216/2008 on behalf of the European
More informationSECTION 6-3 POWER PLANT
SECTION 6-3 SYSTEMS DESCRIPTION Index Page General Description... 6-3-3 Engine Features... 6-3-4 Engine Indication System... 6-3-6 Power Plant Control... 6-3-10 Power Plant System Control... 6-3-12 Power
More informationCFM56-7B POWER PLANT REMOVAL & INSTALLATION
Task No: 737-71-00-00 NG Maint Prog Ref: BAL/BOE/11 Station: A/C Reg: Issue: 5 Date: NOV 2017 A.M.M. Ref: 71-00-02 Check: Aircraft Type CAA App Ref. UK.145.00112 Scheduled / Unscheduled Delete as applicable
More informationBombardier Challenger Auxiliary Power Unit
GENERAL A Honeywell 36 150(CL) constant-speed gas turbine auxiliary power unit (APU) is installed within a fire-resistant compartment in the aft equipment bay. The APU drives a generator, providing AC
More informationCF34 TURBOFAN ENGINE MAINTENANCE MANUAL LIFE LIMITS OF ROTATING ENGINE PARTS
LIFE LIMITS OF ROTATING ENGINE PARTS 1. General. A. The FAA has approved service life-limit cycles (Airworthiness Limitations) for rotating parts installed in the CF34-1A/-3A/-3A2 turbofan engines. B.
More informationINSTRUCTIONS FOR CONTINUED AIRWORTHINESS
INSTRUCTIONS FOR CONTINUED AIRWORTHINESS Beechcraft Super King Air 200/A200/B200 Series Airplanes Equipped With Pratt & Whitney PT6A-52 Engines Installed Per STC SA10824SC Revision A Document Number 200708-30
More informationDO NOT WRITE ON THIS TEST FEB 2013 Elmendorf Aero Club Aircraft Test. Cessna - 182
DO NOT WRITE ON THIS TEST FEB 2013 Elmendorf Aero Club Aircraft Test Cessna - 182 For the following questions, you will need to refer to the Pilots Information Manual for the C-182R. The bonus questions
More informationTYPE-CERTIFICATE DATA SHEET
TYPE-CERTIFICATE DATA SHEET No. E.139 for Engine ASTAZOU II series engines Type Certificate Holder 64510 Bordes France For Models: ASTAZOU II A ASTAZOU II A2 TE.CERT.00052-001 European Aviation Safety
More informationCentral Warning Systems
CIRRUS AIRPLANE MAINTENANCE MANUAL Central Warning Systems CHAPTER 31-50: CENTRAL WARNING SYSTEMS GENERAL 31-50: CENTRAL WARNING SYSTEMS 1. General This section describes the Indicating/Recording Systems
More informationElmendorf Aero Club Aircraft Test
DO NOT WRITE ON THIS TEST JAN 2014 Elmendorf Aero Club Aircraft Test SENECA II For the following questions, you will need to refer to the Pilots Information Manual for the PA-34-200T. USE ANSWER SHEET
More informationCHAPTER 17 LIMITATIONS TABLE OF CONTENTS
CHAPTER 17 LIMITATIONS TABLE OF CONTENTS INTRODUCTION... 5 GENERAL... 5 Flight Crew... 6 Configuration... 6 Optional Equipment... 6 Doors Opened / Removed... 6 Passenger Seats... 6 Cargo... 7 Weight and
More informationXIV.C. Flight Principles Engine Inoperative
XIV.C. Flight Principles Engine Inoperative References: FAA-H-8083-3; POH/AFM Objectives The student should develop knowledge of the elements related to single engine operation. Key Elements Elements Schedule
More informationTYPE CERTIFICATE DATA SHEET 2A10
DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION 2A10 Revision 28 LAVIA ARGENTINA S.A. PA-25 PA-25-235 PA-25-260 TYPE CERTIFICATE DATA SHEET 2A10 July 2, 2013 This data sheet which is a part
More informationCHAPTER 4 ---AUXILIARY POWER UNIT
Table of Contents Vol. 1 04--00--1 CHAPTER 4 ---AUXILIARY POWER UNIT Page TABLE OF CONTENT 04-00 Table of Contents 04--00--1 INTRODUCTION 04-10 Introduction 04--10--1 POWER PLANT 04-20 APU Power Plant
More informationEuropean Aviation Safety Agency
European Aviation Safety Agency EASA TYPE-CERTIFICATE DATA SHEET Number : IM.E.094 Issue : 02 Date : 17 January 2014 Type : Pratt & Whitney Canada series engines Models PT6A-35 PT6A-110 PT6A-112 PT6A-114
More informationDASSAULT AVIATION Proprietary Data
F2000EX EASY 02-49-00 CODDE 1 PAGE 1 / 2 TABLE OF CONTENTS 02-49 02-49-00 TABLE OF CONTENTS 02-49-05 GENERAL Introduction Sources Equipment location 02-49-10 DESCRIPTION Introduction Description Operating
More informationEuropean Aviation Safety Agency
European Aviation Safety Agency EASA TYPE-CERTIFICATE DATA SHEET Number: IM.E.011 Issue: 07 Date: 08 October 2013 Type: Honeywell International Inc. TFE731-20, -40, -50, -60 series engines Models: TFE731-20
More informationTYPE-CERTIFICATE DATA SHEET
TYPE-CERTIFICATE DATA SHEET No. EASA IM.E.038 for s Type Certificate Holder: Pratt and Whitney Canada Corp. 1000 Marie Victorin Longueuil, Québec, J4G 1A1 Canada For Models: PT6A-68 PT6A-68B PT6A-68C PT6A-68D
More informationSECTION 2-14 PNEUMATICS, AIR CONDITIONING AND PRESSURIZATION
AIRPLANE PNEUMATICS SECTION 2-14 PNEUMATICS, TABLE OF CONTENTS Block General... 2-14-05..01 Pneumatic System... 2-14-05..02 Pneumatic System Function Logic... 2-14-05..06 Cross Bleed Valve Operational
More informationAt all times use approved company publications and aircraft manufacturer manuals as sole reference for procedures and data!
Disclaimer These notes have not been approved by any aviation administration, by any airline nor by the aircraft manufacturer to whom it refers. At all times use approved company publications and aircraft
More informationInstructions for Continued Airworthiness
Forced Aeromotive Technologies Instructions for Continued Airworthiness Supercharged IO-550-N Engines Installed On NOTICE This document must be referenced on Block 8 of FAA form 337 and added to the aircraft
More informationIntroduction. I. Introduction Abbreviations Icon Legend Resources
Introduction Management Reference Guide I. Introduction Abbreviations Icon Legend Resources II. Takeoff Performance Computation Limitation Legend Corrections Maximum Takeoff Performance (Full Thrust Method)
More informationElmendorf Aero Club Aircraft Test
DO NOT WRITE ON THIS TEST FEB 2014 Elmendorf Aero Club Aircraft Test Cessna - 185 For the following questions, you will need to refer to the Pilots Information Manual for the C-185F and Graphic Engine
More information17891 Chesterfield Airport Road Chesterfield, MO FAA APPROVED ROTORCRAFT FLIGHT MANUAL SUPPLEMENT TO THE
Supplement No. AFS-BH205-IBF-FMS 17891 Chesterfield Airport Road FAA APPROVED ROTORCRAFT FLIGHT MANUAL SUPPLEMENT TO THE BELL HELICOPTER TEXTRON INC. BELL MODEL 205, UH-1H SERIES AND EAGLE SINGLE (SINGLE
More informationAnswer Key. Page 1 of 10
Name: Answer Key Score: [1] When range and economy of operation are the principal goals, the pilot must ensure that the airplane will be operated at the recommended A. equivalent airspeed. B. specific
More informationCHAPTER 13 INSTRUMENTS
CHAPTER 13 INSTRUMENTS Section Title Page 13.000 Description.............................................. 13.1 13.100 Pitot-Static System......................................... 13.3 13.200 Primary Instruments........................................
More informationVso 61. Vs1 63. Vr 70. Vx 76. Vxse 78. Vy 89. Vyse. 89 (blue line) Vmc. 61 (radial redline) Vsse 76. Va 134) Vno 163
PA34-200T Piper Seneca II Normal procedures V-speeds Knots Vso 6 Vs 63 Vr 70 Vx 76 Vxse 78 Vy 89 Vyse Vmc 89 (blue line) 6 (radial redline) Vsse 76 Va 2-36(@4507lbs 34) Vno 63 Vfe 38 (0*)/2(25*)/07(40*)
More informationNorth American F-86F Sabre USER MANUAL. Virtavia F-86F Sabre DTG Steam Edition Manual Version 1
North American F-86F Sabre USER MANUAL 0 Introduction The F-86 Sabre was a natural replacement for the F-80 Shooting Star. First introduced in 1949 for the United States Air Force, the F-86 featured excellent
More informationa. Lycoming IO-520J 250 HP c. Lycoming O-540-J3C5D 235 HP b. Continental O450T 330 HP d. Lycoming O-360A 180 HP
Three points each question Page 1 of 6 References: Pilot's Operating Handbook for the 1979 Cessna R182 Model; Flying Magazine Article "Cessna 182 Safety Report;" RAFA SOP; and Refueling Instructions found
More informationM1A1 AECU-J1 Diagnostic Connector for use with ABOB and BOB
M1A1 AECU-J1 Diagnostic Connector Signal Description for use with ABOB and BOB Table of Contents 1. Diagnostic Connector Signal Description for use with ABOB and BOB 2. Introduction 3. Pin #1 WFFM (Fuel
More informationThe Aircraft Engine Design Project Fundamentals of Engine Cycles
GE Aviation The Aircraft Engine Design Project Fundamentals of Engine Cycles 1 Spring 2008 Peter Rock Earl Will DeShazer Ken Gould GE Aviation Technical History I-A - First U.S. jet engine (Developed in
More informationDEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION TYPE CERTIFICATE DATA SHEET A18SW. San Antonio, Texas
DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION A18SW Revision 2 Fairchild Aircraft, Inc. SA227-CC SA227-DC (C-26B) November 14, 1996 TYPE CERTIFICATE DATA SHEET A18SW Type Certificate Holder:
More informationDavid s Flight Simulator Operations Manual
DPW Solutions David s Flight Simulator Operations Manual Draft 0.2 David Woolterton Update 10/5/2016 Table of Contents Pre-Start Checklist... 2 Startup Checklist... 3 Before Taxi Checklist... 3 Taxi Checklist...
More informationDEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION TYPE CERTIFICATE DATA SHEET E1IN
DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION E1IN Revision 7 TURBOMECA Artouste 111B Artouste 111B1 Artouste 111D March 20, 2007 TYPE CERTIFICATE DATA SHEET E1IN Engines of models described
More informationCHAPTER ICE AND RAIN PROTECTION SYSTEM
15--00--1 ICE AND RAIN PROTECTION SYSTEM Table of Contents REV 3, May 03/05 CHAPTER 15 --- ICE AND RAIN PROTECTION SYSTEM Page TABLE OF CONTENTS 15-00 Table of Contents 15--00--1 INTRODUCTION 15-10 Introduction
More information