TCDS E6NE

E6NE Revision 17 CFS AEROPRODUCTS INC. ALF502L ALF502L-2 ALF502L-2A ALF502L-2C ALF502L-3 ALF502R-3 ALF502R-3A ALF502R-4 ALF502R-5 ALF502R-6 LF507-1H LF507-1F Date: JANUARY 11, 2023 DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION TYPE CERTIFICATE DATA SHEET NO. E6NE Engines of models described herein conforming with this data sheet (which is part of Type Certificate No. E6NE) and other approved data on file with the Federal Aviation Administration (FAA), meet the minimum standards for use in certificated aircraft in accordance with pertinent aircraft data sheets and applicable portions of the Federal Aviation Regulations, provided they are installed, operated, and maintained as prescribed by the approved manufacturer's manuals and other approved instructions. TYPE CERTIFICATE (TC) HOLDER: CFS Aeroproducts Inc. 2133 Aviation Dr. Suite 201 Upland, CA 91786 USA TYPE CERTIFICATE OWNERSHIP RECORD: Honeywell International Inc. reissued December 15, 1990 111 South 14th Street Phoenix, AZ 85034 Allied Signal reissued December 14, 1999 Tex tron Lycoming issued January 31, 1995 TYPE ALF502R-3 High bypass turbofan, geared fan, single-stage supercharger, axial-centrifugal flow high pressure compressor, reverse flow annular combustor, two-stage high pressure turbine, two-stage low pressure turbine. ALF502R-4 Same as ALF502R-3, but operated at higher thrust. ALF502R-5 Same as ALF502R-4, with improved first-stage and second-stage turbine nozzle assemblies. ALF502R-3A Same as ALF502R-3, with gas producer turbine improvements, but operated at higher thrust. ALF502L High bypass turbofan, geared fan, two-stage supercharger, axial-centrifugal flow high pressure compressor, reverse flow annular combustor, two-stage high pressure turbine, two-stage low pressure turbine. ALF502L-2 Same as ALF502L with fan blade modification for increased altitude performance. ALF502L-3 Same as ALF502L-2 with turbine improvements and automatic power reserve features. ALF502L-2A Same as ALF502L-2 with gas producer turbine improvements and automatic power reserve features. * PAGE 1 2 3 4 5 6 7 8 9 REV. 16 15 16 14 15 15 15 15 16 LEGEND: "- -" INDICATES "SAME AS PRECEDING MODEL" "---" INDICATES "DOES NOT APPLY" NOTICE: SIGNIFICANT CHANGES ARE BLACK-LINED E6NE 2 ALF502L-2C Mechanically identical to ALF502L-2A, but does not include automatic power reserve . ALF502R-6 Similar to ALF502L-2C, but incorporates ALF502R-5 accessory gearbox. LF507-1H Mechanically identical to ALF502R-6, but operated at lower, flat-rated thrust. LF507-1F Mechanically identical to LF-507-1H, but equipped with a single-channel FADEC with hydromechanical backup. RATINGS (SEE NOTE 1) I. MODELS: ALF502R-3 ALF502R-4 ALF502R-5 ALF502R- 3A ALF502L ALF502L- 2 ALF502L- 3 Sea level static thrust, lbs Maximum Continuous Normal Takeoff (5 min) (Note 19) Maximum Takeoff (5 min) (Note 19) 6,300 6,700 6,700 6,550 6,970 6,970 - - - - - - - - - - - - 7,100 7,500 7,500 - - - - - - - - - - - - II. MODELS: ALF502L- 2A ALF502L- 2C ALF502R-6 LF507-1H LF507-1F Sea level static thrust, lbs Maximum Continuous Normal Takeoff (5 min) (Note 19) Maximum Takeoff (5 min) (Note 19) 7,100 7,500 7,500 - - - - - - - - - - - - 6,545 7,000 7,000 - - - - - - 3 COMPONENTS Fuel control Models ALF502R-3/R-4/R-5/R-3A/R-6 / LF507-1H Models ALF502L/L-2/L-3/L-2A/L-2C Model LF507-1F High pressure fuel pump Low pressure fuel pump Ignition system (28-volts DC) Ignitor plugs FUEL (See NOTE 2) OIL (See NOTE 3) PRINCIPAL DIMENSIONS (nominal, inches) Length, nominal, inches Models ALF502R-3/R-4/R-5/R-3A Models ALF502L/L-2/L-3/L-2A/L-2C/R-6/ LF507-1H/1F WEIGHT (dry pounds, maximum) Models ALF502L-2A/L2C/L-3 Models ALF502R-3/R-4/R-5/R-3A Models ALF502L/L-2 Model LF507-1H/ALF502R-6 Model LF507-1F C.G. LOCATION (refer to Engine Installation Instructions) Model ALF502R-3/R-4/R-5/R-3A Models ALF502L/L-2/L-3/L-2A/L-2C/R-6/ LF507-1H/-1F DESCRIPTION Hamilton Sundstrand FC 31 -23 H amilton Sundstrand FC 31-19 Triumph Engine Control Systems EMC-32R F ADEC Hamilton Sundstrand 025028-110 or Triumph Engine Control Systems 774959-1 2-160-790-08 or equivalent I gnition exciter units (Unison or Champion), completely redundant ignition s ystems with additional "continuous-on-demand" ignition compatibility Champion spark plug P/N CH34084 or equivalent A STMD1655 Jet A, Jet A-1, Jet B, MIL-T-5624J Grades JP-4, JP-5, and JP-8 or equivalent MIL-L-7808 and MIL-L-23699 or equivalent LENGTH HEIGHT WIDTH 63.657 55.5 47.8 65.57 54.5 48.6 Weight includes essential engine accessories but excludes starter, hydraulic pump, integrated drive generator and exhaust nozzle. 1,375 1,336 1,375 1,375 1,385 STA B.L. W.L. 105.200 100.000 98.250 104.8 100.29 98.6 E6NE 4 CERTIFICATION BASIS 14 CFR part 33 effective February 1, 1965, as amended by 33-1/-2/-3A/-4 and Special Condition Number 33-66-NE-1. MODEL APPLICATION DATE TYPE CERTIFICATE ISSUED/AMENDED TYPE CERTIFICATE CANCELED ALF502H ALF502R ALF502L ALF502L-2 ALF502R-3 ALF502R-4 ALF502R-5 ALF502L-3 ALF502L-2A ALF502R-3A ALF502L-2C ALF502R-6 LF507-1H LF507-1F 10/09/73 06/03/76 02/01/77 02/11/80 10/15/78 10/06/81 10/06/81 10/15/81 10/14/82 10/14/82 07/20/83 06/22/84 03/25/91 03/25/91 06/11/76 06/11/76 02/29/80 02/29/80 01/16/81 04/14/82 07/02/82 11/30/82 01/07/83 01/07/83 08/24/83 12/12/84 10/15/91 03/20/92 01/16/81 01/16/81 PRODUCTION BASIS None NOTES NOTE 1. Engine ratings are based on calibrated static test stand performance under the following conditions: Static sea level standard condition at 59oF and 29.92 in. Hg. No airbleed, no duct losses, no external power extraction. Engine primary exhaust and fan bypass exhaust system as specified in Figures 3 and 4 of the applicable engine installation instructions. NOTE 2. Engines will operate satisfactorily with fuel contaminated to the levels specified in Paragraph 4.4.1 of the installation instructions for the LF507-1F engine models, and Paragraph 4.4.3 of the installation instructions for the ALF502R, ALF502L and LF507-1H engine models provided the fuel is introduced to the engine through a filter satisfying the requirements of the subject paragraph. NOTE 3. Mixing of these oils (MIL-L-7808 and MIL-L-23699) is prohibited. NOTE 4. Maximum permissible operating speeds for the engine rotors are as follows: Low Pressure Rotor (N1) RPM ALF502 R-3 ALF502 R-4 ALF502 R-5 ALF502 R-3A ALF502 L ALF502 L-2 ALF502 L-3 ALF502 L-2A ALF502 L-2C Maximum takeoff Normal takeoff Maximum continuous 7,300 7,300 7,300 7,350 7,350 7,350 7,374 7,374 7,374 - - - - - - 7,300 7,300 7,300 - - - - - - 7,374 7,184 7,374 - - - - - - - - 7,374 - - Low Pressure Rotor (N1) RPM ALF502 R-6 LF507- 1H LF507- 1F Maximum takeoff Normal takeoff Maximum continuous - - - - - - - - - - - - - - - - - - High Pressure Rotor (N2) RPM ALF502R -3 ALF502R- 4 ALF50 2R-5 ALF50 2R-3A ALF502 L ALF502L -2 ALF502 L-3 ALF502 L-2A ALF502 L-2C Maximum takeoff Normal takeoff Maximum continuous 19,640 19,640 19,380 - - - - - - 19,760 19,760 - - - - - - - - 19,640 19,640 19,280 - - - - - - 19,700 19,420 - - - - - - - - 19,640 19,640 - - E6NE 5 High Pressure Rotor (N2) RPM ALF502R -6 LF507-1H LF507- 1F Maximum takeoff Normal takeoff Maximum continuous 19,760 19,760 19,380 - - - - - - - - - - - - NOTE 5. MAXIMUM PERMISSIBLE TEMPERATURES Starting maximum (*) Maximum takeoff (5 min) Normal takeoff (5 min) Maximum continuous Transient for acceleration Maximum takeoff (**) Normal takeoff (**) GAS TEMPERATURE (DEGREES FAHRENHEIT) AS MEASURED BY 10 THERMOCOUPLES MOUNTED BETWEEN THE THIRD TURBINE NOZZLE VANES ALF502 R-3 ALF502 R-4 ALF502 R-5 ALF502 R-3A ALF502 L ALF502 L-2 ALF502 L-3 ALF502 L-2A ALF502 L-2C 1590 1620 1620 1574 1620 1620 - - 1660 1660 1610 1660 1660 - - - - 1620 1574 - - 1620 - - - - - - - - - - - - 1515 1660 1660 1610 1660 1660 - - - - - - - - - - - - - - 1668 1593 1574 1668 1593 - - - - - - - - - - - - - - 1620 1620 - - 1620 1620 (*) Time limit 10 seconds above 1560oF for ALF502R and LF507-1H and 1460oF for ALF502L series (**) Time limit 15 seconds above takeoff limit GAS TEMPERATURE (DEGREES FAHRENHEIT) AS MEASURED BY 10 THERMOCOUPLES MOUNTED BETWEEN THE THIRD TURBINE NOZZLE VANES ALF502R-6 LF507-1H Starting maximum (*) 1590 - - Maximum takeoff (5 min) 1660 1660 Normal takeoff (5 min) - - - - Maximum continuous 1574 - - Transient for acceleration Maximum takeoff (**) 1660 1660 Normal takeoff (**) - - - - (*) (**) Time limit 10 seconds above 1560oF for ALF502R and LF507-1H and 1460oF for ALF502L series Time limit 15 seconds above takeoff limit EXHAUST GAS TEMPERATURE (DEGREES FAHRENHEIT) AS MEASURED BY 16 THERMOCOUPLE PROBES LF507-1F Starting maximum (*) 1,360 Maximum takeoff (5 min) 1,169 Normal takeoff (5 min) 1,169 Maximum continuous 1,136 Transient for acceleration Maximum takeoff (**) 1,169 Normal takeoff (**) 1,169 (*) For LF507-1F time limit 10 seconds above 1315oF (**) For LF507-1F time limit 15 seconds above takeoff limit NOTE 5. MAXIMUM PERMISSIBLE TEMPERATURES (continued) E6NE 6 OIL TEMPERATURES / MAXIMUM / DEGREES FAHRENHEIT ALF502 R-3 ALF502 R-4 ALF502 R-5 ALF502 R-3A ALF502 L ALF502 L-2 ALF502 L-3 ALF502 L-2A ALF502 L-2C 271** - - - - - - 290* - - - - - - - - * Transient oil temperatures as high as 340oF can be experienced when undergoing a power reduction. Recovery to acceptable oil inlet temperature should occur after two minutes steady-state operation. ** Transient oil temperatures as high as 320oF can be experienced when undergoing a power reduction. Recovery to acceptable oil inlet temperature should occur after two minutes steady-state operation. OIL TEMPERATURES / MAXIMUM / DEGREES FAHRENHEIT ALF502 R-6 LF507- 1H LF507- 1F 271** - - - - * Transient oil temperatures as high as 340oF can be experienced when undergoing a power reduction. Recovery to acceptable oil inlet temperature should occur after two minutes steady-state operation. ** Transient oil temperatures as high as 320oF can be experienced when undergoing a power reduction. Recovery to acceptable oil inlet temperature should occur after two minutes steady-state operation. ACCESSORY TEMPERATURE LIMITS / ALL MODELS Additional accessory temperature data are specified in Table III of the LF507-1H engine model installation instructions, and Table IV of the applicable installation instructions for other ALF502/LF507 engine models. AMBIENT OR SURFACE DEGREES TEMPERATURE FAHRENHEIT Fuel control assembly Ambient 260 Overspeed fuel shut-off valve Ambient 200 Ignition unit Ambient 250 Overspeed control Surface 212 Fuel manifold Surface 390 Interstage bleed actuator Ambient 350 Anti-icing valve Ambient 350 Fan speed sensor Surface 400 Electronic control unit Ambient 185 (*) (*) The electronic control unit (ECU) can operate continuously in an ambient temperature range of minus 65oF to plus 185oF. In addition, the ECU can operate for up to 5 minutes at a maximum transient temperature of 212oF. E6NE 7 NOTE 6. FUEL AND OIL PRESSURE LIMITS / ALL MODELS ALF502 R-3 ALF502 R-4 ALF502 R-5 ALF502 R-3A ALF502 L ALF502 L-2 ALF502 L-3 ALF502 L-2A ALF502 L-2C Fuel Maximum (psig) Minimum (*) 35 - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - (*) True fuel vapor pressure plus 5 psi Oil (psig) Sea level (*) Ground idle 97+10 25 - - - - - - - - (*) At maximum continuous power and above plus 5 psi ALF502 R-6 LF507 1H LF507 1F Fuel Maximum (psig) Minimum (*) - - - - - - - - - - - - (*) True fuel vapor pressure plus 5 psi Oil (psig) Sea level (*) Ground idle - - - - - - - - - - - - (*) At maximum continuous power and above plus 5 psi NOTE 7. ACCESSORY DRIVE PROVISIONS ALF502L, L-2 / L-3 / L-2A / L-2C / R-3 / R-3A/ R-4 / R-5 / R-6 models ALF507-1H / -1F models. Maximum accessory power extraction (shp) is shown in installation instructions paragraph 4.1.2., Figures 12. ACCESSORY DRIVES FOR ALF502R-3 / R-4 / R5- / R-3A / R-6 / LF507-1H / -1F DRIVE TYPE ROTATION FACING ENGINE PAD SPEED Tc Ts To Tst Tmt MAXIMUM OVERHANG MOMENT (lb-in) Starter Special (1) CW 0.8621(2) --- 855 --- 246 --- 200 Hydraulic Pump AND2000-1X1B (MOD) CCW 0.253(2) 300 --- 855 234 590 150 IDG/CSD (3) AS970A-13V (MOD) CW 0.458(2) --- --- 1596 505 1200 (1) Details of pad type and design are available in Table III and in the installation drawings of the applicable engine installation instructions. (2) Speed of the drive – is equal to the constant provided multiplied by the engine high pressure rotor (N2) speed. (3) IDG/CSD pad rating is 96 shp at any engine speed CW = clockwise CCW = counterclockwise Tc = continuous torque rating (lb-in) Ts = static torque rating (lb-in) To = overload torque rating (5 minutes lb-in) Tst = shock torque rating (lb-ft) Tmt = normal maximum torque (20 seconds lb-in) E6NE 8 NOTE 7. (CONTINUED) ACCESSORY DRIVES FOR ALF502L / L-2 / L-3 / L-2A / L-2C DRIVE SPECIFICATION (8) TYPE ROTATION FACING ENGINE PAD GEAR RATIO (6) CONT (1) EMERGENCY IMPACT (5) Starter AND20002-XII-D MODIFIED CCW 0.458 1200 (4) - - 4000 Boost Pump SPECIAL CCW 0.214 70 - - 1000 Power Takeoff AS970A-13V MODIFIED CW 0.458 (9) 1120 (2) 4000 1541 (3) Hydraulic Pump AND20001-X1-B MODIFIED CCW 0.253 (9) 227 (7) 1250 (1) Max permissible continuous torque at any engine speed (lb-in) (2) Max permissible torque for 10 minutes, (in-lb) (3) Max permissible torque for 7 seconds, (in-lb) (4) Max peak torque during starting cycle (5) Max impact torque (in-lb) (6) Relative to N2 speed (7) Maximum permissible torque for 10 minutes (lb-in). Power takeoff pad not to exceed 560 in-lb at this condition. (8) See specification for overhang moment (9) Continuous power extraction capability under all operating conditions is as follows: Power takeoff: 60 shp Hydraulic pump pad: 5 shp (10) See Installation Drawing NOTE 8. For in-flight operation in icing conditions, the minimum permissible N2 rpm is 67%. However, momentary N2 excursions down to 60%, not exceeding 60 seconds duration, are permissible within 300 feet above ground level (AGL) during final approach to landing. NOTE 9. Engine starting torque and speed requirements are shown in Figure 7 of the applicable engine installation instructions. NOTE 10. These engines meet the fire prevention requirements of Special Condition No. 33- 66-NE-1 providing the compartment ventilation design requirements of Paragraph 4.6.2, 4.6.2.1, and 4.6.2.2 of the applicable engine installation instructions are met. NOTE 11. Customer bleed air extraction limits are shown in Paragraph 4.9 of the ALF502L/L-2/L-3/ L-2A/L-2C installation instructions and Paragraph 3.1.1 of the ALF502R-3/R-4/R-5/R-3A/ R-6/LF507-1H/-1F installation instructions. NOTE 12. Fuel venting; emission control is not included on these engines and therefore airframe compliance must be provided in accordance with SFAR-27 (superceded by part 34). NOTE 13. These engines may use approved type fuels separately or mixed in any proportion. Fuel control adjustments are not required when switching fuel types. Fuel additives and concentrations by volume approved for use in fuels for these engines are provided in the applicable engine manual. E6NE 9 NOTE 14. Certain engine parts are life limited. For ALF502R-3/R-4/R-5/R-3A and R-6, these limits are listed in the manufacturer's Service Bulletin No. ALF502-72 -0002. For the ALF502L/L -2/L-3/L-2A and L - 2C, they are listed in Service Bulletin No. ALF502 -72-0004. For model LF507-1H, they are listed in Service Bulletin No. LF507 -1H-72-2. For model LF507- 1F, they are listed in Service Bulletin No. LF507-1F-72-2. NOTE 15. Overhaul and hot end inspection intervals for models ALF502R -3/R-4/R-5/R-3A and R -6 are specified in the manufacturer's Service Bulletin No. ALF502 -72-0001. For models ALF502L/L -2/L- 3/L-2A and L-2C, they are specified in Service Bulletin No. ALF502 -72-0005. For model LF507-1H, they are specified in Service Bulletin LF507 -1H-72-1. For model LF507- 1F, they are specified in Service Bulletin LF507-1F-72-1. These Time Between Inspection/Time Between Overhaul Service Bulletin Nos. ALF502 -72- 0001/LF507-1F-72-1/LF507-1H-72-1 do not apply to FA A approved continuous airworthiness maintenance programs developed in accordance with FAA Maintenance Review Board procedures; e.g. Maintenance Steering Group III Analysis. NOTE 16. Deleted. NOTE 17. The ALF502L, L-2, L-3, L-2A, L-2C, R-3, R- 4, R-5, R- 3A, R-6 and LF507-1H and - 1F models comply with the windmill test requirement of part 33.92, Amendment 9, up to a N1 of 2,000 rpm and a N2 of 3,420 rpm. NOTE 18. ALF502L, L-2, L-3, L-2A, L-2C, R-3, R-4, R-5, R-3A, R-6, and LF507-1H and 1F models comply with the instrument connection requirement of part 33.29, Amendment 5. NOTE 19. A thrust setting limited to 7,800 lbs. (ALF502L -3 and ALF502L -2A) static thrust at sea level, has been established as maximum takeoff thrust rating. A thrust setting limited to 7,500 lbs. (ALF502L-3, ALF502L-2A, and ALF502L -2C) static thrust at sea level, has been established as normal takeoff thrust rating for normal takeoff operation. When the automatic reset mechanism in the fuel control is utilized, operation to the norma l takeoff rating operating limits will insure the maximum takeoff rating operating limits are not exceeded when the reset mechanism is actuated. The time limit at the maximum takeoff rating is five minutes and shall include any time accumulated above the normal takeoff rating. NOTE 20. For the ALF502R -5 and ALF502R-3A: A thrust setting limited to 6,970 lbs. static thrust at sea level flat rated to 71oF with a maximum MGT of 1660 oF has been established as a maximum takeoff thrust rating. A thrust setting limited to 6,970 lbs. static thrust as sea level flat rated to 59 oF with a maximum MGT of 1620 oF has been established as the normal takeoff rating for normal operation of this model. For the LF507-1H: A thrust setting limited to 7,000 pounds static thrust at sea level flat rated to 85 oF with a maximum MGT of 1660oF has been established as the maximum takeoff thrust rating. A thrust setting limited to 7,000 pounds static thrust at sea level flat rated to 74 oF with a maximum MGT of 1620oF has been established as the normal takeoff rating for normal operation of this model. For the LF507-1F: A thrust setting limited to 7,000 pounds static thrust at sea level flat rated to 74 oF with a maximum EGT of 1169 oF has been established as the normal takeoff rating for normal operation of this model. E6NE 10 NOTE 21. The LF507-1F in the manual backup control mode operating configuration is in compliance with the Certification Basis defined herein, when operated in accordance with the instructions contained in the approved manufacturers operating instructions for Part Number 2-003-040-15. ….END…. E6NE