TCDS E26NE

U.S. DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION TYPE CERTIFICATE DATA SHEET E26NE TCDS NUMBER E26NE REVISION: 22 DATE February 9, 2022 PRATT & WHITNEY CANADA CORP. MODELS: PT6A-66 PT6A-67B PT6A-68 PT6A-66A PT6A-67D PT6A-67AG PT6A-67 PT6A-67R PT6A-67T PT6A-67A PT6A-64 PT6A-66D PT6A-67AF PT6A-66B PT6A-67F PT6A-67P PT6A-67RM PT6E-67XP PT6A-68D PT6E-66XT Engines of models described herein conforming with this data sheet (which is part of Type Certificate Number E26NE) and other approved data on file with the Federal Aviation Administration, 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: Pratt & Whitney Canada Corp. 1000 Marie Victorin Longueuil, QC, Canada J4G 1A1 TYPE A free turbine turbo-propeller propulsion engine incorporating a multi-stage compressor driven by a single-stage turbine and a two-stage free turbine driving the propeller shaft through planetary reduction gearing. The PT6A-68 and -68D have an electronic Power Management System with mechanical back up. The PT6E-67XP and PT6E-66XT have an Engine and Propeller Electronic Control System (EPECS) and associated hardware. MODELS PT6A- 66 PT6A- 67 PT6A- 67A PT6A - 67R PT6A- 67RM PT6A- 67T PT6A- 64 PT6A- 66B RATINGS (see NOTE 1) Maximum Continuous at sea level Equivalent shaft horsepower Shaft Horsepower Thrust, pounds Output, RPM (maximum) Gas gen. RPM (maximum) Takeoff (5 min. at sea level) Equivalent shaft horsepower Shaft horsepower Thrust, pounds Output, RPM (maximum) Gas gen., RPM (maximum) Alternate takeoff (5 min. at sea level) Equivalent shaft horsepower Shaft horsepower Thrust, lbs. Output, RPM (maximum) Gas gen. RPM (maximum) Maximum Reverse Shaft horsepower Output, RPM (maximum) 905 1,272 - - 1,294 - - - - 747 1010 850 1,200 - - 1,220 - - - - 700 950 138 181 - - 184 - - - - 119 150 2,000 1,700 - - - - - - - - 2,000 - - 39,000 - - - - - - - - - - - - - - 905 1,272 - - 1,509 - - - - 747 1010 850 1,200 - - 1,424 - - - - 700 950 138 181 - - 212 - - - - 119 150 2,000 1,700 - - 1,700 - - - - 2,000 - - 39,000 - - - - - - - - - - - - - - --- --- --- 1,358 - - --- --- --- --- --- --- 1,281 - - --- --- --- --- --- --- 192 - - --- --- --- --- --- --- 1,700 - - --- --- --- --- --- --- 39,000 - - --- --- --- 800 900 - - - - - - - - 700 800 1,900 1,650 - - - - - - - - 1,900 - - + PAGE 1 2 3 4 5 6 7 REV. 22 22 21 21 22 22 21 PAGE 8 9 10 11 12 13 REV. 22 22 21 21 22 22 ; LEGEND: "- -" INDICATES "SAME AS PRECEDING MODEL" "---" NOT APPLICABLE NOTE: CHANGES, ARE BLACK-LINED IN THE LEFT MARGIN. TCDS E26NE PAGE 2 MODELS (continued) RATINGS (see NOTE 1) Maximum Continuous at sea level Equivalent shaft horsepower Shaft Horsepower Thrust, pounds Output, RPM (maximum) Gas gen. RPM (maximum) Takeoff (5 min. at sea level) Equivalent shaft horsepower Shaft horsepower Thrust, pounds Output, RPM (maximum) Gas gen., RPM (maximum) Maximum Reverse Shaft horsepower Output, RPM (maximum) MODELS (continued) RATINGS (see NOTE 1) Maximum Continuous at sea level Equivalent shaft horsepower Shaft Horsepower Thrust, pounds Output, RPM (maximum) Gas gen. RPM (maximum) Takeoff (5 min. at sea level) Equivalent shaft horsepower Shaft horsepower Thrust, pounds Output, RPM (maximum) Gas gen., RPM (maximum) Maximum Reverse Shaft horsepower Output, RPM (maximum) COMPONENTS/ CONFIGURATION Fuel pump, fuel control unit, ignition system without power source, propeller governor and fuel heater are included as standard equipment as shown in the approved Parts List. The PT6E-67XP and PT6E-66XT models include an Engine and Propeller Electronic Control System (EPECS) and associated hardware. For additional information, refer to Installation Manual. For output drive specifications and C.G. location, refer to Installation Manual. PT6A- 67B PT6A- 67D PT6A- 67AG PT6A- 68 PT6A- 66A PT6A- 66D PT6A- 67AF PT6A- 67F 1,272 1,285 1,294 1,324 905 - - 1294 1796 1,200 1,214 1,220 1,250 850 - - 1220 1700 181 178 184 185 138 137 184 241 1,700 - - - - 2,000 - - - - 1700 - - 39,000 - - - - - - - - - - - - - - 1,272 1,353 1,430 1,324 905 - - 1509 1796 1,200 1,279 1,350 1,250 850 - - 1424 1700 181 186 200 185 138 137 212 241 1,700 1,700 1,700 2,000 - - - - 1700 - - 39,000 - - - - - - - - - - - - - - 900 - - - - --- 800 - - 900 - - 1,650 - - - - --- 1900 - - 1650 - - PT6A- 67P PT6E- 67XP PT6A- 68D PT6E- 66XT 1272 - - 1691 952 1200 - - 1600 895 181 - - 228 143 1700 - - 2000 - - 39,000 - - - - - - 1272 - - 1691 952 1200 - - 1600 895 181 - - 228 143 1700 - - 2000 - - 39,000 - - - - - - 900 - - --- 800 1650 - - --- 1,800 TCDS E26NE PAGE 3 FUEL Fuels conforming to the current P&WC specifications CPW 204 and CPW 46. Refer to the current revision of Service bulletin 14004 for all models except for the PT6A-67AG and PT6A-68. For the PT6A-67AG and PT6A-67F refer to Service Bulletin 14504 and for the PT6A-68, refer to Service Bulletin 18004. For the PT6E-67XP, refer to Maintenance Manual 3076392. For the PT6A-68D, refer to SB 18104. For the PT6E- 66XT, refer to Maintenance Manual 3134822. Refer to the Installation Manuals for further details. LUBRICATING OILS Oils conforming to PWA specification PWA 521 Type II. Refer to the current revision of P&WC Service Bulletin 14001 for acceptable lubrication for all models except the PT6A-68. For the PT6A-68, refer to Service Bulletin 18001. For the PT6E-67XP, refer to Maintenance Manual 3076392. For the PT6A-68D, refer to SB 18101. For the PT6E- 66XT, refer to Maintenance Manual 3134822. PRINCIPAL DIMENSIONS AND WEIGHT PT6A- 66 PT6A- 67 PT6A- 67A PT6A- 67R PT6A- 67RM PT6A- 67T PT6A- 64 PT6A- 66B PT6A- 67B PRINCIPAL DIMENSIONS AT ROOM TEMPERATURE / INCHES / NOMINAL Diameter Length 18.3 69.7 - - 74.2 - - - - - - 75.2 - - - - - - - - - - 69.7 - - - - - - 76.0 WEIGHT / DRY / POUNDS / INCLUDING EXTERNAL ENGINE ACCESSORIES Standard rotation Reverse rotation 469 483 523 --- - - --- 531 --- - - --- - - --- 474 --- 469 483 592 --- Reduction Ratio (Np:Nf) 0.0663:1 0.0568:1 - - - - - - - - 0.0663:1 - - .0568:1 PRINCIPAL DIMENSIONS AND WEIGHT (continued) PT6A- 67D PT6A- 67AG PT6A- 68 PT6A- 66A PT6A- 66D PT6A- 67AF PT6A- 67F PT6A- 67P PT6E- 67XP PRINCIPAL DIMENSIONS AT ROOM TEMPERATURE/ INCHES/ NOMINAL Diameter Length 18.3 74.2 - - 75.2 22.2 71.3 18.3 69.9 - - - - - - 75.2 - - - - - - 76.0 18.9 73.7 WEIGHT/ DRY/ POUNDS/ INCLUDING EXTERNAL ENGINE ACCESSORIES Standard rotation Reverse rotation 533 --- 523 --- 586 --- 474 --- 475 --- 548 --- 590 --- 563 --- 598 --- Reduction Ratio (Np:Nf) 0.0568:1 - - 0.0667:1 0.0663:1 - - 0.0568:1 0.0575:1 0.0568:1 - - PRINCIPAL DIMENSIONS AND WEIGHT (continued) PT6A- 68D PT6E- 66XT PRINCIPAL DIMENSIONS AT ROOM TEMPERATURE/ INCHES/ NOMINAL Diameter Length 22.4 71.7 18.9 67.9 WEIGHT/ DRY/ POUNDS/ INCLUDING EXTERNAL ENGINE ACCESSORIES Standard rotation Reverse rotation 606 --- 533 Reduction Ratio (Np:Nf) .0667:1 .0670:1 TCDS E26NE PAGE 4 CERTIFICATION BASIS MODELS All models except for those listed below. PT6A-68 PT6A-66D, PT6-66B, PT6A- 67F, PT6A-67P, PT6A- 67RM and PT6A-68D PT6E-67XP and PT6E-66XT Airworthiness Standards 14 CFR Part 33 effective February 1, 1965, Amendments 33-1 to 33-10. 14 CFR Part 33 effective February 1, 1965, Amendments 33-1 to 33-14. 14 CFR Part 33 effective February 1, 1965, Amendments 33-1 to 33-20. 14 CFR Part 33 effective February 1, 1965, Amendments 33-1 to 33-33. Emissions Standards 1. All models comply with the applicable requirements of 14 CFR Part 34 effective October 23, 2013, Amendments 34-1 to 34-5A inclusive. a. All models comply with the fuel venting requirements of Subpart B of 14 CFR Part 34, effective October 23, 2013, Amendments 34-1 to 34-5A, inclusive. b. The following models comply with the exhaust emissions smoke requirement of Subpart C of 14 CFR Part 34, effective October 23, 2013, Amendments 34-1 to 34-5A, inclusive: PT6A-67R, PT6A-67RM, PT6A-67T, PT6A-67AG, PT6A-67AF, PT6A-67F and PT6A-68D, MODEL APPLICATION DATE ISSUED/REVISED PT6A-66 MAR 27, 1985 MAR 16, 1987 PT6A-67 MAR 27, 1985 MAR 16, 1987 PT6A-67R AUG 05, 1985 MAR 16, 1987 PT6A-67A JUL 05, 1987 DEC 22, 1987 PT6A-64 DEC 06, 1989 APR 09, 1990 PT6A-67B SEP 12, 1990 MAR 05, 1991 PT6A-67D SEP 12, 1990 MAR 05, 1991 PT6A-67AG MAY 16, 1994 JUNE 23, 1994 PT6A-68 JUNE 11, 1996 JUNE 30, 1997 PT6A-66A NOV 10, 1998 MAR 11, 1999 PT6A-67T NOV 5, 1999 NOV 29, 2000 PT6A-66D MAY 17, 2005 NOV 21, 2005 PT6A-66B APRIL 3, 2006 JAN 29, 2007 PT6A-67AF MAY 17, 2006 JAN 29, 2007 PT6A-67F OCT 5, 2006 AUG 2, 2007 PT6A-67P FEB 9, 2007 NOV 19, 2007 PT6A-67RM MAY 29, 2009 NOV. 4, 2011 PT6E-67XP JAN 31, 2018 OCT 15, 2019 PT6A-68D AUG 28, 2020 MAY 11, 2021 PT6E-66XT OCT 28, 2019 OCT 28, 2021 NOTES NOTE 1. ENGINE RATINGS: The engine ratings are based on dry sea level static ICAO standard atmospheric conditions. No external accessory loads and no air bleed. The quoted ratings are obtained on a test stand with the specified fuel and oil, without intake ducting and utilizing the exhaust port and intake defined in the approved installation manual. TCDS E26NE PAGE 5 NOTE 2. TEMPERATURES MODELS PT6A- 66 PT6A- 67 PT6A- 67A PT6A - 67R PT6A- 67RM PT6A- 67T PT6A- 64 PT6A- 66B Limitations Maximum Continuous Maximum interturbine temp (ITT) Maximum air inlet temp (AIT) for rated power Takeoff (5 mins) Maximum interturbine temp (ITT), Maximum air inlet temp(AIT) for rated power Alternate takeoff (10 min) Maximum interturbine temp (ITT) Maximum air inlet temp (AIT)for rated power Starting (5 secs) Maximum interturbine temp (ITT) 1,526oF - - 1,544oF - - - - - - 1,472oF 1544 oF 135oF 115oF 127oF 119oF - - 92oF 135oF 147 oF 1,526oF 1,544oF 1,562oF 1,571oF - - - - 1,472oF 1562 oF 135oF 124oF 127oF 99oF - - 94oF 135oF 147 oF --- --- --- 1,517oF - - --- --- --- --- --- --- 91oF - - --- --- --- 1,832oF - - - - - - - - - - - - - - MODELS (Continued) PT6A- 67B PT6A- 67D PT6A- 67AG PT6A- 68 PT6A- 66A PT6A- 66D PT6A- 67AF PT6A- 67F Limitations Maximum Continuous Maximum interturbine temp (ITT) Maximum air inlet temp (AIT) for rated power Takeoff (5 mins) Maximum interturbine temp (ITT), Maximum air inlet temp (AIT) for rated power Starting (5 secs) Maximum interturbine temp (ITT) 1,472oF 1436 F 1,472oF 1508oF 1472oF 1544oF - - 1598 F 113oF 115 F 92oF 108oF 122oF 158oF 119 oF 90 F 1,472oF - - - - 1508oF 1472oF 1562oF 1571 oF 1598 F 125oF 118 F 79oF 108oF 122oF 158oF 99 oF 90 F 1,832oF - - - - - - - - - - - - - - MODELS (Continued) PT6A- 67P PT6E- 67XP PT6E- 67XP PT6E- 66XT Limitations Maximum Continuous Maximum interturbine temp (ITT) Maximum air inlet temp (AIT) for rated power Takeoff (5 mins) Maximum interturbine temp (ITT), Maximum air inlet temp (AIT) for rated power Starting (5 secs) Maximum interturbine temp (ITT) 1,544oF - - 1,580oF 1,544oF 122oF - - 88.2oF 149oF 1,562oF - - 1,580oF 1,562oF 111oF - - 88.2oF 149oF 1,832oF - - - - - - TCDS E26NE PAGE 6 NOTE 2. TEMPERATURES (continued) OIL TEMPERATURE LIMITS (degree Fahrenheit) PT6A- 66A PT6A- 66/ 67 PT6A- 67A PT6A- 67R PT6A- 67RM PT6A- 67T PT6A- 64 PT6A- 67B PT6A- 67D Takeoff 32-219 32-230 - - - - - - - - 32-219 32-230 - - Transient (1) 32-230 - - - - - - - - - - - - - - - - Maximum Continuous 32-219 32-230 - - - - - - - - 32-219 32-230 - - Minimum (-40) - - - - - - - - - - - - - - - - PT6A- 67AG PT6A- 68 PT6A- 66D PT6A- 66B PT6A- 67AF PT6A- 67F PT6A- 67P PT6E- 67XP Takeoff (2) Transient (1) Maximum Continuous Minimum 32-230 32-230 32-230 (-40) 50-230 - - 50-230 - - 32-219 - - 32-219 - - 32-230 - - 32-230 - - - - - - - - - - 50-230 - - 50-230 - - 32-230 - - 32-230 - - 50 -230 - - 50 -221 - - PT6A- 68D PT6E- 66XT Takeoff 50-221 32-219 Transient (1) 32-221 32-230 Maximum Continuous 50-221 32.219 Minimum (-40) - - (1) For the PT6A-64, -66A, –66D and PT6E-66XT, the transient time is limited to 10 minutes (2) For the PT6E-67XP and PT6E-66XT when operating the engine without fuel anti-icing additives, the minimum oil temperature at ground idle prior to setting take-off power is 59°F. FUEL TEMPERATURE LIMITS- Fuel temperature limitations are shown in the engine installation manuals. NOTE 3. PRESSURES OIL PRESSURE LIMITS (psig) (1) PT6A- 66 PT6A- 67 PT6A- 67A PT6A- 67R PT6A- 67RM PT6A- 67T PT6A- 64/ 66A PT6A- 67B PT6A- 67D Takeoff 90-135 - - - - - - - - - - 100-135 90-135 - - Maximum Continuous 90-135 - - - - - - - - - - 100-135 90-135 - - Transient 40-200 - - - - - - - - - - - - - - - - Minimum inflight 60 - - - - - - - - - - - - - - - - PT6A- 67AG PT6A- 68 (2) PT6A- 66D PT6A- 66B PT6A- 67AF PT6A- 67F PT6A- 67P PT6E- 67XP Takeoff Maximum Continuous Transient Minimum 90-135 90-135 - - 60 90-120 90-120 40-200 40 100-135 100-135 - - 60 90-135 90-135 - - - - - - - - --- - - - - - - --- - - - - - - --- - - - - - - 40 - 175 - - PT6A- 68D (3) PT6E- 66XT Takeoff Maximum Continuous Transient Minimum 90-125 90-125 70-130 80 100-135 100-135 40-175 60 (1) Gas generator speed 27,000 RPM or above and oil temperature (140-160oF) (2) For the PT6A-68 during aerobatic flight, the allowable steady state oil pressure range is 40-130 psig. At idle power, the minimum allowable transient oil pressure is 15 psig for a maximum of 5 seconds. (3) For expanded oil pressure limits during aerobatic flight see the installation manual. FUEL PRESSURE LIMITS- Fuel pressure limitations are shown in the engine installation manuals TCDS E26NE PAGE 7 NOTE 4. ACCESSORY DRIVE PROVISIONS TORQUE MOMENT TORQUE SPEED RATIO CONTINUOUS OVERHANG STATIC DRIVE ROTATION (1) POWER TURBINE GAS GENERATOR (lb-in) (lb-in) (lb-in) Tachometer, accessory gearbox ** CCW 0.1121 0.1401*** 7 / 11.5 *** 10 100 Starter/generator (pad D) CW 0.2931 170 204 ****** 250 190 ****** 1600 1380 ****** 2nd starter/generator (pad D1)**** CW 0.3207 170 155 1600 Vacuum pump/accessory drive (pad H) CCW 0.1019 60 20 ****** 25 800 Aircraft Accessory Drive (pad C) CCW 0.2041 0.2244 **** 150 30 ****** 25 800 Aircraft Accessory Drive (pad B) ***** / ******* CW 0.3207 135/ 160 *** 25 800 Tachometer, reduction gearbox ** CW 0.1264* 0.1405 0.1421 *** 7 10 100 Propeller overspeed governor ** CW 0.1264* 0.1405/ 0.1421 *** 50 25 850 Propeller governor ** CW 0.1264* 0.1405 0.1421 *** 50 25 850 (1) Direction of shaft rotation, facing engine pad: CCW = Counterclockwise CW = Clockwise Gas generator speed (Ng) 100% = 37,468 RPM Power turbine speed (Np): PT6A-64/66/66A/66D/66B Np 100% = 33,235 RPM (propeller shaft speed 2,205 RPM) PT6A-67/67A/67B/67D/67R/67AG/67T/67AF/ 67P/67RM/PT6E-67XP Np 100% = 29,894 RPM (propeller shaft speed ,1700 RPM) PT6A-68 / PT6A-68D Np100% = 29,906 RPM (propeller shaft speed 1,995 RPM) PT6A-67F Np 100% = 29,564 RPM (Propeller shaft speed 1700 RPM) PT6E-66XT Np 100% = 29,843 RPM (propeller shaft speed 2,000 RPM) * For the PT6A-64, -66, –66A, 66D & 66B series only ** Not applicable to the PT6A-68, PT6E-67XP, PT6A-68D and PT6E-66XT *** For the PT6A-67F **** For the PT6A-67P and PT6E-67XP ***** Not applicable for the PT6A-67P and PT6E-67XP ****** For the PT6A-68D ******* Not applicable to the PT6A-68D TCDS E26NE PAGE 8 NOTE 5. MODEL DESCRIPTION Model Characteristics PT6A-67 Basic turboprop model PT6A-67A A version of the basic -67 model with increased normal and maximum cruise ratings. PT6A-66 Variant model limited to 850 SHP with 2000 RPM standard and opposite rotation gearboxes. PT6A-67R Derivative of PT6A-67, 1424 SHP with 1700 RPM standard rotating gearbox and inclined turbine exhaust case. PT6A-64 Variant model. Derivative of the PT6A-66 with the PT6A-61 reduction gearbox. Limited to 700 SHP with 2000 RPM standard rotation gearbox. PT6A-67B Variant model. Derivative of the basic -67 model using an upgraded reduction gearbox, flat rated at 1200 SHP. PT6A-67D Variant model. Derivative of the basic -67 model, similar to the PT6A-67R but with take-off flat rated to 1279 SHP. PT6A-67AG Variant model. Derivative of the basic -67 model, similar to other PT6A-67R but limited to 1350 SHP for special applications. PT6A-66A Derivative of the PT6A-66 with the PT6A-61 reduction gearbox. Limited to 850 SHP with 2000 RPM, standard rotation gearbox. PT6A-67T Derivative of the basic -67 model, similar to the PT6A-67R but with the -67D hot end hardware. PT6A-68 Derivative of the PT6A-67 family with a 2000 RPM, 1250 SHP gearbox and an electronic Power Management System with mechanical back-up. The engine also features a lubricating system capable of aerobatic maneuvers. PT6A-67AF Derivative of the basic A67 model using the A67R 1424 SHP take off rating for special applications. PT6A-66B Derivative of the PT6A-66 with the PT6A-67A thermal rating. Limited to 950 SHP with 2000 RPM standard & opposite rotation gearboxes. PT6A-66D Derivative of the PT6A-66A, with the PT6A-67A thermal rating. Limited to 850 SHP with 2000 RPM, standard rotation gearbox. PT6A-67F Derivative of the PT6A-67B with a new Reduction Gearbox Rated to 1700 SHP and a new Accessory Gearbox. PT6A-67P Derivative of the PT6A-67B with the -67A thermal rating. The AGB has a mounting provision for a second generator unit. PT6A-67RM Derivative of the PT6A-67R, 1424 SHP with 1700 RPM standard rotating gearbox and inclined turbine exhaust case. PT6E-67XP Derivative of the PT6A-67P includes an Engine and Propeller Electronic Control System (EPECS) and associated hardware. PT6A-68D Derivative of the PT6A-68 with a 2000 RPM, 1600 SHP gearbox and an electronic Power Management System with mechanical back-up. PT6E-66XT Derivative of the PT6E-67XP with a 2000 RPM, 895 SHP gearbox, includes an Engine and Propeller Electronic Control System (EPECS) and associated hardware. NOTE 6. TYPICAL AIRCRAFT ACCESSORIES, COMPONENTS, OR SYSTEM ASSEMBLIES, WITH AIRCRAFT LEVEL REQUIREMENTS, PROVIDED AS PART OF ENGINE TYPE DESIGN: Not Applicable NOTE 7. AIRCRAFTACCESSORIES, COMPONENTS, OR SYSTEM ASSEMBLIES INSTALLED ON THE ENGINE BUT ARE NOT PROVIDED AS PART OF ENGINE TYPE DESIGN: Not Applicable TCDS E26NE PAGE 9 NOTE 8. SPECIAL ANTI-ICING OR DE-ICING REQUIREMENTS: These engines meet the requirements of 14 CFR 33.68 for operation in icing conditions as defined in 14 CFR Part 25 Appendix C when the intake system conforms to the Pratt & Whitney Canada Installation Manual instructions for inertial separation of snow and icing particles. The engines also meet the requirements of 14 CFR 33.27 and do not require external armoring. NOTE 9. ENGINE MOUNT SYSTEM PROVISIONS: Refer to Installation Manuals for the engine mount system. NOTE 10. POWER BOOST, INJECTION OR AUGMENTATION SYSTEMS: Not Applicable NOTE 11. SPECIAL INSTALLATION REQUIREMENTS: The PT6A-67R/-67RM models include provisions for automatic power increases from Alternate Takeoff Power to Takeoff Power. Oil tank usable volume: 1.5 U.S. gallons / 5.68 litres / 1.25 imperial gallons. For PT6A-68 and PT6A-68D 0.79 U.S. gallons / 3.00 litres / 0.66 imperial gallons, normal operation, 0.26 U.S. gallons / 1.00 litre / 0.22 imperial gallons, aerobatic maneuvers. Oil tank total capacity: 2.5 U.S. gallons / 9.46 litres / 2.08 imperial gallons. 4.23 U.S. gallons / 16.00 litres / 3.52 imperial gallons for PT6A-68 and PT6A-68D The software contained in the PT6A-68 Power Management Unit has been designed and developed in accordance with the provisions of RTCA/DO-178A Level 1. The software contained in the PT6A-68D Power Management Unit has been designed and developed in accordance with the provisions of RTCA/DO-178B Level A. For the PT6E-67XP and PT6E-66XT, the software contained in the Engine and Propeller Electronic Control System (EPECS) has been designed, developed, tested and documented in accordance with the provisions of the Critical Category of Level A of RTCA/DO178C. For the PT6A-68 and PT6A-68D, the Power Management Units have not been fire tested and therefore, may only be mounted in a designated fire zone if there are instructions to select manual mode operation in the event of a fire indication in that zone. For the PT6E-67XP and PT6E-66XT, the electronic engine control unit (EEC) has not been fire tested and therefore must not be installed in a designated fire zone. The PT6E-67XP and PT6E-66XT are approved for single engine installations only. Refer to the Installation manual for safety analysis assumptions. For the PT6A-68, PT6A-68D, PT6E-67XP and PT6E-66XT refer to the Installation manual for HIRF and Lightning qualification and conformance. Time Limited Dispatch The model PT6E-67XP engine is equipped with a FADEC which is approved for Time Limited Dispatch (TLD). The dispatch criteria are defined in the Airworthiness Limitations Section of the Maintenance Manual P/N 3076392 and references report number ER 11080 that lists the TLD dispatchable fault categories. The model PT6E-66XT engine is equipped with a FADEC which is approved for Time Limited Dispatch (TLD). The dispatch criteria are defined in the Airworthiness Limitations Section of the Maintenance Manual P/N 3134822 and references report number ER 11190 that lists the TLD dispatchable fault categories. TCDS E26NE PAGE 10 NOTE 12. MANUFACTURER’S SERVICE BULLETINS OR OTHER INSTRUCTIONS COVERING MATTERS OF INTEREST: Service Bulletins, vendor manuals overhaul and maintenance manuals, which contain a statement that the document is Transport Canada approved, are accepted by the FAA and are considered FAA approved. These approvals pertain to the type design only. NOTE 13. SPECIAL OPERATING PROCEDURES: The PT6A-67AF is a special purpose version of the PT6A-67 series of engines intended for use in military and fire fighting aviation. This model may not be re-designated for other than military or firefighting operations. PT6A-67AG is a special purpose version of the PT6A-67 series of engines intended for use in agricultural aviation. This model may not be re-designated for other than agricultural operations. NOTE 14. SPECIAL REPAIR OR OVERHAUL LIMITATIONS: The recommended engine operating time between overhauls is published in Pratt & Whitney Canada Service Bulletin Number 14003 (-67R/67D) 14503 (-67AG only) 14603 (-64/-66/-67/-67A/-67B/-67E/-66A/-67T/- 66D/- 66B/ -67P/-67RM) 14303 (-67AF and -67F) For the PT6E-67XP, refer to the maintenance manual 3076392. 18203 (-68D) For the PT6E-66XT, refer to the maintenance manual 3134822 The PT6A-66/66B engines may be overhauled or maintained as three modules. The gas generator module and the power section module are separated at the "C" flange. The nose section module (2nd-stage reduction gearbox) is separated at the "A" flange: Module PT6A-66 PT6A-66B Gas generator module Power section module Nose section module, standard rotation Nose section module, reverse rotation P/N 3036400 P/N 3036900 P/N 3107180 P/N 3108280 3072313 3072314 3112380 3112480 The PT6A-67/67A/67B/67D/67R/64/67AG/67T/68/68D/66A/66D/67AF/67F/67P/67RM and PT6E-66XT/67XP, engines may be overhauled or maintained as two modules, the gas generator module and the power section module. The separation point is the "C" flange: Gas generator module PT6A-67/67A/67R/64/67AG/66A/67T/67AF P/N 3036400 Gas generator module PT6A-67B P/N 3042300 Gas generator module PT6A-67D P/N 3044900 Gas generator module PT6A-68 P/N 3047000