TCDS E00068EN

PAGE 1 2 3 4 5 REV. 6 6 6 6 6 LEGEND: "- -" INDICATES "SAME AS PRECEDING MODEL" "---" NOT APPLICABLE NOTE: SIGNIFICANT CHANGES ARE BLACK -LINED IN THE LEFT MARGIN. U. S. DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION TYPE CERTIFICATE DATA SHEET E00068EN TCDS NUMBER E00068EN Revision 6 Pratt & Whitney Canada Corp. MODELS: PT6C-67D, PT6C-67C, PT6C-67E, PT6C-67A, PT6C-67C1 Date: March 10, 2021 Engines of models described herein conforming with this data sheet (which is part of Type Certificate Number E00068EN) 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 Twin-spool free turbine turboshaft engine incorporating 4 axial stages and a single stage centrifugal compressor driven by a single stage uncooled turbine, reverse flow annular combustor, and a two stage shrouded power turbine. MODELS: PT6C-67D PT6C-67C PT6C-67C1 PT6C-67E PT6C-67A RATINGS (See NOTE 1) SHAFT HORSEPOWER SHP (KW) 30 sec. OEI 2 min. OEI 30 min. OEI 2 1/2 min. OEI Continuous OEI 30 Min Power Take-off (5 min) Max. Continuous Max. Cruise --- --- --- --- --- --- 1680(1253) 1550(1156) --- --- --- --- 1872(1396) 1679(1252) --- 1679(1252) 1531(1142) --- --- --- --- - - - - --- - - - - --- 2067(1541) 1907(1422) --- --- 1805(1347) 1774(1324) 1774(1324) 1645(1227) --- 2518(1878) 2276(1697) 2202(1642) --- 2014(1502) --- 2014(1502) 1771(1321) 1771(1321) COMPONENTS/ CONFIGURATION For PT6C-67D, PT6C-67C, PT6C-67C1 and PT6C-67E the fuel management module, including fuel pump, electronic engine control (EEC) unit, alternator and ignition system without its power source, are included as standard equipment as per the approved Parts List. For PT6C-67A the Fuel Control Unit including fuel pump and ignition system without its power source, are included as standard equipment as per the approved Parts List. Required equipment for all models also includes a chip detector, or other metallic debris-detecting device to be approved by the FAA or Transport Canada as applicable. For additional information, refer to Installation Manual. For output and accessory drive specifications, principal dimensions, weight and center of gravity location, refer to Installation Manual. FUEL Fuel conforming to the current PWC Specification No. CPW 204 and later revisions. For further details refer to the applicable Maintenance Manual for each model (reference NOTE 15 for Maintenance Manual part number). LUBRICATING OILS Synthetic type conforming to the current PWA Specification Number PWA 521Type I and Type II. Type I is not applicable to the PT6C-67A. For approved brands refer to the applicable Maintenance Manual or Installation Manual for each model (reference NOTE 15 for Manual part numbers). Mixing of brands is not permitted. TCDS E00068EN Page 2 of 5 CERTIFICATION BASIS For PT6C-67D, PT6C-67C and PT6C-67C1, Title 14 of the Code of Federal Regulations (14 CFR Part 33) effective February 1, 1965, as amended by 33-1 through 33-20. For PT6C-67E, 14 CFR Part 33 effective February 1, 1965, as amended by 33-1 through 33-30 and Special Condition:33-010-SC: for 30-minutes all engines operating (AEO) power rating. For PT6C-67A, 14 CFR Part 33 effective February 1, 1965, as amended by 33-1 through 33-33. TYPE CERTIFICATE NUMBER E00068EN MODEL APPLICATION DATE ISSUED/REVISED PT6C-67C MARCH 28, 1998 DECEMBER 5, 2003/AUGUST 10, 2005 PT6C-67D APRIL 20, 2001 AUGUST 14, 2002 PT6C-67E JULY 10, 2008 AUGUST 20, 2012 PT6C-67A AUGUST 21, 2015 NOVEMBER 15, 2017 PT6C-67C1 SEPTEMBER 29,2020 MARCH 10, 2021 CERTIFICATION ENGINE DEFINITION Model Parts List/Drawing PT6C-67D A3055830-01 PT6C-67C A3045379 change H PT6C-67E A3073783-01 change H PT6C-67A A3050458-01 change D PT6C-67C1 3136907 Rev A NOTES Note 1 ENGINE RATINGS: The engine ratings are based on dry sea level static ICAO standard atmospheric conditions, with no external accessory loads and no air bleed. The quoted ratings are obtainable on a test stand with the specified fuel and oil, and with the reference intake and exhaust ducts specified in the Installation Manual. Note 2 TEMPERATURES MODELS PT6C-67D PT6C-67C PT6C-67C1 PT6C-67E PT6C-67A Maximum permissible interturbine temperature limits (ºC) 30 sec. OEI 2 min OEI 30 min OEI 2 1/2 min OEI Continuous OEI 30 min Power Take-off (5 min) Maximum Continuous Maximum Cruise Transient (10 sec)* Starting (2 sec. max.) --- --- --- --- --- 810 775 --- 835 1000 --- --- --- 835 775 775 735 --- 847 1100 --- --- --- - - - - 803 - - --- - - 1000 915 865 --- --- 820 815 815 775 --- 925 --- 925 - - 845 --- 815 --- - - 780 780 877 --- *Refer to Installation Manual; 20 sec for PT6C-67E and 5 sec for PT6C-67A FUEL Refer to Installation Manual. OIL Refer to Installation Manual Starting Minimum: (PT6C-67D) -50°C (PT6C-67C & -67C1) -50°C (PT6C-67E) -50°C (PT6C-67A) -40°C Note 3. PRESSURES FUEL Inlet Head-See Installation Manual for required inlet pressures and lift capability. TCDS E00068EN Page 3 of 5 Viscosity-Maximum cold starting: 12 centistokes. OIL Refer to Installation Manual. Tank Capacity PT6C-67D, PT6C-67C, PT6C-67C1 & PT6C-67E Totals: Liters 8/U.S. Gallons 2.11 PT6C-67A Totals: Liters 6.2/U.S. Gallons 1.63 NOTE 4. ACCESSORY DRIVE PROVISIONS ACCESSORY DRIVE: Drive Pad Configuration MS3326-2 Rotation Speed Ratio Torque (lb.-in.) Overhung Moment (lb.-in.) Continuous Overload Static Starter/Generator CW 0.28991 0.29852 213 - 1780 250 -Pad to respective MS except for ratings and/or dimensions UOS. -CW = Clockwise (facing the drive pad) -Maximum allowable continuous torque values are at any engine speed unless otherwise noted, provided no destructive forces resulting from accessory torsional vibration are present. -Maximum allowable overhung bending moments of accessories about drive face are as indicated, provided no destructive forces result from accessory vibration are present. -Speed ratio relative to gas generator. -Spline must not be lubricated. -No preformed packing required at the engine/accessory interface. 1 PT6C-67C, PT6C-67C1, PT6C-67D, PT6C-67E 2 PT6C-67A NOTE 5. MODEL DESCRIPTION PT6C-67D-Installed in DynCorp UH-1 Golden Eagle PT6C-67C & -67C1-Installed in Leonardo Helicopter AW139 PT6C-67E-Installed in Airbus Helicopter H175 PT6C-67A-Installed in Leonardo Helicopter AW609 NOTE 6. ACCESSORIES, COMPONENTS, OR SYSTEM ASSEMBLIES PROVIDED AS PART OF ENGINE TYPE DESIGN Not Applicable NOTE 7. ACCESSORIES, COMPONENTS, OR SYSTEM ASSEMBLIES NOT PROVIDED AS PART OF ENGINE TYPE DESIGN: PT6C-67A: See Note 13 for information on the Flight Control Computer which is approved at the aircraft level. NOTE 8. SPECIAL ANTI-ICING OR DE-ICING REQUIREMENTS Not Applicable NOTE 9. ENGINE MOUNT SYSTEM PROVISIONS Refer to Installation Manual. NOTE 10. POWER BOOST, INJECTION OR AUGMENTATION SYSTEMS Not Applicable NOTE 11. SPECIAL INSTALLATION REQUIREMENTS The uninstalled engine meets FAA requirements for operating in icing conditions. These engines also meet the requirements of Canadian Airworthiness Manual 533.68 for operation in icing conditions as defined in Canadian Airworthiness Manual 529, Appendix C. The Airframe Manufacturer must give appropriate consideration to installation effects as stated in the Installation Manual. The software for the Electronic Engine Control (EEC) has been developed and tested in accordance with the provisions of "Flight Critical" category (Level A) of RTCA/DO178B or DO178C for the PT6C-67D, PT6C-67C, PT6C-67C1 and PT6C-67E. Lightning protection requirements and electromagnetic interference emitted by the electronic engine control system, including cables, are specified in the Installation Manual The PT6C-67C, PT6C-67C1, PT6C-67D & PT6C-67E EECs have not been fire tested and therefore, must not be mounted in a designated fire zone TCDS E00068EN Page 4 of 5 NOTE 12. MANUFACTURER’S SERVICE BULLETINS OR OTHER INSTRUCTIONS COVERING MATTERS OF INTEREST Service Bulletins, structural repair manuals, vendor manuals, aircraft flight manuals, and 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 Mechanical limits controlled by engine software enable the management of rotorcraft limitations within the certified engine thermal ratings for the PT6C-67D, -67C, 67C1 and 67E engines. The PT6C-67A receives gas generator rotor speed demand via analog electrical signals directly from the aircraft Flight Control Computers (FCCs). The FCC is required to limit the interturbine temperature (ITT) during the application of the 30 second one engine out (OEI) power. NOTE 14. SPECIAL REPAIR OR OVERHAUL LIMITATIONS Not Applicable NOTE 15. APPLICABLE INSTALLATION, MAINTENANCE & OVERHAUL MANUALS 1. Installation Manuals and Interface Control Documents Installation Interface Model Manual P/N Control Document No. PT6C-67D ER5412 ER5166 PT6C-67C & C1 ER4218 ER4206 PT6C-67E 3078130 ER6750 PT6C-67A 3134163 ER9012 2. Maintenance and Overhaul Manuals. Maintenance Overhaul Model Manual P/N Manual P/N PT6C-67D 3056642 3056643 PT6C-67C& C1 3045332 3045333 PT6C-67E 3072872 3072873 PT6C-67A 3045082 Available 2021 3. Cleaning, Inspection and Repair Manuals. Model Manual P/N PT6C-67D 3075447 PT6C-67C & C1 3075447 PT6C-67E 3075447 PT6C-67A Available 2021 Instructions for Continued Airworthiness are incomplete for the PT6C-67A. 14 CFR 21.50(b) requires the holder of this type certificate to ensue these instructions are complete and furnished prior to when the aircraft incorporating these engines are issued standard airworthiness certificates or delivered/returned to service, whichever occurs later. The aircraft must not be issued a standard airworthiness certificate or approved for return to service until the ICA are complete and determined acceptable. NOTE 16. IMPORT REQUIREMENTS To be considered eligible for installation on U.S. - registered aircraft, each engine to be exported to the United States shall be accompanied by a certificate of airworthiness for export or certifying statement endorsed by the exporting cognizant civil airworthiness authority and containing the following language: (1) This engine conforms to its United States type design (Type Certificate Number E00068EN) and is in a condition for safe operation. (2) This engine has been subjected by the manufacturer to a final operational check and is in a proper state of airworthiness. Reference 14 CFR Section 21.500, which provides for the airworthiness acceptance of aircraft engines or propellers manufactured outside of the U.S. and for which a U.S. type certificate has been issued. Additional guidance is contained in FAA Advisory Circular 21-23, Airworthiness Certification of Civil Aircraft, Engines, Propellers and Related Products, Imported into the United States. NOTE 17. LIFE LIMITED PART INFORMATION Certain engine parts are life limited. For PT6C-67C, PT6C-67C1, PT6C-67D, PT6C-67E & PT6C-67A engines, these life limits are listed in PWC maintenance manual P/N 3056642 for the PT6C-67D, P/N 3045332 for PT6C-67C & PT6C- 67C1, P/N 3072872 for the PT6C-67E and P/N 3045082 for the PT6C-67A. NOTE 18. MILITARY MODEL INFORMATION: Not Applicable TCDS E00068EN Page 5 of 5 NOTE 19. ROTOR SPEEDS MODELS PT6C-67D PT6C-67C PT6C-67C1 PT6C-67E PT6C-67A Gas Generator Speed Maximum 30 sec OEI 2 min OEI 30 min OEI 2 1/2 min OEI Continuous OEI 30 min power Take-off (5 min) Maximum Continuous Maximum Cruise Transient (10 sec)* Starting (2 sec. max.) --- --- --- --- --- --- 39,100 38,100 --- 40,500 --- --- --- --- 40,500 39,100 --- - - 38,200 --- 40,900 --- --- --- --- - - - - --- - - - - --- - - --- 41600 40500 --- --- 39500 39200 39200 38500 --- 39500 --- 40500 39300 39100 --- 38600 --- 38600 38000 38000 39500 --- *Refer to Installation Manual; 20 sec for PT6C-67E and 5 sec for PT6C-67A MODELS PT6C-67D PT6C-67C PT6C-67C1 PT6C-67E PT6C-67A Output Shaft Speed Maximum 30 sec OEI 2 min OEI 30 min OEI 2 1/2 min OEI Continuous OEI 30 min power Take-off (5 min) Maximum Continuous Maximum Cruise Transient (10 sec)* Starting (2 sec. max.) --- --- --- --- --- --- 21,520 21,200 --- 23,310 --- --- --- --- 21,420 21,420 --- 21,420 21,420 --- - - --- --- --- --- - - - - --- - - - - --- - - --- 21000 21000 --- --- 21000 22470 22470 22470 --- 23470 --- 30633 30633 30633 --- 30633 --- 30633 30633 25227 33335 --- *Refer to Installation Manual; 20 sec for PT6C-67E and 5 sec for PT6C-67A NOTE 20. OUTPUT SHAFT TORQUE LIMITS MODELS PT6C-67D PT6C-67C PT6C-67C1 PT6C-67E PT6C-67A Maximum torque Limits FT-LB (N-M) 30 sec OEI 2 min OEI 30 min OEI 2 1/2 min OEI Continuous OEI 30 min power Take-off (5 min) Maximum Continuous Maximum Cruise Transient (10 sec)* Starting (2 sec. max.) --- --- --- --- --- --- 292(396) 292(396) --- 400(542) --- --- --- --- 400(542) 350(475) --- 283(384) 268(363) --- 440(597) --- --- --- --- - - - - --- 302.5(410) - - --- - - --- 498(675) 443(600) --- --- 387(525) 325(441) 325(441) 302(410) --- 400(543) --- 402(545) 332(450) 304(412) --- 304(412) --- 268(363) 235(319) 235(319) 440(597) --- *Refer to Installation Manual; 20 sec for PT6C-67E and 5 sec for PT6C-67A NOTE 21. BLEED AIR EXTRACTION PROVISIONS PT6C-67D, PT6C-67C, PT6C-67C1 & PT6C-67E Max. external: 5.25% of inlet airflow PT6C-67A Max. external: 4% of inlet airflow See Installation Manual for allowances above 4% of inlet airflow NOTE 22. ROTOR DISK INTEGRITY AND ROTOR BLADE CONTAINMENT No special requirements. NOTE 23 EXHAUST EMISSIONS AND FUEL VENTING Not Applicable ---END---