TCDS E22EA

* PAGE 1 2 3 4 5 6 7 8 REV. 15 13 13 13 15 13 14 13 LEGEND: "- -" INDICATES "SAME AS PRECEDING MODEL" "---" NOT APPLICABLE NOTE: ALL PAGES ARE REFORMATTED. SIGNIFICANT CHANGES IF ANY, ARE BLACK-LINED IN THE LEFT MARGIN. U.S. DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION TYPE CERTIFICATE DATA SHEET E22EA TCDS NUMBER E22EA REVISION: 15* DATE: December 20, 2012 PRATT & WHITNEY CANADA CORP MODELS: PT6T-3 PT6T-3BE PT6T-3DE PT6T-3A PT6T-6 PT6T-3DF PT6T-3B PT6T-3D PT6T-3BF PT6T-3BG PT6T-9 Engines of models described herein conforming with this data sheet (which is part of Type Certificate Number E22EA) 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 (Formerly Pratt & Whitney, Inc.) (Formerly Pratt & Whitney Aircraft of Canada Ltd. and United Aircraft of Canada, Ltd.) Longueuil, Quebec, Canada J4G1A1 I. MODELS PT6T-3/-3A/-3B/-3BE PT6T-6 PT6T-3D PT6T-3DE TYPE Twin Power Section Turboshaft RATINGS (See NOTE 1) Maximum continuous at sea level Total output shaft hp. Single power section shaft hp. Takeoff at sea level (5 min) Total output shaft hp. Single power section shaft hp. 30 min. helicopter rating at sea level Total output shaft hp. Single power section shaft hp. Continuous OEI power rating at sea level Single power section shaft hp. 2 1/2 min. power rating at sea level Single power section shaft hp. 1600 800 1800 900 --- 900 (-3B, -3BE, 970) --- --- (-3B, -3BE, 1025) 1675 825 1875 925 --- 970 --- 1025 1600 800 1800 900 --- --- 1024 1133 - - - - - - - - --- 1079 --- - - TCDS E22EA PAGE 2 MODELS (continued) PT6T-3DF PT6T-3BF/ -3BG PT6T-9 TYPE Twin Power Section Turboshaft RATINGS (See NOTE 1) Maximum continuous at sea level Total output shaft hp. Single power section shaft hp. Takeoff at sea level (5 min) Total output shaft hp. Single power section shaft hp. 30 min. helicopter rating at sea level Total output shaft hp. Single power section shaft hp. Continuous OEI power rating at sea level Single power section shaft hp. 2 1/2 min. power rating at sea level Single power section shaft hp. 2 minute power rating at sea level, single power section shaft hp. 30 sec. Power rating at sea level, single power section shaft hp. - - - - - - - - --- - - --- - - - - - - - - - - --- 1025 --- 1025 1650 825 1855 928 --- --- 1100 --- 1150 1269 TCDS E22EA PAGE 3 I. MODELS (Cont.) PT6T-3/-3A/-3B/-3BE PT6T-6 PT6T-3D Limitations: Engine speed: (See NOTE 7) Maximum continuous at sea level, When Governor P/N 3018712 is installed, Output r.p.m. (max.) Gas Generator r.p.m. (max.) When Governor P/N 3118388-01 is installed, Output r.p.m. (max.) Gas generator r.p.m. (max.) Takeoff at sea level Output r.p.m. (max.) Gas generator r.p.m. (max.) 30 min. helicopter rating at sea level Output r.p.m. (max.) Gas generator r.p.m. (max.) Continuous OEI rating at sea level Output r.p.m. (max.) Gas Generator r.p.m. (max.) 2 1/2 min. power rating at sea level Output r.p.m. (max.) Gas generator r.p.m. (max.) Engine Torque Maximum continuous lb.-ft. (max.) each power section applies within range of 5610 to 6798 r.p.m. Takeoff (5 min.) lb.-ft. (max) each power section applies within range of 6000 to 6600 r.p.m. (6000 to 6798 for -3D) 30 min. helicopter rating lb.-ft. (max.) each power section Continuous OEI power rating lb.-st. (max.) each power section applies within range of 6000 to 6600 r.p.m. 2 1/2 min. power rating lb.-ft. (max.) each power section applies within range of 6000 to 6800 r.p.m. 6600 38100 (-3B, -3BE, 38,800) 6600 38100 (-3B, -3BE, 38,800) 6600 38100 (-3B, -3BE, 38,800) --- --- --- (-3B, -3BE, 6600) --- (-3B, -3BE, 39,400) 657 738 738 (-3B, -3BE, 815) --- --- (-3B, -3BE, 815) - - 38,400 - - 38,400 - - 38,400 --- --- 6600 39,000 - - - - 815 --- 815 6600 39,300 6798 39,300 --- --- --- --- 6600 41,600 - - - - - - 815 902 Temperature (Measured Inter-Turbine) Maximum continuous Takeoff (5 min.) 30 min. helicopter rating Continuous OEI Starting transient (2 sec.) 2 1/2 min. power rating 1410˚F (765˚C) 1490˚F (810˚C) 1490˚F (810˚C) / --- 1995˚F (1090˚C) (-3B, -3BE 1562˚F, 850˚C) 1099˚F (593˚C) 1154˚F (624˚C) 1154˚F (624˚C) --- 1400˚F (760˚C) 1193˚F (645˚C) 1490˚F (810˚C) 1490˚F (810˚C) --- 1508˚F (820˚C) 1995˚F (1090˚C) 1724˚F (940˚C) TCDS E22EA PAGE 4 I. MODELS (Cont.) PT6T-3DE PT6T-3DF PT6T-3BF/-3BG PT6T-9 Limitations Engine speed: (See NOTE 7) Maximum continuous at sea level, When Governor P/N 3018712 is installed, Output rpm (max.) Gas Generator rpm (max.) When Governor P/N 3118388-01 is installed, Output rpm (max.) Gas generator rpm (max.) Takeoff at sea level Output rpm (max.) Gas generator rpm (max.) 30 min. helicopter rating at sea level Output rpm (max.) Gas generator r.p.m. (max.) Continuous OEI power rating at sea level Output rpm (max) Gas Generator rpm (max) 2 1/2 min. power rating at sea level Output rpm (max.) Gas generator rpm (max.) 2 min. power rating at sea level output rpm(max) gas generator rpm (max) 30 sec power rating at sea level output rpm (max) gas generator rpm (max) Engine Torque Maximum continuous lb.-ft. (max.) each power section applies within range of 5610 to 6798 rpm (6402 to 6798 for PT6T-9) Takeoff (5 min.) lb.-ft. (max) each power section applies within range of 6000 to 6600 rpm (6000 to 6798 for -3D)(6402 to 6798 for PT6T-9) 30 min. helicopter rating lb.-ft. (max.) each power section Continuous OEI power rating lb.-ft. (max) each power section applies within range of 6000 to 6600 rpm (6402 to 6798 for PT6T-9) 2 1/2 min. power rating lb.-ft. (max.) each power section applies within range of 6000 to 6800 rpm 2 min. power rating lb-ft (max) each power section applies within range of 6,402 to 6,798 rpm 30 sec power rating lb-ft (max) each power section applies within range of 6,402 to 6,798 rpm 6600 39,300 6798 39,300 6600 40,250 --- --- 6600 41,600 657 738 859 --- 902 - - - - - - - - - - 40,700 - - - - -- -- -- --- -- 6,600 38,800 6,600 38,800 - - 39,400 6,600 39,400 -- 815 --- 815 --- --- --- --- 6798 38,850 --- --- 6,798 39,500 --- --- 6,798 40,160 6,798 41,200 -- -- --- 875 --- 915 1010 Temperature (Measured Inter-Turbine) Maximum continuous Takeoff (5 min.) 30 min. helicopter rating Continuous OEI Starting transient (2 sec.) 2 1/2 min. power rating 2 min. power rating 30 sec power rating 1490°F (810˚C) 1490°F (810˚C) 1571°F (855˚C) / --- 1995°F (1090˚C) 1724°F, 940˚C) - - - - 1625˚F (885°C) - - - - 1410˚F(766°C) - - 1562˚F (850°C) --- 1995°F (1090˚C) 1562˚F (850˚C) 1445°F(785°C) 1517°F(825°C) --- 1580°F(860°C) - - --- 1661°F(905°C) 1760°F(960°C) TCDS E22EA PAGE 5 II. MODELS ALL BLEED External airbleed shall not exceed 5.25 percent. No airbleed is permissible during the starting cycle. Bleed air contains less than one part per million of engine-introduced contamination. FUEL Refer to Installation Manual. OIL Pressure Power Section Gearbox Temperature The following pressures apply to normal operating temperatures. During extremely cold starts, oil pressure may reach 300 psi 80 to 115 psig at 30,000 rpm gas generator speed and above 40 psig minimum, below 30,000 rpm gas generator speed. For PT6T-9: 80 to 125 psig at 33,000 rpm gas generator speed and above. 40 psig minimum below 30,000 rpm gas generator speed, 71 psig minimum at 30,000 rpm gas generator speed, increasing linearly to 80 psig minimum at 33,00 rpm gas generator speed. 60 to 80 psig output speeds of 6200 to 6798 rpm Pressure will vary between 0 psig at zero output speed and 80 psig at 6798 rpm Takeoff and maximum continuous, 32˚F (0˚C) to 240˚F (115˚C) Limited periods of 5 minutes at 275˚F (135˚C) Starting minimum, PWA 521 Type II -40 ˚F (-40˚C) PWA 521 Type I -65 ˚F (-54˚C) Accessory Drives The following apply to the accessory driv es, which are provided by the engine and included in the basic engine weight: Driven by Maximum Torque Maximum Gas Generator in. - lb. Overhang Turbine Continuous Static In. -lb. Tachometer** Accessory 7.0 50 25 Gearbox Starter* and/or Generator 200 1600 180 Tachometer** Combining Gearbox 7.0 50 25 Blower 155 1500 160 Drive *Overload torque 300 in.-lb. 30 sec. max. per application **Not applicable to the PT6T-9 TCDS E22EA PAGE 6 II. MODELS (Cont.) ALL Specifications Fuel Oil Type Tank Capacity JP-1, JP-4 and JP-5 fuels conforming to PWA Specification No. 522 and later revisions. (See NOTE 2.) Synthetic type conforming to the current PWA 521 Type 1 or PWA 521 Type II Specifications. (See NOTE 3) Power Section 1.60 Gal. Total (EACH) .75 Gal. Usable Gearbox 1.25 Gal. Total .25 Gal. Usable PRINCIPAL DIMENSIONS Nominal Length, in. - 65.2 (-3, -3A, -3B, -3BE, -3BF, -3BG, -3D, -3DE, -3DF); 66.8 (-6): 66.1 (PT6T-9). Nominal width, in. - 44.5 (-3, -3A, -3B, -3BE, -3BF, -3BG, -3D, -3DE, -3DF); 43.5 (-6): 45.0 (PT6T-9) Nominal height, in. - 32.6 (-3, -3A, -3B, -3BE, -3BF, -3BG, -3D, -3DE, -3DF); 32.6 (-6): 35.8 (PT6T-9). C.G. LOCATION Forward of gearbox m ount plane, in. - 18.89 (-3, -3B, -3BE, -3BF, -3BG, -3D, -3DE, -3DF -6) 18.47 (-3A), 19.21 (PT6T-9). Above engine center line, in. - 1.62 (-3, -3B, -3BE, -3BF, -3BG, -3D, -3DE, -3DF -6) 1.63 (-3A), 2.06 (PT6T-9). Right side of engine center line, in. -0.15 (-3, -3B, -3BE, -3BF, -3BG, -3D, -3DE, -3DF -6), 0.07 (-3A), 0.36 (PT6T-9). Forward direction from combining gearbox toward power section intake CERTIFICATION BASIS (See Note 12) FAR 33 dated February 1, 1965, including amendments 33-1 through 33-4 and Special Conditions 33-23-EA-6 dated June 8, 1970, including amendment No. 1 (all except for the PT6T-9) For PT6T-9: FAR 33, dated February 1, 1965, including amendments 33-1 through 33-4 and Special Conditions 33-004-SC plus the following: 1) FAR 33.62, 33.65, 33.81, 33.82 and 33.91, all at Amendment 6. 2) FAR 33.4, 33.5 and 33.99, all at Amendment 9. 3) FAR 33.14, 33.17, 33.27, 33.66, 33.75, 33.77, 33.89 and 33.94, all at Amendment 10. 4) FAR 33.28 Amendment 15. 5) FAR 33.83 Amendment 17. 6) FAR 33.7, 33.29, 33.63, 33.67, 33.85, 33.87, 33.88 and 33.93, all at Amendment 18. Date Type Certificate Model Date of Application Issued/Revised PT6T-3 April 1, 1968 July 9, 1970 PT6T-3A August 18, 1972 October 11, 1972 PT6T-6 December 2, 1974 December 11, 1974 PT6T-3B January 8, 1979 September 14, 1979 PT6T-3BE October 1, 1990 October 12, 1990 PT6T-3D June 14, 1993 August 12, 1993 PT6T-3DE November 24, 1995 November 30, 1995 PT6T-3DF May 15, 1996 June 17, 1996 PT6T-3BF August 28, 1998 October 8, 1998 PT6T-3BG August 28, 1998 October 8, 1998 PT6T-9 March 28, 2000 January 10, 2002 TCDS E22EA PAGE 7 IMPORT REQUIREMENTS To be considered eligible for installation on United States 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, which contains the following language: 1. This engine conforms to its United States type design (Type Certificate Number E22EA) 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 FAR Section 21.500, which provides for the airworthiness acceptance of aircraft engines or propellers manufactured outside of the United States for which a United States type certificate has been issued. Additional guidance is contained in FAA Advisory Circular 21-23, Airworthiness Certification of Civil Aircraft, Engine, Propellers, and Related Products, imported into the United States. NOTES NOTE 1. The engine ratings are based on static sea level conditions. Compressor inlet air (dry) 59˚F, 29.92 in. Hg. Compressor intake screen installed. No external accessory loads and no airbleed. NOTE 2. Emergency use of MIL-G-5572, (all grades) is permitted for a total time period not exceeding 150 hours during any overhaul period. It is not necessary to purge the unused fuel from the system when changing fuel types. For the PT6T-9, refer to the engine maintenance manual. NOTE 3. Pratt & Whitney Canada Service Bulletin 5001 lists approved brand oils. For the PT6T-9, refer to the engine maintenance manual. NOTE 4. This engine meets FAA requirements for opera tion in icing conditions when the intake system conforms with the Pratt & Whitney Canada Installation Manual instructions for inertial separation of snow and icing particles. NOTE 5. For the PT6T-3, PT6T-3B, PT6T-3BE, PT6T -3BF, PT6T-BG, PT6T-3D, PT6T-3DE, PT6T-3DF, and PT6T-6 models, the engine is certificated as a unit comprising two separate power sections with the capability of single engine operation with either power section alone in multi-engined helicopters. The unit is also approved as a single engine. In either event, the installation compatibility of the mixing gearbox components with the rotorcraft drive system will have to be established. NOTE 6. Phillips FPA-55MB anti-icing additive at a concentration not in excess of 0.15% by volume is approved for use in fuels for these engines. For the PT6T-9, refer to the engine maintenance manual. NOTE 7. 100% output shaft speed equals 6600 output shaft r.p.m. or 33,000 power turbine r.p.m. NOTE 8. Certain engine parts are life limited. These limits are listed in Pratt & Whitney Canada Service Bulletin No. 5002 as revised. For the PT6T-9, refer to the engine maintenance manual, airworthiness limitations section. NOTE 9. Power may be restored in hot day conditions by means of water or water/methanol injection when accomplished in accordance with the requirements of the Pratt & Whitney Canada. Installation Manual (PT6T). TCDS E22EA PAGE 8 NOTE 10. The above models incorpor ate the following characteristics: Model Characteristics PT6T-3 Basic model PT6T-3A Similar to PT6T-3 except fo r aluminum instead of magnesium gearbox castings. PT6T-3B Similar to PT6T-3 except fo r single power section contingency ratings and PT6T-6 compressor turbine components. PT6T-6 Similar to PT6T-3 except for 2 1/2 min rating; higher ratings and improved engine parts. PT6T-3BE Same as PT6T-3B except for deletion of the torque sharing function, and a higher limiter setting. PT6T-3D Same as PT6T-3B except for improved hot section hardware to allow for increased ratings. PT6T-3DE Same as PT6T-3D except continuous OEI replaced by 30 minute rating. PT6T-3DF Similar to PT6T-3DE except fo r improved hot section hardware to allow for increased ratings. PT6T-3BF Similar to PT6T-3B except 30 minut e OEI rating is equivalent to the 2 1/2 minute OEI rating. PT6T-3BG Similar to PT6T-3BE except 30 mi nute OEI rating is equivalent to the 2 1/2 minute OEI rating. PT6T-9 Similar to PT6T-3DF except for improved hot section to allow for increased ratings and new 30 second/2 minute OEI ra tings structure. The engine is also equipped with an engine electronic cont rol system (EEC). The software for the EEC has been developed and tested in accordance with the provisions of RTCA/DO178B, level A. The EEC has not been fire tested and, therefore, must not be mounted in a designate d fire zone. Lightning protection limits, including power quality, electromagnetic compatibility and interference for the EEC system are specified in section 6 of the installation manual. NOTE 11. Service bulletins, structural repair manuals, vendor manuals, aircraft flight manuals, and overhaul and maintenance manuals, which contain a statement that the document is approved by Transport Canada, are accepted by the FAA and are considered FAA approved unless otherwise noted. These approvals pertain to the type design only. NOTE 12. The PT6T-9 turboshaft engine configuration is similar to the PT6T-3 series turboshaft engine models. These engines have two identical free-turbine power-sections coupled to a common mixing gearbox module with a single output shaft. One engine inoperative (OEI) power is the rated engine power for operation with one power-section inoperative. ----END----