TCDS E2EA

PAGE 1 2 3 4 5 6 7 8 9 10 REV. 31 31 31 31 31 31 31 31 25 31 LEGEND: "- -" INDICATES "SAME AS PRECEDING MODEL" "---" NOT APPLICABLE U.S. DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION TYPE CERTIFICATE SHEET NO. E2EA TCDS NUMBER E2EA REVISION: 31 DATE: AUGUST 28, 2007 PRATT & WHITNEY MODELS: TURBO WASP JT8D-1 JT8D-7B JT8D-17 JT8D-1A JT8D-9 JT8D-17A JT8D-1B JT8D-9A JT8D-17R JT8D-5 JT8D-11 JT8D-17AR JT8D-7 JT8D-15 JT8D-7A JT8D-15A Engines of models described herein conforming with this data sheet (which is part of Type Certificate Number E2EA) 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 United Technologies Corporation East Hartford, Connecticut 06108 I. MODELS JT8D-1, -1A, -7, -7A JT8D-1B, -7B JT8D-5 JT8D-9 JT8D-9A TYPE Dual, axial 13-stage compressor / four-stage turbine / nine can-annular combustion chambers RATINGS Sea Level Static Thrust (lbs) Maximum continuous Normal takeoff (5 min.) (See NOTE 19) Maximum takeoff (5 min.) (See NOTE 19) 12,600 14,000 14,000 - - - - - - 12,250 12,250 12,250 12,600 14,500 14,500 - - - - - - FUEL CONTROL (See NOTE 17) (Hamilton Standard) JFC60-1 or JFC60-2 - - - - - - - - FUEL PUMP (Argo-Tech Corp.) P/N 243600, 358200, 371900, 378200, or 835800 - - - - - - - - AIR BLEED CONTROL (P&W) P/N 492143, 492143-001, 564651, 564651-001, 593764 593764-001, 658385, 658385-001, 658490, or 658490-001 - - - - 564651, 564651- 001, 593764, 593764- 001, 658385, or 658385-001 - - FUEL See Note 11 - - - - - - - - OIL See Note 12 - - - - - - - - TCDS E2EA PAGE 2 I. MODELS (cont.) JT8D-1, -1A, -7, -7A JT8D-1B, -7B JT8D-5 JT8D-9 JT8D-9A PRINCIPAL DIMENSIONS: Length, in. Width, in. Height, in. 123.56 42.50 53.450 - - - - - - - - - - - - - - - - - - - - - - - - WEIGHT (dry), lb. (includes basic engine with all essential access., with fuel heater, oil tank and fuel oil cooler, but excluding starter exhaust nozzle and power source for the ignition system 3205 - - - - 3252 3402 CENTER OF GRAVITY, INCHES Aft of front mount area centerline Below engine centerline 23.54 1.86 - - - - - - - - - - - - 23.08 2.02 IGNITORS Unison type TCFN-2, TCFN-4, TFN- 32, 42074, 49965, or 49988 exciter with two igniters: P&W P/N 518367 or 709520 NOTES 1-8, 10-15, & 19 - - - - - - - - II. MODELS JT8D-11 JT8D-15 JT8D-15A JT8D-17 JT8D-17A TYPE Dual, axial 13-stage compressor / four-stage turbine / nine can-annular combustion chambers RATINGS Sea Level Static Thrust (lbs) Maximum continuous Normal takeoff (5 min.) (See NOTE 19) Maximum takeoff (5 min.) (See NOTES 19) 12,600 15,000 15,000 13,750 15,500 15,500 - - - - - - 15,200 16,000 16,000 - - - - - - FUEL CONTROL (Hamilton Standard) JFC60-1 or JFC60-2 - - - - JFC60-2 - - FUEL PUMP (Argo-Tech Corp.) P/N 358200, 371900, 378200, or 835800 P/N 378200 or 835800 - - P/N 384300 or 835900 - - AIR BLEED CONTROL (P&W) P/N 658385 or 658385-001 - - - - - - - - FUEL See Note 11 - - - - - - - - OIL See Note 12 - - - - - - - - TCDS E2EA PAGE 3 II. MODELS (cont.) JT8D-11 JT8D-15 JT8D-15A JT8D-17 JT8D-17A PRINCIPAL DIMENSIONS: Length, in. Width, in. Height, in. 123.56 42.50 53.450 - - - - - - - - - - - - - - - - - - - - - - - - WEIGHT (dry), lb. (includes basic engine with all essential access., with fuel heater, oil tank and fuel oil cooler, but excluding starter exhaust nozzle and power source for the ignition system 3389 3414 3474 3430 3475 CENTER OF GRAVITY, INCHES Aft of front mount area centerline Below engine centerline 23.07 1.76 23.10 1.75 23.80 - - 23.70 1.90 24.40 - - IGNITORS Unison type TCFN-2, TCFN-4, TFN- 32, 42074, 49965, or 49988 exciter with two igniters: P&W P/N 518367 or 709520 NOTES 1-8, 10-15, & 19 - - 1-8, 10-15, & 18-19 1-8, 10-15, & 19 1-8, 10-15, & 18- 19 III. MODELS JT8D-17R JT8D-17AR TYPE Dual, axial 13-stage compressor / four-stage turbine / nine can-annular combustion chambers RATINGS Sea Level Static Thrust (lbs) Maximum continuous Normal takeoff (5 min.) (See NOTE 19) Maximum takeoff (5 min.) (See NOTE 19) 15,200 16,400 17,400 - - - - - - FUEL CONTROL (Hamilton Standard) JFC60-3 - - FUEL PUMP (Argo-Tech Corp.) P/N 384300 or 835900 - - AIR BLEED CONTROL (P&W) P/N 658385 or 658385-001 - - FUEL See Note 11 - - OIL See Note 12 - - TCDS E2EA PAGE 4 III. MODELS (cont.) JT8D-17R JT8D-17AR PRINCIPAL DIMENSIONS: Length, in. Width, in. Height, in. 123.56 42.50 53.450 - - - - - - WEIGHT (dry), lb. (includes basic engine with all essential access., with fuel heater, oil tank and fuel oil cooler, but excluding starter exhaust nozzle and power source for the ignition system 3495 3500 CENTER OF GRAVITY, INCHES Aft of front mount area centerline Below engine centerline 23.50 1.80 24.00 - - IGNITORS Unison type TCFN-2, TCFN-4, TFN- 32, 42074, 49965, or 49988 exciter with two igniters: P&W P/N 518367 or 709520 NOTES 1-8, 10-16, & 19 1-8, 10-16, & 18-19 CERTIFICATION BASIS CAR 13 effective June 15, 1956, as amended by 13-1, 13-2, 13-3, 13-4, and 13-5. DATE OF TYPE CERTIFICATE MODEL DATE OF APPLICATION NO. E2EA ISSUED/REVISED JT8D-1 July 5, 1962 February 1, 1963 JT8D-1A February 25, 1971 April 7, 1971 JT8D-1B July 1, 1975 August 14, 1975 JT8D-5 January 24, 1963 February 1, 1963 JT8D-7 January 30, 1966 March 24, 1966 JT8D-7A July 1, 1970 August 4, 1970 JT8D-7B July 1, 1975 August 14, 1975 JT8D-9 September 16, 1966 May 23, 1967 JT8D-9A March 28, 1973 May 30, 1973 JT8D-11 April 19, 1968 September 25, 1968 JT8D-15 October 14, 1969 April 7, 1971 JT8D-15A March 13, 1980 January 26, 1982 JT8D-17 January 15, 1973 February 1, 1974 JT8D-17A March 13, 1980 January 26, 1982 JT8D-17R May 15, 1974 April 29, 1976 JT8D-17AR March 13, 1980 January 26, 1983 PRODUCTION BASIS Producti on Certificate No. 2 TCDS E2EA PAGE 5 NOTES NOTE 1. Rotor Speeds - Maximum permissible engi ne operating speeds for the engine rotors are as follows: JT8D-1, -1A, -1B, -7A, -7B, -9, -9A, -11 JT8D-5 JT8D-15, -15A, -17, -17A JT8D-17R, -17AR Low Pressure rotor (N), rpm Maximum takeoff Normal takeoff High pressure rotor (N2), rpm Maximum takeoff Normal takeoff --- 8,600 --- 12,250 --- 8,500 --- 12,100 --- 8,800 --- 12,250 9,250 8,900 12,600 12,280 NOTE 2. Temperatures - Maximum permissible temperatures are as follows: Turbine outlet gas temperature, °C/°F: JT8D-1, -7 JT8D-5 JT8D-1A, -7A, -9 JT8D-1B, -7B JT8D-9A Normal Takeoff (5 minutes) Maximum continuous Maximum for acceleration (2 minutes) Starting (for 59oF ambient temperature and above) (for 58oF ambient temperature and below) Oil Inlet: continuous operation transient operation 570/1058 535/995 570/1058 420/788 350/662 120/250 157/315 555/1031 - - 555/1031 - - - - - - - - 580/1076 540/1004 580/1076 - - - - - - - - 590/1094 545/1013 590/1094 - - - - - - - - - - - - - - - - - - - - - - JT8D-11 JT8D-15 JT8D-15A JT8D-17 JT8D-17A Normal takeoff (5 min.) Takeoff (5 min.) Maximum continuous Max. for accel. (2 min) Starting (ground) (inflight) Oil Inlet: continuous operation transient operation - - 595/1103 550/1022 595/1103 510/950* 550/1022 130/266 165/329 - - 620/1148 580/1076 630/1166 550/1022 620/1148 - - - - - - - - - - - - 575/1067 - - - - - - - - 650/1202 610/1130 660/1220 550/1022 650/1202 - - - - - - - - - - - - 575/1067 - - - - - - TCDS E2EA PAGE 6 NOTE 2. (Cont.) Temperatures - Maximum permissible temperatures are as follows: Turbine outlet gas temperature, °C/°F: JT8D-17R JT8D-17AR Maximum takeoff (5 min.) Normal takeoff (5 min.) Maximum continuous Max. for accel. (2 min) Starting (ground) (inflight) Oil Inlet: continuous operation transient operation 690/1274 650/1202 610/1130 660/1220 550/1022 650/1202 130/266 165/329 - - - - - - - - 575/1067 - - - - - - NOTE: *Maximum starting limit (ground) is 530ºC/986ºF for JT8D-11 engines that have incorporated P&W Service Bulletin 5455. Transient operation above 120°C (250°F) JT8D-1, -1A, -5, -7, -7A, -7B, -9, -9A 130oC (266oF) JT8D- 11, -15, -15A, -17, -17A, -17R, and -17AR is limited to 15 minutes. External engine components maximum temperature (limiting temperature of specific components) are specified in the engine installation and operating manual. NOTE 3. Pressures - Fuel and oil pressure limits are as follows: Fuel Pressure - At inlet to engine system pump, not less than 5 p.s.i. above the true vapor pressure of the fuel and not greater than 50 p.s.i. with a vapor liquid ratio of zero. Oil Pressure - Minimum 35 psig Normal Range 40-55 psig Note: During cold weather starting, oil pressure in excess of 55 psig may be evidenced until oil viscosities are reduced by increasing oil temperature. Engine operation is limited to idle power when oil pressure is in excess of 55 psig during cold weather starts. TCDS E2EA PAGE 7 NOTE 4. Air Bleed Extraction - Maximum permissible air bleed extraction is as follows: Percentage of Primary Engine Airflow Station Individual Bleeding at a Single Station Normal Maximum * Simultaneous Bleeding of Two or More Stations Normal Maximum * 1. High-Pressure Bleed: a. At 70% maximum continuous thrust and below b. From 70% maximum continuous thrust to maximum continuous thrust c. Above maximum continuous thrust 2. Eighth-Stage Bleed: a. At and below maximum continuous thrust b. Above maximum continuous thrust 3. Low Pressure Bleed: a. At 20% maximum continuous thrust and above b. Below 20% maximum continuous thrust 6.7 3.5 2.8 4.0 2.75 5.0 4.0 8.0 5.5 3.0 4.0 3.25 5.0 4.0 6.7 3.5 2.8 4.0 2.75 4.5 3.5 8.0 5.5 3.0 4.0 3.25 4.5 3.5 Percentage of Secondary Airflow 4. Fan Air Bleed: a. At and below maximum continuous thrust b. Above maximum continuous thrust 3.0 2.0 5.0 2.0 3.0 2.0 3.0 2.0 NOTE: *Usable only when malfunction requires and only until next landing. NOTE 5. The ratings are based on static te st stand operation under the following conditions: Compressor inlet air at 59°F and 29.92 in. Hg. Nozzle exhaust pipe per P&W Drawing PWA 12202 (JT8D-1, -1A, -1B, -5, -7, -7A, -7B, -9, -9A, -11, -15 and -15A); PWA 33811 (JT8D-15 and -15A); PWA 33475 (JT8D-17, -17A, -17R, and -17AR); or PWA 12202 with PWA 33400 extender (JT8D-17, -17A, -17R, and -17AR) P&WA bellmouth on air inlet. No aircraft accessory l oads or air extraction. No anti-icing air flow. Turbine outlet gas temperature limit s and engine rotor speed limits not exceeded. TCDS E2EA PAGE 8 NOTE 6. The following accessory drive provisions are incorporated: Drive Rotation Speed Ratio to Turbine Shaft Torque (lb-in.) Overhang (in.-lb.) Cont. Static Low Rotor: Tachometer C 0.489:1 7 50 --- High Rotor: Starter C 0.597:1 --- * 625 Generator C 0.700:1 1500 6600** 2500 Fluid Power Pump C 0.292:1 1000 4400 400 Tachometer CC 0.343:1 7 50 --- C - Clockwise: CC – Counterclockwise, facing engine pad * - Maximum starter torque is 550 lb-ft. The shear section will fracture at 850 - 0 + 100 lb. ft. ** - Maximum torque when used as a starter is 4920 lb-in. NOTE 7. Power setting, power checks, and control of engine output in all operations is to be based upon P&W engine charts referring to turbine discharge section gas pressures. Pressure probes are included in the engine assembly for this reason. NOTE 8. These engines meet FAA requirements for adequate tu rbine disk integrity and rotor blade containment and do not require external armoring. These engines have demonstrated satisfactory operation in icing conditions as defined in Civil Air Regulations (Amended August 25, 1955) 4b.1(b)7 and 8. NOTE 9. DELETED. NOTE 10. The maximum continuous st atic thrust at sea level at 29oF (JT8D-1, -1A, -1B, -7, -7A, -7B), 69oF (JT8D-5), 26oF (JT8D- 9, -9a), 21oF (JT8D-11) and 30oF (JT8D-15, -15A, -17, -17A, -17R, -17AR) temperature and below is 14,000 lbs. (JT8D-1, -1A, -1B, -7, -7A, -7B), 12,250 lbs. (JT8D-5), 14,500 lbs. (JT8D-9, -9A), 15,000 lbs. (JT8D-11), 15,500, lbs. (JT8D-15, -15A), 16,000 lbs. (JT8D-17, -17A), and 17,400 lbs. (JT8D-17R, -17AR), respectively. The engine installation and operating manual should be consulted for variation in thrust between standard and 29oF (JT8D-1, -1A, - 1B, -7, -7A, -7B), 26oF (JT8D-9, -9A), 21oF (JT8D-11), 30oF (JT8D-15, -15A), 39oF(JT8D-17, -17A), 19oF (JT8D-17R, -17AR). NOTE 11. Fuels approved for these engines are listed in FAA approved P&W Service Bulletin No. 2016 and its later revisions. Approved fuel additives and their allowable concentrations are also listed in P&W Service Bulletin No. 2016 and its later revisions. NOTE 12. The following oils are eligible for these engine: P&W Service Bulletin No. 238 lists approved brand oils. TCDS E2EA PAGE 9 NOTE 13. The above models incorporate the following general characteristics: JT8D Model Characteristics JT8D-1 Basic model. JT8D-1A Same as -1 except for increased tu rbine outlet gas temperature limits with the incorporation of improved engine parts. JT8D-1B Same as -1A except for increased tu rbine outlet gas temperature limits with the incorporation of improved engine parts. JT8D-5 Same as -1 except for minor diffe rences due to installation requirements, reduced ratings and increased disk life. The D-5 engine may be operated at D-1 takeoff ratings and limitations for engine-out emergency use during takeoff and/or aborted landing procedures only. JT8D-7 Same as -1 except 14,000 lb. takeoff static thrust at sea level flat rated to 84oF ambient temperature and other minor altitude thrust increases with the incorporation of improved engine parts. JT8D-7A Same as -7 except for increased tu rbine outlet gas temperature limit with the incorporation of improved engine parts. JT8D-7B Same as -7A except for increased tu rbine outlet gas temperature limits with the incorporation of improved engine parts. JT8D-9 Same as -7 except 14,500 lb. takeoff static thrust at sea level flat rated to 84oF ambient temperature and other minor altitude thrust increases with the incorporation of improved engine parts. JT8D-9A Same as -9 except for increased tu rbine outlet gas temperature limits with the incorporation of improved engine parts. JT8D-11 Same as -9 except for 15,000 lb. takeo ff static thrust at sea level flat rated to 84oF ambient temperature with the incorporation of improved engine parts. JT8D-15 Same as -11 except 15,500 lb. takeoff static thrust at sea level flat rated to 84oF ambient temperature and other minor altitude thrust increases with the incorporation of improved engine parts. JT8D-15A Same as -15 except reduced fuel consumption by incorporation of improved engine parts. JT8D-17 Same as -15 except 16,000 lb. takeoff static thrust at sea level flat rated to 84oF ambient temperature and other minor altitude thrust increases with the incorporation of improved engine parts. JT8D-17A Same as -17 except reduced fuel consumption by incorporation of improved engine parts. JT8D-17R Same as -17 except 16,400 lb. normal tak eoff static thrust at sea level flat rated to 77oF ambient temperature, 17,400 lb. maximum takeoff static thrust at sea level flat rated to 77oF ambient temperature and a takeoff thrust reset mechanism incorporated in the fuel control along with improved engine parts. JT8D-17AR Same as -17R except reduced fuel consumption by incorporation of improved engine parts. NOTE 14. Certain engine parts are life limited. These limits are listed in the FAA-approved Pratt & Whitney JT8D Series Turbofan Engine Manual, Part No. 481672, Time Limit Section. NOTE 15. The following engines meet the February 1, 1974, smoke and emission requirements of SFAR-27: 1. All JT8D-11, -15, -15A, -17, -17A, -17R, and -17AR engines. 2. JT8D-1, -1A, -1B, -7, -7A, -7B, -9, and -9A engines modified in accordance with Pratt & Whitney Engineering Change 197707 or Service Bulletins 2417 or 2531. The following engines meeting the January 1, 1975, fuel venting emission requirements of SFAR-27: 1. All JT8D-15A, -17, -17A, -17R, and -17AR engines. 2. JT8D-1, -1A, -1B, -7, -7A, -7B, -9, -9A, -11, and -15 engines modified in accordance with Pratt & Whitney Engineering Change 275159 or Service Bulletin 3757. TCDS E2EA PAGE 10 NOTE 16. A takeoff thrust setting limited to the normal takeoff rating of 16,400 lb. static thrust at sea level, flat rated to 77oF ambient temperature has been established for normal takeoff operation. When the automatic reset mechanism in the fuel control is utilized, operation to the normal takeoff operating limits will prevent the engine from exceeding the maximum takeoff rating operating limits when the reset mechanism is actuated. The time limit at the normal takeoff rating is 5 minutes and shall include any time accumulated at the maximum takeoff rating. NOTE 17. DELETED. NOTE 18. Turbine outlet gas temperature thermocouple box P/N 792863, cable assemblies P/N 792864 or P/N 798380, and turbine discharge gas pressure averaging probe assemblies P/N 793272 or P/N 793274 should be used for JT8D-15A, -17A, and -17AR engines and for JT8D-11 engines that have incorporated P&W Service Bulletin No. 5455. NOTE 19. The 5 minute takeoff time may be extended to 10 minutes for one engine inoperative or shutdown for engines which have incorporated all the features specified in P&W Service Bulletin Numbers 5514, 5643 and Alert Service Bulletin Number 6196. ----END----