# TCDS E15EA: Erickson Incorporated DBA Erickson Air-Crane - Type: Type certificate data sheet - Status: Current - Holder: Erickson Incorporated DBA Erickson Air-Crane - Revision: 11 - Revised: November 19, 2014 - Product: Engine - Certification basis: Part 33 - Registered aircraft: 35, by the registry models matched to it (OpenAirDocs) - Data sheet PDF: https://openairdocs.org/files/sha256/4f/37/4f370ca2cac7f6f8308c9916e32cc5e6c238240de873540050b76156c6dae0e4 - FAA DRS: https://drs.faa.gov/browse/excelExternalWindow/BFEB6454112839DD86257D96004D59BA.0001 - Page: https://openairdocs.org/tcds/E15EA ## Models (2) As the data sheet lists them. - JFTD12A-4A (T73P-1) - JFTD12A-5A (T73-P-700) ## What the data sheet says From the PDF's text layer, line by line; tables lose their columns. The PDF is the record. ```text * PAGE 1 2 3 4 REV. 10 7 4 8 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 E15EA TCDS NUMBER E15EA REVISION: 11 DATE: November 19, 2014 ERICKSON INCORPORATED MODELS: (T73-P-1) JFTD12A-4A (T73-P-700) JFTD12A-5A Engines of models described herein conforming with this data sheet (which is a part of Type Certificate Number E15EA) 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 Erickson Incorporated, DBA Erickson Air-Crane 3100 Willow Springs Road P.O. Box 3247 Central Point, Oregon 97502-0010 TYPE CERTIFICATE (TC) RECORD: Pratt & Whitney Division transferred TC E15EA to Erickson Air-Crane on September 6, 2013. I. MODELS JFTD12A-4A (T73-P-1) JFTD12A-5A (T73-P-700) TYPE Free Turbine Drive Nine stage axial compressor and eight can-annular combustion chambers and two stage gas generator turbine plus two stage free turbine RATINGS At nominal free turbine operating speed of 9000 rpm Maximum continuous at sea level, hp Takeoff at sea level, (5 min.) hp. 30 minute OEI rating at sea level, hp. 4000 4500 4500 4430 4800 4800 Fuel control Hamilton Standard JFC56-4 JFC56-6 Fuel pump Goodrich Corp 50466A2 - - Fuel See NOTE 11 - - Oil (See NOTE 12) Synthetic type conforming with PWA Spec 521 as revised - - Principal dimensions, in. Length (maximum including nose cone) Diameter (maximum) Radial projection (maximum) 107.0 30.0 22.3 - - - - - - Weight (dry), lb. (includes basic engine with all essential accessories but excluding oil tank, fuel-oil cooler, fuel heater system, inlet bullet nose cone, starter, exhaust duct extension and power source for the ignition system.) 920 (966 for T73-P-1) 935 (981 for T73-P-700) TCDS E15EA PAGE 2 I. MODELS JFTD12A-4A (T73-P-1) JFTD12A-5A (T73-P-700) Center of gravity, in. Aft of rear flange of diffuser case Below engine center line 16.3 1.3 16.1 - - Ignition Two General Laboratories Associates exciters Model 40367 or BF Goodrich Aerospace Simmonds Precision exciters Model 43140, with two spark igniters, Champion FHE 151; or General Laboratories Associates exciters Model 42145 and 42194 or BF Goodrich Aerospace Simmonds Precision exciters Model 42145 and 43141, with two spark igniters, Champion AA-335 - - NOTES 1 through 15 - - CERTIFICATION BASIS Federal Aviation Regulations (FAR) Part 33, effective February 1, 1965, including Amendments 33-1 through 33-2. TYPE CERTIFICATE E15EA MODELS APPLICATION DATE ISSUED/AMENDED JFTD12A-4A MAR 30, 1966 FEB 14, 1967 T73-P-1 DEC 15, 1967 JAN 19, 1968 JFTD12A-5A OCT 30, 1968 JAN 29, 1970 T73-P-700 NOV 20, 1970 NOV 24, 1970 NOTES NOTE 1. Maximum permissible engine operating speeds (rpm) for the engine rotors are as follows: Free Turbine Gas Generator Takeoff 9,500 16,700 30 Minute OEI Rating 9,500 16,700 Maximum Continuous 9,500 16,700 Transient (30 seconds) 9,600 --- NOTE 2. Maximum permissible temperatures are as follows: Free turbine inlet gas temperatures: JFTD12A-4A(T73-P-1) JFTD12A-5A(T73-P-700) Takeoff 688oC (1270oF) 720oC (1328oF) 30 Minute OEI Rating 688oC (1270oF) 720oC (1328oF) Maximum Continuous 655oC (1211oF) 675oC (1247oF) Maximum for Acceleration 688oC (1270oF) 720oC (1328oF) Starting 525oC (977oF) - - - - Oil Inlet 121oC (250oF) - - - - External engine components, max. temperature (limiting temperatures of specific components are as specified in the engine installation and operating manual.) TCDS E15EA PAGE 3 NOTE 3. Fuel and oil pressure limits are as follows: Fuel pressure: At inlet to engine system pump, 7.5 p.s.i. above absolute fuel vapor pressure or 1.5 p.s.i. below fuel tank pressure, whichever is higher, with a maximum of 50 p.s.i. above absolute ambient atmosphere pressure. Oil pressure: At ground idle - 20 p.s.i. minimum Operating range - 45 to 55 p.s.i. NOTE 4. Maximum permissible air bleed extraction is as follows: Percent of primary engine airflow: Idle to maximum continuous - 2.0% Maximum continuous to takeoff - 2.0% NOTE 5. The ratings are based on static test stand operation under the following conditions: Compressor inlet air at 59oF and 29.92 in. Hg. P&WA bellmouth on air inlet No aircraft accessory loads or air extraction No anti-icing airflow Free turbine inlet gas temperature limits and engine rotor speed limits not exceeded. NOTE 6. The following accessory drive provisions are incorporated: SPEED RATIO TORQUE (in. - lb.) OVERHANG DRIVE ROTATION* TO TURBINE SHAFT CONTINUOUS STATIC (in-lb) Tachometer (Gas Generator) Tachometer (Free Turbine) Starter-Generator ** Fluid Power Pump CC C C C .264:1 .464:1 .435:1 .263:1 7 7 500 600 50 50 1260 2700 ___ ___ 500 350 * C - Clockwise, CC - Counterclockwise ** Above limits apply only to generator operation. Maximum continuous starter torque - 1260 in.-lb. Engine starter drive sheer section capable of withstanding a static torque up to 2520 in.-lb. NOTE 7. Additional equipment for JFTD12A-4A and -5A models: included as standard equipment on T73-P-1 and T73-P- 700. Pounds added weight Oil Tank 14.0 Fuel-Oil Cooler 15.0 Fuel Heater 14.0 Inlet Bullet Nose Cone 3.0 NOTE 8. Power setting, power checks, and control of engine output in all operations is to be based upon P&WA engine charts referring to free turbine inlet section gas pressures. Pressure probes are included in the engine assembly for this reason. NOTE 9. This engine meets FAA requirements for operation in icing conditions, for adequate turbine disk integrity and rotor blade containment and does not require external armoring. TCDS E15EA PAGE 4 NOTE 10. The maximum continuous static power at sea level at 17oF (JFTD12A-4A, T73-P-1) and 38oF (JFTD12A-5A, T73- P-700) ambient temperature and below is 4500 hp (JFTD12A-4A, T73-P-1), and 4800 hp (JFTD12A-5A, T73-P- 700) respectively. The engine installation and operating manual should be consulted for variation in power between standard and 17oF (JFTD12A-4A, T73-P-1), and 38oF (JFTD12A-5A, T73-P-700). NOTE 11. JP-1, JP-4 and JP-5 fuels conforming to P&WA Specification No. 522 or P&WA Service Bulletin 2016 may be used separately or mixed in any proportions without adversely affecting the engine operation or power output. No fuel control adjustment is required when switching fuel types. Phillips PFA-55MB anti-icing additive at the use concentration not in excess of 0.15% by volume is approved for use in fuels conforming to P&WA Specification No. 522 or P&WA Service Bulletin 2016. For the T73-P-1 and T73-P-700 fuel conforming to MIL-I-5161 E Grade I or II may be used. NOTE 12. P&WA Turbojet Engine Service bulletin No. 238 lists approved brand oils. For the T73-P-1 and T73-P-700, in addition to the oils listed in PWA Turbojet Engine Service Bulletin No. 238, oil conforming to MIL-I-23699A or MIL-I-7808G may be used. NOTE 13. The military T73-P-1 and T73-P-700 engines are identical to the JFTD12A-4A and JFTD12A-5A respectively and are eligible for use in certificated aircraft; However, these models may not have been operated and maintained in accordance with the Federal Aviation Regulations contained in CFR Title 14. Use of T73-P-1 and T73-P-700 engines or engine parts in commercial service is prohibited unless specific prior FAA (Engine Certification Office, ANE-140) approval is granted. NOTE 14. Certain engine parts are life limited. These limits are listed in the FAA - Approved Pratt & Whitney Aircraft JT12A and JFTD12A Overhaul Manual, Part No. 435108, Table of Limits Section. NOTE 15. The following models incorporate the following general characteristics: JFTD12A Model Characteristics -4A Basic Model -5A Same as -4A except for increased takeoff and maximum continuous ratings with the incorporation of improved engine parts. ----END---- ``` ## ADs (2, in force first) - [AD 97-02-13](https://openairdocs.org/ad/97-02-13): Disk rupture · Pratt & Whitney Division JFTD12A-4A (T73P-1) and JFTD12A-5A (T73-P-700). Effective Apr 4, 1997 - [AD 71-24-05](https://openairdocs.org/ad/71-24-05): Compressor Rotor Discs · Pratt & Whitney Division JFTD12A-4A (T73P-1), JFTD12A-5A (T73-P-700), JT12A-6 and 2 more. Effective May 31, 1974 ## Registered aircraft by registry model (OpenAirDocs) - [Pratt & Whitney JFTD12A series](https://openairdocs.org/engine/pratt-whitney-jftd12a-series): 15 aircraft (registry code 52047) - [Pratt & Whitney JFTD12A-4A](https://openairdocs.org/engine/pratt-whitney-jftd12a-4a): 12 aircraft (registry code 51502) - [Pratt & Whitney JFTD12A-5A](https://openairdocs.org/engine/pratt-whitney-jftd12a-5a): 8 aircraft (registry code 51504) --- OpenAirDocs.org is an independent research project of [Contrail Labs](https://contraillabs.com/). It is not affiliated with the FAA or the NTSB. Source documents are U.S. government works in the public domain.