# TCDS 1E9: Erickson Incorporated DBA Erickson Air-Crane - Type: Type certificate data sheet - Status: Current - Holder: Erickson Incorporated DBA Erickson Air-Crane - Revision: 17 - Revised: August 6, 2014 - Product: Engine - Registered aircraft: 17, by the registry models matched to it (OpenAirDocs) - Data sheet PDF: https://openairdocs.org/files/sha256/8a/89/8a89548552bbd29e904509a681840afc7b76b07b4df98ea5ced779274be4495b - FAA DRS: https://drs.faa.gov/browse/excelExternalWindow/6A0CCA823785AE6386257D2D005FDEC0.0001 - Page: https://openairdocs.org/tcds/1E9 ## Models (4) As the data sheet lists them. - JT12A-6A - JT12A-6 - JT12A-8 - J60-P-5B ## 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 No. 1 2 3 4 Rev. No. 17 14 14 14 LEGEND: "- -" INDICATES "SAME AS PRECEDING MODEL" "---" NOT APPLICABLE U.S. DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION TYPE CERTIFICATE DATA SHEET E15EA TCDS NUMBER 1E9 REVISION: 17 DATE: August 6, 2014 ERICKSON INCORPORATED MODELS: (Turbo Wasp) JT12A-6 JT12A-6A JT12A-8 J60-P-5B Engines of models described herein conforming with this data sheet (which is a part of Type Certificate Number 1E9) 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 1E9 to Erickson Air-Crane on September 6, 2013. Models Turbo Wasp JT12A-6, JT12A-6A/J60-P-5B, JT12A-8 Type Turbojet, nine-stage axial compressor, two-stage turbine and eight cannular combustion chambers Ratings JT12A-6 JT12A-6/J60-P-5B JT12A-8 Maximum continuous static thrust at sea level, pounds 2400 2570 3000 Takeoff static thrust at sea level (5 minutes) pounds 3000 - - 3300 Components Fuel control Holley R-167 or Hamilton Standrad JFC46 (-3 for Lockheed / -4 for North American) Hamilton Standard JFC46 (-10 for Lockheed / -8 for North American) Fuel Pump Goodrich Corp. 50466A2 Goodrich Corp. 50466A2 Ignition General Labratories Associates (GLA) Exciter Model 40367 with two spark ignitors, Champion FHE 151: or GLA Exciter Models 42145 and 42194 with two spark ignitors, Champion AA-338 Fuel See Note 11 Oil (see Note 12) Synthetic type conforming with Pratt & Whitney (PWA) Specification 521, as revised Principal Dimensions Length includes nose drive cover and the aft turbine bearing housing case Length, maximum 78.3 inches - - - - Length, minimum 22.1 inches - - - - Weight, dry Includes basic engine with all essential accessories but excluding starter, propelling nozzle, power source for ignition system and oil supply tank, fuel oil cooler and fuel heater 448 pounds - - 468 pounds 1E9 2 JT12A-6 JT12A-6A/J60-P-5B JT12A-8 Center of Gravity (dry weight) Forward of rear flange of diffuser case 1.9 inches - - - - Below engine center line 2.3 inches - - - - Notes 1 through 15 below Certification Basis CAR 13, effective June 15, 1956, as amended by 13-1, 13-2, and 13-3 Model Type Certificate 1E9 Applied for Issued Cancelled Reinstated JT12A-6 12/29/59 07/28/60 JT12A-6A 09/20/62 09/21/62 JT12A-8 12/07/65 08/17/66 J60-P-5B 11/29/66 12/07/66 11/06/87 02/22/90 NOTES NOTE 1. For the JT12A-6, JT12A-6A, and the JT12A-8, the maximum permissible engine operation speed at takeoff and maximum continuous for the engine rotor is 16,700 rpm. NOTE 2. MAXIMUM PERMISSIBLE TEMPERATURES JT12A-6 JT12A-6A/J60-P-5B JT12A-8 Turbine outlet gas temperature Takeoff (5 minutes) 677°C/1250°F - - 718°C/1325°F Maximum continuous 577°C/1070°F - - 655°C/1210°F Maximum for acceleration (2 min) 677°C/1250°F - - 718°C/1325°F Starting 525°C/ 977°F - - 525°C/ 977°F Oil inlet 121°C/ 250°F - - 121°C/ 250°F External engine components Limiting temperatures of specific components are as specified in the engine installation and operating manual. NOTE 3. FUEL AND OIL PRESSURE LIMITS Fuel pressure At inlet to engine system pump, 7.5 psi above absolute fuel vapor pressure or 1.5 psi below fuel tank pressure, whichever is higher, with a maximum of 50 psi above absolute ambient atmospheric pressure. Oil pressure At idle, 35 psi minimum; operating range, 40 to 50 psi. NOTE 4. MAXIMUM PERMISSIBLE AIR BLEED EXTRACTION Percent of total engine air flow Normal operation Idle to maximum continuous 4.0 percent Maximum continuous through takeoff 3.0 percent One engine out operation Idle to maximum continuous 4.4 percent Maximum continuous through takeoff 3.7 percent NOTE 5. Ratings are based on static test stand operation under the following onditions. Compressor inlet air at 59°F and 29.92 in. Hg. Jet nozzle and exhaust pipe: For the JT12A-6/JT12A-6A/J60-P-5B, per PWA Drawing Number 403201 For the JT12A-8. Per PWA Drawing Number 566001 PWA bellmouth on air inlet No aircraft accessory loads or air extraction No anti-icing airflow Turbine outlet gas temperature limit not exceeded 1E9 3 NOTE 6. ACCESSORY DRIVE PROVISIONS DRIVE Rotation Speed Ratio to Turbine Shaft Torque (in.-lb.) Overhang (in.-lb.) Continuous Static Tachometer CCW (1) .264:1 7 50 - - - Optional Tachomete r CCW .262:1 7 50 - - - Starter-generator (2) CC .435:1 500 1260 500 Fluid power pump CC .263:1 600 2700 350 (1) CCW = Counterclockwise / CC = Clockwise (2) Limits apply only to generator operation Maximum Continuous starter torque – 1260 inch-pound Engine starter drive shear section capable of withstanding a static torque up to 2520 inch-pound NOTE 7. ADDITIONAL EQUIPMENT ADDED WEIGHT Oil tank 14.0 pounds Fuel-oil cooler 10.0 pounds Fuel heater 14.0 pounds Fuel control cross shaft 2.0 pounds for the JT12A-6 & JT12A-6A 2.5 pounds for the JT12A-8 Inlet bullet nose cone 3.0 pounds NOTE 8. Power setting, power checks, and control of engine output in all operations are to be based on PWA engine charts referring to turbine discharge section gas pressures. Pressure probes arc included in the engine assembly for this reason. NOTE 9. This engine meets FAA requirements for adequate turbine disc integrity and rotor blade containment and does not require external armoring. NOTE 10. MAXIMUM CONTINUOUS STATIC THRUST AT SEA LEVEL Model Ambient Temperature Thrust JT12A-6 -3°F and below 3000 pounds JT12A-6A 12°F and below 3000 pounds J60-P-5B 12°F and below 3000 pounds JT12A-8 23°F and below 3300 pounds The engine installation and operating manual should he consulted for variation in thrust between standard day and the temperatures given above. NOTE 11. FUELS: JP-1, JP-4, and JP-5 fuels conforming to PWA Specification No. 522 and later revisions may he used separately or mixed in any proportions without adversely affecting engine operation or power output. No fuel control adjustment is required when switching fuel types. ANTI-ICING ADDITIVE: Phillips PFA-55MB anti-icing additive at the use concentration not in excess of 0.15 percent by volume is approved for use in fuels conforming to PWA Specification No. 522D. ANTI-ICING ADDITIVE: Shell ASA-3 anti-static additive at a concentration that will provide not in excess of 300 conductivity units, which is approximately equivalent to 1 ppm, is approved for use in fuels conforming to PWA Specification No. 522E or later revision. BIOCIDE ADDITIVIE: SOHIO Biobor JF biocide additive at a use concentration not in excess of 20 ppm elemental boron (270 ppm total additive) is approved for use in fuel conforming to PWA Specification No. 522. NOTE 12. PWA Turbojet Engine Service Bulletin No. 238 lists approved brand oil. NOTE 13. JTI2A-6 engines which have been modified in accordance with PWA Engineering Change No. 110181 (Aves Kit) should have the suffix letter “A” added to the engine serial number. All JT12A-6A are so 1E9 4 modified. NOTE 14. MODEL GENERAL CHARACTERISTICS JT12A-6 Basic model JT12A-6A Same as JT 12A-6 except for increased maximum continuous rating with improved engine parts. JT12A-8 Same as JT12A-6A except for increased ratings with improved engine parts. J60-P-5B See Note 15 below. NOTE 15. The J60-P-5B turbojet engine is identical to the JT12A-6A engine and is eligible for use in certificated aircraft. When the J60-P-5B is overhauled, it must undergo a parts conformity to ensure that it meets the JT12A-6A engine parts list. At that time, the JP60-P-5B engine data plate should be revised to reflect the JT12A-6A model designation. - END - ``` ## ADs (3, in force first) - [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 - [AD 71-17-06](https://openairdocs.org/ad/71-17-06): Stage 2, 3, 7 and 8 Compressor Rotor Discs · Pratt & Whitney Division J60-P-5B, JT12A-6, JT12A-6A and 1 more. Effective Aug 17, 1971 - [AD 56-06-02](https://openairdocs.org/ad/56-06-02): Cylinder Flange Attaching Stud · Pratt & Whitney Division Double Wasp CA15, Double Wasp CA17, Double Wasp CA18 and 115 more ## Registered aircraft by registry model (OpenAirDocs) - [Pratt & Whitney JT12A-8](https://openairdocs.org/engine/pratt-whitney-jt12a-8): 12 aircraft (registry code 52052) - [Pratt & Whitney JT12A series](https://openairdocs.org/engine/pratt-whitney-jt12a-series): 3 aircraft (registry code 52056) - [Pratt & Whitney JT12A-6](https://openairdocs.org/engine/pratt-whitney-jt12a-6): 2 aircraft (registry code 51703) - [Pratt & Whitney J60-P-5B](https://openairdocs.org/engine/pratt-whitney-j60-p-5b): 0 aircraft (registry code 51705) - [Pratt & Whitney JT12A-6A](https://openairdocs.org/engine/pratt-whitney-jt12a-6a): 0 aircraft (registry code 51704) --- 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.