# TCDS E-290: Pratt & Whitney Division - Type: Type certificate data sheet - Status: Current - Holder: Pratt & Whitney Division - Revision: 15 - Revised: September 6, 1967 - Product: Engine - Certification basis: CAR 13 - Data sheet PDF: https://openairdocs.org/files/sha256/1c/46/1c4696f895d3ce6ddf5cdd82d085387ced2d65bac88b68460a121179b4b342bd - FAA DRS: https://drs.faa.gov/browse/excelExternalWindow/14218F17E8459A128525670D0061AE8D.0001 - Page: https://openairdocs.org/tcds/E-290 ## Models (4) As the data sheet lists them. - JT3C-7 - JT3C-12 - JT3C-6 - JT3C-4 ## 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. 15 15 15 15 Reformatted 11/93. FEDERAL AVIATION ADMINISTRATION E-290-15 PRATT & WHITNEY Turbo Wasp JT3C-4 JT3C-6 JT3C-7 JT3C-12 September 6, 1967 TYPE CERTIFICATE DATA SHEET NO. E-290 Engines of models described herein conforming with this data sheet (which is a part of type certificate No. 290) 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 Civil Air Regulations provided they are installed, operated, and maintained as prescribed by the approved manufacturer's manuals and other approved instructions. Manufacturer Pratt & Whitney Aircraft Division of United Aircraft Corporation East Hartford, Connecticut Model Turbo Wasp JT3C-4 JT3C-6 JT3C-7 JT3C-12 Type Turbojet, Dual Axial, - - - - - - 16 stage compressor, 3 stage turbine and 8 cannular combustion chambers Ratings (See NOTE 11) Maximum continuous static thrust at sea level, lb. 9500 10,000 10,000 11,500 Takeoff static thrust at sea level, lb. dry (5 minutes) 11,200 11,200 12,000 13,000 with water injection (2-1/2 minutes) 12,500 13,500  - - Fuel control Hamilton JFC-12 - - Hamilton JFC-25 - - Fuel See Note 14 - - - - - - Fuel pump Chandler Evans 9400 two- - - Chandler Evans 9430 - - stage Air bleed governor Holley A 12110 - - Holley A 12115 - - Oil (See Note 15) Synthetic type conforming - - - - - - to P&WA 521 as revised. Principal Dimensions: Length, In. (maximum including front- mounted compressor bleed control) 138.97 - - 137.38 - - Width 38.9 - - - - - - Height 46.7 - - - - - - Weight (dry), lb. (includes basic engine with all essential access., but excluding starter, exhaust nozzle, power source for the ignition system, and oil supply tank) 4234 - - 3495 3550 Center of gravity, in. Aft of front mount area center line 18.34 - - 20.27 20.30 Below engine center line 1.20 - - - - 1.43 Ignition GLA 18200-11 with two spark igniters: Champion AA-15S, AA-35S, AA-37S or AA-72S; BG 12625; AC JB-57, JC-571 or JB-3 - - GLA 40355B with two spark igniters: Champion AA-15S, AA-35S, AA-37S or AA-72S; BG 12625; AC JB-57, JC-571 or JB-3. - - NOTES 1 thru 14 1 thru 14 1 thru 14 1 thru 14 "- -" indicates "same as previous model" " " indicates "not applicable" E-290, Rev 15 Page 2 Certification basis CAR 13, effective June 15, 1956, as amended by 13-1, 13-2, and 13-3. Type Certificate No. 290 issued March 15, 1957, for JT3C-4; JT3C-6 added June 19, 1957; JT3C-7 added May 26, 1959; JT3C-12 added April 14, 1961. Date of Application for Type Certificate September 18, 1956. Production basis Production Certificate No. 2. NOTE 1. Maximum permissible engine operating speeds for the engine rotors are as follows: JT3C-4, -6 JT3C-7 JT3C-12 Low pressure compressor (N1) 7000 6850 - - High pressure compressor (N2) 9950 - - 10150 NOTE 2. Maximum permissible temperatures are as follows: Turbine outlet gas temperatures: Takeoff (5 minutes) (630°C) 1166°F (620°C) 1148°F (665°C) 1229°F Maximum continuous (560°C) 1040°F (540°C) 1004°F (600°C) 1112°F Maximum for acceleration (2 minutes) (650°C) 1202°F - - (695°C) 1283°F Starting: ground (450°C) 842°F - - - - air (500°C) 932°F - - - - Oil inlet (121°C) 250°F - - (121°C) 250°F continuous operation (143°C) 290°F Ten (10) min. Ground operation only External engine components, maximum temperature (Limiting temperature of specific components are as specified in pertinent engine installation and operating manual or P&WA Installation Handbook.) 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 55 p.s.i. above absolute ambient atmospheric pressure. Oil pressure At idle, 30 p.s.i. minimum Operating range, 40 to 50 p.s.i. NOTE 4. Maximum permissible air bleed extraction is as follows: Low compressor: JT3C-4, C-6 JT3C-7 JT3C-12 1% from idle to M.C. 2.75% at idle reducing to 2.0% at M.C. 2.75% at idle reducing to 2.4% at M.C. 2.2% at takeoff speed 2.2% at takeoff speed 1.2% at takeoff speed 1.8% intermittent for thermal anti-icing High compressor: JT3C-4, C-6, C-7 JT3C-12 5.5% from idle to M.C. 5.5% at idle reducing to 4.5% at M.C. 2.0% at takeoff speed 2.4% at takeoff speed 3.1% for three-engine takeoff 3.1% for three-engine takeoff E-290 Page 3 NOTE 5. These ratings are based upon static test stand operation under the following conditions: Compressor inlet air at 59°F and 29.92 in.Hg. Jet nozzle and exhaust pipe per P&WA Dwg. 279401 P&WA bellmouth on air inlet No aircraft accessory loads or air extraction No anti-icing airflow Turbine outlet gas temperature limits not exceeded At engine data plate N2 r.p.m. NOTE 6. The following accessory drive provisions are incorporated: Speed Ratio Direction of to Torque (in. lb.) Overhang Drive Rotation* Turbine Shaft Continuous Static (in. lb.) Low Rotor Tachometer C .679:1 7 50 - High Rotor Starter C .700:1 ** ** 625 Generator C .678:1 1000 4400 625 Fluid power pump*** C .355:1 1000 4400 400 Tachometer C .421:1 7 50 - * "C" - Clockwise when viewed facing pad ** Max. starter torque 550 pound-feet. Shear section should withstand 1100 pound-feet. *** May be used as generator drive when proper shaftgear is installed at same ratio and overhang as other generator drive. NOTE 7. The following optional items, when used, increase the basic engine weight as follows: P&WA water regulator, piping and brackets. JT3C-4 40 lb. JT3C-6 60 lb. P&WA engine-mounted oil tank, Part No. 315183 25 lb. NOTE 8. For water injection operation, the following water flow rates are utilized: JT3C-4 JT3C-6 Constant water flow - lb./min. 250 667 Feed pressure - p.s.i. 150 - 225 350 - 437 Water alone is specified and should contain no more than 10 (PPM) parts per million impurities. Use of water with appreciable mineral content will cause gradual dry power deterioration from deposits on the compressor blades and result in the need for more frequent speed trimming and engine cleaning. Use of water is limited to takeoff operation up to an altitude of 9,000 feet, at 11°F (minus 12°C) or above, ambient temperature, water injection to the engine diffuser only, and at 40°F (5°C) or above, ambient temperature, water injection to the compressor inlet and engine diffuser. NOTE 9. Power setting, power checks, and control of engine output in all operations is to be based upon P&WA engine charts referring to turbine discharge section gas pressures. Pressure probes are included in the engine assembly for this reason. NOTE 10. These engines meet FAA requirements for adequate turbine disc integrity and rotor blade containment and do not require external armoring. These engines have demonstrated satisfactory operation in icing con- ditions as defined in CAR 4b.1(b)7 and 8. NOTE 11. (a) Maximum Continuous Thrust. Maximum continuous static thrust at sea level permitted as follows: JT3C-6: At -22°F ambient temperature and below, 13,500 lb. JT3C-7: At 41°F ambient temperature and below, 12,000 lb. JT3C-12: At 25°F ambient temperature and below, 13,000 lb. The pertinent engine installation and operating manual of P&WA Installation Handbook should be consulted for variation in thrust between standard day and the ambient temperature stated above. (b) Takeoff Thrust. Takeoff thrust (dry) permitted as follows: E-290, Rev 15 Page 4 JT3C-6: Below 11°F inlet temperature, 13,500 lb. for 5 minutes. JT3C-7: Below 43.5°F inlet temperature, 12,500 lb. for 5 minutes. Takeoffs using both water injection and dry takeoff power are limited to a maximum period of 5 minutes including operation with water injection for not more than 2 1/2 minutes. NOTE 12. The serial number suffix "B" designates engine for the Boeing 707 aircraft and the suffix "D" designates engines for the Douglas DC-8 aircraft. Differences in these engines involve differences in the routing of external engine lines. NOTE 13. The above engines incorporate the following detailed characteristics: JT3C Model C-4 Basic model. C-6 Same as C-4 except for increased wet takeoff and maximum continuous ratings. C-7 Same as C-6 except for increased dry takeoff rating, decreased weight and no water injection. C-12 Same as C-7 except for increased ratings with improved engine parts. NOTE 14. JP-1, JP-4, and JP-5 fuels conforming to P&WA Specification No. 522 and later revisions may be used separately or mixed in any proportions without adversely affecting the engine operation or power out- put. 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% volume is approved for use in fuels conforming to P&WA Specification No. 522D. 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 p.p.m. in approved for use in fuels conforming to P&WA Specification No. 522E or later revision. NOTE 15. P&WA Turbojet Engine Service Bulletin No. 238 approved brand oils. NOTE 16. Certain engine parts are life limited. These limits are listed in the FAA-Approved Pratt & Whitney Aircraft JT3C-6 Turbojet Engine Overhaul Manual Part No. 363433, Fits and Clearances Section and the FAA-Approved Pratt & Whitney Aircraft JT3C-7 and -12 Turbojet Engines - Overhaul Manual Part No. 395954, Fits and Clearances Section. ....END.... ``` ## ADs (9, in force first) - [AD 66-21-01](https://openairdocs.org/ad/66-21-01): Rotor Disc Spacer Assemblies · Pratt & Whitney Division JT3C-12 and JT3C-7. Effective Sep 30, 1966 - [AD 66-16-06](https://openairdocs.org/ad/66-16-06): Rotor Disc Spacer Assemblies · Pratt & Whitney Division JT3C-12 and JT3C-7. Effective Jul 2, 1966 - [AD 64-05-05](https://openairdocs.org/ad/64-05-05): Throttle Valve Assemblies · Pratt & Whitney Division JT3C-12, JT3C-7, JT3D-1 and 17 more. Effective Feb 27, 1964 - [AD 62-09-04](https://openairdocs.org/ad/62-09-04): Compressor Rotor Blades · Pratt & Whitney Division JT3C-12 and JT3C-7. Effective Apr 19, 1962 - [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 - [AD 59-10-09](https://openairdocs.org/ad/59-10-09): Turbine Blade · Pratt & Whitney Division JT3C-6 - [AD 60-22-02](https://openairdocs.org/ad/60-22-02): Combustion Chamber Outer Cases · Pratt & Whitney Division JT3C-6 - [AD 60-23-04](https://openairdocs.org/ad/60-23-04): Gearshaft · Pratt & Whitney Division JT3C-6 and JT3C-7 - [AD 62-17-06](https://openairdocs.org/ad/62-17-06): Compressor Rotor Disc · Pratt & Whitney Division JT3C-12 ## Registered aircraft by registry model (OpenAirDocs) - [Pratt & Whitney JT3C-12](https://openairdocs.org/engine/pratt-whitney-jt3c-12): 0 aircraft (registry code 51716) - [Pratt & Whitney JT3C-4](https://openairdocs.org/engine/pratt-whitney-jt3c-4): 0 aircraft (registry code 51713) - [Pratt & Whitney JT3C-6](https://openairdocs.org/engine/pratt-whitney-jt3c-6): 0 aircraft (registry code 51714) - [Pratt & Whitney JT3C-7](https://openairdocs.org/engine/pratt-whitney-jt3c-7): 0 aircraft (registry code 51715) ## STCs approved under this data sheet (2) - [STC SE106SO](https://openairdocs.org/stc/SE106SO): Alternate engine thermocouple fire seal on B-720 engine firewalls.. Eastern Airlines Inc - [STC SE2CE](https://openairdocs.org/stc/SE2CE): Transducer in-flight maintenance and performance recorder.. Trans World Airlines Inc --- 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.