# TCDS 1E16: General Electric Company - Type: Type certificate data sheet - Status: Current - Holder: General Electric Company - Revision: 15 - Revised: August 21, 2008 - Product: Engine - Certification basis: Part 33, CAR 13 - Registered aircraft: 51, by the registry models matched to it (OpenAirDocs) - Data sheet PDF: https://openairdocs.org/files/sha256/2f/39/2f39847f44a08ce9379baab04896e5aa5b0b023eca89fd18e864f8673ed2d2db - FAA DRS: https://drs.faa.gov/browse/excelExternalWindow/DD03F701FB4C96D6862576E9005F3B1E.0001 - Page: https://openairdocs.org/tcds/1E16 ## Models (7) As the data sheet lists them. - CJ610-8A - CJ610-6 - CJ610-1 - CJ610-5 - CJ610-9 - CJ610-4 - CJ610-8 ## 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. 15 15 14 15 LEGEND: "- -" INDICATES "SAME AS PRECEDING MODEL" "---" NOT APPLICABLE NOTICE: ALL PAGES ARE REFORMATTED. SIG NIFICANT CHANGES, IF ANY ARE BLACK.LINED IN THE L EFT MARGIN U.S. DEPARTMENT OF TRANSPORTATION TCDS NUMBER: 1E16 FEDERAL AVIATION ADMINISTRATION REVISION: 15 TYPE CERTIFICATE DATA SHEET DATE: August 21, 2008 1E16 MODELS: CJ610-1, CJ610-4, CJ610-5, CJ610-6, CJ610-8, CJ610-8A, CJ610-9 Engines of models described herein conforming with this data sheet (which is a part of Type Certificate No. 1E16) 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/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: General Electric Company GE – Aviation 1000 Western Ave Lynn, Massachusetts 01910 Model CJ610-1 CJ610-4 CJ610-5 CJ610-6 Type Turbojet: 8 stage axial flow compressor, 2 stage turbine, annular type combustion chamber Ratings (See NOTE 5) Maximum continuous at sea level, static thrust, lb. 2700 - - 2780 - - Takeoff (5 min.) at sea level, static thrust, lb. 2850 - - 2950 - - Fuel control (See NOTE 14) General Electric Model MFC-2 - - - - - - Fuel pump Chandler-Evans Model 9234 with integral boost. - - - - - - Fuel (See NOTES 7, 8, and 11) Kerosene, JP-4 & JP-5 type fuels conforming to G.E. Jet Fuel Spec. D50TF2, current revision. - - - - - - Oil (See NOTE 11) Oil conforming to G.E. Spec. D50TF1, current revision. - - - - - - Principal dimensions Length, in. (flange to flange) 40.50 - - - - - - Max. dia., in. (max. flange) 17.56 - - - - - - Center of gravity (dry weight) with standard equipment: Aft of front frame flange fwd. face, in. 14.1 16.1 14.1 15.55 Below engine horizontal centerline, in. 1.8 1.7 1.8 1.7 To right of engine vertical centerline, in. 0.6 0.5 0.6 0.5 Weight (dry) lb. (includes as standard equipment basic engine accessories and speed control, oil tank, fuel-oil cooler, ignition system less power source, inlet anti- icing system and exhaust thermocouples, Compressor Spool Rotor on CJ610-6 (SB 72-148) and CJ610-8A (SB 72-154)). 403 393 406 418 Usable oil tank capacity (integral), qts. 3 - - - - - - Ignition (24 - 30 volts D.C.) Capac itor discharge exciter P/Ns 37D401588, 4006T58, 4016T54, 4920T03, or 4026T03 and two igniter plugs P/Ns 37B201652, 37C311124 or 4013T35. - - - - - - NOTES 1 thru 11, 13, 14, & 15 - - - - - - TCDS 1E16 Page 2 of 4 Model CJ610-8 CJ610-8A CJ610-9 Type Turbojet: 8 stage axial flow compressor, 2 stage turbine, annular type combustion chamber Ratings (See NOTE 5) Maximum continuous at sea level, static thrust, lb. 2925 2850 2925 Takeoff (5 min.) at sea level, static thrust, lb. 3100 2950 3100 Fuel control (See NOTE 14) General Electric Model MFC-2 - - - - Fuel pump Chandler-Evans Model 9234 with integral boost. - - - - Fuel (See NOTES 7, 8, and 11) Kerosene, JP-4 & JP-5 type fuels conforming to G.E. Jet Fuel Spec. D50TF2, current revision. - - - - Oil (See NOTE 11) Oil conforming to G.E. Spec. D50TF1, current revision. - - - - Principal dimensions Length, in. (flange to flange) 40.50 - - - - Max. dia., in. (max. flange) 17.56 - - - - Center of gravity (dry weight) with standard equipment: Aft of front frame flange fwd. face, in. 16.0 15.65 14.2 Below engine horizontal centerline, in. 1.7 - - 1.8 To right of engine vertical centerline, in. 0.5 - - 0.6 Weight (dry) lb. (includes as standard equipment basic engine accessories and speed control, oil tank, fuel-oil cooler, ignition system less power source, inlet anti- icing system and exhaust thermocouples, Compressor Spool Rotor on CJ610-6 (SB 72-148) and CJ610-8A (SB 72-154)). 411 433 421 Usable oil tank capacity (integral), qts. 3 - - - - Ignition (24 - 30 volts D.C.) Capac itor discharge exciter P/Ns 37D401588, 4006T58, 4016T54, 4920T03, or 4026T03 and two igniter plugs P/Ns 37B201652, 37C311124 or 4013T35. - - - - NOTES 1 thru 11, 13, 14, & 15 - - - - Certification basis: Date Type Certificate Regulations & Amendments Model Date of Application No. 1E16 Issued/Revised CAR 13 effective June 15, 1956 as CJ 610-1 September 14, 1960 December 6, 1961 amended by 13-1, 13-2, 13-3, 13-4 CJ 610-2B September 13, 1961 December 6, 1961 and 13-5 CJ610-4 November 6, 1963 May 11, 1964 CJ610-5 February 15, 1966 June 30, 1966 FAR 33 effective February 1, 1965 CJ 610-6 February 15, 1966 June 30, 1966 as amended by 33-1, 33-2, and 33-3 CJ610-8 June 27, 1967 January 31, 1968 CJ610-9 June 27, 1967 January 31, 1968 J85-GE-17B November 30, 1967 January 15, 1968 CJ610-2B ⎯⎯⎯⎯⎯⎯ Inactive - May 11, 1964 J85-GE-17B ⎯⎯⎯⎯⎯⎯ Inactive - November 15, 1976 CJ610-8A November 23, 1976 April 13, 1977 Production basis: Production Certificate No. 108 TCDS 1E16 Page 3 of 4 NOTE 1. Maximum permissibl e engine rotor speeds are: Takeoff 16,700 r.p.m. Maximum con tinuous 16,500 r.p.m. NOTE 2. Maximum permissible temperatures (°F). CJ610-1 & -4 CJ610-5 & -6 CJ610-8 & -9 CJ610-8A Takeoff (5 min.) T5 1300 1321 1375 1355 Maximum continuous 1250 1295 1345 1335 Maximum transient (10 seconds) 1440 - - - - - - Maximum transient for starting (5 seconds) 1570 - - - - - - Maximum transient for starting (2 seconds) 1670 - - - - - - Oil reservoir (steady state) 365 - - - - - - (transient 3 minutes) 380 - - - - - - No. 2 and No. 3 bearing scavenge oil 380 - - - - - - Refer to Operating Instructions SEI-188 for time-temperature envelope. The exhaust gas temperature is meas ured by 8 thermocouples mounted in a radial plane in the exhaust cone. NOTE 3. Fuel and oil pressure limits: Fuel: Minimum at engine pump inlet: 5 p.s.i. above true fuel vapor pressure; or a pressure equal to fuel supply tank pressure, whichever is greater with a maximum of 50 p.s.i.g. Oil pressure at oil filter inlet or oil cooler discharge: Minimum 5 p.s.i.g. Maximum 60 p.s.i.g. Refer to Operating Instructions SEI-188 for operating range limits. NOTE 4. Accessory drive provisions: Torque Rating H.P. Accessory Speed in. lb. Extraction Pad Drive Pads AND Type r.p.m. Cont. Static Maximum Rotation ** P2 Starter 20002 XII-D 7088 500 2200 56 CC Front Generator P3 Fluid 20002 XII-D 7088 500 2200 56 C Rear Pump P4 Fluid 20001 XI-B 7811 250 1650 31 C Rear Pump P1* Tachometer 20005 XV-B 4190 7 50 0.50 CC Total customer power extraction in any combina tion from Pads 2, 3, and 4 shall not exceed 65 hp. * Tachometer mounted on lube pump. ** "C" - Clockwise, "CC" - C ounter-clockwise facing engine pad. The customer power extrac tion limits vs. engine speed are presented in General Electric CJ610 Installation Manual No. SEI-126A. Location and details of the accessory drive pads are presented on the Installation Drawing, Section 1. NOTE 5. Engine ratings are based on calibrate d stand performance under the following conditions: Operation at rated engine speeds. Static sea level standard conditions of 59°F and 29.92 in. Hg. General Electric bellmouth on air inlet and bullet nose. No external air bleed or accessory drive power for aircraft accessories Exhaust configuration as defined by General Electric Drawing 1076722-457P23 or 1076774-216. No anti-icing airflow. Turbine exhaust gas temperature limits not exceeded. At sea level static conditions below 59°F, rated thrust will increase to maximum physical thrust limits as indicated: CJ610-1 & -4 CJ610-5 & -6 CJ610-8 & -9 CJ610-8A Takeoff 3050 lb. @ 13°F 3180 lb. @ 23°F - - - - Maximum continuous 2960 lb. @ 13°F 3135 lb. @ 11°F 3100 lb. @ 37°F 3135 lb. @ 11°F TCDS 1E16 Page 4 of 4 These limits may be authorized for use at any ambien t temperature for engines whose individual characteristics permit higher than rated thrust to be developed without exceeding approved temperature or r.p.m. limits. For detailed performance data refer to the following General Electric publications: CJ610-1 & -4 CJ610-5 & -6 CJ610-8 & -9 CJ610-8A Performance Bulletin SEI-167 SEI-213 SEI-252 SEI-494 Power Setting Manual TM64S E2103 SEI-213 SEI-252 SEI-494 Performance Deck ⎯ ⎯ ⎯ 77002 NOTE 6. Maximum permissible bleed air extr action for aircraft purposes is 6% of compressor inlet air flow. Refer to the currently approved CJ610 Installation Manual No. SEI-126A for additional data. NOTE 7. Commercial kerosene, JP-4 and JP-5 type fuels are accepta ble, but whenever a change is made or a mixture is used, a readjustment of the fuel control specific gravity setting must be made for optimum acceleration performance. The use of aviation gasoline as an emergency fuel is permitted provided that its use is limited to no more than 25 hours during any one overhaul period. Refer to Maintenance Manual SEI-186. NOTE 8. Optional additives which may be used in approved fuels are: (1) Phillips PFA-55MB or anti-icing additives to Specifica tions MIL-I-27686E at a concentration not in excess of 0.15% by volume. (2) Shell ASA-3 anti-static additive at a concentrati on that will provide not in excess of 300 conductivity units which is approximately equivalent to one (1) RPM. (3) Sohio Biobor JF biocide additive at a concentrati on not in excess of 20 PPM elemental boron (270 PPM total additive). The above additives may be used in combination. NOTE 9. These engines meet FAA requirement s for operation in icing conditions, for adequate turbine disk integrity and rotor blade containment and do not require airframe mounted armoring. Refer to Operating Instructions SEI-188 for operating procedure under icing conditions. NOTE 10. The maximum permissible steady ove rspeed is 17,160 r.p.m. for 2 minutes and 17,820 r.p.m. on a transient basis. When either of these limits is exceeded, the engine must be inspected as defined in Operating Instructions SEI-188. NOTE 11. Refer to General Electric Operati ng Instructions SEI-188 (Operating Engineering Bulletins Nos. 1 and 2) for list of approved fuels and oils. NOTE 12. Deleted NOTE 13. The CJ610-4, CJ610-6, CJ610-8, and CJ610-8A are similar to the CJ610-1, CJ610-5, and CJ610-9 except for location of the accessory gearbox. The CJ610-8 and -9, CJ610-5 and -6, and the CJ610-1 and -4 models are similar except for increased performance with improved parts. The CJ610-8A is similar to the CJ610-8 except for derated performance and increased operating envelope. NOTE 14. An altitude idle speed reset unit (AIR) P/N 6002T64 is av ailable and may be incorporated in the fuel control to automatically establish a special flight idle speed schedule within the limits of the minimum flight idle speeds defined in SEI-126A - CJ610 Installation Manual. For engines not equipped with AIR, either the aircraft system must be capable of maintaining the referenced minimum idle speed schedule or the pilot must monitor and manually reset idle speed to maintain the minimum speed schedule as defined in SEI-126A unless a modified schedule is coordinated with and approved by the General Electric Company. Engines equipped with AIR unit are identified by the letter "A" following the engine serial number. NOTE 15. Certain engine parts are life lim ited. These limits are listed in the FAA approved General Electric CJ610 Engine Overhaul Manual, SEI-136, Section 72-00, Inspection. .....END..... ``` ## ADs (9, in force first) - [AD 2010-09-08](https://openairdocs.org/ad/2010-09-08): AFT Technologies combustion liners · General Electric CF700-2C, CF700-2D, CF700-2D-2 and 7 more. Effective May 28, 2010 - [AD 2001-10-12](https://openairdocs.org/ad/2001-10-12): Unapproved Parts · General Electric CF700-2C, CF700-2D, CF700-2D-2 and 7 more. Effective Jun 7, 2001 - [AD 98-23-06](https://openairdocs.org/ad/98-23-06): Combustion Liner Assemblies · General Electric CF700-2C, CF700-2D, CF700-2D-2 and 7 more. Effective Nov 20, 1998 - [AD 97-25-08](https://openairdocs.org/ad/97-25-08): General Electric CF700-2C, CF700-2D, CF700-2D-2 and 7 more. Effective Jan 2, 1998 - [AD 85-18-03](https://openairdocs.org/ad/85-18-03): Stage 1 Turbine Disk · General Electric CF700-2D, CF700-2D-2, CJ610-8A and 1 more. Effective Nov 15, 1985 - [AD 80-08-06 R1](https://openairdocs.org/ad/80-08-06-R1): Turbine Disks · General Electric CF700-2D, CF700-2D-2, CJ610-8A and 1 more. Effective Feb 2, 1981 - [AD 75-19-05](https://openairdocs.org/ad/75-19-05): Horizontal Drive Shaft · General Electric CF700-2C, CF700-2D, CF700-2D-2 and 1 more. Effective Sep 26, 1975 - [AD 73-23-05](https://openairdocs.org/ad/73-23-05): First Stage Turbine Discs · General Electric CF700-2C, CJ610-1, CJ610-4 and 2 more - [AD 78-07-06](https://openairdocs.org/ad/78-07-06): Compressor Disks · General Electric CF700-2C, CF700-2D, CF700-2D-2 and 2 more ## Registered aircraft by registry model (OpenAirDocs) - [GE CJ610-SER](https://openairdocs.org/engine/ge-cj610-ser-series): 31 aircraft (registry code 30006) - [GE CJ-610-8A](https://openairdocs.org/engine/ge-cj-610-8a): 9 aircraft (registry code 30035) - [GE CJ610-6](https://openairdocs.org/engine/ge-cj610-6): 6 aircraft (registry code 30122) - [GE CJ-610-4](https://openairdocs.org/engine/ge-cj-610-4): 3 aircraft (registry code 30034) - [GE CJ610-1](https://openairdocs.org/engine/ge-cj610-1): 1 aircraft (registry code 30120) - [GE CJ610-8](https://openairdocs.org/engine/ge-cj610-8): 1 aircraft (registry code 30123) - [GE CJ610-5](https://openairdocs.org/engine/ge-cj610-5): 0 aircraft (registry code 30121) - [GE CJ610-9](https://openairdocs.org/engine/ge-cj610-9): 0 aircraft (registry code 30124) ## STCs approved under this data sheet (5) - [STC SE976SO](https://openairdocs.org/stc/SE976SO): Installation of an oil tank sight gauge on a G.E. oil tank, P/N6003T09P04.. JSF Aviation Services Inc. - [STC SE8674SW](https://openairdocs.org/stc/SE8674SW): Modification of the following engine oil tanks by adding a sight glass: 6002T03P01, 6002T03P03, 6003T09P01, 6003T09P02, 6003T09P03, 6003T09P04, 6003T89P01, 6003T89P02, 6003T03P02, 6002T03P04.. Bizjet International Sales & Support Inc - [STC SE1057SO](https://openairdocs.org/stc/SE1057SO): Installation of capacitance type probe with oil quantity indicating system in oil tank.. Aircraft Equipment Certification Corporation - [STC SE949SO](https://openairdocs.org/stc/SE949SO): Installation of an oil level sight gauge.. Aircraft Equipment Certification Corporation - [STC SE6CE](https://openairdocs.org/stc/SE6CE): Installation of slotted disc magnetic pickup on overspeed fuel control.. Woodward Governor Co --- 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.