# TCDS E00070EN: General Electric Company GE Aviation - Type: Type certificate data sheet - Status: Current - Holder: General Electric Company GE Aviation - Revision: 14 - Product: Engine - Certification basis: Part 33 - Registered aircraft: 31, by the registry models matched to it (OpenAirDocs) - Data sheet PDF: https://openairdocs.org/files/sha256/64/55/64555f148cc4560092d48a9b3c46ffe038ddb1ff2a97c078db79490eaaad50e8 - FAA DRS: https://drs.faa.gov/browse/excelExternalWindow/DRSDOCID134980570320240710140408.0001 - Page: https://openairdocs.org/tcds/E00070EN ## Models (11) As the data sheet lists them. - CF34-10E6 - CF34-10E5A1 - CF34-10E7 - CF34-10E7-B - CF34-10E2A1 - CF34-10E5 - CF34-10A16 - CF34-10E6A1 - CF34-10A16-B - CF34-10A16-C - CF34-10A16-D ## What the data sheet says From the PDF's text layer, line by line; tables lose their columns. The PDF is the record. ```text TCDS NUMBER E00070EN U.S. DEPARTMENT OF TRANSPORTATION REVISION: 14 DATE: July 9, 2024 FEDERAL AVIATION ADMINISTRATION GENERAL ELECTRIC COMPANY TYPE CERTIFICATE DATA SHEET MODELS: CF34-10A16, CF34-10A16-B, CF34-10A16-C, CF34-10A16-D, CF34-10E2A1, CF34-10E5, CF34-10E5A1, CF34-10E6, CF34-10E6A1, CF34-10E7, CF34-10E7-B Engines of models described herein conforming with this data sheet 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 manufacturers manuals and other approved instructions. TYPE CERTIFICATE (TC) HOLDER: General Electric Company GE Aviation 1 Neumann Way Cincinnati, OH 45215-6310 I. MODELS CF34-10E2A1 CF34-10E5 CF34-10E5A1 CF34-10E6 CF34-10E6A1 CF34-10E7 CF34-10E7-B TYPE Dual rotor, axial flow, high bypass ratio turbofan with single stage fan, 3-stage low pressure compressor, 9-stage high pressure compressor, annular combustion chamber, single stage high pressure turbine, 4-stage low pressure turbine, a thrust reverser, aft core cowl, exhaust nozzle, starter, and a full authority digital engine control (FADEC). RATINGS (See NOTE 1) Sea level static thrust, lb Maximum takeoff (5 min.) (See NOTES 10 and 13) 16960 18820 18820 18820 18820 20360 - - Normal takeoff (5 min.) (See NOTE 10 and 13) 16960 17390 18820 17390 18820 18820 - - Maximum continuous 15110 17040 17040 17040 17040 17040 - - Flat rate ambient temperature Takeoff 86ºF / 30 C - - - - 95ºF / 35 C - - 86ºF / 30 C - - Maximum continuous 77ºF / 25 C - - - - - - - - - - - - CONTROL SYSTEM COMPONENT Fuel Metering Unit Full Authority Digital Engine Control (FADEC) Hardware Software Configuration Plug Hardware Engine Rating Engine Configuration N1 Trim Setting Ignition System 2 Ignition Exciters 2 Ignition Plugs Fuel Pump 2043M10 2043M11 2043M65 2162M48 2041M41P26 2041M42 2041M43 9238M66 1374M12 2043M12 - - - - - - - - 2041M41P31 - - - - - - - - - - - - - - - - - - 2041M41P30 - - - - - - - - - - - - - - - - - - 2041M41P29 - - - - - - - - - - - - - - - - - - 2041M41P28 - - - - - - - - - - - - - - - - - - 2041M41P32 - - - - - - - - - - - - - - - - - - 2041M41P27 - - - - - - - - - - PAGE 1 2 3 4 5 6 7 8 9 10 REV. 14 12 12 14 12 13 12 12 14 12 LEGEND: "- -" INDICATES "SAME AS PRECEDING MODEL" "---" NOT APPLICABLE NOTE: SIGNIFICANT CHANGES ARE BLACK-LINED IN THE LEFT MARGIN. I. MODELS (continued) CF34-10E2A1 CF34-10E5 CF34-10E5A1 CF34-10E6 CF34-10E6A1 CF34-10E7 CF34-10E7-B FUEL Fuel and additive conforming to GE Jet Fuel Specification No. D50TF2 and GEK 112083, CF34-10E Installation Manual, is applicable for all CF34-10E models. OIL Oil conforming to GE Specification No. D50TF1 and GEK 112083, CF34-10E Installation Manual, is applicable for all CF34-10E models. PRINCIPAL DIMENSIONS AND MEASUREMENTS Length, inches Maximum diameter, inches Weight, pounds (Dry) Center of Gravity Location, inches Engine Station Butt Line Water Line (14 CFR Part 33 Propulsion System: see Installation Manual GEK 112083) 177.93 73.38 x 86.59 4584.2 208.2 99.2 100.4 - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - II. MODELS CF34-10A16 CF34-10A16-B CF34-10A16-C CF34-10A16-D TYPE Dual rotor, axial flow, high bypass ratio turbofan with single stage fan, 3-stage low pressure compressor, 9- stage high pressure compressor, annular combustion chamber, single stage high pressure turbine, 4-stage low pressure turbine, a thrust reverser, aft core cowl, exhaust nozzle, starter, and a full authority digital engine control (FADEC). RATINGS (See NOTE 1) Sea level static thrust, lb Maximum takeoff (5 min.) (See NOTES 10 and 13) 17640 - - - - - - Normal takeoff (5 min.) (See NOTE 10 and 13) 17300 - - - - - - Maximum continuous 16110 - - - - - - Flat rate ambient temperature Takeoff 86ºF / 30 C - - - - - - Maximum continuous 77ºF / 25 C - - - - - - CONTROL SYSTEM COMPONENT Fuel Metering Unit 2044M33 - - - - - - Full Authority Digital Engine Control (FADEC) Hardware Software Configuration Plug Hardware Engine Rating Engine Configuration N1 Trim Setting Ignition System 2 Ignition Exciters 2 Ignition Plugs Fuel Pump 2043M11 2413M46 2162M48 2041M41P34 2041M42 2041M43 9238M66 1374M12 2044M34 - - - - - - 2041M41P34 - - - - - - - - - - - - - - - - 2041M41P39 - - - - - - - - - - - - - - - - 2041M41P40 - - - - - - - - - - FUEL Fuel and additive conforming to GE Jet Fuel Specification No. D50TF2 and GEK 112093, CF34-10A Installation Manual, is applicable for all models. OIL Oil conforming to GE Specification No. D50TF1 and GEK 112093, C34-10A Installation Manual, is applicable for all CF34-10A models. TCDS E00070EN Page 4 of 10 II. MODELS (continued) CF34-10A16 CF34-10A16-B CF34-10A16-C CF34-10A16-D PRINCIPAL DIMENSIONS AND MEASUREMENTS Length, inches Maximum diameter, inches Weight, pounds (Dry) Center of Gravity Location, inches Engine Station Butt Line Water Line (14 CFR Part 33 Propulsion System: see Installation Manual GEK 112093) 158.6 79.313 x 71.534 4644 205.90 101.10 97.23 - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - CERTIFICATION BASIS: (All 10E models) CERTIFICATION BASIS: (All 10A16 models) (1) 14 Code of Federal Regulations (CFR), Part 33, effective February 1, 1965, as amended by amendments 33-1 through 33-20. (2) 14 CFR Part 34, effective October 23, 2013, amendment 34-5A. In addition, 40 CFR Part 87, effective July 18, 2012. (3) Equivalent level of safety 8040-ELOS-04-NE-01 §33.83(c)(1) Vibration Test Type Certificate Model Date of Application Issued/Amended CF34-10E5 February 9, 2001 December 22, 2004 CF34-10E5A1 February 9, 2001 December 22, 2004 CF34-10E6 February 9, 2001 December 22, 2004 CF34-10E6A1 February 9, 2001 December 22, 2004 CF34-10E2A1 January 2, 2006 July 20, 2006 CF34-10E7 January 2, 2006 July 20, 2006 CF34-10E7-B June 4, 2007 June 16, 2008 (1) 14 Code of Federal Regulations (CFR), Part 33, effective February 1, 1965, as amended by amendments 33-1 through 33-20. (2) 14 CFR Part 34, effective May 24, 2024, amendment 34-7A. (3) Equivalent level of safety 8040-ELOS-10-NE-01 §33.83(c)(1) Vibration Test Type Certificate Model Date of Application Issued/Amended Deleted CF34-10A16 January 25, 2006 July 22, 2010 CF34-10A18 January 25, 2006 July 22, 2010 August 1, 2014 CF34-10A16-B April 30, 2018 August 28, 2019 CF34-10A16-C July 2, 2020 April 16, 2021 CF34-10A16-D July 2, 2020 April 16, 2021 See Note 11 (3) for detailed summary of the certification basis for fuel venting and exhaust emissions. PRODUCTION CERTIFICATE CF34-10E/10A Production Certificate No. PC108 TCDS E00070EN Page 5 of 10 NOTE 1. ENGINE RATINGS Engine ratings are based on calibrated test stand performance, and performance calculations are based on accepted parameter correction methods documented in the production data folder. These calculations assume the following conditions: (1) Static sea level standard conditions of 59° F and 29.92 inches Hg (2) US standard atmosphere 1962 (zero humidity) (3) No aircraft accessory loads or air extraction. (4) Production engine inlet and production flight exhaust system (5) Standard lower heating value of 18550 BTU/LB (6) No anti-icing; no inlet distortion; no inlet screen losses; and 100% ram recovery. NOTE 2. TEMPERATURE LIMITS (1) Indicated maximum permissible temperatures are listed below. In addition, the CF34-10E2A1 model incorporates an EGT shunt of 30°C at fan speeds above idle. Thus, for an indicated EGT of 1801°F (983°C), the measured EGT is 1747°F (953°C). All CF34-10E/10A series engines are certified with a takeoff EGT transient allowance. This allowance applies to normal and maximum takeoff EGT, up to 5.5 °C for 2 seconds, 4.4 °C for 5 seconds, 3.6 °C for 15 seconds and 2.4 °C for 30 seconds. Indicated Exhaust Gas Temperature (EGT*), °F (°C) CF34-10E2A1 CF34-10E5 CF34-10E5A1 CF34-10E6 CF34-10E6A1 CF34-10E7 CF34-10E7-B Maximum takeoff (5 min) 1801 (983) - - - - - - - - - - - - Normal takeoff (5 min) 1801 (983) 1733 (945) 1801 (983) 1737 (947) 1801 (983) 1729 (943) - - Maximum continuous 1760 (960) - - - - - - - - - - - - At start-up, ground 1364 (740) - - - - - - - - - - - - At start-up, inflight 1607 (875) - - - - - - - - - - - - CF34-10A16 CF34-10A16-B CF34-10A16-C CF34-10A16-D Maximum takeoff (5 min) 1801 (983) - - - - - - Normal takeoff (5 min) 1744 (951) - - - - - - Maximum continuous 1760 (960) - - - - - - At start-up, ground 1364 (740) - - - - - - At start-up, inflight 1607 (875) - - - - - - *The exhaust gas temperature is measured by 9 probes, which are equally spaced and mounted in the second-stage low-pressure turbine vanes. (2) Refer to GE Engine Manual GEK 112081 and GE Line Maintenance Manual GEK 112081-1 (CF34-10E all models), GEK 112091 (CF34- 10A all models) for inspection requirements when limits are exceeded. (3) Oil temperature limit (oil supply temperature measured in the oil tank), °F (°C) All 10E models All 10A models Continuous operation 311 (155) - - (4) Fuel inlet temperature (at pylon interface), °F (°C) All 10E models All 10A models Continuous operation 155 (68.3) 135 (57.2) NOTES TCDS E00070EN Page 6 of 10 NOTE 3. FUEL AND OIL PRESSURE LIMITS (1) Fuel: For all 10E models, at engine pump inlet: minimum pressure of 5 PSID above the true vapor pressure of the fuel with a vapor/liquid ratio of zero with aircraft boost operative. Operating range 5 PSIG to 50 PSIG. At engine motive flow discharge: minimum pressure of 150 PSIG at idle or above. Operating range is 150 PSIG to 1209 PSIG. See GE Installation Manual GEK 112083 for additional limits. For 10A models, at engine pump inlet: minimum pressure of 5 PSID above the true vapor pressure of the fuel with a vapor/liquid ratio of zero with aircraft boost operative. Operating range 5 PSIG to 50 PSIG. See GE Installation Manual GEK 112093 for additional limits. (2) Oil: Minimum oil pressure limit is 25 psid. For oil temperatures less than –20C, the minimum oil pressure is 5 psid for the first two minutes following an engine start. After two minutes at idle or if the engine power is increased above idle, the minimum oil pressure is 25 psid. See GE Installation Manual GEK 112083 (10E all models), GEK112093 (10A all models) for additional limits. NOTE 4. ACCESSORY DRIVE PROVISIONS LIMITS All CF34-10E Models CW - Clockwise CCW – Counter- Clockwise Accessory Speeds are based on Core Speed: 17160 rpm (1) -40 o F SLS (2) HP is c onstant over the operating range with slight variations due to changes in efficiency. HP extraction is 74.8 HP at 7898 rpm (pad speed) and 73.5 HP at 4618 rpm (pad speed). The 5-minute overload rating is 82.7 HP and the 5 second overload rating is 137.37 (3) 2112 in-lbs at 59oF SLS, 4200 in-lbs at -40o F SLS (4) Overload at 4618 rpm (pad speed) (5) 573 in-lbs at 626 rpm (pad speed) (6) Includes oil and V band coupling Accessory Location on AGB Axis Speed (RPM) HP (Rated) Direction of Rotation facing AGB Torque (lb-in) Static / Continuous / Overload Max Acc. Wt. (lb) Overhung Moment (lb-in) Shear Torque (lb-in) Lube & Scavenge Oil Pump Axis-J Aft 8575 7 CCW 300 (1) /48 / NA 10.3 33 750-850 IDG Axis-G Fwd 7928 74.8 (2) CW 675 (1) / 595 / 1129 (5 min) (4) 1605 (5 sec) (4) 81.2 (6) 720 Maximum 3144-3648 Air Turbine Starter Axis-D Fwd 12281 NA CW 2112, 4200 (3) / NA / NA 27.7 113 6300-7500 Hydraulic Pump Axis-F Fwd 5567 35 CW 573 (1) (5) / 392 / 670 13.9 dry 38.4 2004 maximum Alternator Axis-J Fwd 8575 4 CW NA / NA / NA 3.0 2.6 NA Fuel Pump Axis-E Aft 7928 55 CW 150/240/NA 28.6 142 1400-1540 TCDS E00070EN Page 7 of 10 NOTE 4. ACCESSORY DRIVE PROVISIONS LIMITS (continuation) All CF34-10A models Accessory Location on AGB Axis Speed (RPM) HP (Rated) Direction of Rotation facing AGB Torque (lb-in) Static / Continuous / Overload Max Weight (lb) Overhung Moment (lb-in) Shear Torque (lb-in) Lube & Scavenge Oil Pump Axis-F, AFT 7982 6.2 CCW 33 / 47 (1) / 56 16.2 59.94 750-850 IDG Axis-F, FWD 7982 76.7 CW 675 (2) / 610 (3) / 2184 (4) 80 610 3150-3650 Air Turbine Starter Axis-C, FWD 12269 N/A CW NA / 3360 / NA 29.46 125.91 6300-7500 Hydraulic Pump Axis-D, AFT 5593 38.0 CW 550 / 108 / 670 14.70 43.07 2000 Max Alternator Axis-G, FWD 8604 0.38 CCW NA / 3.5 / 5.8 3.04 2.16 N/A Fuel Pump Axis-E, FWD 7888 26.3 CW 90 / 210 / 353 21 73.94 1400-1540 CW - Clockwise CCW – Counter-Clockwise Accessory Speeds are based on Core Speed: 17160 rpm (1) Calculated at rated speed of 7982 rpm at 6 HP input. (2) Cold start @ -40F and max ramp rate of 450 rpm/sec. Torque peaks at 500 rpm. Zero torque at zero speed. (3) Calculated at continuous operating point 76.5 HP and 7898 rpm (4) 5 sec max at 160 HP and 4618 rpm NOTE 5. MODEL DESCRIPTION Model Characteristics CF34-10E2A1 Embraer Basic Model CF34-10E5 Embraer Basic Model with additional thrust on Maximum Takeoff, Nominal Takeoff and Maximum Continuous rating CF34-10E5A1 Embraer Basic Model with additional thrust on Maximum Takeoff, Nominal Takeoff and Maximum Continuous rating CF34-10E6 Embraer Basic Model with additional thrust on Maximum Takeoff, Nominal Takeoff and Maximum Continuous rating, with higher flat rate ambient temperature capability at Takeoff CF34-10E6A1 Embraer Basic Model with additional thrust on Maximum Takeoff, Nominal Takeoff and Maximum Continuous rating, with higher flat rate ambient temperature capability at Takeoff CF34-10E7 Embraer Basic Model with additional thrust on Maximum Takeoff, Nominal Takeoff and Maximum Continuous rating CF34-10E7-B Embraer Business Jet Basic Model CF34-10A16 COMAC Basic Model CF34-10A16-B COMAC Business Jet Basic Model CF34-10A16-C COMAC Basic Model with additional 5% thrust on Max Cruise rating CF34-10A16-D COMAC Basic Model with additional 5% thrust on Max Cruise rating and additional 3% thrust on Max Continuous rating at altitudes between 20,000 ft and 30,000 ft TCDS E00070EN Page 8 of 10 NOTE 6 . TYPICAL AIRCRAFT ACCESSORIES, COMPONENTS, OR SYSTEM ASSEMBLIES, WITH AIRCRAFT LEVEL REQUIREMENTS PROVIDED AS PART OF ENGINE TYPE DESIGN: For the CF34-10E/10A model series, the 14CFR Part 33 engine type design definition includes thrust reverser system, which is part of the nacelle system, and is identified as follows: Engine Parts List Thrust Reverser Parts List CF34-10E2A1GXX 601E0001-5XX CF34-10E5GXX 601E0001-5XX CF34-10E5A1GXX 601E0001-5XX CF34-10E6GXX 601E0001-5XX CF34-10E6A1GXX 601E0001-5XX CF34-10E7GXX 601E0001-5XX CF34-10E7-BGXX 601E0001-5XX CF34-10A16GXX 604C0010-5XX CF34-10A16-BGXX 604C0010-5XX CF34-10A16-CGXX 604C0010-5XX CF34-10A16-DGXX 604C0010-5XX The GE Engine Manual, GEK 112081 and GE Line Maintenance Manual GEK 112081-1 (CF34-10E all models) and GEK 112091 (CF34-10A all models), defines the installation requirements for the engine GXX or –5XX indicates all parts list designations, for example G01, G02, -501, -502, etc. NOTE 7. AIRCRAFT ACCESSORIES, COMPONENTS, OR SYSTEM ASSEMBLIES INSTALLED ON THE ENGINE THAT ARE NOT PART OF ENGINE TYPE DESIGN: Not Applicable NOTE 8. SPECIAL ANTI-ICING OR DE-ICING REQUIREMENTS Not Applicable NOTE 9. ENGINE MOUNT SYSTEM PROVISIONS Not Applicable NOTE 10. POWER BOOST, INJECTION OR AUGMENTATION SYSTEMS AND LIMITS AS APPLICABLE This engine is equipped with an automatic power reserve function for takeoff operation with one engine inoperative. During takeoff, when the automatic power reserve function is activated, the engine control of the inoperative engine sends an input signal to the engine control of the operating engine. Upon receiving this signal, the engine thrust of the operating engine automatically increases from normal takeoff (NTO) or lower thrust to the corresponding, pre-determined maximum takeoff (MTO) thrust. Full MTO thrust is available to the pilot at any time by throttle selection. The engine control sy stem also incorporates schedules that assure a fully degraded engine, during operation at the NTO of lower thrust, will achieve the specified MTO thrust without exceeding the engine operating limits when the automatic power reserve function is activated. NOTE 11. SPECIAL INSTALLATION REQUIREMENT (1) The maximum permissible inlet distortion for these engines is specified in GE Installation Manual GEK 112083 (CF34-10E all models) and GEK 112093 (CF34-10A all models). Ground operational limits and procedures for operation in crosswind are specified in GE Specific Operating Instructions GEK 112084 (CF34-10E all models) and GEK 112094 (CF34-10A all models). (2) Criteria pertaining to the dispatch and maintenance requirements for the engine control systems are specified in the airworthiness sections of the Engine Manuals, GEK 112081 (CF34-10E all models) and GEK 112091 (CF34-10A all models), which define the various configurations and maximum operating intervals. TCDS E00070EN Page 9 of 10 NOTE 11. SPECIAL INSTALLATION REQUIREMENT (continuation) (3) The following emissions standards promulgated in 14 CFR Part 34, Amendment 5A, effective October 23, 2013, and 40 CFR Part 87, effective July 18, 2012, have been complied with for: CF34-10E2A1, CF34-10E5, CF34-10E5A1, CF34- 10E6, CF34-10E6A1, CF34-10E7, CF34-10E7-B. • Fuel Venting emission standards: 14 CFR 34.10(a) and 34.11; in addition, 40 CFR 87.10(a) and 87.11 • Smoke Number (SN) emission standards: 14 CFR 34.21(e)(2); in addition, 40 CFR 87.23(c)(1) • Carbon Monoxide (CO) emission standards: 14 CFR 34.21(d)(1)(ii); in addition, 40 CFR 87.23(c)(1) • Hydrocarbons (HC) emission standards: 14 CFR 34.21(d)(1)(i); in addition, 40 CFR 87.23(c)(1) • Oxides of Nitrogen (NOx) emission standards: 14 CFR 34.23(b)(1); in addition, 40 CFR 87.23(c)(3) In addition to the FAA's finding of compliance based on the certification requirements defined in this TCDS, the engine manufacturer has declared that the ICAO emissions standards identified in Annex 16, Volume II, Fourth Edition, July 2017, have also been demonstrated for the following: Part II, Chapter 2 for Fuel Venting • Part III, Chapter 2, Section 2.2.2 for Smoke number, • Part III, Chapter 2, Section 2.3.2 for Carbon monoxide and Hydrocarbons, • Part III, Chapter 2, Section 2.3.2. e.1(ii) for Oxides of Nitrogen (also known as CAEP/8), and • Part III, Chapter 4, Section 4.2.2 for non-volatile Particulate Matter (also known as CAEP/10) The following emissions standards promulgated in 14 CFR part 34, amendment 7A, effective May 24, 2024, and 40 CFR part 1031, effective December 23, 2022, have been complied with for: CF34-10A16, CF34-10A16-B, CF34-10A16-C, and CF34-10A16-D. • Fuel Venting Emission Standards: 14 CFR 34.11; in addition, 40 CFR 1031.30(b) • Smoke Number (SN) Emission Standards: 14 CFR 34.21(e); in addition, 40 CFR 1031.60(a)(5) • Hydrocarbons (HC) Emission Standards: 14 CFR 34.21(d)(1)(i); in addition, 40 CFR 1031.60(c) • Carbon Monoxide (CO) Emission Standards: 14 CFR 34.21(d)(1)(ii); in addition, 40 CFR 1031.60(d) • Oxides of Nitrogen (NOx) Emission Standards: 14 CFR 34.23(b)(1); in addition, 40 CFR 1031.60(e)(5) (also known as Tier 8 new type) • non-volatile Particulate Matter (nvPM) Mass Concentration Emission Standards: 14 CFR 34.25(a)(1); in addition, 40 CFR 1031.60(a)(6) (also known as Tier 10) • nvPM Mass and Number Emission Standards: 14 CFR 34.25(a)(2); in addition, 40 CFR 1031.60(b)(2) (also known as Tier 11 in-production) In addition to the FAA's finding of compliance based on the certification requirements defined in this TCDS, the engine manufacturer has declared that the ICAO emissions standards identified in Annex 16, Volume II, Fourth Edition, Amendment 10, effective July 20, 2020, have also been demonstrated for the following: • Part II, Chapter 2 for Fuel Venting • Part III, Chapter 2, Section 2.2.2 for Smoke number, • Part III, Chapter 2, Section 2.3.2 for Carbon monoxide and Hydrocarbons, • Part III, Chapter 2, Section 2.3.2.e.1(ii) for Oxides of Nitrogen (also known as CAEP/8), • Part III, Chapter 4, Section 4.2.2.1 for nvPM Mass Concentration (also known as CAEP/10), and • Part III, Chapter 4, Section 4.2.2.2 for nvPM Mass and Number (also known as CAEP/11) NOTE 12. MANUFACURER’S SERVICE BULLETINS OR OTHER INSTRUCTIONS Recommended maintenance inspection intervals are published in CF34-10E Service Bulletin 71-0000 and CF34-10A GE Service Bulletin 71-0000. NOTE 13. SPECIAL OPERATING PROCEDURES OR LIMITATIONS (1) The time limit at the normal takeoff rating is five minutes and shall include any time accumulated above the normal takeoff rating for that takeoff. The 5-minute takeoff time limit may be extended to 10 minutes for one engine inoperative operation in multi- engine aircraft. (2) Refer to Operating Instructions GEK 112084 (CF34-10E all models) and GEK 112094 (CF34-10A all models) for engine warm-up procedure. (3) Refer to Operating Instructions GEK 112084 (CF34-10E all models) and GEK 112094 (CF34-10A all models) for thrust reverser operation. NOTE 14. SPECIAL REPAIR OR OVERHAUL LIMITATIONS Not applicable. NOTE 15. APPLICABLE INSTALLATION, MAINTENANCE AND OVERHAUL MANUALS The following manuals are approved or accepted for the CF34-10E/10A model series: CF34-10E (all models) CF34-10A (all models) TCDS E00070EN Page 10 of 10 Operating Instructions GEK 112084 GEK 112094 Installation Manual GEK 112083 GEK 112093 Engine Manual GEK 112081 GEK 112091 Line Maintenance Manual GEK112081-1 NA NOTE 16. IMPORT REQUIREMENTS FOR FOREIGN MANUFACTURED ENGINES Not Applicable NOTE 17. LIFE LIMITED PARTS INFORMATION Life limits established for critical components and mandatory inspection requirements are specified in the Airworthiness Limitation Section of GE Engine Manual GEK 112081 (CF34-10E all models) and GEK 112091 (CF34-10A all models). NOTE 18. MILITARY MODEL INFORMATION Not Applicable NOTE 19. MAXIMUM PERMISSIBLE MAIN ROTOR SPEEDS CF34-10E (all models) CF34-10A16 (All models) Low pressure rotor (N1), rpm Maximum takeoff Normal takeoff Maximum continuous High pressure rotor (N2), rpm Maximum takeoff Normal takeoff Maximum continuous 6325 6325 6325 18018 18018 18018 6325 6325 6325 18018 18018 18018 Refer to GE Engine Manual GEK 112081 and GE Line Maintenance Manual GEK 112081-1 (all 10E models), GEK112091 (10A all models), and other manual or inspection requirements when limits are exceeded. 100 percent N1 rotor speed is 5954.4 rpm, 100 percent N2 rotor speed is 17,160 rpm (all 10E/10A models). NOTE 20. OUTPUT/PROPELLER SHAFT TORQUE LIMITS Not Applicable NOTE 21. MAXIMUM PERMISSIBLE BLEED AIR EXTRACTION Air Bleed Extraction - maximum customer air bleed extraction is as follows: Customer bleed air is available from either stage 5 or 9 (compressor discharge) of the compressor at all operating conditions at or above idle (No compressor bleed is permitted below idle). Customer bleed is scheduled to switch from stage 9 bleed at low power operation to stage 5 bleed at high power operation as described in GE Installation Manual GEK 112083 (CF34-10E all models) and GEK 112093 (CF34-10A all models). CF34-10E/10A (all models) Location Maximum Demonstrated Bleed Air (% of Total Compressor Airflow) Compressor Stage 5 8.0 Compressor Stage 9 (Compressor Discharge) 12.0 Maximum Allowable Bleed 12.0 NOTE 22. ROTOR DISK INTEGRITY AND ROTOR BLADE CONTAINMENT (where special requirements apply) Not Applicable -- END-- ``` ## ADs (10, in force first) - [AD 2025-14-03](https://openairdocs.org/ad/2025-14-03): Turbine Section · General Electric Company GE CF34-10E2A1, CF34-10E6, CF34-10E6A1 and 4 more. Effective Aug 25, 2025 - [AD 2025-10-04](https://openairdocs.org/ad/2025-10-04): Turbine Section · General Electric Company GE CF34-10E2A1, CF34-10E5, CF34-10E5A1 and 4 more. Effective Jun 26, 2025 - [AD 2022-05-08](https://openairdocs.org/ad/2022-05-08): Turbine Engine Oil System · General Electric CF34-10E2A1, CF34-10E5, CF34-10E5A1 and 4 more. Effective Apr 11, 2022 - [AD 2018-19-22](https://openairdocs.org/ad/2018-19-22): Turbine Engine Turbine Section · General Electric CF34-10A16, CF34-10E2A1, CF34-10E5 and 5 more. Effective Oct 25, 2018 - [AD 2012-01-10](https://openairdocs.org/ad/2012-01-10): Fan drive shaft · General Electric CF34-10E2A1, CF34-10E5, CF34-10E5A1 and 4 more. Effective Feb 27, 2012 - [AD 2011-18-02](https://openairdocs.org/ad/2011-18-02): Fan rotor spinner · General Electric CF34-10E2A1, CF34-10E5, CF34-10E5A1 and 4 more. Effective Sep 26, 2011 - [AD 2008-05-01](https://openairdocs.org/ad/2008-05-01): Fuel metering units (FMU) · General Electric CF34-10E2A1, CF34-10E5, CF34-10E5A1 and 8 more. Effective Apr 3, 2008 - [AD 2007-12-15](https://openairdocs.org/ad/2007-12-15): Main fuel pump (MFP) · General Electric CF34-10E2A1, CF34-10E5, CF34-10E5A1 and 3 more. Effective Jul 19, 2007 - [AD 2007-12-09](https://openairdocs.org/ad/2007-12-09): Combustor case · General Electric CF34-10E2A1, CF34-10E5, CF34-10E5A1 and 3 more. Effective Jul 10, 2007 - [AD 2006-20-06](https://openairdocs.org/ad/2006-20-06) (historical): Main fuel pump (MFP) inlet strainer · General Electric CF34-10E2A1, CF34-10E5, CF34-10E5A1 and 3 more. Effective Oct 16, 2006 ## Registered aircraft by registry model (OpenAirDocs) - [GE CF34-10E6](https://openairdocs.org/engine/ge-cf34-10e6): 20 aircraft (registry code 30023) - [GE CF34-10E5A1](https://openairdocs.org/engine/ge-cf34-10e5a1): 7 aircraft (registry code 30022) - [GE CF34-10E7 series](https://openairdocs.org/engine/ge-cf34-10e7-series): 4 aircraft (registry code 30164) - [GE CF34-10E5](https://openairdocs.org/engine/ge-cf34-10e5): 0 aircraft (registry code 30021) - [GE CF34-10E6A1](https://openairdocs.org/engine/ge-cf34-10e6a1): 0 aircraft (registry code 30024) --- 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.