# TCDS E00048EN: GE Aviation Czech s.r.o. - Type: Type certificate data sheet - Status: Current - Holder: GE Aviation Czech s.r.o. - Revision: 16 - Revised: March 9, 2020 - Product: Engine - Certification basis: Part 1, Part 5, Part 21, Part 25, Part 33, Part 34 - Registered aircraft: 79, by the registry models matched to it (OpenAirDocs) - Data sheet PDF: https://openairdocs.org/files/sha256/c7/0e/c70ec1b85eddd3df791a5e3dfb87128dfefd28e4dea693e4348c34518357e83a - FAA DRS: https://drs.faa.gov/browse/excelExternalWindow/3164D0C7EDAAABCB8625852800611D6A.0001 - Page: https://openairdocs.org/tcds/E00048EN ## Models (13) As the data sheet lists them. - H80-100 - M601E-11AS - M601D-11 - H80 - M601E-11A - M601E-11 - H80-200 - M601F - M601E-11S - H75-100 - H75-200 - H85-100 - H85-200 ## 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 5 6 7 8 9 REV. 16 16 11 14 14 13 13 15 15 LEGEND: "- -" INDICATES "SAME AS PRECEDING MODEL" "---" NOT APPLICABLE NOTE: SIGNIFICANT CHANGES ARE BLACK-LINED IN THE LEFT MARGIN. U.S. DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION TYPE CERTIFICATE DATA SHEET E00048EN TCDS NUMBER E00048EN REVISION: Revision 16 DATE: March 9, 2020 GE Aviation Czech s.r.o. MODELS: M601D-11 M601E-11, M601E-11S, M601E-11A, M601E-11AS M601F H80, H80-100, H80-200 H75-100, H75-200, H85-100, H85-200 Engines of models described herein conforming with this data sheet (which is part of Type Certificate Number E00048EN) 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: GE Aviation Czech s.r.o. (formerly WALTER Engines a.s., Walter a.s. and MOTORLET a.s.) Beranovych 65 199 02 Praha 9 – Letnany Czech Republic I. MODELS M601E-11 / M601E-11S M601E-11A / M601E-11AS M601F M601D-11 H80 / H80-100 H80-200 TYPE RATINGS (See NOTE 1) Maximum continuous at sea level Total output shaft hp. 657 (490 kW) 650 (485kW) 777 (580 kW) 604 (450kW) 800 (597 kW) 800 (597 kW)* Takeoff at sea level (5 min) Total output shaft hp. 751 (560 kW) 705 (526kW) 777 (580 kW) 604 (450kW) 800 (597 kW) 800 (597 kW) Takeoff (5 min) with water injection Total output shaft hp 751 (560 kW) --- 777 (580 kW) --- --- --- Maximum takeoff (5 min.) Total output shaft hp --- --- 777 (580 kW) --- --- --- MODELS (continuing) H75-100 H75-200 H85-100 H85-200 Maximum continuous at sea level Total output shaft hp. 751 (560 kW) 798 (595kW) 850 (634 kW) 850 (634kW) Takeoff at sea level (5 min) Total output shaft hp. 751 (560 kW) 751 (560kW) 850 (634 kW) 850 (634kW) *L-410 commuter has a maximum continuous at sea level Total output shaft hp of 700 (522 kW). Two rotors, free turbine, turboprop with propeller reduction TCDS E00048EN Page 2 of 9 FUEL: Fuels conforming to the Operation Manual and Installation Manual. OIL: Oils conforming to the Operation Manual and Installation Manual. TANK CAPACITY: Total oil quantity in the oil system 2.85 US gal Quantity of oil in the tank min 1.45 US gal to max 1.85 US gal. PRINCIPAL DIMENSIONS Nominal length, in. 66.0 Nominal height, in. 25.6 Nominal width, in. 23.2 (exhaust nozzles removed) WEIGHT (DRY) Includes standard equipment delivered with the engine but without the exhaust nozzle and alternator gearbox. M601D-11 450 lb M601E-11, M601E-11A, M601F 457 lb M601E-11S, M601E-11AS 495 lb (Also includes the propeller governor and propeller overspeed governor for use with single-acting propellers.) H80, H80-100, H75-100, H85-100 441 lb H80-200, H75-200, H85-200 445.3 lb C.G. LOCATION Forward of mount pad plane, in. 3.386 on the engine center line CERTIFICATION BASIS 14 CFR § 21.29, and 14 CFR part 33 dated February 1, 1965, including amendments 33-1 through 33-12, inclusive and Special FAR 27-5. For H80, H80-100, H80-200, H75-100, H75-200, H85-100 and H85-200 engine models, 14 CFR part 33, effective February 1, 1965, including amendments 33-1 through 33-31, except for §33.70, Engine Life-Limited Parts. Section 33.14, Start-stop cyclic stress (low cycle fatigue) per amendment 33-10 applies. 14 CFR part 34, amendment 5, effective December 31, 2012. See NOTE 19. for detailed summary of the certification basis for fuel venting and exhaust emissions. Date Type Certificate Model Date of Application Issued/Revised M601E-11 MAY 10, 1990 JAN. 6, 1995 M601F JAN. 31, 1996 OCT. 2, 1998 M601D-11 JUNE 9. 1997 JULY 17, 2002 M601E-11A JAN. 11, 2001 JULY 17, 2002 M601E-11S APRIL 25, 2001 JULY 17, 2002 M601E-11AS APRIL 25, 2001 JULY 17, 2002 H80 NOVEMBER 6, 2009 MARCH 13, 2012 H80-100 MARCH 6, 2012 MARCH 13, 2012 H80-200 MARCH 6, 2012 MARCH 13, 2012 H75-100 DECEMBER 7, 2012 APRIL 22, 2014 H75-200 DECEMBER 7, 2012 APRIL 22, 2014 H85-100 DECEMBER 7, 2012 APRIL 22, 2014 H85-200 DECEMBER 7, 2012 APRIL 22, 2014 The Czech Republic Civil Aviation Authority (CAA) originally type certificated this engine. The FAA validated this product under U.S. Type Certificate Number E00048EN. Effective September 28, 2003, the European Aviation Safety Agency (EASA) began oversight of this product on behalf of the Czech Republic CAA. IMPORT REQUIREMENTS To be considered eligible for installation on United States registered aircraft, each new engine to be exported to the United States with Czech Republic CAA or EASA airworthiness approval shall have a Joint Airworthiness Authority (JAA) or EASA Form 1, Authorized Release Certificate. The JAA or EASA Form 1 should state that the engine conforms to the type design approved under the U.S. Type Certificate E00048EN, is in a condition for safe operation and has under gone a final operational check. TCDS E00048EN Page 3 of 9 NOTES NOTE 1. a) Engine ratings are based on ICAO International Standard Atmosphere sea level, static conditions with no installation losses, compressor intake screen installed, no external accessory loads and no air bleed. b) For the M601E-11 and M601E-11S, the takeoff rating is flat rated to 73.4oF (23oC) at 14.7 psi, the takeoff rating with water injection is flat rated to 91.4oF (33oC) at 14.12 psi, and the max. continuous rating is flat rated to 64.4oF (18oC) at 14.7 psi. c) For the M601F, the takeoff rating is flat rated to 73.4oF (23oC) at 14.7 psi, the takeoff rating with water injection is flat rated to 91.4oF (33oC) at 14.12 psi, the max. takeoff rating is flat rated to 86oF (30oC) at 14.46 psi, and the max. continuous rating is flat rated to 77oF (25oC) at 14.7 psi. d) For the M601E-11A and M601E-11AS, the takeoff rating is flat rated to 75.2°F (24°C) at 14.7 psi and the max. continuous rating is flat rated to 87.8° F(31°C) at 14.7 psi. e) For the M601D-11, the takeoff rating is flat rated to 87.8ºF(31ºC) and the maximum continuous rating is flat rated to 68ºF(20ºC), both at 14.7 psi. f) For the H80 and the H80-200 the takeoff and max continuous ratings are flat rated to 105.8°F (41˚C) at sea level static. g) For the H80-100 the takeoff rating is flat rated to 105.8°F (41˚C) at sea level static, and the max. continuous rating is flat rated to 87.8oF (31oC) at sea level static. h) For the H75-100 and H75-200, the take off rating is flat rated to 118°F (48°C). Max. continuous is flat rated to 113°F (45°C) for H75-100 and to 107°F (41°C) for H75-200. i) For the H85-100 and H85-200, the take off rating is flat rated to 94°F (34°C). Max. continuous is flat rated to 90°F (32°C) for H85-100 and to 94°F (34°C) for H85-200. NOTE 2. SPEED LIMITATIONS: 100% gas generator shaft speed equals 36,660 rpm, 100% free turbine shaft speed equals 31,023 rpm. M601E-11 M601E-11S M601E-11A M601E-11AS M601F M601D-11 H80 H80-100 H80-200 Maximum continuous Propeller rpm (max.) Gas Generator speed (max.) Takeoff (5 min) Propeller rpm (max.) Gas Generator speed (max.) Takeoff (5 min) with water injection Propeller rpm (max.) Gas Generator speed (max.) Maximum takeoff (5 min.) Propeller rpm (max.) Gas Generator speed (max.) 2080 97% 2080 100% 2080 100% --- --- - - 98.5% 2080 98.5% --- - - 100.5% 2080 100% 2080 100% 2080 102% 1950 98.5% 1950 100% --- --- --- --- 2080 101.5% 2080 101.5% --- --- --- --- 2080 100.1% 2080 101.5% --- --- --- --- 2080 101.5% 2080 101.5% --- --- --- --- H75-100 H75-200 H85-100 H85-200 Maximum continuous Propeller rpm (max.) Gas Generator speed (max.) Takeoff (5 min) Propeller rpm (max.) Gas Generator speed (max.) 2080* 101.1% 2080* 101.5% 2080 101.5% 2080 101.5% 2080 101.2% 2080 101.5% 2080** 101.5% 2080** 101.5% * See NOTE 22 ** See NOTE 24 Refer also to the Installation Manual and Operation Manual. TCDS E00048EN Page 4 of 9 NOTE 3. M601E-11 M601E-11S M601E-11A M601E-11AS M601F M601D-11 H80 H80-100 Maximum continuous (max.) Takeoff at sea level (max.) (5 min.) Takeoff (5 min) (max) with water injection Maximum takeoff (5 min.) (max.) Starting 1274oF (690oC) 1355oF (735oC) 1355oF (735oC) --- 1346oF (730oC) 1310ºF (710°C) 1310ºF (710°C) --- --- 1346°F(730°C) 1400oF (760oC) 1355oF (735oC) 1355oF (735oC) 1436oF (780oC) - - 1274ºF (690ºC) 1355ºF (735ºC) --- --- - - 1436oF (780oC) 1436oF (780oC) --- --- - - 1382oF (750oC) 1436oF (780oC) --- --- - - H80-200 H75-100 H75-200 H85-100 H85-200 Maximum continuous (max.) Takeoff at sea level (max.) (5 min.) 1436oF (780oC) 1436oF (780oC) 1418ºF (770°C) 1436ºF (780°C) 1436oF (780oC) 1436oF (780oC) 1418ºF (770ºC) 1436ºF (780 ºC 1436oF (780oC) 1436oF (780oC) NOTE 4. TORQUE LIMITATIONS 100% torque equals 1896 lb-ft. for M601D-11, M601E-11/-11S, and M601E-11A/-11AS and 1964 lb-ft. for M601F and 2021 lb-ft. for H80, H80-100 and H80-200 100% torque equals 2021 lb-ft. for H80, H80-100, H80-200 and 1896 lb-ft for H75-100, H75-200 and 2146 lb-ft for H85-100, H85-200. M601E-11 M601E-11S M601E-11A M601E-11AS M601F M601D-11 H80 H80-100 H80-200 Maximum continuous lb-ft (max.) applies within range of 1800 rpm to max. cont. speed limit Takeoff at sea level (5 min) lb-ft (max.) applies at takeoff speed limit Takeoff (5 min.) with water injection lb-ft (max.) applies at 2080 rpm Maximum takeoff (5 min.) (max.) lb-ft (max.) applies at 2080 rpm 1896(2570 Nm) 1896(2570 Nm) 1896(2570 Nm) --- 1782(2415 Nm) 1782(2415 Nm) --- --- 1964(2665 Nm) 1964(2665 Nm) 1964(2665 Nm) 1964(2665 Nm) 1630(2210 Nm) 1630(2210 Nm) --- --- 2021(2740 Nm) 202 (2740 Nm) --- --- H75-100 H75-200 H85-100 H85-200 Maximum continuous lb-ft (max.) applies within range of 1800 rpm to max. cont. speed limit Takeoff at sea level (5 min) lb-ft (max.) applies at takeoff speed limit 1896(2570 Nm)* 1896(2570 Nm)* 2019(2737 Nm) 1896(2570 Nm) 2146(2910 Nm) 2146(2910 Nm) 2146(2910 Nm)** 2146(2910 Nm)** * See NOTE 22 ** See NOTE 24 NOTE 5. FUEL AND OIL LIMITATIONS FUEL Fuel pressure at the main fuel filter intake must be within the range as referenced in the Installation Manual. Temperature at the fuel pump inlet in the range of -50oC (-58oF) to +60oC (140oF). TCDS E00048EN Page 5 of 9 OIL Pressure at the gas generator speed of 80 to 100%: min. 0.18 to max. 0.27 MPa (26.1 to 39.1 psi) Pressure at the gas generator speed below 80%: min 0.12 MPa (17.4 psi) Pressure at oil temperature below 0oC (32oF): max. 0.35 MPa (50.8 psi) Temperature: min. -20oC (-4oF) max. +85oC (185oF) NOTE 6. ACCESSORY DRIVE LIMITATIONS The following apply to the accessory gearbox drives, which are provided by the engine and included in the basic engine weight: Drive Sense of Rotation Speed ratio Max. Torque Nm lb.-in.) Maximum Overhang Nm (lb.-in.) Starter/generator CW .2899 11.2 (100) 21 (186) Spare drive (hydraulic pump drive CCW 0.1974 5.8 (51) M601E: 40 (354) M601D: 4 (35.4) Alternator/engine turning CCW 0.1145 11.5 (102) M601E: 40 (354) M601D: 4 (35.4) Speed Transmitter CW 0.1145 0.5 (4.5) 4 (35.4) NOTE 7. AIR BLEED: Bleed flow limits vary with operating conditions. Representative bleed flow limits are provided below at specific operating conditions. Refer to the appropriate Installation Manual for more detailed information. M601D: Maximum air bleed of 62 g/sec (8.2 l./min) at flight altitude of 2000 m (6560 ft) and air speed of 220 km/hr (120 kt). M601F: Maximum air bleed of 62 g/sec (8.2 lb/min) at flight altitude of 4200 m (13,780 ft) and air speed of 400 km/hr (216 kt). H80, H80-100, H80-200: Maximum air bleed of 80 g/sec (10.58 lb/min) at ground : H=0 m (0 ft) and air speed of 0 km/hr (0 kt), ISA conditions, Gas Generator Rotor Speed=97.8 %. H75-100, H75-200, H85-100, H85-200: Maximum air bleed of 80 g/sec (10.58 lb/min) at ground : H=0 m (0 ft) and air speed of 0 km/hr (0 kt), ISA conditions, Gas Generator Rotor Speed=97.8 %. M601E-11, M601E-11S, M601E-11A, M601E-11AS. M601F (Build Configuration BC01) These engine models can have both a high pressure bleed system (HPBS) and a low pressure bleed system (LPBS). The HPBS is the standard bleed system. The LPBS can be installed as an option and this engine build configuration is indicated on the engine identification plate by the additional designation BC01. HPBS LPBS Maximum Airbleed Flight Altitude True Air Speed g/sec lb/min m ft km/hr Kt 62 44 8.2 5.8 4200 7620 13,780 25,000 400 400 216 216 100 69 13.2 9.1 4200 7620 13,780 25,000 400 400 216 216 TCDS E00048EN Page 6 of 9 The LPBS and HPBS must not be used simultaneously for cabin pressurization/heating. If the LPBS is used then limited bleed flow from the HPBS can be used for deicing purposes only. For details, refer to the Installation Manual. All M601 Models: Use of air bleed when using takeoff power settings is limited. In this circumstance, 25 g/sec (3.3 lb/min) of air from the HPBS can be bled for deicing purpose only. For details, refer to the Installation Manual. Contamination does not exceed the following values for: carbon monoxide: one part per 50,000 parts nitrogen oxide: one part per 300,000 parts NOTE 8. MODEL DESCRIPTION: M601E-11 Basic model. Two rotor, free turbine turboshaft engine. Gas generator with 2 axial compressor stages and 1 centrifugal compressor stage driven by a single stage axial turbine, annular combustor with fuel spray ring, power section with single stage axial turbine and two stage reduction gearbox designed to operate with a dual acting propeller and water injection. M601E-11S Similar to basic model. Designed to operate with single-acting propeller. Propeller governor and propeller overspeed governor added. M601E-11A Similar to basic model. Derated shaft horsepower, no water injection, ITT increased up to 710°C at the max. continuous rating, decreased to 710°C at take-off rating. Max operating altitude up to 30,000 feet, designed to operate with a dual acting propeller. M601E-11AS Similar to M601E-11A. Designed to operate with single-acting propeller. Propeller governor and propeller overspeed governor added. M601F Similar to M601E-11 but with increased power ratings, and increased speed, torque and interturbine temperature redlines. M601D-11 Similar to basic model with derated shaft horsepower. H80 Similar to M601F but with increased power ratings, improved flat ratings, and decreased fuel consumption. H80-100 Similar to M601F but with increased power ratings, improved flat ratings, and decreased fuel consumption. Operate with single-acting propeller. H80-200 Similar to M601F but with increased power ratings, improved flat ratings, and decreased fuel consumption. Operate with double-acting propeller. H75-100 Similar to H80-100 but with decreased power ratings, improved flat ratings, and decreased fuel consumption. Operate with single-acting propeller. H75-200 Similar to H80-200 but with decreased power ratings, improved flat ratings, and decreased fuel consumption. Operate with double-acting propeller. H85-100 Similar to H80-100 but with increased power ratings, improved flat ratings, and decreased fuel consumption. Operate with single-acting propeller. H85-200 Similar to H80-200 but with increased power ratings, improved flat ratings, and decreased fuel consumption. Operate with double-acting propeller. NOTE 9. The M601 series engines meet the requirements of 14 CFR § 33.68 for operation in icing conditions as defined in 14 CFR part 25, Appendix C, when the intake system conforms with the approved design (Part Number (P/N) B 062350). NOTE 10. The M601 series engines meet the requirements of 14 CFR § 33.65 for surge free operation, when the intake system conforms with the approved design (P/N B 062350). NOTE 11. The M601 series engines meet the requirements of 14 CFR § 33.77 for bird ingestion when the intake system conforms with the approved design (P/N B 062350). NOTE 12. Life limits for critical rotating components are published in the M601E-11/M601E-11A/M601F Maintenance Manual, P/N 0982302, the M601D-11 Maintenance Manual, P/N 0982309, and the GE H80/H75/H85 Maintenance Manual, P/N 0983402. TCDS E00048EN Page 7 of 9 NOTE 14. Power may be restored in hot day conditions by means of water injection when accomplished in accordance with the requirements of the Installation Manual and Operation Manual. This applies to M601E-11, M601E-11S and M601F engine models only. NOTE 15. Additives used for improving of anti corrosion and lubrication properties, additives for electric conductivity increase and additives for bonding of free water in the fuel shall be used within the manufacturer's instructions and relevant specifications, and/or with supplementary requirements of authorities. TCDS E00048EN Page 8 of 9 NOTE 16. NOTE 17. NOTE 18. Each of the documents listed below must state that it is approved by the European Aviation Safety Agency or, for approvals made before September 28, 2003, by the Czech Republic CAA. Any such documents, including those approved under a delegated authority, are accepted by the FAA and are considered FAA approved. ● Service bulletins, ● Structural repair manuals, ● Vendor manuals, ● Aircraft flight manuals, ● Overhaul and maintenance manuals These approvals pertain to the type design only. DELETED. APPLICABLE INSTALLATION, MAINTENANCE & OVERHAUL MANUALS: The following Instructions for Continued Airworthiness (ICA) have been accepted under the requirments of 14 CFR § 33.4 (Refer to the table on this Note for specific engine models) The following overhaul manual set, part number (P/N), 0973001, for engine models H75-100, H75- 200, H80, H80-100, H80-200, H85-100, H85-200 includes the following: 1) Engine OverHaul Manual (EOHM), H80-4296G-00002-01 2) Component Maintenance Manual (CMM), H80-429G-00003-00 3) Standard Practice Manual (SPM), SPM-H80-4296G-00 Part 1 4) Illustrated Tools and Equipment Manual (ITEM), H80-4296G-00004-00 Part 1, H80- 4296G-00004-00 Part 2 5) Illustrated Part Catelog (IPC), H80-4296G-00000-00 Operating and Service Instructions Manuals required by 14CFR 33.5 and 14 CFR 33.4 Engine Model Installation Manual Operation Manual Maintenance Manual M601D-11 0982511 0982415 0982309 M601E-11 0982504 0982406 0982302 M601E-11S M601E-11A M601E-11AS M601F 0982509 0982413 0982302 H80, H80-100, H80-200 0983202 0983302 0983402 H75-100, H75-200 H85-100, H85-200, H85- 200-BC04 Engine Build Configuraiton H75-100-BC03 0983764 0983765 0983766 H75-100-BC01E 0983769 0983770 0983766 H80-100-BC01E TCDS E00048EN Page 9 of 9 NOTE 19. The following emissions standards promulgated in 14 CFR part 34, Amendment 5, effective December 31, 2012, and 40 CFR part 87, effective July 18, 2012, have been complied with for: H80, H80-100, H80-200, H75-100, H75-200, H85-100, and H85-200 engine models. Fuel Venting Emission Standards: 14 CFR §§ 34.10(b) and 34.11; in addition, 40 CFR §§ 87.10(b) and 87.11. NOTE 20. Build Configuration (BC01E) for H75‐100, an electronic Engine Control System ( EECS) can be installed on H75‐100 engine with a 1950 RPM reduction gearbox and it is indicated on the engine identification plate by the designation BC01E. It is an electronic control system enabling single‐power‐lever engine/propeller control, automatic engine starting and parameter control & limiting functions. The Operating and Service Instructions may be found in Installation Manual No.EIM‐0983769, Operation Manual No.EOM‐0983770, and Maintenance Manual No.EMM‐0983766. NOTE 21. Build Configuration (BC02) for M601E-11: Equivalent flight cycles before TBO extended to 4000. Hourly TBO limit is unchanged. Engines with build configuration BC02 will have this designation on the engine identification plate. NOTE 22. Build Configuration (BC03) for H75-100: Low RPM speed reduction gearbox option. Engine ratings, operational limits, dimensions, and weight are unchanged. Maximum propeller shaft speed is 1900 RPM and maximum torque is 2076 lb-ft. Engines with build configuration BC03 will have this designation on the engine identification plate. The Operating and Service Instructions are found in the Installation Manual No. 0983764, Operation Manual No. 0983765, and Maintenance Manual No. 0983766. NOTE 23. Build Configuration (BC01E) for H80-100 – an EECS can be installed on H80-100 engine with 2080 RPM reduction gearbox. The Build Configuration is indicated on the engine identification plate by the designation BC01E. It is an electronic control system enabling single-power-lever engine/propeller control, automatic engine starting and parameter control & limiting functions. The Operating and Service Instructions may be found in Installation Manual No.EIM-0983769, Operation Manual No.EOM-0983770, and Maintenance Manual No.EMM-0983766. NOTE 24. Build Configuration (BC04) for H85-200 - Reduction gearbox with 1950 RPM is installed on H85- 200 and this engine build configuration is indicated on the engine identification plate by the additional designation BC04. The engine ratings, operational limits, dimensions, and weight remain unchanged. Maximum propeller shaft speed is 1950 RPM and maximum torque is 2290 lb-ft. The Operating and Service Instructions are found in the Installation Manual No. 0983202, Operation Manual No. 0983302, and Maintenance Manual No. 0983402. ----END---- ``` ## ADs (22, in force first) - [AD 2025-18-08](https://openairdocs.org/ad/2025-18-08): Engine Mount Section; Turbine Engine Compressor Section · GE Aviation Czech s.r.o. M601D-11, M601E-11, M601E-11A and 3 more. Effective Oct 21, 2025 - [AD 2024-03-05](https://openairdocs.org/ad/2024-03-05): Turbine Engine Reduction Gear · GE Aviation Czech s.r.o. M601D-11, M601E-11, M601E-11A and 3 more. Effective Apr 17, 2024 - [AD 2024-02-04](https://openairdocs.org/ad/2024-02-04): Turbine Engine Compressor Section · GE Aviation Czech s.r.o. M601E-11, M601E-11A, M601E-11AS and 1 more. Effective Mar 28, 2024 - [AD 2024-01-03](https://openairdocs.org/ad/2024-01-03): Engine (Turbine/Turboprop) · GE Aviation Czech s.r.o. H75-100, H75-200, H80 and 4 more. Effective Feb 27, 2024 - [AD 2023-12-24](https://openairdocs.org/ad/2023-12-24): Engine · GE Aviation Czech s.r.o. M601E-11AS, M601E-11S, H75-100 and 2 more. Effective Aug 15, 2023 - [AD 2023-01-10](https://openairdocs.org/ad/2023-01-10): Turbine Engine Compressor Section · GE Aviation Czech s.r.o. M601E-11, M601E-11A, M601E-11AS and 2 more. Effective Mar 13, 2023 - [AD 2022-26-01](https://openairdocs.org/ad/2022-26-01): Turbine Engine Combustion Section · GE Aviation Czech s.r.o. M601D-11, M601E-11, M601E-11A and 10 more. Effective Jan 26, 2023 - [AD 2022-14-12](https://openairdocs.org/ad/2022-14-12): Turbine Engine Reduction Gear · GE Aviation Czech s.r.o. M601F, M601E-11, M601E-11A and 3 more. Effective Aug 18, 2022 - [AD 2022-13-16](https://openairdocs.org/ad/2022-13-16): Turbine Engine Compressor Section · GE Aviation Czech s.r.o. M601D-11. Effective Aug 1, 2022 - [AD 2021-20-21](https://openairdocs.org/ad/2021-20-21): Engine Controls, Propeller Governor · GE Aviation Czech s.r.o. H80-200 and H85-200. Effective Nov 18, 2021 - [AD 2021-15-10](https://openairdocs.org/ad/2021-15-10): Fuel Control/Turbine Engines · GE Aviation Czech s.r.o. H75-200, H80-100 and H80-200. Effective Sep 21, 2021 - [AD 2020-23-01](https://openairdocs.org/ad/2020-23-01): Fuel Control/Turbine Engines · GE Aviation Czech s.r.o. H75-200, H80-100, H80-200 and 7 more. Effective Nov 24, 2020 - [AD 2020-15-03](https://openairdocs.org/ad/2020-15-03): Turbine Section · GE Aviation Czech s.r.o. M601D-11, M601E-11, M601E-11A and 3 more. Effective Aug 31, 2020 - [AD 2020-15-04](https://openairdocs.org/ad/2020-15-04): Engine Collector/Tailpipe/Nozzle · GE Aviation Czech s.r.o. H75-100, H75-200, H80 and 10 more. Effective Aug 31, 2020 - [AD 2015-17-20](https://openairdocs.org/ad/2015-17-20): Gas generator turbine (GGT) blades · GE Aviation Czech s.r.o. M601E-11, M601E-11A and M601F. Effective Oct 1, 2015 - [AD 2015-14-02](https://openairdocs.org/ad/2015-14-02): Reduction gearbox and supporting cone · GE Aviation Czech s.r.o. M601E-11, M601E-11A and M601F. Effective Aug 18, 2015 - [AD 2024-06-02](https://openairdocs.org/ad/2024-06-02) (historical): Engine Mount Section; Turbine Engine Compressor Section · GE Aviation Czech s.r.o. M601D-11, M601E-11, M601E-11A and 3 more. Effective Apr 11, 2024 - [AD 2023-01-07](https://openairdocs.org/ad/2023-01-07) (historical): Engine (Turbine/Turboprop) · GE Aviation Czech s.r.o. H75-100, H75-200, H80 and 4 more. Effective Feb 21, 2023 - [AD 2021-13-07](https://openairdocs.org/ad/2021-13-07) (historical): Engine (Turbine/Turboprop) · GE Aviation Czech s.r.o. M601D-11, M601E-11, M601E-11A and 3 more. Effective Jun 30, 2021 - [AD 2018-16-10](https://openairdocs.org/ad/2018-16-10) (historical): Engine Controls · GE Aviation Czech s.r.o. H80-200. Effective Sep 12, 2018 - [AD 2018-03-22](https://openairdocs.org/ad/2018-03-22) (historical): Turbine Section · GE Aviation Czech s.r.o. M601D-11, M601E-11, M601E-11A and 3 more. Effective Mar 21, 2018 - [AD 2016-07-13](https://openairdocs.org/ad/2016-07-13) (historical): Engine power turbine (PT) disk · GE Aviation Czech s.r.o. M601E-11. Effective Apr 22, 2016 ## Registered aircraft by registry model (OpenAirDocs) - [GE AV H80-100](https://openairdocs.org/engine/ge-av-h80-100): 28 aircraft (registry code 30170) - [Walter M601 series](https://openairdocs.org/engine/walter-m601-series): 28 aircraft (registry codes 64002, 64003) - [Walter M601E-11](https://openairdocs.org/engine/walter-m601e-11): 8 aircraft (registry code 64006) - [Walter M601D-11](https://openairdocs.org/engine/walter-m601d-11): 7 aircraft (registry code 64011) - [Walter M601E-11A](https://openairdocs.org/engine/walter-m601e-11a): 2 aircraft (registry code 64008) - [GE AV H80](https://openairdocs.org/engine/ge-av-h80): 1 aircraft (registry code 30177) - [GE AV M601D-11](https://openairdocs.org/engine/ge-av-m601d-11): 1 aircraft (registry code 30176) - [GE AV M601E-11](https://openairdocs.org/engine/ge-av-m601e-11): 1 aircraft (registry code 30171) - [GE Avn CZ H75-100](https://openairdocs.org/engine/ge-avn-cz-h75-100): 1 aircraft (registry code 30180) - [GE H75-200](https://openairdocs.org/engine/ge-h75-200): 1 aircraft (registry code 30182) - [Walter M601E-11S](https://openairdocs.org/engine/walter-m601e-11s): 1 aircraft (registry code 64007) - [GE AV H80-200](https://openairdocs.org/engine/ge-av-h80-200): 0 aircraft (registry code 30178) - [GE AV M601E-11A](https://openairdocs.org/engine/ge-av-m601e-11a): 0 aircraft (registry code 30173) - [GE AV M601E-11AS](https://openairdocs.org/engine/ge-av-m601e-11as): 0 aircraft (registry code 30174) - [GE AV M601E-11S](https://openairdocs.org/engine/ge-av-m601e-11s): 0 aircraft (registry code 30172) - [GE AV M601F](https://openairdocs.org/engine/ge-av-m601f): 0 aircraft (registry code 30175) - [Motorlet M601D-11](https://openairdocs.org/engine/motorlet-m601d-11): 0 aircraft (registry code 46006) - [Motorlet M601E-11](https://openairdocs.org/engine/motorlet-m601e-11): 0 aircraft (registry code 46001) - [Motorlet M601E-11A](https://openairdocs.org/engine/motorlet-m601e-11a): 0 aircraft (registry code 46003) - [Motorlet M601E-11AS](https://openairdocs.org/engine/motorlet-m601e-11as): 0 aircraft (registry code 46004) - [Motorlet M601E-11S](https://openairdocs.org/engine/motorlet-m601e-11s): 0 aircraft (registry code 46002) - [Motorlet M601F](https://openairdocs.org/engine/motorlet-m601f): 0 aircraft (registry code 46005) - [Walter M601E-11AS](https://openairdocs.org/engine/walter-m601e-11as): 0 aircraft (registry code 64009) - [Walter M601F](https://openairdocs.org/engine/walter-m601f): 0 aircraft (registry code 64010) --- 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.