# TCDS 1E6: Honeywell Aerospace US LLC - Type: Type certificate data sheet - Status: Current - Holder: Honeywell Aerospace US LLC - Revision: 4 - Revised: March 27, 2026 - Product: Engine - Data sheet PDF: https://openairdocs.org/files/sha256/1e/b7/1eb70c3b14e62179141091711161903993bfd52bd64ecd8d1cad67343a8fe456 - FAA DRS: https://drs.faa.gov/browse/excelExternalWindow/DRSDOCID185972978420260605173338.0001 - Page: https://openairdocs.org/tcds/1E6 ## Models (1) As the data sheet lists them. - LTC1B-1 ## What the data sheet says From the PDF's text layer, line by line; tables lose their columns. The PDF is the record. ```text DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION 1E6 Revision 4 Honeywell Aerospace US LLC (AlliedSignal) Textron Lycoming) LTC1B-1 March 27, 2026 TYPE CERTIFICATE DATA SHEET NO. 1E6 Engines of models described herein conforming with this data sheet (which is pa1t of Type Ce1tificate No. 1E6) and other approved data on file with the Federal Aviation Administration (FAA) meet the minimum standards for use in certified aircraft in accordance with pe1tinent 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. TYPE CERTIFICATE HOLDER: Honeywell Aerospace US, LLC 111 South 34th Street Phoenix, AZ 85034 TYPE CERTIFICATE HOLDER RECORD: Honeywell International Inc. 111 South 34th Street Phoenix, AZ 85034 TYPE CERTIFICATE HOLDER RECORD: AlliedSignal Inc. 111 South 34th Street Phoenix, AZ 85034 Page No. 1 2 3 Rev. No. 4 4 3 1E6 2 of 3 Model Honeywell LTC1B-1 Type Shaft-turbine for Helicopters Five stage axial compressors Single stage centrifugal compressor Reverse-flow annular combustion chamber Single stage compressor turbine Single stage power turbine 3.22:1 Reduction gear ratio Ratings Maximum continuous at sea level; shaft hp., jet thrust, compressor r.p.m., power turbine r.p.m 770-96-24 140-20-137 Takeoff at sea level; shaft hp., jet thrust , compressor r.p.m., power turbine r.p.p 860-102-24 440-20-156 Fuel control Triumph Group, Inc. Model TA-1 Fuel JP-1 (M) or JP-4 (MIL-DTL-5624) Lubricating oil MIL-PRF-7808 Principal dimensions: Length, overall, in. 47.80 Diameter, nominal, in. 23.80 C.G. Location Fwd. of rear mounting pad centerline 4.238 Below engine centerline 0.066 Drive shaft type Special Weight (dry) lb. 480 (include basic engine with all essential accessories but excluding starter-generator, oil tank, generator cooling system, and exhaust system) Ignition system Bendix-Scintilla ignition unit, low voltage capacitor discharge type, P/N 10/80375-10 with two Bendix-Scintilla P/N 10-102792-1 spark ignitors. Certification Basis Type Certificate Number 1E6, Issued dated June 16, 1960 Date of application August 29, 1957 Production Basis None. The manufacturer does not hold a production certificate for the production of engines under this certificate and, therefore, each engine so produced is subject to a detailed inspection for workmanship and conformity with the approved data by a Federal Aviation Agency representative will tag the engine with Tag Form 186. NOTE 1: Maximum permissible temperatures are as follows: 1E6 3 of 3 Compressor Turbine, r.p.m. 24440 Power Turbine, r.p.m. 20370 NOTE 2: Maximum permissible temperatures are as follows: Turbine exhaust gas temperatures at the tail pipe: Takeoff (5-mintues) 1045℉ (563℃) Maximum continuous 1000℉ (538℃) Maximum for acceleration 1400℉ (760℃) 1200℉ (649℃) for reminder of the transient time Starting (5-minutes) 1400℉ (760℃) Oil inlet temperature 190℉ (88℃) NOTE 4: The engine ratings are guaranteed at the minimum and are based on static sea level conditions as follows: Compressor inlet air 59℉ and 29.92 in. Hg. Inlet nozzle TE 516 Exhaust diffuser extension EXP-1287 with an exit area of 203 sq. in. Exhaust inner cone assy. EXP-1799 No aircraft accessory loads No compressor air bleed No anti-icing airflow NOTE 5: The following accessory drive provisions are incorporated: Rotation Maximum Torque Maximum Drive (C-Clockwise Gear (in.) -lb. Overhang Gas Producer CC-Counter-Clockwise Ratio Cont. Static Moment (in.-lb.) Tachometer C .167 7 50 -- Starter- Generator C .283 150 1290 500 Spare C .147 68 330 25 Power Turbine Tachometer CC .695 7 50 -- NOTE 6: This engine meets the Federal Aviation Administration requirements for adequate turbine disc integrity and rotor blade containment and does not require external armoring. This engine has demonstrated satisfactory operation in icing conditions as defined in 4B.1(b) 7 and 8. NOTE 7: The engine is not eligible for installation in certificated aircraft until approved installation, operation, maintenance, and overhaul manuals are available. --------------END------------ NOTE 3: Fuel and oil pressure limits Fuel, at engine inlet 14.7 p.s.i. a min. TO 50.0 p.s.i.g. max. Oil, at engine inlet 0 to 15 p.s.i.g. Oil pressure at idle 10 p.s.i.g. min. Operating range 70-90 p.s.i.g. ``` ## ADs None name its models. ## Registered aircraft by registry model (OpenAirDocs) - [Alliedsign LTC1B-1](https://openairdocs.org/engine/alliedsign-ltc1b-1): 0 aircraft (registry code 02522) - [Honeywell LTC1B-1](https://openairdocs.org/engine/honeywell-ltc1b-1): 0 aircraft (registry code 33925) - [Lycoming LTC1B-1](https://openairdocs.org/engine/lycoming-ltc1b-1): 0 aircraft (registry code 41608) --- 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.