The Info List - Lycoming T53

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The Lycoming T53, (company designation LTC-1) is a turboshaft engine used on helicopters and (as a turboprop) fixed-wing aircraft since the 1950s. It was designed at the Lycoming Turbine
Engine Division in Stratford, Connecticut by a team headed by Anselm Franz, who was the chief designer of the Junkers Jumo 004
Junkers Jumo 004
during World War II. A much larger engine, similar in overall design, became the Lycoming T55. Both engines are now produced by Honeywell Aerospace.


1 Variants

1.1 Military designations 1.2 Civil designations

2 Applications 3 Specifications (T53-L-701)

3.1 General characteristics 3.2 Components 3.3 Performance

4 References 5 External links

Variants[edit] Military designations[edit]

T53-L-1A T53-L-1B 860 hp (645 kW) T53-L-3 T53-L-5 960 hp (720 kW) T53-L-7 T53-L-11 1100 shp (820 kW) T53-L-13 T53-L-13B 1400 shp (1044 kW) improved L-11 T53-L-701 1,400 hp (1044 kW) Turboprop
variant used on Mohawk and AIDC T-CH-1 T53-L-703 1,800 hp (1343 kW) improved durability variant of the L-13B

Civil designations[edit]

T5307A commercial L-7 T5309A commercial L-9A T5309B commercial L-9B T5309C similar to T5309A but with L-11 combustion chamber T5311A 1100 shp (820 kW) T5313A 1400 shp (1044 kW) commercial variant of the L-13 T5313B 1400 shp (1044 kW) commercial variant of the L-13 T5317A 1500 shp (1119 kW) improved variant of the L-13 LTC1B-2 company designation for L-1A LTC1F-1 company designation for L-3 LTC1F-2 company designation for L-7 LTC1K-1 company designation for L-5 LTC1K-2 company designation for L-9 LTC1K-2A company designation for L-9A LTC1K-2B company designation for L-9B LTC1K-4 company designation for L-13 LTC1K-4A for tilt-wing / tilt-rotor aircraft (Canadair CL-84) LTC1K-4K 1550 shp (1156 kW) direct drive variant of the L-13B LTC1K-5 company designation for L-11


(T53-L-701) AIDC XC-2 Bell 204B (T5311A) Bell 205A (T5313B) Bell 205A-1 (T5313B and T5317A) Bell AH-1 Cobra
AH-1 Cobra
(T53-L-703) Bell UH-1H Iroquois (T53-L-703) Bell XV-15
Bell XV-15
(LTC1K-4K) Boeing Vertol VZ-2
Boeing Vertol VZ-2
(YT53) Canadair CL-84 Doak VZ-4 F+W C-3605 Grumman OV-1D Mohawk (T53-L-701) Kaman HH-43 Huskie Kaman K-1200
Kaman K-1200
(T5317A) Kaman K-MAX Ryan VZ-3 Vertiplane DB Class 210, diesel railway locomotive

Specifications (T53-L-701)[edit] Data from Flight International[2] General characteristics

Type: Turboshaft Length: 58.4 in (1,483 mm) Diameter: 23 in (584 mm) Dry weight: 688 lb (312kg)


Compressor: 5-stage axial compressor and 1-stage centrifugal compressor Combustors: reverse flow Turbine: 2-stage high pressure turbine; 2-stage power turbine


Maximum power output: 1,451 shp (1,082 kW) Overall pressure ratio: 7.4 Air mass flow: 10.7 lb/s (4.853 kg/s) Power-to-weight ratio:


^ https://www.flightglobal.com/pdfarchive/view/1955/1955%20-%201400.html?search=XT53 ^ Turbine
Engines of the World, 1975 

Gunston, Bill (2006). World Encyclopedia of Aero Engines, 5th Edition. Phoenix Mill, Gloucestershire, England, UK: Sutton Publishing Limited. p. 132. ISBN 0-7509-4479-X. 

External links[edit]

Wikimedia Commons has media related to Lycoming T53.

Honeywell T53 page Honeywell T53 Worldwide Parts Distributor page

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Lycoming aircraft engines

Opposed piston engines

O-145 O-233 IO-233 O-235 O-290 O-320 O-340 O-360 (O-360 variants) IO-390 O-435 O-480 O-540 TIO-541 GSO-580 IO-580 IO-720 O-1230

Radial engines and H engines

R-680 R-7755 H-2470


PLF1 ALF 502/YF102 LF 507


AGT1500 LTS101/LTP101 T53 T55

Aero-derivative marine gas turbines


Joint development

Avco (Lycoming)/Pratt & Whitney: T800-APW (Turboshaft)

See also

AlliedSignal Aerospace/Honeywell Aerospace

v t e

Garrett/AlliedSignal/Honeywell aircraft engines


AGT1500 HTS900 LTS101/LTP101* T53* T55* TPE331 TPF351


ALF 502* ATF3 F109 FX5 HTF7000 (AS907) LF507* TFE731

Joint development

CFE Company:

CFE738 (Turbofan)

General Electric/Honeywell:

LV100 (Turboshaft)

International Turbine
Engine Corporation:

F124/TFE1042 F125 (Turbofans)


CTS800 (Turboshaft)

Note: AVCO Lycoming/Textron Lycoming engines marked with *

v t e

United States
United States
military gas turbine aircraft engine designation system


J30 J31 J32 J33 J34 J35 J36 J37 XJ38 J39 J40 XJ41 J42 J43 J44 J45 J46 J47 J48 XJ49 J51 J52 J53 J54 J55 J56 J57 J58 J59 J60 J61 J63 J65 J67 J69 J71 J73 J75 J79 J81 J83 J85 J87 J89 J91 YJ93 J95 J97 J99 J100 YJ101 J102 J400 J401 J402 J403 J700

Turboprops/ Turboshafts

T30 T31 T33 T34 T35 T36 T37 T38 T39 T40 T41 T42 T43 T44 T45 T46 T47 T48 T49 T50 T51 T52 T53 T54 T55 T56 T57 T58 T60 T61 T62 T63 T64 T65 T66 T67 T68 T69 T70 T71 T72 T73 T74 T76 T78 T80 T100 T101 T400 T405 T406 T407 T408 T700 T701 T702 T703 T706 T708 T800 T900 T901


TF30 TF31 TF32 TF33 TF34 TF35 TF37 TF39 TF41 F100 F101 F102 F103 F104 F105 F106 F107 F108 F109 F110 F112 F113 F117 F118 F119 YF120 F121 F122 F124 F125 F126 F127 F128 F129 F130 F135 F136 F137 F138 F400 F401 F402 F404 F405 F408 F412 F414 F415

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