# TCDS TE2CH: Light Helicopter Turbine Engine Company (LHTEC)

- Type: Type certificate data sheet
- Status: Current
- Holder: Light Helicopter Turbine Engine Company (LHTEC)
- Revision: 6
- Revised: May 7, 2025
- Product: Engine
- Certification basis: Part 33
- Data sheet PDF: https://openairdocs.org/files/sha256/29/14/29149cb7547ef106f26989f014153e928e90ab04d0c3be7405fc8158395d784a
- FAA DRS: https://drs.faa.gov/browse/excelExternalWindow/DRSDOCID101223517920250508173248.0001
- Page: https://openairdocs.org/tcds/TE2CH

## Models (4)

As the data sheet lists them.

- CTS800-0
- CTS800-4N
- CTS800-4A
- CTS800-4AT

## 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 
 
 
TYPE CERTIFICATE DATA SHEET NO. TE2CH 
 
Engines of models described herein conforming to this data sheet (which is part of Type Certificate No. TE2CH) 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: Light Helicopter Turbine Engine Company (LHTEC) 
(See NOTE 12) 2001 South Tibbs Avenue 
Indianapolis, IN 46241 
 
Models CTS800-0, CTS800-4N, CTS800-4A, CTS800-4AT 
 
Type  
Free turbine turboshaft engine; fully metric two spool modular design; inlet particle separator (IPS) with scavenge 
blower; two stage centrifugal compressor; annular, reverse-flow combustor; two stage gas generator turbine; two stage 
power turbine; dual channel full authority digital engine control; self-contained lubrication and electrical systems; top 
mounted accessory gearbox. (See NOTE 13) 
 
Ratings (See NOTE 3)   
 CTS800-0 CTS800-4N CTS800-4A CTS800-4AT 
30-Second OEI     
Power kW(SHP) N/A 1208 (1621) 1221 (1637) 1221 (1637) 
Gas Generator Speed (RPM) N/A 46681 46634 46545 
Output Shaft Speed (RPM) N/A 6402 23000 23000 
Measured Gas Temperature °C (°F) * N/A 978 (1794) 976 (1789) 972 (1782) 
 
2- Minute OEI 
Power kW(SHP) N/A 1108 (1487) 1119 (1501) 1119 (1501) 
Gas Generator Speed (RPM) N/A 45556 45511 45495 
Output Shaft Speed (RPM) N/A 6402 23000 23000 
Measured Gas Temperature °C (°F) * N/A 928 (1704) 926 (1699) 924 (1696) 
 
2-1 /2 Minute OEI 
Power kW(SHP) 1058 (1419) N/A N/A  N/A  
Gas Generator Speed (RPM) 45329 N/A N/A  N/A  
Output Shaft Speed (RPM) 23000 N/A N/A  N/A  
Measured Gas Temperature °C (°F) * 899 (1650) N/A N/A  N/A  
 
 
 
PAGE 1 2 3 4 5 6 7 
REV. 6 6 6 6 6 6 6 
TE2CH 
Revision 6 
 
LHTEC 
CTS800-0 
CTS800-4N 
CTS800-4A 
CTS800-4AT 
 
May 7, 2025

TE2CH 2 
 
Ratings (See NOTE 3) (Continued) 
CTS800-0 CTS800-4N CTS800-4A CTS800-4AT 
 
Continuous OEI 
Power kW (SHP) 1014 (1361) 1014 (1361) 1024 (1373) 1024 (1373) 
Gas Generator Speed (RPM) 44896 44576 44527 44547 
Output Shaft Speed (RPM) 23000 6402 23000 23000 
Measured Gas Temperature °C (°F) * 879 (1615) 885 (1626) 883 (1621) 884 (1623) 
 
Takeoff (5 min) and 30-min AEO ** 
Power kW (SHP) 1014 (1361) 1014 (1361) 1024 (1373) 1024 (1373) 
Gas Generator Speed (RPM) 44896 44576 44527 44547 
Output Shaft Speed (RPM) 23000 6402 23000 23000 
Measured Gas Temperature °C (°F) * 879 (1615) 885 (1626) 883 (1621) 884 (1623) 
 
Maximum Continuous 
* For the CTS800-4N, CTS800-4A, and CTS800-4AT this value is compensated Power Turbine Inlet  
** 30-minute AEO only applies to the CTS800-4AT as stated in Special Condition 33-021-SC.  
Temperature (PTIT) Output Shaft Gear Ratio (CTS800-0, CTS800-4A, CTS800-4AT) 1:1 
Output Shaft Gear Ratio (CTS800-4N) 3.593:1 
Reduction Gearbox (with shared lubrication system) included in the CTS800-4N configuration. 
Principal Dimensions of Basic Engine 
Refer to installation drawing provided in installation design manual for dimensions and center of gravity locations. (See 
NOTE 10) 
Weight (maximum) 
Fuels 
Refer to the engine operating manual for approved fuel types, limitations on their use, and approved fuel additives. (See 
NOTE 10) 
 
Lubricating Oils 
Refer to the engine operating manual for approved oil types and limitations on their use. (See NOTE 10) 
 
Oil Tank Volume (CTS800-0):  3.4 liter (0.9 gal) 
Oil Tank Volume (CTS800-4N, CTS800-4A, CTS800-4AT): 3.2 liter (0.83 gal) 
Power kW (SHP) 944 (1266) 955 (1281) 963 (1292) 960 (1287) 
Gas Generator Speed (RPM) 44304 43983 43935 43980 
Output Shaft Speed (RPM) 23000 6402 23000 23000 
Measured Gas Temperature °C (°F) * 852 (1567) 861 (1582) 858 (1577) 861 (1582) 
 
Dry Weight Kg (lb) CTS800-0 142.9 (315) 
Dry Weight Kg (lb) CTS800-4N 185.1 (408) 
Dry Weight Kg (lb) CTS800-4A 170.1 (375) 
Dry Weight Kg (lb) CTS800-4AT 170.1 (375)

3 TE2CH 
 
 
Certification Basis (CTS800-0) 
14 CFR part 33 dated June 3, 1964, as amended by 33-1 through 33-14 inclusive. Original application for Type 
Certificate dated May 27, 1987. Type Certificate No. TE2CH issued for the Model CTS800-0 engine on September 10, 
1993. 
 
Certification Basis (CTS800-4N) 
14 CFR part 33 dated June 3, 1964, as amended by 33-1 through 33-18 inclusive. Original application for amended 
Type Certificate dated May 24, 1996. Type Certificate No. TE2CH amended to include Model CTS800-4N engine on 
December 18, 2003. 
 
Certification Basis (CTS800-4A) 
14 CFR part 33 dated June 3, 1964, as amended by 33-1 through 33-18 inclusive. Original application for amended 
Type Certificate dated February 16, 2009. Type Certificate No. TE2CH amended to include Model CTS800-4A engine 
on April 11, 2012. 
 
Certification Basis (CTS800-4AT) 
14 CFR part 33 dated June 3, 1964, as amended by 33-1 through 33-18 inclusive and Special Conditions 33-021-SC 
(Light Helicopter Turbine Engine Company (LHTEC), CTS800-4AT; 30-Minute All Engines Operating Power 
Rating). Original application for amended Type Certificate dated April 19, 2017.  Type Certificate No. TE2CH 
amended to include Model CTS800-4AT engine on May 7, 2025. 
 
Production Basis 
(See NOTE 12) 
 
NOTE 1 
   
Temperature Limits CTS800-0 CTS800-4N, 
CTS800-4A 
CTS800-4AT 
Maximum Measured Gas Temperature, °C (°F) *    
30-Second OEI N/A 1007 (1844) 1007 (1844) 
2- Minute OEI N/A 953 (1747) 953 (1747) 
2-1/2 Minute OEI 909 (1668) N/A N/A 
Continuous OEI 889 (1632) 905 (1661) 905 (1661) 
Takeoff (5 min) and 30-min AEO** 899 (1632) 905 (1661) 905 (1661) 
Maximum Continuous 862 (1584) 878 (1612) 878 (1612) 
Starting 850 (1562) CTS800-4A: 850 (1562) 
CTS800-4N: Refer to 
operating manual (See 
NOTE 10) 
850 (1562) 
    
Oil Inlet Temperatures, °C (°F)    
Maximum Steady State 130 (266) 130 (266) 130 (266) 
Maximum Transient (5 min) 149 (300) 149 (300) 149 (300) 
Minimum Starting -54 (-65) MIL-PRF-7808 
-40 (-40) MIL-PRF-23699 
-54 (-65) MIL-PRF-7808 
-40 (-40) MIL-PRF-23699 
-40 (-40)  
Refer to Installation 
Design Manual (See 
NOTE 10) 
Minimum Steady State 49 (120) 49 (120) 49 (120) 
    
Engine External Components Surface 
Temperature Limits 
Refer to Installation 
Design Manual (See 
NOTE 10) 
Refer to Installation 
Design Manual (See 
NOTE 10) 
Refer to Installation 
Design Manual (See 
NOTE 10) 
Fuel Pump Inlet Temperature Refer to Installation 
Design Manual (See 
NOTE 10) 
Refer to Installation 
Design Manual (See 
NOTE 10) 
Refer to Installation 
Design Manual (See 
NOTE 10) 
* For the CTS800-4N, CTS800-4A, and CTS800-4AT, this value is compensated Power Turbine Inlet Temperature (PTIT 
** 30-minute AEO only applies to the CTS800-4AT as stated in Special Condition 33-021-SC.

TE2CH 4 
 
NOTE 2  Fuel and Oil Pressure Limits 
 
Fuel Inlet Pressure Limits - refer to applicable installation design manual for details. (See NOTE 10) 
 
Oil Pressure Limits kPa (psig) CTS800-0 CTS800-0 CTS800-4N, 
CTS800-4A, 
CTS800-4AT 
CTS800-4N, 
CTS800-4A, 
CTS800-4AT 
 Minimum 
kPa (psig) 
Maximum 
kPa (psig) 
Minimum 
kPa(psig) 
Maximum 
kPa (psig) 
     
Start Up 0 (0) 1590 (230) 0 (0) 1590 (230) 
     
Normal Steady State:     
Below 35,000 RPM Gas 
Generator Speed (Ng) 
138 (20) 317 (46) N/A N/A 
Above 35,000 RPM (Ng) 262 (38) 317 (46) 262 (38) 414 (60) 
     
30 Second Transient Limit * 35 (5) N/A 35 (5) 
(CTS800-4A and 
CTS800-4AT) 
N/A 
10 Second Transient Limit ** N/A N/A 35 (5) 
(CTS800-4N) 
N/A 
Maximum oil pressure during starting and initial operation, predicated on a 0.013 m2/sec (13,000 centistokes) oil 
viscosity, shall not persist for more than 2.5 minutes. 
Minimum oil pressure during starting and initial operation shall not persist for more than 60 seconds (except as noted 
in ** below).  
Mixing of oils that conform to different oil specifications is prohibited. 
* Operation in the time limited (shaded) area of the attitude envelope of engine operating manual. (See NOTE 10) 
** Minimum oil pressure may not persist for more than 10 seconds for the CTS800-4N.
 
NOTE 3 
 
The Engine Ratings are based on: 
 
(a) Dynamometer operation corrected to U.S. standard atmosphere, sea level static conditions 
(b) Static sea level standard conditions at 59° F and 29.92 in Hg (101.325 millibars) 
(c) Fuel with a lower heating value of 18,500 BTU per lb. 
(d) No customer bleed extraction 
(e) No anti-ice airflow 
(f) No external accessory loads 
(g) 100 percent inlet total pressure recovery 
(h) Reference exhaust duct discharging to ambient static pressure 
(i) Reference compressor vent loss. 
(j) Dry inlet air.

5 TE2CH 
 
 
NOTE 3 (Continued) 
 
The specified engine power ratings do not represent the flat ratings resulting from application of the output shaft torque 
limits (See NOTE 4). The engine installation design manual contains flat rating curves versus ambient temperature that 
incorporate torque, speed, and PTIT limits, and/or refers to the applicable engine performance computer program 
documentation. (See NOTE 10) 
 
NOTE 4 
Output Shaft Torque Limits 
 
 
CTS800-0 CTS800-4N CTS800-4A and CTS800-4AT 
30- Second OEI N/A 1791 N-m (1321 lb-ft) 499 N-m (368 lb-ft) 
2- Minute OEI  N/A 1649 N-m (1216 lb-ft)  459 N-m (339 lb-ft) 
2-1/2 minute OEI 439 N-m (324 lb-ft)  N/A  N/A 
Continuous OEI 424 N-m (313 lb-ft) 1478 N-m (1090 lb-ft) 411 N-m (303 lb-ft) 
Takeoff (5 min) and 30-min AEO* 424 N-m (313 lb-ft) 1478 N-m (1090 lb-ft) 411 N-m (303 
lb-ft) 
Maximum Continuous 395 N-m (291 lb-ft) 1373 N-m (1012 lb-ft) 381 N-m (281 lb-ft) 
* 30-min AEO only applies to the CTS800-4AT as stated in Special Condition 33-021-SC 
 
NOTE 5 
Accessory Drive Provisions 
 
 
 
 
Drive 
 
Type of 
Drive 
 
Rotation 
Facing 
Pad 
 
 
Ratio to 
Rotor 
 
Drive 
Pad 
RPM** 
Max 
Continuous 
Torque 
N-m (lb-in) 
 
Max Static 
Torque 
N-m (lb-in) 
 
 
Overhung Static Moment 
N-m (lb-in) 
 
Starter/ 
Generator* 
Metric CW 0.273 11956 8.7 (77.4) **** 81.4 (720)*** 18.4 (161) for CTS800-0 
103 (928) for CTS800-4N 
103 (928) for CTS800-4A 
103 (928) for CTS800-4AT 
 
*Driven by Gas Generator Turbine 
**Drive speed based on 100% gas generator speed or 43,796 RPM 
***Maximum torque at starter pad from zero to starter cutoff speed 
**** Power extraction limited in accordance with load limits defined in the engine operating manual. (See NOTE 10) 
 
NOTE 6 
Maximum Allowable Speeds 
 
Gas Generator 
Speed 
RPM (%)* 
Power Turbine 
Speed 
RPM (%)** 
Gas Generator 
Speed 
RPM (%)* 
Engine Output 
Speed 
RPM (%)*** 
CTS800-0 CTS800-0 CTS800-4N CTS800-4N 
 
 
30-Second OEI N/A N/A 46,995 (107.3) 6,402(100.0) 
2-Minute OEI N/A N/A 45,812 (104.6) 6,402(100.0) 
2.5 Minute OEI 45,461 (103.8) 24,150 (105.0) N/A N/A 
Continuous OEI 44,992 (102.7) 24,150 (105.0) 44,794 (102.3) 6,754 (105.5) 
Takeoff (5 min) and 30-min 
AEO**** 
44,992 (102.7) 24,150 (105.0) 44,794 (102.3) 6,754 (105.5) 
Max. Continuous 44,992 (102.7) 24,150 (105.0) 44,120 (100.7) 6,754 (105.5) 
Max Permissible (5 sec 46,026 (105.1) 24,840 (108.0) 47,397 (108.2) 7,170 (112.0) 
transient)

TE2CH 6 
 
NOTE 6 Maximum Allowable Speeds (continued) 
 
Gas Generator 
Speed 
RPM (%)* 
Power Turbine 
Speed 
RPM (%)** 
Gas Generator 
Speed 
RPM (%)* 
Power Turbine 
Speed 
RPM (%)** 
CTS800-4A CTS800-4A CTS800-4AT CTS800-4AT 
 
 
30-Second OEI 46,995 (107.3) 23,575 (102.5) 46,995 (107.3) 23,460 (102) 
2-Minute OEI 45,812 (104.6) 23,575 (102.5) 45,812 (104.6) 23,460 (102) 
2.5 Minute OEI N/A N/A N/A N/A 
Continuous OEI 44,794 (102.3) 23,575 (102.5) 44,794 (102.3) 23,460 (102) 
Takeoff (5 min) and 30-min 
AEO **** 
44,794 (102.3) 23,575 (102.5) 44,794 (102.3) 23,460 (102) 
Max. Continuous 44,120 (100.7) 23,575 (102.5) 44,120 (100.7) 23,460 (102) 
Max Permissible (5 second 47,397 (108.2) 25,760 (112.0) 47,397 (108.2) 25,760 (112.0) 
transient)   
 
* 100% Gas Generator Speed = 43,796 RPM 
** 100% Power Turbine Speed = 23,000 RPM 
*** 100% Engine Output Speed (at Reduction Gearbox) = 6,402 RPM 
**** 30-minute AEO only applies to the CTS800-4AT as stated in Special Condition 33-021-SC 
 
NOTE 7 Maximum available customer bleed air is in accordance with the limits defined in the installation design 
manual. (See NOTE 10) 
 
NOTE 8 Life limits for critical rotating components are published in the Airworthiness Limitations section of the 
following documents: 
Engine Maintenance Manual Document No. 72-09-12 (CTS800-0) 
Engine Line Maintenance Manual Document No. T800-4N-20 (CTS800-4N) 
Engine Line Maintenance Manual Document No. T800-4A-20 (CTS800-4A) 
Engine Line Maintenance Manual Document No. T800-4AT-20 (CTS800-4AT) 
 
NOTE 9  These engines meet the requirements of 14 CFR part 33.77 Amendment 10 (Foreign Object Ingestion) 
without the use of an aircraft inlet protection system. 
 
NOTE 10 For additional performance, authorized operation and detailed installation information, refer to the following 
manuals: 
 
Model Installation Design Manual Operating Manual 
CTS800-0 LHA2002-31.1 LHA6002-26 
CTS800-4N LHA6552-31 LHA6552-26 
CTS800-4A LHA6607-31 LHA6607-26 
CTS800-4AT LHA6623-31 LHA6623-26 
 
NOTE 11 (DELETED) 
 
NOTE 12 Light Helicopter Turbine Engine Company (LHTEC) is a partnership comprised of the Rolls -Royce 
Corporation (formerly Allison) of Indianapolis, Indiana, and Honeywell International Inc. (formerly 
AlliedSignal), of Phoenix, Arizona.  LHTEC is the Type Certificate holder. LHTEC does not hold a FAA 
Production Certificate or other FAA production approval for the CTS800-0, CTS800-4N or CTS800-4A engine 
models. 
 
 CTS800-4AT Production Basis: 
 
 Production Certificate No. 413NM for Honeywell International Inc. under license from LHTEC to manufacture 
their subassemblies, component parts and spares as well as perform the final assembly and testing of completed 
engines. 
 
 Production Certificate No. 310 for Rolls -Royce Corporation under license from LHTEC to manufacture their 
subassemblies, component parts and spares.

7 TE2CH 
 
NOTE 13 The CTS800-0 is the initial type certified model with one dual channel control unit mounted on the engine. 
The CTS800-4N is similar to the CTS800-0 except for the addition of 30-second OEI and 2-minute OEI ratings, 
incorporation of a reduction gearbox, and two separate redundant engine control units that are airframe -
mounted. The CTS800-4A is similar to the CTS800-4N except with no reduction gearbox and rated 
performance changes associated with the reduction gearbox removal.  The CTS800-4AT is similar to the 
CTS800-4A except that select engine ratings and limits modified, AEO Special Condition 30-min rating added, 
and minimum starting temperature was increased to -40°C (-40°F). 
 
…END…
```

## ADs

None name its models.

## STCs approved under this data sheet (1)

- [STC SE00757CH](https://openairdocs.org/stc/SE00757CH): Installation of Allison Engine P/N 23051724 speed reduction gearbox assembly.. Allison Engine Company

---
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.