# TCDS E5NE: Intermountain Turbine Services Inc.

- Type: Type certificate data sheet
- Status: Current
- Holder: Intermountain Turbine Services Inc.
- Revision: 21
- Revised: June 9, 2023
- Product: Engine
- Certification basis: Part 33
- Registered aircraft: 51, by the registry models matched to it (OpenAirDocs)
- Data sheet PDF: https://openairdocs.org/files/sha256/3d/b2/3db28af5f3962cb0ee89c9df6d3b8329056588d476c351dc5c0df632df827e80
- FAA DRS: https://drs.faa.gov/browse/excelExternalWindow/DRSDOCID172085135620231129203524.0001
- Page: https://openairdocs.org/tcds/E5NE

## Models (13)

As the data sheet lists them.

- LTS101-700D-2
- LTS101-600A-3
- LTS101-750C-1
- LTS101-650C-3A
- LTS101-850B-2
- LTS101-600A-2
- LTS101-650C-3
- LTS101-750B-2
- LTS101-650B-1
- LTS101-650B-1A
- LTS101-750B-1
- LTS101-600A-3A
- LTS101-650C-2

## 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. E5NE 
 
Engines of models described herein conforming with this data sheet (which is part of Type Certificate No. E5NE) and other 
approved data on file with the Federal Aviation Administration (FAA), 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: Intermountain Turbine Services, Inc. 
270 South 1060 West 
Lindon, UT 84042 
 
 
Type Certificate Holder Record:           Honeywell International, Inc. transferred TC  E5NE to  
Intermountain Turbine Services, Inc. on June 9, 2023. 
 
 
 
 
 
TYPE CERTIFICATE HOLDER RECORD: The TC No. E5NE was originally issued to Avco Lycoming Engine Group, 
Stratford Division, Stratford, Connecticut. The TC was endorsed for transfer on July 20, 1982, and was reissued to Avco 
Lycoming Engine Group, Williamsport Division, Williamsport, Pennsylvania on August 16, 1982. The TC was again endorsed 
for transfer on January 29, 1987, and was reissued to Avco Lycoming Textron, Stratford Division, Stratford, Connecticut, on 
February 27, 1987. The TC was endorsed for a change in the holder's name on October 21, 1987, and was reissued to Textron 
Lycoming, Stratford Division, on October 28, 1987. The TC was endorsed for a change in the holder's name on January 27, 
1995, and was reissued to AlliedSignal Inc. on January 31, 1995. The TC was reissued for a change in the holder’s name to 
Honeywell International Inc. on December 14, 1999. Honeywell International, Inc. transferred ownership of TC No. E5NE to 
Intermountain Turbine Services, Inc. on June 9, 2023. 
 
 
 
 
E5NE 
Revision 21 
 
Intermountain Turbine 
Services, Inc. 
 
LTS101-600A-2 
LTS101-600A-3 
LTS101-600A-3A 
LTS101-650B-1 
LTS101-650B-1A 
LTS101-650C-2 
LTS101-650C-3 
LTS101-650C-3A 
LTS101-700D-2 
LTS101-750B-1 
LTS101-750B-2 
LTS101-750C-1 
LTS101-850B-2 
 
June 9, 2023

PAGE 1 2 3 4 5 6 7 8 9 10 11 12  
REV. 21 17 18 19 21 17 17 20 20 20 21 21 
 LEGEND: "- -" INDICATES "SAME AS PRECEDING MODEL" 
"---" INDICATES "DOES NOT APPLY" 
NOTICE: ALL PAGES ARE REFORMATTED. SIGNIFICANT CHANGES ARE 
BLACK-LINED.

E5NE Page 2 of 13 
 
 
 
 
I. MODELS: LTS101 -600A-2 -600A-3 -650B-1 -650B-1A -650C-2 -650C-3 
-650C-3A 
TYPE 
 
 
RATINGS (See NOTE 1) 
Maximum Continuous 
at sea level, hp. 
Takeoff (5 minutes) 
at sea level, hp. 
30 minute OEI 
Rating at sea level hp. 
2 1/2 minute OEI 
Rating at sea level hp. 
Axial – centrifugal flow, free turbine, turboshaft. Single stage axial and single stage 
centrifugal compressor. Reverse flow annular combustor. Single stage gas generator 
turbine. Single stage power turbine. 
 
590 
 
615 
 
 
--- 
 
--- 
 
- - 
 
- - 
 
 
--- 
 
--- 
 
550(1) 
 
550(2) 
 
 
592(3) 
 
592(4) 
 
550 
 
600 
 
 
600 
 
650 
 
592 
 
628 
 
 
650 
 
675 
 
598 
 
630 
 
 
- - 
 
- - 
 
 
I. MODELS: LTS101 -750B-1 -750B-2 -750C-1 -600A-3A -700D-2 -850B-2 
TYPE 
 
 
RATINGS (See NOTE 1) 
Maximum Continuous 
at sea level, hp. 
Takeoff (5 minutes) 
at sea level, hp. 
30 minute OEI 
at sea level hp. 
2 1/2 minute OEI 
at sea level hp. 
Axial – centrifugal flow, free turbine, turboshaft. Single stage axial and single stage 
centrifugal compressor. Reverse flow annular combustor. Single stage gas generator 
turbine. Single stage power turbine. 
 
550(5) 
 
550(6) 
 
 
694(7) 
 
727(8) 
 
658 
 
690 
 
 
708 
 
742 
 
653 
 
684 
 
 
702 
 
735 
 
625 
 
650 
 
 
--- 
 
--- 
 
650 
 
732 
 
 
--- 
 
--- 
 
746 
 
780 
 
 
807 
 
838 
 
(1)  Available to ambient temperature of 72oF 
(22oC) (5) Available to ambient temperature of 91oF (33oC) 
(2) Available to ambient temperature of 84oF (29oC) (6) Available to ambient temperature of 106oF 
(41oC) 
(3)  Available to ambient temperature of 78oF 
(25oC) 
 
(4)  Available to ambient temperature of 91oF 
(33oC) 
(7) For engines in compliance with SB LTS 101B-72-00-0161, 
NOTE 1 applies. 592 Hp available to ambient temperature of 
100oF (38oC) for LTS101-750B-1 engines not in compliance 
with SB No. LTS 101B-72-00-0161. 
(8) For engines in compliance with SB LTS101B-72-00-0161, 
NOTE 1, applies. 592 Hp available to ambient temperature of 
115oF (46oC) for LTS101-750B-1 engines not in compliance 
with SB No. LTS101B-72-00-0161.

E5NE Page 3 of 13 
 
 
 
 
 
I. MODELS: LTS101 -600A-2 -600A-3 -650B-1 -650B-1A -650C-2 -650C-3 
-650C-3A 
REDUCTION GEAR RATIO  
0.1612 
 
- - 
 
0.1654 
 
0.1612 
 
0.2632 
 
- - (Output Shaft Speed to 
Power Turbine Speed) 
FUEL (See NOTE 2 and NOTE ASTM D1655 Jet - - - - - - - - - - 
16) A, A1, & B, 
MIL-DTL-5624 
Grades JP-4, JP- 
5, and JP-8 or 
equivalent 
OIL (See NOTE 3) MIL-PRF-7808 
MIL-PRF-23699 
- - - - - - - - - - 
PRINCIPAL DIMENSIONS       
Length, in. nominal 30.93 31.56 31.05 30.93 31.21 31.21(-3) 
      31.31(-3A) 
Height, in. nominal 23.64 24.80 25.36 - - 19.45 - - 
Width, in. nominal 19.37 - - 18.52 - - 22.60 - - 
WEIGHT (Dry), lb.  
253 
 
265 
 
281 
 
253 
 
240.3 
 
Maximum (includes essential 240.3(-3) 
engine accessories but 243(-3A) 
excludes starter-generator)  
C.G. LOCATION (dry weight)       
Aft of engine centerline of lower 5.610 - - 5.671 5.820 8.11 8.11(-3) 
mount pads, in.      7.906(-3A) 
Below engine centerline, in. 1.880 - - 1.812 1.720 0.641 0.641(-3) 
      0.598(-3A) 
Left of engine centerline looking 0.150 - - 0.072 0.080 0.240 0.240(-3) 
Aft, in.      0.314(-3A)

E5NE Page 4 of 13 
 
 
 
 
I. MODELS: LTS101 -750B-1 -750B-2 -750C-1 -600A-3A -700D-2 -850B-2 
REDUCTION GEAR RATIO  
0.1654 
 
- - 
 
0.2632 
 
0.1612 
 
0.1654 
 
- - (Output Shaft Speed to Power 
Turbine Speed) 
FUEL (See NOTE 2 and NOTE ASTM D1655 Jet - - - - - - - - - - 
16) A, A-1, & B, 
MIL-DTL-5624 
Grades JP-4, JP-5, 
and JP-8 or 
equivalent 
OIL (See NOTE 3) MIL-PRF-7808 
MIL-PRF-23699 
- - - - - - - - - - 
PRINCIPAL DIMENSIONS       
Length, in. nominal 31.05 32.36 31.31 31.56 - - 31.05 
Height, in. nominal 25.36 24.68 20.15 24.80 - - 25.36 
Width, in. nominal 18.52 19.86 22.60 19.37 - - 18.52 
WEIGHT (Dry), lb.  
295 
 
273 
 
244 
 
265 
 
279* 
 
283 Maximum (includes essential 
engine accessories but 
excludes starter-generator) 
C.G. LOCATION (dry weight)       
Aft of engine centerline of lower 5.542 3.545 7.767 5.610 - - 3.545 
mount pads, in.       
Below engine centerline, in. 1.861 1.567 0.559 1.880 - - 1.567 
Left of engine centerline       
looking aft, in. -0.071 0.075 0.303 0.150 - - 0.075 
 
* For -700D-2, dry weight does not include airframe-mounted electronic overspeed controller of 2.7 lbs.

E5NE Page 5 of 13 
 
 
 
 
CERTIFICATION BASIS 14 CFR part 33 effective February 1, 1965, as amended by 33-1, 33-2, 33-3, 33-4, and 33-5. 
 
MODEL APPLICATION 
DATE 
TYPE CERTIFICATE 
ISSUED/AMENDED 
LTS101-600A APR 11, 1974 OCT 24, 1975 
LTS101-600B SEP 18, 1974 OCT 24, 1975 
LTS101-650A APR 11, 1974 OCT 24, 1975 
LTS101-650C APR 05, 1974 OCT 24, 1975 
LTS101-600A-1 OCT 15, 1975 OCT 24, 1975 
LTS101-600B-3 OCT 15, 1975 OCT 24, 1975 
LTS101-650A-1 OCT 15, 1975 OCT 24, 1975 
LTS101-600A-2 JUL 21, 1977 NOV 30, 1977 
LTS101-600A-1 CANCELED NOV 30, 1977 
LTS101-600B-3 CANCELED NOV 30, 1977 
LTS101-650A-1 CANCELED NOV 30, 1977 
LTS101-650A-2 OCT 25, 1976 FEB 24, 1978 
LTS101-650C-2 OCT 25, 1976 FEB 24, 1978 
LTS101-650A CANCELED MAR 22, 1978 
LTS101-650B-1A FEB 08, 1979 FEB 15, 1979 
LTS101-650C CANCELED MAR 01, 1979 
LTS101-650C-3 MAY 08, 1980 JUN 10, 1980 
LTS101-750A-1 DEC 03, 1980 APR 24, 1981 
LTS101-650B-1 JAN 22, 1981 JUN 03, 1981 
LTS101-750C-1 JAN 22, 1981 AUG 07, 1981 
LTS101-650C-3A SEP 08, 1983 JUL 13, 1984 
LTS101-600A-3 MAR 19, 1984 JUL 13, 1984 
LTS101-750A-3 JAN 04, 1983 SEP 21, 1984 
LTS101-750B-2 FEB 14, 1985 NOV 08, 1985 
LTS101-750B-1 MAR 31, 1983 JUN 17, 1986 
LTS101-600A CANCELED APR 20, 1987 
LTS101-600B CANCELED APR 20, 1987 
LTS101-650A-2 CANCELED APR 20, 1987 
LTS101-750A-1 CANCELED FEB 17, 1988 
LTS101-750A-3 CANCELED FEB 17, 1988 
LTS101-600A-3A MAR 16, 1999 JUL 21, 1999 
LTS101-700D-2 JUN 30, 1999 FEB 13, 2004 
LTS101-850B-2 DEC 13, 2002 FEB 13, 2004 
 
PRODUCTION BASIS NONE 
 
NOTE 1. Engine ratings are based on calibrated stand performance under the following conditions: 
Static sea level standard conditions at 59oF and 29.92 in. Hg. 
No air bleed, no duct losses, no external power extraction. 
Exhaust configuration as specified in the applicable engine Installation Instructions or 
Manual. 
 
NOTE 2. Engines will operate satisfactorily with fuel contaminated to the levels specified in the applicable 
engine Installation Instructions or Manual provided the fuel is introduced to the engine in accordance 
with the installation requirements. 
 
NOTE 3. Mixing of these oil types is prohibited. See Engine Maintenance Manual for approved brands by 
type. 
NOTES

E5NE Page 6 of 13 
 
 
 
 
NOTE 4. Maximum permissible gas generator operating speeds (r.p.m.): 
 
I. MODELS: LTS101 -600A-2 -600A-3 -650B-1 -650B-1A -650C-2 -650C-3 
-650C-3A 
Transient 
2-1/2 Minute OEI 
30 Minute OEI 
Takeoff 
Maximum Continuous 
5 Minute Part Power 
50,548 50,787(1) 50,548 - - - - - - 
--- --- 50,548 50,169 50,548 - - 
--- --- 50,169 49,255 50,169 - - 
49,638 49,830(1) 49,638 49,255 49,638 - - 
49,159 49,255(1) 49,159 48,394 49,159 - - 
--- --- 49,159 --- 49,159 - - 
 
(1) Applicable only if Service Bulletin No. LT101-72-50-0126 and LT101-72-50-0157 are incorporated. For all other engines, 
the limits are the same as the –600A-2. 
 
I. MODELS: LTS101 -750B-1 -750B-2 -750C-1 -600A-3A -700D-2 -850B-2 
Transient 
2-1/2 Minute OEI 
30 Minute OEI 
Takeoff 
Maximum Continuous 
5 Minute Part Power 
50,787 - - - - - - 51,313 52,178 
50,787 - - - - --- --- 51,938 
50,169 50,165 - - --- --- 51,699 
49,830 - - - - - - 51,026 51,029 
49,255 - - - - - - 50,164 50,455 
49,255 - - - - --- --- --- 
 
NOTE 5. Maximum permissible power turbine output shaft torque (ft.-lb.): 
 
I. MODELS: LTS101 -600A-2 -600A-3 -650B-1 -650B-1A -650C-2 -650C-3 
-650C-3A 
Transient 594 - - 649 - - 419 - - 
2-1/2 Minute OEI --- --- 594 - - 383 - - 
30 Minute OEI --- --- 594 541 369 - - 
Takeoff 541 - - 519 541 357 - - 
Maximum Continuous 519 - - - - - - 335 - - 
5 Minute Part Power --- --- 165 --- 335 - - 
No Load (Autorotation) 0 - - - - - - - - - - 
 
I. MODELS: LTS101 -750B-1 -750B-2 -750C-1 -600A-3A -700D-2 -850B-2 
Transient 
2-1/2 Minute OEI 
30 Minute OEI 
Takeoff 
Maximum Continuous 
5 Minute Part Power 
No Load (Autorotation) 
725 - - 480 641** 725** - - 
643 - - 417 --- --- 643 
614 - - 397 --- --- 614 
597 - - 387 583 618 597 
567 - - 367 561 567 --- 
165* - - 343 --- --- --- 
0 - - - - - - - - - - 
 
* Approved for continuous operation at out put shaft speed up to 6,180 r.p.m. and output shaft torque up to 377 ft.-lb. 
** Time limit: 30 seconds above Takeoff torque limit.

E5NE Page 7 of 13 
 
 
 
 
NOTE 6. Maximum permissible output shaft speeds (r.p.m.): 
 
I. MODELS: LTS101 -600A-2 -600A-3 -650B-1 -650B-1A -650C-2 -650C-3 
-650C-3A 
Transient 
2-1/2 Minute OEI 
30 Minute OEI 
Takeoff 
Maximum Continuous 
5 Minute Part Power 
No Load (Autorotation) 
6,300 - - 6,365 6,300 9,784 - - 
--- --- 6,120 6,085 9,545 - - 
--- --- 6,120 6,085 9,545 - - 
6,085 - - 6,120 6,085 9,545 - - 
6,085 - - 6,120 6,085 9,545 - - 
--- --- 6,365 --- 9,930 - - 
6,300 - - 6,365 6,300 9,930 - - 
 
 
Transient 
2-1/2 Minute OEI 
30 Minute OEI 
Takeoff 
Maximum Continuous 
5 Minute Part Power 
No Load (Autorotation) 
*Time limit 12 seconds above 6,460 r.p.m. 
**Approved for continuous operation at output shaft speed up to 6,180 r.p.m. and output shaft torque up to 377 ft.-lb. 
***Time Limit: 5 seconds above 6,780 r.p.m. 
 
NOTE 7. Maximum permissible temperatures: 
 
Measured gas temperature oF (oC) as measured by thermocouples mounted in the combustor housing: 
 
 
LTS101 -600A-2 -600A-3 -650B-1 -650B-1A -650C-2 -650C-3 
-650C-3A 
Starting 
Transient 
2-1/2 Minute OEI 
30 Minute OEI 
Takeoff 
 
Maximum Continuous 
5 Minute Part Power 
1650* (899) - - ** - - * - - - - - - 
1550* (843) 1557 (847)** 1550 (843) - - - - - - 
--- --- 1530 (832) 1485 (807) 1530 (832) - - 
--- --- 1464 (796) 1420 (771) 1464 (796) - - 
1440*** (782) 1447*** 
(786)(1) 
1440*** 
(782) 
1420*** 
(771) 
1440 (782) - - 
1405 (763) 1409 (765)(1) 1405 (763) 1360 (738) 1405 (763) - - 
--- --- 1405 (763) --- 1405 (763) - - 
 
(1) Applicable only if Service Bulletin No. LT 101-72-50-0126 and LT 101-72-50-0157 are incorporated. For all other -600A-3 
engines, the maximum MGT at the takeoff rating shall be 1380oF (749oC) and 1355oF(735oC) at the maximum continuous rating. 
 
LTS101 -750B-1 -750B-2 -750C-1 -600A-3A -700D-2 -850B-2 
Starting 
Transient 
2-1/2 Minute OEI 
30 Minute OEI 
Takeoff 
Maximum Continuous 
5 Minute Part Power 
1650** (899) - - - - - - 1731***(944) 1679**(915) 
1557** (847) - - - - - - 1731***(944) 1679**(915) 
1537 (836) 1512 (822) - - --- --- 1637 (892) 
1472 (800) 1471 (799) - - --- --- 1608 (875) 
1447*** (786) 1447 (786) - - - - *** 1694***(923) 1559 (848) 
1409 (765) 1409 (765) - - - - 1635 (890) 1523 (828) 
1405 (763) - - - - --- --- --- 
I. MODELS: LTS101 -750B-1 -750B-2 -750C-1 -600A-3A -700D-2 -850B-2 
 6,580* - - 9,930 7,200 7,404*** 7,380*** 
6,140 - - 9,545 --- --- 6,780 
6,140 - - 9,545 --- --- 6,780 
6,140 - - 9,545 6,780 - - - - 
6,140 - - 9,545 6,780 - - - - 
6,460** - - 9,930 --- --- --- 
6,460 - - 9,930 6,780 - - - -

E5NE Page 8 of 13 
 
 
 
NOTE 7. Continued 
*Time limit 12 seconds above 1530oF (832oC). 
**Time limit 12 seconds above 1537oF (836oC) (-750B-1, -600A-3, and –600A-3A), and 12 seconds above 1512oF (822oC) 
(-750B-2, and -750C-1), and 12 seconds above 16370F (892oC) (-850B-2). 
 
***For the LTS101-600A-2, -600A-3, and -600A-3A engine models, the transient measured exhaust gas temperature must not 
exceed the takeoff measured exhaust gas temperature for more than 22 seconds. For the LTS101-650B-1, -650B-1A, and 
-750B-1 engine models, the transient measured exhaust gas temperature must not exceed the takeoff measured exhaust gas 
temperature for more than 22 seconds and never exceed 1499oF (815oC) at any time during normal takeoff operation. For the 
LTS101-700D-2, the starting and transient measured gas temperatures must not exceed the takeoff measured gas temperature for 
more than 30 seconds. 
 
The transient limits are not to be used for increased power operation during normal takeoff. 
 
Maximum permissible component temperatures: 
 
LTS101 -600A-2 -600A-3 -650B-1 -650B-1A -650C-2 -650C-3 
-650C-3A 
Zone Temperature (oF):  
Gas Generator Speed Control 250 - - - - - - - - - - 
Ignition Exciter Box 250 - - - - - - - - - - 
Inlet Flow Actuator 410 - - - - - - - - - - 
Thermocouple Harness --- --- --- --- --- --- 
Electrical Harness --- --- --- --- --- --- 
Power Turbine Governor 280 - - - - - - - - - - 
Thermocouple Junction Block 450 - - - - - - - - - - 
Anti-Icing Valve 450 - - - - - - - - - - 
Torque Limiter --- --- --- --- --- --- 
Fuel Manifold --- --- --- --- 350 - - 
Power Turbine Overspeed Trip 250 - - 160 250 - - 160 
(1) 
Fuel Metering Unit --- --- --- --- --- --- 
EFCS Alternator --- --- --- --- --- --- 
Electronic Control Computer --- --- --- --- --- --- 
MGT Transient Compensator --- --- --- --- --- --- 
 
LTS101 -750B-1 -750B-2 -750C-1 -600A-3A -700D-2 -850B-2 
Gas Generator Speed Control 250 - - - - - - - - - - 
Ignition Exciter Box 250 - - - - - - - - - - 
Inlet Flow Actuator 410 - - - - - - - - - - 
Thermocouple Harness --- --- --- --- --- --- 
Electrical Harness --- --- --- --- --- --- 
Power Turbine Governor 280 - - - - - - - - - - 
Thermocouple Junction Block 450 - - - - - - - - - - 
Anti-Icing Valve --- 450 - - - - - - - - 
Torque Limiter --- --- --- --- --- --- 
Fuel Manifold --- --- --- --- --- --- 
Power Turbine Overspeed Trip 160 250 160 250 160 160 
(1) 
Fuel Metering Unit --- --- --- --- --- --- 
EFCS Alternator --- --- --- --- --- --- 
Electronic Control Computer --- --- --- --- --- --- 
MGT Transient Compensator --- 160 - - --- --- ---

E5NE Page 9 of 13 
 
 
 
(1) Zone temperature limit of 250oF is for mechanical power turbine overspeed trip system mounted on the accessory pad 
marked “Alternator”. All other engine models utilize an electronic overspeed system with a 160oF limit for the airframe- 
mounted box. 
 
NOTE 8. Fuel pressure limits and oil pressure and temperature limits: 
 
Fuel pressure limits for the LTS101-600A-2, and -600A-3 engine models are 15 p.s.i.a. minimum and 
45 p.s.i.a. maximum. For all other engine models, the fuel system provides suction lift capability 
without any external assistance. See the applicable engine Installation Instructions for further details. 
 
Oil pressure and temperature (as measured by engine oil temperature bulb located at oil filter 
discharge) limits: 
 
 
 Engine Models Specified Range Condition 
Oil pressure 
during operation 
LTS101-650B-1A 80-100 psig Maximum continuous power 
LTS101-600A-2, -650B-1, -650C-2/C-3/ 
C-3A, -750B-1, -750C-1, -700D-2, 
-850B-2 
80-100 psig  
Max. continuous and above with oil 
 
temperature greater than 150oF 
(65oC) 
LTS101-600A-3, -600A-3A, -750B-2 90-100 psig 
    
Minimum oil pressure LTS101-600A-2 and -650B-1A 20 psig Flight idle and below 
LTS101-600A-3, -600A-3A, -650C-2/C- 
3/C-3A, -750B-2, -750C-1, -700D-2 
20 psig Flight idle, oil inlet temperature 
greater than 50oF (10oC) 
LTS101-650B-1, -750B-1, -850B-2 40 psig Flight idle, oil inlet temperature 
greater than 50oF (10oC) 
LTS101-600A-3, -600A-3A, -650B-1, 
-650C-2/C-3/C-3A, -750B-1/B-2, 
-750C-1, -700D-2, -850B-2 
50 psig Flight idle, oil inlet temperature at 
or below 50oF (10oC) 
    
Maximum transient 
oil pressure (cold oil) 
LTS101-600A-2, -650B-1A 200 psig Starting at ambient temperature less 
than -20oF (-29oC) for a duration 
not to exceed 2.5 minutes 
LTS101-600A-3, -600A-3A, -650B-1, 
-650C-2/C -3/C-3A, -750B-1/B-2, 
-750C-1, -700D-2, -850B-2 
350 psig (spikes) 
120 psig 
During oil warm up from 50oF 
(10oC) to 150oF (65oC) 
    
Maximum oil inlet 
temperature 
LTS101-650C-2/C-3/C-3A, -750C-1 220oF (105oC) Ambient temperature less than 
100oF (38oC) 
LTS101-600A-2, -600A-3, -600A-3A, 
-650B-1*, -650B-1A, -750B-1/B-2, 
-700D-2, -850B-2 
210oF (99oC) Ambient temperature less than 
100oF (38oC) 
LTS101-600A-2, -600A-3, -600A-3A, 
-650B-1*, -650B-1A, -650C-2/C-3/C-3A, 
-750B-1/B-2, -750C-1, -700D-2, -850B-2 
230oF** (110oC) Ambient temperature at or above 
100oF (38oC) 
*50oF (10oC) minimum oil temperature for operation above ground idle. 
150oF (65oC) minimum oil temperature during sustained steady state power. 
 
**Oil temperature limit also applies for one engine inoperative (OEI) conditions.

E5NE Page 10 of 13 
 
 
 
 
NOTE 9. Accessory drive provisions: 
 
LTS101 
Description 
-600A-2 -600A-3 -650B-1 -650B-1A -650C-2 -650C-3 
-650C-3A 
Starter Generator Pad Type 
 
Rotation (viewing pad) 
Gear Ratio(1) 
Maximum Torque (in-lb) 
Starting 
Transient 
Maximum continuous 
 
Accessory Pad Type 
 
Rotation (viewing pad) 
Gear Ratio(2) 
Maximum Torque (in-lb) 
Starting 
Maximum continuous 
Spare Pad Type 
 
Rotation (viewing pad) 
Gear Ratio(2) 
Maximum Torque (in-lb) 
Starting 
Maximum continuous 
AND20001 
Modified (3) 
- - - - - - - - - - 
CW - - - - - - - - - - 
.2512 - - - - - - - - - - 
 
500 
150(5) 
46(6) 
 
- - 
- - 
71(6) 
 
- - 
- - 
- - 
 
- - 
- - 
- - 
 
- - 
- - 
- - 
 
--- 
- - 
- - 
      
AND20002 
Modified (3) 
--- AND20002 
Modified (3) 
- - - - - - 
CW --- CW - - - - - - 
0.3265 --- 0.3265 - - 0.3406 - - 
 
--- 
75 
 
--- 
--- 
 
--- 
75 
 
--- 
- - 
 
--- 
- - 
 
--- 
- - 
      
AND20000 
Modified(3) 
(4) 
- - --- AND20000 
Modified(3) 
(4) 
--- --- 
CCW --- --- CCW --- --- 
0.5375 --- --- 0.5375 --- --- 
 
--- 
20 
 
--- 
- - 
 
--- 
--- 
 
--- 
11 
 
--- 
--- 
 
--- 
--- 
 
LTS101 
Description 
-750B-1 -750B-2 -750C-1 -600A-3A -700D-2 -850B-2 
Starter Generator Pad Type 
 
Rotation (viewing pad) 
Gear Ratio(1) 
Maximum Torque (in-lb) 
Starting 
Transient 
Maximum continuous 
Maximum applied torque 
Accessory Pad Type 
 
Rotation (viewing pad) 
Gear Ratio(2) 
Maximum Torque (in-lb) 
Starting 
Maximum continuous 
Spare Pad Type 
 
Rotation (viewing pad) 
Gear Ratio(2) 
Maximum Torque (in-lb) 
Starting 
Maximum continuous 
AND20001 
Modified (3) 
- - - - - - - - - - 
CW - - - - - - - - - - 
0.2512 - - - - - - - - - - 
 
500 
150(5) 
71(6) 
 
- - 
- - 
- - 
 
- - 
- - 
- - 
 
580 
- - 
- - 
 
- - 
- - 
- - 
 
- - 
- - 
- - 
--- --- --- 1,100 in-lb(7) - - - - 
--- --- AND20002 
Modified (3) 
--- --- --- 
--- --- CW --- --- --- 
--- --- 0.3406 --- --- --- 
 
--- 
--- 
 
--- 
--- 
 
--- 
75 
 
--- 
--- 
 
--- 
--- 
 
--- 
--- 
      
--- --- --- AND20000 
Modified 
(3)(4) 
--- --- 
--- --- --- CCW --- --- 
--- --- --- 0.5375 --- --- 
 
--- 
--- 
 
--- 
--- 
 
--- 
--- 
 
--- 
20 
 
--- 
--- 
 
--- 
---

E5NE Page 11 of 13 
 
 
 
NOTE 9. Continued 
(1) With respect to gas generator. 
(2) With respect to power turbine. 
(3) Limit pad speed and maximum loads modified. See the applicable engine Installation Instructions or Manual for 
further details. 
(4) Pad pilot diameter modified to 1.622 in. Pad spline pitch diameter modified to .4583 in. 
(5) To be used in generating mode only, with a time limit of 30 seconds. 
(6) If the starter generator rating is more than 150 amps., the continuous electric load must be limited to 150 
amps when the gas generator is less than 43,100 r.p.m. 
(7) Applied torque at the starter pad shall not exceed the value stated under any operating or failure condition. 
 
CW - Clockwise, CCW - Counterclockwise 
 
NOTE 10  The LTS101-600A-2 engine model meets the FAA requirements for operation in icing conditions 
provided that the induction system design conforms to Kit Number 4-201-080-01, and a 
minimum of 37,080 r.p.m. gas producer speed is maintained. 
 
The LTS101-600A-3, -600A-3A, -750C-1, and -700D-2 engine models meet the FAA requirements 
for operation in icing conditions provided that the induction system design conforms to Kit Number 
4-201-080-01, and a minimum of 38,294 r.p.m gas generator speed is maintained. 
 
The LTS101-650C-2, -650C-3, and -650C-3A engine models meet the FAA requirements for 
operation in icing conditions provided that a minimum of 37,080 r.p.m. gas producer speed is 
maintained. 
 
The LTS101-650B-1A engine model meets the FAA requirements for operation in icing conditions 
provided that the induction system design conforms to Figure 6.8 of Installation Instructions 
101.14.50, and a minimum bypass flow of 29% at an inlet referred flow rate of 4.8 lb./sec. is 
maintained. 
 
The LTS101-650B-1 engine model meets the FAA requirements for operation in icing conditions 
provided that the induction system design conforms to Figure 18 of Installation Instructions 
101.14.36. 
 
The LTS101-750B-1 engine model meets the FAA requirements of § 33.68, Amendment 10, for 
operation in icing conditions provided that the induction system design conforms to Figure 18 of 
Installation Instructions 83.101.11. 
 
The LTS101-750B-2 engine model meet the FAA requirements of § 33.68, Amendment 10, for 
operation in icing conditions provided that the induction system design conforms to Figure 19 or 
Figure 19A of Installation Manual IM-8020. A minimum bypass flow of 29% at an inlet referred flow 
rate of 5.2 lb./sec. is required when equipped with the induction system design as depicted by Figure 
19 of the Installation Manual. 
 
The LTS101-850B-2 engine model meets the FAA requirements of § 33.68, Amendment 10, for 
operation in icing conditions provided that the induction system design conforms to Attachment 1 of 
Installation Manual IM-8022, Revision A, or later FAA approved revisions, and a maximum gas 
generator speed of 104.1 percent (all engines operating) and 106.1 percent (OEI) is not exceeded.

E5NE Page 12 of 13 
 
 
 
NOTE 11.  These engines have not been tested to evaluate the effects of bird and ice ball ingestion. The bird and 
ice ball ingestion characteristics of the airframe air inlet and engine combination are to be evaluated 
prior to approval of the engine installation. 
 
NOTE 12. Deleted (Revision 19) 
 
NOTE 13. Maximum permissible air bleed extraction is 5% of inlet airflow at the designed customer bleed port 
at standard sea level static conditions. 
 
NOTE 14.  Certain engine parts are life limited. The limits are listed in FAA approved Service Bulletin Number 
LT 101-71-00-0002. 
 
NOTE 15. Engine starter torque and speed requirements are specified in the applicable engine Installation 
Instructions or Manual. 
 
NOTE 16. Approved type fuels and fuel additives are specified in the applicable engine Installation Instructions 
or Manual or LTS101 Operating Instruction, document 21-11045. 
 
NOTE 17. 100% output shaft speed for the LTS101-650C-2, -650C-3A, and -750C-1 is 9545 r.p.m.; for the 
LTS101-700D-2 is 6120 r.p.m.; for the LTS101-650B-1, -650B-1A, -750B-1, -750B-2, and -850B-2 is 
6000 r.p.m.; and for all other models is 5966 r.p.m. 
 
NOTE 18. 100% power turbine shaft speed for the LTS101-600A-2, -600A-3, -600A-3A, and -700D-2 is 37,000 
r.p.m. 
100% power turbine shaft speed for the LTS101-650B-1, -750B-1, -750B-2, and -850B-2 is 36,281 
r.p.m. 
100% power turbine shaft speed for the LTS101-650B-1A is 37,211 r.p.m. 
100% power turbine shaft speed for the LTS101-650C-2, -650C-3, -650C-3A, and -750C-1 is 36,265 
r.p.m. 
 
NOTE 19. 100% gas generator speed equals 47,870 r.p.m. for all engine models. 
 
NOTE 20. The installation for all engine models must incorporate a control system stability accumulator(s) in 
accordance with the applicable engine Installation Instructions or Manual. 
 
NOTE 21. Engine maintenance program requirements are defined in FAA approved Service Bulletin Number LT 101- 
71-00-0001. 
 
NOTE 22. Deleted (Revision 15) 
 
NOTE 23. The LTS101-600A-3A, -650B-1, -650B-1A, -650C-2, -650C-3, -650C-3A, -700D-2, -750B-1, 
-750B-2, -750C-1, and -850B-2 engine models are equipped with a suction feed fuel system meeting 
the FAA requirements of § 33.67, Amendment 6. All other engine models require an aircraft boost 
pump to deliver fuel to the engine (see NOTE 8). 
 
NOTE 24. Deleted (Revision 16) 
 
NOTE 25. Deleted (Revision 16) 
 
NOTE 26. Installation of the LTS101-650B-1, -750B-1, -750B-2, and -850B-2 engine models must include a full 
flow scavenge oil strainer and chip detector to meet the FAA requirements of § 33.71, Amendment 6. 
-END-
```

## ADs (25, in force first)

- [AD 2011-23-13](https://openairdocs.org/ad/2011-23-13): Power turbine governors (PTG) · Honeywell International LTS101-600A-2, LTS101-600A-3, LTS101-600A-3A and 1 more. Effective Nov 29, 2011
- [AD 2011-08-06](https://openairdocs.org/ad/2011-08-06): Power turbine rotors · Honeywell International LTP 101-600A-1A, LTP 101-700A-1A, LTS101-600A-2 and 10 more. Effective May 17, 2011
- [AD 2009-24-12](https://openairdocs.org/ad/2009-24-12): Gas generator · Honeywell International LTP 101-600A-1A, LTP 101-700A-1A, LTS101-600A-2 and 12 more. Effective Jan 4, 2010
- [AD 2002-03-09 R1](https://openairdocs.org/ad/2002-03-09-R1): Impellers · Honeywell International LTP 101-600, LTP 101-600A, LTP 101-600A-1A and 14 more. Effective Mar 27, 2002
- [AD 2001-25-04](https://openairdocs.org/ad/2001-25-04): Fuel Controls · Honeywell International LTP 101-600A-1A, LTP 101-700A-1A, LTS101-600A-2 and 1 more. Effective Jan 23, 2002
- [AD 2001-22-07](https://openairdocs.org/ad/2001-22-07): Rigid Tube Fuel Manifold Assemblies · Honeywell International LTP 101-600, LTP 101-600A, LTP 101-600A-1A and 14 more. Effective Nov 30, 2001
- [AD 2001-17-15](https://openairdocs.org/ad/2001-17-15): Engine Fuel Pumps · Honeywell International LTP 101-600A-1A, LTP 101-700A-1A, LTS101-600A-2 and 2 more. Effective Oct 1, 2001
- [AD 96-12-27](https://openairdocs.org/ad/96-12-27): Gas Generator Turbine Disk · Honeywell International LTP 101-600, LTP 101-600A, LTP 101-600A-1A and 21 more. Effective Aug 19, 1996
- [AD 96-12-05](https://openairdocs.org/ad/96-12-05): Turbine rotors · Honeywell International LTP 101-600, LTP 101-600A, LTP 101-600A-1A and 14 more. Effective Aug 12, 1996
- [AD 96-10-04](https://openairdocs.org/ad/96-10-04): Fuel control · Honeywell International LTS101-600A-2 and LTS101-600A-3. Effective Jun 13, 1996
- [AD 96-06-10](https://openairdocs.org/ad/96-06-10): Power turbine (PT) disk · Honeywell International LTS101-600A-2, LTS101-600A-3 and LTS101-750B-2. Effective May 28, 1996
- [AD 95-26-01](https://openairdocs.org/ad/95-26-01): Power Turbine · Honeywell International LTS101-650B-1, LTS101-650C, LTS101-750B-1 and 1 more. Effective Apr 22, 1996
- [AD 95-16-04](https://openairdocs.org/ad/95-16-04): Axial Compressor Rotors · Honeywell International LTP 101-600, LTP 101-600A, LTP 101-600A-1A and 21 more. Effective Oct 2, 1995
- [AD 95-08-14](https://openairdocs.org/ad/95-08-14): Electronic Overspeed Protection System · Honeywell International LTS101-650B-1, LTS101-650C-3, LTS101-650C-3A and 2 more. Effective May 9, 1995
- [AD 94-18-06](https://openairdocs.org/ad/94-18-06): Bearings · Honeywell International LTP 101-600, LTP 101-600A, LTP 101-600A-1A and 21 more. Effective Sep 26, 1994
- [AD 93-13-11](https://openairdocs.org/ad/93-13-11): Gas Generator Turbine Rotor Disk · Honeywell International LTP 101-600, LTP 101-600A, LTP 101-600A-1A and 22 more. Effective Nov 8, 1993
- [AD 92-15-07](https://openairdocs.org/ad/92-15-07): Integrally Cast Power Turbine (PT) Rotor Blade · Honeywell International LTP 101-600, LTP 101-600A, LTP 101-600A-1A and 21 more. Effective Sep 2, 1992
- [AD 88-14-01](https://openairdocs.org/ad/88-14-01): Power Turbine Disk · Honeywell International LTS101-600A, LTS101-600A-1, LTS101-600A-2 and 17 more. Effective Jul 6, 1988
- [AD 86-10-04](https://openairdocs.org/ad/86-10-04): Gas Producer (G.P.) Blade · Honeywell International LTP 101-600A-1A, LTP 101-700A-1A, LTS101-600A-2 and 11 more. Effective May 16, 1986
- [AD 84-02-07](https://openairdocs.org/ad/84-02-07): Output Gear Assembly and Torquemeter Gear Assembly · Honeywell International LTS101-600A-2. Effective May 7, 1984
- [AD 83-16-03](https://openairdocs.org/ad/83-16-03): Install Overspeed Limiter · Honeywell International LTS101-600A-2. Effective Aug 25, 1983
- [AD 79-06-06 R2](https://openairdocs.org/ad/79-06-06-R2): Lubrication System Contamination · Honeywell International LTP 101-600, LTP 101-600A, LTS101-600A and 3 more. Effective Jun 2, 1980
- [AD 79-20-03](https://openairdocs.org/ad/79-20-03): Fuel Control, Fuel Pump And Oil Pump Drive Gears · Honeywell International LTP 101-600, LTP 101-600A, LTP 101-600A-1A and 5 more. Effective Sep 26, 1979
- [AD 84-14-01](https://openairdocs.org/ad/84-14-01): T4 Indicator System Check · Honeywell International LTS101-600A-2
- [AD 95-09-02](https://openairdocs.org/ad/95-09-02) (historical): Fuel Pumps · Honeywell International LTP 101-600, LTP 101-600A, LTP 101-600A-1A and 12 more. Effective May 10, 1995

## Registered aircraft by registry model (OpenAirDocs)

- [Lycoming LTS-101 series](https://openairdocs.org/engine/lycoming-lts-101-series): 29 aircraft (registry code 41560)
- [Honeywell LTS101-700D-2](https://openairdocs.org/engine/honeywell-lts101-700d-2): 8 aircraft (registry code 33825)
- [Honeywell LTS101-600A3A](https://openairdocs.org/engine/honeywell-lts101-600a3a): 5 aircraft (registry code 33819)
- [Lycoming LTS-101 600A](https://openairdocs.org/engine/lycoming-lts-101-600a-series): 3 aircraft (registry code 41562)
- [Honeywell LTS101-650C-3](https://openairdocs.org/engine/honeywell-lts101-650c-3): 2 aircraft (registry code 33823)
- [Honeywell LTS101-750B-1](https://openairdocs.org/engine/honeywell-lts101-750b-1): 2 aircraft (registry code 33826)
- [Honeywell LTS101-750C-1](https://openairdocs.org/engine/honeywell-lts101-750c-1): 1 aircraft (registry code 33828)
- [Honeywell LTS101-850B-2](https://openairdocs.org/engine/honeywell-lts101-850b-2): 1 aircraft (registry code 33829)
- [Alliedsign LTS101-750B-1](https://openairdocs.org/engine/alliedsign-lts101-750b-1): 0 aircraft (registry code 02656)
- [Honeywell LTS101-600A-2](https://openairdocs.org/engine/honeywell-lts101-600a-2): 0 aircraft (registry code 33817)
- [Honeywell LTS101-600A-3](https://openairdocs.org/engine/honeywell-lts101-600a-3): 0 aircraft (registry code 33818)
- [Honeywell LTS101-650B-1](https://openairdocs.org/engine/honeywell-lts101-650b-1): 0 aircraft (registry code 33820)
- [Honeywell LTS101-650B1A](https://openairdocs.org/engine/honeywell-lts101-650b1a): 0 aircraft (registry code 33821)
- [Honeywell LTS101-650C-2](https://openairdocs.org/engine/honeywell-lts101-650c-2): 0 aircraft (registry code 33822)
- [Honeywell LTS101-650C3A](https://openairdocs.org/engine/honeywell-lts101-650c3a): 0 aircraft (registry code 33824)
- [Honeywell LTS101-750B-2](https://openairdocs.org/engine/honeywell-lts101-750b-2): 0 aircraft (registry code 33827)

## STCs approved under this data sheet (1)

- [STC SE934GL](https://openairdocs.org/stc/SE934GL): Installation of a fuel flow tranducer.. Shadin Avionics

---
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.