# TCDS E4WE: Honeywell Aerospace US LLC

- Type: Type certificate data sheet
- Status: Current
- Holder: Honeywell Aerospace US LLC
- Revision: 35
- Revised: March 27, 2026
- Product: Engine
- Certification basis: Part 33
- Registered aircraft: 236, by the registry models matched to it (OpenAirDocs)
- Data sheet PDF: https://openairdocs.org/files/sha256/c4/1e/c41e26702c3b95d150656ae14a103abfeb3533894c45954b4f8380273f252998
- FAA DRS: https://drs.faa.gov/browse/excelExternalWindow/DRSDOCID117362894020260605175534.0001
- Page: https://openairdocs.org/tcds/E4WE

## Models (48)

As the data sheet lists them.

- TPE331-9U
- TPE331-10GP
- TPE331-10UGR
- TPE331-10J
- TPE331-10UK
- TPE331-10GT
- TPE331-12B
- TPE331-5A
- TPE331-10UG
- TPE331-12UA
- TPE331-10UR
- TPE331-6U
- TPE331-6
- TPE331-11UA
- TPE331-10UJ
- TPE331-3
- TPE331-5
- TPE331-10G
- TPE331-12UAN
- TPE331-10N
- TPE331-10U
- TPE331-10UA
- TPE331-10GR
- TPE331-10R
- TPE331-3UW
- TPE331-5B
- TPE331-5U
- TPE331-10
- TPE331-3U
- TPE331-10P
- TPE331-10T
- TPE331-10A
- TPE331-12JR
- TPE331-10B
- TPE331-11U
- TPE331-12UER
- TPE331-12
- TPE331-9
- TPE331-3W
- TSE331-3U
- TPE331-10UF
- TPE331-5AB
- TPE331-6A
- TPE331-12UHR
- TPE331-10AV
- TPE331-8
- TPE331-12UAR
- TPE331-8A

## 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 
E4WE 
Revision 35 
H
oneywell Aerospace US LLC 
(AlliedSignal, Garrett, 
AirResearch 
March 27, 2026 
TPE331-3 TPE331-8 TPE331-10N TPE331-11U 
TPE331-3U TPE331-8A TPE331-10P TPE331-11UA 
TPE331-3UW TPE331-9 TPE331-10R TPE331-12 
TPE331-3W TPE331-9U TPE331-10T TPE331-12B 
TPE331-5 TPE331-10 TPE331-10U TPE331-12JR 
TPE331-5A TPE331-10A TPE331-10UA TPE331-12UA 
TPE331-5AB TPE331-10AV TPE331-10UF TPE331-12UAN 
TPE331-5B TPE331-10B TPE331-10UG TPE331-12UAR 
TPE331-5U TPE331-10G TPE331-10UGR TPE331-12UER 
TPE331-6 TPE331-10GP TPE331-10UJ TPE331-12UHR 
TPE331-6A TPE331-10GR TPE331-10UK TSE331-3U 
TPE331-6U TPE331-10GT TPE331-10UR 
TPE331-10J 
March 27, 2026 
TY
PE CERTIFICATE DATA SHEET E4WE 
E
ngine models described herein conforming with this data sheet (which is part of Type Certificate No. E4WE) and other approved 
data on file with the Federal Aviation Administration meet the minimum standards for use in certified 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. 
T
ype Certificate Holder:  Honeywell Aerospace US LLC 
111 South 34th Street 
Phoenix, AZ 85034 
T
ype Certificate Record Holder: Honeywell International Inc. 
111 South 34th Street 
Phoenix, AZ 85034 
T
ype Certificate Record Holder: AlliedSignal Inc. 
111 South 34th Street 
Phoenix, AZ 85034 
TY
PE: Single-shaft engine with two-stage 
centrifugal compressor, three- 
 stage axial turbine, and singular 
annular combustion chamber 
Page No. 1 2 3 4 5 6 7 8 9 10 11 12 13 14 
Rev. No. 35 31 34 34 35 35 32 35 35 34 31 31 35 35

E
4WE 2 
Ratings (see NOTES 3, 4, and 5) 
Maximum Continuous Takeoff (5 Minutes) 
Output 
SHP ESHP Output Shaft SHP SHP ESHP ESHP Shaft 
RPM (Dry) (Wet)* (Dry) (Wet)* RPM 
Model TPE331 
-3 840 904 2000 840 940 904 1010 2000 
-3U " " " " " " " " 
-3UW " " " " " " " " 
-3W " " " " " " " " 
-10UA " " " " " " " " 
-5 776 834 1591 776 776 834 834 1591 
-5B " " " " " " " " 
-5U " " " " " " " " 
-10P " " " " " " " " 
-10T " " " " " " " " 
-5A " " " " 840 " 904 " 
-5AB " " " " " " " " 
-10GP " " " " " " " " 
-10GT " " " " " " " " 
-6 715 776 2000 750 N/A 808 N/A 2000 
-6A " " " " " " " " 
-6U " " " " " " " " 
-10AV " 756 " " " 792 " " 
-8 715 755 2000 715 N/A 755 N/A 2000 
-8A " " 1591 " " " " 1591 
-10N " " 2000 " " " " 2000 
-9 865 907 2000 865 N/A 907 N/A 2000 
-9U " " " " " " " " 
-10 900 944 1591 940 940 984 989 1591 
-10G " " " " " " " " 
-10GR " " " " " " " " 
-10R " " " " " " " " 
-10U " " " " " " " " 
-10UF " " " " " " " " 
-10UG " " " " " " " " 
-10UGR " " " " " " " " 
-10UR " " " " " " " " 
-12 " " " " N/A " N/A "

E4WE 3 
Ratings (see NOTES 3, 4, and 5) Continued 
Maximum Continuous Takeoff (5 Minutes) 
Output 
SHP ESHP Output Shaft SHP SHP ESHP ESHP Shaft 
RPM (Dry) (Wet)* (Dry) (Wet)* RPM 
Model TPE331 
-10A 900 944 2000 940 940 984 989 2000 
-10B " " " " " " " " 
-10J 970 1015 1591 1000 1000 1045 1045 1591 
-10UJ " " " " " " " " 
-12JR " 1020 " " " 1050 1050 " 
-10UK " " 2000 " " " " 2000 
-11U 1000 1045 1591 1000 1100 1045 1152 1591 
-11UA " " " " " " " " 
-12B 1100 1151 2000 1100 N/A 1151 N/A 2000 
-12UA 1050 1100 1591 1100 1100 1151 1156 1591 
-12UAR " " " " " " " " 
-12UER " " " " " " " " 
-12UHR " " " " " " " " 
-12UAN “ “ “ “ “ “ “ “ 
Mo
del TSE331 
-3U 700 756 2482 800 N/A 858 N/A 2482 
*Augmented with water-alcohol per NOTE 5

E
4WE 4 
Weight, Dry 
**(Pounds) 
Propeller-Shaft to engine 
rotor ratio 
Model TPE331 
-3, -3U, -3UW, -3W 353 1:20.865 
-5, -5U 360 1:26.229 
-5A 370 " 
-5B 375 " 
-5AB 385 " 
-6, -6U 360 1:20.865 
-6A 375 " 
-8 370 1:20.865 
-8A 370 1:26.229 
-9, -9U 375 1:20.865 
-10, -10G, -10GR, -10R, -10T, -10U, -10UF,
-10UG, -10UGR, -10GT, -10UR, -12
385 1:26.229 
-10P, -10GP 400 1:26.229 
-10A, -10AV 385 1:20.865 
-10B, -10UK 387 " 
-10N 385 " 
-10UA 377 " 
-10J, -10UJ 393 1:26.229 
-11U, -11UA 405 " 
-12B 429 1:20.865 
-12JR 415 1:26.229 
-12UA, -12UAR, -12UER, -12UHR 405 1:26.229 
-12UAN 433 1:26.229 
Mo
del TSE331 
-3U 350 1:16.813 
**
The engine weight shown herein consists of hardware as shown on the engine parts list including nose cone assembly, 
intermediate housing and gear assembly, torque sensor assembly, power group (compressor and turbine), fuel delivery system 
(including low and high pressure pumps and fuel filter with integral bypass and thermostatically controlled valve for filter and 
anti-icing, fuel control unit, fuel-shutoff valve), ignition system, and propeller oil flow tube, but does not include:  (a) hardware 
shown on the engine equipment list with the exception of fuel control unit, or (b) items coded "A" or “N” on the engine parts list.

E4WE 5 
FUEL TYPES AND ADDITIVES 
R
efer to the FAA approved Section of the engine installation manual (IM-5117). 
Co
ntrols (See Note 13) 
P
rincipal dimension of basic engine 
 Refer to the Installation Drawing for each specific engine model configuration for 
 dimensions and center of gravity location. 
Oil 
Oil conforming to Honeywell International Inc. Specification EMS53110 (Type I and Type II) is approved. 
Certification Basis 
1
4 CFR part 33 dated February 1, 1965 and Amendments 33-1, 33-2, and 33-3 
Type Certificate No. E4WE issued March 28, 1969, Model 
TPE331-3, -3U, -3W, and -3UW; 
Model TSE331-3U added April 30, 1970; 
Model TPE331-5, -5U, -6, and -6U added May 15, 1970; 
Model TPE331-8, -9, and -9U added November 19, 1976; 
Model TPE331-10, -10U, and -6A added January 20, 1978; 
Model TPE331-11U added September 28, 1979; 
Model TPE331-10A and -10B added December 12, 1980; 
Model TPE331-8A added December 24, 1981; 
Model TPE331-10R, -10UF, and -11UA added June 25, 1982; 
Model TPE331-10UA added July 29, 1982; 
Model TPE331-10UR added November 14, 1983; 
Model TPE331-10UG, -10UGR, -10GR, and -10G added 
  August 14, 1984; 
Model TPE331-12 added December 19, 1984; 
Model TPE331-12B added December 10, 1986; 
Model TPE331-12UAR added December 18, 1987; 
Model TPE331-5A, -12UA, -10J, and -10UJ added May 4, 1988; 
Model TPE331-10UK added November 4, 1988; 
Model TPE331-12UER added July 22, 1991; 
Model TPE331-10N added February 6, 1992 
Model TPE331-5B and -5AB added July 21, 1992; 
Model TPE331-12UHR added January 7, 1993; 
Model TPE331-10T added April 14, 1994; 
Model TPE331-10GT, -10P, -10GP added December 14, 1994; 
Model TPE331-10AV added July 19, 1996; 
Model TPE331-12JR added October 31, 1997 
Model TPE331-12UAN added May 22, 2014

E4W
E 6 
Production Basis 
Production Certificate No. 413 issued March 4, 1965.  Reissued Production Certificate No. 413NM to 
Honeywell Aerospace US LLC on March 29, 2026.
NOT
E 1: Maximum Permissible Temperatures - oF(oC)
 Exhaust Gas Temperature  Interstage Turbine Temperature 
 Maximum  Takeoff  Takeoff Maximum Takeoff  Takeoff See 
Continuous  (5 min.)  (5 min.) Continuous  (5 min.)  (5 min.) Note 
 (Dry)  (Wet)*  (Dry)  (Wet)* Below 
Model TPE331 
-3 1002(539) 1002(539) 1012(544) 1693(923) 1693(923) 1732(944) 
-3U " " " " " " 
-3UW " " " " " " 
-3W " " " " " " 
-5, -5A 1002(539) 1002(539) 1002(539) 1693(923) 1693(923) 1693(923) 
-5AB, -5B " " " " " " 
-5U " " " " " " 
-6 1002(539) 1002(539) N/A 1693(923) 1693(923) N/A 
-6A " " " " " " 
-6U " " " " " " 
-8 842(450) 842(450) N/A N/A N/A N/A 17 
-8A " " " " " " " 
-10N " " " " " " 20 
-9 842(450) 842(450) N/A N/A N/A N/A 20 
-9U " " " " " " " 
-10, -10A 1202(650) 1202(650) 1202(650) N/A N/A N/A 20 
-10B, -10G " " " " " " " 
-10GR " " " " " " " 
-10J, -10R " " " " " " " 
-10U " " " " " " " 
-10UF " " " " " " " 
-10UG " " " " " " " 
-10UGR " " " " " " " 
-10UJ " " " " " " " 
-10UR " " " " " " " 
-11U " " " " " " " 
-11UA " " " " " " " 
-12 " " " " " " " 
-12B " " " " " " " 
-12JR, -12UA " " " " " " " 
-12UAN " " " " " " " 
-12UAR " " " " " " " 
-12UER " " " " " " " 
-12UHR “ “ “ “ “ “ “

E4WE 7 
NOTE 1:  Maximum Permissible Temperatures - oF(oC) (Continued)
 Exhaust Gas Temperature  Interstage Turbine Temperature 
Maximum  Takeoff  Takeoff Maximum Takeoff Takeoff See 
Continuous  (5 min.)  (5 min.)  Continuous (5 min.)  (5 min.) Note 
 (Dry)  (Wet)*  (Dry)  (Wet)* Below 
Model TPE331 
-10UA 1049(565) 1049(565) 1049(565)  N/A  N/A  N/A 
-10AV  "  "  "  "  "  " 
-10GP  "  "  "  "  "  " 
-10GT  "  "  "  "  "  " 
-10P  "  "  "  "  "  " 
-10T  "  "  "  "  "  " 
-10UK  "  "  "  "  "  " 
Mo
del TSE331 
-3U N/A N/A N/A 1693(923) 1693(923) N/A 
* A
ugmented with water-alcohol per NOTE 5.
F
or engines equipped with Interstage Turbine Temperature (ITT) measurement systems the maximum permissible temperatures do 
not vary with ambient or operating conditions. 
F
or engines with Exhaust Gas Temperature (EGT) measurement systems and not operating with a Single Red-Line (SRL) computer 
or Electronic Engine Control (EEC), the maximum permissible temperatures vary as a function of ambient temperature, altitude, and 
other operating conditions.  Takeoff and maximum continuous EGT temperatures are for International Standard Atmosphere (ISA) 
sea-level, static un-installed conditions.  Consult IM-5117 for other conditions.  The maximum EGT for operation between 65 percent 
and 79 percent engine speed is 760oC for the TPE331-3 through -6 series engines and is 770oC for the TPE331-8 through -12 series
engines. 
F
or engines equipped with EGT measurement systems, and operating with a SRL computer or EEC, the maximum permissible 
temperature does not vary under any condition except engine speed.  The maximum EGT for operation between 65 percent and 79 
percent engine speed is 770oC for the TPE331-8 through -12 series engines.  For engine speeds above 80 percent the maximum
indicated EGT is 450oC for TPE331-8 series, and -10N model engines, or 650oC for TPE331-12B model engine
and engines equipped with a SRL computer, except when APR/RPR is activated.  (See NOTE 20). 
N
OTE 1: Maximum Permissible Temperatures - oF(oC) (Continued)
Maximum Exhaust Gas Maximum Interstage 
Temperature During Temperature During 
Starting (1 sec. Starting (1 sec. 
Limit):  oF(oC) Limit):  oF(oC)
Model TPE331 
-3, -3U, -3W, -3UW, 1500 (815) 2100 (1149) 
-5, -5A, -5U, -5AB, " " 
-5B, -6, -6A, -6U " " 
-8, -8A 1418 (770) N/A 
-9, -9U " " 
-10, -10A, -10AV, -10B " " 
-10G, -10GR " " 
-10J, -10R, -10T, -10GT " " 
-10P, -10GP " " 
-10U, -10UA " " 
-10UF, -10UG " "

E
4WE 8 
-10UGR, -10UJ " " 
-10UK, -10UR, -10N " " 
-11U, -11UA " " 
-12, -12JR, -12UA " " 
-12UAR, -12UER, -12UHR, -12UAN " " 
 
  
-12B “ " 
Mo
del TSE331 
-3U 1500 (815) 2100 (1149) 
Oil Temperature and Specifications: 
H
oneywell Aerospace Specification 
Type of Lubricant 
Equivalent Military 
Specification 
M
inimum of Starting oF (oC) 
EMS 53110 
TYPE I 
MIL-PRF-7808 -40 (-40)
EMS53110 
TYPE II 
MIL-PRF-23699 -40 (-40)
N
ote: Refer to engine installation manual IM-5117, FAA approved section, lubrication system, for oil pressure and temperature 
limits. 
N
OTE 1: Maximum Permissible Temperatures - oF(oC) (Continued)
A
mbient Air Temperature, oF(oC)
S
tarting  Operation 
Minimum -40 (-40)**  -- 
Maximum 13
0 (55)  130 (55) 
*
*Starting in ambient air temperatures below -40oF(-40oC) is acceptable provided the engine oil and electrical components’ steady 
state temperatures are not less than -40 oF(-40oC). 
E
ngine External Components Surface Temperature Limits (Refer to the FAA approved section of engine installation manual 
IM-5117. 
N
OTE 2: Pressure Limits 
Fuel pump inlet pressure, minimum normal operation, refer 
to the FAA approved section of engine installation manual 
IM-5117 for operational limitations 
 5 psig plus true vapor pressure of fuel 
Minimum oil pressure at inlet connection to the engine  2.45 psig 
Oil operating pressure ground idle (minimum at 65% speed)  40 psig 
Normal operating range  70 to 120 psig 
Normal operating range (above 23,000 ft. altitude)  50 to 120 psig 
Minimum water-alcohol augmentation manifold inlet 
pressure  (see NOTE 5)

E4WE 9 
N
OTE 3: The Engine Ratings are based on: 
 D
ynamometer operation at International Standard Atmosphere (ISA), Sea Level Static Conditions, see NOTE 1. 
 MI
L-DTL-5624, Grade JP-4 fuel with lower heating value of 18,400 BTU per pound. 
 MI
L-PRF-23699 type oil, Mobil Oil Jet II, or Exxon 2380. 
 N
o bleed-air extraction. 
 N
o anti-icing airflow. 
 N
o external accessory loads. 
 Z
ero inlet loss. 
 E
xhaust gas discharging to ambient-static pressure through the turbine exhaust diffuser furnished with the engine. 
 T
urbine gas temperature (ITT or EGT) limits not exceeded. 
N
OTE 4:     Equivalent Shaft Horsepower (ESHP) for Static Conditions is based on: 
 ESHP = Net thrust, pounds + SHP 
       2.5 
N
OTE 5: Augmented Performance 
A. Augmented engine ratings are listed on Page 2.
B. Augmented interstage turbine temperature or exhaust gas
temperature limits are stated in NOTE 1.
C. Engine propeller shaft torque limits per NOTE 7 shall remain
the same.
D. Water-alcohol mixture must conform to that shown in the FAA approved section of engine installation manual
IM-5117.
E. Minimum water-alcohol flow rate is dependent on engine power requirements and is determined through
coordination of the aircraft manufacturer and Honeywell Aerospace US LLC.
F. Water-alcohol manifold pressure required to obtain specified flow is stamped on each manifold.
Engine Model 
Water-Alcohol Flow Rate – lb/hr 
(NOTE 5D) 
Water Alcohol Manifold 
Pressure (psig)  (NOTE 5F) 
Minimum Maximum 
-3, -3UW, -3W 780 950 10-14
-10UA, -10UK 528 600 6-8
-5, -5A, -5AB, -5B, -5U, -10T NOTE 5E 950 N/A
-10GT, -10P, -10GP " " " 
-10, -10A, -10B, -10G, -10AV " " " 
-10J, -10R, -10U, -10UF " " " 
-10UG, -10UGR, -10UJ, -10UR " " " 
-11U, -11UA NOTE 5E 1250 " 
-12JR, -12UA, -12UAR, -12UER, -12UHR " 1300 " 
-12UAN “ “ “

E
4WE 10 
NOTE 6:  Accessory Provisions 
A
. Aircraft Accessory
All Models 
Type of drive:  (one each) AND20001 
Type X1-B 
(Modified) 
AND drive modifications Rotation and RPM 
Rotation facing drive pad CCW 
RPM at 100 percent engine speed 3,959 
Maximum torque (lb-in.) 
Tc, continuous torque 
250 
To, torque overload 375 
Ts, static torque 1,650 
Overhung moment (lb-in.) 125 
Speed ratio, drive to engine rotor 0.09487 
B
. Starter, Starter-generator or Alternator
Type of drive:  (one each) AND20002 
Type XII-D 
(Modified) 
AND drive modifications RPM, Tc, To 
and stud pattern 
rotated 30 degrees 
All Models Except: 
TPE331-5, -5A, -5AB, 
-5B, -5U, -6, -6A, -6U,
-10AV, -10GT, -10P,
-10GP, -8, -9, -9U,
-10N, -10T
TPE331-5, -5A, -5AB, -5B, 
-5U, -6, -6A, -6U, -8, -9,
-9U, -10AV,
-10N, -10T, -10GT,
-10P, -10GP
Rotation facing drive pad CW CW 
RPM at 100 percent engine speed 12,175 10,887 
Maximum torque (lb-in.) 
Tc, continuous torque 
300 300 
To, torque overload 600 600 
Ts, static torque 2,200 2,200 
Overhung moment (lb-in.) 500 500 
Speed ratio, drive to engine rotor 0.29175 0.26089

E4WE 11 
NOTE 6: (Continued) 
C
. Tachometer Generator  All Models 
Type of drive:  (one each) AND20005 Type XV-B 
(Modified) 
AND drive modifications Shorter studs and 
thread lengths 
Rotation facing drive pad CW 
RPM at 100 percent engine speed 4,187 
Maximum torque (lb-in.) Tc, continuous torque 7 
Ts, static torque 50 
Overhung moment (lb-in.) 25 
Speed ratio, drive to engine rotor 0.10033 
D. Propeller Governor
 All Models 
Type of drive:  (one each) AND20010 Type XX-A 
(Modified) 
AND drive modifications RPM 
Rotation facing drive pad CW 
RPM at 100 percent engine speed 3,754 
Maximum torque (lb-in.) 
Tc, continuous torque 
125 
To, torque overload 188 
Ts, static torque N/A 
Overhung moment (lb-in.) 125 
E. Propeller Pitch Control
Type of drive:  (one each) Mounting pad provided 
Overhung moment (lb-in.) 30 
N
OTE 7: Maximum Allowable Propeller Shaft Torque as Sensed by the 
Torque Sensor, in Pound Feet 
Model TPE331 5 Minute Torque Limit Maximum Continuous 
-3 2470 2206 
-3U " " 
-3UW " " 
-3W " " 
-10UA " " 
-5, -5B 2564 2564

E4W
E 12 
NOTE 7: (Continued) 
-5U " " 
-8A, -10T, -10P " " 
-5A, -5AB, -10GT, 2773 2564 
-10GP " " 
-6 2040 1878 
-6A " " 
-6U " " 
-8 " " 
-10AV " " 
-10N " " 
-9 2363 2271 
-9U " " 
-10J 3301 3202 
-10UJ " " 
-12JR " " 
-10A 2470 2363 
-10B " " 
-10 3105 2972 
-10G " " 
-10GR " " 
-10R " " 
-10U " " 
-10UF " " 
-10UG " " 
-10UR " " 
-10UGR " " 
-12 " " 
-11U 3631 3466 
-11UA " " 
-12UA " " 
-12UAR " " 
-12UER " " 
-12UHR, -12UAN " " 
-12B 2889 2889 
-10UK 2626 2547 
Model TSE331 5 Min. Torque Limit Maximum Continuous 
-3U 1777 1481 
NOT
E  8: Propeller Output Shaft (Bolted Flange) Maximum Speed, 
Percent (RPM) and Direction of Rotation 
TPE331 
-3, -3
U, -3UW, -3W, -6,
-6A, -6U, -8, -9, -9U,
-10A, -10B, -10N,
-10UA, -10AV, -10UK,
-12B
TPE331 
-5, -5
A, -5AB, -5B, -5U,
-8A, -10, -10G, -10GR,
-10J, -10R, -10U, -10UF,
-10T, -10GT, -10UG,
-10UGR, -10P, -10GP,
-10UJ, -10UR, -11U,
-11UA, -12, -12JR,
-12UA, -12UAR,
-12UER, -12UHR,
-12UAN
TSE331 
-3U

E4WE 13 
No
rmal 
Operation 
100.
0 (2000) 100.
0 (1591) 100.
0 (2482) 
Continuous 
Operation 
101.0 (2020) 101.0 (1607) 101.0 (2507) 
see NOTE 14 
Transient 
Limit 
104.0 (2080) 
NOTE 22 
104.0 (1655) 
NOTE 22 
104.0 (2581) 
Rotation, aft 
loo
king 
forward 
CW 
(CCW FOR -10B) 
CCW CW 
NOT
E   9: Incorporated into NOTE 8. 
NOT
E 10: Up to 10 percent of the engine airflow is available for bleed air purposes (except during starting).  Of this 
10 percent total, 1.2 percent is utilized by the engine mounted anti-icing system. 
NOT
E 11: These engines meet FAA requirements for adequate turbine disk integrity and rotor blade containment, 
and do not require external armoring. 
NOT
E 12: These engines meet FAA requirements for operation in icing conditions within the envelope defined in 
14 CFR part 25 Appendix C, original issue. 
NOT
E 13: Variations in engine configuration and installation components are identified on the engine nameplate by a 
suffix to the basic model number, i.e., TPE331-3-XY (“X” denotes Honeywell Aerospace installed     
configuration rating code number(s) and “Y” denotes Honeywell Aerospace equipment code letter(s) 
identifying the aircraft manufacturer or aircraft supplemental type certificate holder), and by an engine part 
number.  The engine part number shown on the engine nameplate identifies the specific parts list and/or 
equipment list which have been demonstrated as compatible with the basic engine during engine certification. 
Certain features of these installation components are influenced by aircraft design considerations. In the 
engine parts list or equipment list, items coded "A" have been demonstrated as compatible with the basic 
engine during engine certification; however, the operation, functioning, and rigging of these in a specific 
aircraft installation must be demonstrated during aircraft certification.  Subsequent design change to the 
engine associated with these factors is the responsibility of the aircraft manufacturer and must be in 
compliance with 14 CFR part 33. 
NOT
E 14: The maximum allowable continuous operating output shaft speed for the TSE331-3U is 2556 rpm (103 percent 
speed) for 1100oF ITT and below, varying linearly to 2507 rpm (101 percent speed) at 1693oF (ITT).
NOT
E 15:     Certain engine parts are life limited.   These limits are listed in the FAA-Approved Honeywell Aerospace US, 
LLC Service Bulletins as follows: 
Engine Series Honeywell Aerospace Service Bulletins 
TPE331-3, -5, 
-6, TSE331-3
TPE/TSE331-72-0019 Revision 25, or later FAA approved revisions 
TPE331-8, -9 TPE331-72-0117 Revision 13, or later FAA approved revisions 
TPE331-10, -11 TPE331-72-0180 Revision 42, or later FAA approved revisions 
TPE331-12 TPE331-72-0476 Revision 38, or later FAA approved revisions 
NOT
E 16: The following information should be included, as appropriate, in a suitable aircraft placard or FAA approved 
flight manual -  "Avoid operation between 18 and 28 percent rpm, except for transient occurring during start 
and shut-down." 
TPE331 TPE331 TSE331 
NOTE   9: 
NOTE 8: continued:

E4W
E 14 
NOTE 17: The TPE331-8 series engines are equipped with an integrated fuel control system consisting of an engine 
driven hydromechanical control and an aircraft mounted EEC that is energized by the aircraft electrical 
system.  This system may be operated in either an Automatic Mode in which both control components are 
active or in a Manual Mode with the EEC de-activated.  De-activation of the EEC is accomplished 
automatically should certain faults develop in the electronic component.  The operating limits shown in 
NOTE 1 are for Automatic Mode operation.  When operating in the Manual Mode, the rated EGT shown in 
NOTE 1 will be 937oF (503oC) for the TPE331-8 series engines and will vary as a function of ambient
conditions.  Consult the FAA approved section of engine installation manual IM-5117 for other than standard 
day sea level EGT limits. 
NOT
E 18: Deleted with Revision 26. 
NOT
E 19: Deleted with Revision 25. 
NOT
E 20: Certain TPE331-9 series, TPE331-10 series and TPE331-11 and -12 series engine power management systems 
may include a SRL temperature indicating system and an automatic torque and temperature limiting system.  At 
t
he SRL limit value of 1202oF (650oC) [except for -9 series and -10N engines is 842oF (450oC)] these engines
will provide a minimum of rated thermodynamic performance.  The TPE331-10R, -10GR,  
-10UR, -10UGR, -12JR, -12UAR, -12UER, -12UHR, and -12UAN engines have the capability of Automatic
Performance Reserve (APR) or Restricted Power Reserve (RPR) to provide a thermodynamic power increase in
some multi-engine aircraft installations if significant power loss occurs on another engine.
The engines are approved for operation up to an SRL value of 676oC for -10R, 669oC for -10UG/-10UR/
-10UGR, and 675oC for -12JR, -12UAR, -12UER, -12UHR, and -12UAN when the APR/RPR EGT
compensator is not powered and APR/RPR is activated with temperature limiting disabled.  The aircraft may
incorporate EGT compensation that will reduce the indicated EGT to preclude exceeding the EGT limiting set
point (650oC or 660oC depending on the installation), when APR/RPR is activated.
With the SRL computer inoperative, the EGT limit for the TPE331-9 and -9U engines is 937oF (503oC), for 
TPE331-10, -10G, -10R, -10GR, -10U, and -11UA engines is 1049oF (565oC), and for TPE331-10UF, -10J, -10UJ, -
10UG, -10UGR, -10UR and -11U engines is 1079oF (582oC), and 1085oF (585oC) for -12 series engines [except for 
-12JR , -12UHR, and -12UAN engines is 1116oF (602oC)] at ISA/sea level and will vary as a function of ambient
conditions.  Consult IM-5117 for off-standard day EGT limits.
The -10A, -10B, -10N, and -12B engines are equipped with an integrated fuel control system consisting of an 
engine driven hydromechanical control and an aircraft mounted EEC which is energized by the aircraft 
electrical system.  This system may be operated in either an Automatic Mode in which both control 
components are active, or in a Manual Mode with the EEC de-activated.  De-activation of the EEC is 
accomplished automatically should certain faults develop in the electronic component.  The operating limits 
shown in NOTE 1 are for Automatic Mode operation.  When operating in the Manual Mode, the rated EGT 
shown in NOTE 1 will be 1049oF (565oC) for the -10A and -10B engines, 946oF (508oC) for the -10N 
engine, and 1085oF (585oC) for the -12B engine at ISA/sea level and will vary as a function of ambient 
conditions.  Consult IM-5117 for off-standard day EGT limits. 
Component interface and installation requirements of the aircraft-installed components are also prescribed in 
IM-5117. 
NOT
E 21: Deleted with Revision 26. 
NOT
E 22: Transient operation of propeller output shaft speed above 104 percent, to a maximum of 106 percent is 
allowable for fuel control overspeed governor test when the propeller is on the start locks (not applicable to 
T
SE331-3U).  Refer to engine maintenance manual for proper procedures and limitations for this test. 
-----------------------------------End----------------------------------
```

## ADs (46, in force first)

- [AD 2018-22-01](https://openairdocs.org/ad/2018-22-01): Turbine Section · Honeywell International TPE331-10, TPE331-10N, TPE331-10R and 8 more. Effective Dec 10, 2018
- [AD 2018-17-15](https://openairdocs.org/ad/2018-17-15): Turbine Engine Combustion Section · Honeywell International TPE331-1, TPE331-10, TPE331-10AV and 39 more. Effective Oct 22, 2018
- [AD 2018-13-05](https://openairdocs.org/ad/2018-13-05): Turbine Engine Reduction Gear · Honeywell International TPE331-1, TPE331-10, TPE331-10AV and 18 more. Effective Jul 26, 2018
- [AD 2016-21-07](https://openairdocs.org/ad/2016-21-07): Fuel control drive · Honeywell International TPE331-1, TPE331-10, TPE331-10AV and 26 more. Effective Nov 28, 2016
- [AD 2016-18-17](https://openairdocs.org/ad/2016-18-17): Compressor impeller · Honeywell International TPE331-10, TPE331-10AV, TPE331-10GP and 22 more. Effective Nov 4, 2016
- [AD 2015-18-03](https://openairdocs.org/ad/2015-18-03): Engine propeller shaft coupling failures · Honeywell International TPE331-10, TPE331-10R, TPE331-10U and 8 more. Effective Nov 13, 2015
- [AD 2012-02-06](https://openairdocs.org/ad/2012-02-06): First stage turbine disks · Honeywell International TPE331-10, TPE331-10AV, TPE331-10GP and 12 more. Effective Mar 15, 2012
- [AD 2011-18-51 R1](https://openairdocs.org/ad/2011-18-51-R1): Main shaft bearing · Honeywell International TPE331-1, TPE331-10, TPE331-10A and 82 more. Effective Oct 19, 2011
- [AD 2009-17-05](https://openairdocs.org/ad/2009-17-05): First stage turbine disks · Honeywell International TPE331-10, TPE331-10A, TPE331-10AV and 20 more. Effective Sep 1, 2009
- [AD 2006-14-03](https://openairdocs.org/ad/2006-14-03): New flight cycle counting method for first, second, and third-stage turbine rotors · Honeywell International TPE331-1, TPE331-10, TPE331-10A and 48 more. Effective Aug 9, 2006
- [AD 2004-09-29](https://openairdocs.org/ad/2004-09-29): First Stage Turbine Disks · Honeywell International TPE331-10, TPE331-10A, TPE331-10AV and 20 more. Effective Jun 15, 2004
- [AD 2002-25-02](https://openairdocs.org/ad/2002-25-02): First stage compressors implellers · Honeywell International TPE331-10, TPE331-10A, TPE331-10AV and 35 more. Effective Jan 21, 2003
- [AD 2002-21-15](https://openairdocs.org/ad/2002-21-15): Second stage turbine stator inner seal support · Honeywell International TPE331-1, TPE331-2, TPE331-2UA and 9 more. Effective Nov 26, 2002
- [AD 2002-12-09](https://openairdocs.org/ad/2002-12-09): Spectrometric Oil Analysis Program (SOAP) Sampling of Oil and Filter, Gearbox Components · Honeywell International TPE331-11U, TPE331-12B, TPE331-12JR and 3 more. Effective Jul 3, 2002
- [AD 2001-21-02](https://openairdocs.org/ad/2001-21-02): Airplane Flight Manual--Electronic Engine Controls · Honeywell International TPE331-10N, TPE331-12B and TPE331-8. Effective Nov 19, 2001
- [AD 98-12-09](https://openairdocs.org/ad/98-12-09): Fuel Manifold · Honeywell International TPE331-10, TPE331-10A, TPE331-10AV and 29 more. Effective Aug 7, 1998
- [AD 98-04-15](https://openairdocs.org/ad/98-04-15): Turbine Stators · Honeywell International TPE331-1, TPE331-2, TPE331-2UA and 9 more. Effective Apr 27, 1998
- [AD 97-15-10](https://openairdocs.org/ad/97-15-10): Engine Inlet Ice Protection · Honeywell International TPE331-10, TPE331-10A, TPE331-10AV and 39 more. Effective Sep 22, 1997
- [AD 95-16-08](https://openairdocs.org/ad/95-16-08): Life Limited Turbine Components · Honeywell International TPE331-1, TPE331-10, TPE331-10A and 62 more. Effective Sep 5, 1995
- [AD 94-26-07](https://openairdocs.org/ad/94-26-07): Fuel Control Governor Drive · Honeywell International TPE331-10, TPE331-10A, TPE331-10B and 32 more. Effective Apr 18, 1995
- [AD 94-09-08](https://openairdocs.org/ad/94-09-08): Third Stage Stator Turbine Assemblies · Honeywell International TPE331-1, TPE331-2, TPE331-2UA and 7 more. Effective May 20, 1994
- [AD 93-15-11](https://openairdocs.org/ad/93-15-11): Propeller Pitch Control (PPC) Gasket · Honeywell International TPE331-1, TPE331-10, TPE331-10A and 58 more. Effective Sep 7, 1993
- [AD 92-26-08](https://openairdocs.org/ad/92-26-08): Third Stage Stator Assemblies · Honeywell International TPE331-1, TPE331-2, TPE331-2UA and 7 more. Effective Jul 15, 1993
- [AD 93-05-09](https://openairdocs.org/ad/93-05-09): Third Stage Turbine Stator Assemblies · Honeywell International TPE331-1, TPE331-2, TPE331-2UA and 9 more. Effective Jun 28, 1993
- [AD 93-02-01](https://openairdocs.org/ad/93-02-01): Stratoflex Fuel Manifold Assemblies · Honeywell International TPE331-10, TPE331-10A, TPE331-10B and 21 more. Effective Mar 18, 1993
- [AD 89-07-07 R1](https://openairdocs.org/ad/89-07-07-R1): Oil Scavenge Pump Assembly · Honeywell International TPE331-1, TPE331-10, TPE331-10R and 26 more. Effective Oct 30, 1989
- [AD 84-10-06 R1](https://openairdocs.org/ad/84-10-06-R1): Fuel Pump Assemblies · Honeywell International TPE331-1, TPE331-10, TPE331-10B and 45 more. Effective Dec 26, 1984
- [AD 84-01-04](https://openairdocs.org/ad/84-01-04): Third Stage Turbine Wheels · Honeywell International TPE331-1, TPE331-1U, TPE331-1UA and 11 more. Effective Jan 25, 1984
- [AD 73-26-07 R3](https://openairdocs.org/ad/73-26-07-R3): Fuel Pump Shaft Internal Drive Splines · Honeywell International TPE331-1, TPE331-1U, TPE331-1UA and 39 more. Effective Jul 31, 1980
- [AD 78-25-08 R3](https://openairdocs.org/ad/78-25-08-R3): Turbine Rotor · Honeywell International TPE331-1, TPE331-1U, TPE331-1UA and 11 more. Effective Jun 12, 1980
- [AD 79-12-04](https://openairdocs.org/ad/79-12-04): Forged Third Stage Turbine Wheel Blade · Honeywell International TPE331-10. Effective May 10, 1979
- [AD 78-05-02](https://openairdocs.org/ad/78-05-02): Propeller Pitch Control Cam Follower Pin · Honeywell International TPE331-1, TPE331-1U, TPE331-1UA and 11 more. Effective Apr 5, 1979
- [AD 76-16-01](https://openairdocs.org/ad/76-16-01): Bearing Oil Transfer Tube · Honeywell International TPE331-1, TPE331-1U, TPE331-1UA and 11 more. Effective Aug 6, 1976
- [AD 74-10-10](https://openairdocs.org/ad/74-10-10): Fuel Control Assembly Support Bracket · Honeywell International TPE331-1, TPE331-2, TPE331-3U and 2 more. Effective Jul 11, 1975
- [AD 75-10-05](https://openairdocs.org/ad/75-10-05): Torque Sensor Assembly Mounting Arm · Honeywell International TPE331-1, TPE331-2, TPE331-3U and 3 more. Effective Jul 11, 1975
- [AD 74-24-05](https://openairdocs.org/ad/74-24-05): Propeller Pitch Control Sleeve Assembly · Honeywell International TPE331-3U, TPE331-3UW, TPE331-5 and 1 more. Effective Nov 26, 1974
- [AD 73-26-03](https://openairdocs.org/ad/73-26-03): Fuel Control Drive · Honeywell International TSE331-3U. Effective Dec 28, 1973
- [AD 70-16-09](https://openairdocs.org/ad/70-16-09): High Speed Pinion Assembly · Honeywell International TPE331-3W
- [AD 2018-02-14](https://openairdocs.org/ad/2018-02-14) (historical): Turbine Engine Combustion Section · Honeywell International TPE331-1, TPE331-10, TPE331-10AV and 38 more. Effective Feb 28, 2018
- [AD 2015-12-04](https://openairdocs.org/ad/2015-12-04) (historical): Fuel control unit (FCU) · Honeywell International TPE331-1, TPE331-10, TPE331-10AV and 26 more. Effective Jul 22, 2015
- [AD 2006-15-08](https://openairdocs.org/ad/2006-15-08) (historical): Woodward fuel control unit (FCU) assemblies · Honeywell International TPE331-1, TPE331-10, TPE331-10AV and 26 more. Effective Aug 24, 2006
- [AD 88-12-10](https://openairdocs.org/ad/88-12-10) (historical): Turbine Rotor · Honeywell International TPE331-10, TPE331-10R, TPE331-10U and 6 more. Effective Jun 6, 1988
- [AD 2011-18-51](https://openairdocs.org/ad/2011-18-51) (historical): Main shaft bearing · Honeywell International TPE331-1, TPE331-10, TPE331-10A and 82 more
- [AD 90-21-01](https://openairdocs.org/ad/90-21-01) (historical): Third stage stator assembly · Honeywell International TPE331-1, TPE331-2, TPE331-2UA and 7 more
- [AD 91-04-02](https://openairdocs.org/ad/91-04-02) (historical): Third stage stator assembly · Honeywell International TPE331-1, TPE331-2, TPE331-2UA and 7 more
- [AD 92-02-19 PL](https://openairdocs.org/ad/92-02-19-PL) (historical): Fuel Manifold Assembly Leak · Honeywell International TPE331-10, TPE331-10A, TPE331-10AV and 29 more

## Registered aircraft by registry model (OpenAirDocs)

- [Garrett TPE331-12B](https://openairdocs.org/engine/garrett-tpe331-12b): 19 aircraft (registry code 29076)
- [Honeywell TPE331-10 series](https://openairdocs.org/engine/honeywell-tpe331-10-series): 17 aircraft (registry code 33899)
- [Honeywell TPE331-12JR](https://openairdocs.org/engine/honeywell-tpe331-12jr): 15 aircraft (registry code 33806)
- [Honeywell TPE331-10](https://openairdocs.org/engine/honeywell-tpe331-10): 13 aircraft (registry code 33977)
- [Honeywell TPE331-10R](https://openairdocs.org/engine/honeywell-tpe331-10r): 13 aircraft (registry code 33988)
- [Garrett TPE331-11U](https://openairdocs.org/engine/garrett-tpe331-11u): 12 aircraft (registry code 29073)
- [Honeywell TPE331-10N](https://openairdocs.org/engine/honeywell-tpe331-10n): 11 aircraft (registry code 33986)
- [Alliedsign TPE331-12UHR](https://openairdocs.org/engine/alliedsign-tpe331-12uhr): 10 aircraft (registry code 02505)
- [Garrett TPE331-10N](https://openairdocs.org/engine/garrett-tpe331-10n): 8 aircraft (registry code 29062)
- [Honeywell TPE331-10T](https://openairdocs.org/engine/honeywell-tpe331-10t): 8 aircraft (registry code 33989)
- [Honeywell TPE331-11U](https://openairdocs.org/engine/honeywell-tpe331-11u): 8 aircraft (registry code 33996)
- [Garrett TPE331-10](https://openairdocs.org/engine/garrett-tpe331-10): 7 aircraft (registry code 29053)
- [Garrett TPE331-10 series](https://openairdocs.org/engine/garrett-tpe331-10-series): 7 aircraft (registry code 29118)
- [Garrett TPE331-5](https://openairdocs.org/engine/garrett-tpe331-5): 7 aircraft (registry code 29041)
- [Garrett TPE331-6](https://openairdocs.org/engine/garrett-tpe331-6): 6 aircraft (registry code 29046)
- [AiResearch TSE331 series](https://openairdocs.org/engine/airesearch-tse331-series): 5 aircraft (registry codes 01505, 01520)
- [Garrett TPE331-10R](https://openairdocs.org/engine/garrett-tpe331-10r): 5 aircraft (registry code 29064)
- [Garrett TPE331-12UHR](https://openairdocs.org/engine/garrett-tpe331-12uhr): 5 aircraft (registry code 29081)
- [AiResearch TPE331-8 series](https://openairdocs.org/engine/airesearch-tpe331-8-series): 4 aircraft (registry code 01530)
- [Honeywell TPE331-10U](https://openairdocs.org/engine/honeywell-tpe331-10u): 4 aircraft (registry code 33990)
- [Alliedsign TPE331-10T](https://openairdocs.org/engine/alliedsign-tpe331-10t): 3 aircraft (registry code 02587)
- [Garrett TPE331-10T](https://openairdocs.org/engine/garrett-tpe331-10t): 3 aircraft (registry code 29065)
- [Garrett TPE331-8](https://openairdocs.org/engine/garrett-tpe331-8): 3 aircraft (registry code 29049)
- [Honeywell TPE331-10AV](https://openairdocs.org/engine/honeywell-tpe331-10av): 3 aircraft (registry code 33979)
- [Honeywell TPE331-12UHR](https://openairdocs.org/engine/honeywell-tpe331-12uhr): 3 aircraft (registry code 33810)
- [Honeywell TPE331-6](https://openairdocs.org/engine/honeywell-tpe331-6): 3 aircraft (registry code 33970)
- [AiResearch TPE331-10](https://openairdocs.org/engine/airesearch-tpe331-10): 2 aircraft (registry code 01568)
- [AiResearch TPE331-10T](https://openairdocs.org/engine/airesearch-tpe331-10t): 2 aircraft (registry code 01580)
- [AiResearch TPE331-6](https://openairdocs.org/engine/airesearch-tpe331-6): 2 aircraft (registry code 01561)
- [Alliedsign TPE331-10R](https://openairdocs.org/engine/alliedsign-tpe331-10r): 2 aircraft (registry code 02586)
- [Alliedsign TPE331-6](https://openairdocs.org/engine/alliedsign-tpe331-6): 2 aircraft (registry code 02568)
- [Garrett TPE331-10U](https://openairdocs.org/engine/garrett-tpe331-10u): 2 aircraft (registry code 29066)
- [Garrett TPE331-10UGR](https://openairdocs.org/engine/garrett-tpe331-10ugr): 2 aircraft (registry code 29069)
- [Honeywell TPE331-5](https://openairdocs.org/engine/honeywell-tpe331-5): 2 aircraft (registry code 33965)
- [AiResearch TPE331-10R](https://openairdocs.org/engine/airesearch-tpe331-10r): 1 aircraft (registry code 01579)
- [AiResearch TPE331-10U](https://openairdocs.org/engine/airesearch-tpe331-10u): 1 aircraft (registry code 01581)
- [AiResearch TPE331-10UA](https://openairdocs.org/engine/airesearch-tpe331-10ua): 1 aircraft (registry code 01555)
- [AiResearch TPE331-11U](https://openairdocs.org/engine/airesearch-tpe331-11u): 1 aircraft (registry code 01588)
- [AiResearch TPE331-12UHR](https://openairdocs.org/engine/airesearch-tpe331-12uhr): 1 aircraft (registry code 01596)
- [AiResearch TPE331-3U](https://openairdocs.org/engine/airesearch-tpe331-3u): 1 aircraft (registry code 01552)
- [AiResearch TPE331-5](https://openairdocs.org/engine/airesearch-tpe331-5): 1 aircraft (registry code 01556)
- [AiResearch TPE331-8](https://openairdocs.org/engine/airesearch-tpe331-8): 1 aircraft (registry code 01564)
- [Alliedsign TPE331-10AV](https://openairdocs.org/engine/alliedsign-tpe331-10av): 1 aircraft (registry code 02577)
- [Alliedsign TPE331-10N](https://openairdocs.org/engine/alliedsign-tpe331-10n): 1 aircraft (registry code 02584)
- [Alliedsign TPE331-8](https://openairdocs.org/engine/alliedsign-tpe331-8): 1 aircraft (registry code 02571)
- [Garrett TPE331-10AV](https://openairdocs.org/engine/garrett-tpe331-10av): 1 aircraft (registry code 29055)
- [Garrett TPE331-11UA](https://openairdocs.org/engine/garrett-tpe331-11ua): 1 aircraft (registry code 29074)
- [Garrett TPE331-12](https://openairdocs.org/engine/garrett-tpe331-12): 1 aircraft (registry code 29075)
- [Garrett TPE331-12UAR](https://openairdocs.org/engine/garrett-tpe331-12uar): 1 aircraft (registry code 29089)
- [Honeywell TPE331-10UA](https://openairdocs.org/engine/honeywell-tpe331-10ua): 1 aircraft (registry code 33964)

All 190: https://openairdocs.org/tcds/E4WE/aircraft.md

## STCs approved under this data sheet (13)

- [STC SE02538AK](https://openairdocs.org/stc/SE02538AK): Modification of Honeywell TPE331-12JR-702TT engine. TAE Aerospace (CTEC)
- [STC SE03035AT](https://openairdocs.org/stc/SE03035AT): Installation of Royal Atlantic Aviation Engine Oil Filter Bypass Warning System, Kit P/N RAA2003-1-1. Reds Aircraft Service Inc.
- [STC SE00265AT](https://openairdocs.org/stc/SE00265AT): Install Ayres Fuel Manifold Purge Assembly Kit, P/N 21757-1 in accordance with "Installation Instructions - Ayres P/N 21757-1 Fuel Manifold Purge Assy-Kit" Dwg. No. 21757-1(1), Revision none, dated April 20, 1993, or later FAA approved revision.. Thrush Aircraft Inc.
- [STC SE2924SO](https://openairdocs.org/stc/SE2924SO): Installation of Garrett TPE-331-10 combustor and turbine in the TPE331-8 engine.. National Flight Lakeland
- [STC SE01461NY](https://openairdocs.org/stc/SE01461NY): Propeller pitch control system modification. Hartzell HC-E4N-5D/D9690(B) propeller installed per STC SA01462NY. Not approved on serial numbers TC-398 through TC-418.. Hartzell Propeller Inc
- [STC SE01604CH](https://openairdocs.org/stc/SE01604CH): Convert Honeywell TPE331-10AV-511B to a TPE331-10AV-511KA.. National Flight Services, Inc
- [STC SE00229AT](https://openairdocs.org/stc/SE00229AT): Installation of Garrett TPE331-10 Combustor and Turbine in TPE331-6 engine.. National Flight Services, Inc
- [STC SE00275AT](https://openairdocs.org/stc/SE00275AT): Installation of GarrettTPE331-10 combustor and turbine in the TPE331-5 engine.. National Flight Services, Inc
- [STC SE00691CH](https://openairdocs.org/stc/SE00691CH): Modification of a turboprop engine to a turboshaft configuration by incorporation of AlliedSignal (Garrett) TSE331-3U turboshaft gearbox components and other associated changes.. National Flight Services, Inc
- [STC SE8029SW](https://openairdocs.org/stc/SE8029SW): Modify propeller pitch control, P/N 869130, by installing pitch control cam, Garrett P/N869386-1.. Agri Jet Power, Inc
- [STC SE1725CE](https://openairdocs.org/stc/SE1725CE): Modification to replace torque pressure compensator with a plug for raw torque pressure indicating provision.. Air Midwest, Inc
- [STC SE68WE](https://openairdocs.org/stc/SE68WE): Deletion of fireshield installation kit.. West-Figueroa Trust
- [STC SE56WE](https://openairdocs.org/stc/SE56WE): Serial Numbers P-06012 AND P-06024: Installation of heated compressor inlet temperature sensor lines.. AiResearch Manufacturing 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.