TCDS E18NE

DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION E18NE Revision 10 Honeywell Aerospace US LLC (AlliedSignal, Garrett) TPE331-14A TPE331-14B TPE331-14F TPE331-14GR TPE331-14HR TPE331-15AW March 27, 2026 TYPE CERTIFICATE DATA SHEET NO. E18NE Engine models described herein conforming with this data sheet (which is part of Type Certificate No. E18NE) and other approved data on file with the Federal Aviation Administration, meet 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: Honeywell Aerospace US LLC 111 South 34th Street Phoenix, AZ 85034 TYPE CERTIFICATE HOLDER RECORD: Honeywell International Inc. 111 South 34th Street Phoenix, AZ 85034 TYPE CERTIFICATE HOLDER RECORD: AlliedSignal Inc. 111 South 34th Street Phoenix, AZ 85034 TYPE CERTIFICATE HOLDER RECORD: Garrett Turbine Engine Co. 111 South 34th Street Phoenix, AZ 85034 Type Single-shaft engine with two-stage centrifugal compressor, three-stage axial turbine and singular annular combustion chamber. The letters "A", "F" and "G" indicate clockwise propeller rotation. The letters "B" and "H" indicate counterclockwise propeller rotation. The letter "R" indicates automatic power reserve capability. The letter "W" indicates water-methanol augmentation capability. Page No. 1 2 3 4 5 6 7 8 9 10 Revision No. 10 10 10 10 10 9 9 10 10 9 E18NE 2 of 10 RATING (See NOTES 3, 4, and 18) TPE331-14A TPE331-14B TPE331-14GR TPE331-14F TPE331-15AW TPE331-14HR Maximum Continuous SHP 1250 1645 1650 ESHP 1312 1712 1723 Output Shaft RPM 1540 1390 1552 Take off (5minutes) SHP 1250 1645 1650 ESHP 1312 1712 1723 Output Shaft RPM 1540 1390 1552 Automatic Power Reserve, (APR, 10 minutes) SHP NA* NA 1650 ESHP NA NA 1723 Output Shaft RPM NA NA 1552 ⃰ Not Applicable (NA) PRINCIPLE DIMENSIONS PF BASIC ENGINE Refer to the Installation Drawings for each specific engine model configuration for dimensions and center of gravity location. WEIGHT MODEL Weight, dry, lbs. TPE331-14A 581 TPE331-14B 592 TPE331-14F 620 TPE331-14GR 620 TPE331-14HR 633 TPE331-15AW 159 The engine weights shown herein are those of the engine assemblies. Not included are Engine Parts List, or Engine Equipment List items coded "A" together with their attaching hardware (See Note 12). PRINCIPLE OUTPUT SHAFT SPEED RATIO MODEL Propeller-shaft to engine rotor ratio TPE331-14A 1:22.6546 TPE331-14B 1:22.6794 TPE331-14F 1:22.6546 TPE331-14GR 1:22.9671 TPE331-14HR 1:22.9285 TPE331-15AW 1:25.1108 FUEL Engine operation is approved with the following aviation turbine fuels: Honeywell Aerospace US LLC EMS53111 (Type A) Honeywell Aerospace US LLC EMS53112 (Type A-1) Honeywell Aerospace US LLC EMS53112 (British D. Eng. R.D. 2494 Issue 7) Honeywell Aerospace US LLC EMS53113 Class A (British D. Eng. R.D. 2386 Issue 8) E18NE 3 of 10 Honeywell Aerospace US LLC EMS53113 (Type A, JP-4 and Class B-Type B) Honeywell Aerospace US LLC EMS53116 (Type JP-5) Other approved fuels are listed in the Installation Manual (IM)-3500 for -14A, -14B, IM-7364 for TPE331-14F, IM-6350 for TPE331-15AW and IM-7544 for TPE331-14GR, -14HR. Fuels not containing anti-icing inhibitors may have MIL-DTL-85470 Fuel System Icing Inhibitor, or an equivalent inhibitor, added, but not in excess of 0.15 percent by volume. Aviation gasoline MIL-G-5572D, Grade 80/87, not in excess of 1,000 gallons per 100 hours of operation, may be used for emergency fuel operation. Aviation gasoline MIL-G-5572D, Grade 100/130, not in excess of 250 gallons per 100 hours of operation, may be used for emergency fuel operation. Total usage must be limited to 7,000 gallons during any 3,000-hour period. If combinations of the above aviation gasolines are used, the following formula is required for establishing proportions of combinations during any 3,000-hour period: Amount of Grade 100/130 (low lead. gal.) + Amount of Grade 80/87 gal. < 1.0 7, 000 gal. 30,000 gal. If 25 percent or more of aviation gasoline is used at any time, one quart of aviation grade oil must be added to the mixture for 100 gallons of aviation gasoline. Shell ASA-3 anti-static additive, or equivalent, in amounts to bring the fuel up to 300 conductivity units may be used, but in no event shall the additive exceed 1 ppm. Biobor JF Biocide (Sohio or equivalent) 270 ppm maximum (20 ppm of elemental boron) may be used in the fuel for pesticide purposes. OIL Oils conform to Honeywell Aerospace US LLC Specification EMS 53110 (Type I and Type II). CERTIFICATION BASIS 14 CFR part 33 dated February 1, l965 and Amendment 1, 2, 3, 4, 5, 6, 7, 8 and 9 exemption No. 82-ANE-004-E dated December 23, 1982. Model Part 23 Certification Basis Date of Application Date of Issuance/Amended TPE331-14A *as stated above 10/5/1981 4/26/1984 TPE331-14B * 10/5/1981 4/56/1984 TPE331-15AW * 7/6/1984 12/5/1988 TPE331-14F * 5/3/1988 5/24/1989 TPE331-14GR * 7/26/1989 7/13/1992 TPE331-14HR * 7/26/1989 7/13/1992 PRODUCTION BASIS Production Certificate No. 413 issued March 4, 1965. Reissued Production Certificate No. 413NM to Honeywell Aerospace US LLC on March 29, 2026. E18NE 4 of 10 NOTE 1: MAXIMUM PERMISSIBLE TEMPERATURES Exhaust gas temperature, deg F (deg C) TPE331 Engine Model -14A, -14B The above APR, Takeoff and Maximum Continuous exhaust gas temperatures are for uninstalled U.S. Standard sea- level conditions. Exhaust gas temperature will vary as a function of ambient conditions, engine operating speed and installation effects. Consult Installation Manual IM-3500 for TPE331-14A, -14B, IM-7364 for TPE331-14F, IM-6350 for TPE331-15AW or IM-7544 for TPE331-14GR, -14HR for other than standard day sea-level limits. (See NOTE 13). TPE331-14A, -14B, -14F -15AW 14GR/HR Exhaust gas temperature during starting deg F (deg C) for 5 seconds 1429 (776) 1607 (875) See IM for more complete operating limits and actions if above temperature is exceeded Oil temperature, deg F (deg C) Condition Above Hot Oil SHP Limit Maximum Hot Oil SHP Limit Engine Model Oil Type Starting (Minimum) Ground Idle (Maximum) Above Ground Idle to Hot oil SHP Limit (Range for 5 minutes) All MIL-PRF-7808 -40 (-40) 200 (93) 175-200 (79-93) 175 (79) 1000 All MIL-PRF-7808 -40 (-40) 230 (110) 187-215 (86- 102) 187 (86) 1000 TPE331-14A MIL-PRF- 23699 -40 (-40) 260 (127 230-260 (110- 127) 230 (110) 1000 TPE331-14B " " " " " " TPE331-14F " " " " " " TPE331-14GR " " " " " 1500 TPE331-14HR " " " " " " TPE331-15AW " " 230 (110) 230 (110) Max N/A 1650 Ambient Air Temperature, deg F (deg C) Starting Operation Minimum -65 (-54) --- Maximum 131 (55) 131 (55) Maximum Continuous -14F, -15AW 1134 (612) -14GR, -14HR 1159 (626) See Notes 14 & 18A Takeoff (5 minutes) 1134 (612) 1122 (605) Automatic Power Reserve (APR) Not Applicable 1191 (644) (See Note 18B) E18NE 5 of 10 Engine External Components Surface Temperature Limits See Installation Manual IM-3500 for TPE331-14A, -14B, IM-7364 for TPE331-14F, IM-6350 for TPE331-15AW and IM-7544 for TPE331-14GR, -14HR NOTE 2: Pressure Limits TPE331 Engine Model Fuel pump inlet pressure -14A, -14B, -14F See IM -14GR, -14HR See IM -15AW See IM Oil pressure at inlet connection to the engine, minimum 5 psia 5 psia 5 psia Oil operating pressure at ground idle (Minimum at 65 percent speed) 15 psig 15 psig 15 psig Normal oil operating range (95 to 100 percent speed) 35 to 70 psig (130 to 230F 45 to 75 psig (122 to 230F 45 to 75 psig (130 to 230F oil temp.) oil temp.) oil temp.) Minimum water-methanol augmentation 7psig 7psig 7psig Manifold inlet pressure (TPE331-14GR, (See NOTE 17) (See NOTE 17) (See NOTE 17) OTE14HR, & -15AW). NOTE 3: The engine ratings are based on: Dynamometer operation at U.S. Standard Atmosphere, Sea-Level Static Conditions. Honeywell Aerospace EMS53111 aviation turbine fuel Type A with lower heating value of 18,400 BTU per pound. MIL- PRF-23699 Type II No bleed-air extraction No anti-icing airflow. No external accessory loads Zero inlet loss. Exhaust gas discharging to ambient-static pressure through the turbine exhaust diffuser furnished with the engine. NOTE 4: Equivalent horsepower (ESHP) for static conditions is based on: ESHP = Net thrust, pounds + SHP 2.5 E18NE 6 of 10 NOTE 5: ACCESSORY PROVISIONS TPE331 Engine Model Rotation (facing drive pad CCW RPM at 100% engine speed 4010 4014 4087 4080 Maximum torque (lb.-in) Tc, continuous torque 300 To, overload torque 375 Ts, static torque 1,650 Overhung moment (lb.-in) 100 Speed ratio, drive to engine rotor 0.11488 0.11488 0.11466 0.11466 (b) Starter, Starter-Generator All Models -14A -14B -14F -15AW -14GR -14HR Type of Drive: AS468 (one each) Type AV-1 Drive Modifications Rotations RPM Tc, To, Ts Rotation (facing Drive pad) CCW RPM at 100% engine speed 11,881 11,894 11,881, 11,885 12,115 12,095 Maximum torque (lb- in) Tc, continuous torque 132 To, overload torque 265 Ts , static torque 2,200 6,300⃰ 6,300⃰ 500 500 600 600 Overhung moment (lb.in) Speed ratio, drive to engine rotor 0.34054 0.34054 0.34054 0.34054 0.33989 0.33989 *Maximum overhung moment allowed at 1g when starter generator is restrained to engine casing. All -15AW (a) Aircraft Accessory Models -14A, -14F -14B -14GR -14HR Type of Drive: (one each) AS961-1CT X X AND 20001 Type XI-B X X Drive Modifications: Rotation, Ts, To, Stud pattern rotated 37 deg. Rotation Tc, Stud pattern rotated 37 deg. E18NE 7 of 10 NOTE 5. ACCESSORY PROVISIONS – CONTINUED TPE331 Engine Model All Models -14A, -14F, -15AW -14B -14GR -14HR (c) Propeller Governor AND20010 Type of Drive: (one each) Drive Modifications Rotation, RPM Stud length & negative torque system supply port Rotation (facing Drive pad) CCW RPM at 100% engine speed 3739 3743 3807 3801 Maximum torque (lb.-in) Tc, continuous torque 125 To, overload torque 188 Ts, static torque 825 Overhung moment (lb.-in) 125 Speed ratio, Drive to engine rotor 0.10714 (d) Propeller Pitch Control Type of Drive: (one each) Mounting pad provides overhung overhung moment of 30 in-lb. (e) Auxiliary Aircraft Accessory TPE331-15AW TPE331-14F Type of Drive: (one each) AND20002 AND20002 Type XII D Type XII D Modified Modified Drive modifications: Rotation, RPM Rotation, RPM Tc, To, Ts & Tc, To, Ts & Stud pattern rotated 30 deg. Stud pattern rotated 30 deg. Rotation (facing drive pad) RPM at 100% engine speed CCW 12,254 CCW 12,511 Maximum torque (lb.-in) Tc, continuous torque 309 300 To, overload torque 463 463 Ts, static torque 1700 1700 Overhung moment (lb.-in) 500 500 Speed ratio, Drive to engine rotor 0.35107 0.35844 E18NE 8 of 10 NOTE 6: Maximum allowable propeller shaft torque as sensed by the torque sensor, in pound -feet: TPE331-14A, -14B, -14F TPE331-15AW TPE331-14GR, -14HR 5-minute torque limit: 4262 6234 5584 Maximum continuous torque limit: 4262 6234 5584 See IM for transient engines over torque limits. NOTE 7: Propeller Output Shaft (Bolted Flange) Maximum Speed Percent (RPM): TPE331-14A, 14B, 14F TPE331-15AW TPE331-14GR, -14HR Normal operation 100.0(1540) 100.0(1390) 100.0(1552) Continuous operation 101.0(1555) 101.0(1404) 101.0(1568) Transient limit 104.0(1602) 104.0(1446) 104.0(1614) NOTE 8: Propeller Output Shaft, (Bolted Flange) Direction of Rotation: TPE331-14A, -14B, -14F TPE331-14GR, -14HR Rotation when looking forward to turbine exhaust flange CW CCW NOTE 9: High Pressure (HP) Compressor discharge bleed air - Up to 12 percent of the engine airflow is available for bleed air purposes (except during starting). Of this 12 percent total, 1.0 percent is used by the engine mounted anti-icing system. NOTE 10: Low Pressure (LP) Compressor interstage bleed air - Up to 10 percent of the engine airflow is available as option except total of HP and LP bleed not to exceed quantity allowed for HP bleed. These engines meet FAA requirements for adequate turbine disk integrity and rotor blade containment and do not require external armoring. NOTE 11: These engines meet FAA requirements for operation in icing conditions within the envelope defined in Part 25, Appendix C NOTE 12: Variations in engine configuration and installation components are identified by a suffix to the basic model number on the engine nameplate; i.e. TPE331-14A-XY (“X” denotes Honeywell Aerospace installed configurations rating code number(s) and “Y” denotes Honeywell Aerospace equipment code letter(s) of aircraft manufacturer), and an Engine Parts List or Equipment List number. Certain features of these components are influenced by aircraft design considerations. In the Engine Parts List or Equipment List, those items coded "A" have been demonstrated as compatible with the basic engine during engine certification testing; however, the operation, functioning and rigging of these in a specific aircraft installation must be demonstrated during certification. Subsequent design change to the engine associated with these factors is the responsibility of the aircraft manufacturer and must be in compliance with Part 33. E18NE 9 of 10 NOTE 13: The TPE331-14A, -14B, -14F, -14GR, -14HR and -15AW engine have been designed to accommodate a “Variable Red Line/Auto-Start" (VRL) temperature indicating system and an automatic "Torque and Gas Temperature Limiting" system. The temperature limiting system for these engines will vary with the operating condition to produce rated shaft power without exceeding the maximum rated temperature (see Note 3). With the VRL inoperative, the EGT limit the TPE331-14A, -14B, -14F, -14GR, -14HR, and -15AW engines will vary as a function of ambient conditions. Consult IM for off-standard day EGT limits. Component interface and installation requirements of the aircraft-installed components are also described in IM-3500 for TPE331-14A, -14B model engines, IM-7364 for TPE331-14F engine model, IM-6350 for TPE331-15AW model engine and IM-7544 for TPE331-14GR, -14HR model engines. NOTE 14: Certain engine parts are life limited. These are listed in FAA approved Honeywell International Inc. Honeywell Aerospace US LLC Service Bulletins as follows: NOTE 15: Transient operation of propeller output shaft speed above 104 percent to a maximum of 106.0 percent is allowable for fuel control overspeed governor test when the propeller is on the start locks. Refer to engine maintenance manual for proper procedures and limitations for this test. NOTE 16: The power management system incorporates a limited authority IEC (Integrated Engine Computer) that limits engine maximum torque and maximum exhaust gas temperature. This device incorporates digital circuitry. The software programming procedures have been determined to meet the "critical" category under the guidelines of RTCA document DO 178. NOTE 17: Augmented performance for the TPE331-14GR, -14HR and TPE331-15AW models may be obtained by the addition of a water-methanol injection system. Water-methanol mixture must conform to that shown in FAA approved installation manual IM-6350 for the TPE331-15AW and IM-7544 for the TPE331- 14GR, -14HR. The torque limit remains as shown in NOTE 6. Exhaust gas temperature limit remains as per NOTE 1, except that for IEC-inoperative mode, EGT limits per the appropriate IM must be used. TPE331-14GR, -14HR TPE331-15AW SHP at sea level, static, ambient temperature limit 1650 1645 Sea level, static, ambient temperature limit, deg F (deg C) 131(55) 100(38) Minimum Water/Methanol flow rate, lb./hr 1680 1680 Maximum Water/Methanol flow rate, lb./hr 1850 1850 Engine Models Honeywell Aerospace Service Bulletins TPE331-14A, -14B TPE331-72-7002 dated February 27, 1995, or later FAA approved revisions TPE331-14F TPE331-72-7050 dated June 17, 1994, or later FAA approved revisions TPE331-14GR, -14HR TPE331-72-7082 dated April 2, 1999, or later FAA approved revisions TPE331-15AW TPE331-72-7502 dated May 17, 1994, or later FAA approved revisions E18NE 10 of 10 NOTE 18: (a) T he Continuous Power Reserve (CPR) mode of the IEC provides engine operation with EGT between 1 105oF and 1159oF, inclusive, and meets Part 33 requirements. The CPR mode is available only with the IEC operational (refer to Installation Manual IM-7544). The torque limit remains as shown in Note 6. Engine operation above 1104oF EGT requires applying engine hour and cycle maintenance factors in accordance with Engine Maintenance Manuals 72-04-05 and 72-04-07, and Service Bulletins TPE 331-72-7081 dated December 22, 1995, and TPE331-72-7082 dated December 22, 1995. The use of CPR mode in an aircraft installation must be certified per Part 23 or 25 requirements (refer to Note 12 - items coded "A"). (b) The Automatic Power Reserve (APR) feature of the IEC is a 10-minute emergency power rating which automatically increases engine power and the VRL temperature in the event of power loss in another engine. The torque limit remains as shown in NOTE 6. - --------------------------END--------------------------