TCDS E4WE

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----------------------------------