# TCDS E4NE: Honeywell Aerospace US LLC - Type: Type certificate data sheet - Status: Current - Holder: Honeywell Aerospace US LLC - Revision: 7 - Revised: March 27, 2026 - Product: Engine - Certification basis: Part 33 - Registered aircraft: 18, by the registry models matched to it (OpenAirDocs) - Data sheet PDF: https://openairdocs.org/files/sha256/e7/8a/e78a3c3fe95f8d216eff356982b75b32370fc3a3678e4953559146663532ca9d - FAA DRS: https://drs.faa.gov/browse/excelExternalWindow/DRSDOCID132185258120260605175148.0001 - Page: https://openairdocs.org/tcds/E4NE ## Models (2) As the data sheet lists them. - T5508D - AL5512 ## What the data sheet says From the PDF's text layer, line by line; tables lose their columns. The PDF is the record. ```text E4NW 1 of 7 DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION E4NE Revision 7 H oneywell Aerospace US LLC (AlliedSignal,Textron Lycoming) T 5508D AL5512 March 27, 2026 TY PE CERTIFICATE DATA SHEET NO. E4NE E ngines of the models described herein conforming with this data sheet (which is a part of Type Certificate No. E4NE) and other approved data on file with the Federal Aviation Administration meet the minimum standards for use in certificated aircraft in accordance with pertinent aircraft data sheets and applicable portions of the Federal Aviation Regulations provided they are installed, operated, and maintained as prescribed by the approved manufacturer's manuals and other approved instructions. TY PE CERTIFICATE HOLDER: Honeywell Aerospace US LLC 111 South 34th Street Phoenix, AZ 85034 TY PE CERTIFICATE HOLDER RECORD: Honeywell International Inc. 111 South 34th Street Phoenix, AZ 85034 T YPE CERTIFICATE HOLDER RECORD: AlliedSignal Inc. 111 South 34th Street Phoenix, AZ 85034 T YPE CERTIFICATE HOLDER RECORD: Textron Lycoming. 111 South 34th Street Phoenix, AZ 85034 Page No. 1 2 3 4 5 6 7 Revision No. 7 7 7 6 6 6 7 E4NW 2 of 7 Model T5508D AL5512 Type Axial-centrifugal flow free turbine turboshaft. Seven stage axial and single stage centrifugal compressor. Reverse flow annular atomizing combustor. Single stage gas generator turbine. Two stage power turbines. Axial-centrifugal flow free turbine turboshaft. Seven stage axial and single stage centrifugal compressor. Reverse flow annular atomizing combustor. Two stage gas generator turbines. Two stage power turbines. Ratings (See NOTE 1) Maximum continuous at sea level, hp. 2250 2975 Takeoff (5 minutes) at sea level, hp. 2250 4075 30-minute power rating (one engine inoperative) ---- 4355 Rated output shaft speed, r.p.m 14750 16000 Fuel Control Hamilton Standard Model JFC 31-20 with integral single element pump Hamilton Standard Model JFC 31-14 with integral single element pump Fuel (See NOTE 2) MIL-DTL-5624, Grade I (JP-4), ASTMD1655 Jet A, Jet A-1, Jet B MIL-5624, Grade II (JP-5), or commercial equivalents specified in T5508D-1 “Operator’s Handbook” MIL-DTL-5624, Grade JP-4, JP-5, DERD2494 Oil (See NOTE 3) MIL-PRF-7808, MIL-PRF-23699, or commercial equivalents specified in T5508D-1 “Operator’s Handbook” MIL-PRF-7808 MIL-PRF-23699 Principal dimensions Length, in. nominal 45.457 46.527 Diameter, in. nominal 25.057 28.995 Weight (dry), lb. maximum (Includes essential engine accessories but excludes starter-generator, two tachometer-generators, and torque signal conditioner unit) 618 780 C.G. location (dry weight) Aft of main mount (forward) pads centerline, in. 17200 19.70 Below engine horizontal centerline, in. 0.62 0.65 Ignition system (28 volts D.C.) Ignition exciter unit, Bendix Corp. P/N 10-383225-1 or Simmonds Precision P/N 43326, with separate spark splitter lead and coil assembly and four shunted surface gap spark plug ignitors. -- Ignitor plugs Bendix Corp. P/N 390010-1 or Champion P/N FHE200-7. -- NOTES "- -" Indicates "same as preceding model" "¾" Indicates "does not apply" E4NW 3 of 7 Certification Basis Regulations and Amendments Model Application Date Type Certificate Issued/Amended 14 C FR part 33 effective February 1, 1965, as amended by 33-1, 33-2, 33-3, and 33-4 T5508D October 6, 1972 September 16, 1975 14 CFR part 33 effective February 1, 1965, as amended by 33-1, 33-2, 33-3, 33-4, and Special Condition 33-66-NE- 1 AL5512 October 30, 1975 November 7, 1980 P roduction Basis: N OTE 1: N OTE 2 N OTE 3. NOTE 4. Production Certificate No. 413NM issued to Honeywell Aerospace US LLC on March 29, 2026. Engine ratings are based on calibrated stand performance at sea level static conditions of 15°C and 29.92 Hg under the following conditions: T5508D No airbleed, no duct losses, no external power extraction. Exhaust configuration as specified by Honeywell Aerospace US LLC drawings EXP5248 and 2-010-040-02. Use of fuels conforming to and having any of the variations in characteristics permitted by MIL-DTL-5624, JP-4. AL5512 No airbleed other than 3% provided for customer bleed, no duct losses, no external power extraction. Use of an exhaust nozzle, as specified on Honeywell Aerospace US LLC drawing EXP6457, having an area of 460 square inches. Use of fuel conforming to the fuel specification given in the engine installation instructions. The maximum continuous rating increases nonlinearly from 2975 shaft horsepower at 59°F to 3292 shaft horsepower at +40°F. The output is flat rated below +40°F. The takeoff rating increases nonlinearly from 4075 shaft horsepower at 59°F to 4115 shaft horsepower at +56°F. The output is flat rated below +56°F. The 30-minute power rating (one engine inoperative) increase nonlinearly from 4355 shaft horsepower at 59°F to 4527 shaft horsepower at +46°F. The output is flat rated below +46°F. The relationship between output shaft horsepower and ambient temperature for the engine ratings is shown in figure 2 of the Installation Instructions, Honeywell Aerospace US LLC Document 124.60. The T5508D engine will operate satisfactorily with fuel contaminated to levels specified in MIL-E-5007C. The AL5512 engine will operate satisfactorily with fuel contaminated to the level as specified in the installation instruction. Mixing of these oils is prohibited. Maximum power turbine speeds (rpm) are: E4NW 4 of 7 T5508D AL5512 30 minute power rating (one engine inoperative) - 16,000 Takeoff 14,750 16,000 Maximum continuous 1 4,750 16,000 Transient (12 sec.) 14,751 to 16,250 16,001 to 16,400 NOTE 5. Power turbine output shaft torque limits (lb-ft): T5508D AL5512 30 minute power rating (one engine inoperative) - 1,650 Takeoff 1,050 1,500 Maximum continuous 920 1,200 Transient 1,050 1,950 NOTE 6. Maximum permissible gas producer speeds (rpm) are: T5508D AL5512 30 minute power rating (one engine inoperative) - 19,770 Takeoff 18,832 19,500 Maximum continuous 18,327 18,770 Transient 18,833 to 19,770 19,770 NOTE 7. Maximum permissible temperatures are: Measured gas temperature (°F) T5508D AL5512 Starting maximum 1,500 1,670 Starting transient 1,385-1,500 for 5 seconds  1,331-1,384 for 30 seconds 30 minute power rating (one engine inoperative)  1,670 Takeoff (5 minutes) 1,330 @ 130 ambient 1,598 Maximum continuous 1,278 @ 130 ambient 1,391 Maximum permissible gas  temperature varies with ambient temperatures as shown in figure 11 of Installation Instructions. Exhaust gas temperature is measured by three thermocouples located in the exhaust diffuser of the engine. Measured gas temperature is determined by ten thermocouples located in the combustor housing. Engine oil maximum temperature is 295°F. Engine oil maximum temperature is 309°F. E4NW 5 of 7 T5508D Engine accessories and zone temperature limits are as shown in paragraph 4.3 of Installation Instructions. AL551 2 Engine accessories and zone temperature limits are as shown in paragraph 4.7 of Installation Instructions. Transient (30 seconds)  1724°F NOT E 8. Fuel and oil pressure limits: T5508D AL5512 Fuel: 15 psia to 50 psia 5 psia to 50 psia Oil: 50 psig to 100 psig 17 psig to 90 psig 30 psig minimum, idle NO TE 9: Accessory Drive Provisions: T5508D Accessory Drive Gas Producer Section Spec Type Number Required Gear Ratio Maximum P (1) Continuous Permissible Torque (2) Short Time e lb-in. (3) Static Rotation Starter Generator AND20002 X11-D Modified (4) 1 0.4146 140 210 *1340 CW Tachometer Power Section AND20005 XV-B (7) 1 0.2244 7 --- 50 CW Tachometer AND20005 XV-B Modified (6) 1 0.2739 7 --- 50 CW E4NW 6 of 7 AL5512 Accessory Drive Spec Type Numbe r Requir ed Gear Ratio Maximum Permissible Torque lb-in. (1) (2) (3) Continuous Short Time Static Rotation Starter Generator (9) AND20002 X11-D Modified 1 0.4146 900(8) ----- ------ CW Tachometer AND20005 XV-B Modified 1 0.2244 7 50 CW (1) Maximum permissible continuous torque at any engine speed. (2) Maximum permissible continuous torque for 5-minute periods reoccurring at not less than 4-hour intervals. (3) Maximum static torque for any single pad. Remainder of the pads to be unloaded. (4) This pad deviates from the AND20002 X11-D in the following values: Speed - 6935 r.p.m. at maximum rated speed for 75% maximum continuous rated sea level static power. Torque - As listed above except that the continuous torque limit of 140 lb.-in. is a generator limit only. The maximum continuous torque during starting is 900 lb.-in. Overhung Moment - 260 lb.-in. maximum permissible static. (5) Maximum permissible torque during starting is 1340 lb.-in. (6) This pad deviates from the AND20005 XV-B in the following value: Speed - 4040 r.p.m. at maximum rated engine speed. (7) This pad deviates from the AND20005 XV-B in the following value: Speed - 4130 r.p.m. at maximum rated engine speed. (8) Maximum peak torque during starting is 1340 in.-lb. (9) The maximum overhung permissible moment is 225 in.-lb. *May be exceeded up to 2004 lb.-in. for 5 times before mandatory replacement of the accessory drive train. NOTE: 100% (gas generator speed) r.p.m. 18,720 100% (power turbine speed) r.p.m. 15, 333 100% (tachometer drive pad speed) r.p.m. 4, 200 NO TE 10: The T5508D engine is starting to torque and speed requirements are as shown in figure 10 of Installation Instructions. Figure 10.1 shows the required engine staring times. The AL5512 engine starting to torque and speed requirements are shown in figure 7 of Installation Instructions. NO TE 11: The 5508D allowable pad and flange loads are presented in Figure 6 of the Installation Instructions and on Installation Drawing 2-000-001-45. The AL5512 allowable pad and flange loads are presented in Table III of the Installation Instructions and on Installation Drawing 2-000-001-48. NO TE 12: Maximum permissible compressor airbleed is 3% of inlet airflow. The T5508D bleed port is shown on Installation Drawing 2-000-001-45. The AL5512 bleed port is shown on Installation Drawing 2-000-001-48. NO TE 13: These engines meet FAA requirements for operation in icing conditions provided: T5508 D 1) A minimum of 500 shaft horsepower is maintained with customer bleed on. 2) A minimum of 12,600 r.p.m. gas producer speed is maintained with customers bleed off. AL551 2 1) A minimum of 13,100 r.p.m. (70%) gas producer speed is maintained with customers airbleed on. E4NW 7 of 7 NOTE 14: These engines meet FAA requirements for adequate turbine disk integrity and rotor blade containment and do not require airframe mounted armor. An airframe furnished overspeed test switch is required to test the overspeed system. NO TE 15: These engines have not been tested to evaluate the effect of bird, ice ball, or foreign objects. Inlet protection against bird, ice ball, or foreign object damage must be provided by the aircraft installation. NO TE 16: These engines may use JP-4 and JP-5 kerosene-type fuels separately or mixed in any proportion. Fuel control adjustments are not required when switching fuel types.* NO TE 17: Certain engine parts are life limited. The T5508D limits are listed in FAA-Approved Service Bulletin No. 5508D-0002. The AL5512 limits are listed in FAA-Approved Service Bulletin No. 5512-0002. NO TE 18: Deleted (Revision 6). NO TE 19: The T5508D overhaul interval and hot end inspection intervals are specified in FAA-Approved Service Bulletin No. 5508D-0001. The AL5512 overhaul interval and hot end inspection intervals are specified in FAA-Approved Service Bulletin No. 5512-0001. *Ant i-icing additive (MIL-DTL-85470) or any direct equivalent) at concentrations not exceeding 0.15% by volume is required for the AL5512 at ambient temperatures of -10°F or below. -------------- -------------END-------------------------- ``` ## ADs (4, in force first) - [AD 94-02-01](https://openairdocs.org/ad/94-02-01): Impeller · Honeywell International T5508D. Effective Feb 4, 1994 - [AD 86-19-13](https://openairdocs.org/ad/86-19-13): First Stage Turbine Disk · Honeywell International T5508D. Effective Oct 6, 1986 - [AD 78-07-04](https://openairdocs.org/ad/78-07-04): Inner Bevel Gear Assembly · Honeywell International T5508D. Effective Mar 30, 1978 - [AD 76-12-05](https://openairdocs.org/ad/76-12-05): Compressor Air Bleed Band · Honeywell International T5508D. Effective Jun 23, 1976 ## Registered aircraft by registry model (OpenAirDocs) - [Lycoming T5508D](https://openairdocs.org/engine/lycoming-t5508d): 6 aircraft (registry code 41609) - [Honeywell AL5512](https://openairdocs.org/engine/honeywell-al5512): 5 aircraft (registry code 33903) - [Lycoming AL5512](https://openairdocs.org/engine/lycoming-al5512): 4 aircraft (registry code 41581) - [Honeywell T5508D](https://openairdocs.org/engine/honeywell-t5508d): 3 aircraft (registry code 33959) - [Alliedsign AL5512](https://openairdocs.org/engine/alliedsign-al5512): 0 aircraft (registry code 02557) - [Alliedsign T5508D](https://openairdocs.org/engine/alliedsign-t5508d): 0 aircraft (registry code 02556) --- 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.