# TCDS E43NE: PRATT & WHITNEY RZESZOW S.A. - Type: Type certificate data sheet - Status: Current - Holder: PRATT & WHITNEY RZESZOW S.A. - Revision: 3 - Revised: April 27, 2017 - Product: Engine - Certification basis: Part 33 - Data sheet PDF: https://openairdocs.org/files/sha256/e5/b4/e5b4fd5ff5ff52c1d086dffb08bc680e2b542284844f1f5ec856dd1fd3759b28 - FAA DRS: https://drs.faa.gov/browse/excelExternalWindow/6039D6282BF5EB8A862581130065C1D2.0001 - Page: https://openairdocs.org/tcds/E43NE ## Models (1) As the data sheet lists them. - PZL-10W ## What the data sheet says From the PDF's text layer, line by line; tables lose their columns. The PDF is the record. ```text * PAGE 1 2 3 4 5 REV. 3 1 3 3 2 LEGEND: "- -" INDICATES "SAME AS PRECEDING MODEL" "---" NOT APPLICABLE NOTICE: ALL PAGES ARE REFORMATTED. SIGNIFICANT CHANGES, IF ANY, ARE BLACK-LINED IN THE LEFT MARGIN. U.S. DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION TYPE CERTIFICATE DATA SHEET E43NE TCDS NUMBER E43NE REVISION: 3* DATE: April 27, 2017 PRATT & WHITNEY RZESZOW S.A. MODELS: PZL-10W Engines of models described herein conforming with this data sheet (which is part of Type Certificate Number E43NE) 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. TYPE CERTIFICATE (TC) HOLDER: PRATT & WHITNEY RZESZOW S.A. ul. Hetmanska 120 35-078 Rzeszow, Poland TYPE CERTIFICATE HOLDER RECORD: WYTWORNIA SPRZETU KOMUNIKACYJNEGO (WSK) “PZL-RZESZOW” – SPOLKA AKCYJNA (SA) transferred TC E43NE to PRATT & WHITNEY RZESZOW S.A. on August 12, 2015 I. MODELS PZL-10W TYPE Twin spool (free turbine) turboshaft engine with a six stage axial compressor, single stage centrifugal compressor, annular combustion chamber with centrifugal fuel nozzles, two stage axial turbine for gas generator, single stage axial free power turbine, and direct drive output for the PZL W-3 Sokol multi-engine helicopter application. RATINGS (NOTE 1, 2, 3) Shaft horsepower (hp) Maximum continuous Takeoff (5 min.) 30 min. OEI Takeoff (2.5 min. OEI) 780 900 1,000 1,150 NOTE: OEI = one engine inoperative FUEL TYPE Refer to section 2 of approved installation manual or section 3 of approved overhaul manual. OIL TYPE Refer to section 2 of approved installation manual or section 3 of approved overhaul manual. ENGINE CONTROL SYSTEM Fuel Metering Pump: HS Wroclaw (formerly KTEHS "PZL-Hydral" Wroclaw) ALRP- 5 Power Turbine Speed Govenor: HS Wroclaw (formerly KTEHS "PZL-Hydral" Wroclaw) ALRT-2A or ALRT-2B Air Bleed Control Valve: HS Wroclaw (formerly KTEHS "PZL-Hydral" Wroclaw) ALUP-1 Electronic Limiter Unit: HS Wroclaw (formerly KTEHS "PZL-Hydral" Wroclaw) ALAE-2 IGNITION SYSTEM Ignitor KNV-22 (KHB-22) Ignition Plug SE-23 (C∋-23) TCDS E43NE PAGE 2 I. MODELS (cont.) PZL-10W PRINCIPAL DIMENSIONS (in) LENGTH: WIDTH (left variant): WIDTH (right variant): HEIGHT (maximum envelope): 73.819+0.394 29.134+0.394 30.118+0.394 23.425+0.394 WEIGHT (lb) Dry 310.62+6.21 NOTE: Dry weight includes only the equipment needed to run the engine without residual fluid. CENTER OF GRAVITY (in) From mount in aft direction From engine axis in left direction (left variant) From engine axis in left direction (right variant) 2.441+0.080 0.197+0.040 0.040+0.040 MAXIMUM PREMISSIBLE ENGINE OPERATING SPEEDS (RPM) Gas generator Takeoff (2.5 min OEI) 30 min. OEI Takeoff (5 min.) Maximum continuous Transient Free Turbine Nominal speed Transient (15 sec. max.) 32,100 30,900 30,550 29,330 32,100 23,615 25,190 NOTE: 100% gas generator speed = 31,486 RPM 100% free turbine speed = 22,490 RPM MAXIMUM PERMISSIBLE TEMPERATURES (øC/øF) Gas generator turbine exhaust (T4) Takeoff (2.5 min. OEI) 30 min. OEI Takeoff (5 min.) Maximum continuous Starting 770/1418 735/1355 725/1337 670/1238 680/1256 ENGINE OIL TEMPERATURE/PRESSURE LIMITS AND QUANTITY ENGINE FUEL TEMPERATURE/PRESSURE LIMITS Refer to section 2 of Installation Manual Refer to section 2 of Installation Manual AMBIENT TEMPERATURE RANGE (øC/øF) During flight (up to 6,000m/19,685 ft) Ground starting (up to 4,000 m/13,123 ft) -50/-58 to 50/122 -30/-22 to 50/122 TCDS E43NE PAGE 3 I. MODELS (cont.) PZL-10W NOTE: If ambient temperature drops below minimum during ground starting, the engine should be warmed-up in accordance with Operating Instructions. MAXIMUM PERMISSIBLE AIR BLEEDS (kg/sec/lb/sec) (NOTE 4) For cabin ventilation For inlet dust separator Total for aicraft use ROTOR DIRECTION OF ROTATION Gas Generator Rotor Free Turbine Rotor 0.07/0.154 0.04/0.088 0.11/0.243 CCW CW NOTE: CW = Clockwise, CCW = Counter-clockwise ACCESSORY DRIVE PROVISIONS Refer to Installation Manual CERTIFICATION BASIS FAR Part 33, effective February 1, 1965, as amended by 33-1 to 33-13, inclusive. Type Certificate E43NE issued/revised DATE OF DATE TC ISSUED MODEL APPLICATION OR REVISED PZL-10W 05/27/91 05/28/93 Reissued to WSK "PZL-RZESZOW" SA 12/21/94 Reissued to PRATT & WHITNEY RZESZOW S.A. 8/22/2016 The General Inspectorate of Civil Aviation of Poland originally type certificated this engine. The FAA validated this product under U.S. Type Certificate Number E43NE. Effective September 28, 2003, the European Aviation Safety Agency (EASA) began oversight of this product on behalf of Poland. IMPORT REQUIREMENTS To be considered eligible for installation on U.S. registered aircraft, each new engine to be exported to the United States with the General Inspectorate of Civil Aviation of Poland or EASA airworthiness approval shall have a Joint Aviation Authorities (JAA) or EASA Form 1, Authorized Release Certificate. The JAA or EASA Form 1 should state that the engine conforms to the type design approved under the U.S. Type Certificate E43NE, is in a condition for safe operation and has undergone a final operational check. Additional guidance is contained in FAA Advisory Circular 21-23, Airworthiness Certification of Civil Aircraft, Engine, Propellers, and Related Products, imported into the United States. NOTES NOTE 1. The engine ratings are based on dry sea level static ICAO standard atmospheric conditions. No power extraction for helicopter accessories, no airbleed for inlet particle dust separator, and no airbleed for aircraft use and engine icing protection system. NOTE 2. The takeoff (2.5 min. OEI) rating is maintained up to 1,000 m/3,280 ft altitude ISAO + 15øC/59øF when the inlet particle dust separator is inoperative. The 30 min. OEI rating is maintained up to 1,000 m/3,280 ft altitude ISAO, and up to 330 m/1,082 ft ISAO altitude + 15øC/59øF when the inlet particle dust separator is inoperative. NOTE 3. The takeoff (5 min.) and maximum continuous ratings at sea level are maintained for an ambient temperature range of -50øC/-58øF to 30øC/86øF at a minimum sea level atmospheric pressure of 97.3 KPa/14.11 psi, and from sea level to 2,000 m/6,561 ft ISAO altitude conditions. TCDS E43NE PAGE 4 NOTE 4. Continuous air bleed for cabin ventilation is permissible for ratings from idle to maximum continuous at an ambient air temperature not exceeding 45øC/113øF, and for the takeoff (5 min.) rating at an ambient air temperature not exceeding 15øC/59øF. Air bleed for inlet particle dust separator is permissible for ratings from idle to takeoff (5 min.) at an ambient air temperature not exceeding 45øC/113øF. NOTE 5. The engine must be operated with the approved (or equivalent) inlet particle dust separator (Part Number 30.68.120.00.10/20). NOTE 6. The engine operating time between overhauls is in accordance with Maintenance Manual 19.0.400, Chapter 72-02-00. NOTE 7. Life limits for critical rotating components are published in WSK "PZL-Rzeszow" S.A. Maintenance Manual No. 19.0.400. NOTE 8. The PZL-10W engine meets the requirements of FAR 33.65 for surge free operation, when the intake system conforms with the approved inlet particle dust separator (Part Number 30.68.120.00.10/20). NOTE 9. The PZL-10W engine meets the requirements of FAR 33.68 for operation in icing conditions as defined in FAR 25, Appendix C, when the intake system conforms with the approved inlet particle dust separator (Part Number 30.68.120.00.10/20). NOTE 10. The PZL-10W engine meets the requirements of FAR 33.77 for bird ingestion requirements when the intake system conforms with the approved inlet particle dust separator (Part Number 30.68.120.00.10/20). NOTE 11. The engine is not equipped with its own oil tank and related installation hardware. Aircraft installations equipped with this engine model must include an oil tank that meets the requirements of FAR 29 and/or FAR 33. NOTE 12. Overhaul Manual (Instruction for Main Repair) is 19.1.201. NOTE 13. The ALAE-2 electronic limiter meets the high intensity radiated field requirements as outlined in RTCA/DO-160B. A peak electric field strength of 1 volt/meter (category z). For installation requirements, refer to Installation Manual. NOTE 14. The ALAE-2 electronic limiter and UPM-100 torque meter conforms to the requirements of RTCA/DO-160C Category L. For installation requirements, refer to Installation Manual. TCDS E43NE PAGE 5 NOTE 15. SERVICE INFORMATION: Each of the documents listed below must state that it is approved by the European Aviation Safety Agency (EASA) or, for approvals made before September 28, 2003 by the General Inspectorate of Civil Aviation of Poland. Any such documents including those approved under a delegated authority, are accepted by the FAA and are considered FAA approved. • Service bulletins, • Structural repair manuals, • Vendor manuals, • Aircraft flight manuals, and • Overhaul and maintenance manuals. These approvals pertain to the type design only. ----END---- ``` ## ADs (3, in force first) - [AD 2011-18-07](https://openairdocs.org/ad/2011-18-07): Fuel metering pump shaft · Wytwornia Sprzetu Komunikacyjnego PZL-10W. Effective Oct 4, 2011 - [AD 2009-04-01](https://openairdocs.org/ad/2009-04-01): Fuel metering pump units · Wytwornia Sprzetu Komunikacyjnego PZL-10W. Effective Mar 24, 2009 - [AD 2003-18-04](https://openairdocs.org/ad/2003-18-04): Four engine-to-gearbox pin · Wytwornia Sprzetu Komunikacyjnego PZL-10W. Effective Sep 23, 2003 --- 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.