TCDS H15EU

DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION TYPE CERTIFICATE DATA SHEET No. H15EU This data sheet which is part of Type Certificate No. H15EU prescribes conditions and limitation under which the product for which the type certificate was issued meets the airworthiness requirements of the Federal Aviation Regulations. Type Certificate Holder. PZL Swidnik S.A. 21-045 Swidnik Poland I. Model "PZL W-3A" (Transport Helicopter - Category A and Category B), approved May 31, 1993 Engines. Number of engines 2 Engine type PZL-10W Engine category Turboshaft Manufacturer Normal Operation Pratt&Whitney Rzeszow (formerly PZL Rzeszow) Engine Operating Limits. Engine Takeoff Maximum rating (5 minutes) Continuous Torque Max 109% 85% Power tur- Max 105% 105% bine speed Min 100% 105% Gas generator speed Max 97% 93% Gas temperature Max 725ºC 670ºC One Engine Inoperative Engine 2 1/2-minute 30-minute rating limit limit Torque Max 139% 121% Power tur- Max 105% 105% bine speed Min 95% 95% Gas generator speed Max 102% 98% Gas temperature Max 770ºC 735ºC Note: 100% power turbine speed corresponds to 22490 rpm 100% gas generator speed corresponds to 31486 rpm Page No. 1 2 3 4 5 6 Rev. No. 6 1 1 4 6 4 H15EU Revision 6 PZL W-3A November 13, 2025 2 H15EU 8 7 6 5 4 3 2 1 0 Rotor Speed Limitation. Power-Off Power-On Max. transient 112% 112% (15 sec) Maximum 108% 105% Minimum 90% 100% (twin engine operation) 95% (single engine operation) Min. transient 85% 95% (twin engine operation) 85% (single engine operation) Note: 100% rotor speed corresponds to 255.7 rpm C.G. Limitation. C.G. location is determined in X-Y-Z coordinates having the origin in a piercing point of rotor axis on rotor plane of rotation. The X axis is sensed forward and is defined as an intersection of the rotor plane of rotation on the helicopter plane of symmetry. The Y axis is sensed upward and aligns with rotor axis. The Z axis is sensed to the right as viewed from rear. Longitudinal C.G. Limits. 7.3 in (185 mm) fore -1.97 in (-50 mm) aft. Straight line variation between points given - see figures: CENTER OF GRAVITY LIMITS 6.3 0.4 1 10 6400 6100 6000 5000 4600 4000 3850 7.3 LONGITUDINAL C.G. - IN. -1.97 180 160 140 120 100 80 60 40 20 0 -20 -40 185 LONGITUDINAL C.G. -mm -50 Lateral C.G. Limits. (as measured from the rotorcraft centerline): ± 4.7 in (± 120 mm) for airspeeds up to 48 KIAS (90 km/h) ± 3.5 in (± 90 mm) for airspeed above 48 KIAS Empty Weight C.G. Limits. (-3.35 ± 0.4 in) (-85 ± 10 mm) Leveling Means. A plumb line from the ceiling at No 12 frame. GROSS WEIGHT - LB. GROSS WEIGHT -kg 3 H15EU Airspeed Limits. Power-on maximum airspeed is 140 KIAS. H (ft) 20000 16000 12000 8000 4000 80 90 100 110 120 130 140 VNE Knots CAS Note: See VNE placards for variation of VNE with weight, temperature and altitude (installed in the cockpit). Weight Limitations. For Category A and B: - Maximum: - Minimum: 14,100 lb (6400 kgs) 8,488 lb (3850 kgs) Altitude Limitations. - Maximum operating pressure altitude: - Maximum pressure altitude at takeoff or landing site: 19,700 ft (6000 m) 16,400 ft (5000 m) - Engine restart ensured up to: 13,120 ft (4000 m) Crew and Passenger Limitations. Minimum Crew 1 pilot (see Note 3 for IFR operations) Maximum Passenger Luggage Compartment 12 396 lb (180 kg) Flight Limits. Day and Night VFR (see Note 3 for IFR operations) Flight Limitation in Icing Conditions. Flights in known icing conditions are prohibited. Fuel. Type: T-1 conforming GOST 10227-86; T-2 conforming to GOST 10227-86 with PMAM or TK additives TS-1; RT conforming GOST 10227-86; PSM-2 conforming PN-86/C96026; JET A-1 acc. to DERD 2494 or ASTM D 1655-83 Note: Anti-ice additives - See PZL W-3A Rotorcraft Flight Manual. Fuel Capacity. (a) 1720 Litres - 454.4 U.S. Gallons (b) 8.1 Litres - 2.14 U.S. Gallons unusable Oil. Type: a) B-3W conforming to TU-38-101295-75 DENSITY ALTITUDE 4 H15EU b) CASTROL 599 conforming to DERD 2497. c) CASTROL 5000; CASTROL 5050; AEROSHELL TURBINE OIL 500; ELF TURBO JET II conf. to MILL-L-23699C Certification Basis. FAR 21.29, FAR 29 effective 1 February 1965, including Amendments 29-1 through 29-26. FAR Part 36 Noise Standards Amended by Amendments 36-1 through the latest amendment in effect at the time of certification (Amdt. 36-15). The applicant has shown compliance to FAR Part 29.923 for 2 -1/2 minute OEI ratings. The Polish Glowny Inspektorat Lotnictwa Cywilnego (General Inspectorate of Civil Aviation) originally type certificated this rotorcraft under its type certificate number BC 188. The FAA validated this product under U.S. Type Certificate Number H15EU. Effective September 28, 2003, the European Union Aviation Safety Agency (EASA) began oversight of this product on behalf of the Polish Glowny Inspektorat Lotnictwa Cywilnego (General Inspectorate of Civil Aviation). Import Requirements. To be eligible for operation in the United States, each aircraft manufactured under this Type Certificate must be accompanied by a certificate of airworthiness for export or certifying statement endorsed by the exporting civil airworthiness authority which states (in the English language): "This aircraft conforms to its U.S. type design (Type Certificate Number H15EU) and is in a condition for safe operation." The U.S. airworthiness certification basis for aircraft type certificated under FAR Section 21.29 and exported by the country of manufacture is FAR Sections 21.183(c) or 21.185(c). Refer to the applicable bilateral agreement to verify eligibility for import into the United States of both new and used aircraft based on the scope of the agreement, to identify any required statements by the exporting authority on the export certificate of airworthiness (or equivalent document), and for procedures for coordinating exceptions to conformity statements on these documents. Refer to FAA Order 8130.2, Airworthiness Certification of Aircraft, for requirements for issuance of an airworthiness certificate for imported aircraft. The FAA can issue a U.S. airworthiness certificate based on an National Aviation Authority (NAA) Export Certificate of Airworthiness (Export C of A) signed by a representative of the Polish Civil Aviation Authority (Urzad Lotnictwa Cywilnego (ULC) – formerly Glowny Inspektorat Lotnictwa Cywilnego (General Inspectorate of Civil Aviation)) on behalf of the European Community. The Export C of A should contain the following statement: “The aircraft covered by this certificate has been examined, tested, and found to comply with the type design approved under U.S. Type Certificate Number H15EU and to be in a condition for safe operation.” Prior to issuance of the U.S. airworthiness certificate, the aircraft must comply with the foreign Airworthiness Directives (ADs) as listed in the FAA Required Airworthiness Action List (RAAL) in this section. The RAA contains ADs issued by the state of design authority EASA to correct unsafe conditions. EASA has advised the FAA of this mandatory continuing airworthiness information (MCAI), and the FAA has determined that the airworthiness actions identified in the EASA ADs are required in the interest of safety and are necessary for this airplane to be in a condition for safe operation. 5 H15EU The FAA did not issue an equivalent AD because there were no aircraft registered in the U.S when these ADs were published. The Notice of Policy Statement announcing the FAA’s policy with respect to foreign MCAI, when no aircraft of the affected design are currently registered in the U.S., was published in the Federal Register on May 1, 1998, docket 98-11648. If and when a model under this TC is registered in the U.S., the FAA will cease adding MCAI to the RAAL. When the FAA determines that a future AD must be accomplished on U.S. registered aircraft, the FAA will issue an Airworthiness Directive (AD). Any deviation from the requirements of the MCAIs listed in the RAAL must be approved by the Manager, Europe, Middle East & Africa Section, AIR-731, FAA International Validation Branch. FAA Required Airworthiness Action List (RAAL) for this model is as follows: RAAL # EASA AD # & Date Service Information EASA AD Title 1 2021-0270 This AD supersedes EASA AD 2017-0057 dated 06 April 2017 PZL W-3A Instructions for Continued Airworthiness (ICA) Chapter 04 of Maintenance Manual (MM) AE 30.04.20.1 MM (in English) at Revision 16 or AE 30.04.20.1 IOT (in Polish) at Revision 15. ATA 05 – Time Limits / Maintenance Checks – Airworthiness Limitations – Amendment; 2 2025-0235 23 October 2025 This AD supersedes 2025-0149 14 July 2025 AD 2025-0149 supersedes EASA AD 2022-0092 24May 2022 WSK “PZL-ŚWIDNIK” S.A. Alert Service Bulletin (ASB) No. ASB-37-21-330 Revision 1. WSK “PZL-ŚWIDNIK” S.A. ASB No. ASB-37-25- 357 WSK “PZL-ŚWIDNIK” S.A. ASB No. ASB-37-25- 361. ATA 72 – Engine – Vibration Levels – Measurement 3 2021-0276 WSK “PZL-ŚWIDNIK” S.A. Alert Service Bulletin (ASB) No. ASB-37-20-325. ATA 71 – Powerplant – Electrical Harness – Inspection / Repair / Replacement / Modification Service Information. Each of the documents listed below must state that it is approved by the EASA or under the authority of DOA ref. EASA.21J.114, or – for approvals made before September 28, 2003 – by the Polish Glowny Inspektorat Lotnictwa Cywilnego (General Inspectorate of Civil Aviation). Any such documents are accepted by the FAA and are considered FAA approved. • Service Bulletin, • Structural repair manuals, • Vendor manuals, • Aircraft flight manuals, and • Overhaul and maintenance manuals. This applies only to the acceptance of the type design data 6 H15EU Equipment. The basic required equipment as prescribed in the applicable airworthiness regulations (See Certification Basis) must be installed in the helicopter for certification. In addition, the following items of equipment are required with each helicopter as specified: FAA approved Rotorcraft Flight Manual, dated March 31, 1993 or later revisions. NOTES NOTE 1. Current weight and balance report including list of equipment included in the certificated empty weight and loading instructions, when necessary, must be provided for each helicopter at the time of original certification. Weight empty - Total weight of structure, systems equipment and permanent fittings necessary to complete every helicopter version, the weight empty includes weight of fluids in hydraulic system, blade dampers and shock absorbers and extinguisher bottles as well as weight of engine and transmission oil filled up to MAX level and unusable fuel. NOTE 2. The retirement times of certain parts are listed in Chapter 4 of the Model "PZL W-3A Helicopter. Instructions for Continued Airworthiness Maintenance Manual". Those values of retirement or service life cannot be increased without FAA approval. In addition, information essential for proper maintenance of the helicopter is contained in the "PZL W-3A Helicopter. Instructions for Continued Airworthiness Maintenance Manual". NOTE 3. Model PZL W-3A helicopter incorporating IFR equipment per requirements of PZL W-3A RFM Section 1 is eligible for IFR operations. Minimum flight crew: 2 (pilot and co-pilot). ....END.....