TCDS R00009RD

Page No. 1 2 3 4 5 6 7 Rev. No. 3 3 2 3 2 2 2 DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION TYPE CERTIFICATE DATA SHEET No. R00009RD This data sheet which is a part of Type Certificate No. R00009RD prescribes conditions and limitations under which the product for which the type certificate was issued meets the airworthiness requirements of the Code of Federal Regulations. Type Certificate Holder: Airbus Helicopters Aeroport International Marseille - Provence 13725 Marignane CEDEX France Engine. 2 Safran Helicopter Engines, S.A. Arrano 1A TCDS E00096EN Engine Limits. Installed Engine Limitations and Transmission Torque Limits Torque limits [%] at MBG input Gas generator rpm N1 [%] Temperature TOT [°C] AEO 20 sec transient 108% 46,550 (105.5%) 934°C Take-off / 30-min AEO 100% up to Vy+10 kts 93.7% above Vy+ 30 kts 45,910 (104.0%) 912°C AEO-MCP 93.6% 45,470 (103.0%) 886°C OEI (30 sec) 145% (72.5% at output level) 47,590 (107.8%) 991°C OEI (2 min) 127.5% (63.8% at output level) 46,620 (105.6%) 957°C OEI CT 112.1% (56.0% at output level) 46,130 (104.5%) 914°C For other Engine and Transmission Torque limits, refer to approved Rotorcraft Flight Manual (RFM). Fuel. JET A, JET A-1, JP-8, JP8+100, JP-5, No. 3 Jet Fuel, TS-1 (TC-1) / RT(PT) For Code No., specifications, and more details, refer to approved RFM. For alternative authorized fuels, refer to approved RFM. R00009RD Revision 3 Airbus Helicopters H160-B June 16, 2025 I. Model H160-B (Transport Helicopter, Category A and B) Page 2 of 7 Engine Oil. Oil Type NATO code Specification Class Approved oil trademarks France US UK Military Civil RECOMMENDED USE Synthetic 5 cSt O-154 - MIL-PRF-23699 SAE AS 5780 - HTS ‒ Turbonycoil 640 ALERTNATIVES Synthetic 5 cSt O-156 DCSEA 299 MIL-PRF-23699 MIL-PRF- 23699 SAE AS 5780 DEF STAN 91-101 STD ‒ AeroShell Turbine Oil 500 ‒ Castrol 5000 ‒ Mobil Jet Oil II ‒ Total Aeroturbine 535 ‒ Total Preslia SE Jet ‒ Turbonycoil 600 O-154 - - HTS ‒ BP Turbo Oil 2197 ‒ Mobil Jet Oil 254 O-152 - - - CI ‒ Castrol Aero J5 For replacement oil, cold weather oil and and further details, refer to approved RFM. MGB Oil. Type of Oil Temperature limitations Approved brands (other products are excluded) Specifications NATO US UK FR Mineral oil 8 cSt For starting -13°F ≤ OAT (For starting -25°C ≤ OAT) No limitaton for flights Total / Aerogear 823 O-155 MIL PRF 6086 Grade M DTD 581 C OEP 70 AIR 3525 Mineral oil 12 cSt For starting -13°F ≤ OAT (For starting -25°C ≤ OAT) No limitaton for flights Total / Aerogear 1032 Synthetic oil 3 cSt -40 °F ≤ OAT ≤+50°F (-40 °C ≤ OAT ≤+10°C) For starting and flight Nyco / Turbonycoil 160 O-148 MIL PRF 7808 Grade 3 - AIR 3514 For further details, refer to approved RFM. Page 3 of 7 TGB Oil. Type of Oil Temperature limitations Approved brands (other products are excluded) Specifications NATO US UK FR Synthetic oil 3 cSt For starting and flight -40°F ≤ OAT≤+ 122°F (For starting and flight -40°C ≤ OAT≤+ 50°C) Nyco / Tubonyoil 640 O-154 MIL PRF 23699G - - Mineral oil 12 cSt -13 °F ≤ OAT ≤+86°F For starting and flight (-25 °C ≤ OAT ≤+30°C For starting and flight) Total / Aerogear 1032 O-155 MIL PRF 6086 Grade M DTD 581 C OEP 70 AIR 3525 For further details, refer to approved RFM. Hydraulic Fluids. MIL-PRF-83282 or MIL-PRF-87257 Fuel Capacity. Max usable fuel capacity: 380.4 US Gal (1,440 liters) Unusable fuel: 2.6 US Gal (9.9 liters) Oil Capacity. Engine (each): 1.5 US Gal (5.8 liters) MGB: 6.3 US Gal (24 liters) TGB: 0.13 US Gal (0.5 liters) Hydraulic system: Left circuit: 1.4 US Gal (5.1 liters) Right circuit: 1.4 US Gal (5.3 liters) Airspeed Limitations. VNE PWR ON = 170 KIAS up to 5,000 ft PA For reduction of VNE with altitude, refer to approved RFM. VNE OEI and VNE PWR OFF = VNE PWR ON minus 35 KIAS For other speed limitations, refer to approved RFM. Rotor Speed Limitations. Power on: NR regulated range AEO 96.0 - 105.3 % (308.7 – 338.6 rpm) Reference NR 100.0 % (321.6 rpm) Maximum CT 107.8 % (346.7 rpm) Minimum CT AEO 92.0 % (295.9 rpm) Minimum CT OEI 95.5 % (307.1 rpm) Minimum transient 83.0 % (266.9 rpm) Power off: Maximum transient 117.0 % (376.3 rpm) Maximum CT 109.8 % (353.1 rpm) Minimum CT 92.0 % (295.9 rpm) Minimum transient 83.0 % (266.9 rpm) Page 4 of 7 Center of Gravity Range. Longitudinal C.G. limits Maximum forward limit: 200.47 inches (5,092 mm) aft of datum at 11,685 lbs (5,300 kg) 201.96 inches (5,130 mm) aft of datum at 13,338 lbs (6,050 kg) Maximum rearward limit: 212.21 inches (5,390 mm) aft of datum at 9,921 lbs (4,500 kg) 208.15 inches (5,287 mm) aft of datum at 13,338 lbs (6,050 kg) Lateral C.G. Limits Maximum deviation on right / left: 2.56 inches (65 mm) at 12,125 lbs (5,500 kg) 0.79 inches (20 mm) at 13,338 lbs (6,050 kg) For detailed data, refer to approved RFM. Empty Weight C.G. Range. None. Datum. Longitudinal: the datum plane (STA 0.0) is located 205.39 inches (5,217 mm) forward of the main rotor head center. Lateral: Fuselage Symmetry plane Leveling Means. Leveling reference marking on upper deck on LH side near to MGB between Frames 3 and 4. Maximum Weight. In-flight: 13,338 lbs (6,050 kg) On-ground: 13,448 lbs (6,100 kg) Minimum Flight Crew. One pilot (right seat) Maximum Seating Capacity. 14 (Including flight crew) Emergency Exits. 6 Exits, which are: - 1 crew exit on each side of the cockpit - 2 passenger exits on each side of the passenger cabin (See Note 6.) Maximum Baggage/ Cargo Loads. Cargo floor max. load: 662 lbs (300 kg) Cargo floor max. load: 728 lbs (330 kg) with optional cargo extension installed in addition to the use of mandatory approved restraining nets. Cargo floor max. unit load: 61.5 lbs/square foot (300 kg/m²) For complementary limitations and specific loading conditions, refer to approved RFM. Maximum Altitude. Flight altitude -1,500 ft to +20,000 ft PA Take-off and landing altitude: • Minimum: -1,500 ft PA and -4,600 ft DA • Maximum: 13,000 ft DA Temperature Limits. -20°C to ISA+37°C limited to +50°C Operating Limitations. VFR/IFR day and night in non-icing conditions. Flight in falling and blowing snow. Refer to approved RFM. Rotor Blades and For rigging information, refer to the Maintenance Manual. Control Movements. Serial Numbers Eligible. Manufacturer’s eligible serial numbers: S/N 1002 and Subsequent An Export Certificate of Airworthiness endorsed as noted below under "Import Requirements" Page 5 of 7 must be submitted for each individual rotorcraft for which application for FAA certification is made. Import Requirements. To be considered 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 foreign civil airworthiness authority which states: “The aircraft covered by this certificate has been examined, tested, and found to conform to the type design approved under the U.S. Type Certificate Number R00009RD and to be in a condition for safe operation.” 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 type design approved under TC R00009RD is defined by Airbus Helicopters Report no. U000A1723E01_D_TDD_H160 FAA, H160-B Type Design Definition for USA (FAA), Issue D, dated July 05, 2024, and subsequent revisions, defines the list of associated data package codes and dates. Certification Basis. 14 CFR Part 29 Amendment 29-1 through 29-55, dated January 31, 2012. Equivalent Safety Findings: Number TC04277RD-R-F-06 (ELOS finding for one engine inoperative (OEI) training mode) 29.1305 Powerplant instruments; 29.1309 Equipment, systems, and installations; 29.1549 Powerplant instruments. Number TC04277RD-R-P-1 (ELOS finding for part time display of vehicle parameters) 29.1305 Powerplant instruments; 29.1351(b)(6) Generating system; 29.1435(a)(3) Hydraulic systems, Design. Number TC04277RD-R-F-2 (ELOS finding for the airspeed and powerplant indication green marking) 29.1545(b)(4) Airspeed indicator; 29.1549(b) Powerplant instruments. Number TC04277RD-R-C-01 (ELOS finding for other than side-of-fuselage passenger emergency exits) 29.807(c) emergency exits, other than side-of-fuselage. Number TC04277RD-R-C-03 (ELOS finding for the number and type of ditching emergency exits) 29.807(d)(2) Passenger emergency exits; Ditching emergency exits for passengers. Number TC04277RD-R-C-4 (ELOS finding for the emergency exit configuration) 29.807(a)(4) Passenger emergency exits; Type IV. Number TC04277RD-R-P-2 (ELOS finding for PT99 test platform) 29.923 Rotor drive system and control mechanism tests. Number TC04277RD-R-P-5 (ELOS finding for fire detection electrical circuit testability) 29.1203 (d) Fire detector systems. Number TC04277RD-R-SE-1 (ELOS finding for thunderstorm lights) 29.1381 Instrument lights. Number TC04277RD-R-S-2 (ELOS finding for Multipurpose Fire Extinguishing System) 29.1195 (b) (2) Multipurpose Fire Extinguishing System Page 6 of 7 Certification Basis. (Cont’d) Number TC04277RD-R-P-10 (ELOS finding for the air intake fireproof ducts) 29.1103(d)(1) Induction systems ducts and air duct systems. Number TC04277RD-R-P-09 (ELOS finding for firewall backside burning and flammable fluid zone ignition source) 29.901(c) Installation; 29.1191 Firewall. Number TC04277RD-R-S-3 (ELOS finding for the installation of a red/white combination strobing anticollision light) 29.1401(d) Anticollision light system; Color. Number TC04277RD-R-P-11 (ELOS finding for MGB Red Line Limits) 29.1301(d) Function and installation; 29.1305(a)(6) Powerplant instruments; 29.1549(a) Powerplant instruments. Special Conditions: Special Conditions No. 29-053-SC (Special Condition for 30 Minute All Engines Operating (AEO) Power Rating) Special Conditions No. 29-055-SC; (Special Condition for Extended Duration of Flight After Loss of Main Gearbox Lubrication) Exemptions: None Environmental Standards: 14 CFR Part 36 Appendix H Amendment 36-30 The European Union Aviation Safety Agency (EASA) originally type certificated this rotorcraft under its type certificate EASA.R.516. The FAA validated this product under U.S. Type Certificate Number R00009RD, issued June 30, 2023. Date of Application for U.S. Type Certificate: November 7, 2014. Service Information. Each of the documents listed below must state that it is approved by EASA: • Service bulletins • Structural repair manuals • Vendor manuals • Aircraft flight manuals • Overhaul and maintenance manuals The FAA accepts such documents and considers them FAA-approved unless one of the following conditions exists: • The documents change the limitations, performance, or procedures of the FAA approved manuals; or • The documents make an acoustical or emissions change to this product’s U. S. type certificate as defined in 14 CFR 21.93. The FAA uses the FAA-EASA Technical Implementation Procedures (TIP) to approve these documents and changes to these documents. The FAA may delegate on case-by-case to EASA to approve on Behalf of the FAA for the U.S. type certificate. If this is the case, it will be noted on the document. Page 7 of 7 Equipment. The minimum required equipment as prescribed in the applicable airworthiness regulations (see Certification Basis) must be installed in the helicopter for certification. The type design approved under TC R00009RD is defined by Airbus Helicopters Report no. U000A1723E01_D_TDD_H160 FAA, H160 -B Type Design Definition for USA (FAA), Issue D, dated July 05, 2024, and subsequent revisions lists required and optional equipment for the helicopter. In addition, the following equipment is required: EASA-approved Rotorcraft Flight Manual, identified as approved on Behalf of FAA, approval date 12th of December 2023 mentioned in Section 1.2 or later approval date. Approved FAA RFM is the published hard copy (paper) manual. The type design approved under TC R00009RD is defined by Airbus Helicopters Report no. U000A1723E01_D_TDD_H160 FAA, H160-B Type Design Definition for USA (FAA), Issue D, dated July 05, 2024, and subsequent revisions, defines the list of associated data package codes and dates. NOTES. NOTE 1. Weight and Balance: Current weight and balance report including loading instructions and list of equipment included in the certificated empty weight, must be provided for each helicopter at the time of original certification. The certificated empty weight and corresponding center of gravity location must include unusable fuel and engine oil and transmission oil. NOTE 2. Placards: All placards required by either the FAA-approved Rotorcraft Flight Manual, the applicable operating rules, or the Certification Basis must be installed as specified. NOTE 3. Instructions for Continued Airworthiness: Airbus Orion Normal Revision 10.00 (Update 15) 2024.01.29 which corresponds to : • H160-B Maintenance Servicing Manual (Chapter 5) – Airbus Orion H160 Revision 014 (2024.01.29); • Chapter 4, “AIRWORTHINESS LIMITATIONS” – Airbus Orion Revision 015 (2024.01.29). Chapter 4 and 5 defines the retirement life limitations of the helicopter parts which are critical from a fatigue standpoint. These values of retirement of service life cannot be increased without FAA Engineering approval. Additional information essential for proper maintenance of the helicopter is contained in the H160-B Aircraft Maintenance Manual and Repair Manual. NOTE 4. Optional items: The certified optional installations are each approved independently of the basic helicopter and are part of the relevant approved Rotorcraft Flight Manual. NOTE 5. Ditching certification: The H160-B is certified for ditching with the optional installations and operating procedures as defined in approved RFM. NOTE 6. Passenger Emergency Exits: The Sliding Door Jettisonable Window, which is one of the 2 separate exits on each side of the passenger cabin, has been demonstrated to be equivalent to two Type IV emergency exits as specified in 14 CFR 29.807(a)(4) (IP C-04 refers). NOTE 7. APU mode: The APU mode approved at engine level is not approved at aircraft level. NOTE 8. NOTE 9. NOTE 10. NOTE 11. Vibration Health Monitoring (VHM) System: The FAA has not approved the VHM Health Usage Monitoring System (HUMS) for usage or maintenance credit. Aircraft Battery: The FAA has approved for installation on the H160 -B only on a one -time basis, Marathon Norco aircraft battery part number 33378 -001, based on comparative analysis plus additional safety testing. This process of approval is not to be used for any future installation approval. Deleted. Deleted. .....END.....