Type Certificate Data Sheet

RATING MAX TORQUE [% (Nm)] INPUT SPEED [rpm] INPUT POWER [hp] AEO Maximum Continuous 2x100 (334) 14,400 1,350 (675x2) 5 min 2x111 (371) 14,400 1,500 (750x2) 30 min (*) OEI Maximum Continuous 140 (470) 14,400 950 2.5 min 174 (583) 14,400 1,180 (*) if Core Avionic SW phase 4.0 P/N 6F4600A00114, or later, is installed. PW210A1 (helicopters with Kit Enhanced Performance installed) RATING MAX TORQUE [% (Nm)] INPUT SPEED [rpm] INPUT POWER [hp] AEO Maximum Continuous 2x100 (334) 14,400 1,350 (675x2) 5 min 2x122 (407) 1,650 (825x2) 30 min 1,650 (825x2) OEI Maximum Continuous 148 (493) 14,400 1,000 2.5 min 185 (618) 1,250 6. Fluids (Fuel/ Oil/ Additives): 6.1 Fuel: JET A, JET A1, JP8, JP8+100, No.3 Jet Fuel (for code number specification and more details refer to the JCAB approved Rotorcraft Flight Manual) 6.2 Oil: Transmission AEROSHELL TURBO OIL 555 (DoD-L-85734). No different specification or brand is allowed Engine Refer to the JCAB approved Rotorcraft Flight Manual Hydraulics MIL-PRF-83282, MIL-PRF-87257 (as alternative) 6.3 Fuel Additives: Refer to the JCAB approved Rotorcraft Flight Manual 6.4 Coolant: R134a 7. Fluid capacities: 7.1 Fuel: Total A/C capacity litres (kg (*)) Unusable litres (kg (*)) Two main fuel tanks (LH and RH) 1,130 (904) 20 (16) (*) Above fuel mass has been defined assuming a standard fuel density of 0.8 kg/l. 7.2 Oil: Quantity litres (kg) (*) ENGINE (each) min 5.25 (4.948) - max 5.78 (5.448) MAIN GEARBOX (min/max) min 17 (16.968) - max 19 (18.964) (16.8 + 2.2 for oil cooler, oil ducts and filter) INTERMEDIATE GEARBOX 0.77( 0.768) TAIL GEARBOX 1.10 (1.098) HYDRAULIC (per each Power Control Module) 1.3 (1.1) (*) litres (kg at 80°C) 5 No. 85 7.3 Coolant system capacity: 2.1 kg 8. Air Speed Limits: VNE Power On AEO ……………………………165 KIAS VNE Power On AEO* ……………………………160 KIAS VNE Power On OEI ……………………………135 KIAS VNE Power Off ……………………………125 KIAS For reduction of the VNE with Density Altitude (HP/OAT), see RFM. (*) if Core Avionics SW Phase 6.0, or later is installed 9. Rotor Speed Limits: Power On AEO (*) Condition (rpm) (%) Minimum Continuous 317.56 96.0 Maximum Continuous 354.72 103.0 Power On OEI Condition (rpm) (%) Minimum Cautionary 304.05 90.0 Minimum Continuous 341.21 101.0 Maximum Continuous 354.72 105.0 Power Off Condition (rpm) (%) Minimum Continuous 304.05 90.0 Maximum Continuous 371.61 110.0 (*) Maximum and minimum continuous values of the flight envelope. AVSR provides a governing of the rotor speed at different values depending on airspeed (TAS/IAS**) and density altitude. As the NR datum is variable, NR green band is variable as well (±2% across the datum value). (**) IAS if Core Avionics SW Phase 6.0, or later is installed. See RFM for additional rotor speed limitations 10. Maximum Operating Altitude and Temperature: 10.1 Altitude: Maximum flight altitude 15 000 ft* for operation at gross mass up to 4 600 kg, and, 10 000 ft* for operation at gross mass above 4 600 kg without Kit Enhanced Performance installed, or, 15 000 ft* for operation at gross mass above 4 600 kg with Kit Enhanced Performance is installed Maximum Take-off and Landing altitude 15 000 ft* for operation at gross mass up to 4 600 kg, and, 10 000 ft* for operation at gross mass above 4 600 kg without Kit Enhanced Performance installed, or, 15 000 ft* for operation at gross mass above 4 600 kg with Kit Enhanced Performance is installed * altitude in PA/DA (whichever occurs first) 10.2 Temperature: -40°C ～ +50°C (ISA + 35°C) -40°C ～ +50°C (ISA + 35°C) for Cat. A operations For variation of Temperature limitations with altitude, see the 6 No. 85 RFM and applicable supplement 11. Operating Limitations: VFR/IFR day and night operations in non-icing conditions 12. Maximum Weight: 12.1 Take-off and Landing 4,600 kg, or 4,800 kg if P/N 6F0000F00211 is installed 12.2 Taxi and Towing 4,650 kg, or 4,850 kg if P/N 6F0000F00211 is installed 13. Centre of Gravity Range: Refer to the JCAB approved RFM 14. Datum: Longitudinal Datum (STA 0) is located at 3,528 mm forward to the front jack point Lateral Datum (BL 0) is located at +/- 225 mm inboard of LH/RH front jack points 15. Levelling Means: Plumb line from ceiling reference point to index plate on floor of baggage compartment. 16. Minimum Flight Crew: One (1) pilot for VFR day and night and IFR. For NVG operations, two (2) pilots or one (1) pilot and one (1) crew member required. Both pilot and crew member must be equipped with NVGs (see Note 3). 17. Maximum Passenger Seating Capacity: 10 passengers in the passenger cabin + 1 passenger in the cockpit in case of one pilot flight crew. Refer to approved RFM for passenger cabin configurations. 18. Passenger Emergency Exit: 2 on each side of the passenger cabin 1 on each side of the passenger cabin, if the kit Sliding Aft Passenger Windows P/N 6F5630F00411is installed. 19. Maximum Baggage / Cargo Loads: 250 kg located in the Baggage/Cargo compartment 20. Rotor Blade control movement: For rigging info ref to RFM 21. Auxiliary Power Unit (APU): N/A 22. Life-limited parts: refer to the Airworthiness Limitation Section (ALS) of the Maintenance Manual 23. Wheels and Tyres: MLG wheel assembly with 18 x 5.5 tubeless tyres NLG wheel assembly with 5 x 5.5 tubeless tyres IV. Operating and Service Instructions 1. Flight Manual: Rotorcraft Flight Manual, Doc. No. 169F0290X001J, initial issue dated 02 February 2016, JCAB approved on 02 February 2016 or later approved revisions. Doc. No.AW169 RFM-Sup.01-00 covering Doc. No. 169F0290X012, Original issue dated 20 December 2022, JCAB approved 20 December 2022, or later approved revisions, only for helicopters with Kit Enhanced Performance installed. 7 No. 85 2. Maintenance Manual: “AW169 Maintenance Planning Information” Doc. No. 69-A-AMPI-00-P, EASA accepted 15 July 2015, or later revisions, including: - Chapter 4 ALS, initial issue dated 15-07-2015, EASA approved on 15 July 2015 or later approved revisions; - Chapter 5 with Scheduled Maintenance Requirements “Maintenance Review Board Report for AW169 Helicopter” Doc. No. 169F0000M005 “AW169 Maintenance Publication” Doc. No. 69-A-AMP-00-X “AW169 Material Data Information” Doc. No. 69-A-AMDI-00-X “AW169 Corrosion Control Publication” Doc. No. 69-A-ACCP-00-X “AW169 Fault Isolation Publication” Doc. No. 69-A-AFIP-00-X “AW169 Wiring Data Publication” Doc. No. 69-A-AWDP-00-X 3. Structural Repair Manual: “AW169 Structural Repair Publication” Doc. No. 69-A-ASRP-00-X “AW169 Component Repair and Overhaul Publication” Doc. No. 69-A-CR&OP-00-X 4. Weight and Balance Manual: refer to the Section 6 of the RFM and applicable supplements 5. Illustrated Parts Catalogue: “AW169 Illustrated Tool and Equipment Publication” Doc. No. 69-A-ITEP-00-X “AW169 Illustrated Part Data” Doc. No. 69-A-IPD-00-X 6. Service Letters and Service Bulletins: As published by AgustaWestland S.p.A. or Finmeccanica S.p.A. or Leonardo S.p.A. 7. Required Equipment: As per compliance with certification basis and included in Type Design Definition standard. Refer to approved Rotorcraft Flight Manual and MMEL Refer to the JCAB Approved Rotorcraft Flight Manual and related supplements for other approved mandatory and optional equipment. 8 No. 85 V. Notes 1. Serial Numbers 69006 and subsequent 2. Manufacturer AgustaWestland S.p.A. in Italy (*) (*) Effective on 01 January 2016, AgustaWestland S.p.A. ownership was transferred to Finmeccanica S.p.A.; Effective on 28 July 2016, Finmeccanica S.p.A. name was changed into Leonardo S.p.A.. 3. NVG Operations Night Vision Goggle Operations are permitted according to RFM 169F0290X012 Supplement No. 16. The aircraft configuration involving internal/external emitting/reflecting equipment approved for use with NVG is described in the Report No. 169F3360A001 ‘AW169 NVG Compatibility Reference Handbook’. Subsequent modifications and deviations to the NVG helicopter configuration shall be managed in accordance with document 169F3360E001 ‘AW169 Helicopter NVG Policy’. 4. Installation of the TSS-4100 system P/N 6F0630A03113, has been demonstrated compliant with Certification Specifications for Airborne Communications Navigation and Surveillance, CS-ACNS initial issue, dated 17 December 2013. J1. This Type Certificate Data Sheet (TCDS) is based on TCDS No. EASA R.509 Issue 14 dated 22 December 2022. J2. Placards and markings for the emergency evacuation, safety equipment and necessary matters to be notified to passengers in order to assure safe operation of rotorcraft, must be indicated in Japanese in accordance with JCAB Circular No.1-008. The rotorcraft must be operated according to the required Japanese placards and markings which are defined in drawing as documented below. DWG No.6F1100P00211 J3. The rotorcraft must be operated according to the appropriate JCAB Approved Rotorcraft Flight Manual and Rotorcraft Flight Manual Supplements. J4. Import Eligibility To be considered eligible for operation in the Japan, each rotorcraft 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 following (in the English language) “This rotorcraft has been examined, tested and found to conform to the type design approved under JCAB Type Certificate No.85-1 and to be in a condition for safe operation.” J5. Production Basis ENAC Production Certificate of AW169 in Italy Number: IT.21G.0007 (Effective Date: 1 January 2016) … END …