TCDS R00007RD

DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION TYPE CERTIFICATE DATA SHEET NO. R00007RD This data sheet which is a part of Type Certificate No. R00007RD prescribes conditions and limitations under which the product for which the Type Certificate was issued meets the airworthiness requirements of the Federal Aviation Regulations. Type Certificate Holder Leonardo S.p.a. Piazza Monte Grappa, 4 00195 – Roma, ITALY I. Model AW169 (Transport Helicopter: Category A and Category B), Approved 2 February 2017 Engine Two (2) Pratt&Whitney Canada PW210A FAA Engine Type Certificate Data Sheet No E00083EN For Limitations Ref. to PW210A Pratt&Whitney Canada installation Manual (Ref. to 30L2374) Auxiliary Power Unit (APU) N/A Fuel JET A, JET A1, JP8, JP8+100, No. 3 Jet Fuel (for code no. specification and more details refer to Rotorcraft Flight Manual) Oil Hydraulics MIL-PRF-83282, MIL-PRF-87257 (as alternative) Transmissions Engine APU Additives Coolant AEROSHELL TURBO OIL 555 (DoD-L-85734). No different specification or brand is allowed Refer to approved Rotorcraft Flight Manual N/A Refer to approved Rotorcraft Flight Manual R134a Page No. 1 2 3 4 5 6 7 8 9 10 11 12 13 14 15 16 17 Rev. No. 3 3 3 3 3 3 3 3 3 3 3 3 3 3 3 3 3 R00007RD REVISION 3 Leonardo S.p.a. AW169 March 30, 2026 R00007RD 2 Rev.3 Fuel Total A/C capacity litres (Kg (*)) Unusable litres (Kg (*)) Two main fuel tanks (LH and RH) 1130 (904) 20 (16) (*) Above fuel mass has been defined assuming a standard fuel density of 0,8 kg/l. 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) Coolant system capacity 2.1kg Installed Engine Limits PW210A RATING MAX TORQUE [% - Nm (lb ft)] MAX ITT [C] MAX NG [% - RPM] MAX NF [% - RPM] AEO Continuous 118.6 – 395.9 (292) 868 96.5 – 49200 107 - 28120 Take-off 5 min Take-off 30 min* 125.9 – 420.3 (309.9) 930 98.2 - 50100 OEI Continuous 148.3% - 494.9 (365) 941 98.9 - 50430 107 - 28120 2.5 min 174.7% - 583 (429.9) 1020 100.7 - 51360 (*)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 (lb ft)] MAX ITT [C] MAX NG [% - RPM] MAX NF [% - RPM] AEO Continuous 118.6 – 395.9 (292) 868 96.5 – 49200 107 - 28120 Take-off 5 min Take-off 30 min* 125.9 – 420.3 (309.9) 937 98.2 - 50100 OEI Continuous 148.3% - 494.9 (365) 937 98.8 - 50400 107 - 28120 2.5 min 185 - 618.3 1020 100.7 - 51360 R00007RD 3 Rev.3 Transmission Limits PW210A RATING MAX TORQUE [% - Nm (lb ft)] INPUT SPEED [RPM] INPUT POWER [Hp] AEO Maximum Continuous 100 – 334 (246.3) (x2) 14400 1350 (675x2) 30 min* 111 – 371 (273.6) (x2) 14400 1500 (750x2) 5 min OEI Maximum Continuous 140 – 470 (346.6) 14400 950 2.5 min 174 – 583 (429.9) 14400 1180 (*)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 (lb ft)] INPUT SPEED [RPM] INPUT POWER [Hp] AEO Maximum Continuous 2 x 100(334) 14400 1350 (675 x 2) 30 min* 2x 122 (407) 14400 1650 (825 x2) 5 min OEI Maximum Continuous 148 (493) 14400 1000 2.5 min 185 (618) 14400 1250 Rotor Limits (*) 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). See RFM for additional rotor speed limitations (**) IAS if Core Avionics SW Phase 6.0, or later is installed 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 R00007RD 4 Rev.3 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 VIr/VLo (gear extended/gear operating) = VNE -8 KIAS/80 KIAS See approved Rotorcraft Flight Manual for variations with altitude, OAT and weight. (*) if Core Avionics SW Phase 6.0, or later is installed. AW 169 Document N° AW 169 RFM 169F0290X001 AIRSPEED LIMITATION PRESSURE ALTITUDE (m X 100] ISA +35°C PRESSURE ALTITUDE (N1 X 1000] Figure 1-7 Airs er ON, OEI/Power OFF) 08-07-2015 Page 1-13 AIRSPEED LIMITATION PRESSURE ALTITUDE A 100E PRESSURE ALTITUDE [ft X 1000] R00007RD Rev.3 AIRSPEED LIMITATION VNE TAS km/h] 240 260 OAT - [°C] ISA+35°C -1 0 * PRESSURE ALTITUDE (f1 × 1000] 140 150 160 170 169G1580A007 RevA VNE [IAS KI] ICN-69-A-155030-G-A0126-00034-A-01-1 R00007RD 6 Rev.3 Center of Gravity (C. G.) Range AW 169 AW169 - RFM Document N Limitations Section 1 169F0290X001 0.10 3600 0.060 0.02 0.04 0.06 0.08 3300 0.044 Weight / Lateral C.G. Envelope MAST +0.06 -0.04 -0.02 0.00 BL [m] 3300 - 0.025 4600 - 0.045 3700 -0.055 -0.08 -0.10 5000 300 00 4400 4200 4000 3800 3600 3400 3200 3000 2800 2600 2400 GW [kg] Figure 1-4 Weight and Lateral CG Limitations Issue 1 Page 1-7 Weight And Lateral Cg Envelope R00007RD 7 Rev.3 Limitations Section 1 AW169 - RFM Document N° AW 169 169F0290X001 3300 5.426 4.95 5.00 5.05 5.10 5.15 5.20 5.25 5.30 5.35 5.40 5.45 5.50 5.55 5.60 Weight / Longitudinal C.G. Envelope STA [m] 33.00 5.206 4600 5.120 MAST 4200 5.040 3800 5.040 5000 4800 4600 4400 4200 4000 3800 3600 3400 3200 3000 2800 2600 2400 GW [kg] Figure 1-3 Weight and Longitudinal CG Limitations Page 1-6 08-07-2015 EASA Approved Weight And Longitudinal Cg Envelope R00007RD 8 Rev.3 Weight / Longitudinal C.G. Envelope 5200 5000 4800 4800 4800 5.160 5.460 4600 4600 4400 4200 4200 5.040 4065 4000 5.475 GW Ikg] 3800 3800 5,040 3600 3400 3300 3300 3200 5.206 5.426 3000 2800 2600 MAST 4.95 5.00 5.05 5.10 5.15 5.20 5.25 5.30 5.35 5.40 5.45 5.50 5.55 5.60 STA [m] ICN-69-A-155630-G-A0126-00001-A-01-1 Fig. 1: Weight / Longitudinal C.G. envelope Weight / Lateral C.G. Envelope 5200 5000 4800 4800 -0.043 0.048 4800 4600 4600 4400 4200 4000 3800 3700 3600 -0.055 - 3600 0.060 3400 3200 - 3300 3300 3000 -0.025 0.044 2800 MAST 2600 -0.08 -0.06 -0.04 -0.02 0.00 0.02 0.04 0.06 0.08 BL [m] ICN-69-A-155630-G-A0126-00002-A-01-1 Fig. 2: Weight / Lateral C.G. Envelope R00007RD 9 Rev.3 Ambient Temperature Limitations AW 169 Document N° AW169 - RFM Limitations Section 1 169F0290X001 AW169 FLIGHT ENVELOPE OAT - [°F] 15 50 30 10 9 10203040 50 60 7080 100 120 140 - 44 14 Minimum GW permitted • 42 for area A 40 000 н 3550 kg Pressure Altitude - [ft x 1000] NIMUM OAT Pressure Altitude - Im x 100] TAKE OFF and LANDING ENVELOPE -50 -40 -30 -20 -10 0 10 20 30 40 50 60 OAT - [°C] 169F1560A001 Rev.D ICN-89-A-151000-G-A0126-00004-A-03-1 Figure 1-8 Altitude and OAT Limitations Approved Issue 2 Page 1-15 R00007RD 10 Rev.3 OAT - [°F] -50 -30 -10 10 30 50 70 90 110 130 15 14 13 12 Pressure Altitude - [ft x 1000] MINIMUM OAT LIMIT HO LIMIT 10000 fL Pressure Altitude - [m x 100] -2 -50-40 -30 -20 -10 10 20 30 40 50 60 OAT - [°C] 169F1580A007 Rev.D ICN-69-A-155030-G-A0126-00001-A-02-1 Fig. B 6: Flight Envelope for GW above 4600 kg up to 4800 kg R00007RD 11 Rev.3 Maximum Operating Altitude and Temperature Altitude Temperature Maximum Operating 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) -40°C ÷ +50°C (ISA+35°C) -15°C ÷ +50°C (ISA+35°C) for Cat. A operations For variation of Temperature limitations with altitude, see the Rotorcraft Flight Manual and applicable supplement Datum Longitudinal Datum (STA 0) is located at 3528 mm forward to the front jack point Lateral Datum (BL 0) is located at +/- 225 mm inboard of LH/RH front jack points Levelling Means Plumb line from ceiling reference point to index plate on floor of baggage compartment Maximum weights Without Kit P/N 6F0000F00211 installed: - Taxi and Towing 4650 kg - Take-off and Landing 4600 kg With Kit P/N 6F0000F00211 installed: - Taxi and Towing 4850 kg - Take-off and Landing 4800 kg Minimum Crew One (1) for VFR day and One (1) for VFR night and IFR. For Cat. A operations, two (2) pilots are required if take -off and landing is to be carried out from the left seat. For NVG operations, two (2) pilots or one (1) pilot and one (1) crew member are required. Both pilot and crew member must be equipped with NVGs (see NOTE 10). Number of Seats Without Kit P/N 6F2520F00111 installed: 10 (2 crew – 8 passengers maximum) With Kit P/N 6F2520F00111 installed: 12 (2 crew – 10 passengers maximum) Maximum Baggage 250 kg (550 lb) located in the Baggage compartment Baggage compartment max pressure load 450 kg/m2 (92 lb/sq. ft) Baggage compartment max load height 600 mm (2 ft) Rotor Blades and Control Movements For rigging information, refer to the AW169 Maintenance Manual. 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 following (in the English language): 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, R00007RD 12 Rev.3 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 rotorcraft covered by this certificate has been examined, tested and found to conform to the type design approved under FAA Type Certificate No. R00007RD and to be in condition for safe operation.” The only aircraft eligible for import into the United States are those aircraft with the configuration defined in AW Report No. 169F0272N003, “AW169 - FAA Type Design Definition,” dated 23 January 2017 or later issue.. R00007RD 13 Rev.3 Certification Basis (1) 14 CFR Part 21.29. (2) 14 CFR Part 29 Amendment 29-1 through 29-52, dated 30 March 2010. (3) 14 CFR Part 36 Appendix H, Amendment 36-1 through 36-28 dated 11 March 2013. (4) 14 CFR Part 29 Amendment 29-1 through 29-55 only for Hoist Installation (5) Equivalent Level of Safety Findings issued against: • 14 CFR § 29.807(c) Emergency Exits Access (documented in ELOS Memo TC4266RD-R-C- 01). • 14 CFR § 29.807(d) Ditching emergency exits for passengers (documented in ELOS Certification Review Item D-07). • 14 CFR § 29.813(c) Passenger access to each emergency exit (documented in ELOS Memo TC4266RD-R-C-02). • CFR § 29.811(c) Emergency exit marking (documented in ELOS Memo TC4266RD-R-C- 03) • 14 CFR § 29 Subpart B, § 29.1305, § 29.1549 “Engine Training Mode” (documented in ELOS Memo TC4266RD-R-F-01) • 14 CFR § 29.1545(b)4 Airspeed indicator green arcs(documented in ELOS Memo TC4266RD- R-F-02). • 14CFR §29.1305 and §29.1549 Power Index (documented in ELOS Memo TC4266RD-R-F-06) • 14 CFR §29.923, §29.927 Rotor drive system and control mechanism tests: Main gearbox endurance and additional tests (documented in ELOS Memo AT12017IB-R-P-1) Equipment As per compliance with certification basis and included in Type Design Definition standard. Refer to approved Rotorcraft Flight Manual and MMEL Refer to EASA Approved Rotorcraft Flight Manual and related supplements for other approved mandatory and optional equipment. Night Vision Goggle Operations are permitted according to RFM 169F0290X001 Supplement No. 16. The aircraft configuration involving internal/external emitting/reflecting equipment approved for use with NVG is described in the Report N. 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 » Service information Lenonardo S.p.a. service bulletins, structural repair manuals, vendor manuals, aircraft flight manuals, and overhaul and maintenance manuals, which contain a statement that the document is EASA approved, are accepted by the FAA and are considered FAA approved. These approvals pertain to the approved type design only. Flight Manual For helicopters with wheeled landing gear without kit Enhanced Performance installed: EASA approved of behalf of FAA Rotorcraft Flight Manual 169F0290X001 Issue 3 Rev 2 or later approved revision (See Note 5). For helicopters with wheeled landing gear with kit Enhanced Performance installed: EASA approved of behalf of FAA Rotorcraft Flight Manual 169F0290X012 Issue 1 Rev 5 or later approved revision. . R00007RD 14 Rev.3 Maintenance Manual Maintenance Planning Information 69-A-AMPI-00-P Maintenance Publication 69-A-AMP-00-X. R00007RD 15 Rev.3 NOTES NOTE 1 A current weight and balance report, including a list of equipment included in the certificated empty weight, must be provided for each helicopter at the time of original airworthiness certification in accordance with 14 CFR 29.25, 29.27 and 29.29. NOTE 2 All placards required by either FAA Approved Rotorcraft Flight Manual, the applicable operating rules, or the Certification Basis must be installed in the helicopter. NOTE 3 Information essential to the proper maintenance of the helicopter is contained in the Manufacturer’s Maintenance Manual provided with each helicopter. Life limited components and associated retirement times are presented in Chapter 4 and must be replaced accordingly. NOTE 4 The model AW169 rotorcraft employs electronic engine controls, commonly named Full authority Digital Engine Controls (FADEC), that are recognized to be more susceptible to Electromagnetic Interference (EMI) than rotorcraft that have non-electronic controls. (EMI may be the result of radiated or conducted interference.) For this reason modifications that add or change systems that have the potential for EMI, must either be qualified to a standard acceptable to the FAA or tested at the time of installation for interference with the FADEC. This type of testing must employ the particular FADEC diagnostic techniques and external diagnostic techniques. The test procedure must be FAA approved. NOTE 5 The FAA Rotorcraft Flight Manual (RFM) is identical to the EASA approved RFM; any exceptions unique for FAA are presented on yellow pages marked “EASA approved on behalf of FAA”. They must be included in the FAA manual to reflect the differences noted below: 1. Section 1, LIMITATIONS, MINIMUM FLIGHT CREW: One pilot 2. Section 4, Performance Data, NOISE CHARACTERISTICS: Model: AW169 PW210A Gross Weight 4600 kg up to 5.0 Configuration Level Flyover EPNL (EPNdB) Take Off EPNL (EPNdB) Approach EPNL (EPNdB) Clean aircraft No external kits installed 103% NR 96% NR 96% NR 89.3 88.8 94.4 Model: AW169 PW210A Gross Weight 4800 kg up to AP 5.0 Configuration Level Flyover EPNL (EPNdB) Take Off EPNL (EPNdB) Approach EPNL (EPNdB) Clean aircraft No external kits installed 103% NR 96% NR 96% NR 89.3 88.9 94.2 Model: AW169 PW210A Gross Weight 4600 kg AP 6.0 Configuration Level Flyover EPNL (EPNdB) Take Off EPNL (EPNdB) Approach EPNL (EPNdB) Clean aircraft No external kits installed 100% NR 100% NR 100% NR 88.8 86.9 96.0 Model: AW169 PW210A Gross Weight 4800 kg AP 6.0 Configuration Level Flyover EPNL (EPNdB) Take Off EPNL (EPNdB) Approach EPNL (EPNdB) Clean aircraft No external kits installed 100% NR 100% NR 100% NR 88.8 86.9 96.0 Model: AW169 PW210A1 Gross Weight 4600 kg AP 7.0 Configuration Level Flyover EPNL (EPNdB) Take Off EPNL (EPNdB) Approach EPNL (EPNdB) Clean aircraft No external kits installed 100% NR 100% NR 100% NR 88.8 86.9 96.0 Model: AW169 PW210A1 Gross Weight 4800 kg AP 7.0 Configuration Level Flyover EPNL Take Off EPNL Approach EPNL Clean aircraft No external kits installed 100% NR 100% NR 100% NR 88.8 86.9 96.0 NOTE 6 The Model AW169 incorporates an integrated avionics system using software-based line replaceable units (LRU) which share a digital signal transmission bus. The software configuration of the AW169, as delivered from production, is critical to the proper operation of the avionics and cockpit instrumentation system. Modification to the LRU software supplied with the AW169, replacement of an LRU with a different LRU, addition of new LRU, or alteration of an LRU interface could adversely affect the airworthiness of the certified software. No changes to the integrated avionics system should be made without coordination with the FAA Aircraft Certification Office (ACO) having jurisdiction over the modifier. NOTE 7 The hydraulic fluids must conform to MIL-PRF-83282 or MIL-PRF-87257 n - see LIMITATIONS Section of the approved Rotorcraft Flight Manual. R00007RD 16 Rev.3 NOTE 8 Any changes to the type design of this helicopter by means of an amended type certificate (TC), supplemental type certificate (STC), or amended STC, requiring instructions for continued airworthiness (ICA's) must be submitted thru the project aircraft certification office (ACO) for review and acceptance by the Fort Worth -Aircraft Evaluation Group (FTW-AEG) Flight Standards District Office (FSDO) prior to the aircraft delivery, or upon issuance of the first standard airworthiness certificate for the affected aircraft, whichever occurs later as prescribed by Title 14 CFR 21.50. Type design changes by means of a field approval that require ICA's must have those ICA's reviewed by the field approving FSDO. NOTE 9 The AW169 name identifies production batches manufactured in conformity with the same Type Design. Applicable serial numbers: • S/N 69005: and subsequent, manufactured by Leonardo S.p.a. in Italy. NOTE 10 Night Vision Goggle operations may be granted by the local civil aviation authority if the rotorcraft is operated according to the limitations and procedures of RFM 169F0290X001Supplement 16. The rotorcraft configuration involving internal and external light emitting and reflecting equipment approved for use with NVGs is described in Report 169F3360A001 “AW169 NVG Compatibility Reference Handbook”. R00007RD 17 Rev.3 Acronyms and Abbreviations AEO All Engines Operative CFR Code of Federal Regulations Doc. Document EASA European Union Aviation Safety Agency FAA Federal Aviation Administration ICA Instructions for Continued Airworthiness ICAO International Civil Aviation Organisation IFR Instrument Flight Rules ISA International Standard Atmosphere LH Left Hand min. minute No. Number NVG Night Vision Goggle P/N Part Number OAT Outside Air Temperature OEI One Engine Inoperative RFM Rotorcraft Flight Manual RH Right Hand sec. second SL Sea Level STA Station VNE Velocity Never Exceed VFR Visual Flight Rules ….END….