TCDS Q00010NY

Page No. 1 2 3 4 5 6 Rev No. 2 1 1 2 0 1 DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION Q00010NY Revision 2 AutoGyro Certification Limited MTO Sport 2017 May 10, 2022 TYPE CERTIFICATE DATA SHEET NO. Q00010NY This data sheet which is part of Type Certificate No. Q00010NY, prescribes conditions and limitations under which the product for which the Type Certificate was issued meets the airworthiness requirements of the Federal Aviation Regulations (FAR). Type Certificate Holder: Type Certificate Holder Record: AutoGyro Certification Limited Poplar Farm, Prolley Moor Wentnor, Bishops Castle Shropshire UK SY9 5EJ RotorSport UK Ltd transferred to AutoGyro Certification Limited on March 2020. MTOsport2017 Gyroplane, Approved July 8, 2019 by the FAA ENGINES BRP-Rotax 912ULS, BRP-Rotax 914UL turbocharged, BRP-Rotax 915 iS (fuel injected and turbocharged) FUEL OIL 91 Octane Minimum Auto Fuel 91UL AV GAS EN228 Super or Super Plus E10 (unleaded gas with 10% ethanol) 100LL AV GAS* (*requires additional maintenance in flight manual) Engine, Refer to Rotax Engine Operators Manual. ENGINE SPEED 912 ULS 914 UL 915 iS Maximum rpm (5 minutes max operation) 5800 5800 5800 Maximum continuous rpm 5500 5500 5500 COOLANT 912 ULS 914 UL 915 iS Maximum coolant temperature 120 °C 248 °F 120 °C 248 °F 120 °C 248 °F Page 2 of 6 Q00010NY OIL TEMPERATURE 912 ULS and 914 UL 915 iS °C °F °C °F Minimum for Starting (ground) -25 -13 -20 -4 Minimum before accelerating above idle 50 122 50 122 Maximum Continuous 130 266 130 266 Maximum Permissible 130 266 130 266 OIL PRESSURE Limitation Bar psi Minimum oil pressure 0.8 11.6 Normal operating range 2 to 5 29 to 72.5 Maximum oil pressure 7 101.5 Oil pressure is not regulated PROPELLER 912UL and 914UL 915 iS HTC: 1.720m; 3-blade; ground adjustable; composite. -or- HTC: 1.720m; 4-blade; ground adjustable; composite. -or- Ivoprop: DL3-68” in-flight pitch adjustable, composite Woodcomp KW-30 hydraulic in-flight pitch adjustable PROP LIMITS Ivoprop prop limits are computer controlled. Woodcomp prop limits are hydraulically controlled. ROTOR 912UL and 914UL 915 iS Rotorsystem II; 8.4m diameter, red end-caps (Rotorsystem II Not Applicable) 8.4m diameter TOPP, blue end caps 8.6m diameter TOPP, grey end caps ROTOR LIFE LIMIT: 2500 hours for all Rotor Systems. AIRSPEED m.p.h. knots LIMITS Vne 120 104 (IAS ) Vb (into turbulence) 75 65 HTC 912 ULS 914 UL 915 iS Blade pitch angle 18 deg at 75% radius 19 deg at 75% radius 20 deg at 75% radius Page 3 of 6 Q00010NY C. G. RANGE Mainwheel axis datum (Empty aircarft) mm inches 912UL and 914UL Horizontal c.g. Minimum forward of the datum 240 9.45 Maximum forward of the datum 310 12.2 915 iS Horizontal c.g. Minimum forward of the datum 190 7.48 Maximum forward of the datum 310 12.2 DATUM Mainwheel axis. Refer also to the aircraft weight and balance certificate. LEVELING MEANS Keel tube between seats set at 5deg nose down 912 ULS 914 UL & 915iS MAXIMUM WEIGHTS lb. kg. lb. kg. Max. Takeoff 1102 500 1232 560 Max. Landing 1102 500 1232 560 Max. empty weight 680 309 816 371 COCKPIT LOADINGS Individual seating (subject to total) lb. kg. Front seat - minimum 132 60 Front seat - maximum 242 110 Rear seat – minimum 0 0 Rear seat – maximum 242 110 Baggage allowance Nose locker: 22 10 Either side, front footwell, per side: 6.6 3 Either side, rear footwell, per side: 11 5 MINIMUM CREW One (Pilot) MAXIMUM OCCUPANTS 2 (one pilot + one passenger) FUEL CAPACITY Load Weight** Usable U.S. Gal. liters lb. kg Twin tanks 24.8 94 148.9 67.7 Total Unusable (drainable) Twin tanks 0.33 1.27 2.0 0.86 ** Assuming a fuel density of 6.0 lbs/U.S. Gal. OIL CAPACITY Volume including oil cooler U.S. Qts. liters Total 3.6 3.4 MAX. OPERATING 12 000 ft ALTITUDE Page 4 of 6 Q00010NY CONTROL SURFACE MOVEMENTS Rudder deflection Defined by maximum horizontal distance between rudder lower tip and side fin: To left side fin: 27 deg To right side fin: 32 deg Rotor head deflection Roll 16° total Datum: Keel tube Pitch 25° total Datum: main wheel axis TYPE CERTIFICATION APPLICATION DATE June 4th, 2018 SERIAL NUMBERS ELIGIBLE Manufacturer's eligible serial numbers: - RSUK-M01459 and subsequent, manufactured by AutoGyro Certification Limited in the United Kingdom, are eligible. APPROVED PUBLICATIONS (a) Approved Rotorcraft Flight Manual (RFM), RotorSport UK document RSUK0413 Rev 1.1 dated May 20, 2019 (912ULS and 914UL engine versions) or RSUK0442 Rev 1.1 dated Nov 20, 2019 (915 iS engine versions), and subsequent approved revisions. (b) Product Definition Document, RotorSport UK document PDD-008 Issue 1 dated November 21, 2017, and subsequent approved revisions. (c) Instructions for Continued Airworthiness, RotorSport UK document RSUK0414 Issue 1 dated October 29, 2018 (912ULS and 914UL engine versions) or RSUK0443 Rev 1.1 dated Nov 20, 2019 (915 iS engine versions), and subsequent approved revisions contains the Certification Maintenance Tasks, Life Limited Parts and Damage Tolerant Inspections. IMPORT ELIGIBILITY 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 (in the English language): “The aircraft covered by this certificate conforms to the type design approved under the U.S. Type Certificate Number Q00010NY and is found to be in a condition for safe operation.” CERTIFICATION BASIS 14 CFR 21.24 Amdt. 21-92 effective April 16, 2011, Issuance of Type Certificate under Primary Category. Page 5 of 6 Q00010NY For Aircraft Certification and the Powerplant Installation: Section T Light Gyroplanes, of the British Civil Airworthiness Requirements (BCAR), Issue 5, dated May 9, 2013 including UK ELOS for T1302(a)(2) Additional Requirements per 14 CFR Part 23 and 27: §27.337(b) Amdt 27-26 Limit Maneuvering Load Factor §27.773(a)(b) Amdt 27-50 Pilot Compartment View §27.853(a) and (c)(1) Amdt 27-37 Compartment Interior; §27.1365(b) and (c) Amdt 27-35 Electrical Cables; §27.1525 Amdt 27-21 Kinds of Operation §27.1559 Amdt 27-21 Limitations Placard §27.1561(a) Amdt 27-0 Safety Equipment, as applicable to these aircraft. For Engine Assembly Certification: ASTM F2339-06 (2009), "Standard Practice for Design and Manufacture of Reciprocating Spark Ignition Engines for Light Sport Aircraft," except paragraph Al.1.3. For Propeller Certification: Section T Light Gyroplanes, of the BCAR, Issue 5, dated May 9, 2013 ASTM F2506-10 (2009), "Standard Specification for Design and Testing of Fixed-Pitch or Ground Adjustable Light Sport Aircraft Propellers,” paragraph 5.5 Propeller Strength and Endurance and Section 6 Tests and Inspections. FAR Part 36 effective December 1, 1969, as amended by Amendments 36-1 through 36-30. Type Certification No. Q00010NY issued July 8, 2019 Date of Application June 4th, 2018 PRODUCTION BASIS See Import Eligibility above. EQUIPMENT The basic equipment as prescribed in the applicable airworthiness requirements (see Certification Basis) must be installed in the aircraft for certification. SERVICE INFORMATION None NOTE 1 (a) A current weight and balance report including the list of equipment included in the certificated empty weight, and loading instructions when necessary, must be provided for each aircraft at the time of original certification. (b) System fuel, which must be included in the empty weight, is the amount of fuel required to fill the system plumbing and tanks to the undrainable level plus unusable fuel in the fuel tanks. The weight of undrainable and unsuable fuel defined in the Fuel Capacity section must be included in the empty weight of the airplane. NOTE 2 All placards must be installed in accordance with the Approved Rotorcraft Flight Manual RSUK0413 (912ULS and 914UL engine versions) and RSUK0442 (915iS engine version) Page 6 of 6 Q00010NY NOTE 3 The Type Certificate holder has demonstrated compliance with the following regulations for the MTOSport 2017 model when the gyroplane is modified in accordance with the listed Night VFR minimum equipment kit. The low voltage warning system noted in 2.11.2 of the Flight Manual is fitted as standard. Engine 912ULS 914UL 915iS Night VFR Kit Number 2191 2190 2190 Configuration Option Items 1641 – Nose Landing Lights 1642 – Instrument Panel Illumination 1644 – Strobe & Navigation Lights Regulations §27.1381 Amdt 27-0 Instrument Lights §23.1383 Amdt 23-49 Landing Lights §27.1385 Amdt 27-0 Position Light System Installation §27.1387 Amdt 27-7 Position Light System Dihedral Angles §27.1389 Amdt 27-0 Position Light Distribution and Intensities §27.1391 Amdt 27-0 Minimum Intensities in the Horizontal Plane of Forward and Rear Position Lights §27.1393 Amdt 27-0 Minimum Intensities in the Vertical Plane of Forward and Rear Position Lights §27.1395 Amdt 27-0 Maximum Intensities in Overlapping Beams of Forward and Rear Position Lights §27.1397 Amdt 27-6 Color Specifications §27.1401 Amdt 27-10 Anticollision Light System NOTE 4 The airplane life limits and repetitive inspections for components and equipment and information essential for proper maintenance, are listed in AMM RSUK0414 (912ULS and 914UL engine) or RSUK0443 (915 iS engine). These limitations may not be changed without FAA Engineering approval. ATA Equipment / System MLL 62-00-00 Rotor System II 8.4m (P/N 31793) (912ULS or 914UL engine) or RSUK0443 (915 iS engine). Rotor System II 8.4m TOPP (P/N 38946) Rotor System II 8.6m TOPP (P/N 45329) 2500 hrs 62-31-00 Rotor Main Bearing / Teeter Tower assy (P/N 20689 / 43567) 1500 hrs -END-