TCDS Q00011NY

Page No. 1 2 3 4 5 6 Rev No. 2 1 0 2 1 1 DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION Q00011NY Revision 2 AutoGyro Certification Limited Cavalon May 10, 2022 TYPE CERTIFICATE DATA SHEET NO. Q00011NY This data sheet which is part of Type Certificate No. Q00011NY 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: AutoGyro Certification Limited Poplar Farm, Prolley Moor Wentnor, Bishops Castle Shropshire UK SY9 5EJ Type Certificate Holder Record: RotorSport UK Ltd transferred to AutoGyro Certification Limited on March, 2020. Cavalon Gyroplane, Approved July 8, 2019 by the FAA ENGINES FUEL BRP-Rotax 914UL (turbocharged) or 915 iS (fuel injected and turbocharged). 91 Octane Minimum Auto Fuel 91UL AV GAS EN228 Super or Super Plus E10 (unleaded gas with 10% ethanol) 100LL AV GAS* (*requires add’l maintenance in flight manual) OIL Engine, Refer to Rotax Engine Operators Manual. ENGINE SPEED 914 UL and 915 iS Maximum rpm (5 minutes max operation) 5800 Maximum continuous rpm 5500 COOLANT 914 UL and 915 iS Maximum coolant temperature 120°C 248°F OIL TEMPERATURE 914UL 915 iS °C °F °C °F Minimum for Starting (ground) -25 -13 -20 -4 Minimum before accelerating t 50 122 50 122 Maximum Continuous 130 266 130 266 Maximum Permissible 130 266 130 266 Page 2 of 6 Q00011NY 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 MANIFOLD PRESSURE Limitation 914UL 915iS Normal operating range > 31 in HG > 1.77 in HG Maximum pressure 39.9 in HG 51.0 in HG PROPELLER 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 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 ROTOR SPEED RPM LIMITS Maximum 120 Caution 550 Minimum 200 Maximum Pre-Rotation 320 914 UL (HTC 3- blade) 915 iS (HTC 4- blade) Blade pitch angle 19 deg at 75% radius 20 deg at 75% radius Page 3 of 6 Q00011NY AIRSPEED m.p.h. knots LIMITS Vne 120 104 (IAS ) Vb (into turbulence) 80 70 C. G. RANGE Mainwheel axis datum (Empty aircarft) mm inches Horizontal c.g. Minimum forward of the datum 540 21.26 Maximum forward of the datum 325 12.8 DATUM Mainwheel axis. Refer also the the aircraft weight and balance certificate. LEVELING MEANS Center console level. MAXIMUM WEIGHTS lb. kg. Max. Takeoff 1234 560 Max. Landing 1234 560 Max. empty weight 816 371 COCKPIT LOADINGS Individual seating (subject to total, includes baggage behind seat) lb. kg. LH seat - minimum 0 0 LH seat - maximum 242 110 RH seat – minimum 143 65 RH seat – maximum 242 110 Total Maximum Weight in Cockpit (seat+baggage) 484 lb 200 kg MINIMUM CREW One (Pilot) MAXIMUM OCCUPANTS 2 (one pilot + one passenger) FUEL CAPACITY Load Weight** Usable U.S. Gal. liters lb. kg Twin tanks 26.4 100 158.4 72 Total Unusable (drainable) Twin tanks 0.79 3 4.75 2.16 ** 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 Q00011NY CONTROL SURFACE MOVEMENTS Rudder deflection Defined by maximum horizontal distance between rudder lower tip and side fin: mm in To left side fin: 630mm 24.8 To right side fin: 530mm 20.87 Rotor head deflection Roll 16° total Datum: centre console Pitch 24° total Datum: main wheel axis TYPE CERTIFICATION APPLICATION DATE April 18, 2018 SERIAL NUMBERS ELIGIBLE Manufacturer's eligible serial numbers: - RSUK-V00155 and subsequent, manufactured by AutoGyro Certification Limited in the United Kingdom, are eligible. APPROVED PUBLICATIONS (a) Approved Rotorcraft Flight Manual (RFM), RotorSport UK document RSUK0427 Rev 3.1 dated May 20, 2019 (914UL engine) and RSUK0440 Issue 1.1 dated Nov 20th 2019 (915 iS engine), and subsequent approved revisions. (b) Product Definition Document, RotorSport UK document PDD-006 Issue 1 dated May 01, 2019, and subsequent approved revisions. (c) Instructions for Continued Airworthiness, RotorSport UK document RSUK0428 Issue 1 dated May 20 2019 (914UL engine) and RSUK0441 Issue 1 dated September 20th 2019 (915 iS engine) 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 Q00011NY 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 Q00011NY 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 T967(f) 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. Q00011NY issued July 18, 2019 Date of Application April 18th, 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 RSUK0427 (914UL) or RSUK0440 (915 iS engine) Page 6 of 6 Q00011NY NOTE 3 The Type Certificate holder has demonstrated compliance with the following regulations for the Cavalon 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 914UL & 915 iS Night VFR Kit Number 2189 Configuration Option Items 1184 – Nose Landing Lights 1595 – Instrument Panel Illumination 1602 – 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 RSUK428. These limitations may not be changed without FAA Engineering approval. ATA Equipment / System MLL 62-00-00 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 NOTE 5 Additional approval is necessary for parachuting operations detailed in the approved Rotorcraft Flight Manuals listed above. -END-