TCDS R00006RD

Page No. 1 2 3 4 Rev No. 5 2 DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION R00006RD Revision 5 AutoGyro Certification Limited Calidus May 10, 2022 TYPE CERTIFICATE DATA SHEET NO. R00006RD This data sheet which is part of Type Certificate No. R00006RD, 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. AutuGyro USA II, INC transferred to RotorSport UK Ltd on August 13, 2019. AutoGyro USA, LLC transferred to AutoGyro USA II, INC on May 1, 2018. AutoGyro Calidus Gyroplane (Primary Category), Approved November 30th, 2016 by the FAA ENGINES BRP-Rotax 912ULS or BRP-Rotax 914UL turbo. FUEL Type 91-93 MOV GAS 100LL AV GAS OIL Engine, Refer to Rotax Engine Operators Manual. ENGINE LIMITS 912 ULS 914 UL Maximum rpm (5 minutes max operation) 5800 5800 Maximum continuous rpm 5500 5500 COOLANT 912 ULS 914 UL Maximum coolant temperature 120°C 248°F 120°C 248°F OIL TEMPERATURE °C °F Minimum for Starting (ground) -25 -13 Minimum before accelerating above idle 50 122 Maximum Continuous 130 266 Maximum Permissible 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 HTC: 1.720m; 3-blade; ground adjustable; composite. PROPELLER LIMITS 912 ULS 914 UL Blade pitch angle 17.9deg at 75% radius 19.1deg at 75% radius ROTOR Rotorsystem II; 8.4m diameter; red end-caps. Page 2 of 4 R00006RD ROTOR LIFE LIMIT: 2500 hours AIRSPEED LIMITS 912 ULS 914 UL (IAS) m.p.h. knots m.p.h. Knots Vne 120 104 120 104 Vne in severe turbulence 70 61 70 61 C. G. RANGE Nose datum 912 ULS and 914 UL engines mm Inches Horizontal c.g. Minimum forward of the datum 2030 79.9 Maximum forward of the datum 1895 74.6 DATUM Vertical front face of the gyroplane nose. MAXIMUM WEIGHTS lb. kg. Max. Takeoff 1102 500 Max. Landing 1102 500 Max. empty weight (912 ULS) 681 309 Max. empty weight (914 UL) 686 311 COCKPIT LOADINGS Individual seating (subject to total) lb. kg. Front seat - minimum 143 65 Front seat - maximum 275 125 Rear seat – minimum 0 0 Rear seat – maximum 265 120 Baggage allowance Max baggage per locker 4.5 2 MINIMUM CREW One (Pilot) MAXIMUM OCCUPANTS 2 (one pilot + one passenger) FUEL CAPACITY Load Weight** Usable U.S. Gal. liters lb. Kg Twin tanks 19.5 73.8 131.6 59.7 Total Unusable (drainable) Twin tanks 0.4 1.2 2.7 1.2 ** Assuming a fuel density of 6lbs/U.S. Gal. OIL CAPACITY Volume including oil cooler U.S. Qts. liters Total 3.6 3.4 MAXIMUM OPERATING ALTITUDE 10 000 ft CONTROL SURFACE MOVEMENTS Rudder deflection Defined by maximum horizontal distance between rudder lower tip and side fin: To left side fin: 700 mm 27.6 in To right side fin: 620 mm 24.4 Rotor head deflection Roll 16° total Datum: Canopy sill Pitch 24° total Datum: main wheel axis Page 3 of 4 R00006RD TYPE CERTIFICATION APPLICATION DATE March 6th, 2012 SERIAL NUMBERS ELIGIBLE US-C00428 and subsequent Note: Only gyroplanes having a prefix of “US” are eligible for a FAA Certificate of Airworthiness in the Primary Category. APPROVED PUBLICATIONS (a) Approved Rotorcraft Flight Manual (RFM), AutoGyro USA document AGUSA001, and subsequent approved revisions. (b) Product configuration Control document, AutoGyro USA document AGUSA004, and subsequent approved revisions. (c) Maintenance Manual, AutoGyro USA document AGUSA002, and subsequent approved revisions contains the Certification Maintenance Tasks, Life Limited Parts and Damage Tolerant Inspections. IMPORT ELIGIBILITY N/A CERTIFICATION BASIS 14 CFR 21.24 Amdt. 21-92 effective April 16, 2011, Issuance of Type Certificate under Primary Catorgory. For Aircraft Certification and the Powerplant Installation: Section T Light Gyroplanes, of the British Civil Airworthiness Requirements (BCAR), Issue 3, dated August 12, 2005. 14 CFR 27.853(a) and (c)(l) Arndt 27-37 Compartment Interior; §§ 23.735(a) through (c) Arndt 23-62 Brakes except that the reference to § 23.75 is replaced with Section T75 of BCAR Section T, Issue 3; §§ 27.735(a) and (c)(1) Arndt 27-21 Brakes; §§ 27.1365(b) and (c) Arndt 27-35 Electrical Cables; and §27.1561(a) 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 3, dated August 12, 2005; ASTM F2506-10 (2009), "Standard Specification for Design and Testitng of Fixed-Pitch or Ground Adjustbale Light Sport Aircraft Propellers,” paragraph 5.5 Propleller Strength and Endurance and Section 6 Tests and Inspections. Type Certification No. R00006RD issued November 30, 2016 Date of Application March 6th, 2012 FAR Part 36 effective December 1, 1969, as amended by Amendments 36-1 through 36-30. PRODUCTION BASIS Production under TC only for Serial Numbers US-C00428 and US-C00429 only. Production Certificate No. 123NE for Serial Numbers US-C00482 and up. EQUIPMENT The basic equipment as prescribed in the applicable airworthiness requirements (see Certification Basis) must be installed in the gyroplane for certification. SERVICE INFORMATION None Page 4 of 4 R00006RD 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 gyroplane 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 gyroplane. NOTE 2 All placards must be installed in accordance with the Approved Rotorcraft Flight Manual AGUSA001. NOTE 3 The gyroplane life limits and repetitive inspections for components and equipment and information essential for proper maintenance, are listed in Instructions for Continued Airworthiness (ICA) AGUSA002. These limitations may not be changed without FAA Engineering approval. ATA Equipment / System MLL 62-00-00 Rotor System II (P/N 31793) 2500 hrs 62-31-00 Rotor Main Bearing / Teeter Tower (P/N 34432) 1500 hrs - END -