TCDS TA1CH

Page No. 1 2 3 Rev. No. 2 1 - DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION TA1CH Revision 2 QUICKSILVER GT500 June 9, 2014 TYPE CERTIFICATE DATA SHEET NO. TA1CH This data sheet which is part of type certificate No. TA1CH 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: Quicksilver Aeronautics, LLC. 42214 Sarah Way Temecula, CA 92590 Type Certificate Ownership Record: Quicksilver Enterprises, Inc. P. O. Box 1572 Temecula, CA 92593 I. GT500 (Primary Category) July 26, 1994 Engine Rotax 582/48 with C Model Gear Box Reduction Ratio 3.47:1 Fuel Approved Fuel Automoble Gasoline 87 Octane Minimum (R +M/2 method) Aviation Gasoline 100LL Grade Aviation Fuel (Blue) WARNING: See Maintenance Manual for specific maintenance instructions when using Aviation Fuel. Engine Limits Maximum Takeoff Rating 64.1 hp at 6700 r.p.m. Maximum Continuous Rating 64.4 hp at 6500 r.p.m. Propeller and Warp Drive HPL-3-CP-72 Ground Adjustable Propeller Limits Hub is: Model HPL-3 Blades are: CP-72 Diameter Maximum Limit 72 in. Minimum Limit 70 in. No further reduction allowed Initial Blade Pitch Limit is 16o(minimum pitch setting) measured at the 75% station (27 inches from Center of Hub). Adjust pitch as required to allow for correct static RPM at full power. TA1CH -2- Pitch must be adjusted so that the Static Engine r.p.m. is not less than 6200 or greater than 6500 r.p.m. Maximum propeller r.p.m. 1930 Airspeed Limits Vne Never Exceed Speed 103 m.p.h. CAS Vno Max. Structural Cruising Speed 90 m.p.h. CAS VA Maneuver Speed 90 m.p.h. CAS Vfe Maximum Flap Extended Speed 78 m.p.h. CAS Center of Gravity Range (+69.0) to (+73.5) at 1000 lb. (+67.5) to (73.5) at 900 lb. or less Straight line variation between points given. Empty Weight C.G. Range None Datum Centerline of Nosewheel Leveling Means Bottom of Root Tube Maximum Weight 1000 lbs. Number of Seats 2 Foreward Seat (+29.0 to +32.0) Aft Seat (+77.0) Maximum Baggage None Fuel Capacity 16.0 Gallons (2 Wing Tanks) at (+59.4) Unusable Fuel: 2.25 gal.(with 3 gallons of fuel remaining in each tank flight time is limited to 15 minutes per tank). Oil Capacity 4.6 U.S. Fluid Pints at (+105.5) Maximum Operating Altitude 12,500 ft Control Surface Movements Wing Flaps Left Down 33o(+0o, -3o) Right Down 33o (+0o, -3o) Ailerons Up 30o ± 1.5o Down 18o ± 1.5o Rudder Left 25o ± 1.5o Right 25o ± 1.5o Elevator Up 26o ± 1.5o Down 26o ±1.5o Serial Numbers Eligible GT5 TC0101 and up Certification Basis 14 CFR § 21.24 effective September 9, 1992. Compliance with 14 CFR § 21.24 has been shown utilizing TP101 41E effective June 8, 1993. Application for Type Certificate dated June 24, 1993 Type Certificate No. TA1CH issued July 26, 1994 Production Basis Production Certificate No. 703NM TA1CH -3- Equipment The basic required equipment as prescribed in the applicable airworthiness regulations (see Certification Basis) must be installed in the aircraft for certification. In addition to the basic equipment required by the certification the FAA Approved Airplane Flight Manual dated July 25, 1994, or later FAA approved revision is required. Maintenance Maintenance and Inspection of this aircraft must be done in accordance with and Inspection Quicksilver Assembly, Maintenance and Parts Manual, (Section 9) Airworthiness Limitations DOC #932-01, Rev. -, approved September 8, 1994. Cylinder compression check: See Section 8, page 8-28 of the Assembly Maintenance and Parts Manual, DOC #932-01, Rev. -, dated September 15, 1993. NOTE 1 Current Weight and Balance report including list of equipment included in certificated empty weight and loading instructions when necessary must be provided for each aircraft at the time of original certification. The certified empty weight and corresponding center of gravity location must include unusable fuel of 13.50 lbs. at (+59.4). NOTE 2 All placards specified in the FAA Approved Airplane Flight Manual must be displayed in the airplane in the appropriate locations. NOTE 3 See Airworthiness Limitations Section 9 of the Assembly Maintenance and Parts Manual DOC #932-01 approved September 8, 1994, for service life limits on structural components and powerplant. The limitations may not be changed without FAA engineering approval. ....END.....