TCDS 4A23

Page No. 1 2 3 Rev. No. 2 - 1 FEDERAL AVIATION AGENCY 4A23 Revision 2 Dollar Solent Mark III March 4 , 2010 TYPE CERTIFICATE DATA SHEET NO.4A23 This data sheet which is a part of type certificate No. 4A 23 prescribes conditions and limita tions under which the product for which the type certificate was issued meets the airworthiness requirements of the Civil Air Regulations. Type Certificate Holder Dollar Associates, Inc. 311 California St. San Francisco, California I - Model Short Brothers and Harland Limited Solent Mark III, approved October 29, 1958. Engines 4 Bristol Hercules 637V 14 Cylinder Two Row Radial Sleeve Valve Engine inco rporating a single speed supercharger and torque meter type reduction gear (.444 to 1) (See NOTE 4.) Fuel 100/130 min. grade aviation gasoline Engine limits MP H P RPM (in.Hg.) Alt. Maximum continuous at: 1590 2500 43.75 5300 Critical alt. sea level 1525 2500 43.75 S.L. Takeoff (5 min.) at: 1780 2800 46.25 6500 Critical alt. sea level 1690 2800 46.25 S.L. Propeller and 4 DeHavilland 4-Blade propeller limits (a) PD or DC 108/446/1 (b) PD or DC 108/446/2 Hub 4/4000/6 Blades PPR 1241783A-78-1 and PPR 1941783A-78-1 (See NOTE 5) Diameter: Not over 153 in., not under 147 in. Pitch settings at 42 in.sta.: Feathered 92°, Low 27° Airspeed limits Vne (Never exceed) 270 m.p.h. (234 knots) Vno (Normal operating) 220 m.p.h. (191 knots) Va (Maneuvering) 180 m.p.h. (156 knots) Vfe (Flaps extended) 1/3 down 184 m.p.h. (160 knots) 2/3 down 173 m.p.h. (150 knots) Full 162 m.p.h. (141 knots) C.G. range (+408.22) (27.0% MA C) to (+417.65) (32.0% MAC) Datum 400 in. forward of manufacturer's datum id entification metal plate on top surface of hull. MAC 188.52 in. Leading edge of MAC at (+396.0) Leveling means Leveling lugs in tail cone area. Maximum weight 76,200 lb. (Takeoff and landing) Minimum crew Two - pilot and co-pilot (+228.5) No. seats 43 (South Pacific Airlines Report No. 14) Strength of compartment floors gove rns other interior arrangements. Maximum baggage 7060 lb. total Forward hold 3520 lb. (+128.0) Bullion hold 1440 lb. (+163.4) Lower rear 1200 lb. (+809.2) Upper rear 900 lb. (+858.4) Fuel capacity 3168 gal. 12 tanks (6 per wing) Tank Nos. 1 & 2 418 gal. each (+406.8) Tank Nos. 2 & 3 635 gal. each (+398.3) Aux. A Tank Nos. 1 & 4 89 gal. each (+422.0) Aux. B Tank Nos. 1 & 4 116 gal. each (+419.0) Aux. C Tank Nos. 1 & 4 157 gal. each (+411.2) Aux. Tank Nos. 2 & 3 169 gal. each (+462.4) (See NOTE 6 for draining instructions) Oil capacity 144 gal. (36 gal./nacelle (+392.8) Max. operating altitude None established Control surface movements Rudder Right 14° Left 14° Wing flaps 25° Elevator Up 17.8° Down 18.1° Elevator trim tab Up 13.5° Down 13.3° Elevator anti-balance Up 9° Down 9° Aileron RH Up 17.5° Down 17.6° Aileron LH Up 17.8° Down 17.6° Aileron trim tab RH Up 8.8° Down 8.5° Aileron trim tab LH Up 9° Down 9.5° Aileron servo tab Up 0° Down 0° Serial Nos. eligible S1295 and all Short Brothe rs and Harland Limited Solent Mark III Aircraft. Certification basis British Civil Airworthin ess Requirements in effect on June 11, 1946 plus following CAR 4b requirement s in effect on November 12, 1947: 4b.12 Performance, 4b.13 Flight Characteristics 4b.25 Water Loads, 4b.4400 Cooling tests (Hot day) 4b.450 Induction System de-icing 4b-1 Fire Protection (November 1, 1946) 4b-6 Operating Limitations and Information Type Certificate No. 4A23 issued October 29, 1958 Date of Application for Type Certificate July 16, 1953. Production basis None. Prior to original certification of each aircraft an FAA representative must perform a detailed inspection for workmanship, mate rials, and conformity with the approved technical data, and a check of the flight characteristics. Equipment The basic required equipm ent as prescribed in the applicable airworthiness regulations (see Certification Basis) must be installed in the aircraft for certification. In addition, the following items of equipment are required: (a) FAA Approved Airplane Flight Manual (b) Inspection mirror for fire extinguisher system. Page 3 of 3 4A23 NOTE 1. Current weight and balance report including list of equipment included in certificated empty weight, and loading instructions when necessary, must be in each aircraft at the time of original certification and at all times thereafter (except in the case of operators having an approved weight control system). The certificated empty weight and corresponding center of grav ity locations must include system oil of 39.8 lb. (+378) and unusable fuel of 161 lb. (+415) with standard wing fuel tanks. NOTE 2. The following placard must be displayed in front of and in clear view of the pilot: "THIS AIRPLANE MUST BE OPERATED IN COMPLIANCE WITH THE OPERATING LIMITATIONS OF THE AIRPLANE FLIGHT MA NUAL FAA APPROVED SEPTEMBER 25, 1958." NOTE 3. Replacement of the wing spars and joining parts will be required at the expiration of the hours of total airplane operation as listed below and at the same hour intervals thereafter: Wing Spar Joint Hours Outboard front 19,000 Outboard rear 16,000 Inboard front 13,000 Inboard rear 13,000 NOTE 4. The Bristol Hercules 637V e ngines must be modified to incorporat e stiffer bevel pinion nuts per Bristol Drawing FB156796. NOTE 5. Propeller blades must have the letter "R" stamped on the shank to indicate that the shanks have been cold rolled. Blades not having this identification are not eligible for use. NOTE 6. To assure that all accumulated water in the fuel t anks in each wing will be collected in the fuel sumps, each wing must be in an elevated position (opposite wing float in the water) when the fuel sump for that wing is to be drained and all fuel tank valves must be in the "on" position during this draining. Note 7. A FAA Certificate of Airworthiness is not to be issued until compliance is found to SFAR 88. .....END.....