TCDS A20EA

Page No. 1 2 3 4 5 Rev. No. 6 1 1 1 5 DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION TYPE CERTIFICATE DATA SHEET NO. A20EA This data sheet, which is a part of type certificate No. A20EA 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 De Havilland Aircraft of Canada Limited 4100 Westwinds Drive NE Calgary, Alberta Canada T3J 4L2 Type Certificate Holder Record Viking Air Limited 9574 Hampden Road Sidney, British Columbia Canada V8L 5V5 Bombardier Inc. Regional Aircraft 123 Garratt Boulevard Downsview Ontario Canada M3K 1Y5 I - Model DHC-7-1 (Formerly DHC-7) (Transport Category) Approved April 25, 1977 Airspeed limits (See approved Aircraft Fl ight Manual for additional information) (CAS) direct vision (D.V.) windows Maximum weights Ramp 41,300 lb. Takeoff 41,000 lb. Landing 39,000 lb. Zero Fuel 35,500 lb. C.G. range Landing Gear Extended Forward limit 25 percent MAC (Sta. 447.54) all weights Aft limit 40 percent MAC (Sta. 465.22) all weights A20EA Revision 6 De Havilland DHC-7-1 DHC-7-100 DHC-7-101 DHC-7-102 DHC-7-103 October 19, 2026 m.p.h. knots Vmo (Max. Operating) 270 235 Vb (Design Speed for max. gust intensit y 199 173 Va (Maneuvering) 179 155 Vmc (Minimum Control Speed for takeoff and climb) 25° flap 75 65 17° flap 79 69 Vfe (Flaps Extended) 17° deflection 173 150 25° deflection 138 120 45° defection 127 110 Vle (Landing Gear Extended) 190 165 Vlo (Landing Gear Operation) 173 150 Maximum Speed for opening 189 164 2 A20EA Serial Nos. eligible S/N 1 and 2 Approved Publications Aircraft Definition AEROC 7.1.AC.1 Section 3 Flight Manual PSM 1-7-1A Structural Component Life and Inspection Requirements PSM 1-7-2 Chapter 5 II - Model DHC-7-100 (Transport Category) Approved November 9, 1977 DHC-7-101 (Transport Category) Approved May 2, 1979 DHC-7-102 (Transport Category) Approved May 2, 1979 DHC-7-103 (Transport Category) Approved May 2, 1979 The DHC-7-101 is the same as the DHC-7-100 except that a large cargo door in the forward left hand side of the cabin has replaced the Type III emergency exit in that position. Two additional Type III exits are located on each side at approximately the mid cabin. A cargo/pa ssenger interior with a structurally strengthened cabin floor is standard. The DHC-7-103 is the same as the DHC-7-102 except for those same differences between the DHC-7-101 and DHC-7-100 stated above. (See Note 4 for conversion from -100 to -102 or from -101 to -103.) Airspeed limits (See approved Aircraft Flight Manual for add itional information) (CAS) m.p.h. knots Vmo (Max. Operating) 270 235 Vb (Design Speed for max. 201 175 gust intensity) Va (Maneuvering) 179 155 Vmc (Minimum Control Speed for takeoff and climb) 25° flap 75 65 15° flap 79 69 Vfe (Flaps Extended) 15° deflection 173 150 25° deflection 138 120 45° deflection 127 110 Vle (Landing Gear Extended) 190 165 Vlo (Landing Gear Operation) 173 150 Maximum Speed for opening 189 164 direct vision (D.V.) windows Maximum weights DHC-7-100/-101 DHC-7-102/-103 Ramp 43,300 lb. 44,100 lb. Takeoff 43,000 lb. 44,000 lb. Landing 41,000 lb. 42,000 lb. Zero Fuel 39,000 lb. 39,000 lb. C.G. range DHC-7-100/- 101 (Landing Gear Weight Forward Limits Aft. Limits Extended) lb. % MAC (Sta.) % MAC (Sta.) all weights to 42,000 25% (447.54) 43% (468.75) 42,000 to 43,000 Linear variation from 25 to 26% (448.72) 43% (468.75) 43,000 to 43,300 26% ( 448.72) 43% (468.75) DHC-7-102/-103 all weights to 42,000 25% (447.54) 43% (468.75) 42,000 to 44,000 Linear variation from 25 to 27% (449.90) 43% (468.75) 44,100 27% (449.90) 43% (468.75) Serial Nos. eligible S/N 3 and subsequent (See Note 4) 3 A20EA Approved DHC-7-100/-101 DHC-7-102/-103 Publications Aircraft Definition AEROC 7.1.AC.1 AEROC 7.1.AC.1 Section 4 Section 5 Flight Manual PSM 1-71-1A* PSM-17-1A Structural Component Life and Inspection Requirements PSM 1-7-2 Chapter 5 PSM 1-7- 2 Chapter 5 *Note: Add Supplement 8 for DHC-7-101/- 103 airplanes (cargo/passenger interior) DATA PERTINENT TO ALL MODELS EXCEPT AS INDICATED Engines 4-Pratt and Whitney Aircraft of Canada, Limited PT6A-50 (T.C. E4EA) Fuel Fuels conforming to Pratt and Whitney Aircraft of Canada Limited Specification No. PWA 522 Kerosene Type Jet A, Jet A-1, JP-4, JP-5, or Jet B. Oil Pratt and Whitney Aircraft of Canada approved oils to conform to Specification No. PWA-521 Type II. Engine limits Engine Rating (Power Limits) Takeoff (5 min.) 1120 s.h.p. Max. Continuous 973 s.h.p. Temperature Limits (Inter Turbine) Takeoff 1472°F (800°C) Max. Continuous 1472°F (800°C) Torque Limits Takeoff 4860 ft. -lb. Max. Continuous 4860 ft. -lb. Gas Generator Limits Takeoff (5 min.) 38,500 r.p.m. (102.7 percent) Max. Continuous 38, 100 r.p.m. (101.6 percent) Power Turbine Output Shaft r.p.m. Takeoff 1210 r.p.m. Max. Continuous 1210 r.p.m. Propeller and 4-Hamilton Standard 24 PF-305 propeller limits Blade PFA12B1-9B Diameter 11 ft. 3 in. nominal Pitch settings at 0.75 radius: Feather 78.0° Flight fine 6.5° Ground fine - 8.5° Full reverse -18.7° Propeller (Np) - Takeoff 1210 r.p.m. Max. Continuous 1210 r.p.m. Datum Station 0 is 248.0 inches forward of the jig point marked by a plate located on airplane center line on the underside of the fuselage. Mean aerodynamic chord (MAC) 117.84 in. (L eading edge of M.A.C. + 418.08 in.) 4 A20EA Leveling means Longitudinal: Pads on fore an d aft faces of right hand aft door opening. Lateral: Levelling bar on forward face of bulkhead (Station 147.0 in. in nose compartment). Minimum crew 2 - (pilot and copilot) Maximum occupants DHC-7-100/-102 (Passenger Carrying Interior) Not to exceed 59, including 2 pilots, 2 attendants and 1 check pilot. (54 passengers when fitted with an approved interior). DHC-7-101/-103 (Cargo/Passenger Interior) Not to exceed 55, including 2 pilots, 2 attendants and 1 check pilot. (50 passengers when fitted with an approved interior). Aft baggage or S/N 1 and Subsequent; 2200 lb. with Mod. 7/1156 incorporated and cargo limitations moment arm +735.0 fo r uniformly distributed loading. S/N 3 and Subsequent; 2800 lb. with S007036 interior incorporated. Floor Loading (max.) Aisles Under Seats DHC-7-1/-100/-102 75 p.s.f. 37.5 p.s.f. DHC-7-101/-103 200 p.s.f. 200 p.s.f. Fuel capacity U.S. Gal. Imp. Gal. Weight-lb. Moment Arm-in. TOTAL 2 inner tanks (ea). 315 262 2142 +462.0 2 outer tanks (ea). 425 354 2890 +462.0 Total 1480 1232 10,064 +462.0 UNUSABLE 2 inner tanks (ea). 4.6 3.8 31 +462.0 2 inner tanks (ea). 5.6 4.7 38 +462.0 Total 20.4 17.0 139 +462.0 Oil capacity USABLE 1.0 0.8 7.5 +396.0 (per Inboard Engine) +411.4 Outboard Engine UNUSABLE Inboard Engine 3.4 2.7 25.5 + 396.0 Outboard Engine 3.25 2.6 24.4 +411.4 Maximum operating 25,000 ft. (when supplementary breathing e uipment is provid d for all occupants). altitude 20, 400 ft. (limited by cabin pressure altitude requirements of FAR 25.841(a)). Maximum ambient temperature ISA (Sea Level) +36.6°C. (+66°F) Control surface movements See DeHavilland Report AEROC 7.2.AC.0. Section 1.3 Page 1, Issue 2. Generator limits D.C. Generators: Ground 80 percent (200 amp.) Flight 100 percent (250 amp.) A.C. Generators: Ground 15 amp. per phase at 5°C to 3 amp. per phase at 52°C (linear variation) Flight 30 amp. per phase at 5°C to 15 amp. per phase at 52°C (linear variation) Serial Nos. eligible S/N 1 and subsequent 5 A20EA Import eligibility A U.S. Airworthiness Certificate may be issued on the basis of the Canadian Department of Transport "Certificate of Airworthiness for Export" signed by or for the Minister of Transport. This form must contain the following statement: "This certifies that the aircraft described below has been manufactured in conformity with data forming the basis for the D.O.T. Aircraft Type Approval No. A-120, Issue 3, dated August 30, 1979, (FAA Type Certificate No. A20EA). Certification basis FAR Part 25 dated February 1, 1965, plus Amendments 25-1 through 25-31 inclusive. Additional FAA Requirements: (a) FAR Part 36 dated December 1, 1969, plus Amendments 36-1 through 36-5 inclusive. (b) SFAR 27 dated February 1, 1974, plus Amendments SFAR 27-1 and 27-2. (c) Special conditions No. 25-53-EA-10 dated May 7, 1973, (FAA Docket No. 12810). (1) Conventional mode of operation (2) STOL mode of operation. Date of Application for Type Approval April 30, 1972. Type Certificate A20EA issued April 25, 1977. Compliance with the following optional requirement has been established: Ice Protection FAR 25.1419 Ditching FAR 25.801 Part 26- Continued Airworthiness and Sa fety Improvements for Transport Category Airplanes: Based on § 21.101(g) for changes to TCs, applicable provisions of part 26 are included in the certification basis. For any future Part 26 amendments, the holder of this TC must demonstrate compliance with the applicable sections. Compliance has been found for 14 CFR § 26.11 (Amdt. No. 26-0) Equipment The basic required equipment as prescribed in the applicable airworthiness regulations (see Certification Basis) must be installed in the aircraft for certification. NOTE 1. (a) Current weight and balance report, including list of equipment included in the certified empty weight, and loading instructions when necessary, must be provided for each aircraft at the time of original certification. (b) System or unusable fuel, which must be included in the empty weight, is the amount of fuel required to fill the system plumbing and tank to the undrainable level (1.5 gal. total), plus unavailable fuel in the fuel tanks (18.9 gal. total). The total amount of "system fuel" 20.4 gal. total, 139 lb. (+462.0). (c) System oil, which must be included in empty weight, is the amount of oil necessary for engine lubrication and propeller operation. The tota l amount of "system oil" is as follows: 6.8 gal. (total) contained in inboard engines, 5.10 lb. (+396.0) 6.5 gal. (total contained in outboard engines, 48.8 lb. (+411.4) NOTE 2. All placards required in the approved flight ma nual must be installed in the appropriate location. NOTE 3. For models -1, -100, -101, -102, and -103 airplane s the retirement times recorded in DeHavilland Manual PSM 1-7-2 Chapter 5 must be complied with. NOTE 4. The DHC-7-100 may be converted to the -102 or the DHC-7-101 to the -103 by incorporation of the following modifications: DeHavilland Modification No. 7/1271 (Rear Fuselage), 7/1337 (Inboard Nacelle) and 7/1393 (Fore Rudder). .....END.....