TCDS A15EU

A15EU Revision 12 De Havilland SC-7 Series 2 SC-7 Series 3 October 19, 2026 I - Model SC-7 Skyvan Series 2, Variant 200, 20 PCLM (Normal Category), Approved 1 June 1967 DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION TYPE CERTIFICATE DATA SHEET NO. A15EU This Data Sheet, which is a part of Type Certificate No. A15EU, 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 Shorts Brothers & Harland Ltd. transferred TC A15EU to Viking Air Limited on June 28, 2019. (See Note 14) Viking Air Limited transferred TC A15EU to De Havilland Aircraft of Canada Limited on August 1, 2024 Engine 2 Turbomeca Astazou XII Model H-1 (Propeller Turbine) Fuel Specifications, latest issue, (See NOTE 6) American British To prevent icing of fuel system components, all fuel in the tanks before takeoff must contain anti-icing additives in accordance with the limitations of NOTE 6, when route forecast air temperatures are less than 6°C. Engine limits Static Ratings The static ratings for the Astazou XII H-1 engine are specified under the following test conditions: International Standard Atmospheric Conditions at Sea Level. All optional air bleeds closed. Aircraft service accessory drives unloaded. 100% = 42574 rpm Jet Thermic Jet Pipe Conditions SHP (Min.) Thrust (lb.) Load (Power) RPM (Max.) % Temp. (JPT) (C) Takeoff and Maximum Cont. 630 97 100% 101.0 520 See ARB-Approved Flight Manual, Document SBH.2.4 for additional engine operating limitations. Page No. 1 2 3 4 5 6 7 8 9 Rev. No. 12 10 10 10 10 10 10 10 11 JP-1 (MIL-F-5616) o r D.Eng.RD.2482 an d 2494 JP-4 (MIL-J-5624) o r D.Eng.RD.2486 JP-5 (MIL-J-5524) o r D.Eng. RD.2488 JP-5 (MIL-J-5624) o r D.Eng.RD.2498 Page 2 of 9 A15EU Propeller and 2 Ratier-Forest Type FH 76-2-07 B reversible propellers. propeller limits Blades : 3 Type 207 Diameter : 8 ft. - 2.4 ins. Pitch setting at 0.7 radius stations: Ground fine - 5° Flight fine + 7 1/2° Feathered 84° Full Reverse - 11° Airspeed limits (IAS) Vne (Never exceed) 200 Kt. Max. Structural Cruising 178 Kt. Va (Maneuvering) 144 Kt. Vfo (Flap Operation) Takeoff 130 Kt. Landing 100 Kt. Vfe (Flaps Extended) Takeoff 130 Kt. Landing 115 Kt. Vmc (Min. Control Speed) 67 Kt. (See NOTE 8(a)) Maximum weights Takeoff 12,300 lbs. Landing 12,300 lbs. (See NOTE 7 for short range fuel tanks) Maximum baggage Baggage and/or cargo must be loaded in accordance with the Weight and Balance Supplement of the ARB-approved Flight Manual. Fuel capacity 283 U.S. Gals total in 2 tanks 276 U.S. Gals usable (See Note 1 (b) for data on system fuel) (See Note 7 for short range fuel tanks). Oil capacity 2.25 U.S. Gals/tank on each engine. 0.8 U.S. Gals/tank usable Total capacity 4.5 U.S. Gals Total usable = 1.6 U.S. Gals (5.3 pints/Engine) (See NOTE 1 (b) for data on system oil) Other operating Aircraft shall be operated in compliance with the Operating limitations Limitations specified in the ARB-Approved Aircraft Flight Manual Doc. No. SBH/2.4. Control surface movements I - Model SC-7 Skyvan Series 2, Variant 200 (cont'd) Elevator Up 35° Down 12° Elevator Trim Tab Up 11-3/4° Down 16° Rudder Right 30° Left 30° Rudder Trim Tab Right 21° Left 24 1/4° Aileron Up 30° Down 15° Aileron Trim Tab Up 44-3/4° Down 28-3/4° Flaps Inner and Outer Down Landing 45° Down Take Off 18° (See NOTE 8 (b)) Page 3 of 9 A15EU (The Series 3 is similar to the Series 2 except for powerplant installation and increased fuel capacity.) Engine 2 Garrett AiResearch Model TPE 331-2-201A (Propeller Turbine) Fuel Specifications, latest issue, (See NOTE 6) American British Canadian MIL-F-5616-1, Grade JP-1 D.Eng.RD.2482 Arctic Diesel MIL-T-5624G-1, Grade JP-4 D.Eng.RD.2486 CPW-46 Rev. A MIL-T-5624G-1, Grade JP-5 D.Eng.RD.2494 (equivalent to MIL-F-46005A (MR)-1, AiResearch Mfg. Co., Types I and II of Arizona-Spec. ASTM D1655-68T, Types Jet A EMS 53100) and Jet A-1 ASTM D1655-68T, Type Jet B Engine limits Static Ratings The static ratings for the Garrett TPE 331-2-201A engine are specified under the following test conditions: U.S. Standard Atmospheric Conditions at Sea-Level. All optional air bleeds closed. Aircraft service accessory drives unloaded. 100% = 41730 rpm Compensated ESHP SHP Net Thrust Prop Shaft Measured Exhaust Gas Conditions (Min.) (Min .) lb. (Min.) RPM Temp.C (Max) Takeoff (5 min.) and Max. Cont. 755 715 102 2000 578 See ARB-Approved Flight Manual, Document SBH.2.5 for additional engine operating limitations. Propeller and 2 Hartzell HC-B3TN-5C reversible propellers propeller limits Blades : 3 Type T 10282 HB Diameter : 8 ft. - 6 ins. Pitch setting at 30 in. radius stations: Ground fine - 2 1/2° Flight fine + 9 1/4° Feathered 85° Full Reverse - 6° Airspeed limits (IAS) Vne (Never exceed) 200 Kt. (Pre.Mod.1019 only) Vno (Normal Operating) 173 Kt. (Pre.Mod.1019 only) Vmo (Maximum Operating) 173 Kt . (Post Mod.1019, See NOTE 12) Va (Maneuvering) 140 Kt. Vfo (Flap Operation) Takeoff 128 Kt. Landing 98 Kt. Vfe (Flaps Extended) Takeoff 128 Kt. Landing 110 Kt. Vmc (Min. Control Speed) 65 Kt. Maximum weights Takeoff 12,500 Landing 12,500 lbs. II - Model SC-7 Skyvan Series 3, Variant 200, 20 PCLM (Normal Category), Approved June 7, 1968 Page 4 of 9 A15EU Maximum baggage Baggage and/or cargo must be loaded in accordance with the Weight and Balance Supplement of the ARB-approved Flight Manual. Fuel capacity 354 U.S. Gals total in 2 tanks 348 U.S. Gals usable (See NOTE 1 (b) for data on system fuel) Oil capacity 1.75 U.S. Gals/tank on each engine. 0.3 U.S. Gals/tank usable Total capacity 3.5 U.S. Gals Total usable 0.6 U.S. Gals (See NOTE 1 (b) for data on system oil) Other operating Aircraft shall be operated in compliance with the Operating Limitations specified limitations in the ARB-Approved Aircraft Flight Manual Document No. SBH/2.5. Control surface movements Elevato r Up 35° Down 12° Elevator Trim Tab Up 4° Down 5° Rudder Right 30° Left 30° Rudder Trim Tab Right 17° Left 21° Aileron Up 30° Down 15° Aileron Trim Tab Up 44-3/4° Down 28-3/4° Flaps Inne r and Outer Down Landing 50° Down Take Off 18° DATA PERTINENT TO ALL MODELS C.G. Limits (See NOTE 10.) Datum Located on center line of aircraft vertical ly below leading edge of wing, which is at Sta. 152. Horizontal moment arms to the rear of the datum are positive. Standard mean chord (SMC) 70.0 ins. Leading edge of SM C is coincident with wing leading edge. Standard Mean Chord is defined by the wing area divided by wing span, where the wing area includes that area of the fuselage enclosed by the leading and trailing edges of the wing projected to the center line of the airplane. Leveling means Internal datum plates are fitted, 2 on front spar frame and 1 on rear spar frame. Minimum crew 1 pilot unless otherw ise specified by operating rules. Maximum passengers 20 Maximum operating 20,000 ft. when supplemental oxygen is provided for the crew and altitude passengers in accordance with the applicable operating rules. Serial Nos. eligible The United King dom Certificate of Airworthiness for Export, endorsed as noted below under Import Requirements, must be submitted for each individual aircraft for which application for FAA Airworthiness Certification is made. II - Model SC-7 Skyvan Series 3, Variant 200 (cont'd) Forward Limit Aft of Datum (In.) % SMC 10 14.30 Aft Limit Aft of Datum (In.) % SMC 22.4 32.0 Page 5 of 9 A15EU Certification basis FAR 21.29. FAR Pa rt 23 effective February 1, 1965 including Amendments 23-1, 23-2, 23-3, plus Special Conditions notified by the U.S. Government to the Government of the United Kingdom and Northern Ireland in FAA letters of April 1, 1966 and October 19, 1966. Type Certificate A15EU issued June 1, 1967. Date of Application for Type Certificate: February 17, 1966. The Series 3 airplane type design with the following modifications incorporated was approved in accordance with Special Federal Aviation Regulation No. 23 on 26 June 1970. 1. Mod. 970 or 971 : Addition of Rear Passenger Doors (2). 2. Mod. 1019 : Revised A.S.I. marking for Vmo. 3. Mod. 1042 : Alternate Static Source in S2 Static System. 4. ARB Approved Flight Manual Doc. No. SBH.2.5, Amdts. G/5, G/6, and G/7. The United Kingdom Civil Aviation Authority originally type certificated this aircraft under its type certificate. The FAA validated this product under U.S. Type Certificate Number A15EU. Effective September 28, 2003, the European Aviation Safety Agency (EASA) began oversight of this product on behalf of the United Kingdom. Currently there is not an EASA TCDS number for this airplane. Import requirements The FAA can issue a U.S. airworthin ess certificate based on an NAA Export Certificate of Airworthiness (Export C of A) signed by a representative of the United Kingdom Civil Aviation Authority on behalf of the European Community. The Export C of A should contain the following statement: ‘The aircraft covered by this certificate has been examined, tested, and found to comply with U.S. airworthiness regulations 14 CFR Federal Aviation Regulations Part 23, effective February 1, 1965 including Amendments 23-1, 23- 2 and 23-3 plus Special Conditions notified by the U.S. Government to the Government of the United Kingdom and Northern Ireland in their letters April 1, 1966 and October 19, 1966 under U.S. Type Certificate No. A15EU and to be in a condition for safe operation.’ Service Information Each of the documents listed below mu st state that it is approved by the European Aviation Safety Agency (EASA) or – for approvals made before September 28, 2003 – by the Air Registration Board Through the manufacturers ARB Approval, Ref: AD/1023/45, or the United Kingdom Civil Aviation Authority. • Service bulletins, • Structural repair manuals, • Vendor manuals, • Aircraft flight manuals, and • Overhaul and maintenance manuals. The FAA accepts such documents and considers them FAA-approved for type design data only unless one of the following conditions exists: • The documents change the limitations, performance, or procedures of the FAA approved manuals; or • The documents make an acoustical or emissions changes to this product’s U.S. type certificate as defined in 14 CFR § 21.93. The FAA uses the post type validation proce dures to approve these documents. The FAA may delegate on case-by-case to EASA to approve on behalf of the FAA for the U.S. type certificate. If this is the case it will be noted on the document. Page 6 of 9 A15EU Equipment The basic required equipment as prescribed in the applicable airworthiness regulations (see Certification Basis) must be installed in the aircraft for certification. For Series 2 aircraft: See SBH pub lication reference SC/-SVE-1 details. For Series 3 aircraft: See SBH pub lication reference SC7-EAS/1 details. In addition the following items of equipment are required:- (a) Stall Warning Indicator (Safe Flight Ltd. Type No. 165). (b) ARB Approved Flight Manual Doc. No. SBH.2.4 (for Series 2 aircraft). (c) ARB Approved Flight Manual Doc. No. SBH.2.5 (for Series 3 aircraft). NOTES: NOTE 1. (a) Current weight and balance report including list of equipment included in certified 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). (b) "Unusable Fuel and System Oil" and all hydraulic fluid must be included in the certified empty weight. Unusable fuel is that quantity of fuel in the system and in the tanks which is unavailable to the engine under critical flight conditions as defined in FAR. This unusable fuel includes "system fuel" which is defined as the quantity required to fill the system and tanks to the tank outlet level when the airplane is in the ground level altitude. The fuel gauges are calibrated with the unusable fuel level as the zero datum. Th e total amount of fuel is as follows: Usable Fuel Unusable Fuel (@ 6.5 lb./U.S. Gal.) (@ 6.5 lb/U.S. Gal.) Series 2 aircraft: 1794 lb 24 lb (This excludes 14 lb undrainable fuel plus 6 lb. for 1359 lb (with short range fuel zeroing fuel gauges. tanks Mod. 136) Series 3 aircraft: 2262 lb 20 lb (This excludes 14 lb undrainable fuel plus 6 lb for zeroing fuel gauges) System Oil is that amount of oil required to fill the oil systems and engine sumps up to the sump outlet to the engines. The oil capacities shown in this specification include only usable oil. Dipstick readings indicate the amount of usable oil. NOTE 2. All placards required in the Limitations Section of ARB-approved Airplane Flight Manual must be installed in the appropriate location. NOTE 3. The service life limits for aircraft structural parts wh ich are fatigue critical are listed in the Approved Airplane Maintenance Manuals S.B. & H. Publication SC-7-AMM-1 for Series 2 aircraft and S.B. & H. Publication SC-7-AMM-3 for Series 3 aircraft. NOTE 4. Each individual Airplane must be fitted with a placar d which specifies approved types of operation (such as VFR, IFR, Day or Night) to which the airplane is limited by the equipment installed. NOTE 5. No load shall be placed on the rear door. NOTE 6. Fuel Additives Only the following additives may be used with the specified fuels: Series 2 aircraft:- Anti-icing additives to MIL-L-2768D (or D.Eng. R.D.2451) provided that the concentration does not exceed 0.15% by volume. Anti-static additive Shell ASA 3 in concentrations not exceeding 0.75 ppm in kerosene or 0.60 ppm in wide cut fuel. The following anti-icing additives comply with approved specifications: Page 7 of 9 A15EU Phillips PFA 55MB Hoffman - Taff Inc. PRIST fuel additive. Shell - Max and BP Limited fuel additive MG 98/2A Concentration by volume of fuel in aircraft tanks will be within the following limits: Minimum 0.035% Maximum 0.15% Series 3 aircraft:- The following additives may be used with the specified fuels: a) Anti-static additive Shell ASA 3 in concentrations not exceeding 1.0 ppm. b) MIL-I-27686D Inhibitor Fuel System Icing in amounts not to exceed 0.15% by volume. NOTE 7. For Series 2 aircraft with M odification 136 "Introduction of short range fuel tank" embodied, the following apply:- Maximum Weights: Take-off 12,020 lb Landing 12,020 lb Fuel Capacity: 216 U.S. Gals. total in 2 tanks 209 U.S. Gals. usable NOTE 8. For Series 2 aircraft with incorporation of: Modification 196 - Introduction of drooped leading edge inboard of engine nacelle Modification 251 & Introduction of airframe fluid de-icing system 252 Modification 336 Increase maximum flap angle to 50° the following apply: (a) Airspeed Limits Vfo (Flap Operation) Landing 99 kt. Vfe (Flap extended) Landing 112 kt. Vmc (Minimum Control Speed) 71 kt. (b) Control Surface Movement Flaps inner and outer 50° down landing. NOTE 9. Compliance has been demonstrated for operation into known or predicted icing conditions for airplanes that have Goodrich de-icing boots or T.K.S. fluid de-icing system installed on the leading edges of the wing, stabilizer and fin. NOTE 10. For Series 3 aircraft with M odification No. 837 incorporated, which alters the elevator trim tab movement, the following apply: Control Surface Movement Elevator trim tab 7° up 5° down C.G. Limits (+10 in) to (+25 in) NOTE 11. For series 3 aircraft with incorporation of:- Modification 269 : Strengthened rear fuselage longerons Modification 295 : Alteration to door locking structure Modification 1012 : Flight Limitations Pla card/Rear freight door open or removed. These aircraft are cleared for flight with the rear freight door opened or removed in accordance with the Limitations and Procedures contained in the relevant Flight Manual supplement No. 2 Issue 4, to Doc. No. SBH. 2.5. NOTE 12. For Series 3 aircraft with incorporation of:- Modification 1019 : Revised A.S.I. Color Markings the following applies: Airspeed Limits. Vne (Never Exceed Speed) and the Maximum Structural Cruising Speed are replaced by Vmo (Maximum Operating Limit Speed) which is established as 173 kts. Page 8 of 9 A15EU NOTE 13. SKYVAN 3 Series VARIANT 100 (U.K.) CONVERSION TO VARIANT 200 (U.S.A.) The following lists additions, deletions, and changes required to convert a Variant 100 Skyvan, to a Variant 200 Skyvan. 1) Flight Deck Entrance Door Barrier Barriers to be fitted to Port and Starboard Flight Deck Doors, in accordance with DRG SC7-10-1743/4. (No serv ice bulletin available.) 2) Mod 1638 Ditching Hatch Ditching Hatch required in roof of flight deck. (No service bulletin available but Mod Covers Instructions for Retro-Fit). 3) Mod 993 A.S.I. Limitation Placard Existing A.S.I. Limitation Placard on ID Panel to be replaced with A.S.I. Limitation Placard SC7-18-5409. (Service Bulletin 31-51 applies.) 4) Mod 1114 Operations Placard Existing Operations Placard SC7-18-410 on ID panel to be replaced with Placard SC7-18-5771. (Service Bulletin 11-58 applies.) 5) Mod 1514 Engine Fuel Purge System To conform with U.S.A. environmental protection agency fuel venting requirements (if applicable) embody Shorts Service Bulletin 73-50, also Airsearch Bulletin TPE 331-73-0035 will be required to be embodied concurrently. 6) Altimeter Replace milibar scale with inches hg in accordance with one of the following modifications. Mod 848 - Weston Type 22-374A-01-2 Mod 1439 - EDO Aire Type 22-374A-2 Mod 1671 - Aerosonic Type 10173-01467 (dual scale) NOTE. Altimeter panel cutouts and pipe ends may require alterations, refer to Drawing called for on Respective Modifications. (N o Service Bulletins available.) 7) 30 Flap Position (Mod 972) Delete 30 flap position as follows: Refer to Drawing SC7-45-3549 Remove flap gate SC7-45-5079 (Item 2) Remove label SC7-18-5434 (Item 13) SC7-18-5433 (Item 14) Removel label or SC7-18-5642 (Item 15) Fit flap gate SC7-45-3507 (Item 1) Fit label SC7-45-3523 (Item 11) Fit label SC7-45-3522 (Item 12) Refer to DRG SC7-80-5000 (Installation of IP Panel) Delete 30 flap position mark introduced by Drg SC7-80-5298 (Item 26) from the flap indicator gauge. Gauge now meets the requirements of DRG SC7-80-5298 (Item 22). Flap Detent (18  Position) It is not a requirement to reinstate the detent at the 18 flap position, which was deleted as part of Mod 972. Page 9 of 9 A15EU 8) Registration Plate Existing manufacturers plate SC7-18-5363 (B.C.A.R.) to be removed and replaced with plate conforming to the requirements of Drawing SC7-18-5354 (FAA). 9) Flight Manual Existing flight manual to be returned when actions 1 to 8 are completed. CAA to issue new flight manual (Doc SBH 2.5). NOTE 14. The TC transfer from Shorts Brothers & Harland Limited (Shorts Brothers) to Viking Air Limited is also a state of design change from the European Aviation Safety Agency (EASA) to Transport Canada (TCCA). .....END.....