TCDS A19EA

A19EA Revision 3 De Havilland TR-1 October 19, 2026 DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION TYPE CERTIFICATE DATA SHEET NO. A19EA This data sheet which is part of Type Certificate No. A19EA 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, Ltd. #9 - 9600 Canora Road Sidney, British Columbia Canada V8L 4R1 I - Model TR-1 4PCAmM (Normal Category) Approved December 16, 1976, by the FAA and October 27, 1976, by the Canadian Department of Transportation (DOT) Engine Single Teledyne Continental Tiara 6-285-C4 (Reduction gear ratio 0.5:1) Fuel 100/130 minimum grade aviation gasoline Engine Limits For all operations 2000 r.p.m. (285 hp.) Propeller and Hartzell HC-H3YF-3LF/FL-C9684- 12. Pitch setting at 30 in. station: Propeller Limits Low 19 , High 36, Reverse 11 Diameter: Maximum 84 in., Minimum 83 in. No further reduction permitted. Governor: Hartzell F-6-306 Spinner: Hartzell D-4247 Avoid continuous operation of the propeller in the following speed ranges: (a) Between 900 and 1300 propeller r.p.m. in flight (b) Between 900 and 1100 propeller r.p.m. on ground or water Airspeed Limits Vne *(neve r exceed) 180 m.p.h. 156 knots (CAS) Va (maneuvering) 120 m.p.h. 104 knots Vfe (flaps extended-takeoff) 114 m.p.h. 99 knots Vfe (landing) 94 m.p.h. 82 knots Vle (gear extended) 114 m.p.h. 99 knots Vle (floats extended) 114 m.p.h. 99 knots *Up to 10,000 ft. reducing linearly to 134 m.p.h. (116 knots) at 18,000 ft. Center of Gravity +114.17 to +123.87 at gross weights up to 3280 lb. (CG) Range +116.38 to +119.38 at gross weights of 3800 lb. Landing gear and floats extended Straight line variation between points (Moment change due to landing gear retraction +83 in.-lb.) (Distance from Datum) (Moment change due to float retraction +171 in.-lb.) Empty Weight (CG) Change None Page No. 1 2 3 4 Rev. No. 3 2 2 2 A19EA 2 Datum Forward face of bulkhead at Fuselage Station 6.4 (Located 99.35 in. forward of wing leading edge) Mean Aerodynamic Chord 72.45 in. (MAC) Leveling Means Top surface of seat rails laterally and longitudinally. Maximum Weight Minimum Crew 3800 lb. One (Pilot) Number of Seats Two at +57.25 Two at +88.05 Maximum Baggage 150 lb. at +129.6 Fuel Capacity U.S. Gal. Imp. Gal. Arm * 102 85 +129.6 Usable 93.7 78 *See NOTE 1(b) for Weight and Balance Oil Capacity U.S. Qt. Imp. Qt. Arm **9.0 7.5 +147.4 Usable 5.0 4.2 **See NOTE 1(c) for Weight and Balance Maximum Operating Altitude 18, 000 ft. Maximum Operating 90F Air Temperature Control Surface Movements Ailerons 26   2  UP Elevator 30   2  UP Flaps Rudder 26   2 LEFT 17  2  DOWN 20  2  DOWN 30  2  DOWN 26  2  RIGHT Manufacturer’s Serial Those aircraft shown to comply with Canadian DOT Aircraft Type Approval A119. Numbers The Canadian Department of Transport Ce rtificate of Airworthiness for Export endorsed as noted under “Import Eligibility” must be submitted for each individual aircraft for which application for certification is made. Import Requirements 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 DOT Approval No. A119, dated October 27, 1976, (FAA Type Certificate No. A19EA)”. Certification Basis Federal Aviation Regulatio n Part 23, dated September 14, 1969, including amendments 1 through 13 and Federal Aviation Regulation Part 36 amendments 1 through 5, appendix F Type Certification No. A19EA issued December 16, 1976, date of application for Type Certificate - June 3, 1971. 3 A19EA Equipment The basic required equipment as prescribed in the applicable airworthiness regulations (See Certification Basis) must be installed in the aircraft for certification and is given in Trident Approved Equipment List TAR-070. In addition, the following items of equipment are required: (a) Canadian DOT approved Airplane Flight Manual TAR-068 (b) Stall Warning Vane, Safe Flight P/N 1750-1 (c) Stall Warning Horn, Safe Flight P/N 284 NOTE 1. (a) Current weight and balance repor t 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. (b) The following amount of unusable fuel is included in the empty weight: 8.3 U.S. gal. (7 Imp. gal.) Arm +129.6 (c) The following amount of unusable oil is included in the empty weight: 4.0 U.S. qt. (3.3 Imp. qt.) Arm +147.4 NOTE 2: The following placards must be displayed: (a) Forward on left door. THE MARKINGS & PLACARDS INSTALLED IN THIS AIRCRAFT CONTAIN OPERATING LIMITATIONS WHICH MUST BE COMPLIED WITH WHEN OPERATING IN THE NORMAL CATEGORY. OTHER OPERATING LIMITATIONS WHICH MUST BE COMPLIED WITH WHEN OPERATING THIS AIRCRAFT IN THIS CATEGORY ARE CONTAINED IN THE AIRCRAFT FLIGHT MANUAL. THE AIRCRAFT IS APPROVED FOR FLIGHT IN DAY/NIGHT VFR/ IFR WHEN EQUIPPED IN ACCORDANCE TO AIR NAVIGATION ORDERS. FLIGHT INTO KNOWN ICING CONDITIONS PROHIBITED. AEROBATICS INCLUDING SPINS PROHIBITED. (b) Forward on left door. AIRSPEED LIMITATIONS (CAS) MAX. LANDING GEAR/FLOAT OPERATING SPEED 99 KNOTS MAX. FLAP SPEED (0 - T.O.) 99 KNOTS MAX. FLAP SPEED (T.O. - LAND) 82 KNOTS MANEUVERING SPEED 104 KNOTS MAX. STRUCTURAL CRUISE SPEED 130 KNOTS NEVER EXCEED SPEED SEA LEVEL TO 10,000 FT. 156 KNOTS (ABOVE 10,000 FT. REDUCE BY 5 KNOTS PER 1000 FT) (c) On Instrument Panel by Strobe Switch. TURN STROBE LIGHTS OFF WHEN TAXIING IN VICINITY OF OTHER AIRCRAFT AND WHEN IN CLOUD. (d) Large Print on Red Background Beside Hand Pump. EMERGENCY HYDRAULIC HANDPUMP Extend Handle to Operate (e) On Panel by Valve. ALTERNATE STATIC SOURCE ON   OFF  A19EA 4 (f) On Ceiling Near Knob. ALTERNATE ENGINE AIR PULL - ON (g) White Printing on Red Near Reverse Lever. THRUST  FORWARD LEVER REVERSE  WARNING FOR LOW SPEED WATER MANEUVERING ONLY PITCH LEVER FULL FORWARD MAX. RPM 1500 SEE FLIGHT MANUAL (h) On Ceiling by Control. HOT  COLD CABIN AIR OFF CABIN AIR IN CASE OF ON  OFF ENGINE FIRE (I) Near Fuel Quantity Indicator 78 IMPERIAL GALLONS USEABLE 7 IMPERIAL GALLONS UNUSABLE (j) White Print on Red by Knob on Instrument Panel. FUEL SHUT OFF PULL OFF (k) White Print on Red, On Pilot’s Seat. FIRE EXTINGUISHER UNDER PILOT’S SEAT (l) Inside Baggage Door BAGGAGE COMPARTMENT LOAD IN ACCORDANCE WITH WEIGHT AND BALANCE DATA MAXIMUM CAPACITY - 150 LBS. FLOOR LOADING NOT TO EXCEED 75 LB/FT  (m) On Instrument Panel NO SMOKING .....END.....