# TCDS 1A19: De Havilland Aircraft of Canada Limited - Type: Type certificate data sheet - Status: Current - Holder: De Havilland Aircraft of Canada Limited - Revision: 7 - Revised: October 19, 2026 - Product: Aircraft, Large Airplane - Certification basis: CAR 4b - Data sheet PDF: https://openairdocs.org/files/sha256/5f/43/5f4364d1679857dec9396b444dc441532589aaf23ab2bbede2f94abcebf2c20d - FAA DRS: https://drs.faa.gov/browse/excelExternalWindow/DRSDOCID161833947720261019133629.0001 - Page: https://openairdocs.org/tcds/1A19 ## Models (2) As the data sheet lists them. - DHC-4A (Caribou) - DHC-4 ## What the data sheet says From the PDF's text layer, line by line; tables lose their columns. The PDF is the record. ```text DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION TYPE CERTIFICATE DATA SHEET NO. 1A19 This data sheet which is a part of type certificate No. 1A 19 prescribes conditions and limitations under which the product for which the type certificate was issued meets the requirements of the Civil Air 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 8V5 Bombardier, Inc. Regional Aircraft 123 Garratt Boulevard Downsview, Ontario, Canada M3K 1Y5 I - Model DHC-4 (Transport Category), FAA Approved December 23, 1961; Canadian approval July 24, 1959 Model DHC-4A, FAA Approved July 11, 1961; Canadian approval May 19, 1961 DHC-4A same as DHC-4 except for gross weight modifications, see NOTE 4. Engines 2 P&W R-2000-7M2 o r D-5 Propeller reduction gearing 2:1 Fuel 100/130 minimum grade aviation gasoline Engine limits Low impeller gear ratio 7.15:1 HP RPM MP IN HG ALT Takeoff (5 minutes) 1450 2700 50.0 S.L. 1450 2700 49.5 3500' Maximum continuous 1200 2550 42.5 S.L. 1200 2550 41.4 7000' (Straight-line manifold-pressure variation with altitudes shown). Propellers and 2 Ham. Standard, hubs 43D50, blades 7107A-0 standard or 7107B-0 deiced. propeller limits Diameter: Max. 13' 7/8", min. allowable for repairs 12' 9-3/4". Pitch settings at 42 in. sta.: Low pitch 21°, feathered 88° Airspeed Limits (CAS) DHC-4 DHC-4A Altitude (ft.) MPH Knots MPH Knots Vne (never exceed) S.L. to 10,000 248 215 243 211 Above 10,000 ft. speed is reduced 1 mph (1 knot) per 1000 ft. Vno (normal operating) S.L. to 10,000 199 173 193 168 Above 10,000 ft. speed is reduced 3 mph (3 knots) per 1000 ft. Va (maneuvering) 140 122 139 121 Page No. 1 2 3 4 5 Rev. No. 7 - 3 5 3 1A19 Revision 7 De Havilland (Caribou) DHC-4 (Caribou) DHC-4A October 19, 2026 1A19 Page 2 of 5 Vfe (flaps extended) 0 to 15 (all engine powers) 122 107 122 107 15 to 20 (all engine powers) 112 97 112 97 20 to 30 (all engine powers) 100 85 100 85 30 to 40 (all engine powers) 90 80 90 80 Vlo (Landing gear operation) 140 122 140 122 Vle (Landing gear extended) 140 122 140 122 Vmc (Single engine min. control) 76 66 80 69 C.G. range DHC-4 Weight (lb.) 26000* Fwd. Limits (347.4) Aft Limits (357.2) 21000* or less ( 341.4) (357.2) DHC-4A 28500* (347.4) (357.2) 21000* or less ( 341.4) (357.2) *Straight-line variation between these values NOTE: The above C.G. limits are for the landing-gear-extended condition. Loadings based on this condition which fall within these limits will be satisfactory with the landing gear retracted. Datum 193.0 inches forward of jig point which is marked by a plate attached to the underside of the fuselage at the centerline. Values in parentheses ( ) are inches aft of datum. M.A.C. 120.8 inches (L.E. of M.A.C. +310.00) Leveling means Plumb-bob suspension and target bracket s are located on the port side of doorway in cabin forward bulkhead. Maximum weight DHC-4 Takeoff 26,000 lb. Landing 26,000 lb. Zero fuel and oil 26,000 lb. DHC-4A Takeoff 28,500 lb. Landing 28,500 lb. Zero fuel and oil 27,000 lb. Minimum crew 2 (Pilot and copilot) Maximum passengers 30 - See Approved Weight a nd Balance Handbook, DHC Report Aeroc 4.3.G.2 for actual numbers and location Maximum baggage Main Cabin Section Location Centroid Max. Floor (lb./sq/ft.) Capacity (lb./in.run) Total (lb.) C-1 (193.0) to (233.0) (213.0) 200 100 4000 C-2 (233.0) to (273.0) ( 253.0) 200 100 4000 C-3 (273.0) to (313.0) ( 293.0) 200 100 4000 C-4 (313.0) to (353.0) ( 333.0) 200 100 4000 C-5 (353.0) to (393.0) ( 373.0) 200 100 4000 C-6 (393.0) to (433.0) ( 413.0) 200 100 4000 C-7 (433.0) to (473.0) ( 453.0) 200 100 4000 C-8 (473.0) to (513.0) ( 493.0) 200 100 4000 C-9 (513.0) to (538.0) ( 525.5) 200 100 2500 Page 3 of 5 1A19 Fuel capacity See NOTE 1(b) regarding "Unusable fuel and system oil." Usable Fuel Imp. gal. lb. Port wing tank 345 2484 Starboard wing tank 345 2484 Totals 690 4968 (Imperial gallon equals 1.201 U.S. gal.) Oil capacity See NOTE 1(b) regardin g "Unusable fuel and system oil." Usable Fuel Maximum operating 25,000 ft. (When suitable suppl emental breathing equipment is provided for altitude passengers and crew.) Other operating Aircraft sh all be operated in compliance with the operating limitations limitations specified in the approved Airplane Flight Manual. Control surface movements Rudde r Rudder spring tab Rudder trim tab Left Left Left 20° + 1° 24° + 1° 15° + 2° - 1° Right Right Right 20° + 1° 24° + 1° 15° + 2° - 1° Stabilizer - Flaps Up Up 1° + 10' Flaps Down Up 5° + 15' Elevators Up 21° + 1° Down 10° + 1° Elevator trim tab Up 10° + 1° Down 20° + 1° Elevator spring tab Up 29° + 1° Down 20° + 1° Ailerons (Flaps Fully Down) Mid Aileron Up 20° + 1° Down 14 1/2° + 1° Outboard Aileron Up 22 1/2° + 1° Down 22 1/2° + 1° Ailerons (Flaps Fully Up) Mid Aileron Up 9 1/2° + 1° Down 5° + 1° Outboard Aileron Up 21° + 1° Down 16 1/2° + 1° Aileron trim tab Up 15° + 1° Down 15° + 1° Aileron rubber - interconnect tab Up 13° + 1° Down 13° + 1° (Flaps up, aileron neutral, no rudder spring tab wind up) Aileron geared tabs (Flaps up) Aileron up Up 3° + 1° Aileron Down Up 24° + 1° Wing Flaps (Maximum) Root & Inboard fore flap Down 40° + 1° Root & Inboard trailing flap Down fore flap angle plus 22° + 1° Mid fore flap Down 31° + 1° Outboard fore flap Down 31° + 1° Mid trailing flap Down fore flap (Mid aileron) angle plus 2 1/2° + 1° Outboard trailing flap Down fore flap (Outboard aileron) angle + 1° Serial Nos. eligible 2 and 13 and subsequent. The Canadian Department of Transport Certificate of Airworthiness for export endorsed as noted under "Import Requirement" must be submitted for each individual aircraft for which application for certification is made. See NOTE 4 regarding Model DHC-4A. Imp. gal. lb. Port tank 14.1 127 Starboard tank 14.1 127 Totals 28.2 254 1A19 Page 4 of 5 Import requirements A U.S. Airworthiness Certificate may be issued on the basis of Canada Department of Transport "Certificate of Airworthiness for Export" signed by the Controller of Civil Aviation. A "D.O.T. Canada Conformity Certificate - Military Aircraft" form, signed by the Regional Airworthiness Inspector, Department of Transport, may be used in lieu of the "Certificate of Airworthiness for Export" if the deviations listed in the "Conformity Certificate - Military Aircraft" have been modified to conform to the Type Design of the DHC-4. These forms must contain the following statement: "This certifies that the aircraft described below has been manufactured in conformity with data forming the basis for D.O.T. Type Approval No. 49 (FAA Type Certificate No. 1A19)." This certification equivalent to CAR Part 4b dated December 31, 1953 and Amendments 4b-1, 4b-2, 4b-3 and 4b-5 thereto.) Certification basis CAR 10. Type Certificate No. 1A19 issued December 23, 1960. Date of Application for Type Certificate January 16, 1957. In addition to the above, it shall be ascertained that the following Bombardier documents have been complied with on all affected DHC-4 Series aircraft, as indicated below, prior to the issuance of a U.S. Airworthiness Certificate: 1. Engineering Bulletin No. 11, dated May 31, 1961 (Applies to DHC-4 Series aircraft Serial Nos. 2 through 17). 2. Engineering Bulletin No. 12, dated December 28, 1961 (Applies to DHC-4 Series aircraft Serial Nos. 2 through 32). 3. Modification Bulletin No. 4/1099, Issue "3", dated February 23, 1962 (Applies to DHC-4 Series aircraft Serial Nos. 1 through 43, 45, 46, 47, 49, 50, 51, 53, 54, 55, 57, 58 and 59). 4. Modification Bulletin No. 4/1101, Issue "4", dated January 18, 1962 (Applies to DHC-4 Series aircraft Serial Nos. 2 through 22, 24, and 25). 5. Modification Bulletin No. 4/1143, Issue "2", dated January 11, 1962 (Applies to DHC-4 Series aircraft Serial Nos. 2 through 54, except Serial No. 23). 6. Modification Bulletin No. 4/1150, Issue "3", dated July 18, 1962 (Applies to DHC-4 Series aircraft Serial Nos. 1 through 43, 45, 46, 47, 49, 50, 51, 53, 54, 55, 57, 58, and 59). 7. Modification Bulletin No. 4/1182, Issue "2", dated July 17, 1962 (Applies to DHC-4 Series aircraft Serial Nos. 2 through 38, except Serial Nos. 23 and 34). 8. Modification Bulletin No. 4/1203, Issue "3", dated November 8, 1962 (Applies to DHC-4 Series aircraft Serial Nos. 4 through 74, except Serial Nos. 40, 56, and 73). All procedures in these documents, or an FAA-approved equivalent, shall be considered mandatory. Equipment Propeller and Propeller Accessories: 2 Hamilton Standards, Hubs 43D50-651 Blade 7107D-0 De-iced Diameter 13 ft. 7/8 in. (minimum allowable for repairs 12 ft. 9 3/4 in.) Pitch settings at 42 in. Station Reverse -8° Min. Low 21° Feathered 88° Approved equipment is shown in the Equipment List, DHC Report Aeroc 4.1.G.5. The basic required equipment 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) Stall warning system to Modification No. 4/1069 (b) Approved Airplane Flight Manual dated January 20, 1961, reissued April 28, 1961. Page 5 of 5 1A19 NOTE 1. (a) A current Weight and Balance Handbook, DHC Report Ae roc 4.3.G.2, shall be carried in the aircraft at all times. (b) Unusable fuel and system oil and all hydrau lic fluid must be included in the empty weight. Unusable fuel is that quantity of fuel in the system and in the tanks which is unavailable to the engines under critical flight conditions as defined in CAR 4b.416. The total amount of fuel is as follows: Usable fuel Unusable fuel (lb. at 7.2 lb./Imp.gal.) 46 lb. 690 Imp. gal. (4968 lb.) System oil is that amount of oil required to fill the oil system and tanks to the tank outlets to the engines. The total amount of oil is as follows: Usable Oil System Oil (lb. at 9.0 lb./Imp.gal.) 166 lb. 28.2 Imp. gal. (254 lb.) NOTE 2. "All placards required in the approved airplane flight manual must be installed in the appropriate locations." NOTE 3. Reference-Department of Tran sportation Approved Tables AIII-1 and AIII-2 contained in Appendix III Part 7 of the DHC-4 Maintenance Manual for retirement times of various aircraft components. NOTE 4. Model DHC-4 is converted to Model DHC-4A by the embodiment of modifications 4/1015, 4/1016 and 4/1017. Modifications incorporated at time of production in serial No. 23 and subsequent; the equivalent retrofit action is listed in Engineering Bulletin Series DHC-4 No. 10. .....END..... ``` ## ADs (5, in force first) - [AD 2026-13-02](https://openairdocs.org/ad/2026-13-02): Navigation · Airbus Canada Limited Partnership 18, 49-46, 80-A and 555 more. Effective Jul 1, 2026 - [AD 2023-10-02](https://openairdocs.org/ad/2023-10-02): Indicating/Recording System, Navigation · Boeing 18, 23, 35 and 1,060 more. Effective May 26, 2023 - [AD 2008-01-02](https://openairdocs.org/ad/2008-01-02): Upper engine mount · Viking Air DHC-4 and DHC-4A. Effective Jan 23, 2008 - [AD 80-26-03](https://openairdocs.org/ad/80-26-03): Magneto Drive Mechanism · Viking Air DHC-4 and DHC-4A. Effective Dec 19, 1980 - [AD 76-14-01](https://openairdocs.org/ad/76-14-01): Inboard Trailing Flap Assemblies · Viking Air DHC-4 and DHC-4A. Effective Jul 12, 1976 ## STCs approved under this data sheet (19) - [STC SA2622NM](https://openairdocs.org/stc/SA2622NM): Installation of Precise Flight Pulselite Control Unit in landing/taxi system. (767-200 B17) (DHC-8 101). Precise Flight Inc. - [STC SA01967WI](https://openairdocs.org/stc/SA01967WI): Use of GAMI G100UL High Octane Unleaded Avgas. General Aviation Modifications Inc. - [STC ST02613SE](https://openairdocs.org/stc/ST02613SE): Installation of a Supplemental Lighting System manufactured and installed. Aviation Specialties Unlimited Inc. - [STC ST01294NY](https://openairdocs.org/stc/ST01294NY): Installation of Pratt and Whitney Canada PT6A-67T engines, Hartzell HC-B5MA-3M propellers and Rotorburst Protection Shield. Pen Turbo Aviation, Inc - [STC ST01471NY](https://openairdocs.org/stc/ST01471NY): Installation of a Bleed Air System for cabin heat and de-icing system pneumatic service. Pen Turbo Aviation, Inc - [STC ST04176AT](https://openairdocs.org/stc/ST04176AT): Reduction of Maximum Zero Fuel Weight to 25,800 Pounds by decreasing Payload to 7500 pounds. Flightworks Inc - [STC SA02283SE PAGE 2](https://openairdocs.org/stc/SA02283SE%20PAGE%202): Installation of Electronics International Inc. Glass Panel Engine Monitor (with In Flight Data) CGR-30P. Electronics International Inc. - [STC SA02402SE PAGE 1](https://openairdocs.org/stc/SA02402SE%20PAGE%201): Installation of Electronics International Inc. Glass Panel Engine Monitor (with In-Flight Data) CGR-30C. Electronics International Inc. - [STC SA1315WE](https://openairdocs.org/stc/SA1315WE): Installation of Mixture Monitor (exhaust gas temperature probe, gage and selector) in accordance with Delta Products Part Lists A-192 and A-193, or in accordance with Tri-Star Corporation Mixture Monitor Installation Instructions dated December 9, 1981, or later FAA approved revision and/or Drawing List MM-127 dated November 15, 1981, or later FAA approved revision in aircraft models listed in Master Eligibility List P-80-A-6 revised March 29, 1968, copy attached, or later FAA approved revision.. Universal Corporation - [STC SA00068SE](https://openairdocs.org/stc/SA00068SE): Installation of fuel flow/pressure instruments. (W/TSIO-360-MB1). Electronics International Inc. - [STC SA01988SE](https://openairdocs.org/stc/SA01988SE): Installation of Electronics International Inc. Glass Panel Engine Monitor (with In-Flight Data) MVP-50P.. Electronics International Inc. - [STC SA00680SE](https://openairdocs.org/stc/SA00680SE): Installation of Electronics International model UBG-16 or UBG-16T bar graph engine analyzer.. Electronics International - [STC ST00292NY](https://openairdocs.org/stc/ST00292NY): Installation of Bendix/King TCAS II system.. Bombardier Completion Center Inc - [STC SA367SW](https://openairdocs.org/stc/SA367SW): Installation of Bidco products Radome and AN/APN-158 (WP-103) radar.. Rockwell Collins Inc - [STC ST01930AT](https://openairdocs.org/stc/ST01930AT): Installation of a fuselage storage tank and liquid dispersal operating mechanism for aerial firefighting.. Base Documental de la Empresa of Georgia - [STC SA1626NM PAGE 1](https://openairdocs.org/stc/SA1626NM%20PAGE%201): Installation of Electronics Int'l Digital EGT/CHT Instruments and accessories. (201 Series). Electronics International - [STC SA4302NM](https://openairdocs.org/stc/SA4302NM): Installation of Electronics Int'l digital automatic engine analyzer.. Electronics International - [STC SA691NW](https://openairdocs.org/stc/SA691NW): Installation of Sorm Bulk Liquid Cargo Takn Assembly. Sorm Inc - [STC SA13PC](https://openairdocs.org/stc/SA13PC): Installation of foldable cabin bench seats for passenger/cargo convertibility.. Air America Inc --- OpenAirDocs.org is an independent research project of [Contrail Labs](https://contraillabs.com/). It is not affiliated with the FAA or the NTSB. Source documents are U.S. government works in the public domain.