# TCDS A-806: De Havilland Aircraft of Canada Limited - Type: Type certificate data sheet - Status: Current - Holder: De Havilland Aircraft of Canada Limited - Revision: 26 - Revised: October 19, 2026 - Product: Aircraft, Small Airplane - Certification basis: CAR 3, CAR 10 - Registered aircraft: 144, by the registry models matched to it (OpenAirDocs) - Data sheet PDF: https://openairdocs.org/files/sha256/23/90/239060bbf8e52234f7ba3cba5e901fb1c5a6ab4f076bc64b40e87a99f26e7287 - FAA DRS: https://drs.faa.gov/browse/excelExternalWindow/DRSDOCID194315672520261019144058.0001 - Page: https://openairdocs.org/tcds/A-806 ## Models (3) As the data sheet lists them. - DHC-2 Mk.II - DHC-2 Mk.III - DHC-2 Mk.I ## What the data sheet says Some pages are OCR from the scanned FAA data sheet. OCR can misread letters and numbers. ```text A-806 Revision 26 De Havilland DHC-2 Mk. I DHC-2 Mk. II DHC-2 Mk. III October 19, 2026 DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION AIRCRAFT SPECIFICATION NO. A-806 Type Certificate Holder De Havilland Aircraft of Canada Limited 4100 Westwinds Drive NE Calgary, Alberta Canada T3J 4L2 Type Certificate Holder Record deHavill and Aircraft of Canada, Limited transferred TC A-806 to Boeing of Canada, Ltd. (de Havilland Div.) on August 02, 1988 Boeing of Canada, Ltd. (de Havilland Div.) transferred TC A-806 to deHavilland Inc. on June 16, 1993 deHavilland Inc. transferred TC A-806 to Bombardier Inc. on January 26, 2006 Bombardier Inc. transferred TC A-806 to Viking Air Limited on January 31, 2006 Viking Air Limited transferred TC A-806 to De Havilland Aircraft of Canada Limited on August 1, 2024 I. Model DHC-2 Mk. I (L-20A - See Note 4). (Be aver) (Normal Category), approved March 12, 1948 Engine Pratt & Whitney Wasp Jr. R985 SB-3 (See Note 301(a) through 301(j) for optional engines). Fuel 80/87 octane minimum grade aviation gasoline Engine limits Maximum continuous: (Sea level) 34.5 in. Hg. 2200 rpm (400 hp) (Straight-line manifold-pressure variation with alt. to 5000 ft.) 33.5 in. Hg. 2200 rpm (400 hp) Takeoff (one minute): 36.5 in. Hg. 2300 rpm (450 hp) Sea level Propeller and propeller limits Propeller - Ha milton Standard, Counterweight, Hub Model 2D30 Blade Model 6101A-12 to -18. (Diameter 9 ft. -0 in. max.; 8 ft. - 4 in. min. allowable for repairs) Pitch setting at 42 inch station: Low 10.5 degrees; high 24 degrees. Propeller - Hamilton Standard, Hydromatic, Hub Model 22D30 Blade Model 6533A-12 to -18. (Diameter 9 ft. -0 in. max.; 8 ft. - 4 in. min. allowable for repairs) (Eligible on Pratt & Whitney R-085-AN-14B) Pitch setting at 42 inch station: low 10.5 degrees; hig 24 degrees. Constant speed governor Hamilton Standard Type 1A2-G5 or -A5 Hydromatic propeller governor Hamilton Standard Type 4B2-2. Airspeed limits (CAS) Vne (never exceed) Landplane & Skiplane Seaplane at 4650 lb. at 5100 lb. 5090 lb. (mph) (knots) (mph) (knots) (mph) (knots) 195 170 175 152 175 152 Vno (max. structure) cruising) 155 135 140 122 140 122 Vfe (flaps extended) 105 91 105 91 105 91 Page No. 1 2 3 4 5 6 7 8 9 10 11 12 Rev. No. 26 25 25 25 25 20 20 20 25 20 23 25 Page 2 of 12 A-806 I. Model DHC-2 Mk. I (cont’d) Center of Gravity C.G. Range (See Note 10.) Configuration Aircraft Weight (lb.) Limits (in.) Fwd. Aft. of Datum Landplane & Skiplane 5100 -1.25 -8.8 3800 or less +6.60 -8.8 Landplane & Skiplane 5100 -1.25 -4.4 with Items 203 or 204 3800 o r less +6.60 -4.4 Landplane & Skiplane 4820 -1.25 -7.8 with Item 205(d) 3800 or less +6.60 -7.8 Amphibian on wheels 5100 -1.25 -6.1 (Item 101(a)(i)) 3800 or less +6.60 -6.1 Amphibian on Floats 5000 -1.25 -6.1 (Item 101(a)(i) 3800 or less +6.60 -6.1 Floatplane 5090 -1.25 -6.1 (Item 101(d)(i)) 3800 or less +6.60 -6.1 Floatplane (Item 101(d)(i)) 4820 +0.44 -1.5 with Items 205 or 206 3800 or less +6.60 -1.5 Floatplane (Item 101(d)(i)) or Amphibian (Item 101(a)(i)) with Item 207 All weights +0.44 -3.50 The CG. sign convention is the reverse of that normally used, i.e., (+) distance is forward, while (-) distance is aft of datum. Straight line variation between points given. Empty weight C.G. Range None Maximum weights Landplane 4650 lb. (with Item 201(a)) 4820 lb. (with Items 205(d) and 201(b)) 5100 lbs. (with Item 201(b) or 101(a)(i)) Skiplane 4650 lb. (with Items 205(d) and 201(a)) 4820 lb. (with Items 202(a) and (b), or with Items 205(d) and 201(b)) 5100 lb. (with Items 202(c)(iii), (d), (e), (f), (g), (h), and (i)) Floatplane (See Note 5) 4820 lb. (with Items 205 or 206) 5000 lb. (with Items 101(a)(i)) (Seee Note 6) 5090 lb. (with Items 207 or 101(d)) Number of seats Eight 2 front (+5), 3 center (-31), 3 rear (-66). (See approved loading instructions for alternate arrangements.) Maximum baggage See approved loading instructions. Fuel capacity 79 Imperial Gallons (95 U.S. gallons) total (under cabin floor) One tank - 29 Imperial Gallons (35 U.S. gallons) (+4.5 inches) One tank - 29 Imperial Gallons (35 U.S. gallons) (-19.6 inches) One tank - 21 Imperial Gallons (25 U.S. gallons) (-40.0 inches) See Item 200 for external long range and wing tip fuel tanks. Oil capacity Maximum 5.2 Imperial Gall ons (6.2 U.S. gallons) (+37 inches) Page 3 of 12 A-806 I. Model DHC-2 Mk. I (cont’d) Manufacturer’s serial numbers 1 to 79 inclusive; 81 and subs equent (see Notes 3 and 4). The Canadian Department of Transport Certificate of Airworthiness for Export endorsed as noted under “Import Requirements” must be submitted for each individual aircraft for which application for certification is made. (Not required for t hose surplus military aircraft certificated in accordance with Note 4.) Import requirements A U.S. Airworthine ss 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 of D.O.T. Type Approval No. A-22, issue 26 (FAA Type Certificate No. A-806).” Certification basis CAR 10 in conformity with data forming the basis for DOT Aircraft Type Approval No. A-22 based on British Civil Airworthiness Requirements as amended to June 1, 1947, Normal Category, and Information Circular T/4/48 dated March 3, 1948. (This certification equivalent to CAR 3 dated November 13, 1945). FAA Airplane Type Certificate No. A-806 issued on March 12, 1948. Date of application for Type Certificate March 21, 1947 (to the DOT). Equipment 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 must be in each aircraft at all times: 1. Canadian approved DeHavilland DHC-2 Mk. I Beaver Flight Manual dated March 31, 1956. 2. Current deHavilland Beaver Weight and Balance Report, including list of Equipment in Certificated Weight Empty. (Items listed as required equipment must not be removed unless replaced by approved equipment items). II. Model DHC-2 Mk. II, (Beaver) (Normal Category) approved May 6, 1953. Same As DHC-2 Mk. I, except for engine installation and larger fin and rudder in accordance with deHavilland Modification No. 2/950 dated May 20, 1953. (See Note 3 for conversion of DHC-2 Mk. I). Engine Alvis “Leonides” 502/4 Fuel 100/130 octane minimum grade aviation gasoline. Max. lead content 5.5 milliliters Tetraethyl-lead per Imperial Gallon (4.6 mi. T.E.L. per U.S. gallon). Engine limits MP HP RPM In.Hg. ALT Takeoff (5 min.) 540/560 3000 46.2 S.L. 570 3000 46.2 1750 ft. Maximum continuous 425 2900 37.1 S.L. 455 2900 37.1 7250 ft. Maximum Overspeed Condition Overspeeds of up to 3150 rpm are permissible for periods not exceeding 20 seconds. Propeller and propeller limits Propeller three-blade deHavilland Type PD184/313/1 Hydromatic constant speed diameter 9 ft. - 0 inches Low pitch: 19 degrees, high pitch 41 degrees Page 4 of 12 A-806 II. Model DHC-2 Mk. II (cont’d) Airspeed limits (CAS) MPH Knots Vne (never exceed) 175 152 Vno (max. structural cruising) 140 122 Vfe (flaps extended) 105 91 Center of gravity C.G. range (See Note 10.) Configuration Aircraft Weight (lb.) Limits (in.) Fwd. Aft. of Datum Landplane 4066 4325 5100 +6.3 +5.0 +1.2 -7.7 -7.7 -7.7 Empty weight C.G. range None Maximum weight Landplane 5100 lb. (with Item 201(b)). Number of seats Eight - 2 front (+5), 3 center (-31), 3 rear (-66). (See approved loading instructions for alternate arrangements. Maximum baggage See approved loading instructions. Fuel capacity 79 Imperial Gallons (95 U. S. gallons) total (under cabin floor). One tank - 29 Imperial Gallons (35 U.S. gallons) (+4.5 inches) One tank - 29 Imperial Gallons (35 U.S. gallons) (-19.6 inches) One tank - 21 Imperial Gallons (25 U.S. gallons) (-40.0 inches) See Item 200 for external long range and wing tip fuel tanks. Oil capacity Maximum 5.2 Imperial Gallons (6.2 U.S. gallons) (+37 inches). Manufacturer’s serial numbers 80, provided Canadian Depart ment of Transport Certificate of Airworthiness for Export is submitted as noted under “Import Requirements.” Import requirements A U.S. Airworthine ss 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 Type Approval No. A-22, Issue 26 (FAA Type Certificate No. A-806).” Certification basis CAR 10 in conformity with data forming the basis for DOT Aircraft Type Approval No. A-22 based on British Civil Airworthiness Requirements as amended to June 1, 1947, Normal Category, and Information Circular T/4/48 dated March 3, 1948. (This certification equivalent to CAR 3 dated November 13, 1945). FAA Airplane Type Certificate No. A-806 amended to May 6, 1953 was issued. Date of application for Type Certificate March 21, 1947 (to the DOT). Equipment The basic required equipment as prescrib ed in the applicable airworthiness regulations (see Certification Basis) must be installed in the aircraft for certification. In addition, the following items of equipment must be in each aircraft at all times: 1. Canadian approved deHavilland DHC-2 Mk. II Flight Manual dated April 1953. 2. Current deHavilland Beaver Weight and Balance Report, including list of Equipment in Certificated Weight Empty. (Items listed as required equipment must not be removed unless replaced by approved equipment items). Page 5 of 12 A-806 Specifications Pertinent to Models DHC-2 Mk. I and DHC-2 Mk. II Datum 17.5 inches aft of the wing leading edge. (See Note 10.) Values in inches shown in parenthesis after each item represent horizontal arms to the C.G. of the item measured minus (-) aft and plus (+) forward of the datum. Mean Aerodynamic Chord (MAC) 62.5 inches Leveling means Cabin flor level laterally and longitudinally. Control surface movements Elevato r Up 28° + o r -2° Down 20° + or -2° Elevator trim tab Up 1.1 in. + or -0.1 in. Down 1.6 in. + or -0.1 in. Rudder Right 25° + o r -2° Left 25° + or -2° Ailerons Up 4.2 in. + or -0.4 in. Down 2.5 in. + or -0.4 in. Stabilizer fixed flaps Down 12.3 in. + or -0.7 in. (Ref. deHavilland DHC-2 Beaver Maintenance Manual dated February 1, 1959, Part 2, Table VI). Production basis Does not apply. III. Model DHC-2 Mk. III (Turbo-Beaver) (Normal Category), approved January 18, 1965 by the Canadian Department of Transport (DOT) and February 18, 1966 by the FAA. This aircraft is identical to the DHC-2 Mk. I, with the exception of DHC modification 2T/2000. (See Note 8 for conversion of DHC-2 Mk. II. Engine United Aircraft of Canada Ltd. Model PT6A-6A (see Item 301(k) for optional engine). Fuel MIL-J-5624E, JP-1, JP-4, or JP-5 (MIL-G-5572 AVGAS), all grades. Emergency only - limited to 150 hours’ use in any one overhaul cycle). Oil United Aircraft of Canada Ltd. Specification CPW 202. Engine limits Time Limit Rating E.S.H.P. S.H.P. Minutes Takeoff 578 550 * 5 Max. continuous 525 550 ** Unlimited Max. c limb 525 500** Unlimited *Available to 70 degrees F (21 degrees C) ambient temperature. **Available to 65 degrees F (18 degrees C) ambient temperature. Propeller and propeller limits Propeller - Hartzell Reversing Hub Model HC-B3TN-3, -3B, or -3BY Blade Model T10173C + 1 Diameter 8 ft. 6 in. nominal (8 ft. 4 in. min. after repairs) - pitch settings at 30 in. blade station: +11 degrees + or -1/2 degrees low pitch (effective) +15 degrees + or -1/2 degrees low pitch (effective) +87 degrees + or -1/2 degrees high pitch -14-1/2 degrees + 1-1/2 degrees reverse pitch 0 degrees + 1 degree + or -1 degree zero thrust pitch (blade latch propeller) Constant speed governor - Woodward Type 210508 (PT6A-6A engine) or Type 210574 (PT6A-20 engine) Overspeed governor - Woodward Type 210507, 210536, A210507 or A210536 Page 6 of 12 A-806 III. Model DHC-2 Mk. III (cont'd) Airspeed limits (CAS) Landplane, Skiplane and Floatplane at 5370 Ibs. Vne (never exceed) 175 mph 152 knots Vno (max. structural cruising) 140 mph 122 knots Vp (maneuvering) 135 mph 117 knots Vfe (flaps extended) 105 mph 91 knots Center of gravity Landplane (C.G.) Range 5370 GROSS WEIGHT - LBS 5100 4000 19% 26% 36% MAC 194.4 198.8 205.0 ARM HORIZONTAL C.G. LIMIT Skiplane Item 202(e) and 202(j) 5370 L Item 202 (f) GROSS WEIGHT - LBS. DN leaf spring 5100 ski. 4000 19% 26% 33% MAC 194.4 198.8 203.2 ARM HORIZONTAL C.G. LIMIT Page 7 of 12 A-806 III. Model DHC-2 Mk. III (cont'd) Floatplane See NOTE 9 for Mandatory Modification with Float Installation 5370 GROSS WEIGHT - LBS. 5090 Item 101(c) Bristol 679-4930 Floats Item 101(d) (lI) EDO 58-4580 Floats 4500 4300 17% 26% 33% MAC 193.2 198.8 203.2 ARM HORIZONTAL C.G. LIMIT Amphibian of Floats See NOTE 9 for Mandatory Modification with Float Installation - Item 101(b) 5370 Bristol 348-1-4930 GROSS WEIGHT - LBS. 5000 Floats ~ Item 101(a)(ii) Bristol 348-4580 Floats 4500 4300 17% 26% 33% MAC 198.8 203.2 ARM HORIZONTAL C.G. LIMIT Amphibian on Wheels | Item 101(b) 1 Bristol 348-1-4930 Floats 5370 Take-off and - Landing GROSS WEIGHT - LBS. 5100 | Item 101(a)(ii) Bristol 348-4530 Floats Take-Off and Landing 17% 26% 33% MAC 193.2 203.2 ARM HORIZONTAL C.G. LIMIT Page 8 of 12 A-806 III. Model DHC-2 Mk. III (cont’d) Empty weight C.G. range None Datum 17.5 inches aft of the wing leading edge . For weight and balanc e purposes, due to the longer nose of the DHC-2 Mk. III aircraft, this point has been designated as Horizontal Arm 200 inches. Mean Aerodynamic Chord 62.5 inches (MAC) The leading edge of MAC coincides with the leading edge of the wing and is located at Arm 182.5 inches. Leveling means Maximum weights Cabin floor level laterally and longitudinally. Takeoff Landing Landplane (with Item 201(b)) 5370 lb.* 5100 lb. Skiplane (with Item 202(f)) 5100 lb. 5100 lb. Skiplane (with Item 202(e)) or 202(j) 5370 lb.* 5100 lb. Floatplane (with Item 101(c)) 5370 lb.* 5370 lb.* Floatplane (with Item 101(d)(iii) 5090 lb. 5090 lb. Amphibian on wheels (with Item 101(a)(iii)) 5100 lb. 5100 lb. Amphibian on floats (with Item 101(a)(iii)) 5000 lb. 5000 lb. Amphibian on wheels (with Item 101(b)) 5370 lb.* 5100 lb. Amphibian on floats (with Item 101(b)) 5370 lb.* 5370 lb.* *For structural reasons all aircraft weight above 5100 lb. must be fuel in tip tanks. Number of seats Eleven. 2 at Arm 163, 3 at Arm 196, 3 at Arm 229, 3 at Arm 262. (See approved loading instructions for alternate arrangements.) Maximum baggage See approved loading instructions. Fuel capacity Total: 159 Imperial ga llons (191 U.S. gallons) (usable). Front tank: 44 Imperial Gallons (53 U.S. gallons) (+169 in.) Center tank: 58 Imperial Gallons (70 U.S. gallons) (+207.5 in.) Rear tank: 21 Imperial Gallons (25 U.S. gallons) (+240 in.) Tip tanks: 36 Imperial Gallons (43 U.S. gallons) (+210 in.) (Unusable fuel: 2 Imperial gallons (2.4 U.S. gallons) in center tank forward cell) (at Arm 195). Oil capacity Trapped and usable: 2.4 Imperial gallons (2.9 U.S. gallons) (21.7 lb.) (+116.0 in.) Control surface movements Elevato r Up 28° + o r 2° Down 23° + o r 2° -0° -0° Elevator trim tab Up 20° Down 20° Rudder Right 25° + o r -1° Left 20° + o r -1/2° Rudder trim tab Right 18° + o r -2° Left 18° + o r -2° Ailerons Up 18° + o r -2° Down 11° + o r -2° Droop 15° + 1-1/2° (with flaps fully down) Wing flaps Down 58° (port) + or -2° 59° (starboard) (Ref. deHavilland DHC-2 Mk. III Maintenance Manual, Supplement No. 6, Table III). Manufacturer’s serial 1 to 79 inclusiv e, 81 and subsequent. (See Note 8.) numbers New Turbo-Beavers (i.e. Turbo-Beav ers not originating from modified standard Beavers), are identified by double-serial numbers. For example, 1649-TB23 identifies the aircraft as Beaver number 1649 and Turbo-Beaver number 23. When deHavilland Modification 2T/2000 is incorporated on a Mk. 1, however, the serial number remains unchanged. The Canadian Department of Tr ansport Certificate of Airworthiness for Export endorsed as noted under “Import Requirements” must be submitted for each individual aircraft for which application for certification is made. Page 9 of 12 A-806 Import requirements A U.S. Airworthine ss 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 Type Approval No. A-22, Issue 26 (FAA Type Certificate No. A-806). Certification basis FAR Part 21.29(a)(1)(iii). The DHC-2 Mk. III airplane has been developed as a modification to the basic DHC-2 Beaver Mk. I airplane and as such complies with the British Civil Airworthiness Requirements as amended to June 1, 1947, Normal Category, Information Circular T/4/48 dated March 3, 1948, (this certification is equivalent to CAR 3 dated November 13, 1945), and Special Conditions for single engine turbine powered aircraft in accordance with FAA Civil Air Regulations, Part 3, dated March 1964 except for Special Condition No. 23(i). Type Certificate No. A-806, amended to February 18, 1966, was issued. Production basis Does not apply. Equipment 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 must be in each aircraft at all times: 1. Canadian approved deHavilland DHC-2 Mk. II Flight Manual, PSM-1-2T-1A. 2. Current deHavilland DHC-2 Mk. III Weight and Balance Handbook, including list of Equipment in Certificated Weight Empty. (Items listed as required equipment must not be removed unless replaced by aproved equipment items.) APPROVED INSTALLATIONS Item 100. Auxiliary ventral fin installation according to deHavilland Drawing No. C2-UF-235A. (See Note 5.) Item 101. Float Installations (See NOTE 9 for DHC-2 Mk. III Mandatory Mod.) (a) Bristol Amphibious Float Model 348-4580 installed to: (i) deHavilland Modification 2/1192 on DHC-2 Mk. I aircraft by Drawing C2UF2455; or, (ii) deHavilland Modification S.O.O. 2044 on DHC-2 Mk. III Turbo-Beaver Aircraft by Drawing CT2-Z-1042-3. (b) Bristol Amphibious Float Model 348-1-4930 installed to deHavilland Modification S.O.O. 2050 on DHC-2 Mk. III Turbo-Beaver Aircraft by Drawing CT2UF1002 Revision D. (c) Bristol Float Model 679-4930 installed to deHavilland Modification S.O.O. 2052 on DHC-2 Mk. III Turbo-Beaver Aircraft by Drawing CT2UF1001. (See Item 207(d) for Water Bombing.) (d) Edo Float Model 58-4580 or Brisol Model 901 installed to: (i) deHavilland Drawing C2UF3A on DHC-2 Mk. I aircraft; or, (ii) deHavilland Modification S.O.O. 2044 on DHC-2 Mk. III Turbo-Beaver aircraft by Drawing CT2UF1000. Item 200. (a) 36 Imperial Gallons (43 U.S. ga llon) external long range fuel tank installation (under center fuselage) to deHavilland Drawing C2-P-801A -26 lb. (-15 in.). (b) Wing tip long range fuel tank to deHavilland Modification 2/743. Item 201. (a) 7.50 X 10 main wheel tires and tubes, DHC-2 Mk. I aircraft; (b) 8.50 X 10 main wheel tires and tubes, DHC-2 Mk. I, II, or III aircraft. Page 10 of 12 A-806 Item 202. Ski Installations (a) deHavilland Drawing C2-US-201 Issue B, DHC-2 Mk. I aircraft (b) Northwest Industries Limited Drawing NWI 450001 Issue E, DHC 2 Mk. I aircraft (c) Saskatchewan Government Airways’ Drawings: (i) S.GA. 49, DHC-2 Mk. I aircraft (ii) S.G.A. 50 or 121, DHC-2 Mk. I aircraft (d) Federal Aircraft Works Drawing 11R845 Issue N or 11F1078 Issue E, DHC-2 Mk. I aircraft (e) deHavilland retractable installation to deHavilland Drawing C2-US-611A, DHC-2 Mk. I and III aircraft (f) deHavilland leaf-spring installation to deHavilland Drawing C2-US-553A, DHC-2 Mk. I and III aircraft (g) Department of Lands and Forest Installation to Drawing 1488-B-2, DHC-2 Mk. I aircraft; (h) Federal Ski and Engineering Drawing 11R-1472 Issue C, DHC-2 Mk. I aircraft (i) FluiDyne Engineering Corporation wheel ski to FluiDyne Drawing List 6300-3 dated May 14, 1963, for DHC-2 Mk. I aircraft (j) FluiDyne Engineering Corporation C5500 wheel ski to FluiDyne Installation Drawing 11R-1650 for DHC-2 Mk. III aircraft, and 11G-1472 for DHC-2 Mk. I aircraft. Item 203. Spraying Installations (a) Crop spray to deHavilland Drawing C2-M-339 or C2-M-2507; (b) Brush spray to deHavilland Drawing C2-M-2505. Item 204. Dusting Installation (a) deHavilland Drawing C2-M-1001A or C2-M-2503. Item 205. Canoe Carrying Installa tion on Port Side of Aircraft: (a) deHavilland Drawing C2-UF-416 (see Note 7(a)), DHC-2 Mk. I (b) Ontario Provincial Air Services Universal Carrier Drawing 1561. (See NOTE 7(a)). (c) A. Fecteau Transport Aerien Ltee. Drawing 1006, Revision 1. (See Note 7(b)). (d) Saskair Drawings SGA-78 and 79-A revised March 1964, and 79-B revised March 1963. (See NOTE 7(c)). Saskai r Flight Manual Supplement dated March 1964 required. For DHC-2 Mk. I aircraft. Item 206. Lumber or Frei ght Carrying Installations: For DHC-2 Mk. I aircraft. Ontario Provincial Air Services Drawing 1501. Lumber or freight must not exceed 16’ 0” Length, 12’ width, 1’ -8” height and 800 lb. Lumber or freight carried must be symmetrically distributed by weight and dimensions on each side of aircraft. Fore and aft distribution midway between carrier struts. Item 207. Water Dropping Tank In stallations: (See Note 6.) (a) Ontario Department of Lands and Forest Drawing No. 2492 (b) deHavlland Drawing C2-M-5705A, Sheets 1 and 2 (c) Manitoba Government Air Services Drawing AS-115 (d) Edo 679-4930 floats modified in accordance with Field Aviation Company Limited Report 4822 to provide water bombing capability of a maximum of 140 Imperial Gallons (168 U.S. gallons) of water. Approved for DHC-2 Mk. III aircraft at a gross weight of 5370 lb. Aircraft to be operated in accordance with Field Aviation Flight Manual Supplement , Appendix 2 of Field Aviation Report 4822. Page 11 of 12 A-806 Item 301. Engines: (a) Military R-985-AN2 (b) Military R-985-AN4 (c) Military R-985-AN6 Engine limits (a) through (g) same as or -AN6B SB-3 (see DHC-2 Mk.1 Engine Limit Data) (d) Military R-985-AN8 (e) Military R-985-AN10 (f) Military R-985-AN12 or -AN12B (g) Military R-985-AN14B (h) Military R-985-AN-1 (i) Military R-985-AN-3 (j) Military R-985-39 (Provided that the alternator fitted to the or -39A engine is compat ible with 2:1 drive ratio) Engine Limits (h) through (j) HP RPM MP In.Hg. ALT Takeoff (5 min.) 450 2300 37.5 S.L. Maximum continuous 400 2300 34.5 S.L. Maximum continuous 400 2300 33.0 5000 ft. Straight line manifold pressure variation with Alt. to 5000 ft. (k) United Aircraft of Canada Ltd. PT6A-20 (DHC-2 Mk. III only) to DeHavilland Modification T2/2035. Engine to be operated to same limits as PT6A-6A. (Ref. page 5). NOTES NOTE 1. The following must be in the aircraft at all times: Approved deHavilland Beaver DHC-2 Flight Manual, Current Weight and Balance Report, including List of equipment in certificated empty weight, and Loading Instructions. NOTE 2. The following placards must be displayed in front and in clear view of the pilot (a) “THIS AEROPLANE MUST BE OPERATED AS A NORMAL CATEGORY AEROPLANE IN COMPLIANCE WITH THE OPERATING LIMITATIONS SPECIFIED IN THE APPROVED FLIGHT AND MAINTENANCE MANUAL.” (b) For DHC-2 Mk. I with Item 201(b): “NORMAL CATEGORY (G.W. 5100 LB. AS LANDPLANE OR SKIPLANE, 5090 LB. AS FLOATPLANE). ACROBATIC MANEUVERS INCLUDING SPINS NOT APPROVED.” (c) For DHC-2 Mk. I with Item 201(a): “NORMAL CATEGORY (G.W. - 4650 LB. AS LANDPLANE OR SKIPLANE, 5090 LB. AS FLOATPLANE). ACROBATIC MANEUVERS INCLUDING SPINS NOT APPROVED.” NOTE 3. DHC-2 Mk. I eligible for conversion to DHC-2 Mk . II when modified in accordance with deHavilland Modification No. 2/950, dated May 20, 1953, and with Item 201(b). NOTE 4. Those surplus military deHavilland models L-20A/YL-20/U-6A aircraft identified by civil and military serial numbers in deHavilland Report QA/DHC-2/G11, are eligible for a U.S. Standard Airworthiness Certificate without requiring a Canadian Certificate of Airworthiness for Export when all of the following conditions have been satisfied. (a) Aircraft records must indicate, or a determination must be made, that the aircraft has been subjected to FAA initial screening inspection. The screening inspection record must show that the aircraft has a reasonable potential for standard certification. (Those aircraft dispositioned as having no reasonable potential for standard certification are not certifiable unless the reasons for no reasonable potential can be reconciled. These aircraft are sold by U.S. Department of Defense only for the purpose of “Recovery of Parts or Reduction to Scrap.”) Page 12 of 12 A-806 (b) The aircraft must be converted to deHavilland Model DHC-2MK.I in accordance with deHavilland Modification SOO-2022, Issue 8, and deHavilland Service Bulletin No. 2/10, Revision B, February 7, 1975. (c) The applicant shows, and the FAA finds, that the aircraft conforms to the type design and is in a condition for safe operation. (d) A satisfactory “100 hour” type inspection has been accomplished and recorded. (e) Any deviations to the type design must be appropriately approved by an FAA Supplemental Type Certificate or other methods acceptable to the FAA. Upon satisfying all the foregoing conditions, and when all other pertinent U.S. regulatory requirements have been met, a U.S. Standard Airworthiness Certificate may be issued. Certification basis is FAR 21.183(c) since these are import aircraft. Technical data needed for conversion purposes are available to the applicant through deHavilland of Canada Limited. Inquiries for this data shoul d be submitted to The Product Support Department, deHavilland of Canada, Limited, Downsview, Ontario, Canada. NOTE 5. A floatplane must have Item 100 installed if it is to be exported to the United States of America, but Item 100 is not required in Canada. The addition of Item 100 does not affect maximum weight of C.G. limits. NOTE 6. The maximum-all-up-to-weight for the aircraft eq uipped with amphibious floats, (Item 101(a)(iii)), plus the water dropping tanks (Item 207) may be increased from 5000 lbs. to 5090 lbs. if the 90 lb. extra weight is entirely water picked up while the aircraft is taxiing on the step at speeds in excess of 40 mph. NOTE 7. (a) Canoe not to exceed 16’ -6” length, 3’ -5” beam and 95 lb. (Ref. Item 205(a) and (b)). Canoe bow to be between propeller disc and 18 in. forward of propeller disc. (b) Canoe not to exceed 18’ -0” length, 4’ -2” beam and 150 lb. (Ref. Item 205(c)). (c) Canoe not to exceed 18’ -0” length, 36” beam and 150 lb. Saskair Flight Manual Supplement dated March 1964, required. (Ref. Item 205(d)). NOTE 8. DHC-2 Mk. I aircraft may be converted to a DHC-2 Mk. III in accordance with deHavilland Modification 2T/2000. NOTE 9. All DHC-2 Mk. III aircraft equpped with floats or amphibious gear must have deHavilland Modification 2T/2059 incorporated. NOTE 10. All DHC-2 Mk. I and Mk. II aircraft use a revi sed Weight and Balance Manual PSM 1-2-8 that uses a C.G. reference datum 100.0 inches ahead of the original datum. Refer to instructions contained in PSM 1- 2-8 for an acceptable method of conversion. ....END.... ``` ## ADs (42, in force first) - [AD 2023-19-06](https://openairdocs.org/ad/2023-19-06): Airframe · Viking Air DHC-2 Mk.II, DHC-2 Mk.I and DHC-2 Mk.III. Effective Nov 6, 2023 - [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 2023-06-11](https://openairdocs.org/ad/2023-06-11): Wing Spar · Viking Air DHC-2 Mk.I with STC SA01324CH. Effective Apr 28, 2023 - [AD 2022-17-05](https://openairdocs.org/ad/2022-17-05): Fuselage Structure (General) · Viking Air DHC-2 Mk.I, DHC-2 Mk.II and DHC-2 Mk.III. Effective Sep 30, 2022 - [AD 2022-03-15](https://openairdocs.org/ad/2022-03-15): Fuel Quantity Indicator · Garmin G3X Touch Electronic Flight Instrument System (STC SA01899WI or SA02658SE). Effective Mar 21, 2022 - [AD 2020-16-15](https://openairdocs.org/ad/2020-16-15): Fuselage · Viking Air DHC-2 Mk.I and DHC-2 Mk.III with STC SA00299NY or SA945NE. Effective Sep 21, 2020 - [AD 2018-19-11](https://openairdocs.org/ad/2018-19-11): Wings · Viking Air DHC-2 Mk.I, DHC-2 Mk.II and DHC-2 Mk.III. Effective Oct 30, 2018 - [AD 2016-25-22](https://openairdocs.org/ad/2016-25-22): Flight Controls · Viking Air DHC-2 Mk.I, DHC-2 Mk.II and DHC-2 Mk.III. Effective Dec 22, 2016 - [AD 2015-02-10](https://openairdocs.org/ad/2015-02-10): Flight Controls · Viking Air DHC-2 Mk.I, DHC-2 Mk.II and DHC-2 Mk.III. Effective Feb 18, 2015 - [AD 2008-11-11](https://openairdocs.org/ad/2008-11-11): Front spar center · Viking Air DHC-2 Mk.I, DHC-2 Mk.II and DHC-2 Mk.III. Effective Jul 23, 2008 - [AD 2008-12-12](https://openairdocs.org/ad/2008-12-12): Ignition connector plug · Viking Air DHC-2 Mk.I, DHC-2 Mk.II and DHC-3. Effective Jul 23, 2008 - [AD 2007-12-13](https://openairdocs.org/ad/2007-12-13): Wing lift strut lower clevis fitting · Viking Air DHC-2 Mk.I, DHC-2 Mk.II and DHC-2 Mk.III. Effective Jul 16, 2007 - [AD 2005-25-08](https://openairdocs.org/ad/2005-25-08): Electronic Flight Information System (EFIS) · B-N Group BN-2A, 172, 180 and 22 more. Effective Jan 23, 2006 - [AD 2005-18-20](https://openairdocs.org/ad/2005-18-20): "FASTprop" propeller de-icers · Hartzell PHC-C3YF-1RF/F8468A(B,K)-8R constant speed propeller (STC SA00718LA or 17 others). Effective Oct 14, 2005 - [AD 2005-01-19](https://openairdocs.org/ad/2005-01-19): Mode S transponders · GARMIN International GTX 330D, GTX 330, GTX 33D and 830 more. Effective Feb 23, 2005 - [AD 2002-13-08](https://openairdocs.org/ad/2002-13-08): Mass Balance Weights at Elevator Tip Ribs · Viking Air DHC-2 Mk.I, DHC-2 Mk.II and DHC-2 Mk.III. Effective Aug 13, 2002 - [AD 99-15-07](https://openairdocs.org/ad/99-15-07): Rear Fuselage Bulkhead · Viking Air DHC-2 Mk.I, DHC-2 Mk.II and DHC-2 Mk.III. Effective Sep 10, 1999 - [AD 90-02-22](https://openairdocs.org/ad/90-02-22): Fuselage Attachment Brackets · Viking Air DHC-2 Mk.I and DHC-2 Mk.II. Effective Feb 13, 1990 - [AD 84-20-07](https://openairdocs.org/ad/84-20-07): Wing Lift Strut Assembly · Viking Air DHC-2 Mk.I, DHC-2 Mk.II and DHC-2 Mk.III. Effective Oct 12, 1984 - [AD 84-09-06](https://openairdocs.org/ad/84-09-06): Control Column Sub-Assembly · Viking Air DHC-2 Mk.I, DHC-2 Mk.II and DHC-2 Mk.III. Effective May 10, 1984 - [AD 84-07-05](https://openairdocs.org/ad/84-07-05): L/R Aileron Hinge Bracket · Viking Air DHC-2 Mk.I, DHC-2 Mk.II and DHC-2 Mk.III. Effective Apr 18, 1984 - [AD 81-13-01](https://openairdocs.org/ad/81-13-01): Elevator Butt Ribs · Viking Air DHC-2 Mk.I, DHC-2 Mk.II and DHC-2 Mk.III. Effective Jun 18, 1981 - [AD 80-24-02](https://openairdocs.org/ad/80-24-02): Aileron Mount Structures · Viking Air DHC-2 Mk.I, DHC-2 Mk.II and DHC-2 Mk.III. Effective Nov 20, 1980 - [AD 76-14-02](https://openairdocs.org/ad/76-14-02): Various Modifications · Viking Air DHC-2 Mk.I, DHC-2 Mk.II and DHC-2 Mk.III. Effective Jul 12, 1976 - [AD 74-17-03](https://openairdocs.org/ad/74-17-03): Cabin Heater Inspection · Viking Air DHC-2 Mk.I. Effective Aug 12, 1974 - [AD 73-25-05](https://openairdocs.org/ad/73-25-05): Float Support Structure · Viking Air DHC-2 Mk.I. Effective Dec 14, 1973 - [AD 66-17-02](https://openairdocs.org/ad/66-17-02): Front and Rear Spars · Viking Air DHC-2 Mk.I, DHC-2 Mk.II and DHC-2 Mk.III. Effective Jul 22, 1966 - [AD 64-14-02](https://openairdocs.org/ad/64-14-02): Elevator Trim Tab End Blocks · Viking Air DHC-2 Mk.I, DHC-2 Mk.II and DHC-2 Mk.III. Effective Jul 24, 1964 - [AD 53-07-01](https://openairdocs.org/ad/53-07-01): Elevator Hinge Attachment · Viking Air DHC-2 Mk.I, DHC-2 Mk.II and DHC-2 Mk.III - [AD 53-09-02](https://openairdocs.org/ad/53-09-02): Fuselage Skin Cracks · Viking Air DHC-2 Mk.I, DHC-2 Mk.II and DHC-2 Mk.III - [AD 53-10-02](https://openairdocs.org/ad/53-10-02): Wing Skin Cracks · Viking Air DHC-2 Mk.I, DHC-2 Mk.II and DHC-2 Mk.III - [AD 53-11-02](https://openairdocs.org/ad/53-11-02): Engine Oil Sump Chafing · Viking Air DHC-2 Mk.I, DHC-2 Mk.II and DHC-2 Mk.III - [AD 53-12-02](https://openairdocs.org/ad/53-12-02): Hydraulic Hand Pump Seals · Viking Air DHC-2 Mk.I, DHC-2 Mk.II and DHC-2 Mk.III - [AD 53-21-01](https://openairdocs.org/ad/53-21-01): Wing Rear Spar Attachment Bolt · Viking Air DHC-2 Mk.I, DHC-2 Mk.II and DHC-2 Mk.III - [AD 53-23-02](https://openairdocs.org/ad/53-23-02): Fuel Tank Filler Neck · Viking Air DHC-2 Mk.I, DHC-2 Mk.II and DHC-2 Mk.III - [AD 54-15-01](https://openairdocs.org/ad/54-15-01): Control Cable Turnbuckle Threads · Viking Air DHC-2 Mk.I, DHC-2 Mk.II and DHC-2 Mk.III - [AD 2016-19-08](https://openairdocs.org/ad/2016-19-08) (historical): Flight Controls · Viking Air DHC-2 Mk.I, DHC-2 Mk.II and DHC-2 Mk.III. Effective Oct 24, 2016 - [AD 2004-21-06](https://openairdocs.org/ad/2004-21-06) (historical): Firewall Connector Plugs Lockwire Security · Viking Air DHC-3, DHC-2 Mk.I and DHC-2 Mk.II. Effective Dec 6, 2004 - [AD 2002-14-28](https://openairdocs.org/ad/2002-14-28) (historical): Front Fuselage Struts · Viking Air DHC-2 Mk.I, DHC-2 Mk.II and DHC-2 Mk.III. Effective Sep 6, 2002 - [AD 92-24-02](https://openairdocs.org/ad/92-24-02) (historical): Horizontal Stabilizer Front Center Spar · Viking Air DHC-2 Mk.I, DHC-2 Mk.II and DHC-2 Mk.III. Effective Dec 15, 1992 - [AD 88-08-02](https://openairdocs.org/ad/88-08-02) (historical): Wing Strut Assemblies · Viking Air DHC-2 Mk.I and DHC-2 Mk.III. Effective May 11, 1988 - [AD 64-09-03](https://openairdocs.org/ad/64-09-03) (historical): Aileron Mass Balance Weight Arm · Viking Air DHC-2 Mk.I, DHC-2 Mk.II and DHC-2 Mk.III. Effective May 22, 1964 ## Registered aircraft by registry model (OpenAirDocs) - [Dehavilland DHC-2 MK. I(L20A)](https://openairdocs.org/model/dehavilland-dhc-2-mk-i-l20a): 91 aircraft (registry code 2808002) - [Dehavilland DHC 2 MK III](https://openairdocs.org/model/dehavilland-dhc-2-mk-iii): 24 aircraft (registry code 2808005) - [Dehavilland DHC-2 MK.I](https://openairdocs.org/model/dehavilland-dhc-2-mk-i): 20 aircraft (registry code 2808007) - [Dehavilland Acft Canada DHC-2](https://openairdocs.org/model/dehavilland-acft-canada-dhc-2): 4 aircraft (registry code 2821703) - [Dehavilland Acft Of Canada DHC-2 MK I](https://openairdocs.org/model/dehavilland-acft-of-canada-dhc-2-mk-i): 3 aircraft (registry code 2805055) - [Dehavilland-Shawano DHC-2 MK.I](https://openairdocs.org/model/dehavilland-shawano-dhc-2-mk-i): 2 aircraft (registry code 2806001) - [Dehavilland/Hansen DHC2 MK I](https://openairdocs.org/model/dehavilland-hansen-dhc2-mk-i): 0 aircraft (registry code 2808003) ## STCs approved under this data sheet (293, first 50) - [STC SA02571SE](https://openairdocs.org/stc/SA02571SE): Installation of Garmin G500/G600 TXi Integrated Avionics System (Primary Flight Display, Multi-Function Display, and Engine Indicating System Display).. Garmin International Inc. - [STC SA01800SE](https://openairdocs.org/stc/SA01800SE): Fabrication and installation of new or replacement of existing instrument panel lights dimmer control.. TCW Technologies, LLC - [STC SA01861SE](https://openairdocs.org/stc/SA01861SE): Fabrication and installation of Landing Light Controller. TCW Technologies, LLC - [STC SA02279AT](https://openairdocs.org/stc/SA02279AT): Installation of a Boom Beam bulb, starter, and ballast. Whelen Aerospace Technologies - [STC SA04837NY](https://openairdocs.org/stc/SA04837NY): Installation of AeroLED's Holdings, LLC., position lights, navigation lights, strobe lights and beacon lights. AeroLED's Holdings, LLC - [STC SA04652CH](https://openairdocs.org/stc/SA04652CH): To allow use of 100R grade aviation fuel meeting Swift Fuel, LLC specification. Swift Fuels LLC - [STC SA02636SE](https://openairdocs.org/stc/SA02636SE): Installation of Garmin GPS 175 Navigation System and GNX 375 Navigation System with ADS-B In/Out Transponder.. Garmin International Inc. - [STC SA02019SE-D](https://openairdocs.org/stc/SA02019SE-D): Installation of Garmin Model GTN 625/635/650; 725/750 Navigation System. Garmin International Inc. - [STC SA800EA](https://openairdocs.org/stc/SA800EA): Installation of Whelen Anti-Collision, Position, or Anti-Collision/Position Light System, and applicable associated power supplies. Whelen Aerospace Technologies - [STC SA04724NY](https://openairdocs.org/stc/SA04724NY): Installation of Aerocet 6650 amphibious floats. DH2 Floats, LLC - [STC SA348NW](https://openairdocs.org/stc/SA348NW): Installation of JASCO Model 7555-1 alternator kit on P&W R-985 series engine.. Kenmore Air Harbor LLC - [STC SA02511SE](https://openairdocs.org/stc/SA02511SE): Installation of replacement fuel quantity indicator sending unit(s). CiES Inc. - [STC SA11158SC](https://openairdocs.org/stc/SA11158SC): Demonstration of aircraft tolerance to potential electromagnetic interference from certain Transmitting Potable Electronic Devices (T-PEDS). Liberty Partners Inc. - [STC SA02738CH](https://openairdocs.org/stc/SA02738CH): Installation of L-3 Communications Avionics Systems. Acron Aviation Inc. - [STC SA04046CH PAGE 2](https://openairdocs.org/stc/SA04046CH%20PAGE%202): Installation of L-3 GENESIS (TM) Electronic Standby Instrument System (ESI-500/MAG-500). Acron Aviation Inc. - [STC SA11886IB](https://openairdocs.org/stc/SA11886IB): Installation of Alternator Replacement. Skye Avionics Ltd. - [STC SA39CH](https://openairdocs.org/stc/SA39CH): Installation of an Amphibian Landing Gear Position Advisory System/Laser Gear Advisory System. Wipaire Inc. - [STC SA709GL](https://openairdocs.org/stc/SA709GL): Installation of Hartzell HC-B3R30-4, -4A, -4B/ R10152-5 1/2 propeller, C-4 governor, and836-32PR spinner on P&W R-985 series engines (with 4 1/2 and 9th order crankshaft vibration dampers). (DHC-2 (L-20A) MK.I LANDPLANE; SKIPLANE, FLOATPLANE). Wipaire Inc. - [STC SA02386AK](https://openairdocs.org/stc/SA02386AK): Replacement of existing landing and/or taxi light reflector and bulbs with Light Emitting Diode (LED) lighting systems. AeroLED's Holding LLC - [STC SA01757WI](https://openairdocs.org/stc/SA01757WI): To allow the use of UL91 or UL94 (minimum) grade aviation fuel. Swift Fuels LLC - [STC SA02585AK](https://openairdocs.org/stc/SA02585AK): Installation of Tailwind Aviation Viking Air Limited DHC-2 Main Gear Gravel Deflectors. Tailwind Aviation - [STC SA456NW](https://openairdocs.org/stc/SA456NW): Installation of auxiliary vertical seaplane fins. Kenmore Air Harbor LLC - [STC SA02658SE](https://openairdocs.org/stc/SA02658SE): Installation of Garmin GI 275 Multi-Function Display System. Garmin International Inc. - [STC SA01899WI](https://openairdocs.org/stc/SA01899WI): Installation of Garmin G3X Touch Electronic Flight Instrument System. Garmin International Inc. - [STC SA02019WI](https://openairdocs.org/stc/SA02019WI): Installation of the Trig Avionics TX56, TX56A, TX57, or TX57A VHF Nav-Com Radio.. Peregrine - [STC SA00756DE](https://openairdocs.org/stc/SA00756DE): Installation of Automatic Dependent Surveillance Broadcast (ADS-B) Out Equipment using a Trig Avionics TT22 Transponder and an approved Global Positioning System (GPS) Position Sensor. Peregrine - [STC SA3-591](https://openairdocs.org/stc/SA3-591): Installation of Wipaire Skis Model C-5500 main ski and tail ski.. F.Atlee Dodge Aircraft Services - [STC SA1402GL](https://openairdocs.org/stc/SA1402GL): Installation of Cleveland Main Wheels and Brakes.. Kaman Corporation Aircraft Wheel and Brake LLC - [STC SA01967WI](https://openairdocs.org/stc/SA01967WI): Use of GAMI G100UL High Octane Unleaded Avgas. General Aviation Modifications Inc. - [STC SA2258AK](https://openairdocs.org/stc/SA2258AK): Fabrication and installation of a replacement forward fuselage tubular frame. Airforms LLC. - [STC SA02203AK](https://openairdocs.org/stc/SA02203AK): Installation of FlightLogic Synthetic Vision Electronic Flight Information System (EFIS-SV).. Genesys Aerosystems Inc. - [STC ST03434CH](https://openairdocs.org/stc/ST03434CH): Installation of Trace TE600D engine. Aeronautix LLC - [STC SA02567AK](https://openairdocs.org/stc/SA02567AK): Installation of provisions to carry rolled rubber rafts as external loads strapped to the floats. Tailwind Aviation Inc. - [STC SA4-182](https://openairdocs.org/stc/SA4-182): Installation of VIP P/N 101-78 engine mount.. FTG, Inc. - [STC SA02444AK](https://openairdocs.org/stc/SA02444AK): Approval of the L-3 Communications NGT 9000/9000R ADS-B system installed. ADS-B Technologies LLC - [STC SA736NW](https://openairdocs.org/stc/SA736NW): Installation of Cleveland Model 40-46 Wheels and Model 30-31 brakes on Edo/Bristol/deHavilland 58-4580 amphibious floats. Kenmore Air Harbor LLC - [STC SA04714NY](https://openairdocs.org/stc/SA04714NY): Installation of MT-Propeller model MTV-16-1-E-C-F-R(P)/CFR240-55a propeller. Viking Air Limited - [STC SA04701NY](https://openairdocs.org/stc/SA04701NY): Replacement of Fixed Wing Control Cables. Thunder Bay Aviation Ltd - [STC SA01015SE](https://openairdocs.org/stc/SA01015SE): Installation of eligible Alaska Bushwheel, Inc. wheels and TSO-C62d tires. ABI LLC - [STC SA1042NE](https://openairdocs.org/stc/SA1042NE): Installation of a new heater. Kevin Franklin - [STC SA09856AC](https://openairdocs.org/stc/SA09856AC): Installation of BendixKing Aerowave 100 In-flight Data Link System for non-essential, non-required aircraft Cabin Systems & Equipments. Honeywell International Inc (Bendix King) - [STC SA11174SC PAGE 2](https://openairdocs.org/stc/SA11174SC%20PAGE%202): Installation of BendixKing by Honeywell KSN 770 and KSN 765 WAAS LPV approach capable nav/comm systems. Honeywell International Inc (Bendix King) - [STC SA10822SC](https://openairdocs.org/stc/SA10822SC): Installation of EFD1000 Primary Flight Display. Aspen Avionics Inc. - [STC SA02426AK](https://openairdocs.org/stc/SA02426AK): Approval of the FreeFlight FDL-978-TX ADS-B system installed. FreeFlight Systems - [STC SA02275SE](https://openairdocs.org/stc/SA02275SE): Installation of an increased landing weight modification. Kenmore Air Harbor Inc - [STC SA01831WI](https://openairdocs.org/stc/SA01831WI): To allow the use of UL91 (minimum) grade aviation fuel. Petersen Aviation Inc - [STC SA10236SC](https://openairdocs.org/stc/SA10236SC): Installation of a GDC 31 Roll Steering Converter. DAC International Inc - [STC SA01560WI-D](https://openairdocs.org/stc/SA01560WI-D): Installation of the Honeywell KFD 840 Primary Flight Display System.. Honeywell International Inc - [STC SA01725WI](https://openairdocs.org/stc/SA01725WI): Installation of Pratt & Whitney R-985-AN14B or R-985-AN1 engine modified for fuel injection. A & L Aircraft Parts Inc - [STC SA5190NM](https://openairdocs.org/stc/SA5190NM): Installation of Gustin Aviation chip detector light system.. A & L Aircraft Parts Inc All 293: https://openairdocs.org/tcds/A-806/stcs.md --- 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.