TCDS A-806

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).