TCDS A9EA

DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION TYPE CERTIFICATE DATA SHEET NO. A9EA This data sheet which is a part of type certificate No. A9EA prescribes conditions and limitations under which the product for which the type certificate was issued meets the airworthiness 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 1959 de Havilland Way Sidney, British Columbia Canada V8L 5V5 Bombardier Inc. Regional Aircraft 123 Garratt Boulevard Downsview, Ontario, Canada M3K 1Y5 de Havilland, Inc. 123 Garratt Boulevard Downsview, Ontario, Canada M3K 1Y5 I - Model DHC-6-1 (Prototype and four Pre-Production A/C) (Normal Category), Approved June 22, 1966 by the FAA and April 7, 1966 by the Canadian Department of Transport (DOT) Engines 2 United Aircraft of Canada, Limited PT6A-20 Fuel MIL-J-5624E, Grades JP-1, JP-4, JP-5, or Arctic Diesel Fuel to UACL Specification CPW 46. (MIL-G-5572C Avgas (all grades) for emergency use only limited to 150 hours use in any one overhaul cycle.) Oil Synthetic types conforming to CPWA 202, latest issue, (UACL PT6 Engine Service Bulletin No. 1 lists approved brand oils.) Engine rating RATING E.S.H.P. S.H.P. Take-off (5 min.) *579 *550 Max. continuous *579 *550 *Available to 70°F (21°C) Ambient Temperature Engine limits Temperature Limits (Inter-Turbine) Take- off 1380° F (750° C) Max. Continuous 1380°F (750° C) Starting (2 sec.) 1994°F (1090° C) Torque Limits Take-off 42.5 p.s.i. (1315 ft. lb.) Max. Continuous 42.5 p.s.i. (1315 ft. lb.) Gas Generator Take-off 38,100 r.p.m. (101.5%) Max. Continuous 38,100 r.p.m. (101.5%) Page No. 1 2 3 4 5 6 7 8 9 10 11 12 13 14 15 16 17 18 19 20 Rev. No. 22 - 15 8 - 8 15 8 - 15 15 - 15 15 21 21 21 21 20 21 A9EA Revision No.22 De Havilland Aircraft of Canada (Twin Otter) DHC-6-1 DHC-6-100 DHC-6-200 DHC-6-300 DHC-6-400 February 21, 2025 Page 2 A9EA Oil Temperature Starting -40°C Min. Take-off 10°C to 99°C Max. Continuous 10°C to 99°C Oil Pressure Normal (28,000 r.p.m. & above) 65 to 85 p.s.i.g. Min. (below 28,000 r.p.m.) 40 p.s.i.g. Propeller Hartzell Hub HC-B3TN-3, -3B, -3BY Blades T10173+1, T10173E+1 Diameter 8 ft. 6 in. nominal (8 ft. 4 in. minimum after repairs) Pitch Settings at 30" Station Feather +87° Take-off Low Pitch +17° Idle Blade Angle +12° Reverse Blade Angle - 9° Propeller limits Propeller (Np) - Take-off 2200 r.p.m. (100%) Max. Continuous 2200 r.p.m. (100%) Airspeed limits Skiplane (CAS) L andplane & Floatplane M.P.H. Knots M.P.H. Knots Vne (Never exceed) 232.7* 202* 210.8* 183* Vno (Max. structural cruising) 184.3** 160** 184.3** 160** Vp (Maneuvering) 149.8*** 130*** 149.8*** 130*** Vmc (Minimum control) 73.7 64 73.7 64 Vfe (Flaps extended) 115.2 100 115.2 100 Vfe (Flaps extended) 97.9 85 97.9 85 * Reduce Vne 4.6 m.p.h. (4K) per 1000 ft. above 10000 ft. ** Reduce Vno 3.5 m.p.h. (3K) per 1000 ft. above 10000 ft. *** Reduce Vp - Vno above 20000 ft. C.G. range (Landing L andplane and Skiplane gear fixed) Forward Limit 20% M.A.C. (STA. 203.84) at all weights up to max. of 11000 lb. Aft Limit 36% M.A.C. (STA. 216.32) at all weights up to max. of 11000 lb. Floatplane Forward Limit 25% M.A.C. (STA. 207.74) at all weights up to max. of 11000 lb. Aft Limit 32% M.A.C. (STA. 213.20) at all weights up to max. of 11000 lb. Empty weight C.G. range None Maximum w eights Landplane Take-off 11000 lb. Landing 11000 lb. Skiplane Take-off 11000 lb. (with Item 201(a) and (b)) Landing 11000 lb. (with Item 201(a) and (b)) Floatplane Take-off 11000 lb. (with Item 202(a)) Landing 11000 lb. (with Item 202(a)) Minimum Crew One (pilot). (+95.0 in.) No. of seats 16 (including two at Stn. +95.0 in.) - Limited by approved seating arrangement. (See Weight and Balance Handbook). Max. 17 (including two at Stn. +95.0 in.) -Limited by emergency exit requirements. (Approval of seating arrangement is required). Cargo loading conditions See Weight and Balance Handbook PSM 1-6-8 0° to 20° 20° to 40° Page 3 A9EA Maximum baggage 200 lb. max. in forward compartment (arm +41.0 in.) 500 lb. max. in rear compartment (arm +354.0 in.) See Weight and Balance Handbook. Fuel capacity *USABLE FUEL U.S. GALS. IMPERIAL GALS. Forward Tank (+162.5 in.) 176 147 Rear Tank (+240.0 in.) 182 152 TOTAL 358 299 *See NOTE 1(b) for Weight and Balance. Oil capacity * USABLE OIL U.S. GALS. IMPERIAL GALS. WEIGHT LB. Port (+177.0 in.) 1.5 1.2 11 * Se e NOTE 1(c) for Weight and Balance. Maximum Operating 25000 ft. (when supplementary breathing equipment is provided for Altitude all occupants). Control surface movements Aileron (with flaps up) Up 17.5° Down 16° (with flaps in landing position) Up 25° Down 17.5° Trim Tab - or + 15° Geared Tab (flap up) Up 16° Down 17.5° Flaps (inboard forward) 0° to 40° (inboard trailing) 0° to 62.5° (outboard forward) 0° to 26° (outboard trailing) (aileron) Elevator Up 25° Down 16° Tab Up 20° Down 25° Flap interconnect (flap up) Down 12° (flap landing) Up 12° Rudder Left 20° Right 21° Geared Tab - or + 11° Trim Tab - or + 25° See Maintenance Manual PSM-1-6-2 for procedure to rig control surface movements from stop to stop. Serial Nos. eligible 1 to 5 inclusive. The Canadian Department of Transport Certificate 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 eligibility 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 D.O.T. Type Approval No. A-82, Issue 2, dated July 29, 1966. (FAA Type Certificate No. A9EA)." Certification basis CAR 3 dated May 15, 1956 and Amendments 3-1 to 3-8 inclusive, plus Special Conditions for Multi-Engine Turbine Powered Aircraft dated November 6, 1964. Type Certificate No. A9EA issued June 22, 1966. Not approved for use in operations under FAR Part 135 after May 31, 1972, when FAR 135.144 becomes mandatory. (See NOTE 3). Date of application for Type Certificate April 2, 1964. 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 Viking Air Limited (or Bombardier) Report A.E.R.O.C. 6.6.G.1. In addition, the following item of equipment is required: (a) Canadian D.O.T. approved Airplane Flight Manual, PSM-1-61-1A. Starboard (+177.0 in.) 1.5 1.2 11 TOTAL 3.0 2.4 22 Page 4 A9EA II - Model DHC-6-100 (Normal Category), Approved August 1, 1966 by the FAA and July 29, 1966 by the Canadian Department of Transport (DOT). (First Production Series) Engines 2 United Aircraft of Canada, Limited PT6A-20 Fuel MIL-J-5624E, Grades JP-1, JP-4, JP-5, or Arctic Diesel Fuel to UACL Specification CPW 46. (MIL-G-5572C Avgas (all grades) for emergency use only limited to 150 hours use in any one overhaul cycle.) Oil Synthetic types conforming to CPWA 202, latest issue, (UACL PT6 Engine Service Bulletin No. 1 lists approved brand oils.) Engine rating RATING E.S.H.P. S.H.P. Take-off (5 min.) *579 *550 Max. continuous *579 *550 *Available to 70°F (21°C) Ambient Temperature Engine limits Temperature Limits (Inter-Turbine) Take-off 1380°F ( 750°C) Max. Continuous 1380°F ( 750°C) Starting (2 sec.) 1994°F (1090°C) Torque Limits Take-off 42.5 p.s.i. (1315 ft.-lb.) Max. Continuous 42.5 p.s.i. (1315 ft.-lb.) Gas Generator Take-off 38,100 r.p.m. (101.5%) Max. Continuous 38,100 r.p.m. (101.5%) Oil Temperature Starting -40°C Min. Take-off 10°C to 99°C Max. Continuous 10°C to 99°C Oil Pressure Normal (28,000 r.p.m. & above) 65 to 85 p.s.i.g. Min. (below 28,000 r.p.m.) 40 p.s.i.g. Propeller Hartzell Hub HC-B3TN-3, -3B, -3BY Blades T10173+1, T10173E+1 Diameter 8 ft. 6 in. nominal (8 ft. 4 in. minimum after repairs) Pitch Settings at 30" Station Feather +87° Take-off Low Pitch +16° Idle Blade Angle +12° Reverse Blade Angle -14° Propeller limits Propeller (Np) - Take-off 2200 r.p.m. (100%) Max. Continuous 2200 r.p.m. (100%) Airspeed limits Skiplane (CAS) Landplane & Floatplane M.P.H. Knots M.P.H. Knots Vne (Never exceed) 232.7* 202* 210.8* 183* Vno (Max. structural cruising) 184.3** 160** 184.3** 160** Vp (Maneuvering) 149.8*** 130*** 149.8*** 130*** Vmc (Minimum control) 73.7 64 73.7 64 Vfe(Flaps extended) 115.2 100 115.2 100 0° to 20° Vfe (Flaps extended) 97.9 85 97.9 85 20° to 40° *Reduce Vne 4.6 mph (4K) per 1000 ft. above 10000 ft. **Reduce Vno 3.5 mph (3K) per 1000 ft. above 10000 ft. ***Reduce Vp - Vno above 20000 ft. Page 5 A9EA Max Landing WT Above -20°F C.G. range (Landing Without Mod. 6/1020 - Same as Model 1 gear fixed) With Mod. 6/1020 - "Fuselage Beam, Front Wing Spar Reinforcing" LANDPLANE 11,579 11,400 11,000 Max Take-Off Weight Max Landing WT Above -20°F Max Landing WT Below -20°F 10,000 9,000 20 ARM 203.84 22 ARM 205.40 36 ARM 216.32 HORIZONTAL C.G. L IMIT - % MAC SKIPLANE 11,579 11,400 11,000 10,000 Max Take-Off Weight 9,000 20 ARM 203.84 22 23 ARM 206.18 36 ARM 216.32 FLOATPLANE Forward Limit 25% M.A.C. (STA. 207.74) at all weights up to max. of 11,600 lb. Aft Limit 32% M.A.C. (STA. 213.20) at all weights up to max. of 11,600 lb. Empty weight C.G. range None Maximum weights With Mod. 6/1020 - "Fuselage Beam, Front Wing Spar Reinforcing" Landplane (lb.) Skipl ane (lb.) Floatplane (lb.) (With Item 201(a)&(b)) (With Item 202(a)&(b)) Take-off 11579 11579 11600 Landing 11400* 11400* 11600 *See NOTE 5 - Temperature Limitations Without Mod. 6/1020 - Same as Model 1. Minimum Crew One (pilot). (+95.0 in.) No. of seats 21 (including two at Stn. +95.0 in.) - Limited by approved seating arrangement. (See Weight and Balance Handbook). Max. 24 (including two at Stn. +95.0 in.) -Limited by emergency exit requirements. (Approval of seating arrangement is required). Max Landing WT Below -20°F GROSS WEIGHT - LB. GROSS WEIGHT - LB. Page 6 A9EA Cargo loading limitations See Weight and Balance Handbook PSM 1-6-8 Maximum baggage 200 lb. max. in forward compartment (arm +41.0 in.) 500 lb. max. in rear compartment (arm +354.0 in.) See Weight and Balance Handbook. Fuel c apacity *USABLE FUEL U.S. GAL. IMPERIAL GAL. Forward Tank (+162.5 in.) 181 151 Rear Tank (+240.0 in.) 197 164 TOTAL 378 315 *See NOTE 1(b) for Weight and Balance. Oil capacity * *USABLE OIL U.S. GAL. IMPERIAL GAL. WEIGHT LB. Port (+177.0 in.) 1.5 11.2 11 ** See N OTE 1(c) for Weight and Balance. Maximum Operating 25000 ft. (when supplementary breathing equipment is provided for Altitude all occupants). Control surface movements Aileron (with flaps up) Up 17.5° Down 16° (with flaps in landing position) Up 25° Down 17.5° Trim Tab - or + 15° Geared Tab (flap up) Up 16° Down 17.5° Flaps (inboard forward) 0° to 40° (inboard trailing) 0° to 62.5° (outboard forward) 0° to 26° (outboard trailing) (aileron) Elevator Up 25° Down 16° Tab Up 20° Down 25° Flap interconnect (flap up) Down 12° (flap landing) Up 12° Rudder Left 20° Right 21° * Geared Tab - or + 11° Trim Tab - or + 25° See Maintenance Manual Part No. PSM-1-6-2 for procedure to rig control surface movements from stop to stop. *When Item 202(b) is incorporated then the rudder travel limits are: Left 17° Right 21°. Serial Nos. eligible 6 to 115 inclusive. The Canadian Department of Transport Certificate 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 eligibility 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 D.O.T. Type Approval No. A-82, Issue 3, dated June 12, 1967. (FAA Type Certificate No. A9EA)." Certification basis CAR 3 dated May 15, 1956 and Amendments 3-1 to 3-8 inclusive, plus Special Conditions for Mu lti-Engine Turbine Powered Aircraft dated November 6, 1964. Type Certificate No. A9EA issued June 22, 1966. Date of application for Type Certificate April 2, 1964. For this Model airplane intended for use in operations under FAR Part 135, the additional airworthiness requirements of Special Federal Aviation Regulation (SFAR) 23, dated January 7, 1969, and Amendment 1 to SFAR 23, dated December 24, 1969, are also included. See NOTES 3 and 8. Starboard (+177.0 in.) 1.5 1.2 11 TOTAL 3.0 2.4 22 Page 7 A9EA 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 Viking Air Limited (or Bombardier) Report A.E.R.O.C. 6.6.G.1. In addition, the following item of equipment is required: (a) Canadian D.O.T. approved Airplane Flight Manual, Part No. PSM-1-61-1A. III- Model DHC-6-200 (Normal Category), Approved April 1, 1968 by the FAA and March 29, 1968 by the Canadian Department of Transport (DOT). This Series may be identified by: (1) Aircraft nose configuration, See NOTE 6 for optional VAL (or BI) Mod. 6/1077 - Extended Nose that Increases the Volume and Weight Capacity of the Forward Baggage Compartment; and, (2) VAL (or BI) Mod. 6/1075 (Retrofit) or 6/1076 (New Production) -Increase in the Volume of the Rear Baggage Compartment. Engines 2 United Aircraft of Canada, Limited PT6A-20 Fuel MIL-J-5624E, Grades JP-1, JP-4, JP-5, or Arctic Diesel Fuel to UACL Specification CPW 46. (MIL-G-5572C Avgas (all grades) for emergency use only limited to 150 hours use in any one overhaul cycle.) Oil Synthetic types conforming to CPWA 202, latest issue, (UACL PT6 Engine Service Bulletin No. 1 lists approved brand oils.) Engine rating RATING E.S.H.P. S.H.P. Take-off (5 min.) *579 *550 Max. continuous *579 *550 *Available to 70°F (21°C) Ambient Temperature Engine limits Temperature Limits (Inter-Turbine) Take-off 1380° F ( 750° C) Max. Continuous 1380°F ( 750° C) Starting (2 sec.) 1994°F (1090° C) Torque Limits Take-off 42.5 p.s.i. (1315 ft.-lb.) Max. Continuous 42.5 p.s.i. (1315 ft.- lb.) Gas Generator Take-off 38,100 r.p.m. (101.5%) Max. Continuous 38,100 r.p.m. (101.5%) Oil Temperature Starting -40°C Min. Take-off 10°C to 99°C Max. Continuous 10°C to 99°C Oil Pressure Normal (28,000 r.p.m. & above) 65 to 85 p.s.i.g. Min. (below 28,000 r.p.m.) 40 p.s.i.g. Propeller Hartzell Hub HC-B3TN-3, -3B, -3BY Blades T10173+1, T10173E+1 Diameter 8 ft. 6 in. nominal (8 ft. 4 in. after repairs) Pitch Settings at 30" Station Feather +87° Take-off Low Pitch +16° Idle Blade Angle +12° Reverse Blade Angle - 14° Page 8 A9EA Propeller limits Propeller (Np) - Take-off Max. Continuous 2200 r.p.m. (100%) 2200 r.p.m. (100%) Landplane Skiplane Floatplane Airspeed Limits (CAS) Knots M.P.H. Knots M.P.H. Knots M.P.H. Vne (never exceed) 202* 232.7* 183* 211* 183* 211* Vno (max. structural cruising) 160** 184.3** 160** 184.3** 160** 184.3** Vp (design maneuvering) 130*** 149.8*** 130*** 149.8*** 130*** 149.8*** Vmc (minimum control) 68 78.3 68 78.3 64 78.3 Vfe (flaps extended) 100 115.2 100 115.2 100 115.2 0° to 20° Vfe (flaps extended) 85 97.9 85 97.9 85 97.9 20° to 40° *Reduce Vne 4.6 m.p.h. (4K) per 1000 ft. above 10000 ft. **Reduce Vno 3.5 m.p.h. (3K) per 1000 ft. above 10000 ft. ***Reduce Vp - Vno above 20000 ft. C.G. range (Landing With Mod. 6/1020 - "Fuselage Beam, Front Wing Spar Reinforcing" gear fixed) (All Model DHC-6-200 Aircraft Serial Nos. 116 to 230 inclusive have this Mod. embodied). 11,579 11,400 11,000 10,000 9000 20 22 36 ARM ARM 203.84 205.40 HORIZONTAL C.G. LIMIT - % MAC ARM 216.32 11,579 11,400 11,000 10,000 9000 20 22 23 36 ARM ARM 203.84 205.40 206.18 ARM 216.32 HORIZONTAL C.G. LIMIT - % MAC Floatplane Forward Limit 25% M.A.C. (STA. 207.74) at all weights up to max. of 11,600 lb. Aft Limit 32% M.A.C. (STA. 213.20) at all weights up to max. OF 11,600 lb. Max Take-Off Weight SKIPLANE Max Landing WT Below -20°F Max Landing WT Above -20°F GROSS WEIGHT - LB. GROSS WEIGHT - LB. Max Take-Off Weight Max Landing WT Above -20°F Max Landing WT Below -20°F LANDPLANE Page 9 A9EA Empty weight C.G. range None Landplane (lb.) Skiplane (lb.) Floatplane (lb.) (With Item 201(a)&(b)) (With Item 202(a)&(b)) Take-off 11579 11579 11600 Landing 11400* 11400* 11600 *See NOTE 5 - Temperature Limitations Minimum Crew One (pilot). (+95.0 in.) No. of seats 21 (including two at Stn. +95.0 in.) - Limited by approved seating arrangement. (See Weight and Balance Handbook). Max. 24 (including two at Stn. +95.0 in.) -Limited by emergency exit requirements. (Approval of seating arrangement is required). Cargo loading limitations See Weight and Balance Handbook (PSM 1-6-8) Maximum baggage Forward - Short Nose (+ 41.0 in.) 200 lb. Max. Forward - Long Nose (Mod. 6/1077) Rear Rear Extension ( +25.0 in.) (+354.0 in.) (+391.0 in.) 300 lb. Max. 500 lb. Max.* 50 lb. Max.* *Total Rear + Rear Extension not to exceed 500 lb. maximum. Fuel capacity *USABLE F UEL U.S. GALS. IMPERIAL GALS. Forward Tank (+162.5 in.) 181 151 Rear Tank (+240.0 in.) 197 164 TOTAL 378 315 *See NOTE 1(b) for Weight and Balance. Oil capacity **USABLE OIL U.S. GALS. IMPERIAL GALS. WEIGHT LB. Port (+177.0 in.) 1.5 1.2 11 ** See N OTE 1(c) for Weight and Balance. Maximum Operating 25000 ft. (when supplementary breathing equipment is provided for Altitude all occupants). Control surface movements Aileron (with flaps up) Up 17.5° Down 16° (with flaps in landing position) Up 25° Down 17.5° Trim Tab + or -15° Geared Tab (flap up) Up 16° Down 17.5° Flaps (inboard forward) 0° to 40° (inboard trailing) 0° to 62.5° (outboard forward) 0° to 26° (outboard trailing) (aileron) Elevator Up 25° Down 16° Tab Up 20° Down 25° Flap interconnect (flap up) Down 12° (flap landing) Up 12° Rudder Left 20° Right 21° * (Skiplane) Left 18° Right 21° Geared Tab + or -11° Trim Tab + or -25° See Maintenance Manual Part No. PSM-1-6-2 for procedure to rig control surface movements from stop to stop. * When Item 202(b) is incorporated then the rudder travel limits are: Left 17° Right 21°. Starboard (+177.0 in.) 1.5 1.2 11 TOTAL 3.0 2.4 22 Page 10 A9EA Serial Nos. eligible 116 to 230 inclusive (except 130 and 210) plus any other Series aircraft that has been modified to embody the following significant Model Mod. 6/1020, 1075 or 1076, 1077. The Canadian Department of Transport Certificate 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 eligibility 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 D.O.T. Type Approval No. A-82, Issue 4, dated December 20, 1968 (FAA Type Certificate No. A9EA)." Certification basis CAR 3 dated May 15, 1956 and Amendments 3-1 to 3-8 inclusive, plus Special Conditions for Multi-Engine Turbine Powered Aircraft dated November 6, 1964. Type Certificate No. A9EA issued June 22, 1966. Date of application for Type Certificate April 2, 1964. For this Model airplane intended for use in operations under FAR Part 135, the additional airworthiness requirements of Special Federal Aviation Regulation (SFAR) 23, dated January 7, 1969, and Amendment 1 to SFAR 23, dated December 24, 1969, are also included. See NOTES 3 and 8. 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 Viking Air Limited (or Bombardier) Report A.E.R.O.C. 6.6.G.1. In addition, the following item of equipment is required: (a) Canadian D.O.T. approved Airplane Flight Manual, PSM-1-62-1A. IV - Model DHC-6-300 (Normal Category), Approved May 8, 1969 by the FAA and April 25, 1969 by the Canadian Department of Transport (DOT). This is the third production series of the Type DHC-6. This series is identified primarily on basis of: (1) PT6A-27 engine in place of -20 engine; (2) Increase in All-Up-Weight to the maximum allowed by CAR 3 of 12,500 lb.: (3) Addition of two forward exits and deletion of roof exit; and, (4) Aircraft nose configuration, See NOTE 6 for optional VAL (or BI) Mod. 6/1077 - Extended Nose that Increases the Volume and Weight Capacity of the Forward Baggage Compartment. Engines 2 United Aircraft of Canada, Limited PT6A-27 Fuel MIL-J-5624E, Grades JP-1, JP-4, JP-5, or Arctic Diesel Fuel to UACL Specification CPW 46. (MIL-G-5572C Avgas (all grades) for emergency use only - limited to 150 hours use in any one overhaul cycle.) Oil Synthetic types conforming to CPWA 202, latest issue. (UACL PT6 Engine Service Bulletin No. 1 lists approved brand oils.) Engine rating RATING E.S.H.P. S.H.P. Take-off 652* 620* Max. continuous 652* 620* *Available to 91°F (33°C) Ambient Temperature (S.L.) Page 11 A9EA Engine limits Temperature Limits (Inter-Turbine) Take-off 1336°F ( 725° C) Max. Continuous 1336°F ( 725° C) Starting (2 sec.) 1994°F (1090° C) Torque Limits Take-off 50 p.s.i. (1536 ft.-lb.) Max. Continuous 50 p.s.i. (1536 ft.-lb.) Gas Generator Take-off 38,100 r.p.m. (101.5%) Max. Continuous 38,100 r.p.m. (101.5%) Oil Temperature Starting -40°C Minimum Take-off 10°C to 99°C Max. Continuous 10°C to 99°C 5 Minute Limit 104°C Oil Pressure Normal (28,000 r.p.m. & above) 80 to 100 p.s.i.g. Min. (below 28,000 r.p.m.) 40 p.s.i.g. Propeller Hartzell Hub HC-B3TN-3D (Y)* Blades T10282H (B)**+0 Diameter 8 ft. 6 in. nominal (8 ft. 4 in. after repairs) *(Y) designates Zero Thrust Latches **(B) designates De-icing Boots. Pitch Settings at 30" Station Feather +87° Take-off Low Pitch +17° Idle Blade Angle +11° Reverse Blade Angle -15° Propeller limits Propeller (Np) - Take-off 2110 r.p.m. (96%) Max. Continuous 2110 r.p.m. (96%) Airspeed limits (CAS) Knots Landplane M.P.H. Knots Floatplane M.P.H. Vmo (Max. Operating) S/L 160 184.3 160 184.3 5000 ft. 155 179 155 179 10000 ft. 150 173 150 173 15000 ft. 145 167 145 167 20000 ft. 130 149.8 130 149.8 25000 ft. 115 132.5 115 132.5 Vp (Design maneuvering) 136* 156.7* 136* 156.7* Vmc (Minimum control) 66 76 67 76 Vfe (Flaps extended) 0° to 10° 102 117.5 102 117.5 10° to 37-1/2° 95 109.5 95 109.5 *Reduce Vp to Vmo above 18000 ft. Page 12 A9EA Max Take-Off Weight Max Landing Weight LANDPLANE AND WHEEL-SKIPLANE C.G. range (Landing gear fixed) 12,500 12,300 11,600 11,000 9,000 20 25 36 ARM 203.84 ARM 207.74 ARM 216.32 HORIZONTAL C.G. LIMITS - % MAC Floatplane F orward Limit 25% M.A.C. (STA. 207.74) at all weights up to max. of 12500 lb. Aft Limit 32% M.A.C. (STA. 213.20) at all weights up to max. of 12500 lb. Empty weight C.G. range None Maximum weights Landplane (lb. ) (With Item 201(a) or (b)) Floatplane (lb.) (With Item 202(a) Skiplane (lb.) Take-off 12500 12500 12500 Landing 12300* 12500 12300* * Main Wheel Tire Pressure (Below -20°F) 38 p.s.i.g. 34 p.s.i.g. Minimum Crew One pilot. (+95.0 in.) No. of seats 22 (including two at Stn. +95.0 in.) - Limited by approved seating arrangement. (See Weight and Balance Handbook). Cargo loading limitations See Weight and Balance Handbook (PSM 1-63-8) Maximum baggage Forward - Short Nose (+ 41.0 in.) 200 lb. Max. Forward - Long Nose (Mod. 6/1077) ( +25.0 in.) 300 lb. Max. Rear (+354.0 in.)500 lb. Max.* Rear Extension (+391.0 in.)150 lb. Max.* * Total Rear + Rear Extension not to exceed 500 lb. maximum. See Item 208(a) for approved baggage pod installation. Fuel capacity