TCDS A17EU

Page No. 1 2 3 4 5 6 7 8 9 10 11 12 13 14 15 16 Rev. No. 28 28 28 28 28 28 28 28 28 28 28 28 28 28 28 28 Page No. 17 18 19 20 21 22 23 24 25 26 27 28 29 30 31 Rev. No. 28 28 28 28 28 28 28 26 27 28 28 28 28 28 28 DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION A17EU Revision 28 Britten-Norman Aerospace, Ltd. BN2 BN2A-26 BN2A BN2A-27 BN2A-2 BN2B-20 BN2A-3 BN2B-21 BN2A-6 BN2B-26 BN2A-8 BN2B-27 BN2A-9 BN2T BN2A-20 BN2T-4R BN2A-21 BN2T-4S August 19, 2026 TYPE CERTIFICATE DATA SHEET No. A17EU This data sheet which is part of Type Certificate No. A17EU prescribes conditions and limitations under which the product for which the Type Certificate was issued meets the airworthiness requirements of the Federal Aviation Regulations. Type Certificate Holder. Britten-Norman Aerospace Ltd. Bembridge Airport Isle of Wight, PO35 5PR United Kingdom Type Certificate Holder Record Pilatus Britten-Norman Limited transferred TC A17EU to B-N Group Ltd. on December 9, 2002. B-N Group Ltd transferred TC A17EU to Britten-Norman Aircraft Ltd. On December 7, 2022. Britten-Norman Aircraft Ltd. transferred TC A17EU to Britten-Norman Aerospace Ltd. on April 11, 2024. I. Model BN2, 10 PCLM (Normal Category), approved December 19, 1967 Model BN2A, 10 PCLM (Normal Category), approved September 5, 1968 (Model BN2A is similar to Model BN2 except for orifice Modification of the main landing gear shock absorbers). Engines. 2 Lycoming O-540-E4C5 (See NOTE 8) Fuel. 91/96 minimum grade aviation gasoline; 100L; 100LL. Engine Limits. For all operations, 2,700 r.p.m (260 hp.). Propeller and Propeller Limits. Hartzell HC-C2YK-2B/C8477-4, HC-C2YK-2B/C8477A-4, HC-C2YK-2B/8477-4, HC-C2YK-2C/C8477-4, HC-C2YK-2C/C8477A-4 or HC-C2YK-2CF/FC8477A-4 (See NOTE 9) Diameter range 80" maximum, 78" minimum (No further reduction permitted) Pitch setting at 30 in. station: See NOTE 17. Low 12.5° ± .1° High 78.6° ± .5° Governor: Woodward 210275, F210444, 210715, D210659, B210715, G210659 (See NOTE 10) Spinner: Hartzell 836-29 Airspeed Limits VNE (never exceed) 183 knots (210 m.p.h.) (IAS) VNO (max. structural cruising) 141 knots (162 m.p.h.) VA (maneuvering) 112 knots (129 m.p.h.) VFE (flaps extended) 89 knots (102 m.p.h.)- (See NOTE 6) VMC (minimum control) 39 knots ( 45 m.p.h.) Page 2 of 31 A17EU I. Model BN2, Model BN2A (cont’d) C.G. Range. Model BN2 (+17 in.) to (+25.6 in.) at 4,290 lb. (+21 in.) to (+25.6 in.) at 5,700 lb. Straight line variation between points. Model BN2A (+17 in.) to (+25.6 in.) at 5,030 lb. (+21 in.) to (+25.6 in.) at 6,000 lb. Straight line variation between points. Empty Weight C.G. Range. None. Datum. Wing leading edge (Stn. 134.5 in.) Maximum Take-off weight Model BN2 5,700 lb. (See NOTE 4) Maximum Landing weight 5,700 lb. Maximum Take-off weight Model BN2A 6,000 lb. Maximum Landing weight 6,000 lb. Maximum Zero Fuel Weight. Model BN2 5,700 lb. Model BN2A 5,800 lb. Number of seats. 10 (2 at -45.2 in.), (2 at -15.0 in.), (2 at + 15.1 in.), (2 at +44.4 in.) and (2 at +72.4 in.) Maximum Baggage. 250 lb. (+93 in.) (Pre-Mod. NB/M/426) 400 lb. (+93 in.) (Post-Mod. NB/M/426) Fuel Capacity. 137 U.S. gal. total (two 68.5 U.S. gal. wing tanks at +27.0 in.) (116 U.S. gal. usable when Fuel Gauging Mod. NB/M/240 is not incorporated) (130 U.S. gal. usable when Fuel Gauging Mod. NB/M/240 is incorporated) (See NOTE 1A) Oil Capacity. 24 qt. total (12 U.S. qt. per engine at -2.6 in.) See NOTE 1A Control Surface Movements Wing Flaps Full Up 0° (Down) Full Down 56° (Down) Aileron Up 25° Down 15° Elevator Up 24° Down 17° Elevator trim tab* Up 13° Down 18° 1/2° Rudder Right 30° Left 30° Rudder tab Right 20° Left 20° * See NOTE 11. II. Model BN2A-6, 10 PCLM (Normal Category), approved October 22, 1970 (Model BN2A-6 is similar to Model BN2A except for aerodynamic refinements to the wing leading edge between the fuselage and engine nacelle) See NOTE 5 Engines. 2 Lycoming O-540-E4C5 (See NOTE 8) Fuel. 91/96 minimum grade aviation gasoline; 100L; 100LL. Engine Limits. For all operations 2,700 r.p.m (260 hp.). Page 3 of 31 A17EU II. Model BN2A-6 (cont’d) Propeller and Propeller Limits. Hartzell HC-C2YK-2B/C8477-4, HC-C2YK-2B/C8477A-4, HC-C2YK-2B/8477-4, HC-C2YK-2C/C8477-4, HC-C2YK-2C/C8477A-4 or HC-C2YK-2CF/FC8477A-4 (See NOTE 9) Diameter range 80" maximum, 78" minimum (No further reduction permitted) Pitch setting at 30 in. station: See NOTE 17 Low 12.5° ± .1° High 78.6° ± .5° Governor: Woodward 21025, F210444, 210715, D210659, B210715, G210659 (See NOTE 10) Spinner: Hartzell 836-29 Airspeed Limits VNE (never exceed) 177 knots (204 m.p.h.) (IAS) VNO (max. structural cruising) 134 knots (154 m.p.h.) VA (maneuvering) 107 knots (123 m.p.h.) VFE (flaps extended) 88 knots (101 m.p.h.) - (See NOTE 6) VMC (minimum control) 39 knots ( 45 m.p.h.) C.G. Range. (+27.0 in.) to (+25.6 in.) at 5,030 lb. (+21.0 in.) to (+25.6 in.) at 6,200 lb. Straight line variation between points. Empty Weight C.G. Range. None. Datum. 0.8 in. behind cambered leading edge of wing between engine nacelle and fuselage (Sta. 134.5) Maximum take-off weight 6,200 lb. Maximum landing weight 6,200 lb. Maximum Zero Fuel Weight. 5,800 lb. Number of seats. 10 (2 at -45.2 in.), (2 at -15.0 in.), (2 at + 15.1 in.), (2 at +44.4 in.) and (2 at +72.4 in.) Maximum Baggage. 250 lb. (+93 in.) (Pre-Mod. NB/M/426) 400 lb. (+93 in.) (Post-Mod. NB/M/426) Fuel Capacity. 137 U.S. gal. total (Two 68.5 U.S. gal. wing tanks at +27.0 in.) (116 U.S. gal. usable when Fuel Gauging Mod. NB/M/240 is not incorporated) (130 U.S. gal. usable when Fuel Gauging Mod. NB/M/240 is incorporated) See NOTE 1A Oil Capacity. 24 U.S. qt. total (12 U.S. qt. per engine at -2.6 in.) See NOTE 1A Control Surface Movements. Wing flaps Full Up 0º(Down) Full Down 56º(Down) Aileron Up 25º Down 15º Elevator Up 24º Down 17º Elevator trim tab* Up 13º Down 18 1/2º Rudder Right 30º Left 30º Rudder tab Right 20º Left 20º *See NOTE 11. Page 4 of 31 A17EU III. Model BN2A-8, 10 PCLM (Normal Category), approved June 28, 1971. (Model BN2A-8 is similar to the Model BN2A-6 except the wing flaps are drooped 6° when in the full up position) See NOTE 5. Engines. 2 Lycoming O-540-E4C5 (see NOTE 8) Fuel. 91/96 minimum grade aviation gasoline; 100L; 100LL Engine Limits. For all operations 2,700 r.p.m. (260 hp.) Propeller and Propeller Limits. Hartzell HC-C2YK-3B/C8477-4, HC-C2YK-2B/C8477A-4, HC-C2YK-2B/8477-4, HC-C2YK-2C/C8477-4, HC-C2YK-2C/C8477A-4, or HC-C2YK-2CF/FC8477A-4 (See NOTE 9). Diameter range 80" maximum, 78" minimum (No further reduction permitted) Pitch setting at 30 in. station: See NOTE 17 Low 12.5° ± .1° High 78.6° ± .5° Governor: Woodward 21075, F210444, 210715, D210659, B210715, G210659 (See NOTE 10) Spinner: Hartzell 836-29 Airspeed Limits (IAS). VNE (never exceeded) 177 knots (204 m.p.h.) VNO (maximum structural cruising) 134 knots (154 m.p.h.) VA (maneuvering) 107 knots (123 m.p.h.) VFE (flaps extended) 88 knots (101 m.p.h.) (see NOTE 6) VMC (minimum control) 39 knots ( 45 m.p.h.) C.G. Range. (+17.0 in.) to (+25.6 in.) at 5,030 lb. (+21.0 in.) to (+25.6 in.) at 6,200 lb. Straight line variation between points Empty Weight C.G. Range. None. Datum. 0.8 in. behind cambered leading edge of wing between engine nacelle and fuselage (Sta. 134.5). Maximum Take-off Weight. 6,200 lb. Maximum Landing Weight. 6,200 lb. Maximum Zero Fuel Weight. 6,150 lb. Number of Seats. 10 (2 at -45.2 in.), (2 at -15.0 in.), (2 at +15.1 in.), (2 at +44.4 in.) and (2 at +72.4 in.) Maximum Baggage. 250 lb. (+93 in.) (Pre-Mod. NB/M/426) 400 lb. (+93 in.) (Pre-Mod. NB/M/426) Fuel Capacity. 137 gal. U.S. total (Two 68.5 U.S. gal. wing tanks at +27.0 in.) (116 U.S. gal. usable when Fuel Gauging Mod. NB/M/240 is not incorporated) (130 U.S. gal. usable when Fuel Gauging Mod. NB/M/240 is incorporated) See NOTE 1A. Oil Capacity. 24 U.S. qt. total (12 U.S. qt. per engine at -2.6 in.) See NOTE 1A. Control Surface Movements. Wing flaps Full Up 6° (Down) Full Down 56° (Down) Aileron Up 25° Down 15° Elevator Up 24° Down 17° Elevator trim tab* Up 13° Down 18 1/2° Rudder Right 30° Left 30° Rudder tab Right 20° Left 20° Page 5 of 31 A17EU IV. Model BN2A-2, 10 PCLM (Normal Category), approved June 28, 1971 (Model BN2A-2 is similar to Model BN2A-8 except for the powerplant installation) See NOTE 5. Engines. 2 Lycoming IO-540-K1B5 (See NOTE 8) Fuel. 100/130 minimum grade aviation gasoline; 100L; 100LL. Engine Limits. For all operations 2,700 r.p.m. (300 hp.) Propeller and Propeller Limits. Hartzell HC-C2YK-2B/C8477-4, HC-C2YK-2B/C8477A-4, HC-C2YK-2B/8477-4, HC-C2YK-2C/C8477-4, HC-C2YK-2C/C8477A-4 or HC-C2YK-2CF/FC8477A-4 (See NOTE 9) Diameter range 80" maximum, 78" minimum (No further reduction permitted) See NOTE 12. Pitch setting at 30 in. station: See NOTE 17 Low 12.5º + .1º High 78.6º + .5º Governor: Woodward 210275, F210444, 210715, D210659, B210715, G210659 (See NOTE 10) Spinner: Hartzell 836-29 Placard required: "Manifold pressure must not exceed 23 in. Hg. at engine speeds below 2200 r.p.m." Airspeed Limits VNE (never exceed) 184 knots (212 m.p.h.) (IAS). VNO (max. structural cruising) 141 knots (162 m.p.h.) VA (maneuvering) 107 knots (123 m.p.h.) VFE (flaps extended) 88 knots (101 m.p.h.)-(See NOTE 6) VMC (minimum control) 39 knots ( 45 m.p.h) C.G. Range. (+17.0 in.) to (+25.6 in.) at 5,030 lb. (+21.0 in.) to (+25.6 in.) at 6,300 lb. Straight line variation between points. Empty Weight C.G. Range. None Datum. 0.8 in. behind cambered leading edge of wing between engine nacelle and fuselage (Sta. 134.5) Maximum Take-off Weight. 6,300 lb. Maximum Landing Weight. 6,300 lb. Maximum Zero Fuel Weight. 6,150 lb. Number of Seats. 10 (2 at -45.2 in.), (2 at -15.0 in.), (2 at +15.1 in.), (2 at +44.4 in.), and (2 at +72.4 in.) Maximum Baggage. 250 lb. (+93 in.) (Pre-Mod. NB/M/426) 400 lb. (+93 in.) (Post-Mod. NB/M/426) Fuel Capacity. 137 U.S. gal. total (two 68.5 U.S. gal. wing tanks at +27.0 in.) (116 U.S. gal. usable when Fuel Gauging Mod. NB/M/240 is not incorporated) (130 U.S. gal. usable when Fuel Gauging Mod NB/M/240 is incorporated) See NOTE 1A. Oil Capacity. 24 U.S. qt. total (12 U.S. qt. per engine at -2.6 in.) See NOTE 1A. Control Surface Movements Wing Flaps Full Up 6º(Down) Full Down 56º(Down) Aileron Up 25º Down 15º Elevator Up 24º Down 17º Elevator trim tab* Up 13º Down 18 1/2º Rudder Right 30º Left 30º Rudder tab Right 20º Left 20º *See NOTE 11. Page 6 of 31 A17EU V. Model BN2A-9, 10 PCLM (Normal Category), approved May 30, 1972 (Model BN2A-9 is similar to the Model BN2A-8 except that wing tip fuel tanks are installed in accordance with Modification NB/M/364) See NOTE 5. Engines. 2 Lycoming O-540-E4C5 (See NOTE 8) Fuel. 91/96 minimum grade aviation gasoline; 100L; 100LL. Engine Limits. For all operations 2,700 r.p.m. (260 hp.) Propeller and Propeller Limits. Hartzell HC-C2YK-2B/C8477-4, HC-C2YK-2B/C8477A-4, HC-C2YK-2B/8477-4, HC-C2YK-2C/C8477-4, HC-C2YK-2C/C8477A-4, or HC-C2YK-2CF/FC8477A-4 (See NOTE 9) Diameter range 80" maximum, 78" minimum (No further reduction permitted) Pitch setting at 30 in. station: See NOTE 17 Low 12.5º + .1º High 78.6º + .5º Governor: Woodward 210275, F210444, 210715, D210659, B210715, G210659 (See NOTE 10) Spinner: Hartzell 836-29 Airspeed Limits VNE (never exceed) 177 knots (204 m.p.h.) (IAS). VNO (max. structural cruising) 134 knots (154 m.p.h.) VA (maneuvering) 107 knots (123 m.p.h.) VFE (flaps extended) 88 knots (101 m.p.h.) (See NOTE 6) VMC (minimum control) 39 knots ( 45 m.p.h) C.G. Range. (+17.0 in.) to (+25.6 in.) at 5,030 lb. (+21.0 in.) to (+25.6 in.) at 6,300 lb. Straight line variation between points. Empty Weight C.G. Range None Datum. 0.8 in. behind cambered leading edge of wing between engine nacelle and fuselage (Sta. 134.5) Maximum Take-off Weight 6,300 lb. Maximum Landing Weight. 6,300 lb. Maximum Zero Fuel Weight. 5,810 lb. Number of Seats. 10 (2 at -45.2 in.), (2 at -15.0 in.), (2 at +15.1 in.), (2 at +44.4 in.), and (2 at +72.4 in.) Maximum Baggage. 250 lb. (+93 in.) (Pre-Mod. NB/M/426) 400 lb. (+93 in.) (Post-Mod. NB/M/426) Fuel Capacity. 196 U.S. gal. total (two 68.5 U.S. gal. wing tanks at +27.0 in. and two 29.5 U.S. gal. wing tip tanks at +34.7 in.) (190 U.S. gal. usable) See NOTE 1C . Oil Capacity. 24 U.S. qt. total (12 U.S. qt. per engine at -2.6 in.) See NOTE 1C. Control Surface Movements Wing Flaps Full Up 6º(Down) Full Down 56º(Down) Aileron Up 25º Down 15º Elevator Up 24º Down 17º Elevator Trim Tab* Up 13º Down 18 1/2º Rudder Right 30º Left 30º Rudder Tab Right 20º Left 20º *See NOTE 11. Page 7 of 31 A17EU VI. Model BN2A-3, 10 PCLM (Normal Category), approved May 30, 1972 (Model BN2A-3 is similar to the Model BN2A-2 except that wing tip fuel tanks are fitted to Modification NB/M/364) See NOTE 5. Engines. 2 Lycoming IO-540-K1B5 (See NOTE 8) Fuel. 100/130 minimum grade aviation gasoline; 100L; 100LL Engine Limits. For all operations 2,700 r.p.m. (300 hp.) Propeller and Propeller Limits. Hartzell HC-C2YK-2B/C8477-4, HC-C2YK-2B/C8477A-4, HC-C2YK-2B/8477-4, HC-C2YK-2C/C8477-4, HC-C2YK-2C/C8477A-4, or HC-C2YK-2CF/FC8477A-4 (See NOTE 9) Diameter range 80" maximum, 78" minimum (No further reduction permitted) See NOTE 12. Pitch setting at 30 in. station: See NOTE 17. Low 12.5º + .1º High 78.6º + .5º Governor: Woodward 210275, F210444, 210715, D210659, B210715, G210659 (See NOTE 10) Spinner: Hartzell 836-29 Placard required: "Manifold pressure must not exceed 23 in. Hg. at engine speeds below 2200 r.p.m." Airspeed Limits VNE (never exceed) 184 knots (212 m.p.h.) (IAS). VNO (max. structural cruising) 141 knots (162 m.p.h.) VA (maneuvering) 107 knots (123 m.p.h.) VFE (flaps extended) 88 knots (101 m.p.h.) (See NOTE 6) VMC (minimum control) 39 knots ( 45 m.p.h.) C.G. Range. (+17.0 in.) to (+25.6 in.) at 5,030 lb. (+21.0 in.) to (+25.6 in.) at 6,300 lb. Straight line variation between points. Empty Weight C.G. Range. None. Datum. 0.8 in. behind cambered leading edge of wing between engine nacelle and fuselage (Sta. 134.5) Maximum Take-off Weight. 6,300 lb. Maximum Landing Weight. 6,300 lb. Maximum Zero Fuel Weight. 5,810 lb. Number of Seats. 10 (2 at -45.2 in.), (2 at -15.0 in.), (2 at +15.1 in.), (2 at +44.4 in.), and (2 at +72.4 in.) Maximum Baggage. 250 lb. (+93 in.) (Pre-Mod. NB/M/426) 400 lb. (+93 in.) (Post-Mod. NB/M/426) Fuel Capacity. 196 U.S. gal. total (two 68.6 U.S. gal. wing tanks at +27.0 in. and two 29.5 U.S. gal. wing tip tanks at +34.7 in.) (190 U.S. gal. usable) See NOTE 1C Oil Capacity. 24 U.S. qt. total (12 U.S. qt. per engine at -2.6 in.) See NOTE 1C. Control Surface Movements. Wing Flaps Full Up 6º(Down) Full Down 56º(Down) Aileron Up 25º Down 15º Elevator Up 24º Down 17º Elevator Trim Tab* Up 13º Down 18 1/2º Rudder Right 30º Left 30º Rudder Tab Right 20º Left 20º *See NOTE 11. Page 8 of 31 A17EU VII. Model BN2A-20, 10 PCLM (Normal Category), approved May 16, 1974 (Model BN2A-20 is similar to the Model BN2A-2 except that stiffeners are added to the engine firewalls to Modification NB/M/631) . Engines. 2 Lycoming IO-540-K1B5 (See NOTE 8) Fuel. 100/130 minimum grade aviation gasoline; 100L; 100LL. Engine Limits. For all operations 2,700 r.p.m. (300 hp.) Propeller and Propeller Limits. Hartzell HC-C2YK-2B/C8477-4, HC-C2YK-2B/C8477A-4, HC-C2YK-2B/8477-4, HC-C2YK-2C/C8477-4, HC-C2YK-2C/C8477A-4, or HC-C2YK-2CF/FC8477A-4 (See NOTE 9) Diameter range 80" maximum, 78" minimum (No further reduction permitted) See NOTE 12. Pitch setting at 30 in. station: See NOTE 17. Low 12.5º + .1º High 78.6º + .5º Governor: Woodward 210275, F210444, 210715, D210659, B210715, G210659 (See NOTE 10) Spinner: Hartzell 836-29 Placard required: "Manifold pressure must not exceed 23 in. Hg. at engine speeds below 2200 r.p.m." Airspeed Limits VNE (never exceed) 184 knots (212 m.p.h.) (IAS). VNO (max. structural cruising) 141 knots (162 m.p.h.) VA (maneuvering) 107 knots (123 m.p.h.) VFE (flaps extended) 88 knots (101 m.p.h.) (See NOTE 6) VMC (minimum control) 39 knots ( 45 m.p.h.) C.G. Range. (+17.0 in.) to (+25.6 in.) at 5,030 lb. (+20.9 in.) to (+25.6 in.) at 6,560 lb. Straight line variation between points. Empty Weight C.G. Range. None Datum. 0.8 in. behind cambered leading edge of wing between engine nacelle and fuselage (Sta. 134.5) Maximum Take-off Weight. 6,560 lb. Maximum Landing Weight. 6,300 lb. (See NOTE 20) Maximum Zero Fuel Weight. 6,300 lb. Number of Seats. 10 (2 at -45.2 in.), (2 at -15.0 in.), (2 at +15.1 in.), (2 at +44.4 in.), and (2 at +72.4 in.) Maximum Baggage. 250 lb. (+93 in.) (Pre-Mod. NB/M/426) 400 lb. (+93 in.) (Post-Mod. NB/M/426) Fuel Capacity. 137 U.S. gal. total (two 68.5 U.S. gal. wing tanks at +27.0 in.) (116 U.S. gal. usable when Fuel Gauging Mod. NB/M/240 is not incorporated) (130 U.S. gal. usable when Fuel Gauging Mod NB/M/240 is incorporated) See NOTE 1A. Oil Capacity. 24 U.S. qt. total (12 U.S. qt. per engine at -2.6 in.) See NOTE 1A. Control Surface Movements. Wing Flaps Full Up 6º(Down) Full Down 56º(Down) Aileron Up 25º Down 15º Elevator Up 24º Down 17º Elevator Trim Tab* Up 13º Down 18 1/2º Rudder Right 30º Left 30º Rudder Tab Right 20º Left 20º *See NOTE 11. Page 9 of 31 A17EU VIII. Model BN2A-21, 10 PCLM (Normal Category), approved May 16, 1974 (Model BN2A-21 is similar to the Model BN2A-3 except that stiffeners are added to the engine firewalls to Modification NB/M/631) Engines. 2 Lycoming IO-540-K1B5 (See NOTE 8) Fuel. 100/130 minimum grade aviation gasoline; 100L; 100LL. Engine Limits. For all operations 2,700 r.p.m. (300 hp.) Propeller and Propeller Limits. Hartzell HC-C2YK-2B/C8477-4, HC-C2YK-2B/C8477A-4, HC-C2YK-2B/8477-4, HC-C2YK-2C/C8477-4, HC-C2YK-2C/C8477A-4, or HC-C2YK-2CF/FC8477A-4 (See NOTE 9) Diameter range 80" maximum, 78" minimum (No further reduction permitted) See NOTE 12. Pitch setting at 30 in. station: See NOTE 17. Low 12.5º + .1º High 78.6º + .5º Governor: Woodward 210275, F210444, 210715, D210659, B210715, G210659 (See NOTE 10) Spinner: Hartzell 836-29 Placard required: "Manifold pressure must not exceed 23 in. Hg. at engine speeds below 2200 r.p.m." Airspeed Limits VNE (never exceed) 184 knots (212 m.p.h.) (IAS). VNO (max. structural cruising) 141 knots (162 m.p.h.) VA (maneuvering) 107 knots (123 m.p.h.) VFE (flaps extended) 88 knots (101 m.p.h.) (See NOTE 6) VMC (minimum control) 39 knots ( 45 m.p.h.) C.G. Range. (+17.0 in.) to (+25.6 in.) at 5,030 lb. (+21.0 in.) to (+25.6 in.) at 6,600 lb. Straight line variation between points. Empty Weight C.G. Range. None Datum. 0.8 in. behind cambered leading edge of wing between engine nacelle and fuselage (Sta. 134.5) Maximum Take-off Weight. 6,600 lb. Maximum Landing Weight. 6,300 lb. (See NOTE 20) Maximum Zero Fuel Weight. 5,910 lb. Number of Seats. 10 (2 at -45.2 in.), (2 at -15.0 in.), (2 at +15.1 in.), (2 at +44.4 in.), and (2 at +72.4 in.) Maximum Baggage. 250 lb. (+93 in.) (Pre-Mod. NB/M/426) 400 lb. (+93 in.) (Post-Mod. NB/M/426) Fuel Capacity. 196 U.S. gal. total (two 68.5 U.S. gal. wing tanks at +27.0 in. and two 29.5 U.S. gal. wing tip tanks at +34.7 in.) (190 U.S. gal. usable) See NOTE 1C Oil Capacity. 24 U.S. qt. total (12 U.S. qt. per engine at -2.6 in.) See NOTE 1C. Control Surface Movements. Wing Flaps Full Up 6º(Down) Full Down 56º(Down) Aileron Up 25º Down 15º Elevator Up 24º Down 17º Elevator Trim Tab* Up 13º Down 18 1/2º Rudder Right 30º Left 30º Rudder Tab Right 20º Left 20º *See NOTE 11. Page 10 of 31 A17EU IX. Model BN2A-26, 10 PCLM (Normal Category), approved April 6, 1977 (Model BN2A-26 is similar to Model BN2A-8 except that stiffeners are added to the engine firewalls to Modification NB/M/631) See NOTE 5. Engines. 2 Lycoming O-540-E4C5 (See NOTE 8) Fuel. 91/96 minimum grade aviation gasoline; 100L; 100LL. Engine Limits. For all operations 2,700 r.p.m. (260 hp.) Propeller and Propeller Limits. Hartzell HC-C2YK-2B/C8477-4, HC-C2YK-2B/C8477A-4, HC-C2YK-2B/8477-4, HC-C2YK-2C/C8477-4, HC-C2YK-2C/C8477A-4, or HC-C2YK-2CF/FC8477A-4 (See NOTE 9) Diameter range 80" maximum 78" minimum (No further reduction permitted) Pitch setting at 30 in. station: See NOTE 17. Low 12.5º + .1º High 78.6º + .5º Governor: Woodward 210275, F210444, 210715, D210659, B210715, G210659 (See NOTE 10) Spinner: Hartzell 836-29 Airspeed Limits VNE (never exceed) 177 knots (204 m.p.h.) (IAS). VNO (max. structural cruising) 134 knots (154 m.p.h.) VA (maneuvering) 107 knots (123 m.p.h.) VFE (flaps extended -56º) 88 knots (101 m.p.h.) VFE (flaps extended -25º) 114 knots (131 m.p.h.) VMC (minimum control) 39 knots ( 45 m.p.h.) C.G. Range. (+17.0 in.) to (+25.6 in.) at 5,030 lb. (+21.0 in.) to (+25.6 in.) at 6,200 lb. Straight line variation between points. Empty Weight C.G. Range. None Datum. 0.8 in. behind cambered leading edge of wing between engine nacelle and fuselage (Sta. 134.5) Maximum Take-off Weight. 6,200 lb. Maximum Landing Weight. 6,200 lb. (See NOTE 20) Maximum Zero Fuel Weight. 6,200 lb. Number of Seats. 10 (2 at -45.2 in.), (2 at -15.0 in.), (2 at +15.1 in.), (2 at +44.4 in.), and (2 at +72.4 in.) Maximum Baggage. 250 lb. (+93 in.) (Pre-Mod. NB/M/426) 400 lb. (+93 in.) (Post-Mod. NB/M/426) (See NOTE 7) Fuel Capacity. 137 U.S. gal. total (two 68.5 U.S. wing tanks at +27.0 in.) (116 U.S. gal. usable when Fuel Gauging Modification NB/M/240 is no incorporated) (130 U.S. gal. usable when Fuel Gauging Modification NB/M/240 is incorporated) See NOTE 1A.