# TCDS A17EU: Britten-Norman Aerospace Ltd. - Type: Type certificate data sheet - Status: Current - Holder: Britten-Norman Aerospace Ltd. - Revision: 28 - Revised: August 19, 2026 - Product: Aircraft, Small Airplane - Certification basis: Part 23, Part 21 - Registered aircraft: 73, by the registry models matched to it (OpenAirDocs) - Data sheet PDF: https://openairdocs.org/files/sha256/78/75/7875adece1293eca389d8ad292aae130446f48d104ec1539a29b6910f60df42a - FAA DRS: https://drs.faa.gov/browse/excelExternalWindow/DRSDOCID104240953220260819142738.0001 - Page: https://openairdocs.org/tcds/A17EU ## Models (18) As the data sheet lists them. - BN-2A-2 - BN-2A-9 - BN-2B-20 - BN-2A-26 - BN-2B-26 - BN-2A-27 - BN-2T-4R - BN-2A-3 - BN-2T - BN-2A-8 - BN-2B-27 - BN-2A-20 - BN-2A-21 - BN-2A-6 - BN-2A - BN-2 - BN-2B-21 - BN2T-4S ## What the data sheet says From the PDF's text layer, line by line; tables lose their columns. The PDF is the record. ```text 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. 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 11 of 31 A17EU X. Model BN2A-27, 10 PCLM (Normal Category), approved April 6, 1977 (Model BN2A-27 is similar to Model BN2A-9 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 6,360 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. 6,360 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) See NOTE 7. Fuel Capacity. 196 U.S. gal. total (two 68.5 U.S. gal. main 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 12 of 31 A17EU XI. Model BN2B-20, 10 PCLM (Normal Category), approved September 24, 1979 (Model BN2B-20 is similar to Model BN2A-20 except for the improvements introduced by Modification NB/M/982) See NOTE 13 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.) (See NOTE 19) 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 and 19). 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 2250 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 -56º) 88 knots (101 m.p.h.) VFE (flaps extended -25º) 114 knots (131 m.p.h.) VMC (minimum control) 40 knots ( 46 m.p.h.) (See NOTE 19) 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. 6,560 lb. 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. 400 lb. (+121 in.) Fuel Capacity. 137 U.S. gal. total (two 68.5 U.S. wing tanks at +27.0 in.) (130 U.S. gal. usable and 42 lb. unusable at +27 in.) Oil Capacity. 24 U.S. qt. total (12 U.S. qt. per engine at -2.6 in.) See NOTE 1B. 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 6 1/4º Down 18 1/2º ** Rudder Right 30º Left 30º Rudder Tab Right 20º Left 20º *See NOTE 11. **See NOTE 15. Page 13 of 31 A17EU XII. Model BN2B-21, 10 PCLM (Normal Category), approved September 24, 1979 (Model BN2B-21 is similar to the Model BN2A-21 except for the improvements introduced by Modification NB/M/983) See NOTE 13. 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.) (See NOTE 19) 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 and 19). 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 2250 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 -56º) 88 knots (101 m.p.h.) VFE (flaps extended -25º) 114 knots (131 m.p.h.) VMC (minimum control) 40 knots ( 46 m.p.h.) (See NOTE 19) 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. 6,600 lb. 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. 400 lb. (+121 in.) Fuel Capacity. 196 U.S. gal. total (two 68.5 U.S. gal. main tanks at +27.0 in. and two 29.5 U.S. gal. wing tip tanks at +34.7 in.) (190 U.S. gal. usable and 44 lb. unusable at +31.2 in.) 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 6 1/4º Down 18 1/2º ** Rudder Right 30º Left 30º Rudder Tab Right 20º Left 20º *See NOTE 11. **See NOTE 15. Page 14 of 31 A17EU XIII. Model BN2B-26, 10 PCLM (Normal Category), approved September 24, 1979 (Model BN2B-26 is similar to Model BN2A-26 except for the improvements introduced by Modification NB/M/984) See NOTE 13. 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 (See NOTE 12 and 16) 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 -56º) 88 knots (101 m.p.h.) VFE (flaps extended -25º) 114 knots (131 m.p.h.) VMC (minimum control) 40 knots ( 46 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. 6,200 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. 400 lb. (+121 in.) Fuel Capacity. 137 U.S. gal. total (two 68.5 U.S. wing tanks at +27.0 in.) (130 U.S. gal. usable and 42 lb. unusable at +27 in.) Oil Capacity. 24 U.S. qt. total (12 U.S. qt. per engine at -2.6 in.) See NOTE 1B. 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 6 1/4º Down 18 1/2º ** Rudder Right 30º Left 30º Rudder Tab Right 20º Left 20º *See NOTE 11. **See NOTE 15. Page 15 of 31 A17EU XIV. Model BN2B-27, 10 PCLM (Normal Category), approved September 24, 1979 (Model BN2B-27 is similar to the Model BN2A-27 except for the improvements introduced by Modification NB/M/985) See NOTE 13. 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 (See NOTE 12 and 16) 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 -56º) 88 knots (101 m.p.h.) VFE (flaps extended -25º) 114 knots (131 m.p.h.) VMC (minimum control) 40 knots ( 46 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 6,360 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. 6,360 lb. Maximum Landing Weight. 6,360 lb. 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. 400 lb. (+121 in.) 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 and 44 lb. unusable at +31.2 in.) 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 6 1/4º Down 18 1/2º ** Rudder Right 30º Left 30º Rudder Tab Right 20º Left 20º *See NOTE 11. **See NOTE 15. Page 16 of 31 A17EU XV. Model BN2T, 10 PCLM (Normal Category), approved July 15, 1982 (Model BN2T is similar to Model BN2B-26 and BN2B-20 except for the installation of 2 Detroit Diesel Allison 250 B17C turbopropeller engines introduced by Modification NB/M/1104) Engines. 2 Detroit Diesel Allison 250-B17C turbopropeller. Fuel. Jet A or A1, Jet B, JP1, JP4, JP5 and JP8, Diesel No. 1 Engine Limits. Flat rated to 320 shp (equivalent to 830 ft. lb. of torque at the maximum propeller governed RPM of 2030). Propeller and Propeller Limits. Hartzell HC-C3YF-5F/FC8475FK-6. Diameter 78" Pitch setting at 30 in. station: Low 9º High 82.5º Governor: Woodward 8210-018 Spinner: Hartzell C4558-3P Airspeed Limits Without Modification NB-M-1218: (IAS) VMO (maximum operating) 152 knots (174 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) 47 knots ( 54 m.p.h.) With Modification NB-M-1218: VMO (maximum operating) 152 knots (174 m.p.h.) VA (maneuvering) 113 knots (130 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) 47 knots ( 54 m.p.h.) C.G. Range. Without Modification NB-M-1218: (+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. With Modification NB-M-1218: (+17.0 in.) to (+26.4 in.) at 5,030 lb. (+22.0 in.) to (+26.4 in.) at 7,000 lb. Straight line variation between points. Empty Weight C.G. Range. None Datum. Wing leading edge (Sta. 134.5) Without NB-M-1218 With NB-M-1218 Maximum Take-off Weight 6,600 lb. 7,000 lb. Maximum Landing Weight. 6,600 lb. 6,800 lb. Maximum Zero Fuel Weight. 6,300 lb. 6,600 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. 400 lb. (+121 in.) Page 17 of 31 A17EU XV. Model BN2T (cont’d) Fuel Capacity. 137 U.S. gal. total (two 68.5 U.S. wing tanks at +27.0 in.) (130 U.S. gal. usable and 47 lb. unusable at +27 in.) When Modification NB-M-1153 is incorporated: 226 U.S. gal. total (two 68.5 U.S. gal. main tanks at +27.0 in. and two 44.5 U.S. gal. tip tanks at +31.6 in.) (215 U.S. gal. usable and 74 lb. unusable at +28.8 in.) See NOTE 1D. Oil Capacity. 12 U.S. qt. total (6 U.S. qt. per engine at -14.0 in.) See NOTE 1D and 14. 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 15º Down 20º ** Rudder Right 30º Left 30º Rudder Tab Right 20º Left 20º * See NOTE 11 ** See NOTE 15. XVI. Model BN2T-4R (Normal Category), approved December 1, 1994. Model BN2T-4R is similar to Model BN2T except for the increase in weights and change of engine model and propeller. Engines. 2 Allison 250-B17F/1 turbopropeller. Fuel. Jet A or A1, Jet B, JP1, JP4, JP5 and JP8 Engine Limits. Maximum power for all operations is 400 shp (equivalent to 1035 ft. lb torque at the maximum propeller governed RPM of 2030). Propeller and Propeller Limits. Hartzell HC-C3YF-5F/FC7818K. Diameter 78" Pitch setting at 30 in. station: Low 9º High 81.1º Governor: Woodward 8210-018 Spinner: Hartzell C4558-3P Airspeed Limits IAS CAS (IAS) (at 8500 lb) VMO (maximum operating) 151 knots 147.5 knots VA (maneuvering) 129.5 knots 128 knots VFE (flaps extended -41 ½º) 113 knots 111.5 knots VFE (flaps extended -25º) 116 knots 131.5 knots VMC (minimum control) 60 knots 68.5 knots C.G. Range. (+19.5 in.) to (+25.0 in.) at 6,000 lb. (+22.0 in.) to (+25.0 in.) at 8,500 lb. Straight line variation between points. Empty Weight C.G. Range. None Datum. Wing leading edge (Stn. 134.5) Maximum Take-off Weight. 8,500 lb. Maximum Landing Weight. 8,500 lb. Maximum Zero Fuel Weight. 8,300 lb. Page 18 of 31 A17EU XVI. Model BN2T-4R (cont’d) 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. 400 lb. (+121 in.) Fuel Capacity. 226 U.S. gal. total (two 68.5 U.S. gal. main tanks at +27.0 in. and two +44.5 U.S. gal. tip tanks at +31.6 in.) (207.8 U.S. gal. usable and 122 lb. unusable at +28.8). See NOTE 1D. Oil Capacity. 15 U.S. qt. total (7.5 U.S. qt. per engine at -14.0 in.) See NOTE 1D. Control Surface Movements. Wing Flaps Full Up 6º(Down) Full Down 41½º(Down) Aileron Up 25º Down 15º Aileron Trim Tab Up 15º Down 25º Elevator Up 24º Down 19º Elevator Trim Tab* Up 15º Down 20º Rudder Right 30º Left 30º Rudder Tab Right 20º Left 20º *See NOTE 11. XVII. Model BN2T-4S (Normal Category), approved December 15, 2022 Model BN2T-4S is similar to Model BN2T-4R except for the standard nose and stretched fuselage. See NOTE 22 Engines. 2 Allison 250-B17F/1 turbopropeller. Fuel. Jet A or A1, Jet B, JP1, JP4, JP5 and JP8 Engine Limits. Maximum power for all operations is 400 shp (equivalent to 1035 ft. lb torque at the maximum propeller governed RPM of 2030). Propeller and Propeller Limits. Hartzell HC-C3YF-5F/FC7818K. Diameter 78" Pitch setting at 30 in. station: Low 9º High 81.1º Governor: Woodward 8210-018 Spinner: Hartzell C4558-3P Airspeed Limits IAS CAS (IAS) (at 8500 lb) VMO (maximum operating) 151 knots 148 knots VA (maneuvering) 129.5 knots 128 knots VFE (flaps extended -41 ½º) 113 knots 111 knots VFE (flaps extended -10º) 116 knots 116 knots VMC (minimum control) 60 knots 70 knots C.G. Range. (+15.0 in.) to (+25.0 in.) at 6,700 lb. (+20.0 in.) to (+25.0 in.) at 8,500 lb. Straight line variation between points. Empty Weight C.G. Range. None Datum. Wing leading edge (Stn. 134.5) Page 19 of 31 A17EU XVII. Model BN2T-4S (cont’d) Maximum Take-off Weight. 8,500 lb. (See NOTE 23) Maximum Landing Weight. 8,500 lb. (See NOTE 23) Maximum Zero Fuel Weight. 8,300 lb. Number of Seats. 12 (2 at -72.5in), (2 at -42.5 in.), (2 at -12.3 in.), (2 at +17.8 in.), (2 at +47.1 in.), and (2 at +75.1 in.) * See NOTE 21. Maximum Baggage. 400 lb. (+121 in.) Fuel Capacity. 315.6 U.S. gal. total (two 70.9 U.S. gal. main tanks at +27.0 in. and two +86.9 U.S. gal. transfer tanks at +27.0 in.) (298.8 U.S. gal. usable and 112.6 lb. unusable at +27.0). See NOTE 1E. Oil Capacity. 15 U.S. qt. total (7.5 U.S. qt. per engine at -14.0 in.) 12 U.S. qt. usable See NOTE 1E. Control Surface Movements. Wing Flaps Full Up 6º(Down) Full Down 41½º(Down) Aileron Up 25º Down 15º Aileron Trim Tab Up 15º Down 25º Elevator Up 21º Down 21º Elevator Trim Tab* Up 15º Down 6º Rudder Right 30º Left 30º Rudder Tab Right 20º Left 20º *See NOTE 11. Operational Equipment. For Flight into Known Icing (FIKI) approved airplanes, AFM Supplement 03, Issue 1, to AFM/2T-4S/FAA, dated December 8, 2025, or later FAA approved revision. Operational Restrictions. FIKI conditions is allowed when the required equipment is installed per NB-M-1591 and the airplane operated in accordance with AFM Supplement 03, Issue 1, to AFM/2T-4S/FAA, dated December 8, 2025, or later FAA approved revision. Flight into known severe icing, freezing rain, freezing drizzle, or supercooled large drops is prohibited. Flight into known icing conditions requires the ice protection system to be fully-operational. All operational restrictions as defined in the latest FAA approved revision of the AFM Supplement 03 to AFM/2T-4S/FAA. Page 20 of 31 A17EU DATA PERTINENT TO ALL MODELS. Leveling Means. Fore and aft leveling: holes for datum pins on which straight edge is placed are located on the left side of the center fuselage. Lateral leveling: straight edge across datum marks painted on wing above front spar. Serial Numbers Eligible. Each individual aircraft manufactured under this type certificate must be accompanied by an Export Certificate of Airworthiness as noted below under "Import Requirements" when an application for a U.S. airworthiness certificate is made. BN2T-4R: C.2115 and C.2143. Import Requirements. Country of Manufacturer: A U.S. airworthiness certificate may be issued on the basis of an Export Certificate of Airworthiness approved by an authorized representative of the Civil Aviation Authority (CAA) United Kingdom including the following statement: "The aircraft covered by this certificate has been examined, tested and found to conform to 14 CFR Part 23 type design approved under U.S. Type Certificate A17EU and to be in a condition for safe operation." Country other than Manufacturer (U.S. bilateral agreement and the original Export Certificate of Airworthiness issued by the country of manufacture must exist): A U.S. airworthiness certificate may be issued on the basis of a log book certifying statement endorsed by an authorized representative of the civil aviation authority of the exporting country. It is incumbent upon the exporting civil aviation authority to determine that the certifying statement includes evidence of acceptable service history and modification deviations and the following statement: "The aircraft covered by this certificate has been examined, tested, inspected in accordance with the provisions of FAR 21.183(d) or its equivalent, and found to conform to the type design approved under Type Certificate A17EU and is in a condition for safe operation." Refer to the applicable bilateral agreement to verify eligibility for import into the United States of both new and used aircraft based on the scope of the agreement, to identify any required statements by the exporting authority on the export certificate of airworthiness (or equivalent document), and for procedures for coordinating exceptions to conformity statements on these documents. Refer to FAA Order 8130.2, Airworthiness Certification of Aircraft, for requirements for issuance of an airworthiness certificate for imported aircraft Service Information Each of the documents listed below must state that it is approved by the United Kingdom Civil Aviation Authority (CAA) or – for approvals made between September 29, 2003, and December 31, 2020 – by the European Union Aviation Safety Agency (EASA). • Service bulletins, • Structural repair manuals, • Vender manuals, • Aircraft flight manuals, and • Overhaul and maintenance manuals. The FAA accepts such documents and considers the FAA -approved unless on e of the following conditions exists: • The documents change the limitations, performance, or procedures of the FAA approved manuals, or • The documents make an acoustical or emissions change to this product’s U. S. type certificate as defined in 14 CFR 21.93. The FAA uses the post type validation procedures to approve these documents. The FAA may delegate on case -by-case to the United Kingdom CAA or – between September 29, 2003, and December 31, 2020 – to EASA, to approve on behalf of the FAA for the U.S. type certificate. If this is the case it will be noted on the document. Page 21 of 31 A17EU Certification Basis. For Models BN2 and BN2A: FAR 21.17 FAR 21.29 and FAR 23, effective February 1, 1965, plus amendment 23-1. For Models BN2A-2, BN2A-3, BN2A-6, BN2A-8, BN2A-9, BN2A-20, BN2A-21, BN2A-26 and BN2A-27. FAR 21.29 and FAR 23, effective February 1, 1965, including amendment 23-1 and Sections 23.75(a), 23.161(c), 23.175(d) and 23.1585(b)(3) of Amendment 23-7. For Models BN2B-20, BN2B-21, BN2B-26 and BN2B-27: FAR 21.29 and FAR 23, effective February 1, 1965, including amendment 23-1 and Sections 23.75(a), 23.161(c), 23.175(d) and 23.1585(b)(3) and 23.1563 of Amendment 23-7, Section 23.1545 of Amendment 23-23, and FAR 36 through Amendment 8 (See NOTE 13). - Optional modification, NB-M-2159, for Models BN2B-20 and BN2B-26 has been found to comply with the following updated regulations: 23.1301, .1309(a)(1)(3)(b)(c)(d)(e), .1311(a)(1)(2)(6)(7)(b), and .1431 at Amendment 23-62, 23.1351(a)(b)(1)(2)(3)(g), .1359(c), and .1365 at Amendment 23-49, 23.1357 at Amendment 23-43, and 23.1529 at Amendment 23-26. For Model BN2T: FAR 21.29 and FAR 23, effective February 1, 1965 including Amendments 23-1 and through the admendments as follows: 14 CFR 14 CFR 14 CFR Section Amend. No. Section Amend. No. Section Amend. No. 23.2** 23.45 23-21 23.853 23-14 23.1155 23-7 23.49 23-21 23.859 23-5 23.1163 23-14 23.51 23-21 23.901 23-18 23.1165 23-17 23.65 23-21 23.903 23-26 23.1182 23-14 23.67 23-21 23.929 23-14 23.1183 23-15 23.75 23-21 23.937 23-7 23.1189 23-14 23.77 23-21 23.939 23-18 23.1203 23-18 23.141 23-17 23.943 23-18 23.1301 23-20 23.143 23-17 23.951 23-15 23.1303 23-17 * 23.145 23-17 23.955 23-7 23.1305 23-18 23.149 23-21 23.959 23-18 23.1307 23-23 23.153 23-14 23.977 23-17 23.1323 23-20 23.155 23-14 23.991 23-7 23.1337 23-18 23.157 23-14 23.1013 23-15 23.1501 23-21 23.161 23-21 23.1015 23-15 23.1505 23-7 23.173 23-14 23.1017 23-14 23.1521 23-21 23.175 23-17 23.1019 23-15 23.1527 23-7 23.177 23-21 23.1027 23-14 23.1529 23-8 23.181 23-21 23.1041 23-7 23.1541 23-21 23.201 23-14 23.1043 23-21 23.1545 23-23 23.203 23-14 23.1045 23-7 23.1547 23-20 23.205 23-14 23.1091 23-7 23.1549 23-12 23.207 23-7 23.1093 23-18 23.1555 23-21 23.253 23-7 23.1103 23-7 23.1557 23-23 23.361 23-26 23.1111 23-17 23.1563 23-7 23.367 23-7 23.1121 23-18 23.1581 23-21 23.371 23-7 23.1141 23-18 23.1583 23-23 23.629 23-7 23.1143 23-17 23.1585 23-23 23.777 23-7 23.1145 23-18 23.1587 23-21 * Exemption No. 3732 effective May 20, 1983, to FAR 23.1303(e)(1) - SFAR 27, Amendments 27-1 through 27-3 (Fuel Venting). The Allison 250-B17C complies with the fuel venting emission requirements of SFAR 27 by means inherent in the engine type design. Page 22 of 31 A17EU - FAR 36, effective 1 December 1969, including Amendments 36-1 through 36-9. - Optional modification, NB-M-2159, has been found to comply with the following updated regulations: 23.1301, .1309(a)(1)(3)(b)(c)(d)(e), .1311(a)(1)(2)(6)(7)(b), and .1431 at Amendment 23-62, 23.1351(a)(b)(1)(2)(3)(g), .1359(c), and .1365 at Amendment 23-49, 23.1357 at Amendment 23-43, and 23.1529 at Amendment 23-26. Page 23 of 31 A17EU Certification Basis (cont’d) For Model BN2T-4R: FAR 23 dated February 1, 1965, as amended through Amendment 23-1 effective July 29, 1965; and through the following paragraphs as amended through the amendments as follows: 14 CFR 14 CFR 14 CFR Section Amend. No. Section Amend. No. Section Amend. No. 23.2 23-36 23.777 23-7 23.1155 23-7 23.45 23-21 23.785 23-32 23-1163 23-29 23.49 23-21 23.853 23-14 23-1165 23-17 23.51 23-21 23.859 23-5 23-1182 23-14 23.65 23-21 23.901 23-29 23-1183 23-29 23.67 23-21 23.903 23-26 23-1189 23-29 23.75 23-21 23.905 23-29 23-1203 23-18 23.77 23-21 23.929 23-14 23-1301 23-20 23.141 23-17 23.937 23-7 23-1303 23-17* 23.143 23-17 23.939 23-18 23-1305 23-18 23.145 23-17 23.943 23-18 23-1307 23-23 23.149 23-21 23.951 23-15 23-1321 23-20 23.153 23-14 23.955 23-7 23-1322 23-17 23.155 23-14 23.959 23-18 23-1323 23-20 23.157 23-14 23.977 23-17 23-1337 23-18 23.161 23-21 23.991 23-7 23-1351 23-20 23.173 23-14 23.997 23-29 23-1411 23-17 23.175 23-17 23.1013 23-15 23-1413 23-22 23.177 23-21 23.1015 23-15 23-1501 23-21 23.181 23-21 23.1017 23-14 23-1505 23-7 23.201 23-14 23.1019 23-29 23-1521 23-21 23.203 23-14 23.1021 23-29 23-1527 23-7 23.205 23-14 23.1027 23-14 23-1529 23-26 23.207 23-7 23.1041 23-7 23-1541 23-21 23.253 23-7 23.1043 23-21 23-1545 23-23 23.335 23-16 23.1045 23-7 23-1547 23-20 23.361 23-26 23.1091 23-7 23-1549 23-28 23.367 23-7 23.1093 23-29 23-1555 23-21 23.371 23-7 23.1103 23-7 23-1557 23-23 23.473 23-28 23.1111 23-17 23-1563 23-7 23.561 23-7 23.1121 23-18 23.1581 23-21 23.572 23-34 23.1141 23-18 23.1583 23-23 23.629 23-31 23.1143 23-29 23.1585 23-23 23.1145 23-18 23.1587 23-28 23,APP G 23-37 * Exemption 5952 effective August 18, 1994, to 23.1303(e)(l). - SFAR 27 issued February 1, 1974, as amended through Amendment 27-5 on September 15, 1989. - FAR 36 dated December 1, 1969, as amended through Amendment 36-20 effective September 16, 1992. Page 24 of 31 A17EU Certification Basis (cont’d) For Model BN2T-4S: CFR 23 dated February 1, 1965, as amended through Amendment 23-1 effective July 29, 1965; and through the amendments as follows: 14 CFR 14 CFR 14 CFR Section Amend. No. Section Amend. No. Section Amend. No. 23.2 23.36 23.629 23-31 23.1182 23-14 23.45 23-50 23.777 23-7 23.1183 23-29 23.49 23-50 23.785 23-32 23.1189 23-29 23.51 23-50 23.851 23-45 23.1203 23-18 23.53 23-50 23.853 23-14 23.1301 23-20 23.63 23-50 23.859 23-5 23.1303 23-17 * 23.65 23-50 23.901 23-29 23.1305 23-18 23.66 23-50 23.903 23-26 23.1307 23-23 23.67 23-50 23.905 23-29 23.1321 23-20 23.69 23-50 23.929 23-14 23.1322 23-17 23.73 23-50 23.937 23-7 23.1323 23-20 23.75 23-50 23.939 23-18 23.1337 23-18 23.77 23-50 23.943 23-18 23.1351 23-20 23.141 23-17 23.951 23-15 23.1411 23-17 23.143 23-17 23.955 23-7 23.1413 23-22 23.145 23-17 23.959 23-18 23.1501 23-21 23.147 23-45 23.977 23-17 23.1505 23-7 23.149 23-50 23.991 23-7 23.1507 23-45 23.153 23-14 23.997 23-29 23.1521 23-50 23.155 23-14 23.1013 23-15 23.1527 23-7 23.157 23-14 23.1015 23-15 23.1529 23-26 23.161 23-21 23.1017 23-14 23.1541 23-21 23.173 23-14 23.1019 23-29 23.1543 23-50 23.175 23-17 23.1021 23-29 23.1545 23-23 23.177 23-45 23.1027 23-14 23.1547 23-20 23.181 23-21 23.1041 23-7 23.1549 23-28 23.201 23-14 23.1043 23-21 23.1555 23-50 23.203 23-14 23.1045 23-7 23.1557 23-23 23.205 23-14 23.1091 23-7 23.1563 23-50 23.207 23-7 23.1093 23-29 23.1581 23-50 23.235 23-50 23.1103 23-7 23.1583 23-50 23.253 23-7 23.1111 23-17 23.1585 23-50 23.335 23-16 23.1121 23-18 23.1587 23-50 23.361 23-26 23.1141 23-18 23.1589 23-50 23.367 23-7 23.1143 23-29 23.371 23-7 23.1145 23-18 23, APP G 23-37 23.473 23-28 23.1155 23-7 23.561 23-7 23.1163 23-29 23.572 23-34 23.1165 23-17 * Exemption 5952 effective August 18, 1994, to 23.1303(e)(l). - CFR 34 dated September 9, 1990, as amended through Amendment 34-6 effective March 6, 2018. - CFR 36 dated December 1, 1969, as amended through Amendment 36-31 effective November 3, 2017. - Optional modification, NB-M-2159, has been found to comply with the following updated regulations: 23.1301, .1309(a)(1)(3)(b)(c)(d)(e), .1311(a)(1)(2)(6)(7)(b), and .1431 at Amendment 23-62, 23.1351(a)(b)(1)(2)(3)(g), .1359(c), and .1365 at Amendment 23-49, and 23.1357 at Amendment 23-43. - Compliance with ice protection has been demonstrated in accordance with 14 CFR § 23.1416 Amendment 23-23 and 23.1419 at Amendment 23-14. Optional modification for FIKI, NB-M-1591, has been found to comply with the following additional regulations: Page 25 of 31 A17EU 23.773 [23-14], 23.775 [23-45], 23.1309 [23-17], 23.1325(b)(3) [23-20], 23.1327 [23-20], 23.1357(b) [23-20], 23.1365 [23-14], and 23.1525 [23-45]. - Optional modification, NB-M-2182, has been found to comply with the following updated regulations: 23.1301, .1309(a)(1)(3)(b)(c)(d)(e), and .1431(a)(b) at Amendment 23-62, 23.1306 at Amendment 23-61, 23.1308 at Amendment 23-57, 23.1329(f)(g), 23.1351(a)(b)(1)(2)(3)(g), .1359(c), and .1365 at Amendment 23-49, and 23.1357(a)(2)(b)(c)(d)(e) at Amendment 23-43. Page 26 of 31 A17EU Information applicable to all models: All aircraft manufactured after December 12, 1986, must meet the applicable requirements of FAR 23.2. (See NOTE 5) Date of Application for Type Certificate: February 1, 1965. Type Certificate A17EU issued December 19, 1967. (Re-issued to Britten-Norman (Bembridge) Limited on May 30, 1972). Re-issued to Pilatus Britten-Norman Limited on September 24, 1979. Amended: December 1, 1994 The United Kingdom CAA originally type certificated this aircraft under is type certificate Number BA8. The FAA validated this product under U.S. Type Certificate number A17EU. Effective September 28, 2003, the European Aviation Safety Agency (EASA) began oversight of this product on behalf of the United Kingdom CAA. EASA issued TCDS EASA.A.388 Issue 1 in November 2011 that covered some of the BN2A and BN2B models, but not all. (See NOTE 18). Effective January 1, 2021, oversight of this product returned to the United Kingdom CAA. The United Kindom CAA issued TCDS UK.TC.A.00042 Issue 1 on September 5, 2022, that covers all BN2A and BN2B models validated by the FAA. Validation Basis. Type Certificate A17EU was issued pursuant to FAR 21.29 in validation of the United Kingdom Civil Aviation Authority (CAA) certification of compliance with the aforementioned certification basis, and in accordance with the normal category airworthiness certificate provisions of FAR 21.183(c). NOTE: The airworthiness provisions of FAR 21.183(d) may be cited as the basis for issuance of standard airworthiness certificates for aircraft imported from a country other than the country of manufacture. Equipment. The basic required equipment as prescribed in the applicable airworthiness regulations (see Certification Basis) must be installed in the aircraft for airworthiness certification. In addition, the following items of equipment are required: 1. Each individual airplane must be fitted with a placard which specifies approved kinds of operation (such as V.F.R., I.F.R, DAY or NIGHT) to which the airplane is limited by the equipment installed. (See also NOTE 2 and NOTE 12). 2. Stall warning indicator (Safe Flight Type No. 165). 3. Pilot door interlock mechanism. 4. CAA-approved Britten-Norman Islander Airplane Flight Manual as follows: (a) For Model BN2: approved Flight Manual Document FM/2 dated November 27, 1967, or later CAA-approved revisions. (b) For Model BN2A: approved Flight Manual Document FM/2 at revision 1001, dated July 1968 or later CAA-approved revisions. (c) For Model BN2A-6: approved Flight Manual Document FM/2 at revision 1007, dated June 1970 or later CAA-approved revisions. (d) For Model BN2A-8: approved Flight Manual Document FM/2 at revision 1008, dated March 30, 1971, or later CAA-approved revisions. (e) For Model BN2A-2: approved Flight Manual Document FM/10 dated January 28, 1971, or later CAA-approved revisions. (f) For Model BN2A-9: approved Flight Manual Document FM/10 at revision 1008, dated March 30, 1971, or later CAA- approved revisions plus supplement 16 to FM/2. (g) For Model BN2A-3: approved Flight Manual Document FM/10 dated January 28, 1971, or later CAA-approved revisions plus supplement 16 to FM2. (h) For Model BN2A-20: approved Flight Manual Document FM/10 dated January 28, 1971, plus revision 1, dated April 3, 1974 or later CAA-approved revisions. (i) For Model BN2A-21: approved Flight Manual Document FM/10 dated January 28, 1971, plus revision 1 or later CAA- Page 27 of 31 A17EU approved revisions plus supplement 8 to FM/10. (j) For Model BN2A-26: approved Flight Manual Document FM/20 dated June 1, 1976, or later CAA-approved revisions. (k) For Model BN2A-27: approved Flight Manual Document FM/20 dated June 1, 1976, or later CAA-approved revisions plus supplement 1 to FM/20. (l) For Model BN2B-20: approved Flight Manual Document FM/43 dated July 30, 1979, or later CAA-approved revisions. (m) For Model BN2B-21: approved Flight Manual Document FM/43 dated July 30, 1979, or later CAA-approved revisions plus supplement 1 to FM/43. (n) For Model BN2B-26: approved Flight Manual Document FM/42 dated July 30, 1979, or later CAA-approved. (o) For Model BN2B-27: approved Flight Manual Document FM/42 dated July 30, 1979, or later CAA-approved revisions plus supplement 1 to FM/42. (p) For Model BN2T: approved Flight Manual Document FM/101 dated 17 December 1981, or later CAA-approved. (q) For Model BN2T-4R: approved Flight Manual Document FM/401 dated November 22, 1994, or later CAA-approved revisions. (r) For Model BN2T-4S: approved Flight Manual Document AFM/2T-4S/FAA dated September 12, 2022, or later CAA approved revisions. NOTES NOTE 1. Current weight and balance report, including list of equipment included in certificated empty weight and loading instructions when necessary, must be provided for each aircraft at the time of original airworthiness certification. The certificated empty weight and corresponding center of gravity locations must include the following: A. For Models BN2, BN2A, BN2A-2, BN2A-6, BN2A-8, BN2A-20 and BN2A-26 airplanes: On airplanes not embodying fuel gauging system Modification NB/M/240: unusable fuel of 108 lb. (+27.0 in.) and undrainable oil of 0 lb. (- 2.6 in.) On airplanes embodying Modification NB/M/240: unusable fuel of 42 lb. (+27.0 in.) and undrainable oil of 0 lb. (- 2.6 in.) B. For Models BN2B-20 and BN2B-26: Unusable fuel of 42 lb. (+ 27.0 in.) and undrainable oil of 0 lb. (- 2.6 in.) C. For Models BN2A-3, BN2A-9, BN2A-21, BN2A-27, BN2B-21, BN2B-27 airplanes: Unusable fuel of (main and tip 44 lb. (+ 31.2 in.) tank total) and undrainable oil of 0 lb. (- 2.6 in.) D. For Models BN2T and BN2T-4R: BN2T-4R BN2T Unusable fuel of (main tanks) 95 lb. 47 lb. (+ 27.0 in.) Unusable fuel of (tip tanks) 27 lb. 27 lb. (+ 31.6 in.) and undrainable oil of 0 lb. 0 lb. (- 14.0 in.) E. For Model BN2T-4S: Unusable fuel of (main tanks) 95 lb. (+ 27.0 in.) Unusable fuel of (transfer tanks) 17 lb. (+ 27.0 in.) and undrainable oil of 0 lb. (- 14.0 in.) Page 28 of 31 A17EU NOTE 2. The following placards must be displayed on the instrument panel in full view of the pilot: THIS AIRPLANE MUST BE OPERATED AS A NORMAL CATEGORY AIRPLANE IN COMPLIANCE WITH THE OPERATING LIMITATIONS STATED IN THE FORM OF PLACARDS, MARKING AND MANUALS." In addition all placards required in the applicable approved Airplane Flight Manual must be installed in the appropriate location. NOTE 3. For Models BN2T and BN2T-4R: Section 1.7 of the Pilatus Britten-Norman Model BN2T Maintenance Manual, Document No. MM/4, is FAA-approved and it specifies mandatory replacement times, structural inspection intervals, and related structural inspection procedures. These airworthiness limitations may not be changed without FAA approval. NOTE 4. Model BN2 airplanes are eligible for maximum weight of 6,000 lb., when the main landing gear shock absorbers are modified in accordance with Britten-Norman Modification No. NB/M/198 and revision 1001 to Airplane Flight Manual FM/2, is incorporated. NOTE 5. Modifications and Model number re-designation. a. When the approved Britten-Norman Modification described in column 1 and identified in column 2 is incorporated, the BN2 series airplanes must be re-designated as shown in column 3. See "Equipment" Item 4 of this Data Sheet for the Required approved Flight Manual Document for each Model. Column 1 Column 2 Column 3 Modification Modification Model General Description Number NB/M/.... Re-designation Aerodynamic refinements to the NB/M/413 BN2A-6 wing leading edge between the fuselage and engine nacelle. Incorporation of Mod. NB/M/413 NB/M/475 BN2A-8 plus drooped Flaps to Modification NB/M/430. Incorporation of Mods. NB/M/413 NB/M/410 BN2A-2 NB/M/430 and Lycoming IO-540-K1B5 (300 hp) engines. Incorporation of Mod. NB/M/410 NB/M/452 BN2A-3 plus wing tip fuel tanks to Modification NB/M/364. Incorporation of Mods. NB/M/413 NB/M/454 BN2A-9 NB/M/430 and wing tip fuel tanks NB/M/364 Incorporation of Modification NB/M/571 BN2A-20 NB/M/410 stiffeners to the engine firewalls to Modification NB/M/631* Incorporation of Modification NB/M/574 BN2A-21 NB/M/452 plus stiffeners to the engine firewalls to Modification NB/M/631* Incorporation of Modification NB/M/590 BN2A-26 NB/M/475 plus stiffeners to engine firewalls to Modification NB/M/631* Incorporation of Modification NB/M/591 BN2A-27 NB/M/454 plus stiffeners to the Page 29 of 31 A17EU engine firewalls to Modification NB/M/631* Column 1 Column 2 Column 3 Incorporation of product improvements NB/M/982 BN2B-20 of Mod. NB/M/978 ** and IO-540-K1B5 (300 hp) engines to Mod. NB/M/410. Incorporation of Mod. NB/M/982 and NB/M/983 BN2B-21 Wing Tip Fuel Tanks to Mod. NB/M/364. Incorporation of product improvements NB/M/984 BN2B-26 of Mod. NB/M/978 ** (to aircraft basic build standard with O-540-E4C5 (260 hp) engines) Incorporation of Mod. NB/M/982 and NB/M/985 BN2B-27 Wing Tip Fuel Tanks of Mod. NB/M/364. Incorporation of Detroit Diesel Allison NB/M/1104 BN2T 250 B17C turbopropeller engines flat rated to 320 Shp. Incorporation of Mod. NB/M/1104 and NB/M/1218 BN2T*** Wing Tip Fuel Tanks of Modification NB/M/1153*** Incorporation of Modification NB/M/1218, NB/M/1359 BN2T-4R weight increase and associated items of Appendix 1 Modification NB/M/1452, radar nose of or Appendix 3 Modification NB/M/1458, Allison 250 B17F/1 Turbopropeller Engines of Modification NB/M/1454 and Hartzell HC-C3YF-5F/FC7818K Propellers of Modification of NB/M/1457 Incorporation of Mod. NB/M/1545, NB/M/1545 BN2T-4S with stretched fuselage. Incorporation of Passenger Sash Harnesses NB/M/1298 BN2A/2B, -20, -21 complies with the requirements of FAR 23.2 -26, -27, and BN2T * Modification NB/M/631 is satisfied if Modification NB/M/116 - Airframe de-icing is installed. ** See NOTE 13. *** This Modification introduces the BN2T at a M.T.O.W. of 7000 lb., with a Landing Weight of 6800 lb. and a Wing Zero Fuel Weight of 6600 lb. This weight increase had previously been introduced in NB-M-1104, Issue 5 together with the Integral Tip Tank Modification NB-M-1153. NB-M-1218 addresses these Modifications, and is now the certification Modification for the 7000 lb. BN2T Islander. Full and adequate information on the differences between BN2T Aircraft with NB-M-1218 and those without, is given in the main body of Aircraft Flight Manual FM/101. NOTE 6. For all Models which have Britten-Norman Modification NB/M/383 incorporated the maximum operating limit speed with the flaps in the takeoff position (25°) is 114 knots (131 m.p.h.) (IAS). NOTE 7. When Modification NB/M/483 is incorporated Max. Baggage 400 lb. (+121 in.) Post-Mod. NB/M/483. NOTE 8. Britten-Norman Modification NB/M/746 introduces the wide deck variant of Lycoming engine types O-540-E4C5 and IO-540-K1B5. There is no change in the engine type designation Serial Number of wide deck engines contain the letter "A". Example: Standard deck L-132-68-18 becomes wide deck L-132-68-48A. Britten-Norman Service Bulletin BN2/SB 87 also refers. Page 30 of 31 A17EU NOTE 9. Propellers of the type shown are eligible for the incorporation of Hartzell Service Bulletin 114 and Service Instruction 102. Propellers so modified have the letter "U" added to their designation. Example: HC-C2YK-2UCF/FC8477A-4. NOTE 10. For aircraft fitted with Lycoming wide deck engines (See NOTE 8) the only governors to be fitted are G210659 where no unfeathering accumulator is installed and B2101715 where an unfeathering accumulator is installed. For Standard deck engines propeller governor part numbers D210659 and F210444 are interchangeable for aircraft without unfeathering accumulators and part numbers 210715 and 210275 are interchangeable for aircraft with unfeathering accumulators. NOTE 11. Elevator trim tab angles listed are applicable to the elevator in the neutral position. Refer to applicable Maintenance Manual. NOTE 12. Modification NB/M/977 (78 inch propeller) is approved for models BN2A-XX and is included in the BN2B-XX type design. When this Modification is incorporated on any BN2A or BN2B model which has Lycoming Model IO-540-K1B5 engines installed the following placard is required: "MANIFOLD PRESSURE MUST NOT EXCEED 23 INCHES Hg AT ENGINE SPEEDS BELOW 2250 RPM." The approved propellers are as follows: HC-C2YK-2B/C8477-6 2B/C8477A-6 2C/C8477-6 2C/C8477A-6 2CF/FC8477A-6 NOTE 13. The Britten-Norman Model BN2B series airplanes differ from the BN2A series airplanes by the factory only installation of Modification NB/M/978 which includes: Modification NB/M/977 (See Note 12); maximum structural landing weight increase to 6,600 lbs: fin mounted "strobe" beacon; redesigned instrument panel; and other product improvements which do not affect airplane performance and operating limitations. Compliance with FAR 36 for the BN2B models is achieved when propellers to either modification NB/M/977 or NB/M/1361 (BN2B-26 and -27 only) and tachometers to either modification NB/M/1090 or NB/M/1287 are fitted. Refer to Pilatus Britten-Norman Limited "Modification leaflet for Mod. NB-M-1090" Issue 2 dated March 5, 1980. NOTE 14. When external oil filter Modification NB/M/1323 is incorporated, the oil capacity is 7.5 U.S. quarts (7.5 U.S. qt per engine at -14.0 in.) NOTE 15. When elevator trim tab extended down travel Modification NB/M/1394 is incorporated, the down travel is 25° (BN2T and BN2B). NOTE 16. Modification NB/M/1361, alternate Hartzell 3-blade propeller (HC-C3YR-2UF/FC8468-8R) with C4558-2 spinner is approved for models BN2B-26 and BN2B-27 (refer to Flight Manual Document FM/42, supplement 10). NOTE 17. Previous propeller pitch settings of Low 13.0º ± 1º and High 80.5º ± .5º are approved, but not recommended. NOTE 18. When EASA issued the EASA.A.388 TCDS only models BN2A-8, BN2A-9, BN2A-20, -21, -26, -27 BN2B-20, -21, -26, -27, BN2T, BN2T-4R and BN2T-4S are covered. The other 5 models (BN2, BN2A, BN2A-2, BN2A-3, BN2A-6 on this TCDS are covered by issue of the relevant AAN (Airworthiness Approval Note) during the time in the the late 1960’s before EASA. NOTE 19. Modification NB/M/1772, alternate Hartzell Scimitar 3-blade propeller (HC-C3YR-2UF/FC7693F) with C4558-2P is approved for models BN2B-20 and BN2B-21 (refer to Flight Manual Document FM/43, Supplement 14). Modification NB/M/1772 meets noise requirements by reducing the maximum engine speed from 2700 rpm to 2625 rpm. VMC is changed to 42 knots (48 mph) for this modification. Page 31 of 31 A17EU NOTE 20. Modification NB-M-1669, “Introduction of 6600 lb Maximum Landing Weight” is approved for models BN2A-20, -21, -26, and-27. Refer to Flight Manual Supplement 54 to FM/10 for models BN2A-20 and BN2A-21, and Flight Manual Supplement to FM/20 for models BN2A-26 and BN2A-27. NOTE 21. A maximum of 10 seats shall be installed in the BN2T-4S at any time. The total number of occupants is not to exceed 10. NOTE 22. Model BN2T-4S airplanes eligible for import must have the following Britten-Norman modification embodied. These modifications are embodied as standard on constructor’s number C.4021 and later: NB-M-1695 NB-M-1712 Pt. 2 NB-M-1719 Pt. 2 NB-M-1728 Appendix 2, or Britten-Norman Service Bulletin SB.342 NB-M-1741 NB-M-1787 In addition, it should be confirmed that: The one-off procedure for the Emergency Exit Window Sealant (Britten-Norman SB.277) has been performed. The one-off inspection of the Universal Joint (Britten-Norman SB.284) has been performed. NOTE 23. Model BN2T-4S airplanes are eligible for Maximum Take-off Weight of 8,925 lb. and Maximum Landing Weight of 8,925 lb., when the Britten-Norman Modification No. NB-M-2175 is embodied and Flight Manual Supplement AFM/2T-4S Supplement 54 is incorporated.Model BN2T-4S airplanes are eligible for Maximum Take-off Weight of 8,925 lb. and Maximum Landing Weight of 8,925 lb., when the Britten-Norman Modification No. NB-M-2175 is embodied and Flight Manual Supplement AFM/2T-4S Supplement 54 is incorporated. .....END..... ``` ## ADs (63, first 50, in force first) - [AD 2025-01-01](https://openairdocs.org/ad/2025-01-01): Landing Gear System · Britten-Norman Aerospace BN-2, BN-2A, BN-2A-2 and 18 more. Effective Mar 11, 2025 - [AD 2024-08-03](https://openairdocs.org/ad/2024-08-03): Flight Control System Wiring · Britten-Norman BN-2, BN-2A, BN-2A-2 and 18 more. Effective Jun 3, 2024 - [AD 2023-09-09](https://openairdocs.org/ad/2023-09-09): Exhaust Turbine System (Recip) · Aerostar PA-60-600 (Aerostar 600), PA-60-601 (Aerostar 601), PA-60-601P (Aerostar 601P) and 292 more. Effective Jul 17, 2023 - [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 2021-18-01](https://openairdocs.org/ad/2021-18-01): Rudder Control System · B-N Group BN-2, BN-2A, BN-2A-2 and 14 more. Effective Oct 14, 2021 - [AD 2016-26-09](https://openairdocs.org/ad/2016-26-09): Navigation · B-N Group BN-2, BN-2A, BN-2A-2 and 17 more. Effective Feb 9, 2017 - [AD 2016-04-05](https://openairdocs.org/ad/2016-04-05): Engine Controls · B-N Group BN-2, BN-2A, BN-2A-2 and 15 more. Effective Mar 24, 2016 - [AD 2013-13-02](https://openairdocs.org/ad/2013-13-02): Fuel · B-N Group BN-2, BN-2A, BN-2A-2 and 17 more. Effective Aug 1, 2013 - [AD 2011-05-09](https://openairdocs.org/ad/2011-05-09): Flight Controls · B-N Group BN-2, BN-2A, BN-2A-2 and 14 more. Effective Apr 26, 2011 - [AD 2006-23-03](https://openairdocs.org/ad/2006-23-03): Horizontal stabilizer attachment bolts · B-N Group BN-2, BN-2A, BN-2A-2 and 14 more. Effective Dec 14, 2006 - [AD 2006-16-19](https://openairdocs.org/ad/2006-16-19): Elevator final drive control rods. · B-N Group BN-2, BN-2A, BN-2A-2 and 14 more. Effective Sep 18, 2006 - [AD 2006-12-07](https://openairdocs.org/ad/2006-12-07): ECi cylinder assemblies · Aerostar AEIO-320-D1B, AEIO-320-D2B, AEIO-320-E1A and 386 more. Effective Jul 11, 2006 - [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 2002-25-05](https://openairdocs.org/ad/2002-25-05): Universal joint · B-N Group BN-2, BN-2A, BN-2A-2 and 17 more. Effective Feb 3, 2003 - [AD 2002-25-03](https://openairdocs.org/ad/2002-25-03): Left-hand rudder bar · B-N Group BN-2A, BN-2A-2, BN-2A-20 and 10 more. Effective Jan 31, 2003 - [AD 2002-24-09](https://openairdocs.org/ad/2002-24-09): Left and right engine-mounting frame · B-N Group BN-2T and BN-2T-4R. Effective Jan 27, 2003 - [AD 2002-22-02](https://openairdocs.org/ad/2002-22-02): Engine Mount Bracket · B-N Group BN-2, BN-2A, BN-2A-2 and 17 more. Effective Dec 20, 2002 - [AD 2002-03-04](https://openairdocs.org/ad/2002-03-04): Emergency Exit Window Sealant · B-N Group BN-2, BN-2A, BN-2A-2 and 17 more. Effective Mar 29, 2002 - [AD 2002-02-10](https://openairdocs.org/ad/2002-02-10): Inboard Brackets of Elevator Outboard Hinge · B-N Group BN-2, BN-2A, BN-2A-2 and 14 more. Effective Mar 25, 2002 - [AD 2002-02-11](https://openairdocs.org/ad/2002-02-11): Oleo Attachment Brackets · B-N Group BN-2, BN-2A, BN-2A-2 and 17 more. Effective Mar 25, 2002 - [AD 2002-01-11](https://openairdocs.org/ad/2002-01-11): Throttle Friction-Shaft · B-N Group BN-2, BN-2A, BN-2A-2 and 17 more. Effective Feb 28, 2002 - [AD 98-18-07](https://openairdocs.org/ad/98-18-07): Generator System · B-N Group BN-2, BN-2A, BN-2A-2 and 15 more. Effective Oct 12, 1998 - [AD 98-16-14](https://openairdocs.org/ad/98-16-14): Main Landing Gear Fitting Attachment Bolts, Nuts, and Washers · B-N Group BN-2, BN-2A, BN-2A-2 and 14 more. Effective Sep 21, 1998 - [AD 98-04-17](https://openairdocs.org/ad/98-04-17): Diodes On Terminal Switches · B-N Group BN-2, BN-2A, BN-2A-2 and 15 more. Effective Mar 23, 1998 - [AD 98-04-21](https://openairdocs.org/ad/98-04-21): Airplane Flight Manual (AFM) - Limitations - Icing · B-N Group BN-2A, BN-2A-2, BN-2A-20 and 16 more. Effective Mar 13, 1998 - [AD 97-22-01](https://openairdocs.org/ad/97-22-01): Main Landing Gear Torque Link Assembly Area · B-N Group BN-2, BN-2A, BN-2A-2 and 13 more. Effective Nov 28, 1997 - [AD 97-22-02](https://openairdocs.org/ad/97-22-02): Engine Mounting Brackets, Bolts, and Bushes · B-N Group BN-2, BN-2A, BN-2A-2 and 17 more. Effective Nov 24, 1997 - [AD 96-18-21](https://openairdocs.org/ad/96-18-21): Aileron Mass Balance Clamp Unit · B-N Group BN-2, BN-2A, BN-2A-2 and 11 more. Effective Oct 25, 1996 - [AD 95-04-09](https://openairdocs.org/ad/95-04-09): Nose Wheel Steering System · B-N Group BN-2A, BN-2A-2, BN-2A-20 and 16 more. Effective Apr 14, 1995 - [AD 91-05-07](https://openairdocs.org/ad/91-05-07): Electrical System · B-N Group BN-2T and BN-2T-4R. Effective Mar 25, 1991 - [AD 91-05-09](https://openairdocs.org/ad/91-05-09): Engine Ignition System · B-N Group BN-2T and BN-2T-4R. Effective Mar 25, 1991 - [AD 87-04-11](https://openairdocs.org/ad/87-04-11): Isolator Mounting Brackets/Elastomer Cores · B-N Group BN-2T and BN-2T-4R. Effective Mar 9, 1987 - [AD 83-10-06 R1](https://openairdocs.org/ad/83-10-06-R1): Elevator Trim Tabs · B-N Group BN-2, BN-2A, BN-2A-2 and 15 more. Effective Feb 12, 1987 - [AD 86-23-02](https://openairdocs.org/ad/86-23-02): Modification NB/M/990 · B-N Group BN-2, BN-2A, BN-2A-2 and 11 more. Effective Dec 8, 1986 - [AD 83-23-01](https://openairdocs.org/ad/83-23-01): Wing Tank Fuel System Modification · B-N Group BN-2, BN-2A, BN-2A-2 and 15 more. Effective Dec 8, 1983 - [AD 83-07-12 R1](https://openairdocs.org/ad/83-07-12-R1): Fuel Transmitter Float Inspection · B-N Group BN-2, BN-2A, BN-2A-2 and 15 more. Effective Apr 11, 1983 - [AD 83-05-02](https://openairdocs.org/ad/83-05-02): Teleflex Swivel Assembly Inspection · B-N Group BN-2A, BN-2A-2, BN-2A-20 and 10 more. Effective Mar 7, 1983 - [AD 82-24-06 R1](https://openairdocs.org/ad/82-24-06-R1): Carburetor Air Box Shutter · B-N Group BN-2, BN-2A, BN-2A-26 and 7 more. Effective Feb 7, 1983 - [AD 81-19-04](https://openairdocs.org/ad/81-19-04): Hose Assembly · Rajay Hose Assemblies, 500A, 500B and 87 more. Effective Sep 17, 1981 - [AD 78-11-08](https://openairdocs.org/ad/78-11-08): Elevator and Flap Control Rods · B-N Group BN-2A, BN-2A-2, BN-2A-20 and 10 more. Effective Jun 6, 1978 - [AD 77-07-10](https://openairdocs.org/ad/77-07-10): Aileron Mass Balance Support Arm · B-N Group BN-2A, BN-2A-2, BN-2A-20 and 10 more. Effective Apr 18, 1977 - [AD 76-21-07](https://openairdocs.org/ad/76-21-07): Engine Mounting · B-N Group BN-2A, BN-2A-2, BN-2A-20 and 10 more. Effective Nov 5, 1976 - [AD 76-13-12](https://openairdocs.org/ad/76-13-12): Flap Retraction · B-N Group BN-2, BN-2A, BN-2A-2 and 6 more. Effective Jul 15, 1976 - [AD 76-06-05](https://openairdocs.org/ad/76-06-05): Pilot's Seat · B-N Group BN-2A, BN-2A-2, BN-2A-20 and 10 more. Effective Apr 19, 1976 - [AD 76-02-04](https://openairdocs.org/ad/76-02-04): Engine Mounting Frame · B-N Group BN-2A, BN-2A-2, BN-2A-20 and 10 more. Effective Jan 30, 1976 - [AD 75-26-01](https://openairdocs.org/ad/75-26-01): Rudder Control · B-N Group BN-2A, BN-2A-2, BN-2A-20 and 10 more. Effective Dec 23, 1975 - [AD 71-05-05](https://openairdocs.org/ad/71-05-05): Elevator Trim Tab System · B-N Group BN-2, BN-2A, BN-2A-2 and 11 more. Effective Jan 26, 1971 - [AD 70-12-11](https://openairdocs.org/ad/70-12-11): Flap Actuating System · B-N Group BN-2, BN-2A, BN-2A-2 and 11 more. Effective Jun 11, 1970 All 63: https://openairdocs.org/tcds/A17EU/ads.md ## Registered aircraft by registry model (OpenAirDocs) - [Britten-Norman BN2A-26 ISLANDER](https://openairdocs.org/model/britten-norman-bn2a-26-islander): 14 aircraft (registry code 1520226) - [Britten-Norman BN-2A](https://openairdocs.org/model/britten-norman-bn-2a): 8 aircraft (registry code 1520204) - [Britten-Norman BN-2A-8](https://openairdocs.org/model/britten-norman-bn-2a-8): 8 aircraft (registry code 1520209) - [Pilatus Britten-Norman BN2B-20](https://openairdocs.org/model/pilatus-britten-norman-bn2b-20): 6 aircraft (registry code 7080220) - [Britten-Norman BN-2A-27](https://openairdocs.org/model/britten-norman-bn-2a-27): 5 aircraft (registry code 1520227) - [Britten-Norman BN-2A-9](https://openairdocs.org/model/britten-norman-bn-2a-9): 4 aircraft (registry code 1520210) - [Britten-Norman BN-2B-26](https://openairdocs.org/model/britten-norman-bn-2b-26): 4 aircraft (registry code 1520350) - [Pilatus Britten-Norman BN-2B-21](https://openairdocs.org/model/pilatus-britten-norman-bn-2b-21): 4 aircraft (registry code 7080221) - [Britten-Norman BN-2A-20](https://openairdocs.org/model/britten-norman-bn-2a-20): 3 aircraft (registry code 1520220) - [Pilatus Britten-Norman BN-2T](https://openairdocs.org/model/pilatus-britten-norman-bn-2t): 3 aircraft (registry code 7090120) - [Britten Norman BN-2B-20](https://openairdocs.org/model/britten-norman-bn-2b-20): 2 aircraft (registry code 1520302) - [Britten-Norman BN-2A-21](https://openairdocs.org/model/britten-norman-bn-2a-21): 2 aircraft (registry code 1520221) - [Pilatus Britten-Norman BN2T ISLANDER](https://openairdocs.org/model/pilatus-britten-norman-bn2t-islander): 2 aircraft (registry code 7090121) - [B-N Group BN-2A-26](https://openairdocs.org/model/b-n-group-bn-2a-26): 1 aircraft (registry code 1520225) - [Britten-Norman BN-2 ISLANDER](https://openairdocs.org/model/britten-norman-bn-2-islander): 1 aircraft (registry code 1520202) - [Britten-Norman BN-2A-26](https://openairdocs.org/model/britten-norman-bn-2a-26): 1 aircraft (registry code 1520370) - [Britten-Norman BN-2A-6](https://openairdocs.org/model/britten-norman-bn-2a-6): 1 aircraft (registry code 1520205) - [Britten-Norman BN-2B-21](https://openairdocs.org/model/britten-norman-bn-2b-21): 1 aircraft (registry code 1520303) - [Pilatus Britten-Norman BN-2A-26](https://openairdocs.org/model/pilatus-britten-norman-bn-2a-26): 1 aircraft (registry code 7080229) - [Pilatus Britten-Norman BN-2B-26](https://openairdocs.org/model/pilatus-britten-norman-bn-2b-26): 1 aircraft (registry code 7090229) - [Pilatus Britten-Norman BN-2B-27](https://openairdocs.org/model/pilatus-britten-norman-bn-2b-27): 1 aircraft (registry code 7080227) - [B-N Group BN2T ISLANDER](https://openairdocs.org/model/b-n-group-bn2t-islander): 0 aircraft (registry code 1520400) - [Britten Norman BN-2T](https://openairdocs.org/model/britten-norman-bn-2t): 0 aircraft (registry code 1520375) - [Britten Norman BN2A-2](https://openairdocs.org/model/britten-norman-bn2a-2): 0 aircraft (registry code 1520206) - [Britten-Norman BN-2A-3](https://openairdocs.org/model/britten-norman-bn-2a-3): 0 aircraft (registry code 1520215) - [Britten-Norman BN-2A-6-ISLANDER](https://openairdocs.org/model/britten-norman-bn-2a-6-islander): 0 aircraft (registry code 1520222) - [Britten-Norman BN-2T-4R](https://openairdocs.org/model/britten-norman-bn-2t-4r): 0 aircraft (registry code 1520376) - [Britten-Norman BN-2T-4S](https://openairdocs.org/model/britten-norman-bn-2t-4s): 0 aircraft (registry code 1520379) - [Britten-Norman BN2T ISLANDER](https://openairdocs.org/model/britten-norman-bn2t-islander): 0 aircraft (registry code 1520378) - [Pilatus Britten Norman BN-2A-27](https://openairdocs.org/model/pilatus-britten-norman-bn-2a-27): 0 aircraft (registry code 7090227) ## STCs approved under this data sheet (132, 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 SA12428CH](https://openairdocs.org/stc/SA12428CH): Installation of the Lycoming Engines Electronic Ignition System (EIS). Lycoming Engines, An Operating Division of AVCO Corporation - [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 SA02511SE](https://openairdocs.org/stc/SA02511SE): Installation of replacement fuel quantity indicator sending unit(s). CiES Inc. - [STC SA02738CH](https://openairdocs.org/stc/SA02738CH): Installation of L-3 Communications Avionics Systems. Acron Aviation Inc. - [STC SA04046CH PAGE 1](https://openairdocs.org/stc/SA04046CH%20PAGE%201): Installation of L-3 GENESIS (TM) Electronic Standby Instrument System (ESI-500/MAG-500). Acron Aviation Inc. - [STC SA04378CH](https://openairdocs.org/stc/SA04378CH): Installation of an engine modified per STC SE04349CH. SureFly Partners Ltd. - [STC SA01757WI](https://openairdocs.org/stc/SA01757WI): To allow the use of UL91 or UL94 (minimum) grade aviation fuel. Swift Fuels LLC - [STC SA02658SE](https://openairdocs.org/stc/SA02658SE): Installation of Garmin GI 275 Multi-Function Display System. Garmin International Inc. - [STC SA2243WE](https://openairdocs.org/stc/SA2243WE): Installation of Rajay turbocharged Lycoming O-540-E4C5 engines.. TALCO Aviation - [STC SA01435LA](https://openairdocs.org/stc/SA01435LA): Installation of engines modified with Firewall Forward Technologies LLC modified camshaft. Centri-Lube Technologies LLC - [STC SA00076IB](https://openairdocs.org/stc/SA00076IB): Installation of Photo luminescent Safety Systems. STG AEROSPACE GERMANY GmbH - [STC SA02203AK](https://openairdocs.org/stc/SA02203AK): Installation of FlightLogic Synthetic Vision Electronic Flight Information System (EFIS-SV).. Genesys Aerosystems Inc. - [STC SA02254AK](https://openairdocs.org/stc/SA02254AK): Installation of "Single Screen", "2 or 3 Screen", "Dual Screen", or "4 or 6 screen". Genesys Aerosystems 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 SA11174SC PAGE 1](https://openairdocs.org/stc/SA11174SC%20PAGE%201): Installation of BendixKing by Honeywell KSN 770 and KSN 765 WAAS LPV approach capable nav/comm systems. Honeywell International Inc (Bendix King) - [STC SA02430SE](https://openairdocs.org/stc/SA02430SE): Fabrication and installation of a camera housing. Airborne Sensor LLC - [STC SA00401BO](https://openairdocs.org/stc/SA00401BO): Installation of a SkyTrax100B UAT receiver. Avidyne Corporation - [STC SA02426AK](https://openairdocs.org/stc/SA02426AK): Approval of the FreeFlight FDL-978-TX ADS-B system installed. FreeFlight Systems - [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 SA02268CH](https://openairdocs.org/stc/SA02268CH): Installation of Airwolf Filter Corp. Air Oil Separator. Airwolf Filter Corporation - [STC SA01714WI](https://openairdocs.org/stc/SA01714WI): Installation of a Garmin transponders: (a) GTX 330/330D/33/33D with ADS-B Out functionality; (b) GTX 335/335R/345/345R with ADS-B Out and In functionality; or (c) GTX 335R/345R with ADS-B Out functionality in select airplanes installed with G950/G1000 systems.. Garmin International Inc - [STC SA03286CH](https://openairdocs.org/stc/SA03286CH): Install an electronic engine ignition system. Electroair Acquisition Corporation - [STC SA04032CH](https://openairdocs.org/stc/SA04032CH): Install rocker switch assemblies. Electroair Acquisition Corporation - [STC SA2455WE](https://openairdocs.org/stc/SA2455WE): Installation of air conditioning system.. Air Comm Corporation - [STC SA00344BO PAGE 1](https://openairdocs.org/stc/SA00344BO%20PAGE%201): Installation of Parmetheus Plus LED PAR36 and PAR46 taxi and landing lights.. Whelen Aerospace Technologies - [STC SA615EA](https://openairdocs.org/stc/SA615EA): Installation of a Whelen Anti-Collision Strobe Light System as replacement for originally installed anti-collision lights.. Whelen Aerospace Technologies - [STC SA04165NY](https://openairdocs.org/stc/SA04165NY): Installation of Latitude Technologies Skynode S200 Satcom system must be performed. Latitude Technologies Corporation - [STC SA02153LA-D PAGE 1](https://openairdocs.org/stc/SA02153LA-D%20PAGE%201): Installation of Garmin G600 Primary Flight Display (PFD) and Multifunction Display (MFD) System. Garmin International Inc. - [STC SA04424AT](https://openairdocs.org/stc/SA04424AT): Installation of Continental Motors, Inc. (CMI) Shower-of-Sparks Starting Vibrator Booster Systems. Continental Motors, Inc. - [STC SA01828SE](https://openairdocs.org/stc/SA01828SE): Installation of J.P. Instruments (JPI) EDM-960 Primary Engine Data Management System. J. P. Instruments - [STC SA00024NY](https://openairdocs.org/stc/SA00024NY): Installation of Airwolf remote mounted engine oil filter kit AFC-K007 on single or multi-engine fixed wing light aircraft incorporating Lycoming reciprocating engines of 450 horsepower or less.. Airwolf Filter Corporation - [STC SA01933LA-D](https://openairdocs.org/stc/SA01933LA-D): Installation of Garmin Model 400W / 500W Series GPS-WAAS Navigation System. Garmin International Inc - [STC SA02212AK](https://openairdocs.org/stc/SA02212AK): Replacement of existing landing and/or taxi light reflector and bulbs with high intensity discharge (HID) lighting systems. Seaplanes North LLC - [STC SA00382BO](https://openairdocs.org/stc/SA00382BO): Installation of Globalstar Antenna and Cradle provisions to support a Globalstar GPS-1700 in non-composite airplanes. Avidyne Corporation - [STC SA02428SE](https://openairdocs.org/stc/SA02428SE): Installation of an Air Stream Switch for an electric time recording device on non-pressurized aircraft. Henry F Rogers/David E Polley - [STC SA00343BO](https://openairdocs.org/stc/SA00343BO): Installation of a single configuration or a dual configuration Avidyne Corporation Integrated Flight Display, Model IFD540 loaded with Release 10.0 software (or later FAA approved release). Avidyne Corporation - [STC SA1842WE](https://openairdocs.org/stc/SA1842WE): Installation of Brittain Industries, Inc. Model B-5 Flight Control System. Brittain Industries, Inc - [STC SA00352BO PAGE 1](https://openairdocs.org/stc/SA00352BO%20PAGE%201): Installation of an Avidyne Corporation Mode A/C/S Transponder with ADS-B Out capability, Model AXP340 loaded with Version 3.13 software (or later FAA approved version),. Avidyne Corporation - [STC SA01559CH](https://openairdocs.org/stc/SA01559CH): Install Aero Medical Products air ambulance stretcher P/N 125 using Installation Kit P/N 805. Approval is for stretcher structure, structural attachment of an oxygen bottle, and optional medical oxygen system only.. Paul/ Lanna Egan LLC - [STC SA4553SW](https://openairdocs.org/stc/SA4553SW): Installation of Brittain Model NAV Flite IV Model BI-825 system or B5C Model BI826 system. Brittain Industries, Inc - [STC SA02954CH](https://openairdocs.org/stc/SA02954CH): Installation of a replacement pitot static probe.. Seginus, Inc. - [STC SA00944CH](https://openairdocs.org/stc/SA00944CH): Replace Janitrol combustion heater Model 81D94-X (XX) with C&D Associates combustion heater Model CD25K, CD35K, and CD45K. Hartzell Engine Technologies, LLC - [STC SA02119SE PAGE 1](https://openairdocs.org/stc/SA02119SE%20PAGE%201): Installation of Garmin GDL 88 ADS-B UAT Transceiver System. Garmin International Inc - [STC SA01969SE](https://openairdocs.org/stc/SA01969SE): Installation of a Mid-Continent MD302 Standby Attitude Module. Mid-Continent Instruments and Avionics All 132: https://openairdocs.org/tcds/A17EU/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.