# TCDS A11EU: British Aerospace Aircraft Group - Type: Type certificate data sheet - Status: Current - Holder: British Aerospace Aircraft Group - Revision: 6 - Revised: April 17, 2012 - Product: Aircraft, Small Airplane - Certification basis: Part 3, Part 21, Part 23, Part 25, CAR 3 - Registered aircraft: 4, by the registry models matched to it (OpenAirDocs) - Data sheet PDF: https://openairdocs.org/files/sha256/d5/02/d5029386659018c2bd2dec4bb99038f9a0b5da6393f49afc9bc64b38ed14447d - FAA DRS: https://drs.faa.gov/browse/excelExternalWindow/92C4947D0FD1C025862579E600639B83.0001 - Page: https://openairdocs.org/tcds/A11EU ## Models (2) As the data sheet lists them. - B.206 Series 2 - B.206 Series 1 ## 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 Rev No. 6 4 4 4 Surrendered April 17, 2012 DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION A11EU Revision 6 British Aerospace Aircraft Group Scottish Division Beagle B.206 Series 1 & 2 April 17, 2012 TYPE CERTIFICATE DATA SHEET NO. A11EU This data sheet which is part of Type Certificate No. A11E U prescribes conditions and limitations under which the product for which the Type Certificate was issued meets the airworthiness requirements of the Civil Air Regulations. Type Certificate Holder British Aerospace, Aircraft Group, Scottish Division Prestwick Airport Ayrshire Scotland KA9 2RW (1) This TC was surrendered for cancellation on April 17, 2012. Only standard airworthiness certificates issued prior to April 17, 2012 are valid. (2) Future unsafe conditions existing in the aircraft may result in the revocation of the airworthiness certificates of the aircraft if there is no entity to comply with 14 CFR 21.99(a), “Required design changes.” (3) The United Kingdom Civil Aviati on Authority (UK CAA), is has assu med the responsibility for continued airworthiness. Contact Certification Projects Department, at the UK Civil Aviation Authority at +44 (0) 1293 573293, or email certification.projects@caa.co.uk for continued airworthiness requirements. I - Model B.206 Series 1, 7PCLM (Normal Category), Approved November 7, 1966. Engines 2 Continental GIO-470-A Fuel 100/130 minimum grade aviation gasoline Engine limits For all opera tions, 3,200 r.p.m. (310 H.P.) Propeller and McCauley 2AF36C 68/100 RFM-10 2 bladed metal. propeller limits Diameter ra nge 90" maximum - 88" minimum (No further reduction permitted). Pitch setting at 36 in. station: Low 12° High 81.6° Airspeed limits (I.A.S.) Knots M.P.H. Vne (never exceed) 235 270 Vno (Max. structural cruising) 210 242 Vp (Manoeuvering) 155 178 Vfe (Flaps down 20°) 135 155 Vfe (Flaps down 40°) 125 144 Vlo (Landing gear operation) 125 144 Vmc (Minimum control) 66 76 Maximum speed for cooling flaps operation and open. 210 242 C.G. range (Landing (+126.9 in.) to (+134.2 in.) with 6,000 lbs. gear extended) (+128.1 in.) to (+134.2 in.) with 6,400 lbs. Straight line variation between points. Moment due to retracting landing gear - 1,900 in.lb. Empty weight C.G. range None Datum Fuselage station zero which is situ ated 132.5 inches forward of the weighing reference station which is marked on a plate on the fuselage. Leveling means Holes for datum pins on which straight edge is placed, are located on the left side of the fuselage. Maximum weight 6,400 lbs. Number of seats 7 (2 at (+108)), (2 at (+141)), (3 at (+174)) Maximum baggage 210 lbs. (+205) Fuel capacity 228 U.S. galls. usable (+145) (See Note 1 for data on unusable fuel) Oil capacity 7.0 U.S. galls. usable (+75) . (See Note 1 for data on system oil) Control surface movements Wing flaps Down 39° + 1° Aileron Up 23° + 0.25° Down 17° + 0.25° Aileron tab Up 16° + 0.25° Down 16° + 0.25° Elevator Up 25° + 0.25° Down 15° + 0.25° Elevator trim tab Up 15° + 1°, -0.5° Down 25° + 1°, -0.5° Elevator anti-balance tab Up 20° + 1° Down 13° + 1° Rudder Right 25° + 0.5° Left 25° + 0.5° Rudder tab Right 20.5° + 0.5° Left 20.5° + 0.5° Certification basis FAR 21.29 CAR 3, May 15, 1956, including amendments 3-1 through 3-8. Type Certificate No. A11EU issued November 7, 1966. Date of application for Type Certificate January 22, 1965. Equipment Equipment is as listed in Equipment List B2/B206/1. Approved alternate equipment is as listed in CAA letter 9/30/ABA/08 dated August 18, 1976. Basic required equipment as prescribed in the applicable airworthiness regulations (see Certification Basis) is marked with a star in the Equipment List and must be installed in the aircraft for certificati on. In addition, the Flight Manual for the aircraft is the A.R.B. approved Airp lane Flight Manual DOC. No. BS.1-5 dated October 20, 1966. II - Model B.206 Series 2, 7PCLM (Normal Category), Approved April 18, 1967. Engines 2 Continental GTSIO-520-C Fuel 100/130 minimum grade aviation gasoline Engine limits For all operations, 3,200 r.p.m. (340 H.P.) (SEE NOTE 4). Propeller and McCauley 3F 34C86/90LF 3 bladed metal. propeller limits Diameter ra nge 90" maximum - 88" minimum (No further reduction permitted). Pitch setting at 30 in. station: Low 13° High 85° Hartzell HC-A3VF-2D/V8833B Diameter range 88-3/8" maximum - 86-3/8" minimum. (No further reduction permitted) Pitch setting at 30 in. station: Low 15° High 85° Airspeed limits (I.A.S.) Knots M.P.H. Vne (never exceed) 235 270 Vno (Max. structural cruising) 210 242 Vp (Maneuvering) 155 178 Vfe (Flaps down 20°) 140 161 Vfe (Flaps down 40°) 125 144 Vle (Landing gear extended) 140 161 Vlo (Landing gear operation) 125 144 Vmc (Minimum control) 66 76 Maximum speed for cooling flaps operation and open. 210 242 C.G. range (Landing (+123.4 in.) to (+133.5 in.) with 5,750 lbs. gear extended) (+128.0 in.) to (+133.5 in.) with 7,500 lbs. Straight line variation between points. Moment due to retracting landing gear 1,890 in.lb. Maximum weight 7,500 lbs. Maximum zero fuel weight 7,050 lb. Number of seats 8 (2 at (+108)), (2 at (+141)), (2 at (+170)), (2 at (+199)). Maximum baggage 180 lbs. (+232) Fuel capacity 228 U.S. gal. usable (+ 145) (See NOTE 1 for data on unusable fuel) Oil capacity 6.5 U.S. gal. usable (+70) . (See NOTE 1 for data on system oil) Control surface movements Wing flaps Down 39° + 1° Aileron Up 23° + 0.25° Down 17° + 0.25° Aileron tab Up 16° + 0.25° Down 16° + 0.25° Elevator Up 25° + 0.25° Down 15° + 0.25° Elevator trim tab Up 19° + 0.5° Down 29.5° + 0.5° Elevator anti-balance tab Up 19° + 1° Down 15° + 1° (Flaps up) Rudder Right 25° + 0.5° Left 25° + 0.5° Rudder tab Right 20.5° + 0.5° Left 20.5° + 0.5° Certification basis FAR 21.29 CAR 3, May 15, 1956, including ame ndments 3-1 through 3-8, FAR 23.205 as amended by amendment 23-3, and FA R 23.1325 as amended by amendment 23-1. Type Certificate No. A11EU amended April 18, 1967. Date of application for Type Certificate: January 22, 1965. Compliance has been established with the following optional requirements: Ice Protection Provisions FAR 25.1419 when Beagle Modifications 424 and 443, Goodrich deicing boots on the leading edge s of wing, stabilizer and fin have been installed. Equipment Equipment is as lis ted in Equipment List B2/B206/2. Basic required equipment as prescribed in the applicable airwor thiness regulations (see Certification Basis) is marked with a star in the Equipm ent List and must be installed in the aircraft for certification. In addition, the Flight Manual for the aircraft is the A.R.B. Approved Airplane Flight Manua l DOC. No. BS 1/6 dated February 15, 1967. SPECIFICATIONS PERTINENT TO ALL MODELS Datum Fuselage station zero which is situ ated 132.5 inches forward of the weighing reference station which is marked on a plate on the fuselage. Leveling means Holes for datum pins on which straight edge is placed, are located on the left side of the fuselage. Serial Nos. eligible The United Kingdom Certificat e of Airworthiness for Export endorsed as noted under "Import Requirements" must be submitted for each individual aircraft for which application for certification is made. Import requirements A United States Airworthiness Certificate may be issued on the basis of a U.K. Certificate of Airworthiness for Export signed by a representative of the Board of Trade containing the following statement: "The aircraft covered by this Certifi cate has been examined and found to comply with CAR 3 effective May 15, 1956 in cluding amendments 3-1 through 3-8 and conforms to Type Certificate A11EU." NOTE 1: Current weight and balance report including lis t of equipment in certificated empty weight and loading instructions, must be provided for each aircraft at the time of original certification. The certificated empty weight and corresponding cen ter of gravity locations must include unusable fuel of 36 lbs. (146.9) and system oil of 9 lbs. (75.0 Series 1) (70.0 Series 2). NOTE 2: The following placard must be displayed on th e instrument panel in fuel view of the pilot: "THIS AIRPLANE MUST BE OPERATED AS A NORMAL CATEGORY AIRPLANE IN COMPLIANCE WITH THE OPERATING LI MITATIONS STATED IN THE FORM OF PLACARDS MARKINGS AND MANUALS, NO ACROBATIC MANOEUVRES INCLUDING SPINS ARE APPROVED." FOOTNOTE : All placards required in the Approved Airplane F light Manual must be installed in the appropriate locations. NOTE 3: Each individual airplane will be supplied with a placard that specifies the kind of operation such as V.F.R. , I.F.R., day or night to which the operation of the airplane is limited by the equipment installed. NOTE 4: Avoid continuous ope ration between 2800 and 3135 rpm. ---END--- ``` ## ADs (2, in force first) - [AD 78-12-02](https://openairdocs.org/ad/78-12-02): Exhaust System Bellows Assembly · British Aerospace, Aircraft Group B.206 Series 2. Effective Jun 22, 1978 - [AD 77-23-05](https://openairdocs.org/ad/77-23-05): Wing or Empennage Assemblies · British Aerospace, Aircraft Group B.206 Series 1 and B.206 Series 2. Effective Dec 10, 1977 ## Registered aircraft by registry model (OpenAirDocs) - [Beagle B.206 SERIES 1](https://openairdocs.org/model/beagle-b-206-series-1): 2 aircraft (registry code 1121223) - [Beagle B.206 SERIES 2](https://openairdocs.org/model/beagle-b-206-series-2): 2 aircraft (registry code 1121224) ## STCs approved under this data sheet (26) - [STC SA00079NY](https://openairdocs.org/stc/SA00079NY): Installation of Airwolf remote mounted engine oil filter kit AFC-K008 on single and multi engine fixed wing light aircraft incorporating Teledyne Continental reciprocating engines of 450 horsepower or less.. Airwolf Filter Corporation - [STC SA5581SW](https://openairdocs.org/stc/SA5581SW): Installation of ALCOR true-flow/ totalizer system. Alcor LLC - [STC SA02268CH](https://openairdocs.org/stc/SA02268CH): Installation of Airwolf Filter Corp. Air Oil Separator. Airwolf Filter Corporation - [STC SA02930NY](https://openairdocs.org/stc/SA02930NY): Installation of Insight Instrument Corporation Graphic Engine Monitor (GEM 610C) models G3, G2, and G1 and 1200C model G4 as primary Cylinder Head Temperature (CHT), Exhaust Gas Temperature (EGT), and Turbine Inlet Temperature (TIT) Instruments. Insight Instrument Corporation - [STC SA2693NM](https://openairdocs.org/stc/SA2693NM): Installation of Electronics International digital volt/amp gauges and accessories.. Electronics International Inc. - [STC SA593CH](https://openairdocs.org/stc/SA593CH): Install Champion SlickSTART magneto booster system.. Champion Aerospace LLC - [STC SA4005NM](https://openairdocs.org/stc/SA4005NM): Precise Flight Inc. Pulselite Control System. Precise Flight Inc - [STC SA20GL](https://openairdocs.org/stc/SA20GL): Installation of Woodward Type II electronic propeller synchronizer or synchrophaser system. (G-44A MODIFIED COLEMILL - STC 2-13) (500-A modified - Colemill STC SA340SO). Ontic Engineering and Manufacturing Inc. - [STC SA01860NY](https://openairdocs.org/stc/SA01860NY): Installation of Graphic Engine Monitors (GEM) Models GEM-610 and GEMINI 1200.. Insight Instrument Corporation - [STC SA00680SE](https://openairdocs.org/stc/SA00680SE): Installation of Electronics International model UBG-16 or UBG-16T bar graph engine analyzer.. Electronics International - [STC SA2687NM](https://openairdocs.org/stc/SA2687NM): Installation of Truboplus/ Electronics Int'l gauges and switches.. Aero Manufacturing Inc. - [STC SA00804SE](https://openairdocs.org/stc/SA00804SE): Installation of an engine failure indicator system, also referred to as a 'low Thrust Detector system.'. Advanced Aero Safety Inc. - [STC SA1007NW](https://openairdocs.org/stc/SA1007NW): Installation of a low thrust detector system.. Engine-Out Warning Systems, LLC - [STC SA157NE](https://openairdocs.org/stc/SA157NE): Installation of Graphic Engine Monitor System Model GEM-602 S/N 403 and GEM-603 S/N001126and subsequent.. Insight Instrument Corp - [STC SA00627AT](https://openairdocs.org/stc/SA00627AT): Installation of an outward opening door.. South Florida Aircraft - [STC SA1626NM PAGE 1](https://openairdocs.org/stc/SA1626NM%20PAGE%201): Installation of Electronics Int'l Digital EGT/CHT Instruments and accessories. (201 Series). Electronics International - [STC SA300CE](https://openairdocs.org/stc/SA300CE): Installation of Woodward propeller governors on single and twin engine aircraft. (PA-31-325 modified per Colemill STC SA 970SO). Woodward Governor Company - [STC SA2350NM PAGE 1](https://openairdocs.org/stc/SA2350NM%20PAGE%201): Installation of Electronics International Inc digital carburetor/outside air temperature gauges. Electronics International - [STC SA2765SO](https://openairdocs.org/stc/SA2765SO): Installation of intercoolers in the induction system.. Aeronautical Engineers, Inc - [STC SA4302NM](https://openairdocs.org/stc/SA4302NM): Installation of Electronics Int'l digital automatic engine analyzer.. Electronics International - [STC SA3862NM PAGE 1](https://openairdocs.org/stc/SA3862NM%20PAGE%201): Installation of Electronics International Primary TIT/EGT/CHT instruments, remote switches and associated accessories.. Electronics International - [STC SA2190NM PAGE 1](https://openairdocs.org/stc/SA2190NM%20PAGE%201): Installation of electronics International Digital Volt/Amp Gauges and Accessories.. Electronics International - [STC SA1450SO](https://openairdocs.org/stc/SA1450SO): Installation of two engines modified in accordance with STC SE1447SO, derated to 340 HP and equipped with McCauley propellers.. South Florida Aircraft Sales & Leasing, Inc - [STC SA667SO](https://openairdocs.org/stc/SA667SO): Installation of Bendix Model M-4C automatic flight control system.. Bendix Corporation Avionics Div - [STC SA683SO](https://openairdocs.org/stc/SA683SO): Installation of Goodrich wheels, brakes, and tires on main landing gears.. Miami Aviation Corp - [STC SA2350NM](https://openairdocs.org/stc/SA2350NM) (historical): Installation of Electronics International Inc digital carburetor/outside air temperature gauges listed on the attached continuation sheet and the associated accessories.. Electronics International --- 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.