TCDS A27EU

Page No. 1 2 3 4 5 6 Rev. No. 6 6 6 4 5 6 DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION A27EU Revision 6 AIRBUS DEFENCE AND SPACE GMBH EADS DEUTSCHLAND GMBH DAIMLER CHRYSLER AEROSPACE AG DAIMLER-BENZ AEROSPACE AG DEUTSCHE AEROSPACE AG MESSERSCHMITT-BÖLKOW-BLOHM AG MESSERSCHMITT-BÖLKOW-BLOHM GMBH BO-209-150 FV & RV BO-209-160 FV & RV BO-209-150 FF March 4, 2026 TYPE CERTIFICATE DATA SHEET NO. A27EU This data sheet, which is a part of Type Certificate No. A27EU, 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 Airbus Defence and Space GmbH Willy-Messerschmitt-Strasse 1 85521 Ottobrunn Germany Type Certificate Ownership Record Messerschmitt-Bölkow-Blohm GmbH transferred TC A27EU to Messerschmitt-Bölkow- Blohm AG on April 1, 1992 (See NOTE 4.) Messerschmitt-Bölkow-Blohm AG transferred TC A27EU to Deutsche Aerospace AG on November 30, 1992 Deutsche Aerospace AG transferred TC A27EU to Daimler-Benz Aerospace AG on January 2, 1995 Daimler-Benz Aerospace AG transferred TC A27EU to Daimler Chrysler Aerospace AG on November 17, 1998 Daimler Chrysler Aerospace AG transferred TC A27EU to EADS Deutschland GmbH on July 10, 2000 EADS Deutschland GmbH transferred TC A27EU to Airbus Defence and Space GmbH on July 1, 2014 (See NOTE 7.) I - Model BO-209-150 FV and RV, 2 PCLM (Normal and Utility Category), approved 9 July 1971 (FV model has fixed nose L.g.; RV model has retractable nose L.g.). (See NOTE 8) Engine Lycoming O-320-E1C or O-320-E1F Fuel 80/87 minimum grade aviation gasoline Engine limits For all operations, 2700 r.p.m. (150 hp.) Propeller and Hartzell HC-C2YL-1B/7663A-6 propeller limits Diameter: 70 in. no further reduction permitted Pitch setting at 30 in. radius: High 27° Low 12°12' Spinner: MBB P/N 209-61056 Governor: Woodward P/N T210452 or P/N 210681 Airspeed limits (CAS) Normal and Utility Category 2 A27EU Never exceed 173 knots (199 m.p.h.) Maximum structural cruising 135 knots (155 m.p.h.) Maneuvering 117 knots (135 m.p.h.) Flaps extended 88 knots (101 m.p.h.) *Landing gear operation 104 knots (120 m.p.h.) *Landing gear extended 173 knots (199 m.p.h.) (*Applies only to the RV model). C.G. range Normal Category (85.47) to (89.37) at 1265 lb. or less (86.92) to (89.37) at 1808 lb. Utility Category (85.47) to (89.37) at 1265 lb. or less (86.25) to (89.37) at 1565 Maximum weight 1808 lb., for Normal Category 1565 lb., for Utility Category No. of seats 2 at (+ 90.7) Maximum baggage 110 lb. at (+114.2) Fuel capacity 39.2 gal. total (38.6 gal. usable; two 19.6 gal., wing tanks at + 90.7) Oil capacity 8 qt. (+3.94) See NOTE 1 for unusable fuel and undrainable oil data. II - Model BO-209-160 FV and RV, 2 PCLM (Normal and Utility Category), approved 9 July 1971 (FV model has fixed nose L.g.; RV model has retractable nose L.g.). (See NOTE 8) Engine Lycoming IO-320-D1A or IO-320-D1B Fuel 100/130 minimum grade aviation gasoline Engine limits For all operations, 2700 r.p.m. (160 hp.) Propeller and Hartzell HC-C2YL-1B/7663A-6 propeller limits Diameter: 70 in. no further reduction permitted Pitch setting at 30 in. radius: High 27° Low 14°57' Spinner: MBB P/N 209-61056 Governor: Woodward P/N T210452 or P/N 210681 Airspeed limits (CAS) Normal and Utility Category Never exceed 173 knots (199 m.p.h.) Maximum structural cruising 135 knots (155 m.p.h.) Maneuvering 117 knots (135 m.p.h.) Flaps extended 88 knots (101 m.p.h.) *Landing gear operation 104 knots (120 m.p.h.) *Landing gear extended 173 knots (199 m.p.h.) (*Applies only to the RV model). C.G. range Normal Category (85.47) to (89.37) at 1265 lb. or less (86.92) to (89.37) at 1808 lb. Utility Category (85.47) to (89.37) at 1265 lb. or less (86.25) to (89.37) at 1565 lb. Maximum weight 1808 lb. for Normal Category 1565 lb. for Utility Category 3 A27EU No. of seats 2 at (+ 90.7) Maximum baggage 110 lb. at (+ 114.2) Fuel capacity 39.2 gal. total (38.6 gal. usable; two 19.6 gal., wing tanks at + 90.7) Oil capacity 8 qt. (+3.94) See NOTE 1 for unusable fuel and undrainable oil data. III - Model BO-209-150 FF, 2 PCLM (Normal and Utility Category), approved 9 July 1971 (fixed nose L.g.). (See NOTE 8) Engine Lycoming O-320-E2C or O-320-E2F Fuel 80/87 minimum grade aviation gasoline. Engine limits For all operations, 2700 r.p.m. (150 hp.) Propeller and McCauley 1C172MGM-70.5-60 or -66 propeller limits Static r.p.m. at maximum permissible throttle setting: Not over 2400, not under 2100 No additional tolerance permitted. Diameter: Maximum 70.5 in., minimum for repairs 70 in. No further reduction permitted Spinner: MBB P/N 209-61156 Airspeed limits (CAS) Normal and Utility Category Never exceed 173 knots (199 m.p.h.) Maximum structural cruising 135 knots (155 m.p.h.) Maneuvering 117 knots (135 m.p.h.) Flaps extended 88 knots (101 m.p.h.) C.G. range Normal Category (85.47) to (89.37) at 1265 lb. or less (86.92) to (89.37) at 1808 lb. Utility Category (85.47) to (89.37) at 1265 lb. or less (86.25) to (89.37) at 1565 lb. Maximum weight 1808 lb., for Normal Category 1565 lb., for Utility Category No. of seats 2 at (+ 90.7) Maximum baggage 110 lb. at (+114.2) Fuel capacity 39.2 gal. total (38.6 gal. usable; two 19.6 gal., wing tanks at + 90.7) Oil capacity 8 qt. (+3.94) See NOTE 1 for unusable fuel and undrainable oil data. 4 A27EU DATA PERTINENT TO ALL MODELS Control Surface Movements Ailerons Up 29° + 1° Down 14° + 1° Wing flaps Down 35° + 0° - 3° Stabilator Up 18° + 1° Down 9° + 1° Rudder Left 28° + 2° Right 28° + 2° Stabilator trim, distance measured between trailing edge of trim tab and trailing edge of stabilator with stabilator in the neutral position. tab neutral: 0.32 in. Down, + 0.08 in. nose down: 0.20 in. Up, + 0.08 in. nose up: 0.66 in. Down, + 0.08 in. total travel: 0.86 in. + 0.16 in. Datum 75.51 in. forward of wing leading edge at split line of the wing/wing stub fairing. Leveling means Two leveling points on left side of fuselage. Serial Nos. eligible Serial Numbers 121 and subsequent. The Federal Republic of Germany Government Certificate of Airworthiness for Export endorsed as noted below under "Import Requirements" must be submitted for each individual aircraft for which application for airworthiness certification is made. Certification basis FAR 21.29 and FAR 23 dated 1 February 1965 as amended by Amendments 23-1 through 23-9 inclusive. Type Certificate No. A27EU, issued 9 July 1971. Date of Application for Type Certificate: 11 May 1970. The Luftfahrt Bundesamt originally type certificated this aircraft under its type certificate Number 680. The FAA validated this product under U.S. Type Certificate Number A27EU. Effective September 28, 2003, the European Aviation Safety Agency (EASA) began oversight of this product on behalf of Germany. The EASA type certificate for the BO-209 models is EASA.A.357. Import Requirements The FAA can issue a U.S. airworthiness certificate based on an NAA Export Certificate of Airworthiness (Export C of A) signed by a representative of the Luftfahrt Bundesamt on behalf of the European Community. The Export C of A should contain the following statement: ‘The aircraft covered by this certificate has been examined, tested, and found to comply with U.S. airworthiness regulations 14 CFR Part 23 approved under U.S. Type Certificate No. A27EU and to be in a condition for safe operation.’ Service Information Each of the documents listed below must state that it is approved by the European Aviation Safety Agency (EASA) or – for approvals made before September 28, 2003 – by the Luftfahrt Bundesamt. • Service bulletins, • Structural repair manuals, • Vendor manuals, • Aircraft flight manuals, and • Overhaul and maintenance manuals. The FAA accepts such documents and considers them FAA-approved unless one 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 changes to this product’s U.S. type certificate as defined in 14 CFR § 21.93. 5 A27EU Service Information, cont'd The FAA uses the post type validation procedures to approve these documents. The FAA may delegate on case-by-case 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. Equipment The basic required equipment as prescribed in the applicable airworthiness regulations (see Certification Basis) must be installed in the aircraft for certification. In addition, the following items of equipment are required: 1. Stall Warning System. 2. LBA-approved Model BO-209 Approved Flight Manual, Ref. No. LF37E-7/71 dated July 1971 or later LBA-approved revision, (prior to September 28, 2003), or approved by EASA on or after that date. 3. Airplanes S/N 121 through 130 must be modified in accordance with MBB Technical Note TN 9-71 to provide an alternate static system source and an aural landing gear warning system. (These systems are incorporated in production on S/Ns 131 and subsequent). NOTE 1. Current weight and balance report including list of equipment in certificated empty weight, and loading instructions when necessary, must be provided for each airplane at the time of original airworthiness certification. The certificated empty weight and corresponding center of gravity must include undrainable oil of 0 lbs. at +39.4 and unusable fuel of 3.6 lb. at +90.7. NOTE 2. The following placard must be displayed in front and in clear view of the pilot: "This airplane must be operated as a Normal or Utility Category airplane in compliance with their operating limitations stated in the form of placards, markings, and manuals." In addition, all placards required in the LBA-approved Airplane Flight Manual must be installed in the appropriate location. NOTE 3. Information essential for proper maintenance of the airplane is contained in the Messerschmitt-Bolkow- Blohm GmbH., Model BO-209 Maintenance Manual included in MBB document Ref. LF 37E-7/71. NOTE 4. The airplane manufacturer is: Waggon- und Maschienenbau A.G. Donauworth, Laupheim Federal Republic of Germany (A division of Messerschmitt-Bolkow-Blohm). NOTE 5. Installation of a Tost tow coupling (ring type), LBA approval No. 60.230.4 may be approved when installed in accordance with MBB Drwg. 209-85003 (for glider towing) or MBB Drwgs. 209-85003 and 209-8700 (for banner towing). NOTE 6. For issuance of an airworthiness certificate in accordance with 14 CFR Part 21.182(c), the Luftfahrt Bundesamt of Germany must certify that the airplane conforms to the type design and is in a condition for safe operation. In that regard, the Luftfahrt Bundesamt of Germany will certify that the airplane complies with all applicable mandatory continuing airworthiness information (MCAI) it has issued. For issuance of an airworthiness certificate in accordance with 14 CFR Part 21.182(d) the certificating inspector, or other authorized person, must find, among other things, that the product is in a condition for safe operation. In order to make that finding, the certificating inspector or other authorized person should contact ACE -112, Federal Aviation Administration, Small Airplane Directorate, prior to issuance to determine whether showing airplane compliance with certain MCAI is necessary to support a finding that the airplane is in a condition for safe operation. 6 A27EU NOTE 7. Some of these transfers were not notified to the FAA and so in some instances the actual type certificates were not reissued. NOTE 8. The five models listed on this FAA type certificate data sheet are “variants” of the EASA model Bölkow BO 209 MONSUN as listed on TCDS EASA.A.357 (see A.IV. Flight Manual BO 209 MONSUN) and are covered as the same type design as this EASA model. The EASA TCDS is based on LBA TCDS No. 680/SA (at Issue 9, dated 12 April 2005). The model Bölkow BO 209 S, as defined in Section B of EASA.A.357, was not validated by the FAA and is not covered by this FAA TCDS. .....END.....