TCDS A12IN

Page No. 1 2 3 4 Rev. No. 2 1 2 1 FEDERAL AVIATION AGENCY A12IN Revision 2 SUD AVIATION GARDAN GY.80-150 GY.80-160 GY.80-180 March 1, 2012 TYPE CERTIFICATE DATA SHEET NO. A12IN This data sheet which is a part of type certificate No. A12I N prescribes conditions and limita tions under which the product for which the type certificate was issued meets the airworthiness requirements of the Civil Air Regulations. Type Certificate Holder Sud-Aviation Paris, France Type Certificate Ownership Record (1) This TC was considered not valid by the state of design on June 27, 2007, and has been replaced by European Aviation Safety Agency (EASA) Specific Airworthiness Specification (SAS) number EASA.SAS.A.075, issued June 27, 2007. Only standard airworthiness certificates issued prior to March 1, 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) Replacement parts may not be available in the future. I - Model Gardan GY.80-150, 4 PCLM (Normal Category), Approved May 3, 1963 Engine Lycoming O320-A3C Fuel *80/87 minimum grade aviation gasoline Engine limits *For all opera tions, 2700 r.p.m. (150 b.h.p.) Propeller and Hartzell HC-82XL-1/7636D-4 propeller limits Pitch setting at 30 in. sta.: Low 12°, High 24.2° Diameter: Maximum 72 in., Minimum 70 in. No further reduction permitted. or Sensenich M74 DM-61 Static r.p.m. at maximum permissible throttle setting: Not over 2300, not under 2150. No additional tolerance permitted. Diameter: Maximum 74 in. Minimum 72 in. (no further reduction permitted) Airspeed limits (CAS) *Never exceed 186 m.p.h. (162 knots) *Maximum structural cruising 145 m.p.h. (127 knots) Maneuvering 134 m.p.h. (116 knots) Flaps and landing gear extended 106 m.p.h. ( 92 knots) C.G. range (+8.2) to (+17.5) at 2250 lbs. (landing gear extended) (+7.4) to (+17.5) at 1841 lbs. or less Straight line variation between points given Moment change due to retraction of landing gear + 1237 in.-lbs. Empty weight C.G. range None Maximum weight 2250 lbs. No. of seats 4 (2 at +13) (2 at +41.7) Maximum baggage 88 lbs (+61) A12IN 2 Fuel capacity 42 gal. (two 21 gal. tanks in wings) (+4.7) and 10.5 gal. in fuselage at rear place (+38) Oil capacity 6.6 qts. (in the engine) (4.4 qts. usable) II - Model Gardan GY.80-160, 4 PCLM (Normal Category), Approved May 3, 1963 Engine Lycoming O-320-B3C Fuel *91/96 maximum grade aviation gasoline Engine limits *For all opera tions, 2700 r.p.m. (160 b.h.p.) Propeller and Hartzell HC-82XL-1/7636D-4 propeller limits Pitch setting at 30 in. sta.: Low 12°, High 24.2° Diameter: Maximum 72 in., Minimum 70 in. (No further reduction permitted.) or Sensenich M74 DM-61 Static r.p.m. at maximum permissible throttle setting: Not over 2400, not under 2250. No additional tolerance permitted. Diameter: Maximum 74 in. Minimum 72 in. (no further reduction permitted) or Sensenich M74 DM-63 Static r.p.m. at maximum permissible throttle setting: Not over 2250, not under 2100 Diameter: Maximum 74 in. Minimum 72 in. (no further reduction permitted) Airspeed limits (CAS) *Never exceed 186 m.p.h. (162 knots) *Maximum structural cruising 145 m.p.h. (127 knots) Maneuvering 134 m.p.h. (116 knots) Flaps and landing gear extended 106 m.p.h. ( 92 knots) C.G. range (+8.2) to (+17.5) at 2425 lb s. with Hartzell HC-82XL-1 propeller; at (landing gear extended) 2315 lbs. with Se nsenich M74 DM-61 propeller; at 2250 lbs. with Sensenich M 74 DM-63 propeller (+7.4) to (+17.5) at 1841 lbs. or less Straight line variation between points given Moment change due to retraction of landing gear +1237 in. lbs. Empty weight C.G. range None Maximum weight 2425 lbs. with Hartzell HC-82 XL-1 2315 lbs. with Sensenich M74 DM-61 2250 lbs. with Sensenich M74 DM-63 No. of seats 4 (2 at +13) (2 at +41.7) Maximum baggage 88 lbs (+61) Fuel capacity 42 gal. (two 21 gal. tanks in wings) (+4.7) and 10.5 gal. in fuselage at rear place (+38) Oil capacity 6.6 qts. (in the engine) (4.4 qts. usable) III - Model Gardan GY.80-180, 4 PCLM (Normal Category), Approved September 9, 1965 Engine Lycoming O360 A.2.A. Fuel *91/96 minimum grade aviation gasoline Engine limits *For all opera tions, 2700 r.p.m. (180 b.h.p.) Propeller and Sensenich M76 EMM-62 propeller limits Static r.p.m. at maximum permissible throttle setting: Not over 2400, not under 2250. No additional tolerance permitted. Diameter: 76 in. (no further reduction permitted) 3 A12IN Airspeed limits (CAS) *Never exceed 186 m.p.h. (162 knots) *Maximum structural cruising 145 m.p.h. (127 knots) Maneuvering 134 m.p.h. (116 knots) Flaps and landing gear extended 106 m.p.h. ( 92 knots) C.G. range (+8.2) to (+16.5) at 2425 lbs. (landing gear extended) (+7.4) to (+16.5) at 1841 lbs. or less Straight line variation between points given. Moment change due to retraction of landing gear + 1237 in. lbs. Empty weight C.G. range None Maximum weight 2425 lbs. No. of seats 4 (2 at 13) (2 at 41.7) Maximum baggage 88 lbs (+61) Fuel capacity 42 gal. (two 21 gal. tanks in wings) (+4.7) and 10.5 gal. in fuselage at rear place (+38) Oil capacity 6.6 qts. (in the engine) (4.4 qts. usable) DATA PERTINENT TO ALL MODELS Datum Wing leading edge outboard of the wingtank Leveling means Frame under door Control surface movements Tolerances Wing flaps 19° + 0° -2° Aileron Up 20° Down 20° + 0° -1° Elevator Up 13° Down 9° + 1° -1° Elevator anti-servo tab Up 13° Down 9° + 1° -1° Elevator trim tab Up 3°20' Down 6°40' +30' -30' Rudder Right 28° Left 28° + 2° -1° Serial Nos. eligible Only those ai rcraft serials holding a standard airworthiness certificate issued prior to March 1, 2012 are eligible. The S.G.A.C. Certificate of Airworthin ess for Export endorsed as noted below under "Certification basis" must be submitte d for each individual airplane for which application for Certification is made. Certification basis CAR 10 da ted March 1955, French AIR 2052 revised to May 3, 1962 certified by S.G.A.C. as equivalent to U.S. CAR 3 dated May 15, 1956 and amendments 3-1 through 3-5. Type Certificate No. A12IN issued May 3, 1963. Date of Application for Type Certificate March 10, 1961. Import requirements None elig ible after March 1, 2012. Previous to this date: A U.S. Airworthiness Certificate may be issued on the basis of a French Certificat de Navagabilite pour Exportation signed by a representative of the Secretariat General de l'Aviation Ci vile (S.G.A.C.) containing the following statement: "The airplane covered by this certificate has been found to comply with French AIR 2052 effective May 3, 1962 and conforms to Type Certificate No. A12IN." Equipment The basic required equipm ent 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: Stall warning indicator Safe Flight 164. A12IN 4 NOTE 1. Current weight and balance report including list of e quipment included in certificated empty weight, and loading instructions when necessary, must be provided for each aircraft at the time of original certification. NOTE 2. The following placards must be displayed in locations as indicated. A. Applicable to Models GY.80-150, GY.80-160, and GY.80-180 (1) In full view of the pilot: "This airplane must be operated as a normal category airplane in compliance with the operating limitations as stated in the form of placards, markings, and manuals. No acrobatic maneuvers, including spins, approved." Maximum maneuve ring speed 134 m.p.h. Maximum design weight: GY.80-150 2250 lbs. GY.80-160 2250 lbs. or 2315 lbs. or 2425 lbs. GY.80-180 2425 lbs. Maximum flight maneuvering load factor. Flaps up + 3.8; -1.9 Maximum gear and flaps ex tension speed 106 m.p.h. - CAS Before take-off Before Landing 1. Set tabs 1. Fuel selector on fullest tank 2. Electric pump on 2. Mixture rich 3. Mixture rich 3. Gear and flaps down 4. Propeller full in (for Models GY. 80-150, 4. Propeller full in (for Models GY.80-160 with Hartzell HC-82XL-1 propellers Cy.80-150, GY.80-160 with installed) Hartzell HC-82XL-1 propellers ` i n s t a l l e d ) 5. Check fuel selector on fullest tanks 5. Electric pump on (2) On fuel selector valve plate: fuselage tank: 10.5 gal., LEFT + RIGHT wing tank: 42 gal. (3) On the baggage compartm ent "Maximum baggage 88 lbs." "For additional loading instruc tions see weight an balance data." (4) On the fuel tank filler cap: "Tank capacity 21 U.S. gal. (each wing tank) and 10.5 U.S. gal. (Fuselage tank) Grade 80/87 (CY.80-150) Grade 91/96 (GY.80-160 and GY.80-180) (5) In addition to the above placards, the pres cribed operating limitations indicated by * under Section I, II and III above, must be displayed by permanent markings. .....END.....