TCDS A11EA

Page No. 1 2 3 4 5 6 7 8 Rev. No. 13 5 6 5 6 10 8 10 DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION A11EA Revision 13 True Flight Holdings LLC (American General) AA-1 AA-1A AA-1B AA-1C December 12, 2013 TYPE CERTIFICATE DATA SHEET NO. A11EA This data sheet, which is a part of Type Certificate No. A11EA, 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 True Flight Holdings LLC 2300 Madison Highway Valdosta, GA 31601 Type Certificate Holder Record: American Aviation Corporation transferred TC A11EA to Grumman American Aviation Corporation on February 27, 1973 Grumman American Aviation Corporation transferred TC A11EA to Gulfstream American Corporation on September 1, 1978 Gulfstream American Corporation transferred TC A11EA to Gulfstream Aerospace Corporation on November 15, 1982 Gulfstream Aerospace Corporation transferred TC A11EA to American General Aircraft Corporation on October 29, 1992 American General Aircraft Corporation transferred TC A11EA to American General Aircraft Holding Company, Inc. on August 23, 1993 American General Aircraft Holding Corporation, Inc. transferred TC A11EA to Tiger Aircraft LLC on March 22, 2000 Tiger Aircraft LLC transferred TC A11EA to True Flight Holdings LLC on August 31, 2007 I. - Model AA-1, Yankee, 2 PCLM, Utility Category, Approved August 29, 1967, Normal Category Approved July 16, 1968. Engine Lycoming O-235-C2C (Carburetor Setting 10-4953 or 10-3103-1) Fuel 80/87 minimum grade aviation gasoline Engine limits For all operations 2600 r.p.m. (108 h.p.) Propeller and propeller limits 1. McCauley Model 1A105/SCM-7157 fixed pitch propeller. Static r.p.m. at maximum permissible throttle setting; not over 2300; not under 2150. Diameters: not over 71 inches, not under 69.5 inches. A11EA Page 2 2. McCauley Model 1A105/SCM-7153 and 1A105/SCM-7154 fixed pitch propellers. Static r.p.m. at maximum permissible throttle setting; not over 2400; not under 2250. Diameter: not over 71 inches, not under 69.5 inches. 3. McCauley Model 1A106/NCM-7157 fixed pitch propellers. Static r.p.m. at maximum permissible throttle setting; not over 2400; not under 2300. Diameter: not over 71 inches, not under 69.5 inches. 4. McCauley Model 1A106/NCM-7153 hub and fixed pitch propellers. Static r.p.m. at maximum permissible throttle setting; not over 2475; not under 2375. Diameter: not over 71 inches, not under 69.5 inches. Airspeed limits (CAS) Vne Never exceed 195 m.p.h. (169 knots) Vno Maximum structural cruising 144 m.p.h. (125 knots) Va Maneuvering (Utility Category) 132 m.p.h. (115 knots) Va Maneuvering (Normal Category) 125 m.p.h. (109 knots) Vfe Flaps extended 100 m.p.h. ( 87 knots) Canopy half open 130 m.p.h. (113 knots) Center of gravity (C.G) range (+78.5) to (+81.0) at 1500 lb. (+77.5) to (+81.0) at 1430 lb. (+75.0) to (+81.0) at 1245 lb. Straight line variation between points given. Gross Weight lb. 1500 1430 1245 Fuselage Station inches 75.0 77.5 78.5 81.0 Normal Utility Empty weight C.G. range None Maximum weight 1430 lb. (Utility Category) 1500 lb. (Normal Category) Number of seats 2 at (+92.5) (For optional child's seat refer to Equipment List.) Maximum baggage 100 lb. at (+120) Fuel capacity 24 gal. (2 wing tanks) at (+84.5) (See Note 1 for unusable fuel) Oil capacity 6 qt. at (+39) (2 qt. minimum) Control surface movements Elevator 25° ± 2° up 15° ± 2° down Rudder 25° ± 2° left 25° ± 2° right Ailerons 25° ± 2° up 20° ± 2° down Flaps 30° ± 2° down Elevator tab trim 21.5° ± 2° up 11° ± 2° down Serial numbers eligible AA1-0001 and up (Normal and Utility Category) Page 3 A11EA II - Model AA-1A, Trainer, 2 PCLM, Utility Category, Approved January 14, 1971, Normal Category Approved January 14, 1971. Engine Lycoming O-235-C2C (Carburetor Setting 10-4953 or 10-3103-1) Fuel 80/87 minimum grade aviation gasoline Engine limits For all operations 2600 r.p.m. (108 h.p.) Propeller and propeller limits 1. McCauley Model 1A105/SCM-7157 fixed pitch propeller. Static r.p.m. at maximum permissible throttle setting; not over 2300; not under 215C. Diameter: not over 71 inches, not under 69.5 inches. 2. McCauley Model 1A105/SCM-7153 and 1A105/SCM-7154 fixed pitch propellers. Static r.p.m. at maximum permissible throttle setting; not over 2400; not under 2250. Diameter: not over 71 inches, not under 69.5 inches. 3. McCauley Model 1A106/NCM-7157 fixed pitch propellers. Static r.p.m. at maximum permissible throttle setting; not over 2400; not under 2300. Diameter: not over 71 inches, not under 69.5 inches. 4. McCauley Model 1A106/NCM-7153 hub and fixed pitch propellers. Static r.p.m. at maximum permissible throttle setting; not over 2475; not under 2375. Diameter: not over 71 inches, not under 69.5 inches. Airspeed limits (CAS) Vne Never exceed 195 m.p.h. (169 knots) Vno Maximum structural cruising 144 m.p.h. (125 knots) Va Maneuvering (Utility Category) 127 m.p.h. (110 knots) Va Maneuvering (Normal Category) 120 m.p.h. (104 knots) Vfe Flaps extended 115 m.p.h. (100 knots) Canopy half open 130 m.p.h. (113 knots) Center of gravity (C.G) range (+78.5) to (+80.0) at 1500 lb. (+77.5) to (+80.0) at 1430 lb. (+75.0) to (+80.0) at 1245 lb. Straight line variation between points given. Gross Weight lb. 1500 1430 1245 Fuselage Station inches 75.0 77.5 78.5 80.0 Normal Utility Empty weight C.G. range None Maximum weight 1430 lb. (Utility Category) 1500 lb. (Normal Category) Number of seats 2 at (+92.5) (For optional child's seat refer to Equipment List.) Maximum baggage 100 lb. at (+120) Fuel capacity 24 gal. (2 wing tanks) at (+84.5) (See Note 1 for unusable fuel) A11EA Page 4 Oil capacity 6 qt. at (+39) (2 qt. minimum) Control surface movements Elevator 25° ± 2° up 15° ± 2° down Rudder 25° ± 2° left 25° ± 2° right Ailerons 25° ± 2° up 20° ± 2° down Flaps 30° ± 2° down Elevator tab trim 14.5° ± 2° up 18° ± 2° down Serial numbers eligible AA1A-0001 and up (Normal and Utility Category) III - Model AA-1B, Trainer/TR-2, 2 PCLM, Utility Category, Approved June 30, 1972 Engine Lycoming O-235-C2C (Carburetor Setting 10-4953 or 10-3103-1) Fuel 80/87 minimum grade aviation gasoline Engine limits For all operations 2600 r.p.m. (108 h.p.) Propeller and propeller limits 1. McCauley Model 1A105 with 1A105/SCM hub and 7157 blades. Static r.p.m. at maximum permissible throttle setting; not over 2300; not under 2150. Diameter: not over 71 inches, not under 69.5 inches. 2. McCauley Model 1A105/SCM-7153 and 1A105/SCM-7154 fixed pitch propellers. Static r.p.m. at maximum permissible throttle setting; not over 2400; not under 2250. Diameter: not over 71 inches, not under 69.5 inches. 3. McCauley Model 1A106/NCM-7153 fixed pitch propellers. Static r.p.m. at maximum permissible throttle setting; not over 2400; not under 2300. Diameter: not over 71 inches, not under 69.5 inches. 4. McCauley Model 1A106/NCM-7157 fixed pitch propellers. Static r.p.m. at maximum permissible throttle setting; not over 2475; not under 2375. Diameter: not over 71 inches, not under 69.5 inches. Airspeed limits (CAS) Vne Never exceed 195 m.p.h. (169 knots) Vno Maximum structural cruising 144 m.p.h. (125 knots) Va Maneuvering 135 m.p.h. (117 knots) Vfe Flaps extended 115 m.p.h. (100 knots) Canopy half open 130 m.p.h. (113 knots) Center of gravity (C.G) range (+78.25) to (+80.0) at 1560 lb. (+75.0) to (+80.0) at 1300 lb. Gross Weight lb. 1560 1300 Fuselage Station inches 75.0 78.25 80.0 Empty weight C.G. range None Maximum weight 1560 lb. Page 5 A11EA Number of seats 2 at (+92.5) (For optional child's seat refer to Equipment List.) Maximum baggage 100 lb. at (+120) Fuel capacity 24 gal. (2 wing tanks) at (+84.5) (See Note 1 for unusable fuel) Oil capacity 6 qt. at (+39) (2 qt. minimum) Control surface movements Elevator 25° ± 2° up 15° ± 2° down Rudder 25° ± 2° left 25° ± 2° right Ailerons 25° ± 2° up 20° ± 2° down Flaps 30° ± 2° down Elevator tab trim 14.5° ± 2° up 18° ± 2° down Serial numbers eligible AA1B-0001 and up (Utility Category) IV - Model AA-1C, T-Cat/Lynx, 2 PCLM, Utility Category, Approved December 21, 1976. (Same as AA-1B except for engine, propeller, engine mount/baffles, and AA-5 elevator). Engine Lycoming O-235-L2C (Carburetor Setting 10-4953 or 10-3103-1) Fuel 100/130 minimum grade aviation gasoline Engine limits For all operations 2700 r.p.m. (115 h.p.) Propeller and propeller limits 1. Sensenich Model 72CK-0-56 fixed pitch propeller. Static r.p.m. at maximum permissible throttle setting; not over 2275; not under 2125. No additional tolerance permitted. Diameter: not over 72 inches, not under 70.5 inches. 2. Sensenich Model 72CK-0-52 fixed pitch propellers. Static r.p.m. at maximum permissible throttle setting; not over 2475; not under 2325. No additional tolerance permitted. Diameter: not over 72 inches, not under 70.5 inches. Airspeed limits (CAS) Vne Never exceed 195 m.p.h. (169 knots) Vno Maximum structural cruising 144 m.p.h. (125 knots) Va Maneuvering 135 m.p.h. (117 knots) Vfe Flaps extended 115 m.p.h. (100 knots) Canopy half open 130 m.p.h. (113 knots) Center of gravity (C.G) range (+78.00) to (+81.0) at 1600 lb. (+75.5) to (+81.0) at 1385 lb. Gross Weight lb. 1600 1385 Fuselage Station inches 75.50 78.00 81.00 Utility Empty weight C.G. range None Maximum weight 1600 lb. A11EA Page 6 Number of seats 2 at (+92.5) (For optional child's seat refer to Equipment List.) Maximum baggage 100 lb. at (+120) Fuel capacity 24 gal. (2 wing tanks) at (+84.5) (See Note 1 for unusable fuel) Oil capacity 6 qt. at (+39) (2 qt. minimum) Control surface movements Elevator 12° ± 1° up 28° ± 2° down Rudder 25° ± 2° left 25° ± 2° right Ailerons 25° ± 2° up 20° ± 2° down Flaps 30° ± 2° down Elevator tab trim 15° ± 4° up 15° ± 2° down Serial numbers eligible AA1B-0601 and AA1C-0001 and up (Utility Category) DATA PERTINENT TO ALL MODELS: Datum 50.0 inches forward of front face of firewall (wing chord 48 inches for Model AA-1 and 49.32 inches for Models AA-1A, AA-1B, and AA-1C). Leveling means Top of fuselage canopy slide rail. Certification basis FAR 23 effective February 1, 1965, and amendments 23-1 and 23-2; and FAR 36 amended through 36-4 for the Model AA-1C. Type Certificate No. A11EA issued August 29, 1967. Data of Application for Type Certificate October 22, 1965. Production basis None. Prior to original certification of each aircraft manufactured subsequent to May 12, 2000, an FAA representative must perform a detailed inspection for workmanship, materials and conformity with the approved technical data and a check of the flight characteristics. Equipment The basic required equipment prescribed in the applicable airworthiness regulations (see Certification Basis) must be installed in the airplane for certification. In addition, equipment for the particular operation must be installed. NOTE 1. Current weight and balance report including a list of equipment included in the certificated empty weight, a nd loading instructions when necessary must be provided for each aircraft at the time of original certification. The certificated empty weight and corresponding center of gravity location must include 12 lb. (2 gal.) at (+84.5) of unusable fuel. NOTE 2. The following placards must be installed in full view of the pilot: (a) Models AA-1 and AA-1A: "THIS AIRPLANE MUST BE OPERATED AS A NORMAL OR UTILITY CATEGORY AIRPLANE IN COMPLIANCE WITH THE OPERATING LIMITATIONS STATED IN THE FORM OF PLACARDS, MARKINGS, AND MANUALS." NORMAL CATEGORY AA-1 AA-1A Maximum Design Weight 1500 lb. 1500 lb. Design Maneuvering Speed, Va 125 mph CAS 120 mph CAS Flight Load Factors: Flaps Up +3.8, -1.52 +3.8, -1.52 Flaps Down +2.0 +3.5 NO ACROBATIC MANEUVERS INCLUDING SPINS APPROVED (AA-1 and AA-1A) Page 7 A11EA UTILITY CATEGORY AA-1 AA-1A Maximum Design Weight 1430 lb. 1430 lb. Design Maneuvering Speed, Va 130 mph CAS 127 mph CAS Flight Load Factors: Flaps Up +4.4, -1.76 +4.4, -1.76 Flaps Down +2.0 +3.5 ACROBATIC MANEUVERS ARE LIMITED TO THE FOLLOWING: MANEUVER ENTRY SPEED (MPH, CAS) AA-1 AA-1A Chandelles 132 127 Lazy Eights 132 127 Steep Turns 132 127 Stalls (Except Whip Stalls) Slow Deceleration Slow Deceleration Models AA-1B and AA-1C: "THIS AIRPLANE MUST BE OPERATED AS A UTILITY CATEGORY AIRPLANE IN COMPLIANCE WITH THE OPERATING LIMITATIONS STATED IN THE FORM OF PLACARDS, MARKINGS, AND MANUALS." AA-1B AA-1C Maximum Design Weight 1560 Lb. 1600 Lb. Design Maneuvering Speed, Va 135 Mph Cas 117 Knots Cas Flight Load Factors: Flaps Up +4.4, -1.76 +4.4, -1.76 Flaps Down +3.5 +3.5 ACROBATIC MANEUVERS ARE LIMITED TO THE FOLLOWING: MANEUVER ENTRY SPEED (MPH, CAS) ENTRY SPEED (KNOTS, CAS) AA-1B AA-1C Chandelles 135 117 Lazy Eights 135 117 Steep Turns 135 117 Stalls (Except Whip Stalls) Slow Deceleration Slow Deceleration Maximum Altitude Loss In Stalls 300 Feet (AA-1) 250 Feet (AA-1A) 300 Feet (AA-1B) 200 Feet (AA-1C) Demonstrated Crosswind Velocity 15 Mph (AA-1) 13 mph (AA-1A) 18 mph (AA-1B) 16 knots (AA-1C) KNOWN ICING CONDITIONS TO BE AVOIDED. (Models AA-1, AA-1A, and AA-1B) THIS AIRPLANE NOT APPROVED FOR FLIGHT IN ICING CONDITIONS. (Model AA-1C) A11EA Page 8 All Models: THIS AIRPLANE IS CERTIFICATED FOR THE FOLLOWING OPERATIONS AS OF DATE OF ORIGINAL AIRWORTHINESS CERTIFICATE: IFR, VFR, DAY, NIGHT. (When properly equipped per FAR 91) REFER TO WEIGHT AND BALANCE DATA FOR LOADING INSTRUCTIONS. READ FUEL GAGES IN LEVEL FLIGHT ONLY. FOR NORMAL OPERATION, MAINTAIN FUEL BALANCE. DEMONSTRATED FUEL UNBALANCE 7 GAL. (b) On left side of cabin: "130 MPH MAX WITH CANOPY OPEN TO HERE. NO FLIGHT WITH CANOPY OPEN BEYOND THIS POINT." Placard Part No. 5803007-22 or equivalent. (Models AA-1, AA-1A, AA-1B) "113 KNOTS MAX WITH CANOPY OPEN TO HERE. NO FLIGHT WITH CANOPY OPEN BEYOND THIS POINT." Placard Part No. 5803007-51 or equivalent. (Model AA-1C). (c) In baggage compartment (All Models): "BAGGAGE CAPACITY 100 LBS. MAX." Placard Part No. 803007-40 or equivalent. (d) On instrument panel in full view of pilot (All Models): "SPINS PROHIBITED." Placard Part No. 803007-56 or equivalent. (e) On instrument panel near the airspeed indicator stall speed vs. bank angle placard. Placard Part No. 803007-53 (Model AA-1), 803007-54 (Model AA-1A), 803007-55 (Model AA-1B), 803007-67 (Model AA-1C). NOTE 3. Deleted ....END....