TCDS A-813

Page No. 1 2 3 4 5 Rev. No. 4 4 4 4 4 FEDERAL AVIATION AGENCY A-813 Revision 4 PIAGGIO P.136-L P.136-L1 P.136-L2 November 8, 1961 AIRCRAFT SPECIFICATION NO. A-813 Type Certificate Holder Piaggio & C. Genoa, Liguria, Italy I - Model Piaggio P.136-L, 5 PCAmM (Utility Category) Engines 2 Lycoming GO-435-C2B Fuel Minimum grade 80/87 or 91/98 (with carburetor setting 10-3391-1) Engine limits Maximum continuous 3000 rpm (240 bhp) Maximum takeoff 3400 rpm (260 bhp) Economy cruise 2600 rpm (160 bhp) Propellers Type: P.1033/G3-S - 3-bladed (metal) Pitch: Variable (constant speed control) Diameter: 82-11/16 in. (m.2.10) Airspeed limits Never exceed speed 249 mph (216 knots) True Ind. Max. structural cruising speed 165 mph (144 knots) True Ind. Maneuvering speed 163 mph (142 knots) True Ind. Max. gear & flap lowering speed 126 mph (109 knots) True Ind. Max. speed for 1/2 flap 150 mph (130 knots) True Ind. Min. control speed - the min. 90 mph ( 78 knots) True Ind. speed at which the airplane is controllable in flight, with sudden failure of one engine, with takeoff power on the other engine. C.G. range Forward: (+164) (m. 4.15) Rear: (+176) (m. 4.46) Maximum weight 5950 lbs. (2700 Kg.) No. seats 2 (+75) (m. 1.90) 3 (+110) (m. 2.80) Maximum baggage See balance charts issued with each individual aircraft. Fuel capacity 190 U.S. gal. (720 liters) (Two tanks 95 U.S. gal. each) (+173) (m. 4.40) Oil capacity Capacity of the sump 12 quarts each motor (+201) (m. 5.12) A-813 2 I - Model Piaggio P.136-L (cont'd) Control surface movements Elevator Up 27° + 1° Down 17° + 1° Elevator trim tab Up 14° + 0.30' Down 18° + 0.30' Rudder Right 25° + 1° Left 25° + 1° Rudder trim tab Right 16° + 0.30' Left 16° + 0.30' Aileron Up 24° + 1° Down 20° + 1° Flaps Down 45° + 1° Stabilizer Fixed Serial Nos. eligible The Registro Aeronautico Italiano (RAI) Certificate of Airworthiness for Export issued as noted under "Certification basis" must be submitted for each individual aircraft for which application for certification is made. Required equipment 1. Piaggio P.136-L Airplane Flight Manual. II - Model Piaggio P.136-L1, 5 PCAmM (Utility Category) Engines 2 Lycoming GO-480-B, GO-480-B1B or GO-480-B1D Fuel Minimum grade 80/87 Engine limits Maximum continuous 3000 rpm (260 bhp) Maximum takeoff 3400 rpm (270 bhp) Economy cruise 2600 rpm (165 bhp) Propellers Type: Hartzell HC-83x20-2CL/L8433 Pitch: Variable (constant speed control) and feathering Diameter:84 in. (No cutoff permitted for repairs) Placard required: "Avoid continuous operation on ground or on water between 1300 and 1650 rpm and between 2100 and 2500 rpm." Airspeed limits Never exceed speed 222 mph (194 knots) True Ind. Max. structural cruising speed 164 mph (143 knots) True Ind. Maneuvering speed 157 mph (137 knots) True Ind. Max. gear & flap lowering speed 126 mph (109 knots) True Ind. Max. speed for 1/2 flap 150 mph (130 knots) True Ind. Min. control speed - the min. 90 mph ( 78 knots) True Ind. speed at which the airplane is controllable in flight, with sudden failure of one engine, with takeoff power on the other engine. C.G. range Forward: (+164) (m. 4.15) Rear: (+176) (m. 4.46) Maximum weight 6000 lbs. (2720 Kg.) No. seats 2 (+75) (m. 1.90) 3 (+114) (m. 2.90) Maximum baggage See balance charts issued with each individual aircraft. Fuel capacity 190 U.S. gal. (720 liters) (Two tanks 95 U.S. gal. each) (+173) (m. 4.40) Oil capacity Capacity of the sump 12 quarts each motor (+201) (m. 5.12) 3 A-813 II - Model Piaggio P.136-L1 (cont'd) Control surface movements Elevator Up 27° + 1° Down 17° + 1° Elevator trim tab Up 14° + 0.30' Down 18° + 0.30' Rudder Right 25° + 1° Left 25° + 1° Rudder trim tab Right 16° + 0.30' Left 16° + 0.30' Aileron Up 24° + 1° Down 20° + 1° Flaps Down 45° + 1° Stabilizer Fixed Serial Nos. eligible The Registro Aeronautico Italiano (RAI) Certificate of Airworthiness for Export issued as noted under "Certification basis" must be submitted for each individual aircraft for which application for certification is made. Required equipment 1. Piaggio P.136-L1 Airplane Flight Manual. III - Model Piaggio P.136-L2, 5 PCAmM (Normal Category) Approved March 7, 1957. (Same as Model P.136-L1 except for increased gross weight, engine installation, addition of dorsal fin, redesigned oil system since engine has dry sump instead of wet sump). Engines 2 Lycoming GSO-A1A6 Fuel Minimum grade 100/130 Engine limits (Straight line manifold pressure variation with altitudes shown) HP RPM MP ALT Takeoff 340 3400 48.0 S.L. Takeoff 340 3400 44.5 8000 Maximum continuous 320 3200 45.0 S.L. Maximum continuous 320 3200 43.0 7500 Propellers Type: Hartzell HC-83x20-2CL/L9333C - 3 bladed (metal) Pitch: Variable (constant speed control and feathering) Diameter: Max. 88 in., Min. allowable for repairs 87 in. No further reduction permitted. Airspeed limits Never exceed speed 212 mph (184 knots) True Ind Max. structural cruising speed 167 mph (145 knots) True Ind Maneuvering speed 154 mph (134 knots) True Ind Max. flap lowering speed 129 mph (112 knots) True Ind Max. gear extension and extended speed 161 mph (140 knots) True Ind Max. speed for 1/2 flap 150 mph (130 knots) True Ind Min. control speed - the min. 90 mph ( 78 knots) True Ind speed at which the airplane is controllable in flight, with sudden failure of one engine, with takeoff power on the other engine. C.G. range Forward: (+164) (m. 4.15) Rear: (+176) (m. 4.46) Maximum weight Landplane 6614 lbs. Seaplane 6393 lbs. No. seats 2 (+75) (m. 1.90) 3 (+114) (m. 2.90) Maximum baggage See balance charts issued with each individual aircraft. A-813 4 III - Model Piaggio P.136-L2 (cont'd). Fuel capacity 190 U.S. gal. (720 liters) (Two tanks 95 U.S. gal. each) (+173) (m. 4.40) Oil capacity 8 gal. total (4 gal. each tank) (+189) (m.4.8) Control surface movements Elevator Up 27° + 1° Down 18° + 1° Elevator trim tab Up 14° + 1° Down 18° + 1° Rudder Right 30° + 1° Left 30° + 1° Rudder trim tab Right 20° + 1° Left 20° + 1° Aileron Up 24° + 1° Down 19° + 1° Flaps Down 45° + 1° Stabilizer Fixed Serial Nos. eligible The Registro Aeronautico Italiano (RAI) Certificate of Airworthiness for Export issued as noted under "Certification basis" must be submitted for each individual aircraft for which application for certification is made. Required equipment 1. Piaggio P.136-L2 Airplane Flight Manual. Specifications Pertinent to All Models Datum Nose of aircraft Leveling means Datum pads on frame No. 20 and datum pegs at the baggage door frame. Certification basis CAR 10. Type Certificate No. 813 issued August 15, 1955. Each aircraft and any replacement parts manufactured in Italy must be designated as "import" and clearly labeled as such in accordance with CAR 10.30. A. U.S. Airworthiness Certificate may be issued on the basis of a Certificate of Airworthiness for Export signed by a representative of the Registro Aeronautico Italiano (RAI) containing the following statement: (Models P.136-L and P.136-L1) "The airplane covered by this certificate has been examined and found to comply with U.S. Civil Air Regulation - Part 3, published November 1, 1949 and conforms to TC 813." or (Model P.136.L2) "The airplane covered by this certificate has been examined and found to comply with U.S. Civil Air Regulation - Part 3, dated November 1, 1949, including Amendments 3-1 through 3-12, and conforms to TC 813." NOTE 1. Current weight and balance report including list of equipment included in certificated empty weight, and loading instructions when necessary, must be in each aircraft at the time of original certification and at all times thereafter (except in the case of air carrier operators having an approved weight control system). NOTE 2. The following placards must be displayed in front and in clear view of pilot: A. For Model P.136-L: (1) "This airplane must be operated as an utility category airplane in compliance with the operating limitations specified in the Piaggio P.136-L Airplane Flight Manual." (2) "Utility Category (5950 lbs.) Acrobatic maneuvers including spins not approved." B. For Model P.136-L1: (1) "This airplane must be operated as an utility category airplane in compliance with the operating limitations specified in the Piaggio P.136-L1 Airplane Flight Manual." (2) "Utility Category (6000 lbs.) Acrobatic maneuvers including spins not approved." C. For Model P.136-L2: (1) "This airplane must be operated as a normal category airplane in compliance with the operating limitations specified in the Piaggio P.136-L2 Airplane Flight Manual." (2) "Normal Category (6614 lbs.) Acrobatic maneuvers including spins not approved." 5 A-813 NOTE 3. These aircraft must be serviced and maintained in conformance with instructions contained in the publication listed below: A. Model P.136-L (1) Piaggio P.136-L Maintenance and Repair Manual. (2) Lycoming GO-435-C2B Operation, Maintenance and Overhaul Manual. (3) Piaggio three-bladed Operation, Maintenance and Overhaul Manual. B. Model P.136-L1 (1) Piaggio P.136-L1 Maintenance and Repair Manual. (2) Lycoming GO-480-B Operation, Maintenance and Overhaul Manual. (3) Hartzell Propeller Operation, Maintenance and Overhaul Manual. C. Model P.136-L2 (1) Piaggio P.136-L2 Maintenance and Repair Manual. (2) Lycoming GO-480-A1A6 Operation, Maintenance and Overhaul Manual. (3) Hartzell Propeller Operation, Maintenance and Overhaul Manual. .....END.....