TCDS A13EU

Page No. 1 2 3 4 5 6 7 8 9 10 11 12 13 14 15 16 17 18 Rev. No. 16 14 16 16 14 16 16 16 16 16 14 16 11 11 14 11 11 11 DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION A13EU Revision 16 Textron Aviation F150F F152 F150G FA150K F150H FA150L F150J FA150M F150K FA152 F150L FRA150L F150M FRA150M April 1, 2019 WARNING: Use of alcohol-based fuels can cause serious performance degradation and fuel system component damage, and is therefore prohibited on Cessna airplanes. TYPE CERTIFICATE DATA SHEET NO. A13EU This data sheet, which is part of Type Certificate No. A13EU, 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 Textron Aviation Inc. One Cessna Boulevard Wichita, Kansas 67215 Type Certificate Holder Record Cessna Aircraft Company transferred to Textron Aviation Inc. on July 29, 2015 Type Certificate A13EU was transferred from Reims Aviation S.A., 51 Aerodrome de Reims-Prunay, Reims, France, to Cessna Aircraft Company on December 11, 2006. Coincident with this transfer, the Federal Aviation Administration (FAA) has accepted the status of State of Design and State of Manufacture as defined by Annex 8 to the Convention of International Civil Aviation. Prior to December 11, 2006, products identified under Type Certificate A13EU were approved by the FAA in accordance with the Federal Aviation Regulation appropriate to Imported Products (FAR 21.29). Effective December 11, 2006, and after, these products are to be considered domestic products for the purpose of certification, and Federal Aviation Regulations 21.21 becomes appropriate. I. Model F150F, 2 PCLM (Utility Category), Approved February 17, 1966 Engine Continental O-200-A * Fuel 80/87 min. grade aviation gasoline * Engine Limits For all operations, 2750 rpm. (100 hp) Propeller and 1. Sensenich 69CK 24 lb (-32) Propeller Limits Diameter: not over 69 in., not under 67.5 in. Static r.p.m. at maximum permissible throttle setting: Not over 2470, not under 2320 No additional tolerance permitted 2. McCauley 1A101/MCM 21 lb (-32) Diameter: not over 69 in., not under 67.5 in. Static r.p.m. at maximum permissible throttle setting: Not over 2475, not under 2375 No additional tolerance permitted A13EU 2 Rev. 16 I. Model F150F (cont’d) Propeller and 3. McCauley 1A101/DCM 21 lb (-32) Propeller Limits Diameter: not over 69 in., not under 67.5 in. (cont’d) Static r.p.m. at maximum permissible throttle setting : Not over 2600, not under 2500 No additional tolerance permitted Airspeed Limits (CAS) *Never exceed 162 mph (141 knots) *Maximum structural cruising 120 mph (104 knots) *Maneuvering 109 mph (95 knots) *Flaps extended 100 mph (87 knots) C.G. Range (+32.9) to (+37.5) at 1600 lbs. (+31.5) to (+37.5) at 1280 lbs. or less Straight line variation between points given Empty Wt. C.G. Range None Leveling Means Top of tailcone Maximum Weight 1600 lb. No. of Seats 2 at (+39); (For child’s optional jump seat, refer to Equipment List.) Maximum Baggage 120 lb. - Reference weight and balance data Fuel Capacity 26 gal., (22.5 gal. usable, two 13 gal. tanks in wings at +42) See NOTE 1 for system fuel. Oil Capacity 6 qt. (-13.5, unusable 2 qt.). See NOTE 1 for data on system oil. Control Surface Movements Wing Flaps Down 0° - 40° ± 2° Ailerons Up 20° Down 15° Elevator Up 25° Down 15° Elevator Tab Up 10° Down 20° Rudder Right 23° Left 23° (measured parallel to chord) Serial Numbers Eligible F150-0001 thru F150-0067 II. Model F150G, 2 PCLM (Utility Category), Approved September 16, 1966 Model F150H, 2 PCLM (Utility Category), Approved September 5, 1967 Model F150J, 2 PCLM (Utility Category), Approved August 13, 1968 Model F150K, 2 PCLM (Utility Category), Approved August 20, 1969 Engine Rolls Royce Continental O-200-A * Fuel 80/87 min. grade aviation gasoline * Engine Limits For all operations, 2750 rpm. (100 hp) Propeller and 1. McCauley 1A100/MCM 21 lb (-32) Propeller Limits Diameter: not over 69 in., not under 67.5 in. Static rpm. at maximum permissible throttle setting: Not over 2475, not under 2375 No additional tolerance permitted 2. McCauley 1A101/DCM 21 lb (-32) Diameter: not over 69 in., not under 67 in. Not over 2600, not under 2500 Rev. 16 3 A13EU No additional tolerance permitted II. Model F150G, Model F150H, Model F150J, Model F150K (cont’d) Airspeed Limits (CAS) *Never exceed 162 mph (141 knots) *Maximum structural cruising 120 mph (104 knots) *Maneuvering 109 mph (95 knots) *Flaps extended 100 mph (87 knots) C.G. Range (+32.9) to (+37.5) at 1600 lbs. (+31.5) to (+37.5) at 1280 lbs. or less Straight line variation between points given. Empty Wt. C.G. Range None Leveling Means Top surface at tailcone Maximum Weight *1600 lb. No. of Seats 2 at (+39); (For child’s optional jump seat, refer to Equipment List.) Maximum Baggage 120 lb. - Reference weight and balance data Fuel Capacity 26 gal., (22.5 gal. usable two 13 gal. tanks in wings at +42) See NOTE 1 for system fuel and oil. Oil Capacity 6 qt. (-13.5, unusable 2 qt.). See NOTE 1 for data on system fuel and oil. Control Surface Movements Wing Flaps Down 0° - 40° ± 2° Ailerons Up 20° +2°, -0° Down 14° + 2°, - 0° Elevator Up 25° ± 1° Down 15° ± 1° Elevator Tab Up 10° ± 1° Down 20° ± 1° Rudder Right 23° + 0°, -2° Left 23° + 0°, - 2° (measured perpendicularly to hinge line) Serial Numbers Eligible F150G: F150-0068 thru F150-0219 F150H: F150-0220 thru F150-0389 F150J: F150-0390 thru F150-0529 F150K: F15000530 thru F15000658 III. Model FA150K, 2 PCLM (Acrobatic Category), Approved November 5, 1969 Engine Rolls-Royce Continental O-200-A * Fuel 80/87 min. grade aviation gasoline * Engine Limits For all operations, 2750 rpm. (100 hp) Propeller and McCauley 1A101/DCM 21 lb (-32) Propeller Limits Diameter: not over 69 in., not under 67 in. Static rpm. at maximum permissible throttle setting: Not over 2600, not under 2500 No additional tolerance permitted Airspeed Limits (CAS) *Never exceed 193 mph (168 knots) *Maximum structural cruising 140 mph (122 knots) *Maneuvering 118 mph (103 knots) *Flaps extended 100 mph (87 knots) C.G. Range (+32.9) to (+37.5) at 1600 lbs. (+31.5) to (+37.5) at 1280 lbs. or less Straight line variation between points given. A13EU 4 Rev. 16 III. Model FA150K (cont’d) Empty Wt. C.G. Range None Leveling Means Top surface at tailcone Maximum Weight *1600 lb. No. of Seats 2 at (+39); (For child’s optional jump seat, refer to Equipment List.) Maximum Baggage 120 lb. - Reference weight and balance data Fuel Capacity 26 gal., (22.5 gal. usable two 13 gal. tanks in wings at +42) See NOTE 1 for system fuel and oil. Oil Capacity 6 qt. (-13.5, unusable 2 qt.). See NOTE 1 for data on system fuel and oil. Control Surface Movements Wing Flaps Down 0° - 40° ± 2° Ailerons Up 20° +2°, -0° Down 14° + 2°, - 0° Elevator Up 25° ± 1° Down 15° ± 1° Elevator Tab Up 10° ± 1° Down 20° ± 1° Rudder Right 23° + 0°, -2° Left 23° + 0°, - 2° (measured perpendicularly to hinge line) Serial Numbers Eligible FA1500001 through FA1500081 IV. Model F150L, 2PCLM (Utility Category), Approved October 9, 1970 Engine Rolls-Royce Continental O-200-A * Fuel 80/87 min. grade aviation gasoline * Engine Limits For all operations, 2750 r.p.m. (100 hp) Propeller and 1. McCauley 1A101/GCM (1971, 1972, 1973 models) 27.7 lb (-34.5) Propeller Limits Diameter: not over 69 in., not under 67 in. Static r.p.m. at maximum permissible throttle setting: Not over 2600, not under 2500 No additional tolerance permitted 2. McCauley 1A101/HCM (1973, 1974 models) 27.7 lb (-34.5) Diameter: not over 69 in., not under 67 in. Static r.p.m. at maximum permissible throttle setting: Not over 2600, not under 2500 No additional tolerance permitted 3. McCauley 1A101/PCM (1974 models) 27.0 lb (-34.5) Diameter: not over 69 in., not under 67 in. Static r.p.m. at maximum permissible throttle setting: Not over 2600, not under 2500 No additional tolerance permitted (See Note 4 for Data on serial number eligibility) 4. McCauley 1A102/OCM (1971 through 1974 models) 27.0 lb (-34.5) Diameter: not over 69 in., not under 67.5 in. Static r.p.m. at maximum permissible throttle setting: Not over 2560, not under 2460 No additional tolerance permitted Rev. 16 5 A13EU IV. Model F150L (cont’d) Airspeed Limits (CAS) *Never exceed 162 mph (141 knots) *Maximum structural cruising 120 mph (104 knots) *Maneuvering 109 mph (95 knots) *Flaps extended 100 mph (87 knots) C.G. Range (+32.9) to (+37.5) at 1600 lbs. (+31.5) to (+37.5) at 1280 lbs. or less Straight line variation between points given. Empty Wt. C.G. Range None Leveling Means Jig located nut plates and screws at Station +94.63 and Station 132.94 on left side of tailcone. Maximum Weight *1600 lb. No. of Seats 2 at (+39); (For child’s optional jump seat, refer to Equipment List.) Maximum Baggage 120 lb. - Reference weight and balance data Fuel Capacity 26 gal. total, (22.5 gal. usable, two 13 gal. tanks in wings at +42.0) See NOTE 1 for data on unusable fuel. Oil Capacity 6 qt. (-13.5, unusable 2 qt.). See NOTE 1 for data on undrainable oil. Control Surface Movements Wing Flaps Down 0° - 40° ± 2° Ailerons Up 20° +2°, -0° Down 14° + 2°, - 0° Elevator Up 25° ± 1° Down 15° ± 1° Elevator Tab Up 10° ± 1° Down 20° ± 1° Rudder Right 23° + 0°, -2° Left 23° + 0°, - 2° (measured perpendicularly to hinge line) Serial Numbers Eligible F15000659 through F15001143 V. Model FA150L, 2PCLM (Acrobatic Category), Approved October 9, 1970 Engine Rolls-Royce Continental O-200-A * Fuel 80/87 min. grade aviation gasoline * Engine Limits For all operations, 2750 r.p.m. (100 hp) Propeller and 1. McCauley 1A101/GCM (1971, 1972, 1973 models) 27.7 lb (-34.5) Propeller Limits Diameter: not over 69 in., not under 67 in. Static r.p.m. at maximum permissible throttle setting: Not over 2600, not under 2500 No additional tolerance permitted 2. McCauley 1A101/HCM (1971, 1972, 1973 models) 27.7 lb (-34.5) Diameter: not over 69 in., not under 67 in. Static r.p.m. at maximum permissible throttle setting: Not over 2600, not under 2500 No additional tolerance permitted 3. McCauley 1A102/OCM (1971 through 1974 models) 27.0 lb (-34.5) Diameter: not over 69 in., not under 67.5 in. Static r.p.m. at maximum permissible throttle setting: Not over 2560, not under 2460 A13EU 6 Rev. 16 No additional tolerance permitted V. Model FA150L (cont’d) Airspeed Limits (CAS) *Never exceed 193 mph (168 knots) *Maximum structural cruising 140 mph (122 knots) *Maneuvering 118 mph (103 knots) *Flaps extended 100 mph (87 knots) C.G. Range (+32.9) to (+37.5) at 1600 lbs. (+31.5) to (+37.5) at 1280 lbs. or less Empty Wt. C.G. Range None Leveling Means Jig located nut plates and screws at Station +94.63 and Station 132.94 on left side of tailcone. * Maximum Weight 1600 lb. No. of Seats 2 at (+39); (For child’s optional jump seat, refer to Equipment List.) Maximum Baggage 120 lb. - Reference weight and balance data Fuel Capacity 26 gal. total, (22.5 gal. usable, two 13 gal. tanks in wings at +42.0) See NOTE 1 for data on unusable fuel. Oil Capacity 6 qt. (-13.5, unusable 2 qt.). See NOTE 1 for data on undrainable oil. Control Surface Movements Wing Flaps Down 0° - 40° ± 2° Ailerons Up 20° +2°, -0° Down 14° + 2°, - 0° Elevator Up 25° ± 1° Down 15° ± 1° Elevator Tab Up 10° ± 1° Down 20° ± 1° Rudder Right 23° + 0°, -2° Left 23° + 0°, - 2° (measured perpendicularly to hinge line) Serial Numbers Eligible FA1500082 through FA1500120 VI. Model FRA150L or FA150L (when equipped with FKA150-2311 and FKA-2316), 2PCLM (Acrobatic Category), Approved December 3, 1971 Engine Rolls-Royce Continental O-240-A * Fuel 100/130 min. grade aviation gasoline * Engine Limits For all operations, 2800 rpm. (130 hp) Propeller and McCauley 1A135/BRM 24.8 lb (-34.5) Propeller Limits Diameter: not over 71 in., not under 70 in. Static rpm. at maximum permissible throttle setting: Not over 2500, not under 2400 No additional tolerance permitted Airspeed Limits (CAS) *Never exceed 193 mph (168 knots) *Maximum structural cruising 140 mph (122 knots) *Maneuvering 118 mph (103 knots) *Flaps extended 100 mph (87 knots) C.G. Range (+33.0) to (+37.5) at 1650 lbs. (+31.5) to (+37.5) at 1350 lbs. or less Straight line variation between points given. Rev. 16 7 A13EU VI. Model FRA150L or FA150L (when equipped with FKA150-2311 and FKA-2316) (cont’d) Empty Wt. C.G. Range None Leveling Means Jig located nut plates and screws at Station +94.63 and Station 132.94 on left side of tailcone. * Maximum Weight 1650 lb. No. of Seats 2 at (+39); (For child’s optional jump seat, refer to Equipment List.) Maximum Baggage 120 lb. - Reference weight and balance data * Fuel Capacity 26 gal. total, (22.5 gal. usable, two 13 gal. tanks in wings at +42.0) See NOTE 1 for system fuel and oil. Oil Capacity 6 qt. (-18, unusable 2 qt.). See NOTE 1 for data on undrainable oil. Control Surface Movements Wing Flaps Down 0° - 40° ± 2° Ailerons Up 20° +2°, -0° Down 14° + 2°, - 0° Elevator Up 25° ± 1° Down 15° ± 1° Elevator Tab Up 10° ± 1° Down 20° ± 1° Rudder Right 23° + 0°, -2° Left 23° + 0°, - 2° (measured perpendicularly to hinge line) Serial Numbers Eligible FRA1500121 through FRA1500261 FA1500121 through FA1500261 (when equipped with FKA150-2311 and FKA-2316) VII. Model F150M, 2PCLM (Utility Category), Approved October 8, 1974 Engine Continental O-200-A * Fuel 80/87 min. grade aviation gasoline * Engine Limits For all operations, 2750 rpm (100 hp) Propeller and McCauley 1A102/OCM 27.7 lb (-34.5) Propeller Limits Diameter: not over 69 in., not under 67.5 in. Static rpm. at maximum permissible throttle setting: Not over 2560, not under 2460 No additional tolerance permitted Airspeed Limits (CAS) F150M (1975 Model) *Never exceed 162 mph (141 knots) *Maximum structural cruising 120 mph (104 knots) *Maneuvering 109 mph (95 knots) *Flaps extended 100 mph (87 knots) Airspeed Limits (IAS) F150M (1976 Model and on) (See NOTE 3 on use of IAS) *Never exceed 141 knots *Maximum structural cruising 107 knots *Maneuvering 97 knots *Flaps extended 85 knots C.G. Range (+32.9) to (+37.5) at 1600 lbs. (+31.5) to (+37.5) at 1280 lbs. or less Straight line variation between points given. Empty Wt. C.G. Range None A13EU 8 Rev. 16 VII. Model F150M (cont’d) Leveling Means Jig located nut plates and screws at Station +94.63 and Station 132.94 on left side of tailcone. * Maximum Weight 1600 lb. No. of Seats 2 at (+39); (For child’s optional jump seat, refer to Equipment List.) Maximum Baggage 120 lb. - Reference weight and balance data Fuel Capacity 26 gal. total, (22.5 gal. usable, two 13 gal. tanks in wings at +42.0) See NOTE 1 for system fuel and oil. Oil Capacity 6 qt. (-13.5 unusable 2 qt.). See NOTE 1 for data on undrainable oil. Control Surface Movements Wing Flaps Down 0° - 40° ± 2° Ailerons Up 20° +2°, -0° Down 14° + 2°, - 0° Elevator Up 23° ± 1°,-0° Down 15° ± 1° Elevator Tab Up 10° ± 1° Down 20° ± 1° Rudder Right 23° + 0°, -2° Left 23° + 0°, - 2° (measured perpendicularly to hinge line) Serial Numbers Eligible F15001144 through F15001428 VIII. Model FRA150M or FA150M (when equipped with FKA150-2311 and FKA150-2316) 2PCLM (Acrobatic Category), Approved October 8, 1974 Engine Rolls Royce O-240-A or O-240-E (S/N FA00262 and on) * Fuel 100/130 min. grade aviation gasoline * Engine Limits (O-240-A) For all operations, 2800 rpm. (130 hp) (O-240-E) - Takeoff (5 min.) 2800 rpm. (130 hp) For all other operations 2650 rpm. (123 hp) Propeller and McCauley 1A135/BRM 24.8 lb (-34.5) Propeller Limits Diameter: not over 71 in., not under 70 in. Static rpm. at maximum permissible throttle setting: Not over 2500, not under 2400 No additional tolerance permitted Airspeed Limits (CAS) FRA150M (1975 Model) *Never exceed 193 mph (168 knots) *Maximum structural cruising 140 mph (122 knots) *Maneuvering 118 mph (103 knots) *Flaps extended 100 mph (87 knots) Airspeed Limits (IAS) FRA150M (1976 Model and up) (See NOTE 3 on use of IAS) *Never exceed 164 knots *Maximum structural cruising 123 knots *Maneuvering 105 knots *Flaps extended 85 knots C.G. Range (+32.9) to (+37.5) at 1650 lbs. (+31.5) to (+37.5) at 1350 lbs. or less Empty Wt. C.G. Range None Rev. 16 9 A13EU VIII. Model FRA150M or FA150M (when equipped with FKA150-2311 and FKA150-2316) (cont’d) Leveling Means Jig located nut plates and screws at Station +94.63 and Station 132.94 on left side of tailcone. * Maximum Weight 1600 lb. No. of Seats 2 at (+39); (For child’s optional jump seat, refer to Equipment List.) Maximum Baggage 120 lb. - Reference weight and balance data Fuel Capacity 26 gal. (22.5 gal. usable, two 13 gal. tanks in wings at +142.0) See NOTE 1 for data on unusable fuel. Oil Capacity 6 qt. (-13.5 unusable 2 qt.). See NOTE 1 for data on undrainable oil. Control Surface Movements Wing Flaps Down 0° - 40° ± 2° Ailerons Up 20° + 2°, -0° Down 14° + 2°, - 0° Elevator Up 25° + 1°, -0° Down 15° ± 1° Elevator Tab Up 10° + 1°, -0° Down 20° + 1° - 0° Rudder Right 23° + 0°, -2° Left 23° + 0°, - 2° (measured perpendicularly to hinge line) Serial Numbers Eligible FRA1500262 through FRA1500336 FA1500262 through FA1500336 (when equipped with FKA150-2311 and FKA150-2316) IX. Model F152, 2PCLM (Utility Category), Approved June 2, 1977 Engine Lycoming O-235-L2C (1978 through 1982 model) Lycoming O-235-N2C (1983 model and on and aircraft reworked per SK152-15 or SK152-16) * Fuel 100LL/100 min. grade aviation gasoline * Engine Limits For all operations, 2550 rpm. (110 hp) (1978 through 1982 model) For all operations, 2550 rpm. (108 hp) (1983 model and on) Propeller and (a) McCauley 1A103/TCM6958 23.2 lb (-36.5) Propeller Limits Diameter: not over 69 in., not under 67.5 in. Static rpm. at full throttle (carburetor heat off and mixture leaned to maximum rpm. is 2280 to 2380 rpm. No additional tolerance permitted (b) Spinner: Dwg. 0450073 Airspeed Limits (IAS) *Never exceed 149 knots (See NOTE 3 on use of IAS) *Maximum structural cruising 111 knots *Maneuvering 104 knots *Flaps extended 85 knots C.G. Range (+32.65) to (+36.5) at 1670 lbs. (+31.0) to (+36.5) at 1350 lbs. or less Straight line variation between points given. Empty Wt. C.G. Range None Leveling Means Jig located nut plates and screws at Station +94.63 and Station 132.9 on left side of tailcone. A13EU 10 Rev. 16 IX. Model F152 (cont’d) * Maximum Weight 1670 lb. 1675 lb. ramp weight (1979 model and on) No. of Seats 2 at (+39); (For child’s optional jump seat, refer to Equipment List.) Maximum Baggage 120 lb. - Reference weight and balance data Fuel Capacity 26 gal. total, (24.5 gal. usable, two 13 gal. tanks in wings at +42.0) See NOTE 1 for data on unusable oil. Oil Capacity 6 qt. (-14.7 unusable 2 qt.). See NOTE 1 for data on undrainable oil. Control Surface Movements Wing Flaps Down 0° - 30° ± 2° Ailerons Up 20° ± 1° Down 15° + 1° (aileron travel measured from 1° ± 5° droop) Elevator Up 25° ± 1° Down 18° ± 1° Elevator Tab Up 10° ± 1° Down 20° ± 1° Rudder Right 23° + 0°, -2° Left 23° + 0°, - 2° (measured perpendicularly to hinge line) Serial Numbers Eligible F15201429 through F15201980 X. Model FA152, 2PCLM (Acrobatic Category), Approved June 2, 1977 Engine Lycoming O-235-L2C (1978 through 1982 model) Lycoming O-235-N2C (1983 model and on and aircraft reworked per SK152-15 or SK152-16) * Fuel 100LL/100 min. grade aviation gasoline * Engine Limits For all operations, 2550 rpm. (110 hp) (1978 t hrough 1982 model) For all operations, 2550 rpm. (108 hp) (1983 model and on) Propeller and (a) McCauley 1A103/TCM6958 23.2 lb (-36.5) Propeller Limits Diameter: not over 69 in., not under 67.5 in. Static rpm. at full throttle (carburetor heat of f and mixture leaned to maximum rpm.) is 2280 to 2380 rpm. For allowable variations in static rpm. at non-standard temperatures, refer to the Service manual. (b) Spinner: Dwg. 0450073 Airspeed Limits (IAS) *Never exceed 172 knots (See NOTE 3 on use of IAS) *Maximum structural cruising 125 knots *Maneuvering 108 knots *Flaps extended 85 knots C.G. Range (+32.65) to (+36.5) at 1670 lbs. (+31.0) to (+36.5) at 1350 lbs. or less Empty Wt. C.G. Range None Leveling Means Jig located nut plates and screws at Station +94.63 and Station 132.94 on left side of tailcone. * Maximum Weight 1670 lb. 1675 lb. ramp weight (1979 model and on) Rev. 16 11 A13EU X. Model FA152 (cont’d) No. of Seats 2 at (+39); (For child’s optional jump seat, refer to Equi pment List.) Maximum Baggage 120 lb. - Reference weight and balance data Fuel Capacity 26 gal. total, (24.5 gal. usable, two 13 gal. tanks in wings at +42.0) See NOTE 1 for data on unusable oil. Oil Capacity 6 qt. (-14.7 unusable 2 qt.). See NOTE 1 for data on undrainable oil. Control Surface Movements Wing Flaps Down 0° - 30° ± 2° Ailerons Up 20° ± 1° Down 15° ± 1° (aileron travel measured from 1° ± 5° droop) Elevator Up 25° ± 1° Down 18° ± 1° Elevator Tab Up 10° ± 1° Down 20° ± 1° Rudder Right 23° + 0°, -2° Left 23° + 0°, - 2° (measured perpendicularly to hinge line) Serial Numbers Eligible FA1520337 through FA1520425 Data Pertinent To All Models Datum Fuselage station 0.0 (front face of firewall) Certification Basis Part 3 of the Civil Air Regulations dated May 15, 1956, as amended by 3-4. F152/FA152 comply with FAR 36 dated December 1, 1969 plus Amendments 36-1 through 36-5. Date of Application for Type Certificate: 27 September 1966. Type Certificate No. A13EU issued 17 February 1966. Equivalent Safety Items Airspeed indicator CAR 3.757 (See NOTE 3) Operating Limitations CAR 3.778 (a) 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 item of equipment is required: Stall warning indicator, Audible, Cessna Dwg. 0413029. NOTE 1. Current weight and balance report together with list of equipment included in certificated empty weight, and loading instructions when necessary, must be provided for each aircraft at the time of original certification. FRA150M (1976 Model): F150G thru F150M (1976 Model), FA150K, FA150L, FRA150L, FRA150M: The certificated empty weight and corresponding center of gravity location must include unusable fuel of 21 lb. at +40 and undrainable oil of (0) lb at - 13.5. F150M (1977 Model), FRA150M (1977 Model): The certificated empty weight and corresponding center of gravity location must include unusable fuel of 21 lb. at (+40) and full oil of 11.3 lb at ( -13.5) for landplane. F152, FA152: The certificated empty weight and corresponding center of gravity locations must include unusable fuel of 9 lb. at (+40) and full oil of 11.3 lb. at ( -14.7) for landplane. A13EU 12 Rev. 16 Data Pertinent To All Models (cont’d) NOTE 2. The following information must be displayed in the form of composite or individual placards. A. In full view of the pilot: (1) “This airplane must be operated in compliance with the operating limitations stated in the form of placards, markings and manuals”.