TCDS 3A19

Page No. 1 2 3 4 5 6 7 8 9 10 11 12 13 14 15 16 17 18 19 Rev No. 51 43 43 41 42 41 41 41 51 51 41 38 50 30 50 32 32 37 50 DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION 3A19 Revision 51 Textron Aviation 150 150J 150A 150 K 150B A150 K 150C 150L 150D A150L 150E 150M 150F A150M 150G 152 150H A152 August 1, 2024 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. 3A19 This data sheet, which is a part of ty pe certificate No. 3A19, prescribes conditio ns and limitations under which the product fo r which the type certificate was issued meets the airworthiness requirements of the Federal Aviation 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 I. Model 150, 2 PCLM (Utility Category), Approved July 10, 1958 Model 150A, 2 PCLM (Utility Category), Approved June 14, 1960 Model 150B, 2 PCLM (Utility Category), Approved June 20, 1961 Model 150C, 2 PCLM (Utility Category), Approved June 15, 1962 Engine 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. Propeller Propeller Limits (a) Sensenich Hub 69CK 24 lb. (-32) Static r.p.m. at maximum permissible throttle setting: Not over 2470, not under 2320 No additional tolerance permitted Diameter: not over 69 in., not under 67.5 in. 2. Propeller (a) McCauley Hub 1A100/MCM 21 lb. (-32) Static r.p.m. at maximum permissible throttle setting: Not over 2475, not under 2375 No additional tolerance permitted Diameter: not over 69 in., not under 67.5 in. 3. Propeller (a) McCauley Hub 1A101/DCM 21 lb. (-32) Static r.p.m. at maximum permissible throttle setting: Not over 2600, not under 2500 No additional tolerance permitted Diameter: not over 69 in., not under 67.5 in. 3A19 2 Rev. 51 I. Models 150, 150A, 150B, 150C (cont’d) *Airspeed Limits (CAS) Neve r exceed 157 m.p.h. (136 knots) Maximum structural cruising 120 m.p.h. (104 knots) Maneuvering 106 m.p.h. ( 92 knots) Flaps extended 85 m.p.h. ( 74 knots) C.G. Range (+33.4) to (+36.0) at 1500 lb. (+32.2) to (+36.0) at 1250 lb. or less Straight line variation between points given. Empty Weight C.G. Range None Leveling Means Top edge of fuselage splice plate. *Maximum Weight 1500 lb. No. of Seats 2 at (+39); for child's optional jump seat, refer to Equipment List. Maximum Baggage 80 lb. at (+65) Fuel Capacity 26 gal. (22.5 gal. usab le, two 13 gal. tanks in wings at +42) See NOTE 1 for data on system fuel. Oil Capacity 6 qt. (-13.5; unusable 2 qt.) See NOTE 1 for data on system oil. Control Surface Win g flaps Retracte d 0° Movements 1st notch 10° 2nd notch 20° 3rd notch 30° 4th notch 40° Ailerons Up 20° Down 15° Elevato r U p 25° Down 15° Elevator tab Up 10° Down 20° Rudde r Ri ght 16° Left 16° Serial Nos. Eligible Model 150: 617, 17001 thru 17999, 59001 thru 59018 Model 150A: 628, 15059019 thru 15059350 Model 150B: 15059351 thru 15059700 Model 150C: 15059701 thru 15060087 II. Model 150D, 2 PCLM (Utility Category), Approved July 19, 1963 Model 150E, 2 PCLM (Utility Category), Approved June 18, 1964 Model 150F, 2 PCLM (Utility Category), Approved May 27, 1965 Engine 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. Propeller Propeller Limits (a) Sensenich Hub 69CK 24 lb. (-32) Static r.p.m. at maximum permissible throttle setting: Not over 2470, not under 2320 No additional tolerance permitted Diameter: not over 69 in., not under 67.5 in. 2. Propeller (a) McCauley 1A100/MCM 21 lb. (-32) Static r.p.m. at maximum permissible throttle setting: Not over 2475, not under 2375 No additional tolerance permitted Diameter: not over 69 in., not under 67.5 in. Rev. 51 3 3A19 II. Models 150D, 150E, 150F (cont’d) Propeller and 3. Propeller Propeller Limits (cont’d) (a ) McCauley 1A101/DCM 21 lb. (-32) Static r.p.m. at maximum permissible throttle setting: Not over 2600, not under 2500 No additional tolerance permitted Diameter: not over 69 in., not under 67.5 in. *Airspeed Limits (CAS) Never ex ceed 162 m.p.h. (141 knots) Maximum structural cruising 120 m.p.h. (104 knots) Maneuvering 109 m.p.h. ( 95 knots) Flaps extended 100 m.p.h. ( 87 knots) C.G. Range (+32.9) to (+37.5) at 1600 lb. (+31.5) to (+37.5) at 1280 lb. or less Straight line variation between points given. Empty Weight 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 Models 150D, 150E: 120 lb. at (+65) Model 150F: 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 data on system fuel. Oil Capacity 6 qt. (-13.5; unusable 2 qt .) See NOTE 1 for data on system oil Control Surface Wing flaps (150D, 150E) Retracte d 0° Movements 1st Notch 10° 2nd Notch 20° 3rd Notch 30° 4th Notch 40° Win g flaps (150F) Down 0° -40° ±2° Ailerons Up 20° Down 15° Elevato r U p 25° Down 15° Elevator tab Up 10° Down 20° Rudder (150D, 150E) Ri ght 16° Left 16° (150F) Right 23° Left 23° (measured parallel to chord) Serial Nos. Eligible Model 150D: 15060088 thru 15060772 Model 150E: 644, 15060773 thru 15061532 Model 150F: 15061533 thru 15064532 3A19 4 Rev. 51 III. Model 150G, 2 PCLM (Utility Category), Approved May 5, 1966, 2 PCSM (Utility Category), Approved August 12, 1966 Model 150H, 2 PCL-SM (Utility Category), Approved August 10, 1967 Model 150J, 2 PCL-SM (Utility Category), Approved May 2, 1968 Model 150K, 2 PCL-SM (Utility Category), Approved June 5, 1969 Engine 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. Propeller Propeller Limits (a) Sensenich Hub 69CK 24 lb. (-32) Static r.p.m. at maximum permissible throttle setting: Not over 2470, not under 2320 No additional tolerance permitted Diameter: not over 69 in., not under 67.5 in. 2. Propeller (a) McCauley Hub 1A100/MCM 21 lb. (-32) Static r.p.m. at maximum permissible throttle setting: Not over 2475, not under 2375 No additional tolerance permitted Diameter: not over 69 in., not under 67.5 in. 3. Propeller (seaplane only) (a) McCauley Hub 1A90/CF 24 lb. (-32) Static r.p.m. at maximum permissible throttle setting: Not over 2600, not under 2500 No additional tolerance permitted Diameter: not over 75 in., not under 73.5 in. 4. Propeller (a) McCauley Hub 1A101/DCM 21 lb. (-32) Static r.p.m. at maximum permissible throttle setting: not over 2600, not under 2500 No additional tolerance permitted Diameter: not over 69 in., not under 67 in. *Airspeed Limits (CAS) Never ex ceed 162 m.p.h. (141 knots) Maximum structural cruising 120 m.p.h. (104 knots) Maneuvering 109 m.p.h. ( 95 knots) Flaps extended 100 m.p.h. ( 87 knots) C.G. Range Landplane (+32.9) to (+37.5) at 1600 lb. (+31.5) to (+37.5) at 1280 lb. or less Seaplane (+33.8) to (+36.5) at 1650 lb. (+33.0) to (+36.5) at 1400 lb. or less Straight line variation between points given Empty Weight C.G. Range None Leveling Means Top of tailcone *Maximum Weight Landplane 1600 lb. Seaplane 1650 lb. (Edo 88A-1650 floats) No. of Seats 2 at (+39); for child's optional jump seat, refer to Equipment List. Maximum Baggage 120 lb.; Refere nce weight and balance data Rev. 51 5 3A19 III. Models 150G, 150H, 150J, 150K (cont’d) Fuel Capacity Landplane 26 gal. (22.5 gal. usable, two 13 gal. tanks in wings at +42.0) Seaplane 26 gal. (21.5 gal. usable, two 13 gal. tanks in wings at +42.0) See NOTE 1 for data on system fuel. Oil Capacity 6 qt. (-1.5; unusable 2 qt.) See NOTE 1 for data on system oil. Control Surface Wing flaps Down 0° -40° ±2° Movements Ailerons U p 20° +2°, -0° Down 14° +2°, -0° Elevato r Up 25° ±1° Down 15° ±1° Elevator tab U p 10° ±1° Down 20° ±1° Rudde r Right 23° +0°, -2° Left 23° +0°, -2° (measured perpendicularly to hinge line) Serial Nos. Eligible Mode l 150G: 15064533 thru 15067198 (except 15064970) Model 150H: 649, 15067199 thru 15069308 Model 150J: 15069309 thru 15071128 Model 150K: 15071129 thru 15072003 IV. Model A150K, Aerobat, 2 PCLM (Acrob atic Category), Approved June 5, 1969 Engine 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. Propeller Propeller Limits (a) McCauley Hub 1A101/DCM 21 lb. (-32) Static r.p.m. at maximum permissible throttle setting: Not over 2600, not under 2500 No additional tolerance permitted Diameter: not over 69 in., not under 67 in. *Airspeed Limits (CAS) Neve r exceed 193 m.p.h. (168 knots) Maximum structural cruising 140 m.p.h. (122 knots) Maneuvering 118 m.p.h. (103 knots) Flaps extended 100 m.p.h. ( 87 knots) C.G. Range (+32.9) to (+37.5) at 1600 lb. (+31.5) to (+37.5) at 1280 lb. or less Empty Weight 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 +42.0) 3A19 6 Rev. 51 IV. Model A150K (cont’d) Oil Capacity 6 qt. (-13.5; unusable 2 qt.) See NOTE 1 for data on system oil. Control Surface Win g flaps Down 0° -40° ±2° Movements Ailerons Up 20° +2°, -0° Down 14° +2°, -0° Elevato r U p 25° ±1° Down 15° ±1° Elevator tab Up 10° ±1° Down 20° ±1° Rudde r Ri ght 23° +0°, -2° Left 23° +0°, -2° (measured perpendicularly to hinge line) Serial Nos. Eligible M odel A150K: A1500001 thru A1500226 V. Model 150L, 2 PCLM (Utility Category), Approved June 8, 1970 Engine 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. Propeller Propeller Limits (a) McCauley Hub 1A101/GCM 27.7 lb. (-34.5) (1971, 1972, 1973 models) Static r.p.m. at maximum permissible throttle setting: Not over 2600, not under 2500 No additional tolerance permitted Diameter: not over 69 in., not under 67 in. 2. Propeller (a) McCauley Hub 1A101/HCM 27.7 lb. (-34.5) (1972, 1973, 1974 models) Static r.p.m. at maximum permissible throttle setting: Not over 2600, not under 2500 No additional tolerance permitted Diameter: not over 69 in., not under 67 in. 3. Propeller (a) McCauley Hub 1A101/PCM 27.0 lb. (-34.5) (1974 model) Static r.p.m. at maximum permissible throttle setting: Not over 2600, not under 2500 No additional tolerance permitted Diameter: not over 69 in., not under 67 in. 4. Propeller (a) McCauley Hub 1A102/OCM 27.0 lb. (-34.5) (1971 thru 1974 models) Static r.p.m. at maximum permissible throttle setting: Not over 2560, not under 2460 No additional tolerance permitted Diameter: not over 69 in., not under 67.5 in. *Airspeed Limits (CAS) Neve r exceed 162 m.p.h. (141 knots) Maximum structural cruising 120 m.p.h. (104 knots) Maneuvering 109 m.p.h. ( 95 knots) Flaps extended 100 m.p.h. ( 87 knots) C.G. Range (+32.9) to (+37.5) at 1600 lb. (+31.5) to (+37.5) at 1280 lb. or less Straight line variation between points given. Rev. 51 7 3A19 V. Model 150L (cont’d) Empty Weight C.G. Range None Leveling Means Jig located nut plates and screws at Stations +94.63 and +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 +42.0) See NOTE 1 for data on system fuel. Oil Capacity 6 qt. (-13.5; unusable 2 qt.) See NOTE 1 for data on undrainable oil. Control Surface Win g flaps Down 0° -40° ±2° Movements Ailerons Up 20° +2°, -0° Down 14° +2°, -0° Elevato r U p 25° ±1° Down 15° ±1° Elevator tab Up 10° ±1° Down 20° ±1° Rudde r Ri ght 23° +0°, -2° Left 23° +0°, -2° (measured perpendicularly to hinge line) Serial Nos. Eligible 15072004 thru 15072628 (1971 Model) 15072629 thru 15073658 (1972 Model) 15073659 thru 15074850 (1973 Model) 15074851 thru 15075781 (1974 Model) VI. Model A150L, Aerobat, 2 PCLM (Acrob atic Category), Approved June 8, 1970 Engine 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. Propeller Propeller Limits (a) McCauley Hub 1A101/GCM 27.7 lb. (-34.5) (1971, 1972, 1973 models) Static r.p.m. at maximum permissible throttle setting: Not over 2600, not under 2500 No additional tolerance permitted Diameter: not over 69 in., not under 67 in. 2. Propeller (a) McCauley Hub 1A101/HCM 27.7 lb. (-34.5) (1971, 1972, 1973 models) Static r.p.m. at maximum permissible throttle setting: Not over 2600, not under 2500 No additional tolerance permitted Diameter: not over 69 in., not under 67 in. 3. Propeller (a) McCauley Hub 1A102/OCM 27.0 lb. (-34.5) (1971 thru 1974 model) Static r.p.m. at maximum permissible throttle setting: Not over 2560, not under 2460 No additional tolerance permitted Diameter: not over 69 in., not under 67.5 in. 3A19 8 Rev. 51 VI. Model A150L (cont’d) *Airspeed Limits (CAS) Neve r exceed 193 m.p.h. (168 knots) Maximum structural cruising 140 m.p.h. (122 knots) Maneuvering 118 m.p.h. (103 knots) Flaps extended 100 m.p.h. ( 87 knots) C.G. Range (+32.9) to (+37.5) at 1600 lb. (+31.5) to (+37.5) at 1280 lb. or less Empty Weight C.G. Range None Leveling Means Jig located nut plates and screws at Stations +94.63 and +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 +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 Win g flaps Down 0° -40° ±2° Movements Ailerons Up 20° +2°, -0° Down 14° +2°, -0° Elevato r U p 25° ±1° Down 15° ±1° Elevator tab Up 10° ±1° Down 20° ±1° Rudde r Ri ght 23° +0°, -2° Left 23° +0°, -2° (measured perpendicularly to hinge line) Serial Nos. Eligible A1500227 thru A1500276 (1971 Model) A1500277 thru A1500342 (1972 Model) A1500343 thru A1500429 (1973 Model) A1500430 thru A1500523 (1974 Model, except A1500433) VII. Model 150M, 2 PCLM (Utility Category), Approved May 6, 1974 Engine 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. Propeller Propeller Limits (a) McCauley Hub 1A102/OCM 27.7 lb. (-34.5) Static rpm at maximum permissible throttle setting: Not over 2560, not under 2460 No additional tolerance permitted Diameter: not over 69 in., not under 67 in. *Airspeed Limits (CAS) (S/N 15075782 thru 15077005) Never exceed 162 m.p.h. (141 knots) Maximum structural cruising 120 m.p.h. (104 knots) Maneuvering 109 m.p.h. ( 95 knots) Flaps extended 100 m.p.h. ( 87 knots) Rev. 51 9 3A19 VII. Model 150M (cont’d) *Airspeed Limits (IAS) (S/N 15077006 thru 15079405) (See NOTE 4 on Never exceed 141 knots use of IAS) Maximum structural cruising 107 knots Maneuvering 97 knots Flaps extended 85 knots C.G. Range (+32.9) to (+37.5) at 1600 lb. (+31.5) to (+37.5) at 1280 lb. or less Straight line variation between points given. Empty Weight C.G. Range None Leveling Means Jig located nut plates and screws at Stations +94.63 and +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 +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 Wing flaps Down 0° -40° ±2° Movements Ailerons U p 20° +2°, -0° Down 14° +2°, -0° Elevato r Up 23° +1°, -0° Down 15° ±1° Elevator tab U p 10° ±1° Down 20° ±1° Rudde r Right 23° +0°, -2° Left 23° +0°, -2° (measured perpendicularly to hinge line) Serial Nos. Eligible 15075782 thru 15077005 (1975 Model) 15077006 thru 15078505 (1976 Model) 15078506 thru 15079405 (1977 Model) VIII. Model A150M, Aerobat, 2 PCLM (Acr obatic Category), Approved May 6, 1974 Engine 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. Propeller Propeller Limits (a) McCauley Hub 1A102/OCM 27.0 lb. (-34.5) Static r.p.m. at maximum permissible throttle setting: Not over 2560, not under 2460 No additional tolerance permitted Diameter: not over 69 in., not under 67.5 in. *Airspeed Limits (CAS) (S/N 15064970, A1500524 thru A1500609) Never exceed 193 m.p.h. (168 knots) Maximum structural cruising 140 m.p.h. (122 knots) Maneuvering 118 m.p.h. (103 knots) Flaps extended 100 m.p.h. ( 87 knots) 3A19 10 Rev. 51 VIII. Model A150M (cont’d) *Airspeed Limits (IAS) A1500610 thru A1500734 (See NOTE 4 on Never exceed 164 knots use of IAS) Maximum structural cruising 123 knots Maneuvering 105 knots Flaps extended 85 knots C.G. Range (+32.9) to (+37.5) at 1600 lb. (+31.5) to (+37.5) at 1280 lb. or less Straight line variation between points given Empty Weight C.G. Range None Leveling Means Jig located nut plates and screws at Stations +94.63 and +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 +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 Wing flaps Down 0° -40° ±2° Movements Ailerons U p 20° +2°, -0° Down 14° +2°, -0° Elevato r Up 23° +1°, -0° Down 15° ±1° Elevator tab U p 10° ±1° Down 20° ±1° Rudde r Right 23° +0°, -2° Left 23° +0°, -2° (measured perpendicularly to hinge line) Serial Nos. Eligible 15064970, A1500524 thru A1500609 (1975 Model) A1500610 thru A1500684 (1976 Model) A1500685 thru A1500734 (1977 Model) IX. Model 152, 2 PCLM (Utility Category), Approved March 16, 1977 Engine S/N 15279406 thru 15285594 Lycoming O-235-L2C S/N 15285595 and On, aircraft reworked per SK152-15 or SK152-16 Lycoming O-235-N2C *Fuel 100LL/100 min. grade aviation gasoline *Engine Limits S/N 15279406 thru 15285594 For all operations, 2550 r.p.m. (110 hp.) S/N 15285595 and On For all operations 2550 r.p.m. (108 hp.) Rev. 51 11 3A19 IX. Model 152 (cont'd) Propeller and 1. Propeller Propeller Limits (a) McCauley Hub 1A103/TCM 23.2 lb. (-36.5) Static rpm at full throttle (carburetor heat off and mixture leaned to maximum r.p.m.) is 2280 to 2380 r.p.m. For allowable variati ons in static r.p.m. at non-standard temperatures, refer to the Service Manual. Diameter: not over 69 in., not under 67.5 in. (b) Spinner: Dwg. 0450073 *Airspeed Limits (IAS) Never exceed 149 knots (See NOTE 4 on Maximum structural cruising 111 knots use of IAS) Maneuvering 104 knots Flaps extended 85 knots C.G. Range (+32.65) to (+36.5) at 1670 lb. (+31.0) to (+36.5) at 1350 lb. or less Straight line variation between points given. Empty Weight C.G. Range None Leveling Means Jig located nut plates and screws at Stations +94.63 and +132.94 on left side of tailcone. *Maximum Weight 1670 lb. 1675 lb. ramp weight (S/N 15282032 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. (24.5 gal. usable , two 13 gal. tanks in wings at +42.0) See NOTE 1 for data on unusable fuel. Oil Capacity 6 qt. (-14.7; unusable 2 qt.) See NOTE 1 for data on undrainable oil. Control Surface s Wing flaps Down 0° -30° ±2° Movements Ailerons Up 20°  2° Down 15°  1° (aileron travel measured from 1° ±.5° droop) Elevato r Up 25° ±1° Down 18° ±1° Elevator tab U p 10° ±1° Down 20° ±1° Rudde r Right 23° +0°, -2° Left 23° +0°, -2° (measured perpendicularly to hinge line) Serial Nos. Eligible 15279406 thru 15282031 (1978 Model) 15282032 thru 15283591 (1979 Model) 15283592 thru 15284541 (1980 Model) 15284542 thru 15285161 (1981 Model) 15285162 thru 18285594 (1982 Model) 15285595 thru 15285833 (1983 Model) 15285834 thru 15285939 (1984 Model) 15285940 thru 15286033 (1985 Model) 3A19 12 Rev. 51 X. Model A152, Aerobat, 2 PCLM (Acrob atic Category), Approved March 16, 1977 Engine S/N A1500433, A1520735, 681 thru A521014 Lycoming O-235-L2C S/N A1521015 and On, aircraft reworked per SK152-15 or SK152-16 Lycoming O-235-N2C *Fuel 100LL/100 min. grade aviation gasoline *Engine Limits S/N A1500433, A1520735, 681 thru A1521014 For all operations, 2550 r.p.m. (110 hp.) S/N A1521015 and on For all operations, 2550 r.p.m. (108 hp.) Propeller and 1. Propeller Propeller Limits (a) McCauley Hub 1A103/TCM 23.2 lb. (-36.5) Static rpm at full throttle (carburetor heat off and mixture leaned to maximum r.p.m.) is 2280 to 2380 r.p.m. For allowable variati ons in static r.p.m. at non-standard temperatures, refer to the Service Manual. Diameter: not over 69 in., not under 67.5 in. (b) Spinner: Dwg. 0450073 *Airspeed Limits (IAS) Never exceed 172 knots (See NOTE 4 on Maximum structural cruising 125 knots use of IAS) Maneuvering 108 knots Flaps extended 85 knots C.G. Range (+32.65) to (+36.5) at 1670 lb. (+31.0) to (+36.5) at 1350 lb. or less Empty Weight C.G. Range None Leveling Means Jig located nut plates and screws at Stations +94.63 and +132.94 on left side of tailcone. *Maximum Weight 1670 lb. 1675 lb. ramp weight (S/N 681, A1520809 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. (24.5 gal. usable , two 13 gal. tanks in wings at +42.0) See NOTE 1 for data on unusable fuel. Oil Capacity 6 qt. (-14.7; unusable 2 qt.) See NOTE 1 for data on undrainable oil. Control Surface Win g flaps Down 0° -30° ±2° Movements Ailerons Up 20°  1° Down 15°  1° (aileron travel measured from 1° ±.5° droop) Elevato r Up 25° ±1° Down 18° ±1° Elevator tab U p 10° ±1° Down 20° ±1° Rudde r Right 23° +0°, -2° Left 23° +0°, -2° (measured perpendicularly to hinge line) Rev. 51 13 3A19 X. Model A152 (cont’d) Serial Nos. Eligible A1500433, A1520735 thru A1520808 (1978 Model) 681, A1520809 thru A1520878 (1979 Model) A1520879 thru A1520943 (1980 Model) A1520944 thru A1520983 (1981 Model) A1520984 thru A1521014 (1982 Model) A1521015 thru A1521025 (1983 Model) A1521026 thru A1521027 (1984 Model) A1521028 thru A1521049 (1985 Model) Data Pertinent to All Models Datum Fuselage station 0. 0 front face of firewall Certification Basis: