TCDS 7A14

Page No. 1 2 3 4 5 6 7 8 9 10 11 12 13 14 15 16 17 18 Rev. No. 11 7 7 8 8 8 8 8 8 8 11 8 8 8 8 8 8 8 DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION 7A14 Revision 11 SOCATA (MORANE SAULNIER (Rallye) Series) MS 880B Rallye 100S MS 885 Rallye 150T MS 894A Rallye 150ST MS 893A Rallye 235E MS 892A-150 Rallye 235C MS 892E-150 MS 893E MS 894E July 19, 2021 TYPE CERTIFICATE DATA SHEET No. 7A14 This data sheet which is a part of Type Certificate No. 7A14 prescribes conditions and limitations under which the product fo r which the Type Certificate was issued meets the airworthiness requirements of the Civil Air Regulations. Type Certificate Holder DAHER 65921 - TARBES Cedex 9 France Type Certificate Holder Record SOCATA name dropped by owner DAHER in 2015 65921 - TARBES Cedex 9 France S O C A T A - Groupe AEROSPATIALE transferred to SOCATA on October 12, 2011 I - Model MS 880B (Rallye), 3 PCLM (Normal Category), approved 21 November 1961 Model MS 880B (Rallye Club), 3 PCLM (Utility Category), approved 23 June 1971. (See NOTE 4 for conversion from Normal to Utility Category). Engine Continental O-200-A; or Rolls-Royce RR O-200-A Fuel 80/87 minimum grade aviation gasoline Engine limits For all operations, 2750 rpm (100 hp) Propeller and Normal Category: propeller limits McCauley 1A105/SCM-7146 Static r.p.m. at maximum permissible throttle setting: Not over 2500, not under 2400 No additional tolerance permitted. Diameter: Maximum 71 in., minimum allowable for repairs 70 in. No further reduction permitted. Placard required: "Avoid continuous operation over 2650 r.p.m." Normal or Utility Category: McCauley 1A101/DCM-6948 Static r.p.m. at maximum permissible throttle setting: Not over 2500, not under 2400 No additional tolerance permitted. Diameter: Maximum 69 in., minimum allowable for repairs 67 in. No further reduction permitted. 7A14 Page 2 of 18 Airspeed limits (IAS) Categories Normal Utility Never exceed 156 m.p.h. (135 knots) 168 m.p.h. (145 knots) Maximum structural 125 m.p.h. (108 knots) 125 m.p.h. (108 knots) cruising Maneuvering 120 m.p.h. (104 knots) 120 m.p.h. (104 knots) Flaps extended 87 m.p.h. ( 76 knots) 87 m.p.h. ( 76 knots) C.G. range Normal or Utility Category (+32.6) to (+40.7) at 1344 lb., or less (+33.9) to (+40.7) at 1700 lb. Straight line variation between points given. Empty weight C.G. range None Maximum weight 1700 lb., Normal or Utility Category Number of seats 3 (2 at +37.3, 1 at +70.0). See NOTE 3 for rear seat occupancy. Maximum baggage See NOTE 3. Fuel capacity Standard interconnected wing tanks with float level fuel gauge: 27.6 gal., total (27 gal., usable, two 13.8 gal., tanks at +42.0) Long range interconnected wing tanks with float level fuel gauge: 47.6 gal., total (47 gal., usable, two 23.8 gal., tanks at +42.0) Standard separated wing tanks with electrical fuel gauge: 27.8 gal., total (25.4 gal., usable, two 13.9 gal., tanks at +42.0) Long range separated wing tanks with electrical fuel gauge: 48.6 gal., total (45 gal., usable, two 24.3 gal., tanks at +42.0) Oil capacity 5 qt., (-22.0) 6 qt., (-22.0) when Spec. CES 1108 engines are installed See NOTE 1 for unusable fuel and undrainable oil data. Control surface movements Aileron Up 17°30' Down 13°30' Elevator Up 25° Down 30° Elevator trim tab Up 28°* Down 28° Rudder Right 30° Left 30° Wing flaps Takeoff 0° Landing 30° *Up 20° as of the 281th aircraft II - Model MS 885 (Super Rallye), 3 PCLM (Normal Category), approved 23 August 1962 Engine Continental O-300-A or B Fuel 80/87 minimum grade aviation gasoline Engine limits For all operations, 2700 rpm (145 hp) Propeller and McCauley 1C172/MDM 7652 TO 7658 propeller limits Static r.p.m. at maximum permissible throttle setting: Not over 2400, not under 2150 No additional tolerances permitted. Diameter: Maximum 76 in., minimum allowable for repairs 74 in. No further reduction permitted. Spinner: SOCATA P/N 835-33 Airspeed limits (IAS) Never exceed 156 m.p.h. (135 knots) Maximum structural cruising 125 m.p.h. (108 knots) Maneuvering 120 m.p.h. (104 knots) Flaps extended 87 m.p.h. ( 76 knots) C.G. range (+32.6) to (+40.21) at 1499 lb., or less (+33.5) to (+40.21) at 1880 lb. Straight line variation between points given. Empty weight C.G. range None Maximum weight 1880 lb. Number of seats 3 (2 at +37.3, 1 at +70.0). See NOTE 3 for rear seat occupancy. Maximum baggage See NOTE 3. Fuel capacity 47.6 gal., total (47 gal., usable, two 23.8 gal., tanks at +42.0) Oil capacity 8 qt., (-19.4) See NOTE 1 for unusable fuel and undrainable oil data. Control surface movements Aileron Up 17°30' Down 13°30' Elevator Up 25° Down 30° Page 3 of 18 7A14 Elevator trim tab Up 28°* Down 28° Rudder Right 30° Left 30° Wing flaps Takeoff 0° Landing 30° *Up 20° as of the 281th aircraft III - Model MS 894A, 4 PCLM (Normal and Utility Category), approved 29 August 1968 (Similar to MS 885 except for modified rudder, increased skin thickness on airframe and powerplant installation). IV - Model MS 894E (Rallye Minerva 220), 4 PCLM (Normal and Utility Category), approved 29 November 1972 (Similar to MS 894A except control wheel installed in lieu of stick, instrument panel and center pedestal changes, and introduction of electric flap system). Engine Franklin 6A 350 C1 Fuel 100/130 minimum grade aviation gasoline Engine limits For all operations, 2800 rpm (220 hp) Propeller and 1. McCauley 2 A 31C21/84 S-8 propeller limits Diameter: maximum 76 in., minimum allowable for repairs 74 in. No further reduction permitted Pitch setting at 30 in., radius: Low 13°30' High 22° Spinner: SOCATA P/N 894.58.0.147.0 Woodward hydraulic governor 210453 or 210660 2. Hartzell HC - C2YF-1B/8459-4 Diameter: maximum 80 in., minimum allowable for repairs 76 in. No further reduction permitted Pitch setting at 30 in., radius: Low 11°30' High 31° Spinner: SOCATA P/N 894.58.0.147.0 Woodward hydraulic governor 210453 or 210660 Airspeed limits (IAS) Categories Normal Utility Never exceed 190 m.p.h. (164 knots) 202 m.p.h. (175 knots) Maximum structural 155 m.p.h. (135 knots) 155 m.p.h. (135 knots) cruising Maneuvering 124 m.p.h. (108 knots) 130 m.p.h. (113 knots) Flaps extended 100 m.p.h. ( 86 knots) 100 m.p.h. ( 86 knots) C.G. range MS 894A: Normal Category : (+31.5) to (41.15) at weight lower than 1600 lb. (+34.4) to (41.15) at 2205 lb. (+38.2) to (41.15) at 2425 lb. Straight line variation between points given. Utility Category: (+31.5) to (41.15) at weight lower than 1600 lb. (+34.4) to (41.15) at 2205 lb. Straight line variation between points given MS 894E: Normal Category : (+31.0) to (41.15) at weight lower than 1660 lb. (+33.6) to (41.15) at 2205 lb. (+38.2) to (41.15) at 2425 lb. Straight line variation between points given. Utility Category: (+31.0) to (41.15) at weight lower than 1660 lb. (+33.6) to (41.15) at 2205 lb. Straight line variation between points given Empty weight C.G. range None Maximum weight Normal Category: Maximum T.O. - 2425 lb. Maximum Landing - 2314 lb. Utility Category: Max. T.O. & Landing 2205 lb. Number of seats MS 894A: 7A14 Page 4 of 18 4 (2 at +37.3, 2 at +70.0) MS 894E: 4 (2 at +38.1, 2 at +70.0) Maximum baggage 100 lb. (+96.3) Fuel capacity Standard: 48.6 gal., total (45 gal., usable, two 24.3 gal., wing tanks at +42.0) ong range: 62.0 gal., total (58 gal., usable, two 31.0 gal., wing tanks at +42.0) Oil capacity 9.5 qt., (-21.5) See NOTE 1 for unusable fuel and undrainable oil data. Control surface movements Aileron Up 17° Down 13° Elevator Up 25° Down 30° (Down 20° for MS 894E) Elevator trim tab Up 20° Down 28° Rudder Right 30° Left 30° Wing flaps Takeoff 0° Landing 30° Rudder trim tab Right 10° Left 25° V - Model MS 892A-150 (Commodore), 4 PCLM (Utility Category), approved 22 June 1971 (Similar to MS 894A, except for powerplant installation). VI - Model MS 892E-150 (Rallye 150GT), 4 PCLM (Utiltiy Category), approved 29 November 1972 (Similar to MS 894E, except for powerplant installation). Engine Lycoming O-320-E2A Fuel 80/87 minimum grade aviation gasoline Engine limits For all operations, 2700 rpm (150 hp) Propeller and 1. Sensenich 74DM6-0-54 or M74DM-0-54 propeller limits Static r.p.m. at maximum permissible throttle setting: Not over 2500, not under 2400 No additional tolerances permitted. Diameter: Maximum 74 in., minimum allowable for repairs 72 in. No further reduction permitted. Spinner: SOCATA P/N 892.58.0.161.0 2. Sensenich 74DM6-0-56 or M74DM-0-56 Static r.p.m. at maximum permitted throttle setting: Not over 2425, not under 2325 No additional tolerances permitted. Diameter: Maximum 74 in., minimum allowed for repairs 72 in. No further reduction permitted. Spinner: SOCATA P/N 892.58.0.161.0 3. Sensenich 74DM6-0-58 or M74DM-0-58 Static r.p.m. at maximum permitted throttle setting: Not over 2350, not under 2250 No additional tolerances permitted. Diameter: Maximum 74 in., minimum for repairs 72 in. No further reduction permitted. Spinner: SOCATA P/N 892.58.0.161.0 4. McCauley 1C172/MGM-7650 Static r.p.m. at maximum permitted throttle setting: Not over 2510, not under 2410 No additional tolerances permitted. Diameter: Maximum 76 in., minimum for repairs 74 in. No further reduction permitted. Spinner: SOCATA P/N 892.58.0.161.0 5. McCauley 1C172/MGM-7652 Static r.p.m. at maximum permitted throttle setting: Not over 2460, not under 2360 No additional tolerances permitted. Diameter: Maximum 76 in., minimum for repairs 74 in. Page 5 of 18 7A14 No further reduction permitted. Spinner: SOCATA P/N 892.58.0.161.0 Airspeed limits (IAS) Never exceed 180 m.p.h. (156 knots) Maximum structural cruising 155 m.p.h. (135 knots) Maneuvering 130 m.p.h. (113 knots) Flaps extended 100 m.p.h. ( 86 knots) C.G. range (+30.7) to (+41.15) at 1510 lb., or less (+37.1) to (+41.15) at 2160 lb. Straight line variation between points given. Empty weight C.G. range None Maximum weight 2160 lb. Number of seats Model MS 892A-150: 4 (2 at +37.3; 2 at +70.0) Model MS 892E-150: 4 (2 at +38.1; 2 at +70.0) Maximum baggage 100 lb. (+96.3) Fuel capacity Standard: 48.6 gal., total (45 gal., usable, two 24.3 gal., wing tanks at +42.0) Long range: 62.0 gal., total (58 gal., usable, two 31.0 gal., wing tanks at +42.0) Oil capacity 8.5 qt., (-19.4) See NOTE 1 for unusable fuel and undrainable oil data. Control surface movements Aileron Up 17° Down 13° Elevator Up 25° Down 28° (Down 20° for MS 892E-150) Elevator trim tab Up 20° Down 28° Rudder Right 30° Left 30° Wing flaps Takeoff 0° Landing 30° VII - Model MS 893A (Rallye Commodore), 4 PCLM (Normal and Utility Category), approved 22 June 1971 (Similar to MS 894A except for powerplant installation). VIII - Model MS 893E (Rallye 180 GT), 4 PCLM (Normal and Utility Category), approved 29 November 1972 (Similar to MS 894E except for powerplant installation). Engine Lycoming O-360-A1A, O-360-A2A, or O-360-A3A Fuel 91/96 minimum grade aviation gasoline Engine limits For all operations, 2700 rpm (180 hp) Propeller and 1. Sensenich 76EM8-0-54 or M76EMM-0-54 * (with O-360-A2A engine) propeller limits Static r.p.m. at maximum permitted throttle setting: Not over 2500, not under 2400 No additional tolerances permitted. Diameter: Maximum 76 in., no further reduction permitted. Spinner: SOCATA P/N 892.58.0.161.0 2. Sensenich 76EM8-0-56 or M76EMM-0-56 * (with O-360-A2A engine) Static r.p.m. at maximum permitted throttle setting: Not over 2450, not under 2350 No additional tolerances permitted. Diameter: Maximum 76 in., no further reduction permitted. Spinner: SOCATA P/N 892.58.0.161.0 3. Sensenich 76EM8-0-58 or M76EMM-0-58 * (with O-360-A2A engine) Static r.p.m. at maximum permitted throttle setting: Not over 2425, not under 2325 No additional tolerances permitted. Diameter: Maximum 76 in., no further reduction permitted. Spinner: SOCATA P/N 892.58.0.161.0 7A14 Page 6 of 18 4. Sensenich 76EM8-0-60 or M76EMM-0-60 * (with O-360-A2A engine) Static r.p.m. at maximum permitted throttle setting: Not over 2400, not under 2300 No additional tolerances permitted. Diameter: Maximum 76 in., no further reduction permitted. Spinner: SOCATA P/N 892.58.0.161.0 5. Hartzell HC-C2YK-1B/7666A-2 * (with O-360-A1A engine) Diameter: Maximum 74 in., minimum for repairs 72 in. No further reduction permitted. Pitch setting at 30 in., radius: Low 11°30' High 31° Spinner: HARTZELL P/N 835.33 Hartzell hydraulic governor F4-4A *Placards required: Sensenich propellers - "Avoid continuous operation between 2150 and 2350 r.p.m." Hartzell propellers - "Avoid continuous operation between 2000 and 2250 r.p.m." Airspeed limits (IAS) Normal and Utility Category Never exceed 180 m.p.h. (156 knots) Maximum structural cruising 155 m.p.h. (135 knots) Maneuvering 130 m.p.h. (113 knots) Flaps extended 100 m.p.h. ( 86 knots) C.G. range Normal Category: (+30.7) to (+41.15) at 1510 lb., or less (+38.2) to (+41.15) at 2314 lb. Straight line variation between points given. Utility Category: (+30.7) to (+41.15) at 1510 lb., or less (+37.2) to (+41.15) at 2205 lb. Straight line variation between points given. Empty weight C.G. range None Maximum weight Normal Category: Maximum T.O. - 2314 lb. Maximum Landing - 2205 lb. Utility Category: Maximum T.O. and Landing - 2205 lb. Number of seats MS 893A: 4 (2 at +37.3; 2 at +70.0) MS 893E: 4 (2 at +38.1; 2 at +70.0) Maximum baggage 100 lb. (+96.3) Fuel capacity Standard: 48.6 gal., total (45 gal., usable, two 24.3 gal., wing tanks at +42.0) Long range: 62.0 gal., total (58 gal., usable, two 31.0 gal., wing tanks at +42.0) (See NOTE 2). Oil capacity 8.5 qt., (-19.4) See NOTE 1 for unusable fuel and undrainable oil data. Control surface movements Aileron Up 17° Down 13° Elevator Up 25° Down 28° (Down 20° for MS 893E) Elevator trim tab Up 20° Down 28° Rudder Right 30° Left 30° Wing flaps Takeoff 0° Landing 30° Page 7 of 18 7A14 IX - Model Rallye 100S, 2 PCLM (Utility Category), approved 4 April 1975 Engine Continental O-200-A; or Rolls-Royce RR O-200-A Fuel 80/87 minimum grade aviation gasoline or AVGAS 100 L according to Service Bulletin Rolls-Royce T-220/1-T-229 Engine limits For all operations, 2750 rpm (100 hp) Propeller and Utility Category: propeller limits McCauley 1A101/DCM-6948 Static r.p.m. at maximum permissible throttle setting: Not over 2500, not under 2400 No additional tolerances permitted. Diameter: Maximum 69 in., minimum allowable for repairs 67 in. No further reduction permitted. Airspeed limits (IAS) Utility Category: Never exceed 168 m.p.h. (145 knots) Maximum structural cruising 125 m.p.h. (108 knots) Maneuvering 120 m.p.h. (104 knots) Flaps extended 87 m.p.h. ( 76 knots) C.G. range Utility Category: (+32.6) to (+37.1) at 1344 lb., or less (+33.7) to (+37.1) at 1655 lb. Straight line variation between points given. Empty weight C.G. range None Maximum weight 1655 lb. Number of seats 2 at (+37.3) Maximum baggage 44 lb. Fuel capacity Standard separated wing tanks with electrical fuel gauge: 27.8 gal., total (25.4 gal., usable, two 13.9 gal., tanks at +42.0) Oil capacity Never use detergent oil 5 qt., (-22.0) 6 qt., (-22.0) when Spec. CES 1108 engines are installed. See NOTE 1 for unusable fuel and undrainable oil data. Control surface movements Aileron Up 17°30' Down 13°30' Elevator Up 30° Down 25° Elevator trim tab Up 28° * Down 28° Rudder Right 30° Left 30° Wing flaps Takeoff 0° Landing 30° * Up 20° as of the 281th aircraft. X - Model Rallye 150 ST, 4 PCLM (Normal or Utility Category), approved November 18, 1976 Engine Lycoming O-320-E2A Fuel 80/87 or AVGAS 100 L grade aviation gasoline. Engine limits For all operations, 2700 rpm (150 hp) Propeller and Sensenich 74 DM 6 056 propeller limits Static r.p.m. at maximum permissible throttle setting: Not over 2450, not under 2200 No additional tolerances permitted. Diameter: Maximum 74 in., minimum allowable for repairs 72 in. No further reduction permitted. Spinner: SOCATA P/N 892.58.0.161.0 7A14 Page 8 of 18 Airspeed limits (IAS) Normal Category Utility Category Never exceed 156 m.p.h. (135 knots) 168 m.p.h. (145 knots) Maximum structural cruising 125 m.p.h. (108 knots) 125 m.p.h. (108 knots) Maneuvering 120 m.p.h. (104 knots) 120 m.p.h. (104 knots) Flaps extended 99 m.p.h. ( 86 knots) 99 m.p.h. ( 76 knots) C.G. range Normal Category: (+32.0 in.) to (+41.22 in.) at 1642 lb. or less (+34.68 in.) to (+41.22 in.) at 1918 lb. Utility Category (+32.55 in.) to (+35.10 in.) at 1698 lb. (Spins) Straight line variation between points given. Empty weight C.G. range None Maximum weight 1918 lb. Number of seats 4 (2 at +37.3 in.; 2 at +70.0 in.) See NOTE 6 for rear seat occupancy.) Maximum baggage See NOTE 6. Fuel capacity Standard: 27.8 gal., total (25.46 gal., usable, two 13.9 gal., tanks at +42.0) Optional 48.6 gal. total (45 gal. usable, two 24.3 gal. tanks at +42.0) Oil capacity 8.5 qt., (-19.4) See NOTE 1 for unusable fuel and undrainable oil data. Control surface movements Aileron Up 17°30' Down 13°30' Elevator Up 30° Down 25° Elevator trim tab Up 30° Down 28° Rudder Right 30° Left 30° Wing flaps Takeoff 0° Landing 30° XI - Model Rallye 150 T, 4 PCLM (Utility Category), approved November 18, 1976 Engine Lycoming O-320-E2A Fuel 80/87 or AVGAS 100 L grade aviation gasoline Engine limits For all operations, 2700 r.p.m. (150 hp) Propeller and Sensenich 74 DM 6 - 054 at 74 DM 6 - 060 propeller limits Static r.p.m. at maximum permissible throttle setting: Not over 2450, not under 2200 No additional tolerances permitted. Diameter: Maximum 74 in., minimum allowable for repairs 72 in. No further reduction permitted. Spinner: SOCATA P/N 892.58.0.161.0 Airspeed limits (IAS) Utility Category: Never exceed 168 m.p.h. (145 knots) Maximum structural cruising 125 m.p.h. (108 knots) Maneuvering 130 m.p.h. (113 knots) Flaps extended 100 m.p.h. ( 86 knots) C.G. range Utility Category: (+32.0) to (+41.22 in.) at 1642 lb. or less (+36.33 in.) to (+41.22 in.) at 2095 lb. Straight line variation between points given. Empty weight C.G. range None Maximum weight 2095 lb. Number of seats 4 (2 at +37.3 in.; 2 at +70.0 in). See NOTE 6 for rear seat occupancy. Maximum baggage See NOTE 6. Fuel capacity Standard: 48.6 gal., total (45 gal., usable, two 24.3 gal., wing tanks at +42.0 in.) Oil capacity 8 qt., (-19.4 in.) See NOTE 1 for unusable fuel and undrainable oil data. Control surface movements Aileron Up 17° Down 13° Page 9 of 18 7A14 Elevator Up 25° Down 30° Elevator trim tab Up 30° Down 28° Rudder Right 30° Left 30° Wing flaps Takeoff 0° Landing 30° XII - Model Rallye 235 E, 4 PCLM (Normal or Utility Category), approved November 18, 1976 Engine Lycoming O-540-B4-B5 Fuel 80/87 minimum grade aviation gasoline or 100 L AVGAS Engine limits For all operations, 2575 rpm (235 hp) Propeller and Hartzell HC-C2YK-1BF/F8468.A-4. propeller limits Diameter: Maximum 80 in., minimum allowable for repairs 77 in. No further reduction permitted. Pitch setting at 30 in., Radius: low 12°50', high 28°18' Spinner: HARTZELL 835-33 Woodward 210-681 hydraulic governor. Airspeed limits (IAS) Normal Category Utility Category Never exceed 196 m.p.h. (170 knots) 209 m.p.h. (182 knots) Maximum structural cruising 156 m.p.h. (135 knots) 156 m.p.h. (135 knots) Maneuvering 130 m.p.h. (113 knots) 130 m.p.h. (113 knots) Flaps extended 109 m.p.h. ( 95 knots) 109 m.p.h. ( 95 knots) C.G. range Normal Category: (+31.0 in.) to (41.22 in.) at weight lower than 1764 lb. (+33.54 in.) to (41.22 in.) at weight lower than 2315 lb. (+38.2 in.) to (41.22 in.) at weight lower than 2645 lb. Straight line variation between points given. Utility Category (+31.0 in.) to (41.22 in.) at weight lower than 1764 lb. (+33.54 in.) to (41.22 in.) at weight lower than 2205 lb. Straight line variation between points given. Empty weight C.G. range None Maximum weight Normal Category: Maximum T.O. 2645 lb. - Maximum landing 2513 lb. Utiltiy Category: Maximum T.O. and landing - 2205 lb. Number of seats 4 (2 at +38.1 in.; 2 at +70.0 in.) Maximum baggage 100 lb. (+96.3 in.) Fuel capacity Standard separated wing tanks with electrical fuel gauge: 74 gal., total (71.32 gal., usable, two 37 gal. wing tanks at +42.0) Oil capacity 14.3 qt., (-19.7) See NOTE 1 for unusable fuel and undrainable oil data. Control surface movements Aileron Up 17° Down 13° Elevator Up 25° Down 20° Elevator trim tab Up 20° Down 28° Rudder Right 30° Left 30° Wing flaps Takeoff 0° Landing 30° Rudder trim tab Right 10° Left 25° XIV - Model Rallye 235C, 4 PCLM (Normal or Utility Category), approved June 14, 1979 7A14 Page 10 of 18 Engine Lycoming O-540-B4-B5 Fuel 80/87 or AVGAS 100LL grade aviation gasoline. Engine limits For all operations: 2575 rpm (235 hp) Propeller and HARTZELL HC-C2YK-1BF/F-8468 A-4 propeller limits Diameter: Maximum 80 in., minimum allowable for repairs 77 in. No further reduction permitted. Pitch setting at 30 in., Radius: Low 12°50', high 28°18. Spinner: HARTZELL 835-33 Woodward 210-681 hydraulic governor. Airspeed limits (IAS) Normal Category Utility Category Never exceed 196 m.p.h. (170 knots) 209 m.p.h. (182 knots) Maximum structural cruising 155 m.p.h. (135 knots) 155 m.p.h. (135 knots) Maneuvering 130 m.p.h. (113 knots) 130 m.p.h. (113 knots) Flaps extended 109 m.p.h. ( 95 knots) 109 m.p.h. ( 95 knots) C.G. range Normal Category: (+31.0 in.) to (41.22 in.) at weight lower than 1764 lb. (+33.54 in.) to (41.22 in.) at weight lower than 2315 lb. (+38.2 in.) to (41.22 in.) at weight lower than 2645 lb. Straight line variation between points given. Utility Category (+31.0 in.) to (41.22 in.) at weight lower than 1764 lb. (+33.0 in.) to (41.22 in.) at weight lower than 2205 lb. Straight line variation between points given. Empty weight C.G. range None Maximum weight Normal Category: Maximum T.O. 2645 lb. - Maximum landing 2513 lb. Utility Category Maximum T.O. and landing 2205 lb. Number of seats 4 (2 at +38.1 in.; 2 at +70.0 in.) Maximum baggage 100 lb. (96.3 in.) Fuel capacity Standard separated wing tanks with electrical fuel gauge: 74 gal., Total (71.32 gal., usable, two 37 gal. wing tanks at +42.0)