# TCDS 7A14: Daher - Type: Type certificate data sheet - Status: Current - Holder: Daher - Revision: 11 - Revised: July 19, 2021 - Product: Aircraft, Small Airplane - Certification basis: CAR 3, CAR 10 - Registered aircraft: 62, by the registry models matched to it (OpenAirDocs) - Data sheet PDF: https://openairdocs.org/files/sha256/b2/a5/b2a58bf7bffe1fcbaeeefa059189657661cbc9459faa76b0335489f0fa6474d2 - FAA DRS: https://drs.faa.gov/browse/excelExternalWindow/60B016A89C44F7F28625871900578729.0001 - Page: https://openairdocs.org/tcds/7A14 ## Models (13) As the data sheet lists them. - Rallye 150 ST - MS 892A-150 - Rallye 235 E - Rallye 100S - MS 894E - MS 894A - MS 880B - MS 892E-150 - MS 893E - MS 893A - Rallye 235C - MS 885 - Rallye 150 T ## What the data sheet says From the PDF's text layer, line by line; tables lose their columns. The PDF is the record. ```text 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) 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° DATA PERTINENT TO ALL MODELS Datum Front face of firewall. Leveling means Longitudinal fuselage longerons used as canopy rails. Serial Numbers eligible A Certificate of Airworthiness for Export endorsed as noted under "Import Requirements" must be submitted for each individual aircraft for which application for U.S. certification is made. Page 11 of 18 7A14 Certification basis CAR.10 - CAR.3 effective 15 May 1956, including amendments 3-1 through 3-5. Type Certificate No. 7A14 issued 21 November 1961. Application for Type Certificate dated 19 December 1960. The Direction Générale de l’Aviation Civile (DGAC) originally type certificated this aircraft under its type certificate Numbers TC 13 and TC 22. The FAA validated this product under U.S. Type Certificate Number 7A14. Effective September 28, 2003, the European Aviation Safety Agency (EASA) began oversight of this product on behalf of France. Import requirements The FAA can issue a U.S. airworthiness certificate based on an NAA Export Certificate of Airworthiness (Export C of A) signed by a representative of the Direction Générale de l’Aviation Civile (DGAC) on behalf of the European Community. The Export C of A should contain the following statement: ‘The aircraft covered by this certificate has been examined, tested, and found to comply with U.S. airworthiness regulations Civil Air Regulation Part 3 dated 15 May 1956, including Amendments 3-1 through 3-5 approved under U.S. Type Certificate No. 7A14 and to be in a condition for safe operation.’ Refer to the applicable bilateral agreement to verify eligibility for import into the United States of both new and used aircraft based on the scope of the agreement, to identify any required statements by the exporting authority on the export certificate of airworthiness (or equivalent document), and for procedures for coordinating exceptions to conformity statements on these documents. Refer to FAA Order 8130.2, Airworthiness Certification of Aircraft, for requirements for issuance of an airworthiness certificate for imported aircraft. 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 is required: (a) DGAC approved Airplane Flight Manual for the Models MS 894A, MS 894E, Rallye 100 S. Rallye 150 ST, Rallye 150 T, and Rallye 235 E and Rallye 235C only. Service Information Each of the documents listed below must state that it is approved by the European Aviation Safety Agency (EASA) or – for approvals made before September 28, 2003 – by the Direction Générale de l’Aviation Civile (DGAC). • Service bulletins, • Structural repair manuals, • Vendor manuals, • Aircraft flight manuals, and • Overhaul and maintenance manuals. The FAA accepts such documents and considers them FAA -approved unless one of the following conditions exists: • The documents change the limitations, performance, or procedures of the FAA approved manuals; or •The documents make an acoustical or emissions changes to this product’s U.S. type certificate as defined in 14 CFR § 21.93. The FAA uses the post type validation procedures to approve these documents. The FAA may delegate on case -by-case to EASA to approve on behalf of the FAA for the U.S. type certificate. If this is the case it will be noted on the document. NOTES NOTE 1. Current weight and balance report including list of equipment included in certificated empty weight and loading 7A14 Page 12 of 18 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 unusable fuel and undrainable oil as follows: Model Tank Configuration Unusable Fuel Undrainable Oil MS 880B Standard, interconnected tanks 4 lb., (+42.0) 0 lb. MS 880B Long range, interconnected tanks 4 lb., (+42.0) 0 lb. MS 880B Standard, separated tanks 7 lb., (+42.0) 0 lb. MS 880B Long range, separated tanks 7 lb., (+42.0) 0 lb. MS 885 Standard 4 lb., (+42.0) 0 lb. MS 894A & MS 894E Standard 7 lb., (+42.0) 0 lb. MS 894A & MS 894E Long range 7 lb., (+42.0) 0 lb. MS 892A & MS 892E Standard 7 lb., (+42.0) 0 lb. MS 892A & MS 892E Long range 7 lb., (+42.0) 0 lb. MS 893A & MS 893E Standard 7 lb., (+42.0) 0 lb. MS 893A & MS 893E Long range 7 lb., (+42.0) 0 lb. Rallye 100 S Standard, separated tanks 7 lb., (+42.0) 0 lb. Rallye 150 ST Standard, separated tanks 7 lb., (+42.0) 0 lb. Rallye 150 T Standard, separated tanks 7 lb., (+42.0) 0 lb. Rallye 235 E Standard, separated tanks 7 lb., (+42.0) 0 lb. Rallye 235 C Standard, separated tanks 7 lb., (+42.0) 0 lb. NOTE 2. Model MS 880B - Normal Category: (a) The following placard must be displayed in front and in clear of the pilots: 1) "This airplane must be operated in normal category in compliance with the operating limitations stated in the form of placards, markings and manuals. No acrobatic maneuvers, including sins, approved". 2) "Avoid continuous operation over 2650 r.p.m." 3) "Maximum weight 1700 lb. Flight maneuvering load factor (flaps up) + 3.8, - 1.5 Never exceed speed (IAS) 156 m.p.h. (135 knots) Maneuvering speed (IAS) 120 m.p.h. (104 knots) Maximum speed rough air (IAS) 125 m.p.h. (108 knots) Maximum speed flaps extended (IAS) 87 m.p.h. ( 76 knots)" (b) The following placard must be displayed in the rear seat area: "Maximum weight on rear seats 240 lb." For additional loading instructions, see weight and balance data.Model MS 880B - Utility Category: (a) The following placards must be displayed in front and in clear view of the pilots: 1) "This airplane must be operated in Utility Category in compliance with the operating limitations stated in the form of placards, markings and manuals. Acrobatic maneuvers are limited to the following: Maneuver Recommended Entry Speed Lazy eight 137 m.p.h. (119 knots) Chandelle 149 m.p.h. (130 knots) Steep turns 106 m.p.h. ( 92 knots) Stalls (except whip) Slow deceleration Spins are prohibited." 2) "Maximum weight 1700 lb. Flight maneuvering load factor (flaps up) + 4.4, - 1.8 Never exceed speed (IAS) 168 m.p.h. (145 knots) Maneuvering speed (IAS) 120 m.p.h. (104 knots) Maximum speed rough air (IAS) 125 m.p.h. (108 knots) Maximum speed flaps extended (IAS) 87 m.p.h. ( 76 knots)" (b) The following placard must be displayed in the rear seat area: "Maximum weight on rear seats 240 lb." For additional loading instructions, see weight and balance data. Model MS 885: (a) The following placards must be displayed in front and in clear view of the pilots: 1) "This airplane must be operated in normal category in compliance with the operating limitations stated in the form of placards, markings and manuals. No acrobatic maneuvers, including spins, approved". Page 13 of 18 7A14 2) "Maximum weight 1880 lb. Flight maneuvering load factor (flaps up) + 3.8, - 1.5 Never exceed speed (IAS) 156 m.p.h. (135 knots) Maneuvering speed (IAS) 120 m.p.h. (104 knots) Maximum speed rough air (IAS) 125 m.p.h. (108 knots) Maximum speed flaps extended (IAS) 87 m.p.h. ( 76 knots)" (b) The following placard must be displayed in the rear seat: "Maximum weight on rear seats 240 lb." For additional loading instructions, see weight and balance data. Models MS 894A and MS 894E: (a) The following placards must be displayed in front and in clear view of the pilots: - On instrument panel: 1) "This airplane must be operated as a normal or utility category airplane in compliance with the approved airplane flight manual. All markings and placards on this airplane apply to its operations as a normal category airplane. For utility category operations refer to the airplane flight manual". 2) "Only the following acrobatic maneuvers are approved when flying at "Utility category (maximum weight 2205 lb., or less): Steep turn 103 knots 118 m.p.h. Chandelle 130 knots 149 m.p.h. Lazy eight 119 knots 137 m.p.h. Stalls (except whip) Slow deceleration" 3) "No acrobatic maneuvers including spins are approved for normal category operations". 4) "Max. speed with fully extended flaps at 30° 86 knots 100 m.p.h. Maneuvering maximum speed 113 knots 130 m.p.h. Category U Category N Maximum weight 2205 lb. 2425 lb. Flight maneuvering load factor (flaps up) + 4.4, - 1.8 + 3.8, - 1.5 Never exceed speed (IAS) 202 mph (175 kts) 190 mph (164 kts) Maneuvering speed (IAS) 130 mph (113 kts) 124 mph (108 kts) Maximum speed rough air (IAS) 155 mph (135 kts) 155 mph (135 kts) Maximum speed flaps extended (IAS) 100 mph ( 86 kts) 100 mph ( 86 kts)" Models MS 892A-150 and MS 892E-150: (a) The following placards must be displayed in front and in clear view of the pilots: 1) "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. Acrobatic maneuvers are limited to the following: Maneuver Recommended Entry Speed Lazy eight 137 m.p.h. (119 knots) Chandelle 149 m.p.h. (130 knots) Steep turns 109 m.p.h. ( 94 knots) Stalls (except whip) Slow deceleration Spins are prohibited". 2) "Maximum weight 2160 lb. Flight maneuvering load factor (flaps up) + 4.4, - 1.8 Never exceed speed (IAS) 180 m.p.h. (156 knots) Maneuvering speed (IAS) 130 m.p.h. (113 knots) Maximum speed rough air (IAS) 155 m.p.h. (135 knots) Maximum speed flaps extended (IAS) 100 m.p.h. ( 86 knots)" 7A14 Page 14 of 18 (b) The following placards must be displayed on the fuel gauge: 1) Under the left tank gauge - "22.5 gal usable" or "29 gal. usable" (as applicable) 2) Under the right tank gauge - "22.5 gal usable" or "29 gal. usable" (as applicable) (c) The following fuel and oil placards must be displayed on - 1) Each fuel tank cover (2): "80/87 min. grade aviation gasoline". "22.5 gal. usable" or "29 gal. usable" (as applicable) ¦ 2) Oil cap: "8.5 qt". Models MS 893A and MS 893E: (a) The following placards must be displayed in front and in clear view of the pilots: 1) "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. 2) "No acrobatic maneuver, including spins approved when operating in the normal category". 3) "Only the following acrobatic maneuvers are approved when operating in the utiltiy category (maximum weight 2205 lb., or less). Maneuver Recommended Entry Speed Lazy eight 137 m.p.h. (119 knots) Chandelle 149 m.p.h. (130 knots) Steep turns 109 m.p.h. ( 94 knots) Stalls (except whip) Slow deceleration Spins are prohibited." 4) Never exceed speed (IAS) 180 m.p.h. (156 knots) Maneuvering speed (IAS) 130 m.p.h. (113 knots) Maximum speed rough air (IAS) 155 m.p.h. (135 knots) Maximum speed flaps extended (IAS) 100 m.p.h. ( 86 knots)" 5) "Category N Category U Maximum weights: Takeoff 2314 lb. 2205 lb. Landing 2205 lb. 2205 lb. Flight maneuvering load factors (flaps up) + 3.8, - 1.5 + 4.4, - 1.8" 6) "Avoid continuous operation between 2150 and 2350 r.p.m." (Sensenich propellers) "Avoid continuous operation between 2000 and 2250 r.p.m." (Hartzell propeller) (b) The following placards must be displayed on the fuel gauge: 1) Under the left tank gauge - "22.5 gal usable" or "29 gal. usable" (as applicable) except from serial number 2642 on MS-893E only "29 gal. usable" applies) 2) Under the right tank gauge - "22.5 gal usable" or "29 gal. usable" (as applicable) except from serial number 2642 on MS-893E only "29 gal. usable" applies) (c) The following fuel and oil placards must be displayed on - 1) Each fuel tank cover (2): "91/96 min. grade aviation gasoline". "22.5 gal. usable" or "29 gal. usable" (as applicable) except from serial number 2642 on Page 15 of 18 7A14 MS-893E only "29 gal. usable" applies). 2) Oil cap: "8.5 qt". Model Rallye 100 S - Utility Category: (a) The following placards must be displayed in front and in clear view of the pilots: 1) "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. Acrobatic maneuvers are limited to the following: Maneuver Recommended Entry Speed Lazy eight 137 m.p.h. (119 knots) Chandelle 149 m.p.h. (130 knots) Steep turns 106 m.p.h. ( 92 knots) Stalls (except whip) Slow deceleration Spins 62 m.p.h. ( 54 knots)" 2) "Maximum weight 1656 lb. Flight maneuvering load factor (flaps up) + 4.4, - 1.8 Never exceed speed (IAS) 168 m.p.h. (145 knots) Maneuvering speed (IAS) 120 m.p.h. (104 knots) Maximum speed rough air (IAS) 125 m.p.h. (108 knots) Maximum speed flaps extended (IAS) 87 m.p.h. ( 76 knots)" (b) The following placard must be displayed in the baggage compartment: "Maximum weight baggage: 44 lb." For additional loading instructions, see weight and balance data. Model Rallye 150 ST: (a) The following placards must be displayed in front and in clear view of the pilots: 1) "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." 2) "No acrobatic maneuver, including spins approved when operating in the Normal Category". 3) "Only the following acrobatic maneuvers are approved when operating in the Utility Category (maximum weight 1700 lb., or less): Maneuver Recommended Entry Speed Lazy eight 137 m.p.h. (119 knots) Chandelle 149 m.p.h. (130 knots) Steep turns 106 m.p.h. ( 92 knots) Stalls (except whip) Slow deceleration Spins 62 m.p.h. ( 54 knots) 4) Category U Category N "Maximum weight 1698 lb. 1918 lb. Flight maneuvering load factor + 4.4, - 1.8 + 3.8, -1.5 (flaps up) Never exceed speed (IAS) 168 mph (145 knots) 156 mph (135 knots) Maneuvering speed (IAS) 120 mph (104 knots) 120 mph (104 knots) Maximum speed rough air (IAS) 125 mph (108 knots) 125 mph (108 knots) Maximum speed flaps extended (IAS) 99 mph ( 86 knots) 99 mph ( 86 knots) (b) The following placard must be displayed in the rear seat area. "Maximum weight on rear seats: 287 lb". For additional loading instructions see weight and balance data. (c) The following placard must be displayed on the fuel gauge - 1) "Under the left tank gauge : "12.7 gal usable" or "22.5 gal. usable" (as applicable) 2) "Under the right tank gauge : "12.7 gal. usable" or "22.5 gal usable" (as applicable) 7A14 Page 16 of 18 (d) The following fuel and oil placards must be displayed on: 1) Each fuel tank cover (2): "80/87 or 100 L grade aviation gasoline". "12.7 gal. usable" or "22.5 gal. usable" (as applicable) 2) Oil cap: "8.5 qt". Model Rallye 150 T: (a) The following placards must be displayed in front and in clear view of the pilots: 1) "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. Acrobatic maneuvers are limited to the following: Maneuver Recommended Entry Speed Lazy eight 137 m.p.h. (119 knots) Chandelle 149 m.p.h. (130 knots) Steep turns 109 m.p.h. ( 94 knots) Stalls (except whip) Slow deceleration Spins 62 m.p.h. ( 54 knots)" 2) "Maximum weight 2095 lb. Flight maneuvering load factor (flaps up) + 4.4, - 1.8 Never exceed speed (IAS) 168 m.p.h. (145 knots) Maneuvering speed (IAS) 130 m.p.h. (113 knots) Maximum speed rough air (IAS) 125 m.p.h. (108 knots) Maximum speed flaps extended (IAS) 100 m.p.h. ( 86 knots)" (b) The following placard must be displayed in the rear seat area: "Maximum weight on rear seats: 309 lb." For additional loading instructions, see weight and balance data. (c) The following placards must be displayed on the fuel gauge - 1) "Under the left tank gauge : 22.5 gal. usable" 2) "Under the right tank gauge : 22.5 gal usable" (d) The following fuel and oil placards must be displayed on: 1) Each fuel tank cover (2): "80/87 or 100 L grade aviation gasoline 22.5 gal. usable". ¦ 2) Oil cap: "8.5 qt". ¦ Model Rallye 235 E: (a) The following placards must be displayed in front and in clear view of the pilots: 1) "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. 2) "No acrobatic maneuver, including spins, approved when operating in the Normal Category." 3) "Only the following acrobatic maneuvers are approved when operating in the Utility Category (maximum weight 2205 lb., or less): Maneuver Recommended Entry Speed Lazy eight 143 m.p.h. (124 knots) Page 17 of 18 7A14 Chandelle 162 m.p.h. (140 knots) Steep turns 124 m.p.h. (108 knots) Stalls (except whip) Slow deceleration Spins are prohibited." 4) Categories Normal Utility "Maximum weight Takeoff 2645 lb. 2205 lb. Landing 2513 lb. 2205 lb. Flight maneuvering load factor + 3.8, -1.5 + 4.4, - 1.8 (flaps up) Never exceed speed (IAS) 196 mph (170 knots) 209 mph (182 knots) Maneuvering speed (IAS) 130 mph (113 knots) 130 mph (113 knots) Maximum speed rough air (IAS) 155 mph (135 knots) 155 mph (135 knots) Maximum speed flaps extended (IAS) 109 mph ( 95 knots) 109 mph ( 95 knots) 5) Flight conditions: DAY VFR (see NOTE 5). Icing conditions : NOT ALLOWED (b) The following placard must be displayed in the baggage compartment: "Maximum Load: 100 lb." "4 persons, maximum load: 55 lb." For additional loading instructions, see weight and balance data. (c) The following placards must be displayed on the fuel gauge - 1) Under the left tank gauge : 35.66 gal. usable. 2) Under the right tank gauge : 35.66 gal. usable. (d) The following fuel and oil placards must be displayed on: 1) "Each fuel tank cover (2): 80/87 or 100 L AVGAS grade aviation gasoline. 35.66 gal. usable". 2) Oil capacity engine: "14.3 qt". Model Rallye 235C: (a) The following placards must be displayed in front and in clear view of the pilots: 1) "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. 2) No aerobatic maneuvers, including spins, approved when operating in the normal category. 3) Only the following aerobatic maneuvers are approved when operating in the Utility category (maximum weight 2205 lb., or less). Maneuver Recommended Entry Speed Lazy eight 143 m.p.h. (124 knots) Chandelle 162 m.p.h. (140 knots) Steep turns 124 m.p.h. (108 knots) Stalls (except whip) Slow deceleration Spins are prohibited. 4) Categories Normal Utility "Maximum weight Takeoff 2645 lb. 2205 lb. 7A14 Page 18 of 18 Landing 2513 lb. 2205 lb. Flight maneuvering load factor (flaps up) + 3.8, -1.5 + 4.4, - 1.8 Never exceed speed (IAS) 196 mph (170 knots) 209 mph (182 knots) Maneuvering speed (IAS) 130 mph (113 knots) 130 mph (113 knots) Maximum speed rough air (IAS) 155 mph (135 knots) 155 mph (135 knots) Maximum speed flaps extended (IAS) 109 mph ( 95 knots) 109 mph ( 95 knots) 5) Flight conditions: DAY VFR (see NOTE 5). Icing conditions : NOT ALLOWED (b) The following placards must be displayed in the baggage compartment: "Maximum Load: 100 lb." "4 persons, maximum load: 55 lb." For additional loading instructions, see weight and balance data. (c) The following placards must be displayed on the fuel gauge - 1) under the left tank gauge : 35.66 gal. usable. 2) under the right tank gauge : 35.66 gal. usable. (d) The following fuel and oil placards must be displayed on: 1) Each fuel tank cover (2): 80/87 or AVGAS 100 LL grade aviation gasoline. 35.66 gal. usable" 2) Oil cap.: "14.3 qt". NOTE 3. For Models MS 880B and MS 885 - rear seat may be occupied by two persons and/or baggage provided: (a) The total weight on the rear seats (including baggage) is under 240 lb. (b) The rear seat is equipped with two separate safety belts. (c) Weight and C.G. position are within limits. NOTE 4. A Model MS 880B airplanes airworthiness certificated in the normal category may be approved in the utility category after accomplishing the following modifications: (a) Replace the McCauley 1A105/SCM-7146 propeller with a McCauley 1A101/DCM-6948 propeller. (b) Replace the Normal Category placards with Utility Category placards in accordance with NOTE 2. NOTE 5. Kinds of Operations: For Models MS 893A-E, MS 894A-E, 235E and 235C, when equipment required by operating rules is installed and approved the following flight operations should be stated on a placard in full view of the pilot: "DAY-NIGHT VFR IFR" (See Airplane Flight Manual Sections 8 and 9). NOTE 6. For Model Rallye 150ST rear seat may be occupied by two persons and/or baggage provided: (a) The total weight on the rear seats (including baggage) is under 287 lb. (b) The rear seat is equipped with two separate safety belts. (c) Weight and C.G. position are within limits. For Model Rallye 150T rear seat may be occupied by two persons and/or baggage provided: (a) The total weight on the rear seats (including baggage) is under 309 lb. (b) The rear seat is equipped with two separate safety belts. (c) Weight and C.G. position are within limits. .....END..... ``` ## ADs (28, in force first) - [AD 2024-19-09](https://openairdocs.org/ad/2024-19-09): Nose/Tail Landing Gear · DAHER MS 880B, MS 885, MS 892A-150 and 10 more. Effective Nov 26, 2024 - [AD 2022-03-15](https://openairdocs.org/ad/2022-03-15): Fuel Quantity Indicator · Garmin G3X Touch Electronic Flight Instrument System (STC SA01899WI or SA02658SE). Effective Mar 21, 2022 - [AD 2006-12-07](https://openairdocs.org/ad/2006-12-07): ECi cylinder assemblies · Aerostar AEIO-320-D1B, AEIO-320-D2B, AEIO-320-E1A and 386 more. Effective Jul 11, 2006 - [AD 2006-03-08](https://openairdocs.org/ad/2006-03-08): Vacuum pumps · Aero Advantage 14-19, 14-19-2, 14-19-3 and 299 more. Effective Mar 10, 2006 - [AD 2005-01-19](https://openairdocs.org/ad/2005-01-19): Mode S transponders · GARMIN International GTX 330D, GTX 330, GTX 33D and 830 more. Effective Feb 23, 2005 - [AD 2003-26-06](https://openairdocs.org/ad/2003-26-06): Safety Belts and Restraint Systems · Anjou Aeronautique Safety Belts and Restraint Systems, AS332C, AS332L and 14 more. Effective Feb 17, 2004 - [AD 2003-06-07](https://openairdocs.org/ad/2003-06-07): Engine Mount Assembly · SOCATA MS 892A-150, MS 892E-150, MS 893A and 5 more. Effective May 16, 2003 - [AD 2000-22-17](https://openairdocs.org/ad/2000-22-17): Rudder and Elevator Control Clevis · SOCATA MS 880B, MS 885, MS 892A-150 and 10 more. Effective Dec 29, 2000 - [AD 96-09-06](https://openairdocs.org/ad/96-09-06): Air Filter Assemblies · Maule Aerospace Technology 7ACA, 7ECA, 7FC and 180 more. Effective Jun 7, 1996 - [AD 76-26-03](https://openairdocs.org/ad/76-26-03): Carburetor Icing · SOCATA MS 892A-150, MS 892E-150, MS 893A and 3 more. Effective Jan 6, 1977 - [AD 76-24-04](https://openairdocs.org/ad/76-24-04): Oil Return Pipes · SOCATA MS 892A-150, MS 892E-150, MS 893A and 1 more. Effective Dec 14, 1976 - [AD 76-11-02](https://openairdocs.org/ad/76-11-02): Engine Cowl Locks · SOCATA MS 880B, MS 892A-150, MS 892E-150 and 4 more. Effective Jun 7, 1976 - [AD 75-26-09](https://openairdocs.org/ad/75-26-09): Elevator Bellcrank · SOCATA MS 892A-150, MS 893A and MS 894A. Effective Dec 29, 1975 - [AD 75-22-15](https://openairdocs.org/ad/75-22-15): Floor and Control Stick · SOCATA MS 880B, MS 885, MS 892A-150 and 2 more. Effective Nov 4, 1975 - [AD 75-21-04](https://openairdocs.org/ad/75-21-04): Batteries · SOCATA MS 880B. Effective Oct 22, 1975 - [AD 75-17-18](https://openairdocs.org/ad/75-17-18): Aileron Control · SOCATA MS 880B, MS 892E-150, MS 893E and 2 more. Effective Aug 19, 1975 - [AD 75-17-22](https://openairdocs.org/ad/75-17-22): Front Horizontal Stabilizer · SOCATA MS 880B and MS 885. Effective Aug 19, 1975 - [AD 71-16-07](https://openairdocs.org/ad/71-16-07): Carburetor Heating System · SOCATA MS 894A. Effective Aug 4, 1971 - [AD 71-16-03](https://openairdocs.org/ad/71-16-03): Fuel Line Replacement · SOCATA MS 894A. Effective Jul 29, 1971 - [AD 71-15-03](https://openairdocs.org/ad/71-15-03): Generator System Cables · SOCATA MS 880B and MS 894A. Effective Jul 26, 1971 - [AD 70-20-02](https://openairdocs.org/ad/70-20-02): Air Speed Cover Glass · SOCATA MS 880B, MS 885 and MS 894A. Effective Oct 26, 1970 - [AD 70-17-04](https://openairdocs.org/ad/70-17-04): Leaks in Fuel System · SOCATA MS 880B, MS 885 and MS 894A. Effective Sep 12, 1970 - [AD 70-17-05](https://openairdocs.org/ad/70-17-05): Battery Box Modification · SOCATA MS 880B, MS 885 and MS 894A. Effective Sep 12, 1970 - [AD 70-17-06](https://openairdocs.org/ad/70-17-06): Firewall Sealant · SOCATA MS 880B, MS 885 and MS 894A. Effective Sep 12, 1970 - [AD 2016-08-08](https://openairdocs.org/ad/2016-08-08) (historical): Landing Gear · SOCATA MS 880B, MS 885, MS 892A-150 and 10 more. Effective May 18, 2016 - [AD 2002-05-04](https://openairdocs.org/ad/2002-05-04) (historical): Engine Mount Assembly · SOCATA - Groupe Aerospatiale MS 892A-150, MS 892E-150, MS 893A and 5 more. Effective Apr 22, 2002 - [AD 92-06-10](https://openairdocs.org/ad/92-06-10) (historical): Nose Wheel Axle · SOCATA MS 892A-150, MS 892E-150, MS 893A and 5 more. Effective Apr 17, 1992 - [AD 77-15-06](https://openairdocs.org/ad/77-15-06) (historical): Engine Mounts · SOCATA - Groupe Aerospatiale MS 892A-150, MS 892E-150, MS 893A and 3 more. Effective Aug 22, 1977 ## Registered aircraft by registry model (OpenAirDocs) - [S.O.C.A.T.A. MS894A](https://openairdocs.org/model/s-o-c-a-t-a-ms894a): 27 aircraft (registry code 8402842) - [S.O.C.A.T.A. RALLYE 235E](https://openairdocs.org/model/s-o-c-a-t-a-rallye-235e): 16 aircraft (registry code 8400135) - [S.O.C.A.T.A. RALLYE 150 ST](https://openairdocs.org/model/s-o-c-a-t-a-rallye-150-st): 10 aircraft (registry code 8400125) - [Morane-Saulnier MS880B](https://openairdocs.org/model/morane-saulnier-ms880b): 3 aircraft (registry code 5910304) - [Morane Saulnier MS893A](https://openairdocs.org/model/morane-saulnier-ms893a): 2 aircraft (registry code 5910313) - [S.O.C.A.T.A. MS893E](https://openairdocs.org/model/s-o-c-a-t-a-ms893e): 2 aircraft (registry code 8402838) - [Morane Saulnier MS893E](https://openairdocs.org/model/morane-saulnier-ms893e): 1 aircraft (registry code 5910314) - [S.O.C.A.T.A. MS880B](https://openairdocs.org/model/s-o-c-a-t-a-ms880b): 1 aircraft (registry code 8402830) - [Morane-Saulnier MS-885](https://openairdocs.org/model/morane-saulnier-ms-885): 0 aircraft (registry code 5910308) - [Morane-Saulnier MS892A-150](https://openairdocs.org/model/morane-saulnier-ms892a-150): 0 aircraft (registry code 5910312) - [Morane-Saulnier MS892E-150](https://openairdocs.org/model/morane-saulnier-ms892e-150): 0 aircraft (registry code 5910309) - [Morane-Saulnier MS894A](https://openairdocs.org/model/morane-saulnier-ms894a): 0 aircraft (registry code 5910317) - [Morane-Saulnier MS894E](https://openairdocs.org/model/morane-saulnier-ms894e): 0 aircraft (registry code 5910316) ## STCs approved under this data sheet (106, first 50) - [STC SA02571SE](https://openairdocs.org/stc/SA02571SE): Installation of Garmin G500/G600 TXi Integrated Avionics System (Primary Flight Display, Multi-Function Display, and Engine Indicating System Display).. Garmin International Inc. - [STC SA12428CH](https://openairdocs.org/stc/SA12428CH): Installation of the Lycoming Engines Electronic Ignition System (EIS). Lycoming Engines, An Operating Division of AVCO Corporation - [STC SA04837NY](https://openairdocs.org/stc/SA04837NY): Installation of AeroLED's Holdings, LLC., position lights, navigation lights, strobe lights and beacon lights. AeroLED's Holdings, LLC - [STC SA04652CH](https://openairdocs.org/stc/SA04652CH): To allow use of 100R grade aviation fuel meeting Swift Fuel, LLC specification. Swift Fuels LLC - [STC SA02636SE](https://openairdocs.org/stc/SA02636SE): Installation of Garmin GPS 175 Navigation System and GNX 375 Navigation System with ADS-B In/Out Transponder.. Garmin International Inc. - [STC SA02019SE-D](https://openairdocs.org/stc/SA02019SE-D): Installation of Garmin Model GTN 625/635/650; 725/750 Navigation System. Garmin International Inc. - [STC SA00079NY](https://openairdocs.org/stc/SA00079NY): Installation of Airwolf remote mounted engine oil filter kit AFC-K008 on single and multi engine fixed wing light aircraft incorporating Teledyne Continental reciprocating engines of 450 horsepower or less.. Airwolf Filter Corporation - [STC SA02511SE](https://openairdocs.org/stc/SA02511SE): Installation of replacement fuel quantity indicator sending unit(s). CiES Inc. - [STC SA5581SW](https://openairdocs.org/stc/SA5581SW): Installation of ALCOR true-flow/ totalizer system. Alcor LLC - [STC SA04046CH PAGE 1](https://openairdocs.org/stc/SA04046CH%20PAGE%201): Installation of L-3 GENESIS (TM) Electronic Standby Instrument System (ESI-500/MAG-500). Acron Aviation Inc. - [STC SA04378CH](https://openairdocs.org/stc/SA04378CH): Installation of an engine modified per STC SE04349CH. SureFly Partners Ltd. - [STC SA02594SE](https://openairdocs.org/stc/SA02594SE): SkyView HDX Instrumentation and Autopilot System manufactured. Dynon Avionics - [STC SA02386AK](https://openairdocs.org/stc/SA02386AK): Replacement of existing landing and/or taxi light reflector and bulbs with Light Emitting Diode (LED) lighting systems. AeroLED's Holding LLC - [STC SA01757WI](https://openairdocs.org/stc/SA01757WI): To allow the use of UL91 or UL94 (minimum) grade aviation fuel. Swift Fuels LLC - [STC SA04568CH](https://openairdocs.org/stc/SA04568CH): Installation of the uAvionix tailBeaconX, a tail mounted position light with integrated Automatic Dependent Surveillance - Broadcast (ADS-B) Out and 1090MHz Mode-S transponder functionality. uAvionix Corporation - [STC SA02658SE](https://openairdocs.org/stc/SA02658SE): Installation of Garmin GI 275 Multi-Function Display System. Garmin International Inc. - [STC SA01899WI](https://openairdocs.org/stc/SA01899WI): Installation of Garmin G3X Touch Electronic Flight Instrument System. Garmin International Inc. - [STC SA02019WI](https://openairdocs.org/stc/SA02019WI): Installation of the Trig Avionics TX56, TX56A, TX57, or TX57A VHF Nav-Com Radio.. Peregrine - [STC SA01435LA](https://openairdocs.org/stc/SA01435LA): Installation of engines modified with Firewall Forward Technologies LLC modified camshaft. Centri-Lube Technologies LLC - [STC SA00756DE](https://openairdocs.org/stc/SA00756DE): Installation of Automatic Dependent Surveillance Broadcast (ADS-B) Out Equipment using a Trig Avionics TT22 Transponder and an approved Global Positioning System (GPS) Position Sensor. Peregrine - [STC SA11137SC](https://openairdocs.org/stc/SA11137SC): Installation of Plane-Power ALT-FLX alternator. Hartzell Engine Technologies, LLC - [STC SA02987CH](https://openairdocs.org/stc/SA02987CH): Installation of the Electroair Electronic Ignition System. Electroair Acquisition Corporation - [STC SA01967WI](https://openairdocs.org/stc/SA01967WI): Use of GAMI G100UL High Octane Unleaded Avgas. General Aviation Modifications Inc. - [STC SA02444AK](https://openairdocs.org/stc/SA02444AK): Approval of the L-3 Communications NGT 9000/9000R ADS-B system installed. ADS-B Technologies LLC - [STC SA01818WI](https://openairdocs.org/stc/SA01818WI): Installation of Garmin G5 Electronic Flight Instrument. Garmin International Inc. - [STC SA09902AC](https://openairdocs.org/stc/SA09902AC): Installation of BendixKing KFD 900 Flight Display System. Honeywell International Inc. (Bendix King) - [STC SA11174SC PAGE 2](https://openairdocs.org/stc/SA11174SC%20PAGE%202): Installation of BendixKing by Honeywell KSN 770 and KSN 765 WAAS LPV approach capable nav/comm systems. Honeywell International Inc (Bendix King) - [STC SA10822SC](https://openairdocs.org/stc/SA10822SC): Installation of EFD1000 Primary Flight Display. Aspen Avionics Inc. - [STC SA00401BO](https://openairdocs.org/stc/SA00401BO): Installation of a SkyTrax100B UAT receiver. Avidyne Corporation - [STC SA00410BO](https://openairdocs.org/stc/SA00410BO): Installation of an AV-30-C Multi-Mode Indicator. uAvionix Corporation - [STC SA01831WI](https://openairdocs.org/stc/SA01831WI): To allow the use of UL91 (minimum) grade aviation fuel. Petersen Aviation Inc - [STC SA10236SC](https://openairdocs.org/stc/SA10236SC): Installation of a GDC 31 Roll Steering Converter. DAC International Inc - [STC SA01560WI-D](https://openairdocs.org/stc/SA01560WI-D): Installation of the Honeywell KFD 840 Primary Flight Display System.. Honeywell International Inc - [STC SA01714WI](https://openairdocs.org/stc/SA01714WI): Installation of a Garmin transponders: (a) GTX 330/330D/33/33D with ADS-B Out functionality; (b) GTX 335/335R/345/345R with ADS-B Out and In functionality; or (c) GTX 335R/345R with ADS-B Out functionality in select airplanes installed with G950/G1000 systems.. Garmin International Inc - [STC SA03286CH](https://openairdocs.org/stc/SA03286CH): Install an electronic engine ignition system. Electroair Acquisition Corporation - [STC SA04032CH](https://openairdocs.org/stc/SA04032CH): Install rocker switch assemblies. Electroair Acquisition Corporation - [STC SA00344BO PAGE 2](https://openairdocs.org/stc/SA00344BO%20PAGE%202): Installation of Parmetheus Plus LED PAR36 and PAR46 taxi and landing lights.. Whelen Aerospace Technologies - [STC SA00744DE](https://openairdocs.org/stc/SA00744DE): Installation of the Automatic Dependent Surveillance Broadcast (ADS-B) Out Equipment using a Trig Avionics TT31 Transponder and an approved position sensor. Peregrine - [STC SA00765DE](https://openairdocs.org/stc/SA00765DE): Installation of Automatic Dependent Surveillance Broadcast (ADS-B) Out functionality using the BendixKing KT74 Transponder and qualified position sensor. Peregrine - [STC SA04165NY](https://openairdocs.org/stc/SA04165NY): Installation of Latitude Technologies Skynode S200 Satcom system must be performed. Latitude Technologies Corporation - [STC SA01435SE](https://openairdocs.org/stc/SA01435SE): Installation of J.P. Instruments (JPI) Primary Engine Data Management System. J. P. Instruments - [STC SA02153LA-D PAGE 2](https://openairdocs.org/stc/SA02153LA-D%20PAGE%202): Installation of Garmin G600 Primary Flight Display (PFD) and Multifunction Display (MFD) System. Garmin International Inc. - [STC SA01835WI](https://openairdocs.org/stc/SA01835WI): Installation of Trig Avionics TY-96 or TY-97 VHF Communications Radio. Peregrine - [STC SA00024NY](https://openairdocs.org/stc/SA00024NY): Installation of Airwolf remote mounted engine oil filter kit AFC-K007 on single or multi-engine fixed wing light aircraft incorporating Lycoming reciprocating engines of 450 horsepower or less.. Airwolf Filter Corporation - [STC SA00433NY](https://openairdocs.org/stc/SA00433NY): Installation of Airwolf remote mounted engine oil filter model AFC-500 or AFC-600 on multi engine fixed wing light aircraft incorporating Franklin reciprocating engines of 450 horsepower or less.. Airwolf Filter Corporation - [STC SA01933LA-D](https://openairdocs.org/stc/SA01933LA-D): Installation of Garmin Model 400W / 500W Series GPS-WAAS Navigation System. Garmin International Inc - [STC SA02212AK](https://openairdocs.org/stc/SA02212AK): Replacement of existing landing and/or taxi light reflector and bulbs with high intensity discharge (HID) lighting systems. Seaplanes North LLC - [STC SA00382BO](https://openairdocs.org/stc/SA00382BO): Installation of Globalstar Antenna and Cradle provisions to support a Globalstar GPS-1700 in non-composite airplanes. Avidyne Corporation - [STC SA02428SE](https://openairdocs.org/stc/SA02428SE): Installation of an Air Stream Switch for an electric time recording device on non-pressurized aircraft. Henry F Rogers/David E Polley - [STC SA00343BO](https://openairdocs.org/stc/SA00343BO): Installation of a single configuration or a dual configuration Avidyne Corporation Integrated Flight Display, Model IFD540 loaded with Release 10.0 software (or later FAA approved release). Avidyne Corporation All 106: https://openairdocs.org/tcds/7A14/stcs.md --- OpenAirDocs.org is an independent research project of [Contrail Labs](https://contraillabs.com/). It is not affiliated with the FAA or the NTSB. Source documents are U.S. government works in the public domain.