# TCDS 4A15: Mitchell Trimotor Aircraft Corporation - Type: Type certificate data sheet - Status: Current - Holder: Mitchell Trimotor Aircraft Corporation - Revision: 7 - Revised: June 23, 2009 - Product: Aircraft, Small Airplane - Certification basis: CAR 3 - Data sheet PDF: https://openairdocs.org/files/sha256/9e/88/9e88513b3e304f95902d8290caa94f61f49e8c552c9e32510f689d545908e3cd - FAA DRS: https://drs.faa.gov/browse/excelExternalWindow/590E4996CD41B1B0862575E40047218E.0001 - Page: https://openairdocs.org/tcds/4A15 ## Models (2) As the data sheet lists them. - Centaur 101 - Centaur 102 ## 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 Rev. No. 7 6 6 6 6 6 DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION 4A15 Revision 7 MITCHELL (L-13) Centaur 101 Centaur 102 June 23, 2009 TYPE CERTIFICATE DATA SHEET NO. 4A15 Type Certificate Holder Mitchell Trimotor Aircraft Corporation c/o Unipunch Products, Inc. 527 3 rd Avenue PO Box 17 Clear Lake, Wisconsin 54005 Type Certificate Holder Record Consolidated Vultee Aircraft Corporation transferred type certificate (TC) to Leasair Incorporated February 6, 1962 Leasair Incorporated transferred TC to Paul C. Mitchell, Jr. November 5, 1962 Paul C. Mitchell, Jr. transferred TC to Mitc hell Trimotor Aircraft Corporation July 12, 1965 I. - Model Centaur 101 (Longren L-13), 4 PLCM (Normal Category), Approved May 16, 1956 Engine Lycoming R-680-E3 Series Fuel 87 min. grade aviation gasoline Engine Limits Takeoff (Two minutes), 2300 rpm (300 hp) All other operations, 2200 rpm (285 hp) Airspeed Limits Maneuvering 114 mph ( 99 Knots) Design Cruising 118 mph (102 Knots) Never Exceed 150 mph (130 Knots) Flap Speed 89 mph ( 77 Knots) C. G. Range (+106.8) to (+117.0) Empty Weight C.G. Range None Maximum Weight 3550 lb. Number of Seats 4. Two at (+107) and two at (+151) Maximum Baggage 159 lb. (+192) Fuel Capacity 112.5 gallon total and usable. Two wing tanks, 52.5 gallons each (+121), one header tank in fuselage, 7.5 gallons (+118) . 60.0 gallons total and usable for airplanes with a single 52.5 gallon wing tank and the 7.5 gallon header tank. Oil Capacity 5 gallons (+52) Control Surface Flaps 35° Down Movements Elevator 32° Up 20° Down Elevator Tab 20° Up 14° Down Aileron 30° Up 30° Down Aileron Tab Left Side 21° Up 21° Down Rudder 11" Right 11" Left Rudder Tab 1.5" Right 1.5" Left Serial Numbers Eligible Consolidated Vultee Aircraft Corp. Serial numbering retained. All C.V.A.C. military models L-13 series aircraft when modified in accordance with Centaur Aircraft Company approved data. Required Equipment In addition to the pertinent required basic equipment specified in CAR 3, the following items of equipment must be installed: Items 1(a), 1(b), 102, 103, 201(a), 205, 301, 302, 303 and 304. II. - Model Centaur 102, 6 PLCM (Normal Category), Approved September 29, 1961. Same as Model 101 except for engine installation and interior arrangement. Engine Jacobs R-755-A2 Fuel 80 min. grade aviation gasoline Engine Limits All operations 2200 rpm (300 hp.) Airspeed Limits Maneuvering 114 mph ( 99 Knots) (True Ind.) Design Cruising 118 mph (102 Knots) Never Exceed 150 mph (130 Knots) Flap Speed 89 mph ( 77 Knots) C.G. Range (+106.8) to (+117.0) Empty Weight C.G. Range None. Maximum Weight 3550 lbs. Number of Seats 6. Two at (+101) and two at (+133) and two at (+163) Maximum Baggage 159 lb. (+188.5) Fuel Capacity 60 U.S. gallons total and usable. One wing tank, 52.5 gallons (+121), and one header tank in fuselage 7.5 gallons (+118). Oil Capacity 6.5 gallons (+101.8) Control Surface Flaps 35° Down Movements Elevator 32° Up 20° Down Elevator Tab 20° Up 14° Down Aileron 30° Up 30° Down Aileron Tab Left Side 21° Up 21° Down Rudder 11" Right 11" Left Rudder Tab 1.5" Right 1.5" Left Serial Numbers Eligible Consolidated Vultee Aircraft Corp. Serial numbering retained. All C.V.A.C. military models L-13 series aircraft when modified in accordance with Centaur Aircraft Company approved data. Required Equipment In addition to the pertinent require d basic equipment specified in CAR 3, the following items of equipment must be installed: Items 1(c), 1(d), 103, 104, 105, 201(a), 205, 304, 306 , 307 and 308. SPECIFICATIONS PERTINENT TO ALL MODELS Datum 86.5 in. forward of win leading edge. (Fuselage Station 0) Leveling Means Use plane of cabin floor. Certification Basis Type Certificate No. 4A15 (CAR 3), 1949, Amendments 1 through 14. Page 3 of 6 4A15 Production Basis None. Prior to original certification of ai rcraft converted in the United States, a FAA representative must perform a detailed inspection for workmanship, materials, and conformity with the approved technical data and a check of the flight characteristics. Equipment A plus (+) or minus (-) sign preceding the weight of an item indicates net weight change when that item is installed. Propellers and Propeller Accessories 1. Propeller (a) Ham. Std. hub 2B20 with 6135A-6 to 6135A-10 blades 105 lb. (+18) Diameter Limits: Max. 8'2". No further reduction permitted. Pitch Setting at 42" station: with 6135A-6, -7 and -8 blades 19° High, 6½° Low with 6135A-9 and -10 blades 19° High, 8° Low and (b) Ham. Std. constant speed governor, 1M12 4 lb. (+24) (c) Ham. Std. hub 2B20 with 6135-15. -16 blades. Diameter Limits: Max. 93", Mi n. allowable for repairs 91-1/8". No further reduction permitted. Pitch Setting at 42" station: 10. 3° to 12° low, 25.3° to 27° high. and (d) Propeller governor, Hamilton Model 1A4G5. Engine and Engine Accessories - Fuel and Oil System 101. Starter electrical, Eclipse Type E80 20 lb. (+53) 102. Fuel pump engine driven, Thom pson Type AM-4100 2.5 lb. (+45) 103. Fuel pump wobble, hand D2, Model TDF-400-1 3 lb. (+66) 104. Vacuum pump, Pesco Type B-2A 4 lb. (+55) 105. Fuel pump, Pesco Mode l No. 2P-R400 Romec RD-4140 Landing Gear 201. 2 Main wheel-brake assemblies, 27 in. Type I (SC) (a) Hays Model G31A, 6 or 8-ply tires 127 lb. (+86) 205. 1 Tail wheel, 10 in. 6-ply smooth contour 6 lb. (+356) Electrical Equipment 301. Generator, Bendix Type N-75-2SB 24 lb. (+51) 302. Regulator, Bendix Model 17 style "A" 2 lb. (+72) 303. Reverse current relay, AN3025-1 1 lb. (+65) 304. Battery 24 volt, 12AC7D 34 lb. (+195) 305. Landing Lights, GE4523 1 lb. (+95) 306. Generator, Leece Neville L3 24V 35 AMP 307. Reverse current relay, AN3025-1 308. Voltage regulator, Eclipse 1042-7A or AN3206 NOTE 1. Current weight and balance report including list of equipment included in certificated empty weight, and loading instructions when necessary, must be in each aircraft at the time or original certification and at all times thereafter (except in the case of air carrier operators having an approved weight control system). NOTE 2. The following placards must be displayed: A. For Model 101: (a) On instrument panel in full view of the pilot: (1) "This airplane must be operated as a normal category airplane in compliance with FAA approved operating limitations in the form of instruction markings and placards. No acrobatic maneuvers including spins approved." (b) Below airspeed indicator: (1) "Maneuvering speed 114 mph." (c) In baggage compartment: (1) "Maximum baggage allowable 159 lb." (d) On left door panel or readily visible: "Maximum Weight and C.G. Range" Maximum weight 3550 lb. Most Fwd., C.G. +106.8" from datum Most Aft, C.G. +117.0" from datum Datum is 86.5" fwd of wing leading edge. Airspeed Limits Vne Maximum glide or dive 150 mph. TIAS Vc Maximum design cruising speed 118 mph. Vp Maneuvering Speed 114 mph. Vf Maximum flap down speed 89 mph. Maneuvering Load Factors Do not exceed 3.8 load factor flaps up Do not exceed 1.9 load factor flaps down Instrument Marking Red Radial -- Maxi mum or minimum allowable Yellow Arc -- Cautionary range Green Arc -- Normal operating range White Arc -- Flap operating range Engine and Propeller Limits Engine Lycoming R-680-E3 Series Maximum power S.L. 300 BHP at 2300 RPM full throttle 2 min. Maximum continuous power 285 BHP S.L. at 2200 RPM 28.0" Hg. Maximum cylinder temperature (head) 525°F or 274°C. Oil capacity 5 US gallons Maximum oil temperature 200°F. or 93°C. Propeller Ham. Std. 2B20 with 6135A-6 to 6135A-10 blades Diameter Limits: 8' 6" max., 8' 2" min. Pitch settings at 42" station: With 6135A-6, -7 and -8 blade 19° High, 6 ½° Low With 6135A-9 and -10 blade 19° High, 8° Low Page 5 of 6 4A15 Fuel System Use 87 Octane minimum grade aviation fuel. Fuel system consists of 2 fuel tanks, one in each wing, with a capacity of 52.5 gallons each. One header tank in fuselage, 7 ½ U.S. gallon, fed directly by the wing tanks. The total usable fuel is 112.5 U.S. gallon. If airplane is equipped with one wing fuel tank, the total usable fuel will be 52.5 gallons plus 7 ½ gallons in header tank or 60 U.S. gallon. NOTE - Fuselage tank (7 ½ gallons) is not gauge d. When fuel level is below 7½ gallons in fuselage tank a red light on the instrument panel will come on. Switch to opposite wing tank provided there is fuel remaining in tank. WARNING - Should red light fail to go out or no fu el remains in wing tanks, land as soon as practical as there is approximately 16 minutes fuel remaining in the aircraft at M.C. power. Baggage Compartment Do not exceed 159 lb. at station 192. B. For Model 102: (a) On instrument panel in full view of the pilot: "This airplane must be operated as a normal category airplane in compliance with FAA approved operating limitations in the form of instruction markings and placards. No acrobatic maneuvers including spins approved." (b) Below airspeed indicator: "Maneuvering speed 114 mph." (c) In baggage compartment: (1) "Maximum baggage allowable 159 lb." (d) On left door panel or readily visible: "Maximum Weight and C.G. Range Maximum weight 3350 lb. Most Fwd., C.G. +106.8" from datum Most Aft, C.G. +117.0" from datum Datum is 86.5" fwd. of wing leading edge. Airspeed Limits Vne Maximum glide or dive 150 mph TIAS Vc Maximum desi gn cruising speed 118 mph. Vp Maneuvering speed 114 mph. Vf Maximum flap down speed 89 mph. Maneuvering Load Factors Do not exceed 3.8 load factor flaps up Do not exceed 1.9 load factor flaps down Instrument Marking Red Radial -- Maxi mum or minimum allowable Yellow Arc -- Cautionary range Green Arc -- Normal operating range White Arc -- Flap operating range Engine and Propeller Limits: Engine Jacobs R755 A2 Max. power, S.L. = 300 bhp at 2200 rpm, full throttle Max. continuous power, S.L. = 300 bhp at 2200 rpm, full throttle Max. Cyl. Hd Temp. = 500 deg F (260 deg C) Max. Oil Temp. = 200 deg F (93 deg C) Oil capacity - 6.5 US gallon Prop = Ham. Std. 2b20 Hub, 6135A Blade, 7' 7-1/8" to 7' 9" diameter Stops set for 10.3 to 12 deg low, 25.3 to 27 deg high pitch. Measured at 42 inch station. Fuel System Use 80 octane minimum grade aviation fuel Fuselage stump tank (7 ½) is not gauged. When Fuel Low Level Warning Light on instrument panel lights (red), fuel is below 7½ gallons. Should red light fail to go out, or no fuel remains in wing tank(s), land as soon as practical as there is approximately 16 minutes fuel remaining at METO power. Baggage Compartment Do not exceed 159 lb. at station 188.5" ...END... ``` ## ADs None name its models. ## Registered aircraft by registry model (OpenAirDocs) - [Consolidated CENTAUR 101](https://openairdocs.org/model/consolidated-centaur-101): 0 aircraft (registry code 2000102) ## STCs approved under this data sheet (4) - [STC SA04652CH](https://openairdocs.org/stc/SA04652CH): To allow use of 100R grade aviation fuel meeting Swift Fuel, LLC specification. Swift Fuels LLC - [STC SA01967WI](https://openairdocs.org/stc/SA01967WI): Use of GAMI G100UL High Octane Unleaded Avgas. General Aviation Modifications Inc. - [STC SA4-980](https://openairdocs.org/stc/SA4-980): Oil tank.. Serv-Aero Engineering Inc - [STC SA66SO](https://openairdocs.org/stc/SA66SO): Removal of forward right-hand and aft left and right-hand cabin doors or any combination thereof.. Aerolist's Intl Inc --- 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.