# TCDS A-306: Monocoupe Corporation - Type: Type certificate data sheet - Status: Current - Holder: Monocoupe Corporation - Revision: 12 - Revised: October 25, 2011 - Product: Aircraft, Small Airplane - Registered aircraft: 63, by the registry models matched to it (OpenAirDocs) - Data sheet PDF: https://openairdocs.org/files/sha256/38/ea/38eabaeb49c0fffef5c1c9a6b53bcdf99faea8183169bcc494c90875280ea853 - FAA DRS: https://drs.faa.gov/browse/excelExternalWindow/067AAE6C32B6FD1986257936004B82CA.0001 - Page: https://openairdocs.org/tcds/A-306 ## Models (5) As the data sheet lists them. - 90A - 90 - 90AF - 90AF-100 - 90AL-115 ## 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 Rev. No. 12 8 8 8 8 8 8 DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION A-306 Revision 12 Monocoupe 90 90A 90AF 90AF-100 90AL-115 October 25, 2011 TYPE CERTIFICATE DATA SHEET NO. A-306 This data sheet which is part of Type Certificate No. A-306 prescribes conditions and limitations under which the product for which the type certificate was issued meets the airworthiness requirements of the Federal Aviation Regulations. Type Certificate Holder: Monocoupe Corporation 2211 South Grand Blvd Unit #302 St. Louis, MO 63104 I. Model 90, 2-PCL-SM, Approved April 2, 1930 Engine Lambert R-266 Engine Limits For all ope rations, 2375 r.p.m. (90 hp) Airspeed Limits Not available Propeller Limits Not available C.G. Range (+15) to (+17.8) Empty Weight C.G. Range None Maximum Weight Landplane: 1585 lbs. Seaplane: 1580 lbs. No. Seats 2 (+27) Maximum Baggage Landpl ane: 52 lbs. (+47) Seaplane: 12 lbs. (+47) Fuel Capacity 28 gal (+22) (14–gal. tank in each wing) Oil Capacity 2½ gal (-11) Serial No. Eligible Landplane: 500 to 661, inclusive Seaplane: 547 to 661, inclusive Required Equipment Landplane: Items 4, 201(a), 203, 205(b) Seaplane: Items 4, 207(a) II. Model 90A, 2-PCL-SM, Approved April 2, 1930 (Similar to Model 90 except revised fuselage structure, control system, wing flaps, and other minor changes) Engine Lambert R-266 Engine Limits For all ope rations, 2375 r.p.m. (90 hp) Airspeed Limits Flaps extended: 100 m.p.h. CAS Propeller Limits Landplane: Maxi mum permissible diameter: 81 in. Seaplane: Not available C.G. Range Landplane: (+15.2) to (+21.7) Seaplane: (+17.6) to (+19.5) Empty Weight C.G. Range La ndplane: (+14.0) to (+19.4) Seaplane: (+17.1) to (+17.5) When Empty Weight C.G. falls within this range, computation of critical fore-and-aft C.G. positions is unnecessary . Range is not valid for non-standard arrangements. A-306 Rev. 12 2 II. Model 90A, 2-PCL-SM (cont’d) Maximum Weight Landplane: 1610 lbs. Seaplane: 1771 lbs. No. Seats 2 (+25) Maximum Baggage Landplane: 76 lbs. Seaplane: 35 lbs. Fuel Capacity 28 gal (+22) (14–gal. tank in each wing) Oil Capacity 2½ gal (-17) Serial No. Eligible A-662 and up Required Equipment Landplane: Items 4, 101(b) or (c), 201(a), 203, 205(a) Seaplane: Items 4, 101(b), 102(b), 207(b), 301(a) (Seaplane type also must have control stops per Edo Dwg. 47-S-029 installed in addition to fuselage reinforcements. Elevator up movement 15 degrees and rudder movement 16 de grees from centerline of airplane). III. Model 90AF, 2-PCLM, Approved 1942 (Similar to Model 90A except engine installation, control system, and minor revisions) Engine Franklin 4AC-199-E3 Engine Limits For all ope rations, 2500 r.p.m. (90 hp) Airspeed Limits (CAS) Leve l flight or climb 130 m.p.h. Glide or dive 156 m.p.h. Flaps extended 100 m.p.h. Propeller Limits Static r.p.m. at maximum permissible throttle setting: Not more than 2100, not less than 2000 (No additional tolerance permissible) Diameter: Not more than 74 inches, not less than 72 inches C.G. Range (+16.5) to (+18.6) (Rearmo st C.G. limit with baggage is +20) Empty Weight C.G. Range (+15.5) to (+16.7) (with or without baggage) When Empty Weight C.G. falls within this range, computation of critical fore-and-aft C.G. positions is unnecessary . Range is not valid for non-standard arrangements. Maximum Weight 1610 lbs. No. Seats 2 (+25) Maximum Baggage 76 lbs. (+47) Fuel Capacity 28 gal (+22) (14–gal. tank in each wing) Oil Capacity 2 gal (-28) Serial No. Eligible A-816 and up Required Equipment Items 4, 101(d), 102(c), 103( a), 104, 106(a), 201(b), 204(a) or (b), 205(d), 301(c), 302(b) IV. Model 90AF-100, 2-PCLM, Approved September 17, 1948 (Similar to Model 90AF except engine installation, cowling, main landing gear wheels and minor changes) Engine Franklin 4A4-100-B3 Fuel 80 minimum-octane aviation gasoline Engine Limits For all ope rations, 2550 r.p.m. (100 hp) Airspeed Limits (CAS) Leve l flight or climb 130 m.p.h. Glide or dive 156 m.p.h. Flaps extended 100 m.p.h. C.G. Range (+15.8) to (+19.2) or (+15.8) to (+21.7) provided airplane is placarded: “INTENTIONAL SPINS PROHIBITED” Empty Weight C.G. Range None Maximum Weight 1610 lbs. No. Seats 2 (+25) Maximum Baggage 76 lbs. (+47) Rev. 12 A-306 3 IV. Model 90AF-100, 2-PCLM (cont’d) Fuel Capacity 28 gal (+22) (14–gal. tank in each wing) Oil Capacity 2 gal (-29.5) Control Surface Movements Elevator 22 degrees up 26.5 degrees down Aileron 16 degrees up 20 degrees down Rudder 22 degrees right and left Flaps 27 degrees down Serial No. Eligible 861 and up Required Equipment Items 1, 201(d), 202, 204(c) V. Model 90AL-115, 2-PCLM, Approved September 17, 1948 (Similar to Model 90AF except engine installation, cowling, main landing gear wheels and minor changes) Engine Lycoming O-235-C1 Fuel 80 minimum-octane aviation gasoline Engine Limits Maximum c ontinuous 2600 r.p.m. (108 hp) Take-off (One minute) 2800 r.p.m. (115 hp) Airspeed Limits (CAS) Leve l flight or climb 130 m.p.h. Glide or dive 156 m.p.h. Flaps extended 100 m.p.h. C.G. Range (+15.8) to (+18.7) or (+15.8) to (+21.7) provided airplane is placarded: “INTENTIONAL SPINS PROHIBITED” Empty Weight C.G. Range None Maximum Weight 1610 lbs. No. Seats 2 (+25) Maximum Baggage 76 lbs. (+47) Fuel Capacity 28 gal (+22) (14–gal. tank in each wing) Oil Capacity 2 gal (-24.5) Control Surface Movements Elevator 22 degrees up 26.5 degrees down Aileron 16 degrees up 20 degrees down Rudder 22 degrees left 22 degrees right Flaps 27 degrees down Serial No. Eligible 861 and up Required Equipment Items 1, 201(d), 202, 204(c) SPECIFICATIONS PERTINANT TO ALL MODELS Datum Wing leading edge Leveling means Lower surface of wing between spars, 12 inches outboard of root section Certification basis Type Certificate 306 (M odels 90, 90A and 90AF based on Aeronautics Bulletin 7-A, Models 90AF-100 and 90AL-115 based on Aeronautics Bulletin 7-A and CAR 4a) Production basis None 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 Lbs. 90 90A 90AF 90-AF-100 90-AL-115 1. Propeller: Sensenich 72TM50 or any other 11 --- --- --- (-42) (-43) fixed-pitch wood propeller rated for required hp and r.p.m. with following limits: Model 90AF-100: static r.p.m., not over 2110, not under 2010 Diameter: not over 72 in., not under 70 in. Model 90AL-115: static r.p.m., not over 2050, not under 1950 Diameter: not over 72 in., not under 70 in. (No additional tolerance on static r.p.m. limits permitted.) A-306 Rev. 12 4 SPECIFICATIONS PERTINANT TO ALL MODELS (cont’d) Propellers and Propeller Accessories (cont’d) Lbs. 90 90A 90AF 90-AF-100 90-AL-115 2. Propeller: Automatic Controllable 21 --- --- --- (-43) ---- Koppers Aeromatic F200/0074E, Parts list and assem. No. 4283. Low-pitch setting 11.4 at 24-in sta. Static r.p.m. at max. permissible throttle setting: not over 2550, not under 2450. No additional tolerance permitted. Diameter: not over 74 in., not under 72.5 in. (Adjustment of counter-weights and flight r.p.m. must be done as stipulated in Koppers “Installation Procedures and Operating Limitations.” Compliance with paragraph ‘E’ of above is mandatory for operation below base elevation for which counterweights were la st set. Adjustments For higher altitudes are optional.) 3. Propeller: 2-position controllable 18 --- --- --- ---- (-45) Sensenich C-2FM4/PC276A6-2. Pitch setting measured at 27.75 in. sta.: Low 9.7 degrees, high 15 degrees. Diameter: not over 74 in., not under 72.5 in. 4. Propeller: fixed-pitch wood 22 eligible eligible --- ---- ---- 11 --- --- (-43) ---- ---- 5. Propeller: adj. metal (Ham. std. hub 7029, 13 eligible eligible --- ---- ---- blades 25V2). 6. Propeller: adj. wood (Freedman-Burnham 8 --- eligible --- ---- ---- hub PC203, blades P203-78). 7. Propeller: fixed-pitch metal, 19 --- --- --- ---- (-43) McCauley 1S110-GF-7650: Static r.p.m. at max, permissible throttle setting: not over 2150, not under 2050. No additional tolerance permitted. Diameter: not over 76 in., not under 74.5 in. 8. Propeller: McCauley, fixed-pitch metal, 13 --- --- --- ---- (-43) Model 1090-LM Static r.p.m. at max, permissible throttle setting: not over 2200, not under 2150. No additional tolerance permitted. Diameter: not over 72 in., not under 70.5 in. Engine and Engine Accessories: Fuel and Oil System Lbs, 90 90A 90AF 90-AF-100 90-AL-115 101. Engine ring cowl a) Plain 9 eligible --- --- ---- ---- b) Cup type 15 --- eligible --- ---- ---- c) Tunnel type (for serial nos. below A-699) 15 --- eligible --- ---- ---- d) Dwg. 367 15 --- --- (-28) ---- ---- Rev. 12 A-306 5 Engine and Engine Accessories: Fuel and Oil System (cont’d) Lbs. 90 90A 90AF 90-AF-100 90-AL-115 102. Starter a) Electric 19 eligible --- --- ---- ---- b) Eclipse Y - 150 19 --- (-14) --- ---- ---- c) Autolite MBG 4009 15 --- --- (18) ---- ---- d) Delco-Remy 1109651 16 --- --- --- (-17) eligible e) Delco-Remy 1109657 17 --- --- --- ---- (-27) 103. Carburetor Heater 5 --- --- (-28) ---- ---- a) Dwg. 367 right 5 --- --- (-28) ---- ---- b) Dwg. 2002A, 2005A --- --- --- --- eligible ---- c) Dwg. 3002, 3005 --- --- --- --- eligible ---- 104. Oil Cooler (Harrison HE 212) 5 --- --- (-28) ---- ---- 105. Engine compartment ventilator tube 1 --- eligible --- ---- ---- 106. Cabin Heater 2 --- eligible --- ---- ---- a) Dwg. 367 left 4 --- --- (-28) ---- ---- 107. Dual Throttle Control 2 --- eligible --- ---- ---- 30 gal. fuel capacity (15 gal. tank in ea wing) --- eligible --- --- ---- ---- 14.5 gal. auxiliary fuel tank installation 11 --- --- (+47) ---- ---- (Rearward C.G. of +20 may be used and following placard required: a) Use in level flight only b) No baggage may be carried c) Tank valve ‘OFF’ when not in use d) Empty auxiliary tank first e) No intentional acrobatics f) Drain daily through sediment bowl Landing Gear Lbs. 90 90A 90AF 90-AF-100 90-AL-115 201. Wheels a) 6.50 – 10 with brakes and 6.50 – 10 tires 60 eligible (+5) --- ---- ---- b) 18x18 – 3 with brakes 29 eligible (+5) --- ---- ---- and tires 36 --- --- (+5) ---- ---- c) 21 in. streamline with brakes and tires 54 --- (+5) --- ---- ---- d) 6.00 – 6 Type III Firestone Model 16 --- --- --- (+5) (+5) 6C5YFB with brakes 202. 2 main-wheel 4-ply rating tires, 18 --- --- --- (+5) (+5) 6.00 – 6 Type III, with regular tubes (for use with item 201(d)) 203. Tail Skid --- eligible eligible --- ---- ---- 204. Tail Wheels a) 3 3/8 in. diameter – fixed 1 eligible eligible eligible ---- ---- or swivel 3 --- --- --- (+180) (+180) b) Steerable, 3 3/8 inch 2 --- eligible eligible ---- ---- diameter 3 --- --- --- (+180) (+180) c) 6 in. full-swiveling – steerable (Maule Co.) 2 --- --- (+192) (+192) (+192) A-306 Rev. 12 6 Landing Gear (cont’d) Lbs. 90 90A 90AF 90-AF-100 90-AL-115 205. Landing Gears a) ‘Type F’ (Cantilever with shock cord 14 e ligible eligible --- ---- ---- and tread of approx. 66 in.) b) With oleo shock struts (approx. 66 in . --- eligible --- --- ---- ---- tread) c) ‘Optional Type F’ (Cantilever with shock 7 --- eligible --- ---- ---- cord and wide tread of approx. 78 in.). For use with 21 in. streamline or 6.50 – 10 wheels only) d) ‘Type C’ (similar to ‘Optional Type F’ 7 --- eligible eligible ---- ---- except for special axle – for use with 18x18 – 3 wheels only). 206. Wheel Streamlines 25 eligible --- --- ---- ---- a) For use with item 205(c) only 22 --- eligible --- ---- ---- b) For use with item 205(d) only 17 --- eligible --- ---- ---- c) Per Dwg. F-30520 15 --- --- (+5) (+5) (+5) 207. Floats a) Edo H. Large – type tail surfaces --- eligible --- --- ---- ---- required with this item. Large fin has two brace wires on each side, rudder has overall height of 54 3/8 in. and stabilizer has no sweepback of leading edge. b) Edo 47 – 1965, with water rudder. 273 --- eligible --- ---- ---- Seaplane fin (+2 lb) under fuselage is required with this item. 208. Skis (use actual weight) a) Washington Aircraft 1625 --- --- eligible --- ---- ---- b) Alaska Airmotive 3 --- --- eligible --- ---- ---- Electrical Equipment Lbs. 90 90A 90AF 90-AF-100 90-AL-115 301. Batteries 35 (-10) --- --- ---- ---- a) Exide 6-AC7-1 17 --- (-10) --- ---- ---- b) Exide 6TS-7-1 27 --- (-10) --- ---- ---- c) Reading R24L 24 --- --- (-13) (-14) (-18) 302. Generators a) Wind-driven, mounted under fuselage 7 --- (+7) --- ---- ---- b) Autolite GDY4106, 10 amp 12 --- --- (-18) ---- ---- c) Delco-Remy 17556 16 --- --- --- (-17) ---- d) Delco-Remy 110878 10 --- --- --- ---- (-29) 303. Landing Lights a) Pyle National, LAN605, one or two 7 --- (+3) (+3) ---- ---- in wing leading edge each b) Grimes ST-250, one or two each 4 --- (+14) (+14) ---- ---- c) Two Grimes ST-250 9 --- --- --- (+14) (+14) Rev. 12 A-306 7 Interior Equipment Lbs. 90 90A 90AF 90-AF-100 90-AL-115 401. Three 1 ½ min. flares, International MK-1 17 --- (+72) (+72) (+72) (+72) 402. Golf Compartment (opening into baggage 3 --- (+60) (+60) ---- ---- compartment) (Max. capacity 20 lbs. Weight of baggage carried in golf compartment must be included in total baggage as originally placarded) 403. Dual wheel control (Monocoupe Dwg. 353) --- --- eligible --- ---- ---- 404. Extra door on left side --- --- eligible --- ---- ---- NOTE 1 Current weight and balance report including list of e quipment included in certificated weight empty, and loading instructions when necessary, must be in each aircraft at the time of original certification and at all times thereafter. NOTE 2 The following placards must be displayed on models indicated: (a) On all models, on instrument panel in full view of the pilot: “INTENTIONAL ACROBATICS WITH BAGGAGE PROHIBITED” (b) On Models 90AF-100 and 90AL-115 at each fuel valve: “WHEN THIS VALVE IN ON, OTHE R VALVE MUST BE TURNED OFF” (c) On Models 90AF-100 and 90AL-115 at fuel tank drain valves: “DRAIN SEDIMENT DAILY” (d) On Models 90AF-100 and 90AL-115 on instrument pane l in full view of pilot when C.G. range of (+15.8) to (+21.7) is utilized: “INTENTIONAL SPINS PROHIBITED” ...END... ``` ## ADs None name its models. ## Registered aircraft by registry model (OpenAirDocs) - [Monocoupe 90A](https://openairdocs.org/model/monocoupe-90a): 41 aircraft (registry code 5810104) - [Monocoupe 90](https://openairdocs.org/model/monocoupe-90): 11 aircraft (registry code 5810102) - [Monocoupe 90AL-115](https://openairdocs.org/model/monocoupe-90al-115): 6 aircraft (registry code 5810110) - [Monocoupe 90AF](https://openairdocs.org/model/monocoupe-90af): 4 aircraft (registry code 5810107) - [Monocoupe 90AF-100](https://openairdocs.org/model/monocoupe-90af-100): 1 aircraft (registry code 5810108) ## STCs approved under this data sheet (25) - [STC SA04652CH](https://openairdocs.org/stc/SA04652CH): To allow use of 100R grade aviation fuel meeting Swift Fuel, LLC specification. Swift Fuels LLC - [STC SA00081NY](https://openairdocs.org/stc/SA00081NY): Installation of Iceman Aviation Supplies, Inc. Carburetor Ice Detector.. Alcor LLC - [STC SA7965SW](https://openairdocs.org/stc/SA7965SW): Application of fabric and polyurethane finishing system.. Shady Aviation LLC - [STC SA02594SE](https://openairdocs.org/stc/SA02594SE): SkyView HDX Instrumentation and Autopilot System manufactured. Dynon Avionics - [STC SA01757WI](https://openairdocs.org/stc/SA01757WI): To allow the use of UL91 or UL94 (minimum) grade aviation fuel. Swift Fuels LLC - [STC SA4503NM](https://openairdocs.org/stc/SA4503NM): Remove original cloth covering and install Ceconite covering. Ceconite Division of Poly-Fiber Inc. - [STC SA01967WI](https://openairdocs.org/stc/SA01967WI): Use of GAMI G100UL High Octane Unleaded Avgas. General Aviation Modifications Inc. - [STC SA04776NY](https://openairdocs.org/stc/SA04776NY): The HIPEC Covering and Finishing System must be performed and maintained. HIPEC Aircraft Coatings Inc. - [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 SA01734SE](https://openairdocs.org/stc/SA01734SE): Application of Stewart Systems synthetic fabric covering system to aircraft fuselage, wings, tail surfaces, control surfaces and related parts.. Andrew D. Humphrey - [STC SA00478CH](https://openairdocs.org/stc/SA00478CH): Installation of Cooper Superflite 102 Fabric.. Aviation Products Systems Inc. - [STC SA593CH](https://openairdocs.org/stc/SA593CH): Install Champion SlickSTART magneto booster system.. Champion Aerospace LLC - [STC SA8075SW](https://openairdocs.org/stc/SA8075SW): Installation of fiberglass covering. (M-62 SERIES PT-19) (G-73 SCHWEIZER). Razorback Fabrics Inc - [STC SA1008WE](https://openairdocs.org/stc/SA1008WE): Installation of Poly-Fiber covering material.. Poly-Fiber Inc. - [STC SA489EA](https://openairdocs.org/stc/SA489EA): Installation of ARP Inc. carburetor ice detection system. Aircraft & Rotorcraft Products (ARP) Inc - [STC SA2-952](https://openairdocs.org/stc/SA2-952): Installation of fiberglass covering.. Razorback Fabrics Inc - [STC SA5159NM](https://openairdocs.org/stc/SA5159NM): Installation of chip detector system.. Northwest Aircraft Inc - [STC SA1351WE](https://openairdocs.org/stc/SA1351WE): Replace existing fabric on wings, fuselage, empennage, and/or control surfaces, with Ceconite101 material. (262A Series -12). Ceconite Inc - [STC SA1617NM](https://openairdocs.org/stc/SA1617NM): Installation of a Lycoming engine, sensenich propeller, engine mount, Monocoupue cowling, two six gallon auxilliary wing tanks, modified frieze style ailerons, wing flap removal. Max R. Curry - [STC SA308EA](https://openairdocs.org/stc/SA308EA): Installation of carburetor ice detection system 105AP in single and twin engine aircraft and single engine helicopters powered by Continental, Franklin, and Lycoming type engines equipped with Marvel-Schebler MA-2, MA-3, MA-4, MA-4-5, MA-6 and HA-6 series carburetors. (Normal,Utility and Acrobatic Category airplanes and helicopters equipped with engines and carburetors as described.). Alfred R Puccinelli - [STC SA387NW](https://openairdocs.org/stc/SA387NW): Installation of a Warner Super Scarab series 50A engine and engine mount; fiber glass cowling; 3 inch longer landing gear; a model 90 wing; and a Universal (Koppers) 220/0-85 propeller. Ludke, Frederick E. II - [STC SA1071CE](https://openairdocs.org/stc/SA1071CE): Installation of Lycoming IO-320-E1A engine modified per STC SE7CE and Hartzell propeller HC-C2YL-4 with modification of existing fuel system by addition of header tank and associated fuel system changes.. Smith Murlin Gene - [STC SA4-1024](https://openairdocs.org/stc/SA4-1024): Ceconite 101 covering of complete airplane.. Cooper Engineering Corporation - [STC SA001410BO](https://openairdocs.org/stc/SA001410BO) (historical): Installation of an AV-30-C Multi-Mode Indicator. uAvionix Corporation --- 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.