TCDS A-791

Page No. 1 2 3 4 5 6 Rev No. 8 4 7 7 4 7 DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION A-791 Revision 8 THORP T-11 T-211 December 12, 2013 AIRCRAFT SPECIFICATION NO. A-791 Type Certificate Holder: AD Holdings, Inc. c/o Dedicated Micros Orlando 101 West Landstreet Road, Suite 200 Orlando, Florida 32824 Type Certificate Record: Type Certificate 791 issued to Thorp Aircraft Company in Van Nuys, CA on December 22, 1948 T-211 model approval issued to Thorp Aircraft Company in Burbank, CA on April 20, 1964 Reissued to Adams Industries, Inc. in Detroit, MI on July 21, 1981 Reissued to Thorp Aero Inc. in Wheelersburg, OH on August 18, 1989 Reissued to First Kentucky Bank in Sturgis, KY on May 1, 1996 Reissued to DM Aerospace Limited in WA on September 10, 1998 Reissued to AD Aerospace, Inc. in Kennesaw, GA on May 13, 2002 Reissued to AD Holdings, Inc. in Kennesaw, GA on February 18, 2004 I - Model T-11 (Thorp 11) (Normal Category), Approved December 22, 1948 Engine Lycoming O-145-B2 Fuel 73 minimum octane aviation gasoline Engine Limits For all operations, 2550 rpm (65 hp) Airspeed Limits (CAS) Maneuvering 109 mph (95 knots) Maximum structural cruising 101 mph (88 knots). Never exceed 128 mph (111 knots) Flaps extended 81 mph (70 knots) C.G. Range (+37.6) to (+42.0) Empty Weight C.G. Range (+37.5) to (+39.0). Unusable fuel (Item 105) must be included in certificated empty weight 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. Datum Forward face of lower firewall. Leveling Means Lugs in baggage compartment floor Maximum Weight 1050 lbs. No. of Seats 2 (+36) Maximum Baggage 80 lbs. A-791 2 Fuel Capacity Total - 18 gals. (+65) Unusable - 4 gals. (+65) Oil Capacity 5 qts. (-7) Control Surface Movements Elevator (measured in inches from lower rear corner of rudder to upper surface of elevator at tab hinge line) (neutral position: -6.6 + 0.2") -up 3.0 + 0.2"; down 7.6 + 0.2". Elevator tab (measured with respect to elevator) -up 29 + 1° (elevator full up); down 9 + 1° (elevator full down). Rudder - right 33 + 1°; left 33 + 1°. Aileron - up 35 + 1°; down 9 + 1°. Flaps - down 31 + 1°. Serial Nos. Eligible 3, 4 and 6 Required Equipment Items 1, 102, 104, 201, 202, 401 and 402 II - Model T-211 (Thorp 211), 2 PCLM (Normal Category), Approved April 20, 1964 Engine Continental O-200-A modified in accordance with Supplemental Type Certificate No. SE8WE Fuel 80/87 minimum grade aviation gasoline Engine Limits For all operations, 2750 rpm (100 hp) See Note 3. Airspeed Limit (CAS) Maneuvering 113 mph (98 knots). Maximum structural cruising 126 mph (109 knots) Never exceed 159 mph (138 knots) Flaps extended 81 mph (70 knots) C.G. Range (+68.7) to (+70.5) at 1270 lbs. (+65.0) to (+70.5) at 935 lbs. Straight line variation between points Empty Weight C.G. Range None Datum 77 in. forward of wing spar web Leveling Means Leveling marks installed on forward tunnel cover per Thorp Drawing No. 1118. Maximum Weight 1270 lbs. No. Seats 2 (+67) Maximum Baggage 80 lbs. (+87.2) Fuel Capacity Total - 24 gals. (+97) Unusable - 1 gal. (+82.5) Oil Capacity 6 qts. (+23.3) Control Surface Movements Elevator (measured in inches from lower rear corner of rudder to upper surface of elevator at tab hinge line) (neutral position: -6.6 + 0.2") -up 3.0 + 0.2"; down 7.6 + 0.2". Elevator tab (measured with respect to elevator) -up 29 + 1° (elevator full up); down 9 + 1° (elevator full down). Rudder - right 33 + 1°; left 33 + 1°. Aileron - up 35 + 1°; down 9 + 1°. Flaps - down 31 + 1°. 3 A-791 Serial Nos. Eligible Nos. 5, 7, Nos. 10 through 99 Required Equipment Items 2, 102, 106, 107, 201, and 202 III Model T-211 (Thorp 211), 2PCLM (Normal Category), Approved February 20, 1991 Engine Continental O-200-A modified in accordance with Supplemental Type Certificate (STC) No. SE8WE Fuel 80/87 minimum grade aviation gasoline Engine Limits For all operations, 2750 rpm (100 hp) See Note 3. Airspeed Limits (CAS) Maneuvering 113 mph(98 knots) Max. structural cruising 126 mph (110 knots) Never exceed 159 mph (138 knots) Flaps extended 113 mph (98 knots) C.G. Range (+64.2) to (+70.5) at 1270 lbs. (+63.6) to (+70.5) at 872 lbs. Straight line variation between points Empty Weight None Datum 59.15 in. forward of wing leading edge Leveling Means Leveling marks installed on forward tunnel cover per Thorp Drawing No. 1118. Maximum Weight 1270 lbs. No. Seats 2 (+65.16) Maximum Baggage 40 lbs. (+87.2) Fuel Capacity Total - 21 gals. (+94.75) Unusable - 1 gal (+82.5) Oil Capacity 6 qts. (+23.3) Control Surfaces Stabilator (measured in degrees from waterline) up 18° ± 30'; down 3° ± 1° Stabilator trim tab (measured with respect to stabilator) up 23° ± 2° with full nose down trim and stabilator up elevator full up 18° ± 30'; down 7° ± 1° with full nose up trim and stabilator down 3° ± 1° Stabilator trim tab (alternate method) measured from the top surface of trim tab with respect to waterline - up 33° ± 2° with full nose down trim and stabilator up 18° ± 30'; down 16° ± 1° with full nose up trim and stabilator down 3° ± 1° Rudder - right 32° ± 2°; left 32° ± 2° Aileron - up 34° ± 2°; down 10° ± 2° Flaps - down 20° ± 2° Serial Nos. Eligible 100 and higher (See Note 4) Required Equipment Items 3, 106, 109, 110, 111, 112, 203, 204, 306, 307, 308, 309, 310, 401, 403 Certification Basis Modifications certified to Civil Air Regulations (CAR) 3 effective May 15, 1956. A-791 4 Specifications Pertinent to all Models Certification Basis Civil Air Regulations (CAR) 03 effective November 13, 1945 Type Certificate 791, issued December 22, 1948. Date of Application for Type Certificate September 17, 1946 Production Basis None. Prior to original certification of each Model T-211, serial number 104 and subsequent, an FAA representative must perform a detailed inspection for workmanship, materials and conformity with the approved technical data and a check of the flight characteristics. See Note 4. Export Eligibility Aircraft is eligible for the issuance of Export Certificates of Airworthiness. Equipment A Plus (+) or minus (-) sign preceding the weight of an optional item indicates the net weight change between that item and the equivalent required item. Propellers and Propeller Accessories 1. Propeller (Model Thorp T-11 only) - U.S. 63T43, Sensenich 66CB42 or any other fixed pitch wood propeller rated for required hp and rpm with the following limits: 10 lbs (-19) (a) Static rpm at maximum permissible throttle setting: not over 2470, not under 2370. No additional tolerance permitted. Diameter: Not over 63 in., not under 61 in. (b) Static rpm at maximum permissible throttle setting: not over 2390, not under 2290. No additional tolerance permitted. Diameter: Not over 66 in., not under 64 in. 2. Propeller (Model Thorp T-211 only) - McCauley 1A100-MCM Static rpm at maximum permissible throttle setting: not over 2400, not under 2300. No additional tolerance permitted. Diameter: Not over 67 in. No cutoff for repairs permitted 19.5 lbs. (+8.3) 3. Propeller (Model Thorp T-211) - Sensenich 69CKS12-2-56L Propeller and bolts Propeller extension Static RPM at maximum permissible throttle setting: not over 2250, not under 2100. No additional tolerance permitted. Diameter: Not over 67 in. No cutoff for repairs permitted 24.8 lbs. (+5.3) 4.4 lbs. (+8.5) Engine and Engine Accessories - Fuel and Oil System 102. Fuel strainer - Tillotson (Bowl OW363, Cover OW453) 0.5 lbs. (-1) 104. Fuel cell (Model Thorp T-11 only) - Firestone No. 18100, Construction No. E-1024 3 lbs. (+66) 106. Oil sump installed per John W. Thorp Drawing No. 1558 and STC No. SE8WE 107. Engine driven fuel pump - AC Diaphragm type, Continental P/N 40585 2 lbs. (+3) 108. Starter - Delco-Remy P/N 1109656 or Continental 50309 16 lbs. (+23.3) 109. Fuel - Strainer - ACS 10560 110. Fuel cell - Thorp No. 1382 Firestone Construction No. E- 1425-3 111. Engine driven fuel pump - AC Diaphragm type 631391 112. Starter - Prestolite MZ - 4214 or Continental 634464 Landing Gear and Floats 201. Main landing gear wheels - Goodrich Model 451M with brakes, 5.00 -4 4-ply tires and tube (see Note under Item 202) 20.0 lbs. 5 A-791 Engine and Engine Accessories - Fuel and Oil System 202. Nose gear wheel - Thorp wheel assembly, per Drawing No. 1114 NOTE: C.G.'s of wheels (axle stations) vary with degree of shock strut extensions, as follows: Shock strut Main wheel C.G. Nose wheel C.G. Fully Extended +53.7 -3.6 Fully compressed +54.0 -1.9 203. Main landing gear wheels - Cleveland Wheel, 20-65 and brake 30-9, 5.00-5 4-ply tire and tube 204. Nose gear wheel - Cleveland Wheel 40-77, 5.00-5 4-ply tire and tube Electrical Equipment and Radio (Model Thorp T-211 only) 301. Generator, Delco-Remy 1101890 or Continental 534111 9.8 lbs. (+23.3) 302. Voltage Regulator, Delco-Remy 118736 or Continental 534112 1.7 lbs. (+37.5) 303. Battery, Rebat S-24 26.0 lbs. (+114.7) 304. Position Lights a. Grimes A1285-G-12(wing) b. Grimes A1285-R-12(wing) c. Grimes A2064-12 (tail) 1.0 lb. (+77.0) 1.0 lb. (+77.9) 0.5 lb. (+210.9) 305. Radio Skycrafters Model AMT9-AMR4 (Thorp drawing T-211*1555) 7.1 lbs. (+42.5) NOTE: Items 306, 307, 308, and 309 are standard equipment on Thorp T-211. Weights & Arms are included. 306. Alternator 60 AMP-12 volt Continental 633661 307. Voltage Regulator, Zeftronics R15200 308. Battery Rebat S-25 or Gill G-25 309. Position Lights a. Grimes A1285-G-12 (wing) b. Grimes A1285-R-12 (wing) c. Grimes A2064-12 (tail) 310. Aero Flash 178-0003 strobe light 1.37 lb. (+76.3) 311. Transponder; King KR76A 3.1 lb. (+42.6) 312. ADF; King KR87, KA44B, K1227 7.5 lb. (+105.8) 313. Marker Beacon: King KMA24 1.7 lb. .(+43.6) 314. VOR/ILS Indicator: King KI209 1.0 lb. (+45.2) 315. VOR/LOC Indicator: King KI208 1.0 lb. (+44.3) 316. NAV/COM: King KX155 5.7 lb. (+40.5) 317. LORAN: Apollo-800 2.3 lb. (+41.4) Interior Equipment 401. FAA Approved Airplane Flight Manual 402. Back cover baggage compartment (Thorp Dwg. P-735) Neglect weight 403. Back cover baggage compartment (Thorp Dwg. A-1044) Neglect weight 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 time of original certification and at all times thereafter. The certificated empty weight and corresponding center of gravity locations must include unusable fuel and oil. A-791 6 NOTE 2. The following placards must be displayed in front of and in clear view of the pilot: a. (T-11 only) "This airplane must be operated in compliance with the Operating Limitations Section of the FAA Approved Airplane Flight Manual." b. (T-11 only) "No acrobatic maneuvers including spins approved." c. (T-11 only) "Unusable fuel 4 gals.". d. (T-211) "This airplane must be operated as a normal category airplane. No acrobatic maneuvers including spins approved". NOTE 3. The engine and oil cooling of the Model T-211 with Continental O-200-A engine installed have not been investigated for more than 2500 rpm at full throttle (91 hp) in the climb. NOTE 4. The Model T-211, serial numbers 104 thru 107 built by: Venture Light Aircraft Resources, L.L.C. HCR2 Box 270 Tucson, AZ 85735 NOTE 5. Airplanes with serial numbers beginning with “TT” produced in India or “CC” produced in China are not eligible for import certification into the U.S., for example TT-001 and up, or CC-0001 and up. ...END...