TCDS A-694

DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION AIRCRAFT SPECIFICATION NO. A-694 Type Certificate Holder Type Certificate Record Holder Luscombe Aircraft Corporation 3301 Turner Road Jamestown, New York 14701 Luscombe Aircraft Corporation 842 Forest Glen Rd., #932 Twin Peaks, California 92391 Good Earthkeeping Organization, Inc. 1612 Jenks Drive Corona, California 92880 Team Luscombe, LLC 241 South Washington Street Chandler, Arizona 85225 (Transferred ownership of A-694 to Good Earthkeeping Organization, Inc. on October 21, 2011) The Don Luscombe Aviation History Foundation, Inc. P.O. Box 63581 Phoenix, Arizona 85082 Larsen Luscombe Corporation Alaska International Corporation Surety Credit Corporation Silvaire Aircraft Company Temco Aircraft Corporation I - Model 8, 2 PCLM (Normal Category), Approved August 11, 1938 Engine Continental A-50-1 (see item 126A for optional engines). Not eligible for original certification with single ignition engine Fuel 73 minimum octane aviation gasoline Engine limits For all operations, 1900 r.p.m. (50 hp.) Propeller limits Maximum permissible diameter, 79in. Airspeed limits Level flight or climb 115 m.p.h. (100 knots) True Ind. Glide or dive 145 m.p.h. (126 knots) True Ind. C.G. range (+13.6) to (+18.4) Empty weight C.G. range Forward limits (+13.8) with item 105. (+13.4) with items 105 and 106. (+12.3) with items 101 and 105. (+15.9) with items 102. (+14.8) with items 101 and 102. When empty weight C.G. falls within pertinent range, computation of critical fore and aft C.G. positions in unnecessary. Ranges are not valid for non-standard arrangements except as noted. Maximum weight 1200 lb. No. of seats 2 (+20) Maximum baggage 55 lb. (+40) Fuel capacity 14 gal. (+40). See items 101, 102 and 106 for optional tanks. Oil capacity 4 qt. (-24) Control surface movements Elevators Up 29° Down 27° Rudder Right 32° Left 32° Ailerons (not available) Serial Nos. eligible 833 and up (see NOTE 3 for S/N 801 thru 833) Required equipment Items 6, 104, 201 and 203. Page No. 1 2 3 4 5 6 7 8 9 10 11 12 13 14 15 16 Rev No. 27 - - - - - - - - - - - A-694 Revision 27 LUSCOMBE 8 8D 8A 8E 8B 8F 8C T-8F June 23, 2021 A-694 2 II – Model 8A, 2 OCL-SM (Normal Category), Approved March 27, 1939 Same as model 8 except engine installation. Also eligible with all metal wings, with either .016 or .020 aluminum alloy skin covering and .016 skin covering for ailerons per Luscombe dwg. 082201. For .016 skin, no weight increase is necessary. For .020 skin the weight is increased 15 lb. at (+20). Engine Continental A-65-1 (see item 126.B for optional engines.) Not eligible for original certification with single ignition engine. Fuel 73 minimum octane aviation gasoline 80 minimum octane required for seaplane (with item 212 installed) Engine limits For all operations, 2350 r.p.m. (65 hp) Propeller limits Maximum permissible diameter: (Landplane) 79 in. (Seaplane with item 204) 85 in. (Seaplane with item 212, see propeller item 2 (f). Airspeed limits (Landplane) Level flight or climb 115 m.p.h. (100 knots) True Ind. Glide or dive 145 m.p.h. (126 knots) True Ind. (Seaplane) Level flight or climb 109 m.p.h. (95 knots) True Ind. Glide or dive 145 m.p.h. (126 knots) True Ind. C.G. range (Landplane) (+13.6) to (+19.0). When bungee is replaced by elevator trim tab (dwg. 48589) following range must be used: (+13.6) to (+18.8) (Seaplane) (+15.4) to (+18.3) Empty wt. C.G. range Landplane ____________ Forward limits (+11.6) (+12.3) (+12.2) Rear limits (+14.8) (+13.7) (+14.5) (+17.0) (+17.3) (+16.9) Seaplane (With item 204) (+14.0) (+14.7) (+14.4) (+15.1) (+14.2) (+14.9) (+17.0) (+16.7) Seaplane (With item 212) (+14.0) (+14.7) (+14.4) (+14.4) (+14.4) (+14.0) (+17.5) (+16.7) (+15.7) Fuel Tank Installation Item 105, or 101 and 105 or 105 and 106. Item 102 or 112. Item 115. Item 105. Item 101 and 105. Item 105 and 106. Item 102. Item 112. Item 115. When empty weight C.G. falls within the pertinent range, computation of critical fore and aft C.G. position is unnecessary. Ranges are not valid for non-standard arrangements except as noted. Maximum weight (Landplane) 1200 lb. See NOTE 6 for 1260lb. (Seaplane with item 204) 1260lb. (Seaplane with item 212) 1350lb. No. of seats 2 (+20) Maximum baggage 75 lb. (+40) Fuel capacity 14 gal. (+40). Placard required: “Full carburetor air heat required for takeoff and landing.” The reason for this placard is that during takeoff acceleration and initial high-angle-of-attack climb, the fuel flow may not be adequate for proper operation. Application of full carburetor heat in this case helps overcome the possible deficiency of fuel flow during takeoff. Carburetor ice is not a basic consideration in requiring this placard. (See also items 101, 102, 106, 111, 112, and 115 for optional tanks.). Oil capacity 4 qt. (-24) Control surface movements Elevators Up 29° Down 27° Rudder Right 32° Left 32° Aileron Up 25° Down 25° Elevator tab (required for Up 14° Down 28° seaplane with item 212) Serial Nos. eligible 833 and up (see NOTE 3 for S/N 801 thru 833) Required equipment (Landplane) Items 6, 104, 124, 201, 203 (Seaplane with item 204) Items: 6, 104, 122, 124, 204, 605, 606 (Seaplane with item 212) Items: 2(f), 104, 122, 124, 204, 605, 606 A-694 3 A-694 4 III – Model 8B, 2 PCLM (Normal Category), Approved March 18, 1940 Same as model 8 except engine installation Engine Lycoming O-145-B1 (see item 126.C. for optional engines) Not eligible for original certification with single ignition engine. Fuel 73 minimum octane aviation gasoline Engine limits For all operations, 2550 r.p.m. (65 hp.) Propeller limits Static r.p.m. at maximum permissible throttle settings: not over 2500, not under 2060. No additional tolerance permitted. Diameter: Not over 79 in, not under 68 in. Airspeed limits Level flight or climb 115 m.p.h. (100 knots) True Ind. Glide or dive 145 m.p.h. (126 knots) True Ind. C.G. range (+13.6) to (+19.0). When bungee is replaced with elevator trim tab (dwg. 48589) following range must be used: (+13.6) to (+18.8) Empty wt. C.G. range Forward limits (+11.6) with item 105, or 101 and 105. (+12.2) with item 102, or 101 and 102. Empty wt. C.G. range Rear limits (+14.8) with item 105. (+13.7) with items 101 and 105. (+17.0) with item 102. (+15.9) with items 101 and 102. When empty weight C.G. falls within pertinent range, computation of critical fore and aft C.G. positions is unnecessary. Ranges are not valid for non-standard arrangements except as noted. Maximum weight 1200 lb. No. of seats 2 (+20) Maximum baggage 55 lb. (+40) Fuel capacity 14 gal. (+40). (see items 101 and 102 for optional tanks). Oil capacity 5 qt. (-24) Control surface movements Elevators Up 29° Down 27° Rudder Right 32° Left 32° Aileron (not available) Serial Nos. eligible 833 and up (see NOTE 3 for S/N 801 thru 832) Required equipment Items 6, 104, 201, 203. IV – Model 8C, 2PCL-SM (Normal Category), Approved June 17, 1940 Same as model 8 except engine installation. Engine Continental A-7508J (see item 126. for optional engines). Fuel 73 minimum octane aviation gasoline Engine limits For all operations, 2600 r.p.m. (75 hp.) Propeller limits Static r.p.m. at maximum permissible throttle settings (no additional tolerance permitted): (Landplane) not over 2450, not under 1950. (Seaplane) not over 2450, not under 2060. Diameter: (Landplane) not over 79 in., not under 68in. (Seaplane) not over 85 in., not under 68 in. Airspeed limits (Landplane) Level flight or climb Glide or dive (Seaplane) Level flight or climb Glide or dive 115 m.p.h. (100 knots) True Ind. 145 m.p.h. (126 knots) True Ind. 109 m.p.h. (95 knots) True Ind. 145 m.p.h. (126 knots) True Ind. C.G. range (Landplane) (+13.6) to (+19.0). When bungee is replaced by elevator trim tab (dwg. 48589) following range must be used: (+13.6) to (+18.8) (Seaplane) (+15.4) to (+18.3) A-694 5 Empty wt. C.G. range Landplane Forward limits (+11.6) (+12.3) Rear limits (+14.8) (+13.7) (+14.5) (+17.0) (+15.9) Seaplane (+14.0) (+14.7) (+14.0) ( * ) ( * ) (+16.1) ( * ) Fuel Tank Installation Item 105, or 101 and 105 or 105 and 106. Item 102 or 101 and 102 Item 105. Item 101 and 105. Item 105 and 106. Item 102. Item 101 and 102 (*each case must be checked when item 101 or 106 is installed) When empty weight C.G. falls within pertinent range, computation of critical fore and aft C.G. positions unnecessary. Ranges are not valid for non-standard arrangements excepted as noted. Maximum weight (Landplane) 1200 lb. See NOTE 4 regarding higher weights). (Seaplane) 1260 lb. No. of seats 2 (+20) Maximum baggage 55 lb. (+40) Fuel capacity 14 gal. (+40). See items 101, 102 and 106 for optional tanks. Oil capacity 4 qt. (-24) Control surface movements Elevator Rudder Up 29° Right 32° Down 27° Left 32° Ailerons (not available) Serial Nos. eligible 833 and up (see NOTE 3 for S/N 801 thru 832) Required equipment (Landplane) Items: 6, 104, 201 and 203 (Seaplane) Items: 6, 104, 122, 204, 605 and 606 V – Model 8D, 2 PCL-SM (Normal Category), Approved October 24, 1941 Same as Model 8C except for increased maximum weight, wing covering with intermediate or “Grade A fabric, revised fuel system and addition of elevator trim tab replacing bungee. The seaplane model has special engine cooling baffles. Engines Continental A-75-8J (see item 126.E. for optional engines) Fuel 73 minimum octane aviation gasoline Engine limits For all operations, 2600 r.p.m. (75 hp) Propeller limits Static r.p.m. at maximum permissible throttle setting (no additional tolerance permitted). (Landplane) not over 2450, not under 2060. (Seaplane) not over 2325, not under 2225. Diameter: (landplane and seaplane) maximum 72 in., minimum 70 in. Airspeed limits (Landplane) (Seaplane) Level flight or climb Glide or dive Level flight or climb Glide or dive 115 m.p.h. (100 knots) True Ind. 145 m.p.h. (126 knots) True Ind. 109 m.p.h. (95 knots) True Ind.. 145 m.p.h. (126 knots) True Ind. C.G. range (Landplane) (+13.6) to (+19.0). (Seaplane) (+14.5) to (+17.6) Empty wt. C.G. range Landplane Forward limits (+12.3) (+11.3) Rear limits (+17.2) (+16.3) (+14.5) (+13.5) Seaplane (+13.5) (+12.6) (+15.1) (+14.2) (+12.6) ( * ) Fuel Tank Installation Item 102, or 101 and 102 Item 105, or 101 and 105 Item 102 Item 101 and 102 Item 105 Item 101 and 105 (*each case must be checked separately when items 101 and 105 are installed in the seaplane). When the empty weight C.G. falls within the pertinent range, computation of the critical fore and aft C.G. positions is unnecessary. Ranges are not valid for non-standard arrangements except as noted. Maximum weight (Landplane) 1310 lb. (Seaplane) 1375 lb. No. of seats 2 (+20) A-694 6 Maximum baggage 55 lb. (+40) Fuel capacity 23 gal. (two 11-1/2 gal. tanks in weight at +20). (see items 101 and 105 for optional) tanks). Oil capacity 4 qt. (-24) Control surface movements Elevators Rudder Up 29° Right 32° Down 27° Left 32° Ailerons (not available) Serial Nos. eligible (Landplane) 1807 and up (Seaplane) 1885 and up Required equipment (Landplane) Items 6, 104, 201 and 203 (Seaplane) Items 6, 104, 122, 204, 605 and 606 VI – Model 8E, 2PCLM (Normal Category), Approved December 11, 1946; 2 PCSM (Normal Category), Approved May13, 1948 Similar to model 8D except for increased maximum weight, increased horsepower and minor structural changes. Model 8E was formerly designated as Model 8E Optional. It will not be necessary to revise the aircraft operation record to indicate this change in model. Engine Continental C-85-12 (see item 126.F. for optional engines) Fuel 73 minimum octane aviation gasoline, except 80 minimum octane required for seaplane with item 204 or 212 Engine limits For all operations, 2575 r.p.m. (85 hp.) Propeller limits (Landplane) Static r.p.m. at maximum permissible throttle settings, not over 2255, not under 1970. No additional tolerance permitted. (Seaplane) See item 2(e) under “ Propeller and Propeller Accessories” Airspeed limits (Landplane) Level flight or climb Glide or dive (Seaplane) Level flight or climb Glide or dive 115 m.p.h. (100 knots) True Ind. 145 m.p.h. (126 knots) True Ind. 109 m.p.h. ( 95 knots) True Ind. 145 m.p.h. (126 knots) True Ind. C.G. range (Landplane) (+13.6) to (+16.8) (Seaplane) (+14.6) to (+16.7) (with item 204 or 212) Empty wt. C.G. range Landplane Forward limits (+12.3) Rear limits (+13.7) (+13.1) Seaplane (+13.3) (+13.3) (+13.3) Fuel Tank Installation Item 102, or 109, or 111 or 115 Items 102, or 109, or 111 Item 115 When empty weight C.G. falls within the pertinent range, computation of critical fore and aft C.G. positions is necessary. Ranges are not valid for non-standard arrangements excepted as noted. Maximum weight (Landplane) 1400 lb. (Seaplane) with item 204) 1375 lb. (Seaplane with 212) 1470 lb. No. of seats 2 (+20) Maximum baggage 75 lb. (+40) Fuel capacity 25 gal. (two 12-1/2 gal. tanks in wings at +20) (see also items 102, 111, 112, and 115 for optional tanks). Oil capacity 5 qt. (-24) Control surface movements Elevators Rudder Ailerons Elevator tab (landplane) Optional Elevator tab (seaplane) Up 28° Right 28° Up 25° Up 14° Up 10° Up 7° Down 29.5° Left 28° Down 25° Down 25° Down 33° Down 41° Serial Nos. eligible 833 and up when converted in accordance with pertinent provisions of Luscombe Service Department Letter of August 4, 1947. Required equipment (Landplane) (Seaplane with item 204) (Seaplane with item 212) Items 6, 104, 205 and 206 Items 2(e), 104, 113, 204, 605 and 606 Item 2(e), 104, 113, 212 and 605 A-694 7 VII – Model 8F, 2 PCLM (Normal Category), Approved May 25, 1948; 2 PCSM (Normal Category), Approved July 26, 1948 Same as model 8E except engine installation. For conversion of model 8E to 8F airplanes in addition to changes noted below, cowling modification per Luscombe E.O. No. 2167 against dwg. 086085 is required. Engine Continental C-90-12F (see item 126.G. for optional engines) Fuel 80 minimum octane aviation gasoline Engine limits For all operations, 2475 r.p.m. (90 h.p.) Propeller limits (Landplane) See items 4(a) and 5. (Seaplane) See item 4(b). Airspeed limits (Landplane) Level flight or climb Glide or dive (Seaplane) Level flight or climb Glide or dive 115 m.p.h. (100 knots) True Ind. 145 m.p.h. (126 knots) True Ind. 109 m.p.h. ( 95 knots) True Ind. 145 m.p.h. (126 knots) True Ind. C.G. range (Landplane) (+13.6) to (+16.8) (Seaplane with item 204 or 212) (+14.6) to (+16.7) Empty wt. C.G. range Landplane Forward limits (+12.2) (+12.3) Rear limits (+13.2) (+13.4) (+13.3) Seaplane (+13.8) (+13.9) (+15.5) (+15.8) (+15.8) Fuel Tank Installation Item 109 or 102 Item 111 or 112 Item 102 or 109 Item 111 Item 112 When empty weight C.G. falls within the pertinent range, computation of critical fore and aft C.G. positions is necessary. Ranges are not valid for non-standard arrangements except as noted. Maximum weight (Landplane) 1400 lb. (Seaplane with item 204) 1375 lb. (Seaplane with item 212) 1470 lb. No. of seats 2 (+20) Maximum baggage 75 lb. (+40) Fuel capacity 25 gal. (see also item 102, 111 and 112 for optional tanks) Oil capacity 5 qt. (-24) Control surface movements Elevators Rudder Aileron Elevator tab (landplane) Elevator tab (seaplane) Up 28° Right 28° Up 25° Up 10° Up 7° Down 29.5° Left 28° Down 25° Down 33° Down 41° Serial Nos. eligible 1925 thru 6800, S-1 and up Required equipment (Landplane) Items 4(a), 114, 205, and 206 (size 6.00-6 only) (Seaplane with item 204) Items 4(b), 113, 114, 204, 605 and 606 (Seaplane with item 212) Items 4(b), 113, 114, 212 and 605 VIII – Model T-8F, 2 PCLM (Restricted and Standard Categories), Approved June 14, 1948 Same as model 8F except tandem seats, tandem controls, cabin fuselage structure and canopy, landing gear axle moved two inche s forward, minor changes in electrical system and fuel system, battery relocated, hydraulic brakes, dorsal f in. Engines Continental C-90-12F (see item 126 for optional engines) Fuel 80 minimum octane aviation gasoline Engine limits For all operations, 2475 r.p.m. (90 h.p.) Propeller limits See item 4(a) or (b) Airspeed limits Level flight or climb 115 m.p.h. True Ind. Glide or dive 145 m.p.h. True Ind. C.G. range (+12.1) to (+18.1) Empty weight C.G. range When empty weight C.G. falls within this range, computation of critical fore and aft C.G. Positions in unnecessary. Range is not valid for non-standard arrangements except as indicated. Installation of fixed ballast per Luscombe dwg. 481364 not to exceed 30 lb. is approved at (+63) and is placarded: “Removal requires weight and balance check.” Maximum weight 1400 lb. (for crop sprayer, see NOTE 8) No of seats 1 (1 +15, 1 +47). Placard required: “Solo from front seat only.” A-694 8 Maximum baggage None Fuel capacity 30 gal. (see items 109 and 111 for optional tanks) Oil capacity 5qt. min. (-24) Control surface movement Elevators Elevator control tab Rudder Aileron Up 24° Up 10° Right 18° Up 13° Down 23° Down 41° Left 18° Down 14° Serial Nos. eligible 6058 thru 6800, ST-1 and up Required equipment Items 4(a) or (b), 114, 205, 206(g) and 213 Specifications Pertinent to All Models Datum Wings leading edge Leveling means Top of horizontal splice plate on side of fuselage Certification basis Part 4a of the Civil Air Regulations Type Certificate No. 694 issued August 11, 1938 Production basis None. Prior to original certification of any aircraft manufactured after January 2, 1951, an FAA representative must perform a detailed inspection for workmanship, materials conformity with the approved technical data, and a check of flight characteristics. Export eligibility Eligible to all countries subject to the provisions of Advisory Circular 21 -2 effective July 16, 1965, except as follows: (a) Canada – Landplane, seaplane and skiplane eligible. Equipment: A Plus(+) or minus(-) sign preceding the weight of an item indicates net weight change when that item is installed. Special Note: So that all equipment items must be in their proper categories, the following items were renumbered as follows: Propeller and Propeller Accessories 1. Propeller – Beech controllable R002 or R003 for Models 8A 8C and 8D landplanes only. (a) Hub R002-101 or R003-100 Blades R002-205-72 or R003-235-72 (Model 8C) Blades R003-201-72T or R003-231-72T (Models 8A and 8D) Diameter: not over 71 in., not under 70.5 in. Pitch settings at 27 in. sta.: high 19°, low 13° (Model 8A) high 19.5°, low 13.5° (Model 8C) high 18.5°, low 12.0° (Model 8D) +12 lb. (-48) 1/ 2/ 3/ 4/ 5/ 6/ 7/ 8/ 9/ 10/ 11/ 12/ 13/ 14/ 15/ 16/ 17/ 18/ 19/ 20/ 21/ 22/ 23/ Item 6 was formerly item 101. Item 101 was formerly item 201. Item 102 was formerly item 203. Item 103 was formerly item 204. Item 125 was formerly item 208. Item 126 was formerly item 302. Item 127 was formerly item 307. Item 128 was formerly item 312. Item 129 was formerly item 313. Item 201 was formerly item 102. Item 203 was formerly item 103. Item 204 was formerly item 151. Item 205 was formerly item 301. Item 206 was formerly item 303. Item 207 was formerly item 308. Item 208 was formerly item 310. Item 209 was formerly item 311. Item 210 was formerly item 315. Item 301 was formerly item 205. Item 303 was formerly item 206. Item 402 was formerly item 209. Item 403 was formerly item 304. Item 607 was formerly item 210. A-694 9 (b) Control mechanism 1 lb. (-24) 2. Propeller – McCauley 1A90 (a) For Model 8C (landplane and seaplane) with A-75-8J engine with following limits: Static r.p.m. at maximum permissible throttle setting: not over 2330, not under 2110 No additional tolerance permitted. Diameter: not over 71 in., not under 69.5 in. 21 lb. (-45) (b) For Model 8A (landplane and seaplane with item 204 floats) with A-65-8J, -8FJ, -3J, -7J, -9J and -9FJ engines with the following limits: Static r.p.m. at maximum permissible throttle setting: not over 2145, not under 1940 No additional tolerance permitted. Diameter: not over 74 in., not under 72.5 in. 21 lb. (-45) (c) For Model 8A with A-65-8, -8F, -3, -7, -9 and -9F engines with the following limits: Static r.p.m. at maximum permissible throttle setting: not over 2145, not under 2045 (with fuselage tank) not over 2145, not under 1940 (with wing tank) No additional tolerance permitted. Diameter: not over 74 in., not under 72.5 in. 21 lb. (-45) (d) For Model 8D with the following limits (landplane only) Static r.p.m. at maximum permissible throttle setting: not over 2330, not under 2110 No additional tolerance permitted. Diameter: not over 71 in., not under 69.5 in. 21 lb. (-45) (e) For Model 8A seaplane with item 212 floats – 1A90-CF-7144 or any other McCauley 1A90-CF propeller which meets the following limits: Static r.p.m. at maximum permissible throttle setting: not over 2190, not under 2090 No additional tolerance permitted. Diameter: not over 71 in., not under 69.5 in. 21 lb. (-45) (f) For Model 8A seaplane with item 212 floats. Any 1A90-CF propeller which meets the following limits: Static r.p.m. at maximum permissible throttle setting: not over 2170, not under 2070 No additional tolerance permitted. Diameter: not over 74 in., not under 72.5 in. (This propeller change dictated by undesirable vibrations in the static r.p.m. range with the model 1A90-CF-7142. McCauley Service Bulletin No. 12, dated June 2, 1949, covers the same subject). 21 lb. (-45) (g) For Model 8E landplane – 1A90-CF-7144 or any other 1A90-CF propeller which meets the following limits: Static r.p.m. at maximum permissible throttle setting: not over 2255, not under 2000 Not additional tolerance permitted . Diameter: not over 71 in., not under 69.5 in. 21 lb. (-45) 3. Propeller – Hartzell ground adjustable HA-12U (for 8B, 8C, 8D and 8E only) Hub Model – HA-12UO or HA-12UF Blades – 7414 to 6814 or 7214M to 6814M