# TCDS A-694: Luscombe Aircraft Corporation - Type: Type certificate data sheet - Status: Current - Holder: Luscombe Aircraft Corporation - Revision: 27 - Revised: June 23, 2021 - Product: Aircraft, Small Airplane - Certification basis: CAR 4a - Registered aircraft: 1,458, by the registry models matched to it (OpenAirDocs) - Data sheet PDF: https://openairdocs.org/files/sha256/27/8a/278adb01490c8de76b50ec53a3fa4ce5c84935d7249f1ed4c41d186b5164a3da - FAA DRS: https://drs.faa.gov/browse/excelExternalWindow/A09862F37DF538E5862586FC004B8CE4.0001 - Page: https://openairdocs.org/tcds/A-694 ## Models (8) As the data sheet lists them. - 8 - 8D - 8A - 8F - 8B - 8E - 8C - T-8F ## What the data sheet says Some pages are OCR from the scanned FAA data sheet. OCR can misread letters and numbers. ```text 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 Eligible at diameter and station r.p.m. limits shown for fixed pitch wood models (items 6). 18 lb. (-45) 4. Propeller – McCauley 1B90 (a) For models 8F and T-8F landplanes – 1B90-CM-7154 or any other 1B90-CM propeller which meets the following limits: Static r.p.m. at maximum permissible throttle settings: not over 2100, not under 2000 No additional tolerance permitted. Diameter: not over 71 in., not under 69.5 in. 21 lb. (-45) (b) For models 8F seaplane and T-8F landplane – 1B90-CM-7347 or any other 1B90-CM propeller which meets the following limits: (1) For model 8F seaplane 21 lb. (-45) A-694 10 Static r.p.m. at maximum permissible throttle setting: not over 2210, not under 2110 No additional tolerance permitted. (2) For model T-8F landplane Static r.p.m. at maximum permissible throttle setting: not over 2350, not under 2250 No additional tolerance permitted. Diameter: not over 73 in., not under 70 in. (c) For model T-8F landplane with C-90-12FJ engine – 1B90-CM-7345 or any other 1B90-CM propeller which meets the following limits: Static r.p.m. at maximum permissible throttle setting: not over 2370, not under 2270 No additional tolerance permitted. Diameter: not over 72.5 in., not under 71.5 in. (Engine item 116 required with this installation) 21 lb. (-45) 5. For model 8F landplane – Lewis propeller model L77CK-47 or any other fixed pitch wood propeller which is eligible for the engine power and speed and meets the following limits: Static r.p.m. at maximum permissible throttle settings: not over 2125, not under 2025 No additional tolerance permitted. Diameter: not over 72. in., not under 71 in. (Engine item 116 required with this installation) 13 lb. (-45) 1/6. Propeller – wood (fixed or adjustable pitch) (Models 8A, 8b, 8C, 8D, 8E and 8F) 17 lb. (-45) Engines and Engine Accessories – Fuel and Oil Systems 2/101. Five gal. auxiliary fuel tank installation Placard required on instrument panel: “Auxiliary fuel not to be used as reserve.” 14 lb. (+40) 3/102. Two 11.5 gal. metal wing fuel tanks (+20) and revised fuel system Replacing 14 gal. fuselage tank system (models 8, 8A, 8B, 8C, 8E and 8F) +13 lb. (+40) 4/103. Exhaust mufflers (a) Twin mufflers E.D.L. type A4 (models 8A, 8C, 8D only) (b) Aero muffler type A3A (model 8B only) (c) Kay muffler – heater exhaust system per Luscombe dwg. 086142 (models 8E, 8F, T-8F). a 5 qt. oil tank only can be used with this item due to clearance considerations. (d) Hanlon-Wilson model 207 muffler-heater exhaust system per Luscombe dwg. 086149 (models 8A, 8E, 8F, T-8F) (e) Davis Silencer Co. model D-85-90-L for Luscombe 8E, 8F, T-8F, installed per Davis Silencer Co. dwg. D-65-90L. (f) Davis Silencer Co. model D-65-75 for Luscombe 8, 8A, 8C, 8D, installed per Davis Silencer Co. dwg. D-65-90L. 9 lb. (-22) 5 lb. (-22) 3 lb. (-20) 2 lb. (-20) 104. Carburetor air heater (not applicable to Continental “J” engines) 105. 14 gal. fuselage fuel tank system (model 8D with this change requires installation of injector type engines unless item 107 is installed. 17 lb. (+36) 106. Two 4.5 gal. Timm auxiliary wing fuel tanks, Timm dwgs. 2 and 18 or Aero Services dwgs. 102 and 103 (models 8, 8A, 8C) 11 lb. (+19) 107. Engine-driven fuel pump and hand-operated Chevrolet wobble pump +7 lb. (-21) 108. Starter, Delco-Remy EX-30012 (model 8E only) 16 lb. (-22) 109. Two 12.5 gal. wing tank replacing 11.5 gal. wing tanks (models 8A, 8E, 8F, T -8F) +2 lb. (+20) 110. Starter, Righter engine ring model A-1 (Righter instln. dwg. 10600) (models 8, 8A, 8C, 8D only) 7 lb. (-35) 111. Two 15 gal. bladder type wing fuel cells (models with all metal wings – 8A, 8E, 8F, T-8F) 9 lb. (+18) 112. One 15 gal. bladder type wing fuel cell in right wing (models with all metal wings – 8A, 8E, 8F) 5 lb. (+18) 113. Modified engine cowling, Luscombe dwg. 58740 114. Carburetor air heater per Luscombe dwg. 09607, Rev C. (models 8A, 8E, 8F, T-8F). Not required on Continental injector engines. No weight change 115. One 12.5 gal. metal wing tank (models with all metal wings, 8A, 8E) 10 lb. (+20) 116. Center baffle cowl in accordance with Luscombe dwg. 58739-4 (required with propeller items 4(c) and 5 and engine item 126.H.(2) No weight change 117. Starter, Delco-Remy 1109656 (models 8E, 8F, T-8F) 16 lb. (-22) A-694 11 118. Fram oil filter, Fram instln. sheet No. 61517 (models 8A, 8E) 5 lb. ( 0) 119. Blast tube instln. (Luscombe dwg. 481415) No weight change 120. Cowl assembly for model T8F with Continental C-90-12FJ engine (Luscombe dwg. 081411) No weight change 121. Injector fuel system instln. (model T-8F only) (a) Luscombe dwg. 081413 (b) Luscombe dwg. 081425 No weight change 122. Modified engine cowl, dwg. 48720 123. Swing-over engine mount per Luscombe dwg. 581268, installed per Luscombe dwg. 581267 (models 8A, 8C, 8D, 8E, 8F, T-8F) No weight change 124. Pressure vent fuel cap (Luscombe dwg. 486021) required for fuselage tank. Model 8A airplanes with Wally Trim wing fuel tanks must also have Luscombe pressure cap on both main and wing unless equipped with injector engines. No weight change 5/125. Engines shielding 2 lb. (-34) 6/126. Engines (not eligible for original certification with single ignition engines) A. Model 8 (Continental, per Engine Spec. No. 190) (1) A-50-2 (2) A-50-3 or A-50-8 (3) A-50-4 (4) A-50-5 or A50-9 (5) A-50-6 (6) A-50-7 (-32) +6 lb. +10lb. +3 lb. (-32) +13 lb. +16 lb. No weight change B. Model 8A (Continental, per Engine Spec. No. 205) (1) A-65-1J – engine limits same as for A-65-1 (2) A-65-3 or A-65-3J (engine limits for all operations, 2300 r.p.m. 65 hp.) (3) A-65-6 or A-65-7J (engine limits same as (2) (4) A-65-7 or A-75-7J (engine limits same as (2) (5) A-65-8, or A-65-8F or A-65-8FJ (injector engines equipped with high model A injector) Engine limits same as (2) (6) A-65-9, A-65-9F, A-65-9J or A-65-9FJ (injector engines equipped with high model A injector) (-32) +10 lb. +13 lb. No weight change +10 lb. +13 lb. C. Model 8B (Lycoming, per Engine Spec. No. 210) (1) O-145-B2 (2) O-145-B3 (-33) +11 +14 lb. D. Model 8C (Continental per Engine Spec. No. 213) (1) A-75-9J (2) A-75-9 (with item 102 or 107 only) (3) A-75-8 (with item 102 or 107 only) (4) A-75-6 (with item 102 or 107 only) (-32) +3 lb. +3 lb. No weight change +3 lb. E. Model 8D (Continental per Engine Spec. No. 213) (1) A-75-8 (2) A-75-9 or A-75-9J (-32) No weight change +3 lb. F. Model 8E (Continental per Engine Spec. No. 233) (1) C-85-12F (2) C-85-8F No weight change -2 lb. (-32) G. Model 8F (Continental per Engine Spec. No. 252) (1) C-90-8F -4 lb. (-32) H. Model T-8F (Continental per Engine Spec. No. 252) (1) C-90-8F (2) C-90-12FJ (item 4)c), 119, 120, 121, required) When this engine and two tanks are installed, placard panel: “1. Use left tank for takeoff and until at least three-fourths fuel is expended. 2. Use right tank until expended. 3. Use left tank thereafter.” No weight change 7/127. Engine mount per dwg. 48147 (for engines not incorporating integral rubber shocks) No weight change 8/128. Hummer starter, model X (models 8A, 8B, 8C, 8D only) Engines mount tubes from upper engine points to lower firewall attach point must be 5/8 x .035 12 lb. (+4) 9/129. Starter, Eclipse type 635 model 3 18 lb. (-22) 10/130. Model 8E and 8F. Lycoming O-320 or O-320-A1A engine; McCauley 1C172/MGM 7462 Use act. wt. change A-694 12 Propeller; Prestolite ALK5001S4UO alternator; and fuel filler cap with forward facing vent in accordance with STC SA344CE. STC SE5CE required to install alternator on engine. “Instructions for installation of Lycoming O-320 Engine in Luscombe 8E and 8F Airplanes,” all drawings listed therein, and wiring diagram for Prestolite 35 amp AC alternator requi red. Landing Gear and Floats 11/201. 3-in. wheel (Goodyear 3LNBM) with 16 X 7-3 tires 21 lb. (+3) 12/203. Tail Skid 13/204. Float installation – Edo 60-1320, 170 lb. (Including water rudder and auxiliary fin). Installation in accordance with Luscombe dwg. 08732C for 8A, 8E, 8F, and dwg. 58725 for 8C, 8D. Following is applicable to this installation: (a) Rear strut float attachment fittings station 4 must conform to Luscombe dwg. 58730C (b) Placard required: (1) On fuselage skin over hosting lugs: “Spreader-bar must be used during hoisting.” +109 lb. (+25) 14/205. Tail wheel assemblies (a) Luscombe, 3 in (b) Universal Alloy G-4 or GLD-4 or GLD-19 (c) Luscombe, 6 in. (dwg. 48338) (d) Health G1A, 6 in., steerable (e) Scott 3-24-B, 6 X 2.00, steerable (f) Maule SFS-1-4 or SAFS-14 (g) Decker D-501, steerable. Installation requires modified rudder in accordance with either (1) or (2) or NOTE 7. (h) Maule SFS-1-4-P8 +2 lb. (+179) +4 lb. (+181) +4 lb. (+181) 6 lb. (+183) 6 lb. (+183) 6 lb. (+183) 7 lb. (+183) 15/206. Wheels (Silflex cantilever landing gear instln. moves the location of the main wheels 2 in. forward resulting in a location from datum of + 1. See item 213 for Silflex landing gear). (a) 3 in. with brakes (Goodyear 3LMBM) and (1) 16 X 7-3 tires (4-ply) (2) 18 X 8-3 tires (4-ply) (b) 6.00-6 with brakes (Shinn 6C5B) and 4-ply tires (c) 6.00-6 (Cleveland model 6.00 CMB) with 6.00-6 4-ply rating tire casing and regular tube. Wheel assembly No. D48500 Brake assembly No. C7000 (d) 6.00-6 (Goodyear model L6MBD) with 6.00-6 4-ply rating tire casing and regular tube. Wheel assembly No. 511413M Brake assembly No. 511254A (e) 6.00-6 (Goodrich, formerly Hayes model 600M) with 6.00-6 4-ply rating tire casing and regular tube. Wheel assembly No. D-3-47MD Brake assembly No. D-2-129 (f) 6.00-6 (Goodrich, formerly Hayes model 609M) with 6.00-4 4-ply rating tire casing and regular tube Wheel assembly No. D-2-129 (g) 6.00-6 (Goodrich, model 610M) with 6.00-6 4-ply rating tire casing and regular tube Wheel assembly No. D-2-129 Brake assembly No. D-2-129 (h) 6.00-6 (Goodyear model C16HBM) castering, with 6.00-6 4-ply rating tire casing and regular tube Wheel and brake assembly No. 266Ax36-15 & -16. Instln. must conform to Luscombe dwg. SK4206 and Goodyear dwg. 280Ax20. (+3) Use act. wt. change Use act. wt. change Use act. wt. change Use act. wt. change Use act. wt. change Use act. wt. change Use act. wt. change +34 lb. (+1) 16/207. Parking brake 17/208. Wheel streamlines (old gear) (with Siflex dear location) 10 lb. (+3) 10 lb. (+1) 18/209. Skis (eligible on any airplane of these models provided the propeller installation meets the minimum ground clearance. The maximum weight for the skiplane will be the same for the corresponding landplane or that shown in parenthesis after each ski model, whichever is less) (a) Marston MFS-1600 (max. 1600 lb.) (b) Jacobsen (or Escanaba) EAS-100 (max. 1200 lb.) (c) Heath 655 (max. 1310 lb.) Use act. wt. change A-694 13 (d) Air Transport 1220-480 (max. 1220 lb.) (e) Air Transport 1460-580 (max. 1460 lb.) (f) Federal 8A-1 (max. 1200 lb.) (g) Federal 8C-1 (max. 1400 lb.) (h) Marston MFS-1200 (max. 1200 lb.) (i) Federal SA-2 (max. 1400 lb.) (j) Federal SC-2 (max. 1650 lb.) (k) Heath 725 (max. 1450 lb.) (l) Richards 1-B (max. 2220 lb.) (m) Call S2, S6 or S7 installed per Call Aircraft Co. dwg. 1006, Change A, and 1014, Change A. (S2 max. wt. 1800 lb., S6 max. wt. 1450 lb., S7 max. wt. 1850lb.) (n) Federal A1500, instln. dwg. 11G169 (o) Federal A1500A, instln. dwg. 11G169 (p) Federal A1850, instln. dwg. 11G169 (q) Federal A2000, instln. dwg. 11G169 (r) Federal A2000A, instln. dwg. 11G169 (s) Federal CA1850-6, instln. dwg. 11G169 19/210. Decker wheel assy. P/N P1001 in kit form, 2 per airplane (old gear) with Siflex gear location 12 lb. (+3) (+1) 211. Brake pedal , R.H. instln. (Luscombe dwg. 485069) 1 lb. (-12) 212. Float instln., Edo 92-1400 water rudder and auxiliary fin. Instln. shall conform to Luscombe dwg. 08732 for model 8A, dwg. 08731 for model 8E and dwg. 08741 for model 8F. The following is applicable to this instln.: (a) Rear strut float attachment fittings and fuselage frame reinforcements at fuselage station 4 must conform to Luscombe dwg. 58730-C. (b) Placards and markings required: (1) Red radial line to be inscribed on oil temperature gauge at 220°F. (model 8E only). (2) On fuselage skin near hoisting lugs add placard: “Spreader-bar must be used during hoisting.” (c) Fixed elevator tab 58401-6, item 606, must be added to right-hand elevator and bent down 30°; (model 8A only). 178 lb. (+20) 213. Luscombe Siflex cantilever landing gear assy. No. 083310. This installation moves the location of the main landing gear wheels 2 in. forward resulting in a location from datum of (+1). This landing gear is not interchangeable with the original landing gear but may be used on all Luscombe model 8 airplanes S/N 5920 and up. No weight change Electrical Equipment 20/301. Landing lights (a) One Grimes ST-750 (item 303(b) or (c) with item 305(b) required ) 5 lb. (+12) (b) Two G.E. lamps No. 4509 (on all metal wing only) (item 314 with 305(b), (c) or (d) required) 4 lb. (+4) 21/303. Generator, wind-driven (a) 6 v. Air-Lite (b) 12 v. Air-Lite (c) 12 v. Air Associates 8 lb. (+3) 11 lb. (+3) 8 lb. (+3) 305. Battery installation (a) 6 v. 10 a. hr. (Exide 3-AC-7-1) (b) 12 v. 10 a. hr. (Exide 6-AC-7-1) (c) 12 v. 24 a. hr. (5 hour rate) (d) 12 v. 14 a. hr. (5 hour rate) (e) 12 v. 25 a. hr. (Willard AW 12-25) 14 lb. (-15) or 11 lb. (+55) 19 lb. (+55) 24 lb. (+55) 17 lb. (+52) 21 lb. (-20) 309. Lear two-way radio instln. per dwg. 48167 and 28157 20 lb. 314. Generator, engine-drive (a) Delco-Remy model 1101876, P/N 40435 (models 8E, 8F, T-8F) 10 lb. (-22) Interior Equipment 401. Luscombe FAA Approved Airplane flight Manual relative to the model T-8F crop sprayer (restricted) and model T-8F (standard) (required with item 602 in the restricted category – see NOTE 8) A-694 14 22/402. Soundproofing 8 lb. (+27) 23/403. Cabin heater 2 lb. (-22) Miscellaneous (not listed above) 601. Weight shifter device, model CGS-2B, manufactured by Aircraft Devices Co., Wings Field, Ambler, Pa. (models 8, 8A, 8B, 8C, 8D) The following is applicable to this item: (a) Install per Aircraft Devices Co., dwg. 7025 and placard in accordance with dwg. 355B. (b) Is fuselage fuel tank is installed, modify tank per dwg. 3048, placard per dwg. 367 and change fuel filter cap capacity markings from 14 gal. to 12 gal. (c) The weight of the instln. is 20 lb.; with weight in forward position arm is (+52) and with weight in aft position arm is (+126). 602. Crop spraying equipment per Luscombe dwg. 088200 (see NOTE 8 for restrictions) Use act. wt. change 603. Flap, Luscombe dwg. 082300, Change A (model T-8F, metal wing only) Use act. wt. change 604. Flap in accordance with Luscombe instln. dwg. 082301, Change A, or Luscombe kit instln. dwg. 582302, Change A. All model 8 series with metal wings eligible. Add placard to instrument panel: “Do not lower flaps above 90 m.p.h. TIAS.” Use act. wt. change 605. Corrosion proofing (Luscombe Report 915) 606. Elevator tab, dwg. 58700, Change F (deflection 30° downward except when indicated otherwise) 24/607. Goodrich abrasion shoes – stabilizer 5 lb. (+153) NOTE 1. Current weight and balance report together with list of equipment included in certificated empty weight, and loadi ng Instructions when necessary, must be provided for each aircraft at the time of original certification. NOTE 2. The following placards must be installed on the instrument panel or other location as noted below: (a) When item 101 is installed: “Auxiliary fuel not to be used as reserve.” (b) For model T-8F: “Solo from front seat only.” (c) When item 126.H.(1) and two tanks are installed: “1. Use left tank for take-off and unit at least three-fourths fuel is expended. 2. Use right tank until expended. 3. Use left tank thereafter.” (d) Deleted. (e) When item 204 or 212 is installed, following placard on fuselage skin near hoisting lugs: “Spreader -bar must be used during hoisting.” (f) When item 604 is installed: “Do not lower flaps above 90 m.p.h. TIAS.” (g) All model 8A airplanes equipped with carburated Continental A-65 engines and fuselage mounted fuel tank, the following placard is required to be installed on the instrument panel in plain view of the pilot! 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 deficie ncy of fuel flow during takeoff. Carburetor ice is not a basic consideration in requiring this placard. NOTE 3. Serial Nos. 801 thru 832, model 8, 8B or 8C, eligible as above except as follows: Baggage 40 lb. Maximum weight 1130 lb. C.G. range (+13.6) to (+17.9) Empty wt. C.G. range (+11.1) to (+13.1) (with item 105 fuel tank) 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. The serial numbers also eligible at increased maximum weight, baggage capacity, C.G. range, as for Nos. 833 and up when reinforcement at front spar strut point extended as indicated on dwg. 28212, Change B, and dwg. 08203, Change C, and when 3/16 in. rivets are used as part 18030. Permanent trailing edge on elevator required per dwg. 58401, Change A. NOTE 4. Model 8C, S/N 1804 and up, eligible for increased maximum weight with following limitations: A-694 15 Wing coving should be either intermediate or grade “A” fabric. Maximum weight Landplane Seaplane (when equipped with special engine cooling baffles) 1310 lb. 1375 lb. C.G. range Landplane Seaplane (+13.6) to (+19.0) (+14.5) to (+17.6) Empty wt. C.G. range Forward limits: Landplane (+12.3) (+11.3) Rear limits: Landplane (+17.2) (+16.3) (+14.5) (+13.5) Seaplane (+13.5) (+12.6) Seaplane (+15.1) (+14.2) (+12.6) ( * ) Fuel Tanks Installed Item 102, or 101 and 102 Item 105, or 101 and 105 Fuel Tanks Installed Item 102 Item 101 and 102 Item 105 Items101 and 105 (*each case must be checked separately when items 101 and 105 are installed in the seaplane.) 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. Propeller limits (a) Static r.p.m. Landplane – maximum 2450, minimum 2060 Seaplane – maximum 2325, minimum 2225 No additional tolerance permitted. (b) Diameter – not over 72 in., not under 70 in. Airspeed limits Landplane Level flight or climb Glide or dive Seaplane Level flight or climb Glide or dive 115 m.p.h., True Ind. 145 m.p.h., True Ind. 109 m.p.h., True Ind. 145 m.p.h., True Ind. Engine limits For all operations 2600 r.p.m. (75 hp.) Model 8C, S/N 1803 and below, also eligible at the increased maximum weight contingent upon compliance with the following provisions: (a) Limitations as shown above for propeller, engine, C.G. and airspeeds. (b) Addition of reinforcement part 481022 ahead of tail tray , as shown on dwg. 08043, Change P. (c) Change oleo fluid to Univis 90, SAE 20W, Mobilube 90 or equivalent and include the following placard on the arm of the landing gear adjacent to the oleo: “Fill oleo strut with SAE 20W, Univis 90 or Mobilube 90 oil.” (d) Installation of landing gear shackle hinge pin heat treated to 125,000 lb. per sq. in. (e) Wing covering should be with intermediate or grade “A” fabric. NOTE 5. Elevator trim tab, dwg. 48589, may replace bungee with the following C.G. range for models 8A (1200 lb. max. wt. see NOTE 6), 8B, 8C: (+13.6) to (+18.75) (weight change negligible). NOTE 6. Model 8A aircraft are also eligible at 1260 lb. max. wt. with control surface travel and C.G. range limited as follows: Elevators Rudder Ailerons Elevator tab or (optional ) Up 25° Right 28° Up 25° Up 14° Up 10° Down 26° Left 30° Down 25° Down 28° Down 33° C.G. range (+13.6) to (+18.8) Empty wt. C.G. range Forward limits Rear limits (+10.0) (with item 105, or 101 and 105, or 105 and 106) (+12.3) (with item 102 or 112) (+12.2) (with item 115) (+15.3) (with item 105) A-694 16 (+14.2) (with item 101 or 105) (+15.0) (with item 105 or 106) (+17.5) (with item 102) (+16.7) (with item 112) (+16.4) (with item 115) When empty wt. C.G. falls within the pertinent range, computation of critical fore and aft C.G. positions is unnecessary. Ranges are not valid for non-standard arrangements except as noted. NOTE 7. The following rudders are also approved for models 8 thru 8E, landplane or seaplane: (1) The original rudder assembly, dwg. 08403) modified in accordance with Luscombe dwg. SK -5170. (2) The “square” rudder assembly in accordance with Luscombe dwg. 08492. NOTE 8. Model T-8F aircraft approved for a maximum weight of 1470 lb. In the restricted category prior to October 11, 1950, as a sprayer and converted in accordance with Luscombe dwg. 088200 may continue to be operated at that weight. Such aircraft must be operated and converted in accordance with item 401 (Luscombe FAA Approved Flight Manual). Required equipment in this configuration: items 4(b), 113, 114, 205, 206(g), 401 and 602. All original certification in the restricted category after October 11, 1950, must be in accordance with Part 8 of the Civil Air Regulations effective October 11, 1950. - END- ``` ## ADs (16, in force first) - [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 96-24-17 R1](https://openairdocs.org/ad/96-24-17-R1): Wing Inspection Holes · Don Luscombe Aviation History Foundation 8, 8A, 8B and 5 more. Effective Jan 27, 1997 - [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 94-16-02](https://openairdocs.org/ad/94-16-02): Stabilizer Forward Attach Fitting · Don Luscombe Aviation History Foundation 8, 8A, 8B and 5 more. Effective Sep 19, 1994 - [AD 55-24-01](https://openairdocs.org/ad/55-24-01): Corrosion Inspection · Don Luscombe Aviation History Foundation 8, 8A, 8B and 3 more. Effective May 22, 1973 - [AD 62-24-03](https://openairdocs.org/ad/62-24-03): Cabin Heat System · Lycoming O-235-C1, O-235-C2C, O-290-D, O-290-D2, O-320 engine (Luscombe STC SA4-173 or 5 others). Effective Nov 21, 1962 - [AD 61-03-05](https://openairdocs.org/ad/61-03-05): Fuel Line Interference · Don Luscombe Aviation History Foundation 8, 8A, 8B and 5 more. Effective Mar 9, 1961 - [AD 46-30-01](https://openairdocs.org/ad/46-30-01): Control Stick Horn Adjustment Screw · Don Luscombe Aviation History Foundation 8A - [AD 47-10-40](https://openairdocs.org/ad/47-10-40): Rudder Control Arm Reinforcement · Don Luscombe Aviation History Foundation 8, 8A, 8B and 3 more - [AD 47-22-01](https://openairdocs.org/ad/47-22-01): Bulkhead Reinforcement For Seaplanes · Don Luscombe Aviation History Foundation 8, 8A, 8B and 3 more - [AD 48-08-02](https://openairdocs.org/ad/48-08-02): Cleveland Wheels · American Champion 11AC, 11BC, 11CC and 33 more - [AD 48-09-03](https://openairdocs.org/ad/48-09-03): Kollsman Airspeed Baffle · Don Luscombe Aviation History Foundation 8, 8A, 8B and 5 more - [AD 48-49-01](https://openairdocs.org/ad/48-49-01): Vertical Stabilizer Spar Fitting · Don Luscombe Aviation History Foundation 8, 8A, 8B and 5 more - [AD 49-43-02](https://openairdocs.org/ad/49-43-02): Stabilizer Spar Inspection · Don Luscombe Aviation History Foundation 8, 8A, 8B and 5 more - [AD 50-37-01](https://openairdocs.org/ad/50-37-01): Fuel System Modifications · Don Luscombe Aviation History Foundation 8C - [AD 51-10-02](https://openairdocs.org/ad/51-10-02): Control Cable Inspection · Don Luscombe Aviation History Foundation 8, 8A, 8B and 5 more ## Registered aircraft by registry model (OpenAirDocs) - [Luscombe 8A](https://openairdocs.org/model/luscombe-8a): 897 aircraft (registry codes 8190104, 8190111) - [Luscombe 8E](https://openairdocs.org/model/luscombe-8e): 326 aircraft (registry code 8190112) - [Luscombe 8F](https://openairdocs.org/model/luscombe-8f): 119 aircraft (registry code 8190114) - [Luscombe 8C](https://openairdocs.org/model/luscombe-8c): 37 aircraft (registry code 8190108) - [Luscombe T-8F](https://openairdocs.org/model/luscombe-t-8f): 25 aircraft (registry code 8190116) - [Luscombe 8B](https://openairdocs.org/model/luscombe-8b): 16 aircraft (registry code 8190106) - [Luscombe 8D](https://openairdocs.org/model/luscombe-8d): 14 aircraft (registry code 8190110) - [Luscombe 8](https://openairdocs.org/model/luscombe-8): 11 aircraft (registry code 8190102) - [Silvaire 8F](https://openairdocs.org/model/silvaire-8f): 10 aircraft (registry code 8190154) - [Luscombe/Pedersen T-8F](https://openairdocs.org/model/luscombe-pedersen-t-8f): 1 aircraft (registry code 8190117) - [Luscombe/Ranger Avia 8A](https://openairdocs.org/model/luscombe-ranger-avia-8a): 1 aircraft (registry code 8190107) - [Luscombe/Wilder 8A](https://openairdocs.org/model/luscombe-wilder-8a): 1 aircraft (registry code 8190105) - [Fleet 8](https://openairdocs.org/model/fleet-8): 0 aircraft (registry code 1461802) - [Luscombe/Duis 8A](https://openairdocs.org/model/luscombe-duis-8a): 0 aircraft (registry code 8190103) - [Luscombe/Hankins 8E](https://openairdocs.org/model/luscombe-hankins-8e): 0 aircraft (registry code 8190113) - [Luscombe/Nelson Thomas JR LUSCOMBE 8B](https://openairdocs.org/model/luscombe-nelson-thomas-jr-luscombe-8b): 0 aircraft (registry code 8190109) ## STCs approved under this data sheet (131, first 50) - [STC SA01233SE](https://openairdocs.org/stc/SA01233SE): Fabrication and installation of Alaskan Bushwheel LLC tail wheel and fork assembly. ABI, LLC - [STC SA01800SE](https://openairdocs.org/stc/SA01800SE): Fabrication and installation of new or replacement of existing instrument panel lights dimmer control.. TCW Technologies, LLC - [STC SA01861SE](https://openairdocs.org/stc/SA01861SE): Fabrication and installation of Landing Light Controller. TCW Technologies, LLC - [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 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 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 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 SA03898NY](https://openairdocs.org/stc/SA03898NY): Installation and maintenance of ORATEX covering and coating material. Aircraft Design & Certification Ltd - [STC SA4503NM](https://openairdocs.org/stc/SA4503NM): Remove original cloth covering and install Ceconite covering. Ceconite Division of Poly-Fiber Inc. - [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 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 SA01818WI](https://openairdocs.org/stc/SA01818WI): Installation of Garmin G5 Electronic Flight Instrument. Garmin International Inc. - [STC SA02553AK](https://openairdocs.org/stc/SA02553AK): Fabrication and installation of a Tail Wheel Anti-Shimmy Dampener. Keller Engineering Group LLC - [STC SA00940LA](https://openairdocs.org/stc/SA00940LA): Installation of overhead inertia reel shoulder harnesses for pilot and passenger.. Luscombe Aircraft Corporation - [STC SA01049WI](https://openairdocs.org/stc/SA01049WI): Replacement of existing engine with a Continental 0-200-A or O-200-C and suitable propeller in accordance with The Don Luscombe Aviation History Foundation DLAHF Document 0-200 dated December 15, 2001 or later FAA approved revision.. Luscombe Aircraft Corporation - [STC SA01093WI](https://openairdocs.org/stc/SA01093WI): Modification of flap operation mechanism. Install according to Renaissance Aircraft LLC Top Drawing R282315, Revision A, or later FAA approved revisions.. Luscombe Aircraft Corporation - [STC SA01094WI](https://openairdocs.org/stc/SA01094WI): Installation of a hydraulic brake system. Luscombe Aircraft Corporation - [STC SA2500SO](https://openairdocs.org/stc/SA2500SO): Fabrication and installation of front stabilizer attach fitting. Luscombe Aircraft Corporation - [STC SA3215NM](https://openairdocs.org/stc/SA3215NM): Fabrication and installation of pilot's and co-pilot's seat.. Luscombe Aircraft Corporation - [STC SA344CE](https://openairdocs.org/stc/SA344CE): Installation of Lycoming O-320 and O-320-A1A engine, McCauley 1C172/MGM 7462 propeller, and Prestolite ALK 5001 S4UO alternator.. Luscombe Aircraft Corporation - [STC SA4-173](https://openairdocs.org/stc/SA4-173): Installation of Lycoming O-235-C1, O-235-C2C, O-290-D, O-290-D2, O-320 engine.. Luscombe Aircraft Corporation - [STC SA4-642](https://openairdocs.org/stc/SA4-642): Lycoming O-290-D2 engine and Sensenich M76AM-2 propeller.. Luscombe Aircraft Corporation - [STC SA00410BO](https://openairdocs.org/stc/SA00410BO): Installation of an AV-30-C Multi-Mode Indicator. uAvionix Corporation - [STC SA02268CH](https://openairdocs.org/stc/SA02268CH): Installation of Airwolf Filter Corp. Air Oil Separator. Airwolf Filter 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 SA02366NY](https://openairdocs.org/stc/SA02366NY): Increase in Takeoff and Landing Maximum Gross Weight to 1,310 lbs. Wilson R. Lowry - [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 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 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 SA10077SC](https://openairdocs.org/stc/SA10077SC): Installation of push-button starter system.. Hartzell Engine Technologies, LLC - [STC SA02466AK](https://openairdocs.org/stc/SA02466AK): Installation of Grove hydraulic brake system. Endowment Enterprises, LLC - [STC SA00478CH](https://openairdocs.org/stc/SA00478CH): Installation of Cooper Superflite 102 Fabric.. Aviation Products Systems Inc. - [STC SA01768SE](https://openairdocs.org/stc/SA01768SE): Installation of an oil cooler system.. Steve's Aircraft - [STC SA02604CH](https://openairdocs.org/stc/SA02604CH): Installation of a battery powered engine starting system.. SafeStart Starter System - [STC SA02508LA](https://openairdocs.org/stc/SA02508LA): Installation of a MTV-11-C/188-17f 2-blade, 74 inch diameter, constant speed propeller, with lightweight composite blade construction and associated hardware. Edward R Warnock - [STC SA01669CH](https://openairdocs.org/stc/SA01669CH): Installation of Challenger Reusable Air Filter. Challenger Aviation Products Inc. - [STC SA02930NY](https://openairdocs.org/stc/SA02930NY): Installation of Insight Instrument Corporation Graphic Engine Monitor (GEM 610C) models G3, G2, and G1 and 1200C model G4 as primary Cylinder Head Temperature (CHT), Exhaust Gas Temperature (EGT), and Turbine Inlet Temperature (TIT) Instruments. Insight Instrument Corporation - [STC SA10921SC](https://openairdocs.org/stc/SA10921SC): Installation of an alternator and regulator as a replacement to existing OEM generators and mechanical voltage regulators. Hartzell Engine Technologies, LLC - [STC SA02283SE PAGE 1](https://openairdocs.org/stc/SA02283SE%20PAGE%201): Installation of Electronics International Inc. Glass Panel Engine Monitor (with In Flight Data) CGR-30P. Electronics International Inc. - [STC SA02402SE PAGE 1](https://openairdocs.org/stc/SA02402SE%20PAGE%201): Installation of Electronics International Inc. Glass Panel Engine Monitor (with In-Flight Data) CGR-30C. Electronics International Inc. - [STC SA3531NM](https://openairdocs.org/stc/SA3531NM): Installing copper electrical cables. (182 S/N 33000 THRU 33842) (8E 833 and UP). Bogert Aviation - [STC SA02428AK](https://openairdocs.org/stc/SA02428AK): Installation of a hydraulically actuated ski drag assembly. Northern Airframes LLC - [STC SA01026SE](https://openairdocs.org/stc/SA01026SE): Improved fuel gascolator assembly.. Steve's Aircraft - [STC SA02825NY PAGE 1](https://openairdocs.org/stc/SA02825NY%20PAGE%201): Installation of Aerospace Logic Aircraft Instruments. Aerospace Logic Inc. All 131: https://openairdocs.org/tcds/A-694/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.