TCDS A-751

DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION A-751 Revision 4 AERONCA O-58A (Army L-3A) O-58B (Army L-3B, L-3C) SO-58B March 7, 2005 AIRCRAFT SPECIFICATION NO. A-751 Type Certificate Holder National Aeronca Association 806 Lockport Road P.O. Box 2219 Terre Haute, IN 47802 Name change from Aeronca to National Aeronca Association March 7, 2005. I - Model O-58B (Army L-3B, L-3C), 2 PCLM, Approved Sept. 4, 1942 (See NOTE 2 for required modifications for civil certification) Engine Continental A-65-8 Fuel 73 min. octane aviation gasoline Engine limits For all operations, 2300 rpm (65 hp) Airspeed limits Level flight or climb 95 mph True Ind. Glide or dive 129 mph True Ind. Propeller limits Static rpm at maximum permissible throttle setting - not over 2200 not under 2010. No additional tolerance permitted. Diameter - not over 72 in., not under 70 in. C.G. range (+10.9) to (+17.8) Empty weight C.G. range (+12.1) to (+15.9). 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 1260 lbs. No. seats 2 (+8 and +38) Maximum baggage 10 lbs. (+60) Fuel capacity 12 gals. (one 2 gal. tank at -17, one 10 gal. tank at +21). Oil capacity 1 gal. (-38) Control surface movements Elevator trim tab 33 degrees up 12 degrees down Elevator 19 degrees up 25 degrees down Aileron 27 degrees up 15.5 degrees down Rudder 30 degrees right 32.5 degrees left Stabilizer Fixed Serial Nos. eligible C-3172TA to C-4012TA, inclusive, 058B1012 and up Required equipment Items 101, 102, 103 and 104 II - Model SO-58B, 2 PCSM, Approved November 23, 1942 (Same as Model O-58B except for propeller and landing gear) Engine Continental A-65-8 Fuel 73 min. octane aviation gasoline Engine limits For all operations, 2300 rpm (65 hp) Airspeed limits Level flight or climb 95 mph True Ind. Glide or dive 129 mph True Ind. Propeller limits Static rpm at maximum permissible throttle setting - not over 2210, not under 2110. No additional tolerance permitted. Diameter - not over 76 in., not under 70 in. C.G. range (+12.2) to (+18.1) Page No. 1 2 3 4 Rev No. 4 3 3 3 A-751 Page 2 of 4 Empty weight C.G. range (+13.5) to (+16.5). When empty weight C.G. falls within this range, computation of critical fore and aft C.G. positions is unnecessary. Range not valid for non-standard arrangements. Maximum weight 1350 lbs. No. seats 2 (+8 and +38) Maximum baggage 10 lbs. (+60) Fuel capacity 12 gals. (one 2 gal. tank at -17, one 10 gal. tank at +21) Oil capacity 1 gal. (-38) Control surface movements Elevator trim tab 33 degrees up 12 degrees down Elevator 19 degrees up 25 degrees down Aileron 27 degrees up 15.5 degrees down Rudder 30 degrees right 32.5 degrees left Stabilizer Fixed Serial Nos. eligible O-58B1012 and up Required equipment Items 101, 104, 105 and 151 III - Model O-58-A (Army L-3A), 2 PCLM, Approved March 13, 1945 Engine Continental A-65-8 Fuel 73 min. octane aviation gasoline Engine limits For all operations, 2300 rpm (65 hp) Airspeed limits Level flight or climb 95 mph True Ind. Glide or dive 129 mph True Ind. Propeller limits Static rpm at maximum permissible throttle setting - not over 2200 not under 2010. No additional tolerance permitted. Diameter - not over 72 in., not under 70 in. C.G. range (+10.9) to (+17.8) Empty weight C.G. range (+12.1) to (+15.9). When Empty weight C.G. falls within this range, computation of critical fore and aft C.G. positions is unnecessary. Range not valid for non-standard arrangements. Maximum weight 1260 lbs. No. seats 2 (+8 and +38) Maximum baggage 10 lbs. (+60) Fuel capacity 12 gals. (one 2 gal. tank at -17, one 10 gal. tank at +21). Oil capacity 1 gal. (-38) Control surface movements Elevator trim tab 33 degrees up 12 degrees down Elevator 19 degrees up 25 degrees down Aileron 27 degrees up 15.5 degrees down Rudder 30 degrees right 32.5 degrees left Stabilizer Fixed Serial Nos. eligible 7793 to 7812, inclusive, corresponding to AAF Nos. 42-7793 to 42- 7812, inclusive. Required equipment Items 101, 102, 103 and 104 Specifications Pertinent to All Models Datum Wing leading edge Leveling means For O-58B and SO-58B: Plumb line dropped from cotter pin (located about 1-3/4 in. forward of rear spar and 2 in. outboard of wing hinge line) to a 1/8 in. pin projection at lower fuselage longeron. Airplanes having serial Nos. O58B1012 and up are similar to those having serial Nos. C-3172TA to C-4012TA inclusive, except for reinforced wing, fuselage structure and leveling means. The leveling means for aircraft with serial Nos. 058B1012 and up is as shown above whereas the floorboard is used for leveling on aircraft with serial Nos. C-3172TA to C-4012TA inclusive. For O-58A: Cabin floor. Certification basis Type Certificate No. 751 (CAR 4a) A-751 Page 3 of 4 Production basis None. Prior to original certification for each aircraft manufactured subsequent to August 24, 1949, a CAA Manufacturing inspector must perform a detailed inspection for workmanship, materials, and conformity with the approved technical data, and a check of the flight characteristics. Export eligibility Eligible for export to all countries subject to the provisions of MOP 2-4, except as follows: Canada - Landplane - eligible Skiplane - not eligible Equipment: A plus (+) or minus (-) sign preceding the weight of an item indicates net weight change when that item is installed. Propellers and Propeller Accessories 1. Propeller - McCauley 1A90 26 lbs. (-57) (Models O-58B and SO-58B) with following limits: Static rpm at maximum permissible throttle setting: Not over 2250, not under 2100. No additional tolerance permitted. Diameter: Not over 74 in., not under 72.5 in. 2. Propeller - Hartzell ground adjustable, hub HA-12U, blades 7414 18 lbs. (-57) to 6814 or 7214M to 6814M. Eligible at diameter and static rpm limits shown for fi xed pitch wood propellers. 3. Propeller - Sensenich M74CK, fixed pitch metal 21 lbs. (-57) Static rpm at maximum permissible throttle setting: Not over 2250, not under 2100. No additional tolerance permitted. Diameter: Not over 74 in., not under 72 in. 101. Propeller - wood (fixed pitch) 13 lbs. (-57) Engines and Engine Accessories - Fuel and Oil System 104. Carburetor air heater 1 lb. (-41) 105. Oil radiator (Continental) 5 lbs. (-49) 106. Carburetor air intake and filter (Continental A-5810) +2 lbs. (-49) Landing Gear 102. 6.00-6 wheels with brakes (Shinn 6C5HB) and tires 28 lbs. (-4) 103. 6x2.00 tail wheel, full swiveling 8 lbs. (+188) 151. Heath floats model 1460-A (175 lbs.) +100 lbs. (+14) 201. Skis (Eligible on any airplane of these models provided the propeller installation meets the minimum 9 in. ground clearance. The maximum weight for the skiplane will be the same as for the corresponding landplane or that shown in parenthesis after each ski model, whichever is less)Use actual weight change (a) Heath 725A (Maximum 1450 lbs.) (b) Federal SC-1 (Maximum 1400 lbs.) (c) Heath 725 (Maximum 1450 lbs.) (d) Federal SC-2 (Maximum 1650 lbs.) (e) Marston MFS-1600 (Maximum 1600 lbs.) 202. Tail wheel - steerable (Heath 42-T-10) +1 lb. (+188) 301. 6.00-6 brake type wheels (a) (Cleveland Aircraft Pr oducts 6.00 MBA) +2 lbs. (-4) (b) (Goodyear L6MBM) Neglect weight increase (c) (Cleveland Aircraft Pr oducts 6.00 DMB-2) +2 lbs. (-4) 303. Tail wheel, steerable (Universal) +1 lb. (+188) 306. Dual brake system 2 lbs. (+3) A-751 Page 4 of 4 Electrical Equipment 302. Battery (Reading 333LD) 15 lbs (+41) 304. Generator (General Armature AG-40) 8 lbs. (-4) 307. Battery (Reading 324-L or 333-LD) 15 lbs. (-24) 308. Generator (General Armature). Mounted on left wing strut 11 lbs. (-3) NOTE 1. The following placard must be displayed on instru ment panel: "Occupy front seat when flying solo." NOTE 2. Prior to certification of any O-58B (Army L-3B, L-3C) aircraft, the following modifications shall be accomplished: (a) Remove the front back of the rear seat and perman ently install the rear back of the rear seat as follows: Remove rear back of rear seat and drill an 11/64 in . hole through both sides of the fork at the bottom of the vertical support one inch from the inside rounded e nd of the fork. Reinstall seat, sliding above-mentioned fork over the horizontal fuselage cross tube, insert an No. 8-32 x 1 1/4 steel machine screw and fasten with an acceptable No. 8-32 self-locking nut, or plain nut peening end of screw. (b) Remove the 1/4 in. bolt from the top of the rear control stick socket. Insert the control stick, and drill through both the socket and control stick with an "F" (.257) drill, 90 degrees from the original location of the bolt. Remove the spring clip and install the 1/4 in. bolt through the new hole, and fasten with an acceptable self- locking nut or a castle nut with a cotter pin. -END-