TCDS ATC 558

MODELS: Boeing 247-D (Army C-73), 13 PCIM T.C. NUMBER: ATC 558 Engines 2 PEN Wasps S1H1-G or S3H1 or R-1340-AN-1 Fuel 87 minimum octane (CFR) aviation gasoline for S1H1-G engines 80 minimum octane (CFR) aviation gasoline for S3H1 or R-1340-AN-1 engines Placard limits For Wasp S1H1-G: Maximum except take-off, (straight line manifold pressure variation with altitude to 8000 ft.) 2200 pm (550 bp) Sea level) 35.0 in. Hg.. 2200 rpm (550 hp) Take-off (one minute). S3H1 and R-1340-AN-1: E9 (510 hp) Maximum except take-off, (straight line manifold pressure variation with altitude to 5000 ft.) 32.5 in.Hg.. 2200 rpm (550 hp) sea level) 34.0 in.Ng., rake-off (one minute), 34.0 in.Hg.. 2200 rpm (550 ap Propellers See Items 113 (a), Placard ceiling Placard speeds Glide or dive - 220 mph True Ind. (See NOTE 1-212: Level flight or climb - 180 mph True Ind. With S1H1-G engines and either Item 113(a) or 4600 ft. absolute (density altitude) engine inoperative with inoperative controllable propeller idling in high pitch. in standard air with either propeller braked in high pitch, blade down with the remaining engine at maximum, except take-off ip and 2250 rpm with a carburetor air temperature of 100 degrees F. (usable) at an indicated airspeed of 96 mph and 14084 lbs. (with de-icers installed but not operating) in standard air, with either engine inoperative, inoperative propeller fully feathered, operative engine at maximum, except take-off, power, mixture setting for best fuel-air ratio, carburetor air intake on "Cold Air" and With S3H1 or R-1340-AN-1 engines and Item 113 (b) See Part I of Approved CAA Operating Manual. Fuel capacity 273 gallons (3 tanks: one main in left wing - 136-1/2 gallons (+38.5), one main in right wing - 66-1/2 gallons (+22), one auxiliary in right 70 gallons (+54.5)) oil capacity NO. passengers Baggage 2400 1bs. (forward compartment 1400 1bs., rear compartment 1000 1bs.) Standard weight (See NOTES 1 and 6) C.G. limits (22 percent MAC) and (+20.86) (28.5 percent MAC), L.E. MAC (-20.27). Spec. basis Type Certificate No. 558 Serial Nos. 1946 and up manufactured prior to 9/30/39 and al1 (See NOTE 8.) AA? Nos. eligible. Approval expired as of EQUIPMENT: (Datum is front spar centerline) (See NOTE 3.) Class I: 101. Two engine ring cowls 72-81 1bs. 102. Two landing lights 27 1bs. 103. Two flares 42-47 1bs. 44 1bs. and tires with hydraulic brakes 282 1bs. Pressure fire extinguisher 26 1bs. 65-76 1bs. 43 1bs. Starter cranks 4 1bs. each Toilet equipment 8 1bs. 11 1bs. 16x7-3 tail wheel and tire 12 1bs. For use with S1H1-G engines only. Standard hubs 50039 or 3D40, blades 6101A-0 to 6101A-2, inclusive. 9' 10-1/8 minimum.): setting 24 degrees with 550 take- off hp and 20.5 degrees with 510 (See Item 207(a).) For use with S3H1 or R-1340-AN-1 engines only. Constant speed; 12D40 hubs and 6101A-12 to 6101A-14 blades, (Diameter 9'1 maximum, 8'10-5/8i minimum.); 1o% pitch 11.5 degrees; high pitch setting 27 degrees. Propeller accessories (required with Item 113(b) only) 2 propeller governors; Hamilton Standard model 115. Approved Operating Manual (required to be carried in pilot's compartment only when S3H1 or R-1340-AN-1 engines and 12D40/6101A-12 to -14 propellers are installed.) (See NOTE 10-) Class II: 201- Two engine covers 14 1bs. 202. Radio equipment Two-way complete 127 1bs. Stand-by receiver 18 1bs. 30 1bs. 203. Heating and ventilating: 83 1bs. Liquid heater 93 1bs- Heating and ventilating system 124 1bs- 204. Vacuum pumps 205. Soundproofing and carpet 87 1bs. 206. Automatic pilot installation 97 1bs. 207. Propeller accessories: (a) Constant speed controls with Item 113 (a) (low pitch setting 17 degrees) 10 1bs. (b) Brakes (Air Associates HC-950) 208. Stewardess equipment 122 Ibs. 209- Tools and first aid kit 10 1bs. De-icer installation (See NOTE 6) : De-icer equipment - De-icer equipment - removable 32 1bs. Two propeller spinners Propeller de-icer fluid 23 1bs. Miscellaneous items as noted in approved weight and balance report Por use with S1H1-G engines (ruli feathering), hubs 23D40, blades Hamilton Standard hydromatic 6183A-0 to 6183A-2, inclusive. interchangeable blade models see Prop. 10" 1/2" maximum, 9' 9-7/8" minimum; low pitch setting 18 degrees. 65 1bs.* (-54) Class III: None NOTE 1. When standard weight is reduced to 13650 1bs., the glide or dive speed may be increased to 230 mph True Ind. NOTE 2. Weight of stewardess is 135 1bs. Weight and balance report including list of equipment included in certificated weight empty, and loading instructions when necessary, be submitted with original inspector's report and each subsequent report covering changes in such equipment. Pabric covered rudder has fabric covered trim tab balancing tab. Metal covered rudder with aerodynamic balance has metal covered trim tab Metal covered rudder with aerodynamic balance removed has metal covered trim tab and balancing tab. Model 247-D fin, Boeing Drawing 15-2777, must be installed or Model 24? fin, Boeing Drawing 15-2502, must be altered in accordance with Boeing Drawing 15-2777 except that trailing edge fairing may be extended in accordance with united Air Lines Rudder must conform with Boeing Drawing 15-2503, revision J, except that deviation shown on United Air Lines Drawing 3U-33 may be Fabric or metal covered elevator has metal covered trim tab NOTE 5. Hostess jump seat in rear is not to be used by passenger. NOTE 6. Standard weight may be increased 84 lbs. when complete de-icer is installed. NOTE Australia and few Sealand (6/24/cointries except Canada, Great Britain, NOTE 8. The following serial numbers, converted from Model 247 (Approved Type Certificate No. 50, 1412, eliu through 1726, 1728 through 1737, 1686 through 1700, 1702. 1706 through 1710. 1740 and 1741. Aircraft equipped with S3H1 or R-1340-AN-1 engines require the following modifications prior to certification: Add a 3-inch diameter flexible blast tube running from between cylinders 3 and 4 and discharging so that cooling air is directed along the front side of the oil tank. Add a scoop around the oil cooler inlet extending 3 inches forward from the leading edge of the wing. Add a rearvard facing scoop over the oil cooler air outlet. scoop should cover two-thirds of the length of the air outlet opening and should be 4 inches high at its rear end. #O7 6101 12 10-10 propeller are installe: inie alriane shall b2807 placard should be placed on the instrument panel in ¿This airplane shall be operated in accordance with Part I of the CAA Approved Operating Manual the Boeing 247-D airplane."