TCDS TC 2-577

MODELS: Douglas Army B-18, B-18A, B-18 (Special) T.C. NUMBER: 2-577 I - Model Army B-19, B-18A, B-19B, 9PCLM (Approved 4/25/46) Engines Two Wright Military R-1320-53 (See NOTE 4) Fuel 100 minimun octane aviation gasoline Engine limits except takeoff (low (Sea level) 35 in. Hg.. 2100 rpm (830 hp) (3,800 ft.) 35 in. 190. except takeoff (high blower) (5,500 ft.) 38 in. Hg.. 2100 rpm (812 hp) (9,500 £t.) 2200 pm (1000 hp) Maximum weight 23,200 1bs. (takeoff and landing) Required equipment Items 1, 2, 104. 201. 202. 203. 204, 205, 206, 207, 209, 301, 302 II - Model Army B-18 (Special), 9PCIM (Approved 3/31/47) Engines Two Wright Military R-1820-45 (See NOTES 4 and 6) Fuel 91 minimum octane aviation gasoline Engine limits Maxmum, except takeoff (low blower) (Sea level) 34.5 in. Hg.. 2100 rpm (830 hp) (3.200 ft.) 34.5 in. HJ.. 2100 rpm (880 hp) Takeoff, 37.5 in. Hg., 2200 rpm (930 hp) Maximum weight 1204, 205, 206, 261, 208, 361, 902 TrE 205. 206 307, 2081 30,10039 Required equipment 6, 7. 201, 202, 203, Specifications Pertinent to All Models: Airspeed limits Level flight or climb - 205 mph True Ind. Glide or dive - 243 mph True Ind. Flaps extended - 112 mph True Ind. C.G. range (+58.6) (20.5 percent MAC) to (+64.9) (25.0 percent MAC) Datum Leading edge of center section of wing MAC Leveling means Lugs located in rear bomb bay, forward of rear Baggage See NOTE 3(1) Seats Fuel capacity 764 gallons (4 tanks in center section wing - 2 front tanks of 177 gallons each (+48) and 2 rear of 205 gallons each (+94)). Left side 205 gallon gallons reserve. oil capacity gallons (two 29 gallon tanks) (-9) (See NOTE 5) Control surface Movements (7/8" droop) 29 degrees up Aileron tab 14.5 degrees up 10 degrees down Elevator 29 degrees up 19 degrees down Elevator tab 10 degrees up 9 degrees down Rudder 26 degrees right 32.5 degrees left 11 degrees right 11.5 degrees left Wing flaps 55 degrees down Serial Nos. Feligible All Army serial numbers Certification basis Airworthiness Certificate (only CAR 04a) Eligible for export as follows subject to inspection for equipment specified in Chapter XII of Manual of Procedures: a. Landplane - eligible Skiplane - not eligible other countries except Great Britain, Australia, and New Zealand. (Items included in required lists under specification pertinent to indi- vidual models may not be removed unless replaced by approved equivalent itens. The effect upon balance of all equipment changes nust be computed and the aircraft operation record revised accordingly. Values in inches shown in parenthesis after each item represent horizentel arms he tatum..plus len measured minus (-) ahead and plus (+) to the rear of the datum. sign preceding the weight of an optional iten indicates the net weight change between that iten and the equivalent required item. as airplanes of this model are obtained through disposal of surplus military specific information relative to the weight and location of some equipment items has not been obtained and the weight values, therefore, When equipment itens are removed or substitutions made, difference and location of such items should be obtained in order that the pertinent information may be added to the specification.) Propellers and Propeller Accessories (except de-icing equipment): Two propellers - Hamilton Standard hubs 23E50, blades 6163A-19 to 61634-20, Diameter 11'6-3/8" maximum, 11'3/31 mininum. For interchangeable blade models see Propeller Spec. No. 603 Pitch settings: LOW propeller feathering pumps (Pesco Two propeller feathering oil reservoirs Standard hubs 3550, blades 6105A-18 to 6105A-20, Low pitch setting Two constant speed governors No. 1A1 Propeller brake and brake control Engine and Engine Accessories (except de-icing equipment) : 101. Two vacuum pumps (Pesco 207D) 102. IWO fuel pumps (Pesco G-1) 4 1bs. 103. Two hydraulic pumps (Pesco 203 DA) 104. Iwo oil coolers (U-3190V with D-5 valve) 51 1bs. 105. Two starters Army Type C-21 (Eclipse 426) 60 1bs. 106. Hand pump, Type D-2 (Auxiliary oi: system) 107- Type B-3 108. Two fuel pumps, C-7 103. Two hydraulic pumps, Type AR Landing. Gear: Two 45x17:00x16 mail wheels (Bendix 3-3 with Duo brakes) (+23) 202. TWO 45x17:00x16 tires, 10-ply (+28) 203. Two 45x17:00x16 tubes (+28) 204. Tail wheel, Hayes 9:00x6 (+442) 205. 22x9:00x6 tail wheel tire, 8-ply (+442) 206- 22x9:00x6 tube (+442) 207. Four shock struts (Bendix 53420) (+29) 208. Tail wheel shock strut (Douglas Drawing 5044046 OI 5014046) (+423) Electric and Radio Equipment: 301. Two batteries Army D-6-A (Exide TAS-1/) 142 1bs. (+144) 302. Two generators Army E-5 or E-54 (Eclipse 790 or 310) 62 1bs. 303. Two landing and one passing lights (Types A-9 and B-1A) 7 1bs. Interior Equipment: 401. CAA Approved Operating Manual 404. Cabin heater and accessories (+131) 405. Seats: Pilot and co-pilot (Douglas Drawin] 5045564 Or 5026908) (-17 Navigator (Douglas Drawing 5027178) (+32 Radio operator (Douglas Drawing 5046172 0I 5027179) (+91) Windshield): de-icer equipment including boots, valves, fittings, etc. 502. Propeller de-icer equipment includin] pump, lines, tanks, etc. (-73) NOTE 1. certificated weight empty, Weight and Balance report including list of equipnent included in and loading instructions must be submitted for each aircraft with original inspector's report and each subsequent report covering change in equipment. Fach airplane must be weighed to determine its weight and balance prior to original certification, unless a satis- factory Army weight and balance report is available. NOTE 2. The following placards shall be placed on the instrument panel in full view of the pilot: c. Winot's compartment at all times. "This ispirees fill fer tate-ed in accordance with Part I of the CAA Approved Operating Manual. 'Intentional Acrobatics Prohibited." The manual shall be carried in the NOTE 3. Prior to certification as a civil aircraft, the following nust he accomplished: a . The pitot tube installation shall be reworked in such a manner that the distance between the front end of the mounting boom (which contacts the visible rear face of the pitot head) and the wing leading edge is 17-3/16 inches. b. Control cables and pulleys in the cabin should be suitably covered as protection from Jamming due to foreign objects. c. A master switch arrangement (accessible in flight to the pilot or co-pilot) must be installed in order that all electrical power, including batteries and generators, can be disconnected with one operation. All fuses must be made accessible in flight. e. The propeller feathering control sysien fuse must be replaced with non trip-free circuit breakers and a flame resistant cable be installed, if not now in use. f. The emergency exit requirements of CAR 04.462 must be complied with for airplanes provided with seats and safety belts for more than 5 I: Huetruments mist be marked for approved operation limitations. persons. Fuel tank filler caps or adjacent surfaces must be marked to indicate the minimum octane fuel and the tank capacity. i. The filler openings in the oil systen shall be plainly marked with the word "oil" and shall indicate the capacity. J. The autopilot servo units must be modified in accordance with pertinent AD-355 OI AD-618. k. Passenger seats and safety belt installation other than originallj provided by the manufacturer must be shown to meet the requiremerts 1. Cargo and baggage compartments must be placarded for the maximum permissible floor loadings. Ploor beans and flooring provided for such compartments should be capable of withstanding a limit load factor of 3.76 without undue permanent deformation and must have sufficient strength to withstand an ultimate load factor of 5.64. Adequate cargo tie-down provisions must be provided. Each aircraft must satisfactorily pass an inspection for conformity. possible hidden damage, and for workmanship and materials used in making any repairs and/or alterations. In making the inspection for ment thereof as needed in accordance with Airworthiness Directives for Douglas DC-} series aircraft. All other applicable DC-3 Air- worthiness Directives must also be complied with. If any changes have been made which would adversely affect its flight characteristics, the particular airplane must be flight tested. n. Any interior or exterior changes made to the primary structure or equipment nust be either according to approved Douglas drawings or satisfactorily substantiated. o. Upon completion of the conversion to certificated status, the manu- facturer's nameplate on the aircraft should be altered to include the date of conversion. In case the original nameplate is not sufficiently large to include this additional information, a similar plate should be installed near the original plate. Under no circumstances should the original or any succeeding nameplate be removed from the aircraft. The engines must incorporate either 1.023 inch or 1.026 inch damper pins instead of the old type 1,000 inch damper pins. NOTE 5. il capacity may be increased to 88 gallons when 30 dallon auxiliar anks is installed at (+56). NOTE 6. High blower operation of R-1820-45 engines not permissible. Engine must be locked or wired in low blower position.