# TCDS ATC 540: Douglas Aircraft Co. Inc. - Type: Type certificate data sheet - Status: Current - Holder: Douglas Aircraft Co. Inc. - Revision: 0 - Product: Aircraft, Small Airplane - Registered aircraft: 2, by the registry models matched to it (OpenAirDocs) - Data sheet PDF: https://openairdocs.org/files/sha256/0f/1a/0f1af5edf4f5959642927f70d30db43f580f199258bbdc9e805331dc0a32ef1e - FAA DRS: https://drs.faa.gov/browse/excelExternalWindow/43220EA5C959483385256735004D595A.0001 - Page: https://openairdocs.org/tcds/ATC%20540 ## Models (3) As the data sheet lists them. - Army C-39 - Army C-42 - DC-2 (Army C-32; C-32A; C-34; Navy R2D-1) ## What the data sheet says This is OCR from the scanned FAA data sheet. OCR can misread letters and numbers. ```text MODELS: Douglas DC-2 (AImy C-32, C-32A, C-34; Navy R2D-1), AIny C-39, C-42 I.C. NUMBER: ATC 540 I - Mode1 DC-2 (Army C-32, C-32А, C-34; Navy R2D-1), 16-17-18 PCIM Engines 2 Wright Cyclones (a) SGR-1920F-3; OI (b) SGR- 1820F-2 (below serial No. 22747) ; or SGF-1820F-2 (serial No. 22747 and up); or (e) SGR-1820F-53; OI (f) SGR-1820F-52 (except 25319 thru 25322) or SGR-1820F-2B; SGR-1920F-3B; OI (h) GR- 1920F-24 0I GR-1820F-52 (serial Nos. 25319 thru 25322 and Engine limits (Using 87 minimum octane aviation fuel (See NOTE 6) (See NOTES 9 and 10) Maxinum continuous 34-1/2 in. Hg., 1950 Ipm (700 hp) Takeoff (one minute) 37-1/2 in. Ha.. 1950 rpm (710 hp) Takeoff (one minute) 36 in. Hg., taximum continuous 33-1/2 in. H9 1950 Ipn (700 họl laxinum continuous 34-1/2 in. Hg. 1950 pm (720 hp) 37-1/2 in. Ho., 1950 rpm (750 hp Maximum continuous 36-1/2 in. Ho. takeoff (one minute) 37-1/2 in. Hg., 195) Ipm (750 hp) • 1950 [рп (750 hp) makeour (one mouse) 31-1/2 in. Ho.. 2200 kon (770 np) Main continuous 4-12. 2230150h1 akeoff (one minute) 37-1/2 in. Ha.. 2200 Ipm (770 hp Maxinun continuous 35 in. HJ.. 1950 Ipm (750 hp) rakeoff (one minute) 36-1/2 in. H9.. 1350 cp.m (750 bp) Propellers controllable metal (standard installation for engin geared 16:11, Hamilton Standard hubs 3550 or 8452, blades 61114-6. For old type engine neare! and 15%, NUTS 4 00 153g itoms 85, 127, 133, 3:5, Hamilton Standard, hubs 3E40 or Airspeed limits for weights up to and including 19,560 1bs. Level flight or climb - 190 mph True Ind. Glide or dive - 434 mph True Ind. Flaps extended - 100 nph True Ind. For weights betweer ld,560 1bs. and 19,000 1bs. Level flight or clinb - 134 moh True Ind. Glide or dive - 2l9 mpt True Ind. Flaps extended - 100 oph True Ind. Ceilina May be realized unter conditions shown: A por engines Constant speed propeller 16:11 - HuDs 3350 Or 9452, 611906461051-10 61050-24 3:5 - dubs 3540 0r (Item) (Ibs.) (absolute) (a) • (D) 17,560 7600 (a). (h) 18,200 8500 (C) • 18,200 6000 (c) • (d) . (h) 16.560 5100 19,200 9500 (3) (0) 18,560 5600 13,200 8000 18,560 7100 Additional conditions: Standard air octane fuel Fither engine inoperative Inoperative propeller idling at 750 spm B. Full feathering propeller: True Ind. Surface Propeller Engine Propeller celling leight Airspeed De-Icers De-Icers (Item) (Item No.) (1bs.) REM (MPH) Installed (Iten No.) (b) 127 (a) 10,000 (abs.) 18,200 None (b) 127 (a) 9,100 (abs.) 18,560 Hone (b) 127 (a) 0,000 (usable) 18,200 1950 100 Yes 135 (b) 127 (a) 8,400 (usable) 19,560 1950 100 res 135 (b) 127 (D) 9,250 18,200 .. None (b) 127 (b) 9,350 (abs.| 18,560 None (c, €,9) 127 (C) 9,500 (usable) 19,000 2100 110 None (£) 134 (a) 8,700 (usable) 19,000 2100 110 None (£) 134 (b) 9,100 (usable) 18,200 2100 102 NO None (E) 134 (b) 9,600 (usable) 13,560 2100 102 NO None (f) 134 (b) 8,000 (usable) 19,000 2100 102 NO None (g) 134 (b) 9,500 (usable) 19,000 2100 110 YO None (g) 134 (c) 9.900 (usable) 10,000 2100 102 NO None Additional conditions: Standard air 87 octane fuel Either engine inoperative Inoperative propeller fully feathered Carbureton air intake on "Cold Air" Manifold pressure - full throttle Fuel capacity 31 tary fathe and fate stone an a main Oil capacity 38 gallons (2 tanks: one in each nacelle 19 gallons each) (-25) No. passengers Baggage 2000 1bs. (compartment forward of cabin 1000 1bs. (-76) and compartment aft of cabin 1000 1bs. (+327)) Maximum weight Landing 19,000 1bs. Cr 18,200 1bs. (see NOTE 2) or 18,560 1bs. (See NOTES 2, 3 and 8) (See NOTES 2, 3, 8, 11) C.G. limits and (+69) - Leveling pins for weighing at (*199) and (+219) Spec. basis pproved Type Certificate No. 54( Serial Nos. 237 and up manufactured prior to 9/30/39 eligible Approval expired as of that date. FQUIPMENT: (Datum is center section wing ) (* Means net increase) Class I: Two engine collector rings 110 1bs. - 44 Two engine ring cowls 96 1bs. Two landing and one warning lights (in nose) 9 1bs. (-178) 4 - Flares (two 3 minute) 36 1bs. (+307) 5. Flare brackets (two) 12 1bs. (+368) 6. Oil radiators and scoops (two) 56 lbs. (-26) Two starters (electric) 63 1bs. (-17) 8. Battery 12V 63 1bs. (-59.5) Generator 39 1bs. (-31.5) 10. Robot pilot lines and brackets 13 1bs. 11. Robot mechanism (mag. cast) 71 1bs. (-124) 12. Fourteen serving trays 19 1bs. 13- 15.00-16 wheels (Bendix mag. dual brakes) 180 1bs. (+29) 14. 15.00-16 treaded tires 10-ply Or 8-ply H.D. (wheels must be placarded for these special tires) 182 1bs. (+29) 15. Two cactus-proof 15.00-16 tubes 40 1bs. (+28) 16- Two vacuum pumps 12 1bs. (-30) 17. Two spark retard solenoids 10 1bs. (-30) 18. Wing fairing fillets 60 1bs. (+84.5) 19- Wing connection fairings 7 1bs. (+84.5) 20. Radio (THA) transmitter and receiver 124 1bs. (+307) 21. Radio (TWA) dyn. and h'd 50 Ibs. (-70) 22. Pressure fire extinguisher system 30 1bs. (-24) 23. Steam heater system and 5 quarts water 101 1bs. (-88) 24. Ventilating system 77 1bs. (+100) 25. Cabin rug 17 1bs. and lavatory mat 3 lbs. 20 1bs. (+120) 26. Toilet equipment 32 Ibs. (+290) 27. Container and 4 gallons water 38 1bs. (+296) 28. Hold-down straps, etc. 12 1bs. 29- Tail wheel plain tube 2 Ibs. (+419) 30. Tail wheel 8.00-5, 6-ply tire 22 1bs. (+419) 31. Tail wheel oleo strut (Bendix 53103) 10 1bs. (+405) 32. Oildraulic manually operated retracting landing gear system (including :ype FF-1 or FF-1A oildraulic 124 1bs. (+9) 33. Equipped with wing split flaps (I.F.) oildraulic manually operated systen 127 Ibs. 34- and right aileron with adjustable tabs, manually (+476) 35. 81 1bs. (-98) 36. fuel and oil system, exclusive of 33 gallon capacity 45 1bs. (-26) Class II: 41. Steward's folding chair (adjacent to cabin entrance door) 16 1bs. (+267.5) 42. Radio operator's chair (in forward companionway; folds under floor) 16 1bs. (-110) 43. Radio operator's chair (in baggage compartment) 15 1bs. (+327) 44. Radio complete (W.E.) 193 1bs. 45. Radio added accessories 3 Ibs. 46. Radio complete (P.A.A.) 19 1bs. (-85) 47. Radio added accessories 3 1bs. 48. Radio complete (GP-1) 150 1bs. (+328) 49. Navigator's chair (in forward companion way; folds against bulkhead) 5 1bs. Extra battery (installed in forward baggage compartment) 63 1bs. (-75) battery box (installed in forward baggage compartment) 7 1bs. (-75.5) wiring and conduit 10 lbs. Heavy duty battery (under forward baggage compartment - standard location) 78 1bs. (-60) 54. Electric hydraulic pump installation 37 1bs. 55. Wing landing light installation and reinforcements 63 1bs. (+15) 56. Wing landing light installation one 26 1bs. (+15) 57. Oxygen installation (less tanks) 10 1bs. 58. Cabin DeLuxe accessories 33 1bs. (+105) 59. Cabin accessories (Navy) 14 1bs. (+106) 60- Heavier type cabin paneling 3? 1bs.* (*100) 61. Added cabin paneling 12 1bs. * (+100) 62. Cabin light weight sound-proofing Net Decrease 10 1bs. (+100) 63. Rations and buffet 51 1bs. (+300) 64. 15.00-16 wheels (Bendix dural, dual brake) 206 Ibs. (+29) 65. (a) 15.00-16 non-treaded 10-ply or 8-piy H.D. 203 1bs. (+29) 66. 16.00-16 treaded tires 10-piy 15.00-16 tire liners 215 1bs. 24 1bs. (+28) (+28) 67. 16.00-16 cactus-proof tubes 47 1bs. (+29) 68- 16.00-16 plain tire tubes 29 1bs. (+28) 69. Auxiliary brakes on tires 6 1bs. 70. 8.00-5 cactus-proof tail wheel tube 4 Ibs. (+419) 710 Tail wheel self-centering device 12 1bs. (+403) 72. Tail wheel frame reinforcement 2 1bs.* (+403) 73. Robot mechanism (dural castings) 18 lbs.* (-88) 74. De-icer installation (fixed portion 61 LDS.. removable 60 1bs.) (See NOTE 7) 121 1bs. 75. Mechanical safety latch for landing gear 10 1bs. (+29) 76- Two extra engine vacuum drive units 24 1bs. (-30) 77. One vacuum pump 6 1bs. (-30) 78. Heavier type carburetor air scoop 7 lbs.* (-29) 79. Fuel system cross feed 12 1bs. (+23) 80. Heavier type ice buffer 9 1bs.* (-75) 81• Baggage compartment screen 5 1b5- 1bs. (+327) 82- Additional cockpit heater control (-106) 83. Steam heater system with 11 quarts 121 1bs. (-89) 84. Additions to ventilating system 2 lbs. (*100) 85. Propeller blades Hamilton Standard 6105A-18 (replacing Hamilton Standard (See NOTES 9 and 10) 36 1bs.* -70 86. (a) Heavier type propeller contro. 5 lbs. 1-70 Individual propeller controls (in cockpit) 2 lbs. * (-85) 87. Special factory installed reinforcement to fuselage and center section wing (See NOTE 25 1bs. (+87) 89- 89. Auxiliary radio equipment (H.E.) outer wing factory built with beaded 17 1bs. type ribs (replacing factory wing with riveted type ribs) Net Decrease 30 1bs. (+94.5) 90- (a) Small size strong box (installed in forward baggage compartment) 5 1bs. (-69) (D) Large size strong box (installed in forward baggage compartment) 23 Ibs. (-68) 91. Small type generator 28 lbs. (-28) 92- 0il radiator 9 in. type (replacing standard type) 3 1bs.* (-26) 93. Heavier gage fuel tanks (replacing standard tanks) 29 lbs.* (+72) 94- Additional gyro and horizon instrument installation 10 1bs. (-157) 95. Revised vertical control surfaces in accordance with Douglas Drawings 5000642D and 5004183A (replacing standard vertical control surfaces) 31 1bs.* (+436) (When this installation is made, the standard rudder tab control unit must be replaced by revised rudder tab control unit in accordance with Douglas Drawing 5006079 (-141)) (See Item 99) 96. Wing reinforcements (outer and center section) (See NOTE 11 1bs. (+35) 97. Factory installed alternate electric installation Net Decrease 78 1b5. 98. External paint (trimming) 1bs. 99. Aileron hinge fittings, Douglas Drawin? 125397. revision G, may be replaced with aileron hinge fittings, Douglas Drawing 125387, revision F No change in weight (This replacement is recommended whenever installation of Item 95 is made.) 100. Reworked thicker type rudder (Douglas Drawing 570729) No change in weight 101. Floating rib reinforcement 5 1bs.* (+73) 102- (a) fuel dump valves and controls (Douglas Drawing No. 432077) (See NOTE 8) 9 1bs. (+49) (b) Fuel dump valve chute (Douglas Drawing No. 5046038) (See NOTE 3) 12 1bs. (+115) (c) Extendable type fuel dump chute installation in accordance with Douglas Drawing No. 5080140 (See NOTE 3) (+165.5) 103. Estimated addition (service pickup) 104. Synchoroscope (Magneto) ~ (-98) 105. Estimated weight of wing repair (++5) 106. Valve lubricating harness 18 (-52) 107. baggage compartment and floor reinforcement (-74) 108. Extra leather trim (doors) 102. Additional carburetor air intake heaters 10 lbs.* (-32) 110. Misce. distributed throughout airplanes) 30 Ibs. * 111. Heavier type collector ring 3 in. intensifier 18 lbs.* 1-40 112. Floor reinforcement 3 lbs.' (+94) 113. (a) Hamilton Standard constant speed propeller governor on engine 9 1bs. (-50) (b) Heavier engine nose case with governor pad ** lbs.* (-60) (c) Hamilton Standard 20 degrees pro 10 degree brackets 27 lbs.* (-74) 114. Addition to heating system 3 lbs.* (-33) 115. Wright air scoops 30 1bs. (-39) 116- 15.00-16 smooth tread tires, extra duty, 10-ply 184 1bs. 117. oleo (landing gear) heavier type 10 lbs.* (+29) 118. (a) Two F-53 engines (replacing two F-3 engines) 70 Ibs. * (-52) (b) Two F-3B engines (replacing two F-3 engines) 70 1bs.* (-52) (c) Iwo F-3B engines (replacing two F-3A engines) 17 lbs.* 119. Collector engines (replacing al engines) 70 1hs.* -5- 120- Collector ring with double intensifier tubes 10 1bs.* 121. Flap reinforcement 5 1bs. * (-149) 122. Miscellaneous items as noted in approved weight and balance report. 123. Propeller de-icer (includes 2 slinger rings and tank with 3 gallons fluid in forward baggage compartment. 43 1bs. (Forward baggage may be reduced 43 1bs. in lieu of C.G. check for this instal- lation) 124. Two 45 in. streamline wheels and tires 136 1bs.* (+11) 125. Anilol supply tank with 10 gallons anilol installed under roof of front baggage compartment per Pan American Fuel Development Corp. Drawing DA3 Complete installation 100 1hs. (Forward baggage may be reduced 90 1bs. in lieu of C.G. check for this instal- lation) 126. Aileron slot fairings installed in accordance with Douglas Drawing No. 5015631 21 1bs. (+150) 127. (a) Two Curtiss full feathering electric props, hubs C532D, blade 89303-18 or 89305-18, including Two Curtiss full-feathering electric props, hubs C5315S, blades 614Cc1.5-12A or 614-1C15-12 614-1C1.5-12 Change A (or later) (11 ft. diameter), including slinger rings, wiring, for F3A engines only Two Curtiss full-featherinq electric propellers, hubs C5315S, (11 ft. 6 in. diameter), including wiring, F-3B, P-52, bradrets, etc. engines only (low pitch setting 128. Conversion of two Wright SGR-1820F-3 engines to SGR-1820F-3A engines 53 1bs.* (-52) 129. .018 stainless steel inner ring cowl, Douglas Drawing No. 5076264 (replacing • 040 aluminum alloy cowl) 11 1bs.* (-36.5) Engine driven hydraulic system installed with Douglas Drawing No. 5039858 dated 1/3/39, or later 2? lbs.* (-35) 131. Aileron hinge arm and trim tab cut-out cover plates installed in accordance with Douglas Drawing No. 5080776 2 1bs.* (+145) Intake de-icing system using anilol in accordance with Braniff Drawing 428H. Complete installation (forward baggage may be reduced 25 lbs. in lieu of C.G. check for this installation) 25 1bs. Propeller blades Hamilton Standard 6105A-24 (See NOTES 9 and 10) 134. (a) Two Hamilton Standard hydromatic full feathering 23E50, blades 6153A-18 (11'6" diameter) OI 62614-2 (1114" diameter) including controls. 01 1bs.* Two Hamilton Standard hydromatic full feathering props, blades 6259A-0 including controls (See NOTES 9 and 10) 308 1bs. Two Hamilton Standard hydromatic full feathering propellers, hubs 33D50, blades 6495A-18 or Specification No. 749) (See NOTES 9 and 10) 339 Ibs. Goodrich propeller de-icing NOTE 1. weight and balance report including list of equipment included in certificated weight empty, and loading instructions when necessary, must be submitted for each aircraft with original inspector's report and each subsequent report covering change in equipnent. All airplanes eligible must be eguipped with the reworked stronger type landing gear upper structure in accordance with Douglas Drawing The reworked structure may be identified by the No. "18200" stamped on the lower inboard forging. Until this change is made the airplane standard weight shall be limited to 18,000 ibs. serial numbers 1290 to 1300, 1307 to 1316, inclusive, 1322 and up have been or will be equipped at the factorv with the rein- NOTE 3. The landing weight may be increased to 18,560 1bs. provided Itens 95, 87, and 72 are installed. Item 96 (wing and fuselade reinforcement) Item 87 must be installed in accordance with Douglas Drawings Nos. 50000717, 530536 revision Y, and 531027 revision M. NOTE 4. Deleted - 5/12/43. NOTE 5. Eligible for export as follows subject to inspection for required equipment (9/30/39) : (a) Canada - Landplane - Skiplane - not eligible. (b) All other countries except New Zealand. NOTE 6. 80 Minimum octane aviation fuel may be used provided no engine is operated at more than 550 hp (operatiny instructions should he prepared accordingly). This applies to F-2, F-2A, F-3, and F-34 engines only. NOTE 1. Landing and takeoff weights may be increased by an anount equal to .006 x landing weight when complete de-icer is installed. NOTE 8. The following operational limitations shall be observed: a . If provisions other than items 102(a) the fuel dump valves shall be nade positively inoperative. b. If items 102(a) and (c) are installe], the aircraft operation recorl shall incorporate one of the following statements, as the case may Fuel shall not be dumped except in accordance with the provisions of CAR 50.900." (2) Air Carrier. (a) With authorized weight in excess of landing weight &Landing shall not be made at a weight in excess of landing weight except in accordance with CAR 61.7811. dumped except in accordance with CAR 61.7811 and then only if the pilot deems it safer than landing at a weight in (b) With authorized weight not in excess of landing weight &Fuel shall not be dumped except in accordance with CAR 61.7811." NOTE 9. continuous operation is to be avoided in accordance with the folloving table: Engine Avoid Continuous Propeller One Rear Operation Between the Model Model Geared Damper Following Engine RPM Pin Dia. All propellers A11 None 1300 and 1500 Ham. Std. blades 6105A See NOTE 10 61119-5 16:11 1750 and 1850 61534-18 F25,F52 16:11 1.023" 1500 and 1600 6261A-2 F2B. F52 16:11 1.023" 1500 and 1600 6259A-0 P28,952,P3B 16:11 1.023" No restrictions 6495A-18 16:11 1.000" 1750 and 2150 (Takeoff should be only at 2200 RPM) 64954-19 16:11 1.023" NO restrictions Item 85 eligible on F-3, 33-1/2 in. Hg.. 2100 Ipm (935 hp) with the following Items 85 and 133 eligible on F-53 or F-33 Hg.. 2100 rpm (735 hp) Item 134(a) eligible on F-23 or #-52 engines only. F-38, or =-52 engines only. Iten 134 (c) eligible on F-3B engine only. NOTE 11. JOTES 2, 3 and 8 are complied with. F-25, and (c), or equivalent, must 31 or 134 (c) must be installed. and Item 127 (C). Items 102 (a) must also be installed. II - Army Model C-39 and C-42, 16-17 PCIM (See NOTE 3) Engine 2 Wright Cvclones GR-1820-55 or GR-1820G-2 Fuel e1 minimum octane aviation gasoline Engine limits GR-1820-55: Maximum, except takeoff (S. L.) 34.5 1n. Hg., 2100 cpm (805 hp) (3900 ft.) 34.5 in. H1.. 2100 rpm (635 hp Takeoff (one minute) 40.0 in. Hg., 2200 rpm (975 hp) GR-1820G-2: Maxinum, except takeoff (S.L.) 34.5 in. H9.. 2100 pm (820 hp) (5800 ft.) 34.5 in. Hg., 2100 rpm (850 hp Takeoff (one minute) 40.0 in. Hg.. 2200 Ipm (1000 hp) Airspeed limits Level flight or climb - 176 mph True Ind. Glide or dive - 211 mph True Ind. Flaps extended - 100 mph True Ind. Ceiling (See CAA Approved Operating Manual) C.G. range (+5303) to (+66.2) Datum Leading edge of center section wing Leveling means Pins at (+199) and (+21?) Maximum weight 21,500 1bs. (Air Carrier Passenger) 23,000 1bs. (Air Carrier Cargo) Baggage 1000 1bs. maximum in compartment between fuselage stations 62 and 118.5 (-76) Cargo 700 1bs. maximum per floor beam in main cabin, uniformly distributed Fuel capacity 702 gallons (4 tanks in 2s wing; 2 main including fuel system 167 gallons (+94) (See NOTE 3) 184 gallons each (+48) and 2 auxiliary, Oil capacity 58 gallons (1 tank in each nacelle of 29 gallons (-6) including capacity of oil system) Control surface Elevator 30 degrees up 25 degrees down movements Elevator tabs 10 degrees up 10 degrees down Aileron 29 đegrees up 15 degrees down Aileron tabs (right) 12 degrees up 12 degrees down Rudder 27 degrees right 27 degrees left Rudder tab Is degrees right 13 degrees left Serial Nos. eligible (C-39) 2057 through 2059, and 2061 through 2092; (C-42) 2060 Required equipment 102, 103. 200. 201, 202. 203, 204. 205. 206, 207, 300, 301, 303, 304, 305, 306, 401. 402, 501 (a) and (b), 502, 503. 700 Export eligibility Eligible for export as follows subject to inspection for equipment specifiei in Chapter XII of Inspection Handbook: - Landplane - Skiplane - not eligible. (b) All other countries except Australia and New Zealand. EQUIPMENT: Propellers and Propeller Accessories (Except De-Icing Equipment): Two Hamilton Standard 3-blade metal propellers, hubs 23B50, blades 6353A-19 (including slinger rings), low pitch setting 16 degrees at 42 in. station. For interchangeable blade models see NOTE 6 Of Propeller Specification 795 1bs. (-73) 101. Constant speed propeller controls (Hyd. Hamilton Standard) (Douglas Drawing 5075580) 15 1bs. (-71) 102. Propeller feathering control (Douglas Drawing 5075590) 16 1bs. (-34) 103. Two hydraulic propeller feathering pumps (Pesco) (-24) Engine and Engine Accessories (Except De-Icing Eguipment): 200. Two vacuum pumps (Type B-3) 10 1bs. (-48) 201. Two exhaust collector rings (-53) 202. Two starters (Eclipse C-21) (-31) 203. Pressure fire extinguishers and system (Lux) (-88) 204. Two ? in. oil coolers, scoops, etc. (5075035) 68 1bs. (-27) 205. oil dilution system 206. Iwo engine driven fuel pumps (Pesco G-1) 207. Wobble pump (Type D-12) Landing Gear and Floats: Two 16.00-16 wheels (B-1) with 14x3 duo (+29) 16.00-16, 10 or 12 ply treaded tires (+28) cactus proof (+28) Four landing gear shock absorber struts (Drawing 5014049) (+29) 18x8-5 tail wheel (Variety) (+427) 9.00-5, 6-ply tail wheel tire and tube (inflation pressure +427 shock strut (Drawing 5075133) (+413 14x3 duo servo brakes Use actual weight change Electrical Equipment: 400. Two batteries (Type D-6) 131 1bs. (-77) Two generators (Type Е-7) 63 1bs. (-33) Two landing and one passing lights 17 1bs. (+23) Interior Equipment: 500. Radio operator's table 12 1bs. (+303) 501. (a) One fire extinguisher, Type A-2 and brackets 7 ibs. (-86) (b) One fire extinguisher, Type A-2 and brackets 7 lhs. (+300) 502. Standard instruments (including lines and brackets) 90 1bs. (-116) 503. Cabin heaters and ventilation system and 6 quarts water (Steam) 167 1bs. (-7) 504. Lavatory equipment (See NOTE 2) 38 1bs. (+342) 505. Water tank installation (lavatory and 5 gallons water) 51 1bs. (+356) 506. Iwo flares (3 minute) Wiley Type A-8 and brackets 45 1bs. (+358) 507. Radio operator's seat (Douglas Drawing 5076133) 12 1bs. (+279) De-Icer Equipment (Propeller, Wing and windshield) 600. Windshield de-icer equipment including 601. Hopeller de-icer equipment including 7 1bs. (-114) lines, tank, etc. 17 1bs. (-90) Miscellaneous 701. Installation main cabin cargo hold down (5075022) 12 1bs. (+88) Current weight and balance report including list of eguipment included in certificated weight empty, and loading instructions when nation and at all times theater at the in the care of tirier at all times thereafter operators having an approved weight control system) . The following placards should be displayed in locations noted: Lavatory door: "THIS ROOM NOT TO BE OCCUPIED DURING TAKE-OFF OR LANDING." (b) At fuel selector valves: "FILL REAR FUEL TANKS FIRST AND USE FUEL PROM FRONT TANKS FIRST. NEVER HAVE LESS THAN FULL FUEL IN REAR TANK UNLESS FRONT TANKS (c) On the instrument panel in full view of the pilot: 'THIS AIRPLANE SHALL BE OPERATED IN ACCORDANCE WITH PART I OF THE CAA APPROVED OPERATING MANUAL FOR DOUGLAS MODEL C-39 AIRPLANE. THIS MANUAL SHALL BE CARRIED IN THE PILOT'S COMPARTMENT.I (Copies of the approved CAA Approved Operating Manual may be obtained from Aircraft Service, CAA, Washington 25, D.C.) Prior to certification of the Army Model C-39 or C-42 as a civil aircrait, the following must be accomplished: Pach aircraft must satisfactorily pass an inspection for confornity, possible hidden damage, and for workmanship and materials used in making any repairs and/or alterations. In making the inspection for hidden damage, the outer wing panels nust be removed to permit inspection of the doublers and attaching angles for defects and replacement thereof and needed in accordance with the Airworthi- ness Directives for Douglas DC-3 series aircraft as are pertinent adverse lattect the ight characteristics, the particular airplane If any changes have been made must be flight tested. Instrument markings and placards must be installed as reguired by this specification. Attention should be given to the windshield equipment and it should be determined that a satisfactory windshield wiper is installed. The military litter boxes, litters, and supporting structure should Such brackets and supporting structure as will not interfere with the safe operation of the aircraft may, at the operator's discretion, be left in the aircraft as long as the equipment has been rendered inoperative. Flares and flare system as required for the particular operation any interior or exterior changes made to the primary structure or equipment must be either according to approved Douglas drawings or satisfactorily substantiated. Approved wing position lights similar to those installed on the Douglas Model DC-3 must be installed, Douglas drawings 5003503, 5006262 and 5160600 may be referred to in making this installation. The tail light must be replaced with approved unit. switch must be installed in accordance with Douglas Project Sketch 5-840706. The propeller feathering lines must be revised co conform with Douglas Project Sketch No. 5-840705. A portable fire extinguisher accessible to the pilot and co-pilot must be installed in the pilot's compartment. The fire extinquisher mounted at station -86.0 may be moved to the new If this is done, the change in balance should be suitably If the aircraft is certificated as ACP, a satisfactory seat belt sign, visible to all passengers, should be installed in the passenger The gasoline filler caps should be marked with the word "Fuel" and the "Min. Octane Rating" of the fuel that may be used for the engine installation. The oil filler caps should be marked with the word "oil". If the aircraft is to be used in Air Carrier Service, hether all hose used in the oil-in line is approved fire-resistant and if not, replace with approved fire-resistant hose as soon as it becomes available. If the aircraft is to be used in Air Carrier Service, the acceptability and airworthiness of any radio equipment installed in the particular aircraft must be determined by the Chief, Air Carrier Maintenance Upon completion of the conversion to certificated status, the manufacturer'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 no circumstances, the aircraft. ``` ## ADs None name its models. ## Registered aircraft by registry model (OpenAirDocs) - [Douglas DC2](https://openairdocs.org/model/douglas-dc2): 2 aircraft (registry code 3021302) ## STCs approved under this data sheet (6) - [STC SA04652CH](https://openairdocs.org/stc/SA04652CH): To allow use of 100R grade aviation fuel meeting Swift Fuel, LLC specification. Swift Fuels LLC - [STC SA02268CH](https://openairdocs.org/stc/SA02268CH): Installation of Airwolf Filter Corp. Air Oil Separator. Airwolf Filter Corporation - [STC SA01406NY](https://openairdocs.org/stc/SA01406NY): Installation of Airwolf remote mounted engine oil filter kit AFC-K017 on single and multi-engine fixed light aircraft and rotary wing. Airwolf Filter Corporation - [STC SA01734SE](https://openairdocs.org/stc/SA01734SE): Application of Stewart Systems synthetic fabric covering system to aircraft fuselage, wings, tail surfaces, control surfaces and related parts.. Andrew D. Humphrey - [STC SA8075SW](https://openairdocs.org/stc/SA8075SW): Installation of fiberglass covering. (M-62 SERIES PT-19) (G-73 SCHWEIZER). Razorback Fabrics Inc - [STC SA4-31](https://openairdocs.org/stc/SA4-31): Wright R1820-52 engines and Hamilton Standard 33D50/6511-9 propellers.. Mercer D W --- 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.