# TCDS A-618: The Boeing Company - Type: Type certificate data sheet - Status: Current - Holder: The Boeing Company - Revision: 23 - Revised: September 27, 2010 - Product: Aircraft, Large Airplane - Registered aircraft: 8, by the registry models matched to it (OpenAirDocs) - Data sheet PDF: https://openairdocs.org/files/sha256/b0/f7/b0f795a71146eca78522ea9326e7df42207ff3a5c5c542c66a57a372144d5935 - FAA DRS: https://drs.faa.gov/browse/excelExternalWindow/47B08B9DB4B8BA99862577DC00575F64.0001 - Page: https://openairdocs.org/tcds/A-618 ## Models (4) As the data sheet lists them. - DC3-G202A - DC3-G102A - DC3-G103A - DC3-G102 ## What the data sheet says From the PDF's text layer, line by line; tables lose their columns. The PDF is the record. ```text Page No. 1 2 3 4 5 6 7 8 9 10 11 12 13 14 15 16 17 Rev. No. 23 - - - - - - - - - - - - - - - - DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION A-618 Revision 23 BOEING DC3-G102 DC3-G102A(Army C-49E, C-50, C-50A, C-50B, C-50C, C-50D, C-51) DC3-G103A DC3-G202A(Army C-49, C-49A, C-49B, C-49C, C-49D, C-49J, C-49K; Navy R4D-2) September 27, 2010 AIRCRAFT SPECIFICATION NO. A-618 Type Certificate Holder The Boeing Company 4000 Lakewood Boulevard Long Beach, California 90808 Type Certificate Holder Record McDonnell Douglas Cor poration, Long Beach, California merged with The Boeing Company in 1997, Transferred Type Certificate to The Boeing Company on September 27, 2010. Douglas Aircraft Company, Inc., Santa Monica California merged with McDonnell Aircraft Corporation August 25, 1967 I - Model DC3-G102, approved September 20, 1937 Engines 2 Wright Cyclones GR1820G-102 Fuel 90 min. grade aviation gasoline Engine limits Maximum continuous (Sea level) 36.7 in. Hg, 2200 rpm (900 hp) (Straight line manifold variation with altitude to 6000 ft.) 35.0 in. Hg., 2200 rpm (900 hp) Take-off (one minute), 43.0 in. Hg, 2350 rpm (1100 hp), or 43.0 in. Hg, 2200 rpm (1100 hp), or 43.0 in. Hg, 2250 rpm (1100 hp) Note: Unless engines have 1.028 in. dyna mic damper pins, take-off operation with Ham. Std. 3E50 hub and G105 blades must not exceed 2125 rpm. Airspeed limits (a) For weights up to and including 24,800 lbs.: Level flight or climb 216 mph (188 knots) True Ind. Glide or dive 262 mph (228 knots) True Ind. Flaps extended 112 mph ( 97 knots) True Ind. (See NOTE 10 for partial flap speeds) (b) For weights between 24,800 lbs. and 25,200 lbs.: Level flight or climb 211 mph (184 knots) True Ind. Glide or dive 257 mph (224 knots) True Ind. Flaps extended 112 mph ( 97 knots) True Ind. (See NOTE 10 for partial flap speeds) I - Model DC3-G102 (cont'd) Usable ceilings May be realized under conditions s hown. See Item 503(b) and NOTE 5 for reductions necessitated by de-icing equipment: Ceiling (ft.) Weight (lbs.) Manifold Pressure True Ind. Airspeed mph - knots Propellers Installed (Items) Inoperative Propeller Condition 8,500 24,400 Full throttle ----- 1(f) idling 0 24,400 36.7 ----- 1(f) braked 10,000 24,400 Full throttle ----- 1(a) and 2(b) feathered 7,100 24,400 Full throttle 100 - 87 1(b), 2(c) & 2(i) feathered or 1(c), 2(d) & 2(e) 6,000 25,200 Full throttle ----- 1(a) and 2(b) feathered 6,200 25,200 Full throttle 100 - 87 1(b), 2(c) & 2(i) feathered or 1(c), 2(d) & 2(e) 8,400 24,400 Full throttle 102 - 89 1(d), 2(c) & 2(i) feathered or 1(d), 2(d) & 2(e) 7,500 25,200 Full throttle 102 - 89 1(d), 2(c) & 2(i) feathered or 1(d), 2(d) & 2(e) 8,000 24,400 Full throttle 105 - 91 1(e), 2(c) & 2(i) feathered 7,100 25,200 Full throttle 105 - 91 1(e), 2(c) & 2(i) feathered Additional conditions (1) Standard air: (2) Either engine inoperative: (3) Carburetor air intake on "cold air"; (4) Operative engine at 2200 rpm. C.G. range (+47.1) to (+70.6) Maximum weights (a) For Ai r Carrier operation under the non-transport category performance (See NOTE 12 for operation limitations of FAR 121 with Item 1(d) or 1(e) installed: certification under Landing 25,200 lbs. SR-407) Take-off 25,200 lbs. (b) For Air Carrier operation under the non-transport category performance operation limitations of FAR 121 with 1(a) , 1(b), 1(c) or 1(f) installed: Landing 24,400 lbs. Take-off 25,200 lbs. (dump valves required - see NOTE 4.) (c) For passenger operati on other than Air Carrier: Landing 25,200 lbs. Take-off 25,200 lbs. (d) For cargo operation only: Landing 25,200 lbs. Take-off 25,200 lbs. See NOTE 3 for increased wei ghts when de-icers are installed. Maximum occupants See FAR 91.47. Baggage Maximum capacity of compartments: (See NOTE 1 for additional restrictions and placards) 2 adjacent compts. fwd. of cabin right 1250 lbs. (-63) 2 adjacent compts. fwd. of cabin left 700 lbs. (-45) 1 compt. aft of cabin 1500 lbs. (+354) Fuel capacity 822 gals. (4 tanks in center section wing: 2 main including fuel system 210 gals. each (+48) and 2 aux. 201 gals. each (+83.5)) See NOTE 2 for fuel loading procedures. Oil capacity 66-1/2 gals. (1 tank in each nacelle at 33-1/4 gals. each (-8) including capacity of oil system) Serial Nos. eligible 1545 and up (See NOTE 13) Required equipment Items 1(f), 2(a), 103(a), 104( a), 108, 201(d), 202(e), 203(a), 204(a), 205(a), 206(c), 207(a), 208(a), 301(a), 302(b), and 502. 3 A-618 II - Model DC3-G102A, (Army C-49E, C-50, C-50A, C-50B, C-50C, C-50D and C-51), approved March 1, 1939 See NOTE 7 regarding modifications requi red for conversion of military models. Engines 2 Wright Cyclones GR1820G-102A Fuel 90 min. grade aviation gasoline Engine limits Maximum continuous (Sea level) 37.5 in. Hg, 2300 rpm (900 hp) (Straight line manifold press. variation with altitude to 6700 ft.) 35.4 in. Hg., 2300 rpm (900 hp) Take-off (one minute), 43.5 in. Hg, 2350 rpm (1100 hp), Airspeed limits (a) For weights up to and including 24,800 lbs.: Level flight or climb 216 mph (188 knots) True Ind. Glide or dive 262 mph (228 knots) True Ind. Flaps extended 112 mph ( 97 knots) True Ind. (See NOTE 10 for partial flap speeds) (b) For weights between 24,800 lbs. and 25,200 lbs.: Level flight or climb 211 mph (184 knots) True Ind. Glide or dive 257 mph (224 knots) True Ind. Flaps extended 112 mph ( 97 knots) True Ind. (See NOTE 10 for partial flap speeds) Usable ceilings May be rea lized under conditions shown. See Item 503(b) and NOTE 5 for reductions necessitated by de-icing equipment: Ceiling (ft.) Weight (lbs.) RPM Manifold Pressure T.I.A.S. mph, knots Propeller installed 8200 24,400 2300 Full throttle 99, 86 1(c) 7300 25,200 2300 Full throttle 100, 87 1(c) 7700 24,400 2300 Full throttle 102, 89 1(d) 6800 25,200 2300 Full throttle 103, 90 1(d) Additional conditions (1) Standard air: (2) Either engine inoperative: (3) Inoperative propeller fully feathered; (4) Carburetor air intake on "cold air"; C.G. range (+47.1) to (+70.6) Maximum weights (a) For Ai r Carrier operation under the non-transport category performance (See NOTE 12 for operation limitations of FAR 121 with Item 1(c) or 1(d) installed: certification under Landing 25,200 lbs. SR-407) Take-off 25,200 lbs (b) For passenger operation other than Air Carrier: Landing 25,200 lbs. Take-off 25,200 lbs. (c) For cargo operation only: Landing 25,200 lbs. Take-off 25,200 lbs. See NOTE 3 for increased wei ghts when de-icers are installed. Maximum occupants See FAR 91.47. II - Model DC3-G102A, (Army C-49E, C-50, C-50A, C-50B, C-50C, C-50D and C-51) (cont'd) Baggage Maximum capacity of compartments: (See NOTE 1 for additional restrictions and placards) 2 adjacent compts. fwd. of cabin right 1250 lbs. (-63) 2 adjacent compts. fwd. of cabin left 700 lbs. (-45) 1 compt. aft of cabin 1500 lbs. (+354) Fuel capacity 822 gals. (4 tanks in center section wing: 2 main including fuel system 210 gals. each (+48) and 2 aux. 201 gals. each (+83.5)) See NOTE 2 for fuel loading procedures. Oil capacity 66-1/2 gals. (1 tank in each nacelle at 33-1/4 gals. each (-8) including capacity of oil system) Control surface movements Not available Serial Nos. eligible 1545 and up (See NOTE 13) Required equipment Items 1(c), 2(a), 103(a), 104( a), 108, 201(d), 202(e), 203(e), 204(a), 205(a), 206(c), 207(a), 208(a), 301(a), 302(b), and 502. III - Model DC3-G103A, approved August 1, 1939 Engines 2 Wright Cyclones GR-1820G-103A Fuel 90 min. grade aviation gasoline Engine limits Max. continuous, (Sea level) 38 in. Hg, 2300 rpm (860 hp) (Straight line manifold variation with altitude to 11,100 ft.) 34.2 in. Hg., 2300 rpm (860 hp) Take-off (one minute), 43.5 in. Hg, 2350 rpm (1000 hp), Airspeed limits Level flight or climb 224 mph (195 knots) True Ind. Glide or dive 268 mph (233 knots) True Ind. Flaps extended 112 mph ( 97 knots) True Ind. (See NOTE 10 for partial flap speeds) Usable ceilings See Item 503(a) for restri ctions necessitated by de-icing equipment. (a) 10,450 ft. in standard air at an indi cated airspeed of 99 mph at 24,000 lbs. with either engine inoperative and inoperativ e propeller idling with Item 1(f) installed. (b) 11,700 ft. in standard air at an indicat ed airspeed of 98.5 mph at 24,000 lbs. with C.G. at forward limit with either engi ne inoperative and inoperative propeller fully feathered, when items 1(c), 2(d) and 2(e) are installed. C.G. range (+47.1) to (+70.6) Maximum weights Landing 24,000 lbs. Take-off 24,000 lbs. See NOTE 3 for increased wei ghts when de-icers are installed. See NOTE 12 for certification under SR-407. Maximum occupants See FAR 91.47. Baggage Maximum capacity of compartments: (See NOTE 1 for additional restrictions and placards) 2 adjacent compts. fwd. of cabin right 1250 lbs. (-63) 2 adjacent compts. fwd. of cabin left 700 lbs. (-45) 1 compt. aft of cabin 1500 lbs. (+354) 5 A-618 III - Model DC3-G103A (cont'd) Fuel capacity 822 gals. (4 tanks in center section wing: 2 main including fuel system 210 gals. each (+48) and 2 aux. 201 gals. each (+83.5) See NOTE 2 for fuel loading procedures. Oil capacity 66-1/2 gals. (1 tank in each nacelle at 33-1/4 gals. each (-8) including capacity of oil system). Control surface movements Not available Serial Nos. eligible 1545 and up (See NOTE 13) Required equipment Items 1(f), 2(a), 103(a), 104( a), 108, 201(d), 202(e), 203(a), 204(a), 205(a), 206(c), 207(a), 208(a), 301(a), 302(b), and 502. IV - Model DC3-G202A, (Army C-49, C-49A, C-49B, C-49C, C-49D, C-49J, C-49K; Navy R4D-2), approved May 31, 1940 See NOTE 7 regarding modifications required for conversion of military models. Engines 2 Wright Cyclones 702C9GC1, 2, 3 or 4 (GR-1820G-202A) with 3:2 reduction gearing. (See also NOTE 8 On all Wright C9GC Series (G-200 Series ) engines, remove the upper valve washers, for optional engines) Part Nos. 69271 and 113171. E ngines equipped with the two spring combination are satisfactory without change. For engines e quipped with the three spring combination, it will be satisfactory to use Part No. 118815 or No. 113171 or No. 113171J. If either of the latter two is used, it should be of the high dimension type (0.60 inch total height). (Wright Service Bulletin No. C912A covers this same subject.) Fuel 90 min. grade aviation gasoline Engine limits Maximum continuous (Sea level) 39.5 in. Hg, 2300 rpm (1000 hp) or 43.0 in. Hg, 2400 rpm (1100 hp) (Straight line manifold pressure variation with altitude to): (6900 ft.) 37.2 in. Hg, 2300 rpm (1000 hp) (5500 ft.) 40.0 in. Hg, 2400 rpm (1100 hp) Take-off (one minute), 43.0 in. Hg, 2350 rpm (1100 hp), or 45.5 in. Hg, 2500 rpm (1200 hp) Airspeed limits Above 25,200 lbs. & Up to & incl. 25,200 lbs. incl. 26,900 lbs. Level flight or climb 211 mph (184 knots) True Ind. 200 mph (174 knots) True Ind. Glide or dive 257 mph (224 knots) True Ind. 241 mph (210 knots) True Ind. Flaps extended 112 mph ( 97 knots) True Ind. 112 mph ( 97 knots) True Ind. (See NOTE 10 for partial flap speeds) IV - Model DC3-G202A, (Army C-49, C-49A, C-49B, C-49C, C-49D, C-49J, C-49K; Navy R4D-2) (cont'd) Usable ceilings May be realized under conditions shown. See Item 503(b) and (c) and NOTE 5 for reductions necessitated by de-icing equipment: Ceiling (ft.) RPM Manifold Pressure T.I.A.S. mph - knots Propeller Item Propeller De-icer Item 25,200 lbs.: 8500 2300 Full throttle 112 - 97 1(c) None 8300 2300 Full throttle 112 - 97 1(c) 503(b) 7500 2300 Full throttle 112 - 97 1(c) 503(c) 8100 2399 Full throttle 112 - 97 1(d) None 7900 2300 Full throttle 112 - 97 1(d) 503(b) 9100 2300 Full throttle 112 - 97 1(e) None 26,900 lbs.: 6700 2300 Full throttle 112 - 97 1(c) None 6500 2300 Full throttle 112 - 97 1(c) 503(b) 5700 2300 Full throttle 112 - 97 1(c) 503(c) 6300 2300 Full throttle 112 - 97 1(d) None 6100 2300 Full throttle 112 - 97 1(d) 503(b) 7300 2300 Full throttle 112 - 97 1(e) None Additional conditions (1) Standard air: (2) Either engine inoperative: (3) Inoperative propeller fully feathered; (4) Carburetor air intake on "cold air." C.G. range (+47.1) to (+70.6) Maximum weights (a) Fo r Air Carrier operation under the non-transport category (See NOTE 12 for performance operation limitations of FAR 121 with Item 1(c), certification under 1(d), 1(e) or 1(g) installed: SR-407) Landing 25,200 lbs. Take-off 25,200 lbs. (b) For passenger operation other than air carri er with Item 1(c), 1(d), 1(e) or 1(g) installed: Landing 25,200 lbs. Take-off 25,200 lbs. (c) For operation under the conditions set forth in NOTE 11: Landing 26,000 lbs. Take-off 26,200 lbs. (dump valves not required) (d) For cargo operation only, under the conditions set forth in NOTE 9: Landing 26,900 lbs. Take-off 26,900 lbs. (e) For cargo operation under conditions othe r than those set forth in NOTE 9, 11, or 12: Landing 25,200 lbs. Take-off 25,200 lbs. See NOTE 3 for increased wei ghts when de-icers are installed. Maximum occupants See FAR 91.47. Baggage Maximum capacity of compartments: (See NOTE 1 for additional restrictions and placards) 2 adjacent compts. fwd. of cabin right 1250 lbs. (-63) 2 adjacent compts. fwd. of cabin left 700 lbs. (-45) 1 compt. aft of cabin 1500 lbs. (+354) Fuel capacity 822 gals. (4 tanks in center section wing: 2 main including fuel system 210 gals. each (+48) and 2 aux. 201 gals. each (+83.5)) See NOTE 2 for fuel loading procedures. 7 A-618 IV - Model DC3-G202A, (Army C-49, C-49A, C-49B, C-49C, C-49D, C-49J, C-49K; Navy R4D-2) (cont'd) Oil capacity 66-1/2 gals. (1 tank in each nacelle at 33-1/4 gals. each (-8) including capacity of oil system) Control surface movements Not available Serial Nos. eligible 1545 and up (See NOTE 13) Required equipment Items 1(c), 2(a), 103(a), 104( a), 108, 201(d), 202(e), 203(a), 204(a), 205(a), 206(c), 207(a), 208(a), 301(a), 302(b), and 502. SPECIFICATIONS PERTINENT TO ALL MODELS Datum Leading edge of center section of wing Leveling means Pins at (+198) and (+219) Certification basis Type Certificate No. 618 (Aero. Bulletin 7A requirements) Production basis Production Certificate No. 27 Export eligibility Eligible for exports to all countri es subject to the provisions of MOP 2-4 except as follows: (1) All models eligible to all countri es except New Zealand with a maximum landing weight of 24,000 lbs. (2) Models DC3-G102, -G102A and -G202A e ligible to all countries except Australia and New Zealand with a maximum landi ng weight of 24,400 lbs. (Limited to 24,000 lbs. to Australia pending recei pt of a satisfactory landing roll test.) Equipment: A plus (+) or minus (-) sign preceding the weight of an item indicates net weight change when that item is installed.Approval for the installation of all items of equipment listed herein has been obtained by the aircraft manufacturer except those items preceded by an asterisk (*). The asterisk denotes that approval has been obtained by someone other than the aircraft manufacturer. An item marked with an asterisk may not have been manufactured under an FAA m onitored or approved quality control system, and therefore attention should be paid to workmanship and conformity with pertinent data called for in this specification. Propellers and Propeller Accessories (Except Propeller De-icing Equipment) 1. Propellers (a) (124 a) Curtiss propellers, hubs C532D, blades 89305 770 lbs. (-76) (Index 20° to 40°) (b) (128 a) Ham. Std., hubs 23E50, blades 6153-18 703 lbs. (-76) (American Airlines Dwg. EDS484-A) For model G102 only. For interchangeable blade mode ls see Prop. Spec. No. 603 (NOTE 6) Dia.: Max. 11'6-3/8", min. allowable for repairs 11'3-3/8". No further reduction permitted. Min. low pitch setting 14° at 42 in. sta. When oil from the airplane hydraulic system is used for operation, Items 2(c) and (i) must be installed. Eligible with molded shank fairings per NOTE 5. (c) (128 d) Ham. Std., hubs 23E50, blades 6153-18 (Douglas 784 lbs. (-70.5) Dwgs. 5075587 or 5075582). For Models G102, G102A, G103A and G202A. For interchangeable blade mode ls see Prop. Spec. No. 603 (NOTE 6) Dia.: Max. 11'6-3/8", min. allowable for repairs 11'3-3/8". No further reduction permitted. Min. low pitch setting 14° at 42 in. sta. Eligible with molded shank fairings per NOTE 5. (d) (128 h) Ham. Std. hubs 23E50, blad es 6261-0, -1, -2 or -3. Use act. wt. ch. For interchangeable blad e models see Prop. Spec. No. 603 (NOTE 6) Min. low pitch setting 14° at 42 in. sta. For models G102, G102A and G202A only. (e) (128 j) Ham. Std. hubs 33D50, bl ades 6405-18 to 6495-20, incl. 674 lbs. (-76) Dia.: Max. 11'7", min. allowable for repairs 11'4". No additional tolerance permitted. For interchangeable blade models see Prop. Spec. No. 749 (NOTE 6) Min. low pitch setting 14° at 42 in. sta. For G-102 and G-202A engines geared 3:2 with standard nose (or torque meter nose for G-102) and with at least one 4 1/2 N dynamic damper. (f) (Std.) Ham. Std., hubs 3E50, blades 6105-8 710 lbs. (-76) For interchangeable blade m odels see Prop Spec. No. 246 (NOTE 6) Diameter: Max. 11' 6-3/8" , minimum allowable for repairs 11' 3-3/8". No further reduction permitted. Minimum low pitch setting 14° at 42 in. sta. (g) Ham. Std., hubs 23E50, blades 6477-0 to 6477-2, incl. Use. act. wt. ch. Dia.: Max. 11' 6-3/8", min. allowable for repairs 11' 3-3/8". No further reduction permitted. Minimum low pitch setting 20° at 42 in. sta. Eligible only on R-1820 Series engines geared 16:9. See NOTE 8(c). 2. Propeller Controls (a) (23) Constant speed prop. contro l (A-1 Hyd. Ham. Std.) 17 lbs. (-64) (b) (124 b) Curtiss feathering propeller controls, conduits, 35 lbs. (-32) governors, brush assemblies and wiring. (c) (128 b) Propeller feathering controls , tubing fittings, increased 51 lbs. (-84) capacity for hydraulic system tank, 2-1/2 gal. additional fluid. For model G102 only. (d) (128 f) Propeller feathering controls, t ubing, wiring, brackets, etc. 21 lbs. (-40.5) For models G102, G 102A, G103A and G202A only. (e) (128 e) Two feathering oil pumps for mode ls G102, G102A and G103A only. 45 lbs. (-21.5) (f) (72) Propeller slinger rings (two) 12 lbs. (-76) (g) (125) Propeller slinger rings (two) (Curtiss) 5 lbs. (-76) (h) (128 g) Propeller slinger rings (t wo) (Ham. Std. Dwg. 52903). 4 lbs. (-69.5) For Models G102, G102A, and G202A only. (i) (128 c) Residual hydraulic fluid. For Model G102 only. 6 lbs. (-64.5) Engines and Engine Accessories - Fuel and Oil System 101. Reserved. 102. Reserved. 103. Oil Coolers (a) (3) Two oil radiators, 9" dia ., and scoops, UAP U-3190-V 56 lbs. (-28) or AiResearch 2D-481 (b) (101) Two oil radiators with scoops (U.A.P. 10") 66 lbs. (-28) (c) (159) Two oil coolers, scoops, etc. (UAP 11" U-2050-V or 11" 102 lbs. (-27) AiResearch 2D-299) 104. Starters (a) (4) Two starters (Eclipse Type E-160) 67 lbs. (-31.5) (b) (161) Two combination starters and feathering pumps 80 lbs. (-40) 105. Fuel Dump System (a) (120) Extendible chute installation in accordance with Douglas Dwg. 5080140 22 lbs. (+141.5) See NOTE 4 for restrictions on dump valves. *106. Outer wing Tank Installation (a) (188 a) Two tanks in each wing totalling approximately Use act. wt. ch. 400 gals. of fuel per AiResearch Dwg. #4900-11-E. (AiResearch Aviation Serv ice Co., 5907 W. Imperial Blvd., Los Angeles 45, Calif.) (b) (188 b) Two tanks in each wing totalling approximately Use act. wt. ch. 400 gals. of fuel per Grand Central Dwg. #10878 or Dwg. #20458. (Grand Central Aircraft Comp any, 1314 Airways, Glendale, Calif.) 9 A-618 (c) (188 c) Multi-cell (34 to 400 gals.) per Executive Aircraft Use act. wt. ch. Service Dwg. #35267NS (Executive Aircraft Service, Inc., P.O. Box 7307, Dallas, Texas) 107. (a) (151) Dual fuel system including weight increase of pressure +85 lbs. (+3) carburetors (Two Stromberg PD12B-7 or PD12-H3 at +15 lbs. each). (Douglas Dwgs. 5070010 and 4087774) (G100 and G200 series engines only) (b) (153) Dual fuel system (with Chandle r-Groves 1375-F carburetors) +52 lbs. (+18) in accordance with Douglas Dwgs. 5070010 and 4070657 108. (22) Residual fuel and oil in drai ned system (Oil 34.5 lb.; 56 lbs. (-28.5) fuel 21.5 lbs.) 109. (132) Two 29 gal. oil tanks constr ucted in accordance with -8 lbs. (-8) Douglas Dwg. 507759 replacing standard 33-1/4 gal. tanks *110. Engine mount No. 10008 (Orlin M. Sore nson, 5101 Haskle Ave., Encino, Calif.). For R-1820 Series engine up to a maximum of 1350 hp. Landing Gear 201. Main Wheels and Brake Assemblies (a) (83 b) Two 17.00-16 wheels (Bendix mag.) with expander tube brakes 243 lbs. (+28) (Goodrich G-1430 or Hayes) (b) (67) Two 45x20-10 Goodyear wheels with L.P. disc brakes 216 lbs. (+28) (7, 9 or 11 discs) (c) (83 a) Two 17.00-16 Bendix wheels with cast iron drums and 229 lbs. (+28) expander tube brakes (Goodrich H-2-445 or H-2-449) (d) (112) Two 17.00-16 wheels (Bendix Mag., TC-34) 254 lbs. (+28) (e) (174) Two 45x20-10 Goodyear wheels with high pressure 230 lbs. (+28) disc type brakes (7 or 9 discs) (f) (146) Two 17.00-16 Bendix B-3 wheels and duo-servo brakes 263 lbs. (+28) *(g) (186) Two Goodyear Model CL16HBM (cross-wind wheels) +173 lbs. (+28) Wheel Assembly No. 9560031 Brake Assembly No. 9540307 (Installation per Goodyear Dwg. No. 283AX50-500, Rev. D). (Note: When this item is installed, airplane is approved for crosswind landings in wind components up to 40 mph). *(h) Two 17.00-1G Goodrich wheels H-3-269M-1 and brakes H-2-415, 252 lbs. (+28) H-2-445 or H-2-449 *(i) Two 17.00-16 Goodyear wheels 530975M and brakes 530961, 216 lbs. (+28) 9540137, 9540356 or 9540363 *(j) Two 17.00-16 Goodyear wheels 9510517 and brakes 9540385 273 lbs. (+28) 202. Main Wheel Tires (a) (111) Two 17.00-16, 10-ply H.D. (treaded) 257 lbs. (+28) (b) (68 c) Two 45x20-10, 10-ply (treaded) 296 lbs. (+28) (c) (68 a) Two 45x20-10, 10-ply (smooth) 268 lbs. (+28) (d) (180) Two 17.00-16, vaned (Goodrich) 260 lbs. (+28) (e) (16) Two 17.00-16, 10-ply (treaded) 239 lbs. (+28) (f) (96) Two 17.00-16, treaded 12-ply (ribbed safety) 275 lbs. (+28) (g) (68 b) Two 45x20-10, 12 ply 310 lbs. (+28) 203. Main Wheel Tubes ( a) (165) 17.00-16 plain 38 lbs. (+28) (b) (69) 45x20-10 plain 10 lbs. (+28) (c) (17) 17.00-16 cactus proof 56 lbs. (+28) 204. Tail Wheel (a) (19) 9.00x6 9 lbs. (+455.5) 205. Tail Wheel Tire (a) (20) 9.00-6, 8-ply 18 lbs. (+455.5) (b) (109 c) 9.00-6, 8-ply treaded 24 lbs. (+455.5) (c) (162 a) 19.00 streamline 8-ply 13 lbs. (+455.5) 206. Tail Wheel Tube (a) (21) 9.00-6 (cactus-proof) 5 lbs. (+455.5) (b) (162 b) 19.00 plain 2 lbs. (+455.5) (c) (109 a)9.00-6 (plain) 3 lbs. (+455.5) 207. Main Gear Shock Struts (a) (14) Four Bendix Nos. 53420 or 53585 223 lbs. (+28) 208. Tail Wheel Oleo Strut (a) (18) Douglas Dwg. No. 3006620 or Cleveland No. A-6356 12 lbs. (+449) (b) (127) Douglas Dwg. No. 5044046 or 5115222 23 lbs. (+449) Electrical Equipment 301. Generators (a) (5) Two 50 amp. (Eclipse E-5 or E-7) (12 volt) 62 lbs. (-31.5) (b) (62) One Eclipse E-5, M2617-a (12 volt) 31 lbs. (-31.5) (c) (99) One 25 amp. (Eclipse Type D) (12 volt) 28 lbs. (-31.5) (d) (160) Two Eclipse Type 311, 100 amp. (12 volt) 81 lbs. (-31.0) *(e) (187) Two P-1 or equivalent, 200 amp., 28 volts (Reference 88 lbs. (-38.5) FAA Aeronautical Center Standard ization Dwg. Wiring Diagram Page No. 34) 302. Batteries (a) Two 65 amp. (6-TX-19) (12 volt) 126 lbs. (-65) (b) (6) Two batteries 88 amp. hr. (Exide 6-FHM-13) 155 lbs. (-65) (c) (98) One 50 amp. (Exide 6-X-9) (12 volt) 63 lbs. (-65) (d) (63) One Preto-lite, 105 amp. (R 1213G) (12 volt) 91 lbs. (-65) (e) (93) One 88 amp. (Exide 6-FHM-13) (12 volt) 78 lbs. (-65) Interior Equipment 401. Reserved 402. Automatic Pilot (See NOTE 12(g) for Aircra ft Certificated under provisions of SR-407) (a) Hydraulic - Servo unit Model No. C8-D3-B 65 lbs. (-140) (b) (185 a) Sperry Type A-12 205 lbs. (+ 93) Main Servo Units : Aileron: Servo unit model NR.656542 (S-1-180-60-D) Pulley size: 4.25" drum pitch diameter Rudder: Servo unit model NR.656542 (S-1-148-40-D) Pulley size: 4.25" drum pitch diameter Elevator: Servo unit model NR.656542 (S-1-104-20-D) Pulley size: 4.25" drum pitch diameter Elevator Trim Tab Servo Unit : Servo unit model NR.661202 (S-3-2000-3-5E) Pulley size: 2.749" drum pitch diameter (Sperry Dwg. Nos. 5245-90052B, -90053D and -90029B) (1) Servo stall force installation valu es (+0 or -3%) at the pilot's controls: Rudder 70 lbs., elevator 40 lbs., aileron 23 lbs. (2) The following placard should be installe d in a conspicuous place near the automatic pilot controller: "When using auto-pilot in normal operati on (except approach), minimum terrain clearance is 500 feet. When using auto-pilot during an approach, minimum altitude is 200 feet, pilot's seat belt fastened and hand on control wheel. Minimum altitude for each case does not override any higher minimum operational altitudes." *(c) (185 b)(1) Lear Model L-5 automatic pilot, altitude controller and approach 92 lbs. (+113.0) coupler installed in accordance with Lear Dwg. 82784. (2) Lear Model L-2C automatic pilot and altitude controller 68 lbs. (+147.5) (optional equipment) installed in accordance with Lear Dwg. 91326. The following placard should be inst alled in a conspicuous place near the automatic pilot controller: "When using autopilot in normal operation (except approach) minimum terrain cl earance is 500 feet. When using autopilot during an approach, minimum altitude is 200 feet, pilot's seat belt fastened and hand on control wheel. Minimum altitude for each case does not override any higher minimum operational altitude." 11 A-618 Servo stall torques measured at rudder, aileron and elevator servos: 150 in. lbs. minimum, 200 in. lbs. maximum. Servo drum pitch diameters for all three axes are 2.67 inches. *(d) (185 c) Pioneer PB-10 (Three main se rvo units 15601, one elevator Use act. wt. ch. tab servo unit 15602 and two throttle servo units 15602) (Reference Pioneer Pub. No. 95-14, 511-18, 05-8G, 88-31 and FAA Aeronautical Standardization Drawings) (1) Servo stall forces measur ed in pounds at the pilot's controls: Rudder 75 Elevator 39 Aileron 23 These forces are satisfactory for automatic approach. (2) When using autopilot in cruise configuration the minimum terrain clearance is 500 f eet. When using autopilot in approach configuration the minimum terrain clearnace is 200 feet, pilot's seat belt fastened and hand on control wheel. The minimum altitude in each case does not override any higher minimum operating altitude. *(e) (185 d) Minneapolis-Honeywell Model MH-6 (3 servos MG7001A1: 189 lbs. (+31.5) 1 servo MG700A3) installed in accordance with Minneapolis-Honeywell Dwg. ET-1924. (1) Servo Stall forces at pilot's controls: Rudder 120 + 5 lbs. Aileron 50 + 5 lbs. Elevator 30 + 5 lbs. (These forces are satisfactory for automatic approach.) (2) The following should be included on a placard installed near the automatic pilot controller: "Pilot's Operating Manual dated April 21, 1953, for the MH-6 Automatic Pilot is required. Maximum speed demonstrated for use of the Automatic Pilot is 165 mph. Do not use Automatic Pilot below 300 feet above the terrain for cruise configuration or 200 feet for approach." 403. (9) Two flares (3 min.) Wiley Type A- 8 (including brackets, etc., 15 lbs.) 52 lbs. (+389) 404. (118) T.W.A. buffet installation (349 lbs. capacity at +331.5) 51 lbs. (+332) (includes Thermos rack) Rear baggage capacity must be reduced to 1070 lbs. at +368. Load in buffet should be so distributed that a major portion will be carried on the floor of the buffet compartment. De-Icer Equipment (Propeller, Wing and Windshield) 501. (61) De-icer installation co mplete consisting of 165 lbs. (+67) (a) (a) Boots and attachments 92 lbs. (b) (b) Wing and fuselage lines 13 lbs. (c)(c) Pump, controls, valves, clips and brackets and 30 lbs. lines forward of firewall 502. (33) Carburetor and wi ndshield system 32 lbs. (+72) (a) (a) Tank (b) (b) Lines (c) (c) 2 gal. alcohol 503. Propeller De-Icing Provisions (a) (173 a) Goodrich No. 37572 propeller de-icer fluid feed strips Goodrich No. 36889 feed rings may be used on round shank blades With G103A engines the strips sh all not extend beyond the outside diameter of the engine cowl on the propeller blades and the usable ceiling must be reduced by 1,000 feet when installe d. Strips and rings should be installed on the blades in accord with G oodrich Installation Manual furnished with t h e s t r i p s . (b) (173 b) Goodrich No. 37572 propeller de-icer fluid feed strips. Goodrich No. 36889 feed rings may be used on round shank blades. With G102, G102A, and G202A engines the strips shall not extend beyond the 45 in. station on the propeller blades, and the usable ceiling must be reduced by 200 feet when installed. Strips and rings should be installed on the blades in accord with Goodrich Installation Manual furnished with the strips. (c) (173 c) Goodrich No. 37572 propeller de-icer fl uid feed strips max. extension to 60 inch station on 6153 (or equivalent) propeller bl ades eligible with G202A engines only. Reduce usable ceilings 1,000 feet when st rips are installed. Goodrich No. 36889 de-icer fluid feed rings eligible. Strips and ri ngs should be installed on the blades in accordance with Goodrich Installation Manual furnished with the strips. (d) (173 d) Goodrich No. 37572 propeller de-icer fl uid feed strips max. extension to 59 inch station on 6153 or (equivalent) a nd 6261 (or equivalent) propeller blades eligible with G102A engines only. Reduce us able ceiling 1200 feet when strips are installed. Goodrich No. 36889 de-icer fluid feed ri ngs eligible. Strips and rings should be installed on the blades in accordance with G oodrich Installation Manual furnished with the strips. (e) (173 e) Firestone No. YRE-75J99 propeller de -icer fluid feed strips, with G103A engines the strips shall not extend beyond the outside diameter of the engine cowl on the propeller blades and the usable ceiling must be reduced by 1,000 feet when installed. Strips should be installed in accord with Firestone instructions furnished with the strips. (f) (173 f) Firestone No. YRE-75J99 propeller de-icer fl uid feed strips. With G102, G102A and G202A the strips shall not extend beyond the 45 in ch station on the propeller blades and the usable ceiling must be reduced by 200 feet when inst alled. Strips should be installed in accord with Firestone instructions furnished with the strips. (g) (173 g) Firestone No. YRE-75J99 propeller de-icer fluid feed strips extending to 60 inch station on 6153 (or equivalent) propeller blades eligible with G202A engines only. Reduce usable ceiling 1,000 feet when strips are installed. Stri ps should be installed in accordance with Firestone instructions furnished with the strips. (h) (173 h) Firestone No. YRE-75J99 propeller de-icer fluid feed strips extending to 59 inch station on 6153 18 (or equivalent) and 6261 (or equiva lent) propeller blades eligible with G102A engines only. Reduce usable ceiling 1,000 feet when strips are installed. Strips should be installed in accordance with Firestone instructions furnished with the strips. Miscellaneous (Not Listed Above) 601. Heating System (a) (13) Steam heater system and 2 gal. water 109 lbs. (+29.5) (b) (113 a) Heating system boiler, Pr oject Sketch Change 0038B No. wt. change (replacing standard No. 6020541) (c) (113 b) Heating system boile r A.A. No. EDS 271 No. wt. change (replacing standard No. 6020541) (d) (176) Stewart Warner heater (Douglas Dwg. No. 5144982) 51 lbs. ( 30) (replaces 601(a) when installed) *602. Geared Rudder Tab (a) (189 a) AiResearch Dwg. No. C-7100- 19 Instal. Geared Rudder Use act. wt. ch. Tab." (AiResearch Aviation Serive Co., 5907 W. Imperial Blvd., Los Angeles 45, Calif.) (b) (189 b) Executive Aircraft Service Dwg. #35283. (Executive Use act. wt. ch. Aircraft Service, Inc ., P.O. Box 7307, Dallas, Texas) *603. (190) Windshield Installation, Dwg. #352544GDA, Executive Use act. wt. ch. Aircraft Service, Inc. NOTE 1. (a) Weight and balance report including list of equipm ent included in certificated weight empty, and loading instructions when necessary, must be in each aircraft at the time of original certification and at all times thereafter (except in the case of air carrier ope rators having an approved weight control system). (b) An optional forward baggage compartment (-95. 5) may be utilized when noted on approved loading schedule. It is formed by swinging the standard left-hand forward baggage door to the inside snap lock. The optional compartment must be placarded for a maximum capacity of 200 lbs. 13 A-618 (c) Stewardess or stewards seat not to be occupied by passengers. Placard accordingly. (d) Placard lavatory door as follows: "These r ooms not to be occupied during take-off or landing." NOTE 2. (a) Fuel must be loaded in front tanks and then in rear tanks and used in the reverse order except for take-off and landing, unless the carburetor overflow return line is routed to the rear tanks, in which case the fuel loading and usage procedure must be reversed. (b) Models DC3-G102, DC3-G 102A, DC3-G202A and DC3-G103A only: The following placard must be conspic uously posted at each fuel tank filler cap: "Fill with 91 Octane Fuel Only." (c) Model DC3-G202A : With Wright Cyclone R-1820-66 engines, the followi ng placard must be conspicuously posted at each fuel tank filler cap: "Fill with 100 Octane Fuel Only." NOTE 3. Maximum landing (and take-off) we ight may be increased by an amount equal to .006 x maximum landing weight when complete de-icer is installed, except that no allowance may be made for de-icers that will result in take-off or landing weights higher than 25,346 pounds. NOTE 4. Fuel Dumping - Fuel dump valves (Item 105(a)) must be installed for operation of the airplane at weights in excess of the maximum landing weight, unless otherwise noted in this specification. NOTE 5. Hamilton Standard propeller 6153 Se ries and 6495 Series blades are eligible with molded shank fairings. Blades with fairings will be indicated with a letter and a dash preceding the model designation. On G102, G102A, and G202A engines only, fairings may incorporate de-icing fluid grooves and a grooved extension strip. (The complete assembly shall not extend beyond 45 inch station on the blade.) Reduce usable ceiling by 200 ft. when fairings are grooved. NOTE 6. Deleted - May 22, 1957 NOTE 7. The various military models listed were originally built as commercial aircraft but were converted for military use prior to delivery from the factory. Prior to certification as a civil aircraft, the following must be accomplished: (a) Each airplane must satisfactorily pass an insp ection for conformity, possible hidden damage, and for workmanship and materials used in making any re pairs and/or alterations. All Airworthiness Directive Notes must be complied with . (b) Instrument markings and placards must be installed as required by this specification and commercial DC-3 practice. Attention should be given to th e windshield equipment and it should be determined that a satisfactory windshield wiper is installed. (c) Each airplane must be weighed to determine its weight and balance and an approved loading chart or device installed. If any changes have been made which would adversely affect the flight characteristics, the particular airplane must be flight tested. Upon completion of the conversion to certificated status, the manufacturer's nameplate on the aircraft should be altered to include the date of conversion and the new commercial model designation. In case the original nameplate is not sufficiently large to include this additional information, a similar plate should be inst alled near the original plate. Under no circumstances should the original or any succeeding nameplate be removed from the aircraft. NOTE 8. Model DC3-G202A also elig ible with the following engines: (a) Wright Cyclone 730C9GD series engine limits MP H P RPM IN.HG. ALT. Maximum continuous 1000 2300 39.0 S.L.* or 1100 2400 42.5 S.L.* Maximum continuous 1000 2300 36.7 6900* or 1100 2400 39.8 5500* Take-off (one minute) 1200 2500 45.0 S.L. *Straight line variation in manifold pressure with altitude. (b) Wright Cyclone #R-1820-56 or -66 Engine limits MP H P RPM IN.HG. ALT. Maximum continuous 1100 2400 41.5 S.L .** Maximum continuous 1100 2400 40.0 4200 ** Take-off (one minute) 1200 2500 44.0 S.L. *When these engines are installed, the engine supercharger speed control must be safetied in the low blower position. **Straight line variation in manifold pressure with altitude. (c) Wright Cyclone *R-1820-56AM2, -71M1, -72AM1, -70 or -70M1 geared 16:9 Propeller: Item 1(g) only eligible. Engine Limits MP H P RPM IN.HG. ALT. Maximum continuous 1100 2500 40.5 S.L. *** Maximum continuous 1100 2500 40.0 5100 *** Take-off (one minute) 1350 ** 2700 48.0 S.L. *When engines incorporating 2-speed superchargers are installed, the engine supercharger speed control must be safetied in the low blower position. **Only if NOTE 12 is complied with; othe rwise, take-off must be limited to 1200 hp. ***Straight line variation in manifold pressure with altitude. NOTE 9. (a) All DC3 aircraft are eligible for cargo operation at a maximum weight of 26,900 lbs. when engines having at least 1050 hp Maximum Continuous and 1200 hp for Ta ke-off are installed, provided the cabin floor is structurally adequate and when the landing we ight exceeds 25,200 and/or the take-off weight exceeds 26,200 lbs., the following structur al reinforcements are accomplished: (1) Install C-47 type upper main landing gear truss in accordance with Douglas Dwg. 5110569 or 5141775. (2) Install C-47 type landing gear retracting strut and mechanical lock in accordance with Douglas Dwg. 5110586, 5114203, 2114381, 5140045, and 5341742. (3) Add an .040 doubler plate to each front spar uppe r landing gear attach point as shown in Douglas Dwg. No. 5116763-18. (4) It must be determined that the main landing g ear wheels and tires have static ratings of at least 13,450 lbs. Wheels listed under Items 201(e), (f), (h), (i), and (j) are satisfactory at the 26,900 lbs. cargo weight. Similarly, the tires listed under the following items are satisfactory for 26,900 lbs. gross weight: Item No. Inflation Pressure 202(a) 48 p.s.i. 202(b) 38 p.s.i. 202(c) 38 p.s.i. 202(g) 38 p.s.i. In case other wheels and tires have been approve d for particular installations, the approved static ratings for the wheels (refer to wheel specificati ons), and tires (refer to Tire and Rim Association Airplane Handbook) should be determined to be at least 13,450 lbs. before authorizing operation at a weight of 26,900 lbs. 15 A-618 (5) The following Douglas DC-3 axles are sa tisfactory for maximum weights as indicated: Axle Assembly Weight 5007396 25,200 lbs. 5007162 with 5007390 torque collar 25,200 lbs. 5007162 with 5007390RW torque collar 26,900 lbs. 5007162 with changes per Douglas S.B. #242 including 26,900 lbs. 5203324 or 5111575 collar and C-47 type keys and lower oleo caps. 5116596 with 5203324 or 5111575 collar 26,900 lbs. 5367124 26,900 lbs. Douglas Service Bulletin DC 3 No. 261 contains in formation relative to identifying characteristics of the above listed axle assemblies. (b) A flap setting of 15 degrees is required to m eet the take-off and climb requirements at weights in excess of 25,200 lbs. at sea level except for those aircraft operated in accordance with an FAA Approved Airplane Flight Manual or those aircraft eligible for operation in accordance with the take- off limitations of FAR 121, in which case a retracted flap position may be used for take-off. (c) The drawings referenced under (a) are not availa ble to FAA representatives and, in each case, it will be necessary for the applicant to supply the necessary proof of compliance to satisfy the FAA representative that the changes have been incorporated in the individual airplane. Douglas Service Bulletin No. 242 describes in detail how to complete the rework covered by the drawings listed in parts (1), (2) and (3) above. NOTE 10. The following partial flap settings and correspondi ng airspeeds may be used during approach procedures: Flap Setting Maximum Speed 1/4 155 mph (135 knots) True Ind. 1/2 114 mph ( 99 knots) True Ind. 3/4 112 mph ( 97 knots) True Ind. Full (45°) 112 mph ( 97 knots) True Ind. NOTE 11. Model DC3 aircraft with e ngines installed that are rated at 1000 hp Maximum Continuous and 1200 hp for Take-off and authorized to be operated in accordan ce with the performance operation requirements of FAR 121, are eligible for maximum landi ng and take-off weights of 26,000 and 26,200 lbs. respectively, when the conditions as set forth in Items (a) and (c) of NOTE 9 are complied with. For airplanes of United States registry, this applies only to airplanes operated by certificated air carriers. The following airspeed limits are applicable for weights between 25,200 and 26,200 lbs.: Level flight or climb 205 mph (178 knots) True Ind. Glide or dive 251 mph (218 knots) True Ind. Flaps extended 112 mph ( 97 knots) True Ind. See NOTE 10 for partial flap speeds. An FAA Approved Flight Manual will be required for airplanes of United St ates registry operating at these weights. NOTE 12. The following is applicable to airplanes certificat ed under the provisions of CAB Special Regulation SR-407: Model DC3 aircraft have been determin ed to meet the structural requireme nts of CAR 1a as amended April 7, 1950, for a maximum landing and take-off weight of 26,900 lbs. and may be certificated for passenger carrying at weights up to and including 26,900 lbs., when Wri ght R 1820 series or P&W R 1830 series engines are installed whose Maximum Continuous hp does not ex ceed 1100 and whose Take off hp does not exceed 1350, provided that the total weight of the engine-propelle r installation forward of the firewall does not exceed 2500 lbs. and the following are accomplished: (a) The structural modifications and installation of tires and wheels in accordance with NOTE 9 are required if the landing weight exceeds 25,200 lbs. or the take-off weight exceeds 26,200 lbs. (b) If not already accomplished, the center wing spars, the tank covers on the bottom of the center wing and the nacelle to wing attach angles must be rewo rked in accordance with Douglas Project Sketches 10826, 10827, 10828 and 10829 and Douglas Dwg. #5162328 on the follo wing aircraft: All serial numbers up to and including 1976, 1979 through 2003, 2009, 2011 through 2016, and 2019 through 2028. (c) Wright R-1820 series engine s having a Maximum Continuous hp not to exceed 1100 and a Take-off hp not to exceed 1350 are installed. Engines incorpora ting two speed super chargers must be locked in low blower unless satisfactory cooling tests are conduc ted and any modifications found necessary to permit high blower operation are incorporated. (d) Any increase in power above .200 hp must not adversely affect the flight characteristics of the airplane. It has been determined that the directional controlla bility and stability of the DC-3 series aircraft is inadequate in the one- engine out condition if engi nes having more than 1200 hp for take-off are installed. Therefore, suitable modifications must be made to the airplane in a manner acceptable to the Administrator, which will maintain flight character istics equivalent to those previously approved. One such modification which has been approved for a maximum of 1350 hp for take-off is a geared rudder tab installation which is described on Item 602. (e) An FAA Approved Airplane Flight Manual is required and must be carried in the airplane at all times. For airplanes using a maximum of 1200 hp for take-off a maximum weight of 26,200 lbs. has been established and may be approved without furt her tests. For airplanes using over 1200 hp up to 1350 hp for takeoff, if it is desired to increase the maximum weight a bove 26,200 lbs. to a maximum of 26,900 lbs., performance substantiation is required. (f) The following airspeed (T IAS) limits are applicable: Up to and including 24,800 lbs. Between 24,800 lbs. and 25,200 lbs. Between 25,200 lbs. and 26,900 lbs. Vl (level flight or climb) 201 mph (175 knots) 195 mph (170 knots) 183 mph (159 knots) Vne (never exceed) 241 mph (210 knots) 233 mph (202 knots) 219 mph (190 knots) Vf (Flaps 1/4) 155 mph (135 knots) 155 mph (135 knots) 155 mph (135 knots) (Flaps 1/2) 114 mph ( 99 knots) 114 mph ( 99 knots) 114 mph ( 99 knots) (Flaps 3/4) 112 mph ( 97 knots) 112 mph ( 97 knots) 112 mph ( 97 knots) (Flaps full) (45°) 112 mph ( 97 knots) 112 mph ( 97 knots) 112 mph ( 97 knots) (g) The DC-3 series aircraft is not structurally sa tisfactory for take-off weight in excess of 26,900 lbs. Therefore, if the takeoff weight, up to a maximum of 26,900 lbs., does not exceed the landing weight by more than 105%, dump valves are not required. No allowance for de-icer installation will be permitted at any weight. If an automatic pilot is installed in the airplane, satisfactory flight tests must be completed to determine the effects upon the automatic pilot servo fo rces of any modification made to the airplane to maintain its flight characteristic s. The forces shown in items 402(b) and (d) of this specification for the Sperry A-12 and Pioneer PB-10 automatic pilots ha ve been demonstrated to be satisfactory when the "Geared Rudder Tab" (Item 602) is installed provi ded the maximum speed for operation of the automatic pilot is limited to 180 mph. (h) In lieu of installing the Wright R-1820 series engi nes, the P&W R-1830 series engines may be installed in accordance with Aircraft Specification A-669 including NOTE 13 of that specification. Since the Wright engine powered DC-3 aircraft covered by this sp ecification incorporated engine mounts supported at five points on the firewall, while the P&W engine powered DC-3A as covered by Specification A-669 incorporated engine mounts supported at four poi nts on the firewall, the following must be accomplished when installing the P&W R-1830 series engines on ai rcraft originally incorporating the Wright R-1820 series engines: (1) If it is desired to retain or install th e forged mount per Douglas Dwg. No. 5110599, suitable modifications must be made to the nacelle and firewall to withstand the loads imposed by the four-point suspension, or (2) Install a new engine mount, supported at five point s on the firewall, which is structurally adequate to withstand the loads resulting from the increased hp and weight of the power plant installation. P&W R-2000-7M2 or -D5 engines may be installed in lieu of the R-1820 Series engines provided the above items are complied with and the installation is made in accordance with Item 101(d) of Aircraft Specification A-669. 17 A-618 NOTE 13. The following aircraft models are also eligible for an airworthiness certificate under this specification. (a) DST-G102, DST G102A and DT S-G202A, serial numbers 1494 and up. (b) DC3B-G102 and DC3B-G202A, serial nubmers 1922 and up. .....END..... ``` ## ADs (33, in force first) - [AD 2026-13-02](https://openairdocs.org/ad/2026-13-02): Navigation · Airbus Canada Limited Partnership 18, 49-46, 80-A and 555 more. Effective Jul 1, 2026 - [AD 2023-10-02](https://openairdocs.org/ad/2023-10-02): Indicating/Recording System, Navigation · Boeing 18, 23, 35 and 1,060 more. Effective May 26, 2023 - [AD 2011-12-01](https://openairdocs.org/ad/2011-12-01): Equipment/Furnishings · Airbus A300 B2-1A, A300 B2-1C, A300 B2-203 and 268 more. 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Effective Apr 19, 1990 - [AD 78-18-02](https://openairdocs.org/ad/78-18-02): Elevator Control System · Day, Gene C. R4D-8, R4D-8, R4D-8Z and 15 more. Effective Sep 6, 1978 - [AD 77-10-02](https://openairdocs.org/ad/77-10-02): Fire Resistant Prop Feathering System · Boeing DC3-G102, DC3-G102A, DC3-G103A and 11 more. Effective Jun 16, 1977 - [AD 63-23-01](https://openairdocs.org/ad/63-23-01): Wing Attach Angles And Doublers · Boeing DC3-G102, DC3-G102A, DC3-G103A and 11 more. Effective Apr 16, 1970 - [AD 66-18-02](https://openairdocs.org/ad/66-18-02): Wing Attach Angles And Doublers · Boeing DC3-G102, DC3-G102A, DC3-G103A and 11 more. Effective Apr 16, 1970 - [AD 68-07-05](https://openairdocs.org/ad/68-07-05): Elevator Ribs · Boeing DC3-G102, DC3-G102A, DC3-G103A and 11 more. Effective May 9, 1968 - [AD 66-02-01](https://openairdocs.org/ad/66-02-01): Air Conditioners · Beechcraft 56TC, 58, 58A and 39 more. Effective Feb 10, 1966 - [AD 64-03-03](https://openairdocs.org/ad/64-03-03): Blades · Boeing DC-6, DC-6A, DC-6B and 26 more. Effective Mar 1, 1964 - [AD 60-16-03](https://openairdocs.org/ad/60-16-03): Geared Rudder Tab · Boeing DC3-G102, DC3-G102A, DC3-G103A and 11 more - [AD 41-47-01](https://openairdocs.org/ad/41-47-01): Control Surface · Boeing DC3-G102, DC3-G102A, DC3-G103A and 11 more - [AD 46-13-04](https://openairdocs.org/ad/46-13-04): Landing Gear Rear Brace Strut Fittings · Boeing DC3-G102, DC3-G102A, DC3-G103A and 11 more - [AD 46-13-05](https://openairdocs.org/ad/46-13-05): Control Boot Assemblies · Boeing DC3-G102, DC3-G102A, DC3-G103A and 11 more - [AD 46-43-02](https://openairdocs.org/ad/46-43-02): Rudder Pedal Slide Tube Support · Boeing DC3-G102, DC3-G102A, DC3-G103A and 11 more - [AD 47-06-07](https://openairdocs.org/ad/47-06-07): Fire Extinguishing System · Boeing DC3-G102, DC3-G102A, DC3-G103A and 11 more - [AD 47-33-02](https://openairdocs.org/ad/47-33-02): Cowl Flap Hydraulic Lines · Boeing DC3-G102, DC3-G102A, DC3-G103A and 11 more - [AD 48-05-01](https://openairdocs.org/ad/48-05-01): Oil Shutoff Valve 'O' Rings · Boeing DC3-G102, DC3-G102A, DC3-G103A and 11 more - [AD 48-17-01](https://openairdocs.org/ad/48-17-01): Fire Prevention Modifications · Boeing DC3-G102, DC3-G102A, DC3-G103A and 11 more - [AD 50-46-01](https://openairdocs.org/ad/50-46-01): Oil Tank Standpipe · Boeing DC3-G102, DC3-G102A, DC3-G103A and 11 more - [AD 51-02-01](https://openairdocs.org/ad/51-02-01): Ramp Type Door Rework · Boeing DC3-G102, DC3-G102A, DC3-G103A and 11 more - [AD 52-25-01](https://openairdocs.org/ad/52-25-01): Vacuum System Rework · Boeing DC3-G102, DC3-G102A, DC3-G103A and 11 more - [AD 56-14-02](https://openairdocs.org/ad/56-14-02): Landing Gear Axle · Boeing DC3-G102, DC3-G102A, DC3-G103A and 11 more - [AD 56-20-05](https://openairdocs.org/ad/56-20-05): Propeller Operating Limits · Boeing C54-DC, DC-4, DC3-G102 and 3 more - [AD 58-04-01](https://openairdocs.org/ad/58-04-01): Aircraft Passenger Entrance Door · Boeing DC3-G102, DC3-G102A, DC3-G103A and 11 more - [AD 58-08-03](https://openairdocs.org/ad/58-08-03): CB Fire Extinguisher System · Air Trading Navy PV-1, DC3-G102, DC3-G102A and 13 more - [AD 74-08-09 R2](https://openairdocs.org/ad/74-08-09-R2) (historical): Waste Receptacles · Aero Spacelines 377, 377MG, 377SGT and 268 more. Effective Jul 29, 1996 ## Registered aircraft by registry model (OpenAirDocs) - [Douglas DC3-G202A](https://openairdocs.org/model/douglas-dc3-g202a): 7 aircraft (registry code 3021424) - [Douglas DC3-G102A](https://openairdocs.org/model/douglas-dc3-g102a): 1 aircraft (registry code 3021404) - [Douglas DC3-G102](https://openairdocs.org/model/douglas-dc3-g102): 0 aircraft (registry code 3021402) - [Douglas DC3-G103A](https://openairdocs.org/model/douglas-dc3-g103a): 0 aircraft (registry code 3021422) ## STCs approved under this data sheet (139, first 50) - [STC SA04652CH](https://openairdocs.org/stc/SA04652CH): To allow use of 100R grade aviation fuel meeting Swift Fuel, LLC specification. Swift Fuels LLC - [STC SA2622NM](https://openairdocs.org/stc/SA2622NM): Installation of Precise Flight Pulselite Control Unit in landing/taxi system. (767-200 B17) (DHC-8 101). Precise Flight Inc. - [STC SA7965SW](https://openairdocs.org/stc/SA7965SW): Application of fabric and polyurethane finishing system.. Shady Aviation LLC - [STC SA01757WI](https://openairdocs.org/stc/SA01757WI): To allow the use of UL91 or UL94 (minimum) grade aviation fuel. Swift Fuels LLC - [STC SA4503NM](https://openairdocs.org/stc/SA4503NM): Remove original cloth covering and install Ceconite covering. Ceconite Division of Poly-Fiber Inc. - [STC SA01831WI](https://openairdocs.org/stc/SA01831WI): To allow the use of UL91 (minimum) grade aviation fuel. Petersen Aviation Inc - [STC SA02268CH](https://openairdocs.org/stc/SA02268CH): Installation of Airwolf Filter Corp. Air Oil Separator. Airwolf Filter Corporation - [STC SA3-307](https://openairdocs.org/stc/SA3-307): Installation of 145-gallon fuel tanks. Installation of 252-gallon fuel tanks.. Preferred Improvements LLC - [STC ST04262CH](https://openairdocs.org/stc/ST04262CH): Install placarding to restrict total payload to a maximum of six thousand pounds (6,000 lbs). Preferred Improvements LLC - [STC SA01282NY](https://openairdocs.org/stc/SA01282NY): Installation of Airwolf remote mounted engine oil filter kit AFC-K015 on aircraft powered by Pratt & Whitney radial reciprocating engine Series R-985, R-1340 and R-1830.. Airwolf Filter Corporation - [STC SA211CE](https://openairdocs.org/stc/SA211CE): A.P.U. Installation - Ranger Andover Model V-32D-2-1.. Preferred Improvements LLC - [STC SA3-15](https://openairdocs.org/stc/SA3-15): Installation of wheel well enclosure doors.. Preferred Improvements LLC - [STC SA3-422](https://openairdocs.org/stc/SA3-422): Installation of bird resistant windshield.. Preferred Improvements LLC - [STC SA3-434](https://openairdocs.org/stc/SA3-434): Picture window installation and standard window modification.. Preferred Improvements LLC - [STC SA3-461](https://openairdocs.org/stc/SA3-461): Installation of electrically driven emergency hydraulic pump.. Preferred Improvements LLC - [STC SA3-52](https://openairdocs.org/stc/SA3-52): Radome installation.. Preferred Improvements LLC - [STC SA3-78](https://openairdocs.org/stc/SA3-78): Alternate Tee-Bolt radome attachment for STC SA3-52 radome installation.. Preferred Improvements LLC - [STC ST04263CH](https://openairdocs.org/stc/ST04263CH): Install placarding to restrict passenger count to a maximum of nineteen (19) and total payload to a maximum of seven thousand five hundred pounds (7,500 lbs). Preferred Improvements LLC - [STC ST04261CH](https://openairdocs.org/stc/ST04261CH): Installation of a Gear Latch & Ground Shift system. Preferred Improvements LLC - [STC SA4-220](https://openairdocs.org/stc/SA4-220): Installation of tail wheel cover and fairing. Preferred Improvements LLC - [STC SA4-230](https://openairdocs.org/stc/SA4-230): Installation of aileron gap closure. Preferred Improvements LLC - [STC SA4147WE](https://openairdocs.org/stc/SA4147WE): Installation of a Flap and Landing Gear Aural Warning System. United Aeronautical Corporation - [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 SA02283SE PAGE 2](https://openairdocs.org/stc/SA02283SE%20PAGE%202): 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 ST334CH](https://openairdocs.org/stc/ST334CH): Installation of Superflite 102 fabric.. Aviation Products Systems Inc. - [STC SA1CE](https://openairdocs.org/stc/SA1CE): Weather Radar Installation.. Sabreliner Aviation LLC - [STC SA3-141](https://openairdocs.org/stc/SA3-141): Installation of dual Stewart-Warner Model 940-B24 cabin heaters.. Sabreliner Aviation LLC - [STC SA3-142](https://openairdocs.org/stc/SA3-142): Installation of Stewart-Warner Model 940-B24 cabin heater.. Sabreliner Aviation LLC - [STC SA3-173](https://openairdocs.org/stc/SA3-173): Installation of vacuum pump and vacuum system.. Sabreliner Aviation LLC - [STC SA3-240](https://openairdocs.org/stc/SA3-240): Standard installation - swivel chair assembly.. Sabreliner Aviation LLC - [STC SA3-25](https://openairdocs.org/stc/SA3-25): Installation of short exhaust stack (simplified version).. Sabreliner Aviation LLC - [STC SA3-271](https://openairdocs.org/stc/SA3-271): Installation of RCA Model AVQ-50 radar.. Sabreliner Aviation LLC - [STC SA3-272](https://openairdocs.org/stc/SA3-272): Standard seat track installation for SK10187 swivel seat.. Sabreliner Aviation LLC - [STC SA3-282](https://openairdocs.org/stc/SA3-282): Installation of Generator over-heat temperature indicator system.. Sabreliner Aviation LLC - [STC SA3-294](https://openairdocs.org/stc/SA3-294): Installation of airstep door safety chair and release mechanism.. Sabreliner Aviation LLC - [STC SA3-337](https://openairdocs.org/stc/SA3-337): Nacelle modification and installation of short exhaust stacks.. Sabreliner Aviation LLC - [STC SA3-392](https://openairdocs.org/stc/SA3-392): Passenger seat installation.. Sabreliner Aviation LLC - [STC SA3-426](https://openairdocs.org/stc/SA3-426): Engine Fire Control Zones, Fire Detector Installation, Dual Fire Bottle Installation, Oil Cooler Installation, and Propeller Feathering System.. Sabreliner Aviation LLC - [STC SA3-429](https://openairdocs.org/stc/SA3-429): Typical installation of Burns Aero seat.. Sabreliner Aviation LLC - [STC SA3-448](https://openairdocs.org/stc/SA3-448): Installation of Cockpit side windows.. Sabreliner Aviation LLC - [STC SA3-450](https://openairdocs.org/stc/SA3-450): Passenger seat and track installation.. Sabreliner Aviation LLC - [STC SA3-498](https://openairdocs.org/stc/SA3-498): Three-place divan assembly and installation.. Sabreliner Aviation LLC - [STC SA3-522](https://openairdocs.org/stc/SA3-522): Installation of a windshield carburetor propeller alcohol system.. Sabreliner Aviation LLC - [STC SA3-59](https://openairdocs.org/stc/SA3-59): Installation of cabin heater, Stewart-Warner 940-B24.. Sabreliner Aviation LLC - [STC SA3-99](https://openairdocs.org/stc/SA3-99): Collins 537F-1 radar scanner mount installation.. Sabreliner Aviation LLC - [STC SA106CE](https://openairdocs.org/stc/SA106CE): Install Hoskins Model F or B Wing Tip Lights and Model C or K Tail Lights, with or without two Model 1 or 2 Fuselage Lights.. BF Goodrich Aerospace - [STC SA1315WE](https://openairdocs.org/stc/SA1315WE): Installation of Mixture Monitor (exhaust gas temperature probe, gage and selector) in accordance with Delta Products Part Lists A-192 and A-193, or in accordance with Tri-Star Corporation Mixture Monitor Installation Instructions dated December 9, 1981, or later FAA approved revision and/or Drawing List MM-127 dated November 15, 1981, or later FAA approved revision in aircraft models listed in Master Eligibility List P-80-A-6 revised March 29, 1968, copy attached, or later FAA approved revision.. Universal Corporation - [STC SA01988SE](https://openairdocs.org/stc/SA01988SE): Installation of Electronics International Inc. Glass Panel Engine Monitor (with In-Flight Data) MVP-50P.. Electronics International Inc. - [STC SA1-49](https://openairdocs.org/stc/SA1-49): Installation of cockpit jump seat.. Page Avjet Corp All 139: https://openairdocs.org/tcds/A-618/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.