TCDS A-618

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)