TCDS A-781

Page No. 1 2 3 4 5 6 7 8 9 10 11 12 13 14 Rev. No. 38 - - - - - - - - - - - 37 37 DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION A-781 Revision 38 BOEING DC-6 September 27, 2010 AIRCRAFT SPECIFICATION NO. A-781 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 DC-6, Approved June 23, 1947 Engines 4 P & W R2800-34, -83A, -83AM3 or - 83AM4 (20:9 propeller reduction gearing): Double Wasps CA15 or CA18 (20:9 propelle r reduction gearing); or Double Wasps CB16 or CB17 (.45:1 propeller reduction gearing) Fuel Aviation gasoline: All engines ex cept CB17, Grade 100/130; CB17, Grade 108/135 Engine Limits (See NOTES 4 and 5 for additional limits and placards) (Straight line manifold pressure variation with altitudes shown) H P RPM MP in. HG. ALT P & W R2800-34 or -83A Low impeller gear ratio 7.29:1 Take-off (two minutes) (dry) 2100 2800 54.0 S.L. Maximum continuous 1800 2600 45.0 S.L. Maximum continuous 1800 2600 44.0 6500’ High impeller gear ratio 9.45:1 Maximum continuous 1600 2600 46.5 10000’ Maximum continuous 1600 2600 45.0 16200’ P & W R2800-83AM3 or -83AM4 Low impeller gear ratio 7.29:1 Take-off (two minutes) (dry) 2100 2800 54.0 S.L. Take-off (two minutes) (dry) 2100 2800 52.5 3400’ Take-off (two minutes) (wet) 2400 2800 56.5 S.L. Take-off (two minutes) (wet) 2400 2800 56.0 1000’ Maximum continuous 1800 2600 45.0 S.L. Maximum continuous 1800 2600 44.0 6500’ Maximum continuous 1700 2500 44.0 S.L. Maximum continuous 1700 2500 42.0 6500’ High impeller gear ratio 9.45:1 Maximum continuous 1600 2600 46.5 10000’ Maximum continuous 1600 2600 45.0 16200’ Maximum continuous 1500 2500 43.0 10000’ Maximum continuous 1500 2500 42.0 16000’ P & W Double Wasps CA15 A-781 2 Low impeller gear ratio 7.29:1 Take-off (two minutes) (dry) 2100 2800 53.5 S.L. Take-off (two minutes) (wet) 2400 2800 56.5 S.L. Maximum continuous 1800 2600 45.0 S.L. Maximum continuous 1800 2600 44.0 6500’ High impeller gear ratio 9.45:1 Maximum continuous 1600 2600 46.5 10000’ Maximum continuous 1600 2600 45.0 16200’ HP RPM MP in. HG. ALT P & W Double Wasps CA18 Low impeller gear ratio 7.29:1 Take-off (two minutes) (dry) 2100 2800 53.5 S.L. Take-off (two minutes) (wet) 2400 2800 56.5 S.L. (See item 111 for water-alcohol injection installation and Engine Specification E-231 for ADI fluid composition) Maximum continuous 1800 2600 45.0 S.L. Maximum continuous 1800 2600 44.0 6500’ High impeller gear ratio 9.1:1 Maximum continuous 1675 2600 49.0 8000’ Maximum continuous 1675 2600 47.0 13500’ P & W Double Wasps DB16 Low impeller gear ratio 7.29:1 Take-off (two minutes) (dry) 2050 2700* 55.0 S.L. Take-off (two minutes) (dry) 2050 2700* 53.0 6900’ * (See NOTE 5D for propeller governor re-setting prior to “dry” take-off) Take-off (two minutes) (dry) 1950 2800 53.0 S.L. Take-off (two minutes) (dry) 1950 2800 51.0 9800’ Take-off (two minutes) (wet) 2400 2800 59.5 S.L. Take-off (two minutes) (wet) 2400 2800 59.0 5000’ (See item 111 for water-alcohol injection installation and Engine Specification E-264 for ADI fluid composition) Maximum continuous 1800 2600 48.5 S.L. Maximum continuous 1800 2600 46.5 9200’ High impeller gear ratio 8.58:1 Maximum continuous 1700 2600 48.5 10000’ Maximum continuous 1700 2600 47.5 16800’ P & W Double Wasps CB17 Low impeller gear ratio 7.29:1 Take-off (two minutes) (dry) 2200 2800 60.0 S.L. Take-off (two minutes) (dry) 2200 2800 59.0 5200’ (critical altitude) Take-off (two minutes) (wet) 2500 2800 62.0 S.L. Take-off (two minutes) (wet) 2500 2800 61.5 3700’ (critical altitude) (See item 111 for water-alcohol injection installation and Engine Specification e-264 for ADI fluid composition) Maximum continuous 1900 2600 51.5 S.L. Maximum continuous 1900 2600 50.0 7100’ High impeller gear ratio 8.58:1 Take-off (two minutes) (wet) 1900 2600 50.5 10000’ Take-off (two minutes) (wet) 1900 2600 49.0 15700’ Maximum continuous 1750 2600 51.5 10000’ Maximum continuous 1750 2600 49.5 15000’ A-781 3 Airspeed Limits (T.I.A.S.) Max zero fuel and oil gross weight 70,000, 72,000 (see NOTE 6) 68,000# 69,000# 70,000# and 74,000# VC (Max Cruising) 300 mph (261 kts.) 294 mph (256 kts) 287 mph (250 kts) 300 mph (261 kts) S.L. to 11,000’ 1 S.L. to 12,000’ 1 S.L. to 13,000’ 1 S.L. to 11,000’ 1 or 15,000’ 3 or 16,000’ 3 or 17,000 3 or 15,000 3 VNE (Never Exceed) 360 mph (313 kts) 352 mph (306 kts) 344 mph (299 kts) 360 mph (313 kts) S.L. to 7,000’ 1 S.L. to 8,000’ 1 S.L. to 10,000’ 1 S.L. to 7,000 1 or 10,000’ 3 or 11,400’ 3 or 12,500’ 3 or 10,000 3 VP (Maneuvering) 200 mph (174 kts) 200 mph ( 174 kts) 200 mph (174 kts) 200 mph (174 kts) VF (Flaps Down) 0 to 30 200 mph (174 kts) 200 mph (174 kts) 200 mph (174 kts) 200 mph (174 kts) 30 to 50 160 mph (139 kts) 160 mph (139 kts) 160 mph (139 kts) 160 mph (139 kts) 2 VLO (Landing Gear Operation) 200 mph (174 kts) 200 m ph (174 kts) 200 mph (174 kts) 200 mph (174 kts) VLE (Landing gear operation) 200 mph (174 kts) 200 mph (174 kts) 200 mph (174 kts) 200 mph (174 kts) 1 (Above altitudes shown, reduce speed 6 mph (5 knots) per 1,000 feet.) 2 (165 mph (144 knots) for aircraft delivered from the factory with a maximum landing weight of 78,000 lbs. or aircraft modified to increase the landing weight from 75,000 lbs to 78,000 lbs as outlined in the information referred to in footnote 8 of NOTE 6. Aircraft delivered from the factory with a maximum landing weight of 80,000 lbs. should be placarded for a flap speed of 168 mph (146 knots) for flaps down 30 to 50). 3 (Applies only to aircraft incorporating the fifth elevator hinge per Douglas Dwg. 5365533 and nacelle fillet reinforcements per Douglas Dwg. 5333058-W and 5333059-M or Douglas SB DC-6 #453). Maximum Weights Landing 73,000 lbs., 75,000 lbs., 78,000 lbs., or 80,000 lbs. (See NOTE 5 for details) Zero fuel and oil gross weight: 68,000 to 70,000 lbs., 72,000 lbs., or 74,000 lbs. (See NOTE 6 and Airspeed Limits fo r details). (All weight in the airplane above these values must be in fuel and oil in the wing.) Take-off Weights: See Table below and NOTE 6. Dump valves are required as described in NOTE 3. For 3-engine ferrying, see NOTE 7 Propeller Installation Zero Fuel Curtiss Curtiss Curtiss Ham. Std. and Hamilton C632S -B/744-6C2 C632S-B/ C642S-B/ 43D60/6841 Hamilton Engine Oil Gross Standard C 632S-B/744-4C2-0 836-14C2 836-14C 2-18 43D60/6851 Standard Installation Weight 43 D60/ 6825 C632S-B/744-10C2 43D60/6873 43E60/6895 Eight Wing Tank Airplane R-2800-34 68,000 lbs 87,900 lbs 87,900 lbs 87,900 lbs 87,900 lbs 87,900 lbs -83A, or 69,000 lbs 88,900 lbs 88,900 lbs 88,900 lbs 88,900 lbs 88,900 lbs -83AM3 70,000 lbs 89,900 lbs 89,900 lbs 89,900 lbs 89,900 lbs 89,900 lbs 90,550 lbs 8 72,000 lbs 92,980 lbs 8 Double 68,000 lbs 87,900 lbs 87,900 lbs 87,900 lbs 87,900 lbs 87,900 lbs 87,900 lbs Wasp 69,000 lbs 88,900 lbs 88,900 lbs 88,900 lbs 88,900 lbs 88,900 lbs 88,900 lbs CA15 70,000 lbs 89,900 lbs 89,900 lbs 89,900 lbs 89,900 lbs 89,900 lbs 89,900 lbs 74,000 lbs 91,000 lbs 1,6 Double 68,000 lbs 87,900 lbs 1 Wasp 69,000 lbs 88,900 lbs 1 CB16 70,000 lbs 89,900 lbs 1 74,000 lbs 91,000 lbs 1,7 Ten Wing Tank Airplane R2800-34 (3) 91,300 lbs 1 92,650 lbs 1 91,300 1 91,000 lbs 1 93,100 lbs 1 -83A,-83AM3 93,200 lbs 2 93,200 lbs 2 -83AM4 Double (3) 89,000 lbs 1 91,300 lbs 1 92,700 lbs 1 91,000 lbs 1 93,100 lbs 1 Wasp 93,200 lbs 2,4 93,200 lbs 2,4 95,200 lbs 4 CA15 95,200 lbs 4 95,200 lbs 4 Double (3) 91,300 lbs 1 Wasp CA18 93,200 lbs 2,4 95,200 lbs 4 Double (3) 91,300 lbs 1 92,200 lbs1 Wasp CB16 93,200 lbs 2,4 93,200 lbs 4 CB17 95,200 lbs 4 97,200 lbs 4 A-781 4 FOOTNOTES 1Weight based on 20 take-off flap setting (See FAA Approved Airplane Operating Manual) 2Weight based on 0 take-off flap setting (See FAA Approved Airplane Operating Manual, Appendix I). 3Take-off weight on the ten wing tank airplanes is not affected by zero-fuel and oil gross weight. 4Take-off weight with Anti-Detonant Injection (See Engine Specification for ADI Fluid Composition) and 20 take-off flap setting (See FAA Approved Operation Manual). 5 Deleted. February 8, 1965. 6Applies only to those eight-wing tank airplanes shown in NOTE 6 to be structurally eligible for 74,000# zero fuel and oil weight. 7Limited by original certification weight. 8When operating at those weight, FAA Approved Airplane Flight Manual - Douglas Report SM-14595 (Item 401(b)) is required. C.G. Range Landing Gear Extended (1) Landing Gear Retracted (2) Forward (3) Aft Forward Aft Gross Weight % MAC Sta. % MAC Sta. % MAC Sta % MAC Sta. Applies to 68,000 lb., 70,000 lbs., and 72,000 lbs zero fuel and oil gross weight aircraft Up to and including 90,200 lb 95,200 lb 14.0 16.9 418.1 422.8 35.0 35.0 452.5 452.5 12.0 12.0 414.8 414.9 34.0 34.0 450.8 450.8 Applies to 74,000 lb., zero fuel and oil gross weight aircraft Up to and including 74,000 lb 86,680 lb 97,200 lb 14.0 16.1 18.0 418.1 421.5 424.6 35.0 35.0 35.0 452.5 452.5 452.5 12.0 14.7 16.8 414.8 419.2 422.7 34.0 34.0 34.0 450.8 450.8 450.8 (1) Applies for Take-off and Landing (2) Applies for Enroute Operation (3) Straight line variation in forward C.G. between weights shown Minimum Crew For all revenue f lights (passenger and/or cargo) 3 (Pilot and copilot (+108) and flight engineer (+129)) For all other flights (including test, ferry and training flights) 2 (Pilot and copilot (+108)) Additions to the above minimums may be specified by the FAA for long range flights and/or other special conditions. Passengers Variable - see NOTE 1(c) Maximum Baggage Information relative to procedures to be followed in determining maximum cargo compartment capacities based upon fusela ge strength and maximum floor loading for interior arrangements with various fore and aft seat spacings and with four (4) or five (5) abreast seating may be found in Douglas Service Bulletin DC-6 #504, reissued October 15, 1958. Fuel Capacity See NOTE 1(b) regarding “System Fuel and Oil” and NOTE 1(d) regarding required distribution of fuel load. Eight Wing Tank Airplane - 3322 gal. system: 2 outer wing tanks (#1 and 4 main) 360 gal. ea. (+448.0) 2 inboard inner wing tanks (#2 and 3 main) 508 gal. ea. (+440.9) 2 outboard inner wing tanks (#1 and 4 alt.) 431 gal. ea. (+444.1) 2 inner wing fuel cells (#2 a nd 3 alt.) 362 gal. ea. (+437.5) A-781 5 Ten Wing Tank Airplane - 4248 gal or 4262 gal system 2 outer wing tanks (#1 and 4 main) 360 gal. ea. (+448.0) 2 inboard inner wing tanks (#2 and 3 main) 508 gal. ea. (+440.9) 2 outboard inner wing tanks (#1 and 4 alt.) 519 gal. ea. (+448.9) or 2 outboard inner wing tanks ( #1 and 4 alt.) 526 gal. ea. (+448.9) (Serial 43294 and up) 2 inner wing fuel cells (#2 a nd 3 alt.) 527 gal. ea. (+449.0) *2 auxiliary fuel cells (L.H. and R.H.) 210 gal. ea. (+471.0) Ten Wing Tank Airplane - 4722 gal. system 2 outer wing tanks (#1 and 4 main) 360 gal. ea. (+448.0) 2 inboard inner wing tanks (#2 and 3 main) 508 gal. ea. (+440.9) 2 outboard inner wing tanks (#1 and 4 alt) 519 gal. ea. (+448.9) or 2 outboard inner wing tanks ( #1 and 4 alt) 526 gal. ea. (+448.9) (Serial 43294 and up) 2 inner wing fuel cells (#2 a nd 3 alt.) 527 gal. ea. (+449.0) *2 auxiliary fuel cells (L.H. and R.H.) 447 gal. ea. (+500.0) Ten Wing Tank Airplane - 4932 gal . system 2 outer wing tanks (#1 and 4 main) 695 gal. ea. (+460.0) 2 inboard inner wing tanks (#2 and 3 main) 508 gal. ea. (+440.9) 2 outboard inner wing tanks (#1 and 4 alt) 526 gal. ea. (+448.9) 2 inner wing fuel cells (#2 and 3 alt) 527 gal. ea. (+449.0) *2 auxiliary fuel cells (L.H. and R.H.) 210 gal. ea. (+471.0) *When 10 tank aircraft are changed to 8 ta nk aircraft by deleting the auxiliary cells, reduce the total fuel capacity by the cap acity of the two auxiliary tanks and the undumpable fuel is reduced by the amount shown in the appropriate section of NOTE 1(e). Oil Capacity See NOTE 1(b) regarding “Syste m Fuel and Oil” and NOTE 1(f) regarding wing fillet oil tank installation. Hamilton Standard propeller installation: 32 gal. in ea. nacelle (Doug Dwg. #5333289) (+360.0) & (+380.0) or 35 gal. in ea. nacelle (Doug Dwg. #5342754) (+349.0) & (+379.0) Curtiss electric propeller installation: 34 1/2 gal. in ea. nacelle (Doug Dwg. #5333289-500) (+350.0) & (+380.0) or 37 1/2 gal. in ea. nacelle (Doug Dwg. #5342754-500 or -502) (+349.0) & (+379.0) 26 gal. in wing fillet (Required on airc raft having a fuel system capacity of 4722 and up) Serial Nos. Eligible 42854 and up. (See NOTE 6 for complete list) Required Equipment 1(a) and 2 (a) or (c) and 101(b); or 1 (d), (g) or (h) and 2 (a) or (c) and 101(a), (b), (c), (d), (e) or (g); or 1(b), (c), (f) or (I) a nd 101(a), (b), (c), (d), (e) or (g); or 1(k) and 2(c) and 101(b), (c), (d), (e), (f), (g), (h) or (I); 103(b) or (g) and 103(c), (d), (e), (f) or (h); or 103 (h), (I) or (k) and (j); 201(a) or (b); 202; 203; 204; 205(a), (b), (c), (d), (e), (f), (g), (h), (I) or (j); 206 (a), (b) or (c); 207(a), (b) or (c); 208(a) or (b); 401; 402(a), (b), (c) or (d); 416(a); 429. Specification Pertinent to All Models Datum 3 in. aft of nose MAC 163.6 in. (L.E. of MAC +395.2) Leveling Means Bracket at Sta. 387.4 (below floor) and Sta. 64 to 82 (nose wheel well). Control Surface Movements Rudder  20 degrees Elevator 25 degrees up and 25degrees down Ailerons  17 degrees A-781 6 Certification Basis Type Certificate No. 781 (Tra nsport Category, combination CAR 4a and 4b and amendment 4-1 effective Nov. 1, 1946). The forward and aft lower belly cargo compartments are Class “D” Compartments. Smoke detectors, per Amendment 4b-2 effective Aug. 25, 1955, or ex tinguishing provisions are not required. Compliance with the ditching provision of 4b.292 (4b.261) has been demonstrated. Maximum approved operational altitude 25,000 ft. Production Basis Production Certificate No. 27 Export eligibility Eligible for export to all countries subject to the provisions of MOP 2-4 except as follows: (a) Canada - Landplane only eligible. Equipment Propellers and propeller accessories (except De-Icing Equipment) NOTE: When reversing propellers are installed, the minimum permissible force at the throttle knobs required to move each throttle from positive to negative thrust position shall be eight pounds in addition to the throttle system friction. 1. (a) 4 Ham. Std. propellers, hubs 43D 60, blades 6825-0 1,518 lbs (+272.0) Diameter: Max 13’1”, min. allowable for repairs 12’ 9 5/8” No further reduction permitted. Pitch settings at 42” sta.: Reverse - none; min. low +28 ; feathered +95. (see NOTE 5 for installation details and placards.) (b) 4 Curtiss propellers, hubs C632S-B, blades 744-4C2-0 1,563 lbs (+272.0) Pitch settings at 42” sta.: Reverse -19 ; min. low +24.6; feathered +95. (see NOTE 4 for placard.) (c) 4 Curtiss propellers, hubs C632S-B, blades 836-14C2-18 1,666 lbs (+272.0) Pitch settings at 54” sta.: Reverse -25.6 ; min low +25.6 for -34 and -83A engines, +24.6 for CA15 engines; feathered +87 (See NOTE 4 for installation details and placards) (d) 4 Ham. Std. propellers, hubs 43D 60, blades 6841-0 1,518 lbs (+272.0) Diameter: Max. 13’1”, min. allowable for repairs 12’ 9-5/8”. No further reduction permitted. Pitch settings at 42” sta.: Reverse -18 ; min. low +29; feathered +94. (See NOTE 5 for installation details and placards). (e) Deleted. February 8, 1965. (f) 4 Curtiss propellers, hubs C632S-B, blades 744-602-0 1,631 lbs (+272.0) Pitch settings at 42” sta.: Reverse 19 ; min. low +24.6; feathered +95. (See NOTE 4 for placard). (g) 4 Ham. Std. propellers, hubs 43D 60, blades 6873-0 1,611 lbs (+272.0) Diameter: Max. 13’1”, min. allowable for repairs 12’ 9-5/8”. No further reduction permitted. Pitch settings at 42” sta.: Reverse -18 ; min. low +29; feathered +94. (See NOTE 5 for installation details and placards). (h) 4 Ham. Std. propellers, hubs 43D 60, blades 6851-0 1,487 lbs (+272.0) Diameter: Max. 13’1”, min. allowable for repairs 12’ 9-5/8”. No further reduction permitted. Pitch settings at 42” sta.: Reverse -18 ; min. low +29; feathered +94. (See NOTE 5 for installation details and placards). (i) 4 Curtiss propellers, hubs 642S-B, blades 836-14C2-18 1,666 lbs (+272.0) Pitch settings at 54” sta.: Reverse -21 ; min. low +22.5; feathered +87.5. (See NOTE 4 for installation details and placards). (j) 4 Curtiss propellers, hubs C632S-B, blades 744-10C2-0 1,728 lbs (+272.0) Pitch settings at 42” sta. : Reverse -19 ; min. low +24.6; feathered +95. (See NOTE 4 for placard) (k) 4 Ham. Std. propellers, hubs 43E60, blades 6895-8 2,232 lbs (+272.0) Diameter: Max. 13’5-5/16”, mi n. allowable for repairs 13’1-9/16”. No further reduction permitted. Pitch settings at 42” sta. : Reverse -8 ; min. low +29 (except on CB16 or CB17 engines), min low +30 ) on CB16 or CB17 engines; Feathered +96 (approx) (l) 4 Spinners Ham. Std. 511748 with Douglas cowling interliners. 181 lbs (+276.0) A-781 7 2. (a) 4 propeller governors: Ham. St d. 5 x 18 49 lbs (+292.0) (b) Deleted July 12,,1948 (c) 4 propellers governors: Ham Std. 5U18. 52 lbs(+292.0) Engines and Engine Accessories - Fuel and Oil System 101. (a) 4 P & W R2800-34 engines 9,380 lbs. (+294.0) & (+324.0) (b) 4 P & W Double Wasp CA15 engi nes 9,281 lbs. (+294.0) & (+324.0) (c) 4 P & W R2800-34M1 engines 9,380 lbs. (+294.0) & (+324.0) (d) 4 P & W R2800-83AM3 engines 9,328 lbs. (+294.0) & (+324.0) (e) 4 P & W R2800-83A engines 9,328 lbs. (+294.0) & (+324.0) (f) 4 P & W Double Wasp CA18 engine s 9,284 lbs. (+294.0) & (+324.0) (g) 4 P & W R2800-83AM4 engines 9,328 lbs. (+294.0) & (+324.0) (h) 4 P & W Double Wasp CB16 engi nes 9,432 lbs. (+294.0) & (+324.0) (I) 4 P & W Double Wasp CB17 engine s 9,432 lbs. (+294.0) & (+324.0) 102. Fuel Dump Valve System (a) Deleted (b) Eight wing tank system (Doug. Dwg. 5248374) 132 lbs. (+422.0) (c) Ten wing tank system (Doug. Dwg. 5248374-500) 139 lbs. (+431.0) 103. System Fuel and Oil (a) Deleted (b) System fuel, eight wing fuel tanks (40.3 gal.) 242 lbs. (+438.2) (c) System oil, 35 gal. o il tank installation (50.9 gal) Ham. Std. propeller installa tion 382 lbs. (+330.9) (d) System oil, 37.5 gal. oil tank installation (34.5 gal) Curtiss propeller installation 260 lbs. (+331.1) (e) System oil, 32 gal. o il tank installation (50.1 gal) Ham. Std. propeller installa tion 376 lbs. (+330.6) (f) System oil, 34 1/2 gal. oil tank installation (34.5 gal) Curtiss propeller installation 260 lbs. (+331.2) (g) System fuel, 4248 or 4262 gal. capacity ten wing fuel tanks (64.6 gal.) 382 lbs. (+454.7) (h) System oil, 35 gal. tank installation (55 gal) Ham. Std propeller installation with 6895 series blades 413 lbs. (+325.9) (I) System fuel, 4722 gal. capacity ten wing fu el tanks (68.5) 411 lbs. (+458.6) (j) System oil wing fillet tank (50% oil -50% gasoline, 3.1 gals. 6.77#/gal) 21 lbs. (+472.0) (k) System fuel, 4932 gal capacity ten wing fuel tank (61.8 gal) 371 lbs (+457.0) 111. (a) Water-alcohol inj ection (Douglas Dwg. 7352910, 7352911 & 7353320) with water-alcohol regulator P & W No. 106400E (including 21.6 gal. fl uid) 106 lbs (+362.4) (b) Water-alcohol inj ection (Doug. DWG #7352910, 7371946, 5350629 & 5371664) with water-alcohol regulator P & W No. 106400E (including 38.8 gal. fluid) 535 lbs (+413.6) Landing Gear 201. (a) 4 Main wheel tires, 15.50x20, Type III, 16-ply rating, nylon (inflation pressure 110 psi) 540 lbs (+473.8) (b) 4 Main wheel tires, 15.50x20, Type III, 20-ply rating, nylon (inflation pressure 115 psi) 607 lbs (+473.8) 202. 4 Main wheel tubes, 15.50x20 regular 86 lbs (+473.8) 203. Nose wheel tire, 44 in., Type I, rib tread, 12-ply rating, nylon (inflation pressure 70 psi) 93 lbs (+ 99.0) 204. Nose wheel tube, 44 in. regular 16 lbs (+ 99.0) 205. 4 Main Gear - 17.00-20 (Type III) Wheel-Brake Assemblies (a) Goodyear model L20HBM: Wheel assembly No. 531063-M, Brake assembly No. 9540039 664 lbs (+473.8) (b) Goodyear model L20HBMF: Wheel assembly No. 9540049, Brake assembly No. 9540039 648 lbs (+473.8) (c) Goodyear model L20HBMF: Wheel assembly No. 9540049, Brake assembly No. 9540266 (Required for 78,000 lbs landing weight and up) 736 lbs (+473.8) A-781 8 (d) Goodyear model L20HBMF: Wheel assembly No. 9540332, Brake assembly No. 9540039 664 lbs (+473.8) (e) Goodyear model L20HBMF: Wheel assembly No. 9540332, Brake assembly No. 9540266 (Required for 78,000 lbs. landing weight and up) 742 lbs (+473.8) (f) Goodyear model L20HBMF: Wheel assembly No. 9540332, Brake assembly No. 9540471, (Skydrol only) (Required for 78,000 lbs. landing weight and up) 742 lbs (+473.8) (g) Goodyear model LF20HBM: Wheel assembly No. 9540484, Brake assembly No. 9540039 701 lbs (+473.9) (h) Goodyear model LF20HBM: Wheel assembly No. 9540484, Brake assembly No. 9540266 (Required for 78,000 lbs landing weight and up) 766 lbs (+473.8) (I) Goodyear model LF20HBM: Wheel assembly No. 9540484, Brake assembly No. 9540471 (Skydrol only) (Required for 78,000 lbs. landing weight and up) 766 lbs (+473.8) (j) Goodyear model LF20HBM: Wheel assembly No. 9540484, Brake assembly No. 9540505 (Required for 78,000 lbs. landing weight and up) 768 lbs (+473.8) 206. Nose gear - 44 in. (Type I) wheel (a) Goodyear model 448CA: Wheel assembly No. 530339-A 87 lbs (+ 99.0) (b) Goodyear model 448C: Wheel assembly No. 530339-M 62 lbs (+ 99.0) (c) Goodyear model 44NBM: Wheel assembly No. 9540375 72 lbs (+ 99.0) 207. (a) Main gear shock strut assy. (Doug. Dwg. 5342446) (Cleveland 8065E) (Maximum take-off weight 93,200 lbs.) 1,049 lbs (+474.8) (b) Main gear shock strut assy. (Doug. Dwg. 5342446-500) (Cleveland 8065G) (Maximum take-off weight 95,200 lbs.) 1,080 lbs (+474.8) (c) Main gear shock strut assy. (Doug. Dwg. 5342446-502) (Cleveland 8065H) (Maximum take-off weight 97,200 lbs.) 1,112 lbs (+474.8) (d) Main gear shock strut assy. (Doug. Dwg. 5342446-5502) (Skydrol only) (Cleveland 8065HA) 1,114 lbs (+474.8) (e) Main gear shock strut assy. (Doug. Dwg. 5342446-504) (Cleveland 8065J) (Maximum take-off gr oss weight 97,200 lbs.) 1,066 lbs (+474.8) (f) Main gear shock strut assy. (Doug. Dwg. 5342446-5504) (Skydrol only) (Cleve land 8065JA) (Maximum take-off gross weight 97,200 lbs. ) 1,074 lbs (+474.8) 208. (a) Nose gear shock strut assy. (Doug Dwg. 5240509) (Cleveland 8488A or B) 301 lbs (+109.8) (b) Nose gear shock strut assy. (Doug. Dwg. 5240509-500) (Skydrol only) (Cleveland 8488AA or BA) 301 lbs (+109.8) Interior Equipment