TCDS 4A21

Page No. 1 2 3 4 5 6 7 8 9 10 11 12 13 14 15 16 17 18 Rev No. 8 - - - - - - - - - - - - - - - - - Reformatted 12/93. DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION 4A21 Revision 8 BOEING 707-100 Long Body 707-200 707-100B Long Body 707-100B Short Body May 1, 1973 TYPE CERTIFICATE DATA SHEET NO. 4A21 This data sheet which is a part of type certificate No. 4A21 prescribes conditions and limitations under which the product for which the type certificate was issued meets the airworthiness requirements of the Civil Air Regulations. Type Certificate Holder THE BOEING COMPANY P. O. Box 3707 Seattle, Washington 98124 I - Model 707-100 Long Body (Transport Aircraft), approved September 18, 1958 The Model 707-100 Long Body has several different versions due to different installations of fuel tankage, baggage compartment, equipment, interiors, airplane flight manuals, etc. These versions are as follows: Version Serial Nos. Eligible 707-124 17609 thru 17612 and 18012 707-131 17658 thru 17672 Engines 4 Pratt and Whitney Turbo Wasp JT3C-6 Turbojet Fuel See NOTE 12 Certification Limits 707-100 Long Body Engine limits Takeoff static net thrust (standard day), lb., at sea level Dry (5 minutes) 11,200 Water injection (2-1/2 minutes) *13,000 * See NOTE 7(c) for optional engine rating Maximum continuous static thrust, (standard day), lb., at sea level) 10,000 Maximum permissible engine rotors operating speeds: Low pressure compressor (N1), r.p.m. 7,000 (113%) High pressure compressor (N2), r.p.m.9,950 (99.7%) Maximum E.P.R. values shown in the Airplane Flight Manual shall not be exceeded Maximum permissible turbine outlet gas temperatures: Takeoff (5 minutes dry; 2-1/2 minutes wet) (630°C) 1166°F Maximum continuous (560°C) 1040°F Maximum for acceleration (2 minutes) (650°C) 1202°F Starting maximum gas temperature (Ground) (450°C) 842°F 4A21 2 Maximum permissible air bleed extractions of total engine air flow: High pressure compressor From idle to maximum continuous 5.5% At takeoff 2.0% Low pressure compressor From idle to maximum continuous 1.0% At takeoff 2.2% Airspeed limits (IAS) Case I is applicable to the 707-131 version. Case II and Case III are applicable to the 707-124 version. Case I covers normal operations up to a gross weight of 248,000 lb. Case II covers normal operations up to a gross weight of 258,000 lb. with a restriction in forward C.G. limit of 17% up to 250,000 lb. and a linear increase to 18% at 258,000 lb. Case III covers operations up to a gross weight of 258,000 lb. with restriction in airspeeds with the C.G. forward of the Case II limits. Speed limitations for Case I and II are identical. Case I and II Operations Vmo (maximum Operating) 390 m.p.h. at sea level (339 kt.) 398 m.p.h. at 5,000 ft. (345 kt.) 406 m.p.h. at 10,000 ft. (352 kt.) 415 m.p.h. at 15,000 ft. (360 kt.) 425 m.p.h. at 20,000 ft. (369 kt.) 434 m.p.h. at 24,900 ft. (377 kt.) Mmo = .884 at 24,900 ft. and above Va (Maneuvering) 286 m.p.h. at sea level (249 kt.) 292 m.p.h. at 20,000 ft. (254 kt.) 314 m.p.h. at 39,500 ft. (273 kt.) Ma = .884 at 39,500 ft. and above Vfe (Flap Speeds) (flaps not to be extended above 20,000 feet) Max. Flap Deflection (MPH) (KT.) 20° 251 218 30° 239 208 50° 211 183 Vlo (Landing Gear Operation) 310 m.p.h. at sea level to 30,000 ft. (269 kt.) 324 m.p.h. at 30,000 ft. to 35,000 ft. (281 kt.) Mlo = .825 Mach at 35,000 ft. and above Vle (Landing Gear Extended) 367 m.p.h. to 29,300 ft. (319 kt.) Mle = .825 Mach at 29,300 ft and above Landing Light Extended 439 m.p.h. at sea level to 24,200 ft. (381 kt.) M = .884 at 24,200 ft. and above 3 4A21 Maximum Dump Chute Extended and Extending Speed Extending speed 275 m.p.h. to 41,700 ft. (239 kt.) M = .825 above 41,700 ft. Extended speed 315 m.p.h. to 36,200 ft. (274 kt.) M - .825 at 36,200 ft. and above Vmc (Minimum Control Speed) - One engine inoperative For wet takeoff thrust 140 m.p.h. (122 kt.) sea level and standard day For dry takeoff thrust 128 m.p.h. (111 kt.) sea level and standard day Case III Operation Vmo (Maximum Operating) 390 m.p.h. at sea level to 30,000 ft. (339 kt.) to Mmo = .884 at 30,000 ft. and above Other airspeed limitations are the same as Case I and II. C.G. range and Datum The nose gear retraction moment is 18,600 in.-lb. and moves C.G. forward. The main gear retracts parallel to the Wing Reference Axis; hence, has no effect on airplane C.G. All stations noted in the Data Sheet are Body Stations unless identified specifically as moment arms. Dwg. 69-10819 defines Body Stations and moment arms. Datum is 50 in. forward of nose (moment arm = 0) for weight and balance purposes. Horizontal distance of datum to average wing jack point is 810.5 in. The weight and C.G. locations for Case I, II, and III operation are indicated in chart below: Case I Gross Weight Forward Limit Aft Limit 248,000 lb. 15.0% MAC (Sta. 822.5) 32.0% MAC (Sta. 863.6) 238,000 lb. 14.0% MAC (Sta. 820.1) 35.0% MAC (Sta. 870.9) 220,000 lb. 14.0% MAC (Sta. 820.1) 35.0% MAC (Sta. 870.9) 190,000 lb. 14.0% MAC (Sta. 820.1) 33.3% MAC (Sta. 866.8) 185,000 lb. 16.0% MAC (Sta. 824.9) 33.1% MAC (Sta. 866.3) 130,000 lb. 16.0% MAC (Sta. 824.9) 30.0% MAC (Sta. 858.8) Case II 258,000 lb. 18.0% MAC (Sta. 829.7) 25.0% MAC (Sta. 846.7) 250,000 lb. 17.0% MAC (Sta. 827.3) 30.6% MAC (Sta. 860.2) 248,000 lb. 17.0% MAC (Sta. 827.3) 32.0% MAC (Sta. 863.6) 238,000 lb. 17.0% MAC (Sta. 827.3) 35.0% MAC (Sta. 870.9) 220,000 lb. 17.0% MAC (Sta. 827.3) 35.0% MAC (Sta. 870.9) 130,000 lb. 17.0% MAC (Sta. 827.3) 30.0% MAC (Sta. 858.9) Case III 258,000 lb. 16.0% MAC (Sta. 824.9) 25.0% MAC (Sta. 846.7) 250,000 lb. 15.0% MAC (Sta. 822.5) 30.6% MAC (Sta. 860.2) 248,000 lb. 15.0% MAC (Sta. 822.5) 32.0% MAC (Sta. 863.6) 238,000 lb. 15.0% MAC (Sta. 822.5) 35.0% MAC (Sta. 870.9) 220,000 lb. 15.0% MAC (Sta. 822.5) 35.0% MAC (Sta. 870.9) 190,000 lb. 15.0% MAC (Sta. 822.5) 33.3% MAC (Sta. 866.8) 185,000 lb. 17.0% MAC (Sta. 827.3) 33.1% MAC (Sta. 866.3) 130,000 lb. 17.0% MAC (Sta. 827.3) 30.0% MAC (Sta. 858.8) (1) Straight line variation between values. (2) The aft C.G. limitation shown in the above table for gross weights below 220,000 lb. applies to takeoff conditions only. For airborne or landing conditions below 220,000 lb., the aft C.G. limitation is 35.0% MAC (BS 870.9). 4A21 4 Maximum weights 707-131 707-124 (See NOTE 14) (See NOTE 8) (lb.) (lb.) Maximum ramp weight 248,000 258,000 Maximum flight weight, flaps 30° 246,000 256,000 Maximum flight weight, flaps up 243,000 253,000 Maximum flight weight at which the outboard auxiliary fuel tanks can be empty 233,000 233,000 Maximum landing weight 190,000 190,000 Maximum zero fuel weight 170,000 170,000 Maximum baggage 707-124, -131 Maximum Maximum Body Load Concentration Capacity Moment Compt. Station (lb./sq.ft.) (lb./sq.ft.) (lb.) Arm Fwd. Belly 400-600H+6 47 150 9000 + 453 Aft Belly 960-1060 50 150 7000* +1030 Aft Belly 1060-1200 35 150 4900* +1170 Aft Belly 1200-1300 20 150 2000* +1290 *Total aft compartment capacity should not exceed the following: Version Capacity, lb. 707-124 13,900 707-131 10,800 Fuel capacity See NOTE 1(c) for information relative to unusable fuel; NOTE 1(d) for required fuel usage procedure; NOTE 1(e) for undumpable fuel. The following data are given for full fuel tanks. See Boeing Documents indicted below for other fuel and water C.G. locations with partially filled tanks: Version Document 707-124 D6-1854 707-131 D6-1853 Nominal Capacity Max. Capacity (Usable fuel in tank) (lb. per Moment Tanks (U.S. Gal. per Tank) Tank) Arm 707-124 (Serial Nos. 17609 thru 17612 only) No. 1 & No. 4 Reserve 434 2,995 1082.6 No. 1 & No. 4 Main 2,333 16,098 916.2 No. 2 & No. 3 Main 2,283 15,753 791.6 Center 3,386 23,363 740.0 Total 13,486 93,055 707-131 No. 1 & No. 4 Reserve 434 2,995 1082.6 No. 1 & No. 4 Main 2,333 16,098 916.6 No. 2 & No. 3 Main 2,283 15,753 791.2 Center 5,356 36,956 744.6 Total 15,456 106,648 5 4A21 707-124 (Serial No. 18012 only) No. 1 & No. 4 Reserve 434 2,995 1082.6 No. 1 & No. 4 Main 2,333 16,098 916.6 No. 2 & No. 3 Main 2,283 15,753 791.2 Center 7,306 50,411 734.7 Total 17,406 120,103 Oil tank capacity Engine Oil Volume Moment Tank No. Location Capacity Arm 1 Outboard 6.5 gal. 869 Port 2 Inboard 6.5 gal. 686 Port 3 Inboard 6.1 gal. 686 Starboard 4 Outboard 6.1 gal. 869 Starboard The system oil capacities are given in Weight and Balance Control Manuals as noted under "Fuel Capacity". Thrust Augmentation Water Capacity Total Usable Moment Arm (709 gal.) (5913 lb.) *(709 gal.) (5913 lb.) 925.7 * 22.8 gal. is unusable but drainable; therefore, it will not be included in the airplane empty weight. II - Model 707-200 (Transport Aircraft), approved November 5, 1959 (Same as Model 707-100 Long Body except for engines and associated changes and limitations) Version Serial Nos. Eligible 707-227 17691 thru 17695 Engines 4 Pratt and Whitney Turbo Wasp JT4A-3/5 or JT4A-9/10 Turbojet (See NOTE 5 for interchangeability of engines) (Operation of the Pratt and Whitney JT4A-9/-10 Engines must be at JT4A-3/-5 Engine Thrust Settings and Ratings, with the exception stated in NOTE 13.) JT4A-3/5 JT4A-9/10 Engine limits Takeoff static net thrust 15,800 16,800 (standard day), lb., at sea level, Dry (5 minutes) Maximum continuous static thrust, (standard day), lb., at sea level) 12,500 13,500 Maximum permissible engine rotors operating speeds: Low pressure compressor (N1), r.p.m. 6,950 7,060 High pressure compressor (N2), r.p.m. 9,050 9,135 Maximum E.P.R. values shown in the Airplane Flight Manual shall not be exceeded 4A21 6 Maximum permissible turbine outlet gas temperatures: Takeoff (5 min.) (607°C) 1125°F (635°C) 1175°F Maximum continuous (500°C) 932°F (516°C) 960°F Maximum for acceleration (2 min.) (607°C) 1125°F (635°C) 1175°F Starting maximum gas temperature Ground (450°C) 842°F (450°C) 842°F In flight (475°C) 887°F (475°C) 887°F Maximum permissible air bleed extractions of total engine air flow: High pressure compressor At takeoff 1.5% 1.5% All other running 5.5% 5.5% Low pressure compressor At takeoff 1.6% 1.65% All other running 2.0% 2.0% For 3-engine takeoff, N1 bleed 1.9%, N2 bleed 2.2% Airspeed limits (IAS) Vmo (Maximum Operating Speed) 390 m.p.h. at sea level (339 kt.) 398 m.p.h. at 5,000 ft. (345 kt.) 406 m.p.h. at 10,000 ft. (352 kt.) 415 m.p.h. at 15,000 ft. (360 kt.) 425 m.p.h. at 20,000 ft. (369 kt.) 434 m.p.h. at 24,900 ft. (377 kt.) Mmo = .884 at 24,900 ft. and above Va (Maneuvering) 286 m.p.h. at sea level (249 kt.) 292 m.p.h. at 20,000 ft. (254 kt.) 314 m.p.h. at 39,500 ft. (273 kt.) Ma = .884 at 39,500 ft. and above Vfe (Flap Speeds) (flaps not to be extended above 20,000 feet) Max. Flap Deflection (MPH) (KT.) 20° 251 218 30° 240 208 50° 211 183 Vlo (Landing Gear Operation) 310 m.p.h. at sea level to 30,000 ft. (269 kt.) 324 m.p.h. at 30,000 ft. to 35,000 ft. (281 kt.) Mlo = .825 Mach at 35,000 ft. and above Vle (Landing Gear Extended) 367 m.p.h. to 29,300 ft. (319 kt.) Mle = .825 Mach at 29,300 ft. and above Landing Light Extended 439 m.p.h. at sea level to 24,200 ft. (381 kt.) M = .884 at 24,200 ft. and above 7 4A21 Maximum Dump Chute Extended and Extending Speed Extending speed 275 m.p.h. to 41,700 ft. (239 kt.) M = .825 above 41,700 ft. Extended speed 315 m.p.h. to 36,200 ft. (274 kt.) M - .825 at 36,200 ft. and above Vmc (Minimum Control Speed) - One engine inoperative For takeoff thrust 126 m.p.h. (109 kt.) sea level and standard day C.G. range and Datum The nose gear retraction moment is 18,600 in.-lb. and moves C.G. forward. The main gear retracts parallel to the Wing Reference Axis; hence, has no effect on airplane C.G. All stations noted in the Data Sheet are Body Stations unless identified specifically as moment arms. Dwg. 69-10819 defines Body Stations and moment arms. Datum is 50 in. forward of nose (moment arm = 0) for weight and balance purposes. Horizontal distance of datum to average wing jack point is 810.5 in. The weight and C.G. locations are indicated in chart below: Gross Weight Forward Limit Aft Limit 258,000 lb. 16.0% MAC (Sta. 824.9) 18.0% MAC (Sta. 829.7) 25.0% MAC (Sta. 847.7) 250,000 lb. 15.0% MAC (Sta. 822.5) 17.0% MAC (Sta. 827.3) 32.0% MAC (Sta. 863.6) 248,000 lb. 15.0% MAC (Sta. 822.5) 17.0% MAC (Sta. 827.3) 35.0% MAC (Sta. 870.9) 235,000 lb. 15.0% MAC (Sta. 822.5) 17.0% MAC (Sta. 827.3) 35.0% MAC (Sta. 870.9) 195,000 lb. 15.0% MAC (Sta. 822.5) 17.0% MAC (Sta. 827.3) 32.7% MAC (Sta. 865.3) 190,000 lb. 17.0% MAC (Sta. 827.3) 17.0% MAC (Sta. 827.3) 32.4% MAC (Sta. 864.7) 130,000 lb. 17.0% MAC (Sta. 827.3) 17.0% MAC (Sta. 827.3) 29.0% MAC (Sta. 857.6) (1) Straight line variation between values. (2) The aft C.G. limitation shown in the above table for gross weights below 235,000 lb. applies to takeoff conditions only. For airborne or landing conditions below 235,000 lb., the aft C.G. limitation is 35.0% MAC (BS 870.9). (3) A restricted speed zone exists between the forward limits listed above. Aircraft loaded to initial gross weights greater than 248,000 pounds must observe reduced Vmo of 339 knots IAS when operating in this zone. Maximum weights 707-227 Maximum ramp weight 258,000 lb. (See NOTE 8) Maximum flight weight, flaps 30° 257,000 lb. Maximum flight weight, flaps up 256,500 lb. Maximum flight weight at which the outboard auxiliary fuel tanks can be empty 233,000 Maximum landing weight 190,000 Maximum zero fuel weight 170,000 Maximum baggage 707-227, Maximum Maximum Body Load Concentration Capacity Moment Compt. Station (lb./in.) (lb./sq.ft.) (lb.) Arm Fwd. Belly 400-600H+6 47 150 9000 + 453 Aft Belly 960-1060 50 150 7000 +1030 Aft Belly 1060-1200 35 150 4900 +1170 Aft Belly 1200-1300 20 150 2000 +1290 4A21 8 Fuel capacity See NOTE 1(c) for information relative to unusable fuel; NOTE 1(d) for required fuel usage procedure; NOTE 1(e) for undumpable fuel. The following data are given for full fuel tanks. See Boeing Documents D6-3352 for other fuel and water C.G. locations with partially filled tanks: Nominal Capacity Max. Capacity (Usable fuel in tank) (lb. per Moment Tanks (U.S. Gal. per Tank) Tank) Arm No. 1 & No. 4 Reserve 434 2,995 1082.6 No. 1 & No. 4 Main 2,333 16,098 916.6 No. 2 & No. 3 Main 2,283 15,753 791.2 Center 7,306 50,411 744.6 Total 17,406 120,103 Oil tank capacity The system oil capacities are given in Weight and Balance Control Manual D6-3352. Engine Oil Volume Moment Tank No. Location Capacity Arm 1 Outboard 8.33 gal. 868.5 Port 2 Inboard 8.33 gal. 685.8 Port 3 Starboard 8.34 gal. 685.8 Port 4 Outboard 8.34 gal. 868.5 Port III - Model 707-100B Long Body (Transport Aircraft), approved March 1, 1961 (Same as Model 707-100 Long Body except for engines, wing changes and other associated changes and limitations) Version Serial Nos. Eligible 707-121B 17586; 17587; and 17589 thru 17591 707-123B 17628; 17630 thru 17640; 17642 thru 17652; and 19185 thru 19188; 18882 thru 18885; 18054; 19323 thru 19341. 707-131B 18385 thru 18397; 18400 thru 18404; 18758 thru 18762; 18986 thru 18989; 19215 thru 19223; 19436, 19568 and 19569. 707-139B 17903 707-153B 17925 thru 17927 Engines 4 Pratt and Whitney Turbo Wasp JT3D-1, JT3D-1MC6, JT3D-3, JT3D-3B, or JT3D-1MC7, Turbofan (See also NOTE 10) Fuel See NOTE 12 Certification Limits 707-121B, -131B, Engine limits 707-123B -139B, & -153B Takeoff static net thrust (standard day), lb., at sea level Dry (5 minutes) 17,000 18,000 Maximum continuous static thrust (standard day), lb., at sea level 14,500 16,400 Maximum permissible engine rotors operating speeds: Low pressure compressor (N1), r.p.m. 6,800 6,800 High pressure compressor (N2), r.p.m. 10,200 10,250 Maximum E.P.R. values shown in the Airplane Flight Manual shall not be exceeded 9 4A21 Engine limits (cont'd) Maximum permissible turbine outlet gas temps: Takeoff (5 minutes) (530°C) 985°F (555°C) 1031°F) Maximum continuous (460°C) 860°F (490°C) 914°F) Maximum for acceleration (2 minutes) (530°C) 985°F (555°C) 1031°F) Starting (450°C) 842°F (450°C) 842°F) Maximum permissible air bleed extractions of total engine air flow: High pressure compressor From idle to maximum continuous 5.5% 5.5% At takeoff 2.0% 2.0% Low pressure compressor From idle to maximum continuous 2.0% 2.0% At takeoff 2.2% 2.2% Airspeed limits (IAS) Vmo (maximum Operating) 436 m.p.h. at sea level (379 kt.) (379 kt.) 441 m.p.h. at 10,000 ft. (384 kt.) 454 m.p.h. at 20,000 ft. (395 kt.) 459 m.p.h. at 23,000 ft. (399 kt.) Mmo = .90 at 23,000 ft. and above Va (Maneuvering) 290 m.p.h. at sea level (252 kt.) 290 m.p.h. at 5,000 ft (252 kt.) 292 m.p.h. at 10,000 ft. (253 kt.) 294 m.p.h. at 15,000 ft. (255 kt.) 296 m.p.h. at 20,000 ft. (257 kt.) 300 m.p.h. at 25,000 ft. (261 kt.) 307 m.p.h. at 30,000 ft. (267 kt.) 314 m.p.h. at 35,000 ft. (273 kt.) 321 m.p.h. at 39,600 ft. (279 kt.) Ma = .90 at 39,600 ft. and above Vfe (Flaps speeds) Max. Flap Deflection (MPH) (KT.) 20° 253 220 30° 242 210 50° 213 185 Vlo (Landing Gear Operation) Sea Level to 30,000 ft. (311 m.p.h.) (270 kt.) 30,000 ft. to 35,800 ft. (322 m.p.h.) (280 kt.) Mlo = .83 Mach at 35,800 ft. and above Vle (Landing Gear Extended) Sea Level to 30,000 ft. (320 kt.) Mle = .83 at 30,000 ft. and above Dump Chute Operation 276 m.p.h. at Sea Level to 42,000 ft. (240 kt.) Dump Chute Extended 317 m.p.h. at Sea Level to 36,700 ft. (275 kt.) M = .83 at 36,700 ft. and above Vmc (Minimum Control Speed) Minimum control speed (Air) Vmca 125.3 m.p.h. (109 kt.) Maximum takeoff thrust Minimum control speed (Ground) Vmcg 119 m.p.h. (103.5 kt.) 4A21 10 C.G. range and Datum The nose gear retraction moment is 18,600 in.-lb. and moves C.G. forward. The main gear retracts parallel to the Wing Reference Axis; hence, has no effect on airplane C.G. All stations noted in the Data Sheet are Body Stations unless identified specifically as moment arms. For weight and balance purposes, datum is 50 in. forward of nose (moment arm - 0) Horizontal distance of datum to average wing jack point is 810.5 in. TAKEOFF Gross Weight Forward Limit Aft Limit 258,000 lb. 15.0% MAC (Sta. 822.3) 25.0% MAC (Sta. 846.7) 249,400 lb. 14.1% MAC (Sta. 820.3) 31.0% MAC (Sta. 861.2) 238,000 lb. 13.0% MAC (Sta. 817.6) 31.0% MAC (Sta. 861.2) 195,000 lb. 13.0% MAC (Sta. 817.6) 31.0% MAC (Sta. 861.2) 190,000 lb. 14.0% MAC (Sta. 820.1) 31.0% MAC (Sta. 861.2) 179,000 lb. 14.0% MAC (Sta. 820.1) 31.0% MAC (Sta. 861.2) 175,000 lb. 14.0% MAC (Sta. 820.1) 30.7% MAC (Sta. 860.5) 135,000 lb. 14.0% MAC (Sta. 820.1) 28.0% MAC (Sta. 853.9) FLIGHT 258,000 lb. 15.0% MAC (Sta. 822.3) 25.0% MAC (Sta. 846.7) 249,000 lb. 13.7% MAC (Sta. 819.3) 31.0% MAC (Sta. 861.2) 238,000 lb. 12.0% MAC (Sta. 815.2) 31.0% MAC (Sta. 861.2) 200,000 lb. 12.0% MAC (Sta. 815.2) 31.0% MAC (Sta. 861.2) 190,000 lb. 14.0% MAC (Sta. 820.1) 31.0% MAC (Sta. 861.2) 175,000 lb. 14.0% MAC (Sta. 820.1) 31.0% MAC (Sta. 861.2) LANDING 190,000 lb. 16.0% MAC (Sta. 824.5) 35.0% MAC (Sta. 870.9) 185,000 lb. 15.0% MAC (Sta. 822.3) 35.0% MAC (Sta. 870.9) 175,000 lb. 14.0% MAC (Sta. 820.1) 35.0% MAC (Sta. 870.9) Straight line variation between values. Maximum weights (See NOTE 8) Maximum ramp weight 258,000 lb. Maximum flight weight 258,000 lb. Maximum flight weight at start of outboard reserve fuel transfer 248,000 lb. Maximum flight weight at which the outboard reserve tanks can be empty 243,000 lb. Maximum landing weight 190,000 lb. Maximum zero fuel weight 170,000 lb. Maximum effective structural design zero fuel weight 185,000 lb. Maximum baggage Maximum Maximum Body Load Concentration Capacity Moment Compt. Station (lb./in.) (lb./sq.ft.) (lb.) Arm Fwd. Belly 400-600H+6 47 150 9000* 453 Aft Belly 960-1060 50 150 7000 1030 Aft Belly 1060-1200 35 150 4900 1170 Aft Belly 1200-1300 20 150 2000 1290 *Fwd. cargo compartment weight limitation is 5000 lb. when ballast is installed on Bulkhead Station 178. (See NOTE 11) 11 4A21 Fuel capacity (See NOTE 1(c) for information relative to unusable fuel; NOTE 1(d) for required fuel usage procedure; NOTE 1(e) for undumpable fuel.) Maximum fuel capacity in pounds listed below must not be exceeded. See Boeing Documents below for other fuel and C.G. locations with partially filled tanks. 707-121B D6-2884 707-131B D6-1853 707-153B D6-3022 707-123B D6-1840 707-139B D6-5345 Nominal Capacity Max. Capacity (Usable fuel in tank) (lb. per Moment Tanks (U.S. Gal. per Tank) Tank) Arm Overwing Underwing Fueling Fueling No. 1 & No. 4 Reserve 434 434 3,081 1082.6 No. 1 & No. 4 Main 2,326 2,326 16,592 914.3 No. 2 & No. 3 Main 2,228 2,228 16,152 791.6 Center 5,432 5,451 51,874 744.2 Total 15,408 15,427 123,524 Oil tank capacity The system oil capacities are given in Weight and Balance Control Manual D6-1840. Engine Oil Volume Moment