# TCDS 4A21: The Boeing Company - Type: Type certificate data sheet - Status: Current - Holder: The Boeing Company - Revision: 8 - Revised: May 1, 1973 - Product: Aircraft, Large Airplane - Certification basis: CAR 4b - Registered aircraft: 1, by the registry models matched to it (OpenAirDocs) - Data sheet PDF: https://openairdocs.org/files/sha256/2b/51/2b514347c9a6ed86c3459631e52444b5712eb8b883d561bf2611dfae907b93db - FAA DRS: https://drs.faa.gov/browse/excelExternalWindow/8B6EBAA7513BA29A852567240060420C.0001 - Page: https://openairdocs.org/tcds/4A21 ## Models (4) As the data sheet lists them. - 707-100B Short Body - 707-200 - 707-100 Long Body - 707-100B Long Body ## 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 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 Tank No. Location Capacity Arm 1 Outboard 6.0 gal. 866.9 Port 2 Inboard 6.0 gal. 684.1 Port 3 Inboard 6.1 gal. 684.1 Starboard 4 Outboard 6.1 gal. 866.9 Starboard IV - Model 707-100B Short Body (Transport Aircraft), approved July 24, 1961 (Same as Model 707-100 Short Body except for engines, wing changes and other associated changes and limitations.) Version Serial Nos. Eligible 707-138B 17696 thru 17702, 18067 thru 18069, 18334, 18739, and 18740 Engines 4 Pratt and Whitney Turbo Wasp JT3D-1, JT3D-1MC6, or JT3D-1MC7, Turbofan (See also NOTE 10) Fuel See NOTE 12 Engine limits Same as noted in Section III, Model 707-100B Long Body, except that 707-100B Short Body is approved for water augmentation; hence, the following static net thrust is valid: Certification Limits 707-138B Takeoff static net thrust (standard day), lb., at sea level wet (2 1/2 minutes) 17,000 Airspeed limits (IAS) Vmo (maximum Operating) (Basic) 434 m.p.h. at sea level (378 kt.) 443 m.p.h. at 10,000 ft. (384 kt.) 454 m.p.h. at 20,000 ft. (395 kt.) 459 m.p.h. at 25,300 ft. (399 kt.) 4A21 12 Airspeed limits (IAS) (cont'd) Mmo = .91 at 23,500 ft. and above Va (Maneuvering) 290 m.p.h. at sea level (252 kt.) 292 m.p.h. at 5,000 ft (253 kt.) 293 m.p.h. at 10,000 ft. (255 kt.) 295 m.p.h. at 15,000 ft. (256 kt.) 296 m.p.h. at 20,000 ft. (256 kt.) 302 m.p.h. at 25,000 ft. (263 kt.) 308 m.p.h. at 30,000 ft. (268 kt.) 314 m.p.h. at 35,000 ft. (273 kt.) 320 m.p.h. at 39,600 ft. (278 kt.) Ma = .91 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) 311 m.p.h. at sea level to 30,000 ft. (270 kt.) 322 m.p.h. at 30,000 ft. to 35,800 ft. (280 kt.) Mlo = .83 Mach at 35,800 ft. and above Vle (Landing Gear Extended) 368 m.p.h. at sea level to 29,000 ft. (320 kt.) Mle = .83 at 29,000 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 135 m.p.h. (117 kt.) Maximum takeoff thrust Minimum control speed (Ground) Vmcg 129 m.p.h. (112 kt.) 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 110 in. forward of nose (moment arm = 0) Horizontal distance of datum to average wing jack point is 810.5 in. Gross Weight Forward Limit Aft Limit TAKEOFF 258,000 lb. 15.5% MAC (Sta. 823.7) 25.0% MAC (Sta. 846.7) 248,400 lb. 14.4% MAC (Sta. 821.1) 32.0% MAC (Sta. 863.7) 244,650 lb. 14.0% MAC (Sta. 820.1) 33.0% MAC (Sta. 866.0) 235,850 lb. 13.0% MAC (Sta. 817.6) 33.0% MAC (Sta. 866.0) 214,000 lb. 13.0% MAC (Sta. 817.6) 33.0% MAC (Sta. 866.0) 210,000 lb. 13.0% MAC (Sta. 817.6) 32.8% MAC (Sta. 865.6) 13 4A21 C.G. range and Datum (cont'd) Gross Weight Forward Limit Aft Limit TAKEOFF 205,000 lb. 13.0% MAC (Sta. 817.6) 32.6% MAC (Sta. 865.1) 200,000 lb. 13.0% MAC (Sta. 817.6) 32.4% MAC (Sta. 864.6) 195,000 lb. 13.0% MAC (Sta. 817.6) 32.2% MAC (Sta. 864.1) 190,000 lb. 13.0% MAC (Sta. 817.6) 32.0% MAC (Sta. 863.7) 185,000 lb. 13.0% MAC (Sta. 817.6) 31.8% MAC (Sta. 863.1) 176,000 lb. 13.0% MAC (Sta. 817.6) 31.4% MAC (Sta. 862.1) 170,000 lb. 15.0% MAC (Sta. 822.5) 31.1% MAC (Sta. 861.4) 155,000 lb. 15.0% MAC (Sta. 822.5) 30.2% MAC (Sta. 859.2) 135,000 lb. 15.0% MAC (Sta. 822.5) 28.8% MAC (Sta. 855.9) FLIGHT 258,000 lb. 15.5% MAC (Sta. 823.7) 25.0% MAC (Sta. 846.7) 248,000 lb. 14.4% MAC (Sta. 821.1) 32.0% MAC (Sta. 863.7) 244,650 lb. 14.0% MAC (Sta. 820.1) 33.0% MAC (Sta. 866.0) 227,000 lb. 12.0% MAC (Sta. 815.2) 33.0% MAC (Sta. 866.0) 179,000 lb. 12.0% MAC (Sta. 815.2) 33.0% MAC (Sta. 866.0) 170,000 lb. 15.0% MAC (Sta. 822.5) 33.0% MAC (Sta. 866.0) 155,000 lb. 15.0% MAC (Sta. 822.5) 33.0% MAC (Sta. 866.0) LANDING 190,000 lb. 18.3% MAC (Sta. 830.5) 33.0% MAC (Sta. 866.0) 185,000 lb. 17.5% MAC (Sta. 828.5) 33.0% MAC (Sta. 866.0) 170,000 lb. 15.0% MAC (Sta. 822.5) 33.0% MAC (Sta. 866.0) Straight line variation between values shown. Maximum weights (See NOTE 8) 707-138B 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 9650 483 Aft Belly 960-1060 50 150 3000 990 Aft Belly 1060-1200 35 150 4900 1110 Aft Belly 1200-1300 20 150 2000 1230 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.) 4A21 14 The maximum fuel capacity in pounds listed below must not be exceeded. For other fuel C.G. locations with partially filled tanks, see Boeing Manual D6-3021. 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 437 437 3,081 1082.6 No. 1 & No. 4 Main 2320 2320 16,592 913.2 No. 2 & No. 3 Main 2242 2242 16,152 791.6 Center (Six Cell) 7370 7342 51,874 734.4 Total 17,362 17,334 123,524 Oil tank capacity The system oil capacities are given in Weight and Balance Control Manual D6-3021. Engine Oil Volume Moment Tank No. Location Capacity Arm 1 Outboard 6.0 gal. 866.9 Port 2 Inboard 6.0 gal. 684.1 Port 3 Inboard 6.1 gal. 684.1 Starboard 4 Outboard 6.1 gal. 866.9 Starboard Data Pertinent to All Models MAC 241.9 in. (L.E. of MAC is Body Station 786.2) Leveling means A plumb-bob attachment and leveling provision scale are provided in left wheel well. Minimum crew 3 persons for all flights: Pilot, Copilot, Flight Engineer Maximum passengers 179 limited by emergency exit requirements. Approved for 189 when equipped with four (4) inflatable escape chutes installed in accordance with FAA approved type design data. Maximum operating altitude The maximum operating altitude for all models is 42,000 feet. Other operating See FAA Approved Airplane Manuals and Supplements. limitations Control surface movements To insure proper operation of the airplane, the movement of the various control surfaces must be carefully controlled by proper rigging of the flight control systems. The airplane must, therefore, be rigged in accordance with the following FAA approved data: Surfaces Installation Dwg. Aileron and Spoiler 50-8701 Aileron Trim 50-8705 Inboard Aileron Balance Panel Tolerances 50-73133 Outboard Aileron Balance Panel Tolerances 50-73134 Speed Brakes (Spoilers) 50-8716 Elevator 50-8702 Elevator Balance Panel Tolerances 65-8424 Stabilizer Trim 50-8704 Rudder 50-8703 Rudder Trim 50-8706 Rudder Balance Panel Tolerances 65-14035 Wing Flap 50-8707 15 4A21 Service information Boeing Document D6-1649, Structural Repair Manual, is FAA approved. Service Bulletins, D6-1647, and other service information, when FAA approved, will carry a statement to that effect. Certification basis CAR 4b dated December 1953, Amendments 4b-1, 4b-2 and 4b-3 thereto; the Special Conditions and the provisions of Amendments listed in Attachment A of CAA letter to Boeing dated October 30, 1957; and the provisions of Item 2 of Special Civil Air Regulation No. SR- 422. 707-100B Long Body and 707-100B Short Body comply with all of the above except that Boeing chose to comply with Item 2 of Special Civil Air Regulation No. SR-422B in lieu of SR-422. Type Certificate No. 4A21 issued September 18, 1958. Date of Application for Type Certificate July 19, 1955; amended March 12, 1959, for Model 707-100B Long Body and 707-100B Short Body. Compliance with the following optional requirements has been established: Ditching Provisions of 4b.361 Ice Protection Provisions of 4b.640 Production basis Production Certificate No. 700 Equipment The basic required equipment as prescribed in the applicable airworthiness regulations (see Certification Basis) must be installed in the aircraft for certification. Boeing Airplane Company Document D6-5694 contains lists of all required equipment for Model 707-100 Long Body, and 707-200. The required equipment that must be installed as well as optional equipment approved for 707-100B Long Body and 707-100B Short Body are listed in Boeing Documents D6-1840 and D6-3021 respectively. The Weight and Balance Manual Documents indicated for each model under "Fuel Capacity" contain lists of equipment as well as optional installations approved by the FAA. NOTE 1. (a) Current weight and balance report including list of equipment included in certificated empty weight, and loading instructions must be in each aircraft at the time of original certification and at all times thereafter except in the case of the operators having an approved weight control system. (b) The airplane must be loaded so the C.G. is within the specified limits at all times, with the effects of fuel and water use, the movement of crew and passengers from their assigned positions being considered. (c) The "drainable unusable fuel" is that amount of fuel in the tanks which is unavailable to the engines under critical flight conditions as defined in CAR 4b.416. This drainable unusable fuel does not include the "tank trapped fuel" or "line unusable fuel", which is the unusable fuel retrained in the fuel feed and fuel dump lines. The "total unusable fuel", which includes the drainable unusable fuel, tank trapped fuel and line unusable fuel, must be included in the airplane empty weight or be suitably accounted for in the airplane weight and balance report. The total amount of fuel is as follows: For Model 707-100 Long Body except for the 707-124 version: Tank Trapped fuel 10.71 gal Drainable unusable fuel 37.90 gal. Line unusable fuel 7.85 gal. Total unusable fuel 56.46 gal. For the 707-124 only: Tank trapped fuel 8.04 gal. Drainable unusable fuel 29.17 gal. Line unusable fuel 7.85 gal. Total unusable fuel 45.06 gal. For Model 707-200 only: Tank Trapped fuel 10.71 gal Drainable unusable fuel 109.82 gal. Line unusable fuel 7.85 gal. Total unusable fuel 128.38 gal. 4A21 16 For Model 707-100B Long Body and 707-100B Short Body : Tank Trapped fuel 10.71 gal Drainable unusable fuel 109.82 gal. Line unusable fuel 7.85 gal. Total unusable fuel 128.38 gal. (d) I. Model 707-100 Long Body and Model 707-200 Fuel capacity and usage procedure are dictated by structural design. To preserve favorable wing bending moments, the following limitations shall apply: All center section fuel in excess of any included in the zero fuel weight must be used before the transfer of outboard reserve fuel. The airplane gross weight must not exceed 233,000 lb. if the reserve tanks are empty. A. Fuel Loading Limitations 1. Load main tanks 1, 2, 3, and 4 equally. 2. If main tanks are full, load reserve tanks. 3. If all main and reserve tanks are full and additional fuel is required, load center tank to required fuel quantity. NOTE: Center tank fuel may be substituted for payload in any quantity up to the maximum allowable payload* or to the center wing tank capacity, whichever is lower, provided the difference in effect on balance is also accounted for. NOTE: Tanks selected for fuel may be loaded simultaneously. *Maximum Zero Fuel Weight less airplane basic operating weight. B. Fuel Usage Limitations Use tank to engine combination during all takeoffs and landings, except as noted under Minimum Fuel Go-Around. (See Airplane Flight Manual) Center tank fuel in excess of any included in the Zero Fuel Weight must be used after a minimum of 5,000 lb. up to a maximum of 10,000 lb. (total) of main tank fuel has been expended for takeoff and climb to altitude. Do not initiate the transfer of reserve tank fuel until the fuel quantity in each outboard main tank is less than 12,000 lb. II. Model 707-100B Long Body and 707-100B Short Body : To preserve favorable wing bending moments, the following limitations shall apply: All center section fuel in excess of any included in the effective structural design zero fuel weight must be used before the transfer of outboard fuel. The airplane gross weight must not exceed 243,000 lb. if the reserve tanks are empty. A. Fuel Loading Limitations 1. (Applicable to 707-100B Short Body; 707-131B; 707-121B; and 707-139B) Load center tank fuel to 10,000 lb. This limitation is applicable only when the total fuel load is less than 80,000 lb. and the reserve tanks are loaded and the zero fuel weight C.G. is aft of 27% MAC. 2. Load Main tanks 1, 2, 3, and 4 equally. 3. If main tanks are full, load reserve tanks. 4. If all main and reserve tanks are full and additional fuel is required, load center tank to required fuel quantity. 17 4A21 NOTE: Center tank may be substituted for payload in any quantity up to the maximum allowable payload* and 10,000 lb. or to the center wing tank capacity, whichever is lower, provided the difference in effect on balance is also accounted for. When the takeoff C.G. is expected to be in the aft takeoff restricted zone, load up to 15,000 lbs. of center tank fuel before loading main tanks to achieve a more forward C.G. NOTE: Tanks selected for fuel may be loaded simultaneously. *Maximum Zero Fuel Weight less airplane basic operating weight. B. Fuel Usage Limitations Use tank to engine combination during all takeoffs and landings, except as noted under Minimum Fuel Go-Around. (See Airplane Flight Manual) Center tank fuel in excess of any included in the effective structural design zero fuel weight must be used after a minimum of 5,000 lb. up to a maximum of 10,000 lb. (total) of main tank fuel has been expended for takeoff and climb to altitude. Do not initiate the transfer of reserve tank fuel until the fuel quantity in each outboard main tank is less than 12,000 lb. Fuel reserves must be retained in main tanks only. (e) Fuel Dumping Undumpable Fuel For Model 707-100 Long Body and Short Body: 2 outboard main tanks 907 gal. 2 inboard main tanks 640 gal. Center wing tank 160 gal. TOTAL 1707 gal. For Model 707-200 & 707-100B Short Body: 2 outboard main tanks 845 gal. 2 inboard main tanks 986 gal. Center wing tank 141 gal. TOTAL 1972 gal. For Model 707-100B Long Body: 2 outboard main tanks 903 gal. 2 inboard main tanks 1012 gal. Center wing tank 141 gal. TOTAL 2056 gal. NOTE 2. Reserved NOTE 3. Replacement Brake Lining must meet Boeing Specification D10-3072, "Specification for Wheel and Brake Assembly". NOTE 4. Aft of Fuselage Station 850, the airplane design vertical load factors exceed TSO C-39 specifications; therefore, replacement passenger seats aft of Fuselage Station 850 must be evaluated for compliance with 4b.358(c). NOTE 5. For Model 707-200 only: It is permissible to interchange the JT4A-3, -5, -9, and -10 engines in any combination, see appropriate FAA Approved Airplane Flight Manual for limitations. NOTE 6. Whenever fuel is loaded into the center section fuel tanks, drain the sump of water prior to flight. 4A21 18 NOTE 7. (a) and (b) below apply to Model 707-200 only; (c) applies to Model 707-100 Long Body: (a) The oil tank capacity (8.3 gal.) as required per CAR 4b.440(b), is based on a maximum engine oil consumption of 0.4 gal. per hour. Any increase in engine oil consumption above this rate will reduce the operating range of the airplane. (b) Using the Bullseye or Sight Gage as a level for servicing the oil tank will result in a lesser oil quantity and will reduce the operating range of the airplane. (c) The takeoff thrust rating for this engine may be increased to 13,500 lb. when Boeing Service Bulletin No. 538 has been complied with and the appropriate Airplane Flight Manual information is provided. NOTE 8. The Model 707-100 Long Body, 707-100B Long Body and 707-200 airplanes must use 24-ply main landing gear tires when operated at weights of 255,000 lb. and above. NOTE 9. Special fatigue or retirement considerations applicable to the Model 707-100B Long Body and 707-100B Short Body aircraft: (a) The turbo compressor duct must be inspected, maintained and/or retired in accordance with Boeing Service Bulletin No. 1221 dated February 23, 1961, or later FAA approved revisions. NOTE 10. The Models 707-100B Long Body and 707-100B Short Body may intermix the following engines in combinations and with the appropriate limitations noted in the FAA Approved Airplane Flight Manual: JT3D-1, JT3D-1MC6, JT3D-1MC7, JT3D-3, and JT3D-3B NOTE 11. Provisions have been made for installation of ballast on the version 707-123B (not to exceed 1460 lb.) per Boeing Dwg. 65-19695. NOTE 12. JP-1, JP-4 and JP-5 fuels conforming to P&WA Specification No. 522 and later revisions may be used separately or mixed in any proportions without adversely affecting the engine operation or power output. No fuel control adjustment is required when switching fuel types. Phillips anti-icing fuel additive PFA-55MB (MIL-I-27686 USAF) may be used if concentration delivered to airplane does not exceed 0.1% by volume. No fuel system anti-icing credit is allowed. Anti-static fuel additive (Shell ASA-3) may be mixed with the fuel (recommended quantity 0.5 to 1.0 ppm) provided the effective conductivity of the mixture does not exceed 300 picomhos per meter. NOTE 13. Model 707-227 airplane has been approved for operation with P & W JT4A-9/-10 engines at JT4A-9/-10 engine thrust settings and ratings, Appendix I (La Paz, Bolivia) and Supplement IV to the FAA Approved Airplane Flight Manual, D6-1567. NOTE 14. Model 707-131 may operate at the weights shown for the 707-124 providing NOTE 8 (24 ply tires) and Boeing Service Bulletin 538 (JF3C-6 engine thrust increase) have been incorporated as stipulated in the 707-131 Flight Manual Supplement. .....END..... ``` ## ADs (190, first 50, 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 2026-13-15](https://openairdocs.org/ad/2026-13-15): Navigation · Boeing 707-100 Long Body, 707-200, 707-100B Long Body and 74 more. Effective Jul 1, 2026 - [AD 2023-12-15](https://openairdocs.org/ad/2023-12-15): Navigation · Boeing 707-100 Long Body, 707-200, 707-100B Long Body and 74 more. 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Effective Dec 13, 2002 - [AD 2002-02-02](https://openairdocs.org/ad/2002-02-02): Support Structure for the Main Landing Gear (MLG) Uplock Mechanism · Boeing 707-100 Long Body, 707-100B Long Body, 707-100B Short Body and 7 more. Effective Mar 11, 2002 - [AD 2001-22-14](https://openairdocs.org/ad/2001-22-14): Fire Extinguishing System Bottle Cartridges · Airbus A300 B2-1A, A300 B2-1C, A300 B2-203 and 105 more. Effective Dec 10, 2001 - [AD 2001-03-13](https://openairdocs.org/ad/2001-03-13): Wing - Upper Skin Cracking · Boeing 707-100 Long Body, 707-100B Long Body, 707-100B Short Body and 5 more. Effective Mar 22, 2001 - [AD 2000-24-06](https://openairdocs.org/ad/2000-24-06): Main Cargo Door Skin and Frame · Boeing 707-100 Long Body, 707-100B Long Body, 707-100B Short Body and 7 more. Effective Jan 8, 2001 - [AD 2000-24-20](https://openairdocs.org/ad/2000-24-20): Lower Skin Wings · Boeing 707-100 Long Body, 707-100B Long Body, 707-100B Short Body and 7 more. Effective Jan 8, 2001 - [AD 99-23-22 R2](https://openairdocs.org/ad/99-23-22-R2): Transponders · Airbus A300 B2-1A, A300 B2-1C, A300 B2-203 and 74 more. Effective Apr 20, 2000 - [AD 99-04-10](https://openairdocs.org/ad/99-04-10): Fluorescent Light Ballasts · Boeing 707-100 Long Body, 707-100B Long Body, 707-100B Short Body and 49 more. Effective Mar 18, 1999 - [AD 97-04-04](https://openairdocs.org/ad/97-04-04): Auxiliary Power Units · Airbus BAC 1-11 200 Series, BAC 1-11 400 Series, Auxiliary Power Units and 54 more. Effective Mar 24, 1997 - [AD 96-25-12](https://openairdocs.org/ad/96-25-12): Auxiliary Power Units · BAE Systems HS 748 Series 2A, HS 748 Series 2B, 707-100 Long Body and 74 more. Effective Jan 13, 1997 - [AD 95-17-01](https://openairdocs.org/ad/95-17-01): Upper Center Section Cracks · Boeing 707-100 Long Body, 707-100B Long Body, 707-100B Short Body and 7 more. Effective Sep 13, 1995 All 190: https://openairdocs.org/tcds/4A21/ads.md ## Registered aircraft by registry model (OpenAirDocs) - [Boeing 707-138B](https://openairdocs.org/model/boeing-707-138b): 1 aircraft (registry code 138360T) - [Boeing 707-121](https://openairdocs.org/model/boeing-707-121): 0 aircraft (registry code 138360C) - [Boeing 707-123](https://openairdocs.org/model/boeing-707-123): 0 aircraft (registry code 138360F) - [Boeing 707-123B](https://openairdocs.org/model/boeing-707-123b): 0 aircraft (registry code 138360H) - [Boeing 707-124](https://openairdocs.org/model/boeing-707-124): 0 aircraft (registry code 138360I) - [Boeing 707-131](https://openairdocs.org/model/boeing-707-131): 0 aircraft (registry code 138360N) - [Boeing 707-131B](https://openairdocs.org/model/boeing-707-131b): 0 aircraft (registry code 138360P) - [Boeing 707-139](https://openairdocs.org/model/boeing-707-139): 0 aircraft (registry code 13836OV) - [Boeing 707-227](https://openairdocs.org/model/boeing-707-227): 0 aircraft (registry code 138361G) ## STCs approved under this data sheet (238, first 50) - [STC ST00885LA](https://openairdocs.org/stc/ST00885LA): Installation of fire extinguisher cartridges as replacements for Pacific Scientific fire extinguisher cartridges in fire extinguisher bottles.. AMETEK AMERON, LLC d/b/a MASS Systems - [STC ST04222AT](https://openairdocs.org/stc/ST04222AT): Installation of a Fuel System Modification. Omega Air Inc. - [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 SA2579WE](https://openairdocs.org/stc/SA2579WE): Modify installation of wing tip mounted emblem light. The Boeing Company - [STC SA3927NM](https://openairdocs.org/stc/SA3927NM): Installation of floor proximity emergency escape path marking system.. Bruce Aerospace Inc. - [STC ST00098IB](https://openairdocs.org/stc/ST00098IB): Introduction of ADS-B Out. STC Twenty One Limited - [STC SA2534SW-D](https://openairdocs.org/stc/SA2534SW-D): Replacement of Switch assembly Int'l Inflatables Co. P/N 68748, with DME Corp. P/N L-140 in emergency evacuation slide lighting system.. Astronics Luminescent Systems Inc - [STC SA2539SW-D](https://openairdocs.org/stc/SA2539SW-D): Replacement of light assembly, International Inflatables Co. P/N68555-1 with DME Corp. EL-104, EL-104A, and EL-104B in emergency slide lighting system.. Astronics Luminescent Systems Inc - [STC SA863EA](https://openairdocs.org/stc/SA863EA): Incorporation of DME Corporation emergency evacuation slide lighting system. Astronics Luminescent Systems Inc - [STC ST04177AT](https://openairdocs.org/stc/ST04177AT): Installation of a Talon Aerospace LED Replacement General Purpose Lamps. Aaxico Technical Services Inc. - [STC ST09020SC](https://openairdocs.org/stc/ST09020SC): Installation of a C&X band fuselage nose radome shell.. The NORDAM Group LLC - [STC SA1006NW](https://openairdocs.org/stc/SA1006NW): Installation of Avionics and Flight Instruments. Aviation Technical Services - [STC SA948NW](https://openairdocs.org/stc/SA948NW): Installation of zero passenger, zero cargo configuration. Aviation Technical Services - [STC ST04229NY](https://openairdocs.org/stc/ST04229NY): Introduction of a 16G New Generation Stretcher XL P/N 1120030-Series. Bucher Leichtbau AG - [STC SA4063SW](https://openairdocs.org/stc/SA4063SW): Installation of interior arrangement. Associated Air Center, Inc. - c/o CT Corporation System - [STC SA3186SO](https://openairdocs.org/stc/SA3186SO): Installation of a replacement coalescer filter, Greentree Aerotech, Inc. (GAI) P/N 22D10-1.. Purolator Facet, Inc - [STC SA7076NM](https://openairdocs.org/stc/SA7076NM): Installation of Stretcher Carrier.. Air Medic LLC - [STC SA8702SW](https://openairdocs.org/stc/SA8702SW): Installation of triple Canadian Marconi CMA-771 MK-IV Omega/ Global positioning system.. LB Aircraft Engineering Inc - [STC ST00682WI-D](https://openairdocs.org/stc/ST00682WI-D): Modification of Collins VHF-20/VHF-20A/VHF-20B VHF COMM Receiver Transmitter with CTL-20 Control Pro Line I System Installation to a Collins VHF-22C/VHF-22D VHF COMM Receiver Transmitter with CTL-22C Control 8.33 kHz Pro Line II System Installation in accordance with Collins Installation Instructions as listed on AML No. ST00682WI-D, Revision -, or later FAA approved revisions.. Rockwell Collins Inc - [STC SA781SO](https://openairdocs.org/stc/SA781SO): Installation of a cargo loading door. (707-227). Pemco Aeroplex Inc - [STC ST02540AT-D](https://openairdocs.org/stc/ST02540AT-D): Installation of replacement fuel tank sealant system. FFC Manufacturing - [STC SA1076NE](https://openairdocs.org/stc/SA1076NE): Installation of Aerofex livestock carrier P/N TS-QA-400 platform and panel system using size A or size M Class II pallet.. Equine Air Transport Systems LLC - [STC SA3257WE](https://openairdocs.org/stc/SA3257WE): Installation of AiResearch GTCP85-98CK auxiliary power unit in forward cargo compartment. (707-123B, -138B). Airweld Inc. - [STC SA3441WE](https://openairdocs.org/stc/SA3441WE): Installation of airstairs. (707-138B and 707-123B). Airweld Inc. - [STC SA1176WE](https://openairdocs.org/stc/SA1176WE): Interior arrangements.. Flying Tiger Line Inc - [STC SA1229WE](https://openairdocs.org/stc/SA1229WE): United Data Control V557 cockpit voice recorder.. Flying Tiger Line Inc - [STC SA1079GL](https://openairdocs.org/stc/SA1079GL): Installation of Grimes Floor proximity lighting system P/N 10-1309-67.. Honeywell International Inc. - [STC ST02388NY](https://openairdocs.org/stc/ST02388NY): Installation of Automated Flight Information Reporting System (AFIRS) 220 with Optional Global Voice and Global Text Satellite Communications. AeroMechanical Services Ltd - [STC SA1308NM](https://openairdocs.org/stc/SA1308NM): Installation of auxiliary fuel tanks in the forward, mid, and aft cargo compartments.. Rogerson ATS - [STC SA4053WE](https://openairdocs.org/stc/SA4053WE): Installation of an auxiliary fuel tank system consiting of two identical tank assemblies located in the forward cargo compartment and one located in the aft cargo compartment. (707-123B). Rogerson ATS - [STC ST01443SE](https://openairdocs.org/stc/ST01443SE): ONE-ONLY STC (S/N 18740): Non-group aircraft approval for Reduced Vertical Separation Minimum. AeroMech Incorporated - [STC SA1132EA](https://openairdocs.org/stc/SA1132EA): Installation of two Solar Model T-62T-40C2 APU's for ground use only. (707-138B). PATS Aircraft LLC - [STC SA5971NM](https://openairdocs.org/stc/SA5971NM): Installation of flame reistant cargo covers.. Air Transport International LLC. - [STC ST00956LA](https://openairdocs.org/stc/ST00956LA): Installation of Burbank frangible stop flap guard at 30 degrees maximum approach flap position.. Topeka Management, Inc. - [STC ST655SO](https://openairdocs.org/stc/ST655SO): Installation of Mace Galley Model No. 101 in aft passenger compartment and Mace Galley Model No. 102 in forward passenger compartment. (707-121B). Installation is to be made on left side of the aircraft only. No installation is to be made forward of station 380 on 707-121B aircraft 1-99.. B/E Aerospace - [STC SA2988SW](https://openairdocs.org/stc/SA2988SW): Interior modification: Installation of an executive interior and odification of flight avionics system. Exterior modification: Add two ADF Loop Antennas, FS 420 and 460, one transponder antenna, 237Z1, FS 410, one at AT-460 VHF antenna and one TAT probe. L-3 Communications Integrated Systems LP - [STC SA5050SW-D](https://openairdocs.org/stc/SA5050SW-D): Modification of existing gravity flow water system in order to convert to a pressurized system and the installation of floor pans at entrance doors. L-3 Communications Integrated Systems LP - [STC SA8086SW-D](https://openairdocs.org/stc/SA8086SW-D): Installation of a folding cargo bay ladder.. L-3 Communications Integrated Systems LP - [STC SA8087SW-D](https://openairdocs.org/stc/SA8087SW-D): Installation of forward attendant seat/shoulder harness.. L-3 Communications Integrated Systems LP - [STC SA8088SW-D](https://openairdocs.org/stc/SA8088SW-D): Installation of an emergency locator transmitter (ELT) system.. L-3 Communications Integrated Systems LP - [STC SA9167SC-D](https://openairdocs.org/stc/SA9167SC-D): Updated Mission Communications System consisting of a 5 channel International Maritime Satellite(INMARSAT) system, LST-5E UHF SATCOM, secure voice or data capabilities and facsimile/printer. (707-153B). L-3 Communications Integrated Systems LP - [STC SA1889SW](https://openairdocs.org/stc/SA1889SW): Installation of Xerox duplicating machine Model 2600. L-3 Communications Integrated Systems LP - [STC SA1136EA](https://openairdocs.org/stc/SA1136EA): Installation of an onboard-folding passenger loading stairs. (model 707-138B). Patrick Aircraft Products Inc. - [STC ST660SO](https://openairdocs.org/stc/ST660SO): Installation of Radome.. Saint-Gobain Performance Plastics Corp - [STC ST02094AT](https://openairdocs.org/stc/ST02094AT): Design of cabin window plug.. Neill Aircraft Company - [STC SA1263SW](https://openairdocs.org/stc/SA1263SW): Installation of AN/ARC-146 Satellite Communication Terminal.. Rockwell Collins Inc - [STC SA1264SW](https://openairdocs.org/stc/SA1264SW): Installation of Collins 837D-2 and 837K-1 antennas.. Rockwell Collins Inc - [STC SA1699WE](https://openairdocs.org/stc/SA1699WE): Installation of Dual Collins FD-109M flight director systems and Dual Collins DF-203 ADF systems.. Rockwell Collins Inc - [STC SA4000SW](https://openairdocs.org/stc/SA4000SW): Installation of dual Carousel IVA INS System.. Sierra Industries, Inc - [STC SA4010SW](https://openairdocs.org/stc/SA4010SW): Installation of Subfloor seat mounting structure. Sierra Industries, Inc All 238: https://openairdocs.org/tcds/4A21/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.