TCDS 4A26

Page No. 1 2 3 4 5 6 7 8 9 10 11 12 13 14 15 16 17 18 19 20 21 Rev No. 11 10 11 10 10 10 10 11 11 11 11 10 10 10 10 10 10 11 11 11 11 Reformatted 12/93. DEPARTMENT OF TRANSPORATION FEDERAL AVIATION ADMINISTRATION 4A26 Revision 11 BOEING 707-300 Series 707-400 Series 707-300B Series 707-300C Series July 30, 1984 TYPE CERTIFICATE DATA SHEET NO. 4A26 This data sheet which is a part of type certificate No. 4A26 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 Renton, Washington I - Model 707-300 Series (Transport aircraft), Approved July 15, 1959 Model Serial Nos. Eligible 707-321 17592 thru 17608, 18083 thru 18085 707-328 17613 thru 17622, 17918 thru 17924, 18245 thru 18247, 18375 707-329 17623 thru 17627, 18374, 18460 707-331 17673 thru 17690 707-344 17928, 17929, 17930 Engines 4 Pratt and Whitney Turbojet JT4A-9, -1, -11, -12 (See NOTE 9 for interchangeable engine combinations.) Fuel See NOTE 10. Engine limits JT4A-9, -10 JT4A-11, -12 Takeoff static thrust, standard day, sea level conditions (5 min.) lb. 16,800 17,500 Maximum continuous static thrust, standard day, sea level conditions, lb. 13,500 14,900 Maximum permissible engine rotors operating speeds: Low pressure compressor (N1), r.p.m. 7,060 7,160 High pressure compressor (N2), r.p.m. 9,135 9,355 Maximum permissible turbine outlet gas temperatures: Takeoff (5 min.) (635°C) 1175°F (655°C) 1211°F Maximum continuous (516°C) 960°F (560°C) 1040°F Maximum for acceleration (2 min.) (635°C) 1175°F (655°C) 1211°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 oil inlet temperature (121°C) 250°F (121°C) 250°F 4A26 Page 2 Maximum permissible air bleed extractions of total JT4A-9, -10 JT4A-11, -12 engine air flow: High pressure compressor From idle to maximum continuous 5.5% 5.5% Takeoff 1.5% 1.5% Low pressure compressor From idle to maximum continuous 2.00% 2.00% Takeoff 1.65% 1.65% Maximum permissible mechanical extraction 150 hp. 150 hp. Thrust Setting: The appropriate thrust setting curve, (EPR or Pt7), in the Airplane Flight Manual must be used for control of engine thrust. Airspeed limits (AIS) Vmo (Maximum Operating) MPH KTS at Sea Level 390 339 at 5,000 ft. 396 344 at 10,000 ft. 404 351 at 15,000 ft. 413 359 at 20,000 ft. 425 369 at 24,900 ft. 435 378 Mmo (Maximum Operating) at 25,000 ft. and above (M = 0.887) Va (Maneuvering) MPH KTS at sea level 287 249 at 20,000 ft. 299 260 at 37,700 ft. 331 287 Straight line variation between points shown. Ma (Maneuvering) at 37,700 ft. and above (M - 0.887) Vfe (Flaps Extended) Maximum Flap Defection MPH KTS (Flaps not to be 10° 265 230 extended above 20° 252 218 20,000 ft.) 30° 238 207 50° 209 181 Vlo (Landing Gear Operating) at sea level to 30,000 ft. 310 269 at 30,000 ft. to 35,000 ft. 322 280 Mlo (Landing Gear Operating at 35,000 ft. and above (M = 0.825) Vle (Landing Gear Extended) at sea level to 30,000 ft. 367 319 Mle (Landing Gear Extended) at 30,000 ft. and above (M = 0.825) Vdco (Dump Chute Operation) at sea level to 42,000 ft. 275 239 Vdce (Dump Chute Extended) at sea level to 36,000 316 274 Mdce (Dump Chute Extended) at 36,000 ft. and above (M = 0.825) 4A26 Page 3 Vmca (Air Minimum Control Speed) (Sea Level + 15°C) MPH KTS JT4A-11, -12 T.O. Thrust 135 117 JT4A-9, -10 T.O. Thrust 132 115 JT4A-11, -12 Limited Thrust 132 115 Mmcg (Ground Minimum Control Speed) (Sea Level + 15°C) MPH KTS JT4A-11, -12 T.O. Thrust 131 114 JT4A-9, -10 T.O. Thrust 128 111 JT4A-11, -12 Limited Thrust 128 111 C.G. range The nose gear retraction moment is 22,500 in.lb. and moves C.G. forward. The main gear (Landing Gear Extended) retracts parallel to the wing reference axis; hence, has no effect on the airplane longitudinal C.G. 3 1 0 2 9 0 2 7 0 2 5 0 2 3 0 2 1 0 1 9 0 1 7 0 1 5 0 1 6 . 0 1 7 . 5 1 9 .0 2 1 .0 2 3 .0 3 5 . 03 3 . 03 1 .02 9 .02 7 .02 5 .0 C . G. % M A C 7 0 7 -3 0 0 and 7 0 7 -4 0 0 C . G . D iagram T ak eo f f Lim it O n ly En v elo p e Ex t en s io n f o r 7 0 7 -4 0 0 an d 7 0 7 -3 0 0 Series airc raf t eq u ip p ed w it h s t ren g t h lan d in g g ear (See N o t e 8 ). Maximum weights -300 Series with -300 & -400 Restricted Landing -300 & -400 Series with Heavy Gear & Gear (See NOTE 8) with Heavy Gear 7 Cell Center Tank Maximum ramp weight 302,000 lb. 316,000 lb. 316,000 lb. Maximum flight weight with 30° flaps 301,000 lb. 311,000 lb.* 316,000 lb.** Maximum flight weight flaps up 300,000 lb. 310,000 lb. 310,000 lb.* 316,000 lb.** Maximum flight weight at which the outboard auxiliary fuel tanks can be empty 275,000 lb. 275,000 lb. 275,000 lb. Maximum landing weight 198,500 lb. 207,500 lb. 207,500 lb. Maximum zero fuel weight 190,000 lb. 190,000 lb. 190,000 lb. * Basic fuel management ** Alternate fuel management 4A26 Page 4 Minimum crew For any flight, 3 persons (Pilot, Copilot, Flight Engineer). When in the mixed passenger/cargo configuration one flight attendant is required in the passenger compartment. Maximum passengers 179 limited by emergency exit requirements. Approved for 189 passengers if equipped with four (4) inflatable escape chutes installed in accordance with FAA approved type design data. (Review case no. 5 dated July 17, 1963.) Maximum baggage Maximum Maximum Moment Body Load Concentration Capacity Arm Compt. Station lb./in. p.s.f. lb. inches Fwd. Belly 400-600B + 18 48 150 14300 + 389 Aft Belly 960-1060 50 150 7000 +1030 Aft Belly 1060-1200 35 150 4900 +1170 Aft Belly 1200-1300 20 150 2000 +1290 Fuel capacity (See NOTE 1(c) for information relative to unusable fuel; NOTE 1(e) for required fuel usage procedure; NOTE 1(f) for undumpable fuel.) The maximum fuel capacity listed below must not be exceeded. For numbers in parentheses, see NOTE 16. For other fuel C.G. locations with partially filled tanks, see appropriate Boeing Weight and Balance Manuals listed under NOTE 14. Nominal Capacity Maximum Capacity Usable fuel in tank (See NOTE 17) Moment Arm Tank U.S. Gal. per Tank Pounds/Tank Inches No. 1 & No. 4 Reserve 439 3,029 1101.7 No. 1 & No. 4 Main 2,307 15,918 933.4 (2,323) (16,029) (934.6) No. 2 or No. 3 Main 4,065 28,049 788.4 (4,069) (28,076) (788.4) 7-Cell Center 10,193 70,332 706.9 4-Cell Center (707-300 Series and 707-437 only; See NOTE 13) 7,640 52,716 728.6 TOTAL 7-Cell center 23,815 164,324 (23,855) (164,600) TOTAL 4-Cell center 21,262 146,984 Whenever fuel is loaded into the center section fuel tank, drain the sump of water prior to flight. 4A26 Page 5 Oil capacity Tank Total Total Moment Arm Gal. Lb. In. No. 1 tank 8.3 64.0 886 * (a) The oil tank capacity Oil Cooler .4 3.2 862 (8.3 gal.) as required per Engine 1.5 11.0 898 CAR 4b.440(b) is based on a Oil lines 1.4 10.0 871 maximum engine oil consumption of 0.4 gal. per hr. Any increase No. 2 tank 8.3 64.0 702 in engine oil consumption above Oil cooler .4 3.2 678 this rate will reduce the operating Engine 1.5 11.0 714 range of the airplane. Oil lines 1.4 10.0 688 No. 3 tank 8.3 64.0 702 * (b) Using the bullseye or sight Oil cooler .4 3.2 678 glass as a level for servicing Engine 1.5 11.0 714 the oil tank will result in a Oil lines 1.4 10.0 688 lesser oil quantity and will reduce the operating range of the No. 4 tank 8.3 64.0 886 airplane. Oil cooler .4 3.2 862 Engine 1.5 11.0 898 Oil lines 1.4 10.0 871 Total 46.4 352.8 Required equipment The basic required equipment as prescribed in the applicable airworthiness regulations (see Certification Basis) must be installed in the aircraft for certification. The appropriate Weight and Balance Manuals in NOTE 14 contain lists of equipment as well as optional equipment installations approved by the FAA. II - Model 707-400 Series (Transport Aircraft), approved February 12, 1960 Model Serial Nos. Eligible 707-430 17718, 17719, 17720, 17721, 18056 707-436 17703-17717, 18411-18413 707-437 17722-17724, 18055, 18414, 18415 707-441 17905, 17906, 18694 707-458 18070, 18071, 18357 707-465 18372, 18373 Engines 4 Rolls Royce Turbojet Conway Mark 508 (R.CO-12) Fuel Fuel designation: British DERD 2482, 2486, 2494 American JP-1 (U.S. MIL-F-5616) JP-4 (U.S. MIL-F-5624C) Canadian 3-CP-23D, 3-CP-228 Engine limits Takeoff static thrust, standard day, sea level conditions (5 min.), lb. 17,500 Maximum continuous static thrust, standard day, sea level conditions lb. 14,625 Maximum permissible engine rotors operating speeds: Low pressure compressor (N1), r.p.m. 7,560 High pressure compressor (N1), r.p.m. 10,500 4A26 Page 6 Maximum permissible turbine outlet gas temperatures: Takeoff (5 min.) (675°C) 1247°F Maximum continuous (600°C) 1112°F Starting maximum gas temperature (675°C) 1247°F Maximum with reverse thrust selection (675°C) 1247°F Maximum permissible oil inlet temperature (105°C) 221°F Maximum permissible air bleed delivery for engine and aircraft services at sea level conditions as percent of no bleed low pressure compressor mass flow: Takeoff rpm High pressure compressor bleed 5.6% Low pressure compressor bleed 1.1% Maximum continuous rpm High pressure compressor bleed 5.8% Airspeed limits 707-400 series aircraft Vmo Airspeed Limits are identical to those listed in the applicable section Part I of this Data Sheet except the 707-436 and 707-465 Vmo limit at 23,300 feet is 430 mph (375 kts) and the Mmo limit is .852 at 23,300 feet and above. 707-400 series aircraft, Va, Ma, Vfe, Vlo, Mlo, Vle, Mle, Dump Chute Extended and Dump Chute Operation Airspeed Limits are identical to those listed in the applicable section, PART 1, of this Data Sheet. Vmca (Air Minimum Control Speed) MPH KTS (Sea Level and 15°C) 139 121 Vmcg (Ground Minimum Control Speed) 145 126 C.G. range The 707-400 series aircraft C.G. Range and Landing gear retraction moment are (Landing gear extended) shown in applicable Section, PART I, of this Data Sheet. Maximum weights 707-400 series aircraft Maximum Weights are shown in the applicable section, PART I, of this Data Sheet. Minimum crew For any flight, 3 persons (pilot, copilot, flight engineer) Maximum passengers 179 limited by emergency exit requirements. Approved 189 passengers if equipped with four (4) inflatable escape chutes installed in accordance with FAA approved type design data. Maximum baggage 707-400 series aircraft Maximum Baggage is identical to that shown in the applicable section, PART I, of this Data Sheet. Fuel capacity 707-400 series aircraft Fuel Capacity is shown in the applicable Section, PART I, of this Data Sheet. 4A26 Page 7 Oil capacity Moment Arms Tank gal. lb. inches No. 1 Oil in engine tank 3.79 29.15 853.6 Oil in C.S.D. tank 1.43 11.00 853.6 *Oil in system 1.44 11.07 896.4 *Oil in system includes oil in engine, oil cooler, constant No. 2 speed drive and lines. The Oil in engine tank 3.79 29.15 670.4 oil tank capacity (14.45 imp. Oil in C.S.D. tank 1.43 11.00 670.4 pints) as required per CAR 4b.440(b) is based on a maximum Oil in system 1.44 11.07 712.6 engine oil consumption of 0.9 pint per hour. Any increase in No. 3 engine oil consumption above Oil in engine tank 3.71 28.53 670.4 this rate will reduce the Oil in C.S.D. tank 1.48 11.38 670.4 operating range of the airplane. Oil in system 1.44 11.07 712.6 No. 4 Oil in engine tank 3.71 28.53 853.6 Oil in C.S.D. tank 1.48 11.38 853.6 Oil in system 1.44 11.07 896.4 TOTAL 26.58 204.40 Required equipment The basic required equipment as prescribed in the applicable Airworthiness Regulations (See Certification Basis) must be installed in the aircraft for certification. Appropriate Weight and Balance Manuals in NOTE 14 contain lists of equipment as well as optional equipment installations approved by the FAA. III 707-300B Series (Transport Aircraft) approved May 31, 1962 Model 707-312B 19737-19739 707-321B 18335-18339, 18838-18842, 18956-18960, 19264-19266, 19275-19278, 19361-19366, 19374, 19376, 19378, 19693-19699, 20019-20034 707-323B 20170-20179 707-328B 18456-18459, 18685-18686, 18941, 19291 707-330B 18462, 18463, 18819, 18923, 18826-18831, 19315-19316 707-331B 18405-18409, 18764, 18913-18918, 18978-18985, 19224-19227, 19570-19573, 20058-20067 707-336B 20456, 20457 707-337B 18708, 18873, 19247 707-344B 18891, 19133 707-351B 18584-18586, 18693, 18710, 19633-19636 707-353B 18461, 20630 707-358B 19004, 19502, 20097 707-359B 19741, 20340 707-382B 18961, 18962, 19740, 19969, 20136, 20297, 20298 707-384B 20035, 20036 707-387B 19238-19241 707-3J6B 20714-20716 707-3L6B 21049 Engines 4 Pratt & Whitney Turbofan JT3D-3, -3B, -7, * or JT3D-1, -1MC6 and -1MC7 (See NOTE 9 for Interchangeable engine combinations.) * (300C only) Fuel See NOTE 10 4A26 Page 8 Engine limits JT3D-1; Takeoff static net thrust (Std. day), -1MC6: -1MC7 JT3D-3 JT3D-3B JT3D-7 lb., at sea level, dry (5 minutes) 17,000 18,000 18,000 19,000 Take off wet (2 1/2 minutes) 17,000 18,000 18,000 19,000 Maximum continuous static thrust (Std. day), lb., at sea level 14,500 16,400 16,400 17,200 Maximum permissible engine rotors operating speeds: Low pressure compressor (N1), r.p.m. 6,800 6,800 6,850 6,850 High pressure compressor (N2), r.p.m. 10,200 10,250 10,250 10,250 Maximum EPR values shown in the airplane flight manual shall not be exceeded. Maximum permissible turbine outlet gas temperatures: JT3D-1; -1MC6; -1MC7 JT3D-3; -3B JT3D-7 Takeoff (5 minutes) (530°C) 986°F (555°C) 1031°F) (575°C) 1067°F Maximum continuous (460°C) 860°F (490°C) 914°F) (510°C) 950°F Maximum for acceleration (2 minutes) (530°C) 986°F (555°C) 1031°F) (575°C) 1067°F Starting (450°C) 842°F (450°C) 842°F) (450°C) 842°F Maximum permissible air bleed extractions of total engine air flow: Typical High pressure compressor From idle to maximum continuous 5.5% At takeoff 2.0% Low pressure compressor From idle to maximum continuous 2.0% At takeoff 2.2% Maximum permissible oil inlet temperature: Typical Continuous operation (132°C) 270°F Ten minutes operation (143°C) 290°F Airspeed limits (IAS) Vmo (Maximum Operating) MPH KTS at sea level 432 375 at 10,000 ft. 439 381 at 15,000 ft. 443 385 at 20,000 ft. 449 390 at 23,000 ft. 454 394 Mmo (Maximum Operating) at 23,000 ft. and above (M = 0.887) Va (Maneuvering) MPH KTS at sea level 311 270 at 10,000 ft. 319 277 at 20,000 ft. 329 286 at 30,000 ft. 346 300 at 35,000 ft. 356 309 Straight line variation between points shown Ma (Maneuvering) at 35,000 ft. and above (M = 0.887) 4A26 Page 9 Vfe (Flaps Extended) Maximum Flap Deflection MPH KT MPH* KT (Flaps not to be 14° 260 226 242 210 extended above 17° 257 223 242 210 20,000 ft.) 25° 248 215 242 210 50° 225 195 225 195 *Aircraft without Boeing Service Bulletin No. 1826 installed Vlo (Landing Gear Operation) MPH KTS at sea level to 30,000 ft. 311 270 at 30,000 ft. and above 322 280 Mlo at 34,400 ft. and above (M - 0.830) Vle (Landing Gear Extended) 369 320 Mle (Landing Gear Extended) (M - 0.830) Vdco (Dump Chute Operation) 276 240 Mdco (Dump Chute Operation) (M = 0.830) Vdce (Dump Chute Extended) 317 275 Mdce (Dump Chute Extended) (M = 0.830) Landing Light Extended at sea level to 25,000 ft. 441 383 at 25,000 ft. and above (M = 0.887) Vmca (Air Minimum Control Speed) (Sea level + 15°C) JT3D-3, -3B AND -3B extended temperature 133 116 JT3D-38 Extended temperature and improved cowls 135 117.5 JT3D-7 139 121 Vmcg (Ground Minimum Control Speed) (Sea level = 15°C) JT3D-3 133 116 JT3D-3B, -3B extended temperature and -7 139 121 JT3D-3B Extended temperature and improved cowls 143 124 4A26 Page 10 C.G. range The nose gear retraction moment is 22,500 in.lb. and moves C.G. forward. The main gear retracts parallel to the wing reference axis; hence, has no effect on the airplane longitudinal C.G. 1 4 0 3 4 0 3 2 0 3 0 0 2 8 0 2 6 0 2 4 0 2 2 0 2 0 0 1 8 0 1 6 0 1 6 . 0 1 7 . 5 1 9 .0 2 1 .0 2 3 .0 3 5 . 03 3 . 03 1 .02 9 .02 7 .02 5 .0 7 0 7 -3 0 0 B In c reased Gro ss W eig h t an d 7 0 7 -3 5 1 B o n ly . Lan d in g W eig h t En v elo p e 7 0 7 -3 0 0 B In c reased G ro ss W eig h t w it h 7 0 7 -3 0 0 C M ain Lan d in g G ear In st alled . See N O T E 1 2 . C . G. % M A C 7 0 7 -3 5 1 B 7 0 7 -3 0 0 B In c reased Gro ss W eig h t w it h 7 0 7 -3 0 0 C M ain Lan d in g Gear in st alled . See N o t e 1 2 . 7 0 7 -3 0 0 B C . G. D iagram Maximum weights (For spare engine carry, see NOTE 18) Basic Increased Gross Increased Gross Weight Aircraft Weight Aircraft Aircraft (See NOTE 12) Maximum Taxi (Ramp) weight (lb) 328,000 328,000 336,000 *Maximum flight weight (lb) Flaps Down 327,000 328,000 335,000 Flaps Up 318,000 326,000 326,000 (322,000) (328,000) (331,000) With outboard reserve tanks empty 280,000 285,000 285,000 Maximum landing weight (lb.) 207,000 207,000 247,000 Structural design zero fuel 190,000 195,000 195,000 See NOTE 1(e) for necessary fuel management for flaps up flight at weights shown in parenthesis. *At sea level to 11,500 ft., maximum flight weight must be reduced at altitudes above 11,500 ft. at the rate of 1000 lb. per 3500 ft. Minimum crew For any flight, 3 persons (Pilot, Copilot, Flight Engineer) Maximum passengers 179 limited by emergency exit requirements. Approved for 189 if equipped with four (4) inflatable escape chutes installed in accordance with FAA approved type design data. Maximum baggage 707-300B Series aircraft maximum baggage is identical to that shown in the applicable section Part I of this Data Sheet. For Model 707-351B Main Deck Cargo Compartment Limitations, see Weight and Balance Document D6-10949.1. Fuel capacity See NOTE 1(c) for information relative to unusable fuel; NOTE 1(e) for required fuel usage procedure; NOTE 1(f) for undumpable fuel. The maximum fuel capacity listed below must not be exceeded. For other fuel C.G. locations with partially filled tanks, see appropriate Boeing Weight and Balance Manuals listed under NOTE 14. 4A26 Page 11 NOMINAL CAPACITY MAX. CAPACITY MOMENT Usable fuel in tank (7.1 lb/gal) ARM TANK U.S. Gallons Pounds Per Tank Per Tank Inches No. 1 or No. 4 Reserve 439 3,117 1,101.7 No. 1 or No. 4 Main 2,323 16,493 934.6 No. 2 or No. 3 Main 4,069 28,890 788.4 7-Cell Center 10,193 72,370 728.6 Total 23,855 169,370 Whenever fuel is loaded into the center section fuel tank, drain the sump of water prior to flight. Oil Tank capacity The system oil capacities are given in the appropriate Weight and Balance Control Manuals listed under NOTE 14. Engine Oil Volume Moment Arm Tank No. Location Gal. (In.) 1 Outboard Port 6.0 gal. 866.9 2 Inboard Port 6.0 gal. 684.1 3 Inboard Starboard 6.1 gal. 684.1 4 Outboard Starboard 6.1 gal. 866.9 Required equipment The basic required equipment as prescribed in the applicable airworthiness regulations (see Certification Basis) must be installed in the aircraft for certification. The appropriate Weight and Balance Manuals in NOTE 14 contain lists of all required equipment as well as optional equipment installations approved by the FAA. IV - Model 707-100C Series (Transport Aircraft), approved April 30, 1963 Model Serial Nos. 707-307C 19997-20000 707-309C 20261, 20262 707-311C 19789 707-320C 20008, 20275, 20487, 20488 707-321C 18579, 18580, 18591, 18714-18718, 18765-18767, 18790, 18824-18826, 19267-19274, 19367-19373, 19375, 19377, 19379, 20016-20018 707-323C 18689-18692, 18938-18940, 19235-19237, 19380-19384, 19515-19519, 19581-19589, 19574-19577, 20087-20089 707-324C 18886-18887, 19177, 19178, 19350-19353, 19869-19871 707-327C 19104-19108, 19440, 19529-19531 707-328C 18881, 19292, 19521, 19522-19524, 19916, 19917 707-329C 18890, 19162, 19211, 19990, 20198-20200 707-330C 18932, 18937, 19317, 20123, 20124, 20395 707-331C 18711-18713, 18756, 18757, 19213-19214, 19435, 19566, 19567, 20068, 20069 707-336C 18924, 18925, 19498, 19843, 20474, 20475, 20517 707-337C 19248, 19988 707-338C 18808-18810, 18953-18955, 19293-19297, 19621-19630 707-340C 19284-19286, 19866 707-341C 19320, 19321-19322 707-344C 19705, 19706, 20110, 20230, 20283 707-345C 19840-19842 707-347C 19963-19967, 20315-20319 707-348C 18737, 18880, 19001, 19410 707-349C 18975, 18976, 19354, 19355 707-351C 18746-18748, 18888, 18889, 18921, 18922, 18964, 19034, 19163, 19164, 19168, 19209-19211, 19263, 19412, 19434, 19443, 19631, 19632, 19773 - 19777 707-355C 19417, 19664, 19986 707-358C 20127, 20301 4A26 Page 12 707-360C 19736, 19820 707-365C 19416, 19590 707-366C 19844, 19845, 20341, 20342, 20760-20763, 20919, 20920 707-368C 19809, 19810, 21081, 21103, 21104, 21261, 21367, 21368 707-369C 20084-20086, 20546, 20547 707-370C 20889-20891 707-372C 20076, 20077 707-373C 18582, 18583, 18707, 18709, 18738, 18991, 19179, 19 441, 19442, 19715, 19716 707-379C 19821, 19822 707-384C 18948-18950, 19760 707-385C 19000, 19433, 20522 707-386C 20287, 20288, 20741, 21396 707-387C 19961, 19962 707-396C 20043 707-399C 19415, 19767 707-3B4C 20224, 20225, 20259, 20260 707-3D3C 20494, 20495 707-3F5C 20514, 20515 707-3F9C 20474, 20669, 21428 707-3H7C 20629 707-3J6C 20718-20723 707-3J8C 20897, 20898 707-3J9C 20830-20835, 21123-21129, 21475 707-3K1C 20803-20805, 21651 707-3L5C 21228 707-3L6C 21096 707-3M1C 21092 707-3P1C 21334 Engines: See Applicable Section in Part III of This Data Sheet. Fuel: See Applicable Section in Part III of This Data Sheet. Engine limits See Applicable Section in Part III of This Data Sheet. Airspeed limits See Applicable Section in Part III of This Data Sheet. C.G. range The nose gear retraction moment is 23,800 in./lb. and moves the C.G. forward. The main (Landing gear extended) gear retracts parallel to the wing reference axis and has no effect on the airplane longitudinal C.G. 3 4 0 3 2 0 3 0 0 2 8 0 2 6 0 2 4 0 2 2 0 2 0 0 1 8 0 1 6 . 0 1 7 .0 1 9 .0 2 1 .0 2 3 .0 3 5 . 03 3 . 03 1 .02 9 . 02 7 .02 5 .0 C . G. % M A C 7 0 7 -3 0 0 C C . G. D iagram T his f orw ard C. G. env elope m ay be used w hen c arg o is f orw ard o f St at io n 9 6 6 . Inc reased Gross W eig ht A irc raf t 4A26 Page 13 Cargo loaded on the main cargo deck may result in an asymmetrically loaded airplane; that is, more weight may be on the right hand side than on the left hand side of the airplane or vice versa. The asymmetrical moment (resulting from an off-loaded airplane) must not exceed 864,000 inch lbs. Maximum weights See NOTE 1(e) for necessary fuel management for flight with flaps up at weights shown in parentheses. For spare engine carry, see NOTE 18. Basic Increased Gross Model 707-338C Aircraft Weight Aircraft (See NOTE 15) Maximum Taxi Weight (lb) Passenger Configuration 328,000 336,000 336,000 Other Configurations 328,000 332,000 334,000 *Maximum flight weight (lb) Flaps Down 327,000 332,000 334,000 335,000 (Pax Config) Flaps Up Passenger Configuration 322,000 326,000 325,000 (331,600) (331,000) Other Configurations 322,000 325,000 325,000 (330,000) (331,000) Maximum Weight at which Outboard Auxiliary tank can be empty (lb.) 280,000 285,000 285,000 Maximum Landing Weight (lb.) 247,500 247,500 247,500 Zero Fuel Weight (lb.) 230,000 230,000 230,000 220,000 220,000 (Pax Config) (Pax Config) *At sea level to 11,500 ft., maximum flight weight must be reduced at altitudes above 11,500 ft. at the rate of 1000 lb. per 5000 ft. Minimum crew For any flight, three persons (Pilot, Copilot, Flight Engineer). Maximum passengers 195 limited by emergency exit requirements. 219 if compliance with FAR 25.2 is shown. See Note 19. 4A26 Page 14 Maximum baggage For all passenger configuration: See applicable section in Part I of this Data Sheet. For cargo or split passenger/cargo configurations: See the appropriate Weight and Balance Manuals listed under NOTE 14. Maximum cargo For cargo restrictions, see the appropriate Weight and Balance Control Manuals, listed under NOTE 14. Fuel capacity For maximum capacity fuel weights and other fuel data, see applicable section in Part III of this Data Sheet. For fuel C.G. locations with partially filled tanks, see the appropriate Weight and Balance Manuals listed under NOTE 14.