TCDS 4A28

Page No. 1 2 3 4 5 6 7 8 9 10 11 12 13 14 15 Rev No. 8 8 - - - - - - - 8 - 8 8 8 Reformatted 1/94. DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION 4A28 Revision 8 BOEING 720 720B May 1, 1973 TYPE CERTIFICATE DATA SHEET NO.4A28 This data sheet which is a part of type certificate No. 4A28 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 - 720 Series (Transport Aircraft), approved June 30, 1960 The 720 Series airplane has several different models due to different installations of equipment, interiors, airplane flight manuals, etc. These models are as follows: Model Serial numbers Eligible 720-022 17907 thru 17917; 18044 thru 18050; 18072 thru 18082 720-025 18155 thru 18164; 18240 thru 18244 720-027 18064 thru 18066; 18154; 18423 and 18581 720-048 18041 thru 18043 720-062 18376 and 18377 Engines 4 Pratt and Whitney Turbojet JT3C-7, except Model 720-025, which has 4 Pratt and Whitney JT3C-12 engines. Fuel See NOTE 10 Engine limits CERTIFICATION LIMITS Thrust Ratings (pounds) JT3C-7 JT3C-12 Takeoff (standard day) static Sea Level (5 minutes) 12,000 13,000 Below 43.5°F. Compressor inlet temperature (5 minutes) 12,500 --- Maximum continuous, static, sea level 10,000 11,500 At 4°F. ambient temperature and below 12,000 --- At 25°F. ambient temperature and below --- 13,000 Maximum permissible engine rotor operating speeds: Low pressure compressor (N1) rpm 6850 (110.7% 6850 (110.7%) High pressure compressor (N2) rpm 9950 ( 99.7%) 10150 (101.7%) Thrust setting -- Appropriate thrust setting curve (EPR), in the Airplane Flight Manual must be used for control of engine thrust. 4A28 2 Maximum permissible turbine outlet gas temperatures: Takeoff (5 minutes) (620°C) 1148°F (665°C) 1229°F Maximum continuous (540°C) 1004°F (600°C) 1112°F Maximum for acceleration (650°C) 1202°F (695°C) 1283°F (2 minutes) Starting (Ground) (450°C) 842°F (450°C) 842°F (Air) (500°C) 932°F (500°C) 932°F Maximum oil inlet temperature Continuous Operation (121°C) 250°F (121°C) 250°F 10 minutes ground operation only --- --- (143°C) 290°F Airspeed limits Vmo (Normal Operating) (Basic) (IAS) At Sea Level 436 mph (378 knots) At 6,000 feet 439 mph (381 knots) At 10,000 feet 442 mph (384 knots) At 23,400 feet 460 mph (399 knots) Mmo = 0.906 at 23,400 feet and above Vmo (Normal Operating) (Alternate) (See NOTE 5) At Sea Level 394 mph (342 knots) At 5,000 feet 397 mph (344 knots) At 10,000 feet 400 mph (347 knots) At 15,000 feet 404 mph (350 knots) At 20,000 feet 407 mph (354 knots) At 25,000 feet 414 mph (359 knots) Mmo (Alternate = 0.906 at 27,900 feet and above) Va (Maneuvering) At Sea Level 278 mph (241 knots) At 5,000 feet 279 mph (242 knots) At 10,000 feet 280 mph (243 knots) At 15,000 feet 283 mph (245 knots) At 20,000 feet 284 mph (246 knots) At 25,000 feet 289 mph (251 knots) At 30,000 feet 296 mph (257 knots) At 35,000 feet 304 mph (264 knots) At 40,750 feet 316 mph (274 knots) Ma = 0.906 at 40,750 feet and above Vfe (Flap Speeds) (Flaps not to be extended above 20,000 feet) Maximum Flap Deflection MPH KTS 20° 254 220 30° 242 210 50° 213 185 Vlo (Landing Gear Operation) Sea Level to 30,000 feet 311 mph (270 knots) 30,000 to 36,000 feet 323 mph (280 knots) Mlo = 0.83 at 36,000 feet and above Vle (Landing Gear Extended) Sea Level to 29,800 feet 328 mph (285 knots) Mle = 0.83 at 29,800 feet and above 3 4A28 For Emergency Descent Only Vlo = 369 mph (320 knots) Mlo = 0.90 Vle = 292 mph (340 knots) Vle = 0.90 Dump CHute Operation At Sea Level to 42,000 feet 277 mph (240 knots) Dump Chute Extended At Sea Level to 36,600 feet 317 mph (275 knots) M = 0.83 at 36,600 feet and above Vmc (Minimum Control Speed) Vmca (Minimum Control Speed)(Air) 115 mph (100 knots) Maximum takeoff thrust Vmcg (Minimum Control Speed)(Ground) 115 mph (100 knots) Maximum takeoff thrust C.G. range and Datum The nose gear retraction moment is 18,600 in/lb. for Model 720-025; and 14,500 in./lb. for the other 720 Models, and causes the C.G. to move forward. The main gear retracts parallel to the wing reference axis; hence, has no effect on the airplane C.G. All stations noted in the Data Sheet are Body Stations unless identified specifically as moment arms. Drawing 69-10819, defines body stations and moment arms. For weight and balance purposes, datum is 70 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 Model 720-022 213,000 lb. 18.0% MAC (Sta. 829.7) 29.5% MAC (Sta. 857.6) 203,000 lb. 16.6% MAC (Sta. 826.4) 31.0% MAC (Sta. 861.2) 190,000 lb. 15.0% MAC (Sta. 822.5) 31.0% MAC (Sta. 861.2) Model 720-025 230,000 lb. 18.4% MAC (Sta. 830.8) 26.0% MAC (Sta. 843.1) 225,000 lb. 17.8% MAC (Sta. 829.3) 31.0% MAC (Sta. 861.2) 200,000 lb. 15.0% MAC (Sta. 822.5) 31.0% MAC (Sta. 861.2) 150,000 lb. 15.0% MAC (Sta. 822.5) 31.0% MAC (Sta. 861.2) 130,000 lb. 15.0% MAC (Sta. 822.5) 30.0% MAC (Sta. 858.8) Model 720-027 (Serial No. 18066 only) 203,000 lb. 17.0% MAC (Sta. 827.3) 31.0% MAC (Sta. 861.2) 190,000 lb. 15.0% MAC (Sta. 822.5) 31.0% MAC (Sta. 861.2) Model 720-027 218,500 lb. 17.1% MAC (Sta. 827.5) 27.3% MAC (Sta. 852.2) 215,000 lb. 16.7% MAC (Sta. 826.6) 31.0% MAC (Sta. 861.2) 200,000 lb. 15.0% MAC (Sta. 822.5) 31.0% MAC (Sta. 861.2) Model 720-048 230,000 lb. 18.4% MAC (Sta. 830.8) 26.0% MAC (Sta. 849.1) 225,000 lb. 17.8% MAC (Sta. 829.3) 31.0% MAC (Sta. 861.2) 200,000 lb. 15.0% MAC (Sta. 822.5) 31.0% MAC (Sta. 861.2) 4A28 4 Model 720-062 214,000 lb. 16.6% MAC (Sta. 826.4) 31.0% MAC (Sta. 861.2) 213,000 lb. 16.5% MAC (Sta. 826.1) 31.0% MAC (Sta. 861.2) 199,000 lb. 15.0% MAC (Sta. 822.5) 31.0% MAC (Sta. 861.2) 175,000 lb. 15.0% MAC (Sta. 822.5) 31.0% MAC (Sta. 861.2) Straight line variation between values shown. Maximum weights 720-022 720-062 720-027 * 720-048 720-025 Maximum ramp weight 213,000 218,500 230,000 230,000 Maximum inflight weight 213,000 218,500 229,000 229,000 Maximum flight weight at start of outboard reserve fuel transfer with zero fuel weight of 139,000 lbs. 190,000 190,000 190,000 190,000 Maximum flight weight at start of outboard reserve fuel transfer with zero fuel weight of 149,000 lbs. (See NOTE 13) 185,000 185,000 185,000 185,000 Maximum flight weight at which the outboard reserve tanks can be empty with zero fuel weight of 139,000 lbs. 185,000 185,000 185,000 185,000 Maximum flight weight at which the outboard reserve tanks can be empty with zero fuel weight of 149,000 lbs. (See NOTE 13) 180,000 180,000 180,000 180,000 Maximum landing weight 175,000 175,000 175,000 175,000 Maximum Zero Fuel Weight (See NOTE 13) 149,000 149,000 149,000 149,000 Alternate Zero Fuel Weight (See NOTE 5) 142,000 --- --- --- * (See NOTE 15) Maximum baggage Maximum Maximum Moment Compartment Body Sta Load Concentration Capacity Arms Fwd. Belly 400-600H+6 47 lb/in. 150 lb/ft2 11,560 lb. 463 in. Aft Belly 960-1060 50 lb/in. 150 lb/ft2 3,000 lb. 990 in. Aft Belly 1060-1200 35 lb/in. 150 lb/ft2 4,900 lb. 1090 in. Aft Belly 1200-1300 20 lb/in. 150 lb/ft2 2,000 lb. 1210 in. 5 4A28 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 following data is given for full fuel tanks. See Boeing Documents indicated below for other fuel C.G. locations with partially filled tanks. Model Document 720-022 D6-5218 720-025 D6-7441 720-027 D6-5989 720-048 D6-5612 720-062 D6-8075 TANK NOMINAL CAPACITY (Usable fuel in tank) MAXIMUM CAPACITY U.S. Gallons per Tank Overwing Underwing Tanks Loaded Fueling Fueling Pounds Moment Arm Model 720-022 No. 1 and No. 4 Reserve 444 430 3,081 1083.6 No. 1 and No. 4 Main 2,342 2,318 16,592 916.8 No. 2 and No. 3 Main 2,269 2,265 16,152 791.3 Center 3,450 3,464 24,490 739.5 Total 13,560 13,490 96,140 Model 720-027 No. 1 and No. 4 Reserve 444 444 2,995 1083.6 No. 1 and No. 4 Main 2,342 2,342 16,132 916.1 No. 2 and No. 3 Main 2,269 2,269 15,704 791.3 Center 1,740 1,749 12,006 737.1 Total 11,850 11,859 81,668 Model 720-025, 720-048 and 720-062 No. 1 and No. 4 Reserve 444 444 3,081 1083.6 No. 1 and No. 4 Main 2,342 2,342 16,592 916.8 No. 2 and No. 3 Main 2,269 2,269 16,152 791.3 Center 3,450 3,464 24,490 739.5 Total 13,560 13,574 96,140 Oil capacity Engine Oil Tank No. Location Volume Capacity Moment Arm 1 Outboard Port 6.5 gallons 868.8 2 Inboard Port 6.5 gallons 686.1 3 Inboard Starboard 6.1 gallons 686.1 4 Outboard Starboard 6.1 gallons 868.9 The system oil capacities are given in Weight and Balance Control Manuals as noted under "Fuel Capacity." 4A28 6 II - 720B Series (Transport Aircraft), Approved March 3, 1961 (Same as 720 Series, except for engines and other associated changes and limitations.) The 720B Series airplane has several different models due to different installations of equipment, interiors, airplane flight manuals, etc. These models are as follows: Model Serial numbers Eligible 720-023B 18013 thru 18037 720-024B 18416 thru 18419, 18587; 18763; 19002 AND 19003 720-030B 18248 thru 18251; 18057 thru 18060 720-040B 18378 thru 18380 and 18745 720-047B 18061 thru 18063; 18167; 18451 thru 18453; 18588 thru 18590; 18749; 18818; 18820, 18827 thru 18830; 18963; 19160, 19161; 19207; 19208; 19413; 19414; 19438; 19439 and 19523 720-051B 18381 thru 18384; 18420 thru 18422; 18687 and 18688; 18351 thru 18356; 18792 and 18793 720-058B 18424 and 18425 720-059B 18086; 18087; and 18831 720-060B 18454; 18455; and 18977 720-068B 18165 and 18166 Engines 4 Pratt and Whitney JT3D-1, JT3D-1-MC6 or JT3D-1-MC7. See NOTE 11 for intermixing of engines. Fuel See NOTE 10. Engine limits CERTIFICATION LIMITS Thrust Ratings (pounds) JT3D-1 JT3D-3 Takeoff (standard day) static Sea Level (5 minutes) 17,000 18,000 Maximum continuous, standard day, static, Sea Level 14,500 16,400 Thrust setting -- appropriate thrust setting curve (EPR), in the Airplane Flight Manual must be used for control of engine thrust. Maximum permissible rotor operating speeds: Low pressure compressor (N1) rpm 6800 (109.9%) 6800 (109.9%) High pressure compressor (N2) rpm 10200 (105.6%) 10250 (106.2%) Maximum permissible turbine outlet gas temperatures: Takeoff (5 minutes) (530°C) 985°F (555°C) 1031°F Maximum continuous (460°C) 860°F (490°C) 914°F Maximum for acceleration (530°C) 985°F (555°C) 1031°F (2 minutes) Starting (450°C) 842°F (450°C) 842°F Maximum permissible oil inlet temperatures: Continuous Operation (132°C) 270°F (132°C) 270°F 10 minutes operation (143°C) 290°F (143°C) 290°F 7 4A28 Airspeed limits Vmo (Normal Operating) (IAS) At Sea Level 436 mph (378 knots) At 6,000 feet 439 mph (381 knots) At 10,200 feet 442 mph (384 knots) At 23,300 feet 459 mph (399 knots) Mmo = 0.90 at 23,300 feet and above Va (Maneuvering) At Sea Level 277 mph (241 knots) At 5,000 feet 279 mph (242 knots) At 10,000 feet 280 mph (243 knots) At 15,000 feet 281 mph (244 knots) At 20,000 feet 283 mph (246 knots) At 25,000 feet 289 mph (251 knots) At 30,000 feet 296 mph (257 knots) At 35,000 feet 305 mph (265 knots) At 40,600 feet 316 mph (274 knots) Ma = 0.90 at 40,600 feet and above Vfe (Flap Speeds) (Flaps not to be extended above 20,000 feet) Maximum Flap Deflection MPH KTS 20° 253 220 30° 242 210 50° 213 185 Vlo (Landing Gear Operation) Sea Level to 30,000 feet 311 mph (270 knots) 30,000 to 35,900 feet 322 mph (280 knots) Mlo = 0.83 at 35,900 feet and above Vle (Landing Gear Extended) Sea Level to 29,900 feet 369 mph (320 knots) Mle = 0.83 at 29,900 feet and above For Emergency Descent Only Vlo = 369 mph (320 knots) Mlo = 0.90 Vle = 392 mph (340 knots) Mle = 0.90 Dump Chute Operation At Sea Level to 42,000 feet 276 mph (240 knots) Dump Chute Extended At Sea Level to 36,700 feet 317 mph (275 knots) M = 0.83 at 36,700 feet and above Vmc (Minimum Control Speed) Vmca (Minimum Control Speed)(Air) 134 mph (116 knots) (For Model 720-058B only): 136 mph (117.8 knots) Maximum takeoff thrust Vmcg (Minimum Control Speed)(Ground) 128 mph (111 knots) (For Model 720-058B only): 130 mph (112.5 knots) 4A28 8 C.G. range and Datum The nose gear retraction moment is 14,500 in/lb. and moves C.G. forward. The main gear retracts parallel to the wing reference axis; hence, has no effect on the airplane 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 70 inches forward of nose (Moment Arm 0). Horizontal distance of datum to average wing jack point is 810.5 inches. Gross Weight Forward Limit Aft Limit Model 720-023B (See Note 14) 222,000 lb. 17.5% MAC (Sta. 828.5) 26.0% MAC (Sta. 849.1) 217,000 lb. 16.9% MAC (Sta. 827.1) 31.0% MAC (Sta. 861.2) 200,000 lb. 15.0% MAC (Sta. 822.5) 31.0% MAC (Sta. 861.2) Model 720-030B, 720-047B, 720-024B, and 720-023B 230,000 lb. 17.5% MAC (Sta. 828.5) 26.0% MAC (Sta. 849.1) 225,000 lb. 16.5% MAC (Sta. 825.1) 31.0% MAC (Sta. 861.2) 217,000 lb. 15.0% MAC (Sta. 822.5) 31.0% MAC (Sta. 861.2) Model 720-060B, 720-058B, 720-051B, 720-059B, 720-040B, 720-068B, 720-030B (See Note 12) 235,000 lb. 17.5% MAC (Sta. 828.5) 23.0% MAC (Sta. 841.8) 225,000 lb. 16.1% MAC (Sta. 825.1) 31.0% MAC (Sta. 861.2) 217,000 lb. 15.0% MAC (Sta. 822.5) 31.0% MAC (Sta. 861.2) At lightweight aft C.G. locations, pitch up tendency after brake release could result in aircraft rotating onto tail. To prevent this, the noted aft C.G. locations should be observed when taking off at weights equal to or less than those noted below. Gross Weight Forward Limit Aft Limit Model 720-023B (See Note 14 Models 720-030B, 720-047B, 720-051B, 720-059B, 720-040B, and 720-068B) 179,000 lb. 17.5% MAC (Sta. 828.5) 26.0% MAC (Sta. 849.1) 135,000 lb. 16.9% MAC (Sta. 827.1) 31.0% MAC (Sta. 861.2) 200,000 lb. 15.0% MAC (Sta. 822.5) 31.0% MAC (Sta. 861.2) Model 720-030B, 720-047B, 720-024B, and 720-023B 230,000 lb. 17.5% MAC (Sta. 828.5) 26.0% MAC (Sta. 849.1) 225,000 lb. 16.5% MAC (Sta. 825.1) 31.0% MAC (Sta. 861.2) 217,000 lb. 15.0% MAC (Sta. 822.5) 31.0% MAC (Sta. 861.2) Model 720-060B, 720-058B, 720-051B, 720-059B, 720-040B, 720-068B, 720-030B (See Note 12) 235,000 lb. 17.5% MAC (Sta. 828.5) 23.0% MAC (Sta. 841.8) 225,000 lb. 16.1% MAC (Sta. 825.1) 31.0% MAC (Sta. 861.2) 217,000 lb. 15.0% MAC (Sta. 822.5) 31.0% MAC (Sta. 861.2) Straight line variation between values shown. 9 4A28 Maximum weights 720-0308*** 720-040B, 720-047B**** 720-051B, 720-058B 720-023B, 720-024B, 720-059B, 720-060B, 720,023B* 720-030B, 720-047B** 720-068B Maximum ramp weight 222,000 lb. 230,000 lb. 235,000 lb. Maximum flight weight, 30° Flaps 222,000 lb. 229,000 lb. 234,000 lb. Maximum flight weight Zero Flaps 221,000 lb. 228,000 lb. 233,000 lb. Maximum flight weight at start of outboard reserve fuel transfer 190,000 lb. 190,000 lb. 190,000 lb. Maximum flight weight at which the outboard reserve tanks can be empty 185,000 lb. 185,000 lb. 185,000 lb. Maximum landing weight 175,000 lb. 175,000 lb. 175,000 lb. Maximum zero fuel weight 147,000 lb. 149,000 lb. 156,000 lb. * See Note 14. ** See Note 6. *** See Note 12. ****See Note 16 and 17. Maximum baggage Maximum Maximum Moment Compartment Body Sta. Load Concentration Capacity Arms Fwd. Belly 400-600H+6 47 lb/in. 150 lb/ft2 11,560 lb. 463 in. Aft Belly 960-1060 50 lb/in. 150 lb/ft2 3,000 lb. 990 in. Aft Belly 1060-1200 35 lb/in. 150 lb/ft2 4,900 lb. 1090 in. Aft Belly 1200-1300 20 lb/in. 150 lb/ft2 2,000 lb. 1210 in. 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 following data are given for full fuel tanks. See Boeing Documents indicated below for other fuel C.G. locations with partially filled tanks. Model Document 720-023B D6-5400 (Sec. 2b.) 720-024B D6-8074 720-030B D6-5857 720-040B D6-7835 720-047B D6-5858 720-051B D6-7367 720-058B D6-8073 720-059B D6-7239 720-060B D6-7237 720-068B D6-7834 4A28 10 TANK NOMINAL CAPACITY (Usable fuel in tank) MAXIMUM CAPACITY U.S. Gallons per Tank Overwing Underwing Tanks Loaded Fueling Fueling Pounds Moment Arm Model 720-023B No. 1 and No. 4 Reserve 444 430 3,081 1082.6 No. 1 and No. 4 Main 2,322 2,348 6,592 916.1 No. 2 and No. 3 Main 2,269 2,265 16,152 791.3 Center 3,450 3,464 24,490 739.5 Total 13,620 13,550 96,140 Model 720-024B, 720-030B, 720-047B, 720-051B, 720-058B, 720-060B and 720-068B No. 1 and No. 4 Reserve 444 444 3,081 1083.6 No. 1 and No. 4 Main 2,342 2,342 16,592 916.1 No. 2 and No. 3 Main 2,269 2,269 16,152 791.3 Center 4,720 4,741 33,412 750.6 Total 14,830 14,851 105,062 Model 720-040B and 720-059B No. 1 and No. 4 Reserve 444 444 3,081 1083.6 No. 1 and No. 4 Main 2,342 2,342 16,592 916.8 No. 2 and No. 3 Main 2,269 2,269 16,152 791.3 Center 5,945 5,967 42,314 731.7 Total 16,055 16,077 113,966 Engine Oil Tank No. Location Volume Capacity Moment Arm 1 Outboard Port 6.2 gallons 866.9 2 Inboard Port 6.2 gallons 684.1 3 Inboard Starboard 6.4 gallons 684.1 4 Outboard Starboard 6.4 gallons 866.9 The system oil capacities are given in Weight and Balance Control Manuals as noted under "Fuel Capacity." Specifications Pertinent to Both Series MAC 241.9 inches. (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 For all flights: 3 persons: Pilot, Copilot, Flight Engineer. Maximum passengers 139. When inflatable escape chutes are installed per FAA approved type design data, airplane is limited to 140 passengers by emergency exit requirement of 4b.362(d). All 720 and 720B Series aircraft certificated to carry 141 - 149 passengers, except Model 720-025, must have the provisions of Boeing Service Bulletin 2045A installed to be in accordance with approved type design data. For Model 720-025, maximum passengers limited to 165. The installation of interior per Boeing Drawing 65-77197 allows a maximum passenger capacity of 170 for Model 720-025. 11 4A28 Maximum operating altitude The maximum operating altitude for all Models is 42,000 feet: Other operating See FAA Approved Flight Manuals. 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 Drawing 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 50-8424 Stabilizer Trim 50-8704 Rudder 50-8703 Rudder Trim 50-8706 Rudder Balance Panel Tolerances 50-14035 Wing Flap 50-8707 Service information Boeing Report D6-1891, 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 thru 4b-6 thereto; Item 2 of Special Civil Regulation No. SR-422B; the special condition and the provisions of amendments listed in Attachment A of FAA letter to Boeing dated October 12, 1959. Type Certificate No. 4A28 issued June 30, 1960. Date of Application for Type Certificate - April 12, 1957. 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. The following Boeing Documents list all required equipment that must be installed as well as optional equipment approved by FAA. 720 Series Model Document 720-022 D6-5218 720-025 D6-7441 720-027 D6-5989, D6-7014 720-048 D6-5612 720-062 D6-8075 4A28 12 720B Series Model Document 720-023B D6-5400 (Sec. 2b) 720-024B D6-8074 720-030B D6-5857 720-040B D6-7835 720-047B D6-5858 720-051B D6-7367 720-058B D6-8073 720-059B D6-7239 720-060B D6-7237 720-068B D6-7834 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 operators having an approved weight control system. (b) The airplane must be loaded so that the C.G. is within the specified limits (See C.G. Range) at all times with the effects of fuel use and 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 and 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 retained in the fuel 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 unusable fuel for all 720 and 720B Series aircraft is as follows: (d) "System oil" is defined as that amount of oil required to fill the oil system and tank outlets to the engines. System oil and all hydraulic fluid must be included in the airplane empty weight or be suitably accounted for in the airplane weight and balance report. See appropriate Boeing document listed under "Equipment." (e) To preserve favorable wing bending moments, the following limitations shall apply: All center tank fuel in excess of any included in the zero fuel weight must be used before the transfer of reserve tank fuel. For 720 Series aircraft with 149,000 lbs. zero fuel weight, the outboard reserve tanks must be filled when the airplane gross weight exceeds 180,000 lb. and transfer of reserve tank fuel must not be initiated above gross weights of 185,000 lb. In all other cases for 720 Series aircraft and for 720B Series aircraft, the outboard reserve tanks must be filled when the gross weight exceeds 185,000 lbs. and transfer of reserve fuel must not be initiated above gross weights of 190,000 lbs. (1) Fuel Loading Limitations a. Load fuel equally in main tanks 1, 2, 3 and 4 up to a total capacity of 36,000 lbs. (for 720B Series and for 720 Series aircraft utilizing a zero fuel weight of 149,000 lbs.); 43,000 lbs. (for 720 Series aircraft utilizing 139,000 lbs. for zero fuel weight); 29,000 lbs. for 720B Series aircraft utilizing the 156,000 lbs. zero fuel weight). b. If additional fuel is desired, load reserve tank. c. If the reserve tanks are full and additional fuel is required, continue loading fuel equally in main tanks 1, 2, 3, and 4. 13 4A28 d. If main tanks 2 and 3 are full and additional fuel is required, continue to load main tanks 1 and 4 to required fuel quantity. e. If all main and reserve tanks are full and additional fuel is required, load center tank fuel. OPTION: Fuel must be loaded equally in the main tanks only up to a gross weight of 185,000 lbs. or 180,000 lbs. for 720 series aircraft utilizing the 149,000 lbs. zero fuel weight. Additional required fuel must be added first to the reserve tanks and when full, then equally to the main tanks and when full, then to the center tank. NOTE: Observing limitations above, center tank fuel may be substituted for payload in any quantity up to the maximum allowable payload * or to the center tank capacity, whichever is lower, provided the difference in effect on balance is also accounted for. * Maximum zero fuel weight less operating weight empty. NOTE: Tanks selected for flight may be loaded simultaneously. (2) Fuel Usage Limitations Use tank-to-engine combination during all takeoffs and landing except as noted under Minimum Fuel Go-Around. (See Airplane Flight Manual.) The fuel in main tanks 1, 2, 3, and 4 must be used equally at airplane gross weights above 211,000 lbs. (Model 720B); 207,000 lbs. (Model 720). Fuel reserves must be retained in main tanks only. For 720B Series Only