TCDS A23WE

Page No. 1 2 3 4 5 6 7 8 9 10 11 12 13 14 15 16 17 18 Rev. No. 18 18 18 18 16 18 18 18 16 18 18 16 18 18 16 18 18 19 Page No. 19 20 21 22 23 Rev. No. 18 18 18 18 18 DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION A23WE Revision 19 LOCKHEED L-1011-385-1 L-1011-385-1-14 L-1011-385-1-15 L-1011-385-3 January 11, 2010 TYPE CERTIFICATE DATA SHEET A23WE This data sheet which is part of the Type Certificate No. A23WE prescribes conditions and limitations under which the product for which the Type Certificate was issued meets the airworthiness requirements of the Federal Aviation Regulations. Type Certificate Holder Lockheed Martin Corporation Lockheed Martin Aeronautics Company 86 S. Cobb Drive Marietta GA 30063 I - Model L-1011-385-1 (Transport Category Aircraft), Approved April 14, 1972 Engines 3 Rolls-Royce RB 211-22C-02 engines (see NOTE 25) or 3 Rolls-Royce RB 211-22B-02 engines (s ee NOTE 3 for Engine Life limitations. Also see NOTES 10 and 12.) Fuel See NOTE 4. (a). Oil See NOTE 4.(b). -22C Engine Static thrust at sea level Takeoff (5 min.) 41,030 lbs. (flat rated to ISA 1 + 3.8° C) Maximum continuous 36,900 lbs. (flat rated to ISA + 10° C) -22B Engine Static thrust at sea level Takeoff (5 min.) 41,030 lbs. (flat rated to ISA + 13.9° C) 42,670 lbs. (flat rated to ISA + 8.4° C to 5600 ft. Thereafter, thrust reduces linearly to be same as the -22B at ISA + 13.9° C and 10,000 ft.) 2 Maximum continuous 40,140 lbs. (flat ra ted to ISA + 9.0° C to 25,000 ft. and ISA + 13° C above 25,000 ft.) 1ISA - International Standard Atmosphere 2With Rolls-Royce Mod 72-8700 or later FAA approved equivalent A23WE Page 2 of 23 -22C Engine Only -22B Engine Only N 1 (%) N 2 (%) N 3 (%) N 1 (%) N 2 (%) N 3 (%) Takeoff (5min.) 99.0 99.5 95.5 99.5 102.5 95.0 Maximum continuous 97.5 98.8 94.3 101.0 101.5 93.7 94.23 Ground idle 19.3+4.00-0 - - - - 21.0+2.3-0 - - - - Maximum reverse thrust (30 sec.) 90.0 - - - - 101.3 - - - - Transient (20 sec.) 103.0 101.0 97.0 103.0 106.0 96.2 100% N 1 (low pressure rotor) = 3,900 rpm 100% N 2 (intermediate pressure rotor) = 7,000 rpm 100% N 3 (high pressure rotor) = 10,611 rpm Maximum turbine temperature (measured at low pressure NGV 4): -22C Engine Only -22B Engine Only Takeoff (5 min.) 1328° F (720° C) 1342° F (728° C) Maximum continuous 1292° F (700° C) 1292° F (700° C) 1310° F (710° C) 4 Starting (2 sec.) 1022° F (550° C) 1022° F (550° C) Reverse thrust (30 sec.) 1265° F (685° C) 1360° F (738° C) Maximum for acceleration (2 min.) 1337° F (725° C) 1360° F (738° C) APU Limits : See "Data Pertinen t to All Models." Airspeed Limits : Also see "Data Pertin ent to All Models." V fe Load Relieving System Operative Flap Angle Selected, in Degrees Knots IAS/mach No. 4° 250K M = 0.6 10° 230K M = 0.5 14° 215K M = 0.5 18° 210K M = 0.5 22° 205K M = 0.5 27° 5 200K M = 0.5 33° 170K M = 0.4 42° 164K M = 0.4 If the landing flap extension speeds ar e inadvertently exceeded, the LRS will limit flap angle to 28° at airspeeds above 164 knots. When airspeed decreases to 164 knots, flaps will extend, as selected , to 33° or 42°. Limit speed with flaps at LRS position (28°) is 206 KIAS/0.4 mach. V SLAT (slat operation) 250k IAS (M = 0.6) V LO (landing gear) Retraction 230k not to exceed (M = 0.85) Extension 300k not to exceed (M = 0.85) V LE (landing gear extended) 300k not to exceed (M = 0.85) 3DELETED. 4NGV - Nozzle Guide Vanes 5Use of Flap 27 take-off is permitted only with aircraft equipped with flap quadrant 27 detent and which have incorporated S/B 093-27-098 or production equivalent which resets the take-off warning switch to accommodate Flap 27 take-off position. Page 3 of 23 A23WE C.G. Range L-1011-385-1 CENTER OF GR AVITY ENVELOP E S/N 1004 -1 0 1 2 AIRPLANE GROSS WEIGHT(1000 LB) 490 480 470 460 450 440 430 420 410 400 390 380 370 360 350 340 330 320 310 300 290 280 270 260 250 240 230 220 10 12 14 16 18 20 22 24 26 28 30 32 34 36 IN FLIGHT LIMIT TAXI, T AKEOFF LANDING LIMIT AIRPLANE GROSS WEIGHT (1000 LB) A23WE Page 4 of 23 L-1011-385-1 CENTER OF GRAVITY E NVELOPE PERCENT OF MEAN AERODYNAMIC CHORD 490 480 470 460 450 440 430 420 410 400 390 380 370 360 350 340 330 320 310 300 290 280 270 260 250 240 230 220 10 12 14 16 18 20 22 2 42 62 83 03 23 43 6 IN FLIGHT LIMIT TAXI, TAKEOFF LANDING LIMIT S/N 1013 - 1051 AIRPLANE GROSS WEIGHT (1000 LB) Page 5 of 23 A23WE L-1011-385-1 CENTER OF GRAVITY ENVELOPE S/N 1052 & UP AIRPLANE GROSS WEIGHT (1000 LB) PERCENT OF MEAN AERODYNAMIC CHORD 490 480 470 460 450 440 430 420 410 400 390 380 370 360 350 340 330 320 310 300 290 280 270 260 250 240 230 220 10 12 14 16 18 20 22 24 26 28 30 32 34 36 IN FLIGHT LIMIT TAXI, TAKEOFF LANDING LIMIT 500 510 520 530 A23WE Page 6 of 23 Maximum Weights 6, 7 S/N 1004 thru 10128 S/N 1013 thru 10519 S/N 1052 & up10 S/N 1052 & up11,12 S/N 1052 & up13 Taxi and Ramp 472, 000 476,000 468,000 476,000 512,000 Takeoff 470,000 474,000 466,000 474,000 510,000 Landing 368,000 368,000 368,000 368,000 368,000 Zero Fuel14 338,000 338,000 320,000 338,000 338,000 Gear Jacking 472,000 472,000 468,000 468,000 512,000 Fuselage and Wing Jacking 340,000 340,000 340,000 340,000 340,000 Minimum Flight 233, 700 233,700 233,000 233,700 233,000 The aircraft will remain within the above approved we ight and C.G. limits when the aircraft is loaded within the zero fuel weight and C.G. limits and the effect of: (1) landing gear retraction, and (2) movement of crew and passengers from their assigned positions, is accounted for and the fuel is loaded (up to the maximum takeoff we ight) and used in the approved sequence. See NOTES 1.(a), 1.(b), and 1.(c). For fuel dump valves operation, see NOTE 1.(d). Minimum Flight Crew For all flights: Pilot, co-pilot, and flight engineer Maximum Passengers See NOTE 5. Cargo See NOTE 37. Fuel Capacity Full Tank Capacity (lbs.) Structural Limits Usable Fuel Arm Tank (7.1 lb/gallon) (6.7 lb/gallon) (Inches) 2L 27,181 25,650 1371.8 1 57,362 54,130 1157.2 3 57,362 54,130 1157.2 2R 27,181 25,650 1371.8 Total 169,086 159,560 6Weights are in pounds. 7These weights vary as a function of modification standard and fuel management. See FAA Approved Flight Manual and Weight and Balance Manual. 8These weights are applicable to L-1011-385-1 configured aircraft modified in accordance with S/B 093-51-029 to provide increased gross weight capability (see NOTE 38). 9These weights are applicable to L-1011-385-1 configured aircraft modified in accordance with S/B 093-51-030 to provide increased gross weight capability (see NOTE 38). 10These weights are applicable to L-1011-385-1-193L configured aircraft modified in accordance with S/B 093-51-012 to provide increased gross weight capability. 11These weights are applicable to L-1011-385-1 configured aircraft modified in accordance with S/B 093-51-010, 093-28-038, -03-51-022 and 093-51-023 to provide increased gross and zero fuel weights capability (see NOTE 23 and 24). 12S/B 093-51-034 provides modifications of L-1011 aircraft to permit operation at maximum zero fuel weight of 335,000 lbs. at GTOW of 430,000 lbs and MZFW of 325,000 lbs at GTOW of 450,000 lbs. 13These weights are applicable to L-1011-385-1 configures aircraft modified in accordance with S/B 093-51-023 to provide the increased gross weight capability. 14All weight in aircraft above this weight must be fuel. For fuel dump valves operation see NOTE 1.(d). Page 7 of 23 A23WE Oil Capacity 39 pounds/engine usable at 8.0 pounds/g allon with wing engines moment arm at 1050 inches and tail engine moment arm at 2041 inches. Eligibility : Series Eligible Date Approved Serial Numbers Issued to Date 193A April 14, 1972 1004, 1005, 1006, 1009, 1012, 1022, 1038, 1040, 1043, 1050, 1051, 1055, 1123, 1126, 1141, 1142, 1143, 1152, 1153 193B June 5, 1972 1013, 1015, 1017, 1018, 1028, 1035, 1060, 1066, 1072, 1076, 1080 193M November 24, 1972 None. All serial numbers converted to L-1011-385-1-14. 193E December 30, 1972 1021 193K February 9, 1972 1024 193R May 25, 1973 1033 193C September 20, 1973 1052, 1057, 1071, 1074, 1077, 1078, 1081, 1084, 1086, 1088, 1089, 1090, 1095, 1096, 1097, 1135, 1136, 1139, 1147, 1150, 1162, 1167, 1173, 1180, 1199, 1200, 1213, 1224, 1225, 1226 193P December 12, 1973 1062, 1070, 1082, 1100, 1105, 1112, 1113, 1127, 1129, 1134, 1155, 1156 193L June 28, 1973 1064 193N September 27, 1973 1094, 1145 II. - Model L-1011-385-1-14 (Transport Category Aircraft), Approved June 6, 1975 Engines 3 Rolls-Royce RB.211-22B-02 engines (See Section I) or 3 Rolls-Royce RB.211-524B-02 engines (See Section IV) or 3 Rolls-Royce RB.211-524B4-02 engines (See Section IV) or 3 Rolls-Royce RB.211-524B3-02 engines (See Section IV) (See NOTE 3 for Engine Component Life Limitations and NOTE 10 for Engine Intermix.) Fuel See NOTE 4.(a). Oil See NOTE 4.(b). APU Limits See "Data Pertinen t to All Models." A23WE Page 8 of 23 Airspeed Limits (Also see "Data Pertin ent to All Models.") V fe Load Relieving System Operative Flap Angle Selected, in Degrees Knots IAS/mach No. 4° 250K M = 0.6 10° 230K M = 0.5 14° 215K M = 0.5 18° 210K M = 0.5 22° 205K M = 0.5 27° 15 200K M = 0.5 33° 170K M = 0.4 42° 164K M = 0.4 If the landing flap extension speeds ar e inadvertently exceeded, the LRS will limit flap angle to 28° at airspeeds above 164 knots. When airspeed decreases to 164 knots, flaps will extend, as selected , to 33° or 42°. Limit speed with flaps at LRS position (28°) is 208 KIAS/0.4 mach. V SLAT (slat operation) 250k IAS (M = 0.6) V LO (landing gear) Retraction 230k not to exceed (M = 0.85) Extension 300k not to exceed (M = 0.85) V L3 (landing gear extended) 300k not to exceed (M = 0.85) C.G. Range See Center of Gravity envelope page 9. Maximum Weights 16 Taxi and Ramp 468,000 lbs. Takeoff 466,000 lbs. 17,18 Landing 368,000 lbs. Zero Fuel 19 320,000 lbs. 19, 20 Gear Jacking 468,000 lbs. Fuselage and Wing Jacking 340,000 lbs. Minimum Flight 233,700 lbs. Loadability 20 The aircraft will remain within the above approved weight and CG limits when the aircraft is loaded within the zero fu el weight and CG limits and the effect of: (1) landing gear retraction, and (2) movement of crew and passe ngers from their assigned positions, is accounted for and the fuel is loaded (up to the maximum takeoff weight) and used in the approved sequence. For fuel dump valves operation, see NOTE 1.(d). Minimum Flight Crew For all flights: Pilot, co-pilot, and flight engineer Maximum Passengers See NOTE 5. Cargo See NOTE 37. 15Use of Flap 27 for take-off is permitted only with aircraft equipped with flap quadrant 27 detent and which have incorporated S/B 093-27-098 which resets the takeoff warning switch to accommodate Flap 27 take-off position. 16These weights vary as a function of modification standard and fuel management. See FAA Approved Flight Manual and Weight and Balance Manual. 17At 450,000 lb. takeoff weight, the zero fuel weight is 330,000 lbs. and at 440,000 lbs. takeoff weight, the zero fuel weight is 338,000 lbs. 18The Zero Fuel Weight/Takeoff Gross Weight combinations are a linear function. See FAA Approved Airplane Flight Manual and Weight and Balance Manual. 19All weight in aircraft above this weight must be fuel. Fur fuel dump valves operation see NOTE 1.(d). 20See NOTE 1.(a), 1.(b), and 1.(c). Page 9 of 23 A23WE L-1011-385-1-14 CENTER OF GRAVITY ENVELOPE AIRPLANE GROSS WEIGHT (1000 LB) PERCENT OF MEAN AERODYNAMIC CHORD 490 480 470 460 450 440 430 420 410 400 390 380 370 360 350 340 330 320 310 300 290 280 270 260 250 240 230 220 10 12 14 16 18 20 22 24 26 28 30 32 34 36 IN FLIGHT LIMIT TAXI, TAKEOFF LANDING LIMIT A23WE Page 10 of 23 Fuel Capacity Full Tank Capacity (lbs.) Structural Limits Usable Fuel Arm Tank (7.1 lb/gallon (6.7 lb/gallon) (Inches) 2L 27,181 25,650 1371.8 1 57,362 54,130 1157.2 3 57,362 54,130 1157.2 2R 27,181 25,650 1371.8 Total 169,086 159,560 Oil Capacity For -22B engines: 39 pounds/engine usable at 8.0 pounds/gallon with wing engines moment arm at 1050 inches a nd tail engine moment arm at 2041 inches. For -524 engines: 33 pounds/engine usable at 8.0 pounds/gallon with wing engines moment arm at 1050 inches a nd tail engine moment arm at 2041 inches. Eligibility 21 Series Date Eligible Approved Serial Numbers Issued to Date 193S June 6, 1975 None. All seri al numbers converted to L-1011-385-1-15. 193A 1010, 1158 193M 1019, 1023 193E 1048, 1049 193C 1041 193P 1103 193N 1083, 1093, 1101, 1106 III. - Model L-1011-385-1-15 (Transport Category Aircraft), Approved July 25, 1975 Engines 3 Rolls-Royce RB.211-22B-02 engines (See Section I) or 3 Rolls-Royce RB.211-524B-02 engines (see Section IV) or 3 Rolls-Royce RB.211-524B3-02 engines (see Section IV) or 3 Rolls-Royce RB.211-524B4-02 engines (see Section IV) or 3 Rolls-Royce RB.211-524B4-D-02 engines (see Section IV) (See NOTE 3 for Engine Component Life Limitations and NOTE 10 for Engine Intermix.) Fuel See NOTE 4.(a). Oil See NOTE 4.(b). APU Limits See "Data Pertinen t to All Models." 21See NOTE 23. Page 11 of 23 A23WE Airspeed Limits (Also see "Data Pertin ent to All Models.") V fe Load Relieving System Operative Flap Angle Selected, in Degrees Knots IAS/mach No. 4° 250K M = 0.6 10° 230K M = 0.5 14° 215K M = 0.5 18° 210K M = 0.5 22° 205K M = 0.5 27° 22 200K M = 0.5 33° 170K M = 0.4 42° 164K M = 0.4 If the landing flap extension speeds ar e inadvertently exceeded, the LRS will limit flap angle to 28° at airspeeds above 164 knots. When airspeed decreases to 164 knots, flaps will extend, as selected , to 33° or 42°. Limit speed with flaps at LRS position (28°) is 206 KIAS/0.4 mach. V SLAT (slat operation) 250k IAS (M = 0.6) V LO (landing gear) Retraction 230k not to exceed (M = 0.85) Extension 300k not to exceed (M = 0.85) V LE (landing gear extended) 300k not to exceed (M = 0.85) C.G. Range See center of gravity envelope page 12. Maximum Weights 23, 24 Taxi and Ramp 468,000 lbs. 512,000 lbs. Takeoff 466,000 lbs. 510,000 lbs .25 Landing 368,000 lbs. 368,000 lbs .26 Zero Fuel 27 320,000 lbs .26, 28 338,000 lbs. 27 Gear Jacking 468,000 lbs. 512,000 lbs. Fuselage and Wing J acking 340,000 lbs. 340,000 lbs. Minimum Flight 233,700 lbs. 233,700 lbs. 22Use of Flap 27 for take-off is permitted only with aircraft equipped with flap quadrant 27 detent and which have incorporated S/B 093-27-098 which resets the take-off warning switch to accommodate Flap 27 take-off position. 23These weights vary as a function of modification standard and fuel management. See FAA Approved Flight Manual and Weight and Balance Manual. 24These weights are applicable to L-1011-385-1-15 configured aircraft modified in accordance with S/B 093-51-023 to provide the increased gross weight capability to 510,000 lbs. GTOW. 25The Zero Fuel Weight/Takeoff Gross Weight combinations are a linear function. See FAA Approved Airplane Flight Manual and Weight and Balance Manual. 26Aircraft modified by Lockheed Martin Service Bulletin No. 093-51-018 have Maximum Landing Weight of 380,000 lbs. 27All weight in aircraft above this weight must be fuel. For fuel dump valves operation see NOTE 1.(d). 28At 450,000 lbs. Takeoff Weight, the Zero Fuel Weight is 330,000 lbs. and at 440,000 lbs. Takeoff Weight, the Zero Fuel Weight is 338,000 lbs. A23WE Page 12 of 23 L-1011-385-1-15 CENTER OF GRAVITY ENVELOPE AIRPLANE GROSS WEIGHT (1000 LB) PERCENT OF MEAN AERODYNAMIC CHORD 490 480 470 460 450 440 430 420 410 400 390 380 370 360 350 340 330 320 310 300 290 280 270 260 250 240 230 220 10 12 14 16 18 20 22 24 26 28 30 32 34 36 IN FLIGHT LIMIT TAXI, TAKEOFF LANDING LIMIT 500 510 520 530 Page 13 of 23 A23WE Loadability 29 The aircraft will remain within the a bove approved weight and C.G. limits when the aircraft is loaded within the zero fu el weight and C.G. limits and the effect of: (1) landing gear retraction, and (2) movement of crew and pa ssengers from their assigned positions, is accounted for and the fuel is loaded (up to the maximum takeoff weight) and used in the approved sequence. For fuel dump valves, see NOTE 1.(d). Minimum Flight Crew For all flights: Pilot, co-pilot, and flight engineer Maximum Passengers See NOTE 5. Cargo See NOTE 37. Fuel Capacity Full Tank Capacity (lbs.) Structural Limits Usable Fuel Arm Tank (7.1 lb/gallon (6.7 lb/gallon) (Inches) 2L 27,181 25,650 1371.8 1 57,192 53,970 1157.2 1A 10,131 9,560 1132.6 3 57,192 53,970 1157.2 3A 10,313 9,560 1132.6 2R 27,181 25,650 1371.8 Total 189,008 178,360 Oil Capacity For -22B engines 39 pounds/engine usable at 8.0 pounds/gallon with wing engine moment arm at 1050 inches a nd tail engine moment arm at 2041 inches. For -524 engines 33 pounds/engine usable at 8.0 pounds/gallon with wing engine moment arm at 1050 inches a nd tail engine moment arm at 2041 inches. Eligibility Series Date Eligible Approved Serial Numbers Issued to Date 193T July 25, 1975 1118, 1122 193U December 18, 1975 1131, 1133, 1138, 1201, 1203, 1223 193S May 29, 1976 1110, 1116,1137, 1144, 1148, 1149, 1160, 1161, 1170, 1171, 1175, 1187, 1190, 1192, 1214 193N February 29, 1980 1178, 1182, 1193, 1198, 1204, 1205 293C May 12, 1981 1211, 1212 193B September 29, 1981 1109, 1111, 1115, 1124, 1130,1215, 1221, 1230, 1231, 1232 193E 1058, 1067, 1069, 1073 193C 1151, 1227, 1228, 1234, 1237, 1244, 1245 193P 1053 IV. Model L-1011-385-3 (Transport Category Aircraft), Approved April 13, 1979 Engines 3 Rolls-Royce RB.211-524B-02 engines o r 3 Rolls-Royce RB.211-524B3-02 engines o r 3 Rolls-Royce RB.211-524B4-02 engines o r 3 Rolls-Royce RB.211-524B4-D-02 engines (See NOTE 3 for Engine Component Life Limitations and NOTE 10 for Engine Intermix.) Fuel See NOTE 4.(a). 29See NOTE 1.(a), 1.(b), and 1.(c). A23WE Page 14 of 23 Oil See NOTE 4.(b). Engine Limits Rolls-Royce RB.211-524B-02, -524B3-02, -524B4-02, -524B4-D-O2 Engines Static Thrust at Sea Level Takeoff (5 min.) 49,120 lbs. (-524B 4-D-02: Flat Rated to ISA +17.8° C up to 5000 ft. 30; -524B-02, -524B3-02 and -524B4-02: Flat rated to ISA +13.9° C) Maximum continuous 44,780 lbs. (Fla t rated to ISA + 9.0° C to 25,000 ft., ISA + 10° C above 25,000 ft.) N 1 (%) N 2 (%) N 3 (%) Takeoff (5 min.) 103.0 106.0 107.0 31 97.0 97.5 32 Maximum continuous 103.0 102.0 103.5 35 94.5 95.3 32 Ground Idle 22.5 + 1.0-0 - - Maximum Overspeed (20 sec.) 104.0 107.0 108.0 35 98.3 98.5 32 Maximum for Reverse (60 sec.) 90.0 - - 100% N 1 (low pressure rotor) = 3900 rpm 100% N 2 (intermediate pressure rotor) = 7000 rpm 100% N 3 (high pressure rotor) = 10,611 rpm Maximum turbine temperature (measured at low pressure NGV) Takeoff (5 min.) 1444° F (785° C) Maximum continuous 1350° F (732° C) Starting 1022° F (550° C) in flight 1112° F (600° C) on ground APU Limits See "Data Pertinen t to All Models." Airspeed Limits Also, see "Data Per tinent to all Models." V fe Load Relieving System Operative Flap Angle Selected, in Degrees Knots IAS/mach No. 4° 250K M = 0.6 10° 230K M = 0.5 14° 225K M = 0.5 18° 220K M = 0.5 22° 215K M = 0.5 33° 210K M = 0.4 V SLAT (slat operation) 250k IAS (M = 0.6) V LO (landing gear) Retraction 230k not to exceed (M = 0.85) Extension 300k not to exceed (M = 0.85) V L3 (landing gear extended) 300k not to exceed (M = 0.85) 30Also -524B4-02 engines with Rolls-Royce MOD 72-8516 Rev. 3. 31With Rolls-Royce MOD 72-7730 on -524B4-02and –524B4-D-02 engines. Page 15 of 23 A23WE C.G. Range L-1011-385-3 CENTER OF GRAVITY ENVELOPE AIRPLANE GROSS WEIGHT (1000 LB) PERCENT OF MEAN AERODYNAMIC CHORD 490 480 470 460 450 440 430 420 410 400 390 380 370 360 350 340 330 320 310 300 290 280 270 260 250 240 230 220 10 12 14 16 18 20 22 24 26 28 30 32 34 36 IN FLIGHT LIMIT TAXI, TAKEOFF LANDING LIMIT 500 510 520 530 A23WE Page 16 of 23 Maximum Weights 32, 33 Taxi and Ramp 498,000 lbs. 506,000 lbs. 34 512,000 lbs. 35 Take Off 496,000 lb s. 504,000 lbs. 510,000 lbs. Landing 368,000 lbs. 368,000 lbs. 368,000 lbs. Z e r o F u e l 36 338,000 lbs. 338,000 lbs. 338,000 lbs. Gear Jacking 498,000 lbs. 506,000 lbs. 512,000 lbs. Fuselage and Wing Jacki ng 340,000 lbs. 340,000 lbs. 340,000 lbs. Minimum Flight 233,700 lbs. 233,700 lbs. 233,700 lbs. Loadability 37 The aircraft will remain within the above approved weight and C.G. limits when the aircraft is loaded within the zero fu el weight and C.G. limits and the effect of: (1) landing gear retraction and (2) movement of crew and passenge rs from their assigned positions, is accounted for and the fuel is loaded (up to the maximum takeoff weight) and used in the approved sequence. For fuel dump valves operation, see NOTE 1.(d). Minimum Flight Crew For all flights: Pilot, Co-Pilot, and Flight Engineer Maximum Passengers See NOTE 5. Cargo See NOTE 37. Fuel Capacity Full Tank Capacity (lbs.) Structural Limits Usable Fuel Arm Tank (7.1 lb/gallon (6.7 lb/gallon) (Inches) 2L 27,181 25,650 1371.8 1 57,192 53,970 1157.2 1A 28,824 27,200 1122.6 3 57,192 53,970 1157.2 3A 28,824 27,200 1122.6 2R 27,181 25,650 1371.8 Total 226,395 213,640 Oil Capacity For –524 engines- 33 pounds/engine usable at 8.0 pounds/gallon with wing engines moment arm at 1050 inches and tail engine moment arm at 1979 inches. 32See NOTE 35. 33These weights vary as a function of modification standard and fuel management. See FAA Approved Flight Manual and Weight and Balance Manual. 34The weights listed in this column are applicable to L-1011-385-3 configured aircraft modified in accordance with S/B 093-51-016 to provide increased gross weight capability to 504,000 lbs. GTOW. 35The weights listed in this column are applicable to L-1011-385-3 configured modified in accordance with S/B 093-57-169 to provide increased gross weight capability to 510,000 GTOW. 36All weight in aircraft above this weight must fuel. For fuel dump valves operation see Note 1.(d). 37See NOTE 1.(a), 1.(b), and 1.(c). Page 17 of 23 A23WE Eligibility 38 Series Date Eligible Approved Serial Numbers Issued to Date 193V 39 April 16, 1979 1157, 1159, 1164, 1165, 1168, 1174 193G 40 January 17, 1980 1179, 1191 193J 40 April 14, 1980 1183 193Y 40 April 15, 1980 1176, 1177, 1181, 1184, 1185, 1186, 1188, 1194, 1195, 1197, 1208, 1210 193W 41 July 26, 1980 1189 193J 41 October 29, 1980 1196 193H 41 February 20, 1981 1202, 1206, 1207, 1209, 1216, 1218, 1246, 1247, 1248 293A 41 September 9, 1981 1217, 1219, 1220, 1229, 1238, 1249 193G 41 October 28, 1981 1222, 1233, 1250 293F 41 July 28, 1982 1235, 1236 293B 41 November 19, 1982 1239, 1240, 1241, 1242, 1243 DATA PERTINENT TO ALL MODELS (Except As Noted)