# TCDS A23WE: Lockheed Martin Corporation - Type: Type certificate data sheet - Status: Current - Holder: Lockheed Martin Corporation - Revision: 19 - Revised: January 11, 2010 - Product: Aircraft, Large Airplane - Certification basis: Part 21, Part 25, Part 26, Part 121 - Registered aircraft: 4, by the registry models matched to it (OpenAirDocs) - Data sheet PDF: https://openairdocs.org/files/sha256/08/1a/081a58b5cbaf28859f1840cf5a0617705e75f274c266817b45b1c848319fb8e8 - FAA DRS: https://drs.faa.gov/browse/excelExternalWindow/5342E492984E8616862576AC0055FEB3.0001 - Page: https://openairdocs.org/tcds/A23WE ## Models (4) As the data sheet lists them. - L-1011-385-1-14 - L-1011-385-3 - L-1011-385-1 - L-1011-385-1-15 ## 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. 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) APU Limits United Aircraft of Canada ST6L-73 Rotor Speeds (Ng) maximum Steady state 38,100 rpm (101.6%) Transient 38,500 rpm (102.6%) Turbine Gas Temperature Maximum during operation 1066° C (1950° F) During start for 2 seconds 760° C (1400° F) Lubricating Oil - PWA Specification No . 521. See P&WC Service Bulletin No. 9001. Airspeed Limits V mo/Mmo (Maximum Operating) I A S At Sea Level 350K At 10,000 feet 375K At 26,200 feet 375K (M = 0.9) At 42,000 feet 264K (M = 0.9) At 43,000 feet 256K (M = 0.9) V a (Maneuvering) See FAA Approved Airplane Flight Manual. Maximum Operating Altitude 42,000 ft. Models L-1011-385-1 and –1-14 43,000 ft. Models L-1011-385-1-15 and -3. Fuselage Datum 83 inches forward of fuselage nos e Models L-1011-385-1, -1-14 and -1-15. 183 inches forward of fu selage nose Models L-1011-385-3. MAC 293.5 inches (Leading edge of MAC - Arm 1143.0) 38See NOTE 35. 39Without extended wings and active controls system. 40With extended wings and active controls system. A23WE Page 18 of 23 Leveling Means One of two systems in each airplane: (1) Spirit level and leveling pads at Sta. 1355.0 (left main landing gear wheel well). (2) Plumb bob and grid plate at Sta. 1341.5 (left main landing gear wheel well). To ensure proper operation of the airplane, the movement of the control surface must be carefully controlled by proper rigging of the Flight Control Systems. The airplane must therefore be rigged in accordance with the following: Lockheed Martin Report LR-25234 dated 14 April 1972, "L-1011 Primary and Secondary Controls Rigging Proce dure Drawings," and applicable revisions. Certification Basis Issuance of a Type Certification for Model L-1011-385-1, and amended Type Certificates for Models L-1011-385-1-14, L-1011-385-1-15 and L-1011-385-3 are based upon compliance with the following: (1) FAR Part 25 dated February 1, 1965, "Airworthiness Standards: Transport Category Airplanes" including Amendments 25-1 through 25-18, and 25-20; FAR Parts 25.145(c), 25.683, 25. 1331, and 25.1333 of Amendment 25.23; FAR Part 25.1459 41 of Amendment 25-25. (2) FAR 36, "Noise Standard: Aircraft Type Certification," dated December 1, 1969. (3) Based on 14 CFR § 21.17(a) for new type certificates (TCs) , (or 14 CFR § 21.101(g) for changes to TCs), applicable provisions of 14 CFR part 26 are included in the certification basis. For any future 14 CFR part 26 amen dments, the holder of this TC must demonstrate compliance with the applicable secti ons. (4) Special Conditions #25-17-WE-6 Amendment #1 dated December 3, 1971, and Amendment #2 dated April 13, 1979, as applicable. 42 (5) Lockheed Martin Corporation L-1011-385-1, 193L aircraft series has demonstrated compliance with the requirements of "Special Conditions for Lockheed Martin Corporation Model L-1011-385-1, 193L Airplane," No. 25-55-WE-16, dated June 21, 1974. (6) Lockheed Martin Corporation L-1011-385-1, 193N, L-1011-385-1-15, 193T and L-1011- 385-15, 193U Aircraft Series have demonstrated compliance with the requirements of "Special Condition for Lockheed Martin Corporation Model L-1011-385-1 Airplane," No. 25-58-WE-17, dated Sept ember 26, 1974. Model L-1011-385-3 has complied with Amendment #1 dated April 13, 1979. (7) The Lockheed Martin Corporation L-1011-385-1, 193N and L-1011-385-1-15, 193T and L-1011-385- 1-15, 193U aircraft series have demonstrated compliance with the requirements of U.K. Special Conditions of Issue 3 dated August 30, 1974. L-1011-385-3, 193V and L-1011-385-3, 193G aircraft series have demonstrated compliance with the requirements of U.K. Special Conditions Issue 4 dated April 16, 1979. (8) Compliance has been found for the following regulations: 14 CFR §26.11, 26.43 and 26.45, (Amdt. No. 26-0 through 26-3). Production Basis Production Certificate No. 600. 41Compliance with FAR Part 25.1459(a)(7) requires incorporation of LAC Service Bulletin 093-31-012 "Instruments - Digital Flight Data Recorder and Underwater Locating Device - Replacement Of." 42For purposes of administration Special Airframe Conditions Nos. 4-15 contained in Special Conditions No. 25-17-WE-6, Amendment No. 1 dated 3 December 1971 (Docket No. 1005, Amendment No. 1) have been retitled and renumbered. These conditions are contained in the document entitled "SPECIAL CONDITIONS RETITLED AND RENUMBERED BY THE WESTERN REGION" dated 17 December 1971. Page 19 of 23 A23WE Required Equipment The basic required equipment as prescr ibed in the applicable airworthiness regulations (see Certification Basis) must be installed in the aircraft for certification. All of the required e quipment that must be installed as well as optional equipment installations approved by the FAA are contained in Chapter 2, "Weight and Balance Manual." Service Information Lockheed Martin Model L-1011-385-1, L-1011-385-1-14, L-1011-385-1-15 and L-1011-385-3 Structural Repair Manuals are FAA approved. All Lockheed Martin Service Bulletins and other servi ce information, when FAA approved, will carry a statement to that effect. Lockheed Martin L-1011 Maintenance Re view Board Report dated June 20, 1986, or later FAA approved revisions contai ns the basic minimum requirements for a maintenance program for continued airworthiness. NOTES: NOTE 1. (a) The weight of system unusable fuel and oil, as defined below, must be accounted for in the airplane operational empty weight, and is listed in th e FAA Approved Lockheed Martin Weight and Balance Manual specified for each airplane. System Fuel The weight of all fuel required to fill lines and tanks up to the zero fuel on the quantity gages in the most critical flight attitude. This incl udes the unusable tank and plumbing fuel as defined by FAR Part 25.959, and the usable but ungageable fuel in the tanks and plumbing. The L-1011-385-1 and L-1011-385-1-14 airplanes have 206 pounds (based on 6.7 pounds per gallon) of unusable fuel in the tanks and plumbing (see NOTE 1. (e)) and 569 pounds of usable but ungageable fuel in the plumbing (see NOTE 1.(e )). This 569 pounds of fuel must be included in the total unusable fuel to obtain the correct weight and C.G. for takeoff (see FAA Approved Weight and Balance Manual). The L-1011-385-1-15 airplane has 240 pounds (based on 6.7 pounds per gallon) of unusable fuel in the tanks and plumbing, a nd 609 pounds of usable but ungageable fuel in the tanks and plumbing. This 609 pounds of fuel must be included in the total usable fuel to obtain the correct weight and C.G. for take-off. (See FAA Approved Weight and Balance Manual). The L-1011-385-3 airplane has 238 pounds of (bas ed on 6.7 pounds per gallon) of unusable fuel in the tanks and plumbing and 774 pounds of usable but ungageable fuel in the plumbing. This 774 pounds of fuel must be included in the total usable fuel to obtain the correct weight and C.G. for takeoff. (See FAA Appr oved Weight and Balance Manual.) There are 570 pounds (based on 6.7 pounds per ga llon) of ungageable but usable fuel in the L-1011-385-1 and -1-14 tanks, 720 pounds of ungageable but usable fuel in the L-1011-385-1-15 tanks and 607 pounds of ungageable but usable fuel in the L-1011-385-3 tanks. This fuel is included in the tank fuel listed in this data sheet. System Oil The weight of oil remaining in the engine, accessories, lines and tanks after subtracting the oil in the tanks which is above zero gage le vels. The engine oil tank capacities shown elsewhere in this data sheet include only the usable oil for which the tanks must be placarded. NOTE 1. (b) The "unusable" fuel is th at amount of fuel in the tanks and plumbing which is unavailable to the engines under critical flight conditions as defined in FAR Part 25.959. This "unusable" fuel quantity of 206 pounds in the L-1011-385-1 and -1-14 airplanes (see NOTE 1.(e)), 240 pounds in the L-1011-385-1-15 airplanes and 238 pounds in the L-1011-385-3 airplanes is included in the System Fuel as indicated in NOTE 1.(c) and need not be accounted for separately. NOTE 1. (c) Fuel capacities shown in this data sheet as well as fuel loading fuel and usage procedures are dictated by structural design criteria, and to maintain airp lane C.G. within approved limits at completion of fuel uplift. Fuel must be loaded symmetrically about the airplane lateral C.G. within approved limits and in accordance with the Approved Airplane Flight Manual. A23WE Page 20 of 23 NOTE 1. (d) Fuel Jettison - The L-1011-385-1, -1-14 and -1-15 and -3 airplanes have been certificated for operation at maximum takeoff gross weight with and without the fuel jettison system. Refer to the FAA Approved Airplane Flight Manual for limita tions to be observed during operation without the fuel jettison system. Refer to the FAA Approve d Airplane Flight Manual for limitations to be observed during operation without the jettison sy stem and when dumping fuel with the jettison system. Fuel jettisoning may be terminated by th e Flight Crew at any time during the operation, and the total quantity of fuel not jettisoned must be included in the landing weight. The quantity of unjettisonable fuel remaining in th e tanks at automatic cutoff is as follows for fuel weight based on 6.7 pounds per gallon: Tank No . Fuel Quantity (lb.) 2L 3,900 1 7,600 3 7,600 2R 3,900 Manifold 300 In L-1011-385-15 and -3 airplanes, fuel cannot be jettisoned from tanks 1A and 3A. Some fuel may remain in these tanks after termination of the jettison operation. NOTE 1. (e) Until service kits 093/SK28001 and 093/SK28002 are installed in S/Ns 1013, the unusable fuel in the tanks and plumbing is 506 pounds, and the usable but ungageable fuel in the plumbing is 269 pounds. NOTE 2. Reserved. NOTE 3. Life Limitations. (a) All life limited components with the exception of engine and APU components (see NOTE 3.(b) and Note 3(c)) are listed in FAA Approved Lockheed Martin Report LR-27324 and must be replaced as indicated therein. FAA Approved Lockheed Martin Report LR-27324, and FAA approved revisions thereto, are hereby incorporated as part of this Type Certificate Data Sheet A23WE. Copies of the above LR-27324 report may be obtained from the manufacturer: Lockheed Martin Aircraft & Logistics Centers Out of Production Support 120 Orion Street Greenville, South Carolina 29605 (b) Engine life limited parts are identified in RB211-22B and RB211-524 series Time Limits Manual T- 211(22B)-1RR and T-211(524)-3RR, respectively. For RB211-22B Fan Disc Life Limits see Rolls Royce ALERT Service Bulletin 72-A2655. (c) APU life limited parts are identified in "Un ited Technologies Hamilton Maintenance and Overhaul Recommendations for the Hamilton Standard L- 1011 Air Conditioning, Starting, and APU Systems" R4137. NOTE 4. (a) Approved fuels and fuel additives are liste d in the approved Rolls Royce Operating Instructions, Publication Reference F-RB211-T and F-211(524B)-T. (b) Approved oils are listed in the approved Rolls Royce Operating Instructions, Publication Reference F-RB211-T and F-211(524B)-T. Alternate brand oils are permitted when authorized by CAA approved Rolls Royce Service Bulletin. NOTE 5. (a) All replacement seats (crew, passenger a nd lounge), although they may comply with TSO-C39, must also be demonstrated to comply with FA R Part 25.785. Other installations, such as berths, compartments or items of mass which could cr eate a hazard to the safety of passengers and crew must also be demonstrated to meet th e applicable requirements of FAR Part 25.785. (b) L-1011-385-1, -1-14 and -1-15 airplanes. With three Type A passenger doors and one Type 1 Page 21 of 23 A23WE passenger door per side of airc raft, the maximum eligible number of passengers is 345 demonstrated for emergency evacuation and 362 by analysis. With four Type A passenger doors per side of aircraft, the maximum eligible number is 400 demonstrated for emergency evacuation. See FAA approved interior arrangement drawings for maximum passenger capacities approved for each series eligible aircraft when delivered. Thes e drawings are contained in the FAA Approved Lockheed Martin Report LR-25097. (c) L-1011-385-3 airplanes. Maximum eligible numbe r of passengers is 315 with three Type A passenger doors per side of the aircraft. See FAA a pproved interior arrangement drawings for maximum passenger capacities approved for each series eligib le aircraft when delivered. These drawings are contained in the FAA Approved Lockheed Martin Report LR-25097. NOTE 6. DELETED. NOTE 7. Deleted on June 20, 1974, when S/N 1006 ai rcraft was added to 193A series eligible. NOTE 8. Cockpit Voice Recorder (CVR) operates only afte r engine start, and the ground cart disconnected, on the L1011-385-1, 193K, S/Ns 1024 and 1032 aircraft only. NOTE 9. The L-1011-385-1, 193K, S/Ns 1024 and 1032 aircraft have been accepted for export to the United Kingdom with Digital Flight Data Recorder (DFD R) which has not demonstrated compliance with the requirements of FAR Part 25.1309(a). NOTE 10. Engine Installation "Intermix" configurations may be utilized in accordance with Lockheed Martin Report LR-28617, applicable FAA approved Service Bulle tins, and Appendices of FAA Approved Airplane Flight Manuals. NOTE 11. DELETED. NOTE 12. Rolls Royce RB211-22B engines must be installed during production or in accordance with Lockheed Martin Service Bulletin No. 093-71-009. NOTE 13. DELETED. NOTE 14. DELETED. NOTE 15. Automatic Pilot-Flight Director System in cluding approach and automatic landing to Category I, Category II, Category IIIA Weather Minima in acco rdance with FAR Part 25.1329, Advisory Circulars AC 25.1329-1A dated October 1, 1965, AC-20- 57A dated January 12, 1971, AC 120-28A dated December 14, 1971, and AC 120-29 dated September 25, 1970. Automated Navigation in Th ree Systems configurations: (a) Dual area navigation systems (ARINC 582) (A dvisory Circular AC 90-45A dated September 15, 1975). (b) Dual area navigation systems (ARINC 582) with dual inertial reference systems (ARINC 571) (Advisory Circulars AC 90-45A dated Septem ber 15, 1975, and AC 25-4 dated February 18, 1966). (c) Dual area navigation system (ARINC 582) w ith triple inertial reference systems (ARINC 571) (Advisory Circulars 90-45A dated Septem ber 15, 1975, AC 25-4 dated February 18, 1966). NOTE 16. DELETED. NOTE 17. DELETED. A23WE Page 22 of 23 NOTE 18. These Lockheed Martin Corporation L- 1011 series airplanes with serial number 1052 and above (with exception of airplanes in the 193L series) which incorporated the FAA Approved Type Design modifications specified in the FAA Sealed L-1011-385-1 Drawing List Supplement titled "FAA List for Spare Engine Pod (SEP) and Spar e Engine Pod (SEP) Pylon Only Peculiar - Type Design" are eligible to include the Spare Engi ne Pod (SEP) or the Spare Engine Pod (SEP) Pylon Only installation and must be operated in accordance with the FAA Approved Airplane Flight Manual LR-25925, Appendix 9, and FAA Approved Lockheed Martin Weight and Balance Manual. NOTE 19. The glide slope deviation warning (part of the ground proximity warning system, Sundstrand P/N 965-0376-070), was evaluated to the standard set forth in TSO-C92b and FAR Part 121.360(f). NOTE 20. DELETED. NOTE 21. (a) Lockheed Martin Corporation L-1011-385-1 aircraft with improved aircraft loadability with respect to the forward center of gravity limit must be equipped with 36 X 11-16 22 ply; rating nose landing gear tires. (b) Lockheed Martin Corporation L-1011- 385-1, -1-14 and -1-15 aircraft must be equipped with main landing gear wheels, brakes and tires, and nose landing gear wheels and tires as identified in the latest revisions of Service Bulletins 093-51-010, 093-51-014, 093-51-015, 093-51-016, 093-51-022, 093-51-033, 093-51-029 and 093-51-031 for their applicable and listed brake re lease maximum gross takeoff weight. NOTE 22. DELETED. NOTE 23. Modifications in accordance with F AA approved Lockheed Martin Corporation Service Bulletin 093-51-010 constitutes an FAA approved conversion of the Model L-1011-385-1 aircraft to Model L-1011-385-1-14 aircraft. NOTE 24. Modifications in accordance with F AA approved Lockheed Martin Corporation Service Bulletin 093-28-038 constitutes an FAA approved conversion of the Model L-1011-385-1-14 aircraft to Model L-1011-385-1-15 aircraft. NOTE 25. There are no RB.211-22C engines in existence; however, -22C ratings and limits are retained on this TCDS to permit operational use of FAA certified takeoff performance based on -22C takeoff ratings as shown in the FAA Approved L-1011 Airplane Flight Manual (Appendix 8 to Lockheed Martin Report LR-25925) for aircraft equipped with -22B engines. The FAA approved Flight Manual for -22C engine (Lockheed Martin Report LR-25225) is discontinued. NOTE 26. DELETED. NOTE 27. The APU is approved for us e as an alternate in-flight source of electric and pneumatic power. NOTE 28. DELETED. NOTE 29. DELETED. NOTE 30. The FAA approved Airplane Flight Manual for Lockheed Martin Corporation Model L-1011-385-3 (193V series airplanes) is Lo ckheed Martin Report L-25925; Log of Pages DL5. There is no revision service for this Airplane F light Manual and, therefore, in the event of the return to the U.S. of the L-1011-385-3 (193V se ries airplanes), Lockheed Martin Corporation should be contacted for an appropriate cu rrent FAA Approved Airplane Flight Manual. NOTE 31. A functional inspection at intervals not to exceed 5000 hours time in service must be conducted on those airplanes configured with the Rolls Royce RB.211-524 series engines utilizing the bleed air minimum pressure control ejector system. NOTE 32. DELETED. Page 23 of 23 A23WE NOTE 33. Applicable to those aircraft which comply with FAA approved February 9, 1981, Drawing List L-1011-385-3 and derivatives dated January 15, 1981, with RB.211-524B4-02 Engines, Ground Proximity Warning System, Auto Braking Sy stem, Extended Wings, Active Control System and Digital Horizontal Situation Indicator. NOTE 34. DELETED. NOTE 35. Those L-1011-385-3 aircraft manufactured wit hout extended wings and active control system may be modified to this configuration by incorpora tion of FAA approved Lockheed Martin Service Bulletins 093-57-140 and 093-22-122, and are FAA approved to the higher maximum weights as noted on this type certificate data sheet. NOTE 36. DELETED. NOTE 37. Cargo compartment loading limitations are as specified by the appropriate FAA Approved Airplane Flight Manuals and FAA appr oved Weight and Balance Manuals. NOTE 38. Modification in accordance with FAA a pproved Lockheed Martin Corporation Service Bulletins 093-51-029, and 093-51-030 R1 constitute FAA approved conversions of Model L-1011-385-1 aircraft Serial Numbers 1004 to 1012 and 1013 to 1051 respectively, to Model L-1011-385-1-14 aircraft. NOTE 39. DELETED. ....END.... ``` ## ADs (156, 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 2023-10-02](https://openairdocs.org/ad/2023-10-02): Indicating/Recording System, Navigation · Boeing 18, 23, 35 and 1,060 more. Effective May 26, 2023 - [AD 2015-11-02](https://openairdocs.org/ad/2015-11-02): Fuselage · Lockheed Martin L-1011-385-1, L-1011-385-1-14, L-1011-385-1-15 and 1 more. Effective Jul 14, 2015 - [AD 2014-20-08](https://openairdocs.org/ad/2014-20-08): Wings · Lockheed Martin L-1011-385-1, L-1011-385-1-14, L-1011-385-1-15 and 1 more. Effective Nov 7, 2014 - [AD 2013-15-18](https://openairdocs.org/ad/2013-15-18): Standard practices/structures; Doors; Fuselage; Wings · Lockheed Martin L-1011-385-1, L-1011-385-1-14, L-1011-385-1-15 and 1 more. Effective Oct 1, 2013 - [AD 2012-05-06](https://openairdocs.org/ad/2012-05-06): Fuselage · Lockheed Martin L-1011-385-1, L-1011-385-1-14, L-1011-385-1-15 and 1 more. Effective May 10, 2012 - [AD 2011-27-02](https://openairdocs.org/ad/2011-27-02): Wings · Lockheed Martin L-1011-385-1, L-1011-385-1-14, L-1011-385-1-15 and 1 more. Effective Feb 3, 2012 - [AD 2008-11-02 R1](https://openairdocs.org/ad/2008-11-02-R1): Fuel Tank systems · Lockheed Martin L-1011-385-1, L-1011-385-1-14, L-1011-385-1-15 and 1 more. Effective Dec 18, 2009 - [AD 2008-12-17](https://openairdocs.org/ad/2008-12-17): Fuel level control switch · Lockheed Martin L-1011-385-1, L-1011-385-1-14, L-1011-385-1-15 and 1 more. Effective Jul 23, 2008 - [AD 2006-25-11](https://openairdocs.org/ad/2006-25-11): C112 harness clamp assembly · Lockheed Martin L-1011-385-1, L-1011-385-1-14, L-1011-385-1-15 and 1 more. Effective Jan 16, 2007 - [AD 2004-22-01](https://openairdocs.org/ad/2004-22-01): Cargo restraint strap assemblies · Cargo restraint straps (Airline Container Manufacturing STC ST01004NY). Effective Dec 1, 2004 - [AD 2004-09-28](https://openairdocs.org/ad/2004-09-28): Corrosion prevention and control program · Lockheed Martin L-1011-385-1, L-1011-385-1-14, L-1011-385-1-15 and 1 more. Effective Jun 17, 2004 - [AD 2003-14-21](https://openairdocs.org/ad/2003-14-21): Engine turbine cooling air overheat monitoring panel · Lockheed Martin L-1011-385-1, L-1011-385-1-14, L-1011-385-1-15 and 7 more. Effective Aug 25, 2003 - [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 2001-08-27](https://openairdocs.org/ad/2001-08-27): Windshield Heat Wire Bundle · Lockheed Martin L-1011-385-1, L-1011-385-1-14, L-1011-385-1-15 and 1 more. Effective May 14, 2001 - [AD 2000-21-01](https://openairdocs.org/ad/2000-21-01): Structural Elements · Lockheed Martin L-1011-385-1, L-1011-385-1-14, L-1011-385-1-15 and 1 more. Effective Nov 24, 2000 - [AD 2000-16-08](https://openairdocs.org/ad/2000-16-08): Canted Pressure Bulkhead · Lockheed Martin L-1011-385-1, L-1011-385-1-14, L-1011-385-1-15 and 1 more. Effective Sep 20, 2000 - [AD 2000-10-20](https://openairdocs.org/ad/2000-10-20): Fuselage Skin · Lockheed Martin L-1011-385-1, L-1011-385-1-14, L-1011-385-1-15 and 1 more. Effective Jul 12, 2000 - [AD 2000-08-20](https://openairdocs.org/ad/2000-08-20): High Pressure Bleed Valve · Lockheed Martin L-1011-385-1, L-1011-385-1-14, L-1011-385-1-15 and 1 more. Effective Jun 5, 2000 - [AD 99-13-08 R1](https://openairdocs.org/ad/99-13-08-R1): Rear Spar · Lockheed Martin L-1011-385-1, L-1011-385-1-14, L-1011-385-1-15 and 1 more. Effective May 22, 2000 - [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 99-24-12](https://openairdocs.org/ad/99-24-12): AFM - Fuel and Electrical System · Lockheed Martin L-1011-385-1, L-1011-385-1-14, L-1011-385-1-15 and 1 more. Effective Jan 4, 2000 - [AD 99-17-13](https://openairdocs.org/ad/99-17-13): Actuator Pins and Bushings of Horizontal Stabilizer · Lockheed Martin L-1011-385-1, L-1011-385-1-14, L-1011-385-1-15 and 1 more. Effective Sep 24, 1999 - [AD 99-09-14](https://openairdocs.org/ad/99-09-14): Main Frame Inspection · Lockheed Martin L-1011-385-1, L-1011-385-1-14, L-1011-385-1-15 and 1 more. Effective Jun 1, 1999 - [AD 99-08-20](https://openairdocs.org/ad/99-08-20): Bulkhead Fuselage Inspection · Lockheed Martin L-1011-385-1, L-1011-385-1-14, L-1011-385-1-15 and 1 more. Effective May 19, 1999 - [AD 99-07-05](https://openairdocs.org/ad/99-07-05): Elevator Assembly Inspection · Lockheed Martin L-1011-385-1, L-1011-385-1-14, L-1011-385-1-15 and 1 more. Effective Apr 30, 1999 - [AD 99-02-05](https://openairdocs.org/ad/99-02-05): Primary and Secondary Drive Shafts · Lockheed Martin L-1011-385-1, L-1011-385-1-14 and L-1011-385-1-15. Effective Feb 19, 1999 - [AD 98-10-14](https://openairdocs.org/ad/98-10-14): Rear Spar Fatigue Cracking · Lockheed Martin L-1011-385-1, L-1011-385-1-14, L-1011-385-1-15 and 1 more. Effective Jun 19, 1998 - [AD 98-09-23](https://openairdocs.org/ad/98-09-23): Bearing Failure · Lockheed Martin L-1011-385-1, L-1011-385-1-14, L-1011-385-1-15 and 1 more. Effective Jun 3, 1998 - [AD 97-14-07](https://openairdocs.org/ad/97-14-07): High Speed Gearbox · Lockheed Martin L-1011-385-1, L-1011-385-1-14, L-1011-385-1-15 and 1 more. Effective Aug 7, 1997 - [AD 95-26-15 R1](https://openairdocs.org/ad/95-26-15-R1): Traffic Alert and Collision Avoidance Systems · Airbus A300 B2-1A, A300 B2-1C, A300 B2-203 and 159 more. Effective Dec 26, 1996 - [AD 96-02-06](https://openairdocs.org/ad/96-02-06): AFM - Limitations - Windshear · BAE Systems Avro 146-RJ100A, Avro 146-RJ70A, Avro 146-RJ85A and 59 more. Effective Feb 26, 1996 - [AD 95-21-07](https://openairdocs.org/ad/95-21-07): SB Lockheed Doc. LR31889 Sec 7.2 · Lockheed Martin L-1011-385-1, L-1011-385-1-14, L-1011-385-1-15 and 1 more. Effective Nov 17, 1995 - [AD 95-21-16](https://openairdocs.org/ad/95-21-16): Main Landing Gear Actuator Attach Pin Assembly · Lockheed Martin L-1011-385-1, L-1011-385-1-14, L-1011-385-1-15 and 1 more. Effective Nov 17, 1995 - [AD 95-17-03](https://openairdocs.org/ad/95-17-03): Aft Pressure Bulkhead · Lockheed Martin L-1011-385-1, L-1011-385-1-14, L-1011-385-1-15 and 1 more. Effective Aug 25, 1995 - [AD 95-10-17](https://openairdocs.org/ad/95-10-17): Fuselage Frames · Lockheed Martin L-1011-385-1, L-1011-385-1-14, L-1011-385-1-15 and 1 more. Effective May 23, 1995 - [AD 95-06-51](https://openairdocs.org/ad/95-06-51): Flexible Fuel Hose · Lockheed Martin L-1011-385-1, L-1011-385-1-14, L-1011-385-1-15 and 1 more. Effective Apr 21, 1995 - [AD 94-26-09](https://openairdocs.org/ad/94-26-09): Ram Air Turbine · Lockheed Martin L-1011-385-1, L-1011-385-1-14, L-1011-385-1-15 and 1 more. Effective Feb 3, 1995 - [AD 94-23-07](https://openairdocs.org/ad/94-23-07): Flight Controls, Doors, Horizontal Stabilizers · Lockheed Martin L-1011-385-1, L-1011-385-1-14, L-1011-385-1-15 and 1 more. Effective Dec 21, 1994 - [AD 94-14-03](https://openairdocs.org/ad/94-14-03): Water Heaters and Coffee Makers · Airbus A300 B2-1A, A300 B2-1C, A300 B2-203 and 130 more. Effective Aug 1, 1994 - [AD 94-05-01](https://openairdocs.org/ad/94-05-01): Collector SB-Inspect for Cracks · Lockheed Martin L-1011-385-1, L-1011-385-1-14, L-1011-385-1-15 and 1 more. Effective Apr 4, 1994 - [AD 94-03-09](https://openairdocs.org/ad/94-03-09): Flap Vane Lugs · Lockheed Martin L-1011-385-1, L-1011-385-1-14, L-1011-385-1-15 and 1 more. Effective Mar 21, 1994 - [AD 93-24-16](https://openairdocs.org/ad/93-24-16): Protective Breathing Equipment · Airbus A300 B2-1A, A300 B2-1C, A300 B2-203 and 149 more. Effective Feb 4, 1994 - [AD 94-01-04](https://openairdocs.org/ad/94-01-04): Traffic Alert and Collision Avoidance System · Airbus A300 B4-601, A300 B4-603, A300 B4-605R and 136 more. Effective Feb 4, 1994 - [AD 94-01-05](https://openairdocs.org/ad/94-01-05): Traffic Alert and Collision Avoidance System II Processors · Airbus A340-211, A340-212, A340-213 and 85 more. Effective Feb 4, 1994 - [AD 94-01-06](https://openairdocs.org/ad/94-01-06): Traffic Alert and Collision Avoidance System II Processors · Airbus A300 B2-1A, A300 B2-1C, A300 B2-203 and 176 more. Effective Feb 4, 1994 - [AD 93-24-12](https://openairdocs.org/ad/93-24-12): Cargo Door Latching Mechanism · Lockheed Martin L-1011-385-1, L-1011-385-1-14, L-1011-385-1-15 and 1 more. Effective Jan 10, 1994 - [AD 92-16-19](https://openairdocs.org/ad/92-16-19): Stabilizer Lower Actuator Pins · Lockheed Martin L-1011-385-1, L-1011-385-1-14, L-1011-385-1-15 and 1 more. Effective Sep 1, 1992 - [AD 91-10-01](https://openairdocs.org/ad/91-10-01): Traffic Alert and Collision Avoidance Systems · ATR - GIE Avions de Transport Régional ATR42-200, ATR42-300, 727-100 Series and 28 more. Effective Mar 10, 1992 - [AD 91-23-12](https://openairdocs.org/ad/91-23-12): Main Landing Gear Braking Effectiveness · Lockheed Martin L-1011-385-1, L-1011-385-1-14, L-1011-385-1-15 and 1 more. Effective Dec 9, 1991 All 156: https://openairdocs.org/tcds/A23WE/ads.md ## Registered aircraft by registry model (OpenAirDocs) - [Lockheed L-1011-385-1](https://openairdocs.org/model/lockheed-l-1011-385-1): 2 aircraft (registry code 5265010) - [Lockheed L-1011-385-1-15](https://openairdocs.org/model/lockheed-l-1011-385-1-15): 1 aircraft (registry code 5265015) - [Lockheed L-1011-385-3](https://openairdocs.org/model/lockheed-l-1011-385-3): 1 aircraft (registry code 5265020) - [Lockheed L-1011-385-1-14](https://openairdocs.org/model/lockheed-l-1011-385-1-14): 0 aircraft (registry code 5265013) ## STCs approved under this data sheet (224, first 50) - [STC ST12461IB](https://openairdocs.org/stc/ST12461IB): Installation of Cockpit Voice Recorder with optional RIPS Upgrade. Mid- Canada Mod Center - [STC ST00952LA](https://openairdocs.org/stc/ST00952LA): Installation of Mass Systems fire extinguisher cartridges as replacements for Kidde fire extinguisher cartridges in fire extinguisher bottles.. AMETEK AMERON LLC d/b/a MASS Systems - [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 SA2473NM](https://openairdocs.org/stc/SA2473NM): Installation of food service and duty free sales carts.. Safran Cabin Inc. - [STC SA3076WE](https://openairdocs.org/stc/SA3076WE): Installation of a thirteen inch cool beverage cart. (L-1011-385-1-15 193T-Cathay Pacific Service). Safran Cabin Inc. - [STC SA3082NM](https://openairdocs.org/stc/SA3082NM): Installation of heated food service cart.. Safran Cabin Inc. - [STC SA3171NM](https://openairdocs.org/stc/SA3171NM): Installation of cart stowage modules.. Safran Cabin Inc. - [STC SA3315WE](https://openairdocs.org/stc/SA3315WE): Installation of 16-inch beverage cart Model 954000-225 in passenger main deck and/or lower galley service area. (L-1011-385-1-15 1935-Saudia Series). Safran Cabin Inc. - [STC SA3316WE](https://openairdocs.org/stc/SA3316WE): Installation of a 16-inch coach class serving cart Model953000-249, and 7805000-201, -203, -205, -207 in the passenger main deck coach areas and/or lower galley service areas.. Safran Cabin Inc. - [STC SA3317WE](https://openairdocs.org/stc/SA3317WE): Installation of 13-inch waste cart Model 956000-231, -233, -235, -237, -239 in passenger main deck and/or lower galley service areas.. Safran Cabin Inc. - [STC SA5837NM](https://openairdocs.org/stc/SA5837NM): Installation of stowage closet P/N 16500-1.. Safran Cabin Inc. - [STC SA3152NM](https://openairdocs.org/stc/SA3152NM): Installation of Floor Proximity Emergency Escape Path Marking System. Bruce Aerospace Inc. - [STC ST00646CH](https://openairdocs.org/stc/ST00646CH): Installation of a single or dual Honeywell/Trimble HT9100 global navigation system.. Amphenol Cable and Interconnect Technologies Inc. - [STC ST01381CH](https://openairdocs.org/stc/ST01381CH): Installation of Honeywell TCAS II with Change 7.0 software.. Amphenol Cable and Interconnect Technologies, Inc. - [STC ST01923CH](https://openairdocs.org/stc/ST01923CH): Installation of a Honeywell Enhanced Ground Proximity Warning System.. Amphenol Cable and Interconnect Technologies, Inc. - [STC SA2147SO](https://openairdocs.org/stc/SA2147SO): Installation of emergency escape path lighting system.. Astronics Luminescent Systems Inc - [STC SA8011NM](https://openairdocs.org/stc/SA8011NM): Modification to include provisions only for carriage and launch of Pegasus SIV satellite insertion vehicle (SIV).. Orbital Sciences Corporation - [STC ST00032SE](https://openairdocs.org/stc/ST00032SE): Installation of Mark VII ground proximity and windshear warning system.. Honeywell International Inc - [STC ST00894AT](https://openairdocs.org/stc/ST00894AT): Installation of a RDR-4B Weather Radar/Windshear System.. Honeywell International Inc - [STC SA7379SW](https://openairdocs.org/stc/SA7379SW): Remanufacture of Hamilton Standard ECU heat exchanger P/N 733949.. Honeywell International Inc. - [STC SA7423SW](https://openairdocs.org/stc/SA7423SW): Remanufacture of Hamilton Standard APU Oil Cooler Assembly, P/N 738719-2, by replacing core assembly. Honeywell International Inc. - [STC SA4145WE](https://openairdocs.org/stc/SA4145WE): A passenger entertainment system (Bell and Howell video projection system) installed.. Burrana Inc. - [STC SA3474WE](https://openairdocs.org/stc/SA3474WE): Installation of aircraft video system.. Burrana Inc. - [STC SA1085NW](https://openairdocs.org/stc/SA1085NW): A passenger entertainment system (Bell & Howell Video Project System ) installed. Burrana Inc. - [STC SA1100NM](https://openairdocs.org/stc/SA1100NM): A Trans Com Video Projection System. Burrana Inc. - [STC SA1346NM](https://openairdocs.org/stc/SA1346NM): A Trans Com Video Projection System 985-0028-001 is installed. Burrana Inc. - [STC SA158NE](https://openairdocs.org/stc/SA158NE): Installation of Inflight Services video projection system, L-1011-500 BWIA, P/N 105-D-917.. Burrana Inc. - [STC SA1975NM](https://openairdocs.org/stc/SA1975NM): Installation of Hughes-Avicom International Video Projection System No. 492185-0001. Burrana Inc. - [STC SA1996NM](https://openairdocs.org/stc/SA1996NM): Installation of Hughes-Avicom Video Projection System No. 492207-0001. Burrana Inc. - [STC SA120NE](https://openairdocs.org/stc/SA120NE): Installation of a Inflight Motion Picture video projection system L1011-500, P/N 105-D-874.. Burrana Inc. - [STC SA5899NM](https://openairdocs.org/stc/SA5899NM): Installation of World Auxiliary Power Company Onboard airstair in the forward mid passenger doorway.. Dow Aero Logistics LLC - [STC SA2993SO](https://openairdocs.org/stc/SA2993SO): Installation of a replacement coalescer filter P/N 23TD11.. Purolator Facet, Inc - [STC SA4965NM](https://openairdocs.org/stc/SA4965NM): Installation of galley carts.. Commercial Aircraft Equipment - [STC ST00393NY](https://openairdocs.org/stc/ST00393NY): Installation of NNAL 527 Stretcher System. Avmax Aviation Services Inc - [STC ST00881WI-D](https://openairdocs.org/stc/ST00881WI-D): Modification of a TCAS II system installation to Change 7.0 or Change 7.1. Rockwell Collins Inc - [STC SA1360NM](https://openairdocs.org/stc/SA1360NM): A Video Projection System is installed. Burrana Inc. - [STC SA7076NM](https://openairdocs.org/stc/SA7076NM): Installation of Stretcher Carrier.. Air Medic LLC - [STC ST02540LA](https://openairdocs.org/stc/ST02540LA): Installation of Telair International LLC light weight P/Ns PMC100 and PAG100 series cargo pallets. Telair International LLC - [STC ST02489LA](https://openairdocs.org/stc/ST02489LA): Installation of Telair International Inc. light weight LD3 (NAS3610 / SAE36100 - 2K2) cargo container P/N LD3100-31000ZZZ. Telair International LLC - [STC ST407CH](https://openairdocs.org/stc/ST407CH): Install main deck cargo handling system.. Telair US LLC - [STC ST514CH](https://openairdocs.org/stc/ST514CH): Install main deck cargo handling system.. Telair US LLC - [STC ST515CH](https://openairdocs.org/stc/ST515CH): Install lower lobe cargo handling system.. Telair US LLC - [STC ST09112SC](https://openairdocs.org/stc/ST09112SC): Installation of Honeywell/Racal MCS-6000 SATCOM system with Ball Aerospace antenna.. LB Aircraft Engineering Inc - [STC ST09113SC](https://openairdocs.org/stc/ST09113SC): Installation of Collins TCAS-94 traffic alert and collision avoidance system (TCAS II) with Sextant IVSI and dual Collins TDR-94 Mode S transponders.. LB Aircraft Engineering Inc - [STC ST09114SC](https://openairdocs.org/stc/ST09114SC): Installation of a Teledyne digital flight data recorder.. LB Aircraft Engineering Inc - [STC ST09115SC](https://openairdocs.org/stc/ST09115SC): Installation of a floor path escape lighting.. LB Aircraft Engineering Inc - [STC ST09232SC](https://openairdocs.org/stc/ST09232SC): Installation of an MCS-3000 Satellite Communications System and a Tecom T-4000 Top Mounted High Gain Antenna.. LB Aircraft Engineering Inc - [STC ST03483AT](https://openairdocs.org/stc/ST03483AT): Installation of a Portable Beverage Dispensing System, P/N B43-FA-001.. Dynamo Beverage Company, USA, L.L.C. - [STC SA6072NM](https://openairdocs.org/stc/SA6072NM): Installation of video entertainment system.. Rockwell Collins Inc - [STC ST01635WI-D](https://openairdocs.org/stc/ST01635WI-D): Modification of Rockwell Collins, Inc. VHF-4000 and VHF-4000E installations. Rockwell Collins Inc All 224: https://openairdocs.org/tcds/A23WE/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.