# TCDS A22WE: The Boeing Company - Type: Type certificate data sheet - Status: Current - Holder: The Boeing Company - Revision: 13 - Revised: April 30, 2018 - Product: Aircraft, Large Airplane - Certification basis: Part 25 - Registered aircraft: 149, by the registry models matched to it (OpenAirDocs) - Data sheet PDF: https://openairdocs.org/files/sha256/27/a9/27a94e27d5e0cdaffbf8d46a33699b1986850ebdb29f696189270195f3d49a53 - FAA DRS: https://drs.faa.gov/browse/excelExternalWindow/2CF3306625F6FD1586258281006F6D29.0001 - Page: https://openairdocs.org/tcds/A22WE ## Models (11) As the data sheet lists them. - DC-10-40 - MD-11 - MD-10-30F - DC-10-10F - DC-10-30 - DC-10-30F (KC-10A KDC-10) - DC-10-10 - MD-10-10F - DC-10-40F - DC-10-15 - MD-11F ## What the data sheet says From the PDF's text layer, line by line; tables lose their columns. The PDF is the record. ```text The following table identifies the current revision of each page of the Data Sheet: Page No. 1 2 3 4 5 6 7 8 9 10 11 12 13 14 15 16 17 18 19 Rev. No 13 10 10 10 10 10 10 10 10 10 10 10 10 10 11 11 11 10 11 Page No. 20 21 22 23 24 25 26 27 28 29 30 31 32 33 34 35 36 37 38 Rev. No 10 10 10 10 10 10 11 12 11 12 10 11 10 10 10 11 11 10 13 Page No. 39 40 41 42 43 44 45 46 47 48 49 50 Rev. No. 13 13 13 10 10 11 10 11 10 10 11 11 DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION A22WE Revision 13 BOEING DC-10-10 DC-10-40 DC-10-30 DC-10-30F (KC-10A, KDC-10) DC-10-10F DC-10-40F DC-10-15 MD-11 MD-11F MD-10-10F MD-10-30F April 30, 2018 TYPE CERTIFICATE DATA SHEET A22WE This data sheet which is part of Type Certificate No. A22WE prescribes conditions and limitations under which the products for which the Type Certificate was issued meet the airworthiness requirements of the Federal Aviation Regulations. Type Certificate Holder: The Boeing Company 4000 Lakewood Boulevard Long Beach, California 90808 Type Certificate Ownership Record: McDonnell Douglas Corporation, Long Beach, California, merged with The Boeing Company effective January 1, 2010. Transferred type certificate A22WE to The Boeing Company on September 27, 2010. I - Model DC-10-10 (Transport Aircraft), Approved July 29, 1971 Engines: 3 General Electric CF6-6D, CF6-6D1, CF6-6D1A, CF6-6K or CF6-6K2 Turbofan Engines. (CF6-6D and CF6-6K engines may be intermixed in accordance with Appendix XXII of the applicable FAA Approved Airplane Flight Manual. CF6-6D1 and CF6-6D1A engines may be intermixed in accordance with page 2.1 of Section IVB of applicable FAA Approved Airplane Flight Manual.) Fuel: See NOTE 4. Oil: See NOTE 5. Engine Limits: Takeoff Thrust. Sea Level, CF6-6D/-6K CF6-6D1 CF6-6D1A/-6K2 Static (5 min) - flat to 88oF (CF6-6D/-6K) and to 84oF (CF6-6D1/-6D1A/-K2) 39,300 lb. 40,300 lb. 40,900 lb. Maximum Continuous (flat to 77oF) 37,500 lb. 37,500 lb. 37,500 lb. A22WE Page 2 of 50 I - Model DC-10-10 (Transport Aircraft), Approved July 29, 1971 (cont’d) Engine Limits: (cont’d) Maximum permissible engine rotor operating speeds N1 (Low Compressor) 3810 rpm (111%) N2 (High Compressor) 9925 rpm (101%) Maximum permissible engine temperature Turbine exhaust gas temperatures at turbine outlet Take off (5 min.) 1670oF (910oC) Maximum Continuous 1616oF (880oC) Maximum Acceleration (2 min.) 1697oF (925oC) Starting (Max. Transient for 40 sec.) 1652oF (900oC) (Max. No Time Limit) 1382oF (750oC) Maximum permissible oil outlet temperature Continuous operation 320oF (160oC) Transient operation 1 347oF (175oC) APU Limits: AiResearch TSCP700-4B (if installed) Power Rating Maximum at sea level 189 hp Rotor Speeds Low pressure speed (N1) 31,570 rpm (110%) High pressure speed (N2) 38,830 rpm (110%) Exhaust Gas Temperature Maximum during operation 1085oF (585oC) Maximum indicated temperature during each starting cycle 1085oF (585oC) Airspeed Limits: (CAS) VMO / MMO (Maximum Operating) With SB 37-87 Without SB 37-87 At Sea Level 350K 350K At 10,000 ft 350K 376K At 24,820 ft 350K 376K (M=0.88) At 28,310 ft 350K (M=0.88) 350K (M=0.88) At 42,000 ft 258K (M=0.88) 258K (M=0.88) VA (Maneuvering) See FAA Approved Airplane Flight Manual VFE Flap Position (Inboard) 5o 260K (M = 0.51) 15o 250K (M = 0.51) 20o 233K (M = 0.51) 25o 214K (M = 0.51) 35o 187K (M = 0.51) 50o 171K (M = 0.51) 1 Transient operation above 320°F (160°C) is limited to 15 minutes. Page 3 of 50 A22WE I - Model DC-10-10 (Transport Aircraft), Approved July 29, 1971 (cont’d) Airspeed Limits: (cont’d) (CAS) VSLAT (Slat Operating) Takeoff and Approach: Flap Position (Inboard) 5o 260K (M = 0.51) 15o 250K (M = 0.51) 25o 214K (M = 0.51) Landing Flap Position (Inboard) 35o 187K (M = 0.51) 50o 171K (M = 0.51) Autoslat Flaps retracted 260K (M = 0.51) VLO (Landing Gear) Retraction 230K (M = 0.70) Extension 260K (M = 0.70) VLE (Landing Gear Extended) 300K (M = 0.70) V (Landing light extension) Maximum speed extension retraction, or extended position VMO/MMO V (Fuel Dump) 325K up to 28,000 feet M = 0.82 above 28,000 feet C.G. Range: See the appropriate FAA Approved Airplane Flight Manual and Weight and Balance Manual. DC-10-10 Maximum Weight: 440, 000 pound Takeoff Weight 455,000 pound Takeoff Weight (See NOTE 10) See Serial Numbers Eligible See Serial Numbers Eligible Taxi and Ramp 443,000 lb. 458,000 lb. Takeoff 440,000 lb. 455,000 lb. Landing 2 363,500 lb. 363,500 lb. Zero Fuel 3 335,000 lb. 335,000 lb. Gear Jacking 443,000 lb. 443,000 lb. Fuselage and Wing Jacking 388,000 lb. 388,000 lb. Minimum Crew: For all flights: Pilot, Copilot, and Flight Engineer. Maximum Passengers: (See NOTE 6) Maximum Baggage: (See Weight and Balance Manual) 2 Fuel dump valves required for operation in excess of maximum landing weight. See NOTE 1 (f). 3 All weight in airplane above this weight must be fuel. A22WE Page 4 of 50 I - Model DC-10-10 (Transport Aircraft), Approved July 29, 1971 (cont’d) Fuel Capacity: Fuel Tank Capacity (pounds) Usable Location Structural (6.7 lb./gal) Arm (Inches) Main No. 1 42,579 40,116 1488 Main No. 2 68,998 64,969 1296 Main No. 3 42,579 40,116 1488 Center Wing Auxiliary (if installed) 36,849 32,727 1279 Crossfeed Manifold and Lines 609 1429 Oil Capacity: 24.3 lb./engine usable at 8.1 lb./gal. with wing engines moment arm at 1125 in. and tail engine moment arm at 2200 in. Maximum Operating Altitude: 42,000 feet MAC: 300.682 inches (Leading Edge of MAC Station 1299.83) Service Life Limits: See NOTE 3 DC-10-10 Serial Numbers Eligible: Maximum Takeoff Weight of 440,000 pounds (See NOTE 10) 46500, 46502 - 46509, 46511 - 46520, 46522 – 46525, 46603, 46604, 46614, 46632, 46645, 46646, 46700 - 46703, 46706 - 46707, 46709, 46908, 46928, 46942, 46943, 46946, 46977, 46983, 47800, 47802, 47832, 47833, 47966 - 47969. Maximum Takeoff Weight of 455,000 pounds 46501, 46727, 46905, 46906, , (46517, 46525, 46645, 46646, 46908, 46977, 46983, 47832, 47833). 4 Other Information: See "Data Pertinent to All Models" II - Model DC-10-40 (Transport Aircraft), Approved October 20, 1972 Engines: 3 Pratt and Whitney JT9D-20 Turbofan Engines with water injection, or 3 Pratt and Whitney JT9D-20J or JT9D-59A Turbofan Engines (JT9D-59A Engines are installed per Rohr STC SA3139WE) (See Serial Numbers Eligible). Fuel: See NOTE 4. Oil: See NOTE 5. Engine Limits: JT9D-20 JT9D-20J JT9D-59A Static Thrust, Sea Level Takeoff, Dry 5 44,500 lb. 48,050 lb. 51,720 lb. Takeoff, Wet 6 47,000 lb. Maximum Continuous 39,240 lb. 39,240 lb. 44,770 lb. 4 When modified in accordance with McDonnell Douglas Service Bulletin 57-97. 5 5 minutes flat to 84°F for JT9D-20 and 86°F for JT9D-20J and JT9D-59A. 6 2 ½ minutes wet flat to 86°F. Page 5 of 50 A22WE II - Model DC-10-40 (Transport Aircraft), Approved October 20, 1972 (cont’d) Engine Limits (cont’d): Maximum permissible engine rotor speeds N1 (Low Compressor) 3650 rpm (101.4%) 3750 rpm (104.2%) 3780 rpm (105%) N2 (High Compressor) 8000 rpm ( 98.9%) 8000 rpm ( 98.9%) 8011 rpm ( 99%) Maximum permissible engine temperature Turbine exhaust gas temperature at turbine outlet (Tt 6 for JT9D-20 & -20J and Tt 7 for JT9D-59A) Takeoff, Wet or Dry (5 min) 1679oF (915oC) 1805oF (985oC) 1238oF (670oC) Maximum Continuous 1607oF (875oC) 1697oF (925oC) 1202oF (650oC) Maximum Acceleration (2 min) 1679oF (915oC) 1805oF (985oC) 1238oF (670oC) Starting 7 1202oF (650oC) 1202oF (650oC) 941oF (505oC) Maximum permissible oil inlet temperature Continuous Operation 275oF (135oC) 275oF (135oC) 275oF (135oC) Transient Operation 8 320oF (160oC) 320oF (160oC) 320oF (160oC) APU Limits: AiResearch TSCP700-4 (if installed) Power Rating Maximum at sea level 189 hp Rotor Speeds Low pressure rotor speed (N1) 31,750 rpm (110%) High pressure rotor speed (N2) 38,830 rpm (110%) Exhaust Gas Temperature Maximum during operation 1085oF (585oC) Maximum indicated temperature during each starting cycle 1085oF (585oC) Airspeed Limits: VMO / MMO (Maximum Operating) (CAS) At Sea Level 350K At 10,000 ft. 376K At 24,820 ft. 376K (M = 0.88) At 42,000 ft. 258K (M = 0.88) VA (Maneuvering) See FAA Approved Airplane Flight Manual With JT9D-20 or -20J With JT9D-59A Engines (See Serial Engines (See Serial VFE Flap Position (Inboard) Numbers Eligible) Numbers Eligible) 5o 260K (M = 0.51) 270K (M = 0.55) 15o 255K (M = 0.51) 255K (M = 0.51) 20o 240K (M = 0.51) 240K (M = 0.51) 25o 221K (M = 0.51) 221K (M = 0.51) 35o 194K (M = 0.51) 194K (M = 0.51) 50o 178K (M = 0.51) 178K (M = 0.51) 7 Maximum transient for 10 seconds. 8 Transient operation above 275°F (135°C) is limited to 20 minutes. A22WE Page 6 of 50 II - Model DC-10-40 (Transport Aircraft), Approved October 20, 1972 (cont’d) Airspeed Limits: (cont'd) (CAS) VSLAT (Slat Operating) Takeoff and Approach: With JT9D-20 or 20J With JT9D-59A Engines (See Serial Engines (See Serial Flap Position (Inboard) Numbers Eligible) Numbers Eligible) 5o 260K (M = 0.51) 270K (M = 0.55) 15o 255K (M = 0.51) 255K (M = 0.51) 20o 221K (M = 0.51) 221K (M = 0.51) Landing Flap Position (Inboard) 25o 221K (M = 0.51) 221K (M = 0.51) 35o 194K (M = 0.51) 194K (M = 0.51) 50o 178K (M = 0.51) 178K (M = 0.51) Autoslat Flaps retracted 260K (M = 0.51) 270K (M = 0.75) VLO (Landing Gear) Retraction 230K (M = 0.70) 230K (M = 0.70) Extension 260K (M = 0.70) 260K (M = 0.70) VLE (Landing Gear Extended) 300K (M = 0.70) 300K (M = 0.70) V (Landing light extension) VMO/MMO VMO/MMO Maximum speed extension, retraction, or extended position. V (Fuel Dump) 325K up to 28,000 feet M = 0.82 above 28,000 feet C.G. Range: See the appropriate FAA Approved Airplane Flight Manual and Weight and Balance Manual. DC-10-40 Maximum Weight: With JT9D-20 or -20J Engines With JT9D-59A Engines (See NOTE 10) 565,000 pound Takeoff Weight 572,000 pound Takeoff Weight (See Serial Numbers Eligible) (See Serial Numbers Eligible) Center Main Center Main Center Main Center Main Gear Retracted Gear Extended Gear Retracted Gear Extended or Removed Taxi and Ramp 568,000 lb. 443,000 lb. 575,000 lb. 478,000 lb. Takeoff 9 565,000 lb. 440,000 lb. 572,000 lb. 475,000 lb. Landing 10 421,000 lb. 363,500 lb. 421,000 lb. 400,000 lb. Zero Fuel 11 391,000 lb. 363,500 lb. 391,000 lb. 391,000 lb. Gear Jacking Weight 568,000 lb. 443,000 lb. 575,000 lb. 478,000 lb. Fuselage and Wing Jacking Weight 508,000 lb. 443,000 lb. 508,000 lb. 478,000 lb. 9 For takeoff above 555,000 pounds, 28 ply main landing gear tires and modification per Douglas Service Bulletin 57- 28 or equivalent are required. 10 Fuel dump valves required for takeoff in excess of maximum landing weight. See NOTE 1 (f). 11 All weight in airplane above this weight must be fuel. Page 7 of 50 A22WE II - Model DC-10-40 (Transport Aircraft), Approved October 20, 1972 (cont’d) Minimum Crew: For all Flights: Pilot, Copilot, and Flight Engineer. Maximum Passengers: (See NOTE 6). Maximum Baggage: (See Weight and Balance Manual). Fuel Capacity: Fuel Tank Capacity (pounds) Usable Usable 12 Location Structural (6.7 lb./gal.) (6.7 lb./gal.) Arm (inches) Main No. 1 43,202 40,203 40,704 1492.6 Main No. 2 69,495 64,969 65,438 1296.0 Main No. 3 43,202 40,403 40,704 1492.6 Center Wing Auxiliary 104,141 97,409 98,111 1266.1 Crossfeed Manifold & Lines 622 622 1420.1 Oil Capacity: 77 lb./engine usable at 8.1 lb./gal. with wing engines moment arm at 1164.0 in. and tail moment area at 2239.0 in. Maximum Operating Altitude: 42,000 feet MAC: 295.78 inches (Leading Edge of MAC Station 1311.95) Service Life Limits: See NOTE 3 DC-10-40 Serial Numbers Eligible: Maximum Takeoff Weight of 565,000 pounds (See NOTE 10) (with JT9D-20 or -20J Engines) 46750, 46752 – 46771. Maximum Takeoff Weight of 572,000 pounds (with JT9D-59A Engines installed per STC SA3139WE) 46660, 46662, 46913, 46923, 46967, 46974, 47822, 47824 - 47826, 47852, 47853, – 47856, 47857, 48301. Spare Engine Transportation Pod - The Spare Engine Transportation Pod may be carried on models with JT9D-59A engines installed per STC SA3139WE in accordance with the limitations specified in the FAA approved Airplane Flight Manual. Other Information: See "Data Pertinent to All Models" III - Model DC-10-30 (Transport Aircraft), Approved November 21, 1972 Engines: 3 General Electric CF6-50A, CF6-50C, CF6-50CA, CF6-50C1, CF6-50C2, CF6-50C2B or CF6-50C2-R Turbofan Engines. (Engines may be intermixed in accordance with Appendix XXII of applicable FAA Approved Airplane Flight Manual). Fuel: See NOTE 4. 12 When modified per Douglas Service Bulletin 28-27 and 28-32 or equivalents. A22WE Page 8 of 50 III - Model DC-10-30 (Transport Aircraft), Approved November 21, 1972 (cont’d) Oil: See NOTE 5. Engine Limits: CF6-50C/-50CA/ CF6-50A -50C2-R CF6-50C1 CF6-50C2 CF6-50C2B Static Thrust, Sea Level Takeoff 13 48,400 lb. 50,400 lb. 51,800 lb. 51,800 lb. 53,200 lb. Maximum Continuous 46,300 lb. 46,300 lb. 46,300 lb. 46,300 lb. 46,300 lb. (flat to 86°F) Maximum permissible engine rotor operating speeds N1 (Low Compressor) 14 3982 rpm (116%) 3982 rpm (116%) 4068 rpm 4068 rpm 4068 rpm (118.5%)15 4068 rpm (118.5%)15 (118.5%) (118.5%) N2 (High Compressor) 10613 rpm (108%) 10613 rpm (108%) 10761 rpm 10761 rpm 10761 rpm (109.5%)16 10761 rpm (109.5%)16 (109.5%) (109.5%) CF6-50C/-50CA/ CF6-50C2/-50C2B/ CF6-50A -50C1 -50C2-R Maximum permissible engine temperature Turbine exhaust gas temperature at turbine outlet Takeoff (5 min.) 1679oF (915oC) 1715oF (935oC) 1733oF (945oC) 1733oF (945oC)17 Maximum Continuous 1607oF (875oC) 1607oF (875oC) 1670oF (910oC) 1670oF (910oC)17 Maximum for Acceleration (2 min.) 1706oF (930oC) 1742oF (950oC) 1760oF (960oC) 1760oF (960oC)17 Starting (Max. Transient for 40 sec.) 1652oF (900oC) 1652oF (900oC) 1652oF (900oC) (Max. no time limit) 1382oF (750oC) 1382oF (750oC) 1382oF (750oC) Maximum permissible oil outlet temperature Continuous Operation 320oF (160oC) 320oF (160oC) 320oF (160oC) 13 5 minutes flat to 87°F for -50A; 5 minutes flat to 86°F for -50C, -50CA, -50C1, -50C2, and -50C2-R; 5 minutes flat to 79°F for -50C2B. 14 The CF6-50C N1 value of 116% is used for the preparation of the Airplane Flight Manual in lieu of the CF6-50C1 N1 value of 116½% noted in the engine data sheet. 15 When modified per Douglas Service Bulletin 77-46 or production equivalent, for CF6-50A/-50C/-50CA/-50C1. 16 When modified per Douglas Service Bulletin 77-44 or production equivalent, for CF6-50A/-50C/-50CA/-50C1. 17 When modified per Douglas Service Bulletin 77-47 or production equivalent, for CF6-50C/-50CA/-50C1. Page 9 of 50 A22WE III - Model DC-10-30 (Transport Aircraft), Approved November 21, 1972 (cont’d) Engine Limits (cont’d) CF6-50C/-50CA/ CF6-50C2/-50C2B/ CF6-50A -50C1 -50C2-R Transient Operation 18 347oF (175oC) 347oF (175oC) 347oF (175oC) APU Limits: AiResearch TSCP700-4 (if installed) Power Rating Maximum at sea level 189 hp Rotor Speeds Low pressure rotor speed (N1) 31,750 rpm (110%) High pressure rotor speed (N2) 38,830 rpm (110%) Exhaust Gas Temperature Maximum during operation 1085oF (585oC) Maximum indicated temperature each starting cycle 1085oF (585oC) Airspeed Limits: (CAS) VMO/MMO (Maximum Operating) At Sea Level 350K At 10,000 ft 376K At 24,820 ft 376K (M = 0.88) At 42,000 ft 258K (M = 0.88) VA (Maneuvering) See FAA Approved Airplane Flight Manual 572,000 lb./580,000 lb. 565,000 lb. VFE Flap Position Takeoff Weight Takeoff Weight (Inboard) (See Serial Numbers Eligible) (See Serial Numbers Eligible) 5o 270K (M = 0.55) 260K (M = 0.51) 15o 255K (M = 0.51) 255K (M = 0.51) 20o 240K (M = 0.51) 240K (M = 0.51) 25o 221K (M = 0.51) 221K (M = 0.51) 35o 194K (M = 0.51) 194K (M = 0.51) 50o 178K (M = 0.51) 178K (M = 0.51) VSLAT (Slat Operating) Takeoff and Approach Flap Position 5o 270K (M = 0.55) 260K (M = 0.51) 15o 255K (M = 0.51) 255K (M = 0.51) 25o 221K (M = 0.51) 221K (M = 0.51) Landing Flap Position 35o 194K (M = 0.51) 194K (M = 0.51) 50o 178K (M = 0.51) 178K (M = 0.51) 18 Transient operation above 320°F (160°C) is limited to 15 minutes. A22WE Page 10 of 50 III - Model DC-10-30 (Transport Aircraft), Approved November 21, 1972 (cont’d) Airspeed Limits: (cont’d) (CAS) 572,000 lb./580,000 lb. 565,000 lb. Takeoff Weight Takeoff Weight (See Serial Numbers Eligible) (See Serial Numbers Eligible) Autoslat Flaps retracted 270K (M = 0.55) 260K (M = 0.51) VLO Landing Gear Retraction 230K (M = 0.70) 230K (M = 0.70) Extension 260K (M = 0.70) 260K (M = 0.70) VLE (Landing Gear Extended) 300K (M = 0.70) 300K (M = 0.70) V (Landing light extension) - Maximum Speed in extension, retraction, or extended position VMO/MMO V (Fuel Dump) 325K up to 28,000 feet M=0.82 above 28,000 feet C.G. Range: See the appropriate FAA Approved Airplane Flight Manual and Weight and Balance Manual. DC-10-30 Maximum Weight: 565,000 pound Takeoff Weight 572,000 pound Takeoff Weight (See NOTE 10) (See Serial Numbers Eligible) (See Serial Numbers Eligible) Center Main Center Main Center Main Center Main Gear Extended Gear Retracted Gear Extended Gear Retracted Taxi and Ramp 568,000 lb. 463,000 lb. 575,000 lb. 478,000 lb. Takeoff 19 565,000 lb. 460,000 lb. 572,000 lb. 475,000 lb. Landing 20 424,000 lb. 400,000 lb. 424,000 lb. 400,000 lb. Zero Fuel 21 401,000 lb. 391,000 lb. 401,000 lb. 401,000 lb. Gear Jacking 568,000 lb. 463,000 lb. 575,000 lb. 478,000 lb. Fuselage and Wing Jacking 508,000 lb. 463,000 lb. 508,000 lb. 478,000 lb. 580,000 pound Takeoff Weight 590,000 pound Takeoff Weight 24A, 24B (See Serial Numbers Eligible) (See Serial Numbers Eligible) Center Main Center Main Center Main Center Main Gear Extended Gear Retracted Gear Extended Gear Retracted Taxi and Ramp 583,000 lb. 478,000 lb. 593,000 lb. 478,000 lb. Takeoff 22 580,000 lb. 475,000 lb. 590,000 lb. 475,000 lb. 19 For takeoff weights above 555,000 pounds, 28 ply main landing gear tires and modification per Douglas Service Bulletin 57-28 or equivalents are required. 20 Fuel dump valves required for operation in excess of maximum landing weight. See NOTE 1(f). 21 All weight in airplane above this weight must be fuel. 22 For takeoff weights above 555,000 pounds, 28 ply main landing gear tir es and modification per Douglas Service Bulletin 57-28 or equivalents are required. Page 11 of 50 A22WE III - Model DC-10-30 (Transport Aircraft), Approved November 21, 1972 (cont’d) Maximum Weight: (cont’d) (See NOTE 10) 580,000 pound Takeoff Weight 590,000 pound Takeoff Weight (See Serial Numbers Eligible) (See Serial Numbers Eligible) Landing 23 446,000 lb. 400,000 lb. 411,000 lb. 400,000 lb. Zero Fuel 24 424,000 lb. 391,000 lb. 368,000 lb. 368,000 lb. Gear Jacking 583,000 lb. 478,000 lb. 593,000 lb. 478,000 lb. Fuselage and Wing Jacking 508,000 lb. 478,000 lb. 508,000 lb. 478,000 lb. Minimum Crew: For all Flights: Pilot, Copilot, and Flight Engineer. Maximum Passenger: (See NOTE 6). Maximum Baggage: (See Weight and Balance Manual). Fuel Capacity: Fuel Tank Capacity (pounds) Usable Usable 25 Arm Location Structural (6.7 lb./gal.) (6.7 lb./gal.) (inches) Main No. 1. 43,202 40,203 40,704 1492.6 Main No. 2. 69,495 64,969 65,438 1296.0 Main No. 3. 43,202 40,203 40,704 1492.6 Center Wing Auxiliary 104,141 97,409 98,111 1266.1 Aft Aux.26 11,028 N/A 10,280 1819.5 Aft Aux.27 23,052 N/A 21,618 1850.0 Aft Aux.28 24,018 N/A 3,317 Crossfeed Manifold & Lines 609 609 1420.5 NOTE: The integrity of the transfer system must be demonstrated per Maintenance Manual, Chapter 28-21- 100, section titled "Manifold Integrity Check" whenever the system is disturbed for maintenance. Also, if the tank overfilled light is illuminated any time during fueling, comply with the caution note in Chapter 12-11-04, section titled "Safety and Operating Precautions", item pertaining to tank overfilled condition. 23 Fuel dump valves required for operation in excess of maximum landing weight. See NOTE 1(f). 24 All weight in airplane above this weight must be fuel. 24A Serial numbers 48265, 48267, 48290, 48315, 48316, and 48319 have a maximum zero fuel weight of 391,000 lb. 24B Serial numbers 48267, 48290, 48315, 48316, and 48319 have a maximum landing weight of 436,000 lb. 25 When modified per Douglas Service Bulletins 28-27 and 28-32 or equivalents. 26 When modified per Douglas Service Bulletins 28-67, 28-111 and 28-114 or equivalents. 27 When modified per Douglas Service Bulletin 28-79 or equivalent. 28 When modified in accordance with Service Bulletin 28-79 and 28-137 or production equivalent. A22WE Page 12 of 50 III - Model DC-10-30 (Transport Aircraft), Approved November 21, 1972 (cont’d) Oil Capacity: 24.3 lb./engine usable at 8.1 lb./gal. with wing engines moment arm at 1125 in. and tail engine moment arm at 2200 in. Maximum Operating Altitude: 42,000 feet MAC: 295.78 inches (Leading Edge of MAC Station 1311.95) Service Life Limits: See NOTE 3 DC-10-30 Serial Numbers Eligible: Maximum Takeoff Weight of 565,000 pounds (See NOTE 10) 46550 - 46557, 46575 - 46582, 46640, 46685, 46686, 46711 - 46714, 46850 - 46854, 46868, 46870, 46872, 46892, 46911, 46912, 46914 –46416, 46418 - 46919, 46922, 46926, 46927, 46933, 46934, 46940, 46941, 46944, 46945, 46950 - 46954, 46957, 46958, 46963, 46964, 46969, 46971, 46972, 46981, 46982, 46997, 47834, 47837, 47846 - 47849, 47861 - 47867, 47886, 47926, 47927, 47980, 47982, 47981, 48283, 48286. Maximum Takeoff Weight of 572,000 pounds 46542, 46591, 46959, 46961, 46981, 46988, 46990, 46991, 46993, 46995, 47817, 47838, 47956, 47957, 48266, 48317, 48318. Maximum Takeoff Weight of 580,000 pounds 46583, 46584, 46869. Maximum Takeoff Weight of 590,000 pounds 46543, 46595, 46596, 47814, 47815, 47844, 47845, 47850, 47851, 48252, 48265, 48267, 48282, 48285, 48288, 48290, 48292, 48293, 48296, 48315, 48316, 48319. Other Information: See "Data Pertinent to All Models" IV - Model DC-10-30F (Transport Aircraft), Approved March 30, 1973 (KC-10A See NOTE 11 regarding certification) (KDC-10 See NOTE 19 regarding certification) Engines: 3 General Electric CF6-50A, CF6-50C, CF6-50CA, CF6-50C1, CF6-50C2, CF6-50C2B or CF6-50C2-R Turbofan Engines. (Engines may be intermixed in accordance with Appendix XXII of applicable FAA Approved Airplane Flight Manual). Fuel: See NOTE 4 Oil: See NOTE 5 Engine Limits: (See Section III) APU Limits: AiResearch TSCP700-4 (if installed) (See Section III) Page 13 of 50 A22WE IV - Model DC-10-30F (Transport Aircraft), Approved March 30, 1973 (cont’d) (KC-10A See NOTE 11 regarding certification) (KDC-10 See NOTE 19 regarding certification) Airspeed Limits: VMO/MMO (Maximum Operating) (CAS) (KC-10A with Aerial Refueling Boom and Drogue Stowed) (KDC-10 with Aerial Refueling Boom stowed) At Sea Level 350K At 10,000 ft 376K At 24,820 ft 376K (M = 0.88) At 42,000 ft 258K (M = 0.88) VMO/MMO (Maximum Operating) (KC-10A/KDC-10 with Aerial Refueling Boom Deployed) At Sea Level 350K At 10,000 ft 355K At 25,600 ft 370K (M = 0.88) At 37,000 ft 289K (M = 0.88) VMO/MMO (Maximum Operating) (KC-10A with Drogue Deployed) At Sea Level 325K At 10,000 ft 329K At 28,930 ft 345K (M = 0.88) At 37,000 ft 289K (M = 0.88) VA (Maneuvering) See FAA Approved Airplane Flight Manual VFE Flap Position Inboard 5o 270K (M = 0.55) 15o 255K (M = 0.51) 20o 240K (M = 0.51) 25o 221K (M = 0.51) 35o 194K (M = 0.51) 50o 178K (M = 0.51) VSLAT (Slat Operating) Takeoff and Approach Flap Position (Inboard) 5o 270K (M = 0.55) 15o 255K (M = 0.51) 25o 221K (M = 0.51) Landing Flap Position (Inboard) 25o 221K (M = 0.51) 35o 194K (M = 0.51) 50o 178K (M = 0.51) Autoslat Flaps retracted 270K (M = 0.75) VLO Landing Gear Retraction 230K (M = 0.70) Extension 260K (M = 0.70) VLE (Landing Gear Extended) 300K (M = 0.70) A22WE Page 14 of 50 IV - Model DC-10-30F (Transport Aircraft), Approved March 30, 1973 (cont’d) (KC-10A See NOTE 11 regarding certification) (KDC-10 See NOTE 19 regarding certification) Airspeed Limits: (cont’d) (CAS) V (Landing light extension) - Maximum speed in extension, retraction, or extended position VMO/MMO V (Fuel Dump) 325K up to 28,000 feet M = 0.82 above 28,000 feet NOTE - The airspeed limits for DC-10-30F with CF6-50C1 engines are the same as those for DC-10-40 airplanes with JT9D-59A engines. (See Section II). C.G. Range: DC-10-30F: See the appropriate FAA Approved Airplane Flight Manual and Weight and Balance Manual. KC-10A: See the appropriate FAA Approved Airplane Flight Manual and "Basic Weight Checklist and Loading Data", Report No. T.O. 1C-10(K) A-5, Chg. 1, dated 15 March 1981. KDC-10: See the appropriate FAA Approved Airplane Flight Manual and Weight and Balance Manual. DC-10-30F Maximum Weight: 565,000 pound Takeoff Weight 572,000 pound Takeoff Weight (See NOTE 10) (See Serial Numbers Eligible) (See Serial Numbers Eligible) Center Main Center Main Center Main Center Main Gear Retracted Gear Extended Gear Retracted Gear Extended or Removed _ Taxi and Ramp 568,000 lb. 463,000 lb. 575,000lb. 478,000lb. Takeoff 29 565,000 lb. 460,000 lb. 572,000lb. 475,000lb. Landing 30 424,000 lb. 400,000 lb. 424,000lb. 400,000lb. Zero Fuel 31 401,000 lb. 391,000 lb. 401,000lb. 391,000lb. Gear Jacking Wt. 568,000 lb. 463,000 lb. 575,000lb. 478,000lb. Fuselage & Wing Jack Weight 508,000 lb. 463,000 lb. 508,000lb. 478,000lb. 580,000 pounds Takeoff Weight 590,000 pounds Takeoff Weight (See Serial Numbers Eligible) (See Serial Numbers Eligible) Center Main Center Main Center Main Gear Retracted Center Main Gear Retracted Gear Extended or Removed Gear Extended or Removed Taxi and Ramp 583,000 lb. 478,000 lb. 593,000 lb. 478,000 lb. Takeoff 29 580,000 lb. 475,000 lb. 590,000 lb. 475,000 lb. Landing 30 446,000 lb. 400,000 lb. 436,000 lb. 400,000 lb. Zero Fuel 31 424000 lb. 391,000 lb. 414,000 lb. 400,000 lb. Gear Jacking Wt. 583,000 lb. 478,000 lb. 593,000 lb. 478,000 lb. Fuselage & Wing Jack Weight 508,000 lb. 478,000 lb. 508,000 lb. 478,000 lb. 29 For takeoff weights above 555,000 pounds, 28 ply main landing gear tires and modification per Douglas Service Bulletin 57-28 or equivalents are required. 30 Fuel dump valves required for operation in excess of maximum landing weight. See NOTE 1 (f). 31 All weight in airplane above this weight must be fuel. Page 15 of 50 A22WE IV - Model DC-10-30F (Transport Aircraft), Approved March 30, 1973 (cont’d) (KC-10A See NOTE 11 regarding certification) (KDC-10 See NOTE 19 regarding certification) Minimum Crew: For all Flights: Pilot, Copilot, and Flight Engineer. Maximum Passengers: For DC-10-30F: See FAA approved exemption 6752 for the accommodation of up to four supernumeraries immediately aft of the cockpit on freighter aircraft equipped with a Class E cargo compartment. For KC-10A: The KC-10A is approved to operate in the “all cargo” or “combi” (combination passenger and cargo) configuration. For the “combi” configuration, a total of up to 75 passengers are allowed per FAA approved MDC interior schematic drawing number J015113, Revision V, or later FAA approved revisions. Maximum Baggage: (See Weight and Balance Manual). Fuel Capacity: Fuel Tank Capacity (pounds) Usable Usable 32 Location Structural (6.7 lb./gal.) (6.7 lb./gal.) Arm (inches) Main No. 1 43,202 40,203 40,704 1492.6 Main No. 2 69,495 64,969 65,438 1296.0 Main No. 3 43,202 40,203 40,704 1492.6 Center Wing Auxiliary 104,141 97,409 98,111 1266.1 Aft Aux.33 10,884 N/A 10,280 1819.5 Aft Aux.34 22,670 N/A 21,618 1850.0 Crossfeed Manifold & Lines 609 609 1420.5 Fwd. Body (KC-10A only) 59,171 55,308 N/A 959 Aft. Body (KC-10A only) 70,294 66,149 N/A 1641 NOTE: The integrity of the transfer system must be demonstrated per Maintenance Manual, Chapter 28-21- 100, section titled "Manifold Integrity Check" whenever the system is disturbed for maintenance. Also, if the tank overfilled light is illuminated any time during fueling, comply with the caution note in Chapter 12-11-04, section titled "Safety and Operating Precautions", item pertaining to tank overfilled condition. Oil Capacity: 24.3 lb./engine usable at 8.1 lb./gal. with wing engines moment arm at 1125 in. and tail engine moment arm at 2200 in. Maximum Operating Altitude: 42,000 feet MAC: 295.78 inches (Leading Edge of MAC St. 1311.95) Service Life Limits: See NOTE 3. 32 When modified per Douglas Service Bulletins 28-27 and 28-32 or equivalents. 33 When modified per Douglas Service Bulletins 28-67, 28-111 and 28-114 or equivalent. 34 When modified per Douglas Service Bulletin 28-79 or equivalent. A22WE Page 16 of 50 IV - Model DC-10-30F (Transport Aircraft), Approved March 30, 1973 (cont’d) (KC-10A See NOTE 11 regarding certification) (KDC-10 See NOTE 19 regarding certification) DC-10-30F Serial Numbers Eligible: Maximum Takeoff Weight of 565,000 pounds (See NOTE 10) 46891, 46917, 46955, 46956, 46965, 46985, 47868, 47889, 47906 - 47908, 47921 - 47925, 47928, 47929. Maximum Takeoff Weight of 572,000 pounds 46540, 46541, 46590, 46836, 46921, 46931, 46932, 46936, 46937, 46949, 46975, 46976, 46978, 46986, 46987, 46998, 46999, 47816, 47818, 47819 47831, 47840, 47888. Maximum Takeoff Weight of 580,000 pounds 47811, 47813, 47841, 47842. Maximum Takeoff Weight of 590,000 pounds 47843, 47870, 48200, 48211, 48213 – 48251, 48298, 48299, 48303 – 48310. Other Information: See "Data Pertinent to All Models" V - Model DC-10-10F (Transport Aircraft), Approved February 1, 1974 Engines: 3 General Electric CF6-6D, CF6-6D1, CF6-6D1A, CF6-6K or CF6-6K2 Turbofan Engines. (CF6-6D and CF6-6K engines may be intermixed in accordance with Appendix XXII of applicable FAA Approved Airplane Flight Manual. CF6-6D1 and CF6-6D1A may be intermixed in accordance with page 2.1 of Section IV-B of applicable FAA Approved Airplane Flight Manual.) Fuel: See NOTE 4. Oil: See NOTE 5. Engine Limits: Refer to Section I APU Limit: Refer to Section I (if installed) Airspeed Limits: Refer to Section I (CAS) C.G. Range: See the appropriate FAA Approved Airplane Flight Manual and Weight and Balance Manual. Page 17 of 50 A22WE V - Model DC-10-10F (Transport Aircraft), Approved February 1, 1974 (cont’d) DC-10-10F Maximum Weight: 440,000 pound Takeoff Weight 446,000 pound Takeoff Weight (See NOTE 10) (See Serial Numbers Eligible) (See Serial Numbers Eligible) Taxi and Ramp 443,000 lb. 449,000 lb. Takeoff 440,000 lb. 446,000 lb. Landing 35 370,000 lb. 36 375,000 lb. Zero Fuel 37 350,000 lb. 38 355,000 lb. Gear Jacking Weight 443,000 lb. 449,000 lb. Fuselage and Wing Jack Weight 388,000 lb. 388,000 lb. 455,000 pound Takeoff Weight (See Serial Numbers Eligible) Taxi and Ramp 458,000 lb. Takeoff 455,000 lb. Landing 35 375,000 lb. Zero Fuel 37 355,000 lb. Gear Jacking Weight 449,000 lb. Fuselage and Wing Jack Weight 388,000 lb. Minimum Crew: For all flights: Pilot, Copilot, and Flight Engineer. Maximum Passengers: See FAA approved exemption number 6752 for the accommodation of up to four supernumeraries immediately aft of the cockpit on freighter aircraft equipped with a Class E cargo compartment. Maximum Baggage: (See Weight and Balance Manual). Fuel Capacity: Fuel Tank Capacity (pounds) Usable Location Structural (6.7 lb./gal.) Arm (inches) Main No. 1 42,579 40,116 1488 Main No. 2 68,998 64,969 1296 Main No. 3 42,579 40,116 1488 Crossfeed Manifold & Lines 609 1429 Center Wing Auxiliary (if installed) 36,849 32,727 1279 Oil Capacity: 24.3 lb./engine usable at 8.1 lb./gal. with wing engines moment arm at 1125 in. and tail engine moment arm at 2200 in. 35 Fuel dump valves required for operation in excess of maximum landing weight. See NOTE 1(f). 36 370,000 pound landing weight is approved in freighter mode only, when Douglas Drawing SM10000001 and Douglas Service Bulletin 27-156 are incorporated and main landing gear Goodyear brakes 5000709-7 or later are installed, or production equivalent. 37 All weight in airplanes above this weight must be fuel. 38 350,000 pound zero fuel weight is approved in freighter mode only, when Douglas drawing SM10000001 and Douglas Service Bulletin 27-156 are incorporated and main landing gear Goodyear brakes 5000709-7 or later are installed, or production equivalent. A22WE Page 18 of 50 V - Model DC-10-10F (Transport Aircraft), Approved February 1, 1974 (cont’d) Maximum Operating Altitude: 42,000 feet MAC: 300.682 inches (Leading Edge of MAC Station 1299.83) Service Life Limits: See NOTE 3 DC-10-10F Serial Numbers Eligible: Maximum Takeoff Weight of 440,000 pounds (See NOTE 10) None Maximum Takeoff Weight of 446,000 pounds 46705, 46900 - 46903, 47801. Maximum Takeoff Weight of 455,000 pounds None Other Information: See "Data Pertinent to All Models" VI - Model DC-10-40F (Transport Aircraft, Approved November 5, 1976 Engines: 3 Pratt and Whitney Turbofan JT9D-59A Engines installed per Rohr STC SA3139WE. Fuel: See Note 4 Oil: See NOTE 5 Engine Limits: (See Section II) APU Limits: (See Section II) Airspeed Limits: (See Section II) the airspeed limits are the same for airplanes with JT9D-59A engines. C.G. Range: See the appropriate FAA Approved Airplane Flight Manual and Weight and Balance Manual. DC-10-40F Maximum Weight: 572,000 pound Takeoff Weight (See Note 10) (See Serial Numbers Eligible) Center Main Center Main Gear Extended Gear Retracted Taxi and Ramp 575,000 lb. 478,000 lb. Takeoff 39 572,000 lb. 475,000 lb. Landing 40 424,000 lb. 400,000 lb. 39 For takeoff weights above 555,000 pounds, 28 ply main landing gear tires and modifications per Douglas Service Bulletin 57-28 or equivalents are required. 40 Fuel dump valves required for operation in excess of maximum landing weight. See NOTE 1(f). Page 19 of 50 A22WE VI - Model DC-10-40F (Transport Aircraft, Approved November 5, 1976 (cont’d) DC-10-40F Maximum Weight (cont’d) 572,000 pound Takeoff Weight (See NOTE 10) (See Serial Numbers Eligible) Center Main Center Main Gear Extended Gear Retracted Zero Fuel 41 401,000 lb. 391,000 lb. Gear Jacking Weight 575,000 lb. 478,000 lb. Fuselage & Wing Jacking Weight 508,000 lb. 478,000 lb. Minimum Crew: For all flights: Pilot, Copilot, and Flight Engineer. Maximum Passenger: See FAA approved exemption number 6752 for the accommodation of up to four supernumeraries immediately aft of the cockpit on freighter aircraft equipped with a Class E cargo compartment. Maximum Baggage: (See Weight and Balance Manual) Fuel Capacity: (See Section II) Oil Capacity: 77 lb./engine usable at 8.1 lb./gal. with wing engines moment arm at 1164.0 in. and tail engine moment arm at 2239.0 in. Maximum Operating Altitude: 42,000 feet MAC: 295.78 inches (Leading Edge of MAC Station 1311.95) Service Life Limits: (See NOTE 3) DC-10-40F Serial Numbers Eligible: Maximum Takeoff Weight of 572,000 lbs. (See NOTE 10) 46920, 46661, 46966, 47823, 47855. Other Information: See "Data Pertinent to All Models" VII - Model DC-10-15 (Transport Aircraft), Approved June 12, 1981 Engines: 3 General Electric CF6-50C2-F Turbofan Engines Fuel: See NOTE 4. Oil: See NOTE 5. 41 All weight in airplane above this weight must be fuel. A22WE Page 20 of 50 VII - Model DC-10-15 (Transport Aircraft), Approved June 12, 1981 (cont’d) Engine Limits: Takeoff Thrust, Sea Level, Static CF6-50C2-F (5 min. flat to Std. + 28.3oC) 45,600 lb. Maximum Continuous (flat to Std. + 15oC) 43,250 lb. Maximum permissible engine rotor operating speeds N1 (Low Compressor) 4,067.5 rpm (111.3%) N2 (High Compressor) 10,761 rpm (109.5%) Maximum permissible engine temperature Turbine exhaust gas temperatures at turbine outlet Takeoff (5 min.) 1,733oF (945oC) Maximum Continuous 1,670oF (910oC) Maximum for Acceleration (2 min.) 1,760oF (960oC) Starting (Max. Transient for 40 sec.) 1,652oF (900oC) (Max. no time limit) 1,382oF (750oC) Maximum permissible oil outlet temperature Continuous operation 320oF (160oC) Transient operation 42 347oF (175oC) APU Limits: AiResearch TSCP700-4 (if installed) Power Rating Maximum at sea level 189 hp Rotor Speeds Low pressure speed (N1) 31,570 rpm (110%) High pressure speed (N2) 38,830 rpm (110%) Exhaust Gas Temperature Maximum during operation 1085oF (585oC) Maximum indicated temperature during each starting cycle 1085oF (585oC) Airspeed Limits: VMO/MMO (Maximum Operating) (CAS) At Sea Level 350K At 28,310 ft 350K (M = 0.88) At 42,000 ft 258K (M = 0.88) VA (Maneuvering) See FAA Approved Airplane Flight Manual VFE Flap Position (Inboard) 5o 260K (M = 0.51) 15o 250K (M = 0.51) 20o 233K (M = 0.51) 25o 214K (M = 0.51) 35o 187K (M = 0.51) 50o 171K (M = 0.51) 42 Transient operation above 320°F (160°C) is limited to 15 minutes. Page 21 of 50 A22WE VII - Model DC-10-15 (Transport Aircraft), Approved June 12, 1981 (cont’d) Airspeed Limits: (cont’d) (CAS) VSLAT (Slat Operating) Takeoff and Approach Flap Position 5o 260K (M = 0.51) 15o 250K (M = 0.51) 25o 214K (M = 0.51) Landing Flap Position 35o 187K (M = 0.51) 50o 171K (M = 0.51) Autoslat Flap retracted 260K (M = 0.51) VLO (Landing Gear) Retraction 230K (M = 0.70) Extension 260K (M = 0.70) VLE (Landing Gear Extended)300K (M = 0.70) (3) No fuel limitation V (Landing light extension) - Maximum speed in extension, retraction, or extended position VMO/MMO V (Fuel Dump) 325K up to 28,000 feet M = 0.82 above 28,000 feet C.G. Range: See the appropriate FAA Approved Airplane Flight Manual and Weight and Balance Manual. DC-10-15 Maximum Weight (See NOTE 10) 455,000 pounds Takeoff Weight (See Serial Number Eligible) Taxi and Ramp 458,000 lb. Takeoff 455,000 lb. Landing 43 363,500 lb. Zero Fuel 44 335,000 lb. Gear Jacking Weight 443,000 lb. Fuselage and Wing Jack Weight 388,000 lb. Minimum Crew: For all flights: Pilot, Copilot, and Flight Engineer. Maximum Passenger: (See NOTE 6). 43 Fuel dump valves required for operation in excess of maximum landing weight. See NOTE 1(f). 44 All weight in airplane above this weight must be fuel. A22WE Page 22 of 50 VII - Model DC-10-15 (Transport Aircraft), Approved June 12, 1981 (cont’d) Maximum Baggage: (See Weight and Balance Manual). Fuel Capacity: Fuel Tank Capacity (pounds) Usable Location Structural (6.7 lb./gal) Arm (inches) Main No. 1 43,202 40,203 1488 Main No. 2 69,495 64,969 1296 Main No. 3 43,202 40,203 1488 Center Wing Auxiliary 36,849 32,727 1279 Crossfeed Manifold & Lines 609 1429 Oil Capacity: 24.3 lb./engine usable at 8.1 lb./gal. with wing engines moment arm at 1125 in. and tail engine moment arm at 2200 in. Maximum Operating Altitude: 42,000 feet MAC: 300.682 inches (Leading Edge of MAC Station 1299.83) Service Life Limits: See NOTE 3. DC-10-15 Serial Numbers Eligible: Maximum Takeoff Weight of 455,000 lbs. (See NOTE 10) 48258, 48259, 48275, 48276, 48289, 48294, 48295. Other Information: See "Data Pertinent to All Models" VIII - Model MD-11 (Transport Aircraft), Approved November 8, 1990 Engines: 3 General Electric CF6-80C2D1F high-bypass turbofan engines. or 3 Pratt & Whitney PW4460 high-bypass turbofan engines. or 3 Pratt & Whitney PW4462 high-bypass turbofan engines. Fuel: See NOTE 4. Oil: See NOTE 5. Engine Limits, General Electric CF6-80C2D1F: Takeoff thrust, sea level, static (5 min), lb 60,690 Maximum continuous thrust, sea level, static thrust, lb. 56,210 Flat rating ambient temperature: Takeoff 86o F (30o C) Maximum continuous 77o F (25o C) Page 23 of 50 A22WE VIII - Model MD-11 (Transport Aircraft), Approved November 8, 1990 (cont’d) Engine Limits, General Electric CF6-80C2D1F: Maximum permissible engine rotor speeds: (cont'd) Low pressure rotor (N1) 3,854 rpm (117.5%) High pressure rotor (N2) 11,055 rpm (112.5%) Maximum permissible exhaust gas temperatures: Takeoff (5 min) 1760o F (960o C) Maximum continuous 1697o F (925o C) Starting (Max. transient for 40 sec) 1598o F (870o C) Starting (Max. with no time limit) 1382o F (750o C) Maximum permissible oil outlet temperatures: Continuous operation 320o F (160o C) Transient operation 347o F (175o C) (Transient operation is limited to 15 minutes.) Fuel and Oil Pressure Limits: Fuel pressure limits apply at the engine fuel pump inlet. Ground Starting Air Starting and Operation. This limit is from a minimum fuel pressure of not less than 5.0 psia (34.46 kPa, absolute) above the true fuel vapor pressure to a maximum of 70 psig (482.6 kPa gage) (relative to atmosphere) with vapor/liquid ratio of zero at all conditions. Oil: Pressure Limit at Idle. The pressure limit at idle is 9.5 psid (65.5 kPa diff) minimum; varying from 26 to 120 psid (179.4 to 827.6 kPa diff) in the normal operating range. Engine Limits, Pratt & Whitney PW4460: Takeoff thrust, sea level, static (5 min), lb. 60,000 Maximum continuous thrust, sea level, static thrust, lb. 51,050 Flat rating ambient temperature takeoff 86o F (30o C) Maximum continuous 86o F (30o C) Maximum permissible engine rotor speeds: Low pressure rotor (N1) 4,012 rpm (111.4%) High pressure rotor (N2) 10,450 rpm (100.0%) Maximum permissible exhaust temperatures: Takeoff (5 min) 1202o F (650o C) Maximum continuous 1157o F (625o C) Starting on ground 995o F (535o C) Starting in flight 1202o F (650o C) Maximum permissible oil outlet temperatures: Continuous operation 325o F (163o C) Transient operation 350o F (177o C) (Transient operation is limited to 20 minutes) A22WE Page 24 of 50 VIII - Model MD-11 (Transport Aircraft), Approved November 8, 1990 (cont’d) Engine Limits, (cont’d) Pratt & Whitney PW4460 Fuel and Oil Pressure Limits: Fuel pressure limits apply at the engine fuel pump inlet: Minimum fuel pressure must be not less than 5 psig (34.46 kPa, gage) above the true vapor pressure of the fuel. Maximum fuel pressure must be not greater than 70 psig with a vapor-to-liquid ratio of zero. Oil pressure, minimum 70 psid (However, temporary interruption of oil pressure associated with negative "g" operation is limited to 30 seconds maximum. Normal oil pressure will be restored rapidly once the negative "g" effect has been eliminated.) Engine Limits, Pratt & Whitney PW4462: Takeoff thrust, sea level, static (5 min), lb. 62,000 Maximum continuous thrust, sea level, static thrust, lb. 51,050 Flat rating ambient temperature takeoff 86o F (30o C) Maximum continuous 86o F (30o C) Maximum permissible engine rotor speeds: Low pressure rotor (N1) 4,012 rpm (111.4%) High pressure rotor (N2) 10,450 rpm (100.0%) Maximum permissible exhaust temperatures: Takeoff (5 min) 1202o F (650o C) Maximum continuous 1157o F (625o C) Starting on ground 995o F (535o C) Starting in flight 1202o F (650o C) Maximum permissible oil outlet temperatures: Continuous operation 325o F (163o C) Transient operation 350o F (177o C) (Transient operation is limited to 20 minutes) Fuel and Oil Pressure Limits: Fuel pressure limits apply at the engine fuel pump inlet: Minimum fuel pressure must be not less than 5 psig (34.46 kPa, gage) above the true vapor pressure of the fuel. Maximum fuel pressure must be not greater than 70 psig with a vapor-to-liquid ratio of zero. Oil pressure, minimum 70 psig (However, temporary interruption of oil pressure associated with negative "g" operation is limited to 30 seconds maximum. Normal oil pressure will be restored rapidly once the negative "g" effect has been eliminated.) APU Limits: AIResearch TSCP700-4E (if installed) Power Rating Maximum at sea level 189 hp Page 25 of 50 A22WE VIII - Model MD-11 (Transport Aircraft), Approved November 8, 1990 (cont’d) APU Limits: (cont’d) (if installed) Rotor Speeds Low pressure speed (N1) 31,570 rpm (110%) High pressure speed (N2) 38,830 rpm (110%) Exhaust Gas Temperature - Starting 1602o F (872o C) Continuous 1085o F (585o C) Airspeed Limits: (CAS) Vmo/Mmo (MAXIMUM OPERATING) ALTITUDE (feet) KEAS KCAS At sea level 350 350 10,000 359.6 365 25,670 345.54 365 above 25,670 .87 Mach .87 Mach For additional airspeed limits below 90% wing tip fuel, see FAA Approved Airplane Flight Manual. Va (maneuvering). See FAA Approved Airplane Flight Manual. FLAP AND SLAT SPEEDS: FLAP SLAT SPEED MACH GROSS WEIGHT 0 ext 280 .55 MTOGW 15 ext 255 .51 MTOGW 22 ext 240 .51 MTOGW 25 ext 229 .51 MTOGW 28 ext 219 .51 MLW+3000 lb. 35 ext 198 .51 MLW+3000 lb. 50 ext 178 .51 MLW+3000 lb. Vlo (LANDING GEAR SPEEDS:) Gear Extension = 260 KCAS Gear Retraction = 230 KCAS to .7 MACH Vle Landing Gear Extended = 300 KCAS V (Landing Light Extension) Maximum Speed in Extension, Retraction, or Extended Position: Vmo/Mmo V (FUEL DUMP SPEED) No speed restriction is imposed upon the airplane during the time period in which fuel is being dumped. C.G. Range: See MD-11 Weight and Balance Manual Report No. MDC-K0032. A22WE Page 26 of 50 VIII - Model MD-11 (Transport Aircraft), Approved November 8, 1990 (cont’d) MD-11 Maximum Weight: 610,000pound 618,000pound 625, 500pound 630,500pound Takeoff Weight Takeoff Weight Takeoff Weight Takeoff Weight (See Serial Numbers Eligible) Center Main Gear Retracted Taxi and Ramp 613,000 lb. 621,000 lb. 628,000 lb. 633,000 lb. 448,000 lb. Takeoff45, 46 610,000 lb. 618,000 lb. 625,500 lb. 630,500 lb. 445,000 lb. Landing47 458,000 lb. 458,000 lb. 458,000 lb. 458,000 lb. 400,000 lb. Zero Fuel48 430,000 lb. 430,000 lb. 430,000 lb. 430,000 lb. 370,000 lb. Gear Jacking Weight 613,000 lb. 621,000 lb. 628,000 lb. 633,000 lb. Fuselage and Wing Jack Weight 508,000 lb. 508,000 lb. 508,000 lb. 508,000 lb. Minimum Crew: For all flights: pilot, copilot. Maximum Passengers: (See NOTE 6) Maximum Baggage: (See Weight and Balance Manual) Fuel Capacity: FUEL TANK CAPACITY (lb.) CAPACITY 1 MAIN 2 MAIN 3 MAIN AUX FWD CARGO AUX 49 TAIL MAX 7.1 lb./gal 42,908 67,863 42,908 103,968 21,724 13,908 USABLE 6.7 lb./gal 40,491 64,040 40,491 98,111 20,500 13,124 UNDUMPABLE 6.7 lb./gal 12,973 13,917 12,973 0 0 0 Note: An additional 436 lb. (6.7 lb./gal) of useable fuel is available from manifold piping upon the completion of crossfeeding. This fuel is made available when the MANF DRAIN alert is displayed. An additional 173 lb. (6.7 lb./gal) usable fuel in the engine and lines is available to the engine on the fuel runout. No action is required to make this fuel available. 45 All MD-11 passenger aircraft are eligible for 618,000 pounds maximum takeoff weight when modified per Douglas Service Bulletin 103-1 or production equivalent. 46 All MD-11 airplanes are eligible for 630,500 pound maximum takeoff weight when modified in accordance with Douglas Service Bulletins MD11-28-079, MD11-31-073 (or equivalent chapter 31 FMC and FCC Program Option approved Service Bulletin), MD11-32-057, and MD11-57-032 or Service Modification Drawing Number SM11570020 Revision A, or production equivalent. 47 Fuel dump valves required for operation in excess of maximum landing weight (See NOTE 1 (f)). 48 All weight in the airplane above this weight must be fuel. 49 Applicable when forward cargo auxiliary fuel tank is installed per Douglas Service Modification Drawing SM11280036 Revision E, or production equivalent. Page 27 of 50 A22WE VIII - Model MD-11 (Transport Aircraft), Approved November 8, 1990 (cont’d) Oil Capacity: 22 to 23 quarts Indicated 26 to 27 quarts (tank) Maximum Operating Altitude: 43,200 feet MAC: 295.8 inches (Leading Edge of MAC Station 1312) Service Life Limits: See NOTE 3. MD-11 Serial Numbers Eligible: Maximum Takeoff Weight of 610,000 lbs. (See NOTE 10) GE Powered: 48449, 48450, 48459, Maximum Takeoff Weight of 618,000 lbs.50 GE Powered: 48555. P&W Powered: 48437, 48488, 48518, 48519, 48521 Maximum Takeoff Weight of 625,500 lbs51 GE Powered: 48556, 48557, 48558, 48559, 48560, 48561, 48562, 48563. P&W Powered: 48532, 48533 Maximum Takeoff Weight of 630,500 lbs. 52 GE Powered: 48564 P&W Powered: 48623, 48743 Other Information: See "Data Pertinent to All Models" IX - Model MD-11F (Transport Aircraft), Approved November 8, 1990 Engines: See Section VIII (MD-11) Fuel: See NOTE 4. Oil: See NOTE 5. 50 All MD -11 passenger airplanes are eligible for 618,000 pound maximum takeoff weight when modified in accordance with Douglas Service Bulletin 103-1 or production equivalent. 51 All MD-11 passenger airplanes are eligible for 625,500 pound maximum takeoff weight when modified in accordance with Douglas Service Bulletin 103-009 or production equivalent. 52 All MD-11 passenger airplanes are eligible for 630,500 pound maximum takeoff weight when modified in accordance with Douglas Service Bulletins MD11-28-079, MD11-31-073 (or equivalent chapter 31 FMC and FCC Program Option approved Service Bulletin), MD11-32-057, and MD11-57-032, or Service Modification Drawing Number SM11570020 Revision A, or production equivalent. A22WE Page 28 of 50 IX - Model MD-11F (Transport Aircraft), Approved November 8, 1990 (cont’d) Engine Limits: See Section VIII (MD-11) APU Limits: (if installed) See Section VIII (MD-11) Airspeed Limits: See Section VIII (MD-11) C.G. Range: See MD-11 Weight and Balance Manual Report No. MDC-K5542. MD-11F Maximum Weight: (See NOTE 10) 610,000pound 618,000pound 625,500pound 630,500pound Takeoff Weight Takeoff Weight Takeoff Weight Takeoff Weight (See Serial Numbers Eligible) Center Main Gear Retracted Taxi and Ramp 613,000 lb. 621,000 lb. 628,000 lb. 633,000 lb. 448,000 lb. Takeoff 610,000 lb. 618,000 lb. 625,500 lb. 630,500 lb. 445,000 lb. Landing53 471,500 lb. 471,500 lb. 481,500 lb. 491,500 lb. 400,000 lb. Zero Fuel54 451,300 lb. 451,300 lb. 451,300 lb. 461,300 lb. 370,000 lb. Gear Jacking Weight 613,000 lb. 621,000 lb. 628,000 lb. 633,000 lb. Fuselage and Wing Jack Weight 508,000 lb. 508,000 lb. 508,000 lb. 508,000 lb. Minimum Crew: For all flights: Pilot, Copilot. Maximum Passengers: See FAA approved exemption number 6656 for the accommodation of up to two supernumeraries immediately aft of the cockpit. And crew rest facility immediately aft of the smoke barrier and crash net, on MD-11 freighter aircraft equipped with a Class E cargo compartment. See FAA approved exemption number 6753 for the accommodation of up to five supernumeraries immediately aft of the cockpit on MD-11 freighter aircraft equipped with a Class E cargo compartment Maximum Baggage: (See Weight and Balance Manual) Fuel Capacity: See Section VIII MD-11 Oil Capacity: See Section VIII MD-11 Maximum Operating Altitude: 43,200 feet MAC: 295.8 inches (Leading Edge of MAC Station 1312) 53 Fuel dump valves required for operation in excess of maximum landing weight. (See NOTE 1(f)). 54 All weight in the airplane above this weight must be fuel. Page 29 of 50 A22WE IX - Model MD-11F (Transport Aircraft), Approved November 8, 1990 (cont’d) Service Life Limits: See NOTE 3 MD-11F Serial Numbers Eligible: Maximum Takeoff Weight of 610,000 lbs. (See NOTE 10) GE Powered: 48401, 48402, 48459, 48460, 48461, 48514, 48528, 48547, 48548, 48549, 48602, 48603, 48605. Maximum Takeoff Weight of 618,000 lbs. 55 P&W Powered: 48408 Maximum Takeoff Weight of 625,500 lbs. 56 GE Powered: 48415, 48420, 48487, 48542, 48543, 48544, 48545, 48546, 48747, 48748, 48749, 48767 P&W Powered: 48485, 48486, 48616, 48617, 48618, 48629, 48633. Maximum Takeoff Weight of 630,500 lbs. 57 GE Powered: 48404, 48405, 48406, 48411 - 48412, 48413, 48414, 48416, 48417, 48418, 48421, 48426, 48427, 48428, 48429, 48430, 48431, 48434 - 48436, 48439, 48451, 48458, 48481, 48489 - 48491, 48499, 48500, 48501, 48502, 48503, 48504, 48505, 48512, 48513, 48527, 48544, 48550, 48551- 48553, 48581, 48596- 48598, 48630, 48744, 48745, 48753 – 48755, 48758, 48766, 48768, 48769, 48770, 48773, 48775, 48776, 48777, 48778, 48779, 48780, 48781 – 48787, 48789, 48790, 48794, 48798 – 48806. P&W Powered: 48407, 48410, 48443, 48444, 48445, 48446, 48447, 48452, 48453, 48454, 48455, 48456, 48457, 48458, 48461, 48469, 48470, 48471, 48472, 48473, 48474, 48475, 48476, 48477, 48478, 48479, 48480, 48484, 48495, 48496, 48497, 48498, 48520, 48523, 48538, 48539, 48540, 48541, 48565, 48566, 48571, 48572, 48573, 48574, 48575, 48576, 48577, 48578, 48579, 48600, 48601, 48623, 48624, 48631, 48632, 48634, 48746, 48756, 48757, 48774, 48788, 48791, 48792. Other Information: See "Data Pertinent to All Models" X – Model MD-10-10F (Transport Aircraft), Approved May 9, 2000 Engines: 3 General Electric CF6-6D or CF6-6K Turbofan Engines Fuel: See NOTE 4. 55 All MD-11F freighter airplanes are eligible for 618,000 pound maximum takeoff weight when modified in accordance with Douglas Service Bulletin 103-1 or production equivalent. 56 All MD-11F freighter airplanes are eligible for 625,500 pound maximum takeoff weight when modified in accordance with Douglas Service Bulletin 103-009 or009 or production equivalent. 57 All MD-11F Freighter airplanes are eligible for 630,500 pound maximum takeoff weight when modified in accordance with Douglas Service Bulletins MD11-28-079, MD11-31-073 (or equivalent chapter 31 FMC and FCC Program Option approved Service Bulletin), MD11-32-057, and MD11-57-032, or Service Modification Drawing Number SM11570020 Revision A, or production equivalent. A22WE Page 30 of 50 X – Model MD-10-10F (Transport Aircraft), Approved May 9, 2000 (cont’d) Oil: See NOTE 5. Engine Limits: CF6-6D/-6K Takeoff Thrust. Sea Level, Static (5 min) - flat to 88oF 39,300 lb. Maximum Continuous (flat to 77oF) 37,500 lb. Maximum permissible engine rotor operating speeds N1 (Low Compressor) 3810 rpm (111%) N2 (High Compressor) 9925 rpm (101%) Maximum permissible engine temperature Turbine exhaust gas temperatures at turbine outlet Take off (5 min.) 1670oF (910oC) Maximum Continuous 1616oF (880oC) Maximum Acceleration (2 min.) 1697oF (925oC) Starting (Max. Transient for 40 sec.) 1652oF (900oC) (Max. No Time Limit) 1382oF (750oC) Maximum permissible oil outlet temperature Continuous operation 320oF (160oC) Transient operation 58 347oF (175oC) APU Limits: AiResearch TSCP700-4B (if installed) Power Rating Maximum at sea level 189 hp Rotor Speeds Low pressure speed (N1) 31,570 rpm (110%) High pressure speed (N2) 38,830 rpm (110%) Exhaust Gas Temperature Maximum during operation 1085oF (585oC) Maximum indicated temperature during each starting cycle 1085oF (585oC) Airspeed Limits: (CAS) VMO/MMO (Maximum Operating) At Sea Level 340K At 27,860 ft. 340K (M=0.85) At 42,000 ft. 248K (M=0.85) VA (Maneuvering) See FAA Approved Airplane Flight Manual VFE Flap Position (Inboard) 5o 260K (M = 0.51) 15o 250K (M = 0.51) 20o 233K (M = 0.51) 25o 214K (M = 0.51) 35o 187K (M = 0.51) 50o 171K (M = 0.51) 58 Transient operation above 320°F (160°C) is limited to 15 minutes. Page 31 of 50 A22WE X – Model MD-10-10F (Transport Aircraft), Approved May 9, 2000 (cont’d) Airspeed Limits: (cont’d) (CAS) VSLAT (Slat Operating) Takeoff and Approach: Flap Position (Inboard) 5o 260K (M = 0.51) 15o 250K (M = 0.51) 25o 214K (M = 0.51) Landing Flap Position (Inboard) 35o 187K (M = 0.51) 50o 171K (M = 0.51) Autoslat Flaps retracted 260K (M = 0.51) VLO (Landing Gear) Retraction 230K (M = 0.70) Extension 260K (M = 0.70) VLE (Landing Gear Extended) 300K (M = 0.70) V (Landing light extension) Maximum speed extension retraction, or extended position VMO/MMO V (Fuel Dump) 325K up to 28,000 feet M = 0.82 above 28,000 feet C.G. Range: See the appropriate FAA Approved Airplane Flight Manual and Weight and Balance Manual. MD-10-10F Maximum Weight: For Takeoff Weight (See NOTE 10) 440,000 pounds (See Serial Numbers Eligible) Taxi and Ramp 443,000 lb. Takeoff 440,000 lb. Landing 59 375,000 lb. (374,500 lb. when carbon brakes are installed) Zero Fuel 60 355,000 lb. Gear Jacking Weight 443,000 lb. Fuselage and Wing Jack Weight 388,000 lb. Minimum Crew: For all flights: Pilot, Copilot. Maximum Passengers: (See NOTE 23). 59 Fuel dump valves required for operation in excess of maximum landing weight. See NOTE 1(f). 60 All weight in airplanes above this weight must be fuel. A22WE Page 32 of 50 X – Model MD-10-10F (Transport Aircraft), Approved May 9, 2000 (cont’d) Maximum Baggage: (See Weight and Balance Manual). Fuel Capacity: Fuel Tank Capacity (pounds) Usable Location Structural (6.7 lb./gal.) Arm (inches) Main No. 1 42,579 40,116 1488 Main No. 2 68,998 64,969 1296 Main No. 3 42,579 40,116 1488 Crossfeed Manifold & Lines 609 1429 Oil Capacity: 24.3 lb./engine usable at 8.1 lb./gal. with wing engines moment arm at 1125 in. and tail engine moment arm at 2200 in. Maximum Operating Altitude: 42,000 feet MAC: 300.682 inches (Leading Edge of MAC Station 1299.83) Service Life Limits: See NOTE 3 MD-10-10F Serial Numbers Eligible: Conversion from DC-10-10 or –10F to MD-10-10F (See NOTE 24). (See NOTE 10) Maximum Takeoff Weight of 440,000 pounds 46521, 46601, 46602, 46605, 46606, 46607, 46608, 46609, 46610, 46611, 46612, 46613, 46615, 46616, 46617, 46619, 46620, 46621, 46622, 46623, 46624, 46625 - 46628, 46629, 46630, 46631, 46633 - 46636, 46708, 46710, 46907, 46930, 46938, 46939, 46947, 46948, 46970, 46973, 46984, 46989, 46994, 46996, 47803-47808, 47810, 47827, 47828, 47829, 47830, 47965, 48260 - 48262, 48263, 48264. Other Information: See "Data Pertinent to All Models" XI Model MD-10-30F (Transport Aircraft), Approved May 9, 2000 Engines: 3 General Electric CF6-50C2 Turbofan Engines. Fuel: See NOTE 4. Oil: See NOTE 5. Engine Limits: CF6-50C2 Static Thrust, Sea Level Takeoff 61 51,800 lb. Maximum Continuous 46,300 lb. (flat to 86°F) 61 5 minutes flat to 86°F. Page 33 of 50 A22WE XI Model MD-10-30F (Transport Aircraft), Approved May 9, 2000 (cont’d) Engine Limits: (cont’d) CF6-50C2 Maximum permissible engine rotor operating speeds N1 (Low Compressor) 4102 rpm (119.5%) N2 (High Compressor) 10761 rpm (109.5%) Maximum permissible engine temperature Turbine exhaust gas temperature at turbine outlet Takeoff (5 min.) 1733oF (945oC) Maximum Continuous 1670oF (910oC) Maximum for Acceleration (2 min.) 1760oF (960oC) Starting (Max. Transient for 40 sec.) 1652oF (900oC) (Max. no time limit) 1382oF (750oC) Maximum permissible oil outlet temperature Continuous Operation 320oF (160oC) Transient Operation 62 347oF (175oC) APU Limits: AiResearch TSCP700-4B (if installed) Power Rating Maximum at sea level 189 hp Rotor Speeds Low pressure speed (N1) 31,570 rpm (110%) High pressure speed (N2) 38,830 rpm (110%) Exhaust Gas Temperature Maximum during operation 1085oF (585oC) Maximum indicated temperature during each starting cycle 1085oF (585oC) Airspeed Limits: VMO/MMO (Maximum Operating) (CAS) At Sea Level 350K At 10,000 ft. 376K At 24,820 ft. 376K (M = 0.88) At 42,000 ft. 258K (M = 0.88) VA (Maneuvering) See FAA Approved Airplane Flight Manual 62 Transient operation above 320°F (160°C) is limited to 15 minutes. A22WE Page 34 of 50 XI Model MD-10-30F (Transport Aircraft), Approved May 9, 2000 (cont’d) Airspeed Limits: (cont’d) (CAS) For Takeoff Weight For Takeoff Weights VFE Flap Position 565,000 lb. 572,000 lb./580,000 lb. (Inboard) (See Serial Numbers Eligible) (See Serial Numbers Eligible) 5o 260K (M = 0.51) 270K (M = 0.55) 15o 255K (M = 0.51) 255K (M = 0.51) 20o 240K (M = 0.51) 240K (M = 0.51) 25o 221K (M = 0.51) 221K (M = 0.51) 35o 194K (M = 0.51) 194K (M = 0.51) 50o 178K (M = 0.51) 178K (M = 0.51) VSLAT (Slat Operating) Takeoff and Approach Flap Position 5o 260K (M = 0.51) 270K (M = 0.55) 15o 255K (M = 0.51) 255K (M = 0.51) 25o 221K (M = 0.51) 221K (M = 0.51) Landing Flap Position 35o 194K (M = 0.51) 194K (M = 0.51) 50o 178K (M = 0.51) 178K (M = 0.51) Autoslat Flaps retracted 260K (M = 0.51) 270K (M = 0.55) VLO Landing Gear Retraction 230K (M = 0.70) 230K (M = 0.70) Extension 260K (M = 0.70) 260K (M = 0.70) VLE (Landing Gear Extended) 300K (M = 0.70) 300K (M = 0.70) V (Landing light extension) - Maximum speed in extension, retraction, or extended position VMO/MMO V (Fuel Dump) 325K up to 28,000 feet M = 0.82 above 28,000 feet C.G. Range: See the appropriate FAA Approved Airplane Flight Manual and Weight and Balance Manual. Page 35 of 50 A22WE XI Model MD-10-30F (Transport Aircraft), Approved May 9, 2000 (cont’d) MD-10-30F Maximum Weight: (See NOTE 10) For Takeoff Weight For Takeoff Weight 565,000 pound 572,000 pound (See Serial Numbers Eligible) (See Serial Numbers Eligible) Center Main Center Main Center Main Center Main Gear Retracted Gear Extended Gear Retracted Gear Extended or Removed _ Taxi and Ramp 568,000 lb. 463,000 lb. 575,000 lb. 478,000 lb. Takeoff 63 565,000 lb. 460,000 lb. 572,000 lb. 475,000 lb. Landing 64 421,000 lb. 400,000 lb. 424,000 lb. 400,000 lb. Zero Fuel 65 401,000 lb. 391,000 lb. 401,000 lb. 391,000 lb. Gear Jacking Wt. 568,000 lb. 463,000 lb. 575,000 lb. 478,000 lb. Fuselage & Wing Jack Weight 508,000 lb. 463,000 lb. 508,000 lb. 478,000 lb. For Takeoff Weight 580,000 pounds (See Serial Numbers Eligible) Center Main Center Main Gear Retracted Gear Extended or Removed Taxi and Ramp 583,000 lb. 478,000 lb. Takeoff 66 580,000 lb. 475,000 lb. Landing 67 424,000 lb. 400,000 lb. Zero Fuel 68 401,000 lb. 391,000 lb. Gear Jacking Wt. 583,000 lb. 478,000 lb. Fuselage & Wing Jack Weight 508,000 lb. 478,000 lb. Minimum Crew: For all Flights: Pilot, Copilot Maximum Passengers: (See NOTE 23). 63 For takeoff weights above 555,000 pounds, 28 ply main landing gear tires and modification per Douglas Service Bulletin 57-28 or equivalents are required. 64 Fuel dump valves required for operation in excess of maximum landing weight. See NOTE 1 (f). 65 All weight in airplane above this weight must be fuel. 66 For takeoff weights above 555,000 pounds, 28 ply main landing gear tires and modification per Douglas Service Bulletin 57-28 or equivalents are required. 67 Fuel dump valves required for operation in excess of maximum landing weight. See NOTE 1 (f). 68 All weight in airplane above this weight must be fuel. A22WE Page 36 of 50 XI Model MD-10-30F (Transport Aircraft), Approved May 9, 2000 (cont’d) Maximum Baggage: (See Weight and Balance Manual). Fuel Capacity: Fuel Tank Capacity (pounds) Usable Usable 69 Location Structural (6.7 lb./gal.) (6.7 lb./gal.) Arm (inches) Main No. 1 43,202 40,203 40,704 1492.6 Main No. 2 69,495 64,969 65,438 1296.0 Main No. 3 43,202 40,203 40,704 1492.6 Center Wing Auxiliary 104,141 97,409 98,111 1266.1 Crossfeed Manifold & Lines 609 609 1420.5 NOTE: The integrity of the transfer system must be demonstrated per Maintenance Manual, Chapter 28-21- 100, section titled "Manifold Integrity Check" whenever the system is disturbed for maintenance. Also, if the tank overfilled light is illuminated any time during fueling, comply with the caution note in Chapter 12-11-04, section titled "Safety and Operating Precautions", item pertaining to tank overfilled condition. Oil Capacity: 24.3 lb./engine usable at 8.1 lb./gal. with wing engines moment arm at 1125 in. and tail engine moment arm at 2200 in. Maximum Operating Altitude: 42,000 feet MAC: 295.78 inches (Leading Edge of MAC St. 1311.95) Service Life Limits: See NOTE 3. MD-10-30F Serial Numbers Eligible: Conversion from DC-10-30 or –30F to MD-10-30F (See NOTE 24). (See NOTE 10) Maximum Takeoff Weight of 565,000 pounds 46800, 46801, 46802, 46871, 47835, 47836. Maximum Takeoff Weight of 572,000 pounds 46835, 46837, 46992, 47820, Maximum Takeoff Weight of 580,000 pounds 48287, 48291, 48297, 48300, 48311, 48312, 48313, 48314. Other Information: See "Data Pertinent to All Models" Datum: For DC-10: 239 inches forward of fuselage nose (Station 0) For MD-11: 139 inches forward of fuselage nose (Station 0) For MD-10: 239 inches forward of fuselage nose (Station 0) 69 When modified per Douglas Service Bulletins 28-27 and 28-32 or equivalents. Page 37 of 50 A22WE DATA PERTINENT TO ALL MODELS Leveling Means: One of the following three systems in each airplane: (a) Two sets of lugs in nose wheel well (1) DC-10: Lateral at station 595 MD-11: Lateral on centerline 2 inches forward of station 495. MD-10: Lateral at station 595 (2) DC-10: Longitudinal 24 inches left of centerline, 20 inches and 40 inches forward of station 595. MD-11: Longitudinal 24 inches left of centerline, 20 inches and 40 inches forward of station 495. MD-10: Longitudinal 24 inches left of centerline, 20 inches and 40 inches forward of station 595. (b) Plumb bob and grid plate at station 1516 aft bulkhead, right hand main gear wheel well, if installed per Service Bulletin 53-52. (c) Set of lugs at station 1521 in right hand main gear wheel well. Lay flat plate on which to put level for either lateral or longitudinal. Control Surface: To ensure 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: For DC-10: Douglas Drawing NXH 6004, "Rigging Procedures," and NXH-6005, "Throws - Flight Controls." For MD-11: Douglas Drawing NXH 6704, "Rigging Instructions – Flight & Accessory Controls," and NXH-6705, "Throws - Flight Controls." For MD-10: Douglas Drawing SP10270016, "Rigging Procedures," and NXH-6005, "Throws - Flight Controls." Certification Basis: For all Model DC-10 airplanes issuance of a Type Certificate is based upon compliance with the following: (1) FAR 25, dated February 1, 1965, with Amendments 1 through 22 "Airworthiness Standards: Transport Category Airplanes," and FAR 25.471 of Amendment 25-23. (2) FAR Part 36 "Noise Standards: Aircraft Type Certification." (3) Special Conditions No. 25-18-WE-7 dated January 7, 1970 and Special Conditions No. 25-18-WE-7, Amendment No. 1 dated July 9, 1971. 70 (4) Special Condition No. 25-46-WE-14 dated October 26, 1972. (Models DC-10-30, DC-10-30F, DC-10-40, and DC-10-40F) 70 See NOTE 7 A22WE Page 38 of 50 DATA PERTINENT TO ALL MODELS (cont’d) Certification Basis: (cont’d) (5) Based on 14 CFR § 21.101(g) for changes to type certificates (TCs), applicable provisions of 14 CFR part 26 are included in this certification basis. For any future 14 CFR part 26 amendments, the holder of this TC must demonstrate compliance with the applicable sections. Compliance has been found for the following regulations: 14 CFR § 26.11 (Amdt. No. 26-0), 26.43 and 26.45 (Amdt.No. 26-1). Compliance with the following optional requirements has been established: Ditching Provisions 25.801 (Overwater operation can be approved when the aircraft has been equipped and installation has been approved according to FAR 25.801) Ice Protection Provisions 25.1419 In accordance with Title 14 CFR Part 21.21(b)(1), the following Equivalent Safety Findings (ESF) exist for the DC-10 with respect to the following regulations: §25.981(a)(3) at Amdt. 102 Fault Current Detectors The following exemptions are part of the DC-10 certification 1. Number 1573 issued April 28, 1972 - exemption from §25.807(c)(5) to permit evacuation with a passenger seating capacity of 80 for a pair of oversize Type I exits. 2. Number 2453 issued September 26, 1977 - exemption from §25.807(c)(1) to permit evacuation of passengers with either of the following exit-seat configurations: a. one oversize Type I emergency exit meeting the conditions specified in Exemption No. 1573 on each side of the fuselage with a passenger seating capacity of 50; or b. one Type A emergency exit on each side of the fuselage with a passenger seating capacity of 70. 3. Number 6752 dated April 18, 1997, - exemption from 14 CFR §§ 25.785(d), 25.807(c)(1), 25.857(e), and 25.1447(c)(1) for the accommodation of up to four supernumeraries immediately aft of the cockpit on freighter aircraft equipped with a Class E cargo compartment. 4. Number 10842 issued August 15, 2013, - exemptions from 14 CFR §§ 25.981(a)(3) and 25.901(c), for the installation of an improved fuel pump electrical connector independently of the improved fuel pump electrical connector until such time as both are required to be installed by AD 2013-08- 23. For all Model MD-11 airplanes issuance of a Type Certificate is based upon compliance with the following: (1) Part 25 of the Federal Aviation Regulations, as amended by Amendments 25-1 through 25-61, except for §§ 25.607, 25.631 71, and 25.1309 72 as amended by Amendment 25-22; §25.109 as amended by Amendment 25-41; and §25.832 73 and §25.858. 71 New structure will comply with Amendment 25-61. 72 New systems and systems with major changes will comply with Amendment 25-61. 73 The ozone converters are not required for MD-11F airplanes operated in all cargo configurations. Page 39 of 50 A22WE DATA PERTINENT TO ALL MODELS (cont’d) Certification Basis: (cont’d) (2) Special Federal Aviation Regulation (SFAR) 27, as amended by Amendments 27-1 through 27-6 and any later amendments in existence at the time of certification. (3) Part 36 of the Federal Aviation Regulations, as amended by Amendments 36-1 through 36-16, and any later amendments in existence at the time of certification. McDonnell Douglas has elected to comply with the Stage 3 noise level requirements. (4) Special Condition No. 25-ANM-35 dated October 12, 1990. "Lightning and External High Energy Radio Frequency (RF) Protection and Automatic Longitudinal and Lateral Stability Augmentation System" (All MD-11 Models). (5) Based on 14 CFR § 21.101(g) for changes to type certificates (TCs), applicable provisions of 14 CFR part 26 are included in this certification basis. For any future 14 CFR part 26 amendments, the holder of this TC must demonstrate compliance with the applicable sections. Compliance has been found for the following regulations: 14 CFR § 26.11 (Amdt. No. 26-0), § 26.33 (Amdt. No 26-3), and § 26.43 and § 26.45 (Amdt.No. 26-1). Compliance with the following optional requirements has been established: Ditching Provisions 25.801 (Overwater operation can be approved when the aircraft has been equipped and installation has been approved according to FAR 25.801) Ice Protection Provisions 25.1419 In accordance with Title 14 CFR Part 21.21(b)(1), the following Equivalent Safety Findings (ESF) exist for the MD-11 with respect to the following regulations: §25.677(b) Trim Position Indicator §25.819 Isolated Cabin Crew Rest module §25.981(a)(3) at Amdt. 102 Fault Current Detectors §25.1447(c)(1) & (c)(3) Lavatory oxygen installation §25.1459(a)(6) Flight Data Recorder time marking of SATCOM Transmissions The following exemptions are part of the MD-11 certification basis: (1) Number 1573 issued April 28, 1972 - exemption from §25.807(c)(5) to permit evacuation with a passenger seating capacity of 80 for a pair of oversize Type I exits. (2) Number 2453 issued September 26, 1977 - exemption from §25.807(c)(1) to permit evacuation of passengers with either of the following exit-seat configurations: a. one oversize Type I emergency exit meeting the conditions specified in Exemption No. 1573 on each side of the fuselage with a passenger seating capacity of 50; or b. one Type A emergency exit on each side of the fuselage with a passenger seating capacity of 70. (3) Number 5405 issued February 11, 1992, - exemption from §25.813(e) to permit installation of a door between passenger compartments. (4) Number 6656 dated December 4, 1996 and April 3, 1997, - exemption from 14 CFR §§ 25.785(d), 25.807(c)(1), 25.857(e), and 25.1447(c)(1) for the accommodation of up to two supernumeraries immediately aft of the cockpit. And crew rest facility immediately aft of the smoke barrier and crash net, on MD-11 freighter aircraft equipped with a Class E cargo compartment. A22WE Page 40 of 50 DATA PERTINENT TO ALL MODELS (cont’d) Certification Basis: (cont’d) (5) Number 6753 April 21, 1998, - exemption from 14 CFR §§ 25.785(d), 25.807(c)(1), 25.857(e), and 25.1447(c)(1) for the accommodation of up to five supernumeraries immediately aft of the cockpit on MD-11 freighter aircraft equipped with a Class E cargo compartment (6) Number 10842 issued August 15, 2013, - exemptions from 14 CFR §§ 25.981(a)(3) and 25.901(c), for the installation of an improved fuel pump electrical connector independently of the improved fuel pump electrical connector until such time as both are required to be installed by AD 2013-08- 23. For all Model MD-10 airplanes issuance of a Type Certificate is based upon compliance with the following: (1) 14 CFR Part 25 of the Federal Aviation Regulations, dated February 1, 1965, with Amendments 1 through 22 "Airworthiness Standards: Transport Category Airplanes," and FAR 25.471 of Amendment 25-23, for all areas not affected by the change. (2) 14 CFR Part 25 of the Federal Aviation Regulations, dated February 1, 1965, including Amendments 25-1 through 25-89 for all areas affected by the change. The following list indicates the FAR’s that are complied with through Amendment Level 25-89. 25.103 25.603 25.683 25.831 25.1019 25.1323 25.1431 25.1529 25.125 25.605 25.685 25.841 25.1039 25.1325 25.1435 25.1541 25.145 25.607 25.689 25.843 25.1141 25.1326 25.1439 25.1543 25.149 25.609 25.693 25.855 25.1142 25.1327 25.1441 25.1545 25.207 25.611 25.699 25.857 25.1145 25.1329 25.1443 25.1549 25.301 25.613 25.703 25.858 25.1161 25.1331 25.1445 25.1551 25.303 25.615 25.729 25.863 25.1165 25.1333 25.1447 25.1553 25.305 25.619 25.733 25.901 25.1207 25.1335 25.1449 25.1555 25.307 25.621 25.771 25.903 25.1301 25.1337 25.1451 25.1563 25.397 25.623 25.773 25.943 25.1303 25.1351 25.1453 25.1581 25.399 25.625 25.777 25.952 25.1305 25.1353 25.1457 25.1583 25.405 25.629 25.779 25.954 25.1307 25.1355 25.1459 25.1585 25.561 25.671 25.783 25.961 25.1309 25.1357 25.1461 25.1587 25.571 25.672 25.789 25.991 25.1316 25.1363 25.1501 25.581 25.675 25.801 25.993 25.1321 25.1381 25.1525 25.601 25.677 25.812 25.1001 25.1322 25.1419 25.1527 (3) Compliance as defined in McDonnell Douglas Report MDC 97K1097 where some equipment installations and equipment comply with §25.1309 as amended by Amendment 25-22 and others comply with §25.1309 as amended through Amendment 25-89. (4) 14 CFR Part 36 of the Federal Aviation Regulations "Noise Standards: Aircraft Type Certification", effective December 1, 1969, including Amendments 36-1 through 36-22. (5) 14 CFR Part 34 of the Federal Aviation Regulation “Fuel Venting and Exhaust Emissions Requirements” effective September 10, 1990, Amendment 34-1 through 34-3. (6) Special Conditions No. 25-18-WE-7 dated January 7, 1970 and Special Conditions No. 25-18-WE-7, Amendment No. 1 dated July 9, 1971. 74 (7) Special Condition No. 25-46-WE-14 dated October 26, 1972. (Models DC-10-30, DC-10-30F, DC-10-40, and DC-10-40F.) 74 See NOTE 7 Page 41 of 50 A22WE DATA PERTINENT TO ALL MODELS (cont’d) Certification Basis: (cont’d) (8) Special Condition “High Intensity radiated Fields (HIRF)” Special Condition No. 25-156-SC dated February 15, 2000. (9) Special Condition No. 25-ANM-35 dated October 12, 1990. "Lightning and External High Energy Radio Frequency (RF) Protection" (On components originally certified on MD-11 Models, see McDonnell Report MDC 97K1097 where some equipment installations and equipment comply.) (10) Based on 14 CFR § 21.101(g) for changes to type certificates (TCs), applicable provisions of 14 CFR part 26 are included in this certification basis. For any future 14 CFR part 26 amendments, the holder of this TC must demonstrate compliance with the applicable sections. Compliance has been found for the following regulations: 14 CFR § 26.11 (Amdt. No. 26-0), § 26.33 (Amdt. No 26-3), and § 26.43 and § 26.45 (Amdt.No. 26-1). Compliance with the following optional requirements has been established: Ditching Provisions 25.801 (Overwater operation can be approved when the aircraft has been equipped and installation has been approved according to FAR 25.801.) Ice Protection Provisions 25.1419 In accordance with Title 14 CFR Part 21.21(b)(1), the following Equivalent Safety Findings (ESF) exist for the MD-10 with respect to the following regulations: §25.677(b) Trim Position Indicator §25.981(a)(3) at Amdt. 102 Fault Current Detectors §25.1309(a)(1). Unwanted In-Flight Thrust Reversal Deployment The following exemption is part of the MD-10 certification basis: (1) Number 6873 issued March 23, 1999, - exemptions from 14 CFR §§ 25.785(d), 25.807(c)(1), 25.857(e), and 25.1447(c)(1) for the accommodations up to four supernumeraries in a “courier area” aft of the cockpit door and forward of a rigid cargo barrier. Or allow up to two supernumeraries in a “courier module” area aft of the cockpit door and forward of a 9g crash net MD-10 freighter aircraft equipped with a Class E cargo compartment. (2) Number 10842 issued August 15, 2013, - exemptions from 14 CFR §§ 25.981(a)(3) and 25.901(c), for the installation of an improved fuel pump electrical connector independently of the improved fuel pump electrical connector until such time as both are required to be installed by AD 2013-08- 23. Certification Maintenance Requirements: DC-10 Certification Maintenance Requirements (CMR) are listed in FAA approved MDC Report No. MDC-03K1006, Revision NEW or later FAA approved revision and the engine Type Certificate Data Sheet. The more restrictive requirement from these two documents shall be in force. MD-11 Certification Maintenance Requirements (CMR) are listed in FAA approved MDC Report No. MDC-K4174, Revision Q or later FAA approved revision and the engine Type Certificate Data Sheet. The more restrictive requirement from these two documents shall be in force. MD-10 Certification Maintenance Requirements (CMR) are listed in FAA approved MDC Report No. MDC-99K1069, Revision B or later FAA approved revision and the engine Type Certificate Data Sheet. The more restrictive requirement from these two documents shall be in force. Production Basis: Production Certificate No. 27, which transferred to production certificate No. 700, on 30 January 1998. A22WE Page 42 of 50 DATA PERTINENT TO ALL MODELS (cont’d) Required Equipment: The basic required equipment as prescribed in the applicable airworthiness regulations (See Certification Basis) must be installed in the aircraft for certification. All of the required equipment that must be installed as well as optional equipment installations approved by the FAA are contained in the following: DC-10-10 Report No. MDC-J0994, Chapter 2, "Weight and Balance Manual" DC-10-10F Report No. MDC-J0997, Chapter 2, "Weight and Balance Manual" DC-10-15 Report No. MDC-J0995, Chapter 2, "Weight and Balance Manual" DC-10-40 Report No. MDC-J0998, Chapter 2, "Weight and Balance Manual" DC-10-30 Report No. MDC-J1001, Chapter 2, "Weight and Balance Manual" DC-10-30F Report No. MDC-J1002, Chapter 2, "Weight and Balance Manual" DC-10-30F (KC-10A) T.O. 1C-10(K) A-5, Chg. 1 dated March 18, 1981, Section II. DC-10-30F (KDC-10) Report No. MDC-94K0295, Chapter 2, "Weight and Balance Manual" DC-10-40F Report No. MDC-J0999, Chapter 2, "Weight and Balance Manual" MD-11 Report No. MDC-K0032, Chapter 2, "Weight and Balance Manual." Model MD-11. MD-11 Report No. MDC-K5542, Chapter 2, "Weight and Balance Manual." Model MD-11F. MD-10-10F Report No. MDC 98K1080, Chapter 2, "Weight and Balance Manual." MD-10-30F Report No. MDC 99K1043, Chapter 2, "Weight and Balance Manual." Service Information: McDonnell Douglas Model DC-10, MD-11 and MD-10 Structural Repair Manual, Volume I and Volume IV is FAA approved. All McDonnell Douglas Service Bulletins and other service information, when FAA approved will carry a statement to this effect. Automatic Landing System Limitations: See NOTE 8. NOTES 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. The following Douglas Aircraft Company Report or Military Tech. order contains loading information for each airplane and interior arrangement configuration as delivered. This report contains, or refers to, information relative to location of all passenger and crew member seats, location and capacity of all cargo and baggage compartments, buffets, storage spaces and coat rooms, location and capacity of lounges and lavatories, and the required placards in the passenger compartment. Report No. MDC-J0994, "Weight & Balance Manual", Model DC-10-10. Report No. MDC-J0997, "Weight & Balance Manual", Model DC-10-10F. Report No. MDC-J0998, "Weight & Balance Manual", Model DC-10-40. Report No. MDC-J1001, "Weight & Balance Manual", Model DC-10-30. Report No. MDC-J1002, "Weight & Balance Manual", Model DC-10-30F. T.O. 1C-10(K) A-5, Chg. 1, dated 15 March 1981, "Basic Weight Checklist and Loading Data," KC-10A. Report No. MDC-94K0295, "Weight and Balance Manual", Model DC-10-30F (KDC-10). Report No. MDC-J0999, “Weight & Balance Manual", Model DC-10-40F. Report No. MDC-J0995, "Weight & Balance Manual", Model DC-10-15. Report No. MDC-K0032, "Weight & Balance Manual", Model MD-11. Report No. MDC-K5542, "Weight & Balance Manual", Model MD-11F. Page 43 of 50 A22WE Report No. MDC-K5543, "Weight & Balance Manual", Model MD-11F (Combi) Report No. MDC-93K1163, Chapter 2, "Weight & Balance Manual", Model MD-11F (CF) Report No. MDC 98K1080, "Weight & Balance Manual", Model MD-10-10F Report No. MDC 99K1043, "Weight & Balance Manual", Model MD-10-30F (b) The airplane must be loaded so that the C.G. is within specified limits at all times, considering fuel loading and usage, gear retraction, and movement of crew and passengers from their assigned positions. The lateral loading limits contained in the weight and balance document listed above should not be exceeded. (c) The weight of system fuel and oil, as defined below and hydraulic fluid, all of which must be included in the airplane empty weight, is listed in Douglas Master Weight and Balance Manual or Military Tech. Order specified in paragraph (a) above, for each airplane. System Fuel: The weight of all fuel required to fill all lines and tanks up to the zero fuel point on the fuel gages in the most critical flight attitude. This includes the unusable tank fuel as defined by FAR Part 25.959. The DC-10-10, DC-10-10F, DC-10-15, DC-10-30, DC-10-30F, MD-11, MD-11F, MD-10-10F and MD-10-30F have 609 pounds and the DC-10-40 and DC-10-40F have 622 pounds (based on 6.7 lb./gal fuel) of usable fuel in the cross feed manifold lines, manifolds, and engine that is not part of the system fuel and must be included in the total usable fuel to obtain correct weight and C.G. for takeoff. (See FAA Approved AFM for approved procedures.) System Oil: The weight of oil remaining in the engine, constant speed drive, lines and tanks after subtracting the oil in the tanks which is above the standpipe (zero gage) levels. The engine oil tank capacities shown elsewhere in this data sheet include only the usable oil for which the tanks must be placarded. (d) The "Unusable” fuel is that amount of fuel in the tanks which is unavailable to the engines under critical flight conditions as defined in FAR Part 25.959. See Weight and Balance Manual for "Unusable” fuel. This "Unusable" fuel is included in System Fuel as indicated in 1(c) above and need not be accounted for separately. (e) Fuel capacities shown in Sections I and II as well as fuel loading and usage procedures are dictated by structural design and to maintain airplane C.G. within approved limits. Fuel must be loaded symmetrically about the airplane centerline and in accordance with the following procedures and used as described below unless alternate procedures are approved and incorporated in the FAA Approved Airplane Flight Manual. The fuel system contains automatic transfer and quantity control features, which will permit main tank-to-engine utilization of all fuel without manual control. During engine-out conditions, symmetrical fuel distribution must be maintained by cross feed or transfer of fuel to the tanks being used. Fuel Loading - All Model MD-11, all Model MD-10 and all Model DC-10 (including DC-10-30F(KDC-10)) airplanes except DC-10-30F (KC-10A) Fill all main tanks equally until No. 1 and No. 3 tanks are full. Add additional fuel to No. 2 tank until full. Load remainder into center wing auxiliary fuel tank, if installed on DC-10 or MD-10. MD-11 only: After filling of center wing aux tank, load remainder of fuel into the horizontal tail fuel tank. Fuel Loading - (DC-10-30F (KC-10A)) Load fuel per T.O. 1C-10 (K) A-5, Chg. 1, dated 15 March 1981. Fuel Usage - All Model MD-11, all Model MD-10 and all Model DC-10 airplanes, except KC-10A and KDC-10: Each main tank feeds its respective engine. Additional fuel added to the lower center wing auxiliary fuel tank, if installed, and the upper center wing auxiliary fuel tank, if installed, is transferred to the three main tanks numbers 1, 2, and 3. Simultaneously as the upper auxiliary tank fuel is used, fuel is transferred to it from the lower auxiliary tank until the lower auxiliary is depleted and the transfer of the fuel from the upper A22WE Page 44 of 50 auxiliary tank is continued until it is empty. Fuel transfer is then initiated from No. 2 main tank to main tanks No. 1 and 3 until fuel in all main tanks is equal. Then use fuel equally from each fuel tank. Fuel Usage - KC-10A Only: Fuel offloading is accomplished using fuel from the forward and aft fuselage fuel tanks, the center wing tanks and the main tanks as required. When off loading is complete, if the C.G. of the airplane, less usable fuel, is aft of 23.8 percent MAC, 15,000 pounds of fuel must remain in the forward fuel tank until the main fuel tanks are depleted to 5,000 pounds each. The 15,000 pounds in the forward fuselage fuel tanks may then be transferred equally to the main fuel tanks or off loaded. Fuel Usage - KDC-10 Only: Fuel off loading is accomplished using fuel from the center wing tanks and the main tanks as required. When off loading is complete, transfer center wing fuel to the three main tanks until the center wing tank is empty. Transfer the excess fuel from the No. 2 main tank to main tanks No. 1 and No. 3 until fuel in all main tanks is equal. Then use fuel equally from each fuel tank. (f) Fuel Dump Refer to FAA Approved Airplane Flight Manual for limitations to be observed during fuel dumping. The total undumpable fuel remaining in the fuel tanks after dumping is as follows for fuel weight based on 6.7 lb. /gal. fuel: All DC-10 Models All MD-10 Models All MD-11 Models No.1 Main Tank 12,973 lb. 12,973 lb. No.2 Main Tank 13,917 lb. 13,917 lb. No.3 Main Tank 12,973 lb. 12,973 lb. Center Wing Auxiliary Tank (if installed) 0 lb. 0 lb. AFT Auxiliary Tank (if installed) 0 lb. Manifold Piping 436 lb. 436 lb. Undumpable fuel not applicable to MD-11 tail tank. NOTE 2: Reserved. NOTE 3: Life Limited Parts and Airworthiness Limitations: (a) DC-10 life limited components are listed in FAA approved Report MDC-J5752. (b) MD-11 life limited components and required structural inspections for damage tolerant structure, are listed in FAA approved Report MDC-K5225. (c) The DC-10/MD-11 FAA mandatory brake wear limits are contained in FAA Airworthiness Directives or McDonnell Douglas Report MDC-94K1158. (d) MD-10 life limited components are listed in the FAA approved Airworthiness Limitations Instructions (ALI) Report MDC-99K1082. (e) The MD-10 brake system was not affected by the DC-10 to MD-10 modification, therefore the FAA mandatory brake wear limits are identical to the DC-10 and are contained in the DC-10 portion of McDonnell Douglas Report MDC-K1158. (f) DC-10, MD-11, and MD-10 non-structural components which are life limited, fuel system critical design configuration control limitations (CDCCL), and fuel system ALIs are listed in report MDC- 02K1003, “Trijet Special Compliance Item Report.” The life limited components must be replaced as indicated in the appropriate life limit report and revisions thereto. The MD-11 damage tolerance inspections must be conducted in accordance with Report MDC- Page 45 of 50 A22WE K5225. The MD-10 damage tolerance inspections must be conducted in accordance with Report MDC- 99K1082. Copies of the reports may be obtained from the manufacturer: Boeing Commercial Airplane Group Data and Service Management (C1-L5A) Mail Code D800-0024 3855 Lakewood Blvd. Long Beach, CA 90846 NOTE 4: (a) The following fuels are eligible provided and to the extent they are allowed by P&W Service Bulletin No. 2016 for PW engines, or they conform to GE Specification No. D50TF2 for GE engines: MD-11: Kerosene type fuels MIL-T-5624H (JP-5), MIL-T-83133 (JP-8) and ASTM D 1655-657 (Jet A and A-1). Russian fuels conforming to Specification GOST 10227 (RT and TS-1), Chinese fuel conforming to Specification SY1008-80 (RP-3/Number 3 Jet Fuel), and any fuel conforming to P&W Service Bulletin No. 2016 for PW engines, or any fuel conforming to GE Specification No. D50TF2 for GE engines, may be used separately or mixed in any proportions without adversely affecting the engine operation or power output. No fuel control adjustment is required when switching fuel types. To Use MIL-T-5624 (JP-4), Jet B, or any wide cut fuels in MD-11 and MD-11F airplanes, McDonnell Douglas Drawing PZV0007 or Production Equivalent must be installed and the following limitations found in the MD-11 AFM Appendix 14 must be applied. DC-10: Kerosene type fuels MIL-T-5624G (JP-4 and JP-5), ASTM D 1655-65T (Jet A, A-1 and B), and MIL-T-83133 (JP-8). Russian fuels conforming to Specification GOST 10227 (RT and TS-1), Chinese fuel conforming to Specification SY1008-80 (RP-3/Number 3 Jet Fuel), and any fuel conforming to P&W Service Bulletin No. 2016 for PW engines, or any fuel conforming to GE Specification No. D50TF2 for GE engines, may be used separately or mixed in any proportions without adversely affecting the engine operation or power output. No fuel control adjustment is required when switching fuel types. To use MIL-T-5624 (JP-4), Jet B, or any wide cut fuels in DC-10-10 and DC-10-10F airplanes that have not incorporated Service Bulletin No. 28-13, the following limitations must be applied. 1. A maximum altitude of 10,000 feet with a tank fuel temperature above 80° F. 2. A maximum altitude of 25,000 feet with a tank fuel temperature at 80° F or below. 3. A minimum of two aft tank pumps must be on for engine number 2 operation. 4. A minimum of one aft tank pump must be on for each wing engine. MD-10: Kerosene type fuels MIL-T-5624G (JP-4 and JP-5), ASTM D 1655-65T (Jet A, A-1 and B), and MIL-T-83133 (JP-8). Russian fuels conforming to Specification GOST 10227 (RT and TS-1), Chinese fuel conforming to Specification SY1008-80 (RP-3/Number 3 Jet Fuel), and any fuel conforming to GE Specification No. D50TF2 for GE engines may be used separately or mixed in any proportions without adversely affecting the engine operation or power output. No fuel control adjustment is required when switching fuel types. To use MIL-T-5624 (JP-4), Jet B, or any wide cut fuels in MD-10-10F and MD-10-30F airplanes the following limitations found in the MD-10 AFM Appendix 14 must be applied. (b) Additives that may be used (in addition to those authorized by GE specification D50TF2 or by P&WA Specification 522, for the respective engines) in the approved fuel are listed below. These additives may be used in combination. 1. Philips PFA-55MB or anti-icing additive to Specifications MIL-I-27686E at a concentration not in excess of 0.15 percent by volume. A22WE Page 46 of 50 2. Sohio Biobor JF biocide additive at a concentration not in excess of 20 ppm elemental boron (270 ppm total additive). 3. Shell ASA-3 anti-static additive at a concentration that will provide not in excess of 3000 conductivity units, which is approximately equivalent to one ppm. (c) NALCO 5403 or DU PONT DCI-4A corrosion inhibitor fuel additive may be used if concentration delivered to airplane does not exceed 8 lb/1000bbl (23mg/l) of turbine fuel. NOTE 5: The following oils are eligible for all CF6 engines: Synthetic type conforming to GE Specification D501F1, classes A or B. GE Service Bulletin No.79-1 lists approved brand oils. The following oils are eligible for all JT9D engines: Oil specified in P&WA Specification 521. (P&WA Service Bulletin 238) NOTE 6: (a) For DC-10 model airplanes, the maximum number of passengers demonstrated for emergency evacuation is 380. See FAA approved interior schematic drawing for maximum passenger capacities approved for each aircraft when delivered. (b) For MD-11 model airplanes, the maximum number of passengers approved for emergency evacuation is 410. Airplanes with a passenger configuration between 400 and 410 passengers require incorporation of MCDonnell Douglas Service Bulletin 25-145 or production equivalent. See FAA approved interior schematic drawing for the maximum passenger capacities approved for each aircraft when delivered. NOTE 7: For purposes of administration, Special Airframe Conditions Numbers 5-17 contained in Special Conditions No. 25-18-WE-7, Amendment No. 1 dated 9 July 1971 (Docket No. 10058; Amendment No. 1) have been retitled and renumbered. Special Systems Condition No. 3 contained in the aforementioned Special Conditions has also been renumbered. These conditions are contained in the document entitled "SPECIAL CONDITIONS RETITLED AND RENUMBERED BY THE WESTERN REGION" dated 9 July 1971. Flammability requirements for compartment interior materials and electric wiring and cable insulation are also contained in FAR 25.853 and 25.1359(d) as revised by Amendment 25-32. NOTE 8: Only those DC-10 model airplanes which meet, in addition to normal maintenance requirements, criteria of McDonnell Douglas Report No. MDC-J1221 dated October 21, 1975, are eligible for Category IIIa auto- landings. Only those MD-11 model airplanes which meet, in addition to normal maintenance requirements, the MD-11 Certification Maintenance Requirements (CMR) listed in FAA approved report MDC-K4174, revision Q or later FAA approved revision and have incorporated MD-11 Service Bulletin 22-4 or production equivalent, are eligible for Category IIIb auto-landings. MD-10 model aircraft airplanes are eligible for Category IIIb auto-landings. NOTE 9: Adding (CF) to the DC-10-10F, DC-10-30F or MD-11F model designation does not alter the aircraft. For example, a DC-10-10F airplane and DC-10-10F (CF) airplane are the same. The convertible freighter "CF" designator signifies that there is a FAA Approved passenger and freighter configuration, delivered by the manufacture, for the aircraft. The "CF" designator may be used in parentheses, but must be accompanied by the official designator (i.e., DC-10-10F (CF)). NOTE 10: The identified serial numbers are eligible for these weights when appropriately configured. Specific airplanes may not attain these weights without structural, gear, and other changes. The Airplane Flight Manual (AFM) defines the actual weight approved for each serial number. NOTE 11: KC-10A airplanes are tanker/cargo versions of the Model DC-10-30F. Prior to operation as a commercial aircraft, the following must be accomplished: (a) The maintenance, overhaul and modifications records of each aircraft must be reviewed for changes made by the military services that may affect the airworthiness of the aircraft. Modifications, Page 47 of 50 A22WE changes of equipment and repairs, which affect the safety or performance of the aircraft, must be approved by the FAA. (b) All aircraft returned to civil operations must comply with all applicable Airworthiness Directives. (c) All items that are not FAA approved must be removed from the aircraft if they affect the safety or performance of the aircraft. (d) Each deviation from the FAA approved type design as listed on FAA Form 8130-2, "Conformity Certificate - Military Aircraft” that is required for civil certification must be corrected per FAA approved data. NOTE 12: The MD-11 incorporates a number of computer systems which feature "option pins" allowing easy selection of variable features (i.e., "split" flight director command bars versus "single cue" flight director command bars - selection of one or the other made by grounding the appropriate connector pin on the Flight Control Computer) Some features are required and are identified as follows: (a) On the Ground Proximity Warning System (GPWS) computer, "Envelope Modulation" must be disabled. After incorporation of Service Bulletin 34-16 and Service Bulletin 34-17, or production equivalent, "Envelope Modulation" may be enabled. (b) On the Automatic Flight System (AFS) computer, "A/P Disconnect Aural warning" must be enabled. "G/S - LOC Capture No Priority" must be disabled. After incorporation of Service Bulletin 22-05 or production equivalent, "A/P Disconnect Aural Warning" may be disabled. After incorporation of Service Bulletin 22-10 and Service Bulletin 31-42, or production equivalent, "G/S - LOC Capture No Priority" may be enabled. (c) On the Electronic Display System (EIS) DEU, "Tape Engine Instrument" must be disabled. "Deletes Digital Altitude" must be disabled. After incorporation of Service Bulletin 31-09, or production equivalent, "Tape Engine Instrument" may be enabled. (d) On the Flight Management System (FMS) computer, "V Speed Inhibit" must be enabled. "Alternate T/O Thrust #1" must be disabled. "Install Fuel Dipstick 2" must be disabled. "Install BFE ACARS System" must be disabled. "Install Single Weight & Balance System" must be disabled. After incorporation of Service Bulletin 34-16 or production equivalent, "V Speed Inhibit" may be disabled. After incorporation of Service Bulletin 34-16 or production equivalent and Collins ACARS P/N 622-9967-001, "Install BFE ACARS System" may be enabled. Also, this option pin maybe enabled when Teledyne Controls ACARS P/N 2231500-2 or 2231500-6A is installed. After installation of Service Bulletin 34-16 and Service Bulletin 31-30, or production equivalent "Install Single Weight & Balance System" may be enabled. After incorporation of Service Bulletin 34-33 or production equivalent, "Alternate T/O Thrust #1" may be enabled. A22WE Page 48 of 50 After incorporation of Service Bulletin 34-33 or production equivalent, "Install Fuel Dipstick 2" may be enabled. NOTE 13: McDonnell Douglas DC-10, MD-11 and MD-10 FAA Approved Maintenance Review Board Reports contain the initial minimum requirements used for development of a maintenance program that meets the requirements for continued airworthiness. NOTE 14: Engine and APU life limited components are listed in the respective manufacturers overhaul manuals and engine and APU Type Certificate Data Sheets. NOTE 15: Reserved. NOTE 16: MD-11F with 160” Aft Main Deck Cargo Door: (a) Factory Serial Numbers (FSN's) 48426, 48427, 48428, 48429 and 48430 are eligible to operate in the all-passenger configuration when the 160 inch main deck cargo door deactivated in accordance with Douglas Report No. MDC-91K0528. (b) Factory Serial Numbers (FSN's) 48426, 48427, 48428, 48429 and 48430 are eligible to operate in the Combi, 192 passenger/4 pallet configuration when: 1. Service Bulletin 25-109, Revision 1 or production equivalent is incorporated, and 2. Configured in accordance with Douglas Drawing NZZ6760-1. 3. The upper exterior surface of the fuselage forward of station 1821.0 between longerons 16R and 16L must be painted white. Any deviation to this requirement must be FAA approved. (c) Factory Serial Numbers (FSN's) 48426, 48427, 48428, 48429 and 48430 are eligible to operate in the main deck all-freight configuration when: 1. MDC drawing SP11251075 is installed, and 2. The upper exterior surface of the fuselage forward of station 1821.0 between longerons 16R and 16L must be painted white. Any deviation to this requirement must be FAA approved. NOTE 17: The location of flight attendant seats demonstrated to comply with the direct view requirements of FAR 25.785(h)(1), for the MD-11, are shown on the manufacturers interior arrangement drawing, entitled, "FAA Interior Schematic." NOTE 18: The number of required flight attendants which have been used to demonstrate compliance with the emergency evacuation requirements of FAR 25.803(c) or (d) is as follows: (a) For between one (1) and 306 passengers: One (1) flight attendant for every 50 passenger seats plus two (2) additional flight attendants, when the following slides are installed: Part Number 60289-101, or -103 at door 1, Part Number 60290-101, or -103 at doors 2 and 4 Part Number 60291-101 through -104 at door 3. See note 18(e) (b) For between one (1) and 381 passengers and 165 passenger seats or less in Zone "C": One (1) flight attendant for every 50 passenger seats, when the following slides, or later FAA approved slides are installed: Part Number 60289-111, or -113 at door 1, Part Number 60290-111, or -113 at doors 2 and 4 Part Number 60291-111 through -114 at door 3. See note 18(e) Page 49 of 50 A22WE (c) For between one (1) and 381 passengers and more than 165 passenger seats in Zone "C": One (1) flight attendant for every 50 passenger seats plus one (1) additional flight attendants when the following slides, or later FAA approved slides are installed: Part Number 60289-111, or -113 at door 1, Part Number 60290-111, or -113 at doors 2 and 4 Part Number 60291-111 through -114 at door 3. See NOTE 18(e) (d) For between 382 and 410 passengers: One (1) flight attendant for every 50 passenger seats plus one (1) additional flight attendant (total of 9 flight attendants maximum), and the following slides, or later FAA approved slides must be installed: Part Number 60289-115, or -117 at door 1, Part Number 60290-115, or -117 at doors 2 and 4 Part Number 60291-115 through -118 at door 3. If less than eight flight attendants are required for a particular passenger capacity, the flight attendants should be located at each overwing exit first, and then distributed equally throughout the cabin at the exit doors. If nine flight attendants are required, the ninth should be located at door 2. The number and location of flight attendants for compliance with FAR 25.803(c) or (d) shall not conflict with the requirements of NOTE 17, and may require additional attendants to meet both requirements. (e) AD 92-23-02 amendment 39-8402 effective November 25, 1992 requires upgraded slides to be installed. NOTE 19: KDC-10 Airplanes Factory Serial Numbers 46956 and 46985 are tanker/cargo versions of the Model DC-10- 30F when modified in accordance with Douglas Aircraft Drawing SP10280012, Revision B, dated April 6, 1995. The KDC-10 is equipped with a Remote Aerial Refueling Operator (RARO) station in the main cabin. Only two RARO stations with the following Part Numbers (P/N) are approved for installation on the KDC-10 aircraft: P/N 1D83300-1, Serial Numbers 0001 and 0002. Prior to operation as a commercial aircraft, the following must be accomplished: (a) The maintenance, overhaul and modifications records of each aircraft must be reviewed for changes made by the military services that may affect the airworthiness of the aircraft. Modifications, changes of equipment and repairs, which affect the safety or performance of the aircraft, must be approved by the FAA. (b) All aircraft returned to civil operations must comply with all applicable Airworthiness Directives. (c) All items that are not FAA approved must be removed from the aircraft if they affect the safety or performance of the aircraft. NOTE 20: The DC-10 aircraft is qualified for operations within Reduced Vertical Separation Minimum (RVSM) airspace. See McDonnell Douglas Service Bulletin DC10-34-134 for establishing the basis for operational approval. NOTE 21: The MD-11 aircraft is qualified for operations within Reduced Vertical Separation Minimum (RVSM) airspace. See McDonnell Douglas Service Bulletin MD11-34-065 for establishing the basis for operational approval. A22WE Page 50 of 50 NOTE 22 The MD-10 aircraft is qualified for operations within Reduced Vertical Separation Minimum (RVSM) airspace, when equipped with approved MD-10 Air Data Systems that are maintained in accordance with the MD-10 Maintenance Review Board Document. NOTE 23: MD-10 Maximum Passengers: The following is applicable to crew and supernumeraries: For MD-10 model airplanes, a maximum of four supernumeraries in a “courier area” aft of the cockpit door and forward of a rigid cargo barrier, or two supernumeraries in a “courier module” area aft of the cockpit door and forward of a 9g crash net is permitted per FAA approved exemption number 6873. NOTE 24: Conversion of a DC-10 to an MD-10-10F or –30F can be accomplished by either Douglas Aircraft Drawing SP10250349 or SP10250354, as appropriate, along with the requirement in NOTE 25. NOTE 25: For MD-10 model airplanes, upon induction of a specific aircraft for modification, a review must be conducted to ensure that all DC-10 AD’s are accounted for per Report MDC 99K1087, Revision A or later. NOTE 26: Upon completion of the modification from DC-10-10/-10F, DC-10-30/-30F to MD-10-10F, MD10-30F, respectively, in accordance with Douglas Aircraft Drawing SP10250349 or SP10250354, a data plate must be installed adjacent to the existing data plate in accordance with Douglas Aircraft Drawing No. SP10510226 or SP10530234. NOTE 27: The MD-10 Anomalies are contained in the MD-10 Aircraft Fault Anomalies Report, Report No. MDC 00K1108. NOTE 28: Each Aircraft modified to a MD-10-10F or -30F, must have an applicable FAA approved “Airplane Flight Manual”. NOTE 29: For specific dimensional and weight limits, static unbalance, rated pressure, load rating, speed rating, etc., see the following McDonnell Douglas Tire Specification Drawing: Tire Spec. Dwg. Tire Max. Weight Airplane Series PS5914 H54x21.0-24 325 lbs MD-10-10F (when carbon brakes are installed) END ``` ## ADs (475, first 50, in force first) - [AD 2026-13-02](https://openairdocs.org/ad/2026-13-02): Navigation · Airbus Canada Limited Partnership 18, 49-46, 80-A and 555 more. Effective Jul 1, 2026 - [AD 2026-13-15](https://openairdocs.org/ad/2026-13-15): Navigation · Boeing 707-100 Long Body, 707-200, 707-100B Long Body and 74 more. Effective Jul 1, 2026 - [AD 2025-23-53](https://openairdocs.org/ad/2025-23-53): Nacelles/pylons · Boeing MD-11, MD-11F, MD-10-10F and 8 more. Effective Dec 1, 2025 - [AD 2025-02-07](https://openairdocs.org/ad/2025-02-07): Navigation · Modification of Rockwell Collins, Inc. Multi-Mode Receiver (STC ST01883WI or 4 others). Effective Mar 17, 2025 - [AD 2024-24-03](https://openairdocs.org/ad/2024-24-03): Engine Exhaust · Boeing MD-11, MD-11F and CF6-80C2D1F. Effective Jan 13, 2025 - [AD 2023-12-15](https://openairdocs.org/ad/2023-12-15): Navigation · Boeing 707-100 Long Body, 707-200, 707-100B Long Body and 74 more. Effective Jun 21, 2023 - [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 2021-24-02](https://openairdocs.org/ad/2021-24-02): Electrical power · Boeing MD-11 and MD-11F. Effective Feb 1, 2022 - [AD 2021-08-10](https://openairdocs.org/ad/2021-08-10): Nacelles/pylons · Boeing DC-10-10, DC-10-10F, DC-10-15 and 6 more. Effective May 25, 2021 - [AD 2020-22-15](https://openairdocs.org/ad/2020-22-15): Fuselage · Boeing DC-10-10, DC-10-10F, DC-10-15 and 8 more. Effective Dec 18, 2020 - [AD 2018-22-10](https://openairdocs.org/ad/2018-22-10): Fuel · Boeing DC-10-10, DC-10-10F, DC-10-15 and 8 more. Effective Dec 12, 2018 - [AD 2018-07-20](https://openairdocs.org/ad/2018-07-20): Fuel · Boeing MD-11 and MD-11F. Effective May 21, 2018 - [AD 2018-01-01](https://openairdocs.org/ad/2018-01-01): Fuel · Boeing MD-11 and MD-11F. Effective Feb 7, 2018 - [AD 2017-14-10](https://openairdocs.org/ad/2017-14-10): Fuel System · Boeing MD-11 and MD-11F. Effective Aug 21, 2017 - [AD 2015-02-05](https://openairdocs.org/ad/2015-02-05): Navigation · Boeing 717-200, DC-10-10, DC-10-10F and 13 more. Effective Mar 5, 2015 - [AD 2014-21-05](https://openairdocs.org/ad/2014-21-05): Fuselage · Boeing DC-10-10, DC-10-10F, DC-10-30 and 4 more. Effective Dec 2, 2014 - [AD 2014-17-02](https://openairdocs.org/ad/2014-17-02): Communications · Airbus A300 B2-1A, A300 B2-1C, A300 B2-203 and 137 more. Effective Sep 9, 2014 - [AD 2013-19-20](https://openairdocs.org/ad/2013-19-20): JASC Code 32, Landing Gear · Boeing DC-10-10 and MD-10-10F. Effective Nov 7, 2013 - [AD 2012-19-03](https://openairdocs.org/ad/2012-19-03): Fuselage · Boeing DC-10-10, DC-10-10F, DC-10-15 and 6 more. Effective Nov 5, 2012 - [AD 2011-25-06](https://openairdocs.org/ad/2011-25-06): Horizontal stabilizer structure · Boeing MD-11 and MD-11F. Effective Jan 17, 2012 - [AD 2011-24-04](https://openairdocs.org/ad/2011-24-04): Wings · Boeing DC-10-10, DC-10-10F and MD-10-10F. Effective Jan 3, 2012 - [AD 2011-21-08](https://openairdocs.org/ad/2011-21-08): Equipment/Furnishings · ATR - GIE Avions de Transport Régional ATR42-200, ATR42-300, ATR42-320 and 202 more. Effective Nov 23, 2011 - [AD 2011-12-01](https://openairdocs.org/ad/2011-12-01): Equipment/Furnishings · Airbus A300 B2-1A, A300 B2-1C, A300 B2-203 and 268 more. Effective Aug 1, 2011 - [AD 2011-11-05](https://openairdocs.org/ad/2011-11-05): Fuel · Boeing DC-10-10, DC-10-10F, DC-10-15 and 10 more. Effective Jul 6, 2011 - [AD 2011-02-01](https://openairdocs.org/ad/2011-02-01): Fuel · Boeing MD-11 and MD-11F. Effective Feb 16, 2011 - [AD 2010-21-13](https://openairdocs.org/ad/2010-21-13): Fuel · Boeing DC-10-10, DC-10-10F, DC-10-30 and 3 more. Effective Nov 18, 2010 - [AD 2010-20-13](https://openairdocs.org/ad/2010-20-13): Fuel · Boeing DC-10-30, DC-10-30F (KC-10A, KDC-10), DC-10-40 and 2 more. Effective Nov 9, 2010 - [AD 2010-20-14](https://openairdocs.org/ad/2010-20-14): Fuel · Boeing DC-10-10, DC-10-10F, DC-10-15 and 8 more. Effective Nov 5, 2010 - [AD 2010-16-03](https://openairdocs.org/ad/2010-16-03): Ice and rain protection · Boeing MD-11 and MD-11F. Effective Sep 9, 2010 - [AD 2010-13-06](https://openairdocs.org/ad/2010-13-06): Wings · Boeing DC-10-10, DC-10-10F and MD-10-10F. Effective Jul 28, 2010 - [AD 2010-11-12](https://openairdocs.org/ad/2010-11-12): Fuel · Boeing MD-11 and MD-11F. Effective Jul 6, 2010 - [AD 2010-09-12](https://openairdocs.org/ad/2010-09-12): Fuel · Boeing DC-10-10, DC-10-10F, DC-10-15 and 8 more. Effective Jun 8, 2010 - [AD 2009-21-10 R1](https://openairdocs.org/ad/2009-21-10-R1): Oxygen · Airbus A300 B4-605R, A300 B4-620, A300 B4-622 and 138 more. Effective Feb 4, 2010 - [AD 2008-06-21 R1](https://openairdocs.org/ad/2008-06-21-R1): Fuel tank systems · Boeing DC-10-10, DC-10-10F, DC-10-15 and 8 more. Effective Dec 10, 2009 - [AD 2009-03-02](https://openairdocs.org/ad/2009-03-02): Auxiliary hydraulic pumps · Boeing DC-10-10, DC-10-10F, DC-10-15 and 8 more. Effective Mar 31, 2009 - [AD 2008-17-16](https://openairdocs.org/ad/2008-17-16): Fuel boost pump · Boeing DC-10-10, DC-10-10F, DC-10-15 and 8 more. Effective Oct 2, 2008 - [AD 2006-16-18 R1](https://openairdocs.org/ad/2006-16-18-R1): Installing a warning placard on the TAWS/RMI · Airbus A300 B2-1A, A300 B2-1C, A300 B2-203 and 100 more. Effective Jul 18, 2008 - [AD 2008-11-14](https://openairdocs.org/ad/2008-11-14): Horizontal pressure panel · Boeing DC-10-10F, DC-10-30F (KC-10A, KDC-10), DC-10-40F and 4 more. Effective Jul 3, 2008 - [AD 2008-09-17](https://openairdocs.org/ad/2008-09-17): Stray nickel or chrome plating deposits · Boeing DC-10-10, DC-10-10F, DC-10-15 and 1 more. Effective Jun 6, 2008 - [AD 2007-25-20](https://openairdocs.org/ad/2007-25-20): Thrust reverser command wiring · Boeing DC-10-10, DC-10-10F, DC-10-15 and 6 more. Effective Jan 22, 2008 - [AD 2007-19-15](https://openairdocs.org/ad/2007-19-15): Flight management system (FMS) · Boeing 717-200, MD-10-10F, MD-10-30F and 2 more. Effective Oct 26, 2007 - [AD 2007-19-17](https://openairdocs.org/ad/2007-19-17): System 3 hydraulic piping · Boeing DC-10-10, DC-10-10F, DC-10-15 and 8 more. Effective Oct 26, 2007 - [AD 2007-19-02](https://openairdocs.org/ad/2007-19-02): Fuel tank and the fuel transfer pump housing flange · Boeing DC-10-30, DC-10-30F (KC-10A, KDC-10), DC-10-40 and 4 more. Effective Oct 17, 2007 - [AD 2007-19-13](https://openairdocs.org/ad/2007-19-13): Hydrolok retaining pin · Airbus A300 B2-1A, A300 B2-1C, A300 B2-203 and 66 more. Effective Oct 3, 2007 - [AD 2007-13-10](https://openairdocs.org/ad/2007-13-10): Fuel pump wire harness · Boeing DC-10-30 and DC-10-30F (KC-10A, KDC-10). Effective Aug 3, 2007 - [AD 2007-11-15](https://openairdocs.org/ad/2007-11-15): Center main wheel well · Boeing DC-10-30, DC-10-30F (KC-10A, KDC-10), DC-10-40 and 2 more. Effective Jul 5, 2007 - [AD 2007-11-16](https://openairdocs.org/ad/2007-11-16): Center main wheel well · Boeing MD-11 and MD-11F. Effective Jul 5, 2007 - [AD 2007-10-12](https://openairdocs.org/ad/2007-10-12): Reinforced flight deck door · Reinforced cockpit door (Safran Cabin STC ST01335LA or 2 others). Effective Jun 27, 2007 - [AD 2007-07-04](https://openairdocs.org/ad/2007-07-04): Principal structural elements (PSEs) · Boeing MD-11 and MD-11F. Effective May 2, 2007 - [AD 2007-04-17](https://openairdocs.org/ad/2007-04-17): Control modules of the fire detection systems · Boeing DC-10-10, DC-10-10F, DC-10-15 and 6 more. Effective Mar 23, 2007 All 475: https://openairdocs.org/tcds/A22WE/ads.md ## Registered aircraft by registry model (OpenAirDocs) - [Mcdonnell Douglas MD-11F](https://openairdocs.org/model/mcdonnell-douglas-md-11f): 100 aircraft (registry code 3023600) - [Mcdonnell Douglas MD-10-30F](https://openairdocs.org/model/mcdonnell-douglas-md-10-30f): 13 aircraft (registry code 3024020) - [Mcdonnell Douglas DC-10-30F](https://openairdocs.org/model/mcdonnell-douglas-dc-10-30f): 12 aircraft (registry code 3023504) - [Douglas DC-10-40](https://openairdocs.org/model/douglas-dc-10-40): 6 aircraft (registry code 3023508) - [Mcdonnell-Douglas DC-10-30](https://openairdocs.org/model/mcdonnell-douglas-dc-10-30): 5 aircraft (registry code 3023501) - [Boeing MD-11F](https://openairdocs.org/model/boeing-md-11f): 4 aircraft (registry code 3023604) - [Mcdonnell Douglas MD-11](https://openairdocs.org/model/mcdonnell-douglas-md-11): 4 aircraft (registry code 3023602) - [Mcdonnell Douglas MD-10-10F](https://openairdocs.org/model/mcdonnell-douglas-md-10-10f): 2 aircraft (registry code 3022112) - [Douglas DC-10-30F](https://openairdocs.org/model/douglas-dc-10-30f): 1 aircraft (registry code 3023503) - [Douglas DC-10-40F](https://openairdocs.org/model/douglas-dc-10-40f): 1 aircraft (registry code 3023507) - [Mcdonnell Douglas DC-10-30F (KDC-10)](https://openairdocs.org/model/mcdonnell-douglas-dc-10-30f-kdc-10): 1 aircraft (registry code 3023505) - [Mcdonnell Douglas DC-10-10](https://openairdocs.org/model/mcdonnell-douglas-dc-10-10): 0 aircraft (registry code 3022110) - [Mcdonnell Douglas DC-10-15](https://openairdocs.org/model/mcdonnell-douglas-dc-10-15): 0 aircraft (registry code 3022118) - [Mcdonnell-Douglas DC-10-10F](https://openairdocs.org/model/mcdonnell-douglas-dc-10-10f): 0 aircraft (registry code 3022111) ## STCs approved under this data sheet (767, first 50) - [STC ST00885LA](https://openairdocs.org/stc/ST00885LA): Installation of fire extinguisher cartridges as replacements for Pacific Scientific fire extinguisher cartridges in fire extinguisher bottles.. AMETEK AMERON, LLC d/b/a MASS Systems - [STC ST00272AT](https://openairdocs.org/stc/ST00272AT): Installation of an Airshow 210 enter- tainment system.. AIRCRAFT RECONFIG TECHNOLOGIES, LLC - [STC ST01735AT-D](https://openairdocs.org/stc/ST01735AT-D): Installation of Collins VHG-700B transceivers and gables radio tuning panels with 8.33 KHz spacing.. AIRCRAFT RECONFIG TECHNOLOGIES, LLC - [STC ST01983AT-D](https://openairdocs.org/stc/ST01983AT-D): Interior modification. AIRCRAFT RECONFIG TECHNOLOGIES, LLC - [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 ST09142SC](https://openairdocs.org/stc/ST09142SC): Installation of a cargo/executive "combi" interior. Omega Air Inc. - [STC SA2622NM](https://openairdocs.org/stc/SA2622NM): Installation of Precise Flight Pulselite Control Unit in landing/taxi system. (767-200 B17) (DHC-8 101). Precise Flight Inc. - [STC SA5040NM](https://openairdocs.org/stc/SA5040NM): Installation of cargo pallet and net.. Satco Inc. - [STC ST00892LA](https://openairdocs.org/stc/ST00892LA): Installation of Emergency Vision Assurance System (EVAS).. VisionSafe LLC - [STC ST00030IB](https://openairdocs.org/stc/ST00030IB): Installation of Test Tech ELT. APTOZ EHF - [STC ST03885AT](https://openairdocs.org/stc/ST03885AT): Installation of an Avionica, Inc. avCM Cellular Module. Aircraft Systems and Manufacturing Inc. - [STC SA1368NM](https://openairdocs.org/stc/SA1368NM): Installation of C&D Interiors P/N 1441002.. Safran Cabin Inc. - [STC SA1369NM](https://openairdocs.org/stc/SA1369NM): Installation of closets.. Safran Cabin Inc. - [STC SA1380NM](https://openairdocs.org/stc/SA1380NM): Installation of lounge furnishings.. Safran Cabin Inc. - [STC SA2049NM](https://openairdocs.org/stc/SA2049NM): Installation of C&D Interiors P/N 1751001-101, -102. Safran Cabin Inc. - [STC SA2175NM](https://openairdocs.org/stc/SA2175NM): Installation of the Centerline Overhead Stowage Retrofit Kit. Safran Cabin Inc. - [STC SA2471NM](https://openairdocs.org/stc/SA2471NM): Installation of centerline bin, overhead side bin.. Safran Cabin Inc. - [STC SA2499NM](https://openairdocs.org/stc/SA2499NM): Installation of closet/windscreen.. Safran Cabin Inc. - [STC SA3127NM](https://openairdocs.org/stc/SA3127NM): Installation of Closet.. Safran Cabin Inc. - [STC SA3422NM](https://openairdocs.org/stc/SA3422NM): Installation of a galley. Safran Cabin Inc. - [STC SA3460NM](https://openairdocs.org/stc/SA3460NM): Installation of centerline stowage bins.. Safran Cabin Inc. - [STC SA3804NM](https://openairdocs.org/stc/SA3804NM): Installation of the Centerline SkyBin Stowage Interior kit. Safran Cabin Inc. - [STC SA3967NM](https://openairdocs.org/stc/SA3967NM): Installation of bi-fold lavatory door.. Safran Cabin Inc. - [STC SA4832NM](https://openairdocs.org/stc/SA4832NM): Installation of C&D Interiors Part Numbers 3001001-105 Credenza, 4761001-101 C/L Closet, and 4771001-101 and -102 L.H. and R.H. Closet.. Safran Cabin Inc. - [STC SA5045NM](https://openairdocs.org/stc/SA5045NM): Installation of LH module P/N 15900-1 and RH module P/N 15940-1.. Safran Cabin Inc. - [STC SA5046NM](https://openairdocs.org/stc/SA5046NM): Installation of LH closet P/N 15880-1, cart stowage module P/N 15920-1.. Safran Cabin Inc. - [STC SA5047NM](https://openairdocs.org/stc/SA5047NM): Installation of partition P/N 16080-1, 16240-1, -2, header assembly P/N 16060-1.. Safran Cabin Inc. - [STC SA5048NM](https://openairdocs.org/stc/SA5048NM): Installation of partition P/N 16260-1, header assembly P/N 16070-1.. Safran Cabin Inc. - [STC SA5492NM](https://openairdocs.org/stc/SA5492NM): Installation of galleys, dividers, closet, and fold-down table.. Safran Cabin Inc. - [STC SA5547NM](https://openairdocs.org/stc/SA5547NM): Installation of P/N 1451001-211 meal cart, P/N 1451001-215 beverage cart, P/N 1451001-217 waste cart, and P/N 1451001-219 dish cart.. Safran Cabin Inc. - [STC SA5802NM](https://openairdocs.org/stc/SA5802NM): Installation of articulating overhead cabin module bin kit, P/N CDK327-2.. Safran Cabin Inc. - [STC SA5806NM](https://openairdocs.org/stc/SA5806NM): Installation of P/N 1451001-111 meal cart, P/N 1451001-115 beverage cart, P/N 1451001-117 waste cart, and P/N 1451001-119 dish cart.. Safran Cabin Inc. - [STC SA5850NM](https://openairdocs.org/stc/SA5850NM): Installation of crew rest P/N 15700-1.. Safran Cabin Inc. - [STC SA6055NM](https://openairdocs.org/stc/SA6055NM): Installation of forward and aft closets, outboard class dividers, centerline class divider, center partition, curtain assemblies, overhead stowage bin rework kit.. Safran Cabin Inc. - [STC SA7065NM](https://openairdocs.org/stc/SA7065NM): Installation of Closet Assembly. Safran Cabin Inc. - [STC SA8001NM](https://openairdocs.org/stc/SA8001NM): Installation of C&D Interiors class divider and ceiling panel.. Safran Cabin Inc. - [STC ST00495LA](https://openairdocs.org/stc/ST00495LA): Installation of lavatories.. Safran Cabin Inc. - [STC ST00547LA](https://openairdocs.org/stc/ST00547LA): Installation of coat closets, L/H and R/H.. Safran Cabin Inc. - [STC ST00584LA](https://openairdocs.org/stc/ST00584LA): Installation of centerline bin kits.. Safran Cabin Inc. - [STC ST00650LA](https://openairdocs.org/stc/ST00650LA): Installation of lavatories.. Safran Cabin Inc. - [STC ST00796LA](https://openairdocs.org/stc/ST00796LA): Installation of interior modification kit.. Safran Cabin Inc. - [STC ST01077LA](https://openairdocs.org/stc/ST01077LA): Installation of passenger service unit (PSU). Safran Cabin Inc. - [STC ST01391LA](https://openairdocs.org/stc/ST01391LA): Installation of a reinforced cockpit door.. Safran Cabin Inc. - [STC ST02111LA](https://openairdocs.org/stc/ST02111LA): Installation of Coatroom. Safran Cabin Inc. - [STC SA3411NM](https://openairdocs.org/stc/SA3411NM): Installation of floor proximity emergency escape path marking system.. Bruce Aerospace Inc. - [STC ST01694AT](https://openairdocs.org/stc/ST01694AT): Installation of additional sensors for recording additional parameters on Digital Flight Data Recorder (DFDR).. Acron Aviation Inc. - [STC ST03489AT](https://openairdocs.org/stc/ST03489AT): Installation of L-3 Communications Solid State Flight data Recorder (SSFDR) Model FA2100 (any of the following part numbers: 2100-4042-00, 2100-4043-00, 2100-4043-02, or 2100-4044-00) as a replacement for the existing Tape based FDR P/N 980-4100DXUS (or equivalent FDR installed per ARINC 573 / 717).. Acron Aviation Inc. - [STC ST02472AT](https://openairdocs.org/stc/ST02472AT): Installation of a mini Quick Access Recorder (QAR) model MKI, MKII, or MKIII. Aircraft Systems and Manufacturing Inc. - [STC ST02117CH](https://openairdocs.org/stc/ST02117CH): Installation of Honeywell Enhanced Ground Proximity Warning System and GPS antenna. Amphenol Cable and Interconnect Technologies Inc. - [STC ST02184CH](https://openairdocs.org/stc/ST02184CH): Installation of elementary or enhanced surveillance Mode S transponders. Amphenol Cable and Interconnect Technologies Inc. All 767: https://openairdocs.org/tcds/A22WE/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.