TCDS A22WE

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