TCDS 4A25

Page No. 1 2 3 4 5 6 7 8 9 10 11 12 13 14 15 16 17 18 19 20 Rev. No. 41 37 32 32 32 32 32 32 32 32 32 32 32 32 32 32 32 32 32 32 Page No. 21 22 23 24 25 26 27 28 29 30 31 32 33 34 35 36 37 38 39 40 Rev. No. 32 32 32 32 34 32 32 32 32 36 32 32 36 32 32 32 32 36 32 32 Page No. 41 42 43 44 45 46 47 48 49 50 51 52 53 54 55 56 57 58 59 Rev. No. 32 32 40 38 39 39 38 38 38 32 32 39 39 38 33 35 32 32 39 DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION 4A25 Revison 41 BOEING DC-8-11 DC-8F-55 DC-8-12 DC-8-55 DC-8-21 DC-8-61 DC-8-31 DC-8-61F DC-8-32 DC-8-62 DC-8-33 DC-8-62F DC-8-41 DC-8-63 DC-8-42 DC-8-63F DC-8-43 DC-8-71 DC-8-51 DC-8-71F DC-8-52 DC-8-72 DC-8-53 DC-8-72F DC-8F-54 DC-8-73 DC-8-73F September 27, 2010 TYPE CERTIFICATE DATA SHEET NO. 4A25 This data sheet which is a part of Type Certificate No. 4A25 prescribes conditions and limitations under which the product for which the Type Certificate was issued meets the airworthiness requirements of the Civil Air Regulations. Type Certificate Holder The Boeing Company 4000 Lakewood Boulevard Long Beach, California 90808 Type Certificate Ownership Record McDonnell Douglas Cor poration, Long Beach, California, merged with The Boeing Company in 1997. Transferred Type Certificate to The Boeing Company on Septeber 27, 2010 Douglas Aircraft Company, Inc., Santa Monica, California merged with McDonnell Aircraft Corporation August 25, 1967 The following table defines how specific airplane models are identified in the applicability of airworthiness directives (AD): Airplane Model Applicability of ADs Prior to March 1, 2002 Applicability of ADs as of March 1, 2002 1. DC-8 DC-8-10 through DC-8-40 series airplanes; OR DC-8-11 series airplanes, DC-8-12 series airplanes, DC-8-21 series airplanes, DC-8-31 series airplanes, DC-8-32 series airplanes, DC-8-33 series airplanes, DC-8-41 series airplanes, DC-8-42 series airplanes, and DC-8-43 series airplanes. DC-8-11 airplanes, DC-8-12 airplanes, DC-8-21 airplanes, DC-8-31 airplanes, DC-8-32 airplanes, DC-8-33 airplanes, DC-8-41 airplanes, DC-8-42 airplanes, and DC-8-43 airplanes. 4A25 Page 2 of 59 2. DC-8, Series 50 DC-8-50 series airplanes; OR DC-8-51 series airplanes, DC-8-52 series airplanes, DC-8-53 series airplanes, and DC-8-55 series airplanes. DC-8-51 airplanes, DC-8-52 airplanes, DC-8-53 airplanes, and DC-8-55 airplanes. Airplane Model Applicability of ADs Prior to March 1, 2002 Applicability of ADs as of March 1, 2002 3. DC-8F DC-8F series airplanes; OR DC-8F-54 series airplanes, and DC-8F-55 series airplanes. DC-8F-54 airplanes, and DC-8F-55 airplanes. 4. DC-8, Series 60 DC-8-60 series airplanes; OR DC-8-61 series airplanes, DC-8-62 series airplanes, and DC-8-63 series airplanes. DC-8-61 airplanes, DC-8-62 airplanes, and DC-8-63 airplanes. 5. DC-8, Series 60F DC-8-61F, DC-8-62F, and DC-8-63F series airplanes. DC-8-61F airplanes, DC-8-62F airplanes, and DC-8-63F airplanes. 6. DC-8, Series 70 DC-8 series 70; OR DC-8-70 series airplanes; OR DC-8-71 series airplanes, DC-8-72 series airplanes, and DC-8-73 series airplanes. DC-8-71 airplanes, DC-8-72 airplanes, and DC-8-73 airplanes. 7. DC-8, Series 70F DC-8-71F series airplanes, DC-8-72F series airplanes, and DC-8-73F series airplanes. DC-8-71F airplanes, DC-8-72F airplanes, and DC-8-73F airplanes. NOTE: In ADs prior to March 1, 2002, “Model DC-8 series airplanes,” as listed in the applicability of the AD, may have affected those models listed in rows one through seven above. Also, with respect to ADs issued prior to March 1, 2002, the information provided in the table is very general and should not be the only information utilized to determine the applicability of ADs to specific airplane models. The ADs contain separate applicability statements that rely heavily on service bulletins for determination of the applicability. I - Model DC-8-11 (Transport Aircraft), Approved August 31, 1959, (See NOTE 8 for conversion to DC-8-12 and NOTE 11 for subsequent conversion to DC-8-21 or DC-8-51) NOTE: The DC-8-11 aircraft (S/N listed belo w) have been converted to DC-8-12 and subsequently to DC-8-21 or DC-8-51. At such time as additional Model DC-8-11 aircraft may be presented for an Airworthiness Certificate, appropriate limitations will be included in this Type Certificate Data Sheet. Serial Numbers Eligible 45280 thru 45289, 45408 thru 45413, 45588 thru 45593 II - Model DC-8-21 (Transport Aircraft), Approved January 19, 1960, (See NOTE 11(e) for conversion from DC-8-12) Engines 4 Pratt and Whitney Turbojet JT4A-3, JT4A-5, JT4A-9, JT4A10, JT4A-11, or JT4A-12 (See NOTE 6 regarding intermixing of engines) Fuel Commercial Aircraft Turbine Fuel c onforming to P&WA Service Bulletin No. 2016 (PWA Specification 522). (See NOTE 14) Engine Limits See Section III, Mode l DC-8-32, for JT4A-9 and JT4A-10 engines; Section VIII, Model DC-8-33, for JT4A-11 and JT4A-12 engines. JT4A-3 and JT4A-5 Page 3 of 59 4A25 Static Thrust (Std. Day) S.L. Takeoff (5 min.) (Dry) 15,800 lbs. Maximum Continuous 12,500 lbs. Engine Limits Maximum pe rmissible engine rotor operating speeds: N 1 (Low Compressor) 6,950 r.p.m. N 2 (High Compressor) 9,050 r.p.m. Maximum permissible gas temperatures turbine outlet: Takeoff (5 min.) 607°C 1125°F Maximum Continuous 500°C 932°F Maximum Acceleration (2 min.) 607°C 1125°F Starting (Ground) 450°C 842°F Starting (Air) 475°C 887°F Oil Inlet 121°C 250°F Airspeed Limits (IAS) (S ee NOTE 10 for calibration) 2 Segment Airspeed Indicator VMO (Maximum Operating - S.L.) 340K VMO (Maximum Operating - 22,800 ft.) 378K MMO (Maximum Operating - 22,800 ft.) 378K* (M = 0.85) MMO (Maximum Operating - 40,000 ft.) 270K* (M = 0.88) MMO (Maximum Operating - 40,000 ft. to 42,000 ft.)** (M = 0.88) 3 Segment Airspeed Indicator VMO (Maximum Operating - S.L.) 340K VMO (Maximum Operating - 22,400 ft.) 377K MMO (Maximum Operating - 22,400 ft.) 377K* (M = 0.844) MMO (Maximum Operating - 29,300 ft.) 342K* (M = 0.88) MMO (Maximum Operating - 42,000 ft.) 258K* (M = 0.88) VA (Maneuvering - S.L.) 235K* VA (Maneuvering - 35,000 ft.) 269K* VA (Maneuvering - above 35,000 ft.) (M = 0.79) * Straight line variation between values shown. **See data under "Maximum Operating Altitude." (For buffet envelope, refer to Airplane Flight Manual) Up to 15,000 ft. Above 15,000 ft. VFE (Flaps Down 0 to 15°) 230K M = 0.46 (Flaps Down 16 to 25°) 210K M = 0.42 (Flaps Down 26 to 50°) 182K M = 0.37 Up to 32,000 ft. Above 32,300 ft. VLO (Landing Gear Operation) 230K M = 0.65 VLE (Landing Gear Extended) 230K M = 0.65 V (Landing Light Extension) V MO/MMO V (Fuel Dump Extension and Operation) 167K Min. - 260K Max. or M = 0.75 (whichever is the lesser) C.G. Range See the appropriate FAA Approved Ai rplane Flight Manual and Weight and Balance Manual 4A25 Page 4 of 59 Maximum Weights Taxi a nd Ramp (4) 278,000 lbs. Start of Takeoff (4) 276,000 lbs. Airborne (4) 275,500 lbs. Zero Fuel (1) (2) 167,500 lbs. Landing (3) 199,500 lbs. (1) All weight in airplane above this weight must be fuel. (2) S/N's 45422-45427, 45429-45431 and 45433-45437 are eligible for maximum zero fuel weight of 173,500 lbs. (3) Fuel dump valves required for operati on in excess of maximum landing weight. See NOTE 1(f). (4) See NOTE 16 regarding increased weights. Minimum Crew For all flights: Pilot, c opilot, and flight engineer. (See NOTE 4) Maximum Passengers (See NOTES 4 and 7) Maximum Baggage Capacity Maximum Loading Compartment Station lbs. lbs/sq. ft lbs./in. C.G. Fwd. Belly 310-640 10,350 120 48.3 + 479 in. Aft Belly 980-1337 10,350 120 44.2 +1148 in. Above values are satisfactory for a maximum of six abreast seating and a minimum of 35 inch seat spacing. (See NOTE 1(a)). Fuel Capacity See NOTE 1(c) for system fuel; NOTE 1(d) for unusable fuel; NOTE 1(e) for fuel loading and usage procedures; NOTE 1(f) for undumpable fuel; and NOTE 1(g) for fuel tank capacities. Oil Capacity Inbd. and Outbd. Engine s 70.5 lbs. ea. (+685.0) and (+814.0) Constant Speed Drives 17.5 lbs. ea. (+676.0) and (+823.0) See NOTE 1(c) for System Oil. Oil weight based upon 7.7 lbs./gal. Serial Numbers Eligible 45278, 45291- 45300, 45391-45393, 45422-45427, 45429-45431, 45433-45437, 45594-45597, and DC-8-12 S/N 45279-45283, 45289, 45304-45306, 45588-45593 when converted (See NOTE 11(e)). III - Model DC-8-32 (Transport Aircraft), Approved February 1, 1960, (See NOTE 11 for conversion to DC-8-33) Engines 4 Pratt and Whitney Turbojet JT4A-3, JT 4A-5, JT4A-9, JT4A10, JT4A-11, or JT4A-12 (See NOTE 6 regarding intermixing of engines) Fuel Commercial Aircraft Turbine Fuel c onforming to P&WA Service Bulletin No. 2016 (PWA Specification 522). (See NOTE 14) Engine Limits See Section II, M odel DC-8-21, for JT4A-3 and JT4A-5 engines; Section VIII, Model DC-8-33, for JT4A-11 and JT4A-12 engines. JT4A-9 and JT4A-10 Static Thrust (Std. Day) S.L. Takeoff (5 min.) (Dry) 16,800 lbs. Maximum Continuous 13,500 lbs. Maximum permissible engi ne rotor operating speeds: N 1 (Low Compressor) 7,060 r.p.m. N 2 (High Compressor) 9,135 r.p.m. Page 5 of 59 4A25 Maximum permissible gas temperatures - turbine outlet: Takeoff 635°C 1175°F Maximum Continuous 516°C 960°F Maximum Acceleration (2 min.) 635°C 1175°F Starting (Ground) 450°C 892°F Starting (Air) 475°C 887°F Oil Inlet 121°C 250°F Airspeed Limits (IAS) (S ee NOTE 10 for calibration) VMO (Maximum Operating - S.L.) 340K VMO (Maximum Operating - 23,000 ft.) 374K MMO (Maximum Operating - 23,000 ft.) 374K* (M = 0.847) MMO (Maximum Operating - 40,000 ft.) (M = 0.88) MMO (Maximum Operating - 40,000 ft. to 42,000 ft.)** (M = 0.88) 3 Segment Airspeed Indicator VMO (Maximum Operating - S.L.) 340K VMO (Maximum Operating - 23,000 ft.) 374K MMO (Maximum Operating - 23,000 ft.) 374K* (M = 0.847) MMO (Maximum Operating - 29,300 ft.) 342K* (M = 0.88) MMO (Maximum Operating - 42,000 ft.)** 258K* (M = 0.88) VA (Maneuvering - S.L.) 235K* VA (Maneuvering - 35,000 ft.) 269K* VA (Maneuvering - above 35,000 ft.) (M = 0.79) *Straight Line Varia tion between values shown. **See data under "Maximum Operating Altitude." (For buffet envelope, refer to Airplane Flight Manual) Up to 15,000 ft. Above 15,000 ft. VFE (Flaps Down 0 to 15°) 230K M = 0.46 (Flaps Down 16 to 25°) 210K M = 0.42 (Flaps Down 26 to 50°) 182K M = 0.37 VLO (Landing Gear Operation) 230K M = 0.65 VLE (Landing Gear Extended) 230K M = 0.65 V (Landing Light Extension) V MO/MMO V (Fuel Dump Extension and Operation) 167K Min. - 260K Max. or M = 0.75 (whichever is the lesser) C.G. Range See the appropriate FAA Approved Ai rplane Flight Manual and Weight and Balance Manual. 4A25 Page 6 of 59 Maximum Weights Taxi and Ramp 312,000 lbs. Start of Takeoff 310,000 lbs. Airborne 309,000 lbs. Zero Fuel (With JT4A-5, JT4A-10 Engi nes installed) (1) 175,900 lbs. (With JT4A-3, JT4A-9 or JT4A- 11 Engines installed) (1) 176,500 lbs. (With JT4A-12, Engines in stalled) (1) (2) 175,700 lbs. Landing (3) (4) 202,000 lbs. (1) All weight in airplane above this weight must be fuel. (2) When leading edge tanks are installed on aircraft incorporating JT4A-12 engines, the zero fuel weight may be increased 500 lbs. (3) Fuel dump valves required for ope rating in excess of maximum landing weight. See NOTE 1(f). (4) 207,000 lbs. when intercostal installati on on longeron 31 is installed in accordance with DC-8 Service Bulletin No. 53-26, or its production equivalent Minimum Crew For all flights: Pilot, c opilot, and flight engineer. (See NOTE 4) Maximum Passengers (See NOTES 4 and 7) Maximum Baggage Capacity Maximum Loading Compartment Station lbs. lbs/sq. ft lbs./in. C.G. Fwd. Belly 310-640 10,350 120 48.3 + 479 in. Aft Belly 980-1337 10,350 120 44.4 +1148 in. Above values are satisfactory for a maximum of six abreast seating and a minimum of 34 inch seat spacing. (See NOTE 1(a)). Fuel Capacity See NOTE 1(c) for system fuel; NOTE 1(d) for unusable fuel; NOTE 1(e) for fuel loading and usage procedures; NOTE 1(f)for undumpable fuel; and NOTE 1(g) for fuel tank capacities. Oil Capacity Inbd. and Outbd. Engine s 70.5 lbs. ea. (+685.0) and (+823.0) Constant Speed Drives 17.5 lbs. ea. (+676.0) and (+814.0) See NOTE 1(c) for System Oil. Oil weight based upon 7.7 lbs./gal. Serial Numbers Eligible 45256-45269, 45376- 45382, 45384-45390, 45416, 45418, 45419, 45421, 45526, 45567, 45569, 45602, 45603, 45605, 45606. (DC-8-32 S/N 45420, See NOTE 11(b); and S/N 45417, 45568, 45604, See NOTE 11(d)). IV - Model DC-8-41 (Transport Aircraft), Approved March 23, 1960 Engines 4 Rolls Royce Turbojet Conway Mark 509 Fuel Commercial Aircraft Turbine Fuel conforming to: British DERD 2482, 2486, 2494 American JP-1 (U.S. MIL-F-5616) JP-4 (U.S. MIL-F-5624C) Canadian 3-CP-23D, 3-CP-22B Engine Limits Static Thrust (Std. Day) S.L. Takeoff (5 min.) (Dry) 17,500 lbs. Maximum Continuous 14,625 lbs. Page 7 of 59 4A25 Engine Limits (cont’d) Maximu m allowable thrust for below Std. inlet air temperatures at sea level for 5 minutes at takeoff 20,000 lbs. Maximum permissible engine rotor operating speeds: N 1 (Low Compressor) 7,335 r.p.m. N 2 (High Compressor) 10,060 r.p.m. Maximum permissible gas Temperatures - turbine outlet: Takeoff 675°C 1247°F Maximum continuous 600°C 1112°F Maximum Acceleration (2 min.) 675°C 1247°F Starting (Momentary) 675°C 1247°F Ground Operation (10 sec.) 700°C 1292°F Maximum permissible oil inlet Temperature: Starting -55°C to +105°C -67°F to +221°F Other Operations -20°C to +105°C -4°F to +221°F (For transient conditions Not to exceed 15 min.): +120°C +248°F Maximum permissible air bleed ex traction of total engine airflow: Under all conditions air bleed may be used for aircraft and engine services up to the maximum delivery permitted by the engine air bleed parts, provided that the r.p.m. or turbine gas temperature operating limitations are not exceeded. Airspeed Limits See Section III, DC-8-32 C.G. Range See the appropriate FAA Approved Ai rplane Flight Manual and Weight and Balance Manual. Maximum Weights Taxi and Ramp 302,000 lbs. Start of Takeoff 300,000 lbs. Airborne 299,500 lbs. Zero Fuel (1) 173,200 lbs. Landing (2) 207,000 lbs. (1) All weight in airplane above this weight must be fuel. (2) Fuel dump valves required for operati on in excess of maximum landing weight. See NOTE 1(f). Minimum Crew For all flights: Pilot, cop ilot, and flight engineer. (See NOTE 4) Maximum Passengers (See NOTES 4 and 7) Maximum Baggage Capacity Maximum Loading Compartment Station lbs. lbs/sq. ft. lbs./in. C.G. Fwd. Belly 310-640 10,350 120 48.3 + 479 in. Aft Belly 980-1337 10,500 120 44.2 +1148 in. Above values are satisfactory for a maximum of six abreast seating and a minimum of 35 inch seat spacing. [See NOTE 1(a)]. 4A25 Page 8 of 59 Fuel Capacity See NOTE 1(c) for system fuel; NOTE 1(d) for unusable fuel; NOTE 1(e) for fuel loading and usage procedures; NOTE 1(f) for undumpable fuel; and NOTE 1(g) for fuel tank capacities. Oil Capacity Inbd. and Outbd. Engines 18.5 lbs. ea. (+701.0) and (+839.0) Constant Speed Drives 7.2 lbs. ea. (+684.0) and (+812.0) See NOTE 1(c) for System Oil. Oil weight based upon 7.7 lbs./gal. Serial Numbers Eligible 45442 thru 45445. V - Model DC-8-31 (Transport Aircraft), Approved March 30, 1960 Engines 4 Pratt and Whitney Turbojet JT4A-3, JT 4A-5, JT4A-9, JT4A-10, JT4A-11, or JT4A-12 (See NOTE 6 regarding intermixing of engines) Fuel Commercial Aircraft Turbine Fuel c onforming to P&WA Service Bulletin No. 2016 (PWA Specification 522). (See NOTE 14) Engine Limits See Section II, M odel DC-8-21, for P&W JT4A-3 and JT4A-5 engines; Section III, Model DC-8-32, for JT4A-9 and JT4A-10 engines; Section VIII, Model DC-8-33, for JT4A-11 and JT4A-12 engines. Airspeed Limits See Section III, DC-8-32. C.G. Range See the appropriate FAA Approved Ai rplane Flight Manual and Weight and Balance Manual. Maximum Weights Taxi and Ramp 302,000 lbs. Start of Takeoff 300,000 lbs. Airborne 299,500 lbs. Zero Fuel (1) 173,200 lbs. Landing (2) 207,000 lbs. (1) All weight in airplane above this weight must be fuel. (2) Fuel dump valves required for operati on in excess of maximum landing weight. See NOTE 1(f). Minimum Crew For all flights: Pilot, c opilot, and flight engineer. (See NOTE 4) Maximum Passengers (See NOTES 4 and 7) Maximum Baggage Capacity Maximum Loading Compartment Station lbs. lbs/sq. ft. lbs./in. C.G. Fwd. Belly 310-640 10,350 120 48.3 + 479 in. Aft Belly 980-1337 10,500 120 44.2 +1148 in. Above values are satisfactory for a maximum of six abreast seating and a minimum of 34 inch seat spacing. (See NOTE 1(a)). Fuel Capacity See NOTE 1(c) for system fuel; NOTE 1(d) for unusable fuel; NOTE 1(e) for fuel loading and usage procedures; NOTE 1(f) for undumpable fuel; and NOTE 1(g) for fuel tank capacities. Oil Capacity Inbd. and Outbd. Engines 70.5 lbs. ea. (+685.0) and (+823.0) Constant Speed Drives 17.5 lbs. ea. (+676.0) and (+814.0) See NOTE 1(c) for System Oil. Oil weight based upon 7.7 lbs./gal. Page 9 of 59 4A25 Serial Numbers Eligible 45274-45277 VI - Model DC-8-42 (Transport Aircraft), Approved April 26, 1960 (See NOTE 11 for conversion to DC-8-43) Engines 4 Rolls Royce Conway Mark 509 Turbojet Fuel Commercial Aircraft Turbine Fuel conforming to: British DERD 2482, 2486, 2494 American JP-1 (U.S. MIL-F-5616) JP-4 (U.S. MIL-F-5624C) Canadian 3-CP-23D, 3-CP-22B Engine Limits See S ection IV, DC-8-41. Airspeed Limits See Section III, DC-8-32. C.G. Range See the appropriate FAA Approved Ai rplane Flight Manual and Weight and Balance Manual. Maximum Weights Taxi and Ramp 312,000 lbs. Start of Takeoff 310,000 lbs. Airborne 309,000 lbs. Zero Fuel (1) 174,600 lbs. Landing (2) (3) 202,000 lbs. (1) All weight in airplane above this weight must be fuel. (2) Fuel dump valves required for operation in excess of maximum landing weight. See NOTE 1(f). (3) 207,000 lbs. when intercostal installa tion on longeron 31 is installed in accordance with DC-8 Service Bulletin No. 53-26 or its production equivalent. Minimum Crew For all flights: Pilot, c opilot, and flight engineer. (See NOTE 4) Maximum Passengers (See NOTES 4 and 7) Maximum Baggage Capacity Maximum Loading Compartment Station lbs. lbs/sq. ft. lbs./in. C.G. Fwd. Belly 310-640 10,350 120 48.3 + 479 in. Aft Belly 980-1337 10,500 120 44.2 +1148 in. Above values are satisfactory for a maximum of six abreast seating and a minimum of 34 inch seat spacing. (See NOTE 1(a)). Fuel Capacity See NOTE 1(c) for system fuel; NOTE 1(d) for unusable fuel; NOTE 1(e) for fuel loading and usage procedures; NOTE 1(f) for undumpable fuel; and NOTE 1(g) for fuel tank capacities. Oil Capacity Inbd. and Outbd. Engines 18.5 lbs. ea. (+701.0) and (+839.0) Constant Speed Drives 7.2 lbs. ea. (+674.0) and (+812.0) See NOTE 1(c) for System Oil. Oil weight based upon 7.7 lbs./gal. Serial Numbers 45565. 45566. 45598-45601, and 45609. 4A25 Page 10 of 59 VII - Model DC-8-12 (Transport Aircraft, Approved July 1, 1960, (See NOTE 8 for conversion from DC-8-11; See NOTE 11 for conversion to DC-8-21 or DC-8-51) NOTE: The DC-8-12 aircraft (S/N listed below) ha ve been converted to DC-8-21 or DC-8-51. At such time as additional Model DC-8-12 aircraft may be presented for an Airworthiness Certificate, appropriate limitations will be included in this Type Certificate Data Sheet. Serial Numbers Eligible 45279, 45304-45306 and DC-8-11 converted (See NOTE 8). VIII - Model DC-8-33 (Transport Aircraft), Approved November 28, 1960. (See NOTE 11 for conversion from DC-8-32) Engines 4 Pratt and Whitney Turbojet JT4A-3, JT 4A-5, JT4A-9, JT4A-10, JT4A-11, or JT4A-12 (See NOTE 6 regarding intermixing of engines). Fuel Commercial Aircraft Turbine Fuel c onforming to P&WA Service Bulletin No. 2016 (PWA Specification 522). (See NOTE 14) Engine Limits See Section II, Mode l DC-8-21, for JT4A-3 and JT4A-5 engines; Section III, Model DC- 8-32, for JT4A-9 and JT4A-10 engines. JT4A-11 and JT4A-12 Static Thrust (Std. Day) S.L. Takeoff (5 min.) (Dry) 17,500 lbs. Maximum Continuous 14,900 lbs. Maximum permissible engi ne rotor operating speeds: N 1 (Low Compressor) 7,160 r.p.m. N 2 (High Compressor) 9,355 r.p.m. Maximum permissible gas temperatures - turbine outlet: Takeoff 655°C 1211°F Maximum continuous 560°C 1040°F Maximum Acceleration (2 min.) 655°C 1211°F Starting (Ground) 450°C 842°F Starting (Air) 475°C 887°F Oil Inlet 121°C 250°F Airspeed Limits See Section III, DC-8-32. C.G. Range See the appropriate FAA Approved Ai rplane Flight Manual and Weight and Balance Manual. Maximum Weights Taxi and Ramp 318,000 lbs. Start of Takeoff 315,000 lbs. Airborne 314,000 lbs. Zero Fuel (with JT4A-12 engines) (1) (2) 178,200 lbs. (with JT4A-5 or JT4A-10 engines) (1) 178,400 lbs. (with JT4A-3, JT4A-9 or JT4A-11 engines) (1) 179,000 lbs. Landing (3) 207,000 lbs. (1) All weight in airplane above this weight must be fuel. (2) When leading edge tanks are installed on aircraft incorporating JT4A-12 engines, the zero fuel weight may be increased 500 lbs. (3) Fuel dump valves required for operation in excess of maximum landing weight. See NOTE 1(f). Page 11 of 59 4A25 Minimum Crew For all flights: Pilot, c opilot, and flight engineer. (See NOTE 4) Maximum Passengers (See NOTES 4 and 7) Maximum Baggage Capacity Maximum Loading Compartment Station lbs. lbs/sq. ft. lbs./in. C.G. Fwd. Belly 310-640 10,350 120 48.3 + 479 in. Aft Belly 980-1337 10,500 120 44.2 +1148 in. Above values are satisfactory for a maximum of six abreast seating and a minimum of 34 inch seat spacing. (See NOTE 1(a)). Fuel Capacity See NOTE 1(c) for system fuel; NOTE 1(d) for unusable fuel; NOTE 1(e) for fuel loading and usage procedures; NOTE 1(f) for undumpable fuel; and NOTE 1(g) for fuel tank capacities. Oil Capacity Inbd. and Outbd. Engines 70.5 lbs. ea. (+685.0) and (+823.0) Constant Speed Drives 17.5 lbs. ea. (+676.0) and (+814.0) See NOTE 1(c) for System Oil. Oil weight based upon 7.7 lbs./gal. Serial Numbers Eligible 45253-45255, 45270-45272, 45570, 45626, 45627, and DC-8-32 converted (See NOTE 11). IX - Model DC-8-43 (Transport Aircraft), Approved February 1, 1961 (See NOTE 11 for conversion from DC-8-42) Engines 4 Rolls Royce Conway Mark 509 Turbojet Fuel Commercial Aircraft Turbine Fuel conforming to: British DERD 2482, 2486, 2494 American JP-1 (U.S. MIL-F-5616) JP-4 (U.S. MIL-F-5624C) Canadian 3-CP-23D, 3-CP-22B Engine Limits See S ection IV, DC-8-41. Airspeed Limits See Section III, DC-8-32. C.G. Range See the appropriate FAA Approved Ai rplane Flight Manual and Weight and Balance Manual. Maximum Weights Taxi and Ramp 318,000 lbs. Start of Takeoff 315,000 lbs. Airborne 314,000 lbs. Zero Fuel (1) 178,200 lbs. Landing (2) 207,000 lbs. (1) All weight in airplane above this weight must be fuel. (2) Fuel dump valves required for operation in excess of maximum landing weight. See NOTE 1(f). Minimum Crew For all flights: Pilot, c opilot, and flight engineer. (See NOTE 4) Maximum Passengers (See NOTES 4 and 7) 4A25 Page 12 of 59 Maximum Baggage Capacity Maximum Loading Compartment Station lbs. lbs/sq. ft. lbs./in. C.G. Fwd. Belly 310-640 10,350 120 48.3 + 479 in. Aft Belly 980-1337 10,500 120 44.2 +1148 in. Above values are satisfactory for a maximum of six abreast seating and a minimum of 34