TCDS A6WE

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 Rev. No. 30 2 26 26 26 26 26 26 26 26 26 26 26 26 26 26 26 Page No. 18 19 20 21 22 23 24 25 26 27 28 29 30 31 32 33 34 Rev. No. 26 26 26 26 26 26 26 26 26 26 26 26 26 26 26 26 26 Page No. 35 36 37 38 39 40 41 42 43 44 45 46 47 48 49 50 51 Rev. No. 26D 26 26 26 26 26 26 26 26 29 29 26 29 26 29 26 26 Page No. 52 53 54 55 56 57 58 59 60 61 62 63 64 65 66 67 68 Rev. No. 26 26 26 26 26 26 26 26 26 26 26 26 26 26 26 26 26 Page No. 69 70 71 72 73 74 75 76 77 78 79 80 81 82 83 84 85 Rev. No. 26 27 26 29 30 29 30 27 27 29 26 27 26 26 26 27 29 Page No. 86 Rev. No. 29 DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION A6WE Revision 30 BOEING DC-9-11, DC-9-12, DC-9-13, DC-9-14, DC-9-15, DC-9-15F, DC-9-21, DC-9-31, DC-9-32, DC-9-32 (VC-9C), DC-9-32F, DC-9-32F (C-9A, C-9B), DC-9-33F, DC-9-34, DC-9-34F, DC-9-41, DC-9-51, DC-9-81 (MD-81), DC-9-82 (MD-82), DC-9-83 (MD-83), DC-9-87 (MD-87), MD-88, MD-90-30, 717-200 March 25, 2014 TYPE CERTIFICATE DATA SHEET NO. A6WE This data sheet, which is a part of Type Certificate No. A6WE, prescribes conditions and limitations under which the product for which the Type Certificate was issued meets the airworthiness requirements of the Civil Air Regulations and 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 in 1997. They retained ownership of the TC A6WE and on January 30, 1998, granted The Boeing Company a license to manufacture these aircraft under the production certificate. MDC is a subsidiary of The Boeing Company. Transferred Type Certificate to The Boeing Company on September 27, 2010. Douglas Aircraft Company, Inc., Long Beach, California merged with McDonnell Aircraft Corporation August 25, 1967 A6WE 2 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-9, Series 10 DC-9, series 10; OR DC-9-10 series airplanes; OR DC-9-11 series airplanes, DC-9-12 series airplanes, DC-9-13 series airplanes, DC-9-14 series airplanes, DC-9-15 series airplanes, and DC-9-15F series airplanes. DC-9-11 airplanes, DC-9-12 airplanes, DC-9-13 airplanes, DC-9-14 airplanes, DC-9-15 airplanes, and DC-9-15F airplanes. 2. DC-9, Series 20 DC-9-20 series airplanes DC-9-21 airplanes 3. DC-9, Series 30 C-9 DC-9-30 series airplanes; OR DC-9-31 series airplanes, DC-9-32 series airplanes, DC-9-32 (VC-9C) series airplanes, DC-9-32F series airplanes, DC-9-33F series airplanes, DC-9-34 series airplanes, and DC-9-34F series airplanes. C-9 (military) airplanes (Note: may be listed without parenthetical) DC-9-31 airplanes, DC-9-32 airplanes, DC-9-32 (VC-9C) airplanes, DC-9-32F airplanes, DC-9-33F airplanes, DC-9-34 airplanes, DC-9-34F airplanes, and DC-9-32F (C-9A, C-9B) airplanes. 4. DC-9, Series 40 DC-9-40 series airplanes, OR DC-9-41 series airplanes DC-9-41 airplanes 5. DC-9, Series 50 DC-9-50 series airplanes, OR DC-9-51 series airplanes DC-9-51 airplanes 6. DC-9-81 (MD-81) DC-9-82 (MD-82) DC-9-83 (MD-83) DC-9-87 (MD-87) DC-9-81 (MD-81) series airplanes, DC-9-82 (MD-82) series airplanes, DC-9-83 (MD-83) series airplanes, and DC-9-87 (MD-87) series airplanes; OR DC-9-80 (MD-80) series airplanes. *Note: may be listed without parenthetical DC-9-81 (MD-81) airplanes, DC-9-82 (MD-82) airplanes, DC-9-83 (MD-83) airplanes, and DC-9-87 (MD-87) airplanes. 7. MD-88 MD-88 airplanes MD-88 airplanes 8. MD-90 MD-90-30 series airplanes, OR MD-90 series airplanes MD-90-30 airplanes 9. 717 717-200 series airplanes, OR 717 series airplanes 717-200 airplanes NOTE: In ADs prior to March 1, 2002, “Model DC-9 series airplanes,” as listed in the applicability of the AD, included those models listed in rows one through five above, but did not include DC -9-81 (MD-81), -82 (MD-82), - 83, (MD-83), and -87 (MD-97) airplanes. If all Model DC-9 series airplanes are NOT subject to the requirements of the AD, the applicability of the AD lists each affected model. 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. A6WE 3 I - Models DC-9-11, -12, -13, -14 (Transport Aircraft) approved November 23, 1965; Model DC-9-15 (Transport Aircraft), approved January 21, 1966; (See NOTE 9 for conversions, Models DC -9-11, -12, -13 and -14). Engines 2 Pratt and Whitney Turbojet JT8D-1, JT8D-1A, JT8D-1B, JT8D-5, JT8D-7, JT8D-7A, JT8D-7B, JT8D-9, JT8D-9A, JT8D-11, JT8D-15 or JT8D-17 (See NOTE 5 regarding intermixing of engines). Fuel Commercial Aircraft Turbine Fuel conforming to P&W Specification 522 as revised. (See NOTE 7). Engine Limits See Section II, Model DC-9-31 for JT8D-9, 9A or -15 engines. See Section VIII, Model DC-9-21, for JT8D-11 engines. See Section IX, Model DC-9-51, for JT8D-17 engines. P&W JT8D-1, JT8D-1A, JT8D-1B, JT8D-7, JT8D-7A and JT8D-7B Static Thrust, S.L. Take-off (5 min.)(JT-8D-1 Std. Day)(JT8-D-7 Flat Rated to 84°F) 14,000 lb Maximum Continuous 12,600 lb Maximum permissible engine rotor operating speeds: N1 (Low Compressor) 8,600 rpm (100.1%) N2 (High Compressor) 12,250 rpm (100%) Maximum permissible temperatures: Turbine exhaust gas JT8D-1, -7 JT8D-1A, -7A JT8D-1B, -7B Take-off (5 min.) 570°C 1,058°F 580°C 1,076°F 590°C 1,094°F Maximum Continuous 535°C 995°F 540°C 1,004°F 545°C 1,013°F Maximum Acceleration 570°C 1,058°F 580°C 1,076°F 590°C 1,094°F Starting - At ambient temperatures of: 15°C and above 420°C 788°F below 15°C 350°C 662°F Oil Inlet (continuous operation) 120°C 248°F Oil Inlet (15 min. max.) 157°C 315°F P&W JT8D-5 Static Thrust, S.L. Take-off (5 min.) (Flat Rated to 90°F) 12,250 lb Maximum Continuous (Std. Day) 12,250 lb Maximum permissible engine rotor operating speeds: N1 (Low Compressor) 8,500 rpm (98.9%) N2 (High Compressor) 12,100 rpm (98.8%) Maximum permissible temperatures: Turbine exhaust gas Take-off (5 min.) 555°C 1031°F Maximum Continuous 535°C 995°F Maximum Acceleration 555°C 1031°F Starting - At ambient temperatures of: 15°C and above 420°C 788°F below 15°C 350°C 662°F Oil Inlet (continuous operation) 120°C 248°F Oil Inlet (15 min. max.) 157°C 315°F A6WE 4 I - Models DC-9-11, -12, -13, -14, -15 APU Limits (if installed) AiResearch GTCP85-98D or -98W GTCP85-98DC[A], 98DC[B], or 98DC[C] Maximum permissible EGT temperatures: Starting (30 seconds) 760°C 1398°F 760°C 1398°F Idle (no load)(continuous) --- ---- --- ---- Maximum load (continuous) 710°C 1270°F 677°C 1251°F Transient overload 732°C 1350°F 710°C 1270°F Maximum rotor speed - all conditions 110% 110% See Section IX, Model DC-9-51 for GTCP85-98DCK. See Section XII, Model DC-9-81 for GTCP85-98DHF. Airspeed Limits (CAS) VMO (Normal Operating - 25,850' to 35,000') M=0.84 VA (Maneuvering - S.L.) 220K VA (Maneuvering - 35,000') 249K (See AFM for variation in VA speed vs. alt.) VFE (Flaps down 0° to 10°) 280K M=0.57 (Flaps down 10° to 20°) 240K M=0.57 (Flaps down 20° to 30°) 210K M=0.57 (Flaps down 30° to 50°) 180K M=0.57 VLO (Landing gear operation) 215K M=0.51 VLE (Landing gear extended) 215K M=0.51 VLO (Landing gear operation) (Gear retraction) 250K (1) M=0.70 (Gear extension) 300K (1) M=0.70 VLE (Landing gear extended) 300K (1) M=0.70 V (Landing light extension) VMO/MMO (1) Airspeed limits after DC-9 Service Bulletin No. 32-50, or production equivalent, has been accomplished. C.G. Range LANDING GEAR EXTENDED (1) LANDING GEAR RETRACTED (1) Gross Weight Pounds Forward Aft Forward Aft 44,000 569.4 604.6 566.3 604.6 77,000 -- 604.6 -- -- 78,000 569.4 -- 567.7 -- 79,000 -- 601.7 -- 604.6 81,000 -- 598.9 -- 601.7 81,700 570.4 -- -- -- 87,000 571.3 -- 569.8 -- 90,700 585.2 569.8 588.0 91,500 571.3 584.1 A6WE 5 I - Models DC-9-11, -12, -13, -14, -15 (cont’d) C.G. Range (cont’d) (1) Straight line variation between weights shown. Landing gear retraction moment is -38,813 lb which moves C.G. forward. When the aircraft is loaded within the above limits and the effect of landing gear retraction and crew and passenger movement from thei r assigned positions is accounted for and the fuel is loaded (up to the maximum takeoff weight) and used in the approved sequence, the aircraft will remain within approved C.G. limits. (See NOTE 1(b) and (e)). Maximum Weights Taxi and Ramp 91,500 lb (1)(2) Start of Take-off 90,700 lb (1)(2)(4) Zero Fuel 74,000 lb (3) Landing 81,700 lb (1) 20 ply rating main gear tires required for weights 85,700 lb and above. (2) Brake Assembly P/N 9560743 must be installed for weights above 86,300 lb (3) All weight above this value must be fuel in main tanks. (4) Dump system not required (See exemption under Certification Basis). Minimum Crew For all flights: Pilot and Copilot. Maximum Passengers See NOTES 6 and 8. Maximum Baggage Fuselage Capacity Max. Loading H-Arm Compartment Station (lb) lb/ft2 lb in. Sta. Fwd. Belly 218-482.5 5595 150 34.0 352.1 Aft Belly [646-715 715-817] ---- 3405 --- 150 34.0 27.0 ----- 724.9 With 1780 Gal. Fuselage Tank (DC-9-15) Fwd. Belly 218-373 3900(1) 150 34.0 286.8 Aft Belly 646-817 (no cargo) --- --- --- Above values satisfactory for a maximum of 5 abreast seating and a minimum seat spacing of 29 inches. (1) With fuselage tank empty or fueled. Fuel Capacity Total Usable H-Arm Sta. #1 and #2 Main Tank 9947 lb each 9892 lb each 585.7 Center Wing Tank 6518 lb 6442 lb 535.8 Fwd. Fuselage Tank (780 gal.) (1) 5543 lb 5538 lb 421.0 Aft Fuselage Tank (1000 gal.) (1) 7109 lb 7100 lb 706.5 (1) Eligible for installation in Model DC-9-15 airplane (S/N 47151) only. Fuel weights based upon fuel density of 7.1 lb/gal. (See NOTE 1(c) for system fuel; NOTE 1(d) for unusable fuel; NOTE 1(e) for fuel loading and usage procedures). Oil Capacity H-Arm Sta. Engine Oil 31.0 lb each 771.0 CSD 9.4 lb each 811.0 APU (if installed) 7.75 lb each 856.5 Oil weight based upon 7.74 lb/gal. (See NOTE 1(c) for system oil). A6WE 6 I - Models DC-9-11, -12, -13, -14, -15 (cont’d) Serial Numbers Eligible DC-9-11: None DC-9-12: None DC-9-13: None DC-9-14: 45695-45709, 45711-45716, 45725-45730, 45735-45737, 45742-45749, 45770, 45771, 45795, 45796, 45825, 45829-45832, 45842-45844, 47043, 47049, 47056, 47060, 47081, 47309. DC-9-15: 45717-45724, 45731, 45732, 45738-45741, 45772, 45773, 45775, 45776, 45778- 45787, 45797-45799, 45841, 47000-47002, 47033-47035, 47048, 47059, 47063, 47064, 47078, 47085, 47100, 47122-47127, 47151, 47204-47206. DC-9-11: S/Ns 45728-45730 modified to DC-9-14 (See NOTE 11). DC-9-12: S/N 47056 modified to DC-9-14 (See NOTE 11). II - Model DC-9-31 (Transport Aircraft) Approved December 19, 1966. Engines 2 Pratt and Whitney Turbojet JT8D-1, JT8D-1A, JT8D-1B, JT8D-5, JT8D-7, JT8D-7A, JT8D-7B, JT8D-9, JT8D-9A, JT8D-11, JT8D-15, JT8D-15A, JT8D-17, or JT8D-17A (See NOTE 5 regarding intermixing of engines). Fuel Commercial Aircraft Turbine Fuel conforming to P&W Specification 522 as revised. (See NOTE 7). Engine Limits See Section I, Models DC-9-11, -12, -13, -14, -15, for JT8D-1, -1A, -1B, -5, -7, -7A or -7B engines. See Section VIII, Model DC-9-21, for JT8D-11 engines. See Section IX, Model DC-9-51 for JT8D-17, or JT8D-17A engines. P&W JT8D-9 and JT8D-9A Static Thrust, S.L. Take-off (5 min.) (Flat Rated to 84°F) 14,500 lb Maximum continuous (Std. Day) 12,600 lb Maximum permissible engine rotor operating speeds: N1 (Low compressor) 8,600 rpm (100.1%) N2 (High Compressor) 12,250 rpm (100%) Maximum permissible temperatures: Turbine exhaust gas JT8D-9 JT8D-9A Take-off (5 min.) 580°C 1076°F 590°C 1094°F Maximum Continuous 540°C 1004°F 545°C 1013°F Maximum Acceleration 580°C 1076°F 590°C 1094°F Starting - At ambient temperatures of: 15° and above 420°C 788°F above 15°C 350°C 662°F Oil Inlet (continuous operation) 120°C 248°F Oil Inlet (15 min. max.) 157°C 315°F A6WE 7 II - Model DC-9-31 (Transport Aircraft) Approved December 19, 1966 (cont’d) Engine Limits (cont’d) P&W JT8D-15 and JT8D-15A Static Thrust, S.L. Take-off (5 min.) (Flat Rated to 84°F) 15,500 lb Maximum continuous (Std Day) 13,750 lb Maximum permissible engine rotor operating speeds: N1 (Low compressor) 8,800 rpm (102.4%) N2 (High Compressor) 12,250 rpm (100%) Maximum permissible temperatures: Turbine exhaust gas Take-off (5 min.) 620°C 1148°F Maximum Continuous 580°C 1076°F Maximum Acceleration (2 min.) 630°C 1166°F Starting - Ground 550°C 1022°F Inflight 620°C 1148°F Oil Inlet (continuous operation) 130°C 266°F Oil Inlet (15 min. max.) 165°C 329°F APU Limits See Section I, Models DC-9-11, -12, -13, -14, -15 for GTCP85-98D, GTCP85-98W, (If installed) GTCP85-98DC[A],-98DC[B] and -98DC[C]. See Section IX, Model DC-9-51 for GTCP85-98DCK. See Section XII, Model DC-9-81 for GTCP85-98DHF. Airspeed Limits (CAS) VMO (Normal Operating - S.L.) 350K VMO (Normal Operating - 23,500') 367K M=0.84 VMO (Normal Operating - 23,500 to 35,000') M=0.84 VA (Maneuvering - S.L.) (below 100,000 lb) 235K 244K (1) (Maneuvering - 35,000') (below 100,000 lb) 258K 260K (1) (Maneuvering - S.L.) (100,000 lb and up) 241K (Maneuvering - 35,000') (100,000 lb and up) 256K (See AFM for variation in VA speed vs. alt) VFE (Flaps down 0° to 10°) 280K M=0.57 (Flaps down 10° to 20°) 240K M=0.57 (Flaps down 20° to 25°) 210K M=0.57 (Flaps down 25° to 50°) 180K M=0.57 VLO (Landing Gear operation) (Gear retraction) 250K M=0.70 (Gear extension) 300K M=0.70 VLE (Landing gear extended) 300K M=0.70 V (Slat operation or extended) (S.L. to 15,540') 280K M=0.57 (Above 15,540') M=0.57 (Landing light extension) VMO/MMO (1) For airplanes with maximum takeoff gross weight 108,000 lb A6WE 8 II - Model DC-9-31 (Transport Aircraft) Approved December 19, 1966 (cont’d) C.G. Range For Maximum Ramp Weight of 106,000 lb (2) (3) LANDING GEAR EXTENDED (1) LANDING GEAR RETRACTED (1) Gross Weight Pounds Forward Aft Forward Aft 52,000 667.2 709.7 52,000 89,000 667.2 -- 89,000 94,000 -- 709.7 94,000 104,400 670.8 -- 104,400 105,000 672.0 (4) 693.5 669.0 693.5 106,000 672.7 (4) 692.0 -- -- For Maximum Ramp Weight of 109,000 lb (2) (3) LANDING GEAR EXTENDED (1) LANDING GEAR RETRACTED (1) Gross Weight Pounds Forward Aft Forward Aft 52,000 667.2 709.7 662.0 709.7 89,000 667.2 709.7 664.6 709.7 94,000 -- 709.7 -- 709.7 99,000 669.6 702.3 667.3 702.3 108,000 671.8 689.1 (5) 669.7 689.1 (5) 109,000 672.1 687.6 (5) -- -- (1) Straight line variation between weights shown. Landing gear retraction moment is -48,900 in lb which moves C.G. forward. When the aircraft is loaded within the above limits and the effect of landing gear retraction, and crew and passenger movement from their assigned positions is accounted for and the fuel is loaded (up to the maximum takeoff weight) and used in the approved sequence, the aircraft will remain within the approved C.G. limits. (See NOTE 1(b) and (e)). (2) Airplanes with ramp weight greater than 104,000 lb not approved for operations with low pressure tires. (3) Airplanes with ramp weight greater than 104,000 lb must use 10 ply nose tires and 24 ply main tires. (4) Forward C.G. limits may be extended to 671.1 @ 105,000 lb and 671.4 @ 106,000 lb when tires are installed in accordance with (3) above. (5) Aft C.G. limits may be extended to 698.8 @ 108,000 lb and 697.6 @ 109,000 lb when tires are installed in accordance with (3) above. Maximum Weights Taxi and Ramp 106,000 lb (2)(3) 109,000 lb(3) Start of Take-off 105,000 lb (2)(3) 108,000 lb(3) Zero Fuel 87,000 lb (1) Landing 99,000 lb (1) All weight above this value must be fuel in main tanks. Additional fuel may be added to the center wing tank when the main tanks are full to attain max. ramp weights. (2) Maximum for Airplane Serial Numbers 45733, 45734, 45833, 45834, 47003, 47004, 47007. (3) Seven (7) rotor disk brakes required for weights over 103,000 pounds. Minimum Crew For all flights: Pilot and Copilot. Maximum Passengers See NOTES 6 and 8. A6WE 9 II - Model DC-9-31 (Transport Aircraft) approved December 19, 1966 (cont’d) Maximum Baggage Fuselage Capacity Max. Loading H-Arm Compartment Station (lb) lb/ft2 lb in. Sta. Fwd. Belly [218-370 370-596] 8430 150 26 34 408.9 Aft Belly [760-897 897-996] 4995 150 34 18 868.4 Above values satisfactory for a maximum of 5 abreast seating and a minimum seat spacing of 29 inches. Fuel Capacity Total Usable H-Arm Sta. #1 and #2 Main Tank 9893 lb each 9838 lb each 699.6 Center Wing Tank 6518 lb 6442 lb 649.8 Fuel weights based upon fuel density of 7.1 lb/gal. (See NOTE 1(c) for system fuel; NOTE 1(d) for usable fuel; NOTE 1(e) for fuel loading and usage procedures). Oil Capacity H-Arm Sta. Engine Oil 31.0 lb each 950.0 CSD 9.4 lb each 990.0 APU (if installed) 7.75 lb each 1035.5 Oil weight based upon 7.74 lb/gal. (See NOTE 1(c) for system oil). Serial Numbers Eligible 45733, 45734, 45833-45840, 45846, 45863-45876, 47003-47009, 47020, 47023, 47026, 47036, 47042, 47050-47054, 47057, 47058, 47065-47068, 47072-47075, 47082, 47083, 47095-47099, 47119-47121, 47130, 47134-47146, 47149, 47150, 47157-47167, 47171, 47181-47189, 47202, 47203, 47207-47212, 47214-47217, 47244-47256, 47263, 47264, 47267-47272, 47280, 47310, 47315, 47316, 47325-47338, 47343-47347, 47351, 47352, 47362, 47369-47375, 47382, 47389-47391, 47393, 47399-47406, 47411, 47412, 47415- 47421, 47429, 47439-47441, 47487, 47490, 47491, 47501, 47505-47508, 47517, 47526- 47528, 47547-47552, 47564, 47574, 47576, 47583, 47588-47590, 47593, 48114-48120, 48131, 48138-48147, 48154-48159. DC-9-31, S/N 47442, 47450, 47566, 47572, 47573, 47638, 47647, 47649, 47664, 47720, 47721, and 47727 modified to DC-9-32 (See NOTE 11). S/N 45846, 47020, 47023, 47026, 47068, 47351 and 47352 were DC-9-32 modified to DC-9- 31 (See NOTE 11). The following serial numbered airplanes demonstrated compliance at time of delivery with FAR 36 dated December 1, 1969 and Amendments 36-1 and 36-2: 47589, 48114-48120, 48131, 48138-48147, 48154-48159. III - Model DC-9-15F (Transport Aircraft) Approved March 1, 1967. Engines 2 Pratt and Whitney Turbojet JT8D-1, JT8D-1A, JT8D-1B, JT8D-5, JT8D-7, JT8D-7A, T8D- 7B, JT8D-9, JT8D-9A, JT8D-11, JT8D-15 or JT8D-17 (See NOTE 5 regarding intermixing of engines). Fuel Commercial Aircraft Turbine Fuel conforming to P&W Specification 522 as revised. (See NOTE 7). A6WE 10 III - Model DC-9-15F (Transport Aircraft) Approved March 1, 1967 (cont’d) Engine Limits See Section I, Models DC-9-11, -12, -13, -14, and -15 for JT8D-1, -1A, -1B, -5, -7, -7A, or -7B engines. See Section II, Model DC-9-31 for JT8D-9, -9A or -15 engines. See Section VIII, Model DC-9-21 for JT8D-11 engines. See Section IX, Model DC-9-51 for JT8D-17 engines. APU Limits See Section I, Models DC-9-11, -12, -13, -14, -15 for GTCP85-98D, GTCP85-98W, (if installed) GTCP85-98DC[A],-98DC[B] and -98DC[C]. See Section IX, Model DC-9-51 for GTCP85-98DCK. See Section XII, Model DC-9-81 for GTCP85-98DHF. Airspeed Limits See Section I, Model DC-9-11, -12, -13, -14, and -15. C.G. Range LANDING GEAR EXTENDED (1) LANDING GEAR RETRACTED (1) Gross Weight Pounds Forward Aft Forward Aft 44,000 569.4 604.6 566.3 604.6 77,000 -- 604.6 -- -- 79,000 -- 601.7 -- 604.6 81,000 569.4 598.9 567.7 601.7 90,700 571.3 585.2 569.7 588.0 91,500 571.5 584.1 (1) Straight line variation between weights shown. Landing gear retraction moment is - 38,813 in.-lb. Moves C.G. fwd. When the aircraft is loaded within the above limits and the effect of landing gear retraction and crew and passenger movement from their assigned positions is accounted for and the fuel is loaded (up to the maximum takeoff weight) and used in the approved sequence, the aircraft will remain within approved C.G. limits. (See NOTE 1(b) and (e)). Maximum Weights Taxi and Ramp 91,500 lb (1) Start of Takeoff 90,700 lb (1) (3) Zero Fuel 74,000 lb (2) Landing 81,700 lb (1) With 20 ply rating main gear tires. (2) All weight above this value must be fuel in main tanks. (3) Dump system not required (See exemption under Certification Basis). Minimum Crew For all flights: Pilot and Copilot. Maximum Passengers See NOTES 6 and 8. Maximum Baggage Fuselage Capacity Max. Loading H-Arm Compartment Station (lb) lb/ft2 lb in. Sta. Fwd. Belly 218-482.5 5595 150 34.0 352.1 Aft Belly [646-718 718-817] ---- 3405 --- 150 34.0 27.0 ----- 724.9 Above values satisfactory for a maximum of 5 abreast seating and a minimum seat spacing of 29 inches when operating as a passenger airplane. III - Model DC-9-15F (Transport Aircraft), Approved March 1, 1967 (cont’d) A6WE 11 Maximum Baggage (cont’d) For additional information concerning loading limitations when operating as a passenger airplane as well as when operating as a cargo or combination passenger/cargo airplane, see NOTE 1(a). Fuel Capacity See Section I, Models DC-9-11, -12, -13, -14, and -15. Oil Capacity H-Arm Sta. Engine Oil 31.0 lb each 771.0 CSD 9.4 lb each 811.0 APU (if installed) 7.75 lb each 856.5 Oil weight based upon 7.74 lb/gal. (See NOTE 1(c) for system oil). Serial Numbers Eligible 45826, 45828, 47010-47018, 47044, 47045, 47055, 47061, 47062, 47086, 47087, 47152- 47156, 47240. IV - Model DC-9-32 (Transport Aircraft), Approved March 1, 1967. Engines 2 Pratt and Whitney Turbojet JT8D-1, JT8D-1A, JT8D-1B, JT8D-5, JT8D-7, JT8D-7A, JT8D-7B, JT8D-9, JT8D-9A, JT8D-11, JT8D-15, JT8D-15A, JT8D-17, or JT8D-17A (See NOTE 5 regarding intermixing of engines). Fuel Commercial Aircraft Turbine Fuel conforming to P&W Specification 522 as revised. (See NOTE 7) Engine Limits See Section I, Models DC-9-11, -12, -13, -14, -15 for JT8D-1, -1A, -1B, -5, -7, -7A, or -7B engines. See Section II, Model DC-9-31 for JT8D-9, -9A, -15, or -15A engines. See Section VIII, Model DC-9-21 for JT8D-11 engines. See Section IX, Model DC-9-51 for JT8D-17, or -17A engines. APU Limits See Section I, Models DC-9-11, -12, -13, -14, -15 for GTCP85-98D, GTCP85-98W, (if installed) GTCP85-98DC[A],-98DC[B] and -98DC[C]. See Section IX, Model DC-9-51 for GTCP85-98DCK. See Section XII, Model DC-9-81 for GTCP85-98DHF. Airspeed Limits (CAS) VMO (Normal Operating - S.L.) 350K VMO (Normal Operating - 25,850') 350K M=0.84 VMO (Normal Operating - 25,850 to 35,000') M=0.84 VA (Maneuvering - S.L.) (below 100,000 lb) 235K (Maneuvering - 35,000') (below 100,000 lb) 257K (Maneuvering - S.L.) (100,000 to 108,000 lb) 245K (Maneuvering - S.L.) (above 108,000 lb) 250.4K (Maneuvering - 35,000') (above 108,000 lb) 262.5K (See AFM for variation in VA speed vs. alt) VFE (Flaps down 0° to 10°) 280K M=0.57 (Flaps down 10° to 20°) 240K M=0.57 (Flaps down 20° to 25°) 210K M=0.57 (Flaps down 25° to 50°) 180K M=0.57 A6WE 12 IV - Model DC-9-32 (Transport Aircraft), Approved March 1, 1967 (cont’d) Airspeed Limits (CAS) (cont’d) VLO (Landing Gear operation) (Gear retraction) 250K M=0.70 (Gear extension) 300K M=0.70 VLE (Landing gear extended) 300K M=0.70 V (Slat operation or extended) (S.L. to 15,540') 280K M=0.57 (Above 15,540') M=0.57 (Landing light extension) VMO/MMO C.G. Range For Maximum Ramp Weight of 109,000 lb LANDING GEAR EXTENDED (1) LANDING GEAR RETRACTED (1) Gross Weight Pounds Forward Aft Forward Aft 58,000 667.2 709.7 663.3 709.7 89,000 667.2 -- 664.6 -- 94,000 -- 709.7 -- 709.7 108,000 668.9 689.1 666.7 689.1 109,000 668.9 687.6 For Maximum Ramp Weight of 111,000 lb LANDING GEAR EXTENDED (1) LANDING GEAR RETRACTED (1) Gross Weight Pounds Forward Aft Forward Aft 58,000 667.2 709.7 663.3 709.7 89,000 -- -- 664.6 --