# TCDS A6WE: The Boeing Company - Type: Type certificate data sheet - Status: Current - Holder: The Boeing Company - Revision: 30 - Revised: March 25, 2014 - Product: Aircraft, Large Airplane - Certification basis: Part 25, CAR 4b - Registered aircraft: 229, by the registry models matched to it (OpenAirDocs) - Data sheet PDF: https://openairdocs.org/files/sha256/97/90/9790985346fdefb858b23e98b166eb2ee41b8f91c7bec6f9a7f5369c55d77873 - FAA DRS: https://drs.faa.gov/browse/excelExternalWindow/81BB7F7F3CAF760686257CA80068D081.0001 - Page: https://openairdocs.org/tcds/A6WE ## Models (25) As the data sheet lists them. - DC-9-12 - DC-9-15F - DC-9-32F (C-9B) - MD-88 - DC-9-32F (C-9A) - DC-9-41 - DC-9-13 - DC-9-34F - DC-9-81 (MD-81) - DC-9-33F - DC-9-83 (MD-83) - DC-9-11 - DC-9-51 - DC-9-87 (MD-87) - DC-9-82 (MD-82) - 717-200 - MD-90-30 - DC-9-31 - DC-9-32F - DC-9-32 - DC-9-32 (VC-9C) - DC-9-21 - DC-9-34 - DC-9-15 - DC-9-14 ## 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 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 -- 94,000 -- 709.7 -- 709.7 96,000 667.2 -- -- 100,200 -- 708.2 -- 708.2 109,000 -- 697.6 -- 697.6 110,000 672.5 694.8 670.3 694.8 111,000 672.8 691.9 (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 approved C.G. limits. (See NOTE 1(b) and (e)). Maximum Weights ALTERNATE CONFIGURATION (3) VC-9C (4) Taxi and Ramp 109,000 lb 111,000 lb 111,000 lb Start of Takeoff 108,000 lb (2) 110,000 lb (2) 110,000 lb (2) Zero Fuel 89,000 lb (1) 92,000 lb (1) 92,000 lb (1) Landing 99,000 lb 102,000 lb (5) 99,000 lb (1) All weight above this value must be fuel in main tanks. Additional fuel may then be added to the center wing and/or forward fuselage tank (if installed) when the main tanks are full to attain max. ramp weight. (2) Dump system not required (See exemption under Certification Basis). IV - Model DC-9-32 (Transport Aircraft), Approved March 1, 1967 (cont’d) A6WE 13 Maximum Weights (cont’d) (3) Passenger seating limited to 5 abreast between stations 222 and 935 with a minimum spacing of 31 inches. (4) Passenger seating limited to 5 abreast between stations 213 and 857 with minimum seat spacing of 36 inches (for VC-9C). (5) See NOTE 3 for nose landing gear component safe life limits. 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 [218-370 370-596] 8430 150 26 34 408.9 Fwd. Belly [218-370 370-511] (1) 150 24.2 34 361.5 Aft Belly [760-897 897-996] 4995 150 34 18 868.4 With 1780 Gal. Fuselage Tank (108,000 lb maximum ramp weight only) Fuselage Capacity Max. Loading H-Arm Compartment Station (lb) lb/ft2 lb in. Sta. Fwd. Belly [218-370 370-487] (2) 150 26 34 347.3 Aft Belly [881-897 897-996] (3) 150 24 18 946.8 With 2250 Gal. Fuselage Tank (VC-9C Only) Fwd. Belly [218-432] (4) 150 27.85 314.6 Aft Belly [882-996] (5) 150 23.70 938.2 Above values satisfactory for a maximum of 5 abreast seating and a minimum seat spacing of 29 inches (alternate configuration of 111,000 lb maximum ramp weight has a minimum seat spacing of 31 inches). Alternate configuration of 111,000 lb maximum ramp weight with 2250 gallon fuselage tank installation has a minimum seat spacing of 36 inches. (1) With 580 gal fwd fuselage tank, 7215 lb with fuselage tank empty and 6330 lb with fuselage tank fueled (up to full). (2) With 780 gal fwd fuselage tank, 6655 lb with fuselage tank empty and 5760 lb with fuselage tank fueled. (3) With 1000 gal aft fuselage tank, 2106 lb with fuselage tank empty and 2025 lb with fuselage tank fueled. (4) With 1250 gal fwd fuselage tank (and 1000 gal aft fuselage tank), 5960 lb with fwd. fuselage tank empty or fueled. (5) With 1000 gal aft fuselage tank (and 1250 gal fwd. fuselage tank), 2700 lb with aft fuselage tank empty or fueled. A6WE 14 IV - Model DC-9-32 (Transport Aircraft), Approved March 1, 1967 (cont’d) Fuel Capacity Total Usable H-Arm Sta. #1 and #2 Main Tank 9893 lb each 9838 lb ea 699.6 Center Wing Tank 6518 lb 6442 lb 649.8 Fwd. Fuselage Tank (580 gal) or 4122 lb 4118 lb 547.0 Fwd. Fuselage Tank (780 gal) * 5543 lb 5538 lb 535.0 Aft Fuselage Tank (1000 gal) * 7109 lb 7100 lb 820.5 Fwd. Fuselage Tank (1250 gal)* 8903 lb 8875 lb 507.7 * (if installed) 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 45710, 45774, 45788-45793, 45827, 45845, 45847, 47019, 47021, 47022, 47024, 47025, 47027-47032, 47037-47039, 47046, 47047, 47069-47071, 47076, 47077, 47079, 47080, 47084, 47088-47094, 47101-47113, 47118, 47128, 47129, 47131-47133, 47168-47170, 47172-47177, 47190, 47195-47201, 47213, 47218, 47219, 47222-47239, 47243, 47257- 47262, 47265, 47266, 47273-47278, 47281-47285, 47289, 47290, 47292-47294, 47311- 47314, 47317-47324, 47339-47342, 47348-47350, 47353, 47354, 47356-47359, 47364, 47365, 47368, 47376-47381, 47383, 47385, 47386, 47392, 47394, 47397, 47422-47427, 47430-47438, 47442-47447, 47450-47461, 47463, 47466, 47468-47470, 47472-47474, 47477-47482, 47484-47486, 47488, 47489, 47500, 47502-47504, 47514, 47516, 47518- 47525, 47529, 47531-47535, 47539, 47542-47544, 47546, 47553-47557, 47559-47563, 47566-47573, 47575, 47579, 47582, 47591, 47592, 47594, 47595, 47598, 47600-47602, 47607, 47609, 47611, 47621, 47622, 47635-47645, 47647-47650, 47653, 47664, 47666, 47667, 47669, 47672-47675, 47678, 47680, 47701, 47720-47723, 47727, 47730, 47734, 47740, 47741, 47744, 47765, 47788-47795, 47797-47799, 48111-48113, 48125-48130, 48132, 48133, 48150, 48151. S/N 47442, 47450, 47566, 47572, 47573, 47638, 47647, 47649, 47664, 47720, 47721, and 47727 were DC-9-31 modified to DC-9-32 (See NOTE 11). DC-9-32, S/N 45846, 47020, 47023, 47026, 47068, 47351 and 47352 modified to DC -9-31 (See NOTE 11). DC-9-32 (VC-9C) 47668, 47670, 47671. 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. 47592, 47594, 47598, 47601, 47602, 47607, 47609, 47611, 47621, 47622, 47635- 47645, 47647-47650, 47653, 47664, 47666-47675, 47678, 47680, 47701, 47720-47723, 47727, 47730, 47734, 47740, 47741, 47744, 47765, 47788-47795, 47797-47799, 48111-48113, 48125-48130, 48132-48133, 48150, 48151. STC Note S/N 47431, 47474, 47477, and 47639 modified with STCs SA2541SO, SA2542SO, and SA2446SO: (See NOTE 26 for special instructions) A6WE 15 V - Model DC-9-32F (Transport Aircraft), Approved October 4, 1967. (C-9A, C-9B, See NOTE 10 Regarding Certification). 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 (1) For Model DC-9-32F (All-passenger and All-cargo configurations, and DC-9-32F (C- 9B)), see Airspeed Limits as specified for Model DC-9-32. (2) For Model DC-9-32F (C-9A Aeromed), See Airspeed Limits as specified for Model DC- 9-31. C.G. Range: For Model DC-9-32F All passenger configuration, all-cargo configuration, Passenger/Cargo passenger/cargo configuration and C-9B configuration. 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 -- 94,000 -- 709.7 -- 709.7 96,000 667.2 -- -- -- 100,200 -- 708.2 -- 708.2 109,000 -- 697.6 -- 697.6 110,000 672.5 694.8 670.3 694.8 111,000 672.8 691.9 -- -- For Model DC-9-32F, (C-9A Aeromed configuration) 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 -- 94,000 -- 709.7 -- 709.7 96,000 667.2 -- -- -- 100,200 -- 708.2 -- 708.2 108,000 671.8 698.8 669.7 698.8 109,000 672.1 697.6 V - Model DC-9-32F (Transport Aircraft), Approved October 4, 1967 (cont’d). A6WE 16 (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 position 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 DC-9-32F All Passenger, All Cargo C-9B C-9A Taxi and Ramp 111,000 lb 111,000 lb 109,000 lb, Start of Takeoff 110,000 lb (2) 110,000 lb (2) 108,000 lb (2) Zero Fuel 96,000 lb (1) 92,000 lb (1) 90,000 lb (1) Landing 102,000 lb (3) 99,000 lb (3) 99,000 lb (1) All weight above this value must be fuel in main tanks. Additional fuel may then be added to the center wing and/or fuselage tank (if installed) when the main tanks are full to attain max. ramp weight. (2) Dump system not required (see exemption under Certification Basis). (3) See NOTE 3 for nose landing gear component safe-life limits. 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 [218-370 370-596] 8430 150 26 34 408.9 Fwd. Belly [218-370 370-596] (1) 150 24.2 34 361.5 Aft Belly [760-897 897-996] 4995 150 34 18 868.4 With 1780 Gal. Fuselage Tank (C-9A only) Fwd. Belly [218-370 370-487] (2) 150 26 34 347.3 Aft Belly [897-996] (3) 150 18 946.8 With 2250 Gal. Fuselage Tank (C-9B only) Fwd. Belly [218-432] (4) 150 27.85 314.6 Aft Belly [882-996] (5) 150 23.70 938.2 Above values satisfactory for a maximum of 5 abreast seating and a minimum seat spacing of 29 inches (36 inches minimum seat spacing for C-9B). (1) With 580 gal fwd fuselage tank, 7215 lb with fuselage tank empty and 6330 lb with fuselage tank fueled (up to full). (2) With 780 gal fwd fuselage tank 7680 lb with fuselage tank empty and 5760 lb with fuselage tank fueled. (3) With 1000 gal aft fuselage tank, 2700 lb with fuselage tank empty and 2025 lb with fuselage tank fueled. A6WE 17 V - Model DC-9-32F (Transport Aircraft), Approved October 4, 1967 (cont’d). (4) With 1250 gal fwd fuselage tank (and 1000 gal. aft fuselage tank), 5960 lb with fwd. fuselage tank empty or fueled. (5) With 1000 gal aft fuselage tank (and 1250 gal. fwd. fuselage tank), 2700 lb with fwd. fuselage tank empty or fueled. For additional information concerning loading limitations when operation as passenger airplane as well as where operating as a cargo or combination passenger/cargo airplanes, see NOTE 1 (a). 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 Fwd. Fuselage Tank (580 gal) or 4122 lb 4118 lb 547.0 Fwd. Fuselage Tank (780 gal) * 5543 lb 5538 lb 535.0 Aft Fuselage Tank (1000 gal) * 7109 lb 7100 lb 820.5 Fwd. Fuselage Tank (1250 gal)* 8903 lb 8875 lb 507.7 * (if installed) 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 DC-9-32F 47040, 47041, 47147, 47148, 47220, 47221, 47355. DC-9-32F (C-9A) 47241, 47242, 47295, 47297-47300, 47366, 47367, 47448, 47449, 47467, 47471, 47475, 47495, 47536-47538, 47540, 47541. DC-9-32F (C-9B) 47577, 47578, 47580, 47581, 47584-47587, 47681, 47684, 47687, 47690, 47691, 47698- 47700, 48137, 48165, 48166. 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: 47681, 47684, 47687, 47690, 47691, 47698-47700, 48137, 48165, 48166. VI - Model DC-9-41 (Transport Aircraft), Approved February 21, 1968. Engines 2 Pratt and Whitney Turbojet 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. VI - Model DC-9-41 (Transport Aircraft), Approved February 21, 1968 (cont’d) A6WE 18 Engine Limits (cont’d) 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 See Section VII, Model DC-9-33F. C.G. Range: LANDING GEAR EXTENDED (1) LANDING GEAR RETRACTED (1) Gross Weight Pounds Forward Aft Forward Aft 50,000 703.8 749.6 699.2 749.6 97,000 703.8 -- 701.4 -- 105,000 -- 749.6 -- 749.6 107,000 (2) -- 749.6 (2) -- 749.6 (2) 114,000 705.4 731.0 703.3 731.0 739.2 (2) 739.2 115,000 705.4 729.0 737.8 (2) C.G. Range (1) Straight line variation between weights shown. Landing Gear Retraction Moment is - 53,882 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 approved C.G. limits. (See NOTES 1(b) and (e)). (2) For airplanes with 1360 gal. fuselage tanks. Maximum weights Taxi and Ramp 115,000 lb Start of Takeoff 114,000 lb (2) Zero Fuel 96,000 lb (1) Landing 102,000 lb (1) All weight above this value must be fuel in main tanks. Additional fuel may then be added to the center wing and/or fuselage tank (if installed) when the main tanks are full to attain max. ramp weight. (2) 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 [218-370 370-634] 370-350 150 26 34 429.2 Fwd. Belly [218-370 370-549] (1) 150 24 34 382.2 Aft Belly [798-973 973-1072] 5925 150 34 18 924.4 Above values satisfactory for a maximum of 5 abreast seating and a minimum seat spacing of 29 inches. VI - Model DC-9-41 (Transport Aircraft), Approved February 21, 1968 (cont’d) A6WE 19 With 1360 Gal. Fuselage Tank Maximum Baggage Fuselage Capacity Max. Loading H-Arm Compartment Station (lb) lb/ft2 lb in. Sta. Fwd. Belly [218-370 370-549] (1) 150 24.18 26.7 382.2 Aft Belly [894-973 973-1072] (2) 150 30.89 17.58 976.0 With 2250 Gal. Fuselage Tank (C-9B only) Fwd. Belly [218-432] (4) 150 27.85 314.6 Aft Belly [882-996] (5) 150 23.70 938.2 Above values satisfactory for a maximum of 5 abreast seating and a minimum seat spacing of 32 inches between stations 222-414 and 31 inches between stations 414-1039. (1) With 580 gal. aft fuselage tank, 5925 lb with fuselage tank empty and 3570 lb with fuselage tank fueled (up to full). Fuel Capacity Total Usable H-Arm Sta. #1 and #2 Main Tank 9893 lb each 9838 lb each 737.6 Center Wing Tank 6518 lb 6442 lb 687.8 Fwd. Fuselage Tank (580 gal) or 4122 lb 4118 lb 585.0 Aft Fuselage Tank (780 gal) * 5543 lb 5538 lb 845.9 * (if installed) 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 47114-47117, 47178-47180, 47286-47288, 47395, 47396, 47464, 47492-47494, 47497- 47499, 47509-47513, 47596, 47597, 47599, 47603-47606, 47608, 47610, 47612-47620, 47623-47634, 47646, 47725, 47747, 47748, 47750, 47759-47762, 47766-47768, 47777- 47781. 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. 47596, 47597, 47599, 47603-47606, 47608, 47610, 47612-47620, 47623-47634, 47646, 47725, 47747, 47748, 47750, 47759-47762, 47766-47768, 47777-47781. A6WE 20 VII - Model DC-9-33F (Transport Aircraft), Approved April 5, 1968. Engines 2 Pratt and Whitney Turbojet 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.) 340K VMO (Normal Operating - 27,260') 340K M=0.84 VMO (Normal Operating - 27,260 to 35,000') M=0.84 VA (Maneuvering - S.L.) (below 100,000 lb) 235K (Maneuvering - 35,000') (below 100,000 lb) 258K (Maneuvering - S.L.) (114,000 lb) 250K (Maneuvering - 35,000') (114,000 lb) 267K (See AFM for variation in VA speed vs. alt) (VA speeds Linear between 100,000 lb & 114,000 lb) VFE (Flaps down 0° to 10°) 280K M=0.57 (Flaps down 10° to 20°) 240K M=0.57 (Flaps down 20° to 25°) 220K M=0.57 (Flaps down 25° to 50°) 190K 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 (Landing light extension) VMO/MMO V (Slat operation or extended) (S.L. to 15,500') 280K M=0.57 (Above 15,540') M=0.57 C.G. Range LANDING GEAR EXTENDED (1) LANDING GEAR RETRACTED (1) Gross Weight Pounds Forward Aft Forward Aft 52,000 667.2 709.7 662.8 709.7 89,000 667.2 -- 664.6 -- 94,000 -- 709.7 -- 709.7 111,700 -- 705.7 -- 705.7 114,000 668.9 693.3 666.8 693.3 115,000 668.9 688.0 A6WE 21 VII - Model DC-9-33F (Transport Aircraft), Approved April 5, 1968 (cont’d) C.G. Range (cont’d) (1) Straight line variation between weights shown. Landing gear retraction moment is -53,882 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 approved C.G. limits. (See NOTE 1(b) and (e)). Maximum weights Taxi and Ramp 115,000 lb Start of Takeoff 114,000 lb (2) Zero Fuel 96,000 lb (1) Landing 102,000 lb (1) All weight above this value must be fuel in main tanks. Additional fuel may then be added to the center wing and/or forward fuselage tank (if installed) when the main tanks are full to attain max. ramp weight, not to exceed their individual capacities. (2) 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 [218-370 370-596] 8430 150 26 34 408.9 Fwd. Belly [218-370 370-511] (1) 150 24.2 34 361.5 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 between stations 238-628 and 30 inches between stations 628-1005. (1) With 580 gal fwd fuselage tank, 7215 lb with fuselage tank empty and 6330 lb with fuselage tank full. For additional information concerning loading limitations when operating as passenger airplane as well as when operating as a cargo or combination passenger/cargo airplane, see NOTE 1(a). 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 Fwd. Fuselage Tank (580 gal) or 4122 lb 4118 lb 547.0 Fwd. Fuselage Tank (780 gal) * 5543 lb 5538 lb 535.0 Aft Fuselage Tank (1000 gal) * 7109 lb 7100 lb 820.5 Fwd. Fuselage Tank (1250 gal)* 8903 lb 8875 lb 507.7 * (if installed) 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). VII - Model DC-9-33F (Transport Aircraft), Approved April 5, 1968 (cont’d) A6WE 22 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 47191-47194, 47279, 47291, 47363, 47384, 47407-47410, 47413, 47414, 47428, 47462, 47465, 47476, 47496, 47530, 47545, 47565. VIII - Model DC-9-21 (Transport Aircraft), Approved November 25, 1968. Engines: 2 Pratt and Whitney Turbojet JT8D-9, JT8D-9A or JT8D-11 (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 or -9A engines. 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 P&W JT8D-11 Static Thrust, S.L. Take-off (5 min.) (Flat Rated to 84°F) 15,000 lb Maximum continuous (Std. Day) 12,600 lb Maximum permissible engine rotor operation speeds: N1 (Low Compressor) 8,600 rpm (100.1%) N2 (High Compressor) 12,250 rpm (100%) A6WE 23 VIII - Model DC-9-21 (Transport Aircraft), Approved November 25, 1968 (cont’d) Engine Limits P&W JT8D-11 (cont’d) Maximum permissible temperatures: Turbine exhaust gas Take-off (5 min.) 595°C 1103°F Maximum Continuous 550°C 1022°F Maximum Acceleration (2 min.) 595°C 1103°F Starting - Ground 510°C 950°F Inflight 550°C 1022°F Oil Inlet (continuous operation) 130°C 266°F Oil Inlet Transient (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 MMO (Normal Operating - 23,500 to 35,000') M=0.84 VA (Maneuvering - S.L.) 226K VA (Maneuvering - 35,000') 263K (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 (Landing light extension) VMO/MMO V (Slat operation or extended) (S.L. to 15,540') 280K M=0.57 (Above 15,540') M=0.57 C.G. Range LANDING GEAR EXTENDED (1) LANDING GEAR RETRACTED (1) Gross Weight Pounds Forward Aft Forward Aft 50,000 562.2 596.1 559.0 596.1 86,000 562.2 -- 560.3 -- 95,300 564.1 -- 562.5 -- 100,000 563.1 -- 561.5 -- 101,000 563.0 596.1 (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 position 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)). A6WE 24 VIII - Model DC-9-21 (Transport Aircraft), Approved November 25, 1968 (cont’d) Maximum weights Taxi and Ramp 101,000 lb Start of Takeoff 100,000 lb Zero Fuel 84,000 lb (1) Landing 95,300 lb (1) All weight above this value must be fuel in main tanks. 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 7460 150 34 352.1 Aft Belly 646-817 4540 150 27 724.9 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 585.6 Center Wing Tank 6518 lb 6442 lb 535.8 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 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 47301-47308, 47360, 47361. IX - Model DC-9-51 (Transport Aircraft), Approved August 11, 1975. Engines 2 Pratt and Whitney Turbojet JT8D-15, JT8D-15A, JT8D-17, JT8D-17A. 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-15 or JT8D-15A engines. P&W JT8D-17 and JT8D-17A Static Thrust, S.L. Take-off (5 min.)(Flat Rated to 84°F) 16,000 lb Maximum Continuous (Std. Day) 15,200 lb Maximum permissible engine rotor operation speeds: N1 (Low Compressor) 8,800 rpm (102.4%) N2 (High Compressor) 12,250 rpm (100%) A6WE 25 IX - Model DC-9-51 (Transport Aircraft), Approved August 11, 1975 (cont’d) Engine Limits P&W JT8D-17 and JT8D-17A (cont’d) Maximum permissible temperatures: Turbine outlet gas Take-off (5 min.) 650°C 1202°F Maximum Continuous 610°C 1130°F Maximum Acceleration (2 min.) 660°C 1220°F Starting - Ground 550°C 1022°F Inflight 650°C 1202°F Oil Inlet (continuous operation) 130°C 266°F Oil Inlet Transient (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 XII, Model DC-9-81 for GTCP85-98DHF. AiResearch GTCP85-98DCK Maximum permissible EGT temperatures: Starting (30 seconds) 760°C Idle (no load)(continuous) --- Maximum allowable (continuous) 663°C Maximum Rated 621°C Maximum rotor speed - all conditions 110% Airspeed Limits (CAS) VMO (Normal Operating - S.L.) 340K VMO (Normal Operating - 27,260') 321K M=0.84 VMO (Normal Operating - 27,260 to 35,000') M=0.84 VA (Maneuvering - S.L.) 242K VA (Maneuvering - 35,000') 254K (See AFM for variation in VA speed vs. alt) VFE (Flaps down 0° to 10°) 280K (Flaps down 10° to 20°) 240K (Flaps down 20° to 25°) 222K (Flaps down 25° to 40°) 195K (Flaps down 40° to 50°) 190K VLO (Landing Gear operation) (Gear retraction) 250K M=0.7 (Gear extension) 300K M=0.7 VLE (Landing gear extended) 300K M=0.7 V (Landing light extension) 350K M=0.84 V (Slat operation or extended) (S.L. to 15,540') 280K M=0.57 (Above 15,540') M=0.57 A6WE 26 IX - Model DC-9-51 (Transport Aircraft), Approved August 11, 1975 (cont’d) C.G. Range LANDING GEAR EXTENDED (1) LANDING GEAR RETRACTED (1) Gross Weight Pounds Forward Aft Forward Aft 58,000 752.7 806.5 749.0 806.5 90,000 752.7 806.5 749.0 806.5 102,500 752.7 806.5 752.7 806.5 110,000 754.9 806.5 754.9 806.5 116,000 756.7 806.5 756.7 806.5 122,200 758.6 782.6 758.6 782.6 At intermediate weights, C.G. limits vary linearly. (1) Straight line variation between weights shown. Landing gear retraction moment is -53,882 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 position 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 123,200 lb Start of Takeoff 122,200 lb (2) Zero Fuel 100,500 lb (1) Landing 110,000 lb (1) All weight above this value must be fuel in main tanks. Additional fuel may then be added to the center wing and/or fuselage tank (if installed) when the main tanks are full to attain max. ramp weight not to exceed their individual capacities. (2) 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 [218-370 370-693] -- 10,755 150 150 24.18 29.23 -- 459.5 Aft Belly [855-1068 1068-1167 -- 6,855 150 150 32.02 17.58 -- 1001.2 With 580 gal. Fuselage Tank (1) Fwd. Belly [218-370 370-554] -- 8,655 150 150 24.18 24.14 -- 413.9 Aft Belly [851-1068 1068-1167] -- 6,855 150 150 32.02 17.58 -- 1001.2 With 1360 gal. Fuselage Tank (1) Fwd. Belly [218-370] 370-606] -- 8,655 150 150 24.18 28.14 -- 413.9 Aft Belly [951-1068 1068-1167] -- 4,500 150 150 31.45 17.58 -- 1051.4 A6WE 27 IX - Model DC-9-51 (Transport Aircraft), Approved August 11, 1975 (cont’d) Maximum Baggage (cont’d) With 780 gal. Fuselage Tank (1) Fuselage Capacity Max. Loading H-Arm Compartment Station (lb) lb/ft2 lb in. Sta. Fwd. Belly [218-370 370-582] -- 8,085 150 150 24.18 27.74 -- 400.9 Aft Belly [855-1068 1068-1167] -- 6,855 150 150 32.02 17.58 -- 1001.2 With 1000 gal. Fuselage Tank (1) Fwd. Belly [218-370 370-554] 7,395 150 150 24.18 26.96 385.2 Aft Belly [835-1068 1068-1167] -- 6,855 150 150 32.02 17.58 -- 1001.2 Above values satisfactory for a maximum of 5 abreast seating and a minimum seat spacing of 31 inches. Three seats in the first row of the passenger cabin may be spaced 30 inches from the second row instead of 31 inches. (1) With Fuselage Tank(s) empty or fueled. Fuel Capacity Total Usable H-Arm Sta. #1 and #2 Main Tank 9893 lb each 9838 lb each 794.6 Center Wing Tank 6518 lb 6442 lb 744.8 Fus. Tank (580 gal)* 4122 lb 4118 lb 642.0 Fus. Tank (780 gal)* 5543 lb 5538 lb 630.0 Fus. Tank (1000 gal)* 7109 lb 7100 lb 622.0 Aft Fus. Tank (780 gal)* 5543 lb 5538 lb 909.0 *(if installed) 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 1121.0 CSD 9.4 lb each 1161.0 APU (if installed) 7.75 lb each 1206.5 Oil weight based upon 7.74 lb/gal. (See NOTE 1(c) for system oil). Serial Numbers Eligible 47651, 47652, 47654-47663, 47665, 47676, 47677, 47679, 47682, 47683, 47685, 47686, 47688, 47689, 47692-47697, 47703, 47705, 47708-47710, 47712-47719, 47724, 47726, 47728, 47729, 47731-47733, 47735-47739, 47742, 47743, 47745, 47746, 47749, 47751, 47753-47758, 47763, 47764, 47769-47776, 47782-47787, 47796, 48100-48102, 48107- 48110, 48121, 48122, 48134-48136, 48148, 48149. Noise Standards : Airplanes of the Model DC-9-51 issued an original U.S. Standard Airworthiness Certificate comply with FAR 36 dated December 1, 1969, and Amendment 36-1 and 36-2. Airplane operation in excess of 121,000 pounds has not been evaluated for compliance with FAR Part 36 dated December 1, 1969, and amendments 36-1 and 36-2. A6WE 28 X - Model DC-9-34F (Transport Aircraft) Approved April 20, 1976. Engines 2 Pratt and Whitney Turbojet 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 No. 522 as revised. (See NOTE 7). Engine Limits 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.) 340K VMO (Normal Operating - 27,260') 321K M=0.84 VMO (Normal Operating - 27,260 to 35,000') M=0.84 VA (Maneuvering - S.L.) 248.7K VV (Maneuvering - 35,000') 254K (See AFM for variation in VA speed vs. alt) VFE (Flaps down 0° to 10°) 280K (Flaps down 10° to 20°) 240K (Flaps down 20° to 25°) 220K (Flaps down 25° to 40°) 195K (Flaps down 40° to 50°) 190K VLO (Landing Gear operation) (Gear retraction) 250K M=0.7 (Gear extension) 300K M=0.7 VLE (Landing gear extended) 300K M=0.7 V (Landing light extension) 350K M=0.84 V (Slat operation or extended) (S.L. to 15,540') 280K M=0.57 (Above 15,540') M=0.57 C.G. Range LANDING GEAR EXTENDED (1) LANDING GEAR RETRACTED (1) Gross Weight Pounds Forward Aft Forward Aft Up to 52,000 667.1 709.6 662.7 709.6 Up to 89,000 667.1 709.6 -- 709.6 At 89,000 667.1 709.6 664.5 709.6 94,000 -- 709.6 -- 709.6 111,700 -- 705.6 -- 705.6 121,000 669.0 689.7 667.3 689.7 122,000 669.2 687.9 At intermediate weights, C.G. limits vary linearly. A6WE 29 X - Model DC-9-34F (Transport Aircraft) Approved April 20, 1976 (cont’d) C.G. Range (cont’d) (1) Straight line variation between weights shown. Landing gear retraction moment is -53,903 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 position 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 122,000 lb Start of Takeoff 121,000 lb (2) Zero Fuel 98,500 lb (1) Landing 110,000 lb (1) All weight above this value must be fuel in main tanks. Additional fuel may then be added to the center wing and/or fuselage tank (if installed) when the main tanks are full to attain max. ramp weight not to exceed their individual capacities. (2) 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 With 780 gal. Fuselage Tank (1) Fuselage Capacity Max. Loading H-Arm Compartment Station (lb) lb/ft2 lb in. Sta. Fwd. Belly [218-370 370-465 465-597] 8430 150 150 150 24 23 32 408.7 Aft Belly [856-897 897-996] 2640 150 150 29.48 17.58 922 With 1360 gal. Fuselage Tank (1) Fwd. Belly [218-370 370-511] 6330 150 150 24.18 25.11 361.5 Aft Belly [856-897 897-996] 2640 150 150 29.48 17.58 922.2 Above values satisfactory for a maximum for 5 abreast seating and a minimum seat spacing of 30 inches. (1) With fuselage tank(s) empty or fueled. For additional information concerning loading limitations when operating as a passenger airplane as well as when operating as a cargo airplane, see NOTE 1(a). 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 Fwd. Tank (580 gal) 4122 lb 4118 lb 547.0 Aft Fus. Tank (780 gal) 5543 lb 5538 lb 807.9 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). X - Model DC-9-34F (Transport Aircraft) Approved April 20, 1976 (cont’d) A6WE 30 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 47702, 47704, 47706, 47707, 47752. Noise Standards Airplanes of the Model DC-9-34F issued an original U.S. Standard Airworthiness Certificate comply with FAR part 36 dated December 1, 1969, and Amendments 36 -1 and 36-2. XI - Model DC-9-34 (Transport Aircraft) Approved November 3, 1976. Engines 2 Pratt and Whitney Turbojet 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 No. 522 as revised. (See NOTE 7). Engine Limits 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.) 340K VMO (Normal Operating - 27,260') 321K M=0.84 VMO (Normal Operating - 27,260 to 35,000') M=0.84 VA (Maneuvering - S.L.) 248.7K VV (Maneuvering - 35,000') 254K (See AFM for variation in VA speed vs. alt) VFE (Flaps down 0° to 10°) 280K (Flaps down 10° to 20°) 240K (Flaps down 20° to 25°) 220K (Flaps down 25° to 40°) 195K (Flaps down 40° to 50°) 190K VLO (Landing Gear operation) (Gear retraction) 250K M=0.7 (Gear extension) 300K M=0.7 VLE (Landing gear extended) 300K M=0.7 V (Landing light extension) 350K M=0.84 V (Slat operation or extended) (S.L. to 15,540') 280K M=0.57 (Above 15,540') M=0.57 A6WE 31 XI - Model DC-9-34 (Transport Aircraft) Approved November 3, 1976 (cont’d) C.G. Range LANDING GEAR EXTENDED (1) LANDING GEAR RETRACTED (1) Gross Weight Pounds Forward Aft Forward Aft Up to 52,000 667.1 709.6 662.7 709.6 Up to 89,000 667.1 709.6 -- 709.6 At 89,000 667.1 709.6 664.5 709.6 94,000 -- 709.6 -- 709.6 111,700 -- 705.6 -- 705.6 121,000 669.0 689.7 667.3 689.7 122,000 669.2 687.9 (1) Straight line variation between weights shown. Landing gear retraction moment is -53,903 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 position 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 122,000 lb Start of Takeoff 121,000 lb (2) Zero Fuel 98,500 lb (1) Landing 110,000 lb (1) All weight above this value must be fuel in main tanks. Additional fuel may then be added to the center wing and/or fuselage tank (if installed) when the main tanks are full to attain max ramp weight not to exceed their individual capacities. (2) 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 With 1360 gal. Fuselage Tank (1) Fuselage Capacity Max. Loading H-Arm Compartment Station (lb) lb/ft2 lb in. Sta. Fwd. Belly [218-370 370-511] 6330 150 150 24.18 25.11 361 Aft Belly [856-897 897-996] 2640 150 150 29.48 17.58 922.2 With 1780 gal. Fuselage Tank (1) Fwd. Belly [218-370 370-489] 5760 150 150 23.88 23.87 347.3 Aft Belly [882-897 897-996] 2025 150 150 25.33 17.58 938.2 With 2250 gal. Fuselage Tank (1) Fwd. Belly [218-370 370-432] 4470 150 150 23.88 18.06 314.6 Aft Belly [882-897 897-996] 2025 150 150 25.33 17.58 938.2 A6WE 32 XI - Model DC-9-34 (Transport Aircraft) Approved November 3, 1976 (cont’d) Maximum Baggage (cont’d) Above values satisfactory for a maximum for 5 abreast seating and a minimum seat spacing of 30 inches. (1) With fuselage tank(s) empty or fueled. For additional information concerning loading limitations when operating as a passenger airplane as well as when operating as a cargo airplane, see NOTE 1(a). 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 Fwd. Fus. Tank (580) * 4122 lb 4118 lb 547.0 Aft Fus. Tank (780) * 5543 lb 5538 lb 807.9 Fwd. Fus. Tank (780) * 5543 lb 5538 lb 535.0 Fwd. Fus. Tank (1250) * 8903 lb 8875 lb 507.7 Aft Fus. Tank (1000) * 7109 lb 7100 lb 820.5 * (if installed) 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: 47711, 48103-48106, 48123, 48124. Noise Standards : Airplanes of the Model DC-9-34F issued an original U.S. Standard Airworthiness Certificate comply with FAR part 36 dated December 1, 1969, and Amendments 36-1 and 36-2. XII - Model DC-9-81 (Transport Aircraft) Approved August 25, 1980. (MD-81, See NOTE 14, regarding certification) Engines 2 Pratt and Whitney Turbofan JT8D-209, -217, -217A, -217C, or -219. (See NOTE 5 regarding intermixing of engines). Oil P&W Turbojet Engine Service Bulletin No. 238 lists approved brand oils. Synthetic type oil conforming to P&W Specification 521 as revised. Fuel Commercial aircraft turbine fuel conforming to P&W Specification 522 as revised. (See NOTE 7). Engine Limits See Section XIII, Model DC-9-82 for JT8D-217, -217A and -217C engines. Power Rating JT8D-209 JT8D-219 Maximum Static Thrust at sea level Maximum Takeoff (5 min. flat-rated to 84°F)* 19,250 lb 21,700 lb Normal Takeoff (5 min. flat-rated to 77°F)* 18,500 lb 21,000 lb Maximum Takeoff, Engine Inoperative (10 min)** 19,250 lb 21,700 lb A6WE 33 XII - Model DC-9-81 (Transport Aircraft) Approved August 25, 1980 (cont’d) Engine Limits (cont’d) Maximum Takeoff Rating is the maximum thrust certified for takeoff operation. The Maximum takeoff Rating is available through actuation of the fuel control Automatic Reserve Thrust System (ARTS) when the engine is operating at the Normal Takeoff Rating, or manually by throttle movement. Normal Takeoff Rating is the maximum thrust to be set for takeoff operation with the aircraft Automatic Reserve Thrust System (ARTS) operative. When set, this rating ensures that the Takeoff Rating will be achieved upon actuation of ARTS. Maximum Continuous 16,000 lb 18,900 lb Rotor Speed, Maximum N1 (Low Compressor) Takeoff 8,150 rpm (99.2%) 8,350 rpm (101.6%) Normal Takeoff 7,850 rpm (95.5%) 8,120 rpm (98.8%) N2 (High Compressor) Takeoff 12,370 rpm (101.0%) 12,550 rpm (102.5%) Normal Takeoff 12,150 rpm (99.2%) 12,350 rpm (100.9%) Exhaust Gas Temperature, Maximum Maximum Takeoff (2 min.) 630°C (1166°F) Maximum Takeoff (5 min.)*, (10 min)** 570°C (1058°F) 625°C (1157°F) Normal Takeoff (2 min.)* 595°C (1103°F) Normal Takeoff (5 min.)* 550°C (1022°F) 590°C (1094°F) Continuous 530°C (986°F) 580°C (1076°F) Starting Ground *** 475°C (887°F) 475°C (887°F) In-Flight 570°C (1058°F) 625°C (1157°F) * The total time at both Takeoff Thrust Levels must not exceed 5 minutes. ** In the event of an engine failure during Takeoff or Go-Around, a total time of Ten (10) minutes of Takeoff Thrust is required. *** The ground starting EGT limit for the JT8D-209/-217/-217A/-217C/-219 engines is increased to 500°C (932°F) when Appendix 11 of the applicable FAA Approved Airplane Flight Manual is utilized. Oil-Inlet Temperature-Maximum Continuous operation 135°C (275°F) Transient operation 165°C (329°F) Transient operation above 135°F (275°C) is limited to 15 minutes. Oil Pressure Limits 40 to 55 psi Fuel Pressure Limits Normal at engine pump inlet -15 psi Minimum at engine pump inlet -not less than 5 psi above true fuel vapor pressure Maximum at engine pump inlet -no greater than 50 psi with a vapor liquid ratio of zero Air Bleed Extraction % High Compressor Bleed 13th Stage Normal Maximum At 90% and below Max. Cont. Thrust 8.0 8.0 Above 90% Max. Cont. Thrust 3.5 5.5 A6WE 34 XII - Model DC-9-81 (Transport Aircraft) Approved August 25, 1980 (cont’d) Engine Limits (cont’d) Air Bleed Extraction % Low Compressor Bleed 8th Stage Normal Maximum At and below Max. Cont. Thrust 4.0 4.0 Above Max. Cont. Thrust 2.75 3.25 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. AiResearch GTCP85-98DHF Maximum permissible EGT temperatures: Starting (30 seconds) 760°C Maximum allowable (continuous) 663°C Maximum Rated 621°C Maximum rotor speed - all conditions 46,000 (110%) Maximum allowable rotor speed 110% Maximum rated RPM - all conditions 42,000 100% RPM 42,000 Fuel Pressure Limits, Minimum of 5 psi above true vapor pressure up to 40 psi. Oil Capacity total 5 qts Oil Capacity usable 4 qts Oil Pressure, Normal and Idle operation 95 + 5 psi Low Oil pressure (Master Caution) 45 psi Maximum Oil Temperature 255°F APU Envelope, Start up to 30,000 feet Operate up to 35,000 feet APU Electrical Load must not exceed 57% of rated load above 25,000 ft. Airspeed Limits (CAS) VMO (Maximum Operating - S.L.) 340K VMO (Maximum Operating - 27,240') 340K (M=0.84) VMO (Maximum Operating - 27,300 to 37,000') (M=0.84) VA (Maneuvering - S.L.) 263K (Maneuvering - 30,000') 297K (Maneuvering - 37,000') 262K (See AFM for variation in VA speeds vs. altitude.) VFE (Flaps down 0.1° - 13°) 280K (M=0.57) (Flaps down 13.1° - 20°) 240K (M=0.57) (Flaps down 20.1° - 25°) 220K (M=0.57) (Flaps down 25.1° - 30°) 200K (M=0.57) (Flaps down 31° - 40°) 195K (M=0.57) V (Slat Extended Takeoff, 17.8°) 280K (M=0.51) (Slat Extended Landing, 21°) 240K (M=0.51) (Autoslat Extension) 280K (M=0.51) 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 (Landing light extension) 350K (M=0.84) A6WE 35 XII - Model DC-9-81 (Transport Aircraft), Approved August 25, 1980 (cont’d) C.G. Range Gross Weight LANDING GEAR LANDING GEAR EXTENDED (1) RETRACTED (1) Pounds Kilograms Forward Aft Forward Aft 70,000 31,751 884.3 938.5 881.1 938.5 118,000 53,524 -- 938.5 -- 938.5 124,000 56,245 884.3 936.0 881.1 936.0 130,000 58,967 886.0 933.6 883.3 933.6 140,000 63,503 -- 929.5 887.8 929.5 141,000 63,957 890.5 929.1 142,000 64,410 -- 928.8 888.7 928.8 143,000 64,864 891.4 928.5 NOTE: Inflight weight limited to 79,000 pounds (35,834 kg) minimum. (1) Straight line variation between weights shown. Gear retraction moment is -10,154 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 weigh t) and used in the approved sequence, the aircraft will remain within approved C.G. limits. (2) Main landing gear has "zero" retraction moment. Maximum weights Taxi and Ramp 143,000 lb (3) Start of Takeoff 142,000 lb (2) Zero Fuel 120,000 lb (1) Landing 130,000 lb (1) All weight in excess of 120,000 lb must be in usable fuel. After filling the main wing tanks, additional fuel may then be added to the center wing tank to attain the maximum design taxi weight. (2) Fuel jettisoning system not installed. (See exemption under Certification Basis). (3) 26 Ply rating MLG tires required for all ramp weights over 141,000 lb Minimum Crew For all flights. Pilot and Copilot. Maximum Passengers SEE NOTES 6 and 8. A6WE 36 XII - Model DC-9-81 (Transport Aircraft) Approved August 25, 1980 (cont’d) Maximum Baggage: FORWARD CARGO COMPARTMENT Area Designation A B A + B Location (Sta. to Sta.) 218 to 370 370 to 541 218 to 541 H-Arm (Fus. Sta.) 294.9 467.5 378.6 Usable Volume (Cu/Ft) 239 225 464 Maximum Running Load (lb/in. of Fuselage Length) 24.0 24.0 24.0 Placard Capacity (lb) 3585 3375 6960 Combined Capacity (lb) Sta. 218 to 541 -- -- 6960 Maximum floor loading not to exceed 150 lb/ft2 Each of the above limitations is independent of the others. Do not exceed any limitation. NOTE: The combined capacity of Fus. Sta. 218 to 786.5 is not to exceed 12,150 pounds. NOTE: The above section and compartment limitations are applicable only to the following Factory Serial Numbers: 48002-48022, 48024-48059, 48062, 48063, 48066-48074, 48079, 48080, 48083, 48086-48099, 49100-49104, 49110-49127, 49138-49145, 49149-49190, 49192-49222, 49229, 49230, 49237, 49245, 49246, 49249-49251, 49253-49265, 49269-49273, 49277, 49278, 49286-49289, 49430-49435, 49531, 49549-49552, 49669, 49740, 49794-49796, 49969-49975, 53053-53062, 53176-53181, 53203-53206, 53216-53235. See Section XIV for limitations applicable to other DC-9-81 and -82 airplanes. A6WE 37 XII - Model DC-9-81 (Transport Aircraft) Approved August 25, 1980 (cont’d) MIDDLE CARGO COMPARTMENT Area Designation C1 C2 C1 + C2 = C Location (Sta. to Sta.) 541 to 636 636 to 786.5 541 to 786.5 H-Arm (Fus. Sta.) 588.5 721.9 663.7 Usable Volume (Cu/Ft) 151 195 346 Maximum Running Load (lb/in. of Fuselage Length) 32 32 32 Placard Capacity (lb) 3020 3900 6920 Combined Capacity (lb) Sta. 541 to 786.5 - - 6920 Maximum floor loading must not exceed 150 lb/ft2. Each of the above limitations is independent of the other. Do not exceed any limitation. NOTE: Combined capacity of Fus. Sta. 218 to 786.5 is not to exceed 12,150 pounds. The above section and compartment limitations are applicable only to the following Factory Serial Numbers - 48002-48022, 48024-48059, 48062, 48063, 48066-48074, 48079, 48080, 48083, 48086- 48099, 49100-49104, 49110-49127, 49138-49145, 49149-49190, 49192-49222, 49229, 49230, 49237, 49245, 49246, 49249-49251, 49253-49265, 49269-49273, 49277, 49278, 49286-49289, 49430-49435, 49531, 49549-49552, 49669, 49740, 49794, 49796, 49969-49975, 53053-53062, 53176-53181, 53203- 53206, 53216-53235. See Section XIV for limitations applicable to other DC-9-81 and -82 airplanes. A6WE 38 XII - Model DC-9-81 (Transport Aircraft) Approved August 25, 1980 (cont’d) AFT CARGO COMPARTMENT (WITHOUT AUXILIARY FUEL SYSTEM) Area Designation D1 D2 D1 + D2 = D Location (Sta. to Sta.) 1007 to 1155 1155 to 1320 1007 to 1320 H-Arm (Fus. Sta.) 1081 1245.4 1157.8 Usable Volume (Cu/Ft) 236 207 443 Maximum Running Load (lb/in. of Fuselage Length) 32 22.5 -- Placard Capacity (lb) 4720 3105 6645 Combined Capacity (lb) - - 6645 Maximum compartment floor loading must not exceed 150 lb/ft2. Each of the above section and compartment limitations is independent of the other. Do not exceed any limitation. NOTE: The above section and compartment limitations are applicable to all DC-9-81, -82, -83 Factory Serial Numbers, except as specified in certain other cargo compartment limitation sections. Fuel Capacity Three Tank System Total Capacity Total Usable H-Arm STA. Main Wing Tanks (2) 19,752 lb 19,638 lb 951.0 Center Wing Tank 21,867 lb 21,825 lb 884.8 Lines 120 lb 36 lb 1006.0 Engine 26 lb 7 lb 1322.0 Total 41,765 lb 41,506 lb 916.3 NOTE: H-ARM applies to usable fuel. 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). A6WE 39 XII - Model DC-9-81 (Transport Aircraft) Approved August 25, 1980 (cont’d) Oil Capacity Total Capacity Total volume Usable Per engine Usable weight H-Arm Sta. Engine Oil 6.92 gal 4 gal 31.0 lb 1300.0 CSD 1.25 gal 1.23 gal 9.4 lb 1319.0 APU 1.1 gal 1.1 gal 7.75 lb 1377.5 Oil Weight based upon 7.74 lb/gal. (See NOTE 1(c) for system oil) Serial Numbers Eligible 48002-48021, 48024-48046, 48049-48053, 48058, 48059, 48070-48074, 48092-48094, 48099, 49100, 49115, 49164, 49278-49283, 49356-49359, 49380-49382, 49420, 49422, 49436, 49438, 49461-49463, 49554, 49570-49572, 49603, 49613, 49820, 49821, 49907- 49914, 49998, 49999, 53000-53008, 53043, 53275, 53297-53302, 53314, 53315, 53347, 53365, 53366, 53368. See NOTE 11 for model conversion. XIII - Model DC-9-82 (Transport Aircraft) Approved July 29, 1981 (MD-82, See NOTE 14, regarding certification) Engines 2 Pratt and Whitney Turbofan JT8D-209, -217, -217A, -217C, or -219. (See NOTE 5 regarding intermixing of engines). Fuel Commercial aircraft turbine fuel conforming to P&W Specification 522 as revised (see NOTE 7). Oil P&W Turbojet Engine Service Bulletin Number 238 lists approved brand oils. Synthetic type oil conforming to P&W Specifications 521 as revised. Engine Limits See Section XII, Model DC-9-81 for JT8D-209 and JT8D-219 engines. P&W JT8D-217, -217A and -217C Power Rating Maximum Static Thrust at sea level Maximum Takeoff (5 min. flat-rated to 84°F)* 20,850 lb Normal Takeoff (5 min. flat-rated to 77°F)* 20,000 lb Maximum Takeoff, Engine Inoperative (10 min)** 20,850 lb NOTE: Maximum Takeoff Rating is the maximum thrust certified for takeoff operation. The Maximum Takeoff Rating is available through actuation of the fuel control Automatic Reserve Thrust System (ARTS) when the engine is operating at the Normal Takeoff Rating, or manually by throttle movement. Normal Takeoff Rating is the maximum thrust to be set for takeoff operation with the aircraft Automatic Reserve Thrust System (ARTS) operative. When set, this rating ensures that the Takeoff Rating will be achieved upon actuation of ARTS. A6WE 40 XIII - Model DC-9-82 (Transport Aircraft), Approved July 29, 1981 (cont’d) Engine Limits (cont’d) Exhaust Gas Temperature, Maximum Maximum Takeoff (2 min.)* 630°C (1166°F) Maximum Takeoff (5 min.)*, (10 min)** 625°C (1157°F) Normal Takeoff (2 min.)* 595°C (1103°F) Normal Takeoff (5 min.)* 590°C (1094°F) Maximum Continuous 580°C (1076°F) Starting - Ground *** 475°C ( 887°F) - In-Flight 625°C (1157°F) * The total time at both Takeoff Thrust Levels must not exceed 5 minutes. ** In the event of an engine failure during Takeoff or Go-Around, a total time of Ten (10) Minutes at Takeoff Thrust is required. *** The ground starting EGT limit for the JT8D-209/-217/-217A/-217C/-219 engines is increased to 500°C (932°F) when Appendix 11 of the applicable FAA Approved Airplane Flight Manual is utilized. Oil-Inlet Temperature-Maximum Continuous operation 135°C ( 275°F) Transient operation 165°C ( 329°F) Transient operation above 135° C (275°C) is limited to 15 minutes. Oil Pressure Limits 40 to 55 psi Fuel Pressure Limits Normal at engine pump inlet -15 psi Minimum at engine pump inlet -not less than 5 psi above true fuel vapor pressure Maximum at engine pump inlet -no greater than 50 psi with a vapor liquid ratio of zero Air Bleed Extraction % High Compressor Bleed 13th Stage Normal Maximum At 90% and below Max. Cont. Thrust 8.0 8.0 Above 90% Max. Cont. Thrust 3.5 5.5 % Low Compressor Bleed 8th Stage Normal Maximum At and below Max. Cont. Thrust 4.0 4.0 Above Max. Cont. Thrust 2.75 3.25 APU Limits See Section I, Models DC-9-11, -12, -13, -14 and -15 for GTCP85-98D, GTCP85-98W, GTCP85-98DC[A], GTCP85-98DC[B] and GTCP85-98DC[C]. See Section IX, Model DC-9-51, for GTCP85-98DCK. See Section XII, Model DC-9-81, for GTCP85-98DHF. Airspeed Limits (CAS) 147,000 lb 149,500 lb VMO (Maximum Operating - S.L.) 340K VMO (Maximum Operating - 27,240') 340K (M=0.84) VMO (Maximum Operating - 270.8K 27,240 to 37,000') (M=0.84) 304.0K VA (Maneuvering - S.L.) 268.5K 270.0K VA (Maneuvering - 29,000) 303.0K 304.1K VA (Maneuvering - 30,000') 298.4K 299.0K VA (Maneuvering - 37,000') 263.8K 262.1K (See AFM for variation in VA speeds vs. altitude) XIII - Model DC-9-82 (Transport Aircraft), Approved July 29, 1981 (cont’d) A6WE 41 Airspeed Limits (CAS) (cont’d) VFE (Flaps down 0.1° - 13°) 280K (M=0.57) (Flaps down 13.1° 20°) 240K (M=0.57) (Flaps down 20.1° - 25°) 220K (M=0.57) (Flaps down 25.1° - 30°) 200K (M=0.57) (Flaps down 31° - 40°) 195K (M=0.57) V (Slat Extended Takeoff, 17.8°) 280K (M=0.57) (Slat Extended Landing, 21°) 240K (M=0.57) (Autoslat Extension) 280K (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 (Landing light extension) 350K (M=0.84) C.G. Range Gross Weight LANDING GEAR LANDING GEAR EXTENDED (1) RETRACTED (1) Pounds Kilograms Forward Aft Forward Aft 70,000 31,751 884.3 938.5 881.1 938.5 118,000 53,524 -- 938.5 -- 938.5 126,000 57,153 884.3 935.3 881.1 935.3 130,000 58,967 -- 933.6 -- 933.6 140,000 63,503 890.1 929.5 -- 929.5 141,000 63,967 -- -- 888.4 -- 147,000 66,678 -- -- 888.4 927.6 148,000 67,132 890.6 927.1 149,500 67,812 891.3 926.6 888.4 926.6 150,500 68,266 891.9 926.3 NOTE: Inflight weight limited to 79,000 pounds (35,834 kg) minimum. (1) Straight line variation between weights shown. Gear retraction moment is -10,154 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 approved C.G. limits. Maximum weights Taxi and Ramp 150,000 lb (3) Start of Takeoff 149,500 lb (2) Zero Fuel 122,000 lb (1) Landing 130,000 lb (1) All weight in excess of 122,000 lb must be in usable fuel. After filling the main wing tanks, additional fuel may then be added to the center wing tank to attain the maximum design taxi weight. (2) Fuel jettisoning system not installed. (See exemption under Certification Basis). (3) 26 ply rating MLG tires required for all ramp weights over 141,000 lb Minimum Crew For all flights. Pilot and Copilot. Maximum Passengers SEE NOTES 6 and 8. XIII - Model DC-9-82 (Transport Aircraft), Approved July 29, 1981 (cont’d) A6WE 42 Maximum Baggage See Section XII, Model DC-9-81. Fuel Capacity See Section XII, Model DC-9-81 for DC-9-82s with three tank system. See Section XIV, Model DC-9-83, for DC-9-82s with 1130 Gallon Auxiliary Fuel Five Tank System. Oil Capacity: See Section XII, Model DC-9-81. Serial Numbers Eligible 48022, 48047, 48048, 48054-48057, 48062, 48063, 48066-48069, 48079, 48080, 48083, 48086-48091, 48095-48098, 49101-49104, 49110-49114, 49116-49127, 49138-49145, 49149-49163, 49165-49190, 49192-49222, 49229-49237, 49245-49251, 49253-49267, 49269-49273, 49277, 49286-49329, 49331-49343, 49350, 49355, 49363-49374, 49379, 49383-49387, 49391-49394, 49415-49419, 49421, 49423-49435, 49437, 49439-49441, 49443, 49444, 49450-49457, 49459, 49460, 49468-49494, 49501-49524, 49531, 49549- 49553, 49555, 49558-49566, 49569, 49580-49582, 49592-49601, 49604, 49615, 49634, 49635, 49647-49656, 49660, 49661, 49667, 49669, 49675-49684, 49701-49704, 49728, 49730-49740, 49794-49806, 49825, 49844, 49849-49853, 49877, 49889-49903, 49905, 49906, 49915-49925, 49931, 49932, 49969-49975, 49987-49996, 53017, 53025-53034, 53053-53062, 53064-53066, 53083-53092, 53117-53119, 53121, 53147, 53148-53160, 53162-53171, 53173-53181, 53203-53206, 53216-53235, 53244-53250, 53294-53296, 53468-53469, 53479, 53480, 53481, 53542, 53577, and 53581. See NOTE 11 for model conversion. XIV - Model DC-9-83 (Transport Aircraft) Approved: October 17, 1985 (MD-83, See NOTE 14, regarding certification) Engines 2 Pratt and Whitney Turbofan JT8D-209, -217, -217A, -217C, or -219 engines. (See NOTE 5 regarding intermixing of engines). Fuel Commercial aircraft turbine fuel conforming to P&W Specification 522 as revised (see NOTE 7). Oil P&W Turbojet Engine Service Bulletin Number 238 lists approved brand oils. Synthetic type oil conforming to P&W Specification 521 as revised. Engine Limits See Section XII, Model DC-9-81 for JT8D-209 and JT8D-219 engines. See Section XIII, Model DC-9-82 for JT8D-217, -217A and -217C engines. APU Limits See Section I, Models DC-9-11, -12, -13, -14 and -15 for GTCP85-98D, GTCP85-98W, GTCP85-98DC[A], GTCP85-98DC[B] and GTCP85-98DC[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 (Maximum Operating - S.L.) 340K (Maximum Operating - 27,240') 340K (M=0.84) (Maximum Operating 27,300 to 37,000') (M=0.84) VA (Maneuvering - S.L.) 280.6K (Maneuvering - 29,000') 306.2K (Maneuvering - 30,000') 301.1K (Maneuvering - 37,000') 263.5K (See AFM for variation in VA speeds vs. altitude) A6WE 43 XIV - Model DC-9-83 (Transport Aircraft) Approved: October 17, 1985 (cont’d) Airspeed Limits (CAS) (cont’d) VFE (Flaps down 0.1° - 13°) 280K (M=0.57) (Flaps down 13.1° - 20°) 240K (M=0.57) (Flaps down 20.1° - 25°) 220K (M=0.57) (Flaps down 25.1° - 30°) 205K (M=0.57) (Flaps down 31° - 40°) 200K (M=0.57) V (Slat Extended Takeoff, 17.8°) 280K (M=0.57) (Slat Extended Landing, 21°) 240K (M=0.57) (Autoslat Extension) 280K (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 (Landing light extension) 350K (M=0.84) K = KCAS C.G. Range Gross Weight LANDING GEAR LANDING GEAR EXTENDED (1) RETRACTED (1) Pounds Kilograms Forward Aft Forward Aft 80,000* 36,287 884.3 938.5 881.1 938.5 118,000 53,524 -- 938.5 -- 938.5 126,000 57,153 884.3 935.3 881.1 935.3 130,000 58,967 -- 933.6 -- 933.6 139,500 63,276 887.8 -- 884.4 -- 140,000 63,503 -- 929.5 -- 929.5 149,500 67,812 -- 926.4 884.3 926.6 150,500 68,266 -- 926.3 -- 926.3 156,000 70,760 887.4 -- 884.1 -- 156,000 70,760 887.9 -- 884.8 -- 160,000 72,575 -- 923.9 884.6 923.9 161,000 73,028 887.8 923.6 NOTE: *Inflight weight limited to 80,000 pounds (36,287 kg) minimum. (1) Straight line variation between weights shown. Gear retraction moment is -10,154 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 approved C.G. limits. Maximum weights Taxi and Ramp 150,500 lb (5) 161,000 lb (3)(4) Start of Takeoff 149,500 lb (5) 160,000 lb (2)(3)(4) Zero Fuel 122,000 lb (1) Landing 130,000 lb (5) (1) All weight in excess of 122,000 lb must be in usable fuel. After filling the main wing tanks, additional fuel may then be added to the center wing tank to attain the maximum design taxi weight. (2) Fuel jettisoning system not installed. (See exemption under Certification Basis). (3) 26 ply rating MLG tires required for all ramp weights over 141,000 lb (4) 28 ply rating MLG tires required for all ramp weights over 150,500 lb XIV - Model DC-9-83 (Transport Aircraft) Approved: October 17, 1985 (cont’d) A6WE 44 Maximum weights (cont’d) (5) Maximum weights with Sperry 4034241-906 Digital Flight Guidance Computer (DFGC) installed. Minimum Crew For all flights: Pilot and Copilot. Maximum Passengers See NOTES 6 and 8. Maximum Baggage: FORWARD CARGO COMPARTMENT Area Designation A B A + B Location (Sta. to Sta.) 218 to 370 370 to 522 218 to 522 H-Arm (Fus. Sta.) 294.9 459.0 368.7 Usable Volume (Cu/Ft) 239 195 434 Maximum Running Load (lb/in. of Fuselage Length) 24.0 24.0 24.0 Placard Capacity (lb) 3585 2925 6510 Combined Capacity (lb) Sta. 218 to 522 - - 6510 Maximum floor loading not to exceed 150 lb/ft2. Each of the above limitations is independent of the others. Do not exceed any limitation. NOTE: The combined capacity of Fus. Sta. 218 to 786.5 is not to exceed 10,305 pounds. The above section and compartment limitations are applicable to all DC-9-81, -82, -83 and MD-88 Factory Serial Numbers except as specified in certain other cargo compartment limitation sections. A6WE 45 XIV - Model DC-9-83 (Transport Aircraft) Approved: October 17, 1985 (cont’d) FORWARD CARGO COMPARTMENT (WITH 1960 GALLON AUXILIARY FUEL SYSTEM) Area Designation A B A + B Location (Sta. to Sta.) 218 to 370 370 TO 503 218 TO 503 H-Arm (Fus. Sta.) 294.9 449.1 357.8 Usable Volume (Cu/Ft) 239 165 404 Maximum Running Load (lb/in. of Fuselage Length) 24.0 24.0 24.0 Placard Capacity (lb) 3585 2460 6045 Combined Capacity (lb) Sta. 218 to 503 - - 6045 Maximum floor loading not to exceed 150 lb/ft2. Each of the above limitations is independent of the others. Do not exceed any limitation. NOTE: The combined capacity of Fus. Sta. 218 to 786.5 is not to exceed 9839 pounds. The above section and compartment limitations are applicable to all DC-9-81, -82, -83 and MD-88 Factory Serial Numbers except as specified in certain other cargo compartment limitation sections. A6WE 46 XIV - Model DC-9-83 (Transport Aircraft) Approved: October 17, 1985 (cont’d) MIDDLE CARGO COMPARTMENT (WITHOUT AUXILIARY FUEL SYSTEM) Area Designation C1 C2 C1 + C2 = C Location (Sta. to Sta.) 522 to 636 636 to 786.5 522 to 786.5 H-Arm (Fus. Sta.) 579.1 721.9 653.2 Usable Volume (Cu/Ft) 181 195 376 Maximum Running Load (lb/in. of Fuselage Length) 32 32 32 Placard Capacity (lb) 3620 3900 7520 Combined Capacity (lb) 522 to 786.5 - - 7520 Maximum floor loading must not exceed 150 lb/ft2 Each of the above limitations is independent of the other. Do not exceed any limitation. NOTE: Combined capacity of Fus. Sta. 218 to 786.5 is not to exceed 12,150 pounds. The above section and compartment limitations are applicable to all DC-9-81, -82, -83 and MD-88 Factory Serial Numbers except as specified in certain other cargo compartment limitation sections. A6WE 47 XIV - Model DC-9-83 (Transport Aircraft) Approved: October 17, 1985 (cont’d) MIDDLE CARGO COMPARTMENT (WITH 1130 GALLON AUXILIARY FUEL SYSTEM) Area Designation C1 C2 C1 + C2 = C Location (Sta. to Sta.) 600 to 636 636 to 786.5 600 to 786.5 H-Arm (Fus. Sta.) 618 721.9 698.1 Usable Volume (Cu/Ft) 58 195 253 Maximum Running Load (lb/in. of Fuselage Length) 32 32 32 Placard Capacity (lb) 1160 3900 5060 Combined Capacity (lb) 600 to 786.5 5060 Maximum compartment floor loading must not exceed 150 lb/ft2. Each of the above section and compartment limitations is independent of the other. Do not exceed any limitation. NOTE: Combined capacity of Fus. Sta. 218 to 786.5 is not to exceed 10,305 pounds. The above section and compartment limitations are applicable to all DC-9-81, -82, and -83 Factory Serial Numbers except as specified in certain other cargo compartment limitation sections. A6WE 48 XIV - Model DC-9-83 (Transport Aircraft) Approved: October 17, 1985 (cont’d) MIDDLE CARGO COMPARTMENT (WITH 1960 GALLON AUXILIARY FUEL SYSTEM) Area Designation C1 C2 C1 + C2 = C Location (Sta. to Sta.) 600 to 636 636 to 786.5 600 to 786.5 H-Arm (Fus. Sta.) 618 721.9 698.1 Usable Volume (Cu/Ft) 58 195 253 Maximum Running Load (lb/in. of Fuselage Length) 32 32 32 Placard Capacity (lb) 1160 3900 5060 Combined Capacity (lb) 600 to 786.5 5060 Maximum compartment floor loading must not exceed 150 lb/ft2. Each of the above section and compartment limitations is independent of the other. Do not exceed any limitation. NOTE: Combined capacity of Fus. Sta. 218 to 786.5 is not to exceed 9,841 pounds. The above section and compartment limitations are applicable to all DC-9-81, -82, or -83 Factory Serial Numbers except as specified in certain other cargo compartment limitation sections. A6WE 49 XIV - Model DC-9-83 (Transport Aircraft) Approved: October 17, 1985 (cont’d) AFT CARGO COMPARTMENT (WITH 1130 GALLON AUXILIARY FUEL SYSTEM) Area Designation D1 D2 D1 + D2 = D Location (Sta. to Sta.) 1081 to 1155 1155 to 1320 1081 to 1320 H-Arm (Fus. Sta.) 1118.0 1245.4 1198.6 Usable Volume (Cu/Ft) 119 207 326 Maximum Running Load (lb/in. of Fuselage Length) 32 22.5 -- Placard Capacity (lb) 2380 3105 4890 Combined Capacity (lb) -- -- 4890 Maximum compartment floor loading must not exceed 150 lb/ft2. Each of the above section and compartment limitations is independent of the other. Do not exceed any limitation. NOTE: The above section and compartment limitations are applicable to all DC-9-81, -82, or -83 Factory Serial Numbers except as specified in certain other cargo compartment limitation sections. A6WE 50 XIV - Model DC-9-83 (Transport Aircraft) Approved: October 17, 1985 (cont’d) AFT CARGO COMPARTMENT (WITH 1960 GALLON AUXILIARY FUEL SYSTEM) Area Designation D Location (Sta. to Sta.) 1152 to 1320 H-Arm (Fus. Sta.) 1242.3 Usable Volume (Cu/Ft) 213 Maximum Running Load (lb/in. of Fuselage Length) 22.5 Placard Capacity (lb) 3194 Maximum compartment floor loading must not exceed 150 lb/ft2. Each of the above section and compartment limitations is independent of the other. Do not exceed any limitation. NOTE: The above section and compartment limitations are applicable to all DC-9-81, -82, or -83 Factory Serial Numbers except as specified in certain other cargo compartment limitation sections. Fuel Capacity Three Tank System Total Capacity Total Usable H-Arm STA. Main Wing Tanks (2) 19,752 lb 19,638 lb 951.0 Center Wing Tank 21,867 lb 21,825 lb 884.8 Lines 120 lb 36 lb 1006.0 Engine 26 lb 7 lb 1322.0 Total 41,765 lb 41,506 lb 916.3 A6WE 51 XIV - Model DC-9-83 (Transport Aircraft) Approved: October 17, 1985 (cont’d) Fuel Capacity (cont’d) Five Tank System (1130 Gallons) Total Capacity Total Usable H-Arm STA. Main Wing Tanks (2) 19,752 lb 19,638 lb 951.0 Center Wing Tank 21,867 lb 21,825 lb 884.8 Fwd Fus Aux Tank 4,056 lb 4,019 lb 564.0 Aft Fus Aux Tank 4,056 lb 4,019 lb 1042.8 Lines 147 lb 56 lb 935.5 Engine 26 lb 7 lb 1322.0 Total 49,904 lb 49,564 lb 897.9 Five Tank System (196 Gallons) Total Capacity Total Usable H-Arm STA. Main Wing Tanks (2) 19,752 lb 19,638 lb 951.0 Center Wing Tank 21,843 lb 21,801 lb 884.8 Fwd Fus Aux Tank 5,566 lb 5,500 lb 551.3 Aft Fus Aux Tank 8,487 lb 8,399 lb 1080.0 Lines 175 lb 41 lb 1005.8 Engine 26 lb 7 lb 1322.0 Total 55,849 lb 55,386 lb 904.9 NOTE: H-ARM applies to usable fuel. 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 procedure). Oil Capacity: See Section XII, Oil Capacity Serial Nos. Eligible 49252, 49284, 49344-49349, 49351-49353, 49390, 49395-49402, 49442, 49448, 49449, 49458, 49525-49530, 49556, 49557, 49567, 49568, 49574-49579, 49602, 49617-49632, 49642, 49643, 49657-49659, 49662, 49663, 49668, 49672, 49707-49710, 49741, 49769, 49784-49793, 49807-49809, 49822-49824, 49826, 49845-49848, 49854-49857, 49904, 49930, 49933-49952, 49965, 49966, 49968, 49985, 49986, 53012-53016, 53018-53024, 53044-53046, 53050-53052, 53063, 53074-53079, 53093, 53120, 53122-53126, 53137- 53141, 53182-53192, 53198, 53199, 53251-53256, 53284-53293, 53377, 53435, 53436, 53448-53453, 53463-53467, 53470-53473, 53485-53488, 53520, 53561-53566, 53591-53599, 53602, 53603, and 53611-53634. See NOTE 11 for model conversion. XV - Model DC-9-87 (Transport Aircraft) Approved: October 21, 1987 (MD-87, See NOTE 14, regarding certification) Engines 2 Pratt and Whitney Turbofan JT8D-217A, -217C, and -219 engines. (See NOTE 5 regarding intermixing of engines). Engine Limits See Section XII, Model DC-9-81 for JT8D-219 engines. See Section XIII, Model DC-9-82 for JT8D-217A and -217C engines. XV - Model DC-9-87 (Transport Aircraft) Approved: October 21, 1987 (cont’d) A6WE 52 APU Limits See Section I, Models DC-9-11, -12, -13, -14, and -15 for GTCP85-98D, GTCP85-98W, GTCP85-98DC[A], GTCP85-98DC[B] and GTCP85-98DC[C]. See Section IX, Model DC-9-51 for GTCP85-98DCK. See Section XII, Model DC-9-81, for GTCP85-98DHF. Fuel Commercial aircraft turbine fuel conforming to P&W Specification 522 as revised. (See NOTE 7). Oil P&W Turbojet Engine Service Bulletin Number 238 lists approved brand oils. Synthetic type oil conforming to P&W Specification 521 as revised. Airspeed Limits (CAS) VMO (Maximum operating - S.L.) 340K VMO (Maximum Operating - 25,970') 340K (M=0.82) VMO (Maximum Operating - 25,970 to 37,000') (M=0.82) VA (Maneuvering - S.L.) 272.1K (Maneuvering - 29,000') 303.3K (Maneuvering - 30,000') 298.0K (Maneuvering - 37,000') 262.9K (See AFM for variation in VA speeds vs. altitude) VFE (Flaps down 0.1° - 13°) 280K (M=0.57) (Flaps down 13.1° - 20°) 240K (M=0.57) (Flaps down 20.1° - 25°) 220K (M=0.57) (Flaps down 25.1° - 30°) 200K (M=0.57) (Flaps down 31° - 40°) 195K (M=0.57) V (Slat Extended Takeoff, 17.8°) 280K (M=0.57) (Slat Extended Landing, 21°) 240K (M=0.57) (Autoslat Extension) 280K (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 (Landing light extension) 350K (M=0.84) K = CAS C.G. Range Gross Weight FUSELAGE STATIONS LANDING GEAR RETRACTED Pounds Kilograms Forward Aft *70,500 31,752 774.56 823.22 130,000 58,967 774.56 ---- 140,000 63,503 ---- ---- 141,000 63,957 775.19 823.22 149,500 67,812 ---- 815.77 150,500 68,266 775.67 815.14 * Inflight weight limited to 71,600 pounds (32,477 kg) minimum. NOTE: Straight line variation between weights shown. Gear retraction moment is -10,154 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 approved C.G. limits. XV - Model DC-9-87 (Transport Aircraft) Approved: October 21, 1987 (cont’d) A6WE 53 Maximum weights Taxi and Ramp 126,000 lb (4) 150,500 lb (3) Start of Takeoff 125,000 lb (2)(4) 149,500 lb (2)(3) Zero Fuel 112,000 lb (1)(4) 112,000 lb (1) Landing 120,000 lb (4) 130,000 lb (3) (1) All weight in excess of 112,000 lb must be in usable fuel. After filling the main wing tanks, additional fuel may then be added to the center wing tank to attain the maximum design taxi weight. (2) Fuel jettisoning system not installed. (See exemption under Certification Basis). (3) 26 ply rating MLG tires required for all ramp weights over 141,000 lb (4) Maximum for airplane serial numbers 49464 and 49465. Minimum Crew: For all flights: Pilot and Copilot. Maximum Passengers: See NOTES 6 and 8. Maximum Baggage: FWD CARGO COMPARTMENT Area Designation A B A + B Location (Sta. to Sta.) 219 to 313 313 to 408 219 to 408 H-Arm (Fus. Sta.) 266.8 368.6 309.5 Usable Volume (Cu/Ft) 146 106 252 Maximum Running Load (lb/in. of Fuselage Length) 24.0 24.0 24.0 Placard Capacity (lb) 2190 1590 3780 Combined Capacity (lb) Sta. 219 to 408 - - 3780 Maximum floor loading not to exceed 150 lb/ft2. Each of the above limitations is independent of the other. Do not exceed any limitation. NOTE: The combined capacity of Fus. Sta. 219 to 672.7 is not to exceed 9,420 pounds. XV - Model DC-9-87 (Transport Aircraft) Approved: October 21, 1987 (cont’d) A6WE 54 MIDDLE CARGO COMPARTMENT (WITHOUT AUXILIARY FUEL TANK) Area Designation C1 C2 C1 + C2 = C Location (Sta. to Sta.) 408 to 522 522 to 672.7 408 to 672.7 H-Arm (Fus. Sta.) 465.0 608.2 539.2 Usable Volume (Cu/Ft) 181 195 376 Maximum Running Load (lb/in. of Fuselage Length) 32 32 32 Placard Capacity (lb) 3620 3900 7520 Combined Capacity (lb) Sta. 408 to 672.7 - - 7520 Maximum floor loading must not exceed 150 lb/ft2. Each of the above limitations is independent of the other. Do not exceed any limitation. NOTE: Combined capacity of Fus. Sta. 219 to 672.7 is not to exceed 9,420 pounds. A6WE 55 XV - Model DC-9-87 (Transport Aircraft) Approved: October 21, 1987 (cont’d) MIDDLE CARGO COMPARTMENT (WITH 1130 AUXILIARY FUEL SYSTEM) Area Designation C1 C2 C1 + C2 = C Location (Sta. to Sta.) 486 to 522 522 to 672.7 408 to 672.7 H-Arm (Fus. Sta.) 504.0 608.2 584.3 Usable Volume (Cu/Ft) 58 195 253 Maximum Running Load (lb/in. of Fuselage Length) 32 32 32 Placard Capacity (lb) 1160 3900 5060 Combined Capacity (lb) Sta. 486 to 672.7 --- --- 5060 Maximum compartment floor loading must not exceed 150 lb/ft2. Each of the above section and compartment limitations is independent of the other. Do not exceed any limitation. NOTE: Combined capacity of Fus Sta 219 to 672.7 is not to exceed 9,420 pounds. A6WE 56 XV - Model DC-9-87 (Transport Aircraft) Approved: October 21, 1987 (cont’d) AFT CARGO COMPARTMENT (WITHOUT AUXILIARY FUEL SYSTEM) Area Designation D1 D2 D1 + D2 = D Location (Sta. to Sta.) 893 to 1030 1030 to 1111 893 to 1111 H-Arm (Fus. Sta.) 960.4 1068.8 992.2 Usable Volume (Cu/Ft) 219 91 310 Maximum Running Load (lb/in. of Fuselage Length) * 22.5 --- Placard Capacity (lb) 4111 1380 4650 Combined Capacity (lb) Sta. 893 to 1111 --- --- 4650 Maximum compartment floor loading must not exceed 150 lb/ft2. Each of the above section and compartment limitations is independent of the other. Do not exceed any limitation. *Sta. 893 to Sta. 1002: 32 lb/in. *Sta. 1002 to Sta. 1030: 22.5 lb/in. A6WE 57 XV - Model DC-9-87 (Transport Aircraft) Approved: October 21, 1987 (cont’d) AFT CARGO COMPARTMENT (WITH 780 GALLON AUXILIARY FUEL TANK) Area Designation D1 D2 D1 + D2 = D Location (Sta. to Sta.) 989 to 1030 1030 to 1111 989 to 1111 H-Arm (Fus. Sta.) 1008.9 1068.8 1044.3 Usable Volume (Cu/Ft) 63 91 154 Maximum Running Load (lb/in. of Fuselage Length) * 22.5 --- Placard Capacity (lb) 1029 1380 2310 Combined Capacity (lb) Sta. 893 to 1111 --- --- 2310 Maximum compartment floor loading must not exceed 150 lb/ft2. Each of the above limitations is independent of the other. Do not exceed any limitation. *Sta. 989 - Sta. 1002: 32 lb/in. *Sta. 1002 - Sta. 1030: 22.5 lb/in. A6WE 58 XV - Model DC-9-87 (Transport Aircraft) Approved: October 21, 1987 (cont’d) AFT CARGO COMPARTMENT (WITH 1130 GALLON AUXILIARY FUEL SYSTEM) Area Designation D1 D2 D1 + D2 = D Location (Sta. to Sta.) 967 to 1030 1030 to 1111 967 to 1111 H-Arm (Fus. Sta.) 997.6 1068.8 1031.7 Usable Volume (Cu/Ft) 99 91 190 Maximum Running Load (lb/in. of Fuselage Length) * 22.5 --- Placard Capacity (lb) 1760 1380 2850 Combined Capacity (lb) --- --- 2850 Maximum compartment floor loading must not exceed 150 lb/ft2. Each of the above section and compartment limitations is independent of the other. Do not exceed any limitation. *Sta. 967 to Sta. 1002: 32 lb/in. *Sta. 1002 to Sta. 1030: 22.5 lb/in. Fuel Capacity Three Tank System Total Capacity Total Usable H-Arm STA. Main Wing Tanks (2) 19,752 lb 19,638 lb 837.0 Center Wing Tank 21,867 lb 21,825 lb 770.8 Lines 111 lb 28 lb 943.9 Engine 26 lb 7 lb 1113.0 Total 41,756 lb 41,498 lb 802.3 A6WE 59 XV - Model DC-9-87 (Transport Aircraft) Approved: October 21, 1987 (cont’d) Fuel Capacity (cont’d) Four Tank System Total Capacity Total Usable H-Arm STA. Main Wing Tanks (2) 19,752 lb 19,638 lb 837.0 Center Wing Tank 21,867 lb 21,825 lb 770.8 Aft Fus Aux Tank 5,581 lb 5,512 lb 940.9 Lines 125 lb 34 lb 927.0 Engine 26 lb 7 lb 1113.0 Total 47,351 lb 47,016 lb 818.6 Five Tank System Total Capacity Total Usable H-Arm STA. Main Wing Tanks (2) 19,752 lb 19,638 lb 837.0 Center Wing Tank 21,867 lb 21,825 lb 770.8 Fwd Fus Aux Tank 4,056 lb 4,019 lb 449.0 Aft Fus Aux Tank 4,056 lb 4,019 lb 930.3 Lines 138 lb 47 lb 704.0 Engine 26 lb 7 lb 1113.0 Total 49,895 lb 49,555 lb 783.9 Oil Capacity Total Capacity Total volume Usable Per engine Usable weight H-Arm STA. Engine oil 6.92 gal 4.2 gal 31.0 lb 1091.0 CSD 1.25 gal 1.23 gal 9.4 lb 1110.0 APU 1.1 gal 1.1 gal 7.75 lb 1168.5 Oil weight based upon 7.74 lb/gal. (See NOTE 1(c) for system oil) Serial Nos. Eligible 49389, 49403-49405, 49411-49414, 49464-49467, 49585-49587, 49605-49612, 49614, 49641, 49670, 49671, 49673, 49706, 49724-49727, 49767, 49768, 49777-49780, 49827-49843, 49888, 49997, 53009-53011, 53039-53042, 53207-53213, 53336, 53337, 53340, 53348, 53351, 53416-53423, 53446, and 53447. XVI - Model MD-88 (Transport Aircraft) Approved December 8, 1987 Engines 2 Pratt and Whitney Turbofan JT8D-217A, -217C and -219 engines. (See NOTE 5 regarding intermixing of engines). Engine Limits See Section XII, Model DC-9-81 for JT8D-219 engines. See Section XIII, Model DC-9-82 for JT8D-217A and -217C engines. APU Limits See Section I, Models DC-9-11, -12, -13, -14 and -15 for GTCP85-98D, GTCP85-98W, GTCP85-98DC[A], GTCP85-98DC[B] and GTCP85-98DC[C]. See Section IX, Model DC-9-51 for GTCP85-98DCK. See Section XII, Model DC-9-81 (MD-81) for GTCP85-98DHF. Fuel Commercial aircraft turbine fuel conforming to P&W Specification 522 as revised (See NOTE 7). XVI - Model MD-88 (Transport Aircraft) Approved December 8, 1987 (cont’d) A6WE 60 Oil P&W Turbojet Engine Service Bulletin 238 lists approved brand oils. Synthetic type oil conforming to P&WA Specifications 521, as revised. Airspeed Limits (CAS) 149,500 lb 160,000 lb VMO (Maximum Operating - S.L.) 340K 340K (Maximum Operating - 27,240 ') 340K (M=0.84) 340K (M=0.84) (Maximum Operating - 27,240 to 37,000 ') (M=0.84) (M=0.84) VA (Maneuvering - S.L.) 270.0K 280.6K (Maneuvering - 29,000 ') 340.1K 306.2K (Maneuvering - 30,000 ') 299.0K 301.1K (Maneuvering - 37,000 ') 262.1K 263.5K (See AFM for variation in VA speeds versus altitude) VFE (Flaps down 0.1° - 13°) 280K (M=0.57) 280K (M=0.57) (Flaps down 13.1° - 20°) 240K (M=0.57) 240K (M=0.57) (Flaps down 20.1° - 25°) 220K (M=0.57) 220K (M=0.57) (Flaps down 25.1° - 30°) 200K (M=0.57) 205K (M=0.57) (Flaps down 31° - 40°) 195K (M=0.57) 200K (M=0.57) V (Slat Extended Takeoff, 17.8°) 280K (M=0.57) 280K (M=0.57) (Slat Extended Landing, 21°) 240K (M=0.57) 240K (M=0.57) (Autoslat Extension) 280K (M=0.57) 280K (M=0.57) VLO (Landing Gear operation) (Gear retraction) 250K (M=0.70) 250K (M=0.70) (Gear extension) 300K (M=0.70) 300K (M=0.70) VLE (Landing gear extended 300K (M=0.70) 300K (M=0.70) V (Landing light extension) 350K (M=0.84) 350K (M=0.84) K=KCAS C.G. Range Gross Weight LANDING GEAR LANDING GEAR EXTENDED (1) RETRACTED (1) Pounds Kilograms Forward Aft Forward Aft 70,000 31,751 884.3 938.5 881.1 938.5 80,000* 36,287 884.3 938.5 881.1 938.5 117,000 53,524 -- 938.5 -- 938.5 126,000 57,153 884.3 935.3 881.1 935.3 130,000 58,967 -- 933.6 -- 933.6 139,500 63,276 887.8 -- 884.4 -- 140,000 63,503 -- 929.5 -- 929.5 141,000 63,957 -- 929.5 -- 929.5 148,000 67,132 890.6 -- -- -- 149,500 67,812 -- 926.4 884.3 926.6 150,500 68,266 -- 926.3 -- 926.3 156,000 70,760 887.4 -- 884.1 -- 156,000 70,760 887.9 -- 884.8 -- 160,000 72,575 -- 923.9 884.6 923.9 161,000 73,028 887.8 923.6 -- -- NOTE: *Inflight weight limited to 80,000 pounds (36,287 kg) minimum. A6WE 61 XVI - Model MD-88 (Transport Aircraft) Approved December 8, 1987 (cont’d) C.G. Range: (cont’d) (1) Straight line variation between weights shown. Gear retraction moment is -10,154 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 approved C.G. limits. Maximum weights Taxi and Ramp 161,000 lb (3)(4) Start of Takeoff 160,000 lb (2)(3)(4) Zero Fuel 122,000 lb (1) Landing 150,000 lb (3) (1) All weight in excess of 122,000 lb must be in usable fuel. After filling the main wing tanks, additional fuel may then be added to the center wing tank to attain the maximum design taxi weight. (2) Fuel jettisoning system not installed. (See exemption under Certification Basis). (3) 26 ply rating MLG tires required for all ramp weights over 141,000 lb (4) 28 ply rating MLG tires required for all ramp weights over 150,500 lb Minimum Crew For all flights: Pilot and Copilot. Maximum Passengers See NOTES 6 and 8. Maximum Baggage See Section XIV, Model DC-9-83. Fuel Capacity See Section XIV, Model DC-9-83. Oil Capacity See Section XII, Model DC-9-81. Serial Numbers Eligible 49532-49546, 49573, 49583, 49584, 49591, 49644-49646, 49705, 49711-49723, 49759- 49766, 49810-49819, 49878-49887, 49926-49929, 49956-49959, 49967, 49976-49984, 49997, 53047-53049, 53115, 53116, 53161, 53172-53175, 53193-53197, 53214, 53215, 53241-53243, 53257-53259, 53266-53268, 53273, 53274, 53303-53310, 53311-53313, 53338, 53339, 53341-53346, 53351, 53362-53364, 53370-53372, 53378-53380, 53409, 53410, 53415-53423, 53446, 53447, 53546, 53547-53549, and 53550. XVII - Model MD-90-30 (Transport Aircraft) Approved November 4, 1994 (Note: For Model MD-90-30 equipped with Enhanced Flight Deck configuration, approved on March 3, 1998, refer to additional certification basis.) Engines 2 International Aero Engines (IAE) V2525-D5 or V2528-D5 engines. (Intermixing of engines not permitted. See NOTE 5). Engine Limits Thrust Ratings V2525-D5 V2528-D5 Takeoff (5 min.) 25,000 lb 28,000 lb (static thrust at sea level, flat-rated to 86°F) Takeoff, Engine Inoperative (10 min.) 25,000 lb 28,000 lb (static thrust at sea level, flat-rated to 86°F) (Takeoff Rating is the maximum thrust certified for takeoff operation.) XVII - Model MD-90-30 (Transport Aircraft) Approved November 4, 1994 (cont’d) A6WE 62 Engine Limits (cont’d) V2525-D5 V2528-D5 Maximum Continuous 23,900 lb 25,660 lb (static thrust at sea level) Maximum Permissible Engine Operating Speeds (All Models) N1 (Low Pressure Rotor) Takeoff 5,650 rpm (100%) 5,650 rpm (100%) N2 (High Pressure Rotor) Takeoff 14,950 rpm (100%) 14,950 rpm (100%) Maximum Permissible Indicated Engine Exhaust Gas Temperatures * Takeoff (5 min.) 620°C 635°C Maximum Continuous 610°C 610°C Starting on Ground 635°C 635°C in Flight 635°C 635°C * See NOTE 19 of Engine TCDS E40NE. Oil Outlet Temperature (All Models) Continuous Operation 155°C/311°F Transient Operation (15 min.) 165°C/329°F Maximum Oil Pressure Limits 60 psig Minimum Fuel Pressure At the inlet to the engine system pump, not less than 5 psig above the true vapor pressure of the fuel and not greater than 70 psig with a vapor/liquid ratio of zero. Maximum permissible air bleed extraction is as follows: (All Models) Max Bleed Limit ** 7th Stage Bleed % of Inlet Core Flow (WA26) At or below 90% corrected high rotor speed 8.2% From 90% to 97% corrected high rotor speed Linear variation from 8.2% to 6.0% At or above 97% corrected high rotor speed 6.0% 10th Stage Bleed * At or below 61% corrected high rotor speed 13.7% From 61% to 78% corrected high rotor speed Linear variation from 13.7% to 12% From 78% to 97% corrected high rotor speed Linear variation from 12.0% to 6.0% At or above 97% corrected high rotor speed 6.0% * Below 24,000 ft: - at ambient temperatures above 40°F, no 10th stage bleed is allowed at max. continuous rating and above. - at 40°F ambient temperatures and below, a maximum of 2% 10th stage bleed is allowed at takeoff rating and 4% 10th stage bleed at max. continuous rating. ** Simultaneous use of 7th and 10th stage bleed due to a malfunction is allowed only until the next landing. Airspeed Limits (KCAS) VMO (Maximum Operating - S.L.) 340K VMO (Maximum Operating - 27,240') 340K (M=0.84) VMO (Maximum Operating - 27,240' to 37,000') (M=0.84) VA (Maneuvering - S.L.) 273K VA (Maneuvering - 29,000') 296K XVII - Model MD-90-30 (Transport Aircraft) Approved November 4, 1994 (cont’d) A6WE 63 Airspeed Limits: (cont’d) VA (Maneuvering - 30,000') 290K (Maneuvering - 37,000') 256K (See AFM for variation in VA with altitude) VFE (Flaps down 0.1° - 13°) 280K (M=0.57) (Flaps down 13.1° - 20°) 240K (M=0.57) (Flaps down 20.1° - 25°) 220K (M=0.57) (Flaps down 25.1° - 30°) 205K (M=0.57) (Flaps down 31° - 40°) 200K (M=0.57) V (Slat Extended Takeoff, 17.8°) 280K (M=0.57) (Slat Extended Landing, 21°) 240K (M=0.57) (Autoslat Extension) 280K (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 (Landing light extension) 350K (M=0.84) C.G. Range See FAA Approved Airplane Flight Manual Maximum weights Taxi and Ramp 161,000 lb 166,500 lb 168,500 lb Start of Takeoff 160,500 lb 166,000 lb (2) 168,000 lb (2) Zero Fuel 132,000 lb (1) 132,000 lb (1) 132,000 lb (1) Landing 142,000 lb 142,000 lb 142,000 lb (1) All weight in excess of 132,000 lb must be in usable fuel. After filling the main wing tanks, additional fuel may then be added to the center wing tank to attain the maximum design taxi weight. (2) 28 ply tires are required for all ramp weights over 166,000 lb Minimum Crew For all flights: Pilot and copilot. Maximum Passengers See NOTES 6 and 8. Maximum Baggage See Weight and Balance Manual Report No. MDC-91K0981. Fuel Capacity Three Tank System Total Capacity Total Usable H-Arm STA. Main Wing Tanks (2) 19,964 lb 19,837 lb 1008.8 Center Wing Tank 21,656 lb 21,612 lb 941.9 Lines 124 lb 36 lb 1063.0 Engine 28 lb 7 lb 1398.0 Total 41,772 lb 41,492 lb 974.1 A6WE 64 XVII - Model MD-90-30 (Transport Aircraft) Approved November 4, 1994 (cont’d) Fuel Capacity: (cont’d) Four Tank System Total Capacity Total Usable H-Arm STA. Main Wing Tanks (2) 19,964 lb 19,837 lb 1008.8 Center Wing Tank 21,656 lb 21,612 lb 941.9 Fwd Aux Tank 4,056 lb 4,019 lb 564.0 Lines 157 lb 36 lb 1063.0 Engine 28 lb 7 lb 1398.0 Total 45,861 lb 45,511 lb 937.9 NOTE: H-ARM applies to usable fuel. 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 TOTAL CAPACITY TOTAL VOLUME USABLE PER ENGINE USABLE WEIGHT H-ARM STA. ENGINE OIL (2) 11.5 gal 6.0 gal 44.4 lb 1365.0 VSCF (2) 0.7 gal 0.5 gal 3.7 lb 1360.3 APU (1) 1.6 gal 0.85 gal 6.3 lb 1422.5 Oil Weight based upon 7.4 lb/gal. (See NOTE 1(c) for system oil) Serial Numbers Eligible Maximum Takeoff Weight of 160,500 lb 53352-53355, 53381-53392*, 53489, 53490, 60001, and 60002. Maximum Takeoff Weight of 166,000 lb 53356-53359, 53360, 53361, 53393-53396, 53457-53462, 53491-53493, 53523-53526, 53527, 53528, 53534-53538, 53539, 53543, 53544, 53551-53554, 53555-53557, 53567, 53568-53570, 53571, 53573, 53574, and 53582-53584. Maximum Takeoff Weight of 168,000 lb 53494-53519, 53529, 53530, 53531, 53532, 53533, 53558, 53559, 53560, 53572, 53576, 53578, 53579, 53580, 53585, 53586, 53587, 53588, 53589, 53590, and 53601. (*) Serial numbers within the range of 53381 thru 53392 are eligible to operate at maximum takeoff weight of 166,000 lb provided Boeing Service Bulletin MD90-57-028 is installed. APU Limits AlliedSignal Engines 131-9 [D] Rotor Speeds, Maximum Allowable (108%) 52,704 RPM Maximum for normal operation (104%) 50,752 RPM Minimum for normal operation (96%) 46,848 RPM Exhaust Gas Temperatures Maximum allowable for all operations 106% on EGT gauge* including starting and transients * 1235oF for standard day at sea level, ECS and MES mode. Maximum rated for continuous operation 100% on EGT gauge** ** 1052°F for standard day at sea level, ECS mode. A6WE 65 XVII - Model MD-90-30 (Transport Aircraft) Approved November 4, 1994 (cont’d) APU Limits (cont’d) Fuel Pressure Limits, Minimum of 4 psig. Oil Capacity, 6.5 qt total, 3.4 qt usable. Oil Pressure, Normal operation 67.5 + 7.5 psi Low Oil pressure (Master Caution) 35.0 + 5.0 psi Oil Temperature, Maximum 325°F APU Envelope, Start up to 35,000 feet Operate up to 37,000 feet APU Maximum Continuous Electrical Loads must not exceed: Ground 1.00 Indicated Inflight 0.6 Fuel Commercial aircraft turbine fuel conforming to specifications listed in NOTE 7. Oil Oil to be used in the IAE V2525-D5 and V2528-D5 engines must conform to the following specification: MIL-L-23699. Oil brands qualified for use include: Mobil Jet II and Exxon 2380. XVIII - Model 717-200 (Transport Aircraft) Approved September 1, 1999 (See NOTE 22, regarding certification, NOTE 29, regarding flammability) Engines 2 Rolls-Royce Deutschland Ltd & Co KG BR700-715A1-30 or BR700-715C1-30 engines. (See Notes 5, 25) Engine Limits Thrust Ratings BR700-715A1-30 BR700-715C1-30 Takeoff (5 min.) 18,920 lb 21,430 lb (static thrust at sea level, flat-rated to 86°F) Takeoff, Engine Inoperative (10 min.) 18,920 lb 21,430 lb (static thrust at sea level, flat-rated to 86°F) (Takeoff Rating is the maximum thrust certified for takeoff operation.) Maximum Continuous 18,700 lb 20,420 lb (static thrust at sea level) Maximum Permissible Engine Operating Speeds N1 (Low Pressure Rotor) Takeoff 6,096 rpm (100.0%) N2 (High Pressure Rotor) Takeoff 16,661 rpm (100.0%) Maximum Permissible Indicated Engine Exhaust Gas Temperatures *Takeoff (5 min.) 900°C Maximum Continuous 850°C Starting on Ground 700°C Starting in Flight 850°C *Takeoff rating may be used for 10 min. if an engine becomes inoperative. Oil Outlet Temperature: Continuous Operation 160°C/320°F Transient Operation (15 min.) 160°C/320°F Maximum Oil Pressure Limits 25 psig for N2 less than 72.3% 35 psig for N2 more than 90% XVIII - Model 717-200 (Transport Aircraft) Approved September 1, 1999 (cont’d) A6WE 66 Airspeed Limits (KCAS) VMO (Maximum Operating - S.L.) 340K VMO (Maximum Operating - 26,000') 340K (M=0.82) VMO (Maximum Operating -26,000 to 37,000') (M=0.82) VA (Maneuvering - S.L.) 263K (Maneuvering - 26,000') 297K (Maneuvering - 31,000') 279K (Maneuvering - 35,000') 259K (See AFM for variation in VA with altitude) VFE (Flaps down 0.1° - 10°) 280K (M=0.57) (Flaps down 10.1° - 20°) 240K (M=0.57) (Flaps down 20.1° - 25°) 220K (M=0.57) (Flaps down 25.1° - 40°) 200K (M=0.57) V (Slat Operation or Extended) 280K (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 (Landing light extension) 340K (M=0.82) C.G. Range: See FAA Approved Airplane Flight Manual Maximum weights Taxi and Ramp 122,000 lb/55,338 kg Start of Takeoff 121,000 lb/54,885 kg Zero Fuel 100,500 lb/45,586 kg (1) Landing 110,000 lb/49,895 kg (1) All weight in excess of 100,500 lb (45,586 kg) must be in usable fuel. After filling the main wing tanks, additional fuel may then be added to the center wing tank to attain the maximum design taxi weight. Minimum Crew For all flights: Pilot and copilot. Maximum Passengers See NOTE 6. Maximum Baggage See Weight and Balance Manual Report No. MDC 97K9261 Fuel Capacity Three Tank System Total Capacity Total Usable H-Arm STA. Main Wing Tanks (2) 19,687 lb 19,638 lb 762.3 Center Wing Tank 6,526 lb 6,440 lb 705.4 Lines 108 lb 36 lb 870.7 Engine 25 lb 7 lb 1036.0 Total 26,346 lb 26,121 lb 748.5 NOTE: H-ARM applies to usable fuel. 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) A6WE 67 XVIII - Model 717-200 (Transport Aircraft) Approved September 1, 1999 (cont’d) Oil Capacity TOTAL CAPACITY TOTAL VOLUME USABLE PER ENGINE USABLE WEIGHT H-ARM STA. Engine Oil Tank Only (2) 2.97 US gal 1.64 US gal 12.7 lb 1034.0 Total Engine Oil (2) 5.30 US gal 1.64 US gal 12.7 lb 1034.0 IDG Sump Only (2) 0.44 US gal 0. 44 US gal 3.3 lb 1033.0 APU (1) 0.8 US gal 0.25 US gal 1.8 lb 1080.0 Oil Weight based upon 7.74 lb/gal. (See NOTE 1(c) for system oil) Serial Numbers Eligible 55001, 55002, 55003-55042, 55043-55048, 55049-55051, 55052, 55053-55057, 55058, 55059-55068, 55069-55117, 55118, 55121-55125, 55126-55129, 55130-55132, 55134-55140, 55141-55150, 55151-55155, 55166-55185, 55186-55187, 55190-55194, 55195-55196 APU Limits Auxiliary Power International Corporation (APIC) APS 2100 Rotor Speeds, Maximum Allowable (105%) 47,486 RPM Maximum for normal operation (103%) 46,582 RPM Minimum for normal operation (97%) 43,868 RPM Exhaust Gas Temperatures Maximum allowable for all operations 100% on EGT display including starting and transients Maximum rated for continuous operation 100% on EGT display* * 1345°F for standard day at sea level Fuel Pressure Limits Minimum of 5 psig. Oil Capacity 3.3 qt total, 1.0 qt usable. Oil Pressure, Normal operation 42.5 psig +/- 2.5 psi Low Oil pressure (Master Caution) 20 psig +/- 2.0 psi Oil Temperature, Maximum 275°F APU Envelope: Start (up to 37,000 feet) Operate (up to 37,000 feet) APU Maximum Continuous Electrical Loads must not exceed: Ground (60 KVA) 1.0 Indicated Inflight (40 KVA) 1.0 indicated Fuel Commercial aircraft turbine fuel conforming to specifications listed in NOTE 7. Oil For 717-200 approved engine oils, see latest revision of the BR715 Engine Operating Instructions, OI-715-3BR, as indicated by FAA Type Certificate Data Sheet E00061EN. Data Pertinent to All Models Maximum Operating Altitude 35,000 ft. (DC-9-11 thru DC-9-51) 37,000 ft. (DC-9-81, -82, -83, -87, MD-88, MD-90-30 and 717-200) A6WE 68 Data Pertinent to All Models (cont’d) Operating Limitations See NOTES 2, 3, and 4. Other Operating Limitations See FAA Approved Airplane Flight Manual. Datum 7 inches forward of nose (Sta. 0). MAC 141.5 in. (L.E. of MAC at Sta. 549.1). Models DC-9-11, -12, -13, -14, -15, -15F 147.4 in. (L.E. of MAC at Sta. 544.5). Model DC-9-21 147.4 in. (L.E. of MAC at Sta. 658.5). Models DC-9-31, -32, -32F, -33F 147.4 in. (L.E. of MAC at Sta. 696.5). Model DC-9-41 147.4 in. (L.E. of MAC at Sta. 753.4). Model DC-9-51 147.4 in. (L.E. of MAC at Sta. 658.4). Models DC-9-34, -34F 158.5 in. (L.E. of MAC at Sta. 885.5). Models DC-9-81, -82, -83 and MD-88 158.5 in. (L.E. of MAC at Sta. 771.5). Model DC-9-87 158.5 in. (L.E. of MAC at Sta. 942.5). Model MD-90-30 147.4 in. (L.E. of MAC at Sta. 715.5). Model 717-200 Leveling Means One of two systems in each airplane: (a) Spirit levels and leveling pads at Sta. 58.7 or (b) Plumb bob and grid plate at Sta. 69.5 Control Surface Movements 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: Model DC-9 Douglas Dwg. 7910641, Model MD-90 Douglas Dwg. 7940643 or Model 717-200 Douglas Dwg. 7940906 "Inspection Procedure - Surface Throws, Flight Control" new or later change. Service Life Limits See NOTE 3 Certification Basis: Models DC-9-11, -12, -13, -14, -15, -15F, -21, -31, -32, -32F -33F, -34,-34F, -41, -51 CAR 4b dated December 31, 1953, Amendments 4b-1 thru 4b-16, the Special Conditions contained in Attachment "A" of FAA letter to Douglas dated October 20, 1965, the provisions of SR -422B and the following exemptions: 415D - CAR 4b.437, "Fuel Jettisoning System" (See wts. DC-9-10, -30, -40 and -50 Series Airplanes). 424 - CAR 4b.362, "Emergency Exit/Passenger Ratio" (DC-9-11, -12, -13, -14, -15, and 15F that incorporate one Type I and one Type III exit per side and tail cone exit). NOTE: CAR 4b with Amendments 4b-1 thru 4b-16 is considered equivalent to FAR Part 25 (New) effective February 1, 1965. All aircraft not flown before December 1, 1973 must comply with FAR 36 dated December 1, 1969, and Amendments 36-1 and 36-2. Compliance with the following optional requirements has been established: A6WE 69 Data Pertinent to All Models (cont’d) Certification Basis (cont’d) Ditching Provision 4b.361, including 4b.362(d) and 4b.742(e) and excluding 4b.645 and 4b.646. When the operating rules require emergency ditching equipment, compliance with 4b.645 and 4b.646 must be demonstrated. In such cases when the manufacturer has complied with part or all of the provisions of 4b.645 and 4b.646, the items of equipment will be called out on the pertinent interior arrangement drawing, entitled "FAA Approval Drawing," or "FAA Interior Schematic." Ice Protection Provisions 4b.640. Based on 14 CFR § 21.101(g) for changes to type certificates (TC), 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). Models DC-9-81 and -82 FAR 25, effective February 1, 1965, as amended by amendments 25-1 through 25-40, effective May 2, 1977, except for the following sections which are limited to showing compliance with the amendments indicated: Section Amendment Section Amendment Section Amendment 25.21 25-7 25.701 * 25.979 * 25.251(a) 25-23 25.721 25-15 25.1001 * 25.251(b) 25-23 25.251(c) 25-23 25.787 * 25.251(e) 25-23 25.803(c) 25-46 25.255 25-42 25.803(e) 25-15 25.395 * 25.807 25-15 25.1093 25-36 25.571 25-10 25.809 25-15 25.1203 * 25.607 * 25.811 25-15 25.1305 25-11 25.631 (N/A) 25.812 25-28 25.1309 *, ** 25.671 * 25.863 * 25.1333* * 25.1351(d) ** 25.672 (N/A) 25.933 * 25.1401 25-27 25.695 * 25.1435 * 25.697 * 25.951 * 25.699 * 25.955 * Based on 14 CFR § 21.101(g) for changes to type certificates (TC), 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). A6WE 70 Data Pertinent to All Models (cont’d) Certification Basis (cont’d) Models DC-9-83, -87 and MD-88 All provisions, as applicable, including Special Conditions and Exemptions mandated for the DC -9-80 series airplanes are applicable in total for the MD-88 airplane. Part 25, effective February 1, 1965, as amended by Amendments 25-1 through 25-40, effective May 2, 1977, except showing compliance with the following sections is limited to the amendments as shown in the following table: Models DC-9-83, -87 and MD-88 (cont’d) Section Amendment Section Amendment Section Amendment 25.21 25-7 25.701 * 25.955 * 25.251(d) (N/A) 25.721 25-15 25.979 * 25.255 25-42 25.787 * 25.1001 * 25.395 * 25.803(c)(d) 25-46 25.1093 25-36 25.571 25-10 25.803(e) 25-15 25.1203 * 25.607 * 25.807 25-15 25.1305 25-11 25.631 (N/A) 25.809 25-15 25.1309 *, ** 25.671 * 25.811 25-15 25.1333 * 25.672 (N/A) 25.812 25-28 25.1351(d) ** 25.695 * 25.863 * 25.1401 25-27 25.697 * 25.933 * 25.1435 * 25.699 * 25.951 * Based on 14 CFR § 21.101(g) for changes to type certificates (TC), 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). Applies to DC-9-81, -82, -83, -87, MD-88 and MD-90-30 (N/A) indicates sections added to FAR 25 by later amendments for which compliance is not applicable. (*) as Adopted at original issuance of FAR 25. (**) Thru Amendment 25-41 for operation without normal electrical power, autoland system and post stall recovery (stick pusher) system. Special Condition, No. 25-88-WE-25, "Automatic Takeoff Thrust Control System (ATTCS)", issued March 9, 1979, for the Model DC-9-80/MD-80 series airplanes. Special Conditions, No. 25-95-WE-27, "Hydraulic System Failure", "In Flight Thrust Reversal", and "Environmental Flight Testing", issued April 3, 1980, for the Model DC-9-80/MD-80 series airplanes. Special Condition No. 25-ANM-15, "Lightning Protection for new Electronic Systems," issued October 19, 1987, for the Model DC-9-80/MD-80 series airplanes. Exemption No. 415D, FAR 25.1001, "Fuel Jettisoning System", issued June 23, 1980, for the Model DC-9-80/MD-80 series airplanes, (See Maximum Weights DC-9-81, -82, -83, -87 and MD-88). Applicable noise standards per FAR 36, effective December 1, 1969, as amended by Amendments 36 - 1 through 36-11 for the DC-9-81, and through 36-12 for the -82, -83, -87 and MD-88, and through 36- 20 for the MD-90-30. This includes retroactive noise requirements and requirements for an acoustical change in accordance with FAR 36-2 and 36-7 respectively. A6WE 71 Data Pertinent to All Models (cont’d) Certification Basis: (cont’d) Applies to DC-9-81, -82, -83, -87, MD-88 and MD-90-30 (cont’d) Air Pollution requirements of EPA regulations Part 87, as implemented by SFAR 27, at the amendment current on the date of certification. Compliance with the following optional requirements has been established: Ditching Provisions 25.801, including 25.807 (d) and excluding 25.1411 and 25.1415. When the operating rules require emergency ditching equipment, compliance with 25.1411 and 25.1415 must be demonstrated. In such cases when the manufacturer has complied with part or all of the provisions of 25.1411 and 25.1415, the items of equipment will be called out on the pertinent interior arrangement drawing, entitled "FAA Interior Schematic." Ice Protection Provisions 25.1419 Part 25, as amended by Amendment 25-1 thru 25-59 (except Section 25.1333), is applicable for the new equipment identified for the Model MD-88. Model MD-90-30 The type certification basis for the MD-90-30 Model airplane is Federal Aviation Regulations Part 25, effective February 1, 1965, as amended by Amendments 25-1 through 25-70 except as indicated below: SECTION THRU AMENDMENT 25-XX 25.109(a) (*) 25.251(d) 22 (**) 25.561(b)(3)(iii) 63 25.562(a), (c)(1), (c)(3), (c)(5), & (c)(6) 63 (**) 25.571(e)(1) 44 (**) 25.607 22 25.631 22 (**) 25.699(a) 22 25.701 22 25.777(c) 45 25.783 53 25.807(c) 31 25.809(b) & (f)(1)(i) 31 25.809(f)(1)(v) 45 (**) 25.979 10 25.1309 22 (***) 25.1401(b) & (f) 26 (*) Compliance with Amendment 25-42 as modified by the proposed requirements developed from results of FAA/JAA harmonization. (**) Requirements of this section have been added to FAR Part 25 by amendment since the original type certification basis and are not applicable to this type design. See NOTE 8 for additional Seats and Stowable Berth information. (***) Compliance as defined in McDonnell Douglas Report MDC-K4925 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 25-41. A6WE 72 Data Pertinent to All Models (cont’d) Certification Basis: (cont’d) Model MD-90-30 (cont’d) Based on 14 CFR § 21.101(g) for changes to type certificates (TC), 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). The Special Conditions applying to the Model MD-90-30 are as follows: (1) Special Conditions No. 25-95-WE-27 Airframe "Hydraulic System Failure" is applicable. Powerplant "In-Flight Thrust Reversal" is applicable. Flight Test "Environmental Flight Testing" is not required since FAR 25.253(a)(2)(iii) Amendment 54 incorporates its intent. (2) Special Condition, No. 25-88-WE-25, "Automatic Takeoff Thrust Control System" is not required since "Automatic Reserve Thrust Control System" (ARTS) is deleted. (3) Special Condition No. 25-ANM-26 "Windshear" is applicable. (4) Special Condition No. 25-ANM-15 "Lightning Protection for New Electronic Systems" is applicable. A Special Condition on High Intensity Radiated Fields (HIRF) (S.C. No. 25 -ANM-60) is required as indicated in Issue Paper G-4, Stage 3, Closed May 6, 1992. Note: For Model MD-90-30 equipped with Enhanced Flight Deck configuration, approved on March 3, 1998, refer to additional certification basis. Additional Certification Basis for Model MD-90-30 Equipped with Enhanced Flight Deck Configuration: (Approved March 3, 1998) The Saudi Arabian Airlines MD-90-30 configuration is equipped with six-across flight deck Liquid Crystal Displays. For this configuration, an additional certification basis was established. Based on the date of notification of major changes, April 5, 1996, in conjunction with the MD -90-30 certification basis, the certification basis for the Saudi Arabian Airlines MD-90-30 configuration is Federal Aviation Regulations Part 25, effective February 1, 1965, as amended by Amendments 25-1 through 25-84. In addition, a new Special Condition concerning aircraft operations without normal electrical power has been applied to the MD-90-30 model equipped with Enhanced Flight Deck Configuration. For those areas and components for which, as part of the original MD -90-30 certification, exceptions were granted and are not impacted by the changes, no additional justification is required. A6WE 73 Data Pertinent to All Models (cont’d) Certification Basis: (cont’d) Model MD-90-30 (cont’d) There are four significant changes that constitute a substantial flight deck change and are required to be certified to Federal Aviation Regulations Part 25 as amended by Amendments 25 -1 through 25-84. These changes relate to the incorporation of the new Electronic Display System which feature an integrated flight deck display system with six-across Liquid Crystal Displays. These changes are: • Six Across Liquid Crystal Displays / Electronic Instrument System • Dual Pegasus Flight Management Computers • Improved Overhead Control Panel • Integrated Standby Instrument System (Note: Takeoff Operation System / Host Performance Computer portion was canceled and is not installed in the Saudi Arabian Airlines Enhanced Flight Deck Configuration.) In addition, there are eight major changes that support the flight deck changes. These are for systems and components where a fundamental design change was not made to the system but certain changes were necessary for interfacing these systems and components to the new flight deck. These changes do not constitute a substantial change and therefore compliance was substantiated to the certification basis of the baseline MD-90-30. • Brake Temperature Monitor System • Pneumatic System Controller Part Number Change • Fuel System Interface to Electronic Instrument System (EIS) • Flight Deck Lighting • Cabin Pressure Acquisition Module • Landing Gear Control Handle • Control Wheel Interface to EIS • 115V 60HZ and 12V DC Medical Outlets Serial Number Eligible for Model MD-90-30 Enhanced Flight Deck Configuration: 53491 through 53519 Model 717-200 The type certification basis for the 717-200 Model airplane is Federal Aviation Regulations Part 25, effective February 1, 1965, as amended by Amendments 25-1 through 25-82 except as indicated below: SECTION SUBJECT THRU AMENDMENT 25-XX 25.519(b)(2) Static Ground Load Conditions 81 (Note 1) 25.562 Emergency Landing Dynamic Conditions 64 (b)(2) (Note 2) (c)(5) (Note 3) (c)(6) (Note 4) 25.571(e)(1) Bird Strike Speed 71 25.607 Fasteners 22 (Note 5) 25.631 Bird Strike Damage (8lb) 22 25.701(d) Flap & Slat Interconnection 22 (Note 6) 25.783(f) Doors 53 25.809(b) Emergency Exit Arrangement 31 (Not part of TC Basis) 25.810(a)(1)(i) Emergency Egress Assist Means & Escape Routes (Note 7) A6WE 74 Data Pertinent to All Models (cont’d) Certification Basis: (cont’d) Model 717-200 (cont’d) 25.810(a)(1)(v) Emergency Egress Assist Means & Escape Routes (Note 8) 25.856(a) Thermal/Acoustic Insulation Materials (Note 29) 25.979(b) Pressure Fueling System 10 25.1141(f)(2) Powerplant Controls for APU 39 25.1309 Equipment, Systems & Installation Safety Analysis 22 (Note 9) (Note 1) Except that §25.519(b)(2)(ii) is applicable only for a vertical limit load of 1.33 times the vertical static reaction at each jacking point acting singly and in combination with the horizontal load of 0.33 times the vertical static reaction applied in any direction. (Note 2) Except for cockpit floor deformation only. Compliance required for the passenger cabin floor. (Note 3) Exception for HIC for pilot/co-pilot seats, observer seat and front row passenger seats only. Compliance required with row to row HIC requirements for all seating in addition to cabin attendant seats. (Note 4) Exception for leg injury criterion for pilot/co-pilot seats and observer seats. (Note 5) This exception is for derivative structure only. The landing gear and all new 717-200 structure and design areas of the MD-90 which were incorporated in the 717-200 design will comply with amendment. (Note 6) Exception for the flap system only. (Note 7) Compliance to § 25.809(f)(1)(i), Amendment 25-15, in lieu of § 25.810(a)(1)(i), Amendment 25-72. (Note 8) Compliance to § 25.809(f)(1)(v), Amendment 25-45, in lieu of § 25.810(a)(1)(v), Amendment 25-72. (Note 9) Exception applies to DC-9 and MD-80 systems designed to the single failure concept that are unchanged or have minor alterations or improvements will comply through Amendment 25 -22. New or significantly modified DC-9, MD-80, and MD-90 systems, or those 717-200 systems common to the MD-80 or MD-90 that have prior safety analysis performed, will comply with Amendments 25-82. DC-9, MD-80, and MD-90 systems modified to implement new functions or applications for the 717- 200 design will comply with Amendment 82 for the modified areas. The detail information is provided in MDC report MDC 95K9080. All systems that the FAA considers new or significantly modified as well as for all existing systems affected by the changes will require compliance through 25-82. Based on 14 CFR § 21.101(g) for changes to type certificates (TC), 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). The type certification basis for the 717-200 Model airplane includes the following Equivalent Safety as indicated below: (1) FAR 25.103, "Stall Speed", CIP B-04 (2) FAR 25.109(a), "Accelerate-stop Distance", CIP B-01 (3) FAR 25.807(a)(3), "Emergency Exits", CIP D-06 (4) FAR 25.813(c)(1), "Emergency Exit Access", CIP D-14 A6WE 75 Data Pertinent to All Models (cont’d) Certification Basis: (cont’d) Model 717-200 (cont’d) (5) FAR 25.1397(a), "Color Specifications", CIP F-18 The Special Conditions applying to the Model 717-200 are as follows: (1) Special Conditions No. 25-ANM-26, “Windshear Triggered Autothrottle System” is applicable. (2) Special Condition No. 25-ANM-60, “High Intensity Radiated Fields (HIRF) is applicable. (3) Special Condition No. 25-95-WE-27, “Dual Hydraulic System Failure” is applicable. (4) Special Condition No. 25-144-SC, “Operation Without Normal Electric Power” is applicable. (5) Special Condition No. 25-489-SC, “Seats With Inflatable Lapbelts” is applicable. The Environmental Standards applying to the Model 717-200 are as follows: Applicable fuel venting and emission standards per US Environmental Protection Agency part 87, as implemented by FAR part 34. Applicable noise standards per FAR part 36, effective on December 1, 1969, as amended by Amendment 36-1 through Amendment 36-21 for the 717-200 airplane. McDonnell Douglas Corporation originally made application for Type Certification of the MD -95-30 on August 8, 1994. Subsequently, McDonnell Douglas Corporation merged with The Boeing Company, and updated its application for Type Certification on March 27, 1998 with the new model designation of 717-200. The FAA/JAA initially accepted the change in model designation on May 4, 1998. The FAA/JAA formally accepted the change in model designation on August 21, 1998. All compliance substantiation and related correspondence from the FAA/JAA using the MD-95 or MD-95- 30 model designator is applicable to the 717 or 717-200, as applicable. Type Certificate/Production Basis Type Certificate No. A6WE approved: November 23, 1965 for Models DC-9-11, -12, -13, and -14 January 21, 1966 for Model DC-9-15 December 19, 1966 for Model DC-9-31 March 1, 1967 for Models DC-9-15F and -32 October 4, 1967 for Model DC-9-32F February 21, 1968 for Model DC-9-41 April 5, 1968 for Model DC-9-33F November 25, 1968 for Model DC-9-21 August 11, 1975 for Model DC-9-51 April 20, 1976 for Model DC-9-34F November 3, 1976 for Model DC-9-34 August 25, 1980 for Model DC-9-81 July 29, 1981 for Model DC-9-82 October 17, 1985 for Model DC-9-83 October 21, 1987 for Model DC-9-87 December 10, 1987 for Model MD-88 November 4, 1994 for Model MD-90-30 September 1, 1999 for Model 717-200 A6WE 76 Data Pertinent to All Models (cont’d) Certification Basis: (cont’d) Production Basis: Production Certificate Number 700. On January 30, 1998, The Boeing Company and the McDonnell Douglas Corporation (MDC) merged the two Production Certificates, PC-27 and PC-700 into one Production Certificate, PC-700. The following aircraft factory serial numbers were produced under PC-27: 45695 (fus 001) thru 53581 (fus 2204) 53566 (fus 2206) thru 53591 (fus 2208) 53566 (fus 2210) thru 53558 (fus 2212) 53602 (fus 2214) thru 53572 (fus 2217) The following aircraft factory serial numbers were produced under PC-700: 53492 (fus 2205), -53493 (fus 2209), 53494 (fus 2213) 53495 (fus 2215), 53496 (fus 2216), 53603 (fus 2218) 53497 (fus 2219), 53496 (fus 2220) and subsequent. 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 Chapter 2 of Master Weight and Balance Manual listed in NOTE 1(a) below. Service Information The repairs called out in the Douglas Model DC-9 Structural Repair Manual are FAA approved. All Douglas Service Bulletins and other service information, when FAA approved, will carry a statement to that effect. NOTES NOTE 1. (a) A current weight and balance report, including a 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 McDonnell Douglas Reports contain loading information and interior arrangement configuration(s) for each airplane (listed by fuselage number and factory serial number) as delivered. These reports contain, or refer to, information relative to location of all passenger and crewmember seats, location and capacity of all cargo and baggage compartments, buffets, storage spaces and coatrooms, location and capacity of lounges and lavatories, and the required placards in the passenger compartment. Refer to appropriate Model DC-9 Report(s) for factor serial number affectivity. Models DC-9-11, -12, -13, -14, and -15 Report No. LB-32360, Chapter 1, "Master Weight and Balance Manual." Model DC-9-15F Report No. DAC-33247, Chapter 1, "Master Weight and Balance Manual." Model DC-9-21 Report No. DAC-66957, Chapter 1, "Master Weight and Balance Manual." Models DC-9-31, -32 Report No. DAC-33098, Chapter 1, "Master Weight and Balance Manual." Report No. MDC-07282, Chapter 1, "Master Weight and Balance Manual." A6WE 77 Data Pertinent to All Models (cont’d) NOTES (cont’d) NOTE 1. (cont’d) Model DC-9-32F, Serial Nos. 47040, 47041, 47147 and 47148. Report No. DAC-33098, Chapter 1 with Section 1-8 "Master Weight and Balance Manual." Models DC-9-32F, (except as noted above) -33F and -34F Report No. DAC-33870, Chapter 1, "Master Weight and Balance Manual." Report No. MDC-J7283, Chapter 1, "Master Weight and Balance Manual." Model DC-9-32F (C-9A Aeromed), -32 (VC-9C) Report No. DAC-33756, Chapter 1, "Master Weight and Balance Manual." Model DC-9-32F (C-9B) Report AN 01-1B-40, "Weight and Balance Data Handbook." Report No. MDC-J7283, Chapter 1, "Master Weight and Balance Manual." Model DC-9-34 Report No. MDC-J7282, Chapter 1, "Master Weight and Balance Manual." Model DC-9-41 Report No. DAC-33871, Chapter 1, "Master Weight and Balance Manual." Model DC-9-51 Report No. MDC-J6201, Chapter 1, "Master Weight and Balance Manual." Model DC-9-81, -82, -83, and MD-88 Report No. MDC-J8358, Chapter 1, "Master Weight and Balance Manual." Model DC-9-87 Report No. MDC-J3855, Chapter 1, "Master Weight and Balance Manual." Model DC-90-30 Report No. MDC-91K0981, Chapter 1, "Master Weight and Balance Manual." Model 717-200 Report No. MDC-97K9261, Chapter 1, "Master Weight and Balance Manual." (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. (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 the Master Weight and Balance Manual 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 CAR 4b.416 (DC-9-11 thru -51) or FAR 25.959 (DC-9-81, -82, -83, -87, MD-88 , MD-90-30 and 717-200). System Oil: The weight of oil remaining in the engine, constant speed drive and starter for the DC-9 airplane (VSCF generator for MD-90-30 or IDG for 717-200), 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. A6WE 78 Data Pertinent to All Models (cont’d) NOTES (cont’d) NOTE 1. (cont’d) (d) The "unusable" fuel is that amount of fuel, including tank trapped fuel, in the tanks which is unavailable to the engines under critical flight conditions as defined in CAR 4b.416 (DC -9-11 thru -51) or FAR 25.959 (DC-9-81, -82, -83, -87, MD-88 , MD-90-30 and 717-200) and may be obtained by taking the differences between the "total" and "usable" tank capacities shown under "fuel capacity." This "unusable" fuel is included in system fuel as indicated in 1(c) above and need not be accounted for separately. (e) All weight in excess of the maximum certificated zero fuel weight must be fuel in the main tanks, except for Models DC-9-31, -32, -32F, -33F, -34, -34F, -41, -51, -81, -82, -83, -87, MD-88, MD-90-30 and 717-200, (See Footnote (1) under Maximum Weights). Two fuel pumps must be operating in each main tank unless extra reserve fuel is loaded to compensate for an inoperative pump in accordance with the AFM. The center wing tank will supply fuel to both engines directly. Fuselage tank pumps must be off for all take-offs and landings for those airplanes which have fuselage tanks that supply the engines directly. The maximum unbalance in fuel between the main tanks should not exceed 1,500 lb in flight. NOTE 2. Refer to Cabin Pressurization in the FAA Approved Airplane Flight Manual (AFM) Limitations Section 1 for Takeoff and Landing Unpressurized. NOTE 3. Life Limited Parts and Airworthiness Limitations. DC-9 and MD-80 structural components which are life limited are listed in Report MDC- J0005 and must be replaced as indicated therein. MD-90 structural components which are life limited are listed in Part 1, Safe Life Limits, of Section 1 to the Airworthiness Limitations Instructions (ALI) Document, Report MDC-94K9000, and must be replaced as indicated therein. 717 structural components which are life limited are listed in Report MDC-96K9063 (717 ALI), and must be replaced as indicated therein. The MD-90 damage tolerance inspections must be conducted in accordance with Report MDC-94K9000 and the 717 damage tolerance inspections must be performed in accordance with Report MDC -96K9063. DC-9, MD-80, MD-90 and 717 non-structural components which are life limited, fuel system Critical Design Configuration Design Limitations (CDCCL), and fuel system ALIs are listed in report MDC-92K9145, "DC-9/ MD-80/ MD-90/ 717 Special Compliance Items Report." Reports MDC-J0005, MDC-94K9000, MDC-96K9063 and MDC-92K9145, and revisions thereto, are hereby incorporated as part of Data Sheet No. A6WE. Copies of these reports may be obtained from the manufacturer at the address below: The Boeing Company Attn: Data & Services Management 2401 E Wardlow Rd Long Beach, CA 90807-5309 OR Please send a Service Request via the Boeing Communication System (BCS) A6WE 79 Data Pertinent to All Models (cont’d) NOTES (cont’d) NOTE 3. (cont’d) The following applies to the Models DC-9-81, -82, -83, -87, MD-88, MD-90-30 and 717-200 as applicable: Equipment Functional Check Intervals as defined in FAA Approved MDC Report MDC - J1271, "DC-9-80 Fixed Maintenance Intervals" for the MD-80, MDC-93K9014 "MD-90 Certification Maintenance Requirements" for the MD-90 and MDC 98K9284 "717-200 Certification Maintenance Requirements" for the 717-200, shall not be extended, and any later approved revisions thereto, are hereby incorporated as part of Data Sheet No. A6WE. Such later revisions may be used only if approved by the Manager, Los Angeles Aircraft Certification Office. Copies may be obtained from the manufacturer at the above address. Brake Wear Limits: See Report No. MDC-92K9064, "Twinjet Brake Wear Limits." NOTE 4. For specific dimensional and weight limits, static unbalance, rated pressure, load rating, speed rating, etc., see the following McDonnell Douglas Tire Specification Drawing: (See Note 14 for DC-9 Series explanation.) Tire Spec. Dwg. Tire Max. Weight Airplane Series_ 7924523 26x6.6 (Chine) 40 lb Series 10, Models -31, -32, and -41 7929726 26x6.6 (Bias) 40 lb Series 10, -20, -30, -40, -50, -80, MD-88, MD-90-30 and 717-200 (see Note 4a) 7929726 26x6.6R14 (Radial) 40 lb 717-200 [see Note 4.(a)] 7911309 40x14 150 lb Series 10, -20, and Models -31, -32, and -32F 7926174 41x15-18 175 lb Series 40, -50 and Models -33F, -34 and -34F 7935357 H44.5x16.5-20 240 lb Series 80 and MD-88 PS5554 H44.5x16.5-21 220lb MD-90-30 PS5621 H41x15.0-19 170 lb 717-200 NOTE 4. (a) For 717-200: Bias/Radial nose tire intermix not permitted. NOTE 5. If engines are intermixed, the maximum thrust must be limited to that associated with the lowest powered engine. Combinations of engines which can be intermixed and their respective limitations are covered in the FAA Approved Airplane Flight Manual. For DC-9-81, -82, -83, -87 and MD-88: Engine installation "Intermix" configurations may be utilized in accordance with MDC DC-9-80 Maintenance Manual, Chapter 71, Engine Intermix, and the applicable appendices of the FAA Approved Airplane Flight Manual. For DC-9-83: Pratt and Whitney JT8D-219 engines may be intermixed in combination with JT8D-209, -217, -217A and -217C engines on the DC-9-83 airplanes, provided that the intermixed combinations and their respective limitations are covered in the FAA Approved Airplane Flight Manual. For DC-9-87 and MD-88: Pratt and Whitney JT8D-219 engines may be intermixed in combination with JT8D-217A and JT8D-217C engines on the DC-9-87 and MD-88 airplanes provided that the intermixed combinations and their respective limitations are covered in the FAA Approved Airplane Flight Manual. For MD-90-30: Intermix not permitted. For 717-200: Intermix not permitted. Data Pertinent to All Models (cont’d) A6WE 80 NOTES (cont’d) NOTE 6. (a) To assure that required overwing emergency exits will meet the pertinent CAR, or FAR, refer to the passenger seat installation drawing prepared by the manufacturer for each operator and approved by the Aircraft Engineering Division. The Drawings define the dimensions for locating seats in relation to the center line of the Type III overwing emergency exits and other limitations relative to type of seats, location of armrest and seat back recline, etc., for each of the approved seat models called out on the drawings. (b) Maximum Passenger Capacity: DC-9-11, -12, -13, -14, -15, -15F and –21 EXITS REQUIRED PASSENGER CAPACITY (1) TYPE I / SIDE TYPE III / SIDE TAIL EXIT 79 1 1 1 (3) 94 1 1 1 (4) 109 1 2 (2) 1 (3) DC-9-31, -32, -32F, -33F, -34, and -34F EXITS REQUIRED PASSENGER CAPACITY (1) TYPE I / SIDE TYPE III / SIDE TAIL EXIT 109 (1) 1 2 (2) 1 (3) 127 1 2 (2) 1 (5) 127 1 (9) 2 (2) 1 (10) DC-9-41 EXITS REQUIRED PASSENGER CAPACITY (1) TYPE I / SIDE TYPE III / SIDE TAIL EXIT 128 (6) 1 2 (2) 1 (5) DC-9-51 EXITS REQUIRED PASSENGER CAPACITY (1) TYPE I / SIDE TYPE III / SIDE TAIL EXIT 139 (6) 1 2 (2) 1 (5) DC-9-81, -82, -83, MD-88 and MD-90-30 PASSENGER CAPACITY (1) EXITS REQUIRED TYPE I / SIDE TYPE III / SIDE TAIL EXIT TYPE I LH SIDE AFT 172 (6) (12) 1 2 (7) 1 (8) 1 DC-9-87 PASSENGER CAPACITY (1) EXITS REQUIRED TYPE I / SIDE TYPE III / SIDE TAIL EXIT TYPE I LH SIDE AFT 139 (6) 1 2 (7) 1 (8) 1 (11) A6WE 81 Data Pertinent to All Models (cont’d) NOTES (cont’d) NOTE 6. (cont’d) 717-200 EXITS REQUIRED PASSENGER CAPACITY (1) TYPE I / SIDE TYPE III / SIDE TAIL EXIT 134 (6) 1 2 (7) 1 (1) Passenger capacity may be increased by 5 when inflatable slides are installed at Type I exits. (2) Aft Type III exit per side may be limited to Type IV qualifications. (3) Required exit consists of tail cone exit with assist rope. (4) Required exit consists of tail cone exit, slide and assist space per Exemption No. 424. (5) Tail cone exit must show compliance with§ 25.807(c)(6)(ii), effective October 24, 1967. (6) Aircraft must show compliance with § 25.2. (7) Aft overwing exit per side is considered Type III exit by equivalent safety finding per FAA letter to Douglas Aircraft Company, dated August 22, 1980. (8) Tail cone exit must be in compliance with the FAA requirements contained in FAA letter dated November 16, 1977. (9) Installation of approved inflatable slide required. (10) Tail cone exit must show compliance with § 25.807(c)(6)(iii) and FAR 25.809(f)(1) effective October 24, 1967. (11) Optional, not installed on all aircraft and not required for the maximum passenger capacity. If installed, must meet all Type I exit requirements of FAR 25.807 through 25.813 (see certification basis for applicable amendment). (12) Issue Paper SE-1 allows a maximum of 103 seats to be installed forward of the forward overwing exit on the MD-90-30. NOTE 7. (a) For Pratt and Whitney engines, the following fuels are eligible provided and to the extent they are allowed by P & W Service Bulletin No. 2016, and provided that for any wide cut fuels the JP-4/JET B procedures (restrictions and limitations) are followed: MIL-J-5624E (Grades JP-4 & JP-5), ASTM D1655 (Type JET A, A-1, & JET B) Russian fuels conforming to specification GOST 10227 (RT and TS-1), Chinese fuel conforming to Specification SY 1008-80 (RP-3/Number 3 Jet Fuel), and any other fuels conforming to P & W Service Bulletin No. 2016 or P & W Specification No. 522 and later revisions 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. (b) Shell anti-static fuel additive ASA-3 may be used if concentration delivered to the engine does not exceed 1 (one) p.p.m. A6WE 82 Data Pertinent to All Models (cont’d) NOTES (cont’d) NOTE 7. (cont’d) (c) MALCO 5403 corrosion inhibitor fuel additive may be used if concentration delivered to airplane does not exceed 8 lb/1000bbl (23mg/l) of turbine fuel. (d) For IAE engines, the following fuels are eligible provided and to the extent they are allowed by the International Aero Engines V2500A5/-D5 Installation and Operating Manual (IAE- 0043)/(IAE-0174), and provided that for any wide cut fuels, the JP-4/JET B procedures (restrictions and limitations) are followed: Kerosene type fuels as defined in ASTM D-1655 (Type JET A, A-1, & JET B) , MIL-T-5624 (Grades JP-4 and JP-5), MIL-T-83133 (Grade JP-8), as specified in engine Type Certificate Data Sheet E40NE, may be used. Russian fuels conforming to Specification GOST 10227 (RT and TS-1), Chinese fuel conforming to Specification SY 1008-80 (RP-3/Number 3 Jet Fuel), and fuels conforming to the specifications listed in the latest applicable issue of the International Aero Engines V2500A5/-D5 Installation and Operating Manual (IAE- 0043)/(IAE-0174) may be used. These fuels may be used separately or mixed in any proportions without adversely affecting the engine operation or power output. (e) For BR700-715 Engines, fuel conforming to ASTM- D-1655, Jet A or A-1, MIL-T-5624 Grade JP5 and MIL-T-83133 Grade JP8, British: Def. Stan. 91-87, 91-91, 91-86, IATA Kerosene Type, Air 3404 and 3405 (French), CAN/CGSB-3.23 and 3-GP-24 (Canadian), and Russian fuels conforming to specifications GOST 10227-86 (RT and TS-1). Also wide cut fuel grades conforming to ASTM D1655-94 Jet B, MIL-T-5624 Grade JP4. British: Def. Stan. 91-88, Canadian: CAN/CGSB-3.22, French: AIR 3407, IATA: JP-4 type fuel (1994). Fuels and fuel additives approved for use are listed in and will conform to specifications in accordance with BMW Rolls-Royce operating manual OI-715-3BR (see NOTE 15 of the FAA engine type certification data sheet E00061EN). NOTE 8. All replacement seats (crew, passenger and lounge), although they may comply with TSO - C39 or TSO C-127, must also be demonstrated to comply with CAR 4b.358(c)(DC-9-11 thru -51), § 25.785(i) (DC-9-81,-82,-83,-87, MD-88 and MD-90-30) (Certification basis for applicable amendment) (DC-9-81, -82, -83, -87, MD-88 and MD-90-30). For the 717-200, all replacement seats (crew, passenger and lounge), although they may comply with TSO -C127, must also be demonstrated to comply with FAR 25.785(f). Other installations, such as berths, buffets, compartments, or items of mass which could create a hazard to the safety of passengers and crew must also be demonstrated to meet the same requirements. MD -90-30 passenger seats must also comply with FAR 25.562(b), (c)(2), (c)(4), (c)(7), (c)(8) and stowable berth is not required to comply with FAR 25.562 for transporting non-ambulatory occupant. All 717-200 seats must comply with § 25.562 as defined by the type certification basis. NOTE 9. Any serial numbers eligible for Model DC-9-11, -12, -13, -14 may be converted to another model (DC- 9-11, -12, -13, -14) by adding a new nameplate, obtained from the manufacturer, installed adjacent to the original nameplate. The new nameplate must include the date of conversion and the new model designation. The original nameplate must not be removed. Appropriate FAA Airplane Approved Flight Manual pages must be obtained from the manufacturer for the new model. The model designation for serial numbers noted is as delivered by the manufacturer. A6WE 83 Data Pertinent to All Models (cont’d) NOTES (cont’d) NOTE 10. C-9A airplanes are the same as the basic Model DC-9-32F except for the interior and loading ramp. The limitations applicable to C-9A Aeromed airplanes are based on the fuselage loading distributions associated with this particular interior configuration and are not therefore applicable to other Model DC-9-32F airplanes. C-9B airplanes are the same as the basic Model DC-9-32F. VC-9C airplanes are the same as the basic Model DC-9-32 except for interior configuration and installation of 2250 gal. auxiliary fuselage belly tanks. The limitations applicable to the VC-9C airplanes are based on loading distribution associated with this particular configuration and are not therefore applicable to other Model DC-9-32 airplanes. Prior to operation as a commercial aircraft, the following must be accomplished: (a) The C-9A Aeromed military litters are not FAA approved and must be removed from the aircraft. (b) 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. (c) All aircraft returned to civil operations must comply with all applicable Airworthiness Directives. (d) Aircraft will be certificated as a Model DC-9-32 or DC-9-32F as applicable. A modification nameplate shall be installed adjacent to the original nameplate and shall contain the following information: Modifier's Name __________________________ Civil Model __________________________ Date of Modification __________________________ (e) An FAA Approved Airplane Flight Manual applicable to the Model DC-9-32 or DC-9-32F as modified for the particular operation intended must be provided for each airplane. NOTE 11. DC-9-11 aircraft, S/N 45728 was modified to a DC-9-14 per MDC Letter C1-25-6317, dated August 26, 1971; DC-9-11 aircraft, S/N's 45729 and 45730 were modified to DC-9-14, per MDC Letter C1-25-2156, dated March 9, 1970. DC-9-12 aircraft, S/N 47056 was modified to a DC-9-14 per MDC Letter C1-25-3641, dated May 10, 1967. DC-9-31 aircraft, S/N's 47442, 47450, 47566, 47572, 47573, 47638, 47647, 47649, 47664, 47720, 47721 and 47727, were modified to Model DC-9-32 in accordance with Report No. MDC-J0846, and a new nameplate was installed adjacent to the original to include this new model designation and date of conversion. A6WE 84 Data Pertinent to All Models (cont’d) NOTES (cont’d) NOTE 11 (cont’d) DC-9-32 aircraft, S/N's 45846, 47020, 47023, 47026, 47068, 47351, 47352, were modified to a DC-9-31. A new nameplate was installed adjacent to the original to include this new model designation and date of conversion. Subsequent changes of model designation to S/N's 47026, 47351, 47352, airplanes must be made in accordance with Douglas Report MDC - J0846. DC-9-81 airplane S/N's 48095-48098 were reassigned to DC-9-82 airplanes prior to manufacture and delivery. A DC-9-81 airplane, may be designated a DC-9-82, a DC-9-82 airplane may be designated a DC-9-83 and a DC-9-82 may be designated a DC-9-81 when modified in accordance with McDonnell Douglas Report MDC-J2725; and, by adding a new nameplate, obtained from the manufacturer, installed adjacent to the original nameplate. The new nameplate must include the date of conversion and the new model designation. The original nameplate must not be removed. Appropriate FAA Airplane Approved Flight Manual pages must be obtained from the manufacturer for the new model. DC-9-82 airplanes, S/Ns 49532 through 49539, were converted to MD-88s in accordance with McDonnell Douglas Service Bulletins 22-89, 34-183, 34-188, and 53-199 and McDonnell Douglas letter 88FAA-C1-E65-3498, dated June 1, 1988. Appropriate FAA Approved Airplane Flight Manual pages must be obtained from the manufacturer for the new model. NOTE 12. The use of the suffix - CF instead of -F when referring to the DC-9-15F, DC-9-32F, DC-9- 33F or DC-9-34F Model designations does not alter the aircraft. For example, a DC-9-34F airplane and a DC-9-34CF airplane are the same and the Model designations may be referred to interchangeable. NOTE 13. In the DC-9-81, -82, -83, -87, and MD-88, all interior materials must comply with the fire protection requirements of § 25.853, effective May 2, 1977. In the MD-90-30, all interior materials must comply with the fire protection requirements of § 25.853, effective September 26, 1988. In the 717-200, all interior materials must comply with the fire protection requirements of FAR 25.853, effective August 20, 1990. NOTE 14. The official designator for the McDonnell Douglas Model DC-9-81, -82, -83, or -87 is the DC-9-81, -82, -83, or -87. The "MD" designator may be used in parentheses, but, must be accompanied by the official designator (i.e., DC-9-81 (MD-81)). The DC-9 Series 10 (DC-9-10) includes DC-9-11, DC-9-12, DC-9-13, DC-9-14, DC-9-15, and DC-9-15F; Series 20 (DC-9-20) include DC-9-21; Series 30 (DC-9-30) includes 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, and DC-9-34F; Series 40 (DC-9-40) includes DC-9-41; Series 50 (DC-9-50) includes DC-9-51. NOTE 15. The Model DC-9 Series airplanes have a mandated supplemental Structural Inspection Program (SIP). These programs were prepared in accordance with the provisions of AC 91 -56. Evaluation of structural elements, type of damage considered (fatigue, corrosion , service, and production damage) and the inspection and/or modification criteria should, to the extent practicable, be in accordance with the damage tolerance principles (Amendment 25 -45) of the current FAR 25.571 standards. A6WE 85 Data Pertinent to All Models (cont’d) NOTES (cont’d) NOTE 16. The location of flight attendant seats demonstrated to comply with the direct view requirements of § 25.785(h)(1), for the MD-90-30, and 25.785(h)(2), for the 717-200, are shown on the manufacturers interior arrangement drawing, entitled, "FAA Interior Schematic." NOTE 17. McDonnell Douglas MD-80, MD-90 and 717-200 FAA accepted Maintenance Review Board reports contain the initial minimum maintenance/inspection requirements to be used in the development of an approved continuous airworthiness maintenance program for the airframe, engines, systems and components. The tasks and their frequencies given in t his report form a part of the instructions for continued airworthiness as required by FAR Part 25, Appendix H. NOTE 18. For MD-90-30 Model, the APU life limited components are listed in the manufacturer's maintenance manual. NOTE 19. For MD-90-30 Systems Anomalies, refer to McDonnell Douglas Report No. 94K9143 "Nuisance Discrepancies Report." NOTE 20 The DC-9-81, -82, -83, -87 and MD-88 aircraft are qualified for operations within Reduced Vertical Separation (RVSM) airspace. See MDC Service Bulletin MD-80-34-289 for establishing the basis for operational approval. NOTE 21 The MD-90-30 airplane is qualified for operations within Reduced Vertical Separation (RVSM) airspace. See MDC Service Bulletin MD-90-34-006 for establishing the basis for operational approval. The 717-200 airplane is qualified for operations within Reduced Vertical Separation (RVSM) airspace. See MDC Report 99K9203 (latest revision) for establishing the basis for operational approval. NOTE 22 Deleted. NOTE 23 For the 717-200 airplane, the lower cargo compartments are certified as "Class C" equipped with smoke detection system and fire suppression system. NOTE 24 The 717-200 airplane time limited exemption has been removed since Boeing has shown compliance to § 25.571(b), Amendment 25-72 and § 25.671(c)(1), Amendment 25-23 for the 717-200 flap system (ref: CIP C-08) NOTE 25 At the time of the original 717-200 airplane certification on September 1, 1999, the engine suppliers name was BMW Rolls-Royce Aero Engines. In January 2000, the engine supplier changed their name to Rolls-Royce Deutschland GmbH. In December 2000, the engine supplier has changed their name to Rolls-Royce Deutschland Ltd & Co KG. All compliance substantiation and related correspondence from the FAA/JAA using the BMW Rolls-Royce Aero Engines or Rolls-Royce Deutschland GmbH name remains applicable to the 717 airplane using engines with Rolls-Royce Deutschland Ltd & Co KG engine nameplates. NOTE 26 For DC-9-32, FSN’s 47431, 47474, 47477, and 47639; issuance of a Standard Airworthiness Certificate is prohibited unless modifications of STC’s SA2541SO, SA2542SO, and SA2446SO are removed and the airplanes are returned to original type design. A6WE 86 Data Pertinent to All Models (cont’d) NOTES (cont’d) NOTE 27 The type design reliability and performance of the Model DC-9-81, -82, -83, -87, and MD-88 airplanes have been evaluated in accordance with FAA Advisory Circular 120 -42A and found suitable for 120 minute Extended Range Operations with Two-Engine Airplanes (ETOPS) when operated and maintained in accordance with Douglas Report MDC-K1629 entitled, “MD-80 Extended Range Operations Configuration, Maintenance, and Procedures”. This finding does not constitute approval to conduct ETOPS operations. NOTE 28 The type design reliability and performance of the Model 717-200 airplane has been evaluated in accordance with FAA Advisory Circular 120-42A and found suitable for 75 minute Extended Range Operations with Two-Engine Airplanes (ETOPS) when operated and maintained in accordance with Boeing Report MDC-04K9007 entitled, “717 Extended Range Operations Configuration, Maintenance, and Procedures”. This finding does not constitute approval to conduct ETOPS operations. NOTE 29 14 CFR § 121.312(e), Amendment 121-289 requires thermal/acoustic insulation materials installed in the fuselage to meet the requirements of § 25.856, Amendment 25-111, effective September 2, 2003. Compliance to § 25.856(a), Amendment 25-111, for the 717-200 was met on airplane serial numbers 55051, 55052, 55098, 55099, 55187, and 55190-55194. ......END...... ``` ## ADs (520, 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 2025-21-05](https://openairdocs.org/ad/2025-21-05): Landing Gear · Boeing 717-200. Effective Jan 2, 2026 - [AD 2025-09-11](https://openairdocs.org/ad/2025-09-11): Flight controls · Boeing DC-9-81 (MD-81), DC-9-82 (MD-82), DC-9-83 (MD-83) and 20 more. Effective Jun 12, 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 2024-21-01](https://openairdocs.org/ad/2024-21-01): Wings · Boeing 717-200. Effective Nov 7, 2024 - [AD 2024-20-02](https://openairdocs.org/ad/2024-20-02): Fuselage · Boeing 717-200, DC-9-11, DC-9-12 and 16 more. Effective Oct 21, 2024 - [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 2023-02-09](https://openairdocs.org/ad/2023-02-09): Stabilizers · Boeing DC-9-81 (MD-81), DC-9-82 (MD-82), DC-9-83 (MD-83) and 2 more. Effective Mar 20, 2023 - [AD 2023-01-13](https://openairdocs.org/ad/2023-01-13): Wings · Boeing DC-9-81 (MD-81), DC-9-82 (MD-82), DC-9-83 (MD-83) and 2 more. Effective Mar 13, 2023 - [AD 2021-12-12](https://openairdocs.org/ad/2021-12-12): Wings · Boeing 717-200. Effective Jul 29, 2021 - [AD 2021-02-16](https://openairdocs.org/ad/2021-02-16): Ice and rain protection · Boeing 717-200. Effective Mar 30, 2021 - [AD 2020-21-02](https://openairdocs.org/ad/2020-21-02): Fire protection · Airbus Canada Limited Partnership BD-500-1A10, BD-500-1A11, A330-201 and 45 more. Effective Nov 19, 2020 - [AD 2020-10-10](https://openairdocs.org/ad/2020-10-10): Wings · Boeing DC-9-81 (MD-81), DC-9-82 (MD-82), DC-9-83 (MD-83) and 2 more. Effective Jun 26, 2020 - [AD 2019-24-17](https://openairdocs.org/ad/2019-24-17): Wings · Boeing MD-90-30. Effective Jan 24, 2020 - [AD 2018-23-12](https://openairdocs.org/ad/2018-23-12): Equipment/furnishings · Airbus A300 B2-1A, A300 B2-1C, A300 B2-203 and 180 more. Effective Dec 28, 2018 - [AD 2018-07-04](https://openairdocs.org/ad/2018-07-04): Ice and rain protection · Boeing DC-9-81 (MD-81), DC-9-82 (MD-82), DC-9-83 (MD-83) and 3 more. Effective Sep 10, 2018 - [AD 2018-10-08](https://openairdocs.org/ad/2018-10-08): Stabilizers · Boeing 717-200. Effective May 31, 2018 - [AD 2018-03-04](https://openairdocs.org/ad/2018-03-04): Airspeed/Mach Indicator · Boeing 717-200, DC-9-11, DC-9-12 and 23 more. Effective Mar 16, 2018 - [AD 2017-19-05](https://openairdocs.org/ad/2017-19-05): Smoke Detection · Airbus A330-201, A330-202, A330-203 and 30 more. Effective Oct 31, 2017 - [AD 2017-17-19](https://openairdocs.org/ad/2017-17-19): Fuselage · Boeing DC-9-81 (MD-81), DC-9-82 (MD-82), DC-9-83 (MD-83) and 2 more. Effective Oct 4, 2017 - [AD 2017-09-09](https://openairdocs.org/ad/2017-09-09): Passenger Compartment Equipment · Boeing 717-200, MD-90-30, CL-600-2C10 (Regional Jet Series 700) and 17 more. Effective Jun 28, 2017 - [AD 2017-11-02](https://openairdocs.org/ad/2017-11-02): Stabilizers · Boeing MD-90-30. Effective Jun 27, 2017 - [AD 2017-01-03](https://openairdocs.org/ad/2017-01-03): Standard practices/structures · Boeing 717-200. Effective Mar 14, 2017 - [AD 2016-25-26](https://openairdocs.org/ad/2016-25-26): Navigation · Boeing MD-90-30. Effective Feb 2, 2017 - [AD 2016-25-06](https://openairdocs.org/ad/2016-25-06): Stabilizers · Boeing DC-9-81 (MD-81), DC-9-82 (MD-82), DC-9-83 (MD-83) and 2 more. Effective Jan 25, 2017 - [AD 2016-22-18](https://openairdocs.org/ad/2016-22-18): Fuselage · Boeing MD-90-30. Effective Nov 21, 2016 - [AD 2016-07-08](https://openairdocs.org/ad/2016-07-08): Fuel · Boeing DC-9-83 (MD-83). 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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 2014-05-27](https://openairdocs.org/ad/2014-05-27): Navigation · Airbus A319-111, A319-112, A319-113 and 99 more. Effective May 2, 2014 - [AD 2014-05-22](https://openairdocs.org/ad/2014-05-22): Fuselage · Boeing 717-200. Effective Apr 15, 2014 - [AD 2013-25-12](https://openairdocs.org/ad/2013-25-12): Fuselage Main Bulkhead · Boeing DC-9-11, DC-9-12, DC-9-13 and 13 more. Effective Jan 31, 2014 - [AD 2013-19-22](https://openairdocs.org/ad/2013-19-22): JASC Code 53, Fuselage · Boeing 717-200. Effective Nov 6, 2013 - [AD 2013-05-02](https://openairdocs.org/ad/2013-05-02): Stabilizers · Boeing DC-9-81 (MD-81), DC-9-82 (MD-82), DC-9-83 (MD-83) and 2 more. Effective Apr 15, 2013 - [AD 2012-21-18](https://openairdocs.org/ad/2012-21-18): Wings · Boeing MD-90-30. Effective Dec 5, 2012 - [AD 2012-22-04](https://openairdocs.org/ad/2012-22-04): Wings · Boeing MD-90-30. Effective Dec 5, 2012 - [AD 2012-21-13](https://openairdocs.org/ad/2012-21-13): Wings · Boeing DC-9-81 (MD-81), DC-9-82 (MD-82), DC-9-83 (MD-83) and 2 more. Effective Dec 4, 2012 - [AD 2012-12-09](https://openairdocs.org/ad/2012-12-09): Horizontal Stabilizer Structure · Boeing 717-200. Effective Jul 23, 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 2011-17-11](https://openairdocs.org/ad/2011-17-11): Wings · Boeing DC-9-81 (MD-81), DC-9-82 (MD-82), DC-9-83 (MD-83) and 2 more. Effective Sep 26, 2011 - [AD 2011-15-01](https://openairdocs.org/ad/2011-15-01): Stabilizers · Boeing DC-9-81 (MD-81), DC-9-82 (MD-82), DC-9-83 (MD-83) and 2 more. Effective Aug 19, 2011 - [AD 2011-14-03](https://openairdocs.org/ad/2011-14-03): Stabilizers · Boeing DC-9-81 (MD-81), DC-9-82 (MD-82), DC-9-83 (MD-83) and 2 more. Effective Aug 10, 2011 All 520: https://openairdocs.org/tcds/A6WE/ads.md ## Registered aircraft by registry model (OpenAirDocs) - [Boeing 717-200](https://openairdocs.org/model/boeing-717-200): 111 aircraft (registry code 1383700) - [Mcdonnell Douglas DC-9-83(MD-83)](https://openairdocs.org/model/mcdonnell-douglas-dc-9-83-md-83): 49 aircraft (registry codes 3022083, 3022085) - [Mcdonnell Douglas DC-9-82(MD-82)](https://openairdocs.org/model/mcdonnell-douglas-dc-9-82-md-82): 22 aircraft (registry code 3022082) - [Mcdonnell Douglas MD-88](https://openairdocs.org/model/mcdonnell-douglas-md-88): 14 aircraft (registry codes 3023688, 3023689) - [Mcdonnell Douglas DC-9-87](https://openairdocs.org/model/mcdonnell-douglas-dc-9-87): 13 aircraft (registry code 3022087) - [Mcdonnell Douglas DC-9-15F](https://openairdocs.org/model/mcdonnell-douglas-dc-9-15f): 3 aircraft (registry code 302203K) - [Mcdonnell Douglas DC-9-33F](https://openairdocs.org/model/mcdonnell-douglas-dc-9-33f): 3 aircraft (registry code 302207C) - [Mcdonnell Douglas MD-90-30](https://openairdocs.org/model/mcdonnell-douglas-md-90-30): 3 aircraft (registry codes 3023690, 302369A) - [Boeing MD-90-30](https://openairdocs.org/model/boeing-md-90-30): 2 aircraft (registry code 13848ME) - [Douglas DC-9-15F](https://openairdocs.org/model/douglas-dc-9-15f): 1 aircraft (registry code 3022037) - [Douglas DC-9-21](https://openairdocs.org/model/douglas-dc-9-21): 1 aircraft (registry code 302205A) - [Douglas DC-9-32F](https://openairdocs.org/model/douglas-dc-9-32f): 1 aircraft (registry code 3022067) - [Douglas DC-9-33F](https://openairdocs.org/model/douglas-dc-9-33f): 1 aircraft (registry code 302207A) - [Douglas DC-9-83](https://openairdocs.org/model/douglas-dc-9-83): 1 aircraft (registry code 3020305) - [Douglas DC9-15](https://openairdocs.org/model/douglas-dc9-15): 1 aircraft (registry code 3022036) - [Mcdonnell Douglas DC-9-32](https://openairdocs.org/model/mcdonnell-douglas-dc-9-32): 1 aircraft (registry code 302206C) - [Mcdonnell Douglas DC-9-32F](https://openairdocs.org/model/mcdonnell-douglas-dc-9-32f): 1 aircraft (registry code 302206E) - [Mcdonnell Douglas DC-9-87 (MD-87)](https://openairdocs.org/model/mcdonnell-douglas-dc-9-87-md-87): 1 aircraft (registry code 3022086) - [Boeing 717-231](https://openairdocs.org/model/boeing-717-231): 0 aircraft (registry code 1383701) - [Boeing DC-9-83](https://openairdocs.org/model/boeing-dc-9-83): 0 aircraft (registry code 3022001) - [Douglas DC-9-11](https://openairdocs.org/model/douglas-dc-9-11): 0 aircraft (registry code 3022028) - [Douglas DC-9-12](https://openairdocs.org/model/douglas-dc-9-12): 0 aircraft (registry code 3022030) - [Douglas DC-9-14](https://openairdocs.org/model/douglas-dc-9-14): 0 aircraft (registry code 3022034) - [Douglas DC-9-31](https://openairdocs.org/model/douglas-dc-9-31): 0 aircraft (registry code 3022065) - [Douglas DC-9-32](https://openairdocs.org/model/douglas-dc-9-32): 0 aircraft (registry code 3022066) - [Douglas DC-9-41](https://openairdocs.org/model/douglas-dc-9-41): 0 aircraft (registry code 302207N) - [Mcdonnell Douglas DC-9-11](https://openairdocs.org/model/mcdonnell-douglas-dc-9-11): 0 aircraft (registry code 302202B) - [Mcdonnell Douglas DC-9-12](https://openairdocs.org/model/mcdonnell-douglas-dc-9-12): 0 aircraft (registry code 302203B) - [Mcdonnell Douglas DC-9-13](https://openairdocs.org/model/mcdonnell-douglas-dc-9-13): 0 aircraft (registry code 302203D) - [Mcdonnell Douglas DC-9-14](https://openairdocs.org/model/mcdonnell-douglas-dc-9-14): 0 aircraft (registry code 302203F) - [Mcdonnell Douglas DC-9-15](https://openairdocs.org/model/mcdonnell-douglas-dc-9-15): 0 aircraft (registry code 302203H) - [Mcdonnell Douglas DC-9-21](https://openairdocs.org/model/mcdonnell-douglas-dc-9-21): 0 aircraft (registry code 302205C) - [Mcdonnell Douglas DC-9-31](https://openairdocs.org/model/mcdonnell-douglas-dc-9-31): 0 aircraft (registry code 302206A) - [Mcdonnell Douglas DC-9-34](https://openairdocs.org/model/mcdonnell-douglas-dc-9-34): 0 aircraft (registry code 302207E) - [Mcdonnell Douglas DC-9-34F](https://openairdocs.org/model/mcdonnell-douglas-dc-9-34f): 0 aircraft (registry code 302207D) - [Mcdonnell Douglas DC-9-41](https://openairdocs.org/model/mcdonnell-douglas-dc-9-41): 0 aircraft (registry code 302207P) - [Mcdonnell Douglas DC-9-51](https://openairdocs.org/model/mcdonnell-douglas-dc-9-51): 0 aircraft (registry code 3022051) - [Mcdonnell Douglas DC-9-81(MD-81)](https://openairdocs.org/model/mcdonnell-douglas-dc-9-81-md-81): 0 aircraft (registry code 3022081) - [Mcdonnell Douglas DC-9-82](https://openairdocs.org/model/mcdonnell-douglas-dc-9-82): 0 aircraft (registry code 3022084) ## STCs approved under this data sheet (1,071, first 50) - [STC ST12461IB](https://openairdocs.org/stc/ST12461IB): Installation of Cockpit Voice Recorder with optional RIPS Upgrade. Mid- Canada Mod Center - [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 ST01649AT-D](https://openairdocs.org/stc/ST01649AT-D): Installation of Collins DLM-900 Acars system.. AIRCRAFT RECONFIG TECHNOLOGIES, LLC - [STC ST01650AT-D](https://openairdocs.org/stc/ST01650AT-D): Installation of Collins VHF-900 Communication system.. AIRCRAFT RECONFIG TECHNOLOGIES, LLC - [STC ST01765AT-D](https://openairdocs.org/stc/ST01765AT-D): Installation of Collins VHF-900 Communications System in a provisioned aircraft.. AIRCRAFT RECONFIG TECHNOLOGIES, LLC - [STC ST01766AT-D](https://openairdocs.org/stc/ST01766AT-D): Installation of Collins DLM-900 ACARS system with a Miltope printer, in a provisioned aircraft.. AIRCRAFT RECONFIG TECHNOLOGIES, LLC - [STC ST02129AT-D](https://openairdocs.org/stc/ST02129AT-D): Installation of G1 and G2 Galley.. AIRCRAFT RECONFIG TECHNOLOGIES, LLC - [STC ST02463AT](https://openairdocs.org/stc/ST02463AT): Installation of an Intrusion/Penetration Resistance Flightdeck Door and Reinforced Flightdeck Door Surround.. AIRCRAFT RECONFIG TECHNOLOGIES, LLC - [STC ST02945AT-D](https://openairdocs.org/stc/ST02945AT-D): Interior Reconfiguration. AIRCRAFT RECONFIG TECHNOLOGIES, LLC - [STC ST03184AT-D](https://openairdocs.org/stc/ST03184AT-D): Interior modification. AIRCRAFT RECONFIG TECHNOLOGIES, LLC - [STC ST03203AT](https://openairdocs.org/stc/ST03203AT): Installation of a Flight Data Acquisition Module (FDAM) and Flight Data Recorder (FDR), sensors Sensor Kit with Level E software.. AIRCRAFT RECONFIG TECHNOLOGIES, LLC - [STC ST03815AT-D](https://openairdocs.org/stc/ST03815AT-D): Interior Reconfiguration. AIRCRAFT RECONFIG TECHNOLOGIES, LLC - [STC ST03849AT-D](https://openairdocs.org/stc/ST03849AT-D): Installation of an Interior Reconfiguration.. AIRCRAFT RECONFIG TECHNOLOGIES, LLC - [STC ST03941AT](https://openairdocs.org/stc/ST03941AT): Interior Reconfiguration. AIRCRAFT RECONFIG TECHNOLOGIES, LLC - [STC ST03966AT](https://openairdocs.org/stc/ST03966AT): Lavatory refurbishment and PED power installation. AIRCRAFT RECONFIG TECHNOLOGIES, LLC - [STC ST03990AT](https://openairdocs.org/stc/ST03990AT): Interior Reconfiguration. AIRCRAFT RECONFIG TECHNOLOGIES, LLC - [STC ST04122AT](https://openairdocs.org/stc/ST04122AT): Installation of an oven. AIRCRAFT RECONFIG TECHNOLOGIES, LLC - [STC ST04231AT](https://openairdocs.org/stc/ST04231AT): PED power installation. 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 ST01541AT-D](https://openairdocs.org/stc/ST01541AT-D): Installation of Collins DLM-900 ACARS Management unit.. AIRCRAFT RECONFIG TECHNOLOGIES, LLC - [STC ST04816NY](https://openairdocs.org/stc/ST04816NY): Installation of Electronically Steerable (ESA) Antenna and Power Supply. ALOFT AeroArchitects - [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 ST12026AT](https://openairdocs.org/stc/ST12026AT): Installation of Portable Emergency Locator Transmitter. Delta Flight Products LLC - [STC ST02478NY](https://openairdocs.org/stc/ST02478NY): Installation of an advertisement container on the bottom of a seat back tray table on Weber Model 5300 passenger seats (Weber Part Numbers 852454, 852455, 852456, 852457, 852458, and 852459). Atin OOH, LLC - [STC ST04752NY](https://openairdocs.org/stc/ST04752NY): Replacement of Dual Analog Radio Altimeter Transceivers with Dual 5G Tolerant Collins Aerospace or Honeywell Digital Radio Altimeters Transceivers and Dual Shadin Digital-to-Analog Converters. S. LB Aircraft Engineering - [STC ST00030IB](https://openairdocs.org/stc/ST00030IB): Installation of Test Tech ELT. APTOZ EHF - [STC ST04813NY](https://openairdocs.org/stc/ST04813NY): Installation of Hughes Satellite Connectivity and Wifi Cabin Distribution System. ALOFT AeroArchitects - [STC ST09180AC](https://openairdocs.org/stc/ST09180AC): Installation of DeVore Wing Forward Position Lights. The Boeing Company - [STC ST09181AC](https://openairdocs.org/stc/ST09181AC): Installation of main landing gear spotlights. The Boeing Company - [STC ST03885AT](https://openairdocs.org/stc/ST03885AT): Installation of an Avionica, Inc. avCM Cellular Module. Aircraft Systems and Manufacturing Inc. - [STC SA1003NW](https://openairdocs.org/stc/SA1003NW): Installation of CDRI-II interior retrofit kit.. Safran Cabin Inc. - [STC SA1983NM](https://openairdocs.org/stc/SA1983NM): Installation of coatroom/cart stowage module.. Safran Cabin Inc. - [STC SA2040NM](https://openairdocs.org/stc/SA2040NM): Installation of closet and windscreen.. Safran Cabin Inc. - [STC SA2130NM](https://openairdocs.org/stc/SA2130NM): Installation of the Extended spacial concept interior(ESCI) retrofit kit.. Safran Cabin Inc. - [STC SA2134NM](https://openairdocs.org/stc/SA2134NM): Installation of a Contemporary Deep Rack Interior (CDRI) Modification Kit. Safran Cabin Inc. - [STC SA2153NM](https://openairdocs.org/stc/SA2153NM): Installation of the Extended Special Concept Interior (ESCI) Retrofit Kit. Safran Cabin Inc. - [STC SA2621NM](https://openairdocs.org/stc/SA2621NM): Installation of the extended spacial concept interior (ESCI) retrofit kit.. Safran Cabin Inc. - [STC SA335NW](https://openairdocs.org/stc/SA335NW): Installation of Contemporary Deep Rack Interior. Safran Cabin Inc. - [STC SA3469NM](https://openairdocs.org/stc/SA3469NM): Installation of Closet/Stowage Compartments/Coat Compartment/ Coatroom.. Safran Cabin Inc. - [STC SA3494NM](https://openairdocs.org/stc/SA3494NM): Installation of auxiliary galley.. Safran Cabin Inc. - [STC SA3497NM](https://openairdocs.org/stc/SA3497NM): Installation of closet/stowage units.. Safran Cabin Inc. - [STC SA3997NM](https://openairdocs.org/stc/SA3997NM): Installation of Driessen Galleys G1; P/N 14910-101 and G2; P/N 14920-101 and Driessen Serving Carts, P/Ns DLH 801-003 and DLH 177-009. Safran Cabin Inc. - [STC SA4371NM](https://openairdocs.org/stc/SA4371NM): Installation of retrofit/modular lavatories.. Safran Cabin Inc. - [STC SA4744NM](https://openairdocs.org/stc/SA4744NM): Installation of Extended Spacial Concept Interior III Retrofit Kit.. Safran Cabin Inc. - [STC SA4770NM](https://openairdocs.org/stc/SA4770NM): Installation of a Modular Lavatory(Retrofit Installation).. Safran Cabin Inc. - [STC SA4822NM](https://openairdocs.org/stc/SA4822NM): Installation of galleys, coatrooms, and a partition.. Safran Cabin Inc. - [STC SA4831NM](https://openairdocs.org/stc/SA4831NM): Installation of closet/stowage units.. Safran Cabin Inc. - [STC SA5542NM](https://openairdocs.org/stc/SA5542NM): Installation of galley, stowage unit, coatroom, PSU kit, drop ceiling.. Safran Cabin Inc. - [STC SA5786NM](https://openairdocs.org/stc/SA5786NM): Installation of an overhead life raft stowage compartment kit.. Safran Cabin Inc. - [STC SA5834NM](https://openairdocs.org/stc/SA5834NM): Installation of C&D Interiors galley and stowage units.. Safran Cabin Inc. All 1,071: https://openairdocs.org/tcds/A6WE/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.