Faa Tcds Md80 - A6we Rev. 30 (25-Mar-14)

DEPARTMENT OF TRANSPORTATIONFEDERAL 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 The following table identifies the current revision of each page of the Data Sheet: Page No. Rev. No. Page No. Rev. No. Page No. Rev. No. Page No. Rev. No. Page No. Rev. No. Page No. Rev. No. 1 30 18 26 35 26D 52 26 69 26 86 29 2 2 19 26 36 26 53 26 70 27 3 26 20 26 37 26 54 26 71 26 4 26 21 26 38 26 55 26 72 29 5 26 22 26 39 26 56 26 73 30 6 26 23 26 40 26 57 26 74 29 7 26 24 26 41 26 58 26 75 30 8 26 25 26 42 26 59 26 76 27 9 26 26 26 43 26 60 26 77 27 10 26 27 26 44 29 61 26 78 29 11 26 28 26 45 29 62 26 79 26 12 26 29 26 46 26 63 26 80 27 13 26 30 26 47 29 64 26 81 26 14 26 31 26 48 26 65 26 82 26 15 26 32 26 49 29 66 26 83 26 16 26 33 26 50 26 67 26 84 27 17 26 34 26 51 26 68 26 85 29 A6WE 2 The following table defines how specific airplane models are identified in the applicability of airworthiness directives (AD): Airplane Model 1. DC-9, Series 10 Applicability of ADs Prior to March 1, 2002 DC-9, series 10; OR DC-9-10 series airplanes; OR 2. DC-9, Series 20 3. DC-9, Series 30 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-9-20 series airplanes 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 4. DC-9, Series 40 5. DC-9, Series 50 6. DC-9-81 (MD-81) DC-9-82 (MD-82) DC-9-83 (MD-83) DC-9-87 (MD-87) C-9 (military) airplanes (Note: may be listed without parenthetical) DC-9-40 series airplanes, OR DC-9-41 series airplanes DC-9-50 series airplanes, OR DC-9-51 series airplanes 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 Applicability of ADs as of March 1, 2002 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. DC-9-21 airplanes 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. DC-9-41 airplanes DC-9-51 airplanes 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. DC-9-80 (MD-80) series airplanes. 7. MD-88 8. MD-90 9. 717 *Note: may be listed without parenthetical MD-88 airplanes MD-90-30 series airplanes, OR MD-90 series airplanes 717-200 series airplanes, OR 717 series airplanes MD-88 airplanes MD-90-30 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. 3 A6WE 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) Maximum Continuous 14,000 lb 12,600 lb Maximum permissible engine rotor operating speeds: N1 (Low Compressor) N2 (High Compressor) 8,600 rpm (100.1%) 12,250 rpm (100%) Maximum permissible temperatures: Turbine exhaust gas JT8D-1, -7 Take-off (5 min.) 570°C 1,058°F Maximum Continuous 535°C 995°F Maximum Acceleration 570°C 1,058°F Starting - At ambient temperatures of: 15°C and above below 15°C Oil Inlet (continuous operation) Oil Inlet (15 min. max.) JT8D-1A, -7A 580°C 1,076°F 540°C 1,004°F 580°C 1,076°F 420°C 350°C 120°C 157°C JT8D-1B, -7B 590°C 1,094°F 545°C 1,013°F 590°C 1,094°F 788°F 662°F 248°F 315°F P&W JT8D-5 Static Thrust, S.L. Take-off (5 min.) (Flat Rated to 90°F) Maximum Continuous (Std. Day) 12,250 lb 12,250 lb Maximum permissible engine rotor operating speeds: N1 (Low Compressor) N2 (High Compressor) 8,500 rpm (98.9%) 12,100 rpm (98.8%) Maximum permissible temperatures: Turbine exhaust gas Take-off (5 min.) Maximum Continuous Maximum Acceleration Starting - At ambient temperatures of: 15°C and above below 15°C Oil Inlet (continuous operation) Oil Inlet (15 min. max.) 555°C 535°C 555°C 1031°F 995°F 1031°F 420°C 350°C 120°C 157°C 788°F 662°F 248°F 315°F A6WE 4 I - Models DC-9-11, -12, -13, -14, -15 APU Limits (if installed) AiResearch GTCP85-98D or -98W Maximum permissible EGT temperatures: Starting (30 seconds) Idle (no load)(continuous) Maximum load (continuous) Transient overload Maximum rotor speed - all conditions 760°C --710°C 732°C 1398°F ---1270°F 1350°F 110% GTCP85-98DC[A], 98DC[B], or 98DC[C] 760°C --677°C 710°C 1398°F ---1251°F 1270°F 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') VA (Maneuvering - S.L.) VA (Maneuvering - 35,000') (See AFM for variation in VA speed vs. alt.) VFE (Flaps down 0° to 10°) (Flaps down 10° to 20°) (Flaps down 20° to 30°) (Flaps down 30° to 50°) VLO (Landing gear operation) VLE (Landing gear extended) VLO (Landing gear operation) (Gear retraction) (Gear extension) VLE (Landing gear extended) V (Landing light extension) M=0.84 220K 249K 280K 240K 210K 180K 215K 215K M=0.57 M=0.57 M=0.57 M=0.57 M=0.51 M=0.51 250K (1) M=0.70 300K (1) M=0.70 300K (1) M=0.70 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 44,000 77,000 78,000 79,000 81,000 81,700 87,000 90,700 91,500 Forward Aft Forward Aft 569.4 -569.4 --570.4 571.3 604.6 604.6 -601.7 598.9 --585.2 584.1 566.3 -567.7 ---569.8 569.8 604.6 --604.6 601.7 --588.0 571.3 Fuel Capacity #1 and #2 Main Tank Center Wing Tank Fwd. Range (cont’d) (1) Straight line variation between weights shown. Maximum Weights Taxi and Ramp Start of Take-off Zero Fuel Landing 91. -15 (cont’d) C.G. 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.0 lb each 9. Fuselage Tank (780 gal. Loading lb in.75 lb each H-Arm Sta. (4) Dump system not required (See exemption under Certification Basis).0 856.8 421.) (1) Total 9947 lb each 6518 lb 5543 lb 7109 lb Usable 9892 lb each 6442 lb 5538 lb 7100 lb H-Arm Sta.5 (1) Eligible for installation in Model DC-9-15 airplane (S/N 47151) only.500 lb (1)(2) 90. -14. . limits.0 811. (See NOTE 1(c) for system fuel. Minimum Crew For all flights: Pilot and Copilot.300 lb (3) All weight above this value must be fuel in main tanks. Landing gear retraction moment is -38. -13. Maximum Passengers See NOTES 6 and 8. 771. Fuselage Tank (DC-9-15) 218-373 3900(1) 150 646-817 (no cargo) --- H-Arm Sta.8 --- Above values satisfactory for a maximum of 5 abreast seating and a minimum seat spacing of 29 inches.G. NOTE 1(d) for unusable fuel.0 34.4 lb each 7.Models DC-9-11. 34. Fuel weights based upon fuel density of 7. Oil Capacity Engine Oil CSD APU (if installed) 31. Belly Aft Belly Fuselage Station Capacity (lb) Max.74 lb/gal.) (1) Aft Fuselage Tank (1000 gal.813 lb which moves C. NOTE 1(e) for fuel loading and usage procedures).700 lb (1) 20 ply rating main gear tires required for weights 85. lb/ft2 218-482.1 ----724.7 535. Belly Aft Belly Fwd.0 706. (2) Brake Assembly P/N 9560743 must be installed for weights above 86.1 lb/gal. (1) With fuselage tank empty or fueled. -12.5 5595 150 [646-715 -----715-817] 3405 150 With 1780 Gal.700 lb (1)(2)(4) 74. Maximum Baggage Compartment Fwd.G.000 lb (3) 81.9 34. (See NOTE 1(b) and (e)). the aircraft will remain within approved C.5 Oil weight based upon 7.0 27.0 --- 286. 585. forward.700 lb and above.5 A6WE I . (See NOTE 1(c) for system oil).0 352. S. -7. 47059.) (Flat Rated to 84°F) Maximum continuous (Std. 47063. Take-off (5 min. 47085.L. 45725-45730.600 rpm (100. max.1%) N2 (High Compressor) 12. 47060.500 lb 12. Models DC-9-11. -12. 47081. JT8D-11. JT8D-9. 45776. 45732. DC-9-12: S/N 47056 modified to DC-9-14 (See NOTE 11). 47309. 47048. 45841. -1B. JT8D-15. Day) 14. 47056. 47122-47127. 47064. DC-9-15: 45717-45724. -12. See Section IX. -15 (cont’d) Serial Numbers Eligible DC-9-11: None DC-9-12: None DC-9-13: None DC-9-14: 45695-45709. JT8D-1B.) 580°C 1076°F Maximum Continuous 540°C 1004°F Maximum Acceleration 580°C 1076°F Starting .Models DC-9-11. Engines 2 Pratt and Whitney Turbojet JT8D-1. 45795.600 lb Maximum permissible engine rotor operating speeds: N1 (Low compressor) 8. 47049. 4577845787. P&W JT8D-9 and JT8D-9A Static Thrust. 47100.A6WE 6 I .250 rpm (100%) Maximum permissible temperatures: Turbine exhaust gas JT8D-9 Take-off (5 min. -5. 47043. 45775. for JT8D-1. JT8D-7A. 47151. 45770. -1A. JT8D-17. Model DC-9-21. 45829-45832. 45796. JT8D-5. -15. 47033-47035. Fuel Commercial Aircraft Turbine Fuel conforming to P&W Specification 522 as revised. Engine Limits See Section I. See Section VIII. 47000-47002. 47204-47206. 45771. -13. 45738-45741. for JT8D-11 engines.Model DC-9-31 (Transport Aircraft) Approved December 19. (See NOTE 7). 45825.At ambient temperatures of: 15° and above 420°C above 15°C 350°C Oil Inlet (continuous operation) 120°C Oil Inlet (15 min. 47078. 45711-45716. -13. 45797-45799. 1966. -7A or -7B engines. 45731. JT8D-9A. or JT8D-17A (See NOTE 5 regarding intermixing of engines). JT8D-7. 45842-45844. DC-9-11: S/Ns 45728-45730 modified to DC-9-14 (See NOTE 11). -14. JT8D-7B. JT8D-15A.) 157°C JT8D-9A 590°C 1094°F 545°C 1013°F 590°C 1094°F 788°F 662°F 248°F 315°F . -14. JT8D-1A. 45742-45749. or JT8D-17A engines. 45773. Model DC-9-51 for JT8D-17. 45772. 45735-45737. II . 540') (Landing light extension) 350K 367K 235K 258K 241K 256K M=0.35. -14.84 244K (1) 260K (1) 280K M=0.S.540') (Above 15. See Section IX. GTCP85-98W.000 lb) (Maneuvering .70 280K M=0.000 lb) (Maneuvering .57 VMO/MMO (1) For airplanes with maximum takeoff gross weight 108.000 lb and up) (See AFM for variation in VA speed vs.70 M=0.23. alt) (Flaps down 0° to 10°) (Flaps down 10° to 20°) (Flaps down 20° to 25°) (Flaps down 25° to 50°) (Landing Gear operation) (Gear retraction) (Gear extension) (Landing gear extended) (Slat operation or extended) (S.000') (below 100.57 250K 300K 300K M=0.750 lb Maximum permissible engine rotor operating speeds: N1 (Low compressor) 8.) Starting Ground Inflight Oil Inlet (continuous operation) Oil Inlet (15 min.500') (Normal Operating .) (below 100. GTCP85-98DC[A]. -13.000 lb and up) (Maneuvering .L.) (Normal Operating .7 A6WE II .) (Flat Rated to 84°F) Maximum continuous (Std Day) 15.) (100.84 M=0. -15 for GTCP85-98D. Models DC-9-11. 1966 (cont’d) Engine Limits (cont’d) P&W JT8D-15 and JT8D-15A Static Thrust.35.800 rpm (102.4%) N2 (High Compressor) 12.S.250 rpm (100%) Maximum permissible temperatures: Turbine exhaust gas Take-off (5 min.57 M=0. S.) Maximum Continuous Maximum Acceleration (2 min.) APU Limits (If installed) 620°C 580°C 630°C 1148°F 1076°F 1166°F 550°C 620°C 1022°F 1148°F 130°C 165°C 266°F 329°F See Section I. See Section XII.000') (100. Take-off (5 min.57 M=0.L. Model DC-9-81 for GTCP85-98DHF.000 lb .57 M=0.L.L. -12.Model DC-9-31 (Transport Aircraft) Approved December 19.57 240K 210K 180K M=0.70 M=0. Airspeed Limits (CAS) VMO VMO VMO VA VFE VLO VLE V (Normal Operating .500 to 35. Model DC-9-51 for GTCP85-98DCK. to 15.S.000') (Maneuvering . max.500 lb 13.23.L.-98DC[B] and -98DC[C]. forward.000 lb(3) (1) All weight above this value must be fuel in main tanks.8 @ 108. (See NOTE 1(b) and (e)).0 664.G.6 671.3 689.000 lb 109.2 667. Minimum Crew For all flights: Pilot and Copilot.3 669.000 lb and 697.000 lb when tires are installed in accordance with (3) above.1 @ 105.6 @ 109. 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.000 lb and 671.000 lb (2)(3) 87.G.000 lb (1) 99. Maximum Weights Taxi and Ramp Start of Take-off Zero Fuel Landing 106.5 692.000 99. 45834.G.000 104.400 693. (3) Airplanes with ramp weight greater than 104.000 lb(3) 108.7 -693.7 702. (5) Aft C.0 (4) 672.6 (5) 662.6 -667.2 667. (4) Forward C.2 -670.900 in lb which moves C.7 709.7 709. 47003.8 672.000 Forward Aft 667. Range For Maximum Ramp Weight of 106.0 Forward Aft 669.1 (5) 687.000 94.000 89. 45734.000 108.000 Forward Aft Forward Aft 667.000 94.000 lb must use 10 ply nose tires and 24 ply main tires.000 89. .7 -- 709.5 -- For Maximum Ramp Weight of 109. 47007.7 709. limits may be extended to 671. limits may be extended to 698. (2) Maximum for Airplane Serial Numbers 45733.000 lb when tires are installed in accordance with (3) above.400 105.7 (4) 709. Maximum Passengers See NOTES 6 and 8.G.000 89.000 106.3 689.000 lb (2)(3) 105.1 (5) -- (1) Straight line variation between weights shown. When the aircraft is loaded within the above limits and the effect of landing gear retraction. Landing gear retraction moment is -48. Additional fuel may be added to the center wing tank when the main tanks are full to attain max.0 -- 52.000 pounds.2 -669. 45833. 47004.000 104. 1966 (cont’d) C. the aircraft will remain within the approved C.A6WE 8 II . (3) Seven (7) rotor disk brakes required for weights over 103. ramp weights.4 @ 106.000 94.000 lb (2) (3) LANDING GEAR EXTENDED (1) LANDING GEAR RETRACTED (1) Gross Weight Pounds 52.7 702.000 lb not approved for operations with low pressure tires.7 -709.8 672.000 109.G.Model DC-9-31 (Transport Aircraft) Approved December 19. (2) Airplanes with ramp weight greater than 104.7 709.1 709.000 lb (2) (3) LANDING GEAR EXTENDED (1) LANDING GEAR RETRACTED (1) Gross Weight Pounds 52. limits. 48138-48147.1 lb/gal. 47720.4 lb each 7. (See NOTE 1(c) for system oil). 47214-47217.6 649. 47450. 47491. 47082. 47351 and 47352 were DC-9-32 modified to DC-931 (See NOTE 11). 47134-47146.9 A6WE II . 48154-48159. 48154-48159. JT8D-7A. 47026. 47083. 47264. 1967. 47399-47406. JT8D-9A. 47280. 47042. 47157-47167. 47150. 47050-47054. 47351. 47439-47441. 47057. Fuel Capacity Total 9893 lb each 6518 lb #1 and #2 Main Tank Center Wing Tank Usable 9838 lb each 6442 lb H-Arm Sta. 47026.0 lb each 9. 47362. 47023. 47588-47590. 47068. 47325-47338. 1966 (cont’d) Maximum Baggage Compartment Fwd. JT8D-5. 47487. 47181-47189. 48131. 47036. 47343-47347. 48114-48120.4 Above values satisfactory for a maximum of 5 abreast seating and a minimum seat spacing of 29 inches. 47490. JT8D-9. 47501. Engines 2 Pratt and Whitney Turbojet JT8D-1. Belly Aft Belly Fuselage Station [218-370 370-596] [760-897 897-996] Capacity (lb) Max. 4752647528. 47207-47212. 45846. 47638. 47649. 48114-48120. DC-9-31. 47130. 47072-47075. Fuel Commercial Aircraft Turbine Fuel conforming to P&W Specification 522 as revised. The following serial numbered airplanes demonstrated compliance at time of delivery with FAR 36 dated December 1. 48138-48147. 47202. 47505-47508. 47020. JT8D-15 or JT8D-17 (See NOTE 5 regarding intermixing of engines). S/N 45846. 47352. (See NOTE 7).Model DC-9-15F (Transport Aircraft) Approved March 1. 47316. lb/ft2 8430 150 4995 150 26 34 34 18 H-Arm Sta. 45833-45840. 47267-47272. 47566. (See NOTE 1(c) for system fuel.Model DC-9-31 (Transport Aircraft) approved December 19. III . 47429.8 Fuel weights based upon fuel density of 7.9 868. 47647. 47664. JT8D-1A. and 47727 modified to DC-9-32 (See NOTE 11). 45863-45876. 47393. JT8D-7. 47023. 47119-47121. 47412. 47203. 47263. 47564. 47382. NOTE 1(e) for fuel loading and usage procedures). 47058. Loading lb in. 47574. JT8D-11. 47389-47391. 1969 and Amendments 36-1 and 36-2: 47589. 48131. Serial Numbers Eligible 45733. 4741547421. JT8D-1B.0 990. 950. 47572. 47003-47009. 408. 47576.5 Oil weight based upon 7. S/N 47442. 47547-47552. 47573.74 lb/gal. . T8D7B. 47095-47099. 45734. 47310. 47517. 47583. 699. NOTE 1(d) for usable fuel. 47065-47068. 47171. 47244-47256. 47315. 47721. Oil Capacity Engine Oil CSD APU (if installed) 31. 47020. 47593. 47149. 47369-47375. 47411.0 1035.75 lb each H-Arm Sta. 6 601.3 571.0 H-Arm Sta. Model DC-9-51 for JT8D-17 engines. III .1 Forward 566. Maximum Passengers See NOTES 6 and 8.500 lb (1) 90. See Section XII. (See NOTE 1(b) and (e)).9 585. See Section VIII. Model DC-9-81 for GTCP85-98DHF.G.700 lb (1) (3) 74.2 584. limits. Range LANDING GEAR EXTENDED (1) LANDING GEAR RETRACTED (1) Gross Weight Pounds 44. -12. -14. -13.4 571. -7A. Model DC-9-31 for JT8D-9.0 (1) Straight line variation between weights shown. C.G. -15 for GTCP85-98D. -1A. fwd.5 [646-718 718-817] 5595 ---3405 Max. See Section II.7 569. and -15 for JT8D-1.813 in. Maximum Weights Taxi and Ramp Start of Takeoff Zero Fuel Landing 91. -12. Minimum Crew For all flights: Pilot and Copilot.-98DC[B] and -98DC[C]. Model DC-9-51 for GTCP85-98DCK.5 Aft 604. 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. -1B. (3) Dump system not required (See exemption under Certification Basis).6 604. Airspeed Limits See Section I.3 --567.700 lb (1) With 20 ply rating main gear tires.0 --34.7 Aft 604. -9A or -15 engines. Loading lb in.0 150 27.000 79.7 598. Maximum Baggage Compartment Fwd.000 lb (2) 81. 1967 (cont’d) .700 91. Belly Aft Belly Fuselage Station Capacity (lb) 218-482.9 Above values satisfactory for a maximum of 5 abreast seating and a minimum seat spacing of 29 inches when operating as a passenger airplane. -13. the aircraft will remain within approved C. -14.G. 352. -14. 1967 (cont’d) Engine Limits See Section I. See Section IX.Model DC-9-15F (Transport Aircraft) Approved March 1. Model DC-9-11. Models DC-9-11. Moves C. -5.6 -604.000 81. APU Limits (if installed) See Section I. Models DC-9-11. or -7B engines.000 77. GTCP85-98DC[A].500 Forward 569.000 90. -12.A6WE 10 III . Approved March 1. GTCP85-98W.Model DC-9-15F (Transport Aircraft). Model DC-9-21 for JT8D-11 engines.1 ----724. lb/ft2 150 34.4 --569. and -15. (2) All weight above this value must be fuel in main tanks. Landing gear retraction moment is 38.7 588. See Section IX.6 601. -7. -13.-lb. -98DC[B] and -98DC[C]. alt) (Flaps down 0° to 10°) (Flaps down 10° to 20°) (Flaps down 20° to 25°) (Flaps down 25° to 50°) 350K 350K M=0. Model DC-9-51 for JT8D-17. -14. See Section VIII. (See NOTE 7) Engine Limits See Section I.000') (Maneuvering . 47055. Model DC-9-31 for JT8D-9. 47240. -7. Models DC-9-11. JT8D-1B.000 lb) (See AFM for variation in VA speed vs.57 M=0. JT8D-5. IV . -12. 47045. JT8D-15A.850 to 35.000 lb) (Maneuvering . See Section II. -12.L.25. -9A. Models DC-9-11.000 lb) (Maneuvering .S.4 lb each 7. 47044. See Section XII.74 lb/gal. -15. GTCP85-98W. Engines 2 Pratt and Whitney Turbojet JT8D-1. Oil Capacity Engine Oil CSD APU (if installed) 31. JT8D-11. 47086. Model DC-9-51 for GTCP85-98DCK.0 856.) (below 100. JT8D-7.57 M=0. APU Limits (if installed) See Section I. Model DC-9-81 for GTCP85-98DHF.0 811. GTCP85-98DC[A].L.Model DC-9-32 (Transport Aircraft). -1A.0 lb each 9.) (Normal Operating .000') (above 108. 47087. Fuel Capacity See Section I.75 lb each H-Arm Sta. or JT8D-17A (See NOTE 5 regarding intermixing of engines).57 M=0. See Section IX. See Section IX. -15 for JT8D-1. Fuel Commercial Aircraft Turbine Fuel conforming to P&W Specification 522 as revised. -12.35. 771.000 to 108.25. Approved March 1.S. Serial Numbers Eligible 45826.S.850') (Normal Operating . 47062. and -15. -1B. JT8D-7A. -13. 4715247156.57 .4K 262.S. 47061.L.000') (below 100. JT8D-9A.84 235K 257K 245K 250. -13. 47010-47018. -5. JT8D-17.) (above 108. 1967.11 A6WE 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). -15 for GTCP85-98D. or -17A engines.84 M=0. -13. or -7B engines. JT8D-7B.) (100.L. Airspeed Limits (CAS) VMO VMO VMO VA VFE (Normal Operating . JT8D-15. Model DC-9-21 for JT8D-11 engines.5 Oil weight based upon 7. -14. (See NOTE 1(c) for system oil).5K 280K 240K 210K 180K M=0. JT8D-1A. Models DC-9-11. -7A. -14.000 lb) (Maneuvering . JT8D-9.000 lb) (Maneuvering . 45828. or -15A engines.35. 7 -708.000 108. Approved March 1.2 -668.000 lb LANDING GEAR EXTENDED (1) LANDING GEAR RETRACTED (1) Gross Weight Pounds 58.000 lb (1) 99. Landing gear retraction moment is -48.000 109.7 689.000 111. Approved March 1. (See NOTE 1(b) and (e)).Model DC-9-32 (Transport Aircraft).6 694.540') (Landing light extension) 250K 300K 300K M=0.6 ----670. Range (Landing Gear operation) (Gear retraction) (Gear extension) (Landing gear extended) (Slat operation or extended) (S.70 M=0.000 lb (2) 92.6 -666.000 Forward 667.2 --667.9 Forward 663.540') (Above 15.70 280K M=0. the aircraft will remain within approved C.7 -709. When the aircraft is loaded within the above limits and the effect of landing gear retraction.000 lb (2) 89.7 -709.6 Forward 663.7 708.8 (1) Straight line variation between weights shown.000 lb (2) 92.G.000 lb ALTERNATE CONFIGURATION (3) 111.7 -709.900 in-lb which moves C.1 687.7 -709. 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. IV . 1967 (cont’d) Airspeed Limits (CAS) (cont’d) VLO VLE V C.000 100. limits.000 lb 108.000 89. forward.000 89.000 94.000 94.57 M=0.000 lb LANDING GEAR EXTENDED (1) LANDING GEAR RETRACTED (1) Gross Weight Pounds 58.000 Forward 667.3 664.2 697. 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.000 110.200 109.9 Aft 709.2 667. ramp weight.000 lb 110.6 694.2 --672.000 96.G.57 VMO/MMO For Maximum Ramp Weight of 109.70 M=0. Maximum Weights Taxi and Ramp Start of Takeoff Zero Fuel Landing 109.8 Aft 709.3 664.3 Aft 709.7 689.L. to 15.000 lb (1) All weight above this value must be fuel in main tanks.9 668.A6WE 12 IV .Model DC-9-32 (Transport Aircraft).8 691.000 lb (5) VC-9C (4) 111.G.5 672.000 lb (1) 99.2 697.1 For Maximum Ramp Weight of 111. 1967 (cont’d) . (2) Dump system not required (See exemption under Certification Basis).000 lb 110.000 lb (1) 102.7 Aft 709. Belly Aft Belly [218-370 370-487] [881-897 897-996] (2) 150 (3) 150 26 34 24 18 150 150 27. 347. 408. .3 946.9 361. (2) With 780 gal fwd fuselage tank. (3) With 1000 gal aft fuselage tank. 2106 lb with fuselage tank empty and 2025 lb with fuselage tank fueled. (1) With 580 gal fwd fuselage tank.8 314.000 lb maximum ramp weight has a minimum seat spacing of 31 inches). Belly Aft Belly Fuselage Station [218-370 370-596] [218-370 370-511] [760-897 897-996] Capacity (lb) Max. Loading lb in.000 lb maximum ramp weight only) Fuselage Capacity Max. (4) With 1250 gal fwd fuselage tank (and 1000 gal aft fuselage tank). Belly Fwd. 2700 lb with aft fuselage tank empty or fueled. Fuselage Tank (VC-9C Only) Fwd. 7215 lb with fuselage tank empty and 6330 lb with fuselage tank fueled (up to full). (5) With 1000 gal aft fuselage tank (and 1250 gal fwd.13 A6WE Maximum Weights (cont’d) (3) Passenger seating limited to 5 abreast between stations 222 and 935 with a minimum spacing of 31 inches. Loading Compartment Station (lb) lb in.000 lb maximum ramp weight with 2250 gallon fuselage tank installation has a minimum seat spacing of 36 inches.2 Above values satisfactory for a maximum of 5 abreast seating and a minimum seat spacing of 29 inches (alternate configuration of 111. Belly [218-432] (4) Aft Belly [882-996] (5) H-Arm Sta. fuselage tank). Maximum Passengers See NOTES 6 and 8. Maximum Baggage Compartment Fwd. fuselage tank empty or fueled. lb/ft2 8430 150 (1) 150 4995 150 26 34 24. lb/ft2 Fwd. (4) Passenger seating limited to 5 abreast between stations 213 and 857 with minimum seat spacing of 36 inches (for VC-9C).85 23. Alternate configuration of 111. 5960 lb with fwd. Minimum Crew For all flights: Pilot and copilot.70 With 2250 Gal.5 868. Fuselage Tank (108.2 34 34 18 With 1780 Gal. (5) See NOTE 3 for nose landing gear component safe life limits. 6655 lb with fuselage tank empty and 5760 lb with fuselage tank fueled.4 H-Arm Sta.6 938. 47671. 47744. 47131-47133.Model DC-9-32 (Transport Aircraft). Serial Numbers Eligible 45710. 48150. 47797-47799. 47664. 47607. 47273-47278. 45847. and 47639 modified with STCs SA2541SO.74 lb/gal. 47484-47486. and SA2446SO: (See NOTE 26 for special instructions) . 47601. 48125-48130. 47595. The following serial numbered airplanes demonstrated compliance at time of delivery with FAR 36 dated December 1. 47741. 47514. 47666-47675. 47129. 47609. 47531-47535. 47353. 47442-47447. 48111-48113. 47727. 47734. 47364. 48132-48133. 47621. 47222-47239. 47664. (See NOTE 1(c) for system oil).0 820. 47744. Fuselage Tank (580 gal) or Fwd. 47600-47602. 47023. 47516. 47317-47324. 47579. Fuselage Tank (780 gal) * Aft Fuselage Tank (1000 gal) * Fwd.A6WE 14 IV . 48133. 47339-47342. DC-9-32. 47079.0 990. 47195-47201. 47592. NOTE 1(d) for usable fuel.0 535. 950. 47368. 45788-45793. 47289. 47243. 47502-47504. 47669. 4751847525. 47546.8 547. 47450-47461. 47598. 47021. 45774. 47037-47039. 47422-47427. 47647-47650. 47477-47482. 47027-47032. 47611. SA2542SO. 47670. 47788-47795. 47281-47285. 47653. 47392. 47394. 47118. 47348-47350. 47607. 47765. 47213. 48111-48113. 47472-47474. 47101-47113. 47598. 47354. 47450. 47365. 4731147314. 47529. STC Note S/N 47431. 1969 and Amendments 36-1 and 36-2. 47397. 47653. 47190. 47602. 47572. 47701. Approved March 1. 47667. 47720-47723. 48125-48130. 47218. 47797-47799. 47463. 47680. 47730. 47376-47381.75 lb each H-Arm Sta. and 47727 were DC-9-31 modified to DC-9-32 (See NOTE 11). 47500. S/N 45846. 47077. 47609. 47046. 48151. 47678. 47356-47359. 47566. Oil Capacity Engine Oil CSD APU (if installed) 31. 47474. 47026. 47559-47563. 47622. 47351 and 47352 modified to DC-9-31 (See NOTE 11). 47730. 48151. 48150. 47430-47438.0 1035. 47621.5 507. 47666. 47539. 47566-47573. DC-9-32 (VC-9C) 47668. 47647. 47172-47177. 47477. 47128. 47592. 47622. 47022. 47488. 47019. 47701. 47727.1 lb/gal. 47219. 47080. 47168-47170. 47672-47675. 47635-47645. 47720-47723. 47765. S/N 47442. 47582. 47292-47294. 47386. 47573. 47489. 47084.5 Oil weight based upon 7. 45827. 47025. 47680. 47720. 47635-47645. 4725747262. 47594. 699. (See NOTE 1(c) for system fuel. 47068. 47740. 1967 (cont’d) Fuel Capacity #1 and #2 Main Tank Center Wing Tank Fwd. 47383. 47638. 45845. 47265. 47542-47544. 47069-47071. 47024. 47788-47795. 47678. 47575. 47076. 47047. 47266. 47594. 47020. 47611. 47734. 47290. 47721. 47649. Fuselage Tank (1250 gal)* * (if installed) Total 9893 lb each 6518 lb 4122 lb 5543 lb 7109 lb 8903 lb Usable 9838 lb ea 6442 lb 4118 lb 5538 lb 7100 lb 8875 lb H-Arm Sta.0 lb each 9.7 Fuel weights based upon fuel density of 7. 47664. 47088-47094.4 lb each 7. 47466. 47740.6 649. 47468-47470. 47385. 47647-47650. 47591. 47553-47557. NOTE 1(e) for fuel loading and usage procedures). 48132. 47741. 000 Forward 667.G.3 664. -1B.2 -671. Fuel Commercial Aircraft Turbine Fuel conforming to P&W Specification 522 as revised.7 -709. -7. -7A. -12.3 664. -15 for JT8D-1. APU Limits (if installed) See Section I. -9A.-98DC[B] and -98DC[C]. JT8D-1A. See Section XII. -5. Models DC-9-11. -15 for GTCP85-98D.7 -709.2 697. Airspeed Limits (1) For Model DC-9-32F (All-passenger and All-cargo configurations.Model DC-9-32F (Transport Aircraft). JT8D-7A. (C-9A Aeromed configuration) LANDING GEAR EXTENDED (1) LANDING GEAR RETRACTED (1) Gross Weight Pounds 58.000 96. Model DC-9-51 for GTCP85-98DCK.8 672. C. Approved October 4. Model DC-9-51 for JT8D-17. See Section II. 1967 (cont’d).5 672. Model DC-9-21 for JT8D-11 engines.15 A6WE V .1 Aft 709. Approved October 4. See Section IX. Model DC-9-81 for GTCP85-98DHF.6 694. or -7B engines. See Airspeed Limits as specified for Model DC9-31. (C-9A.000 Forward 667.6 ---669. and DC-9-32F (C9B)).7 -708. JT8D-15. JT8D-9A. Engine Limits See Section I. -12. JT8D-15A. See NOTE 10 Regarding Certification). See Section IX. See Section VIII.2 --667.8 Aft 709.7 -709. JT8D-11.000 109. -13.7 -709.200 109.9 Forward 663.3 -- Aft 709. Range: For Model DC-9-32F All passenger configuration. -1A.000 96. Passenger/Cargo passenger/cargo configuration and C-9B configuration.000 100.7 V .200 108. C-9B.7 -708. JT8D-17 or JT8D-17A.6 694. (2) For Model DC-9-32F (C-9A Aeromed).2 697. all-cargo configuration.7 -708. Aft 709.000 94. or -17A engines. Engines 2 Pratt and Whitney Turbojet JT8D-1.000 89.000 110. Models DC-9-11. (See NOTE 7).000 100. (See NOTE 5 regarding intermixing of engines). or -15A engines.2 698.000 111. see Airspeed Limits as specified for Model DC-9-32. -15.6 ----670.2 698.8 691.2 --672. 1967. JT8D-1B. GTCP85-98DC[A].000 94. JT8D-7B. -14.6 Forward 663. JT8D-9. -13.000 89.8 . JT8D-5.8 697.7 -708. Model DC-9-31 for JT8D-9.Model DC-9-32F (Transport Aircraft). JT8D-7. LANDING GEAR EXTENDED (1) LANDING GEAR RETRACTED (1) Gross Weight Pounds 58.2 --667.8 -- For Model DC-9-32F. -14. GTCP85-98W. 000 lb (2) 92. 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.5 868.000 lb (1) All weight above this value must be fuel in main tanks.G. Maximum Baggage Compartment Fwd. 7215 lb with fuselage tank empty and 6330 lb with fuselage tank fueled (up to full).000 lb (2) 96. limits. Fuselage Tank (C-9A only) Fwd. [(SEE NOTE 1(b) and (e)] Maximum Weights Taxi and Ramp Start of Takeoff Zero Fuel Landing DC-9-32F All Passenger. (3) With 1000 gal aft fuselage tank.70 314. (2) With 780 gal fwd fuselage tank 7680 lb with fuselage tank empty and 5760 lb with fuselage tank fueled.A6WE 16 (1) Straight line variation between weights shown. the aircraft will remain within approved C. Maximum Passengers SEE NOTES 6 and 8. Belly Aft Belly [218-370 370-596] [218-370 370-596] [760-897 897-996] Capacity (lb) 408. 108. All Cargo 111. 2700 lb with fuselage tank empty and 2025 lb with fuselage tank fueled.000 lb. Pilot and Copilot. (2) Dump system not required (see exemption under Certification Basis). Landing gear retraction moment is -48. Belly [218-370 370-487] (2) Aft Belly [897-996] (3) 150 150 26 34 18 347.000 lb (2) 90.900 inlb which moves C. (1) With 580 gal fwd fuselage tank.8 With 2250 Gal. 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.2 34 34 18 With 1780 Gal.000 lb 110. Loading lb in. (3) See NOTE 3 for nose landing gear component safe-life limits. forward.G. lb/ft2 H-Arm Sta.9 361.2 Fwd.85 23.000 lb 110. .000 lb (3) C-9B C-9A 111. and the fuel is loaded (up to the maximum takeoff weight) and used in the approved sequence.6 938.000 lb (1) 102.4 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). Belly Fuselage Station Max. 8430 150 (1) 150 4995 150 26 34 24. Minimum Crew For all flights. Belly [218-432] (4) Aft Belly [882-996] (5) 150 150 27. Fuselage Tank (C-9B only) Fwd.3 946.000 lb (1) 99.000 lb (3) 109.000 lb (1) 99. ramp weight. or -7B engines. JT8D-15A. 47495. 47581. 47448.75 lb each H-Arm Sta. 47684. VI . 48165. Models DC-9-11. 47540. 699. 2700 lb with fwd. 47147.Model DC-9-32F (Transport Aircraft). 47691. fwd. 47242. (See NOTE 1(c) for system oil). 48165. 47584-47587. or JT8D-17A (See NOTE 5 regarding intermixing of engines).0 lb each 9. 47449. VI . DC-9-32F (C-9A) 47241. 47148. Engines 2 Pratt and Whitney Turbojet JT8D-9. -14. JT8D-9A. 1968. 47536-47538. 47580. Fuselage Tank (1250 gal)* * (if installed) Total 9893 lb each 6518 lb 4122 lb 5543 lb 7109 lb 8903 lb Usable 9838 lb each 6442 lb 4118 lb 5538 lb 7100 lb 8875 lb H-Arm Sta. (4) With 1250 gal fwd fuselage tank (and 1000 gal. 47687. 1967 (cont’d). -7A.17 A6WE V . Fuselage Tank (780 gal) * Aft Fuselage Tank (1000 gal) * Fwd.5 Oil weight based upon 7. 1968 (cont’d) . -15 for JT8D-1.4 lb each 7. (5) With 1000 gal aft fuselage tank (and 1250 gal. 47578.0 990. 5960 lb with fwd. 47684. Engine Limits See Section I. -13. JT8D-15. Approved February 21. Serial Numbers Eligible DC-9-32F 47040. 47220. JT8D-17.Model DC-9-41 (Transport Aircraft). -1A. 47687. JT8D-11.8 547.74 lb/gal. -9A. 48137. 47471. NOTE 1(e) for fuel loading and usage procedures). Fuel Capacity #1 and #2 Main Tank Center Wing Tank Fwd. -15. 950. See Section II. 47467. fuselage tank empty or fueled.0 820. Fuselage Tank (580 gal) or Fwd. 47366. 47295. 48166. For additional information concerning loading limitations when operation as passenger airplane as well as where operating as a cargo or combination passenger/cargo airplanes. 1969 and Amendments 36-1 and 36-2: 47681. 48166. See Section VIII. 4769847700.6 649. fuselage tank empty or fueled. 47681. 47355. 47367. Oil Capacity Engine Oil CSD APU (if installed) 31. Model DC-9-31 for JT8D-9. Approved October 4. 47541. Fuel Commercial Aircraft Turbine Fuel conforming to P&W specification 522 as revised (See NOTE 7). or -15A engines. fuselage tank).1 lb/gal. (See NOTE 1(c) for system fuel. 48137. 47690. 47221. 47297-47300. -7. 47690. DC-9-32F (C-9B) 47577. -5. aft fuselage tank). see NOTE 1 (a). NOTE 1(d) for usable fuel. The following serial numbered airplanes demonstrated compliance at time of delivery with FAR 36 dated December 1. 47691. 47041.Model DC-9-41 (Transport Aircraft). Model DC-9-21 for JT8D-11 engines.0 1035.5 507.0 535. -1B. 47698-47700. Approved February 21. -12. 47475.7 Fuel weights based upon fuel density of 7. lb/ft2 H-Arm Sta.8 (2) Forward 699. VI . Model DC-9-51 for JT8D-17.G. Models DC-9-11. the aircraft will remain within approved C. limits. Model DC-9-81 for GTCP85-98DHF.2 (2) 729.2 701. See Section IX.882 in-lb which moves C.6 -749. -15 for GTCP85-98D.000 lb (1) All weight above this value must be fuel in main tanks. Belly Fuselage Station Capacity (lb) Max. forward.000 107. Loading lb in. Landing Gear Retraction Moment is 53.2 Aft Belly [798-973 34 973-1072] 5925 150 18 924.0 737.G. (2) Dump system not required (see exemption under Certification Basis).2 Fwd.000 Forward 703. Minimum Crew For all flights.8 --705.4 Above values satisfactory for a maximum of 5 abreast seating and a minimum seat spacing of 29 inches. GTCP85-98W.000 (2) 114.4 115.6 -749.6 (2) 731.4 --703.G. Belly [218-370 24 370-549] (1) 150 34 382. ramp weight. See Section XII. Maximum Passengers SEE NOTES 6 and 8. C. [218-370 26 370-634] 370-350 150 34 429.6 (2) 731. Approved February 21. Model DC-9-51 for GTCP85-98DCK.000 lb (2) 96. Airspeed Limits See Section VII. GTCP85-98DC[A].000 705.000 lb 114.000 105.0 739. Pilot and Copilot. See Section I. Range LANDING GEAR EXTENDED (1) LANDING GEAR RETRACTED (1) Gross Weight Pounds 50. 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.-98DC[B] and -98DC[C]. -14.2 (1) Straight line variation between weights shown. (See NOTES 1(b) and (e)). Maximum Baggage Compartment Fwd.6 749.G. Maximum weights Taxi and Ramp Start of Takeoff Zero Fuel Landing 115.Model DC-9-41 (Transport Aircraft). -12. 1968 (cont’d) .8 703. -13.3 Aft 749.0 739.A6WE 18 Engine Limits (cont’d) APU Limits (if installed) See Section IX.4 Aft 749. Model DC-9-33F.000 97. Range: C. 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. or -17A engines. fuselage tanks. (2) For airplanes with 1360 gal.000 lb (1) 102.6 749. Fuselage Tank (C-9B only) Fwd.5 Oil weight based upon 7. 47725. Serial Numbers Eligible 47114-47117.6 687.74 lb/gal. NOTE 1(e) for fuel loading and usage procedures). 47777-47781. 47603-47606. (See NOTE 1(c) for system fuel.9 Fuel weights based upon fuel density of 7. 47612-47620. 950. 47612-47620.0 1035. 47623-47634. 47747.0 990. 47610.0 845. 47750. 47395. 47608.0 314. 47766-47768. (See NOTE 1(c) for system oil). NOTE 1(d) for usable fuel. 47759-47762.7 30. 47748. 382. 47599.1 lb/gal. Belly [218-432] (4) Aft Belly [882-996] (5) Max. 47596.8 585. 47464.70 H-Arm Sta. 47603-47606. and Amendments 36-1 and 36-2. 47646. Fuel Capacity #1 and #2 Main Tank Center Wing Tank Fwd. 47766-47768.2 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. 47492-47494. 47178-47180. The following serial numbered airplanes demonstrated compliance at time of delivery with FAR 36 dated December 1.0 lb each 9. 47596. (1) With 580 gal. aft fuselage tank. 1969. 47286-47288. 737.18 150 26. 47509-47513. 47623-47634. 47646. lb/ft2 24.6 938. 47747.89 150 17. 47759-47762.58 150 150 27. 47599. 47748. 47608. Belly Aft Belly [218-370 370-549] [894-973 973-1072] A6WE Capacity (lb) (1) (2) With 2250 Gal.2 976.19 Maximum Baggage With 1360 Gal.4 lb each 7. 4749747499. . Oil Capacity Engine Oil CSD APU (if installed) 31. 4777747781. 47396. Fuselage Tank Fuselage Compartment Station Fwd.85 23. 47725. 47610. 47597. 47597. Fuselage Tank (580 gal) or Aft Fuselage Tank (780 gal) * * (if installed) Total 9893 lb each 6518 lb 4122 lb 5543 lb Usable 9838 lb each 6442 lb 4118 lb 5538 lb H-Arm Sta.75 lb each H-Arm Sta. 47750. Loading lb in. 5925 lb with fuselage tank empty and 3570 lb with fuselage tank fueled (up to full). 70 (Gear extension) 300K M=0.000 lb) (Flaps down 0° to 10°) 280K M=0.57 (Flaps down 25° to 50°) 190K M=0.000 lb & 114.S. JT8D-15.Model DC-9-33F (Transport Aircraft). Model DC-9-31 for JT8D-9.) 340K (Normal Operating .L. Model DC-9-81 for GTCP85-98DHF.000 lb) 267K (See AFM for variation in VA speed vs. JT8D-9A. JT8D-7B. -1B. -14.7 -709. JT8D-7A. Model DC-9-51 for JT8D-17. See Section XII.9 Aft 709. to 15. 1968.700 114. Fuel Commercial Aircraft Turbine Fuel Conforming to P&W Specification 522 as revised.000 Forward 667.000 89.8 664. JT8D-9. -7A.A6WE 20 VII .84 (Normal Operating .3 688. -7.000 lb) 235K (Maneuvering .8 Aft 709.540') M=0. Range LANDING GEAR EXTENDED (1) LANDING GEAR RETRACTED (1) Gross Weight Pounds 52.000 94. or -15A engines. Engines 2 Pratt and Whitney Turbojet JT8D-7.S. APU Limits (if installed) See Section I. or -17A engines. See Section IX.57 (Above 15. See Section VIII. GTCP85-98DC[A].000 lb) 258K (Maneuvering . -12. See Section IX. -13.000') (below 100. -13.7 693.3 . -9A.L. -1A.2 667. or JT8D-17A (See NOTE 5 regarding intermixing of engines).2 --668.70 (Landing gear extended) 300K M=0.L.-98DC[B] and -98DC[C].70 (Landing light extension) VMO/MMO (Slat operation or extended) (S.S.260 to 35.6 --666.57 C. JT8D-17.000 115.L.000 111.35. See Section II. JT8D-15A.84 (Maneuvering .27.) (114. GTCP85-98W.G.260') 340K M=0.000') (114.57 (Flaps down 20° to 25°) 220K M=0. -12. alt) (VA speeds Linear between 100.7 705.000') M=0. -14.9 668.7 693.57 (Landing Gear operation) (Gear retraction) 250K M=0.0 Forward 662. -15 for JT8D-1. Model DC-9-21 for JT8D-11 engines.7 -709.500') 280K M=0.000 lb) 250K (Maneuvering . Airspeed Limits (CAS) VMO VMO VMO VA VFE VLO VLE V V (Normal Operating . Model DC-9-51 for GTCP85-98DCK. (See NOTE 7) Engine Limits See Section I. or -7B engines. -15.57 (Flaps down 10° to 20°) 240K M=0. JT8D-11. -5.27. Models DC-9-11.7 705. Approved April 5. Models DC-9-11. -15 for GTCP85-98D.) (below 100.35. Fuselage Tank (780 gal) * Aft Fuselage Tank (1000 gal) * Fwd. 408.7 Fuel weights based upon fuel density of 7. For additional information concerning loading limitations when operating as passenger airplane as well as when operating as a cargo or combination passenger/cargo airplane.8 547. 1968 (cont’d) . Landing gear retraction moment is -53.9 361. ramp weight. 699. Approved April 5.0 535.4 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. (See exemption under Certification Basis) For all flights.G.5 507. Belly Aft Belly Fuselage Station [218-370 370-596] [218-370 370-511] [760-897 897-996] Capacity (lb) Max. 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. lb/ft2 8430 150 (1) 150 4995 150 26 34 24.Model DC-9-33F (Transport Aircraft). Pilot and Copilot. 1968 (cont’d) C.882 in-lb which moves C. NOTE 1(d) for usable fuel.G. limits.2 34 34 18 H-Arm Sta. not to exceed their individual capacities. (1) With 580 gal fwd fuselage tank. forward.6 649.5 868.000 lb (1) 102.G. 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. Loading lb in. Fuselage Tank (580 gal) or Fwd. Belly Fwd.000 lb (1) All weight above this value must be fuel in main tanks. Fuselage Tank (1250 gal)* * (if installed) Total 9893 lb each 6518 lb 4122 lb 5543 lb 7109 lb 8903 lb Usable 9838 lb each 6442 lb 4118 lb 5538 lb 7100 lb 8875 lb H-Arm Sta. (See NOTE 1(c) for system fuel. Fuel Capacity #1 and #2 Main Tank Center Wing Tank Fwd. see NOTE 1(a).000 lb 114. (2) Minimum Crew Dump system not required. Approved April 5. Maximum Baggage Compartment Fwd.0 820.21 A6WE VII . Range (cont’d) (1) Straight line variation between weights shown. the aircraft will remain within approved C.1 lb/gal. NOTE 1(e) for fuel loading and usage procedures).000 lb (2) 96. VII .Model DC-9-33F (Transport Aircraft). Maximum weights Taxi and Ramp Start of Takeoff Zero Fuel Landing 115. Maximum Passengers SEE NOTES 6 and 8. (See NOTE 1(b) and (e)). 7215 lb with fuselage tank empty and 6330 lb with fuselage tank full. Ground Inflight 620°C 580°C 630°C 550°C 620°C 1148°F 1076°F 1166°F 1022°F 1148°F Oil Inlet (continuous operation) Oil Inlet (15 min. JT8D-9A or JT8D-11 (See NOTE 5 regarding intermixing of engines). 47413.600 rpm (100.Model DC-9-21 (Transport Aircraft). 47407-47410.L. Day) 15. Fuel: Commercial Aircraft Turbine Fuel conforming to P&W Specification 522 as revised. Serial Numbers Eligible 47191-47194.75 lb each Oil weight based upon 7. 47428. (See NOTE 1(c) for system oil).000 lb 12.) Starting .74 lb/gal. Take-off (5 min. 47363. S. 47291. Day) 15. 47465. Take-off (5 min.500 lb 13.0 lb each 9. VIII .1%) N2 (High Compressor) 12. 950.4%) N2 (High Compressor) 12. 47565. P&W JT8D-15 and JT8D-15A Static Thrust.) (Flat Rated to 84°F) Maximum continuous (Std. 1968. 47279.)(Flat Rated to 84°F) Maximum continuous (Std. 47476. (See NOTE 7).600 lb Maximum permissible engine rotor operation speeds: N1 (Low Compressor) 8.5 31.0 990. Approved November 25. 47384. Model DC-9-31 for JT8D-9 or -9A engines.A6WE 22 Oil Capacity Engine Oil CSD APU (if installed) H-Arm Sta.750 lb Maximum permissible engine rotor operating speeds: N1 (Low compressor) 8.250 rpm (100%) . Engine Limits See Section II.250 rpm (100%) Maximum permissible temperatures: Turbine exhaust gas Take-off (5 min. Engines: 2 Pratt and Whitney Turbojet JT8D-9.) Maximum Continuous Maximum Acceleration (2 min. max.4 lb each 7.) 130°C 165°C 266°F 329°F P&W JT8D-11 Static Thrust. 47496. 47545. 47414. 47462.0 1035. S. 47530.800 rpm (102.L. 1 563. limits. See Section XII. Landing gear retraction moment is 48. -13.000 95.5 561. . GTCP85-98W.5 Aft 596. -12. See Section IX. 1968 (cont’d) Engine Limits APU Limits (if installed) P&W JT8D-11 (cont’d) Maximum permissible temperatures: Turbine exhaust gas Take-off (5 min.2 562.1 ---- (1) Straight line variation between weights shown. alt) (Flaps down 0° to 10°) (Flaps down 10° to 20°) (Flaps down 20° to 25°) (Flaps down 25° to 50°) (Landing Gear operation) (Gear retraction) (Gear extension) (Landing gear extended) (Landing light extension) (Slat operation or extended) (S.57 M=0.70 300K M=0.000 101. -14.1 ---596.84 226K 263K 280K 240K 210K 180K M=0. to 15.-98DC[B] and -98DC[C].0 Aft 596.G. -15 for GTCP85-98D.) Starting .000') (See AFM for variation in VA speed vs.000 86.Model DC-9-21 (Transport Aircraft).500') (Normal Operating .1 Forward 559.L. Approved November 25.23 A6WE VIII .23.70 300K M=0.35.2 564.57 M=0.G.3 562. forward.57 M=0. GTCP85-98DC[A].540') (Above 15.Ground Inflight 595°C 550°C 595°C 510°C 550°C 1103°F 1022°F 1103°F 950°F 1022°F Oil Inlet (continuous operation) Oil Inlet Transient (15 min.70 VMO/MMO 280K M=0.G.S.000 Forward 562.57 LANDING GEAR EXTENDED (1) LANDING GEAR RETRACTED (1) Gross Weight Pounds 50.) (Normal Operating .57 M=0.84 M=0.900 in-lb which moves C.) 130°C 165°C 266°F 329°F See Section I. Model DC-9-81 for GTCP85-98DHF. 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.1 563.000') (Maneuvering .300 100.L. (See NOTE 1(b) and (e)). Airspeed Limits (CAS) VMO VMO MMO VA VA VFE VLO VLE V V (Normal Operating .L.S. the aircraft will remain within approved C.500 to 35.23. Model DC-9-51 for GTCP85-98DCK.540') C.0 560. Range 350K 367K M=0.) Maximum Continuous Maximum Acceleration (2 min. max. Models DC-9-11.57 250K M=0.) (Maneuvering . 000 lb 15.6 535.1 lb/gal.9 Above values satisfactory for a maximum of 5 abreast seating and a minimum seat spacing of 29 inches. Maximum Baggage Compartment Fuselage Station Capacity (lb) Fwd.5 Oil weight based upon 7. Oil Capacity Engine Oil CSD APU (if installed) 31. Model DC-9-31 for JT8D-15 or JT8D-15A engines. NOTE 1(d) for usable fuel. IX . Approved November 25.4%) 12.)(Flat Rated to 84°F) Maximum Continuous (Std. JT8D-15A. 352.L. Minimum Crew For all flights. P&W JT8D-17 and JT8D-17A Static Thrust. Engine Limits See Section II.Model DC-9-51 (Transport Aircraft). Approved August 11. NOTE 1(e) for fuel loading and usage procedures).800 rpm (102. lb/ft2 150 34 150 27 H-Arm Sta. Day) 16. (See NOTE 7). S. 1975.200 lb Maximum permissible engine rotor operation speeds: N1 (Low Compressor) N2 (High Compressor) 8.000 lb (1) 95.300 lb (1) All weight above this value must be fuel in main tanks.000 lb 84.250 rpm (100%) . (See NOTE 1(c) for system oil).5 646-817 7460 4540 Max. 1968 (cont’d) Maximum weights Taxi and Ramp Start of Takeoff Zero Fuel Landing 101. Take-off (5 min. 771. 47361. Belly Aft Belly 218-482.8 Fuel weights based upon fuel density of 7.75 lb each H-Arm Sta. JT8D-17A. Fuel Capacity Total 9893 lb each 6518 lb #1 and #2 Main Tank Center Wing Tank Usable 9838 lb each 6442 lb H-Arm Sta.74 lb/gal. Loading lb in.0 811. 585. 47360.4 lb each 7.0 856. JT8D-17. Maximum Passengers SEE NOTES 6 and 8. Engines 2 Pratt and Whitney Turbojet JT8D-15.000 lb 100.A6WE 24 VIII .Model DC-9-21 (Transport Aircraft).1 724.0 lb each 9. (See NOTE 1(c) for system fuel. Fuel Commercial Aircraft Turbine Fuel Conforming to P&W Specification 522 as revised. Serial Numbers Eligible 47301-47308. Pilot and Copilot. 25 A6WE IX - Model DC-9-51 (Transport Aircraft), Approved August 11, 1975 (cont’d) Engine Limits APU Limits (if installed) P&W JT8D-17 and JT8D-17A (cont’d) Maximum permissible temperatures: Turbine outlet gas Take-off (5 min.) Maximum Continuous Maximum Acceleration (2 min.) Starting - Ground Inflight 650°C 610°C 660°C 550°C 650°C 1202°F 1130°F 1220°F 1022°F 1202°F Oil Inlet (continuous operation) Oil Inlet Transient (15 min. max.) 130°C 165°C 266°F 329°F See Section I, Models DC-9-11, -12, -13, -14, -15 for GTCP85-98D, GTCP85-98W, GTCP85-98DC[A],-98DC[B] and -98DC[C]. See Section XII, Model DC-9-81 for GTCP85-98DHF. AiResearch Maximum permissible EGT temperatures: Starting (30 seconds) Idle (no load)(continuous) Maximum allowable (continuous) Maximum Rated Maximum rotor speed - all conditions Airspeed Limits (CAS) VMO VMO VMO VA VA VFE VLO VLE V V GTCP85-98DCK (Normal Operating - S.L.) (Normal Operating - 27,260') (Normal Operating - 27,260 to 35,000') (Maneuvering - S.L.) (Maneuvering - 35,000') (See AFM for variation in VA speed vs. alt) (Flaps down 0° to 10°) (Flaps down 10° to 20°) (Flaps down 20° to 25°) (Flaps down 25° to 40°) (Flaps down 40° to 50°) (Landing Gear operation) (Gear retraction) (Gear extension) (Landing gear extended) (Landing light extension) (Slat operation or extended) (S.L. to 15,540') (Above 15,540') 760°C --663°C 621°C 110% 340K 321K M=0.84 M=0.84 242K 254K 280K 240K 222K 195K 190K 250K 300K 300K 350K M=0.7 M=0.7 M=0.7 M=0.84 280K M=0.57 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 58,000 90,000 102,500 110,000 116,000 122,200 Forward 752.7 752.7 752.7 754.9 756.7 758.6 Aft 806.5 806.5 806.5 806.5 806.5 782.6 Forward 749.0 749.0 752.7 754.9 756.7 758.6 Aft 806.5 806.5 806.5 806.5 806.5 782.6 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 Start of Takeoff Zero Fuel Landing 123,200 lb 122,200 lb (2) 100,500 lb (1) 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 Maximum Passengers For all flights. Pilot and Copilot. SEE NOTES 6 and 8. Maximum Baggage Compartment Fwd. Belly Fuselage Station Capacity (lb) [218-370 370-693] [855-1068 1068-1167 -10,755 -6,855 Max. Loading lb in. lb/ft2 H-Arm Sta. 150 150 150 150 24.18 29.23 32.02 17.58 -459.5 -1001.2 With 580 gal. Fuselage Tank (1) [218-370 -370-554] 8,655 Aft Belly [851-1068 -1068-1167] 6,855 150 150 150 150 24.18 24.14 32.02 17.58 -413.9 -1001.2 With 1360 gal. Fuselage Tank (1) [218-370] -370-606] 8,655 Aft Belly [951-1068 -1068-1167] 4,500 150 150 150 150 24.18 28.14 31.45 17.58 -413.9 -1051.4 Aft Belly Fwd. Belly Fwd. Belly 27 A6WE 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 Compartment Station (lb) Fwd. Belly Aft Belly [218-370 370-582] [855-1068 1068-1167] -8,085 -6,855 With 1000 gal. Fuselage Tank (1) [218-370 370-554] 7,395 Aft Belly [835-1068 -1068-1167] 6,855 Fwd. Belly Max. Loading lb in. lb/ft2 H-Arm Sta. 150 150 150 150 24.18 27.74 32.02 17.58 -400.9 -1001.2 150 150 150 150 24.18 26.96 32.02 17.58 385.2 -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 #1 and #2 Main Tank Center Wing Tank Fus. Tank (580 gal)* Fus. Tank (780 gal)* Fus. Tank (1000 gal)* Aft Fus. Tank (780 gal)* *(if installed) Total 9893 lb each 6518 lb 4122 lb 5543 lb 7109 lb 5543 lb Usable 9838 lb each 6442 lb 4118 lb 5538 lb 7100 lb 5538 lb H-Arm Sta. 794.6 744.8 642.0 630.0 622.0 909.0 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 Engine Oil CSD APU (if installed) 31.0 lb each 9.4 lb each 7.75 lb each H-Arm Sta. 1121.0 1161.0 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, 4810748110, 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 (if installed) See Section I, Models DC-9-11, -12, -13, -14, -15 for GTCP85-98D, GTCP85-98W, 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 VMO VMO VA VV VFE VLO VLE V V (Normal Operating - S.L.) (Normal Operating - 27,260') (Normal Operating - 27,260 to 35,000') (Maneuvering - S.L.) (Maneuvering - 35,000') (See AFM for variation in VA speed vs. alt) (Flaps down 0° to 10°) (Flaps down 10° to 20°) (Flaps down 20° to 25°) (Flaps down 25° to 40°) (Flaps down 40° to 50°) (Landing Gear operation) (Gear retraction) (Gear extension) (Landing gear extended) (Landing light extension) (Slat operation or extended) (S.L. to 15,540') (Above 15,540') C.G. Range 340K 321K M=0.84 M=0.84 248.7K 254K 280K 240K 220K 195K 190K 250K 300K 300K 350K M=0.7 M=0.7 M=0.7 M=0.84 280K M=0.57 M=0.57 LANDING GEAR EXTENDED (1) LANDING GEAR RETRACTED (1) Gross Weight Pounds Up to 52,000 Up to 89,000 At 89,000 94,000 111,700 121,000 122,000 Forward 667.1 667.1 667.1 --669.0 669.2 Aft 709.6 709.6 709.6 709.6 705.6 689.7 687.9 At intermediate weights, C.G. limits vary linearly. Forward 662.7 -664.5 --667.3 Aft 709.6 709.6 709.6 709.6 705.6 689.7 5 922. 1976 (cont’d) . see NOTE 1(a). forward. Maximum weights Taxi and Ramp Start of Takeoff Zero Fuel Landing 122.58 24. 1976 (cont’d) C. 408. lb/ft2 [218-370 370-465 465-597] [856-897 897-996] 8430 2640 150 150 150 150 150 With 1360 gal. (2) Dump system not required (See exemption under Certification Basis).Model DC-9-34F (Transport Aircraft) Approved April 20. Range (cont’d) (1) Straight line variation between weights shown.9 Fuel weights based upon fuel density of 7. NOTE 1(d) for usable fuel. (See NOTE 1(c) for system fuel. NOTE 1(e) for fuel loading and usage procedures). (See NOTE 1(b) and (e)). Fuel Capacity #1 and #2 Main Tank Center Wing Tank Fwd.48 17.903 in-lb which moves C. Minimum Crew For all flights. Maximum Baggage Compartment Fwd.11 29. the aircraft will remain within approved C. Pilot and Copilot. Loading Station (lb) lb in.000 lb 121. Fuselage Tank (1) [218-370 150 370-511] 6330 150 [856-897 150 897-996] 2640 150 24 23 32 29.18 25.Model DC-9-34F (Transport Aircraft) Approved April 20.000 lb (2) 98. 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.G. 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.2 Above values satisfactory for a maximum for 5 abreast seating and a minimum seat spacing of 30 inches. limits.G. 699. Tank (780 gal) Total 9893 lb each 6518 lb 4122 lb 5543 lb Usable 9838 lb each 6442 lb 4118 lb 5538 lb H-Arm Sta.500 lb (1) 110. (1) With fuselage tank(s) empty or fueled.8 547.0 807.G. Tank (580 gal) Aft Fus.6 649. Fuselage Tank (1) Fuselage Capacity Max. ramp weight not to exceed their individual capacities.000 lb (1) All weight above this value must be fuel in main tanks.1 lb/gal. Belly Aft Belly With 780 gal.7 922 361.58 H-Arm Sta. X . Belly Aft Belly Fwd. Maximum Passengers SEE NOTES 6 and 8.29 A6WE X .48 17. For additional information concerning loading limitations when operating as a passenger airplane as well as when operating as a cargo airplane. Landing gear retraction moment is -53. or JT8D-17A (See NOTE 5 regarding intermixing of engines). 1969. Airplanes of the Model DC-9-34F issued an original U. -9A.7 M=0. Engines 2 Pratt and Whitney Turbojet JT8D-9. 47707.) (Normal Operating . XI .000') (Maneuvering . JT8D-15.75 lb each H-Arm Sta.L. 47706.74 lb/gal.7 M=0.5 Oil weight based upon 7.-98DC[B] and -98DC[C]. 47752.000') (See AFM for variation in VA speed vs. Models DC-9-11. Model DC-9-81 for GTCP85-98DHF.S. 522 as revised. JT8D-11. JT8D-17.L.540') (Above 15. Model DC-9-21 for JT8D-11 engines. (See NOTE 7).A6WE 30 Oil Capacity Engine Oil CSD APU (if installed) 31.35. 1976. Airspeed Limits (CAS) VMO VMO VMO VA VV VFE VLO VLE V V (Normal Operating . -15. Model DC-9-31 for JT8D-9.540') 340K 321K M=0.7K 254K 280K 240K 220K 195K 190K 250K 300K 300K 350K M=0.S. or 17A engines. -14.4 lb each 7. or -15A engines.0 990. Model DC-9-51 for GTCP85-98DCK. See Section XII.27. and Amendments 36-1 and 36-2. -15 for GTCP85-98D.7 M=0. Engine Limits See Section II. JT8D-15A. Serial Numbers Eligible Noise Standards 47702. to 15. See Section IX.0 lb each 9. (See NOTE 1(c) for system oil). 950. -12. See Section VIII. 47704. GTCP85-98W.0 1035.27. JT8D-9A.57 M=0.84 M=0.260 to 35. GTCP85-98DC[A]. -13. Standard Airworthiness Certificate comply with FAR part 36 dated December 1. APU Limits (if installed) See Section I.Model DC-9-34 (Transport Aircraft) Approved November 3.260') (Normal Operating .57 . See Section IX. alt) (Flaps down 0° to 10°) (Flaps down 10° to 20°) (Flaps down 20° to 25°) (Flaps down 25° to 40°) (Flaps down 40° to 50°) (Landing Gear operation) (Gear retraction) (Gear extension) (Landing gear extended) (Landing light extension) (Slat operation or extended) (S. Fuel Commercial Aircraft Turbine Fuel Conforming to P&W Specification No.L.) (Maneuvering .84 248.84 280K M=0. Model DC-9-51 for JT8D-17.S. 6 709.6 938. Belly Aft Belly Fwd.6 709.000 Up to 89.000 At 89.500 lb (1) 110.G. Loading Station (lb) lb in. Fuselage Tank (1) [218-370 150 370-432] 4470 150 [882-897 150 897-996] 2025 150 23.7 (1) Straight line variation between weights shown. Range LANDING GEAR EXTENDED (1) LANDING GEAR RETRACTED (1) Gross Weight Pounds Up to 52.1 667.6 705.6 709.3 Aft 709.6 705. 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. 361 922.7 -664.7 687.6 709. 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.700 121.2 347.06 25.000 lb (1) All weight above this value must be fuel in main tanks.5 --667.000 Forward 667.000 lb (2) 98.87 25. Maximum weights Taxi and Ramp Start of Takeoff Zero Fuel Landing 122. Belly Aft Belly With 1360 gal.31 A6WE XI .000 lb 121.0 669.2 .903 in-lb which moves C.000 111. limits. (See NOTE 1(b) and (e)).000 94. Minimum Crew Maximum Passengers For all flights.3 938.58 With 1780 gal. 1976 (cont’d) C. Fuselage Tank (1) [218-370 150 370-489] 5760 150 [882-897 150 897-996] 2025 150 23.6 709.33 17.G. SEE NOTES 6 and 8.6 689. Belly Aft Belly Fwd.58 With 2250 gal.6 709.1 667.6 689.48 17. the aircraft will remain within approved C. lb/ft2 [218-370 370-511] [856-897 897-996] 6330 2640 150 150 150 150 24.2 Aft 709. Maximum Baggage Compartment Fwd. (2) Dump system not required (See exemption under Certification Basis).58 H-Arm Sta.1 --669.9 Forward 662.11 29. Fuselage Tank (1) Fuselage Capacity Max. Pilot and Copilot.000 122.Model DC-9-34 (Transport Aircraft) Approved November 3. Landing gear retraction moment is -53.18 25.2 314.33 17.88 18. forward.88 23.G. Tank (1000) * * (if installed) Total 9893 lb each 6518 lb 4122 lb 5543 lb 5543 lb 8903 lb 7109 lb Usable 9838 lb each 6442 lb 4118 lb 5538 lb 5538 lb 8875 lb 7100 lb H-Arm Sta. 699. Noise Standards : Airplanes of the Model DC-9-34F issued an original U.700 lb . Model DC-9-82 for JT8D-217.A6WE 32 XI . Tank (580) * Aft Fus. Engine Inoperative (10 min)** JT8D-209 JT8D-219 19. Fus.000 lb 21. Power Rating Maximum Static Thrust at sea level Maximum Takeoff (5 min.500 lb 19. 48123. regarding certification) Engines 2 Pratt and Whitney Turbofan JT8D-209. 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.0 990. For additional information concerning loading limitations when operating as a passenger airplane as well as when operating as a cargo airplane. Fuel Capacity #1 and #2 Main Tank Center Wing Tank Fwd. -217C. (1) With fuselage tank(s) empty or fueled. See NOTE 14.Model DC-9-81 (Transport Aircraft) Approved August 25. -217. NOTE 1(e) for fuel loading and usage procedures).5 Oil weight based upon 7. (MD-81. Fuel Commercial aircraft turbine fuel conforming to P&W Specification 522 as revised. -217A. 1969.0 807. flat-rated to 77°F)* Maximum Takeoff.6 649. Standard Airworthiness Certificate comply with FAR part 36 dated December 1. NOTE 1(d) for usable fuel. XII . or -219. (See NOTE 5 regarding intermixing of engines). Tank (780) * Fwd. Oil P&W Turbojet Engine Service Bulletin No. -217A and -217C engines.0 507. Tank (1250) * Aft Fus.4 lb each 7.Model DC-9-34 (Transport Aircraft) Approved November 3. 950. Synthetic type oil conforming to P&W Specification 521 as revised.7 820.250 lb 18. Tank (780) * Fwd. Engine Limits See Section XIII. 48103-48106. and Amendments 36-1 and 36-2. (See NOTE 7). (See NOTE 1(c) for system fuel.1 lb/gal. 238 lists approved brand oils.8 547.75 lb each H-Arm Sta. Fus.700 lb 21. 1980.S.9 535. Oil Capacity Engine Oil CSD APU (if installed) 31. flat-rated to 84°F)* Normal Takeoff (5 min.5 Fuel weights based upon fuel density of 7.74 lb/gal.250 lb 21. Serial Numbers Eligible: 47711.0 1035. Fus. (See NOTE 1(c) for system oil). see NOTE 1(a).0 lb each 9. 48124. *** 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. 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.Model DC-9-81 (Transport Aircraft) Approved August 25.)* Normal Takeoff (5 min. Cont. a total time of Ten (10) minutes of Takeoff Thrust is required. (10 min)** Normal Takeoff (2 min.6%) 8. 1980 (cont’d) Engine Limits (cont’d) Maximum Takeoff Rating is the maximum thrust certified for takeoff operation. Maximum Continuous Rotor Speed.000 lb 18.150 rpm (99.5 5.5%) 8.370 rpm (101.900 lb 8. 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.5 .5%) 12.0 8.150 rpm (99.)* Continuous Starting Ground *** In-Flight 16. or manually by throttle movement. Cont.) Maximum Takeoff (5 min. Thrust 8.120 rpm (98.850 rpm (95.9%) 630°C (1166°F) 570°C (1058°F) 595°C (1103°F) 550°C (1022°F) 530°C (986°F) 475°C (887°F) 570°C (1058°F) 625°C (1157°F) 590°C (1094°F) 580°C (1076°F) 475°C (887°F) 625°C (1157°F) * The total time at both Takeoff Thrust Levels must not exceed 5 minutes.2%) 7.550 rpm (102.0%) 12.33 A6WE XII . Normal Takeoff Rating is the maximum thrust to be set for takeoff operation with the aircraft Automatic Reserve Thrust System (ARTS) operative.350 rpm (101.0 Above 90% Max. 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. Maximum Maximum Takeoff (2 min. Maximum N1 (Low Compressor) Takeoff Normal Takeoff N2 (High Compressor) Takeoff Normal Takeoff Exhaust Gas Temperature.350 rpm (100.2%) 12. Thrust 3. this rating ensures that the Takeoff Rating will be achieved upon actuation of ARTS.8%) 12. When set. ** In the event of an engine failure during Takeoff or Go-Around.)*. Cont.) 263K (Maneuvering .000 ft. Model DC-9-51.75 3. altitude. Minimum of 5 psi above true vapor pressure up to 40 psi.84) (M=0.-98DC[B] and -98DC[C].000') (Maneuvering . Thrust APU Limits (if installed) % Low Compressor Bleed 8th Stage Normal Maximum 4.57) (M=0.70) (M=0.000 feet APU Electrical Load must not exceed 57% of rated load above 25.30°) 200K (Flaps down 31° .51) (M=0.70) (M=0.0 4. 17. Airspeed Limits (CAS) VMO VMO VMO VA VFE V VLO VLE V (Maximum Operating .all conditions 46.) 340K (Maximum Operating .1° .57) (M=0.57) (M=0.000 Fuel Pressure Limits.51) (M=0. 21°) 240K (Autoslat Extension) 280K (Landing Gear operation) (Gear retraction) 250K (Gear extension) 300K (Landing gear extended) 300K (Landing light extension) 350K (M=0. See Section IX.240') 340K (Maximum Operating .51) (M=0. Thrust Above Max.37.L.000 (110%) Maximum allowable rotor speed 110% Maximum rated RPM .27. GTCP85-98DC[A].20°) 240K (Flaps down 20.L. Oil Capacity total 5 qts Oil Capacity usable 4 qts Oil Pressure.70) (M=0. -15 for GTCP85-98D. Cont. -13.27. Models DC-9-11.S. -14.13°) 280K (Flaps down 13.000') 262K (See AFM for variation in VA speeds vs. -12. Normal and Idle operation 95 + 5 psi Low Oil pressure (Master Caution) 45 psi Maximum Oil Temperature 255°F APU Envelope.25 See Section I.1° . GTCP85-98W. AiResearch GTCP85-98DHF Maximum permissible EGT temperatures: Starting (30 seconds) 760°C Maximum allowable (continuous) 663°C Maximum Rated 621°C Maximum rotor speed .40°) 195K (Slat Extended Takeoff. Start up to 30.84) (M=0.Model DC-9-81 (Transport Aircraft) Approved August 25. for GTCP85-98DCK.8°) 280K (Slat Extended Landing.30.57) (M=0.57) (M=0.000 feet Operate up to 35.300 to 37.) (Flaps down 0.000') 297K (Maneuvering . 1980 (cont’d) Engine Limits (cont’d) Air Bleed Extraction At and below Max.S.0 2.1° .84) .A6WE 34 XII .all conditions 42.25°) 220K (Flaps down 25.000 100% RPM 42.1° . (1) Straight line variation between weights shown. 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.35 A6WE XII .5 888.G.-lb which moves C.751 118.6 -929.5 Gross Weight Pounds Kilograms 70.000 lb (3) 142. Approved August 25.6 887. (2) Fuel jettisoning system not installed.5 -938.0 886. (3) 26 Ply rating MLG tires required for all ramp weights over 141. Gear retraction moment is -10.000 58.5 -938.000 63.245 130. limits.000 56.G. the aircraft will remain within approved C.5 881.5 929.864 LANDING GEAR RETRACTED (1) Forward Aft 881.000 64.957 142.Model DC-9-81 (Transport Aircraft).1 936. After filling the main wing tanks.5 884.0 933. Maximum weights Taxi and Ramp Start of Takeoff Zero Fuel Landing 143. .8 891.8 NOTE: Inflight weight limited to 79.154 in. additional fuel may then be added to the center wing tank to attain the maximum design taxi weight.000 64.4 928.000 53.8 929.000 lb Minimum Crew Maximum Passengers For all flights.000 lb (1) All weight in excess of 120.000 lb must be in usable fuel.410 143. Pilot and Copilot.1 938.5 890. 1980 (cont’d) C. Range LANDING GEAR EXTENDED (1) Forward Aft 884.3 936.967 140.000 63.000 pounds (35.000 lb (2) 120.503 141. (See exemption under Certification Basis). SEE NOTES 6 and 8.0 883.000 31. (2) Main landing gear has "zero" retraction moment. Forward.1 -928.000 lb (1) 130.3 938.834 kg) minimum.G.524 124.7 928.3 933. 48086-48099. 48083. See Section XIV for limitations applicable to other DC-9-81 and -82 airplanes. 49246. 48079. Sta. 49269-49273.) H-Arm (Fus. 49100-49104.6 464 24. 49430-49435. 48080. 49249-49251. 49277. 49149-49190. 49230. 1980 (cont’d) Maximum Baggage: FORWARD CARGO COMPARTMENT Area Designation Location (Sta. 53176-53181. 49110-49127.150 pounds.9 239 24.0 B 370 to 541 467. 218 to 541 A 218 to 370 294. 49253-49265. 49531. 49278. 49229. . 48062. NOTE: The combined capacity of Fus. 49794-49796. 48063. 218 to 786. of Fuselage Length) Placard Capacity (lb) Combined Capacity (lb) Sta. 49237.) Usable Volume (Cu/Ft) Maximum Running Load (lb/in.5 225 24. 49245. 49138-49145. 48024-48059. Sta. 53053-53062. 49669. 49969-49975.A6WE 36 XII . 49740. 53203-53206.Model DC-9-81 (Transport Aircraft) Approved August 25.0 3585 -- 3375 -- 6960 6960 2 Maximum floor loading not to exceed 150 lb/ft Each of the above limitations is independent of the others.0 A+B 218 to 541 378. to Sta. 53216-53235. Do not exceed any limitation. 49192-49222. 49549-49552. 48066-48074. 49286-49289. NOTE: The above section and compartment limitations are applicable only to the following Factory Serial Numbers: 48002-48022.5 is not to exceed 12. 48024-48059. 53053-53062. 49549-49552. 49253-49265.Model DC-9-81 (Transport Aircraft) Approved August 25. 541 to 786. Sta. 49192-49222.48002-48022. 49794.37 A6WE XII . Sta. The above section and compartment limitations are applicable only to the following Factory Serial Numbers .9 195 32 663. 49149-49190. 49229. 49138-49145.5 is not to exceed 12. 53216-53235. 49740.) H-Arm (Fus. 48079. 48063. Each of the above limitations is independent of the other. 49278. Do not exceed any limitation.5 2 Maximum floor loading must not exceed 150 lb/ft . . of Fuselage Length) Placard Capacity (lb) C1 541 to 636 C2 636 to 786. 49277. 1980 (cont’d) MIDDLE CARGO COMPARTMENT Area Designation Location (Sta. 49246. 49230. 5320353206. 49269-49273.7 346 32 3020 3900 6920 - - 6920 Combined Capacity (lb) Sta. 48080.) Usable Volume (Cu/Ft) Maximum Running Load (lb/in. NOTE: Combined capacity of Fus. 49531.5 151 32 721.5 C1 + C2 = C 541 to 786. 48083. to Sta. 49245. 48062. 4808648099. 49430-49435. 49110-49127.5 588. 49669. 49237.150 pounds. 49969-49975. 49249-49251. 49286-49289. 49100-49104. 218 to 786. 49796. See Section XIV for limitations applicable to other DC-9-81 and -82 airplanes. 48066-48074. 53176-53181. 867 lb 120 lb 26 lb 41.638 lb 21. Each of the above section and compartment limitations is independent of the other. Fuel Capacity Three Tank System Main Wing Tanks (2) Center Wing Tank Lines Engine Total Total Capacity 19.) 1081 1245. Sta. 1980 (cont’d) AFT CARGO COMPARTMENT (WITHOUT AUXILIARY FUEL SYSTEM) Area Designation Location (Sta. except as specified in certain other cargo compartment limitation sections. NOTE 1(e) for fuel loading and usage procedures).506 lb H-Arm STA.0 884. of Fuselage Length) Placard Capacity (lb) Combined Capacity (lb) 32 22.765 lb Total Usable 19. Fuel Weights based upon fuel density of 7. to Sta. NOTE 1(d) for unusable fuel.Model DC-9-81 (Transport Aircraft) Approved August 25.8 1006. 951.752 lb 21.825 lb 36 lb 7 lb 41.A6WE 38 XII . -82.0 916.3 NOTE: H-ARM applies to usable fuel.0 1322. NOTE: The above section and compartment limitations are applicable to all DC-9-81.) D1 1007 to 1155 D2 1155 to 1320 D1 + D2 = D 1007 to 1320 H-Arm (Fus. .8 Usable Volume (Cu/Ft) 236 207 443 Maximum Running Load (lb/in. -83 Factory Serial Numbers. (See NOTE 1(c) for system fuel.4 1157.5 -- 4720 - 3105 - 6645 6645 2 Maximum compartment floor loading must not exceed 150 lb/ft . Do not exceed any limitation.1 lb/gal. 49436.0 lb 9. Normal Takeoff Rating is the maximum thrust to be set for takeoff operation with the aircraft Automatic Reserve Thrust System (ARTS) operative. -217C. 49420. 53366.74 lb/gal. 49278-49283. 49999.850 lb NOTE: Maximum Takeoff Rating is the maximum thrust certified for takeoff operation. 53315. Engine Limits See Section XII. P&W JT8D-217. regarding certification) Engines 2 Pratt and Whitney Turbofan JT8D-209.1 gal Total volume Usable 4 gal 1. 53347. 1980 (cont’d) Oil Capacity Engine Oil CSD APU Total Capacity 6. 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. 49998. 48058. Synthetic type oil conforming to P&W Specifications 521 as revised.75 lb H-Arm Sta. flat-rated to 84°F)* Normal Takeoff (5 min. 53275. 53365. 48024-48046. Fuel Commercial aircraft turbine fuel conforming to P&W Specification 522 as revised (see NOTE 7). or -219. -217. 53043. 53314.23 gal 1. 4990749914.39 A6WE XII .1 gal Per engine Usable weight 31. 1981 (MD-82. Engine Inoperative (10 min)** 20. 49356-49359. 53297-53302. 49613. 49554. or manually by throttle movement. Model DC-9-81 for JT8D-209 and JT8D-219 engines. 53368.0 1377. 49438. 49115. -217A. (See NOTE 1(c) for system oil) Serial Numbers Eligible 48002-48021. 1300. 49820. 49100. 48049-48053.Model DC-9-82 (Transport Aircraft) Approved July 29. 48070-48074. 49821. flat-rated to 77°F)* Maximum Takeoff. 48099.850 lb 20.25 gal 1. 49164.5 Oil Weight based upon 7. .000 lb 20. 49422. 48059. XIII .4 lb 7. -217A and -217C Power Rating Maximum Static Thrust at sea level Maximum Takeoff (5 min.Model DC-9-81 (Transport Aircraft) Approved August 25. 49461-49463.92 gal 1. 49380-49382. 49603. When set. (See NOTE 5 regarding intermixing of engines). 53000-53008. See NOTE 14. See NOTE 11 for model conversion.0 1319. 48092-48094. this rating ensures that the Takeoff Rating will be achieved upon actuation of ARTS. 49570-49572. Oil P&W Turbojet Engine Service Bulletin Number 238 lists approved brand oils. 0 2.25 See Section I.S. Cont.000 lb (Maximum Operating . Thrust Above 90% Max. Thrust At and below Max. -14 and -15 for GTCP85-98D.000') 263.75 3.1K 299.0K 304. Approved July 29. 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 At 90% and below Max.000) 303. *** 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.8K 304.0K 270.27.84) (Maximum Operating 27. ** In the event of an engine failure during Takeoff or Go-Around. altitude) XIII .500 lb 270. 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.Model DC-9-82 (Transport Aircraft).4K VA (Maneuvering . Airspeed Limits (CAS) VMO VMO VMO 147. GTCP85-98W.0K 262. (10 min)** Normal Takeoff (2 min.5 5. Model DC-9-51.5K VA (Maneuvering . Cont.) 268.0 8. Thrust Above Max.37.In-Flight 630°C (1166°F) 625°C (1157°F) 595°C (1103°F) 590°C (1094°F) 580°C (1076°F) 475°C ( 887°F) 625°C (1157°F) * The total time at both Takeoff Thrust Levels must not exceed 5 minutes.0 4.) 340K (Maximum Operating . Approved July 29. Cont.240 to 37. Cont.)* Maximum Takeoff (5 min. See Section XII.000') (M=0. for GTCP85-98DHF.Model DC-9-82 (Transport Aircraft). a total time of Ten (10) Minutes at Takeoff Thrust is required. GTCP85-98DC[B] and GTCP85-98DC[C].)*.30. for GTCP85-98DCK. -13.29. Models DC-9-11.0K VA (Maneuvering .8K (See AFM for variation in VA speeds vs. See Section IX.84) VA (Maneuvering .0 3.L.S.240') 340K (M=0.000') 298. GTCP85-98DC[A]. Thrust APU Limits % High Compressor Bleed 13th Stage Normal Maximum 8. Maximum Maximum Takeoff (2 min.L.A6WE 40 XIII .)* Maximum Continuous Starting .Ground *** . -12. Model DC-9-81. 1981 (cont’d) Engine Limits (cont’d) Exhaust Gas Temperature.)* Normal Takeoff (5 min. 1981 (cont’d) 149.1K .5 % Low Compressor Bleed 8th Stage Normal Maximum 4. limits. Approved July 29.57) (M=0.1 935.3 926.1° 20°) (Flaps down 20.41 A6WE Airspeed Limits (CAS) (cont’d) VFE V VLO VLE V (Flaps down 0.1 891.6 890.6 927.70) (M=0.000 67.751 118.57) (M=0.1° . (3) 26 ply rating MLG tires required for all ramp weights over 141. forward.6 -929.000 lb must be in usable fuel. Pilot and Copilot.G.1 938.000 31.6 888.6 891.000 63.30°) (Flaps down 31° .13°) (Flaps down 13.5 884. the aircraft will remain within approved C.500 lb (2) 122.57) (M=0. (2) Fuel jettisoning system not installed.000 lb (1) 130.57) (M=0.25°) (Flaps down 25. 1981 (cont’d) .57) 250K 300K 300K 350K (M=0.000 66.70) (M=0.1 929.1° .57) (M=0.57) (M=0.84) LANDING GEAR EXTENDED (1) Forward Aft 884.4 926.-lb which moves C.524 126.834 kg) minimum.000 53.967 140. 17.Model DC-9-82 (Transport Aircraft).40°) (Slat Extended Takeoff.000 63.967 147.000 lb (1) All weight in excess of 122.500 68. Maximum weights Taxi and Ramp Start of Takeoff Zero Fuel Landing 150. After filling the main wing tanks.503 141.132 149.3 -933.57) (M=0.5 -938.1° .6 NOTE: Inflight weight limited to 79.500 67. (See exemption under Certification Basis).3 -933. Gear retraction moment is -10.3 938.812 150. 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. SEE NOTES 6 and 8. Range 280K 240K 220K 200K 195K 280K 240K 280K (M=0.4 927. additional fuel may then be added to the center wing tank to attain the maximum design taxi weight.5 881.000 57. XIII .5 -938.000 58.9 926.G.000 lb (3) 149.154 in. 21°) (Autoslat Extension) (Landing Gear operation) (Gear retraction) (Gear extension) (Landing gear extended) (Landing light extension) C.266 LANDING GEAR RETRACTED (1) Forward Aft 881.153 130.5 888.8°) (Slat Extended Landing.G.3 Gross Weight Pounds Kilograms 70.3 935. (1) Straight line variation between weights shown.70) (M=0.678 148.000 pounds (35.5 ----890.4 -888.000 lb Minimum Crew Maximum Passengers For all flights. 53121. GTCP85-98W. See Section XIV. See NOTE 14. Model DC-9-81 for JT8D-209 and JT8D-219 engines. 49443. 49825. 49459. 48048. 53117-53119. 49647-49656. 49558-49566. 49439-49441. 53216-53235. 53468-53469.27. See Section IX.84) (M=0. regarding certification) Engines 2 Pratt and Whitney Turbofan JT8D-209. -217C. 53294-53296. 49604. Model DC-9-81 for DC-9-82s with three tank system. 49501-49524.84) . 49383-49387. See Section XII. 49101-49104. 49460. 49423-49435. 49889-49903. 49350. 49331-49343. XIV .000') 263.S. See Section XII. 49444. 49730-49740. -217. Serial Numbers Eligible 48022. 49253-49267. (See NOTE 5 regarding intermixing of engines). GTCP85-98DC[B] and GTCP85-98DC[C]. 48062. for DC-9-82s with 1130 Gallon Auxiliary Fuel Five Tank System. 48080. 49701-49704. 49569.000') 306. Model DC-9-83. 49415-49419. 49932. See NOTE 11 for model conversion. 49794-49806.A6WE 42 Maximum Baggage Fuel Capacity Oil Capacity: See Section XII. 49269-49273.) 340K (Maximum Operating . 53147.L. Models DC-9-11. 49421. 49229-49237. 49138-49145. Model DC-9-82 for JT8D-217. 48066-48069.300 to 37. 53064-53066. 49615. -217A. 53577. 49877. 53017. APU Limits See Section I.30. altitude) (M=0. 49391-49394. 49286-49329. 49450-49457. 49906. Oil P&W Turbojet Engine Service Bulletin Number 238 lists approved brand oils. 49675-49684. 49931.5K (See AFM for variation in VA speeds vs. 49277. 53083-53092. 49468-49494. 49669. 53025-53034. 48095-48098. 49165-49190. 49905. Model DC-9-81. 53480. 53479.000') (Maneuvering . Engine Limits See Section XII. 48054-48057. 48063.L. 53148-53160. Synthetic type oil conforming to P&W Specification 521 as revised. Model DC-9-81.2K (Maneuvering . 49849-49853. Model DC-9-81. 49116-49127. 49355.) 280. 49437. GTCP85-98DC[A]. for GTCP85-98DHF. 48086-48091. -14 and -15 for GTCP85-98D. 53542. 53053-53062. 49555. or -219 engines. 53481. 49531. -217A and -217C engines. 49660. 49245-49251.000') 301. 4954949553. 49592-49601. 49580-49582. 49987-49996. 49661. 49379. 48083. -12. 53244-53250. Airspeed Limits (CAS) VMO VA (Maximum Operating .29.37. 53173-53181. 49844.Model DC-9-83 (Transport Aircraft) Approved: October 17. 48079. 53162-53171. 49634.S. 49635. and 53581. 49667. 1985 (MD-83. -13. 49915-49925. 49149-49163. 49363-49374.1K (Maneuvering . Fuel Commercial aircraft turbine fuel conforming to P&W Specification 522 as revised (see NOTE 7). See Section XIII.6K (Maneuvering . 49110-49114. 49969-49975. 49192-49222. 49728. Model DC-9-51 for GTCP85-98DCK See Section XII.240') 340K (Maximum Operating 27. 48047. 53203-53206. 1 935.57) (M=0.153 130.1 -884.5 884.287 kg) minimum.70) (M=0.6 -926.20°) (Flaps down 20.57) (M=0.500 lb (5) 149. 1985 (cont’d) Airspeed Limits (CAS) (cont’d) VFE V VLO VLE V (Flaps down 0. (1) Straight line variation between weights shown.70) (M=0.000 72.30°) (Flaps down 31° .6 923.266 156.G.57) (M=0.000 58. 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. forward.25°) (Flaps down 25. Maximum weights Taxi and Ramp Start of Takeoff Zero Fuel Landing 150.760 160.9 NOTE: *Inflight weight limited to 80.287 118.3 -933.Model DC-9-83 (Transport Aircraft) Approved: October 17.524 126. 1985 (cont’d) .5 881. 17.000 73.000 pounds (36.500 63.3 938.000 70. (3) 26 ply rating MLG tires required for all ramp weights over 141.500 68.000* 36.4 -926. Gear retraction moment is -10.6 LANDING GEAR RETRACTED (1) Forward Aft 881.000 lb (2)(3)(4) 122. additional fuel may then be added to the center wing tank to attain the maximum design taxi weight.575 161.57) (M=0.3 935. After filling the main wing tanks.5 -926.967 139.40°) (Slat Extended Takeoff.5 -938.500 lb XIV .1° .000 lb (3)(4) 160.1 938.8 --929.8 -884.154 in.4 --929. limits.G. the aircraft will remain within approved C.1° .8°) (Slat Extended Landing.028 280K 240K 220K 205K 200K 280K 240K 280K (M=0.760 156.13°) (Flaps down 13. Range Gross Weight Pounds Kilograms 80. (See exemption under Certification Basis). 21°) (Autoslat Extension) (Landing Gear operation) (Gear retraction) (Gear extension) (Landing gear extended) (Landing light extension) K = KCAS C.000 lb (4) 28 ply rating MLG tires required for all ramp weights over 150.1° .812 150.000 63.57) (M=0.000 70.70) (M=0.000 lb (5) (1) All weight in excess of 122.43 A6WE XIV .3 884.000 53.9 887.57) (M=0.5 -938.5 884.57) 250K 300K 300K 350K (M=0.3 887.500 67.6 887.4 -887.-lb which moves C.6 884.84) LANDING GEAR EXTENDED (1) Forward Aft 884.503 149.3 926.276 140.000 57.3 -933.000 lb must be in usable fuel.500 lb (5) 161.9 --923.G. (2) Fuel jettisoning system not installed.8 923.1° .57) (M=0.000 lb (1) 130.Model DC-9-83 (Transport Aircraft) Approved: October 17. Maximum Passengers See NOTES 6 and 8. .5 is not to exceed 10.0 24. of Fuselage Length) Placard Capacity (lb) Combined Capacity (lb) Sta. -83 and MD-88 Factory Serial Numbers except as specified in certain other cargo compartment limitation sections.0 368. Each of the above limitations is independent of the others.305 pounds.9 459.0 24.) A 218 to 370 B 370 to 522 A+B 218 to 522 294. Sta. Minimum Crew For all flights: Pilot and Copilot. The above section and compartment limitations are applicable to all DC-9-81. 218 to 786.7 Usable Volume (Cu/Ft) 239 195 434 Maximum Running Load (lb/in.A6WE 44 Maximum weights (cont’d) (5) Maximum weights with Sperry 4034241-906 Digital Flight Guidance Computer (DFGC) installed. Maximum Baggage: FORWARD CARGO COMPARTMENT Area Designation Location (Sta.0 3585 - 2925 - 6510 6510 H-Arm (Fus. 218 to 522 24. -82.) Maximum floor loading not to exceed 150 lb/ft2. Do not exceed any limitation. NOTE: The combined capacity of Fus. to Sta. Sta. 9 449.1 357. to Sta. 218 to 786. 1985 (cont’d) FORWARD CARGO COMPARTMENT (WITH 1960 GALLON AUXILIARY FUEL SYSTEM) Area Designation Location (Sta.Model DC-9-83 (Transport Aircraft) Approved: October 17.) A 218 to 370 B 370 TO 503 A+B 218 TO 503 294. NOTE: The combined capacity of Fus. Each of the above limitations is independent of the others. . Do not exceed any limitation.0 24. -82. 218 to 503 24. Sta. Sta. of Fuselage Length) Placard Capacity (lb) Combined Capacity (lb) Sta.8 Usable Volume (Cu/Ft) 239 165 404 Maximum Running Load (lb/in. The above section and compartment limitations are applicable to all DC-9-81.0 3585 - 2460 - 6045 6045 H-Arm (Fus.) Maximum floor loading not to exceed 150 lb/ft2.0 24. -83 and MD-88 Factory Serial Numbers except as specified in certain other cargo compartment limitation sections.5 is not to exceed 9839 pounds.45 A6WE XIV . Model DC-9-83 (Transport Aircraft) Approved: October 17.9 653. NOTE: Combined capacity of Fus. Do not exceed any limitation.1 721. of Fuselage Length) Placard Capacity (lb) Combined Capacity (lb) 522 to 786. 1985 (cont’d) MIDDLE CARGO COMPARTMENT (WITHOUT AUXILIARY FUEL SYSTEM) Area Designation Location (Sta. Sta.2 Usable Volume (Cu/Ft) 181 195 376 Maximum Running Load (lb/in.5 is not to exceed 12. Sta. 218 to 786.) H-Arm (Fus. .A6WE 46 XIV .150 pounds.5 579.) C1 522 to 636 C2 636 to 786. -82. to Sta.5 32 32 32 3620 - 3900 - 7520 7520 2 Maximum floor loading must not exceed 150 lb/ft Each of the above limitations is independent of the other.5 C1 + C2 = C 522 to 786. The above section and compartment limitations are applicable to all DC-9-81. -83 and MD-88 Factory Serial Numbers except as specified in certain other cargo compartment limitation sections. 5 H-Arm (Fus. Each of the above section and compartment limitations is independent of the other. NOTE: Combined capacity of Fus.5 C1 + C2 = C 600 to 786.) 618 721. and -83 Factory Serial Numbers except as specified in certain other cargo compartment limitation sections.5 32 32 32 1160 3900 5060 5060 2 Maximum compartment floor loading must not exceed 150 lb/ft .47 A6WE XIV . Do not exceed any limitation. -82. 1985 (cont’d) MIDDLE CARGO COMPARTMENT (WITH 1130 GALLON AUXILIARY FUEL SYSTEM) Area Designation Location (Sta. Sta. Sta. of Fuselage Length) Placard Capacity (lb) Combined Capacity (lb) 600 to 786. 218 to 786. The above section and compartment limitations are applicable to all DC-9-81.305 pounds.1 Usable Volume (Cu/Ft) 58 195 253 Maximum Running Load (lb/in.5 is not to exceed 10. to Sta.Model DC-9-83 (Transport Aircraft) Approved: October 17.) C1 600 to 636 C2 636 to 786. .9 698. or -83 Factory Serial Numbers except as specified in certain other cargo compartment limitation sections. Each of the above section and compartment limitations is independent of the other.9 698.5 is not to exceed 9. Do not exceed any limitation.841 pounds. of Fuselage Length) Placard Capacity (lb) Combined Capacity (lb) 600 to 786. 218 to 786.5 C1 + C2 = C 600 to 786.1 Usable Volume (Cu/Ft) 58 195 253 Maximum Running Load (lb/in. 1985 (cont’d) MIDDLE CARGO COMPARTMENT (WITH 1960 GALLON AUXILIARY FUEL SYSTEM) Area Designation Location (Sta. . to Sta.Model DC-9-83 (Transport Aircraft) Approved: October 17.5 32 32 32 1160 3900 5060 5060 2 Maximum compartment floor loading must not exceed 150 lb/ft . Sta. -82. Sta.A6WE 48 XIV .) 618 721. NOTE: Combined capacity of Fus.5 H-Arm (Fus. The above section and compartment limitations are applicable to all DC-9-81.) C1 600 to 636 C2 636 to 786. 0 1245. NOTE: The above section and compartment limitations are applicable to all DC-9-81. . Each of the above section and compartment limitations is independent of the other. to Sta.) 2 Maximum compartment floor loading must not exceed 150 lb/ft . -82. Sta.6 Usable Volume (Cu/Ft) 119 207 326 Maximum Running Load (lb/in.5 -- 2380 -- 3105 -- 4890 4890 H-Arm (Fus.4 1198. Do not exceed any limitation.49 A6WE XIV . 1985 (cont’d) AFT CARGO COMPARTMENT (WITH 1130 GALLON AUXILIARY FUEL SYSTEM) Area Designation Location (Sta.Model DC-9-83 (Transport Aircraft) Approved: October 17. of Fuselage Length) Placard Capacity (lb) Combined Capacity (lb) 32 22. or -83 Factory Serial Numbers except as specified in certain other cargo compartment limitation sections.) D1 1081 to 1155 D2 1155 to 1320 D1 + D2 = D 1081 to 1320 1118. Each of the above section and compartment limitations is independent of the other.825 lb 36 lb 7 lb 41.) H-Arm (Fus.765 lb Total Usable 19. or -83 Factory Serial Numbers except as specified in certain other cargo compartment limitation sections. 951.867 lb 120 lb 26 lb 41.) D 1152 to 1320 1242.8 1006. Sta.3 .752 lb 21.638 lb 21.A6WE 50 XIV .3 Usable Volume (Cu/Ft) 213 Maximum Running Load (lb/in.0 916.0 884.0 1322. -82. to Sta.Model DC-9-83 (Transport Aircraft) Approved: October 17. NOTE: The above section and compartment limitations are applicable to all DC-9-81. Do not exceed any limitation. 1985 (cont’d) AFT CARGO COMPARTMENT (WITH 1960 GALLON AUXILIARY FUEL SYSTEM) Area Designation Location (Sta.5 3194 2 Maximum compartment floor loading must not exceed 150 lb/ft .506 lb H-Arm STA. of Fuselage Length) Placard Capacity (lb) 22. Fuel Capacity Three Tank System Main Wing Tanks (2) Center Wing Tank Lines Engine Total Total Capacity 19. 49672. 49284. 49966.0 904. 53448-53453. 53591-53599.487 lb 175 lb 26 lb 55. 53251-53256. -217C.843 lb 5.3 1080. 49458.9 H-ARM applies to usable fuel.801 lb 5. 53199. 49557.904 lb Total Usable 19.566 lb 8. 49568.825 lb 4.Model DC-9-87 (Transport Aircraft) Approved: October 21. 53520.8 564. 49617-49632. 49784-49793.386 lb H-Arm STA.564 lb H-Arm STA. 1987 (cont’d) . Oil Capacity: See Section XII.9 Five Tank System (196 Gallons) Main Wing Tanks (2) Center Wing Tank Fwd Fus Aux Tank Aft Fus Aux Tank Lines Engine Total Total Capacity 19. 53603. 53198. 49395-49402. 1987 (MD-87. 49642.1 lb/gal.Model DC-9-87 (Transport Aircraft) Approved: October 21. 49643. 49602.0 1005.51 A6WE XIV . 49933-49952. 49807-49809. 53120. 49525-49530. 49845-49848.Model DC-9-83 (Transport Aircraft) Approved: October 17. 49351-49353. 49826. 53435. 53182-53192. See NOTE 11 for model conversion. 49822-49824. 53377. 53063.752 lb 21. 53284-53293.8 551. See Section XIII. 53485-53488. 49769. 49930. 1985 (cont’d) Fuel Capacity (cont’d) NOTE: Five Tank System (1130 Gallons) Main Wing Tanks (2) Center Wing Tank Fwd Fus Aux Tank Aft Fus Aux Tank Lines Engine Total Total Capacity 19. 53074-53079. and -219 engines. 53463-53467.8 935. 49390.752 lb 21.399 lb 41 lb 7 lb 55.5 1322. 53561-53566.638 lb 21. 49965. Model DC-9-81 for JT8D-219 engines. Eligible 49252. 49662. 49985.0 884. Oil Capacity Serial Nos. 49574-49579. 49442. 951. 49707-49710. and 53611-53634.500 lb 8. Engine Limits See Section XII. See NOTE 14. 49556.849 lb Total Usable 19. 49854-49857. 49668. regarding certification) Engines 2 Pratt and Whitney Turbofan JT8D-217A. 49986. Model DC-9-82 for JT8D-217A and -217C engines. 53018-53024. 49344-49349.0 884.056 lb 4. 49567.019 lb 56 lb 7 lb 49. 49904. 53050-53052. XV . XV .8 1322. 5313753141. 49449. Fuel weights based upon fuel density of 7. 53602. 53436. 49968. (See NOTE 5 regarding intermixing of engines). (See NOTE 1(c) for system fuel. NOTE 1(d) for unusable fuel.019 lb 4. 53470-53473. 49657-49659.056 lb 147 lb 26 lb 49. 49448. 49663. NOTE 1(e) for fuel loading and usage procedure). 53044-53046.0 1042. 53012-53016. 53122-53126. 53093.638 lb 21. 49741.0 897. 951.867 lb 4. 000') 303.957 149.503 141.500 68.77 775.57) (Flaps down 13.22 ---815.57) (Flaps down 31° . and -15 for GTCP85-98D.1° . 21°) 240K (M=0.S.57) (Slat Extended Landing. Synthetic type oil conforming to P&W Specification 521 as revised. -13.500 31.1K (Maneuvering .22 774. Fuel Commercial aircraft turbine fuel conforming to P&W Specification 522 as revised.-lb which moves C.L.000 58.G.25.13°) 280K (M=0.266 FUSELAGE STATIONS LANDING GEAR RETRACTED Forward Aft 774.477 kg) minimum. GTCP85-98W.3K (Maneuvering . for GTCP85-98DHF. (See NOTE 7).970 to 37. limits. See Section XII.A6WE 52 APU Limits See Section I.000') (M=0.8°) 280K (M=0.57) (Slat Extended Takeoff.000 63. Model DC-9-81. 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.500 67.82) (Maneuvering .57) (Autoslat Extension) 280K (M=0.30°) 200K (M=0.9K (See AFM for variation in VA speeds vs.000') 262. XV .1° .20°) 240K (M=0.970') 340K (M=0.70) (Gear extension) 300K (M=0.G.57) (Flaps down 25.29.70) (Landing light extension) 350K (M=0.) 272. Models DC-9-11.G. forward.70) (Landing gear extended) 300K (M=0. GTCP85-98DC[A].57) (Flaps down 20.56 ---------775.82) (Maximum Operating .) 340K (Maximum Operating . GTCP85-98DC[B] and GTCP85-98DC[C].14 * Inflight weight limited to 71.000') 298. 1987 (cont’d) . 17.37.57) (Landing Gear operation) (Gear retraction) 250K (M=0.25. Oil P&W Turbojet Engine Service Bulletin Number 238 lists approved brand oils.30.Model DC-9-87 (Transport Aircraft) Approved: October 21. Model DC-9-51 for GTCP85-98DCK.25°) 220K (M=0.967 140.600 pounds (32.154 in. -14.1° .S. the aircraft will remain within approved C. Airspeed Limits (CAS) VMO VMO VMO VA VFE V VLO VLE V (Maximum operating . -12.84) K = CAS C.752 130.812 150. Gear retraction moment is -10.0K (Maneuvering . altitude) (Flaps down 0.19 823.000 63.L. Range Gross Weight Pounds Kilograms *70.1° .40°) 195K (M=0. See Section IX.56 823. NOTE: Straight line variation between weights shown.67 815. Maximum Passengers: See NOTES 6 and 8.0 24.000 lb (4) A6WE 150.000 lb (1) 130. (2) Fuel jettisoning system not installed.0 24.6 309.0 2190 - 1590 - 3780 3780 2 Maximum floor loading not to exceed 150 lb/ft . 1987 (cont’d) .) H-Arm (Fus. Sta.000 lb must be in usable fuel. (3) 26 ply rating MLG tires required for all ramp weights over 141. Each of the above limitations is independent of the other.420 pounds. 219 to 408 24.000 lb (2)(4) 112. Do not exceed any limitation. NOTE: The combined capacity of Fus. Maximum Baggage: FWD CARGO COMPARTMENT Area Designation Location (Sta. (See exemption under Certification Basis).5 Usable Volume (Cu/Ft) 146 106 252 Maximum Running Load (lb/in.7 is not to exceed 9.Model DC-9-87 (Transport Aircraft) Approved: October 21.000 lb (4) 125. Sta.500 lb (2)(3) 112.500 lb (3) 149. of Fuselage Length) Placard Capacity (lb) Combined Capacity (lb) Sta.000 lb (1)(4) 120.000 lb (4) Maximum for airplane serial numbers 49464 and 49465. additional fuel may then be added to the center wing tank to attain the maximum design taxi weight. 219 to 672.000 lb (3) (1) All weight in excess of 112.) A 219 to 313 B 313 to 408 A+B 219 to 408 266. to Sta. After filling the main wing tanks. Minimum Crew: For all flights: Pilot and Copilot.53 Maximum weights Taxi and Ramp Start of Takeoff Zero Fuel Landing 126.8 368. XV . ) Usable Volume (Cu/Ft) Maximum Running Load (lb/in.7 608. to Sta.2 376 32 3620 - 3900 - 7520 7520 2 Maximum floor loading must not exceed 150 lb/ft . .) H-Arm (Fus.A6WE 54 MIDDLE CARGO COMPARTMENT (WITHOUT AUXILIARY FUEL TANK) Area Designation Location (Sta. 219 to 672. Sta. Do not exceed any limitation. 408 to 672.7 539. of Fuselage Length) Placard Capacity (lb) Combined Capacity (lb) Sta. NOTE: Combined capacity of Fus.7 is not to exceed 9.420 pounds.0 181 32 C2 522 to 672.2 195 32 C1 + C2 = C 408 to 672.7 C1 408 to 522 465. Sta. Each of the above limitations is independent of the other. 486 to 672.) Usable Volume (Cu/Ft) Maximum Running Load (lb/in. .7 is not to exceed 9.) H-Arm (Fus.3 253 32 1160 --- 3900 --- 5060 5060 2 Maximum compartment floor loading must not exceed 150 lb/ft .7 584. Do not exceed any limitation.55 A6WE XV .2 195 32 C1 + C2 = C 408 to 672.Model DC-9-87 (Transport Aircraft) Approved: October 21. Each of the above section and compartment limitations is independent of the other. to Sta. 1987 (cont’d) MIDDLE CARGO COMPARTMENT (WITH 1130 AUXILIARY FUEL SYSTEM) Area Designation Location (Sta. NOTE: Combined capacity of Fus Sta 219 to 672. Sta.420 pounds.7 608. of Fuselage Length) Placard Capacity (lb) Combined Capacity (lb) Sta.7 C1 486 to 522 504.0 58 32 C2 522 to 672. 1030: 22. Each of the above section and compartment limitations is independent of the other. 1002 to Sta.A6WE 56 XV . Sta. *Sta.4 219 * D2 1030 to 1111 1068.) H-Arm (Fus.5 lb/in. 893 to 1111 D1 893 to 1030 960. to Sta. .2 310 --- 4111 --- 1380 --- 4650 4650 2 Maximum compartment floor loading must not exceed 150 lb/ft . 1987 (cont’d) AFT CARGO COMPARTMENT (WITHOUT AUXILIARY FUEL SYSTEM) Area Designation Location (Sta.) Usable Volume (Cu/Ft) Maximum Running Load (lb/in. *Sta.5 D1 + D2 = D 893 to 1111 992. 1002: 32 lb/in. 893 to Sta. of Fuselage Length) Placard Capacity (lb) Combined Capacity (lb) Sta.Model DC-9-87 (Transport Aircraft) Approved: October 21.8 91 22. Do not exceed any limitation. Sta. *Sta.Sta.5 lb/in. 893 to 1111 D1 989 to 1030 1008. 1030: 22. Do not exceed any limitation.5 D1 + D2 = D 989 to 1111 1044. Sta. *Sta.) Usable Volume (Cu/Ft) Maximum Running Load (lb/in.) H-Arm (Fus. 1002: 32 lb/in. 1987 (cont’d) AFT CARGO COMPARTMENT (WITH 780 GALLON AUXILIARY FUEL TANK) Area Designation Location (Sta.8 91 22.Model DC-9-87 (Transport Aircraft) Approved: October 21. 989 . of Fuselage Length) Placard Capacity (lb) Combined Capacity (lb) Sta. . to Sta. 1002 . Each of the above limitations is independent of the other.57 A6WE XV .3 154 --- 1029 --- 1380 --- 2310 2310 2 Maximum compartment floor loading must not exceed 150 lb/ft .9 63 * D2 1030 to 1111 1068. 837.5 lb/in. *Sta.638 lb 21.) H-Arm (Fus.752 lb 21. Sta. 1002: 32 lb/in. Fuel Capacity Three Tank System Main Wing Tanks (2) Center Wing Tank Lines Engine Total Total Capacity 19.A6WE 58 XV . 1030: 22.5 D1 + D2 = D 967 to 1111 1031.756 lb Total Usable 19.9 1113.3 . 1002 to Sta. of Fuselage Length) Placard Capacity (lb) Combined Capacity (lb) D1 967 to 1030 997.6 99 * D2 1030 to 1111 1068.825 lb 28 lb 7 lb 41. to Sta.867 lb 111 lb 26 lb 41. 1987 (cont’d) AFT CARGO COMPARTMENT (WITH 1130 GALLON AUXILIARY FUEL SYSTEM) Area Designation Location (Sta. 967 to Sta.Model DC-9-87 (Transport Aircraft) Approved: October 21. Do not exceed any limitation.0 770.8 91 22.0 802.) Usable Volume (Cu/Ft) Maximum Running Load (lb/in. Each of the above section and compartment limitations is independent of the other.7 190 --- 1760 --- 1380 --- 2850 2850 2 Maximum compartment floor loading must not exceed 150 lb/ft .498 lb H-Arm STA.8 943. *Sta. 49605-49612. 53039-53042.752 lb 21.0 818. -13.1 gal Total Capacity 19. Model DC-9-81 for JT8D-219 engines.Model DC-9-87 (Transport Aircraft) Approved: October 21.8 940.9 927.6 H-Arm STA.75 lb H-Arm STA. See Section XIII. Models DC-9-11. 49777-49780.0 930. 49768. See Section IX. 49641.016 lb Total Usable 19.59 A6WE XV .867 lb 5. 53351. 49670. 1987 (cont’d) Fuel Capacity (cont’d) Four Tank System Main Wing Tanks (2) Center Wing Tank Aft Fus Aux Tank Lines Engine Total Five Tank System Main Wing Tanks (2) Center Wing Tank Fwd Fus Aux Tank Aft Fus Aux Tank Lines Engine Total Oil Capacity Engine oil CSD APU Total Capacity 6.0 1168. 49464-49467. 49997. GTCP85-98DC[B] and GTCP85-98DC[C]. 49673.25 gal 1.351 lb Total Capacity 19.825 lb 5. -14 and -15 for GTCP85-98D. Engine Limits See Section XII. 49767. 53416-53423. 837. XVI .0 770. 49827-49843. 49706.0 1110.0 770.3 704.2 gal 1. and 53447. GTCP85-98DC[A]. -12. 1091. 53009-53011. Eligible 49389.056 lb 4. 49671. 49724-49727. 837. 1987 Engines 2 Pratt and Whitney Turbofan JT8D-217A. Fuel Commercial aircraft turbine fuel conforming to P&W Specification 522 as revised (See NOTE 7).0 783.752 lb 21. -217C and -219 engines. See Section XII.74 lb/gal.056 lb 138 lb 26 lb 49.4 lb 7. 49403-49405. 49411-49414.Model MD-88 (Transport Aircraft) Approved December 8.895 lb Total Usable 19.0 1113.638 lb 21.92 gal 1. 53207-53213. (See NOTE 1(c) for system oil) Serial Nos. 49888. GTCP85-98W.019 lb 4. 49614. Model DC-9-81 (MD-81) for GTCP85-98DHF. 53446. 53340. Model DC-9-51 for GTCP85-98DCK.8 449.0 lb 9. 53336.867 lb 4.638 lb 21.555 lb Total volume Usable 4.825 lb 4. (See NOTE 5 regarding intermixing of engines).5 Oil weight based upon 7.581 lb 125 lb 26 lb 47.512 lb 34 lb 7 lb 47. 53348. APU Limits See Section I.23 gal 1.Model MD-88 (Transport Aircraft) Approved December 8. XVI . Model DC-9-82 for JT8D-217A and -217C engines.1 gal Per engine Usable weight 31.0 1113.9 H-Arm STA.019 lb 47 lb 7 lb 49. 1987 (cont’d) . 49585-49587. 53337. 40°) 195K (M=0.132 149.760 156.6 923.812 150.1 -884.57) (Landing Gear operation) (Gear retraction) 250K (M=0. 160.751 80.000 53.70) (M=0.0K (Maneuvering .6 NOTE: *Inflight weight limited to 80.967 139.1° .70) (Landing gear extended 300K (M=0.6 -926. as revised.028 LANDING GEAR EXTENDED (1) Forward Aft 884.500 67.6K 306. Range Gross Weight Pounds Kilograms 70.5 -938.57) (Slat Extended Takeoff.6 887.575 161.000 31.84) 280.000 ') 340.8 923.9 --923.4 --929.1° .25°) 220K (M=0.84) (Maneuvering .000 lb 340K 340K (M=0.27.8°) 280K (M=0.287 kg) minimum.5 884.000 70.37.276 140.000* 36.57) (M=0.29.57) (M=0.287 117.L.240 to 37.000 58.20°) 240K (M=0.1K 263.57) 250K 300K 300K 350K (M=0.1° .8 --929.000 73.4 -887.S.3 884.5 881.57) (M=0.500 63.5 884. 21°) 240K (M=0.266 156.57) (M=0.9 --- .000 pounds (36.57) (Flaps down 20.57) (M=0.000 67.5 -929.000 57. Airspeed Limits (CAS) VMO VA VFE V VLO VLE V 149.000 ') 299.1K (See AFM for variation in VA speeds versus altitude) (Flaps down 0.5 -938.3 887.000 ') 262.57) (Flaps down 13.1 938.57) (Flaps down 31° .70) (M=0.957 148.6 884.000 72.1 938.8 -884.3 -933.70) (Gear extension) 300K (M=0.57) (Slat Extended Landing.30°) 200K (M=0.30.70) (Landing light extension) 350K (M=0.000 ') (M=0.3 926.70) (M=0.57) (Flaps down 25.57) (Autoslat Extension) 280K (M=0.3 938.57) (M=0.A6WE 60 Oil P&W Turbojet Engine Service Bulletin 238 lists approved brand oils.4 -926.5 --884.500 68.L. 17.524 126.000 70.G.S.503 141.240 ') 340K (M=0.1° .000 63.3 938.9 887. Synthetic type oil conforming to P&WA Specifications 521.3 -933.5 890.000 63.84) LANDING GEAR RETRACTED (1) Forward Aft 881.57) (M=0.1 935.) 340K (Maximum Operating .6 --926.153 130.3 935.0K (Maneuvering .84) (M=0.2K 301.1K (Maneuvering .5 881.84) K=KCAS C.5 -929.500 lb (Maximum Operating .84) (Maximum Operating 27.760 160.) 270.5K 280K 240K 220K 205K 200K 280K 240K 280K (M=0.13°) 280K (M=0. 53351.000 lb (3)(4) 160.000 lb (2)(3)(4) 122. 53215. Model DC-9-83. the aircraft will remain within approved C. 53370-53372. 53409. Gear retraction moment is -10.000 lb (4) 28 ply rating MLG tires required for all ramp weights over 150.) (static thrust at sea level.G. 53193-53197. forward.000 lb V2528-D5 28.Model MD-90-30 (Transport Aircraft) Approved November 4.-lb which moves C. 53410. 49878-49887. 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. (Intermixing of engines not permitted. 53115. 49967.000 lb Takeoff. 49705. Oil Capacity See Section XII. Serial Numbers Eligible 49532-49546. 53547-53549. 53161. 1998. 53362-53364.000 lb must be in usable fuel. 53257-53259.000 lb (3) (1) All weight in excess of 122. 49583. limits. 53338. 49584.G. Maximum Passengers See NOTES 6 and 8.Model MD-90-30 (Transport Aircraft) Approved November 4. After filling the main wing tanks. 53447. 1994 (cont’d) . and 53550. 53341-53346.154 in. Maximum weights Taxi and Ramp Start of Takeoff Zero Fuel Landing 161.) Engines 2 International Aero Engines (IAE) V2525-D5 or V2528-D5 engines.61 A6WE XVI . 53546. Engine Limits Thrust Ratings Takeoff (5 min. 49997.000 lb (static thrust at sea level.) XVII . flat-rated to 86°F) V2525-D5 25. refer to additional certification basis. Model DC-9-81. XVII .000 lb (1) 150. 1987 (cont’d) C. 49976-49984. Range: (cont’d) (1) Straight line variation between weights shown. additional fuel may then be added to the center wing tank to attain the maximum design taxi weight. 53116. Fuel Capacity See Section XIV. 53339. flat-rated to 86°F) (Takeoff Rating is the maximum thrust certified for takeoff operation. 53214. 53273. 49956-49959. 4975949766. 53047-53049. 53241-53243. 49644-49646. Maximum Baggage See Section XIV.G. Engine Inoperative (10 min. 53274. 53446. 53415-53423. 49573. (See exemption under Certification Basis).Model MD-88 (Transport Aircraft) Approved December 8. 53266-53268. 49810-49819. 53172-53175. 49591. 1994 (Note: For Model MD-90-30 equipped with Enhanced Flight Deck configuration. approved on March 3. 53303-53310.000 lb 28. (2) Fuel jettisoning system not installed.) 25. 53378-53380. Model DC-9-83. See NOTE 5). 53311-53313. 49711-49723. 49926-49929. (3) 26 ply rating MLG tires required for all ramp weights over 141.500 lb Minimum Crew For all flights: Pilot and Copilot. 84) .950 rpm (100%) Maximum Permissible Indicated Engine Exhaust Gas Temperatures * Takeoff (5 min.7% Linear variation from 13. 1994 (cont’d) (M=0.29.) (Maneuvering .660 lb Maximum Permissible Engine Operating Speeds (All Models) N1 (Low Pressure Rotor) Takeoff 5. 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.Model MD-90-30 (Transport Aircraft) Approved November 4.240' to 37.84) (M=0.950 rpm (100%) 5.) 620°C Maximum Continuous 610°C Starting on Ground 635°C in Flight 635°C 635°C 610°C 635°C 635°C See NOTE 19 of Engine TCDS E40NE.2% From 90% to 97% corrected high rotor speed Linear variation from 8.0% Below 24. Oil Outlet Temperature (All Models) Continuous Operation 155°C/311°F Transient Operation (15 min. a maximum of 2% 10th stage bleed is allowed at takeoff rating and 4% 10th stage bleed at max.2% to 6.S.650 rpm (100%) N2 (High Pressure Rotor) Takeoff 14.L.900 lb V2528-D5 25.0% At or above 97% corrected high rotor speed 6.A6WE 62 Engine Limits (cont’d) Maximum Continuous (static thrust at sea level) * V2525-D5 23.000 ft: at ambient temperatures above 40°F.000') 340K 340K 273K 296K XVII . at 40°F ambient temperatures and below.27. Airspeed Limits (KCAS) VMO VMO VMO VA VA (Maximum Operating .0% 6.650 rpm (100%) 14. continuous rating and above. 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 Operating . no 10th stage bleed is allowed at max.000') (Maneuvering .0% 10th Stage Bleed * At or below 61% corrected high rotor speed From 61% to 78% corrected high rotor speed From 78% to 97% corrected high rotor speed At or above 97% corrected high rotor speed * 13. - ** Simultaneous use of 7th and 10th stage bleed due to a malfunction is allowed only until the next landing.) 165°C/329°F Maximum Oil Pressure Limits 60 psig Minimum Fuel Pressure At the inlet to the engine system pump.S.27.L.0% to 6.7% to 12% Linear variation from 12.240') (Maximum Operating . continuous rating. 1008. Fuel Capacity Three Tank System Main Wing Tanks (2) Center Wing Tank Lines Engine Total Total Capacity 19.000 lb 160.500 lb 166.0 974.57) (M=0.000 lb (1) 142.57) (M=0.57) (M=0.500 lb 168.8 941.964 lb 21.0 1398.57) (M=0.492 lb H-Arm STA.70) (M=0.37.772 lb Total Usable 19.13°) 280K (Flaps down 13.000 lb Minimum Crew For all flights: Pilot and copilot.84) See FAA Approved Airplane Flight Manual Maximum weights Taxi and Ramp Start of Takeoff Zero Fuel Landing 161. 17.000') 290K (Maneuvering .30°) 205K (Flaps down 31° .000') 256K (See AFM for variation in VA with altitude) (Flaps down 0.40°) 200K (Slat Extended Takeoff. 21°) 240K (Autoslat Extension) 280K (Landing Gear operation) (Gear retraction) 250K (Gear extension) 300K (Landing gear extended 300K (Landing light extension) 350K (M=0.G.000 lb (1) 142.000 lb (2) 132.1° . After filling the main wing tanks.000 lb (1) 142.57) (M=0.25°) 220K (Flaps down 25.000 lb 166.57) (M=0.000 lb (1) All weight in excess of 132.1 .000 lb (2) 132.1° .1° .1° .70) (M=0.63 A6WE Airspeed Limits: (cont’d) VA VFE V VLO VLE V C.837 lb 21.30. Range (Maneuvering .57) (M=0.656 lb 124 lb 28 lb 41. additional fuel may then be added to the center wing tank to attain the maximum design taxi weight.000 lb must be in usable fuel.8°) 280K (Slat Extended Landing.500 lb 132.9 1063.20°) 240K (Flaps down 20. MDC-91K0981.612 lb 36 lb 7 lb 41. Maximum Passengers See NOTES 6 and 8. Maximum Baggage See Weight and Balance Manual Report No.57) (M=0.70) (M=0. (2) 28 ply tires are required for all ramp weights over 166.000 lb 168. (See NOTE 1(c) for system oil) Serial Numbers Eligible Maximum Takeoff Weight of 160. 53571.3 lb H-ARM STA. Maximum Takeoff Weight of 166.000 lb 53494-53519. 53534-53538. 53586.861 lb 19.9 NOTE: H-ARM applies to usable fuel. 53531. 53568-53570. 53574. ECS mode.5 gal 0. 53489. 1365. 53559. 53381-53392*. 53361.0 gal 0. 53532.0 1398. Maximum Allowable (108%) 52. APU Limits AlliedSignal Engines 131-9 [D] Rotor Speeds.5 gal 0. 53529.8 941. 53585. 53567. 53589.000 lb provided Boeing Service Bulletin MD90-57-028 is installed. 1994 (cont’d) Fuel Capacity: (cont’d) Four Tank System Total Capacity Total Usable H-Arm STA. ECS and MES mode. 53523-53526.7 lb 6.0 1063. (*) Serial numbers within the range of 53381 thru 53392 are eligible to operate at maximum takeoff weight of 166.A6WE 64 XVII .656 lb 4.612 lb 4. 53572. 53528. 53533.9 564.511 lb 1008.848 RPM Exhaust Gas Temperatures Maximum allowable for all operations 106% on EGT gauge* including starting and transients * 1235oF for standard day at sea level.4 lb/gal. 53393-53396.500 lb 53352-53355.4 lb 3. 60001.85 gal PER ENGINE USABLE WEIGHT 44. 53587.056 lb 157 lb 28 lb 45. NOTE 1(e) for fuel loading and usage procedures) Oil Capacity TOTAL CAPACITY ENGINE OIL (2) VSCF (2) APU (1) 11. 53578.5 Oil Weight based upon 7.000 lb 53356-53359. 53360. 53491-53493. Maximum rated for continuous operation 100% on EGT gauge** ** 1052°F for standard day at sea level. 53551-53554.019 lb 36 lb 7 lb 45.1 lb/gal (See NOTE 1(c) for system fuel. and 60002. 53576.704 RPM Maximum for normal operation (104%) 50. and 53601. 53580. 53558. 53588.6 gal TOTAL VOLUME USABLE 6.0 937. 53490. 53527. Maximum Takeoff Weight of 168. 53555-53557.752 RPM Minimum for normal operation (96%) 46.7 gal 1.Model MD-90-30 (Transport Aircraft) Approved November 4. . 53573. Fuel weights based upon fuel density of 7. 53457-53462.0 1360. and 53582-53584. 53579.837 lb 21.3 1422. 53539. 53544. NOTE 1(d) for unusable fuel. 53543. 53590. 53560. 53530.964 lb 21. Main Wing Tanks (2) Center Wing Tank Fwd Aux Tank Lines Engine Total 19. 096 rpm (100.430 lb (static thrust at sea level. Oil brands qualified for use include: Mobil Jet II and Exxon 2380. Start up to 35.5 + 7. Oil Pressure. 25) Engine Limits Thrust Ratings BR700-715A1-30 BR700-715C1-30 Takeoff (5 min. XVIII .) Oil Pressure Limits 160°C/320°F 160°C/320°F Maximum 25 psig for N2 less than 72.5 psi Low Oil pressure (Master Caution) 35. Oil Oil to be used in the IAE V2525-D5 and V2528-D5 engines must conform to the following specification: MIL-L-23699.Model 717-200 (Transport Aircraft) Approved September 1. Normal operation 67.661 rpm (100.000 feet Operate up to 37.920 lb 21. 3. 1994 (cont’d) APU Limits (cont’d) Fuel Pressure Limits.Model 717-200 (Transport Aircraft) Approved September 1.430 lb (static thrust at sea level.000 feet APU Maximum Continuous Electrical Loads must not exceed: Ground 1.) 900°C Maximum Continuous 850°C Starting on Ground 700°C Starting in Flight 850°C *Takeoff rating may be used for 10 min.) 18. Oil Capacity. 6. Engine Inoperative (10 min.) 18. Minimum of 4 psig.Model MD-90-30 (Transport Aircraft) Approved November 4. Oil Outlet Temperature: Continuous Operation Transient Operation (15 min. if an engine becomes inoperative. regarding certification. Maximum 325°F APU Envelope.65 A6WE XVII . regarding flammability) Engines 2 Rolls-Royce Deutschland Ltd & Co KG BR700-715A1-30 or BR700-715C1-30 engines.0%) Maximum Permissible Indicated Engine Exhaust Gas Temperatures *Takeoff (5 min.6 Fuel Commercial aircraft turbine fuel conforming to specifications listed in NOTE 7.00 Indicated Inflight 0.4 qt usable.700 lb 20. 1999 (See NOTE 22.420 lb (static thrust at sea level) Maximum Permissible Engine Operating Speeds N1 (Low Pressure Rotor) Takeoff 6.0 + 5. (See Notes 5.5 qt total.920 lb 21. flat-rated to 86°F) Takeoff.0%) N2 (High Pressure Rotor) Takeoff 16. 1999 (cont’d) . flat-rated to 86°F) (Takeoff Rating is the maximum thrust certified for takeoff operation.0 psi Oil Temperature.) Maximum Continuous 18. NOTE 29.3% 35 psig for N2 more than 90% XVIII . 121 lb H-Arm STA.895 kg (1) All weight in excess of 100. Range: (Maximum Operating .4 870.000 lb/54.G.526 lb 108 lb 25 lb 26.687 lb 6.1° .000') (Maneuvering . After filling the main wing tanks.25°) 220K (Flaps down 25.) 340K (Maximum Operating .31.346 lb Total Usable 19.0 748.40°) 200K (Slat Operation or Extended) 280K (Landing Gear operation) (Gear retraction) 250K (Gear extension) 300K (Landing gear extended 300K (Landing light extension) 340K (M=0.638 lb 6.000 lb/49. NOTE 1(e) for fuel loading and usage procedures) . MDC 97K9261 Three Tank System Main Wing Tanks (2) Center Wing Tank Lines Engine Total Total Capacity 19.000') 259K (See AFM for variation in VA with altitude) (Flaps down 0. Fuel weights based upon fuel density of 7.57) (M=0.70) (M=0. Maximum Passengers Maximum Baggage Fuel Capacity See NOTE 6.885 kg 100.26.S.57) (M=0.57) (M=0.000') 279K (Maneuvering .000 lb/55.1° .S. NOTE 1(d) for unusable fuel.) 263K (Maneuvering .1° .70) (M=0.L.500 lb (45. See Weight and Balance Manual Report No. additional fuel may then be added to the center wing tank to attain the maximum design taxi weight.500 lb/45. Minimum Crew For all flights: Pilot and copilot.70) (M=0.440 lb 36 lb 7 lb 26.57) (M=0.A6WE 66 Airspeed Limits (KCAS) VMO VMO VMO VA VFE V VLO VLE V C.L.35.10°) 280K (Flaps down 10.586 kg (1) 110.82) (M=0.000') 340K (Maximum Operating -26.20°) 240K (Flaps down 20.338 kg 121.82) (M=0.586 kg) must be in usable fuel.82) See FAA Approved Airplane Flight Manual Maximum weights Taxi and Ramp Start of Takeoff Zero Fuel Landing 122.7 1036. 762.1° .5 NOTE: H-ARM applies to usable fuel.1 lb/gal (See NOTE 1(c) for system fuel.26.000') 297K (Maneuvering .000 to 37.57) (M=0.3 705. (DC-9-81. 55059-55068. 1999 (cont’d) Oil Capacity TOTAL CAPACITY Engine Oil Tank Only (2) Total Engine Oil (2) IDG Sump Only (2) APU (1) PER ENGINE USABLE WEIGHT 12. -83.5 psi 20 psig +/.0 psi APU Envelope: Start (up to 37.000 feet) APU Maximum Continuous Electrical Loads must not exceed: Ground (60 KVA) 1.0 1080. 55052. Oil For 717-200 approved engine oils. 55053-55057.2.868 RPM 100% on EGT display 100% on EGT display* Fuel Pressure Limits Minimum of 5 psig. 55002.7 lb 3.000 feet) Operate (up to 37. MD-90-30 and 717-200) .2.74 lb/gal. 55151-55155.582 RPM 43. 55121-55125.000 ft. (See NOTE 1(c) for system oil) Serial Numbers Eligible 55001. 55043-55048. (DC-9-11 thru DC-9-51) 37.0 indicated Fuel Commercial aircraft turbine fuel conforming to specifications listed in NOTE 7. 55058. 55166-55185. 55141-55150. 55003-55042.67 A6WE XVIII . 55186-55187. 55118.Model 717-200 (Transport Aircraft) Approved September 1. Maximum 275°F 3.8 US gal 1. 55049-55051. see latest revision of the BR715 Engine Operating Instructions. 55134-55140. Oil Capacity Oil Pressure. MD-88.3 lb 1. OI-715-3BR.486 RPM 46. 2.0 qt usable.0 1034. 55190-55194.0 1033. 55195-55196 APU Limits Auxiliary Power International Corporation (APIC) APS 2100 Rotor Speeds.3 qt total.64 US gal 0. -87.64 US gal 5. 55130-55132. -82.30 US gal 0. 44 US gal 0.000 ft.25 US gal 12.5 psig +/. as indicated by FAA Type Certificate Data Sheet E00061EN.7 lb H-ARM STA. 1. 55069-55117.44 US gal 0. Normal operation Low Oil pressure (Master Caution) Oil Temperature. 55126-55129. 42.0 Indicated Inflight (40 KVA) 1.97 US gal TOTAL VOLUME USABLE 1. Data Pertinent to All Models Maximum Operating Altitude 35. Maximum Allowable (105%) Maximum for normal operation (103%) Minimum for normal operation (97%) Exhaust Gas Temperatures Maximum allowable for all operations including starting and transients Maximum rated for continuous operation * 1345°F for standard day at sea level 47.8 lb 1034.0 Oil Weight based upon 7. 4 in. 771. 549. -31. DC-9-10.CAR 4b.E. (L. 158. the Special Conditions contained in Attachment "A" of FAA letter to Douglas dated October 20. (L.4). 544. of MAC at Sta. of MAC at Sta. 1953. -15.5). -13.-34F.CAR 4b. NOTE: CAR 4b with Amendments 4b-1 thru 4b-16 is considered equivalent to FAR Part 25 (New) effective February 1. of MAC at Sta.5). of MAC at Sta.4 in.4 in.E.5).5 in. -21. 147. -12. Model MD-90 Douglas Dwg. of MAC at Sta. -14. 715. (L. 58. -13. Datum 7 inches forward of nose (Sta. -83 and MD-88 Model DC-9-87 Model MD-90-30 Model 717-200 Leveling Means One of two systems in each airplane: (a) Spirit levels and leveling pads at Sta.E.4 in. 658. "Emergency Exit/Passenger Ratio" (DC-9-11. (L. 7940906 "Inspection Procedure . Flight Control" new or later change. (L. 942. Service Life Limits See NOTE 3 Certification Basis: Models DC-9-11.E.5). 7940643 or Model 717-200 Douglas Dwg. 885. 158. -32F -33F.5 in. -13.5 in. of MAC at Sta. -34F Models DC-9-81.4 in.5 in. of MAC at Sta. the movement of the various control surfaces must be carefully controlled by proper rigging of the Flight Control Systems.7 or (b) Plumb bob and grid plate at Sta. -15F. 1965. the provisions of SR-422B and the following exemptions: 415D . 7910641.437. (L. Other Operating Limitations See FAA Approved Airplane Flight Manual. -30. 147. 147.5). -14.Surface Throws. and 15F that incorporate one Type I and one Type III exit per side and tail cone exit). 1965. The airplane must therefore be rigged in accordance with the following: Model DC-9 Douglas Dwg. 658.E. of MAC at Sta. (L. 753. -33F Model DC-9-41 Model DC-9-51 Models DC-9-34. of MAC at Sta.362. 147.E. 1973 must comply with FAR 36 dated December 1.5). -15.5). 0). 158. -12. 69. "Fuel Jettisoning System" (See wts. -40 and -50 Series Airplanes). and Amendments 36-1 and 36-2. 3.5 Control Surface Movements To ensure proper operation of the airplane. All aircraft not flown before December 1. -34. and 4. -41. -51 CAR 4b dated December 31. (L. -32. Models DC-9-11. -14. -82. (L. -15. 424 . 147.4). (L. -12. Compliance with the following optional requirements has been established: .E. MAC 141. -15F Model DC-9-21 Models DC-9-31. 147.E. of MAC at Sta. 696. 1969.E.E. -32F. Amendments 4b-1 thru 4b-16.A6WE 68 Data Pertinent to All Models (cont’d) Operating Limitations See NOTES 2.1). -32.4 in. 1351(d) 25. as amended by amendments 25-1 through 25-40.697 25. applicable provisions of 14 CFR part 26 are included in this certification basis.979 25.1401 25. applicable provisions of 14 CFR part 26 are included in this certification basis.21 25. No.101(g) for changes to type certificates (TC).787 25.255 25. the items of equipment will be called out on the pertinent interior arrangement drawing. 26-1).809 25.721 Amendment * 25-15 25. No 26-3).101(g) for changes to type certificates (TC).1309 25. Models DC-9-81 and -82 FAR 25. For any future 14 CFR part 26 amendments.1333* 25.933 * 25.43 and 26.646. the holder of this TC must demonstrate compliance with the applicable sections.803(e) 25.671 Amendment 25-7 25-23 25-23 25-23 25-23 25-42 * 25-10 * (N/A) * 25.251(a) 25. § 26. and § 26.807 25.955 * * Section 25.812 25. Compliance has been found for the following regulations: 14 CFR § 26.645 and 4b. When the operating rules require emergency ditching equipment.803(c) 25. In such cases when the manufacturer has complied with part or all of the provisions of 4b." or "FAA Interior Schematic.251(c) 25.1001 Amendment * * 25.863 * 25-46 25-15 25-15 25-15 25-15 25-28 * 25.1435 25-36 * 25-11 *.1093 25.631 25. compliance with 4b.607 25.1203 25.361.646 must be demonstrated. 26-1)." Ice Protection Provisions 4b.571 25.672 25.951 25.395 25. effective May 2.251(e) 25. the holder of this TC must demonstrate compliance with the applicable sections.33 (Amdt. 26-0). Based on 14 CFR § 21. ** * ** 25-27 * Based on 14 CFR § 21.645 and 4b.11 (Amdt.645 and 4b.362(d) and 4b. including 4b.699 (N/A) * * * Section 25.811 25.69 A6WE Data Pertinent to All Models (cont’d) Certification Basis (cont’d) Ditching Provision 4b.742(e) and excluding 4b. § 26.701 25.11 (Amdt.646. For any future 14 CFR part 26 amendments.45 (Amdt. . Compliance has been found for the following regulations: 14 CFR § 26.1305 25.43 and 26.695 25. 26-0).No.No. 1965.45 (Amdt.640. effective February 1.251(b) 25. 1977. No. except for the following sections which are limited to showing compliance with the amendments indicated: Section 25. entitled "FAA Approval Drawing. (*) as Adopted at original issuance of FAR 25.1435 * Based on 14 CFR § 21. Applicable noise standards per FAR 36. for the Model DC-9-80/MD-80 series airplanes. 25-ANM-15. -87 and MD-88.721 25-15 25.43 and 26.1001. 1987.101(g) for changes to type certificates (TC). effective December 1. 1980.33 (Amdt. including Special Conditions and Exemptions mandated for the DC-9-80 series airplanes are applicable in total for the MD-88 airplane. No. (See Maximum Weights DC-9-81.933 * 25. Compliance has been found for the following regulations: 14 CFR § 26.807 25-15 25. "Automatic Takeoff Thrust Control System (ATTCS)". § 26. -83.A6WE 70 Data Pertinent to All Models (cont’d) Certification Basis (cont’d) Models DC-9-83. -87 and MD-88 All provisions. "In Flight Thrust Reversal".255 25. No 26-3). (**) Thru Amendment 25-41 for operation without normal electrical power. "Hydraulic System Failure".672 25. and "Environmental Flight Testing".21 25.1093 25-36 25. 1977. for the Model DC-9-80/MD-80 series airplanes. 415D. for the Model DC-9-80/MD-80 series airplanes.1401 25-27 25.863 * 25. Special Condition No.979 * 25.No. 25-95-WE-27.803(e) 25-15 25. MD-88 and MD-90-30 (N/A) indicates sections added to FAR 25 by later amendments for which compliance is not applicable. as applicable. issued April 3.45 (Amdt.811 25-15 25." issued October 19.812 25-28 25.1351(d) ** 25. Exemption No. applicable provisions of 14 CFR part 26 are included in this certification basis. 1980.631 25.701 * 25. -82. 1969.955 * 25.1305 25-11 25. ** 25. 26-1). -82. effective May 2. effective February 1. This includes retroactive noise requirements and requirements for an acoustical change in accordance with FAR 36-2 and 36-7 respectively.803(c)(d) 25-46 25. -83.1001 * 25. except showing compliance with the following sections is limited to the amendments as shown in the following table: Models DC-9-83.395 25. No. and through 36-12 for the -82. Part 25. autoland system and post stall recovery (stick pusher) system. -87. Applies to DC-9-81.697 25. Special Condition. -83. and § 26. .671 25.699 Amendment 25-7 (N/A) 25-42 * 25-10 * (N/A) * (N/A) * * * Section Amendment 25.607 25. and through 3620 for the MD-90-30. 25-88-WE-25. for the Model DC-9-80/MD-80 series airplanes. as amended by Amendments 25-1 through 25-40. the holder of this TC must demonstrate compliance with the applicable sections. as amended by Amendments 361 through 36-11 for the DC-9-81.951 * Section Amendment 25. For any future 14 CFR part 26 amendments. -87 and MD-88). FAR 25.1203 * 25. issued March 9.571 25. 1965. -87 and MD-88 (cont’d) Section 25.695 25.1333 * 25. "Fuel Jettisoning System". No. Special Conditions.251(d) 25. issued June 23. 26-0).11 (Amdt.1309 *. 1979.809 25-15 25. "Lightning Protection for new Electronic Systems.787 * 25. -87." Ice Protection Provisions 25.1309 as amended through Amendment 25-41.1415. & (c)(6) 25. -83.1415. compliance with 25.571(e)(1) 25.1411 and 25. as implemented by SFAR 27.979 25. See NOTE 8 for additional Seats and Stowable Berth information. 1965. effective February 1. Compliance with the following optional requirements has been established: Ditching Provisions 25.561(b)(3)(iii) 25. (c)(3).801.701 25. (***) Compliance as defined in McDonnell Douglas Report MDC-K4925 where some equipment installations and equipment comply with §25.783 25.1309 25.251(d) 25. -82. When the operating rules require emergency ditching equipment.809(f)(1)(v) 25.1401(b) & (f) THRU AMENDMENT 25-XX (*) 22 (**) 63 63 (**) 44 (**) 22 22 (**) 22 22 45 53 31 31 45 (**) 10 22 (***) 26 (*) Compliance with Amendment 25-42 as modified by the proposed requirements developed from results of FAA/JAA harmonization.1415 must be demonstrated. including 25. as amended by Amendment 25-1 thru 25-59 (except Section 25.562(a).1419 Part 25.1333). (c)(1).807(c) 25.1411 and 25.1411 and 25. the items of equipment will be called out on the pertinent interior arrangement drawing. In such cases when the manufacturer has complied with part or all of the provisions of 25.71 A6WE Data Pertinent to All Models (cont’d) Certification Basis: (cont’d) Applies to DC-9-81. (**) 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. MD-88 and MD-90-30 (cont’d) Air Pollution requirements of EPA regulations Part 87.109(a) 25. Model MD-90-30 The type certification basis for the MD-90-30 Model airplane is Federal Aviation Regulations Part 25.1309 as amended by Amendment 25-22 and others comply with §25. is applicable for the new equipment identified for the Model MD-88.807 (d) and excluding 25.809(b) & (f)(1)(i) 25.631 25.699(a) 25.777(c) 25. at the amendment current on the date of certification.607 25. (c)(5). as amended by Amendments 25-1 through 25-70 except as indicated below: SECTION 25. entitled "FAA Interior Schematic. . 26-1). No. effective February 1.43 and 26. § 26. Powerplant "In-Flight Thrust Reversal" is applicable. For those areas and components for which. 1992. (2) Special Condition. and § 26. exceptions were granted and are not impacted by the changes. 1996. 25-ANM-15 "Lightning Protection for New Electronic Systems" is applicable. Compliance has been found for the following regulations: 14 CFR § 26. as part of the original MD-90-30 certification. For any future 14 CFR part 26 amendments. A Special Condition on High Intensity Radiated Fields (HIRF) (S. the certification basis for the Saudi Arabian Airlines MD-90-30 configuration is Federal Aviation Regulations Part 25. Additional Certification Basis for Model MD-90-30 Equipped with Enhanced Flight Deck Configuration: (Approved March 3. 1965. No. 26-0). the holder of this TC must demonstrate compliance with the applicable sections. Note: For Model MD-90-30 equipped with Enhanced Flight Deck configuration. 25-88-WE-25. The Special Conditions applying to the Model MD-90-30 are as follows: (1) Special Conditions No. . Flight Test "Environmental Flight Testing" is not required since FAR 25.45 (Amdt. No 26-3).A6WE 72 Data Pertinent to All Models (cont’d) Certification Basis: (cont’d) Model MD-90-30 (cont’d) Based on 14 CFR § 21.253(a)(2)(iii) Amendment 54 incorporates its intent. 1998. refer to additional certification basis. 25-ANM-60) is required as indicated in Issue Paper G-4.C. applicable provisions of 14 CFR part 26 are included in this certification basis. In addition. Based on the date of notification of major changes.101(g) for changes to type certificates (TC). (4) Special Condition No. Stage 3. For this configuration. as amended by Amendments 25-1 through 25-84. "Automatic Takeoff Thrust Control System" is not required since "Automatic Reserve Thrust Control System" (ARTS) is deleted. No.33 (Amdt. 25-ANM-26 "Windshear" is applicable. no additional justification is required. 25-95-WE-27 Airframe "Hydraulic System Failure" is applicable. 1998) The Saudi Arabian Airlines MD-90-30 configuration is equipped with six-across flight deck Liquid Crystal Displays. Closed May 6. in conjunction with the MD-90-30 certification basis. April 5.No. (3) Special Condition No. approved on March 3. an additional certification basis was established.11 (Amdt. 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. 519(b)(2) 25.701(d) 25. These changes do not constitute a substantial change and therefore compliance was substantiated to the certification basis of the baseline MD-90-30.571(e)(1) 25. 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.809(b) Static Ground Load Conditions Emergency Landing Dynamic Conditions (Note 2) (Note 3) (Note 4) Bird Strike Speed Fasteners Bird Strike Damage (8lb) Flap & Slat Interconnection Doors Emergency Exit Arrangement (Not part of TC Basis) Emergency Egress Assist Means & Escape Routes 25. effective February 1. there are eight major changes that support the flight deck changes. 1965. 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. • • • • • • • • 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 25.783(f) 25. 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.631 25.562 (b)(2) (c)(5) (c)(6) 25. as amended by Amendments 25-1 through 25-82 except as indicated below: SECTION SUBJECT 25.810(a)(1)(i) THRU AMENDMENT 25-XX 81 (Note 1) 64 71 22 (Note 5) 22 22 (Note 6) 53 31 (Note 7) .607 25.73 A6WE 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. (Note 7) Compliance to § 25. in lieu of § 25. CIP D-06 (4) FAR 25.810(a)(1)(v) 25.11 (Amdt. Amendment 25-15. MD-80. (Note 3) Exception for HIC for pilot/co-pilot seats. Amendment 25-45. CIP B-04 (2) FAR 25. will comply with Amendments 25-82.A6WE 74 Data Pertinent to All Models (cont’d) Certification Basis: (cont’d) Model 717-200 (cont’d) 25. Amendment 25-72. For any future 14 CFR part 26 amendments.810(a)(1)(v). or those 717-200 systems common to the MD-80 or MD-90 that have prior safety analysis performed. in lieu of § 25. MD-80. observer seat and front row passenger seats only. (Note 2) Except for cockpit floor deformation 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.101(g) for changes to type certificates (TC).809(f)(1)(i).103. Compliance has been found for the following regulations: 14 CFR § 26.33 times the vertical static reaction applied in any direction. (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 25-22.45 (Amdt.519(b)(2)(ii) is applicable only for a vertical limit load of 1. 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. (Note 8) Compliance to § 25. "Accelerate-stop Distance". applicable provisions of 14 CFR part 26 are included in this certification basis. Compliance required with row to row HIC requirements for all seating in addition to cabin attendant seats. the holder of this TC must demonstrate compliance with the applicable sections.33 times the vertical static reaction at each jacking point acting singly and in combination with the horizontal load of 0.979(b) 25. The detail information is provided in MDC report MDC 95K9080.810(a)(1)(i). DC-9. and § 26. CIP B-01 (3) FAR 25. 26-1). CIP D-14 . No 26-3). New or significantly modified DC-9. (Note 4) Exception for leg injury criterion for pilot/co-pilot seats and observer seats.807(a)(3). Based on 14 CFR § 21.43 and 26. The type certification basis for the 717-200 Model airplane includes the following Equivalent Safety as indicated below: (1) FAR 25. 26-0). "Emergency Exit Access". "Emergency Exits". § 26. Systems & Installation Safety Analysis (Note 8) (Note 29) 10 39 22 (Note 9) (Note 1) Except that §25. No. "Stall Speed". Compliance required for the passenger cabin floor.109(a).813(c)(1). (Note 5) This exception is for derivative structure only.1141(f)(2) 25.No.809(f)(1)(v).856(a) 25. Amendment 25-72. and MD-90 systems modified to implement new functions or applications for the 717200 design will comply with Amendment 82 for the modified areas.33 (Amdt.1309 Emergency Egress Assist Means & Escape Routes Thermal/Acoustic Insulation Materials Pressure Fueling System Powerplant Controls for APU Equipment. and MD-90 systems. 1965 for Models DC-9-11. “Operation Without Normal Electric Power” is applicable. (4) Special Condition No. 1981 for Model DC-9-82 October 17.1397(a). as amended by Amendment 36-1 through Amendment 36-21 for the 717-200 airplane. 1994. 1968 for Model DC-9-41 April 5. 25-ANM-26. Type Certificate/Production Basis Type Certificate No. 1998. 1966 for Model DC-9-31 March 1. 1980 for Model DC-9-81 July 29. 1969. “Seats With Inflatable Lapbelts” is applicable. 1976 for Model DC-9-34 August 25. 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. 1987 for Model MD-88 November 4. effective on December 1. 1968 for Model DC-9-21 August 11. The FAA/JAA formally accepted the change in model designation on August 21. 1966 for Model DC-9-15 December 19. A6WE approved: November 23. 25-144-SC. (2) Special Condition No. The FAA/JAA initially accepted the change in model designation on May 4. as implemented by FAR part 34. 1998 with the new model designation of 717-200. 1976 for Model DC-9-34F November 3. and -14 January 21. (5) Special Condition No. Subsequently. -12. 1967 for Model DC-9-32F February 21. McDonnell Douglas Corporation merged with The Boeing Company. All compliance substantiation and related correspondence from the FAA/JAA using the MD-95 or MD-9530 model designator is applicable to the 717 or 717-200. 1987 for Model DC-9-87 December 10. Applicable noise standards per FAR part 36. 1968 for Model DC-9-33F November 25. 1998. and updated its application for Type Certification on March 27. 1967 for Models DC-9-15F and -32 October 4. McDonnell Douglas Corporation originally made application for Type Certification of the MD-95-30 on August 8. CIP F-18 The Special Conditions applying to the Model 717-200 are as follows: (1) Special Conditions No. 25-ANM-60. 1985 for Model DC-9-83 October 21. 25-95-WE-27.75 A6WE Data Pertinent to All Models (cont’d) Certification Basis: (cont’d) Model 717-200 (cont’d) (5) FAR 25. "Color Specifications". 1994 for Model MD-90-30 September 1. as applicable. “Dual Hydraulic System Failure” is applicable. 1999 for Model 717-200 . 1975 for Model DC-9-51 April 20. -13. “Windshear Triggered Autothrottle System” is applicable. “High Intensity Radiated Fields (HIRF) is applicable. 25-489-SC. (3) Special Condition No. DAC-33247. -13. MDC-07282. location and capacity of lounges and lavatories. 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. "Master Weight and Balance Manual. 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." Model DC-9-15F Report No. (a) A current weight and balance report. 53496 (fus 2220) and subsequent. 1998. LB-32360. storage spaces and coatrooms. and -15 Report No. when FAA approved. Models DC-9-11." Report No. Required Equipment The basic required equipment as prescribed in the applicable airworthiness regulations (See Certification Basis) must be installed in the aircraft for certification. 53496 (fus 2216). These reports contain. will carry a statement to that effect. Service Information The repairs called out in the Douglas Model DC-9 Structural Repair Manual are FAA approved." Model DC-9-21 Report No. "Master Weight and Balance Manual. information relative to location of all passenger and crewmember seats. Chapter 1. "Master Weight and Balance Manual. -53493 (fus 2209). buffets. -32 Report No. 53494 (fus 2213) 53495 (fus 2215). 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. including a list of equipment included in certificated empty weight. "Master Weight and Balance Manual. NOTES NOTE 1. "Master Weight and Balance Manual. PC-27 and PC-700 into one Production Certificate. On January 30. -12. Refer to appropriate Model DC-9 Report(s) for factor serial number affectivity. All Douglas Service Bulletins and other service information. Chapter 1. The Boeing Company and the McDonnell Douglas Corporation (MDC) merged the two Production Certificates." Models DC-9-31. or refer to. DAC-33098." . 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).A6WE 76 Data Pertinent to All Models (cont’d) Certification Basis: (cont’d) Production Basis: Production Certificate Number 700. and the required placards in the passenger compartment. -14. 53603 (fus 2218) 53497 (fus 2219). location and capacity of all cargo and baggage compartments. Chapter 1. Chapter 1. DAC-66957. Chapter 1. PC-700. Chapter 1. "Master Weight and Balance Manual." Model DC-90-30 Report No. MD-88 . "Master Weight and Balance Manual. 47040. MDC-97K9261." Model DC-9-51 Report No. "Master Weight and Balance Manual. MDC-J6201. MDC-J8358." (b) The airplane must be loaded so that the C. for each airplane. constant speed drive and starter for the DC-9 airplane (VSCF generator for MD-90-30 or IDG for 717-200). is within specified limits at all times." Models DC-9-32F. "Master Weight and Balance Manual. -82. MDC-91K0981. Chapter 1. Chapter 1. Chapter 1 with Section 1-8 "Master Weight and Balance Manual. Serial Nos." Model DC-9-41 Report No. 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. MDC-J7283. "Master Weight and Balance Manual. -32 (VC-9C) Report No. Chapter 1.959 (DC-9-81. Chapter 1. -87. "Master Weight and Balance Manual. Chapter 1." Model DC-9-81. (except as noted above) -33F and -34F Report No. Report No. considering fuel loading and usage. The engine oil tank capacities shown elsewhere in this data sheet include only the usable oil for which the tanks must be placarded." Model DC-9-87 Report No." Report No. MDC-J7283. DAC-33098. (c) The weight of system fuel and oil. Chapter 1. 47147 and 47148. all of which must be included in the airplane empty weight. as defined below. System Oil: The weight of oil remaining in the engine. "Master Weight and Balance Manual. is listed in the Master Weight and Balance Manual specified in paragraph (a) above." Model 717-200 Report No. "Master Weight and Balance Manual. -82. Chapter 1. gear retraction. DAC-33871. DAC-33870. DAC-33756. Chapter 1.77 A6WE Data Pertinent to All Models (cont’d) NOTES (cont’d) NOTE 1. MDC-J7282. MD-90-30 and 717-200).416 (DC-9-11 thru -51) or FAR 25. MDC-J3855. 47041. "Master Weight and Balance Manual." Model DC-9-34 Report No. lines and tanks after subtracting the oil in the tanks which is above the standpipe (zero gage) levels." Model DC-9-32F (C-9B) Report AN 01-1B-40. and hydraulic fluid.G. and movement of crew and passengers from their assigned positions. "Master Weight and Balance Manual. . Chapter 1. -83." Model DC-9-32F (C-9A Aeromed). "Master Weight and Balance Manual. and MD-88 Report No. Chapter 1. This includes the unusable tank fuel as defined by CAR 4b. (cont’d) Model DC-9-32F." Report No. -83. "Weight and Balance Data Handbook. and revisions thereto. MDC-94K9000. MD-90 structural components which are life limited are listed in Part 1. -41. Fuselage tank pumps must be off for all take-offs and landings for those airplanes which have fuselage tanks that supply the engines directly.500 lb in flight." Reports MDC-J0005. -32. -82. (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. MD-90 and 717 non-structural components which are life limited. 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. -33F. -82. in the tanks which is unavailable to the engines under critical flight conditions as defined in CAR 4b. and must be replaced as indicated therein. MD-88 .416 (DC-9-11 thru -51) or FAR 25. -83. -81. of Section 1 to the Airworthiness Limitations Instructions (ALI) Document. Life Limited Parts and Airworthiness Limitations. NOTE 2. CA 90807-5309 OR Please send a Service Request via the Boeing Communication System (BCS) . -87. MDC-96K9063 and MDC-92K9145. "DC-9/ MD-80/ MD-90/ 717 Special Compliance Items Report. MD-90-30 and 717-200.959 (DC-9-81. A6WE. The center wing tank will supply fuel to both engines directly. and must be replaced as indicated therein. are hereby incorporated as part of Data Sheet No. MD-88." This "unusable" fuel is included in system fuel as indicated in 1(c) above and need not be accounted for separately. 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. and fuel system ALIs are listed in report MDC-92K9145. -34.A6WE 78 Data Pertinent to All Models (cont’d) NOTES (cont’d) NOTE 1. Report MDC-94K9000. DC-9 and MD-80 structural components which are life limited are listed in Report MDCJ0005 and must be replaced as indicated therein. NOTE 3. (See Footnote (1) under Maximum Weights). -51. -83. 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. Safe Life Limits. 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 maximum unbalance in fuel between the main tanks should not exceed 1. -32F. DC-9. fuel system Critical Design Configuration Design Limitations (CDCCL). MD-80. -34F. 717 structural components which are life limited are listed in Report MDC-96K9063 (717 ALI). including tank trapped fuel. -87. (cont’d) (d) The "unusable" fuel is that amount of fuel. Refer to Cabin Pressurization in the FAA Approved Airplane Flight Manual (AFM) Limitations Section 1 for Takeoff and Landing Unpressurized. Weight 40 lb 40 lb 40 lb 150 lb 175 lb 240 lb 220lb 170 lb Airplane Series_ Series 10. A6WE. Data Pertinent to All Models (cont’d) . -217A and -217C engines on the DC-9-83 airplanes. For DC-9-83: Pratt and Whitney JT8D-219 engines may be intermixed in combination with JT8D-209. -32. -82. Chapter 71. MD-90-30 and 717-200 as applicable: Equipment Functional Check Intervals as defined in FAA Approved MDC Report MDCJ1271. -83. load rating. (cont’d) The following applies to the Models DC-9-81. -217. -20. For DC-9-81.79 A6WE Data Pertinent to All Models (cont’d) NOTES (cont’d) NOTE 3. For MD-90-30: Intermix not permitted. and any later approved revisions thereto. MDC-92K9064..0-19 NOTE 4. -83.) Tire Spec.6 (Bias) 7929726 7911309 7926174 7935357 PS5554 PS5621 26x6. rated pressure. -40. For specific dimensional and weight limits. -20. provided that the intermixed combinations and their respective limitations are covered in the FAA Approved Airplane Flight Manual. 7924523 7929726 Tire 26x6. -87.(a)] Series 10.5-21 H41x15.6 (Chine) 26x6. Brake Wear Limits: See Report No. and -41 Series 10. -34 and -34F Series 80 and MD-88 MD-90-30 717-200 (a) For 717-200: Bias/Radial nose tire intermix not permitted. etc. and Models -31. MDC-93K9014 "MD-90 Certification Maintenance Requirements" for the MD-90 and MDC 98K9284 "717-200 Certification Maintenance Requirements" for the 717-200. the maximum thrust must be limited to that associated with the lowest powered engine. MD-90-30 and 717-200 (see Note 4a) 717-200 [see Note 4. shall not be extended. "Twinjet Brake Wear Limits. Combinations of engines which can be intermixed and their respective limitations are covered in the FAA Approved Airplane Flight Manual. -87 and MD-88: Engine installation "Intermix" configurations may be utilized in accordance with MDC DC-9-80 Maintenance Manual. For 717-200: Intermix not permitted. Dwg." NOTE 4. see the following McDonnell Douglas Tire Specification Drawing: (See Note 14 for DC-9 Series explanation. Los Angeles Aircraft Certification Office. Such later revisions may be used only if approved by the Manager. Models -31. -30. static unbalance.5x16.5-20 H44. are hereby incorporated as part of Data Sheet No. -80.6R14 (Radial) 40x14 41x15-18 H44. -50 and Models -33F. MD-88.5x16. Engine Intermix. and -32F Series 40. and the applicable appendices of the FAA Approved Airplane Flight Manual. "DC-9-80 Fixed Maintenance Intervals" for the MD-80. NOTE 5. 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. -32. speed rating. -82. MD-88. If engines are intermixed. Copies may be obtained from the manufacturer at the above address. Max. -50. or FAR. -13. -32F. -14.A6WE 80 NOTES (cont’d) NOTE 6. location of armrest and seat back recline. -33F. -34.. -12. -82. (a) To assure that required overwing emergency exits will meet the pertinent CAR. refer to the passenger seat installation drawing prepared by the manufacturer for each operator and approved by the Aircraft Engineering Division. for each of the approved seat models called out on the drawings. 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. MD-88 and MD-90-30 PASSENGER CAPACITY (1) 172 (6) (12) TYPE I / SIDE 1 EXITS REQUIRED TYPE III / SIDE TAIL EXIT 2 (7) 1 (8) TYPE I LH SIDE AFT 1 TYPE I / SIDE 1 EXITS REQUIRED TYPE III / SIDE TAIL EXIT 2 (7) 1 (8) TYPE I LH SIDE AFT 1 (11) DC-9-87 PASSENGER CAPACITY (1) 139 (6) . and -34F PASSENGER CAPACITY (1) 109 (1) 127 127 TYPE I / SIDE 1 1 1 (9) EXITS REQUIRED TYPE III / SIDE 2 (2) 2 (2) 2 (2) TAIL EXIT 1 (3) 1 (5) 1 (10) TYPE I / SIDE 1 EXITS REQUIRED TYPE III / SIDE 2 (2) TAIL EXIT 1 (5) TYPE I / SIDE 1 EXITS REQUIRED TYPE III / SIDE 2 (2) TAIL EXIT 1 (5) DC-9-41 PASSENGER CAPACITY (1) 128 (6) DC-9-51 PASSENGER CAPACITY (1) 139 (6) DC-9-81. etc. -15F and –21 PASSENGER CAPACITY (1) 79 94 109 EXITS REQUIRED TYPE I / SIDE TYPE III / SIDE 1 1 1 1 1 2 (2) TAIL EXIT 1 (3) 1 (4) 1 (3) DC-9-31. -83. (b) Maximum Passenger Capacity: DC-9-11. -15. -32. p. (4) Required exit consists of tail cone exit. (9) Installation of approved inflatable slide required. (2) Aft Type III exit per side may be limited to Type IV qualifications. not installed on all aircraft and not required for the maximum passenger capacity. (8) Tail cone exit must be in compliance with the FAA requirements contained in FAA letter dated November 16. (3) Required exit consists of tail cone exit with assist rope. (6) Aircraft must show compliance with § 25.809(f)(1) effective October 24.807(c)(6)(ii).2. Chinese fuel conforming to Specification SY 1008-80 (RP-3/Number 3 Jet Fuel). 424. 2016. effective October 24. A-1.807 through 25. 1967. 1977. If installed. and any other fuels conforming to P & W Service Bulletin No. 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).m. slide and assist space per Exemption No. (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. (cont’d) 717-200 PASSENGER CAPACITY (1) 134 (6) NOTE 7.807(c)(6)(iii) and FAR 25. . (10) Tail cone exit must show compliance with § 25. the following fuels are eligible provided and to the extent they are allowed by P & W Service Bulletin No. No fuel control adjustment is required when switching fuel types. (a) TYPE I / SIDE 1 EXITS REQUIRED TYPE III / SIDE 2 (7) TAIL EXIT 1 (1) Passenger capacity may be increased by 5 when inflatable slides are installed at Type I exits. (b) Shell anti-static fuel additive ASA-3 may be used if concentration delivered to the engine does not exceed 1 (one) p. 1967.81 A6WE Data Pertinent to All Models (cont’d) NOTES (cont’d) NOTE 6. & JET B) Russian fuels conforming to specification GOST 10227 (RT and TS-1). 2016 or P & W Specification No.813 (see certification basis for applicable amendment). (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. (11) Optional. ASTM D1655 (Type JET A. For Pratt and Whitney engines. (5) Tail cone exit must show compliance with§ 25. 522 and later revisions may be used separately or mixed in any proportions without adversely affecting the engine operation or power output. must meet all Type I exit requirements of FAR 25. such as berths. passenger and lounge). Russian fuels conforming to Specification GOST 10227 (RT and TS-1). 91-88.562 for transporting non-ambulatory occupant. -12. NOTE 9. British: Def. Stan. Also wide cut fuel grades conforming to ASTM D1655-94 Jet B. the JP-4/JET B procedures (restrictions and limitations) are followed: Kerosene type fuels as defined in ASTM D-1655 (Type JET A. (c)(2).358(c)(DC-9-11 thru -51). For the 717-200. CAN/CGSB-3. The model designation for serial numbers noted is as delivered by the manufacturer.785(f). MD-90-30 passenger seats must also comply with FAR 25. A-1.-87. MIL-T-5624 (Grades JP-4 and JP-5).785(i) (DC-9-81. although they may comply with TSOC39 or TSO C-127. the following fuels are eligible provided and to the extent they are allowed by the International Aero Engines V2500A5/-D5 Installation and Operating Manual (IAE0043)/(IAE-0174). Canadian: CAN/CGSB-3.562(b). Air 3404 and 3405 (French). fuel conforming to ASTM. & JET B) . MIL-T-5624 Grade JP4. Appropriate FAA Airplane Approved Flight Manual pages must be obtained from the manufacturer for the new model.22. (c)(7).-82. -12. 91-86. . The new nameplate must include the date of conversion and the new model designation. 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). -13. Jet A or A-1. -83. must also be demonstrated to comply with FAR 25. all replacement seats (crew.D-1655. § 25. and Russian fuels conforming to specifications GOST 10227-86 (RT and TS-1). Chinese fuel conforming to Specification SY 1008-80 (RP-3/Number 3 Jet Fuel). MD-88 and MD-90-30). (e) For BR700-715 Engines. must also be demonstrated to comply with CAR 4b. and provided that for any wide cut fuels. -82. may be used. NOTE 8.-83. installed adjacent to the original nameplate. All 717-200 seats must comply with § 25. -14) by adding a new nameplate. 91-91. 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. MIL-T-5624 Grade JP5 and MIL-T-83133 Grade JP8. 91-87. (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. The original nameplate must not be removed. MIL-T-83133 (Grade JP-8). British: Def. and fuels conforming to the specifications listed in the latest applicable issue of the International Aero Engines V2500A5/-D5 Installation and Operating Manual (IAE0043)/(IAE-0174) may be used. obtained from the manufacturer.23 and 3-GP-24 (Canadian). as specified in engine Type Certificate Data Sheet E40NE. (c)(4). compartments. Other installations. IATA: JP-4 type fuel (1994). although they may comply with TSO-C127. MD-88 and MD-90-30) (Certification basis for applicable amendment) (DC-9-81. buffets. These fuels may be used separately or mixed in any proportions without adversely affecting the engine operation or power output. IATA Kerosene Type. Stan. -87. French: AIR 3407. passenger and lounge).562 as defined by the type certification basis. Any serial numbers eligible for Model DC-9-11. -13. (d) For IAE engines. -14 may be converted to another model (DC9-11. (c)(8) and stowable berth is not required to comply with FAR 25.A6WE 82 Data Pertinent to All Models (cont’d) NOTES (cont’d) NOTE 7. All replacement seats (crew. MDC-J0846. changes of equipment and repairs. (b) The maintenance.83 A6WE Data Pertinent to All Models (cont’d) NOTES (cont’d) NOTE 10. 47573. 47664. the following must be accomplished: (a) The C-9A Aeromed military litters are not FAA approved and must be removed from the aircraft. and a new nameplate was installed adjacent to the original to include this new model designation and date of conversion. S/N 45728 was modified to a DC-9-14 per MDC Letter C1-25-6317. 1971. (c) All aircraft returned to civil operations must comply with all applicable Airworthiness Directives. . C-9B airplanes are the same as the basic Model DC-9-32F. DC-9-11 aircraft. VC-9C airplanes are the same as the basic Model DC-9-32 except for interior configuration and installation of 2250 gal. dated May 10. 47566. 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. 47572. S/N's 45729 and 45730 were modified to DC-9-14. 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. must be approved by the FAA. 1970. were modified to Model DC-9-32 in accordance with Report No. Modifications. 47647. 1967. S/N's 47442. dated August 26. 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. per MDC Letter C1-25-2156. A modification nameplate shall be installed adjacent to the original nameplate and shall contain the following information: (e) NOTE 11. dated March 9. (d) Aircraft will be certificated as a Model DC-9-32 or DC-9-32F as applicable. DC-9-31 aircraft. Prior to operation as a commercial aircraft. which affect the safety or performance of the aircraft. 47720. DC-9-12 aircraft. DC-9-11 aircraft. C-9A airplanes are the same as the basic Model DC-9-32F except for the interior and loading ramp. 47649. S/N 47056 was modified to a DC-9-14 per MDC Letter C1-25-3641. 47721 and 47727. Modifier's Name __________________________ Civil Model __________________________ Date of Modification __________________________ 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. 47450. 47638. and 53-199 and McDonnell Douglas letter 88FAA-C1-E65-3498. NOTE 15. The DC-9 Series 10 (DC-9-10) includes DC-9-11. S/N's 45846. all interior materials must comply with the fire protection requirements of § 25. and MD-88. and DC-9-15F. DC-9-34. 47351.853. DC-932 (VC-9C). be in accordance with the damage tolerance principles (Amendment 25-45) of the current FAR 25. installed adjacent to the original nameplate. all interior materials must comply with the fire protection requirements of § 25. In the MD-90-30. NOTE 12. were converted to MD-88s in accordance with McDonnell Douglas Service Bulletins 22-89. must be accompanied by the official designator (i. NOTE 13. The use of the suffix . airplanes must be made in accordance with Douglas Report MDCJ0846. These programs were prepared in accordance with the provisions of AC 91-56. In the DC-9-81. obtained from the manufacturer. A new nameplate was installed adjacent to the original to include this new model designation and date of conversion. 1990.. The new nameplate must include the date of conversion and the new model designation.e. DC-9-15. corrosion.853. 47026. 47068. or -87. 34-188. -82. 1988. DC-933F or DC-9-34F Model designations does not alter the aircraft. For example. Series 50 (DC-9-50) includes DC-9-51. DC-9-13. The official designator for the McDonnell Douglas Model DC-9-81. Subsequent changes of model designation to S/N's 47026. 1977. effective August 20.A6WE 84 Data Pertinent to All Models (cont’d) NOTES (cont’d) NOTE 11 (cont’d) DC-9-32 aircraft. by adding a new nameplate. DC-9-32F. -83. all interior materials must comply with the fire protection requirements of FAR 25. DC-9-32F. -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. -83. . 34-183. The "MD" designator may be used in parentheses.853. 47023. 1988. DC-9-33F. service. Series 20 (DC-9-20) include DC-9-21. The Model DC-9 Series airplanes have a mandated supplemental Structural Inspection Program (SIP).CF instead of -F when referring to the DC-9-15F. DC-9-81 airplane S/N's 48095-48098 were reassigned to DC-9-82 airplanes prior to manufacture and delivery. -83. effective May 2. to the extent practicable. S/Ns 49532 through 49539. and production damage) and the inspection and/or modification criteria should. dated June 1. effective September 26. DC-9-32F (C-9A. were modified to a DC-9-31. and DC-9-34F. DC-9-32. -82. DC-9-12. Appropriate FAA Approved Airplane Flight Manual pages must be obtained from the manufacturer for the new model. DC-9-82 airplanes. Series 30 (DC-9-30) includes DC-9-31. A DC-9-81 airplane.571 standards. and. The original nameplate must not be removed. -87. Evaluation of structural elements. or -87 is the DC-9-81. type of damage considered (fatigue. Appropriate FAA Airplane Approved Flight Manual pages must be obtained from the manufacturer for the new model. Series 40 (DC-9-40) includes DC-9-41. In the 717-200. C-9B). DC-9-14. a DC-9-34F airplane and a DC-9-34CF airplane are the same and the Model designations may be referred to interchangeable. 47351. 47352. DC-9-81 (MD-81)). 47352. but. 47020. NOTE 14. may be designated a DC-9-82. " NOTE 17. McDonnell Douglas MD-80. See MDC Service Bulletin MD-90-34-006 for establishing the basis for operational approval. NOTE 21 The MD-90-30 airplane is qualified for operations within Reduced Vertical Separation (RVSM) airspace. for the MD-90-30. "FAA Interior Schematic. and 25.671(c)(1). In December 2000." NOTE 20 The DC-9-81. the engine supplier has changed their name to Rolls-Royce Deutschland Ltd & Co KG. 94K9143 "Nuisance Discrepancies Report.785(h)(2). 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. and 47639. the engine supplier changed their name to Rolls-Royce Deutschland GmbH. entitled. NOTE 24 The 717-200 airplane time limited exemption has been removed since Boeing has shown compliance to § 25. SA2542SO. the engine suppliers name was BMW Rolls-Royce Aero Engines. 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. For MD-90-30 Model. -87 and MD-88 aircraft are qualified for operations within Reduced Vertical Separation (RVSM) airspace. 1999.85 A6WE Data Pertinent to All Models (cont’d) NOTES (cont’d) NOTE 16. The tasks and their frequencies given in this report form a part of the instructions for continued airworthiness as required by FAR Part 25. Appendix H. FSN’s 47431. -83. . the lower cargo compartments are certified as "Class C" equipped with smoke detection system and fire suppression system.785(h)(1). See MDC Service Bulletin MD-80-34-289 for establishing the basis for operational approval. NOTE 22 Deleted. for the 717-200. issuance of a Standard Airworthiness Certificate is prohibited unless modifications of STC’s SA2541SO. See MDC Report 99K9203 (latest revision) for establishing the basis for operational approval. NOTE 23 For the 717-200 airplane. refer to McDonnell Douglas Report No. 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. NOTE 19. NOTE 18. The location of flight attendant seats demonstrated to comply with the direct view requirements of § 25. are shown on the manufacturers interior arrangement drawing. systems and components. and SA2446SO are removed and the airplanes are returned to original type design. -82. Amendment 25-72 and § 25. engines. In January 2000. the APU life limited components are listed in the manufacturer's maintenance manual. The 717-200 airplane is qualified for operations within Reduced Vertical Separation (RVSM) airspace. 47474. NOTE 26 For DC-9-32. For MD-90-30 Systems Anomalies. 47477.571(b). effective September 2.. Amendment 25-111. for the 717-200 was met on airplane serial numbers 55051... NOTE 29 14 CFR § 121. Maintenance. 2003. -87. “717 Extended Range Operations Configuration. .312(e).. This finding does not constitute approval to conduct ETOPS operations.856. -82. Amendment 121-289 requires thermal/acoustic insulation materials installed in the fuselage to meet the requirements of § 25. 55187. 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. 55099. 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. and Procedures”. -83. This finding does not constitute approval to conduct ETOPS operations.END.. and 55190-55194. Compliance to § 25... and Procedures”.856(a). 55052.. Maintenance. “MD-80 Extended Range Operations Configuration. 55098.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. .. Amendment 25-111..