TCDS A2WE

Page No. 1 2 3 4 5 6 7 8 9 10 11 12 13 14 15 Rev. No. 28 19 19 19 19 19 19 19 21 19 23 19 19 19 19 Page No. 16 17 18 19 20 21 22 23 24 25 26 27 28 Rev. No. 19 19 19 19 27 19 19 19 19 24 26 19 27 DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION A2WE Rev. 28 SABRELINER NA-265 NA-265-20 NA-265-30 NA-265-40 NA-265-60 NA-265-65 NA-265-70 NA-265-80 April 29, 2014 | | TYPE CERTIFICATE DATA SHEET NO. A2WE This data sheet, which is a part of Type Certificate No. A2WE, prescribes conditions and limitations under which the product for which the Type Certificate was issued meets the airworthiness requirements of the Civil Air Regulations. Type Certificate Holder Sabreliner Aviation LLC Perryville Municipal Airport 1390 Highway H Perryville, Missouri 63775 Type Certificate Holder Record North America Rockwell Corporation transferred to Rockwell International Corporation on April 19, 1968 Rockwell International Corporation transferred to Sabreliner Corporation on June 30, 1983 Sabreliner Corporation transferred to Sabreliner Aviation LLC on April 29, 2014 I. Model NA-265 (Transport Aircraft), Approved March 23, 1962 Military Model T-39A Model NA-265-20 (Transport Aircraft), Approved August 31, 1962 Military Model T-39B Model NA-265-30 (Transport Aircraft), Approved December 20, 1962 Military Model T-39D Engines 2 Pratt and Whitney Turbo Wasp JT12A-6A Fuel Commercial Aircraft Turbine Engine Fuel conforming to PWA Specification PWA 522 as revised. Fuel Controls 2 Holley P/N 31501 hydro-mechanical controls. Minimum flow schedule must be adjusted between 308-325 p.p.h. per PWA components calibration schedule (CCS) requirements. Engine Limits Engine Model JT12A-6A Static thrust (see Engine Data Sheet 1E9, NOTE 5) Takeoff (5 min) 3,000 lbs. Maximum continuous 2,570 lbs. Maximum permissible engine rotor operating speed 16,700 r.p.m. A2WE -2- Rev. 28 I. Model NA-265, Model NA-265-20, Model NA-265-30 (cont’d) Engine Limits (cont’d) Maximum permissible gas temperature at the turbine outlet Takeoff 677°C 1,250°F Maximum continuous 577°C 1,070°F Maximum acceleration (2 min) 677°C 1,250°F Starting (momentary) 525°C 977°F Oil inlet temperature 121°C 250°F Maximum permissible air bleed extraction of total engine airflow Two engine operation (each engine) Idle to maximum continuous 4.0% Maximum continuous through takeoff 3.0% One engine operation Idle to maximum continuous 4.4% Maximum continuous through takeoff 3.7% NOTE: Thrust setting: Appropriate thrust setting curves (EPR) in FAA Approved Airplane Flight Manual must be used for control of the engine thrust. Engines installed must meet the minimum thrust coefficient (Cg) as shown in the following table. Engines are to be equipped with 443 series tapered PT5 probes. PT5/PO 1.2 1.4 1.6 1.8 2.0 2.2 2.4 2.6 Cg - P and WA Acceptance Test* .850 .870 .890 .905 .918 .925 .934 .938 Cg - installed in NA-265** .897 .908 .915 .920 .923 .926 .927 .928 *With jet nozzle and exhaust pipe per PWA Drawing No. 403201 **With tail pipe per NR Drawing No. 265-420023-11 Oil Aircraft Turbine Engine Lubricant conforming to P&W Specification PWA 521, as revised. Airspeed Limits (CAS) NA-265 NA-265-20 NA-265-30 VMO (Max. operating at S.L.) 333K 333K VMO (Max. operating - 21,340 ft.) 346K 346K VMO (Max. Operating above 21,340 ft.) .765M .765M VA (Maneuvering at S.L.) 218K 205K VA (Maneuvering - 39,000 ft. 236K - - MA (Maneuvering above 39,000 ft. .765M - - VA (Maneuvering - 40,500 ft.) - - 228K MA (Maneuvering above 40,500 ft.) - - .765M VFE (Flaps down 23.5° (100%) indicated) 183K 183K VLO (Landing gear operating) 183K 183K VLE (Landing gear extended) 183K 183K VSB (Speed brake extension) Any speed Any speed (Speed brake retraction) Any speed Any speed V (Fuel jettisoning) Any speed Any speed NOTE: For variation between values shown and corresponding IAS Limits, for the airspeed system installed, refer to FAA Approved Airplane Flight Manual. For Buffet Envelope and Limit Maneuvering Load Factor variation with airspeed, weight, fuel loading and altitude, refer to FAA Approved Airplane Flight Manual. A2WE Rev. 28 Model NA-265, Model NA A-265-30 (cont'd) C.G. Range NA 265, -20. -30 C. G. Digrem жі АпІ NA 285 C. G. Diogram 111 NA 75570 C. G ram 12) Aleplane Graza Maighe lIbe, X 107) (9) Modified per NOTE 71al 121 Modified per NOTE 7ibl 13 12 Zere Fuel Weight 10 20 27 Camer of Gravity (Percens of MACI The landing gear retraction moment is -380 in.-lb. and results in a negligible forward movement of the C.G. When the airplane is loaded within the above C.G. envelope limits as applicable at both the start of takeoff and zero fuel weights, and the restrictions concerning crew and passenger movement specified in the FAA Approved Load and Balance Schedule are complied with, the airplane will remain within the approved C.G. limits. A2WE -4- Rev. 28 I. Model NA-265, Model NA-265-20, Model NA-265-30 (cont’d) Maximum Weight (in Pounds) Airplane Model NA-265, -20, -30 NA-265 Modified per Note 7(a) NA-265-30 Modified per Note 7(b) Equipped with brake P/N 9541544 9543102 9543102 9550338 Anti-skid installed and operational No No Yes Yes Ramp and taxi 17,760 17,760 18,650 18,650 Start of takeoff 17,450 17,450 18,340 18,340 Airborne 17,375 17,375 18,265 18,265 Airborne (no fuselage fuel) 16,527 -- -- -- Zero fuel 10,984 10,984 12,250 12,250 Landing 13,000 14,000 17,500 17,500 NOTE: Fuel jettison valves required for operation in excess of 105 percent of the maximum landing weight. Refer to the FAA Approved Airplane Flight Manual for fuel jettisoning procedures. See NOTE 1 Minimum Crew 2 pilots Maximum Passengers 4 - NA-265, -20, -30 7 - NA-265 when modified per NOTE 7(a) NOTE: See NOTE 1(a) and (b) Maximum Baggage Airplane Model Airplane Serial Numbers Location Inches from Datum Capacity (pounds) Max. Load (p.s.f.) C.G. Inches from Datum NA-265 NA-265-20 NA-265-30 265-1 thru 265-88 270-1 thru 270-6 277-1 thru 277-10 285-1 thru 285-32 Forward 145-206 250 100 180 NA-265 276-1 thru 276-55 Forward Aft 145-206 298-320 250 170 100 50 180 315 NA-265 Modified per NOTE 7(a) 265-1 thru 265-88 276-1 thru 276-55 Forward Aft 145-206 298-320 270 340 100 50 180 309 Fuel Capacity Pressure Refueling (lbs.) Gravity Refueling (lbs.) C.G. Inches from Datum Fuel at 6.50 lb/gal. Total Usable Total Usable 2 wing tanks 6,021 5,867 5,951 5,797 256 1 fuselage tank 1,046 1,043 1,065 1,063 345 See NOTE 1(c) for system fuel Oil Capacity 1.6 gal./engine, 12 pounds each. C.G. is 324 inches from datum. This weight must be included in the aircraft empty weight. Maximum Operating 45,000 feet Altitude NOTE: Pressure cabin service life is based on the following pressurization limits which must not be exceeded. Airplane Model Airplane Altitude (feet) Cabin Altitude (feet) NA-265, NA-265-20, and NA-265-30 Sea Level to 8,000 8,000 to 45,000 Ambient Pressure 8,000 A2WE -5- Rev. 28 I. Model NA-265, Model NA-265-20, Model NA-265-30 (cont’d) Serial Numbers Eligible Civil Model Rockwell International Serial No. Military Model Military Model Deviation NR Report No. NA-265 265-1 thru 265-88 276-1 thru 276-55 USAF T-39A NA-62-399 NA-265-20 270-1 thru 270-6 USAF T-39B NA-62-636 NA-265-30 277-1 thru 277-10 285-1 thru 285-32 USAF T-39B NA-62-637 NOTE: Military Aircraft bearing the above serial numbers and having been issued Form ACA-970, Conformity Certificate - Military Aircraft, are eligible for FAA Certificate of Airworthiness when brought into the type design configuration as referenced in the deviation report. In addition, a supplemental name plate must be installed adjacent to the original name plate, listing the name of the modifier, the date of modification, and the civil model designation. The original name plate, however, must not be removed. See NOTE 5. Fatigue Life Limits See NOTE 3(b). II. Model NA-265-40 (Transport Aircraft), Approved April 17, 1963 Engines 2 Pratt & Whitney Turbo Wasp JT12A-6A or 2 Pratt & Whitney Turbo Wasp JT12A-8 NOTE: Engines may be intermixed on airplane S/N 282-1 through 282-97. See FAA Approved Airplane Flight Manual for Operating Limitations. Airplane S/N 282-98 and subsequent require two JT12A-8 engines. Fuel Commercial Aircraft Turbine Engine Fuel conforming to PWA Specification PWA 522 as revised. Fuel Controls Hamilton Standard JFC-46-8 Hydro-Mechanical Controls (JT12A-8 engine) Hamilton Standard JFC-46-4 Hydro-Mechanical Controls (JT12A-6A engine) Engine Limits See Section I for Engine Model JT12A-6A, Engine Limits Engine Model (See Fatigue Life Limits Data for All Models and NOTE 7(d)) JT12A-8 Static thrust (See Engine Data Sheet 1E9, NOTE 5). Takeoff (5 min.) 3,300 lbs. Maximum continuous 3,000 lbs. Maximum permissible engine rotor operating speed 16,700 r.p.m. Maximum permissible gas temperature at the turbine outlet Takeoff 718°C 1,325°F Maximum continuous 655°C 1,211°F Maximum acceleration (2 min.) 718°C 1,325°F Starting (momentary) 525°C 977°F Oil inlet temperature 121°C 250°F Maximum permissible air bleed extraction of total engine airflow Two engine operation (each engine) Idle to maximum continuous 4.0% Maximum continuous through takeoff 3.0% A2WE -6- Rev. 28 II. Model NA-265-40 (cont’d) Engine Limits (cont’d) One engine operation Idle to maximum continuous 4.4% Maximum continuous through takeoff 3.7% NOTE: Thrust setting: Appropriate thrust setting curves (EPR) in FAA Approved Airplane Flight Manual must be used for control of the engine thrust. Oil Aircraft Turbine Engine Lubricant conforming to P&W Specification PWA 521, as revised. Airspeed Limits (CAS) S/N 282-1 thru 282-62 not modified per Note 6 S/N 282-1 thru 282-62 modified per Note 6 SN 282-63 & subsequent VMO (Max. operating) (at S.L.) 333K 350K VMO (at 21,340 ft.) 346K - - MMO (above 21,340 ft.) .765M - - VMO (at 21,130 ft.) - - 365K MMO (above 21,130 ft. - - .800M VA (Maneuvering) (at S.L.) 195K 197K VA (at 42,500 ft.) 218K - - VA (at 44,180 ft.) - - 220K MA (above 42,500 ft. .765M - - MA (above 44,180 ft.) - - .800M VFE (Flaps down 15.7°) (66% indicated) 225K 225K VFE (Flaps down 23.5°) (100% indicated) 179K 179K VLO (Landing gear operating) 179K 179K VLE (Landing gear extended) 179K 179K VSB (Speed brake extension) Any speed Any speed (Speed brake retraction) Any speed Any speed V (Fuel jettisoning) Any speed Any speed VTR (Minimum operating, max. reverse thrust) 60K 60K NOTE: For variation between values shown and corresponding IAS limits, for the airspeed system installed, refer to FAA Approved Airplane Flight Manual. For Buffet Envelope and Limit Maneuvering Load Factor variation with airspeed, weight, fuel, loading and altitude, refer to FAA Approved Airplane Flight Manual. A2WE -7- Rev. 28 II. Model NA-265-40 (cont’d) C.G. Range Model NA-265-40 (Transport Aircraft) (S/N 282-1 thru 282-85 & S/N 282-90 thru 282-199) Gross weight vs. Center of Gravity (Approved Limits) The landing gear retraction moment is -500 in.-lbs. and results in a negligible movement of the C.G. When the airplane is loaded within the above C.G. envelope limits as applicable at both start of takeoff and zero fuel weights, and the restrictions concerning crew and passenger movement specified in the FAA Approved Load and Balance Schedule are complied with, the airplane will remain within the approved C .G. limits. A2WE -8- Rev. 28 II. Model NA-265-40 (cont’d) The landing gear retraction moment is -500 in.-lbs. and results in a negligible movement of the C.G. When the airplane is loaded within the above C.G. envelope limits as applicable at both start of takeoff and zero fuel weights, and the restrictions concerning crew and passenger movement specified in the FAA Approved Load and Balance Schedule are complied with, the airplane will remain within the approved C .G. limits. A2WE -9- Rev. 28 II. Model NA-265-40 (cont’d) Maximum Weight (in Pounds) Minimum Crew 2 pilots NOTE: The delivery configuration minimum flight crew is one pilot and one flight crew assistant. No persons other than the flight crew may be carried. See FAA Approved Airplane Flight Manual (Addendum A) for additional limitations. Maximum Passengers 7 Maximum Baggage Location In. from Datum Capacity (pounds) Capacity* (pounds) Max. load (p.s.f.) In. from Datum Forward 145-206 200 270 100 170 Aft 298-320 340 510 50 311 *When airplane is modified per NOTE 7(e). Fuel Capacity Fuel at 6.70 lbs./gal.: Pressure Refueling (lbs.) Gravity Refueling (lbs.) C.G. Inches Total Usable Total Usable from Datum 2 wing tanks 6,206 6,047 6,134 5,975 256 1 fuselage tank 1,078 1,075 1,098 1,096 345 See NOTE 1(c) for system fuel. Oil Capacity 1.6 gal./engine, 12 pounds each. C.G. is 324 inches from Datum. This weight must be included in the aircraft empty weight. Maximum Operating Altitude 45,000 feet NOTE: Pressure cabin service life is based on the following pressurization limits which must not be exceeded: Airplane Altitude Cabin Altitude Sea Level to 21,000 ft. Sea Level 21,000 ft. to 40,000 ft. 8.2 p.s.i. differential 40,000 ft. to 45,000 ft. 8,000 ft. altitude Serial Nos. Eligible 282-1 through 282-199 Fatigue Life Limits See NOTE 3(b) Airplane Model NA-265-40 NA-265-40 Modified Per: NA-265-40 S/N 282-1 thru S/N 282-97 S/N 282-98 and sub- sequent S/N 282-1 thru 282-97 only NOTE 7(c) NOTE 7(f) NOTE 7(e) S/N 282-86 thru -89 (FAA) Note 7(e) Equipped with Brake P/N 9542384 9542384 9550338 9543102 9543102 9550338 9550338 9550338 9550338 Anti-Skid Installed and Operational no yes no no yes no no no yes Ramp and Taxi 17,760 18,650 19,035 17,760 18,650 18,650 19,035 19,922 20,372 With JT12A-8 Start of Takeoff Airborne 17,450 17,375 18,650 18,650 18,650 18,650 17,450 17,375 18,650 18,650 18,650 18,650 18,650 18,650 19,612 19,537 20,172 20,172 With JT12A-6A Start of Takeoff Airborne 17,450 17,375 18,340 18,340 N/A N/A 17,450 17,450 18,650 18,265 18,650 18,265 18,650 18,650 N/A N/A N/A N/A Zero Fuel Landing 12,800 14,000 12,800 15,000 12,800 17,500 12,800 14,000 12,800 17,500 12,800 17,500 12,800 17,500 12,800 17,500 13,300 17,500 A2WE -10- Rev. 28 III. Model NA-265-60 (Transport Aircraft), Approved April 28, 1967 Engines 2 Pratt and Whitney Turbo Wasp JT12A-8 Fuel Commercial Aircraft Turbine Engine Fuel conforming to PWA Specification PWA 522 as revised. Fuel Controls Hamilton Standard JFC-46-8 Hydro-Mechanical Controls Engine Limits See Section II for Engine Model JT12A-8, Engine Limits. Oil Aircraft Turbine Engine Lubricant conforming to PWA Specification PWA 521, as revised. Airspeed Limits VMO (Max. operating) (at S.L.) 350K VMO (at 21,130 ft.) 365K VMO (above 21,130 ft.) .800M VA (at S.L.) 195K VA (at 44,300 ft.) 220K MA (above 44,300 ft.) .800M VFE (Flaps Down 16.7 deg.) (66% ind.) 225K VFE (Flaps Down 25 deg.) (100% ind.) 180K VLO (Landing Gear Operating) 180K VLE (Landing Gear Extended) 180K VSB (Speed Brake Extension) Any Speed (Speed Brake Retraction) Any Speed V (Fuel Jettisoning) Any Speed VTR (Minimum operating, Full reverse thrust) 60K NOTE: For variation between values shown and corresponding IAS limits, for the airspeed system installed, refer to FAA Approved Airplane Flight Manual. For Buffet Envelope and Limit Maneuvering Load Factor variation with airspeed, weight, fuel loading, and altitude, refer to FAA Approved Airplane Flight Manual. A2WE -11- Rev. 28 III. Model NA-265-60 (cont'd) C.G. Range Model NA-265-60 (Transport Aircraft) Serial Numbers 306-1 Thru 306-63 (See NOTE 8) Gross Weight Vs. Center of Gravity (Approved Limits) 21 LANCING SEAR PATENCH 20 AIRPLANE GROSS WEIGHT -- THOUSANDS OF POUNDS 19 18 17 16 - FORWARD FUGHT LIMIT- 20 28 32 36 AIRPLANE CENTER OF GRAVITY -- % MAC A2WE -12- Rev. 28 III. Model NA-265-60 (cont’d) The landing gear retraction moment is -475 in.-lb. and results in a negligible movement of the C.G. When the airplane is loaded within the above C.G. envelope limits as applicable at both start of takeoff and zero fuel weights and the restrictions concerning crew and passenger movement specified in the FAA Approved Load and Balance Schedule are complied with, the airplane will remain within the approved C.G. limits. Maximum Weights (In pounds - With or without anti-skid equipment) Ramp and taxi 20,372 Start of takeoff 20,172 Airborne 20,172 Zero fuel 13,250 (S/N 306-1 throught 306-63) (See NOTE 8) Zero fuel 13,800 (S/N 306-64 and subsequent) (See NOTE 8) Landing 17,500 Minimum Crew 2 pilots NOTE: Delivery configuration minimum flight crew is one pilot and one flight crew assistant. No persons other than the flight crew may be carried. See FAA Approved Airplane Flight Manual (Addendum A) for additional limitations. Maximum Passengers 10 A2WE -13- Rev. 28 III. Model NA-265-60 (cont’d) Maximum Baggage Location Inches from Datum Capacity (Pounds) Max. Load (p.s.f.) Inches from Datum Forward 143-206 300 100 170 Aft 336-371 510 80 342 Fuel Capacity Fuel at 6.70 lbs./gal. Pressure Refueling (lbs.) Gravity Refueling (lbs.) C.G. Inches Total Usable Total Usable from Datum 2 wing tanks 6,206 6,047 6,134 5,975 273 1 fuselage tank 1,078 1,075 1,098 1,096 383 See NOTE 1(c) for system fuel Oil Capacity 1.6 gal./engine, 12 pounds each. C.G. is 362 inches from Datum. This weight must be included in the aircraft empty weight. Maximum Operating Altitude 45,000 feet NOTE: Pressure cabin service life is based on the following pressurization limits which must not be exceeded: Airplane Altitude Cabin Altitude Sea Level to 21,000 ft. Sea level 21,000 ft. to 40,000 ft. 8.2 p.s.i. differential 40,000 ft. to 45,000 ft. 8,000 ft. altitude Serial Nos. Eligible 306-1 through 306-199 Fatigue Life Limits See NOTE 3(b) IV. Model NA-265-70 (Transport Aircraft), Approved June 17, 1970 Engines 2 Pratt and Whitney Turbo Wasp JT12A-8 Fuel Commericial Aircraft Turbine Engine Fuel conforming to PWA Specification PWA 522, as revised. Fuel Controls Hamilton Standard JFC-46-8 Hydro-Mechanical Controls Engine Limits See Section II for Engine Model JT12A-8, Engine Limits Oil Aircraft Turbine Engine Lubricant conforming to PWA Specification PWA 521, as revised. Airspeed Limits VMO (Max. operating) (at S.L.) 350K (CAS) VMO (at 21,130 ft.) 365K MMO (above 21,130 ft.) .800M VA (Maneuvering) (at S.L.) 221K VA (at 40,000 ft.) 243K MA (above 40,000 ft.) .800M VFE (Flaps Down 16.7°) (66% indicated) 225K VFE (Flaps Down 25°) (100% indicated) 180K VLO (Landing Gear Operating) 180K VLE (Landing Gear Extended) 180K A2WE -14- Rev. 28 IV. Model NA-265-70 (cont’d) Airspeed Limits (cont’d) VSB (Speed Brake Extension) Any Speed (Speed Brake Retraction) Any Speed V (Fuel Jettisoning) Any Speed VTR (Minimum operating, Full reverse thrust) 60K NOTE: For variation between values shown and corresponding IAS limits, for the airspeed system installed, refer to FAA Approved Airplane Flight Manual. For Buffet Envelope and Limit Maneuvering Load Factor variation with airspeed, weight, fuel loading, and altitude, refer to FAA Approved Airplane Flight Manual. C.G. Range Model NA-265-70 (Transport Aircraft) Gross Weight vs. Center of Gravity (Approved Limits) The landing gear retraction moment is +591 in.-lb. and results in a negligible movement of the C.G. When the airplane is loaded within the above C.G. envelope limits as applicable at both start of takeoff and zero fuel weights and the restrictions concerning crew and passenger movement specified in the FAA Approved Load and Balance Schedule are complied with, the airplane will remain within the approved C.G. limits. A2WE -15- Rev. 28 IV. Model NA-265-70 (cont’d) Maximum Weights (In pounds - With or without anti-skid equipment) Ramp and taxi 21,200 Start of takeoff 21,000 Airborne 21,000 Zero fuel 14,300 Landing 18,500 NOTE: Fuel jettison valves are required for operation in excess of 105 percent of the maximum landing weight. Refer to the FAA Approved Airplane Flight Manual for fuel jettisoning procedures. See NOTE 1. Minimum Crew 2 pilots NOTE: Delivery configuration minimum flight crew is one pilot and one flight crew assistant. No persons other than the flight crew may be carried. See FAA Approved Airplane Flight Manual (Addendum A) for additional limitations. Maximum Passengers 10 Maximum Baggage Location Inches from Datum Capacity (Pounds) Max. Load (p.s.f.) Inches from Datum Forward 143-206 300 100 170 Aft 336-371 510 80 342 Fuel Capacity Fuel at 6.70 lbs./gal. Pressure Refueling (lbs.) Gravity Refueling (lbs.) C.G. Inches Total Usable Total Usable from Datum 2 wing tanks 6,206 6,047 6,134 5,975 273 1 fuselage tank 1,338 1,333 1,369 1,365 383 See NOTE 1(c) for system fuel Oil Capacity 1.6 gal./engine, 12 pounds each. C.G. is 362 inches from Datum. This weight must be included in the aircraft empty weight. Maximum Operating 45,000 feet Altitude NOTE: Pressure cabin service life is based on the following pressurization limits which must not be exceeded: Airplane Altitude Cabin Altitude Sea Level to 21,000 ft. Sea Level 21,000 ft. to 40,000 ft. 8.2 p.s.i. differential 40,000 ft. to 45,000 ft. 8,000 ft. altitude Serial Nos. Eligible NA-370-1 through 370-199 Fatigue Life Limits See NOTE 3(b) V. Model NA-265-80 (Transport Aircraft), Approved November 30, 1973 (FAA Flight Inspection Aircraft), Approved April 15, 1975 NOTE: See Serial Numbers Eligible, page 20 Engines 2 General Electric Aft Turbofan CF700-2D-2 "B" Suffix Serial Number A2WE -16- Rev. 28 V - Model NA-265-80 (cont’d) Fuel Aviation Turbine Fuels conforming to General Electric Specification D50TF2, Current Revision Fuel Controls General Electric MFC-2 Engine Limits Engine Model CF700-2D-2 Static Thrust (see Engine Data Sheet E7EA, as revised) Takeoff 4,500 lbs. Maximum Continuous 4,120 lbs. Maximum Permissible Engine Rotor Speed 16,700 r.p.m. (101.2%) Maximum Permissible Fan Rotor Speed 9,000 r.p.m. (105.0%) Maximum Permissible Exhaust Gas Temperatures Takeoff (5 min.) 1365°F (741°C) Maximum Continuous 1335°F (724°C) Starting (2 sec.) 1670°F (910°C) Oil Reservoir Temperature Steady State 365°F (185°C) Maximum Permissible Bleed Air Extraction of Compressor Inlet Airflow 6.0% NOTE: Thrust Setting: Appropriate Thrust Setting Curves (EPR) in FAA Approved Airplane Flight Manual must be used for Control of Engine Thrust. If the EGT obtained, when using the chart MAXIMUM CONTINUOUS THRUST EPR SETTING, is less than 670° C. below 20,000 feet or 695° at or above 20,000 feet pressure altitude, increased performance may be obtained by increasing the EGT to 670°/695° C. If the EGT obtained when setting the chart EPR exceeds 670°/695° C., then maintain chart EPR setting and observe the 724° C. EGT limit. Oil Aircraft Gas Turbine Lubricating Oil conforming to General Electric Specification D50TFI, current revision. Airspeed Limits VMO (Max. operating) (at S.L.) 350K (CAS) VMO (at 21,200 ft.) 365K MMO (above 21,200 ft.) .800M VA (Maneuvering) (at S.L.) 221K VA (at 40,000 ft.) 243K MA (above 40,000 ft.) .800M VFE (Flaps Down 16.7º) (66% indicated) 225K VFE (Flaps Down 25º) (100% indicated) 180K VLO (Landing Gear Operating) 180K VLE (Landing Gear Extended) 180K (Landing-Taxi Lights Extended Speed) 250K VSB (Speed Brake Extension) Any Speed (Speed Brake Retraction) Any Speed NOTE: For variation between values shown and corresponding IAS limits, for the airspeed system installed, refer to FAA Approved Airplane Flight Manual.