TCDS T00012WI

Page No. 1 2 3 4 5 6 7 8 9 10 11 12 13 14 15 Rev. No. 18 10 16 9 15 15 18 16 17 14 13 12 18 16 15 DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION T00012WI Revision 18 Textron Aviation 680 680A Se ptember 18, 2025 TYPE CERTIFICATE DATA SHEET NO. T00012WI This data sheet, which is part of Type Certificate No. T00012WI, prescribes conditions and limitations under which the product for which the type certificate was issued meets the airworthiness requirements of the Federal Aviation Regulations. Type Certificate Holder Textron Aviation Inc. One Cessna Boulevard Wichita, Kansas 67215 Type Certificate Holder Record Cessna Aircraft Company transferred to Textron Aviation Inc. on July 29, 2015 I. Model 680 Sovereign (Transport Category ) S/N 680-0001 through 680-0500 Approved June 2, 2004; S/N 680-0501 and On Approved December 20, 2013 Engines S/N 680-0001 thru 680-0500 Two Pratt & Whitney Canada Corp. PW306C turbofans S/N 680-0501 and On Two Pratt & Whitney Canada Corp. PW306D turbofans Fuel Commercial kerosene Jet A, Jet A-1, Jet B, JP-4, JP-5, JP-8, TS-1, RT, and No. 3 Jet. Engine Limits Static thrust standard day, sea level S/N 680-0001 thru 680-0500 Takeoff 5,770 lb. Max. Continuous 5,770 lb. S/N 680-0501 and On Takeoff 5,907 lb. Max. Continuous 5,907 lb. Max. permissible engine rotor operating speeds (Takeoff and Maximum Continuous) N1 (fan) 105.0% (100% = 10,608 r.p.m.) N2 (Gas Gen.) 105.0% (100% = 26,930 r.p.m.) Max. permissible interturbine gas temperatures: Takeoff 920 Degrees C Max. Continuous 920 Degrees C Transient (20 sec.) and starting 950 Degrees C T00012WI Page 2 of 15 Rev. 18 I. Model 680 Sovereign (cont’d) Airspeed limitations (S/N 680-0001 thru 680-0500): Vmo (maximum operating) Below 8,000 ft. 270 KIAS (270 KCAS) 8,000 ft. to 29,833 ft. 305 KIAS (305 KCAS) Mmo above 29,833 ft. 0.80 M I (0.80 MACH calibrated) Va (maneuvering sea level) 30,300 lb. 169 KIAS (169 KCAS) See AFM for variations with weight and altitude. VRA (Rough air speed) Below 38,813 ft. 225 KIAS (225 KCAS) Above 38,813 ft. 0.73 M I (0.73 MACH calibrated) Flap extension speeds V FE (0° to 7° extension) 250 KIAS (250 KCAS) V FE (7° to 15° extension) 200 KIAS (200 KCAS) V FE (15° to 35° extension) 175 KIAS (174 KCAS) V MCA (Minimum control speed) Air 7 deg flaps 92 KIAS (93 KCAS) VMCA (Minimum control speed) Air 15 deg flaps 90 KIAS (91 KCAS) VMCL (Minimum control speed) Landing 15 deg flaps 88 KIAS (89 KCAS) VMCL (Minimum control speed) Landing 35 deg flaps 84 KIAS (84 KCAS) VMCG (Minimum control speed) Ground 7 deg flaps 96 KIAS (97 KCAS) VMCG (Minimum control speed) Ground 15 deg flaps 97 KIAS (98 KCAS) VLO (landing gear operating) 210 KIAS (207 KCAS) VLE (landing gear extended) 210 KIAS (207 KCAS) VSB (speed brakes extension) A ny speed with or without flaps Maximum autopilot operating speed Below 8,000 ft. 270 KIAS (270 KCAS) 8,000 to 29,833 ft. 305 KIAS (305 KCAS) Above 29,833 ft. 0.80 M I (0.80 MACH calibrated) Maximum tire ground speed 182 knots Airspeed limitations (S/N 680-0501 and On): Vmo (maximum operating) Below 8,000 ft. 270 KIAS (269 KCAS) 8,000 ft. to 29,833 ft. 305 KIAS (304 KCAS) Mmo above 29,833 ft. 0.80 M I (0.80 MACH calibrated) Va (maneuvering sea level) 30,775 lb. 193 KIAS (193 KCAS) (See AFM for variations with weight and altitude) VRA (Rough air speed) Below 38,813 ft. 225 KIAS (225 KCAS) Above 38,813 ft. 0.73 M I (0.73 MACH calibrated) Flap extension speeds VFE (Up (0°) to 1 (7°) extension) 250 KIAS (249 KCAS) VFE (1 (7°) to 2 (15°) extension) 200 KIAS (200 KCAS) VFE (2 (15°) to Full (35°) extension) 175 KIAS (175 KCAS) VMCA (Minimum control speed) Air 7 deg flaps 88 KIAS (88 KCAS) VMCA (Minimum control speed) Air 15 deg flaps 85 KIAS (85 KCAS) VMCL (Minimum control speed) Landing 15 deg flaps 84 KIAS (84 KCAS) VMCL (Minimum control speed) Landing 35 deg flaps 80 KIAS (80 KCAS) VMCG (Minimum control speed) Ground 7 deg flaps 88 KIAS (88 KCAS) VMCG (Minimum control speed) Ground 15 deg flaps 88 KIAS (88 KCAS) Rev. 18 Page 3 of 15 T00012WI I. Model 680 Sovereign (cont’d) Airspeed limitations (S/N 680-0501 and On) (cont’d): VLO (landing gear operating) 210 KIAS (210 KCAS) VLE (landing gear extended) 210 KIAS (210 KCAS) VSB (speed brakes extension) A ny speed with or without flaps Maximum autopilot operating speed Below 8,000 ft. 270 KIAS (269 KCAS) 8,000 to 29,833 ft. 305 KIAS (304 KCAS) Above 29,833 ft. 0.80 M I (0.80 MACH calibrated) Maximum tire ground speed 182 knots C.G. Range (Landing Gear Extended) Design C.G. Limits (S/N 680-0001 thru 680-0500): Forward: 18.00% MAC at 19,000 lb. to 23,700 lb. Linear variation from 18.00% MAC at 23,700 lb. to 21.43% MAC at 30,550 lb. Takeoff Forward 21.30% at 30,300 lb. Aft: 31.00% MAC at 17,500 lb. to 23,000 lb. 30.00% MAC at 26,000 lb. to 27,100 lb. 31.00% MAC at 28,500 lb. to 30,550 lb. With straight line variation between points. Landing Gear retracting moment -8,095 in-lb. C.G. Range (Landing Gear Extended) Design C.G. Limits (S/N 680-0501 and On): Forward: 18.00% MAC at 19,702 lb. to 23,700 lb. Linear variation from 18.00% MAC at 23,700 lb. to 21.67% MAC at 31,025 lb. Takeoff Forward 21.54% at 30,775 lb. Aft: 31.00% MAC at 18,345 lb. to 23,475 lb. 30.00% MAC at 26,475 lb. to 27,575 lb. 31.00% MAC at 28,975 lb. to 31,025 lb. With straight line variation between points. Landing Gear retracting moment -8,370 in-lb. Empty Wt. C.G. None Range MAC 107.06 in. (L.E. of MAC at +382.68 in. aft of datum) Maximum Weight S/N 680-0001 thru 680-0500: Takeoff 30,300 lb. Landing 27,100 lb. Ramp 30,550 lb. Zero Fuel 20,800 lb. S/N 680-0501 and On: Takeoff 30,775 lb. Landing 27,575 lb. Ramp 31,025 lb. Zero Fuel 21,000 lb. T00012WI Page 4 of 15 Rev. 18 I. Model 680 Sovereign (cont’d) Minimum Crew One pilot and one copilot for all flights Number of Seats Maximum 14 (two crew plus 12 passenger seats) Maximum Baggage S/N 680-0001 thru 680-0500: Aft cabin 295 lb. (+440.82 in. aft of datum) Tailcone 1,000 lb. (+522.07 in. aft of datum) S/N 680-0501 and On: Aft cabin 312 lb. (+441.63 in. aft of datum) Tailcone 1,000 lb. (+522.09 in. aft of datum) Fuel Capacity S/N 680-0001 thru 680-0500: (usable) Total usable fuel 11,223 lb. (1,675.2 gal). Two wing tanks with 5,611.5 lb. (837.6 gal) usable each (See NOTE 1 for unusable); +412.80 in. aft of datum. S/N 680-0501 and On: Total usable fuel 11,394 lb. (1,700 gal). Two wing tanks with 5,697 lb. (850 gal) usable each (See NOTE 1 for unusable); +413.43 in. aft of datum. Oil Capacity Tank mounted on each engine: 5.28 quarts usable each engine; (usable) +534.17 in. aft of datum (see NOTE 1). Maximum Operating 47,000 ft. Altitude Control Surface Elevator Up 16.6 +1/-0 degrees Movements Down 9.4 +1/-0 degrees Elevator Trim Tab Down 2.1 +/-0.5 degrees Down 11.0 +/-0.5 degrees The upper and lower elevator trim tab limits are both below the control surface neutral position. Rudder Right 30.5 +/-0.5 degrees Left 30.5 +/-0.5 degrees Rudder Trim Tab Right 3.0 +/-0.5 degrees Left 3.0 +/-0.5 degrees Horizontal Stabilizer Up 6.9 +/-0.5 degrees Down 1.2 +/-0.5 degrees Aileron Left Up 18.8 +/-0.5 degrees Down 13.4 +/-0.5 degrees Aileron Right Up 18.5 +/-0.5 degrees Down 13.6 +/-0.5 degrees Aileron Trim Tab Up 10.0 +/-0.5 degrees Down 10.0 +/-0.5 degrees Wing Flap Up 0 +/-0.2 degrees T.O. 7 +/-0.5 degrees T.O./Appr. 15 +/-1.0 degrees (680-0001 thru -0500) Land 35 +2.0/-2.0 degrees (680-0501 and On) Land 35 +1.0/-2.0 degrees Speed Brakes – Panels 5, 6 0-24.0 +/-1.0 degrees Speed Brakes – Panels 1, 10 0-35.0 +/-1.0 degrees Roll Spoilers – Panels 2, 3, 8, 9 0-35.0 +/-1.0 degrees Roll Spoilers – Panels 4, 7 0-24.0 +/-1.0 degrees See Airplane Maintenance Manual for rigging instructions. Rev. 18 Page 5 of 15 T00012WI I. Model 680 Sovereign (cont’d) Serial Nos. Eligible 680-0001 and On Datum 140.40 in. forward of the nose jack point. Leveling Means Longitudinal: Place level on the outboard fl oor panel at BL 13.00 inches, inside of the cabin door. Lateral: Place level across inboard seat trac ks behind crew seats at most aft position. Certification Basis (S/N 680-0001 thru 680-0500): 1. 14 CFR Part 25 effective February 1, 1965, as amended by Amendments 25-1 through 25-98. 2. 14 CFR Part 34 effective Se ptember 10, 1990, as amended by Amendments 34-1 through 34-3. 3. 14 CFR Part 36 effective December 1, 1969, as amended by Amendment 36-1 through 36-28. 4. Compliance with the Noise Control Act of 1972. 5. Special Conditions. a. No. 25-214-SC, High Intensity Radiated Fields (HIRF). b. No. 25-248-SC, Side-Facing Single-Occupant Seats. c. No. 25-680-SC, Non-Rechargeable Lith ium Batteries, effective to design changes applied for after May 26, 2017. 6. Exemptions. a. Exemption No. 7625A, from the general occupant protect ion requirements of §25.785(b) for multiple-occupancy, side-facing divans b. Exemption No. 8280, from the lateral trim requirements of §25.161(d) (see NOTE 11). c. Exemption No. 10089, from oxygen dispen sing unit requirements of §25.1447(c)(1). 7. Equivalent Levels of Safety (ELOS). a. TC2548WI-T-AG-1, Ditching Em ergency Exits for Passengers. b. TC2548WI-T-AG-2, Door Betw een Passenger Compartments. c. TC2548WI-T-AG-3, Width of Aisle. d. TC2548WI-T-AG-4, Exit Loca tor and Exit Marking Signs. e. TC2548WI-T-AG-5, Placards for Main Entry Door. f. TC2548WI-T-AG-6, Gust and Continuous Turbulence Loads. g. TC2548WI-T-F-1, Use of 1-G Stall Speeds Instead of Mi nimum Speed in the Stall as a Basis for Determining Compliance. h. TC2548WI-T-P-1, Digital APU Indi cators (Oil Temperature, Gas Temperature, Tachometer). j. TC2548WI-T-P-2, Digital Engi ne Parameter, Fuel Flow. k. TC2548WI-T-P-5, Use of Single Fire Suppression Bottl e for Protection of APU and Baggage Compartment. l. TC2548WI-T-P-6, Certification of Thrust Reversers. m. TC2548WI-T-SE-5, Electric Standby Direction Indicator (Compass). n. TC2548WI-T-SG-1, Cabin Pressurization - Hi gh Altitude Takeoff and Landing Operation. p. Cessna-066650-SG-5, Operation at High Altitude Ai rports between 14,000 ft. and 15,000 ft. MSL. 8. 14 CFR 25.801 ditching not complied with. 9. Compliance with ice protection has been demonstrated in accordance with §25.1419. T00012WI Page 6 of 15 Rev. 18 I. Model 680 Sovereign (cont’d) Certification Basis (S/N 680-0501 and On): 1. 14 CFR Part 25 effective February 1, 1965, as amended by Amendments 25-1 through 25-98. a. Additions (as shown in table). Section Title Amendment Level Comments 25.899 Electrical bonding and protection against static electricity 25-129 Winglet installation and all aircraft installations requiring electrical bonding and p-static protection 25.1317 High Intensity Radiated Field (HIRF) Protection 25-129 Avionics upgrade, winglet installation, upgraded interior and autothrottle 25.1323 Airspeed indicating syste m 25-129 Entire airplane 25.1325 Static pressure systems 25-129 Entire airplane 25.1419 Ice protection 25-129 Entire airplane (see Additional Design Requirement (9)(c)) 25.1431 Electronic equipment 25-129 Winglet installation, powerplant improvements, and avionics systems 25.1459 Fli ght data recorders 25-129 When the o ptional flight data recorder is installed 25.1001 Fuel jettisoning system 25-129 Entire air plane Subpart B Flight 25-115 Entire airplane Subpart G Operating Limitations and Information 25-115 Entire airplane (see Additional Design Requirement (9)(c)) 25.773 Pilot compartment vi ew 25-108 Entire airplane 25.1329 Flight guidance system 25-119 Autothrottle only 25.981 Fuel tank ignition prevention 25-125 Winglet installation 25.1457(a)(6) Cock pit voice recorders 25-124 When an o ptional data link system is installed 25.1457(d)(5) Cockpit voice recorders 25-124 When the optional flight data recorder is also required 2. 14 CFR Part 34 effective Se ptember 10, 1990, as amended by Amendments 34-1 through 34-4. 3. 14 CFR Part 36 effective December 1, 1969, as amended by Amendment 36-1 through 36-28. 4. Compliance with the Noise Control Act of 1972. 5. Special Conditions. a. No. 25-248-SC, Side-Facing Single-Occupant Seats. b. No. 25-507-SC, Aircraft Electronic System Securi ty Protection from Unauthorized Internal Access. c. No. 25-508-SC, Aircraft Electronic System Securi ty Protection from Unauthorized External Access. d. No. 25-680-SC, Non-Rechargeable Lith ium Batteries, effective to design changes applied for after May 26, 2017. 6. Exemptions. a. Exemption No. 7625A, from the general occupant protect ion requirements of §25.785(b) for multiple-occupancy, side-facing divans. b. Exemption No. 10902, §25.901(c) Unc ontrollable High Thrust (see NOTE 12). 7. Equivalent Levels of Safety (ELOS). a. TC2548WI-T-AG-1, Ditching Em ergency Exits for Passengers. b. TC2548WI-T-AG-2, Door between Passenger Compartments. c. TC2548WI-T-AG-3, Width of Aisle. d. TC2548WI-T-AG-4, Exit Loca tor and Exit Marking Signs. e. TC2548WI-T-AG-5, Placards for Main Entry Door. f. TC2548WI-T-AG-6, Gust and Continuous Turbulence Loads. g. TC2548WI-T-P-6, Certification of Thrust Reversers. h. TC2548WI-T-SE-5, Electric Standby Direction Indicator (Compass). Rev. 18 Page 7 of 15 T00012WI I. Model 680 Sovereign (cont’d) Certification Basis (S/N 680-0501 and On) (cont’d): 7. Equivalent Levels of Safety (ELOS) (cont’d). j. AT5438WI-T-P-5, 14 CFR 25.901(c), 25.903(d)(2), 25. 1305, 25.1309(a)(b)(c), 25.1321(c)(2), 25.1322, 25.1549, Digital-Only Display of Turbine Engine High Pressure Rotor Speed (N2), Oil Pressure, Oil Temperature and Fuel Flow. k. AT5438WI-T-P-1, 14 CFR 25.1305(a)(4)(5)(6), 25.1549( a)(b)(c), Digital display of APU Instruments l. TC2548WI-T-P-5, 14 CFR 25.857, 25.1195, Use of Singl e Fire Suppression Bottle for Protection of both a Class C baggage compartment and APU installation. m. TC2548WI-T-SG-1, 14 CFR 25.841(a)(b)(6)(8), Cabin Pressurization - High Altitude Takeoff and Landing Operation. n. Cessna-072100-P-4, 14 CFR 25.1141(f)(2), Powerplant Valve Indication. o. TXTAV-011158-F-1, 14 CFR 25.125(a), Steep Approach Re ference Height of 35 feet instead of 50 feet. 8. 14 CFR 25.801 ditching not complied with. 9. Additional Design Requirements. a. Flight in Icing Conditions. The design complies with 25.21(g), 25.103, 25.105, 25.107, 25.111, 25.119, 25.121, 25.123, 25.125, 25.143, 25.207, 25.237 and 25.253, at Amendment 25-129, except that compliance may be shown using ice accretions based on the atmospheric icing conditions defined in Appendix C, at Amendment 25-0. b. In-Flight Engine Restart. A minimum restart capability after an all-engines-out scenario must be established under the following conditions using procedures provided in the Airplane Flight Manual (AFM): 1) During the take-off and the initial climb-out portion of the flight, the airplane has the capability for the flight crew to restore engine power immediately following an all-engine-out scenario and when the fuel source to the engine is restored. 2) During the high-altitude portion of the flight at cr uise speed and maximum altitude, the airplane has the capability for the flight crew to restart engines from a stabilized windmill speed prior to descending below an altitude of 15,000 ft., by showing either or both: a) All but one engine s hould be restarted and accelerated to produce maximum continuous thrust/power, or b) The engine(s) should be restarted, and the necessary thrust/power achieved, to enable the airplane to maintain level flight. 3) During flight at speeds greater than the minimum fl aps-up “holding speed” and at altitudes below 20,000 ft, the airplane has the capability for the flight crew to restart engines from a stabilized windmill speed prior to descending 5,000 ft., from the initiation of the restart procedure and prior to exceeding an airspeed of 300 knots, by showing either or both: a) All but one engine should be restarted and accelerated to produce maximum continuous thrust/power, or b) The engine(s) should be restarted, and the necessary thrust/power achieved, to enable the airplane to maintain level flight. c) AFM: The AFM text associated with the design maneuvering speed (V A) meets the requirements of 14 CFR 25.1583, Amendment 25-130. 10. 14 CFR Part 26 is not applicable. T00012WI Page 8 of 15 Rev. 18 I. Model 680 Sovereign (cont’d) Production Basis Production Certificate No. 4 amended to ad d Model 680, effective September 1, 2004. See NOTE 10 for airplane serial number effectivity of Production Certificate No. 4 on new airplane serial numbers. Equipment The basic required equipment as prescribed in the applicable airworthiness regulations (see Certification Basis) must be installed in the airplane for certification. NOTE 1. Current weight and ba lance information, including list of equipment included in certificated empty weight, and loading instructions are provided for each airplane at the time of original certification. The certificated empty weight and corresponding center of gravity location must include: S/N 680-0001 thru 680-0500 Unusable fuel 82.90 lb. at +405.86 in. Full oil 33.50 lb. at +534.17 in. Hydraulic Fluid 46.83 lb. at +505.53 in. S/N 680-0501 and On Unusable fuel 86.85 lb. at +410.66 in. Full oil 33.50 lb. at +534.17 in. Hydraulic Fluid 46.83 lb. at +505.53 in. NOTE 2. S/N 680-0001 thru 680-0500: Airplanes must be operated according to the FAA Approved AFM, part number 68FM-00 (or later FAA approved revision). All placards required by either the FAA Approved AFM, the applicable operating rules, or the certification basis, must be installed as specified for this Type Certificate via Parts List 6900000, Airplane Assembly. A useful placarding reference is the Textron Aviation Illustrated Parts Catalogue (IPC). Any discrepancies identified between the IPC and an aircraft under inspection need to be reconciled using the previously stated parts list. S/N 680-0501 and On: Airplanes must be operated according to the FAA Approved AFM, part number 68FMA-00 (or later FAA approved revision). All placards required by either the FAA Approved AFM, the applicable operating rules, or the certification basis, must be installed as specified for this Type Certificate via Parts List 6900000, Airplane Assembly. A useful placarding reference is the Textron Aviation Illustrated Parts Catalogue (IPC). Any discrepancies identified between the IPC and an aircraft under inspection need to be reconciled using the previously stated parts list. NOTE 3. See Maintenance Manual, Chapter 4 Airworthine ss Limitations, for inspections, mandatory retirement life information, and other requirements for continued airworthiness. NOTE 4. Aircraft definition for Type Certif icate is Parts List 6900000, Airplane Assembly. NOTE 5. Certification Maintenance Requirements (CMR) are found in the Maintenance Manual, Chapter 4. Engineering approval of the CMR’s is documented in the Cessna System Safety Assessment reports. NOTE 6. Deleted. NOTE 7. Model 680 has been approved for high altitude oper ations (altitudes above 41,000 ft) by compliance with certain Part 25 sections. To ensure the compliance is maintained, any modifications to the pressure vessel must be approved in accordance with the requirements as shown in the appropriate certification basis. To ensure pressurization compliance is not affected, this includes modifications which could result in a pressure vessel opening, either through crack-growth or antenna loss, greater than 3.98 sq. in. Rev. 18 Page 9 of 15 T00012WI I. Model 680 Sovereign (cont’d) NOTE 8. Model 680 received a Provisional Type Certificat e (TC) on December 24, 2003, that was subsequently cancelled when TC T00012WI was issued on June 2, 2004. NOTE 9. Model 680 has been shown to meet the airworth iness requirements for operations in Reduced Vertical Separation Minimum (RVSM) airspace. No Service Bulletin is associated with this requirement. All serial numbers are eligible. Each operator must obtain RVSM operating approval directly from the FAA. NOTE 10. The following serial number will be certified TC only: S/N 680-0501. Production Certificate No. 4 applies to the following Model 680 S/N: 680-0005 and On. NOTE 11. Exemption No. 8280, from the lateral trim requirem ents of 14 CFR 25.161(d), is only applicable to S/N 680-0001 thru 680-0049. NOTE 12. The FAA has concluded that the occurrence of any uncontrollable high-thrust failure condition, or any of the associated causal failures listed within Cessna Document (Maintenance Manual, Chapter 4 Airworthiness Limitations), may endanger the safe operation of an airplane. Consequently, the FAA recommends that operators be encouraged to report any such failures in accordance with Title 14, CFR Part 121.703(c), 125.409(c), and 135.415(c). NOTE 13. The following serial numbers are manufactu red under the name Cessna Aircraft Company: S/N 680-0001 thru 680-0547. NOTE 14. Company name change effect ive 7/29/2015. The following serial numbers are manufactured under the name Textron Aviation Inc.: S/N 680-0548 and On. NOTE 15. Required Equipment: The basic requi red equipment prescribed in the applicable airworthiness requirements (see certification basis) must be installed in the aircraft. Only hand fire extinguishers that use water and U.S. – UL 5B:C – Halotron BrX (2-BTP), C3H2BrF3, CAS Number 1514 82 5 OR U.S. – UL 2A:10B:C – Halotron (HCFC Blend-B), C2HCI2BrF3, CAS Number 306-83-2 are approved for use. No airplanes may have a combination of Halotron BrX AND Halotron I hand fire extinguishers installed. II. Model 680A Latitude (Transport Catego ry) S/N 680A0001 and On Approved June 5, 2015 Engines Two Pratt & Whitney Canada Corp. PW306D1 turbofans Fuel Commercial kerosene Jet A, Jet A-1, Jet B, JP-4, JP-5, JP-8, TS-1, RT, and No. 3 Jet Engine Limits Static thrust standard day, sea level Takeoff 5,907 lb. Max. Continuous 5,907 lb. Max. permissible engine rotor operating speeds (Takeoff and Maximum Continuous) N1 (fan) 105.0% (100% = 10,608 r.p.m.) N2 (Gas Gen.) 105.0% (100% = 26,930 r.p.m.) Max. permissible interturbine gas temperatures: Takeoff 920 Degrees C Max. continuous 920 Degrees C Transient (20 sec.) and starting 950 Degrees C Airspeed limitations VMO (maximum operating) Below 8,000 ft. 270 KIAS (270 KCAS) 8,000 ft. to 29,833 ft. 305 KIAS (305 KCAS) MMO above 29,833 ft. 0.80 M I (0.80 MACH calibrated) VA (maneuvering sea level) 30,800 lb. 191 KIAS (191 KCAS) See AFM for variations with weight and altitude. T00012WI Page 10 of 15 Rev. 18 II. Model 680A Latitude (cont’d) Airspeed limitations (cont’d) VRA (Rough air speed) Below 38,813 ft. 225 KIAS (225 KCAS) Above 38,813 ft. 0.73 M I (0.73 MACH calibrated) Flap extension speeds VFE (Position UP to 1) 250 KIAS (250 KCAS) VFE (Position 1 to 2) 200 KIAS (200 KCAS) VFE (Position 2 to FULL) 175 KIAS (175 KCAS) VMCA (Minimum Control Speed) Air Flaps 1 88 KIAS (88 KCAS) VMCA (Minimum Control Speed) Air Flaps 2 83 KIAS (83 KCAS) VMCL (Minimum Control Speed) Landing Flaps 2 83 KIAS (83 KCAS) VMCL (Minimum Control Speed) Landing Flaps FULL 78 KIAS (78 KCAS) VMCG (Minimum Control Speed) Ground Flaps 1 88 KIAS (88 KCAS) VMCG (Minimum Control Speed) Ground Flaps 2 91 KIAS (91 KCAS) VLO (Landing Gear Operating) 210 KIAS (211 KCAS) VLE (Landing Gear Extended) 210 KIAS (211 KCAS) VSB (Speed Brakes Extension) A ny speed with or without flaps Maximum autopilot operating speed Below 8,000 ft. 270 KIAS (270 KCAS) 8,000 to 29,833 ft. 305 KIAS (305 KCAS) Above 29,833 ft. 0.80 M I (0.80 MACH calibrated) Maximum tire ground speed 182 knots C.G. Range (Landing Gear Extended) Design C.G. Limits: Forward: 18.00% MAC at 19,700 lb. to 23,700 lb. Linear variation from 18.00% MAC at 23,700 lb. to 21.68% MAC at 31,050 lbs. Takeoff Forward 21.56% MAC at 30,800 lb. Aft: 31.00% MAC at 17,500 lb. to 31,050 lb. Landing Gear retracting moment -7,954 in-lb. Empty Wt. None C.G. Range MAC 107.06 in. (L.E. of MAC at +368.24 in. aft of datum) Maximum Weight Takeoff 30,800 lb. Landing 27,575 lb. Ramp 31,050 lb. Zero Fuel 21,430 lb. Minimum Crew One pilot and one copilot for all Flights Number of Seats Maximum 11 (two crew plus nine passenger seats) Maximum Baggage Tailcone 1,000 lb. (+500.09 in. aft of datum)