TCDS T00015AT

Page No. 1 2 3 4 5 6 7 8 9 10 11 12 13 14 15 16 17 18 19 20 Rev No. 22 21 21 22 21 22 22 22 22 22 22 22 22 22 22 22 22 22 22 22 Page No. 21 22 23 24 25 26 27 28 29 30 31 32 33 34 35 36 37 38 39 40 Rev. No. 22 22 22 22 22 22 22 22 22 22 22 22 22 22 22 22 22 22 22 22 Page No. 41 42 43 Rev. No. 22 22 22 DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION T00015AT Revision 22 Gulfstream GVI GVIII-G700 GVIII-G800 April 16, 2025 TYPE CERTIFICATE DATA SHEET NO. T00015AT This data sheet, which is part of Type Certificate No. T00015AT, 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: Gulfstream Aerospace Corporation 500 Gulfstream Road Savannah, Georgia 31408 I - GVI (Transport Category), Approved September 7, 2012 Engines: Two - Rolls-Royce Deutschland Ltd & Co KG Turbofan Engine Models: BR700-725A1-12 (Engine Type Certificate No. E00057EN) Fuel: Fuel shall conform to the specification as listed. See the approved Airplane Flight Manual for additional information. Kerosene Type (AVTUR, JP8) NATO Code F-24, F-34, F-35 American British Canadian ASTM D1655, Jet A ASTM D1655, Jet A-1 MIL-T-83133, JP-8 MIL-DTL-83133, JP8 DEF STAN 91-87 DEF STAN 91-91 CAN/CGSB-3.23 French CIS Chinese DCSEA 134/A TS-1 & RT (GOST 10227, AM 1) GSTU 320.001149943.007-97 (RT Type) GSTU 320.001149943.011-99 (TS-1 Type) GB 6537-2006 including the fuel additives limited to the concentrations stated in Annex A of GB 6537-2006 (see Chinese Fuel Additives note below) NOTE: Approved Chinese Fuel Additives 1. Static Dissipater additive: Stadis 450 2. Antioxidant: 2,6-ditertiary-butyl-4-methyl-phenol 3. Icing Inhibitor: Ethylene Glycol Monomethyl Ether or Diethylene Glycol Monomethyl Ether T00015AT Page 2 4. Metal Deactivator: N,N’-disalicylidene 1,2-propanediamine The following Chinese fuel additives are not approved for use on this Gulfstream aircraft model: Static Dissipater additive T1502 and antifriction additives T1601 or T1602. Engine Limits: See the approved Airplane Flight Manual for engine ratings. Auxiliary Power Unit (APU): Honeywell – Model RE220[GVI] See the approved Airplane Flight Manual for APU ratings. Airspeed Limits: Vmo / Mmo = 340 KCAS / 0.925 Mach For other airspeed limits, see the approved Airplane Flight Manual. C.G. Range: See the approved Airplane Flight Manual. Empty Weight C.G. Range: None. M.A.C. 187.24 in. (L.E. of M.A.C. = Fuselage Station 624.54) Datum: For weight and balance purposes, the zero datum is 100 inches forward of the tip of the radome. Leveling Means: Longitudinal: Leveling brackets along left nose wheel well door longeron STA 163.0 & 174.0. Lateral: Jig Point on Leveling Brackets on rear face of radome bulkhead STA 149 in nose wheel well. See Aircraft Maintenance Manual for level procedure. Maximum Weights (lbs): Configuration Max. Zero Fuel Max. Ramp Max. Take-Off Max. Landing TC Configuration 60,500 100,000 99,600 83,500 ASC 014 60,500 104,000 103,600 83,500 ASC 026 60,500 74,900 74,900 74,900 ASC 027 60,500 90,000 90,000 83,500 ASC 028 60,500 95,000 95,000 83,500 ASC 029* 60,500 100,000 99,600 83,500 ASC 030* 60,000 100,000 99,600 83,500 ASC 030*† 60,000 104,000 103,600 83,500 ASC 046* 59,500 100,000 99,600 83,500 ASC 046*† 59,500 104,000 103,600 83,500 ASC 082* 60,500 100,710 100,310 83,500 ASC 137 60,500 100,000 99,600 65,000 ASC 137† 60,500 104,000 103,600 65,000 *Note: ASC 014 is a prerequisite for ASCs 029, 030, 046, and 082. †Note: ASCs 030, 046 and 137 are applicable to both the G650 and G650ER. These rows represent the Configuration for the G650ER. Minimum Crew: 2 Pilot and co-pilot per the approved Airplane Flight Manual. Maximum Passengers: 19 With approved cabin interior (see Note 4). Maximum passenger capacity is limited by emergency exit door requirements of § 25.807(g). Page 3 T00015AT 0 For aircraft without an approved cabin interior (i.e., “green” aircraft as defined by Gulfstream drawing 60P0000000-001, GVI Aircraft Level Configuration Control Document, revision M, or later FAA approved revision). Maximum Occupants: 22 With approved cabin interior (see Note 4). Total reflects the maximum aircraft capacity of 19 passengers plus 3 crewmembers . 3 For aircraft without an approved cabin interior (i.e.“green” aircraft as defined by Gulfstream drawing 60P0000000-001, GVI Aircraft Level Configuration Control Document, revision M, or later FAA approved revision). Total represents 3 crewmembers and 0 passengers . Fuel Capacity: See the approved Airplane Flight Manual. Oil Capacity: Total engine oil tank capacity 26.4 lb. / 28.1 U.S. pints (each engine) Usable engine oil tank capacity 11.7 lb. / 12.5 U.S. pints (each engine) (Arm = +923.6) Oil weight based upon oil density 7.5 lb. per gal. Capacities shown above are for oil tankage only. Total engine oil is 26.4 lb. / 28.1 U.S. pints per engine APU oil 9.5 lb. / 10.2 U.S. pints (Arm = +923.6) Maximum Operating Altitude: 51,000 feet Control Surface Movements: To ensure proper operation of the airplane, the movement of the various control surfaces must be carefully controlled by proper rigging of the flight control system. The airplane must, therefore, be rigged according to the following approved data and the approved Aircraft Maintenance Manual. Conditions: System mode of operation (Maintenance Mode both aircraft and flight control system) On Ground Stationary = True Flap Position = 0° (Unless otherwise specified) Horizontal Stabilizer Position = 0° (Unless otherwise specified) Maximum control surface travel: Control Surface Maximum TEU/TEL (Deg.) Maximum TED/TER (Deg.) Aileron 18.0° to 20.0° 10.0° to 12.0° Rudder 25.0° to 27.0° 25.0° to 27.0° Elevator 23.0° to 25.0° 12.0° to 14.0° Outboard Spoilers 54.0° to 56.0° N/A Midboard Spoilers 54.0° to 56.0° N/A Inboard Spoilers 54.0° to 56.0° N/A T00015AT Page 4 Control Surface Maximum TEU/TEL (Deg.) Maximum TED/TER (Deg.) Horizontal Stabilizer 10.6° to 10.8° 0.6° to 0.8° Flaps N/A -0.5° to 0.5° 9.5° to 10.5° 19° to 21° 38° to 40° TEU = Trailing Edge Up TED = Trailing Edge Down TEL = Trailing Edge Left TER = Trailing Edge Right Trim Authority Lateral (Roll) 50% Directional (Yaw) 75% Manufacturer Serial No. Eligible: 6001 and subsequent. Other Operating Limitations: The aircraft must be operated in accordance with the latest FAA approved revision to the Airplane Flight Manual:  The Model GVI (G650) Airplane Flight Manual is GAC-AC-G650-OPS-0001.  The Model GVI (G650ER) Airplane Flight Manual is GAC-AC-G650ER-OPS-0001 II - GVIII-G700 (Transport Category), Approved March 29, 2024 Engines: Two - Rolls-Royce Deutschland Ltd & Co KG Turbofan Engine Models: BR700-730B2-14 (Engine Type Certificate No. E00099EN Revision 1). Fuel: Fuel shall conform to the specification as listed. See the approved Airplane Flight Manual for additional information. Kerosene Type (AVTUR, JP8, JP5) NATO Code F34, F-44 American British Canadian ASTM D1655, Jet A CAN/CGSB-3.23 (Jet A) ASTM D1655, Jet A-1 DEF STAN 91-91 AVTUR (Jet A-1) CAN/CGSB 3.23 (Jet A-1) MIL-DTL-831331, JP- 82,3 & F-342,3 DEF STAN 91-87 AVTUR/FSII (F-34) CAN/CGSB 3.24 (Grade F-34) MIL-DTL-5624, JP-52 and F-442 DEF STAN 91-86 AVCAT/FSII (F-44) CAN/CGSB 3.24 (Grade F-44) French Commonwealth of Independent States (C.I.S.) People’s Republic of China (P.R.C.) DCSEA 134D (Jet A-1 & F-34) DCSEA 144D (F-44) GOST 10227-86 (TS-1 & RT) GB 6537-2018 (No. 3 Jet Fuel) including the fuel additives limited to the concentrations stated in Annex A of GB 6537-2018 (see Chinese Fuel Additives note below) Page 5 T00015AT Ukraine GSTU 320.00149943.007-97 (RT) GSTU 320.00149943.011-99 (TS-1) NOTES: 1. MIL-DTL-83133 covers three grades of aviation fuels, which are similar to as commercial fuel, Jet A-1, but specified additives are necessary. 2. Contains Fuel System Icing Inhibitor (FSII) Diethylene Glycol Monomethyl Ether (DIEGME) for NATO fuel. Refer to MIL-DTL- 85470 or NATO Code S-1745. 3. Contains static dissipator (electrical conductivity) additive. NOTE: Approved Chinese Fuel Additives 4. Static Dissipater additive: Stadis 450 5. Antioxidant: 2,6-ditertiary-butyl-4-methyl-phenol 6. Icing Inhibitor: Ethylene Glycol Monomethyl Ether or Diethylene Glycol Monomethyl Ether 7. Metal Deactivator: N,N’-disalicylidene 1,2-propanediamine The following Chinese fuel additives are not approved for use on this Gulfstream aircraft model: Static Dissipater additive T1502 and antifriction additives T1602. Engine Limits: See the approved Airplane Flight Manual for engine ratings. Auxiliary Power Unit (APU): Honeywell – Model RE220[GVI] See the approved Airplane Flight Manual for APU ratings. Airspeed Limits: Vmo / Mmo = 340 KCAS / 0.935 Mach For other airspeed limits, see the approved Airplane Flight Manual. C.G. Range: See the approved Airplane Flight Manual. Empty Weight C.G. Range: None. M.A.C. 187.24 in. (L.E. of M.A.C. = Fuselage Station 624.54) Datum: For weight and balance purposes, the zero datum is 31.5 inches forward of the tip of the radome. Leveling Means: Longitudinal: Leveling Brackets along left nose wheel door longeron X STA 94.5 & 105.5. Lateral: Jig Point on Leveling Brackets on rear face of radome bulkhead X STA 80.5 in nose wheel well. See Aircraft Maintenance Manual for leveling procedure. Maximum Weights (lbs): Configuration Max. Zero Fuel Max. Ramp Max. Take-Off Max. Landing TC Configuration 62,750 108,000 107,600 83,500 ASC 005 62,750 74,900 74,900 74,900 T00015AT Page 6 ASC 009 62,750 90,000 90,000 83,500 ASC 011 62,750 95,000 95,000 83,500 ASC 017 62,750 100,000 99,600 83,500 Minimum Crew: 2 Pilot and co-pilot per the approved Airplane Flight Manual. Maximum Passengers: 19 With approved cabin interior (see Note 4). Maximum passenger capacity is limited by emergency exit door requirements of § 25.807(g). 0 For aircraft without an approved cabin interior (i.e., “green” aircraft as defined by Gulfstream drawing 62P0000000-001, GVIII-2 Aircraft Level Configuration Control Document, revision A, or later FAA approved revision). Maximum Occupants: 22 With approved cabin interior (see Note 4). Total reflects the maximum aircraft capacity of 19 passengers plus 3 crewmembers. 3 For aircraft without an approved cabin interior (i.e.“green” aircraft as defined by Gulfstream drawing 62P0000000-001, GVIII-2 Aircraft Level Configuration Control Document, revision A, or later FAA approved revision). Total represents 3 crewmembers and 0 passengers. Fuel Capacity: See the approved Airplane Flight Manual. Oil Capacity: Total engine oil tank capacity 18.1 lb. / 19.3 U.S. pints (each engine) Usable engine oil tank capacity 13.1 lb. / 14.0 U.S. pints (each engine) (Arm = +972.7) Oil weight based upon oil density 7.5 lb. per gal. Capacities shown above are for oil tankage only. Total engine oil is 21.4 lb. / 22.8 U.S. pints per engine Maximum Operating Altitude: 51,000 feet Control Surface Movements: To ensure proper operation of the airplane, the movement of the various control surfaces must be carefully controlled by proper rigging of the flight control system. The airplane must, therefore, be rigged according to the following FAA-approved data in the following GVIII-G700 Aircraft Maintenance Manual: FCS System FAA-Accepted Gulfstream Document Aileron Control AMM Section 27-10-03 Aileron Electrical Rig - Function Test - Test Follow-on Rudder Control AMM Section 27-20-02 Rudder Electrical Rig - Function Test Follow-on Elevator Control AMM Section 27-30-02 Elevator Electrical Rig - Function Test Follow-on Horizontal Stabilizer Actuation System AMM Section 27-40-02 Horizontal Stabilizer - Function Test Follow-on Flap Control AMM Section 27-50-03 Flap System - Operation Test Spoiler Control AMM Section 27-60-02 Spoiler Electrical Rig - Function Test Follow-on Page 7 T00015AT Cond itions: Sy stem mode of operation (Normal Mode flight control system) On Ground Stationary = True Flap Position = 0° (Unless otherwise specified) Horizontal Stabilizer Position = 0° (Unless otherwise specified) Maximum control surface travel: Control Surface Maximum TEU/TEL (Deg.) Maximum TED/TER (Deg.) Aileron 18.0° to 20.0° 10.0° to 12.0° Rudder 27.0° to 28.0° 27.0° to 28.0° Elevator 23.0° to 25.0° 12.0° to 14.0° Outboard Spoilers 54.0° to 56.0° N/A Midboard Spoilers 54.0° to 56.0° N/A Inboard Spoilers 54.0° to 56.0° N/A Horizontal Stabilizer 10.6° to 10.8° 0.6° to 0.8° Flaps N/A -0.5° to 0.5°9.5° to 10.5° 19° to 21° 38° to 40° TEU = Trailing Edge Up TED = Trailing Edge Down TEL = Trailing Edge Left TER = Trailing Edge Right Manufacturer Serial No. Eligible:87001 and subsequent. Other Operating Limitations: The aircraft must be operated in accordance with the latest FAA approved revision to the Airplane Flight Manual:  The Model GVIII-G700 (G700) Airplane Flight Manual is GAC-AC-GVIII-G700-OPS-0001. III - GVIII-G800 (Transport Category), Approved April 16, 2025 Eng ines: Two - Rolls-Royce Deutschland Ltd & Co KG Turbofan Engine Models: BR700-730B2-14 (Engine Type Certificate No. E00099EN Revision 1). Fuel: Fuel shall conform to the specification as listed. See the approved Airplane Flight Manual for additional information. Kerosene Type (AVTUR, JP8, JP5) NATO Code F34, F-44 T00015AT Page 8 Americ an British Canadian ASTM D1655, Jet A CAN/CGSB-3.23 (Jet A) ASTM D1655, Jet A-1 DEF STAN 91-91 AVTUR (Jet A-1) CAN/CGSB 3.23 (Jet A-1) MIL-DTL-831331, JP- 82,3 & F-342,3 DEF STAN 91-87 AVTUR/FSII (F-34) CAN/CGSB 3.24 (Grade F-34 ) MIL-DTL-5624, JP-52 and F-442 DEF STAN 91-86 AVCAT/FSII (F-44) CAN/CGSB 3.24 (Grade F-44 ) French Commonwealth of Independent States (C.I.S.) People’s Republic of China (P.R.C.) DCSEA 134D (Jet A-1 & F-34) DCSEA 144D (F-44) GOST 10227-86 (TS-1 & RT) GB 6537-2018 (No. 3 Jet Fuel) including the fuel additives limited to the concentrations stated in Annex A of GB 6537-2018 (see Chinese Fuel Additives note below) Ukra ine GS TU 320.00149943.007-97 (RT) GSTU 320.00149943.011-99 (TS-1) NOT ES: 1. MIL-DTL-83133 covers three grades of aviation fuels, which are similar to as commercial fuel, Jet A-1, but specified additives are necessary. 2. Contains Fuel System Icing Inhibitor (FSII) Diethylene Glycol Monomethyl Ether (DIEGME) for NATO fuel. Refer to MIL-DTL- 85470 or NATO Code S-1745. 3. Contains static dissipator (electrical conductivity) additive. NOTE: Approved Chinese Fuel Additives 4. Static Dissipater additive: Stadis 450 5. Antioxidant: 2,6-ditertiary-butyl-4-methyl-phenol 6. Icing Inhibitor: Ethylene Glycol Monomethyl Ether or Diethylene Glycol Monomethyl Ether 7. Metal Deactivator: N,N’-disalicylidene 1,2-propanediamine The following Chinese fuel additives are not approved for use on this Gulfstream aircraft model: Static Dissipater additive T1502 and antifriction additives T1602. Engine Limits: See the approved Airplane Flight Manual for engine ratings. Auxiliary Power Unit (APU): Honeywell – Model RE220[GVI] Page 9 T00015AT See the approved Airplane Flight Manual for APU ratings. Airspeed Limits: Vmo / Mmo = 340 KCAS / 0.935 Mach For other airspeed limits, see the approved Airplane Flight Manual. C.G. Range: See the approved Airplane Flight Manual. Empty Weight C.G. Range: None. M.A.C. 187.24 in. (L.E. of M.A.C. = Fuselage Station 624.54) Datum: For weight and balance purposes, the zero datum is 100 inches forward of the tip of the radome. Leveling Means: Longitudinal: Leveling Brackets along left nose wheel door longeron STA 163.0 & 174.0. Lateral: Jig Point on Leveling Brackets on rear face of radome bulkhead STA 149 in nose wheel well. See Aircraft Maintenance Manual for leveling procedure. Maximum Weights (lbs): Configuration Max. Zero Fuel Max. Ramp Max. Take-Off Max. Landing TC Configuration 60,500 106,000 105,600 83,500 ASC 005 60,500 74,900 74,900 74,900 ASC 009 60,500 90,000 90,000 83,500 ASC 011 60,500 95,000 95,000 83,500 ASC 017 60,500 100,000 99,600 83,500 Minimum Crew: 2 Pilot and co-pilot per the approved Airplane Flight Manual. Maximum Passengers: 19 With approved cabin interior (see Note 4). Maximum passenger capacity is limited by emergency exit door requirements of § 25.807(g). 0 For aircraft without an approved cabin interior (i.e., “green” aircraft as defined by Gulfstream drawing 61P0000000-001, GVIII-G800 Aircraft Level Configuration Control Document, revision A, or later FAA approved revision). Maximum Occupants: 22 With approved cabin interior (see Note 4). Total reflects the maximum aircraft capacity of 19 passengers plus 3 crewmembers. 3 For aircraft without an approved cabin interior (i.e.“green” aircraft as defined by Gulfstream drawing 61P0000000-001, GVIII-G800 Aircraft Level Configuration Control Document, revision A, or later FAA approved revision). Total represents 3 crewmembers and 0 passengers. Fuel Capacity: See the approved Airplane Flight Manual. Oil Capacity: Total engine oil tank capacity 18.1 lb. / 19.3 U.S. pints (each engine) Usable engine oil tank capacity 13.1 lb. / 14.0 U.S. pints (each engine) (Arm = +972.7) Oil weight based upon oil density 7.5 lb. per gal. Capacities shown above are for oil tankage only. Total engine oil is 21.4 lb. / 22.8 U.S. pints per engine T00015AT Page 10 Maximum Operating Altitude: 51,000 feet Control Surface Movements: To ensure proper operation of the airplane, the movement of the various control surfaces must be carefully controlled by proper rigging of the flight control system. The airplane must, therefore, be rigged according to the following FAA-approved data in the following GVIII-G800 Aircraft Maintenance Manual: FCS System FAA-Accepted Gulfstream Document Aileron Control AMM Section 27-10-03 Aileron Electrical Rig - Function Test - Test Follow-on Rudder Control AMM Section 27-20-02 Rudder Electrical Rig - Function Test Follow-on Elevator Control AMM Section 27-30-02 Elevator Electrical Rig - Function Test Follow-on Horizontal Stabilizer Actuation System AMM Section 27-40-02 Horizontal Stabilizer - Function Test Flap Control AMM Section 27-50-03 Flap System - Operation Test Spoiler Control AMM Section 27-60-02 Spoiler Electrical Rig - Function Test Follow-on Conditions: System mode of operation (Normal Mode flight control system) On Ground Stationary = True Flap Position = 0° (Unless otherwise specified) Horizontal Stabilizer Position = 0° (Unless otherwise specified) Maximum control surface travel: Control Surface Maximum TEU/TEL (Deg.) Maximum TED/TER (Deg.) Aileron 18.0° to 20.0° 10.0° to 12.0° Rudder 27.0° to 28.0° 27.0° to 28.0° Elevator 23.0° to 25.0° 12.0° to 14.0° Outboard Spoilers 54.0° to 56.0° N/A Midboard Spoilers 54.0° to 56.0° N/A Inboard Spoilers 54.0° to 56.0° N/A Horizontal Stabilizer 10.6° to 10.8° 0.6° to 0.8° Flaps N/A -0.5° to 0.5° 9.5° to 10.5° 19° to 21° 38° to 40° TEU = Trailing Edge Up TED = Trailing Edge Down TEL = Trailing Edge Left TER = Trailing Edge Right Page 11 T00015AT Manufacturer Serial No. Eligible:88001 and subsequent. Other Operating Limitations: The aircraft must be operated in accordance with the latest FAA approved revision to the Airplane Flight Manual:  The Model GVIII-G800 (G800) Airplane Flight Manual is GAC-AC-GVIII-G800-OPS-0001. Certification Basis: Model GVI; S/N 6001 and subsequent; 14 CFR part 25, Airworthiness Standards: Transport Category Airplanes, effective February 1, 1965, including Amendments 25-1 through 25-120 and 25-122, 25-124, 25-132, 25-137* and 25-144** Amendment 25-118 was not published and therefore has no applicability. *Amendment 25-137 only applies to 14 CFR 25.1302(a)(b)(c)(d) for new and novel functions associated with avionic changes. **Amendment 25-144 only applies to 14 CFR 25.773(e) for EFVS operations to touchdown and rollout and associated subsystems. 14 CFR part 34, Fuel Venting and Exhaust Emission Requirements for Turbine Engine Powered, effective September 10, 1990, including Amendments 34-1 through 34-4. 14 CFR part 36, Noise Standards: Aircraft Type Certification and Airworthiness Certification, effective December 1, 1969, including Amendments 36-1 through 36-28. Compliance with Section 44715(e) of Title 49 U.S.C. (Noise Control Act of 1972) Optional Design Regulations: (a) The Model GVI has been shown to comply with the requirements for ditching: § 25.801, 25.563, 25.807(e), and 25.1585(a). When the operating rules require emergency ditching equipment, compliance with §§ 25.1411 and 25.1415 must be shown. Gulfstream Report GVI-GER-1709, entitled “Design Requirements Document for Ditching Equipment” provides an acceptable means for showing compliance with 25.1411 and 25.1415. (b) The Model GVI is approved for flight into known icing conditions and has demonstrated compliance to § 25.1419. The following special conditions in accordance with 14 CFR part 21 apply to the Model GVI: SC No. Subject 25-416-SC Enhanced Flight Vision System 25-422-SC Electronic Flight Control System Mode Annunciation Awareness/Annunciation 25-423-SC High Incidence Protection Function 25-427-SC Electronic Flight Control System: Control Surface Position Awareness 25-428-SC Single-Occupant Side-Facing Seats 25-429-SC Automatic Speed Protection for Design Dive Speed T00015AT Page 12 25-433-SC Design Roll Maneuver Requirement for Electronic Flight Controls 25-434-SC Interaction of Systems and Structures 25-435-SC Operation Without Normal Electrical Power 25-436-SC Electronic Systems Security Isolation or Protection From Unauthorized Passenger Systems Access 25-437-SC Electronic Systems Security Protection From Unauthorized External Access 25-441-SC Limit Engine Torque Loads for Sudden Engine Stoppage 25-452-SC Pilot Compartment View - Hydrophobic Coatings in Lieu of Windshield Wipers 25-455-SC Rechargeable Lithium-Batteries and Rechargeable Lithium-Battery Systems 25-563-SC Electro-hydraulically Actuated Seats Equipped With a Backup Power Supply 25-612-SC Non-Rechargeable Lithium Batteries, effective to design changes applied for after April 22, 2017. See the applicability section of this special condition for more information on which design changes must meet it. Exemptions from 14 CFR part 25 in accordance with 14 CFR part 11: a) Exemption No. 9761, §§ 25.562(a) and 25.785(b) Side Facing Divan b) Exemption No. 9940, § 25.1447(c)(1) High Landing Field Elevation c) Exemption No. 10188, § 25.813(e) Acoustic and Forward Vestibule Door d) Exemption No. 10387A, § 25.981(a)(3) Fuel Tank Ignition Prevention e) Exemption No. 10614, § 25.901(c) Uncontrollable High Thrust (see Note 15) f) Exemption No. 13281A, § 25.813(e) Mid Cabin Doors for 14 CFR Part 91 Operations (see Note 18) g) Exemption No. 11035, §§ 25.562 & 25.785(b) Medical-Stretcher Installations h) Time-Limited Exemption No. 17825, § 25.1309(b) Non-Rechargeable Lithium Batteries for Emergency Locator Transmitter installations in Life Rafts (see Note 20) i) Exemption No. 17727, § 25.841(a)(2) with regard to Uncontained Engine Rotor Failures. Equivalent Safety Findings according to the provisions of 14 CFR part 21.21(b)(1) for the following subjects: TC8700AT-T-A-5 § 25.331(c) Checked Pitch Maneuver TC8700AT-T-A-6 § 25.341(b) Continuous Gust Design Criteria TC8700AT-T-A-8, Rev. 1 § 25.415 Ground Gust TC8700AT-T-A-9 §§ 25.561(c), 25.721, 25.963(d), 25.994 Structural Integrity of Fuel Tanks for Emergency Landing Conditions and Landing Gear TC8700AT-T-A- 16 § 25.629(d)(9) Failure Criteria Considered Under the Aeroelastic Stability Requirements of § 25.629 Page 13 T00015AT TC8700AT-T-S- 17, Rev. 1 § 25.671 Flight Control System Failure Criteria TC8700AT-T-C- 1, Rev. 2 § 25.807 (g)(1)(2)(3) & (i)(1)(2) Emergency Exits TC8700AT-T-C- 10 § 25.809(a) Overwing Emergency Exits - Means for Viewing Likely Areas of