# TCDS T00015AT: Gulfstream Aerospace Corporation - Type: Type certificate data sheet - Status: Current - Holder: Gulfstream Aerospace Corporation - Revision: 22 - Revised: April 16, 2025 - Product: Aircraft, Large Airplane - Certification basis: Part 25 - Registered aircraft: 610, by the registry models matched to it (OpenAirDocs) - Data sheet PDF: https://openairdocs.org/files/sha256/57/df/57dfc74d827b990828d9f2da5287e47ba4b16a9fde8aebec9648f197daf814b8 - FAA DRS: https://drs.faa.gov/browse/excelExternalWindow/DRSDOCID130146034520250423155605.0001 - Page: https://openairdocs.org/tcds/T00015AT ## Models (3) As the data sheet lists them. - GVI - GVIII-G700 - GVIII-G800 ## What the data sheet says From the PDF's text layer, line by line; tables lose their columns. The PDF is the record. ```text 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 Evacuee Ground Contact AT5177AT-T-C-1, Rev. 3 §§ 25.811(d), 25.812(b) Emergency Exit Marking, Locator, and Bulkhead/ Divider Signs TC8700AT-T-C-7 Rev. 2 § 25.813(c)(2)(ii) Seat/Furnishing Encroachment Into the Overwing Emergency Exit Openings TC8700AT-T-S- 28, Rev. 1 § 25.831(g) Acceptable High Temperature Physiological Environment During Failure Conditions TC8700AT-T-S- 23, Rev. 1 § 25.841(b)(6) Cabin Pressurization- High Field Elevation Takeoff and Landing Operations AT5080AT-T-P-1, Rev. 2 § 25.933 Flight Critical Thrust Reverser TC8700AT-T-P- 14, Rev. 1 §§ 25.1182, 25.1183 Flammable Fluid Carrying Components in Nacelle Areas Behind the Firewall TC8700AT-T-P-6 § 25.1203(a) Turbine Engine Tailpipe Fire Detection TC8700AT-T-P-8, Rev. 1 § 25.1203(d) Oil Fire Detection System TC8700AT-T-S-9 Rev. 1 §§ 25.1301, 25.1309 Equipment, Systems, and Installation Requirements: Use of ARAC ecommendations TC8700AT-T-S- 37 §§ 25.1303(a)(3), 25.1327, 25.1547 Use of an Electric-Only Direction Indicator Standby Instrumentation TC8700AT-T-P-7, Rev. 1 § 25.1305(c)(6) Fuel Filter Indication System TC8700AT-T-S- 38, Rev. 1 § 25.1325(c)(1) Pitot Tube Water Evaporation TC8700AT-T-F-2 § 25.1517 Rough Airspeed Criteria TC8700AT-T-P-9 §§ 25.1549(a)(b)(c), Digital-Only Display of Engine High Pressure Rotor Speed TC8700AT-T-P-3 Part 25 subpart E, F, and G Adoption of Draft Harmonized Rules for APU Certification T00015AT Page 14 TC8700AT-T-A- 20 § 26.21 Widespread Fatigue Damage Limit of Validity TD-01-2016- 0039-F-14 § 25.125(f) Equivalent Level of Safety (ELOS) for Use of All-Engine Operating Landing Distance for Steep Approach Destination Planning SD-05-2022- 0038-C-05 R1 § 25.785(d) Non-TT&L Seats ADDITIONAL DESIGN REQUIREMENTS AND CONDITIONS: The following design details or information must be maintained to ensure that an unsafe design condition is not present: Class B Cargo Compartment The GVI has a Class B cargo compartment located aft of the main cabin. The fire protection requirements of Class B cargo compartments, as specified in § 25.857(b), rely on manual firefighting as the primary method of controlling fires. The following design features are required to ensure an unsafe condition does not exist with regards to the ability to fight a fire in this compartment: 1. The baggage compartment volume must be less than 200 cubic feet, 2. The compartment must be configured to allow for a crew member to access the stored baggage and move articles out of the way to uncover any article that may be smoldering or burning, and 3. A Halon 1211 portable fire bottle charged with 13 pounds of agent and a UL Rating of 2A:40B:C must be installed adjacent to the compartment. Fire Extinguishing Plumbing and Wiring Connections The engine and APU fire extinguishing plumbing and electrical connections must be constructed, arranged and installed such that cross connection is not possible during normal maintenance actions such as changing the fire extinguishing bottles or trouble shooting the system. In-flight Engine Restart The Gulfstream GVI engines incorporate numerous technological advances intended to increase efficiency and reliability. However, some of these features have the potential to decrease engine in-flight starting performance relative to the engines envisioned when the applicable sections of part 25 were promulgated. The following criteria for engine in- flight starting performance must be met to ensure that the level of safety intended by §§ 25.903(e) and 25.1585(a)(3) is maintained on airplanes powered by current technology engines. The means to restart engines, while inflight, following flameout or inflight shutdown of all engines, must be substantiated by flight test. The means must provide all-engine restart capability in the following situations: Page 15 T00015AT 1. Immediately following an all-engine power loss at high torque or power settings; 2. Following loss of all-engine power at maximum cruise altitude conditions; and 3. From any initial airspeed within the normal flight envelope below an altitude of 20,000 feet. Fuel Vent System Fire Protection The fuel vent lines of the GVI aircraft must be equipped with a means, such as a flame arrestor, to prevent fire from propagating up the fuel vent lines after an accident. The design must show a flame holding capability for a minimum period of 2.5 minutes to allow passenger evacuation following an accident. The design of the vent system must also be arranged in such manner to avoid vent reduction or stoppage due to ice formation or debris. This will ensure the flow rate capacity and pressure differential between the interior and exterior of the tank are maintained within acceptable safe levels. This must be substantiated for all phases of flight (normal and emergency) including ground operation (such as refueling/de-fueling). Fan Blade Out / Windmilling Descent Profile Gulfstream has shown compliance to the applicable requirements relative to fan blade out (FBO) / windmilling (including §§ 25.143(b), 25.571, 25.1309(a), and 25.1431(a)), and have demonstrated that the aircraft will maintain an acceptable level of vibration throughout the FBO emergency descent profile. See the Flight Standardization Board (FSB) Report for areas of emphasis. A copy of the FSB report may be obtained from the FAA Dynamic Regulatory System (DRS) at https://drs.faa.gov/browse/FSB_REPORTS/doctypeDetails Return Landing Capability Development of airplanes, with exceptional takeoff performance, particularly large two engine airplanes, has resulted in an unsafe condition under many foreseeable conditions where the airplane is not capable of a return landing without exceeding equipment capabilities. Compliance with §§ 25.1301 and 25.1309 requires the airplane systems to perform their intended functions during foreseeable abnormal operating conditions. On previous generation airplanes the return landing was not the critical design case for the brakes, tires, etc., because those aircraft incorporated fuel jettisoning systems. The Model GVI airplane does not incorporate a fuel jettisoning system and thus compliance to the part 25 sections listed above must be demonstrated by a combination of failure analysis, equipment qualification testing, or the installation of a fuel jettisoning system that would reduce airplane gross weight, and hence the airplane landing speed, during foreseeable abnormal conditions. Subjects to be addressed should include, but may not be limited to the following: 1. Exceedance of certificated maximum brake energies; 2. Exceedance of tire speed limits; 3. Controllability (e.g., hydraulic and/or flight control system failures); 4. Margins to flap placard, or load relief operation speeds in turbulent air; 5. Climb capability, engine-inoperative procedures; and 6. Landing distances (including wet runway, anti skid off, spoiler failures, etc.). T00015AT Page 16 Yaw Oscillations Service experience has shown that an unsafe rudder system design feature may contribute to a yaw related aircraft-pilot coupling (APC) event that could potentially lead to a structural failure of the vertical stabilizer. If this feature exists excessive rudder pedal inputs may drive loads beyond the ultimate design. The following criteria for rudder performance must be demonstrated to ensure a safe rudder control system design per §§ 25.143(a), 25.143 (b), and 25.671(a), and that it does not have the described unsafe characteristics: 1. The rudder control system design characteristics including pedal sensitivity, breakout forces, lateral accelerations as a function of pedal force, the ability to adequately modulate rudder control throughout the flight envelope, and displacement and harmony with other flight controls provide safe handling qualities throughout the flight envelope. 2. The airplane is adequately protected from the adverse effects of inappropriate rudder inputs, including the potential for loss of control, APC / PIO, or exceeding the airplane’s structural design envelope. Type Certificate Information (GVI) Application for type certificate was first dated September 29, 2005, followed by a re-application on October 4, 2006, and an extension of the effective application date to September 18, 2007 (granted by way of FAA letter dated August 25, 2011). Type Certificate T00015AT was first issued as a provisional type certificate on November 18, 2011. Model GVIII-G700; S/N 87001 and subsequent; 14 CFR part 25, Airworthiness Standards: Transport Category Airplanes, effective February 1, 1965, including Amendments 25-1 through 25-146 with the exceptions per 14 CFR 21.101 shown: 14 CFR Amendment APPLICABLE AREA NOTES SECTION TITLE 25.21 Proof of compliance. 25-135 GVIII-G700 25.105 Takeoff 25-121 GVIII-G700 25.111 Takeoff path. 25-121 GVIII-G700 25.119 Landing climb: All engines operating. 25-121 GVIII-G700 25.121 Climb: One-engine inoperative. 25-121 GVIII-G700 25.123 En route flight paths. 25-121 GVIII-G700 25.125 Landing. 25-121 GVIII-G700 25.143 General. 25-129 GVIII-G700 25.237 Wind velocities. 25-121 GVIII-G700 25.253 High speed characteristics. 25-135 GVIII-G700 25.611(b) Accessibility provisions. 25-123 GVIII-G700 except as noted below 25.611(b) Accessibility provisions. N/A (See Note) EWIS components in the wing and empennage All design areas comply with the EWIS requirements at Amendment 25- 123, except the wing and empennage. 25.621 Casting factors. 25-0 GVIII-G700 Page 17 T00015AT 14 CFR Amendment APPLICABLE AREA NOTES SECTION TITLE 25.729 Retracting mechanism. 25-75 GVIII-G700 except as noted below 25.729(c) Retracting mechanism 25-136 Human factors aspects of the landing gear emergency operation 25.729(e) Retracting mechanism. 25-136 Landing Gear Control and Indication System (LGCIS) 25.773(b)(1)(i) Pilot compartment view. 25-108 GVIII-G700 25-452-SC 25.813(c)(2)(ii ) Emergency exit access. TC8700AT-T-C-7 Rev 2 GVIII-G700 25.795 Security considerations 25-106 GVIII-G700 25.851 Fire extinguishers. 25-74 GVIII-G700 except as noted below 25.851(a)(8) Fire extinguishers. 25-142 Increased cabin volume due to fuselage stretch 25.855(a)(b)(d )(e)(f)(g)(h)(1) (2)(i) Cargo or baggage compartments. 25-123 GVIII-G700 25.855(j) Cargo or baggage compartments. 25-123 GVIII-G700 except as noted below 25.855(j) Cargo or baggage compartments. N/A (See Note) EWIS components in the wing and empennage All design areas comply with the EWIS requirements at Amendment 25- 123, except the wing and empennage. 25.857(b) Cargo compartment classification 25-93 GVIII-G700 25.869(a)(3) Fire protection: Systems. 25-123 GVIII-G700 except as noted below 25.869(a)(3) Fire protection: Systems. N/A (See Note) EWIS components in the wing and empennage All design areas comply with the EWIS requirements at Amendment 25- 123, except the wing and empennage. 25.869(a)(4) Fire protection: Systems 25-113 EWIS components in the wing and empennage: Unchanged LRUs in fuselage, pylon, engine, wing, and empennage; Electrical changes integral to unrelated, not significant changes 25.869(a)(4) [25- 113] applies to unchanged LRUs from the GVI in the fuselage, pylon, engine, wing, empennage and to electrical changes in the wing and empennage and EWIS components integral to unrelated, not-significant changes in accordance with 14 CFR 21.101(b)(2). T00015AT Page 18 14 CFR Amendment APPLICABLE AREA NOTES SECTION TITLE 25.954 Fuel system lightning protection. 25-14 GVIII-G700 25.975 Fuel tank vents and carburetor vapor vents. 25-0 GVIII-G700 25.981 Fuel tank explosion prevention. 25-102 GVIII-G700 25.1203(d) Fire detector system TC8700AT-T-P-8 Rev. 1 GVIII-G700 25.1301(b) Function and installation. 25-123 GVIII-G700 except as noted below 25.1301(b) Function and installation. N/A (See Note) EWIS components in the wing and empennage All design areas comply with the EWIS requirements at Amendment 25- 123, except the wing and empennage. 25.1309(f) Equipment, systems, and installations. 25-123 GVIII-G700 except as noted below 25.1309(f) Equipment, systems, and installations. N/A (See Note) EWIS components in the wing and empennage All design areas comply with the EWIS requirements at Amendment 25- 123, except the wing and empennage. 25.1323 Airspeed indicating system. 25-109 GVIII-G700 25.1324 Angle of attack system. N/A GVIII-G700 25.1325 Static pressure system 25-108 GVIII-G700 25.1353 Electrical equipment and installations. 25-113 GVIII-G700 except as noted below 25.1353 Electrical equipment and installations. 25-123 -Data Concentration & Network -Engine -Flight Control System:  Active Control Sidestick -Flight Deck:  Touch Screen Controllers 25.1420 Supercooled Large Drop Icing Conditions N/A GVIII-G700 25.1703 Function and installation: EWIS 25-123 GVIII-G700 except as noted below 25.1703 Function and installation: EWIS N/A (See Note) EWIS components in the wing and empennage All design areas comply with the EWIS requirements at Amendment 25- 123, except the wing and empennage. 25.1705 Systems and functions: EWIS 25-123 GVIII-G700 except as noted below Page 19 T00015AT 14 CFR Amendment APPLICABLE AREA NOTES SECTION TITLE 25.1705 Systems and functions: EWIS N/A (See Note) EWIS components in the wing and empennage All design areas comply with the EWIS requirements at Amendment 25- 123, except the wing and empennage. 25.1707 System separation: EWIS 25-123 GVIII-G700 except as noted below 25.1707 System separation: EWIS N/A (See Note) EWIS components in the wing and empennage All design areas comply with the EWIS requirements at Amendment 25- 123, except the wing and empennage. 25.1709 System safety: EWIS 25-123 GVIII-G700 except as noted below 25.1709 System safety: EWIS N/A (See Note) EWIS components in the wing and empennage All design areas comply with the EWIS requirements at Amendment 25- 123, except the wing and empennage. 25.1711 Component identification: EWIS 25-123 GVIII-G700 except as noted below 25.1711 Component identification: EWIS N/A (See Note) EWIS components in the wing and empennage All design areas comply with the EWIS requirements at Amendment 25- 123, except the wing and empennage. 25.1713 Fire protection: EWIS 25-123 GVIII-G700 except as noted below 25.1713 Fire protection: EWIS N/A (See Note) EWIS components in the wing and empennage 25.1713 is not applicable for unchanged LRUs from the GVI in the fuselage, pylon, engine, wing, and empennage; 25.1713 does not apply to EWIS components in the wing and empennage and EWIS components integral to unrelated, not-significant changes in accordance with 14 CFR 21.101(b)(2). 25.1715 Electrical bonding and protection against static electricity: EWIS 25-123 GVIII-G700 except as noted below T00015AT Page 20 14 CFR Amendment APPLICABLE AREA NOTES SECTION TITLE 25.1715 Electrical bonding and protection against static electricity: EWIS N/A (See Note) EWIS components in the wing and empennage All design areas comply with the EWIS requirements at Amendment 25- 123, except the wing and empennage. 25.1717 Circuit protective devices: EWIS 25-123 GVIII-G700 except as noted below 25.1717 Circuit protective devices: EWIS N/A (See Note) EWIS components in the wing and empennage All design areas comply with the EWIS requirements at Amendment 25- 123, except the wing and empennage. 25.1719 Accessibility provisions: EWIS 25-123 GVIII-G700 except as noted below 25.1719 Accessibility provisions: EWIS N/A (See Note) EWIS components in the wing and empennage All design areas comply with the EWIS requirements at Amendment 25- 123, except the wing and empennage. 25.1721 Protection of EWIS 25-123 GVIII-G700 except as noted below 25.1721 Protection of EWIS N/A (See Note) EWIS components in the wing and empennage All design areas comply with the EWIS requirements at Amendment 25- 123, except the wing and empennage. 25.1723 Flammable fluid fire protection; EWIS 25-123 GVIII-G700 except as noted below 25.1723 Flammable fluid fire protection; EWIS N/A (See Note) EWIS components in the wing and empennage All design areas comply with the EWIS requirements at Amendment 25- 123, except the wing and empennage. 25.1725 Powerplants: EWIS 25-123 GVIII-G700 except as noted below 25.1725 Powerplants: EWIS N/A (See Note) EWIS components in the wing and empennage All design areas comply with the EWIS requirements at Amendment 25- 123, except the wing and empennage. 25.1727 Flammable fluid shutoff means: EWIS 25-123 GVIII-G700 except as noted below 25.1727 Flammable fluid shutoff means: EWIS N/A (See Note) EWIS components in the wing and empennage All design areas comply with the EWIS requirements at Amendment 25- 123, except the wing and empennage. 25.1729 Instructions for Continued Airworthiness: EWIS 25-123 GVIII-G700 except as noted below Page 21 T00015AT 14 CFR Amendment APPLICABLE AREA NOTES SECTION TITLE 25.1729 Instructions for Continued Airworthiness: EWIS N/A (See Note) EWIS components in the wing and empennage All design areas comply with the EWIS requirements at Amendment 25- 123, except the wing and empennage. 25.1731 Powerplant and APU fire detector system: EWIS 25-123 GVIII-G700 except as noted below 25.1731 Powerplant and APU fire detector system: EWIS N/A (See Note) EWIS components in the wing and empennage All design areas comply with the EWIS requirements at Amendment 25- 123, except the wing and empennage. 25.1733 Fire detector systems, general: EWIS 25-123 GVIII-G700 except as noted below 25.1733 Fire detector systems, general: EWIS N/A (See Note) EWIS components in the wing and empennage All design areas comply with the EWIS requirements at Amendment 25- 123, except the wing and empennage. C25.1 Appendix C, Part I - Atmospheric Icing Conditions. Appendix C, Part II - Airframe Ice Accretions for Showing Compliance with Subpart B. 25-129 GVIII-G700 H25.1 General. 25-123 GVIII-G700 except as noted below H25.1 General. 25-68 (See Note) EWIS components in the wing and empennage All design areas comply with the EWIS requirements at Amendment 25- 123, except the wing and empennage. H25.4 Airworthiness Limitations Section 25-132 GVIII-G700 H25.5 Electrical Wiring Interconnection System (EWIS) Instructions for Continued Airworthiness. 25-123 GVIII-G700 except as noted below H25.5 Electrical Wiring Interconnection System (EWIS) Instructions for Continued Airworthiness. N/A (See Note) EWIS components in the wing and empennage All design areas comply with the EWIS requirements at Amendment 25- 123, except the wing and empennage. Appendix M Fuel Tank System Flammability Reduction Means. N/A N/A Appendix N Fuel Tank Flammability Exposure and Reliability Analysis. N/A N/A T00015AT Page 22 14 CFR Amendment APPLICABLE AREA NOTES SECTION TITLE Appendix O Supercooled Large Drop Icing Conditions. N/A N/A 14 CFR part 34, Fuel Venting and Exhaust Emission Requirements for Turbine Engine Powered, effective September 10, 1990, including Amendments 34-1 through 34-6. 14 CFR part 36, Noise Standards: Aircraft Type Certification and Airworthiness Certification, effective December 1, 1969, including Amendments 36-1 through 36-31. Compliance with Section 44715(e) of Title 49 U.S.C. (Noise Control Act of 1972). Optional Design Regulations: a) The Model GVIII-G700 has been shown to comply with the requirements for ditching: § 25.801. b) The Model GVIII-G700 has been shown to comply with the requirements for public address systems: § 25.1423. c) The Model GVIII-G700 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 GVIII-G700: Page 23 T00015AT SC No. Subject 25-422-SC Electronic Flight Control System Mode Annunciation 25-429-SC Automatic Speed Protection for Design Dive Speed 25-433-SC Design Roll Maneuver Requirement for Electronic Flight Controls 25-434-SC Interaction of Systems and Structures 25-452-SC Windshield Coating in Lieu of Wipers 25-563-SC Electro-hydraulically Actuated Seats Equipped with a Backup Power Supply 25-612-SC Non-Rechargeable Lithium Battery Installations 25-850-SC Limit Pilot Forces for Side-Stick Controllers 25-853-SC Flight Envelope Protection: High Incidence Protection System (Non-icing and Icing Conditions) 25-849-SC Side Stick Controllers – Controllability and Maneuverability 25-846-SC Electronic System Security Protection from Unauthorized Internal Access 25-847-SC Electronic System Security Protection from Unauthorized External Access 25-855-SC Electronic Flight Control System: Control Surface Position Awareness 25-852-SC Operation Without Normal Electrical Power 25-862-SC Dynamic Test Requirements for Single – and Multiple-Occupant Side-Facing Seats with or without Airbag Systems 25-848-SC Installation of Large Non-Structural Glass in the Passenger Compartment 25-858-SC Flight Envelope Protection: Takeoff Stall Protection 25-851-SC Installation of Therapeutic Oxygen System Exemptions from 14 CFR part 25 in accordance with 14 CFR part 11: a) Exemption No. 18499, § 25.809(a); Over wing exit viewing b) Exemption No. 10188B, § 25.813(e); Acoustic and Forward Vestibule Door c) Exemption No. 18556B, § 25.813(e); Mid Cabin Doors for 14 CFR Part 91 Operations and Part 135 Operations d) Exemption No. 10387C, § 25.981(a)(3); Fuel Tank Ignition Prevention e) Exemption No. 9940B, § 25.1447(c)(1); High Landing Field Elevation f) Exemption No. 17727B, § 25.841(a)(2); Cabin Pressurization Requirements for Baggage Compartment Access g) Partial Time-Limited Exemption No. 21815, §25.901(c); Uncontrollable High Thrust Failure Conditions (See Note 21) h) Partial Time-Limited Exemption No. 21744A, §25,951(c), 25.952(a), and 25.901(d); Fuel Feed Icing Threat T00015AT Page 24 Equivalent Safety Findings according to the provisions of 14 CFR part 21.21(b)(1) for the following subjects: AT-01-2015- 0016-A-1 § 25.629(d)(9) Failure Criteria Considered Under the Aeroelastic Stability Requirements of § 25.629 AT-01-2015- 0016-A-03-GVIII § 25.683(a) Operation Test Compliance for Fly-by- Wire Flight Control Systems SD-05-2022- 0038-C-05 R1 § 25.785(d) Non-TT&L Seats AT-01-2015- 0016-F-1-GVII § 25.255 Out-of-Trim Characteristics AT-01-2015- 0016-F-15-GVII § 25.251(b) Vibration / Buffeting Compliance Criteria for External Modifications AT-01-2015- 0016-P-1-GVII § 25.1155 Reverse Thrust Control and Indication AT-01-2015- 0016-P-3-GVII § 25.1203(a) Turbine Engine Tailpipe Fire Detection AT-01-2015- 0016-P-3, Rev. 1 § 25.1549(a)-(c) Digital-Only Display of Engine High Pressure “HP” Rotor Speed (N2) AT-01-2015- 0016-P-06 § 25.1193(e)(3) Engine Fire Protection AT-01-2015- 0016-P-7-GVII § 25.1145(a) Ignition Switches AT-01-2015- 0016-P-08 14 CFR Part 25 Subpart E, F, and G Auxiliary Power Unit (APU) Certification Requirements AT-01-2015- 0016-P-12 § 25.1141(f)(2) Engine Fuel Shutoff Valve Indication AT-01-2015- 0016-P-13 § 25.934 Turbojet Engine Thrust Reverser System Tests AT-01-2015- 0016-S-1 §§ 25.1301(a)(4), 25.1309(a)-(e) Equipment, Systems, and Installation Requirements: Use of ARAC Recommendations AT-01-2015- 0016-S-20-GVII §§ 25.1303(a)(3), 25.1327, 25.1547 Use of an Electric-Only Direction Indicator Standby Instrumentation AT-01-2015- 0016-S-26-GVII § 25.1459(a)(2) Use of Inertial Reference System for Flight Data Recorder Vertical Acceleration AT-01-2015- 0016-S-27-GVII §§ 25.841 and 25.843 Combined Aircraft Pressurization Outflow and Positive Pressure Differential Relief Valves Page 25 T00015AT AT-01-2015- 0016-S-29-GVII § 25.783(c)(1) Electrical Main Entry Door Pressurization Prevention Means TC8700AT-T-C- 1, Rev. 2 § 25.807(g)(1), (2), and (3)(i)(1) and (2) Emergency Exits TC8700AT-T-C- 7, Rev. 2 § 25.813(c)(2)(ii) Seat/Furnishing Encroachment Into the Overwing Emergency Exit Openings TC8700AT-T-P-7, Rev. 1 § 25.1305(c)(6) Fuel Filter Indication System TC8700AT-T-P-8, Rev. 1 § 25.1203(d) Oil Fire Detection System TC8700AT-T-S- 17, Rev. 1 § 25.671 Flight Control System Failure Criteria TC8700AT-T-S- 23, Rev. 1 § 25.841(b)(6) Cabin Pressurization – High Field Elevation Takeoff and Landing Operations TC8700AT-T-S- 28, Rev. 1 § 25.831(g) Acceptable High Temperature Physiological Environment During Failure Conditions TC8700AT-T-S- 38, Rev. 1 §§ 25.1323(h) and 25.1325(c)(1) Pitot-Static System Moisture Control AT5177AT-T-C-1, Rev. 3 §§ 25.811(d), 25.812(b) Emergency Exit Marking, Locator, and Bulkhead/Divider Signs AT5080AT-T-P-1, Rev. 2 § 25.933(a)(1)(ii) Flight Critical Thrust Reverser ADDITIONAL DESIGN REQUIREMENTS AND CONDITIONS: The following design details or information must be maintained to ensure that an unsafe design condition is not present: Fuel Feed System Icing Threats The design of the Model GVIII series airplanes provides mitigation for fuel icing and allows for completion of the certification activities after type certification to show full compliance with the regulations to ensure that an unsafe feature or characteristic does not exist on the Gulfstream Model GVIII-G700 airplane. 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 should have the capability for the flightcrew to restore engine power immediately following an all-engine-out scenario and when the fuel source to the engine is interrupted. 2. During the high altitude portion of the flight at cruise speed and maximum altitude, the airplane should have the capability for the flightcrew to restart engines from a stabilized windmill speed prior to T00015AT Page 26 descending below an altitude of 15,000 feet, 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. 3. During flight at speeds greater than the minimum flaps-up “holding speed” and at altitudes below 20,000 feet, the airplane should have the capability for the flightcrew to restart engines from a stabilized windmill speed prior to descending 5000 feet 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 Class B Cargo Compartment and Hand Held Fire Extinguishers The GVIII-G700 has a Class B cargo compartment located aft of the main cabin. The fire protection requirements of Class B cargo compartments, as specified in § 25.857(b), rely on manual firefighting as the primary method of controlling fires. The following design features are required to ensure an unsafe condition does not exist with regards to the ability to fight a fire in the compartment: 1. The baggage compartment volume must be less than 200 cubic feet, 2. The compartment must be configured to allow for a crew member to access the stored baggage and move articles out of the way to uncover any article that may be smoldering or burning, and 3. A Halon 1211 portable fire bottle charged with minimum 13 pounds of agent and a UL Rating of 2A:40B:C must be installed adjacent to the compartment Fire Extinguishing Plumbing and Wiring Connections The engine and APU fire extinguishing plumbing and electrical connections must be constructed, arranged, and installed such that cross connection is not possible during normal maintenance actions such as changing the fire extinguishing bottles or troubleshooting the system. Fuel Vent System Fire Protection The fuel vent lines of the GVIII-G700 aircraft must be equipped with a means, such as a flame arrestor, to prevent fire from propagating up the fuel vent lines after an accident. The design must show a flame holding capability for a minimum period of 2.5 minutes to allow passenger evacuation following an accident. The design of the vent system must also be arranged in such manner to avoid vent reduction or stoppage due to ice formation or debris. This will ensure the flow rate capacity and pressure differential between the interior and exterior of the tank are maintained within acceptable safe levels. This must be substantiated for all phases of flight (normal and emergency) including ground operation (such as refueling / de-fueling). Fan Blade Out / Windmilling Descent Profile Page 27 T00015AT Gulfstream has shown compliance to the applicable requirements relative to fan blade out (FBO) / windmilling (including §§ 25.143(b), 25.571, 25.1309(a), and 25.1431(a)), and has demonstrated that the aircraft will maintain an acceptable level of vibration through the FBO emergency descent profile. See the Flight Standardization Board (FSB) Report for areas of emphasis. A copy of the FSB report may be obtained from the FAA Dynamic Regulatory System (DRS) at https://drs.faa.gov/browse/FSB_REPORTS/doctypeDetails Yaw Oscillations Service experience has shown that an unsafe rudder system design feature may contribute to a yaw related aircraft-pilot coupling (APC) event that could potentially lead to a structural failure of the vertical stabilizer. If this feature exists, excessive rudder pedal inputs may drive loads beyond the ultimate design. The following criteria for rudder performance must be demonstrated to ensure a safe rudder control system design per §§ 25.143(a), 25.143(b), and 25.671(a), and that it does not have the unsafe characteristics described above: 1. The rudder control system design characteristics, including pedal sensitivity, breakout forces, lateral accelerations as a function of pedal force, the ability to adequately modulate rudder control throughout the flight envelope, and displacement and harmony with other flight controls provide safe handling qualities throughout the flight envelope. 2. The airplane is adequately protected from the adverse effects of inappropriate rudder inputs, including the potential for loss of control, APC / PIO, or exceeding the airplane’s structural design envelope. Type Certificate Information (GVIII-G700) Application for amended type certificate was first dated November 18, 2015. Updated effective application date is December 31, 2019. Production Basis Production Certificate No. 7SO, issued September 1,1978, See Notes 16 and 17. Equipment The basic required equipment as prescribed in the applicable airworthiness regulations (see Certification Basis) must be installed in the aircraft for certification. In addition, the following items of equipment are required: 1. Approved Airplane Flight Manual. Model GVIII-G800; S/N 88001 and subsequent; 14 CFR part 25, Airworthiness Standards: Transport Category Airplanes, effective February 1, 1965, including Amendments 25-1 through 25-146 with the exceptions per 14 CFR 21.101 shown: 14 CFR Amendment APPLICABLE AREA NOTES SECTION TITLE 25.21 Proof of compliance. 25-135 GVIII-G800 25.105 Takeoff 25-121 GVIII-G800 25.111 Takeoff path. 25-121 GVIII-G800 25.119 Landing climb: All engines operating. 25-121 GVIII-G800 25.121 Climb: One-engine inoperative. 25-121 GVIII-G800 T00015AT Page 28 14 CFR Amendment APPLICABLE AREA NOTES SECTION TITLE 25.123 En route flight paths. 25-121 GVIII-G800 25.125 Landing. 25-121 GVIII-G800 25.143 General. 25-129 GVIII-G800 25.237 Wind velocities. 25-121 GVIII-G800 25.253 High speed characteristics. 25-135 GVIII-G800 25.611(b) Accessibility provisions. 25-123 GVIII-G800 except as noted below 25.611(b) Accessibility provisions. N/A (See Note) EWIS components in the wing and empennage All design areas comply with the EWIS requirements at Amendment 25- 123, except the wing and empennage. 25.621 Casting factors. 25-0 GVIII-G800 25.729 Retracting mechanism. 25-75 GVIII-G800 except as noted below 25.729(c) Retracting mechanism 25-136 Human factors aspects of the landing gear emergency operation 25.729(e) Retracting mechanism. 25-136 Landing Gear Control and Indication System (LGCIS) 25.773(b)(1)(i) Pilot compartment view. 25-108 GVIII-G800 25-452-SC 25.795 Security considerations 25-106 GVIII-G800 25.813(c)(2)(ii ) Emergency exit access. TC8700AT-T-C-7 Rev 2 GVIII-G800 25.851 Fire extinguishers. 25-74 GVIII-G800 except as noted below 25.851(a)(8) Fire extinguishers. 25-142 ECS Flow Schedule Change To maintain consistent certification basis with GVIII-G700 25.855(a)(b)(d )(e)(f)(g)(h)(1) (2)(i) Cargo or baggage compartments. 25-123 GVIII-G800 25.855(j) Cargo or baggage compartments. 25-123 GVIII-G800 except as noted below 25.855(j) Cargo or baggage compartments. N/A (See Note) EWIS components in the wing and empennage All design areas comply with the EWIS requirements at Amendment 25- 123, except the wing and empennage. 25.857(b) Cargo compartment classification 25-93 GVIII-G800 25.869(a)(3) Fire protection: Systems. 25-123 GVIII-G800 except as noted below 25.869(a)(3) Fire protection: Systems. N/A (See Note) EWIS components in the wing and empennage All design areas comply with the EWIS requirements at Amendment 25- 123, except the wing and empennage. Page 29 T00015AT 14 CFR Amendment APPLICABLE AREA NOTES SECTION TITLE 25. 869(a)(4) Fire protection: Systems 25-113 EWIS components in the wing and empennage: Unchanged LRUs in fuselage, pylon, engine, wing, and empennage; EWIS components integral to unrelated, not significant changes 25.869(a)(4) [25- 113] applies to unchanged LRUs from the GVI in the fuselage, pylon, engine, wing, empennage and to electrical changes in the wing and empennage and EWIS components integral to unrelated, not-significant changes in accordance with 14 CFR 21.101(b)(2). 25.901(d) Installation 25-126 GVIII-G800 except as noted below See ELOS AT-01-2015-0016-P-08 25.901(d) Installation TC8700AT-T-P-3 Rev. 1 Unchanged or unaffected APU installation components 25.954 Fuel system lightning protection. 25-14 GVIII-G800 25.975 Fuel tank vents and carburetor vapor vents. 25-0 GVIII-G800 25.981 Fuel tank explosion prevention. 25-102 GVIII-G800 25.1203(d) Fire detector system TC8700AT-T-P-8 Rev. 1 GVIII-G800 25.1301(b) Function and installation. 25-123 GVIII-G800 except as noted below 25.1301(b) Function and installation. N/A (See Note) EWIS components in the wing and empennage All design areas comply with the EWIS requirements at Amendment 25- 123, except the wing and empennage. 25.1309(f) Equipment, systems, and installations. 25-123 GVIII-G800 except as noted below 25.1309(f) Equipment, systems, and installations. N/A (See Note) EWIS components in the wing and empennage All design areas comply with the EWIS requirements at Amendment 25- 123, except the wing and empennage. 25.1323 Airspeed indicating system. 25-109 GVIII-G800 25.1324 Angle of attack system. N/A GVIII-G800 25.1325 Static pressure system 25-108 GVIII-G800 25.1353 Electrical equipment and installations. 25-113 GVIII-G800 except as noted below T00015AT Page 30 14 CFR Amendment APPLICABLE AREA NOTES SECTION TITLE 25.1353 Electrical equipment and installations. 25-123 -Data Concentration & Network -Engine -Flight Control System:  Active Control Sidestick -Flight Deck:  Touch Screen Controllers 25.1420 Supercooled Large Drop Icing Conditions N/A GVIII-G800 25.1703 Function and installation: EWIS 25-123 GVIII-G800 except as noted below 25.1703 Function and installation: EWIS N/A (See Note) EWIS components in the wing and empennage All design areas comply with the EWIS requirements at Amendment 25- 123, except the wing and empennage. 25.1705 Systems and functions: EWIS 25-123 GVIII-G800 except as noted below 25.1705 Systems and functions: EWIS N/A (See Note) EWIS components in the wing and empennage All design areas comply with the EWIS requirements at Amendment 25- 123, except the wing and empennage. 25.1707 System separation: EWIS 25-123 GVIII-G800 except as noted below 25.1707 System separation: EWIS N/A (See Note) EWIS components in the wing and empennage All design areas comply with the EWIS requirements at Amendment 25- 123, except the wing and empennage. 25.1709 System safety: EWIS 25-123 GVIII-G800 except as noted below 25.1709 System safety: EWIS N/A (See Note) EWIS components in the wing and empennage All design areas comply with the EWIS requirements at Amendment 25- 123, except the wing and empennage. 25.1711 Component identification: EWIS 25-123 GVIII-G800 except as noted below 25.1711 Component identification: EWIS N/A (See Note) EWIS components in the wing and empennage All design areas comply with the EWIS requirements at Amendment 25- 123, except the wing and empennage. 25.1713 Fire protection: EWIS 25-123 GVIII-G800 except as noted below Page 31 T00015AT 14 CFR Amendment APPLICABLE AREA NOTES SECTION TITLE 25.1713 Fire protection: EWIS N/A (See Note) EWIS components in the wing and empennage 25.1713 is not applicable for unchanged LRUs from the GVI in the fuselage, pylon, engine, wing, and empennage; 25.1713 does not apply to EWIS components in the wing and empennage and EWIS components integral to unrelated, not-significant changes in accordance with 14 CFR 21.101(b)(2). 25.1715 Electrical bonding and protection against static electricity: EWIS 25-123 GVIII-G800 except as noted below 25.1715 Electrical bonding and protection against static electricity: EWIS N/A (See Note) EWIS components in the wing and empennage All design areas comply with the EWIS requirements at Amendment 25- 123, except the wing and empennage. 25.1717 Circuit protective devices: EWIS 25-123 GVIII-G800 except as noted below 25.1717 Circuit protective devices: EWIS N/A (See Note) EWIS components in the wing and empennage All design areas comply with the EWIS requirements at Amendment 25- 123, except the wing and empennage. 25.1719 Accessibility provisions: EWIS 25-123 GVIII-G800 except as noted below 25.1719 Accessibility provisions: EWIS N/A (See Note) EWIS components in the wing and empennage All design areas comply with the EWIS requirements at Amendment 25- 123, except the wing and empennage. 25.1721 Protection of EWIS 25-123 GVIII-G800 except as noted below 25.1721 Protection of EWIS N/A (See Note) EWIS components in the wing and empennage All design areas comply with the EWIS requirements at Amendment 25- 123, except the wing and empennage. 25.1723 Flammable fluid fire protection; EWIS 25-123 GVIII-G800 except as noted below T00015AT Page 32 14 CFR Amendment APPLICABLE AREA NOTES SECTION TITLE 25.1723 Flammable fluid fire protection; EWIS N/A (See Note) EWIS components in the wing and empennage All design areas comply with the EWIS requirements at Amendment 25- 123, except the wing and empennage. 25.1725 Powerplants: EWIS 25-123 GVIII-G800 except as noted below 25.1725 Powerplants: EWIS N/A (See Note) EWIS components in the wing and empennage All design areas comply with the EWIS requirements at Amendment 25- 123, except the wing and empennage. 25.1727 Flammable fluid shutoff means: EWIS 25-123 GVIII-G800 except as noted below 25.1727 Flammable fluid shutoff means: EWIS N/A (See Note) EWIS components in the wing and empennage All design areas comply with the EWIS requirements at Amendment 25- 123, except the wing and empennage. 25.1729 Instructions for Continued Airworthiness: EWIS 25-123 GVIII-G800 except as noted below 25.1729 Instructions for Continued Airworthiness: EWIS N/A (See Note) EWIS components in the wing and empennage All design areas comply with the EWIS requirements at Amendment 25- 123, except the wing and empennage. 25.1731 Powerplant and APU fire detector system: EWIS 25-123 GVIII-G800 except as noted below 25.1731 Powerplant and APU fire detector system: EWIS N/A (See Note) EWIS components in the wing and empennage All design areas comply with the EWIS requirements at Amendment 25- 123, except the wing and empennage. 25.1733 Fire detector systems, general: EWIS 25-123 GVIII-G800 except as noted below 25.1733 Fire detector systems, general: EWIS N/A (See Note) EWIS components in the wing and empennage All design areas comply with the EWIS requirements at Amendment 25- 123, except the wing and empennage. C25.1 Appendix C, Part I - Atmospheric Icing Conditions. Appendix C, Part II - Airframe Ice Accretions for Showing Compliance with Subpart B. 25-129 GVIII-G800 H25.1 General. 25-123 GVIII-G800 except as noted below Page 33 T00015AT 14 CFR Amendment APPLICABLE AREA NOTES SECTION TITLE H25.1 General. 25-68 (See Note) EWIS components in the wing and empennage All design areas comply with the EWIS requirements at Amendment 25- 123, except the wing and empennage. H25.4 Airworthiness Limitations Section 25-132 GVIII-G800 H25.5 Electrical Wiring Interconnection System (EWIS) Instructions for Continued Airworthiness. 25-123 GVIII-G800 except as noted below H25.5 Electrical Wiring Interconnection System (EWIS) Instructions for Continued Airworthiness. N/A (See Note) EWIS components in the wing and empennage All design areas comply with the EWIS requirements at Amendment 25- 123, except the wing and empennage. Appendix M Fuel Tank System Flammability Reduction Means. N/A N/A Appendix N Fuel Tank Flammability Exposure and Reliability Analysis. N/A N/A Appendix O Supercooled Large Drop Icing Conditions. N/A N/A 14 CFR part 34, Fuel Venting and Exhaust Emission Requirements for Turbine Engine Powered, effective September 10, 1990, including Amendments 34-1 through 34-6. 14 CFR part 36, Noise Standards: Aircraft Type Certification and Airworthiness Certification, effective December 1, 1969, including Amendments 36-1 through 36-31. Compliance with Section 44715(e) of Title 49 U.S.C. (Noise Control Act of 1972). Optional Design Regulations: a) The Model GVIII-G800 has been shown to comply with the requirements for ditching: § 25.801. b) The Model GVIII-G800 has been shown to comply with the requirements for public address systems: § 25.1423. c) The Model GVIII-G800 is approved for flight into known icing conditions and has demonstrated compliance to § 25.1419. T00015AT Page 34 The following special conditions in accordance with 14 CFR part 21 apply to the Model GVIII-G800: SC No. Subject 25-422-SC Electronic Flight Control System Mode Annunciation 25-429-SC Automatic Speed Protection for Design Dive Speed 25-433-SC Design Roll Maneuver Requirement for Electronic Flight Controls 25-434-SC Interaction of Systems and Structures 25-452-SC Windshield Coating in Lieu of Wipers 25-563-SC Electro-hydraulically Actuated Seats Equipped with a Backup Power Supply 25-612-SC Non-Rechargeable Lithium Battery Installations 25-850-SC Limit Pilot Forces for Side-Stick Controllers 25-853-SC Flight Envelope Protection: High Incidence Protection System (Non-icing and Icing Conditions) 25-849-SC Side Stick Controllers – Controllability and Maneuverability 25-846-SC Electronic System Security Protection from Unauthorized Internal Access 25-847-SC Electronic System Security Protection from Unauthorized External Access 25-855-SC Electronic Flight Control System: Control Surface Position Awareness 25-852-SC Operation Without Normal Electrical Power 25-862-SC Dynamic Test Requirements for Single – and Multiple-Occupant Side-Facing Seats with or without Airbag Systems 25-848-SC Installation of Large Non-Structural Glass in the Passenger Compartment 25-858-SC Flight Envelope Protection: Takeoff Stall Protection 25-851-SC Installation of Therapeutic Oxygen System Exemptions from 14 CFR part 25 in accordance with 14 CFR part 11: a) Exemption No. 19417, § 25.809(a); Over wing exit viewing b) Exemption No. 10188B, § 25.813(e); Acoustic and Forward Vestibule Door c) Exemption No. 18556B, § 25.813(e); Mid Cabin Doors for 14 CFR Part 91 Operations and Part 135 Operations d) Exemption No. 10387C, § 25.981(a)(3); Fuel Tank Ignition Prevention e) Exemption No. 9940B, § 25.1447(c)(1); High Landing Field Elevation f) Exemption No. 17727B, § 25.841(a)(2); Cabin Pressurization Requirements for Baggage Compartment Access g) Partial Time-Limited Exemption No. 21744A, §25,951(c), 25.952(a), and 25.901(d); Fuel Feed Icing Threat Page 35 T00015AT Equivalent Safety Findings according to the provisions of 14 CFR part 21.21(b)(1) for the following subjects: AT-01-2015- 0016-A-1 § 25.629(d)(9) Failure Criteria Considered Under the Aeroelastic Stability Requirements of § 25.629 AT-01-2015- 0016-A-03-GVIII § 25.683(a) Operation Test Compliance for Fly-by- Wire Flight Control Systems SD-05-2022- 0038-C-05 R1 § 25.785(d) Non-TT&L Seats AT-01-2015- 0016-F-1-GVII § 25.255 Out-of-Trim Characteristics AT-01-2015- 0016-F-15-GVII § 25.251(b) Vibration / Buffeting Compliance Criteria for External Modifications AT-01-2015- 0016-P-1-GVII § 25.1155 Reverse Thrust Control and Indication AT-01-2015- 0016-P-3-GVII § 25.1203(a) Turbine Engine Tailpipe Fire Detection AT-01-2015- 0016-P-3, Rev. 1 § 25.1549(a)-(c) Digital-Only Display of Engine High Pressure “HP” Rotor Speed (N2) AT-01-2015- 0016-P-06 § 25.1193(e)(3) Engine Fire Protection AT-01-2015- 0016-P-7-GVII § 25.1145(a) Ignition Switches AT-01-2015- 0016-P-08 14 CFR Part 25 Subpart E, F, and G Auxiliary Power Unit (APU) Certification Requirements TC8700AT-T-P-3, Rev 1 14 CFR Part 25 Subpart E, F, and G Adoption of Draft Harmonized Rules for APU Certification AT-01-2015- 0016-P-12 § 25.1141(f)(2) Engine Fuel Shutoff Valve Indication AT-01-2015- 0016-P-13 § 25.934 Turbojet Engine Thrust Reverser System Tests AT-01-2015- 0016-S-1 §§ 25.1301(a)(4), 25.1309(a)-(e) Equipment, Systems, and Installation Requirements: Use of ARAC Recommendations AT-01-2015- 0016-S-20-GVII §§ 25.1303(a)(3), 25.1327, 25.1547 Use of an Electric-Only Direction Indicator Standby Instrumentation AT-01-2015- 0016-S-26-GVII § 25.1459(a)(2) Use of Inertial Reference System for Flight Data Recorder Vertical Acceleration T00015AT Page 36 AT-01-2015- 0016-S-27-GVII §§ 25.841 and 25.843 Combined Aircraft Pressurization Outflow and Positive Pressure Differential Relief Valves AT-01-2015- 0016-S-29-GVII § 25.783(c)(1) Electrical Main Entry Door Pressurization Prevention Means TC8700AT-T-C- 1, Rev. 2 § 25.807(g)(1), (2), and (3)(i)(1) and (2) Emergency Exits TC8700AT-T-C- 7, Rev. 2 § 25.813(c)(2)(ii) Seat/Furnishing Encroachment Into the Overwing Emergency Exit Openings TC8700AT-T-P-7, Rev. 1 § 25.1305(c)(6) Fuel Filter Indication System TC8700AT-T-P-8, Rev. 1 § 25.1203(d) Oil Fire Detection System TC8700AT-T-S- 17, Rev. 1 § 25.671 Flight Control System Failure Criteria TC8700AT-T-S- 23, Rev. 1 § 25.841(b)(6) Cabin Pressurization – High Field Elevation Takeoff and Landing Operations TC8700AT-T-S- 28, Rev. 1 § 25.831(g) Acceptable High Temperature Physiological Environment During Failure Conditions TC8700AT-T-S- 38, Rev. 1 §§ 25.1323(h) and 25.1325(c)(1) Pitot-Static System Moisture Control AT5177AT-T-C-1, Rev. 3 §§ 25.811(d), 25.812(b) Emergency Exit Marking, Locator, and Bulkhead/Divider Signs AT5080AT-T-P-1, Rev. 2 § 25.933(a)(1)(ii) Flight Critical Thrust Reverser ADDITIONAL DESIGN REQUIREMENTS AND CONDITIONS: The following design details or information must be maintained to ensure that an unsafe design condition is not present: Fuel Feed System Icing Threats The design of the Model GVIII series airplanes provides mitigation for fuel icing and allows for completion of the certification activities after type certification to show full compliance with the regulations to ensure that an unsafe feature or characteristic does not exist on the Gulfstream Model GVIII-G800 airplane. 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 should have the capability for the flightcrew to restore Page 37 T00015AT engine power immediately following an all-engine-out scenario and when the fuel source to the engine is interrupted. 2. During the high altitude portion of the flight at cruise speed and maximum altitude, the airplane should have the capability for the flightcrew to restart engines from a stabilized windmill speed prior to descending below an altitude of 15,000 feet, 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. 3. During flight at speeds greater than the minimum flaps-up “holding speed” and at altitudes below 20,000 feet, the airplane should have the capability for the flightcrew to restart engines from a stabilized windmill speed prior to descending 5000 feet 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 Class B Cargo Compartment and Hand Held Fire Extinguishers The GVIII-G800 has a Class B cargo compartment located aft of the main cabin. The fire protection requirements of Class B cargo compartments, as specified in § 25.857(b), rely on manual firefighting as the primary method of controlling fires. The following design features are required to ensure an unsafe condition does not exist with regards to the ability to fight a fire in the compartment: 1. The baggage compartment volume must be less than 200 cubic feet, 2. The compartment must be configured to allow for a crew member to access the stored baggage and move articles out of the way to uncover any article that may be smoldering or burning, and 3. A Halon 1211 portable fire bottle charged with minimum 13 pounds of agent and a UL Rating of 2A:40B:C must be installed adjacent to the compartment Fire Extinguishing Plumbing and Wiring Connections The engine and APU fire extinguishing plumbing and electrical connections must be constructed, arranged, and installed such that cross connection is not possible during normal maintenance actions such as changing the fire extinguishing bottles or troubleshooting the system. Fuel Vent System Fire Protection The fuel vent lines of the GVIII-G800 aircraft must be equipped with a means, such as a flame arrestor, to prevent fire from propagating up the fuel vent lines after an accident. The design must show a flame holding capability for a minimum period of 2.5 minutes to allow passenger evacuation following an accident. The design of the vent system must also be arranged in such manner to avoid vent reduction or stoppage due to ice formation or debris. This will ensure the flow rate capacity and pressure differential between the interior and exterior of the tank are maintained within acceptable safe levels. This must be substantiated for T00015AT Page 38 all phases of flight (normal and emergency) including ground operation (such as refueling / de-fueling). Fan Blade Out / Windmilling Descent Profile Gulfstream has shown compliance to the applicable requirements relative to fan blade out (FBO) / windmilling (including §§ 25.143(b), 25.571, 25.1309(a), and 25.1431(a)), and has demonstrated that the aircraft will maintain an acceptable level of vibration through the FBO emergency descent profile. See the Flight Standardization Board (FSB) Report for areas of emphasis. A copy of the FSB report may be obtained from the FAA Dynamic Regulatory System (DRS) at https://drs.faa.gov/browse/FSB_REPORTS/doctypeDetails Yaw Oscillations Service experience has shown that an unsafe rudder system design feature may contribute to a yaw related aircraft-pilot coupling (APC) event that could potentially lead to a structural failure of the vertical stabilizer. If this feature exists, excessive rudder pedal inputs may drive loads beyond the ultimate design. The following criteria for rudder performance must be demonstrated to ensure a safe rudder control system design per §§ 25.143(a), 25.143(b), and 25.671(a), and that it does not have the unsafe characteristics described above: 1. The rudder control system design characteristics, including pedal sensitivity, breakout forces, lateral accelerations as a function of pedal force, the ability to adequately modulate rudder control throughout the flight envelope, and displacement and harmony with other flight controls provide safe handling qualities throughout the flight envelope. 2. The airplane is adequately protected from the adverse effects of inappropriate rudder inputs, including the potential for loss of control, APC / PIO, or exceeding the airplane’s structural design envelope. Type Certificate Information (GVIII-G800) Application for amended type certificate was first dated November 18, 2015. Updated effective application date is June 30, 2020. Production Basis Production Certificate No. 7SO, issued September 1,1978, See Notes 16 and 17. Equipment The basic required equipment as prescribed in the applicable airworthiness regulations (see Certification Basis) must be installed in the aircraft for certification. In addition, the following items of equipment are required: 1. Approved Airplane Flight Manual. NOTES: NOTE 1. Weight and Balance: A current weight and balance report, including a list of equipment included in certificated empty weight, and loading instructions when necessary, must be provided for each aircraft at the time of original certification. The certificated basic empty weight and corresponding center of gravity location must include that total engine oil, hydraulic fluid, and unusable fuel. Loading of the aircraft must be accomplished in a manner that always Page 39 T00015AT maintains the center of gravity within the specified limits considering crew and occupant movements as well as fuel consumption and transfer. NOTE 2. Airplane operation must be in accordance with the approved Airplane Flight Manual. All placards required by either the FAA-approved Airplane Flight Manual, the applicable operating rules, or the certification basis must be installed as specified. NOTE 3. Instructions for Continued Airworthiness: The Instructions for Continued Airworthiness are contained in the Aircraft Maintenance Library, which includes the associated Maintenance Review Board Report. These documents meet the requirements of §§ 25.1529 and 25.1729 (where applicable to GVIII- G700 and GVIII-G800), and part 25 Appendix H (Sections H25.2, H25.3, H25.4 and H25.5 where applicable to GVIII-G700 and GVIII-G800), including information on description, operation, maintenance (troubleshooting, removal/replacement, cleaning, inspection, etc.), and scheduling, as well as an Airworthiness Limitations Section (ALS). See Note 11 for additional information regarding airworthiness limitations. NOTE 4. Type Certificate T00015AT is for a “green” aircraft configuration only, as defined by: GVI Gulfstream drawing 60P0000000-001, GVI Aircraft Level Configuration Control Document, revision M, or later FAA approved revision GVIII-G700 Gulfstream drawing 62P0000000-001, GVIII-2 Aircraft Level Configuration Control Document, revision A, or later FAA approved revision(s). GVIII-G800 Gulfstream drawing 61P0000000-001, GVIII-G800 Aircraft Level Configuration Control Document, revision A, or later FAA approved revision(s). Cabin interior installations (including passenger seating configurations) must receive separate FAA approval, and are required prior to any operation with passengers. See Note 10 for additional information regarding interior certification requirements. NOTE 5. Aircraft Service Changes: GVI Aircraft Service Change (ASC) 001, "G650 Modification" will designate those aircraft as Model GVI (G650). Those aircraft shall be operated under Airplane Fight Manual GAC- AC-G650-OPS-0001. Applicable to S/N 6001 and subsequent. Aircraft Service Change (ASC) 010, "European Aviation Safety Agency (EASA) Certification Basic Requirements” converts aircraft to the configuration required by the EASA Type Certificate for the GVI (No. EASA.IM.A.169). Data supporting ASC 010 are FAA approved for GVI aircraft under Gulfstream control specifically being prepared for and prior to export to an EASA member country, or to a country that requires the EASA Type Design configuration. Following transfer to the foreign registry, if the aircraft is returned to U.S. registration and an application for Standard Airworthiness is submitted, then this ASC must be removed and the aircraft returned to its U.S. Type Design configuration. Aircraft fitted with ASC 010 shall be operated under the latest approved version of Airplane Fight Manual, GAC-AC-G650-OPS-0001, plus Airplane Flight Manual Supplement No. EASA-G650-2012-01. Applicable to S/N 6001 and subsequent. T00015AT Page 40 Aircraft Service Change (ASC) 011, “Engine Electronic Controller – K6.2.1 Software Upgrade. Applicable to S/N 6003 - 6059. Aircraft Service Change (ASC) 014,”GVI Extended Range (G650ER) - Modifications” will designate those aircraft as Model GVI (G650ER). Those aircraft shall be operated under Airplane Flight Manual GAC-AC-G650ER-OPS-0001. Applicable to S/N 6001 and subsequent GVIII-G700 ASC 007, “European Aviation Safetry Agency (EASA) Certification Basic Requirements,” converts GVIII-G700 aircraft to the configuration required by the EASA Type Certificate for the GVIII-G700 models (No. EASA.IM.A.169). Data supporting GVIII-G700 ASC 007 are FAA approved for GVIII-G700 aircraft under Gulfstream control specifically being prepared for and prior to export to an EASA member country, or to a country that requires the EASA Type Design configuration. Following transfer to a foreign registry, if the aircraft is returned to U.S. registration and an application for Standard Airworthiness is submitted, then this ASC must be removed and the aircraft returned to its U.S. Type Design configuration. Aircraft fitted with GVIII-G700 ASC 007 shall be operated under the latest approved version of GAC-AC-GVIII-G700-OPS-0001, Gulfstream GVIII-G700 Airplane Flight Manual, plus Airplane Flight Manual Supplement No. EASA-GVIII-G700- 2023-01. Applicable to S/N 87001 and subsequent GVIII-G800 ASC 007, “European Aviation Safetry Agency (EASA) Certification Basic Requirements,” converts GVIII-G800 aircraft to the configuration required by the EASA Type Certificate for the GVIII-G800 models (No. EASA.IM.A.169). Data supporting GVIII-G800 ASC 007 are FAA approved for GVIII-G800 aircraft under Gulfstream control specifically being prepared for and prior to export to an EASA member country, or to a country that requires the EASA Type Design configuration. Following transfer to a foreign registry, if the aircraft is returned to U.S. registration and an application for Standard Airworthiness is submitted, then this ASC must be removed and the aircraft returned to its U.S. Type Design configuration. Aircraft fitted with GVIII-G800 ASC 007 shall be operated under the latest approved version of GAC-AC-GVIII-G800-OPS-0001, Gulfstream GVIII-G800 Airplane Flight Manual, plus Airplane Flight Manual Supplement No. EASA-GVIII-G800- 2023-01. Applicable to S/N 88001 and subsequent NOTE 6. Cockpit Field of View: The cockpit front windshield dimensions for the Gulfstream Model GVI, GVIII-G700, and GVIII-G800 airplanes are critical for forward field of view certification requirements; therefore, no equipment should be installed on top of the glare shield without prior coordination with the FAA Certificate Management Certification Branch (CMCB) for the Gulfstream GVI, GVIII-G700, and GVIII-G800. NOTE 7. Cockpit Video Display: The avionics architecture of the Gulfstream Model GVI, GVIII-G700, and GVIII-G800 includes a capability to display multiple, assorted video inputs on the cockpit display units positioned directly in front of the pilots. Because these displays affect crew workload, changes to the approved video input sources (including the addition of new video sources or capabilities) will require a specific FAA approval, including specific acknowledgement and concurrence from the FAA CMCB for the GVI, GVIII-G700, and GVIII-G800. Page 41 T00015AT NOTE 8. Cockpit Modifications: Any modifications or changes in cockpit configuration which may affect aircrew workload, cockpit noise level, or day/night lighting must be evaluated in coordination with the FAA CMCB for the GVI, GVIII-G700, and GVIII-G800. NOTE 9. Systems Modifications: The GVI, GVIII-G700, and GVIII-G800 models incorporate integrated avionics and flight control systems using software-based line replaceable units (LRU’s) which share a digital signal transmission bus. The avionics and flight control configuration of the GVI, GVIII- G700, and GVIII-G800 as delivered from production is critical to the proper operation of the aircraft. Modification to the LRU software supplied with the GVI,GVIII-G700, or GVIII-G800, replacement of an LRU with a different LRU, addition of new LRU, or alteration of an LRU interface could adversely affect the airworthiness of the certified product. Accordingly, no changes to the integrated avionics or flight control system should be made without coordination with the FAA CMCB for the GVI, GVIII-G700, and GVIII-G800 TC. NOTE 10. Information to Modifiers: GVI Information to modifiers on limitations which impact original certification requirements of the Gulfstream GVI is contained in the latest FAA approved revision of Gulfstream Report GVI-GER-6855, “GVI Interior Certification Requirements Document”. Any changes to, or deviations from GVI-GER-6855 must be coordinated with the FAA CMCB. This report must be used by any company that will perform an initial cabin interior installation on a “green” GVI aircraft (as defined in Note 4). For other major interior modifications, the need to obtain and utilize Gulfstream Report GVI-GER-6855 to ensure the “green” aircraft compliance findings are not invalidated should be coordinated between the FAA East Certification Branch and the FAA CMCB for the GVI TC. GVI-GER-6855 provides guidance on design limitations and regulatory requirements for a GVI aircraft interior installation, but does not authorize any such installation. A separate FAA approval such as a supplemental type certificate (STC) or amended type certificate (ATC) is required to approve the design and installation of a GVI. Exterior emergency exit lighting during low light ambient conditions - the level of illumination exhibited during certification ground testing exceeds the requirements of § 25.812(g). Any changes to the exterior emergency exit lighting must be coordinated with the FAA CMCB for the GVI TC, and require a separate equivalent level of safety finding for § 25.809(a) for the GVI. GVIII-G700 Information to modifiers on limitations which impact original certification requirements of the Gulfstream GVIII-G700 is contained in the latest FAA approved revision of Gulfstream Report GVIII-GER-0025, “GVIII Interior Certification Requirements Document”. Any changes to, or deviations from GVIII-GER-0025 must be coordinated with the FAA CMCB. This report should be used by any company that will perform an initial cabin interior installation on a “green” GVIII-G700 aircraft (as defined in Note 4). For other major interior modifications, the need to obtain and utilize Gulfstream Report GVIII-GER- 0025 to ensure the “green” aircraft compliance findings are not invalidated should be coordinated between the FAA East Certification Branch and the FAA CMCB for the GVIII- G700 TC. GVIII-GER-0025 provides guidance on design limitations and regulatory requirements for a GVIII-G700 aircraft interior installation, but does not authorize any such installation. A separate FAA approval such as a supplemental type certificate (STC) or amended type T00015AT Page 42 certificate (ATC) is required to approve the design and installation of a GVIII-G700 interior. Exterior emergency exit lighting during low light ambient conditions - the level of illumination exhibited during certification ground testing exceeds the requirements of § 25.812(g). Any changes to the exterior emergency exit lighting must be coordinated with the FAA CMCB for the GVIII-G700 TC, and require separate compliance activities per Exemption No. 18499, § 25.809(a) for the GVIII-G700. GVIII-G800 Information to modifiers on limitations which impact original certification requirements of the Gulfstream GVIII-G800 is contained in the latest FAA approved revision of Gulfstream Report GVIII-GER-0025, “GVIII Interior Certification Requirements Document”. Any changes to, or deviations from GVIII-GER-0025 must be coordinated with the FAA CMCB. This report should be used by any company that will perform an initial cabin interior installation on a “green” GVIII-G800 aircraft (as defined in Note 4). For other major interior modifications, the need to obtain and utilize Gulfstream Report GVIII-GER- 0025 to ensure the “green” aircraft compliance findings are not invalidated should be coordinated between the FAA East Certification Branch and the FAA CMCB for the GVIII- G800 TC. GVIII-GER-0025 provides guidance on design limitations and regulatory requirements for a GVIII-G800 aircraft interior installation, but does not authorize any such installation. A separate FAA approval such as a supplemental type certificate (STC) or amended type certificate (ATC) is required to approve the design and installation of a GVIII-G800 interior. Exterior emergency exit lighting during low light ambient conditions - the level of illumination exhibited during certification ground testing exceeds the requirements of § 25.812(g). Any changes to the exterior emergency exit lighting must be coordinated with the FAA CMCB for the GVIII-G800 TC, and require separate compliance activities per Exemption No. 19417, § 25.809(a) for the GVIII-G800. NOTE 11. Airworthiness Limitations: The replacement times, inspection intervals, related inspection procedures, and design configuration control limitations required by §§ 25.571, 25.981, 25.1529 and Appendix H.25.4 are contained in the “Airworthiness Limitation Section” (ALS) located in the Gulfstream Aircraft Maintenance Manual, Chapter 5, Section 05-10-10. The “Limit of Validity” required by § 25.571(a)(3), Amdt 25-132 is also included in the ALS. The times and procedures listed in the ALS cannot be altered without FAA Engineering approval. Unless an Airworthiness Directive is issued, the appropriate ALS revision level is determined based on the issuance of the standard airworthiness certificate, predicated on this TC, and the applicable operating and maintenance regulations, such as §§ 91.403 or 43.16. NOTE 12. RVSM: The Model GVI, GVIII-G700, and GVIII-G800 baseline TC configurations have been approved to operate in “Reduced Vertical Separation Minimum” (RVSM) airspace. Continued airworthiness and operational approval aspects of RVSM must be constructed according to Advisory Circular (AC) 91-85, titled “Authorization of Aircraft and Operators for Flight in Reduced Vertical Separation (RVSM) Minimum Airspace.” Page 43 T00015AT NOTE 13. Forward Observer’s Seat (Jump Seat) The Forward Observer’s Seat (Jump Seat) is approved for taxi, takeoff, and landing on the GVI, GVIII-G700, and GVIII-G800 models as part of Type Design. NOTE 14. Control Column The GVI implements an electronic flight control system, therefore no items may be mounted on the control column without coordination with the FAA CMCB for the GVI TC. NOTE 15. GVI The FAA has concluded that the occurrence of any uncontrollable high-thrust failure condition, or any of the associated causal failures listed in Section 05-10-10 of the applicable Aircraft Maintenance Manual “may endanger the safe operation of an airplane” and hence are reportable under FAR 121.703, 125.409, and 135.415. Incorporation of ASC 011 on the GVI satisfies the conditions identified as time limited in Exemption No. 10614. All non-time limited aspects of Exemption No. 10614 are still applicable to all GVI aircraft regardless of ASC 011 incorporation. GVIII-G700 The FAA has concluded that the occurrence of any uncontrollable high thrust failure conditions, or any of the associated causal failures listed within Gulfstream Document GVIII-GER-1725, may endanger the safe operation of an airplane. Consequently, the FAA recommends that operators report instances of uncontrollable high thrust in accordance with Title 14, Code of Federal Regulations 121.703(c), 125.409, and 135.415(c). NOTE 16. The following GVI aircraft serial numbers were produced under the Type Certificate only: 6001, 6006 – 6015, 6017, 6019 – 6022, 6032 – 6039. The following GVIII-G700 aircraft serial numbers were produced under the Type Certificate only: 87001 – 87007, 87009 – 87011, 87013, 87015, 87017, 87018, 87020, 87021, 87025. The following GVIII-G800 aircraft serial numbers were produced under the Type Certificate only: 88001 – 88015. NOTE 17. The Production Limitation Record (PLR) for Production Certificate No. 7SO was revised to include the GVI (G650) on December 20, 2012, on November 26, 2014, to include the GVI (G650ER), on April 2, 2024, to include the GVIII-G700, and again on April 16, 2025, to include the GVIII-G800. Gulfstream is authorized to issue airworthiness certificates under the Organization Delegation Authorization (ODA) Procedures of 14 CFR part 183, subpart D, and FAA Order 8100.15. All aircraft not listed in Note 16 were produced under the Production Certificate. NOTE 18. GVI interior STC No. ST04252AT-D was originally approved using the following portions of SFAR 109 in lieu of compliance to 14 CFR 25.813(e) at Amendment 25-116 for mid cabin doors: · SFAR 109 paragraph 2(a), (b), (c) and (d); · SFAR 109 paragraph 2(e) modified for the following placard wording, “Operation involving the carriage of persons or property for compensation or hire are prohibited, unless the mid-cabin door is locked in an open position”; · SFAR 109 paragraph 2(g) to allow operation under part 135 when the mid-cabin door is locked in the open position in accordance with procedures contained within Instructions for Continued Airworthiness; and SFAR 109 paragraph 10(a) through (f). T00015AT Page 44 On January 15, 2016, the FAA signed Exemption No. 13281A which granted a partial exemption to 14 CFR 25.813(e) at Amendment 25-116 for mid cabin doors. This exemption supercedes and replaces the previously approved requirements of SFAR 109 for STC No. ST04252AT-D. Compliance with the requirements of Exemption No. 13281A is required for all type design changes or alterations approved after February 22, 2016 which include installation of mid cabin doors. NOTE 19. Personal Electronic Devices (PEDs): The GVIII-G700 and GVIII-G800 are PED tolerant aircraft and have demonstrated compliance with PS-ANM-25-13 and sections 5.2 and 5.3 of DO-307B; however, operators must establish compliance with 14 CFR 91.21, 121.306, and 135.144 requirements. Any changes to aircraft doors, windows, or other apertures, interior furnishings, or antenna/receiver locations can affect the spurious emissions tolerance and must be assessed per the latest FAA approved revision of GVIII-G700 and GVIII- G800 Interior Certification Requirements Document (GVIII-GER-0025). NOTE 20. Time-Limited Partial Exemption 17825: In accordance with the FAA Decision contained in Time-limited Exemption No. 17825 for 14 CFR Section 25.1309(b): Non-Rechargeable Lithium Battery Installations in Life Raft ELTs, no GVI aircraft may operate after May 8, 2020 unless compliance is recorded with Gulfstream GVI Customer Bulletin number 244 – Equipment/Furnishings (ATA 25), Replacement - Life Raft Containing SRB406 ELT. NOTE 21. Time-Limited Partial Exemption 21815: In accordance with the FAA Decision contained in Time-Limited Exemption No. 21815 for 14 CFR Section 25.901(c): Uncontrollable High Thrust Failure Conditions, no GVIII-G700 aircraft may operate after January 31, 2027 unless fitted with Electronic Engine Controller Software F4.1.1 or later approved software. ``` ## ADs (13, in force first) - [AD 2026-13-51](https://openairdocs.org/ad/2026-13-51): Power Plant · Gulfstream Aerospace GVIII-G700 and GVIII-G800. Effective Jul 17, 2026 - [AD 2026-13-02](https://openairdocs.org/ad/2026-13-02): Navigation · Airbus Canada Limited Partnership 18, 49-46, 80-A and 555 more. Effective Jul 1, 2026 - [AD 2026-01-02](https://openairdocs.org/ad/2026-01-02): Wings · Gulfstream Aerospace GVI. Effective Feb 24, 2026 - [AD 2023-10-02](https://openairdocs.org/ad/2023-10-02): Indicating/Recording System, Navigation · Boeing 18, 23, 35 and 1,060 more. Effective May 26, 2023 - [AD 2020-11-01](https://openairdocs.org/ad/2020-11-01): Flight Controls · Gulfstream Aerospace GVI. Effective Jul 27, 2020 - [AD 2020-02-18](https://openairdocs.org/ad/2020-02-18): Flight Controls · Gulfstream Aerospace GVI, GVII-G500 and GVII-G600. Effective Feb 13, 2020 - [AD 2019-23-11](https://openairdocs.org/ad/2019-23-11): Flight Controls · Gulfstream Aerospace GVI. Effective Dec 30, 2019 - [AD 2018-20-04](https://openairdocs.org/ad/2018-20-04): Flight Controls · Gulfstream Aerospace GVI. Effective Oct 15, 2018 - [AD 2018-12-07](https://openairdocs.org/ad/2018-12-07): Landing Gear · Gulfstream Aerospace GVI. Effective Jul 23, 2018 - [AD 2017-20-08](https://openairdocs.org/ad/2017-20-08): Airborne Auxiliary Power and Fuselage · Gulfstream Aerospace G-IV, GIV-X, GV and 2 more. Effective Nov 6, 2017 - [AD 2017-04-01](https://openairdocs.org/ad/2017-04-01): Flight controls · Gulfstream Aerospace GVI. Effective Mar 28, 2017 - [AD 2015-20-10](https://openairdocs.org/ad/2015-20-10): Pneumatic · Gulfstream Aerospace GVI. Effective Nov 13, 2015 - [AD 2015-24-06](https://openairdocs.org/ad/2015-24-06) (historical): Landing gear · Gulfstream Aerospace GVI. Effective Dec 4, 2015 ## Registered aircraft by registry model (OpenAirDocs) - [Gulfstream Aerospace GVI (G650ER)](https://openairdocs.org/model/gulfstream-aerospace-gvi-g650er): 291 aircraft (registry code 3980050) - [Gulfstream Aerospace GVIII-G700](https://openairdocs.org/model/gulfstream-aerospace-gviii-g700): 131 aircraft (registry codes 3980221, 3980222) - [Gulfstream Aerospace GVIII-G800](https://openairdocs.org/model/gulfstream-aerospace-gviii-g800): 104 aircraft (registry code 3980321) - [Gulfstream Aerospace GVI (G650)](https://openairdocs.org/model/gulfstream-aerospace-gvi-g650): 53 aircraft (registry code 3980214) - [Gulfstream Aerospace GVI](https://openairdocs.org/model/gulfstream-aerospace-gvi): 31 aircraft (registry code 3980121) ## STCs approved under this data sheet (44) - [STC ST12243IB](https://openairdocs.org/stc/ST12243IB): Installation of a VVIP cabin interior. Jet Aviation AG - [STC ST04603CH](https://openairdocs.org/stc/ST04603CH): Installation of SpaceX Starlink Aviation System. Nextant Aerospace - [STC ST00197IB](https://openairdocs.org/stc/ST00197IB): Installation of the Universal Quick Access Recorder (uQAR). Flight Data Technologies Inc. - [STC ST11969AT](https://openairdocs.org/stc/ST11969AT): Installation of Gogo Galileo HDX System. Gulfstream Aerospace Corporation - [STC ST04328NY](https://openairdocs.org/stc/ST04328NY): The Manufacture and Installation of Exterior Placards, Labels and Signs is to be performed, installed. Libellule Monde Inc - [STC ST03875NY](https://openairdocs.org/stc/ST03875NY): Installation of interior placards, signs and markings. Libellule Monde Inc. - [STC ST04570AT](https://openairdocs.org/stc/ST04570AT): Installation of SpaceX Starlink Aviation System. Gulfstream Aerospace Corporation - [STC ST04351AT-D](https://openairdocs.org/stc/ST04351AT-D): Installation of an Air Ionization System. Gulfstream Aerospace Corporation - [STC ST04539AT](https://openairdocs.org/stc/ST04539AT): Installation of Satellite TV System. Gulfstream Aerospace Corporation - [STC ST04347AT-D](https://openairdocs.org/stc/ST04347AT-D): Installation of Satcom Direct Plane Simple System. Gulfstream Aerospace Corporation - [STC ST00892LA](https://openairdocs.org/stc/ST00892LA): Installation of Emergency Vision Assurance System (EVAS).. VisionSafe LLC - [STC ST12147IB](https://openairdocs.org/stc/ST12147IB): Installation of VVIP Interior Completion. Jet Aviation AG - [STC ST03885AT](https://openairdocs.org/stc/ST03885AT): Installation of an Avionica, Inc. avCM Cellular Module. Aircraft Systems and Manufacturing Inc. - [STC ST04649NY](https://openairdocs.org/stc/ST04649NY): Installation of Avionic Instruments Frequency Converters. Kilroy Aviation LLC - [STC ST04350AT-D](https://openairdocs.org/stc/ST04350AT-D): Installation of an Airplane Interior. Gulfstream Aerospace Corporation - [STC ST02472AT](https://openairdocs.org/stc/ST02472AT): Installation of a mini Quick Access Recorder (QAR) model MKI, MKII, or MKIII. Aircraft Systems and Manufacturing Inc. - [STC ST11981IB](https://openairdocs.org/stc/ST11981IB): Installation of a VVIP Cabin Interior. Jet Aviation AG - [STC ST01117DE](https://openairdocs.org/stc/ST01117DE): Installation of the Gogo ATG C1.. Peregrine - [STC ST04541AT](https://openairdocs.org/stc/ST04541AT): Installation of an Airplane Medevac Interior. Gulfstream Aerospace Corporation - [STC ST04540AT](https://openairdocs.org/stc/ST04540AT): Installation of SpaceX Starlink Aviation System. Gulfstream Aerospace Corporation - [STC ST04348AT-D](https://openairdocs.org/stc/ST04348AT-D): Installation of Honeywell AIS-2000 High Definition (HD) Upgrade. Gulfstream Aerospace Corporation - [STC ST00126IB](https://openairdocs.org/stc/ST00126IB): Replacement of Halon agent with alternate Halon-free Portable Fire Extinguisher agent. AMAC Aerospace Switzerland AG - [STC ST00105IB](https://openairdocs.org/stc/ST00105IB): Introduction of Activation of Wireless Charging Systems for Portable Electronic Devices. AMAC AEROSPACE SWITZERLAND AG - [STC ST04787NY](https://openairdocs.org/stc/ST04787NY): Installation of True Blue Power TFC4000 AC-to-AC Converter. Sterling Helicopter - [STC ST04252AT-D](https://openairdocs.org/stc/ST04252AT-D): Installation of an Airplane Interior. Gulfstream Aerospace Corporation - [STC ST04101NY](https://openairdocs.org/stc/ST04101NY): Installation of a Honeywell Go-Direct Router. Delta Engineering Corporation - [STC ST04177AT](https://openairdocs.org/stc/ST04177AT): Installation of a Talon Aerospace LED Replacement General Purpose Lamps. Aaxico Technical Services Inc. - [STC ST04339AT-D](https://openairdocs.org/stc/ST04339AT-D): Installation of Air Ionizer System. Gulfstream Aerospace Corporation - [STC ST04319AT-D](https://openairdocs.org/stc/ST04319AT-D): Installation of Satcom Direct Gateway (SDR-G) System. Gulfstream Aerospace Corporation - [STC ST04334AT-D](https://openairdocs.org/stc/ST04334AT-D): Installation of Viasat Ka-Broadband High Speed Data System. Gulfstream Aerospace Corporation - [STC ST02672LA](https://openairdocs.org/stc/ST02672LA): Installation of Honeywell DU-1310-2 Display Unit in accordance. Honeywell International Inc - [STC ST04340NY](https://openairdocs.org/stc/ST04340NY): Installation of TCAS 7.1 (ACAS II) upgrade of Prior Existing TCAS 7.0. Scandinavian Avionics Design ApS - [STC ST04320AT-D](https://openairdocs.org/stc/ST04320AT-D): Installation of ViaSat Ka Broadband High Speed Data System. Gulfstream Aerospace Corporation - [STC ST04440AT](https://openairdocs.org/stc/ST04440AT): Installation of Aviation Clean Air Ionization Units in cold air supply Duct/ECS system. Southern Aviation Parts and Services - [STC ST00391BO](https://openairdocs.org/stc/ST00391BO): Installation of a Honeywell CNX-900 Cabin Network Accelerator and PED tolerance certification. Pro Star Aviation LLC - [STC ST04309AT-D](https://openairdocs.org/stc/ST04309AT-D): Installation of Iridium SATCOM System (FANS-1/A+Over Iridium). Gulfstream Aerospace Corporation - [STC ST04306AT-D](https://openairdocs.org/stc/ST04306AT-D): Installation of Tailwind 500 Satellite TV System. Gulfstream Aerospace Corporation - [STC ST11071SC](https://openairdocs.org/stc/ST11071SC): Demonstration of aircraft critical equipment and antenna systems tolerance of radio frequency interference (RFI) from intentional or spurious transmissions from certain Portable Electronic Devices (PEDs). Liberty Partners Inc - [STC ST03776NY](https://openairdocs.org/stc/ST03776NY): Modification to upgrade existing Rockwell Collins TCAS (Model: TTR-920, TTR-921, and TTR-4000) at VERSION 7.0 to Rockwell Collins TCAS (Model: TTR-921, TTR-4000, and TTR-4100) at VERSION 7.1 (ACAS II). Scandinavian Avionics Design ApS - [STC ST04028AT-D](https://openairdocs.org/stc/ST04028AT-D): Installation of a TrueNorth Iridium Telephone/WLAN System. Gulfstream Aerospace Corporation - [STC ST04027AT-D](https://openairdocs.org/stc/ST04027AT-D): Installation of Satcom Direct Router (SDR).. Gulfstream Aerospace Corporation - [STC ST04254AT-D](https://openairdocs.org/stc/ST04254AT-D): Installation of Broadband Multi-Link (BBML) System. Gulfstream Aerospace Corporation - [STC ST04277AT-D](https://openairdocs.org/stc/ST04277AT-D): Installation of a Honeywell LSZ-860 Lightning Sensor System. Gulfstream Aerospace Corporation - [STC ST04253AT-D](https://openairdocs.org/stc/ST04253AT-D): Installation of a Honeywell AIS-2000 Satellite TV System. Gulfstream Aerospace Corporation --- OpenAirDocs.org is an independent research project of [Contrail Labs](https://contraillabs.com/). It is not affiliated with the FAA or the NTSB. Source documents are U.S. government works in the public domain.