# TCDS T00021AT: Gulfstream Aerospace Corporation

- Type: Type certificate data sheet
- Status: Current
- Holder: Gulfstream Aerospace Corporation
- Revision: 13
- Revised: April 9, 2026
- Product: Aircraft, Large Airplane
- Certification basis: Part 25
- Registered aircraft: 449, by the registry models matched to it (OpenAirDocs)
- Data sheet PDF: https://openairdocs.org/files/sha256/4f/27/4f2793fbcb609a477e09252176184775cfb39fbed343cdcf8828c09ce860b0d8
- FAA DRS: https://drs.faa.gov/browse/excelExternalWindow/DRSDOCID110649851120260422133842.0001
- Page: https://openairdocs.org/tcds/T00021AT

## Models (2)

As the data sheet lists them.

- GVII-G500
- GVII-G600

## What the data sheet says

From the PDF's text layer, line by line; tables lose their columns. The PDF is the record.

```text
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Rev No. 11  11  7  7  11  3  3  9 3  6  9  3  3  6 10  10  11  3  5  13 
Page No. 21 22 23                  
Rev No. - - -                  
 
DEPARTMENT OF TRANSPORTATION 
FEDERAL AVIATION ADMINISTRATION 
T00021AT 
Revision 13 
 
Gulfstream 
GVII-G500 
GVII-G600 
 
April 09, 2026 
 
TYPE CERTIFICATE DATA SHEET NO. T00021AT 
 
This data sheet, which is part of Type Certificate No. T00021AT, 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. - GVII-G500 (Transport Category), Approved July 20, 2018 
 
Engines Two - Pratt & Whitney Canada Corp. Turbofan Engine Model: 
PW814GA (Engine Type Certificate No. E00093EN)  
 
Fuel Fuel shall conform to the specification as listed. See the approved 
GVII-G500 Airplane Flight Manual (AFM) or GVII-G500 Aircraft 
Maintenance Manual (AMM) for additional information. 
 
Kerosene Type 
American British Canadian 
ASTM D 1655, Jet A 
ASTM D 1655 Jet A-1 
MIL-T-83133 (JP-8) 
DEF. STAN. 91-91 
DEF. STAN. 91-87 
 
CAN/CGSB-3.23 
 
French CIS People’s 
Republic of 
China (P.R.C.) 
N/A GOST 10227-86, RT 
GOST 10227-86, TS-1 
(with/without Decree 
118) 
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)

T00021AT  Page 2 
 
JP-5 Type 
American British Canadian 
MIL-DTL-5624 DEF STAN 91-86 CAN/GCSB -3.24 
French   
DCSEA 144B   
  
For required use of anti-icing additives and emergency use of 
alternate fuel types, refer to the FAA-approved Airplane Flight 
Manual. 
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 
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 T1602. 
 
Engine Limits See the approved GVII-G500 Airplane Flight Manual for engine 
ratings. 
 
Auxiliary Power Unit (APU) Honeywell HGT400[G]  
See the approved GVII-G500 Airplane Flight Manual for APU 
ratings. 
 
Airspeed Limits (CAS) VMO/MMO = 340 KCAS / 0.925 Mach 
For other airspeed limits, see the approved GVII-G500 Airplane 
Flight Manual 
 
C.G. Range:  See the approved Airplane Flight Manual. 
 
Empty Weight C.G. Range:  None.  
 
M.A.C.  161 in. (L.E. of M.A.C. = Fuselage Station 582.5)  
 
Datum:  For weight and balance purposes, the zero datum is 100 inches 
forward of the tip of the radome. 
 
Leveling Means:  Longitudinal: Lugs at left nose wheel well door longeron STA 
163.0 & 174.0.  
Lateral: Lugs on rear face of bulkhead STA 148.5 in nose wheel 
well.  
 See GVII-G500 Aircraft Maintenance Manual for level procedure 
 
Weight limits (lb) Configuration Max. Zero 
Fuel 
Max. 
Ramp 
Max. 
Take-Off 
Max. 
Landing 
 TC Configuration 52,100 80,000 79,600 64,350 
 ASC 005 52,100 74,900 74,900 64,350 
 
Minimum Crew 2 (Pilot and Co-Pilot)

Page 3  T00021AT 
 
Maximum Passengers 19 With approved cabin interior (See Note 4).  Maximum 
passenger capacity is limited by emergency exit door 
requirements of 14 CFR §25.807(g). 
 
   0 For aircraft without an approved cabin interior (i.e., “green” 
aircraft as defined by Gulfstream drawing 72P0000000-001, 
GVII-G500 Aircraft Level Configuration Control Document, 
revision C 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 72P0000000-001, 
GVII-G500 Aircraft Level Configuration Control Document, 
revision C or later FAA-approved revision).  Total represents 
3 crewmembers and 0 passengers 
 
Fuel Capacity  See GAC-AC-GVII-G500-OPS-0001, Gulfstream GVII-G500 
Airplane Flight Manual, or GAC-AC-GVII-G500-OPS-0002, GVII-
G500 Airplane Flight Manual for Aircraft with ASC 901, ASC 022, 
ASC 025, as applicable. 
 
Oil Capacity  Total engine oil tank capacity 18.8 lb. / 20.1 U.S. pints (each engine) 
  Usable engine oil tank capacity 7.1 lb. / 7.6 U.S. pints (each engine) 
  (Arm = +855) 
  Oil weight based upon oil density 7.5 lb per gal. 
  Capacities shown above are for oil tankage only. 
  Total engine oil is 18.8 lb. / 20.1 U.S. pints per engine 
 
  APU oil 9.5 lb. / 10.2 U.S. pints (Arm = +855). 
 
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 controlled by proper rigging of 
the flight control system. The airplane must be rigged according to 
the following FAA-approved data in the following GVII-G500 
Aircraft Maintenance Manual sections: 
 
FCS System FAA-Approved Gulfstream Document 
Aileron Control GAC500-A-27-10-03-00A-340A-A 
Rudder Control GAC500-A-27-20-02-00A-340A-A 
Elevator Control GAC500-A-27-30-02-00A-340A-A 
Horizontal 
Stabilizer 
Actuation System 
GAC500-A-27-40-01-00A-340A-A 
Flap Control GAC500-A-27-50-01-00A-273A-A 
GAC500-A-27-50-02-00A-340A-A 
Spoiler Control GAC500-A-27-60-01-00A-273A-A 
GAC500-A-27-60-02-00A-340A-A

T00021AT  Page 4 
 
 
Conditions: 
System mode of operation  
On Ground Stationary = True 
Flap Position = 0° (unless otherwise specified) 
Pitch Trim = 0° 
Roll Trim = 0° 
Yaw Trim = 0° 
 
Maximum control surface travel: 
Control Surface Maximum TEU/TEL (Deg.) Maximum TED/TER (Deg.) 
Aileron -19.7 to -21.70 +12.20 to +14.20 
Rudder +25.70 to +27.70 -25.70 to -27.70 
Elevator -25.80 to -27.80 +13.90 to +15.90 
Horizontal Stabilizer +10.5 to +10.8 (Acft Nose Up) -0.5 to -0.8 (Acft Nose Down) 
Flaps 0° 
10.0 ± 0.5° 
20.0 ± 0.5° 
39.0 ± 0.5° 
Outboard Spoilers 
(w/flaps @ 10°) +54.00 to +56.00 0.0 
Midboard Spoilers 
(w/flaps @ 10°) +54.00 to +56.00 0.0 
Inboard Spoilers 
(w/flaps @ 10°) +54.00 to +56.00 0.0 
TEU = Trailing Edge Up TED = Trailing Edge Down 
TEL = Trailing Edge Left TER = Trailing Edge Right 
 
Serial No. Eligible  S/N 72001 and subsequent  
 
Other Operating Limitations The aircraft must be operated in accordance with the latest FAA 
approved revision of GAC-AC-GVII-G500-OPS-0001, Gulfstream 
GVII-G500 Airplane Flight Manual, or GAC-AC-GVII-G500-OPS-
0002, GVII-G500 Airplane Flight Manual for Aircraft with ASC 901, 
ASC 022, ASC 025, as applicable.   
 
II. - GVII-G600 (Transport Category), Approved June 28, 2019 
 
Engines Two - Pratt & Whitney Canada Corp. Turbofan Engine Model: 
PW815GA (Engine Type Certificate No. E00093EN)  
 
Fuel Fuel shall conform to the specification as listed. See the approved 
GVII-G600 Airplane Flight Manual (AFM) or GVII-G600 Aircraft 
Maintenance Manual (AMM) for additional information. 
 
Kerosene Type 
American British Canadian 
ASTM D 1655, Jet A 
ASTM D 1655 Jet A-1 
MIL-T-83133 (JP-8) 
DEF. STAN. 91-91 
DEF. STAN. 91-87 
 
CAN/CGSB-3.23

Page 5  T00021AT 
 
French CIS People’s 
Republic of 
China (P.R.C.) 
N/A GOST 10227-86, RT 
GOST 10227-86, TS-
1 (with/without 
Decree 118) 
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) 
JP-5 Type 
American British Canadian 
MIL-DTL-5624 DEF STAN 91-86 CAN/GCSB -3.24 
French   
DCSEA 144B   
  
For required use of anti-icing additives and emergency use of 
alternate fuel types, refer to the FAA-approved Airplane Flight 
Manual. 
 
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 
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 T1602. 
 
 
Engine Limits See the approved GVII-G600 Airplane Flight Manual for engine 
ratings. 
 
Auxiliary Power Unit (APU) Honeywell HGT400[G] - See the approved GVII-G600 Airplane 
Flight Manual for APU ratings. 
 
Airspeed Limits (CAS) VMO/MMO = 340 KCAS / 0.925 Mach 
For other airspeed limits, see the approved GVII-G600 Airplane 
Flight Manual 
 
C.G. Range:  See the approved Airplane Flight Manual. 
 
Empty Weight C.G. Range:  None.  
 
M.A.C.  179.41 in. (L.E. of M.A.C. = Fuselage Station 599.83)  
 
Datum:  For weight and balance purposes, the zero datum is 100 inches 
forward of the tip of the radome.

T00021AT  Page 6 
 
Leveling Means:  Longitudinal: Lugs at left nose wheel well door longeron STA 
163.0 & 174.0.  
Lateral: Lugs on rear face of bulkhead STA 148.5 in nose wheel 
well.  
See GVII-G600 Aircraft Maintenance Manual for level procedure 
 
Weight limits (lb) Configuration Max. Zero 
Fuel 
Max. 
Ramp 
Max. 
Take-Off 
Max. 
Landing 
 TC Configuration 57,440 95,000 94,600 76,800 
 ASC 005 57,440 74,900 74,900 74,900 
 ASC 006 Part 1 56,940 95,000 94,600 76,800 
 ASC 006 Part 2 56,440 95,000 94,600 76,800 
 ASC 030 57,440 90,000 90,000 76,800 
 
Minimum Crew 2 (Pilot and Co-Pilot) 
 
Maximum Passengers 19 With approved cabin interior (See Note 4).  Maximum 
passenger capacity is limited by emergency exit door 
requirements of 14 CFR §25.807(g). 
 
   0 For aircraft without an approved cabin interior (i.e., “green” 
aircraft as defined by Gulfstream drawing 73P0000000-001, 
GVII-G600 Aircraft Level Configuration Control Document, 
revision B 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 73P0000000-001, 
GVII-G600 Aircraft Level Configuration Control Document, 
revision B or later FAA-approved revision).  Total represents 
3 crewmembers and 0 passengers 
Fuel Capacity See GVII-G600 Aircraft Flight Manual 
 
Oil Capacity   Total engine oil tank capacity 18.8 lb. / 20.1 U.S. pints (each engine) 
   Usable engine oil tank capacity 7.1 lb. / 7.6 U.S. pints (each engine) 
   (Arm = +886.6) 
   Oil weight based upon oil density 7.5 lb per gal. 
   Capacities shown above are for oil tankage only. 
   Total engine oil is 18.8 lb. / 20.1 U.S. pints per engine 
 
   APU oil 9.5 lb. / 10.2 U.S. pints (Arm = +886.6) 
 
 
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 controlled by proper rigging of 
the flight control system. The airplane must be rigged according to 
the following FAA-approved data in the following GVII-G600 
Aircraft Maintenance Manual sections:

Page 7  T00021AT 
 
 
FCS System FAA-Approved Gulfstream Document 
Aileron Control GAC600-A-27-10-03-00A-340A-A 
Rudder Control GAC600-A-27-20-02-00A-340A-A 
Elevator Control GAC600-A-27-30-02-00A-340A-A 
Horizontal 
Stabilizer 
Actuation System 
GAC600-A-27-40-01-00A-340A-A 
Flap Control GAC600-A-27-50-01-00A-273A-A 
GAC600-A-27-50-02-00A-340A-A 
Spoiler Control GAC600-A-27-60-01-00A-273A-A 
GAC600-A-27-60-02-00A-340A-A 
 
Conditions: 
System mode of operation  
On Ground Stationary = True 
Flap Position = 0° (unless otherwise specified) 
Pitch Trim = 0° 
Roll Trim = 0° 
Yaw Trim = 0° 
 
Maximum control surface travel: 
Control Surface Maximum TEU/TEL (Deg.) Maximum TED/TER (Deg.) 
Aileron -19.70 to -21.70 +12.50 to +14.50 
Rudder +25.70 to +27.70 -25.70 to -27.70 
Elevator -25.80 to -27.80 +14.30 to +16.30 
Horizontal Stabilizer +10.5 to +10.8 (Acft Nose Up) -0.5 to -0.8 (Acft Nose Down) 
Flaps 0.0 
10.0 ± 0.5° 
20.0 ± 0.5° 
39.0 ± 0.5° 
Outboard Spoilers 
(w/flaps @ 10°) +54.00 to +56.00 0.0 
Midboard Spoilers 
(w/flaps @ 10°) +54.00 to +56.00 0.0 
Inboard Spoilers 
(w/flaps @ 10°) +54.00 to +56.00 0.0 
TEU = Trailing Edge Up TED = Trailing Edge Down 
TEL = Trailing Edge Left TER = Trailing Edge Right 
Serial No. Eligible  S/N 73001 and subsequent  
 
Other Operating Limitations The aircraft must be operated in accordance with the latest FAA 
approved revision to the GVII-G600 Airplane Flight Manual,  
GAC-AC-GVII-G600-OPS-0001. 
 
Certification Basis Model GVII-G500; S/N 72001 and subsequent; 
 
 14 CFR Part 25, Airworthiness Standards: Transport Category 
Airplanes, effective February 1, 1965 including Amendments 25-1

T00021AT  Page 8 
 
through 25-137, 25-143 for §25.975(a)(7) only, and 25-144 for 
§25.773(e) only. 
 
Amendment 25-118 was not published and therefore has no 
applicability. 
 
14 CFR Part 34, Fuel Venting and Exhaust Emission 
Requirements for Turbine Engine Powered Airplanes, effective 
September 10, 1990, including Amendments 34-1 through 34-5A.   
 
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) 
 
The following optional design regulations have been complied 
with: 
 
Ditching The Model GVII-G500 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  
GVII-GER-0187, entitled “Ditching Equipment 
System Requirements Document” provides an 
acceptable means for showing compliance with  
§§ 25.1411 and 25.1415. 
 
Ice Protection 14 CFR § 25.1419 
 
The following special conditions in accordance with 14 CFR part 
21 apply to the Model GVII-G500:  
 
SC No.  Subject 
25-585-SC  Limit Pilot Forces for Side Stick Controls 
25-592-SC  Electronic Flight Control System: Control Surface 
Position Awareness 
25-598-SC  Limit Engine Torque Loads for Sudden Engine 
Stoppage 
25-600-SC  Automatic Speed Protection for Design Dive Speed 
25-601-SC  Side-Stick Controllers; Controllability and 
Maneuverability 
25-613-SC  Airplane Electronic System Security Protection from 
Unauthorized External Access 
25-614-SC Pilot Compartment View Requirements with an 
Enhanced Flight Vision System 
25-617-SC  Design Roll Maneuver Requirement 
25-618-SC  Technical Criteria for Approving Side-Facing Seats 
25-619-SC Isolation or Protection of Airplane Electrical-System 
Security from Unauthorized Internal Access

Page 9  T00021AT 
 
25-628-SC Interaction of Systems and Structures Through a 
Three-Axis Fly-by-Wire System 
25-641-SC  Electronic Flight Control System Mode 
Annunciation 
25-662-SC  Non-Rechargeable Lithium Battery Installations 
25-691-SC  Airbag Systems on Multiple-Place and Single-Place 
Side-Facing Seats 
25-715-SC Operation Without Normal Electrical Power 
25-732-SC Flight Envelope Protection - High Incidence 
Protection System 
25-754-SC Electro-Hydraulically Actuated Seats Equipped 
With Backup Power Supply 
 
Exemptions from 14 CFR part 25 in accordance with 14 CFR part 
11: 
 
a) Exemption No. 13504, § 25.809(a), Overwing Viewing Means 
b) Exemption No. 11610, § 25.813(e), Forward Vestibule and 
MED Acoustic Door 
c) Exemption No. 17045, § 25.813(e), Mid-Cabin Pocket Doors 
d) Partial Exemption No. 17636A, § 25.981(a)(3), Fuel Tank 
Ignition Prevention - Requirements for Structural Design 
Features and Fuel Tank Systems Lightning Protection 
e) Partial Exemption No. 13582, § 25.1447(c)(1), High Landing 
Field Elevation 
f) Exemption No. 17434, § 25.1711(a), EWIS Component 
Marking (Limited to 4 specific GVII-G500 aircraft) 
g) Time-Limited Exemption No. 17825, § 25.1309(b), Non-
Rechargeable Lithium Battery Installations in Life Raft ELTs, 
granted through May 8, 2020 (See Note 17) 
h) Time-Limited Partial Exemption No. 17907, § 25.1191(b)(1), 
Inlet and Thrust Reverser Fastener Cap Sealant, granted 
through July 20, 2019 (See Note 18) 
i) Time-Limited Partial Exemption No. 17965, § 25.1309(b), Non-
Rechargeable Lithium Battery Installations in Seat Airbag 
Systems, granted through August 31, 2019 (See Note 19) 
j) Exemption No. 18102, § 25.841(a)(2); Cabin Pressure Altitude 
 
 
 
 
 
Equivalent Safety Findings according to the provisions of 14 CFR 
part 21.21(b)(1) for the following subjects: 
 
TC-01-2010-0024-F-1 § 25.255 Electronic Flight 
Control System: Out-
of-Trim 
Characteristics 
 
TC-01-2010-0024-A-5-
GVI 
§ 25.331 Checked Pitch 
Maneuver

T00021AT  Page 10 
 
TC-01-2010-0024-A-6-
GVI 
§ 25.341(b) Continuous Gust 
Design Criteria 
 
TC-01-2010-0024-A-8-
GVI 
§ 25.415 Ground Gust 
 
 
TC-01-2010-0024-A-5 §§ 25.561, 25.721, 
25.963(d), and 
25.994 
Structural Integrity of 
Fuel Tanks for 
Emergency Landing 
Conditions and 
Landing Gear 
 
ST-05-2014-0004-C-7 § 25.562,  
SC 25-618-SC 
Side-Facing Seat 
ATD Placement to 
Prevent Recline 
Position 
 
ST-05-2014-0004-C-8 § 25.562,  
SC 25-618-SC, 
Item 2(g) 
Side-Facing Seat 
ATD Submarining 
   
TC-01-2010-0024-A-6 § 25.629(d)(9) Failure Criteria 
Considered Under 
the Aeroelastic 
Stability 
Requirements of § 
25.629 
 
TC-01-2010-0024-S-
17-GVI 
§ 25.671 Flight Control 
System Failure 
Criteria 
 
TC-01-2010-0024-A-9 § 25.683 Operation Test 
Compliance for Fly-
by-Wire Flight 
Control Systems 
 
TC-01-2010-0024-S-29 § 25.783(c) and 
(c)(1) 
Electric Main Entry 
Door, Pressurization 
Prevention Means 
 
TC-01-2010-0024-C-1-
GVI Rev. 1 
§ 25.807(a)(3), 
(g)(1)(2)(3), (i)(1)(2) 
 
Emergency Exits 
TC-01-2010-0024-C-1-
GIV-X Rev. 1 
§§ 25.811(d) and 
25.812(b)(1)(i)(ii)(2) 
 
Emergency Exit 
Marker, Locator and 
Bulkhead/Divider 
Signs

Page 11  T00021AT 
 
TC-01-2010-0024-C-7-
GVI Rev. 1 
§ 25.813(c)(2)(ii) Seat/Furnishing 
Encroachment into 
Overwing 
Emergency Exit 
Openings 
 
TC-01-2010-0024-S-14 § 25.831(g) Acceptable High 
Temperature 
Physiological 
Environment During 
Failure Conditions 
 
TC-01-2010-0024-S-11 § 25.841(a), (b)(6) Cabin Pressurization 
- High Field 
Elevation Takeoff 
and Landing 
Operations 
 
TC-01-2010-0024-S-27 §§ 25.841(b)(1) 
and 25.843(b)(1) 
Combined Aircraft 
Pressurization 
Outflow and Positive 
Pressure Differential 
Relief Valves 
 
TC-01-2010-0024-C-10 §§ 25.853(a) and 
25.855(d) 
Use of Reduced 
Vertical Bunsen 
Burner Flammability 
Requirements for 
Interior Materials 
 
TC-01-2010-0024-P-09 § 25.901(c)(d) APU Certification 
Requirements 
 
TC-01-2010-0024-P-1-
GIV-X 
§ 25.933(a)(1)(ii) Flight Critical Thrust 
Reverser 
   
TC-01-2010-0024-P-07 § 25.1145(a) Ignition Switches 
   
TC-01-2010-0024-P-1 § 25.1155 Reverse Thrust 
Control and 
Indication 
 
TC-01-2010-0024-P-15 § 25.1193(e)(3) Engine and APU Fire 
Protection 
 
TC-01-2010-0024-P-03 § 25.1203(a) Turbine Engine 
Tailpipe Fire 
Detection

T00021AT  Page 12 
 
TC-01-2010-0024-S-1 §§ 25.1301(a)(4) 
and 25.1309 
Equipment, Systems, 
and Installation 
Requirements:  Use 
of ARAC 
Recommendations 
 
TC-01-2010-0024-S-20 §§ 25.1303(a)(3), 
25.1327 and 
25.1547 
Use of an Electric-
Only Direction 
Indicator for Standby 
Instrumentation 
 
TC-01-2010-0024-S-
38-GVI 
 
§ 25.1325(c)(1) Pitot-Static System 
Moisture Control 
TC-01-2010-0024-S-26 § 25.1459(a)(2) Use of Inertial 
Reference System 
for Flight Data 
Recorder Vertical 
Acceleration Sensor 
Data) 
 
TC-01-2010-0024-F-2-
GVI 
 
§ 25.1517 Rough Airspeed 
Criteria 
TC-01-2010-0024-P-12 
Rev 1 
 
 
TD-01-2019-0050-F-15 
 
 
§ 25.1549(a)(b)(c) 
 
 
 
§ 25.251(b) 
Digital-Only Display 
of Engine 
Parameters 
 
Vibration/Buffeting 
Compliance Criteria 
for External 
Modifications 
 
TD-01-2016-0036-F-14 §25.125(g) Use of All-Engine 
Operating Landing 
Distance for Steep 
Approach 
Destination Planning 
 
ADDITIONAL DESIGN REQUIREMENTS AND CONDITIONS: 
 
The following design details or information must be maintained to 
ensure that an unsafe design condition is not present: 
 
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. 
 
In-Flight All-Engines Restart:

Page 13  T00021AT 
 
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): 
a. During the take-off and 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. 
b. 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: 
1) All but one engine should be restarted and 
accelerated to produce maximum 
thrust/power, or 
2) The engine(s) should be restarted, and the 
necessary thrust/power achieved, to enable 
the airplane to maintain level flight. 
c. 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: 
1) All but one engine should be restarted and 
accelerated to produce maximum 
continuous thrust/power, or 
2) The engine(s) should be restarted, and the 
necessary thrust/power achieved, to enable 
the airplane to maintain level flight. 
 
Fuel Feed System Icing Threats 
The aircraft/engine fuel feed system has been designed to prevent 
an accumulation of ice anywhere within the fuel tank and feed 
system from being released into the engine fuel system, and has 
been designed such that no loss of engine thrust occurs due to 
the release of any ice accumulation, anywhere within the 
airplane/engine operating envelope.  Any change to the 
aircraft/engine fuel feed system must be assessed against the 
same criteria. 
 
Engine Damage from Wing Ice Caused by Cold Soaked Fuel 
The potential hazards associated with ice that may form on the 
wings due to cold soaked fuel have been addressed through an 
analysis of the basic aircraft design, plus an airplane flight manual 
(AFM) procedure specific to this concern.  Any change to 
maximum landing weight, minimum zero fuel gross weight, or 
maximum fuel load at landing will require a new analysis to show 
that the cold soaked fuel cannot come in contact with the upper 
wing surface at maximum landing weight and thereby cause an 
undetected ice accumulation.  Additionally, the AFM pre-flight

T00021AT  Page 14 
 
inspection procedure (with inspection criteria based on fuel 
temperature and observed ambient weather conditions) must be 
retained such that any ice accumulation on the upper wing surface 
after refueling will be detected and addressed. 
 
Engine Nacelle Damage Caused by Burst Bleed Duct 
The GVII-G500 and GVII-G600 engine nacelles have been 
designed and tested to demonstrate structural integrity/capability 
to withstand the effects of heat impingement from a leaking bleed 
air duct.  A crew alert has been implemented to warn of slow, 
insidious leakage and procedures are prescribed for the flightcrew 
to take action in the event of a detected leak, to prevent the 
damage to and loss of the nacelle components, and potential 
damage to critical surfaces of the airplane.  Changes to the engine 
nacelle or to the flightcrew alert related to bleed duct leakage must 
be substantiated against the same criteria. 
 
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 (GVII-G500) 
Application for the type certificate was first dated October 28, 
2010, followed by reapplication on June 30, 2013 and an 
extension made on April 25, 2018 changing the effective 
application date to September 30, 2013.  The Type Certificate was 
obtained under delegation of the Gulfstream Organization 
Designation Authorization (ODA). 
 
Model GVII-G600; S/N 73001 and subsequent; 
 
14 CFR Part 25, Airworthiness Standards: Transport Category 
Airplanes, effective February 1, 1965 including Amendments 25-1 
through 25-138, 14 CFR 25.975(a)(7) at Amendment 25-143, and 
14 CFR 25.773(e) at Amendment 25-144.

Page 15  T00021AT 
 
Amendment 25-118 was not published and therefore has no 
applicability. 
 
14 CFR Part 34, Fuel Venting and Exhaust Emission 
Requirements for Turbine Engine Powered Airplanes, effective 
September 10, 1990, including Amendments 34-1 through 34-5A.   
   
14 CFR Part 36, Noise Standards: Aircraft Type Certification and 
Airworthiness Certification, effective December 1, 1969, including 
Amendments 36-1 through 36-31.   
 
The following optional design regulations have been complied 
with: 
 
Ditching The Model GVII-G600 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  
GVII-GER-0187, entitled “Ditching Equipment 
System Requirements Document” provides an 
acceptable means for showing compliance with  
§§ 25.1411 and 25.1415. 
 
Ice Protection 14 CFR § 25.1419 
 
Special conditions in accordance with 14 CFR part 21: 
All special conditions listed above for the GVII-G500 apply to the 
GVII-G600.  There were no new special conditions developed 
uniquely for the GVII-G600. 
 
Exemptions in accordance with 14 CFR part 11: 
With the exception of the items listed below, all exemptions listed 
above for the GVII-G500 apply to the GVII-G600. There were no 
new exemptions developed uniquely for the GVII-G600. 
 
The exemptions from 14 CFR part 25 requirements noted below 
were effective for the GVII-G500, but do not apply to the  
GVII-G600: 
 
a) Exemption No. 17434, § 25.1711(a), EWIS Component 
Marking (Limited to 4 specific GVII-G500 aircraft) 
b) Time-Limited Exemption No. 17825, § 25.1309(b), Non-
Rechargeable Lithium Battery Installations in Life Raft ELTs, 
granted through May 8, 2020 (See Note 17) 
c) Time-Limited Partial Exemption No. 17907, § 25.1191(b)(1), 
Inlet and Thrust Reverser Fastener Cap Sealant, granted 
through July 20, 2019 (See Note 18) 
d) Time-Limited Partial Exemption No. 17965, § 25.1309(b), Non-
Rechargeable Lithium Battery Installations in Seat Airbag 
Systems, granted through August 31, 2019 (See Note 19)

T00021AT  Page 16 
 
Equivalent Safety Findings according to the provisions of 14 CFR 
part 21.21(b)(1): 
 
All equivalent safety findings listed above for the GVII-G500 apply 
to the GVII-G600 with the exception of TD-01-2016-0036-F-14.  In 
addition: 
 
TD-01-2019-0019-F-14 §25.125(g) Use of All-Engine 
Operating Landing 
Distance for Steep 
Approach 
Destination Planning 
 
 
ADDITIONAL DESIGN REQUIREMENTS AND CONDITIONS: 
 
The design details and information listed above for the Model 
GVII-G500 apply to the Model GVII-G600 and must be maintained 
to ensure that an unsafe design condition is not present. 
 
Type Certificate Information (GVII-G600) 
Application for the amended type certificate was first dated 
October 28, 2010, followed by reapplication on March 29, 2012.  
Gulfstream re-applied for the GVII-G600 on May 20, 2014, 
requesting an effective application date of December 18, 2013.  A 
final extension was made on December 14, 2018, changing the 
effective application date to July 20, 2014.  The amended Type 
Certificate was obtained under delegation of the Gulfstream 
Organization Designation Authorization (ODA). 
 
Production Basis Production Certificate No. 7SO, issued September 1, 1978, see 
Note 16. 
 
Equipment The basic required equipment as prescribed in the applicable 
airworthiness regulations (see Certification Basis) must be 
installed in the aircraft for certification. See the Illustrated Parts 
Catalog (IPC) for an approved equipment listing.  In addition, the 
following items of equipment are required: 
(a) FAA 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 maintains the center of gravity 
within the specified limits considering crew and occupant movements as well as 
fuel consumption and transfer.

Page 17  T00021AT 
 
NOTE 2. Placards: 
Airplane operation must be in accordance with the approved Airplane Flight 
Manual.  All placards required in the AFM must be installed in the appropriate 
locations. 
NOTE 3. Instructions for Continued Airworthiness: 
The Instructions for Continued Airworthiness (ICA) are contained in the Aircraft 
Maintenance Manual, which includes the associated Maintenance Review Board 
Report.  This document meets the requirements of 14 CFR §§ 25.1529, 25.1729, 
and part 25 Appendix H, 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. Aircraft Interior Configurations: 
Type Certificate T00021AT is for a “green” aircraft configuration only, as defined 
by Gulfstream drawing 72P0000000-001, GVII-G500 Aircraft Level Configuration 
Control Document, Revision D, and 73P0000000-001, GVII-G600 Aircraft Level 
Configuration Control Document, Revision B, 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: 
 
GVII-G500 
 
Aircraft Service Change (ASC) GVII-G500 ASC 005, “Placards and Markings 
(ATA 11) Airport Access – 74,900 Pound Weight Limitation.” Aircraft fitted with 
GVII-G500 ASC 005 require the latest approved version of Airplane Flight 
Manual Supplement GVII-G500-2019-01. 
Applicable to S/N 72001 and subsequent. 
 
GVII-G500 ASC 007, "European Aviation Safety Agency (EASA) Certification 
Basic Requirements,” converts GVII-G500 aircraft to the configuration required 
by the EASA Type Certificate for the GVII models (No. EASA.IM.A.595). Data 
supporting GVII-G500 ASC 007 are FAA approved for GVII-G500 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 GVII-G500 ASC 007 shall be operated under the 
latest approved version of GAC-AC-GVII-G500-OPS-0001, Gulfstream GVII-
G500 Airplane Flight Manual, plus Airplane Flight Manual Supplement No. 
EASA-GVII-G500-2016-01; or GAC-AC-GVII-G500-OPS-0002, GVII-G500 
Airplane Flight Manual for Aircraft with ASC 901, ASC 022, ASC 025, plus 
Airplane Flight Manual Supplement No. EASA-GVII-G500-Issue1-2020-01, as 
applicable.

T00021AT  Page 18 
 
Applicable to S/N 72001 and subsequent. 
 
 
GVII-G600 
 
GVII-G600 ASC 005, “Placards and Markings (ATA 11) Airport Access – 74,900 
Pound Maximum Ramp and Takeoff Weight Limitation”. Aircraft fitted with GVII-
G600 ASC 005 require the latest approved version of Airplane Flight Manual 
Supplement GVII-G600-2020-07. 
Applicable to S/N 73001 and subsequent. 
 
GVII-G600 ASC 006, “Placards and Markings (ATA 11) - Maximum Zero Fuel 
Weight Reduction - Installation”.  Aircraft fitted with GVII-G600 ASC 006 require 
the latest approved version of Airplane Flight Manual Supplement GVII-G600-
2020-08 (Part 1) or GVII-G600-2020-10 (Part 2). 
Applicable to S/N 73001 and subsequent. 
 
GVII-G600 ASC 007, "European Aviation Safety Agency (EASA) Certification 
Basic Requirements” converts GVII-G600 aircraft to the configuration required by 
the EASA Type Certificate for the GVII models (No. EASA.IM.A.595). Data 
supporting GVII-G600 ASC 007 are FAA approved for GVII-G600 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 GVII-G600 ASC 007 shall be operated under the 
latest approved version of GAC-AC-GVII-G600-OPS-0001, Gulfstream GVII-
G600 Airplane Flight Manual, plus Airplane Flight Manual Supplement No. 
EASA-GVII-G600-2018-01. 
Applicable to S/N 73001 and subsequent. 
 
GVII-G600 ASC 030, “Placards and Markings (ATA 11) Airport Access – 90,000 
LB Maximum Ramp and Takeoff Weight Limitation.”  Aircraft fitted with GVII-
G600 ASC 030 require the latest approved version of Airplane Flight Manual 
Supplement GVII-G600-2020-07. 
Applicable to S/N 73001 and subsequent. 
NOTE 6. Cockpit Field of View: 
The cockpit front windshield dimensions for the GVII model 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 Aircraft Certification Office (CMACO) for the 
Gulfstream GVII-G500 and GVII-G600.

Page 19  T00021AT 
 
NOTE 7. Cockpit Video Display: 
The avionics architecture of the Gulfstream Model GVII-G500 and GVII-G600 
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 
CMACO for the GVII-G500 and GVII-G600. 
NOTE 8. Cockpit Modifications: 
Any modification 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 CMACO for the GVII-G500 and GVII-G600. 
NOTE 9. Systems Modifications: 
The GVII model airplanes incorporate integrated avionics and flight control 
systems using software-based line replaceable units (LRU) that share a digital 
signal transmission bus.  The avionics configuration of the GVII as delivered from 
production is critical to the proper operation of the cockpit instrumentation 
system.  Modification to the LRU software supplied with the GVII, 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 system should be made 
without coordination with the FAA CMACO for the GVII-G500 and GVII-G600. 
NOTE 10. Information to Modifiers: 
Information to modifiers on limitations which impact original certification 
requirements on the Gulfstream GVII-G500 and GVII-G600 are contained in the 
latest FAA approved revision of Gulfstream report GVII-GER-0149, GVII-G500 
and GVII-G600 Interior Certification Requirements Document.  Any changes to, 
or deviations from GVII-GER-0149 must be coordinated with the FAA CMACO 
for the GVII-G500 and GVII-G600.  This report must be used by any company 
that will perform an initial cabin interior installation on a “green” GVII-G500 or 
GVII-G600 aircraft (as defined in Note 4). For other major interior modifications, 
the need to obtain and utilize Gulfstream Report GVI-GER-0149 to ensure that 
“green” aircraft compliance findings are not invalidated should be coordinated 
between the FAA Project Aircraft Certification Office and the FAA CMACO for the 
GVII TC. 
GVII-GER-0149 provides guidance on design limitations and regulatory 
requirements for a GVII-G500 or GVII-G600 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 GVII-G500 or GVII-G600 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 CMACO for the GVII-G500 and GVII-G600, 
and separate compliance activities will be necessary per Exemption No. 13504 
for § 25.809(a).

T00021AT  Page 20 
 
NOTE 11. Airworthiness Limitations: 
The replacement times, inspection intervals, related inspection procedures, and 
critical design configuration control limitations required by 14 CFR §§ 25.571, 
25.981, 25.1529 and Appendix H.25.4 are contained in the “Airworthiness 
Limitation Section” (ALS) of the Gulfstream Aircraft Maintenance Manual, 
Chapter 5, Section 05-10-10.  The “Limit of Validity” required by 14 CFR § 
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 14 CFR §§ 91.403 or 43.16. 
NOTE 12. RVSM: 
Per the approved Type Design, the Gulfstream Models GVII-G500 S/N 72001 
and subsequent, and GVII-G600 S/N 73001 and subsequent meet the 
airworthiness requirements and are eligible 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 “Authorization of Aircraft and Operators for Flight in 
Reduced Vertical Separation Minimum Airspace.” 
NOTE 13. Portable Electronic Devices (PEDs): 
The GVII-G500 and GVII-G600 are PED tolerant aircraft and have demonstrated 
compliance with PS-ANM-25-13 and sections 5.2 and 5.3 of DO-307A; 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 GVII-G500 and GVII-G600 Interior Certification Requirements Document 
(GVII-GER-0149). 
NOTE 14. Forward Observer Seat (Jump Seat): 
The Forward Observer Seat (Jump Seat) is approved for taxi, takeoff, and 
landing on the GVII-G500 and GVII-G600 as part of Type Design.  
NOTE 15. Direction Indicator Requirements: 
The Gulfstream Models GVII-G500 and GVII-G600 meet 14 CFR §25.1303(a)(3) 
requirements for a direction indicator (non-stabilized magnetic compass) by 
installation of two independent standby instruments (ISI) through the following 
means: 
The GVII-G500 and GVII-G600 ISI are driven by magnetometers and micro-
electro mechanical system gyros. 
Any change to the standby instruments or related equipment will require 
coordination with the FAA CMACO for the GVII-G500 and GVII-G600 and a 
separate equivalent safety finding for §§ 25.1303(a)(3), 25.1327, and 25.1547.

Page 21  T00021AT 
 
NOTE 16.  Production Basis: 
The Production Limitation Record (PLR) for Production Certificate 7SO was 
revised on July 20, 2018, to include the GVII-G500.  It was further revised on 
June 28, 2019 to include the GVII-G600.  Gulfstream is authorized to issue 
airworthiness certificates under the Organization Designation Authorization 
(ODA) Procedures of 14 CFR part 183, subpart D, and FAA Order 8100.15.  All 
Airplanes were produced under the Production Certificate. 
NOTE 17.  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 GVII-G500 aircraft may operate after May 8, 
2020 unless compliance is recorded with Gulfstream GVII-G500 Customer 
Bulletin number 001 – Equipment/Furnishings (ATA 25), Replacement - Life Raft 
Containing SRB406 ELT. 
NOTE 18.  Time-Limited Partial Exemption 17907: 
In accordance with the FAA Decision contained in Time-limited Exemption No. 
17907 for 14 CFR Section 25.1191(b)(1): Inlet and Thrust Reverser Fastener 
Cap Sealant: no GVII-G500 aircraft may operate after July 20, 2019 unless 
compliance is recorded with Gulfstream GVII-G500 Customer Bulletin number 
005 – Nacelles and Pylons (ATA 54), Inspection – Inlet Cowl Insulation Blanket 
Installation or the engineering inspection documented in Engineering Inspection 
Report GVII-GER-0713 has been completed. 
NOTE 19.  Time-Limited Partial Exemption 17965: 
In accordance with the FAA Decision contained in Time-limited Exemption No. 
17965 for 14 CFR Section 25.1309(b): Non-Rechargeable Lithium Battery 
Installations in Seat Airbag Systems, no GVII-G500 aircraft may operate after 
August 31, 2019 unless compliance is recorded with Gulfstream GVII-G500 
Customer Bulletin number 003, Equipment / Furnishings (ATA 25), Installation – 
Divan Airbag Restraint System Electronic Module Assembly Containment Bag.
```

## ADs (13, in force first)

- [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 2026-01-03](https://openairdocs.org/ad/2026-01-03): Main Landing Gear · Gulfstream Aerospace GVII-G500 and GVII-G600. Effective Feb 24, 2026
- [AD 2024-25-03](https://openairdocs.org/ad/2024-25-03): Fuel · Gulfstream Aerospace GVII-G500 and GVII-G600. Effective Feb 12, 2025
- [AD 2024-10-15](https://openairdocs.org/ad/2024-10-15): Powerplant · Gulfstream Aerospace GVII-G500 and GVII-G600. Effective Jun 7, 2024
- [AD 2024-05-04](https://openairdocs.org/ad/2024-05-04): Fuel Boost Pump · Gulfstream Aerospace GVII-G500 and GVII-G600. Effective May 2, 2024
- [AD 2023-14-08](https://openairdocs.org/ad/2023-14-08): Flight Controls · Gulfstream Aerospace GVII-G600. Effective Aug 24, 2023
- [AD 2023-11-09](https://openairdocs.org/ad/2023-11-09): Flight controls · Gulfstream Aerospace GVII-G500 and GVII-G600. Effective Jul 18, 2023
- [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 2022-10-05](https://openairdocs.org/ad/2022-10-05): Flight controls · Gulfstream Aerospace GVII-G500 and GVII-G600. Effective May 9, 2022
- [AD 2021-15-03](https://openairdocs.org/ad/2021-15-03): Trailing Edge Flaps · Gulfstream Aerospace GVII-G500. Effective Aug 26, 2021
- [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 2020-23-04](https://openairdocs.org/ad/2020-23-04) (historical): Fuel Boost Pump · Gulfstream Aerospace GVII-G500 and GVII-G600. Effective Nov 24, 2020
- [AD 2020-05-12](https://openairdocs.org/ad/2020-05-12) (historical): Flight controls · Gulfstream Aerospace GVII-G500 and GVII-G600. Effective Mar 13, 2020

## Registered aircraft by registry model (OpenAirDocs)

- [Gulfstream Aerospace GVII-G600](https://openairdocs.org/model/gulfstream-aerospace-gvii-g600): 226 aircraft (registry codes 3980219, 05637SM)
- [Gulfstream Aerospace GVII-G500](https://openairdocs.org/model/gulfstream-aerospace-gvii-g500): 223 aircraft (registry codes 3980225, 3980226)

## STCs approved under this data sheet (14)

- [STC ST04570AT](https://openairdocs.org/stc/ST04570AT): Installation of SpaceX Starlink Aviation System. Gulfstream Aerospace Corporation
- [STC ST04343AT-D](https://openairdocs.org/stc/ST04343AT-D): Installation of Air Ionization System. Gulfstream Aerospace Corporation
- [STC ST04347AT-D](https://openairdocs.org/stc/ST04347AT-D): Installation of Satcom Direct Plane Simple System. Gulfstream Aerospace Corporation
- [STC ST00105IB](https://openairdocs.org/stc/ST00105IB): Introduction of Activation of Wireless Charging Systems for Portable Electronic Devices. AMAC AEROSPACE SWITZERLAND AG
- [STC ST04346AT-D](https://openairdocs.org/stc/ST04346AT-D): Installation of Satcom Direct Router (SDR) Databus Wire Harness. Gulfstream Aerospace Corporation
- [STC ST04319AT-D](https://openairdocs.org/stc/ST04319AT-D): Installation of Satcom Direct Gateway (SDR-G) System. Gulfstream Aerospace Corporation
- [STC ST04310AT-D](https://openairdocs.org/stc/ST04310AT-D): Installation of an Airplane Interior. Gulfstream Aerospace Corporation
- [STC ST04324AT-D](https://openairdocs.org/stc/ST04324AT-D): Installation of an Airplane Interior. Gulfstream Aerospace Corporation
- [STC ST04325AT-D](https://openairdocs.org/stc/ST04325AT-D): Installation of Gogo AVANCE L5. Gulfstream Aerospace Corporation
- [STC ST04326AT-D](https://openairdocs.org/stc/ST04326AT-D): lnstallation of Ka-Band Jetwave High Speed Data (HSD) System. Gulfstream Aerospace Corporation
- [STC ST04312AT-D](https://openairdocs.org/stc/ST04312AT-D): Installation of a Ka Band JetWave System. Gulfstream Aerospace Corporation
- [STC ST04315AT-D](https://openairdocs.org/stc/ST04315AT-D): Installation of an Honeywell AIS-2000 Satellite TV System. Gulfstream Aerospace Corporation
- [STC ST04311AT-D](https://openairdocs.org/stc/ST04311AT-D): Installation of a Fin Cap Radome Replacement. Gulfstream Aerospace Corporation
- [STC ST04313AT-D](https://openairdocs.org/stc/ST04313AT-D): Installation of Gogo High Speed Data ATG-500 System. Gulfstream Aerospace Corporation

---
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