# TCDS 1A17: Gulfstream Aerospace Corporation

- Type: Type certificate data sheet
- Status: Current
- Holder: Gulfstream Aerospace Corporation
- Revision: 19
- Revised: April 15, 1987
- Product: Aircraft, Large Airplane
- Certification basis: Part 1, Part 25, CAR 4b
- Registered aircraft: 5, by the registry models matched to it (OpenAirDocs)
- Data sheet PDF: https://openairdocs.org/files/sha256/a7/c8/a7c85e597568aec0a45d55eca63c1077922b19b269cb60d8217900056544dbce
- FAA DRS: https://drs.faa.gov/browse/excelExternalWindow/A80C1B327A2B789D85256727006C25C1.0001
- Page: https://openairdocs.org/tcds/1A17

## Models (1)

As the data sheet lists them.

- G-159 (Gulfstream I; Grumman G-I)

## 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
Rev No. 19 18 18 15 15 18 18
Reformatted 5/94.
DEPARTMENT OF TRANSPORTATION
FEDERAL AVIATION ADMINISTRATION
1A17
Revision 19
Gulfstream
G-159
April 15, 1987
TYPE CERTIFICATE DATA SHEET NO. 1A17
This data sheet, which is a part of Type Certificate No. 1A17, 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
P.O. Box 2206
Savannah, GA  31402-2206
I - Model G-159, Gulfstream I, (Transport Category), Approved May 21, 1959
Engines 2 Rolls-Royce Dart Mark 529-8E, Mark 529-8H, Mark 529-8X, Mark M529-8X
(Mod 1814), Mark 529-8Y, or Mark M529-8Z.  (Turboprop)  (See Note 6 for required
modifications and procedures for Engines Mark 529-8X (Mod 1814), Mark 529-8Y
and Mark 529-8Z).  Reduction Gearing 0.093.1.
Fuels (fuels shall conform to Kerosene Type U.S. : ASTM D.1655-74
the specifications as listed) Jet A and A-1
MIL-T-5624-J
Grade JP-5
British : D. Eng. R.D. 2498
Issue 6
D. Eng. R.D. 2494
Issue 7
Amendment 1
D. Eng. R.D. 2453
Issue 3
Amendment 1
Canadian : 3-GP-23h
3-GP-24g
Wide-Cut Fuels U.S. : ASTM D.1655-74
Jet B
MIL-T-5624-J
Grade JP-4
British : D. Eng. R.D. 2486
  Issue 8
  Amendment 1
D. Eng. R.D. 2454
  Issue 3
  Amendment 1
Canadian: 3-GP-22h

1A17 Page 2
Fuel Specification D. Eng. R.D. 2453 and D. Eng. R.D. 2454 already include
HITEC-E515 (formerly Santolene C) and anti-icing additive to Specification
E. Eng. R.D. 2451 (Issue 2, or later issue) to approved limitations.
Approved deviations
Fuels with the following deviations from Specification D. Eng. R.D. 2494 are
acceptable:
Flash point: Minimum 28 deg. C.
(82.4 deg. F.)
Mercaptan Maximum 0.005 per cent
sulphur content: by weight
Mixing of fuels
Any mixture of the above type fuels may be used without readjustment of the
engine fuel control unit and without loss in engine power or aircraft performance.
Wide-Cut Fuel
The use of wide-cut fuel, as agreed to by the Operator, Rolls-Royce and
appropriate Airworthiness Authority may result in a reduction in H.P. fuel
pump life.
Fuel conforming to emergency fuel specification ES-2-74 may be used on an
exception basis.
Refer to Airplane Flight Manual for approved fuel additives.
Water/Methanol Refer to Rolls-Royce Specification
Mixture: AEP-1-W/M, latest issue.
Oil (engine, gearbox and APU) ESSO/EXXON Extra Turbo Oil 274
CASTROL 98
CASTROL UK 98
CASTROL 98 Gas Turbine Oil
AEROSHELL Turbine Oil 750
TEXACO Synthetic Aircraft Turbine Oil 35 (T.S.A.T.O. 35)
    Also marketed as CALTEX Synthetic Turbo Oil 35
And those oils as approved for common usage in the engine, propeller and
gearbox by Rolls Royce, Dowty Rotol, and the Civil Aviation Authority (U.K.)
in DART OPERATING INSTRUCTIONS (F-DA-7-G), Rolls Royce Service
Bulletins and Dowty Rotol Maintenance Manuals No. 865/1 and 865A/1 for
G-159 aircraft and for use in APU Model No. GTC 85-37-2 in AiResearch
Maintenance Manual 6A-243.
Engine Limits
Static Sea Level Ratings MK.529
-8E & 8H -8X, -8Y, -8Z
Wet Takeoff (5 min.)
  Shaft Horsepower (Shp.) 1950 1990
  Jet Thrust (Lb.)   510   520
Dry Takeoff (Unrestricted)
  Shaft Horsepower (Shp.) 1910 1910
  Jet Thrust (Lb.)   500   500
Max. Continuous (Unrestricted)
  Shaft Horsepower (Shp.) 1910 1910
  Jet Thrust (Lb.)   500   500

Page 3 1A17
Engine Limits (cont'd) Engine Speed Max. Permissible
(R.P.M.) Turbine Gas Temp.
(GT) °C
Mk. 529-8E, -8H, -8X, -8Y, -8Z
Wet Takeoff (5 min.) 15,000   860
Dry Takeoff (5 min.) 15,000   825
Max. Continuous 15,000   850 (-8E, -8H, -8X)
  (Unrestricted)
For airplanes incorporating ASC 246;
Max. continuous TGT at 15,000 RPM:
-8X Engines = 870°C
-8Y Engines = 910°C
-8Z Engines = 920°C
Starting Momentary   930
At low altitude at temperature below ISA, the engines may produce more power at
takeoff than the airplane has been certified for.  Under these conditions, the placarded
torquemeter limitations should not be exceeded.
Oil Inlet Temperature:
Maximum +120°C
Minimum for Starting -30°C
Minimum for Opening Power Lever -15°C
Propeller and 2 Rotol Model (C) R 184/4-30-4/50, with 4 R.A. 25907 blades each.
  Propeller Limits Diameter:  11.5 feet (nominal)
  Minimum allowable for repairs 11' 4".  No further reduction permitted.
Pitch setting at .7 radius:
  Ground fine pitch 0
  Flight fine pitch +20°
  Cruise pitch +34° 30'
  Feathered +85° 30'
Maximum governing e. r.p.m. 15,000
Minimum governing e. r.p.m. 11,000
E. r.p.m. limit (max. 20 sec.) 17,000
See NOTE 2(b) for idling e. r.p.m. limitations.
Airspeed Limits (IAS) Vmo (max. operating) 290 knots (334 m.p.h.)
  12,000 ft. and below
Mmo M = .54 above 12,000 ft. is indicated
  by red & white limit on airspeed indicator.
 Va (maneuvering) 174 knots (200 m.p.h.)
Vfe (flaps down 12.5°) 219 knots (252 m.p.h.)
Vfe (flaps down 20°) 162 knots (187 m.p.h.)
Vfe (flaps down 33°) 143 knots (165 m.p.h.)
Vlo (landing gear operation) 193 knots (222 m.p.h.)
Vle (landing gear extended) 193 knots (222 m.p.h.)
Vmc (minimum control one engine inoperative)
     Feathered 101 knots (116 m.p.h.) Gear up.
T.O. flaps
     Feathered 113 knots (130 m.p.h.) Clean
     Windmilling 127 knots (146 m.p.h.) Gear up.
T.O. flaps
     Windmilling 138 knots (159 m.p.h.) Clean
V11 (Landing light extension and
  operation) 290 knots (334 m.p.h.)
Vdb Dive brake extension 310 knots (357 m.p.h.)
        Dive brake retraction 199 knots (229 m.p.h.)
C.G. Range
%MAC Sta. %MAC Sta.

1A17 Page 4
Takeoff & Landing
(landing gear and flaps down)
20,000 lbs. 14.3 298.0 28.2 311.8
23,700 lbs. 14.3 298.0 - - -
26,100 lbs. 30.4 313.9
33,600 lbs. 20.8 304.4 31.9 315.5
34,285 lbs. 21.2 304.8 32.0 315.6
35,100 lbs. 21.8 305.4 32.2 315.8
36,000 lbs. 22.3 306.0 32.3 315.9
Linear variation of limits between points shown.  Landing gear retraction moment
is -30,000 in.-lb.  Flap retraction moment is -6,600 in.-lb.
Datum Station 0 is 8 in. forward of the nose, or 45 in. forward of the jig point at the
centerline of the airplane in the nose wheel well.
M.A.C. 99.4 in.  (L.E. of M.A.C. +283.8)
Leveling Means Longitudinal: Lugs at left nose wheel door longeron, Sta. 61.5 and 72.5.
Lateral: Lugs on rear face of Bulkhead Sta. 44.5 in nose wheel well.
Maximum Weight Takeoff
33,600 lb. on aircraft S/N 1 through S/N 60 including S/N 114.
35,100 lb. on aircraft S/N 61 through S/N 162 (excluding aircraft S/N 114),
S/N 322 and 323 on aircraft S/N 1 thru 60 and S/N 114 when modified in
accordance with Grumman Service Change No. 69.
36,000 lb. on aircraft S/N 163 through S/N 200 and on aircraft S/N 1 through 162,
S/N 322 and 323, when modified in accordance with Grumman Service
Change Nos. 69 and 175.
Landing
32,000 lb. on aircraft S/N 1 through S/N 60 including S/N 114.
33,600 lb. on aircraft S/N 61 through S/N 162, (excluding aircraft S/N 114),
S/N 322 and 323, and on aircraft S/N 1 through 60 and S/N 114 when
modified in accordance with Grumman Service Change No. 69.
34,285 lb. on aircraft S/N 163 through S/N 200 and on aircraft S/N 1 through
162, S/N 322 and 323, when modified in accordance with Grumman
Service Change Nos. 69 and 175.
Zero usable fuel, oil and water/methanol (aircraft with outer wing panel fuel tank
installation must include usable W/M).
29,707 lb. when takeoff weight is not more than 35,100 lbs.
27,303 lb. when takeoff weight is 36,000 lb. with linear variation between
gross weights of 35,100 lb. and 36,000 lb.
Minimum Crew 2 - Pilot and Copilot
Maximum Number of Occupants The total number of occupants shall not exceed 23.  The total number of passengers
shall not exceed 19 as determined by emergency exit requirements.  When Aircraft
Service Change 153A is incorporated the total number of occupants shall not
exceed 28.  The total number of passengers shall not exceed 24 as determined by
emergency exit requirements.  (See Review Case Number 6.)

Page 5 1A17
Maximum Baggage
Compartment
Forward Aft Aft-Shelved
Station Boundary 133-193 525-571 525-586 525-586
Capacity (lb.) 400 736 1700* 800*
Max. Floor Loading   50   64     64   64
  (#/sq. ft.)
Shelf Loading None None Variable Variable
C.G. 163.0 543.0 Variable Variable
*1700 lb. is the capacity at a Zero usable fuel, oil and W/M weight of 26,103 lb.  This
decreases linearly to 800 lb. at a Zero usable fuel, oil and W/M weight of 29,707 lbs.
Fuel Capacity 1550 gal. total usable fuel in 2 wing tanks of 775 gal. each (F.S. 321).
For aircraft with outer wing panel fuel tank installation, 1793.6 gal. total usable
  fuel (left tank 893.9 gallon, right tank 899.7 gallon)  (F.S. 321).
See NOTE 1(b) for system fuel.
Water/Methanol Aircraft S/N 1 through 106 and 114 - 84 gal.
Total usable in two parts of wing bladder tanks of 42 gallons each pair (F.S. 321).
For aircraft with outer wing panel fuel tank installation (Gulfstream Aircraft
service Change No. 125), the total usable water/methanol is 47.4 gal. in two wing
fillet tanks of 23.7 gal. each (F.S. 384.1).
For aircraft S/N 107 and subsequent and airplanes incorporating Gulfstream Airport
Service Change No. 165, the total usable water/methanol is 46 gal. in two wing
bladder tanks of 23 gal. each (F.S. 321).
See NOTE 1(b) for system W/M.
Oil Capacity 8.4 gal. total "Usable" 67.2 lb. located in integral engine tanks of 4.2 gal. each
(F.S. 200.5).  See NOTE 1(c) for system oil.
Maximum Operating Altitude 30,000 ft. with APU or ASC 126 installed
25,000 ft. with Auxiliary Power Unit inoperative or not installed.
Control Surface Movements Elevator Up 25° + 1/2° -1½° Down 14° + 0° -2°
Elevator trim tab Up   3° ±  ½° Down 20° ± 2°*
Up   2° ± ½° Down 20° ± 2°**
Rudder Right 22° + 0° -1° Left 22° + C° -1°
Rudder tab Right 10° ± 1° Left 10° ± 1°
  (spring or trim)
Aileron Up 16° ± 1° Down 12° ± 1°
Aileron tab (trim) Up 20° ± 2° Down 20° ± 2°
Aileron tab (spring) Up 15° ± 1 Down 15° ± 1°
Flaps Down 33° ± 1°
*For S/N 26 and subsequent excluding aircraft S/N 114.
**For S/N 1 through 25 and S/N 114.
Serial Nos. Eligible 1 and up.

1A17 Page 6
Certification Basis CAR 4b dated December 31, 1953, including Amendments 4b-1 to 4b-5 inclusive,
Amendment 4b-6 Items 7, 8, 12, 16, 17, 19, 22, 23, 24, 25, 26, 28, 31, 32, 34, 35, 38,
39, 42 and 44, 4b-7 all Items, 4b-8 Items 2, 5, 6, 12, 17, 20, 21, 22, and 23, Special
Regulation SR 422A, and Special Conditions in Attachment A of CAA letter to
Grumman dated December 2, 1957, and exemption No. 689, CAR 4b.437, "Fuel
Jettisoning System."  Type Certificate 1A17 issued May 21, 1959.  Date of
Application for Type Certificate May 14, 1957.  FAR 25.771, Amendment 4.  A
lockable door is not required between the pilot and passenger compartments.
Compliance with the following optional requirements has been established:
Ice Protection CAR 4b.640.
Data covering ditching requirements of 4b.361 including 4b.362(d) and 4b.742(e)
(but excluding 4b.645 and 4b.646) are approved.  When the operating rules
require emergency ditching equipment, compliance with 4b.645 and 4b.646 must
be demonstrated.  Grumman Report 1159-GER-7, revised July 25, 1977, entitled
"Outfitting Requirements for FAA Certification for Ditching," provides an
acceptable means for showing compliance with 4b.645 and 4b.646.  Airplane Flight
Manual Interim Revision 22.3, or later FAA approved revision must be incorporated.
Production Basis None.  Prior to original certification of aircraft manufactured subsequent to serial
numbers 1 through 12, 14 through 112, 114 through 200, plus 322 and 323, an FAA
representative must perform a detailed inspection for workmanship, materials and
conformity with the approved data, and a check of the flight characteristics (see
NOTE 5.)
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:
a. FAA approved Airplane Flight Manual, dated May 21, 1959.  Reissued July 1, 1960.
b. Crew oxygen system installation.  When an aircraft is outfitted to carry passengers,
an FAA approved passenger oxygen system must be installed.
Service Information Service bulletins and other service information, when FAA approved, will carry a
statement to that effect.  See NOTE 4 regarding Grumman Gulfstream Service Change
Number 147.
NOTE 1. (a) Current weight and balance report, including 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.
(b) System or unusable fuel, which must be included in the empty weight, is the amount of fuel required to fill
the system plumbing and tank to the undrainable level (2.4 gal. total), plus unavailable fuel in the fuel tanks
(8.3 gal. total).  The total amount of "system fuel" 10.7 gal. total, 72 lb. (325).  System or unusable and
undrainable water/methanol are in identical quantity (3.4 gal. or 27 lb. total) and also must be included in
the empty weight (325).  For aircraft with outer wing panel fuel tank installation (Service Change No. 125),
system water/methanol equals 1.8 gal. or 14 lb. total (346).
(c) System oil, which must be included in empty weight, is the amount of oil necessary for engine lubrication
and propeller operation.  The total amount of "system oil" is as follows:  5.7 gal. (total) contained in engines,
45.8 lb. (200.5).
NOTE 2. The following placards must be displayed in the locations indicated:
(a) On the forward side of the passenger compartment forward door:  (if installed)
"This door must be OPEN during take-off and landing."

Page 7 1A17
(b) On the instrument panel below r.p.m. indicators:
"Avoid all continuous operation below 7000 RPM."
(c) On aircraft serial numbers 3 and 114 adjacent to each swivel seat:
"This seat must be forward facing during take-off and landing."
(d) On aircraft serial numbers 2, 3, and 114 on the back rest of the jump seat:
"Not to be used during take-off and landing."
(e) On the forward side of the passenger compartment rear door:  (This placard is required for 24 passenger
aircraft and recommended for others.)
"This door must be OPEN during take-off and landing."
NOTE 3. Retirement Times:
The retirement times of fatigue critical life limited components are listed in Section IV, Part 1 of the Gulfstream
Aerospace Model 159 (Gulfstream I) Inspection Schedule Manual.  The retirement times of these life limited
components cannot be increased/changed without FAA Engineering approval.
NOTE 4. Grumman Gulfstream Service Change No. 147 regarding large cargo door may be incorporated when the
structural inspections specified in Service Change No. 147 are complied with.  Grumman Flight Manual
Supplement dated 31 August 1962 is also required for this modification.
NOTE 5. Spare parts and aircraft may be manufactured at Grumman, Bethpage, Long Island, New York, facility under
their production Certificate No. 23.  Spare parts may be manufactured at Gulfstream Aerospace Corporation,
Savannah, Georgia, under Production Certificate No. 507.
NOTE 6. When Aircraft Service Change No. 246, "Nacelle Modification to Operate Dart Mark 529-8X, -8Y, and -8Z
engines at Higher Maximum Continuous Power Settings" is installed, one of the following Airplane Flight
Manual (AFM) Supplements is required.
Engine Supplement No.
-529-8X G1-82-002
-529-8Y G1-82-003
-529-8Z G1-82-004
The higher maximum continuous power settings below can be used where maximum continuous power setting
follows use of wet takeoff power.
*Engine Rolls Royce Mod RPM TGT (°C) Time Limit
-529-8X 1814 15,000 870 Unrestricted
-529-8Y 1806 15,000 910 Unrestricted
-529-8Z 1810 15,000 920 Unrestricted
*These engines must incorporate listed Rolls Royce modifications in order to use above higher maximum
continuous power settings.
...END...
```

## ADs (34, 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 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 2006-25-02](https://openairdocs.org/ad/2006-25-02): Structural assemblies · Gulfstream Aerospace G-159. Effective Jan 11, 2007
- [AD 2001-18-05](https://openairdocs.org/ad/2001-18-05): Flight Eagle Tires · Boeing 720 Series, 720B Series, 111 and 6 more. Effective Sep 24, 2001
- [AD 2000-10-11](https://openairdocs.org/ad/2000-10-11): Pneumatic Deicing Boots · Gulfstream Aerospace G-159. Effective Jun 26, 2000
- [AD 98-13-30](https://openairdocs.org/ad/98-13-30): AFM - Limitations Section - Power Levers · Gulfstream Aerospace G-159. Effective Jul 29, 1998
- [AD 98-04-36](https://openairdocs.org/ad/98-04-36): AFM - Limitations Section - Icing · Gulfstream Aerospace G-159. Effective Mar 25, 1998
- [AD 97-16-05](https://openairdocs.org/ad/97-16-05): Wing Center Section Skin · Gulfstream Aerospace G-159. Effective Sep 5, 1997
- [AD 97-14-13](https://openairdocs.org/ad/97-14-13): Engine Mount Tube And Upper Diagonal Truss · Gulfstream Aerospace G-159. Effective Aug 15, 1997
- [AD 97-14-08](https://openairdocs.org/ad/97-14-08): MLG Uplock Beam Bracket · Gulfstream Aerospace G-159. Effective Aug 7, 1997
- [AD 97-14-09](https://openairdocs.org/ad/97-14-09): Elevator Trim Tab Actuators Mounting Lugs · Gulfstream Aerospace G-159. Effective Aug 7, 1997
- [AD 97-14-10](https://openairdocs.org/ad/97-14-10): Main Landing Gear Fittings · Gulfstream Aerospace G-159. Effective Aug 7, 1997
- [AD 96-25-12](https://openairdocs.org/ad/96-25-12): Auxiliary Power Units · BAE Systems HS 748 Series 2A, HS 748 Series 2B, 707-100 Long Body and 74 more. Effective Jan 13, 1997
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- [AD 95-22-01](https://openairdocs.org/ad/95-22-01): Fluorescent Lighting System · Aerospace Lighting Fluorescent lighting systems, A310-203, A310-204 and 74 more. Effective Dec 4, 1995
- [AD 94-01-05](https://openairdocs.org/ad/94-01-05): Traffic Alert and Collision Avoidance System II Processors · Airbus A340-211, A340-212, A340-213 and 85 more. Effective Feb 4, 1994
- [AD 87-05-51](https://openairdocs.org/ad/87-05-51): Floor Proximity Lighting · Boeing 707-100 Long Body, 707-100B Long Body, 707-100B Short Body and 48 more. Effective May 18, 1987
- [AD 84-20-08](https://openairdocs.org/ad/84-20-08): Forward/AFT Eng. Mount Assys. · Gulfstream Aerospace G-159. Effective Jan 22, 1985
- [AD 81-04-02](https://openairdocs.org/ad/81-04-02): Incorporation Of AFM Revisions · Gulfstream Aerospace G-159. Effective Feb 12, 1981
- [AD 79-06-03](https://openairdocs.org/ad/79-06-03): Electrical Shunts · Gulfstream Aerospace G-1159 and G-159. Effective Apr 2, 1979
- [AD 77-13-01](https://openairdocs.org/ad/77-13-01): Jumpseat · Gulfstream Aerospace G-1159 and G-159. Effective Apr 21, 1978
- [AD 74-23-08](https://openairdocs.org/ad/74-23-08): Fire Extinguishers · Gulfstream Aerospace G-159. Effective Nov 15, 1974
- [AD 73-14-07](https://openairdocs.org/ad/73-14-07): Interior Lining Attachments · Gulfstream Aerospace G-1159 and G-159. Effective Sep 30, 1974
- [AD 72-07-08](https://openairdocs.org/ad/72-07-08): Main Landing Gear Drag Brace · Gulfstream Aerospace G-159. Effective Mar 30, 1972
- [AD 71-23-02](https://openairdocs.org/ad/71-23-02): Attachment Fittings · Gulfstream Aerospace G-159. Effective Nov 26, 1971
- [AD 67-02-04](https://openairdocs.org/ad/67-02-04): Accessory Gear Boxes · British Aerospace Argosy AW.650 Series 101, Accessory Gear boxes, G-159 and 1 more. Effective Jun 23, 1970
- [AD 69-20-03](https://openairdocs.org/ad/69-20-03): Fuel Temperature Indicator · Gulfstream Aerospace G-159. Effective Jan 23, 1970
- [AD 69-21-02](https://openairdocs.org/ad/69-21-02): Cabin Superchargers · British Aerospace Argosy AW.650 Series 101, F27 Mark 100, F27 Mark 300 and 18 more. Effective Oct 9, 1969
- [AD 68-23-01](https://openairdocs.org/ad/68-23-01): Cabin Superchargers · British Aerospace Argosy AW.650 Series 101, F27 Mark 100, F27 Mark 300 and 18 more. Effective Nov 21, 1968
- [AD 67-33-04](https://openairdocs.org/ad/67-33-04): Aileron Control Idler · Gulfstream Aerospace G-159. Effective Dec 30, 1967
- [AD 65-13-04](https://openairdocs.org/ad/65-13-04): Nose Gear Strut Assembly · Gulfstream Aerospace G-159. Effective Jun 12, 1965
- [AD 65-09-03](https://openairdocs.org/ad/65-09-03): APU Turbine Wheel · Gulfstream Aerospace G-159. Effective Apr 21, 1965
- [AD 62-26-02](https://openairdocs.org/ad/62-26-02): Integral Tanks · Gulfstream Aerospace G-159. Effective Dec 6, 1962
- [AD 74-08-09 R2](https://openairdocs.org/ad/74-08-09-R2) (historical): Waste Receptacles · Aero Spacelines 377, 377MG, 377SGT and 268 more. Effective Jul 29, 1996

## Registered aircraft by registry model (OpenAirDocs)

- [Grumman G-159](https://openairdocs.org/model/grumman-g-159): 4 aircraft (registry code 3952202)
- [Grumman American Avn. G-159](https://openairdocs.org/model/grumman-american-avn-g-159): 1 aircraft (registry code 3960301)
- [Gulfstream Aerospace G-159](https://openairdocs.org/model/gulfstream-aerospace-g-159): 0 aircraft (registry code 3980201)

## STCs approved under this data sheet (259, first 50)

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- [STC ST238CH](https://openairdocs.org/stc/ST238CH): Installation of BFGoodrich TCAS I.. Acron Aviation Inc.
- [STC ST01930LA](https://openairdocs.org/stc/ST01930LA): Installation of Sandel Avionics SN4500 Electronic Horizontal Situation Indicator (EHSI). Sandel Avionics LLC
- [STC SA2-931](https://openairdocs.org/stc/SA2-931): Installation of Sperry SP-40 Gyropilot.. Honeywell International Inc
- [STC SA1732GL](https://openairdocs.org/stc/SA1732GL): Install air ambulance conversion.. Spectrum Aeromed LLC dba Spectrum Aeromed
- [STC SA571SW](https://openairdocs.org/stc/SA571SW): Installation of Collins radio altimeter system.. Associated Air Center, Inc. - c/o CT Corporation System
- [STC ST00425WI](https://openairdocs.org/stc/ST00425WI): Installation of Keddeg Company P/N 21BC120 Coalescer Assembly  as a replacement for P/N 83237-14 on Gulfstream G-159 Airplanes. Purolator Facet, Inc
- [STC ST02628LA](https://openairdocs.org/stc/ST02628LA): Installation of Honeywell CAS-67A Traffic Alert Collision Avoidance System (TCAS II) with Dual Honeywell MST-67A Transponder System and removal of L-3 TRC-497 Skywatch TCAS system. Battelle Memorial Institute, Pacific Northwest Division
- [STC SA1536SW](https://openairdocs.org/stc/SA1536SW): Installation of Foxtronics TRAMM BTI-600 nickel cadmium battery temperature system and an optional generator voltage control system. FoxCart GSE, LLC
- [STC SA2016NM](https://openairdocs.org/stc/SA2016NM): Installation of a de-icing system on the Rolls Royce P/N RK29954A engine inlet cowl. ROBERT W. MURRAY
- [STC SA302WE](https://openairdocs.org/stc/SA302WE): Incorporate a de-icing system (as manufactured by applicant) externally on Rotol propeller spinner as an alternate to Dowty Rotol internal elements. If applied to original spinner, Montgomery Systems Tech., Inc. P/N 72196-2 will apply. If applied to a new aluminum nose spinner P/N 72196-1 will apply. Dowty Rotol Service Bulletin Section 61-170 pages 1 and 2 outlines a revised spinner de-icing system. This is a Napier external system. Approval of the A.R.B. is indicated. (Continued on page 3). ROBERT W. MURRAY
- [STC SA122CE](https://openairdocs.org/stc/SA122CE): Install Hoskins supplementary light system consisting of colored Model A(or clear or colored Model E) wing tip lights, a Model C or 2 tail light, and optionally, two of Model 2 fuselage lights with M-3 or M-5 power supply.. BF Goodrich Aerospace
- [STC SA3687SW](https://openairdocs.org/stc/SA3687SW): :  Installation of Floor Proximity Lighting System in accordance with Vista Manufacturing, Inc., Drawing List G1-1000, Revision C, Dated December 02, 1986 or later FAA approved revision. BF Goodrich Aerospace
- [STC ST00682WI-D](https://openairdocs.org/stc/ST00682WI-D): Modification of Collins VHF-20/VHF-20A/VHF-20B VHF COMM Receiver Transmitter with CTL-20 Control Pro Line I System Installation to a Collins VHF-22C/VHF-22D VHF COMM Receiver Transmitter with CTL-22C Control 8.33 kHz Pro Line II System Installation in accordance with Collins Installation Instructions as listed on AML No. ST00682WI-D, Revision -, or later FAA approved revisions.. Rockwell Collins Inc
- [STC SA00068SE](https://openairdocs.org/stc/SA00068SE): Installation of fuel flow/pressure instruments. (W/TSIO-360-MB1). Electronics International Inc.
- [STC SA2693NM](https://openairdocs.org/stc/SA2693NM): Installation of Electronics International digital volt/amp gauges and accessories.. Electronics International Inc.
- [STC ST02540AT-D](https://openairdocs.org/stc/ST02540AT-D): Installation of replacement fuel tank sealant system. FFC Manufacturing
- [STC SA1681GL](https://openairdocs.org/stc/SA1681GL): Installation of Chrysler Pentastar Aviation auxiliary generator adapter assembly.. Phoenix Air Group Inc
- [STC SA1699GL](https://openairdocs.org/stc/SA1699GL): Installation of electrical system.. Phoenix Air Group Inc
- [STC SA1610SO](https://openairdocs.org/stc/SA1610SO): Installation of a composite custom executive interior.. Page AvJet Corp
- [STC SA1612SO](https://openairdocs.org/stc/SA1612SO): Installation of the Collins FCS-80 flight control system.. Page AvJet Corp
- [STC SA1704SO](https://openairdocs.org/stc/SA1704SO): Installation of a single Global GNS-500A series 3B VLF/Omega Navigation System.. Page AvJet Corp
- [STC SA2072SO](https://openairdocs.org/stc/SA2072SO): Installation of 24-passenger interior.. Page AvJet Corp
- [STC SA2079SO](https://openairdocs.org/stc/SA2079SO): Installation of emergency lighting system.. Page AvJet Corp
- [STC SA2080SO](https://openairdocs.org/stc/SA2080SO): Installation of a Fairchild A100A cockpit voice recorder.. Page AvJet Corp
- [STC SA3154SO](https://openairdocs.org/stc/SA3154SO): Installation of an interior.. Page AvJet Corp
- [STC ST01483WI-D](https://openairdocs.org/stc/ST01483WI-D): Installation of Cabin Re-configuration.. Duncan Aviation Inc
- [STC SA888EA](https://openairdocs.org/stc/SA888EA): Installation of Grimes three light strobe kit 34-0303-1 as supplemental lighting.. Honeywell International Inc.
- [STC ST00844WI-D](https://openairdocs.org/stc/ST00844WI-D): Modification of Collins TCAS II or TCAS-94 (TCAS II) system installation with Collins TTR-920 Change 7.0 Receiver Transmitter to a Collins TCAS II or TCAS-94 OTCAS II) system installation with Collins TTR-921 or Collins TTR-4000 Change 7.0 TCAS Receiver Transmitter.. Rockwell Collins Inc
- [STC ST03055AT](https://openairdocs.org/stc/ST03055AT): Installation of either a Single or Dual Sandel Model 3400 TAWS 
with RMI System.. Phoenix Air Group Inc
- [STC SA00680SE](https://openairdocs.org/stc/SA00680SE): Installation of Electronics International model UBG-16 or UBG-16T bar graph engine analyzer.. Electronics International
- [STC SA2893SW](https://openairdocs.org/stc/SA2893SW): Installation of one, two, or three- place side facing seat attached to seat tracks.. Aviation Fabricators Inc
- [STC ST00743NY-D](https://openairdocs.org/stc/ST00743NY-D): Installation of AlliedSignal GTCP36-150J Auxillary Power Unit.. Phoenix Air Group Inc
- [STC SA1181EA](https://openairdocs.org/stc/SA1181EA): Installation of Garrett AiResearch GTCP36-100(H) APU.. PATS Aircraft LLC
- [STC SA1204EA](https://openairdocs.org/stc/SA1204EA): Installation of Solar T-62T-40C2 APU.. PATS Aircraft LLC
- [STC SA1222EA](https://openairdocs.org/stc/SA1222EA): Replacement of bleed-air driven fan with electrically powered fan.. PATS Aircraft LLC
- [STC SA3304NM](https://openairdocs.org/stc/SA3304NM): Installation of monorail sun visor system in accordance with FAA approved Rosen Product Development, Inc., Drawing List RG-I-II-00DL, Revision N/C, or later FAA approved revision.. Rosen Sunvisor Systems LLC
- [STC ST01676CH](https://openairdocs.org/stc/ST01676CH): Installation of a Honeywell/AlliedSignal CAS-81 TCAS II Traffic Alert and Collision Avoidance System.. Flight Systems Engineering, Inc
- [STC ST01605CH](https://openairdocs.org/stc/ST01605CH): Installation of an Allied Signal CAS-67A TCAS II Traffic Alert and Collision Avoidance System in accordance with Pro-Tech Avionics Corporation Master Drawing List Document No. 81-328L001, Revision E, dated December 6, 2001, or later FAA approved revision.. Phoenix Air Group Inc
- [STC SA1373GL](https://openairdocs.org/stc/SA1373GL): Installation of Norton Radome Kit No. 4772W.. Saint-Gobain Performance Plastics Corp
- [STC SA2687NM](https://openairdocs.org/stc/SA2687NM): Installation of Truboplus/ Electronics Int'l gauges and switches.. Aero Manufacturing Inc.
- [STC SA2-1020](https://openairdocs.org/stc/SA2-1020): Interior arrangement in the cabin from Station 133 to 525.. Signature Flight Support Corporation
- [STC SA2-910](https://openairdocs.org/stc/SA2-910): Installation of electronic and interior equipment.. Signature Flight Support Corporation
- [STC SA2899SW](https://openairdocs.org/stc/SA2899SW): Installation of hostess jump seat and table.. Signature Flight Support Corporation
- [STC SA2900SW](https://openairdocs.org/stc/SA2900SW): Installation of toilet and outside toilet service.. Signature Flight Support Corporation
- [STC SA1202SW](https://openairdocs.org/stc/SA1202SW): Modification to aircraft electrical power system.. Rockwell Collins Inc
- [STC SA1514SW](https://openairdocs.org/stc/SA1514SW): Installation of following dual Collins equipment: 618M-2D VHF transceivers, 51RV-2B VHF NAV receivers, 621A-3 transponders; installation of the following single equipment:  Collins 346D-1B Paging Amplifier, Collins DN101/NC103 Doppler, Collins 860F-1 DME; IDC 519-227022 Encoding Alimeter; IDC 22719-101 Vertical Speed Indicator, and Dayton Aircraft Products EB-28CD Emergency Locator Transmitter. Rockwell Collins Inc
- [STC SA1745SW](https://openairdocs.org/stc/SA1745SW): Installation of ANS-70A Area Navigation System.. Rockwell Collins Inc
- [STC SA1852SW](https://openairdocs.org/stc/SA1852SW): Installation of dual FD-109 flight director/AP-105 autopilot, 54W-1C comparator, dual ALT-50 radio altimeter, dual MC-103 compasses, dual ILS-70/Bendix RVA33A VOR/ILS, 51Z-4 marker, dual 860E-3 DME, dual DF-203 ADF, 621A-6 transponder, 621A-3 transponder, dual 346B-3 audio system, AVQ-10 radar, and IDC air data system.. Rockwell Collins Inc
- [STC SA815SW](https://openairdocs.org/stc/SA815SW): Installation of Collins VOR antenna type 837B-1 on vertical fin.. Rockwell Collins Inc

All 259: https://openairdocs.org/tcds/1A17/stcs.md

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