# TCDS A57EU: GROB Aircraft SE

- Type: Type certificate data sheet
- Status: Current
- Holder: GROB Aircraft SE
- Revision: 16
- Revised: July 19, 2021
- Product: Aircraft, Small Airplane
- Certification basis: Part 23, Part 21
- Registered aircraft: 5, by the registry models matched to it (OpenAirDocs)
- Data sheet PDF: https://openairdocs.org/files/sha256/fb/4c/fb4c28c983b3535eeabce30cb412ac663302e58bb595eb59c3060b100d014b91
- FAA DRS: https://drs.faa.gov/browse/excelExternalWindow/17DC41689360CABB86258719005B532D.0001
- Page: https://openairdocs.org/tcds/A57EU

## Models (8)

As the data sheet lists them.

- G115A
- G115C
- G115D
- G115B
- G115D2
- G115
- G115C2
- G115EG

## 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. 16 10 10 10 16 15 15 
 
DEPARTMENT OF TRANSPORTATION 
FEDERAL AVIATION ADMINISTRATION 
 
A57EU 
Revision 16 
GROB Aircraft SE 
G 115 
G 115A 
G 115B 
G 115C 
G 115C2 
G 115D 
G 115D2 
G 115EG 
July 19, 2021       
 
TYPE CERTIFICATE DATA SHEET NO. A57EU 
 
This Data Sheet which is a part of Type Certificate No. A57EU 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: GROB Aircraft SE 
Lettenbachstrasse 9 
86874 Tussenhausen-Mattsies 
Germany 
 
Type Certificate Ownership Record: Grob Werke GmbH & Co. KG Unternehmensbereich Burkhart Grob Fleugzeugbau 
transferred TC A57EU to BURKHART GROB Luft- und Raumfahrt GmbH & Co. 
KG on November, 1989. 
 
BURKHART GROB Luft- und Raumfahrt GmbH & Co. KG transferred TC A57EU 
to GROB Aerospace GmbH on December, 2006. 
 
GROB Aerospace GmbH transferred TC A57EU to GROB Aerospace GmbH i.l. on 
August, 2008. 
 
GROB Aerospace GmbH i.l. transferred TC A57EU to GROB Aircraft AG on 
February, 2009. 
 
GROB Aircraft AG transferred TC A57EU to GROB Aircraft SE on September 01, 
2017. 
 
 
I. Model G 115 (Normal and Utility Category), approved December 21, 1988. 
 Model G 115A (Normal and Utility Category), approved December 06, 1990. 
 Model G 115B (Normal and Utility Category), approved July 19, 1993. 
 Model G 115C (Utility Category), approved August 13, 1993. 
 Model G 115C (Utility and Acrobatic Category), approved February 8, 1996. 
 Model G 115C2 (Utility Category), approved September 14, 1994 
 Model G 115D (Utility and Acrobatic Category), approved October 28, 1993 
 Model G 115D2 (Utility and Acrobatic Category), approved September 14, 1994 
 Model G 115EG (Acrobatic Category), approved February 6, 2001 
 
Engine Avco Lycoming O-235-H2C (G 115 and G 115A) 
Avco Lycoming O-320-D1A or -D2A or -D3G (G 115B) 
Avco Lycoming O-320-D1A (G 115C) 
Avco Lycoming O-360-A1F6 (G 115C2) 
Avco Lycoming AEIO-360-B1F (G 115D) 
Avco Lycoming AEIO-320-D1B (G 115D2) 
Avco Lycoming AEIO-360-B1B (G 115EG) 
 
Fuel AVGAS 100 or 100 LL.

Page 2 of 7  A57EU 
 
Engine Limits G 115,G 115A(O-235): G 115B,G 115C, G 115D2, (O-320, AEIO-320): 
 Max. power 115 HP (85.8 KW) 160 HP (119.3 KW) 
 Max. permitted RPM 2800 RPM 2700 RPM 
 Max. continuous power 112 HP (83.5 KW) 160 HP (119.3 KW) 
 Max. continuous RPM  2700 RPM 2700 RPM 
Engine Limits 
 
 
G 115D, G 115C2, G 115EG (O-360, AEIO-360): 
 Max. power 180 HP (134.2 KW) 
 Max. permitted RPM 2700 RPM 
 Max. continuous power 180 HP (134.2 KW) 
 Max. continuous RPM 2700 RPM 
 
 
Propeller and Propeller G 115, G 115A  G 115, G 115A G 115B G 115C 
Limits Hoffmann Sensenich Sensenich Sensenich 
 HO 14-175 120 72 CKS6-2-53 74 DM6S5-2-64 74 DM7S14-2-64 
or       HO 14 HM -175 120    
Diameter max. 5.74 ft (1.75 m) 5.84 ft (1.78 m) 6.00 ft (1.83 m) 6.00 ft (1.83 m) 
Pitch at 0.75 R 3.94 ft (1.20 m) 4.43 ft (1.35 m) 5.35 ft (1.63 m) 5.35 ft (1.63 m) 
Propeller RPM Limits 2900 2800 2800 2800 
Static RPM Limits 2400 2350 2250 2250 
     
Propeller and Propeller 
Limits 
 
G 115C2 
 
G 115D 
 
G 115D2 
 
G 115EG 
 Hartzell Hoffmann Hoffmann MT-Propeller 
 HC-F2YR-1F/F7666A-3R HO-V 343 K()-V/180 FP HO23CHM-() 188 156 MTV-12-B-C/C-
183-17e 
     
Diameter max. 6.09 ft (1.86 m) 5.90 ft (1.80 m) 6.17 ft (1.88 m) 6.004 ft (1.83 m) 
Pitch at .75 R 13° ± 0.2° 4.43 ft (1.35 m) 5.12 ft (1.56 m) 5.36 ft (1.635 m) 
Propeller RPM Limits 2900 2700 2700 2800 
Static RPM Limits 2600 2550 2200 2600 
     
 
Airspeed Limits G 115, G 115A G 115B G 115C, G 115C2 G 115C* G 115D G 115D2 
      
VNE  (never exceed) 164 kts (303 km/h) 159 kts (295 km/h) 184 kts (341 km/h) 184 kts (341 km/h) 166 kts (308 km/h) 
VNO  (normal operating) 135 kts (250 km/h) 129 kts (240 km/h) 134 kts (248 km/h) 134 kts (248 km/h) 134 kts (248 km/h) 
VA (maneuvering)      
       normal aircraft   95 kts (176 km/h) 100 kts (186 km/h)    
       utility aircraft   99 kts (184 km/h) 104 kts (192 km/h) 114 kts (212 km/h) 114 kts (212 km/h) 114 kts (212 km/h) 
       acrobatic aircraft     128 kts (237 km/h) 128 kts (237 km/h) 
VFE  (flaps extended)   94 kts (175 km/h)   94 kts (175 km/h) 112 kts (208 km/h) 112 kts (208 km/h) 112 kts (208 km/h) 
* G 115C only if used for limited acrobatics according to Service Bulletin 1078-55. 
 
Airspeed Limits 
 
G115EG 
  
VNE  (never exceed) 184 kts (341 km/h) 
VNO  (normal operating) 150 kts (278 km/h) 
VA (maneuvering)  
 acrobatic aircraft 130 kts (241  km/h) 
   
   
VFE  (flaps extended) 112 kts (208 km/h)

Page 3 of 7  A57EU 
 
C.G. Range. G 115, G 115A  G 115B G 115C, G 115C2 G 115C*, G 115D,  
Most Forward C.G. (Between the given values linear change)    G 115D2 
     
Normal aircraft 8.70 in (221 mm) 10.04 in (255 mm)   
 aft of datum at aft of datum at   
 1874.0 lbs (850 kg) 2028.2 lbs (920 kg)   
 7.83 in (199 mm)  7.83 in (199 mm)   
 aft of datum at aft of datum at   
 1818.8 lbs (825 kg) 1851.4 lbs (840 kg)   
      or less      or less   
     
Utility aircraft 7.83 in (199 mm) 10.04 in (255 mm) 8.94 in (227 mm) 8.94 in (227 mm) 
 aft of datum aft of datum aft of datum at aft of datum at 
  at 1873.9 lbs (850 kg) 2182 lbs (990 kg) 2182 lbs (990 kg) 
  7.83 in (199 mm) 7.76 in (197 mm) 7.76 in (197 mm) 
  aft of datum at aft of datum at aft of datum at 
  1763.7 lbs (800 kg) 1653 lbs (750 kg) 1653 lbs (750 kg) 
       or less   
     
Acrobatic  aircraft    8.62 in (219 mm) 
    aft of datum at 
    2028 lbs (920 kg) 
    7.76 in (197 mm) 
    aft of datum at 
    1653 lbs (750 kg) 
 
C.G. Range. G 115EG 
Most Forward C.G. (Between the given values linear change) 
  
Acrobatic  aircraft 8.46 in (215 mm) 
 aft of datum at 
 2183.0 lbs (990 kg) 
 7.76 in (197 mm) 
 aft of datum at 
 1653 lbs (750 kg) 
      or less 
 
Most rearward C.G. G 115, G 115A G 115B G 115C, G 115C2 G 115C*, G 115D,  
    G 115D2 
Normal aircraft 11.72 in (298 mm) 11.72 in (298 mm)   
 aft of datum aft of datum   
     
Utility aircraft 11.72 in (298 mm) 11.72 in (298 mm) 11.72 in (298 mm) 11.72 in (298 mm) 
 aft of datum aft of datum aft of datum at aft of datum at 
   2182 lbs (990 kg) 2182 lbs (990 kg) 
   11.34 in (288 mm) 11.34 in (288 mm) 
   aft of datum at aft of datum at 
   1653 lbs (750 kg) 1653 lbs (750 kg) 
     
Acrobatic aircraft    11.61 in (295 mm) 
    aft of datum at 
    2028 lbs (920 kg) 
    11.34 in (288 mm) 
    aft of datum at 
    1653 lbs (750 kg)

Page 4 of 7  A57EU 
Most rearward C.G.: G 115EG 
  
Acrobatic aircraft 11.73 in (298 mm) 
 aft of datum at 
 2183 lbs (990 kg) 
 11.48 in (292 mm) 
 aft of datum at 
 1653 lbs (750 kg) 
 
Empty Weight C.G. See Flight Manual (weight and balance, Section 6) 
 
Datum Wing leading edge 
 
Leveling Means Canopy sill 
 
Maximum Weight G 115,G 115A G 115B  G 115C, G 115C2 G 115C*, G 115D, 
G 115D2 
G 115EG 
      
Normal aircraft 1873.9 lbs (850 kg)  2028.2 lbs (920 kg)    
Utility aircraft 1763.7 lbs (800 kg) 1873.9 lbs (850 kg) 2182.6 lbs (990 kg) 2182.6 lbs (990 kg)  
Acrobatic aircraft    2028.2 lbs (920 kg) 2183 lbs (990 kg) 
 
Minimum Crew 1 pilot 
 
Number of Seats 2 (side by side) 9.84 in (250 mm) aft of datum 
 
Maximum Baggage 44.1 lbs (20 kg) 35.43 in (900 mm) aft of datum 
(for G115, G115A, G115B) 
121 lbs (55 kg) 38.98 in (990 mm) aft of datum 
(for G115C, G115C2, G115D, G115D2, G115EG) 
 
Fuel Capacity G 115,G 115A: G 115B: G 115C, G 115C2, 
G 115D, G 115D2, 
G 115EG: 
    
Total Contents 26.42 U.S. gal (100 l) 29.59 U.S. gal (112 l) 39.63 U.S. gal (150 l) 
 35.04 in (890 mm) 35.04 in (890 mm) 13.19 in (335 mm) 
 aft of datum aft of datum aft of datum 
    
Usable 24.23 U.S. gal (91.7 l) 28.27 U.S. gal (107 l) 37.77 U.S. gal (143 l) 
    
 
Oil Capacity G 115, G 115A: G 115B: G 115C, G 115C2, 
G 115D, G 115D2, 
G 115EG: 
G 115EG: 
 6 quarts (5.7 l) 8 quarts (7.6 l) 8 quarts (7.6 l)   8 quarts (7.6 l)   
 52.36 in (1330 mm) 52.36 in (1330 mm) 52.36 in (1330 mm) 50.79 in (1290 mm) 
 fwd of datum fwd of datum  fwd of datum fwd of datum

Page 5 of 7  A57EU 
Control Surface Movements 
 
 
 
 
G 115 G 115A G 115B G 115C, G 115C2 
G 115D, G 115D2 
G 115EG 
 (in)              (mm) (in)             (mm) (in)             (mm) (in) (mm) (in) (mm) 
Flaps  UP 0                      0 0                     0 0                      0 0 0 0 0 
  DOWN 6.97± 0.35   177± 9 6.97±0.35   177±9 6.97±0.35   177±9 9.96+0. 2 
       -0.39 
253 +5 
       -10 
10.11 
       -0.39 
257 +0 
       -10 
Aileron  UP 2.76±0.28      70±7 2.76±0.28     70±7 2.76±0.20     70±5 2.83±0.12 72±3 2.99±0.12 76±3 
  DOWN 1.42±0.28      36±7 1.42±0.28     36±7 2.36±0.20     60±5 2.56±0.12 65±3 2.79±0.12 71±3 
Aileron 
 servo 
 
only S/N 
 UP 
(aileron on 
   stop) 
3.54±0.12      90±3     if installed, same 
     movements as 
         G 115 
    
  8008 
through 
  8031 
 DOWN 
(aileron on 
   stop) 
1.54±0.12      39±3       
Elevator  UP 3.46±0.28      88±7 3.46±0.28     88±7 3.46±0.28     88±7 6.69±0.20 170±5 7.0±0.20 178±5 
  DOWN 2.80±0.28      71±7 2.52±0.20     64±5 2.52±0.20     64±5 3.94±0.20 100±5 4.13±0.20 105±5 
Trim tab  UP 1.14±0.08      29±2 1.14±0.08     29±2 1.14±0.08     29±2 1.69±0.12 43±3 0.6±0.08 15±2 
(elevator 
 neutral) 
 DOWN 2.01±0.08      51±2 
 
2.01±0.08     51±2 
 
2.01±0.08     51±2 
 
2.36±0.12 60±3 2.36±0.12 65±3 
Rudder 
up to S/N 
8065 
 LH 11.42±0.79  290±20 11.42±0.39  290±10 11.42±0.39   290±10 10.28±0.20 261±5 10.83 +0 
       -0.39 
275±10 
  RH 11.42±0.79  290±20 11.42±0.39  290±10 11.42±0.39   290±10 10.28±0.20 261±5   
as of S/N 
8066 and 
     for 
 LH 11.06±0.75   281±19 
replacement  RH 11.06±0.75   281±19 
 
Serial Nos. Eligible Model G 115 Serial No. 8008 through 8088 
Model G 115A Serial No. 8090 through 8109 
Serial No. 8008 through 8109 must be modified according to GROB Service 
Bulletin TM 1078-5 "Special equipment of GROB G 115 for the export to the 
USA". 
Model G 115B is formed by modification of Serial No. 8008 through 8088 and 8090 
through 8109 according to GROB Service Bulletin TM 1078-27/2 "Modification 
of the G 115/G 115A to the G 115B standard". 
Model G 115C as of Serial No. 82001/C. 
Model G 115C2 as of Serial No. 82015/C2. 
Model G 115D as of Serial No. 82003/D. 
Model G 115D2 as of Serial No.82002/D2. 
Model G 115EG as of Serial No. 82200. 
 
Import Requirements The FAA can issue a U.S. Standard Airworthiness Certificate based on an Export 
Certificate of Airworthiness (Export C of A) signed by a representative of the 
German civil airworthiness authority, the Luftfahrt Bundesamt (LBA), on behalf of 
the European Community. The Export C of A should contain the following 
statement: ‘The aircraft covered by this certificate has been examined, tested, and 
found to comply with U.S. airworthiness regulations 14 CFR  Part 23 approved under 
U.S. Type Certificate No. A57EU and to be in a condition for safe operation.’  
     
Refer to the applicable bilateral agreement to verify eligibility for import into the 
United States of both new and used aircraft based on the scope of the agreement, to 
identify any required statements by the exporting authority on the export certificate of 
airworthiness (or equivalent document), and for procedures for coordinating 
exceptions to conformity statements on these documents. Refer to FAA Order 
8130.2, Airworthiness Certification of Aircraft, for requirements for issuance of an 
airworthiness certificate for imported aircraft. 
 
Certification Basis 1) 14 CFR Sections 21.29, 21.183(c) and 14 CFR 23, effective February 1, 1965,  
including Amendments 23-1 through 23-32, and 
2) 14 CFR Section 36, effective November 18, 1969, including Amendments 36-1 
through amendment in effect at the time of U.S. Type Certification, and

Page 6 of 7  A57EU 
Certification Basis, continued 
3) Special Conditions; GROB Model G 115 - Series Airplanes, published in 
Federal Register 53FR39448, and 
4) Section 611(b) of the FAA Act of 1958 
The LBA originally type certificated this aircraft under its Type Certificate No. 1078. 
The FAA validated this product under U.S. Type Certificate No. A57EU. Effective 
September 28, 2003, the European Aviation Safety Agency (EASA) began oversight 
of this product on behalf of Germany.  
 
The EASA type certificate for the G115 series models is EASA.A.364. 
 
Equipment The basic required equipment as prescribed in the applicable airworthiness 
regulations (see Certification Basis) must be installed in the airplane for certification. 
 
Service Information Service bulletins, aircraft flight manuals, maintenance and overhaul manuals, 
structural repair manuals, and vendor manuals which contain a statement that the 
document is approved by the EASA, are accepted by the FAA and are considered 
FAA approved. (These approvals pertain to the design data only.) 
 
NOTES 
 
Note 1. Current weight and balance data together with a list of equipment included in the certificated empty 
weight, and loading instructions, when necessary, must be provided for each powered aircraft at the time 
of original certification.  The certificated empty weight and corresponding center of gravity locations 
must include the following: 
a) unusable fuel of 13.18 lbs (G 115, G 115A), 7.94 lbs (G 115B) at 35.04 in aft of datum, 11.10 
lbs (G 115C, G 115C2, G115D, G 115D2, G 115EG) at 13.19 in aft of datum. 
b) engine oil of 11.18 lbs (G 115, G 115A) respectively 14.91 lbs (G 115B, G 115C, G 115C2, G 
115D, G 115D2) at 52.36 in and 50.79 in (G 115EG) fwd of datum. 
 
Note 2. The placards listed in Section 2 of the LBA-approved Airplane Flight Manual GROB G 115, G 115B, G 
115C, G 115C2, G 115D, G 115D2, G 115EG must be displayed.  See Note 9. 
 
Note 3. Service Life Limited components airframe: 
 
12,000 flight hours for G 115, G 115A, G 115B, G 115C, G 115C2; extended to 22,900 flight 
hours if inspected in accordance with AMM chapter 05-41 (see also Service Bulletin 
MSB1078-161) 
 
4,000 flight hours for the G 115D, G 115D2 and for the G 115C if certified for limited acrobatics in 
accordance with Service Bulletin 1078-55. This Service Life Limit can be  extended to 12,000 flight 
hours, if an inspection in accordance with Service Bulletin OSB1078-105 is performed before 
reaching 4,000 flight hours. 
 
Every 3000 flight hours for the G 115, G 115A, G 115B, G 115C, G 115C2 a scheduled inspection 
must be performed in accordance with the Maintenance Manual. 
 
After 2,000, 6,000, 8,000 and 10,000 flight hours for the G 115D, G 115D2 and for the G 115C if 
certified for limited acrobatics in accordance with Service Bulletin 1078-55, a scheduled inspection 
must be performed in accordance with the Maintenance Manual, including a fuel tank pressure test 
after 8,000 flight hours.  
 
24,000 flight hours for G 115EG. 
 
Note 4. Changes to the factory delivered paint schemes have to be coordinated with the TC Holder or the FAA's 
Certificate Management Office responsible for this type certificate. 
 
Note 5. Major structural repairs must be accomplished by a properly certificated mechanic in accordance with 
data approved by the FAA. 
 
Note 6. All G 115 models are approved for VFR day and night. 
G 115C, G 115C2, G 115D and G 115D2 models are approved for IFR when equipped with Service 
Bulletin 1078-50 and the associated Airplane Flight Manual Supplement as shown in Service Bulletin 
1078-50 or later (LBA) approved AFM Supplement Revision.

Page 7 of 7  A57EU 
 
Note 7. Only G 115, G 115A, G 115B: 
Normal Category: Acrobatic maneuvers inclusive spins are not approved. 
Utility Category: Spins with equipment according to Service Bulletin TM 1078-9/2 and with 
flap setting 0° are approved.  Spins without wheel fairings are not 
approved. 
 
Control Surface Movements (restricted): 
(in) (mm) 
Elevator  Down   2.52±0.20  64 ±5 
Rudder  LH 11.42±0.39 290±10 
RH 11.42±0.39 290±10 
 
Note 8. Airplanes of the model G 115C may be operated in the acrobatic category for limited acrobatics after 
embodiment of Service Bulletin 1078-55.  The equipment required by Service Bulletin 1078-55 may be 
installed already complete or partly by the manufacturer.  So modified airplanes are marked with the 
suffix “/C1” to the S/N and the sales designation is “G 115C1 ACRO”.  The G 115C must be operated in 
the acrobatic category according to Supplement 2 to the Airplane Flight Manual G 115C, LBA approved. 
 
Note 9. In addition to all other requirements of this type certificate data sheet, G 115EG airplanes must 
additionally have the following instruments marked in US units: 
 
1) EGT and OAT indicator in degrees centigrade (or Fahrenheit). 
2) Manifold pressure in inches of mercury pressure, fuel flow indicator in gallons. 
3) Fuel quantity in gallons. 
4) Oil temperature and pressure in degrees centigrade (or Fahrenheit) and in pounds per square 
inch, (psi). 
5) Fuel pressure and cylinder head temperature, in psi and degrees centigrade (or Fahrenheit). 
 
The following placards must be shown in US units: 
 
1) Limitations must be in US units, weight in pounds. 
2) Fuel Filler Cap, gallons. 
3) Fuel Tank Selector, consistent with fuel quantity indicator. 
4) Fuel Flow, gallons per hour.   
5) Manifold Pressure, inches of mercury 
 
Procedures and methods for accomplishing this remarking should be obtained from the manufacturer. 
 
 
 
- END -
```

## ADs (2, in force first)

- [AD 2022-05-14](https://openairdocs.org/ad/2022-05-14): Flight Control System · GROB Aircraft SE G115EG. Effective Mar 24, 2022
- [AD 2022-03-15](https://openairdocs.org/ad/2022-03-15): Fuel Quantity Indicator · Garmin G3X Touch Electronic Flight Instrument System (STC SA01899WI or SA02658SE). Effective Mar 21, 2022

## Registered aircraft by registry model (OpenAirDocs)

- [Burkhart Grob GROB G115C](https://openairdocs.org/model/burkhart-grob-grob-g115c): 3 aircraft (registry code 1660303)
- [Burkhart Grob Luft-Und GROB G115C2](https://openairdocs.org/model/burkhart-grob-luft-und-grob-g115c2): 1 aircraft (registry code 1660305)
- [Burkhart Grob Luft-Und GROB G115D 2](https://openairdocs.org/model/burkhart-grob-luft-und-grob-g115d-2): 1 aircraft (registry code 1660313)

## STCs approved under this data sheet (61, first 50)

- [STC SA12428CH](https://openairdocs.org/stc/SA12428CH): Installation of the Lycoming Engines Electronic Ignition System (EIS). Lycoming Engines, An Operating Division of AVCO Corporation
- [STC SA12406WI](https://openairdocs.org/stc/SA12406WI): Installation of a Garmin AXIS Flight Display System. Garmin International Inc.
- [STC SA04652CH](https://openairdocs.org/stc/SA04652CH): To allow use of 100R grade aviation fuel meeting Swift Fuel, LLC specification. Swift Fuels LLC
- [STC SA02636SE](https://openairdocs.org/stc/SA02636SE): Installation of Garmin GPS 175 Navigation System and GNX 375 Navigation System with ADS-B In/Out Transponder.. Garmin International Inc.
- [STC SA02019SE-D](https://openairdocs.org/stc/SA02019SE-D): Installation of Garmin Model GTN 625/635/650; 725/750 Navigation System. Garmin International Inc.
- [STC SA02738CH](https://openairdocs.org/stc/SA02738CH): Installation of L-3 Communications Avionics Systems. Acron Aviation Inc.
- [STC SA04046CH PAGE 1](https://openairdocs.org/stc/SA04046CH%20PAGE%201): Installation of L-3 GENESIS  (TM) Electronic Standby Instrument System (ESI-500/MAG-500). Acron Aviation Inc.
- [STC SA04378CH](https://openairdocs.org/stc/SA04378CH): Installation of an engine modified per STC SE04349CH. SureFly Partners Ltd.
- [STC SA01757WI](https://openairdocs.org/stc/SA01757WI): To allow the use of UL91 or UL94 (minimum) grade aviation fuel. Swift Fuels LLC
- [STC SA04568CH](https://openairdocs.org/stc/SA04568CH): Installation of the uAvionix tailBeaconX, a tail mounted position light with integrated Automatic Dependent Surveillance - Broadcast (ADS-B) Out and 1090MHz Mode-S transponder functionality. uAvionix Corporation
- [STC SA02658SE](https://openairdocs.org/stc/SA02658SE): Installation of Garmin GI 275 Multi-Function Display System. Garmin International Inc.
- [STC SA02571SE](https://openairdocs.org/stc/SA02571SE): Installation of Garmin G500/G600 TXi Integrated Avionics System (Primary Flight Display, Multi-Function Display, and Engine Indicating System Display).. Garmin International Inc.
- [STC SA02019WI](https://openairdocs.org/stc/SA02019WI): Installation of the Trig Avionics TX56, TX56A, TX57, or TX57A VHF Nav-Com Radio.. Peregrine
- [STC SA01967WI](https://openairdocs.org/stc/SA01967WI): Use of GAMI G100UL High Octane Unleaded Avgas. General Aviation Modifications Inc.
- [STC SA02203AK](https://openairdocs.org/stc/SA02203AK): Installation of FlightLogic Synthetic Vision Electronic Flight Information System (EFIS-SV).. Genesys Aerosystems Inc.
- [STC SA02444AK](https://openairdocs.org/stc/SA02444AK): Approval of the L-3 Communications NGT 9000/9000R ADS-B system installed. ADS-B Technologies LLC
- [STC SA11174SC PAGE 1](https://openairdocs.org/stc/SA11174SC%20PAGE%201): Installation of BendixKing by Honeywell KSN 770 and KSN 765 WAAS LPV approach capable nav/comm systems. Honeywell International Inc (Bendix King)
- [STC SA10822SC](https://openairdocs.org/stc/SA10822SC): Installation of EFD1000 Primary Flight Display. Aspen Avionics Inc.
- [STC SA00401BO](https://openairdocs.org/stc/SA00401BO): Installation of a SkyTrax100B UAT receiver. Avidyne Corporation
- [STC SA00410BO](https://openairdocs.org/stc/SA00410BO): Installation of an AV-30-C Multi-Mode Indicator. uAvionix Corporation
- [STC SA01831WI](https://openairdocs.org/stc/SA01831WI): To allow the use of UL91 (minimum) grade aviation fuel. Petersen Aviation Inc
- [STC SA02268CH](https://openairdocs.org/stc/SA02268CH): Installation of Airwolf Filter Corp. Air Oil Separator. Airwolf Filter Corporation
- [STC SA01714WI](https://openairdocs.org/stc/SA01714WI): Installation of a Garmin transponders: (a) GTX 330/330D/33/33D with ADS-B Out functionality; (b) GTX 335/335R/345/345R with ADS-B Out and In functionality; or (c) GTX 335R/345R with ADS-B Out functionality in select airplanes installed with G950/G1000 systems.. Garmin International Inc
- [STC SA00744DE](https://openairdocs.org/stc/SA00744DE): Installation of the Automatic Dependent Surveillance  Broadcast (ADS-B) Out Equipment using a Trig Avionics TT31 Transponder and an approved position sensor. Peregrine
- [STC SA00765DE](https://openairdocs.org/stc/SA00765DE): Installation of Automatic Dependent Surveillance  Broadcast (ADS-B) Out functionality using the BendixKing KT74 Transponder and qualified position sensor. Peregrine
- [STC SA04165NY](https://openairdocs.org/stc/SA04165NY): Installation of Latitude Technologies Skynode S200 Satcom system must be performed. Latitude Technologies Corporation
- [STC SA02153LA-D PAGE 1](https://openairdocs.org/stc/SA02153LA-D%20PAGE%201): Installation of Garmin G600 Primary Flight Display (PFD) and Multifunction Display (MFD) System. Garmin International Inc.
- [STC SA01835WI](https://openairdocs.org/stc/SA01835WI): Installation of Trig Avionics TY-96 or TY-97 VHF Communications Radio. Peregrine
- [STC SA00024NY](https://openairdocs.org/stc/SA00024NY): Installation of Airwolf remote mounted engine oil filter kit AFC-K007 on single or multi-engine fixed wing light aircraft incorporating Lycoming reciprocating engines of 450 horsepower or less.. Airwolf Filter Corporation
- [STC SA01933LA-D](https://openairdocs.org/stc/SA01933LA-D): Installation of Garmin Model 400W / 500W Series GPS-WAAS Navigation System. Garmin International Inc
- [STC SA00343BO](https://openairdocs.org/stc/SA00343BO): Installation of a single configuration or a dual configuration Avidyne Corporation Integrated Flight Display, Model IFD540 loaded with Release 10.0 software (or later FAA approved release). Avidyne Corporation
- [STC SA00352BO PAGE 1](https://openairdocs.org/stc/SA00352BO%20PAGE%201): Installation of an Avidyne Corporation Mode A/C/S Transponder with ADS-B Out capability, Model AXP340 loaded with Version 3.13 software (or later FAA approved version),. Avidyne Corporation
- [STC SA02119SE PAGE 1](https://openairdocs.org/stc/SA02119SE%20PAGE%201): Installation of Garmin GDL 88 ADS-B UAT Transceiver System. Garmin International Inc
- [STC SA01229SE PAGE 1](https://openairdocs.org/stc/SA01229SE%20PAGE%201): Installation of GNS 480 (CNX80) GPS WAAS Navigator with integrated VHF Navigation and Communication radios. Garmin International Inc
- [STC SA02442AK PAGE 1](https://openairdocs.org/stc/SA02442AK%20PAGE%201): Approval of the L-3 Communications NGT 2000/2500 ADS-B system. ADS-B Technologies, LLC
- [STC SA01933LA-D PAGE 1](https://openairdocs.org/stc/SA01933LA-D%20PAGE%201): Installation of Garmin Model 400W / 500W Series GPS-WAAS Navigation
System. Garmin International Inc
- [STC SA02283SE PAGE 1](https://openairdocs.org/stc/SA02283SE%20PAGE%201): Installation of Electronics International Inc. Glass Panel Engine Monitor (with In Flight Data) CGR-30P. Electronics International Inc.
- [STC SA02402SE PAGE 1](https://openairdocs.org/stc/SA02402SE%20PAGE%201): Installation of Electronics International Inc. Glass Panel Engine Monitor (with In-Flight Data) CGR-30C. Electronics International Inc.
- [STC SA02717NY PAGE 1](https://openairdocs.org/stc/SA02717NY%20PAGE%201): Installation of VoiceFlight Systems LLC VFS101 Speech Recognition Module. VoiceFlight Systems LLC
- [STC SA02015SE-D](https://openairdocs.org/stc/SA02015SE-D): Installation of Garmin G500 Primary Flight Display (PFD) and Multifunction Display (MFD) System.. Garmin International Inc
- [STC SA01692SE](https://openairdocs.org/stc/SA01692SE): Installation of a Garmin GMX 200 Multi-Function Display. Garmin International Inc
- [STC SA03148NY](https://openairdocs.org/stc/SA03148NY): The installation of the Latitude Technologies Corporation S100 Tracking System. Latitude Technologies Corporation
- [STC SA01487SE-D](https://openairdocs.org/stc/SA01487SE-D): Installation of a GDL 69 or GDL 69A XM Satellite Receiver. Garmin International Inc
- [STC SA00243BO](https://openairdocs.org/stc/SA00243BO): Installation of Centurion Consulting, Inc. GPS Steering Assist Module (SAM) with roll steering (p/n 0025-5100), or without roll steering (p/n 0025-5200).. Icarus Avionics, LLC
- [STC SA00068SE](https://openairdocs.org/stc/SA00068SE): Installation of fuel flow/pressure instruments. (W/TSIO-360-MB1). Electronics International Inc.
- [STC SA02293AK](https://openairdocs.org/stc/SA02293AK): Installation of FlightLogic Synthetic Vision Electronic Flight Information System (EFIS-SV).. Chelton Flight Systems Inc.
- [STC SA01988SE](https://openairdocs.org/stc/SA01988SE): Installation of Electronics International Inc. Glass Panel Engine Monitor (with In-Flight Data) MVP-50P.. Electronics International Inc.
- [STC SA563CH](https://openairdocs.org/stc/SA563CH): Authorizes installation of engines equipped w/Unison Limited Authority Spark Advance Regulator (LASAR) ignition system w/Cylinder Head Temp. (CHT) monitoring capability on airframes. engines.. Champion Aerospace LLC
- [STC SA593CH](https://openairdocs.org/stc/SA593CH): Install Champion SlickSTART magneto booster system.. Champion Aerospace LLC
- [STC SA01473SE](https://openairdocs.org/stc/SA01473SE): Installation of a GTX 32 (mode C), GTX 33 (mode S), or GTX 33D (mode S with diversity) Remote Transponde. Garmin AT Inc.

All 61: https://openairdocs.org/tcds/A57EU/stcs.md

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