# TCDS A26EU: Textron Aviation Inc.

- Type: Type certificate data sheet
- Status: Current
- Holder: Textron Aviation Inc.
- Revision: 6
- Revised: January 6, 2025
- Product: Aircraft, Small Airplane
- Certification basis: Part 21, Part 23
- Registered aircraft: 3, by the registry models matched to it (OpenAirDocs)
- Data sheet PDF: https://openairdocs.org/files/sha256/dc/eb/dceb617dda665085ba2c2140fe4bfb713b7c0669cb953206aa944217b7dfbc69
- FAA DRS: https://drs.faa.gov/browse/excelExternalWindow/DRSDOCID128570473220250116173738.0001
- Page: https://openairdocs.org/tcds/A26EU

## Models (1)

As the data sheet lists them.

- F177RG

## 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 
Rev. No. 6 3 6 4 4 6 
 
DEPARTMENT OF TRANSPORTATION 
FEDERAL AVIATION ADMINISTRATION 
 
A26EU 
Revision 6 
Textron Aviation 
 F177RG 
January 6, 2025 
 
 
WARNING: Use of alcohol-based fuels can cause serious performance degradation and fuel 
system component damage and is therefore prohibited on Cessna airplanes. 
 
TYPE CERTIFICATE DATA SHEET NO. A26EU 
 
This data sheet, which is a part of Type Certificate No. A26EU, 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 Textron Aviation Inc. 
   One Cessna Boulevard 
   Wichita, KS 67215 
 
Type Certificate Holder Record Cessna Aircraft Company transferred to  
   Textron Aviation Inc. on July 29, 2015 
 
Type Certificate A26EU was transferred from Reims Aviation S.A., 51 Aerodrome de Reims-Prunay, Reims, France, to Cessna 
Aircraft Company on December 11, 2006. Coincident with this transfer, the Federal Aviation Administration (FAA) has accepted 
responsibilities of State of Design for all airplanes, and State of Manufacture for airplanes manufactured after December 11, 
2006, as defined by Annex 8 to the Convention on International Civil Aviation.  Prior to December 11, 2006, products identified 
under Type Certificate A26EU were approved by the FAA in accordance with the Federal Aviation Regulation appropriate to 
Imported Products (FAR 21.29).  Effective December 11, 2006, and after, these products are to be considered domestic products 
for the purpose of design certification, continued airworthiness, and administered under Federal Aviation Regulations §21.21. 
 
I. Model F177RG, 4 PCLM (Normal Category), Approved April 26, 1971 
 
 Engine Lycoming IO-360-A1B6 or IO-360-A1B6D 
 
 *Fuel 100/130 minimum grade aviation gasoline 
 
 *Engine Limits For all operations, 2700 rpm (200 hp) 
 
 Propeller and  1. McCauley propeller 
  Propeller Limits  Hub: B2D34C206/78TA  
Diameter: Not over 78 in., not under 76.5 in. 
Pitch at 30-inch station: 
 Low pitch:  12.9   
 High pitch: 27.5  
a. Hydraulic governor: 
 (1)  Woodward C210460 (IO-360-A1B6 only). 
 (2) McCauley C290D2/T11 (IO-360-A1B6),  
  or C290D2/T12 (IO-360-A1B6D). 
b. Cessna spinner:  0752637

A26EU  2 Rev. 6 
I. Model F177RG  (cont’d) 
 
 Propeller and 2. McCauley propeller 
  Propeller Limits (cont’d)  Hub: B2D34C207/78TCA 
Diameter: Not over 78 in., not under 76.5 in. 
Pitch at 30-inch station: 
 Low pitch:  12.9   
 High pitch: 27.5  
a. Hydraulic governor: 
 (1)  Woodward C210460 (IO-360-A1B6 only). 
 (2) McCauley C290D2/T11 (IO-360-A1B6),  
  or C290D2/T12 (IO-360-A1B6D). 
b. Cessna spinner:  0752637 
 
 *Airspeed Limits (CAS) Never exceed 195 mph (169 knots) 
Maximum structural cruising 160 mph (139 knots) 
Maneuvering 130 mph (113 knots) 
Flaps extended 110 mph  ( 96 knots) 
Landing gear operating speed 140 mph (122 knots) 
Landing gear extended speed 140 mph (122 knots) 
 
 C.G. Range (+101.0) to (+114.7) at 2200 lb. or less 
 (Landing gear extended) (+105.8) to (+114.7) at 2800 lb. 
Straight line variation between points given. 
Moment change due to retracting landing gear (+2776 in. -lb.) 
 
 Empty Wt. C.G. Range None 
 
 *Maximum Weight Normal category 2800 lb. 
 
 Number of Seats Four (two at sta. +93.0, two at sta. +145.0) 
 
 Maximum Baggage 120 lb. (+154.5 fwd. of wheel well, +178.5 aft of wheel well) 
 
 Fuel Capacity S/N F177RG0001 thru F177RG0062 
51 gal. (two 25.5 gal. fuel bays in wing at sta. +112; 50 gal. usable). 
 
S/N F177RG0063 and On: 
61 gal. (two 30.5 gal. fuel bays in wing at sta. +112; 60 gal. usable). 
 
See NOTE 1 for data on unusable fuel. 
 
 Oil Capacity W ithout oil filter: 
8 qt. (+44), (2 qt. unusable) 
 
With oil filter: 
9 qt. (+45). (3 qt. unusable; 2 qt. in sump plus 1 qt. in oil filter). 
 
See NOTE 1 for data on undrainable oil.  
 
 Control surface movements Wing Flaps    Down 30° + 2° -0° 
Aileron Up 20° + 2° Down 15° + 2° 
Stabilator  Up 20° + 1° Down   5° + 1° 
Stabilator tab Up   5° + 1° Down 13° + 1° 
Rudder (measured  Right 24° + 1° Left 24° + 1° 
perpendicularly to  
hinge line) 
 
 Serial No’s Eligible  F177RG0001 thru F177RG0177

Rev. 6  3 A26EU 
DATA PERTINENT TO ALL MODELS 
 
Datum  54.0 forward of front face of lower portion of firewall 
 
Leveling Means Jig located nutplates and screws at sta. +213.0 and sta. +238.0 on left of tailcone. 
 
Certification Basis Part 23 of the Federal Avia tion Regulations (FAR) dated February 1, 1965,  
as amended by 23-1 thru 23-6. 
Application for Type Certificate dated 26 April 1971. 
Type Certificate No. A26EU issued 17 May 1971, obtained by the manufacturer under 
delegation option procedures. 
 
Compliance for the Carry-Thru Spar Spare (P/N 171076-1) has been demonstrated in 
accordance with 14 CFR 23.572(a)(1)(b) as amended by Amendment 23-48. 
 
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 item of equipment is required: 
 
Stall warning indicator, Cessna Dwg No. 2070002. 
 
NOTE 1. 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. 
 
The certificated empty weight and the corresponding center of gravity locations must include undrainable  
oil of 0.0 lb. at 44.0 and unusable fuel of 6 lb. at 100.0 
 
NOTE 2. The following placards must be displayed as indicated: 
 
 1. In full view  of the pilot: 
 
“This airplane must be operated as a normal category airplane in compliance with the operating  
limitations as stated in the form of placards, markings, and manuals. 
 
MAXIMUMS 
Maneuvering speed 130 mph-CAS (113 knots) 
Gear extension speed 140 mph-CAS (122 knots) 
 
Gross weight    2800 lb. 
Flight load factor Flaps up +3.8  -1.52 
Flaps down +2.0 
 
No acrobatic maneuvers, including spins, approved.   
Altitude loss in a stall recovery 190 ft.   
Flight into known icing conditions prohibited.   
This airplane is certified for the following flight operations as of date of original airworthiness 
certificate:   
 
(DAY NIGHT VFR IFR) (As applicable)” 
 
2. On control lock:  "Control lock - remove before starting engine"

A26EU  4 Rev. 6 
DATA PERTINENT TO ALL MODELS 
NOTE 2. (cont’d) 
 
3. By fuel valve (at appropriate locations): 
a. S/N F177RG0001 thru F177RG0062: 
 "ON - 50 GAL. 
 OFF" 
b. S/N F177RG0063 and On: 
 "BOTH - 60 GAL. 
 LEFT - 30 GAL" 
 RIGHT - 30 GAL. 
 Use both for take-off and landing. 
 When switching from a dry tank, turn auxiliar y pump on and use full rich mixture until power 
 is restored." 
 
4. Aft of fuel tank cap: 
a. S/N F177RG0001 thru F177RG0062: 
 "Service this airplane with 100/130 grade aviation gasoline. 
 Total capacity 25.5 gal. 
 Capacity to line of holes inside filler neck, 22.0 gal." 
b. S/N F177RG0063 and On 
 "Service this airplane with 100/130 grade aviation gasoline. 
 Total capacity 30.5 gal. 
 Capacity to line of holes inside filler neck, 22.0 gal." 
 
5. In baggage compartment: 
a. "120 lb. maximum baggage. 
b. For additional loading instructio ns see weight and balance data." 
 
6. Next to door ventilation windows: 
"Do not open window above 120 mph or when using alternate static source." 
 
 7. On airspeed indicator: 
a. "Radial red line 195 mph  (CAS) 
b. Yellow arc 160 - 195 mph  (CAS) 
c. Green arc 70 - 160 mph  (CAS) 
d. White arc 60 - 110 mph  (CAS)" 
 
8. On oil temperature gage: 
a. “Red line at 245° F 
b. Green arc 100° to 245° F” 
 
9. On oil pressure gage: 
a. “Red line at 25 psi 
b. Green arc 60 psi to 90 psi 
c. Red line at 100 psi”  
 
10. Tachometer: 
"Normal operating 2100 - 2500 rpm (green arc) 
Caution 1400 - 1750 rpm (yellow arc) 
Maximum allowable             2700 rpm (red line)" 
 
11. On fuel flow gage: 
a. “Red line at 10 psi 
b. Green arc 6 to 13 gph” 
 
12. Near fuel flow gage: 
a. “Max. power Alt. S.L. 4000 8000 12000 
b. Mixture  GPH 17  15 13  10”

Rev. 6  5 A26EU 
DATA PERTINENT TO ALL MODELS 
NOTE 2. (cont’d) 
 
13. On flap control indicator: 
a. "0 to 10° - T.O.  (Takeoff range with blue  color code and 150 mph callout; also, mechanical  
   detent at 10°)." 
b. "10° - 20° - 30°  (Indices at  these positions with white color code and 110 mph callout; also,  
   mechanical detent at 20°)." 
 
14. Proximity of tachometer: 
"Avoid continuous operation between 1400-1750 rpm with less than 10" manifold pressure." 
 
15. On cylinder head temperature gage: 
a. “Red line at 475° F” 
b. “Green arc 200° to 475° F” 
 
16. On instrument panel (S/N F177RG0001 thru F177RG0042 only): 
 "Do not turn off alternator in flight except in emergency." 
 
17. On Emergency Landing Gear Pump Handle Cover: 
 
"EMERGENCY HAND PUMP PULL UP 
 
TO EXTEND GEAR MANUALLY: 
a. Place gear leve r in down position. 
b. Extend pump handle. 
c. Pump approximately 40 pressure strokes. 
d. Stop when resistance becomes heavy. 
e. Verify gear is down by observing green light. 
 
IMPORTANT 
To permit gear retraction after hand pump use full relief valve knob for a minimum period of five 
seconds.  Then move gear lever to the UP position." 
 
18. On manifold pressure gage: 
 "15 to 25 in.hg. (green arc)." 
 
NOTE 3. The cylinder head probe location for the Model F177RG is the No. 3 cylinder. 
 
In addition to the placards  specified above, the prescribed operating limitations indicated by an asterisk (*) 
under Section I of this data sheet must also be displayed by permanent markings. 
 
NOTE 4. Aircraft manufactured in France prior to December  11, 2006, and subsequently placed on the U.S. Registry, 
may be granted a U.S. Airworthiness Certificate based on 14 CFR Part 21, Section 21.183(d).  This will be a 
recurrent airworthiness certification and requires a statement or attestation of conformity to the applicable 
type design at the time of original manufacture be obtained from the DGAC France (e.g., the French TC / 
U.S. 21.29).  This “baseline” conformity determination can then be used as a starting point for which to 
evaluate the aircraft’s present conformity of type design and condition for safe operation as required by 
21.183(d) (e.g., review of all modifications and repairs, AD compliance, appropriate maintenance, etc., 
depending upon the current exporting authority and any applicable bilateral agreement).

A26EU  6 Rev. 6 
DATA PERTINENT TO ALL MODELS 
 
NOTE 5. Service Information 
 
The appropriate airplane service manual contains structural retirement lives, which may not be changed 
without FAA Engineering approval, for the following components: 
 
Component Part Numbe r Hours Model Numbe r 
Wing Carry-Thru Spar 1710706-1 23,800 177 Series 
 
a. If geophysical mapping missions have been flown, the operator must contact Textron Aviation prior to 
23,800 flight hours (or within the next 300 flight hours if 23,800 hours on the carry-thru spar has been 
exceeded). 
b. Refer to Section 2A-14-22, S upplemental Inspection No. 53-11-04. 
 
 
 
------ END ------
```

## ADs (19, in force first)

- [AD 2024-14-03](https://openairdocs.org/ad/2024-14-03): Autopilot System · Garmin GFC 500 Autopilot (STC SA01866WI). Effective Aug 20, 2024
- [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 2023-02-17](https://openairdocs.org/ad/2023-02-17): Fuselage Main, Structure · Textron 210N, 210R, P210N and 8 more. Effective Mar 20, 2023
- [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
- [AD 2011-10-09](https://openairdocs.org/ad/2011-10-09): Seat Rails and Roller Housing Inspections · Cessna 150A, 150B, 150C and 221 more. Effective Jun 17, 2011
- [AD 2008-26-10](https://openairdocs.org/ad/2008-26-10): Alternate static air source selector valve · Cessna 172, 172A, 172B and 179 more. Effective Jan 5, 2009
- [AD 2000-06-01](https://openairdocs.org/ad/2000-06-01): Fuel Strainer Assembly · Cessna 150F, 150G, 150H and 163 more. Effective May 5, 2000
- [AD 97-01-13](https://openairdocs.org/ad/97-01-13): Fuel, Oil and Hydraulic Hoses · Cessna 150, 150A, 150B and 232 more. Effective Feb 3, 1997
- [AD 88-12-12](https://openairdocs.org/ad/88-12-12): Fuel System · Cessna 177RG and F177RG. Effective Jul 5, 1988
- [AD 86-24-07](https://openairdocs.org/ad/86-24-07): Engine Controls Installation · Cessna 150C, 150D, 150E and 142 more. Effective Jan 7, 1987
- [AD 86-19-11](https://openairdocs.org/ad/86-19-11): Contaminated Fuel · Cessna 177, 177A, 177B and 83 more. Effective Oct 4, 1986
- [AD 72-03-03 R3](https://openairdocs.org/ad/72-03-03-R3): Wing Flap Actuators Jack Screw · Cessna F150F, F150G, F150H and 83 more. Effective Oct 15, 1984
- [AD 80-25-07 R1](https://openairdocs.org/ad/80-25-07-R1): Oil Coolers · American Champion 7ECA, 7GCAA, 7GCBC and 39 more. Effective Sep 24, 1981
- [AD 81-15-03](https://openairdocs.org/ad/81-15-03): Engine Inlet Air Filters · Replace existing engine induction air filter (Brackett Aero Filters STC SA693CE or SA71GL). Effective Jul 20, 1981
- [AD 76-04-03](https://openairdocs.org/ad/76-04-03): ARC PA-500A Actuators · Cessna 172L, 172M, 177B and 43 more. Effective Feb 26, 1976
- [AD 75-07-02](https://openairdocs.org/ad/75-07-02): Air Filter Seal · Cessna F177RG, 177, 177A and 2 more. Effective Mar 26, 1975
- [AD 74-16-06](https://openairdocs.org/ad/74-16-06): Oil Pressure Gage Line · Cessna F177RG, 177, 177A and 2 more. Effective Aug 9, 1974
- [AD 74-08-01](https://openairdocs.org/ad/74-08-01): Autopilot Servo Actuators · Aircraft Radio Autopilot Servo Actuators, 172L, 172M and 29 more. Effective Apr 9, 1974
- [AD 87-20-03 R2](https://openairdocs.org/ad/87-20-03-R2) (historical): Seat Tracks · Cessna 150A, 150B, 150C and 212 more. Effective Sep 24, 1990

## Registered aircraft by registry model (OpenAirDocs)

- [Cessna F177RG](https://openairdocs.org/model/cessna-f177rg): 2 aircraft (registry code 2075736)
- [Reims Aviation S A F177RG](https://openairdocs.org/model/reims-aviation-s-a-f177rg): 1 aircraft (registry code 7530216)

## STCs approved under this data sheet (78, 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 SA04837NY](https://openairdocs.org/stc/SA04837NY): Installation of AeroLED's Holdings, LLC., position lights, navigation lights, strobe lights and beacon lights. AeroLED's Holdings, LLC
- [STC SA12406WI](https://openairdocs.org/stc/SA12406WI): Installation of a Garmin AXIS Flight Display System. 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 SA02511SE](https://openairdocs.org/stc/SA02511SE): Installation of replacement fuel quantity indicator sending unit(s). CiES Inc.
- [STC SA01866WI](https://openairdocs.org/stc/SA01866WI): Installation of Garmin GFC 500 Autopilot with Electronic Stability and Protection. 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 SA02594SE](https://openairdocs.org/stc/SA02594SE): SkyView HDX Instrumentation and Autopilot System manufactured. Dynon Avionics
- [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 SA01899WI](https://openairdocs.org/stc/SA01899WI): Installation of Garmin G3X Touch Electronic Flight Instrument System. Garmin International Inc.
- [STC SA11137SC](https://openairdocs.org/stc/SA11137SC): Installation of Plane-Power ALT-FLX alternator. Hartzell Engine Technologies, LLC
- [STC SA02987CH](https://openairdocs.org/stc/SA02987CH): Installation of the Electroair Electronic Ignition System. Electroair Acquisition Corporation
- [STC SA01967WI](https://openairdocs.org/stc/SA01967WI): Use of GAMI G100UL High Octane Unleaded Avgas. General Aviation Modifications 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 SA01818WI](https://openairdocs.org/stc/SA01818WI): Installation of Garmin G5 Electronic Flight Instrument. Garmin International 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 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 SA04032CH](https://openairdocs.org/stc/SA04032CH): Install rocker switch assemblies. Electroair Acquisition Corporation
- [STC SA00344BO PAGE 1](https://openairdocs.org/stc/SA00344BO%20PAGE%201): Installation of Parmetheus Plus LED PAR36 and PAR46 taxi and landing lights.. Whelen Aerospace Technologies
- [STC SA01435SE](https://openairdocs.org/stc/SA01435SE): Installation of J.P. Instruments (JPI) Primary Engine Data Management System. J. P. Instruments
- [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 SA02013CH](https://openairdocs.org/stc/SA02013CH): Installation of Avidyne Corporation Traffic Advisory System (TAS). Avidyne Corporation
- [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 SA04200CH](https://openairdocs.org/stc/SA04200CH): Installation of Hartzell propeller model HC-C2YR-IBFP/F7894. Hartzell Propeller Inc
- [STC SA02212AK](https://openairdocs.org/stc/SA02212AK): Replacement of existing landing and/or taxi light reflector and bulbs with high intensity discharge (HID) lighting systems. Seaplanes North LLC
- [STC SA02428SE](https://openairdocs.org/stc/SA02428SE): Installation of an Air Stream Switch for an electric time recording device on non-pressurized aircraft. Henry F Rogers/David E Polley
- [STC SA00353BO](https://openairdocs.org/stc/SA00353BO): Installation of an auto lean system. Flight Enhancements LLC
- [STC SA00780SE](https://openairdocs.org/stc/SA00780SE): Installation of the True Lock Safety Retention Axle Lock Nut System. True Lock LLC
- [STC SA03699NY](https://openairdocs.org/stc/SA03699NY): The installation of MT-Propeller Entwicklung GmbH's Model# MTV-9-B/198-52 3-Blade constant speed propeller. MT- Propeller Entwicklung GmbH
- [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 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 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 SA02121SE](https://openairdocs.org/stc/SA02121SE): Installation of Garmin GTS 825 (TAS) or GTS 855 (TCAS I) Traffic System. Garmin International Inc
- [STC SA02825NY PAGE 1](https://openairdocs.org/stc/SA02825NY%20PAGE%201): Installation of Aerospace Logic Aircraft Instruments. Aerospace Logic Inc.
- [STC SA2067NM](https://openairdocs.org/stc/SA2067NM): Installation of BAS, Inc. TSO Shoulder Harness and BAS Inc. Harness System. BAS Inc
- [STC SA2693NM](https://openairdocs.org/stc/SA2693NM): Installation of Electronics International digital volt/amp gauges and accessories.. Electronics International 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 SA593CH](https://openairdocs.org/stc/SA593CH): Install Champion SlickSTART magneto booster system.. Champion Aerospace LLC
- [STC SA03623AT](https://openairdocs.org/stc/SA03623AT): Installation of Power Flow, Inc. (PFS) "improved performance" exhaust system.. Power Flow Systems Inc
- [STC SA4005NM](https://openairdocs.org/stc/SA4005NM): Precise Flight Inc. Pulselite Control System. Precise Flight Inc
- [STC SA00271WI](https://openairdocs.org/stc/SA00271WI): Replacement of the hydraulic system pressure switch with a new switch. APPH Wichita Inc.
- [STC SA02446CH](https://openairdocs.org/stc/SA02446CH): Installation of the Courtesy Light Kit.. Knots 2U Ltd.
- [STC SA477CH](https://openairdocs.org/stc/SA477CH): Installation of McCauley Propeller model B3D36C428/82NPA-6.. McCauley Propeller Systems
- [STC SA00680SE](https://openairdocs.org/stc/SA00680SE): Installation of Electronics International model UBG-16 or UBG-16T bar graph engine analyzer.. Electronics International

All 78: https://openairdocs.org/tcds/A26EU/stcs.md

---
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