# TCDS A25CE: Textron Aviation Inc.

- Type: Type certificate data sheet
- Status: Current
- Holder: Textron Aviation Inc.
- Revision: 14
- Revised: October 25, 2024
- Product: Aircraft, Small Airplane
- Certification basis: Part 23
- Registered aircraft: 26, by the registry models matched to it (OpenAirDocs)
- Data sheet PDF: https://openairdocs.org/files/sha256/e0/d9/e0d9589fef8e35c7db24ae1b35beb06cb0e90ea399e910ea31b4067ea509a9ae
- FAA DRS: https://drs.faa.gov/browse/excelExternalWindow/DRSDOCID123036712220250115153604.0001
- Page: https://openairdocs.org/tcds/A25CE

## Models (2)

As the data sheet lists them.

- 406 (Caravan II)
- 404

## 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. 14 13 9 13 14 8 
 
DEPARTMENT OF TRANSPORTATION 
FEDERAL AVIATION ADMINISTRATION 
 
 A25CE  
 Revision 14  
 Textron Aviation   
 404   
 406   
 October 25, 2024  
 
TYPE CERTIFICATE DATA SHEET NO. A25CE  
 
This data sheet which is part of Type Certificate No. A25CE 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, Kansas 67215 
 
Type Certificate Holder Record Cessna Aircraft Company transferred to  
  Textron Aviation Inc. on July 29, 2015 
 
I. Model 404, Titan, (Normal Ca tegory), Approved July 21, 1976 
 
 Engines Two Teledyne Continental GTSIO-520-M 
  Reduction gear ratio .667:1 
 
 Fuel 100/130 or 100 low-lead minimum grade aviation gasoline 
  (See NOTE 3 for optional anti-icing additive) 
 
 Engine Limits For all operations, 2235 propeller r.p.m. (375 hp.) 
  40.0 in. Hg. mp. up to critical altitude of 16,000 feet in standard atmosphere.  Above  
  16,000 feet the following maximum mp. applies for maximum r.p.m. 
 
Altitude (ft.)  Max. Allowable Mp. (in. Hg) 
 16,000 40.0 
 18,000 37.5 
 20,000 35.0 
 22,000 32.0 
 24,000 29.2 
 26,000 26.0 
 28,000 23.0 
 30,000 20.0 
 
 Propeller and 1. Two McCauley full-fe athered, three-bladed propeller:  
   Propeller Limits  Hub: 3FF32C501  
Blade: 90UMB-0  
Diameter:   Not over 90.0 in., not unde r 88.5 in. (no further reduction permitted) 
Pitch settings at 30.0 in. sta.: 
 Low pitch: 16.6°, +0.2°  
 Feathered: 84.6°, +0.3°

A25CE 2 Rev. 14 
 
I. Model 404 (cont’d) 
 
 Propeller and  S/N 404-0001 thru 404-0600 
  Propeller Limits (cont’d)  a. Hydraulic governor: 
 McCauley DCF290D2/T6, DCFU290D2/T6, DCFS290D2/T6,  
 DCFUS290D2/T6, DCF290D7/T6, DCFU290D7/T6 or  
 DCFU290D13/T6, DCFS290D7/T6, DCFUS290D7/T6 or  
 DCFUS290D13/T6 
 S/N 404-0601 and On 
 b. Hydraulic governor: 
 McCauley DCF290D7/T6, DCFU290D7/T6 or DCFU290D13/T6,  
 DCFS290D9/T6, DCFUS290D9/T6 
 
 c. Propeller spinner and bulkhead assembly: 
  McCauley D3534/D-4506 
 
 Airspeed Limits Maneuvering  160 KIAS 
   (IAS) Maximum structural cruising  212 KIAS 
  Never exceed   241 KIAS 
  Landing gear operating 182 KIAS 
  Landing gear extended 182 KIAS 
  Flaps extended - takeoff 182 KIAS 
  Flaps extended - landing 152 KIAS 
  Minimum control    78 KIAS 
 
 C.G. Range (Landing  (+170.31) to (+179.08) at 8400 lb.  
   Gear Extended) (+165.6) at 6100 lb. or less 
  Straight line variation between points given 
  Landing gear retracted moment change:  +1113 in./lbs. 
 
 Empty Wt. C.G. Range None 
 
 Leveling Means Two screws located on W. L. 93.80 @ sta. 248.25 and sta. 272.65 
 
 Maximum Weight S/N 404-0001 thru 404-0200 
  Landing: 8100 lb.  
  Takeoff:  8400 lb. 
 
  S/N 404-0201 and On 
  Landing:  8100 lb.  
  Ramp:  8450 lb.  
  Takeoff:  8400 lb. 
 
 No. of Seats One (1) thru 11  
  (Two at +137.0, Two at +171.0, Two at +199.0, Two at +227.0, One at +255.0,   
  Two at +296.0) 
  See manufacturer's equipment lis t for other seating arrangements. 
 
 Maximum Baggage 250 lb. (+32.0), 350 lb. (+71.0), 400 lb. (+211.0), 400 lb. (+301.0), 100 lb. (+317.0) 
 
 Fuel Capacity S/N 404-0001 thru 404-0200 
  348.0 gallons (Two wing tanks, 174.0 gallons  each, 170.0 gallons usable at +181.2) 
 
  S/N 404-0201 and On 
  348.0 gallons (Two wing tanks, 174.0 gallons  each, 172.0 gallons usable at +181.2) 
 
  (See NOTE 1 for data on unusable fuel)

Rev. 14 3 A25CE 
 
I. Model 404 (cont’d) 
 
 Oil Capacity 26 quarts (13 quarts in each e ngine at +129.0; usable 7.0 quarts per engine) 
  (See NOTE 1 for data on undrainable oil) 
 
 Maximum Operating Altitude 30,000 feet 
 
 Control Surface Movements Wing flaps   Down 35°, +1° 
     (Inboard) 
     Down  23°, +0°, -1° 
     (Outboard) 
  Main surfaces 
  Aileron Up 25°, +1°, -0° Down 15°, +1°, -0° 
  Elevator Up 24°, +1°, -0° Down 15°, +1°, -0° 
  Rudder Right 32°, +1°, -0° Left 32°, +1°, -0° 
    (Read degrees normal to rudder hinge line) 
  Tab (main surface in neutral) 
    Aileron Up 15°, +1°,  -0° Down 15°, +1°, -0° 
    Elevator Up   4°, +0.5°, -0.0° Down 14°, +0.0°, -0.5° 
    Rudder Right   9°, +0.0°,  -0.5° Left   9°, +1°, -0° 
    (Read degrees normal to rudder hinge line) 
 
 Serial Nos. Eligible 404-0001 thru 404-0859 
 
 
II. Model 406, Caravan II, (Normal Category), Approved June 27, 1986 
 
 Engines Two Pratt and Whitney Aircraft of Canada, Ltd., PT6A-112 turboprops 
 
 Fuel  Aviation turbine fuel ASTM D-1655, Jet A,  Jet A-1, or Jet B; MIL-T-5624, JP-4, JP-5;  
  MIL-T-83133, JP-8.  Anti-icing additive per MIL-I-27686D, MIL-I-27686E, or Phillips  
  PFA55MB must be blended into the aircraft fuel in concentrations not less than 0.060%  
  or more than 0.15% by volume.  For emergency use of aviation gasoline and fueling  
  procedures, refer to appr oved Airplane Flight Manual. 
 
Engine Limits O perating Limits 
  
 
Shaft 
Horsepower 
Ng Gas 
Generator 
Speed 
(% r.p.m.) 
 
Indicated 
Torque 
(ft.-lbs.) 
Prop 
Shaft 
Speed 
(r.p.m.) 
Maximum 
Permissible 
Interturbine 
Temp. (C) 
Takeoff static and max. 
  continous 
 
500 
 
101.6 
 
1382 
 
1900 
 
725 
Starting (2 seconds) - - - - 1090 
Maximum reverse 480 101.6 1382 1815 725 
 
 
 Propeller and 1. Two McCauley full-fe athered, three-bladed propeller:  
   Propeller Limits  Hub: 3GFR34C701  
Blade:  93KB-0 
Diameter:   Not over 93.0 in., not under 90-5/8 in.  
 (no further reduction permitted) 
Pitch settings at 30.0 in. sta.: 
 Low pitch: 18.5° 
 Feathered: 85.5° 
 Reverse: -13.5°

A25CE 4 Rev. 14 
 
II. Model 406 (cont’d) 
 
 Airspeed Limits V MO  (Maximum operating) 
   (IAS)   Sea level to 21,500 ft. 229 knots 
MMO  Above 21,500 ft.  .52 mach 
VA   (Maneuvering) 162 knots 
VFE  (Flaps extended) 
  30° (Landing) 180 knots 
  20° (Approach) 200 knots 
  10° (Takeoff) 200 knots 
VMCA  (Air minimum control speed)   90 knots 
VLO   (Landing gear operating) 180 knots 
VLE   (Landing gear extended) 180 knots 
 
 C.G. Range (Landing (+166.99 in.) to (+180.28 in .) at 6,500 lb. or less (11% to 32% MAC) 
   Gear Extended) (+172.42 in.) to (+180.28 in.) at 9,360 lb. (19.6% to 32% MAC) 
  Variation is linear between points 
  Landing gear retracting moment (+1346 in.-lb.) 
 
 Empty Wt. C.G. Range None 
 
 Leveling Means Two screws located on W. L. 93.80 @ sta. 248.25 and sta. 272.65 
 
 Maximum Weight Takeoff: 9,360 lb. 
Landing: 9,360 lb. 
Zero fuel: 8,500 lb. 
  (with zero wing locker payload) 
Ramp: 9,435 lb. 
 
 Number of Seats One (1) through 14  
  (Two at +137.0, Two at +166.0, Two at  +192.0, Two at +218.0, Two at +244.0, 
  Two at +270.0, Two at +296.0) 
  See manufacturer's equipment lis t for other seating arrangements. 
 
 Maximum Baggage 250 lbs. (+32.0), 350 lbs. (+71.0), 400 lbs. (+211.0), 400 lbs. (+301.0), 100 lbs. (+317.0)   
 
 Fuel Capacity 3227 lb. (481.5 gal.) total in two wing tanks, 
1613.5 lb. (240.75 gal.) each 
3183 lb. (475 gal.) usable total, 
1591.5 lb. (237.5 gal.) in each tank at sta. +181.9 
Fuel weight based on 6.70 lbs./gal. 
(See NOTE 1 for data on unusable fuel) 
 
 Oil Capacity  5.28 gal. total, 3.00 gal. usable (2.3 gal. in each engine-mounted tank at +142.1) 
  (See NOTE 1 for data on undrainable oil) 
 
 Maximum Operating Altitude 30,000 ft. 
 
 Control Surface Movements Elevator (horn faired) Up 14°, +1°, -0° Down 17°, +1°, -0° 
Elevator trim tabs Up   8°, +1°, -0° Down 10°, +2°, -0° 
Rudder (perpendicular to 
  hinge 0° faired with fin) Right  32°, +1°, -0° Left 32°, +1°, -0° 
Rudder trim tab 
  (perpendicular to hinge) Right 11°, +1°, -0° Left 16°, +1°, -0° 
Aileron Up 25°, +1°, -0° Down 14°, +1°, -0° 
Aileron trim tab Up 19°, +1°, -0° Down 19°, +1°, -0° 
Wing flap (inboard)   Down 30°, +1°, -0° 
Wing flap (outboard)   Down 20°, +1°, -0° 
 
 Serial Nos. Eligible 406-0001 and On

Rev. 14 5 A25CE 
 
Data Pertinent to All Models 
 
Datum: 100.0 inches forward of forward face of fuselage bulkhead forward of rudder pedals. 
 
Certification Basis:  
Model 404: 
Part 23 of the Federal Aviation Regulations (FAR) effective February 1, 1965, as amended by 23-1 through 23-13 except Subpart 
B as amended through 23-14; and FAR 23.1385(c) as amended through 23-21; and 23.1327 as amended through 23-23.  Findings 
of equivalent level of safety were made for FAR 23.1189(a), 23.1545, and 23.1583(a).  In addition, effective S/N 404-0601, FAR 
36 dated December 1, 1969, as amended by 36-1 through 36-4. 
 
In addition to the above certification basis, compliance with ice protection has been demonstrated in accordance with FAR 
23.1419 of Amendment 23-14 effective December 20, 1973, when ice protection equipment is installed in accordance with 
Cessna Drawing 5114400, Factory Kit (FK) No. 194, and Pilot's Operating Handbook (POH)/FAA Approved Airplane Flight 
Manual (AFM).  Aircraft which have been modified in compliance with Accessory Kit (AK) No. 421-106 are considered to be  
equivalent to those with FK No. 194. 
 
Model 406: 
Part 23 of the FAR effective February 1, 1965, as amended by 23-1 through 23-13 except Subpart B as amended through 23-14; 
and 23.427, 23.929, 23.979, 23.1017, 23.1027, 23.1163, 23.1182, 23.1189, 23.1192 as amended through 23-14; 23.951, 23.997, 
23.1013, 23.1015, 23.1019(a)(1), 23.1019(a)(2), 23.1019(a)(4), 23.1019(a)(5), 23.1019(b), 23.1183 as amended through 23-15; 
23.933, 23.971, 23.977, 23.999, 23.1111, 23.1125, 23.1143, 23.1165, 23.1303 (a)(b)(c)(d), 23.1385(c), 23.1549 as amended 
through 23-17; 23.901, 23.939, 23.943, 23.959, 23.967, 23.973, 23.975, 23.995, 23.1093, 23.1121, 23.1141, 23.1145, 23.1193, 
23.1203, 23.1305(a)(b)(c)(d)(e)(f)(g)(h)(i)(j)(k)(l)(m)(n)(o)(p)(q)(r)(s)(t)(u)(w), 23.1337 as amended through 23-18; 23.1323, 
23.1325, 23.1327, 23.1351, 23.1357, 23.1547 as amended through 23-20; 23.45, 23.49, 23.65, 23.67, 23.77, 23.161, 23.1043, 
23.1353, 23.1521 as amended through 23-21; 23.1545 as amended through 23-23; 23.903, 23.1529 as amended through 23-26; 
SFAR 27 as amended by 27-1 through 27-4; Part 36 as amended by 36-1 through 36-12; SFAR 41C; and Exemption No. 4661 
from exact compliance with the requirements of Section 23.207(c).  Findings of equivalent level of safety were made for FAR 
23.1189(a), and that design of the elevator tab control system provides the level of safety intended by the requirements of FAR 
21.21(b)(2) by preventing an unsafe condition.  Therefore, FAR 23.629(f), as amended by Amendment 23-23, is applicable to the 
elevator tab control system, in addition to other requirements in the cited certification basis. 
 
Model 406 (cont’d) 
In addition to the above certification basis, compliance with ice protection has been demonstrated in accordance with FAR 
23.773 and 23.1419 of Amendment 23-14, FAR 23.1309 as amended through Amendment 23-17, and FAR 23.1416 of 
Amendment 23-23 when ice protection equipment is installed in accordance with Cessna Drawing 6015006, FK No. 194, and 
Pilot's Operating Handbook and FAA Approved AFM.  Aircraft which have been modified in accordance with AK No. 421-106 
are considered to be equivalent to those with FK No. 194. Application for type certificate dated October 9, 1973.  Type 
Certificate No. A25CE issued July 21, 1976, obtained by the manufacturer under delegation option procedures. 
 
Production Basis:  
Production Certificate No. 312 issued, and Delegation Option Manufacturer No. CE-3 authorized, to issue airworthiness 
certificates under delegation option provisions of Part 21 of the FAR.  Effective February 15, 1985, and On, Production 
Certificate No. 4 is applicable to all spares production for the Model 404 and to all production on the Model 406. 
 
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. 5818008 (404), or as modified by MEB-34-07 (404), 5718030 (406) or 
Angle-of-Attack Indicator System - Cessna Dwg. 0800302 (404)

A25CE 6 Rev. 14 
 
Data Pertinent to All Models (cont’d) 
 
NOTE 1. Current weight and bala nce report together with 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 certified empty weight and corresponding center of gravity location must include undrainable oil (not  
 included in Oil Capacity) and unusable fuel as follows: 
 
a. S/N 404-0001 thru 404-0200 
 Fuel  48 lbs. at (+177.6) 
 
 S/N 404-0201 and On 
 Fuel 28 lbs. at (+177.6) 
 
 S/N 406-0001 and On 
 Fuel 44 lbs. (6.5 gal.) at (+186.7) 
 
b. Oil  0.0 lbs. 
 
NOTE 2. The placards specified in the FAA Approved AFM must be displayed. 
 
NOTE 3. (404-0001 and On) 
1%, by volume, isopropyl alcohol approved for use as fuel anti-icing additive when used as outlined in 
Cessna Service Letter ME73-25 dated November 2, 1973, or subsequent revisions. 
 
NOTE 4. (S/N 404-0201 and On ), (S/N 406-0001 and On) 
An optional cargo configuration is available which excludes the passenger air distribution and seating.    
Such airplanes may be operated with passenger seats installed provided the operating rules for supplemental 
oxygen are complied with. 
 
NOTE 5. Aircraft operators must observe limitations and placar ds shown in the applicable Pilot's Operating Manual (POH) 
  and FAA Approved AFM, or later a pproved revisions as listed below: 
 
Cessna P/N D1540-3-13:  Model 404 S/N 404-0001 thru 404-0136 (1977 Model) 
Cessna P/N D1563-1-13: Model 404 S/N 404-0201 thru 404-0246 (1978 Model) 
Cessna P/N D1572-2-13PH: Model 404 S/N 404-0401 thru 404-0460 (1979 Model) 
Cessna P/N D1583-3-13PH: Model 404 S/N 404-0601 thru 404-0695 (1980 Model) 
Cessna P/N D1593-1-13PH: Model 404 S/N 404-0801 thru 404-0859 (1981 Model) 
Cessna P/N D1624-13PH: Model 406 S/N 406-0001 and On 
 
NOTE 6. The Model 406 type design has been duplicated as Model F406 in Type Certificate No. A54EU. 
  The type design file is common be tween Models 406 and F406 and duplicates of the type design file are  
  maintained by the respective type certificate holders. 
 
 
 
------- END -------
```

## ADs (20, in force first)

- [AD 2023-09-09](https://openairdocs.org/ad/2023-09-09): Exhaust Turbine System (Recip) · Aerostar PA-60-600 (Aerostar 600), PA-60-601 (Aerostar 601), PA-60-601P (Aerostar 601P) and 292 more. Effective Jul 17, 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 2005-20-25](https://openairdocs.org/ad/2005-20-25): Avionics bus circuit breaker switches · Cessna 401, 401A, 401B and 15 more. Effective Nov 9, 2005
- [AD 2005-01-19](https://openairdocs.org/ad/2005-01-19): Mode S transponders · GARMIN International GTX 330D, GTX 330, GTX 33D and 830 more. Effective Feb 23, 2005
- [AD 2001-23-17](https://openairdocs.org/ad/2001-23-17): GNS 430 units · Cessna 172, 182, 206 and 209 more. Effective Dec 28, 2001
- [AD 2000-01-16](https://openairdocs.org/ad/2000-01-16): Exhaust System · Cessna 320, 320-1, 320A and 28 more. Effective Feb 15, 2000
- [AD 98-25-02](https://openairdocs.org/ad/98-25-02): Top-mounted Antenna · Bell Helicopter Textron Canada 407, 172, 172A and 243 more. Effective Dec 22, 1998
- [AD 98-04-28](https://openairdocs.org/ad/98-04-28): AFM - Limitations Section - Icing · Cessna 310R, 335, 340A and 12 more. Effective Mar 13, 1998
- [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 96-12-22](https://openairdocs.org/ad/96-12-22): Full Flow Engine Oil Adapter · Bellanca CH-300 Pacemaker, 120, 140 and 361 more. Effective Jul 31, 1996
- [AD 95-09-13](https://openairdocs.org/ad/95-09-13): Fuel Inlet Float Valve · Cessna 402C, 404, 414A and 2 more. Effective Jun 14, 1995
- [AD 92-16-18](https://openairdocs.org/ad/92-16-18): Passenger Seat Reinforcement · Cessna 401, 402, 402A and 9 more. Effective Sep 10, 1992
- [AD 87-21-02 R1](https://openairdocs.org/ad/87-21-02-R1): Fuel Filler Openings · Cessna 310D, 310E, 310F and 41 more. Effective Jun 16, 1989
- [AD 86-20-12](https://openairdocs.org/ad/86-20-12): Engine Mount Beams · Cessna 404. Effective Oct 21, 1986
- [AD 84-20-02](https://openairdocs.org/ad/84-20-02): Nose Landing Gear · Cessna 402C, 404, 414A and 3 more. Effective Nov 1, 1984
- [AD 80-17-04](https://openairdocs.org/ad/80-17-04): Fuel Flow Transducers · Aerosonic Fuel Flow Transducers, PA-60-600 (Aerostar 600), PA-60-601 (Aerostar 601) and 9 more. Effective Aug 13, 1980
- [AD 80-15-06](https://openairdocs.org/ad/80-15-06): Elevator Trim Tab Assembly · Cessna 404. Effective Jul 24, 1980
- [AD 80-13-14](https://openairdocs.org/ad/80-13-14): Fuel Flow Transducer · Cessna 310R, 335, 340A and 4 more. Effective Jul 22, 1980
- [AD 78-13-05](https://openairdocs.org/ad/78-13-05): Improperly Installed Seats · Cessna 340, 340A, 402B and 7 more. Effective Jul 5, 1978
- [AD 78-11-05](https://openairdocs.org/ad/78-11-05): Autopilot Actuator · Cessna 210M, 310R, 340A and 9 more. Effective Jun 5, 1978

## Registered aircraft by registry model (OpenAirDocs)

- [Cessna 404](https://openairdocs.org/model/cessna-404): 26 aircraft (registry code 2075901)
- [Cessna 406](https://openairdocs.org/model/cessna-406): 0 aircraft (registry code 2076500)

## STCs approved under this data sheet (161, first 50)

- [STC SA01800SE](https://openairdocs.org/stc/SA01800SE): Fabrication and installation of new or replacement of  existing instrument panel lights dimmer control.. TCW Technologies, LLC
- [STC SA01861SE](https://openairdocs.org/stc/SA01861SE): Fabrication and installation of Landing Light Controller. TCW Technologies, LLC
- [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 SA02019SE-D](https://openairdocs.org/stc/SA02019SE-D): Installation of Garmin Model GTN 625/635/650; 725/750 Navigation System. Garmin International Inc.
- [STC SA5581SW](https://openairdocs.org/stc/SA5581SW): Installation of ALCOR true-flow/ totalizer system. Alcor LLC
- [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 SA00279SE](https://openairdocs.org/stc/SA00279SE): Installation of American Aviation Inc. redesigned engine exhaust stacks.. American Aviation Inc.
- [STC SA02386AK](https://openairdocs.org/stc/SA02386AK): Replacement of existing landing and/or taxi light reflector and bulbs with Light Emitting Diode (LED) lighting systems. AeroLED's Holding LLC
- [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 SA02532AT](https://openairdocs.org/stc/SA02532AT): Installation of subject Michelin tires on appropriate aircraft. For Michelin 5, 6, 8, and 10-inch rim diameter tires on General Aviation Aircraft.. Michelin North America Inc.
- [STC SA00756DE](https://openairdocs.org/stc/SA00756DE): Installation of Automatic Dependent Surveillance  Broadcast (ADS-B) Out Equipment using a Trig Avionics TT22 Transponder and an approved Global Positioning System (GPS) Position Sensor. Peregrine
- [STC SA781GL](https://openairdocs.org/stc/SA781GL): Replace existing main wheel and brakes by installing Parker Hannifin conversion kit 199-78.. Kaman Corporation Aircraft Wheel and Brake LLC
- [STC SA01967WI](https://openairdocs.org/stc/SA01967WI): Use of GAMI G100UL High Octane Unleaded Avgas. General Aviation Modifications Inc.
- [STC SA02254AK](https://openairdocs.org/stc/SA02254AK): Installation of "Single Screen", "2 or 3 Screen", "Dual Screen", or "4 or 6 screen". 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 SA04195NY](https://openairdocs.org/stc/SA04195NY): Installation of the KFC 230 Aerocruze Automatic Flight Control System (FCS) upgraded from KFC 200 FCS. Honeywell International Inc. (Bendix King)
- [STC SA09856AC](https://openairdocs.org/stc/SA09856AC): Installation of BendixKing Aerowave 100 In-flight Data Link System for non-essential, non-required aircraft Cabin Systems & Equipments. Honeywell International Inc (Bendix King)
- [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 SA10236SC](https://openairdocs.org/stc/SA10236SC): Installation of a GDC 31 Roll Steering Converter. DAC International Inc
- [STC SA04514NY](https://openairdocs.org/stc/SA04514NY): Single/Dual Transponder System ADS-B Upgrade. Scandinavian Avionics Design ApS
- [STC SA1297CE](https://openairdocs.org/stc/SA1297CE): Installation of King KFC 200 2-axis(3 optional) flight control system with a King KI 255 (or -256) Flight Command Indicator or a KG 258 Attitude Horizon Gyro with a KC 292 Mode Controller. Honeywell International Inc
- [STC SA1528CE-D](https://openairdocs.org/stc/SA1528CE-D): Installation of King KAS 297 altitude selector option. Honeywell International Inc
- [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 SA143RM](https://openairdocs.org/stc/SA143RM): Installation of air conditioner system.. Air Comm 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 SA00571SE](https://openairdocs.org/stc/SA00571SE): Replacement of certain BF Goodrich pneumatic deicer boots.. SMR Technologies 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 SA02013CH](https://openairdocs.org/stc/SA02013CH): Installation of Avidyne Corporation Traffic Advisory System (TAS). Avidyne Corporation
- [STC SA01828SE](https://openairdocs.org/stc/SA01828SE): Installation of J.P. Instruments (JPI) EDM-960 Primary Engine Data Management System. J. P. Instruments
- [STC SA01835WI](https://openairdocs.org/stc/SA01835WI): Installation of Trig Avionics TY-96 or TY-97 VHF Communications Radio. Peregrine
- [STC SA2872SW](https://openairdocs.org/stc/SA2872SW): Installation of wing nacelle locker tanks.. OCR Aviation
- [STC SA2993SW](https://openairdocs.org/stc/SA2993SW): Installation of nose fuselage fuel tank.. OCR Aviation
- [STC SA01933LA-D](https://openairdocs.org/stc/SA01933LA-D): Installation of Garmin Model 400W / 500W Series GPS-WAAS Navigation System. Garmin International Inc
- [STC SA01935LA](https://openairdocs.org/stc/SA01935LA): Installation of external aft body strakes.. Aircraft Performance Modifications
- [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 SA01114CH](https://openairdocs.org/stc/SA01114CH): Installation of P2 Incorporated 6600 Audio Advisory system. P2 Incorporated
- [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 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 SA1274GL](https://openairdocs.org/stc/SA1274GL): Install Egan Aviation air ambulance stretcher P/N 125 using Installation Kit P/N 805.. Paul/Lanna Egan LLC
- [STC SA01118WI](https://openairdocs.org/stc/SA01118WI): Installation of the Concorde FLA or VRSLA RG series batteries. Concorde Battery Corporation
- [STC SA00944CH](https://openairdocs.org/stc/SA00944CH): Replace Janitrol combustion heater Model 81D94-X (XX) with C&D Associates combustion heater Model CD25K, CD35K, and CD45K. Hartzell Engine Technologies, LLC
- [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

All 161: https://openairdocs.org/tcds/A25CE/stcs.md

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