# TCDS A16EU: General Atomics AeroTec Systems GmbH

- Type: Type certificate data sheet
- Status: Current
- Holder: General Atomics AeroTec Systems GmbH
- Revision: 15
- Revised: January 29, 2025
- Product: Aircraft, Small Airplane
- Certification basis: Part 23, Part 21
- Registered aircraft: 13, by the registry models matched to it (OpenAirDocs)
- Data sheet PDF: https://openairdocs.org/files/sha256/7e/66/7e6624a0c322f46854ed79f4a6ac19584c47aecbc16fdeb431e9fa6ceacf9b6f
- FAA DRS: https://drs.faa.gov/browse/excelExternalWindow/DRSDOCID176186756420250129140934.0001
- Page: https://openairdocs.org/tcds/A16EU

## Models (8)

As the data sheet lists them.

- Dornier 228-100
- Dornier 228-200
- Dornier 228-101
- Do 28 D
- Dornier 228-202
- Dornier 228-201
- Dornier 228-212
- Do 28 D-1

## 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 8 9 10 11 
Rev. No. 15 8 8 12 8 15 13 8 8 8 15 
 
DEPARTMENT OF TRANSPORTATION 
FEDERAL AVIATION ADMINISTRATION 
 
A16EU 
Revision 15 
General Atomics AeroTec Systems  
 Do 28 D 
 Do 28 D-1 
 Dornier 228-100 
 Dornier 228-101 
 Dornier 228-200 
 Dornier 228-201 
 Dornier 228-202 
 Dornier 228-212 
January 29, 2025 
 
TYPE CERTIFICATE DATA SHEET NO. A16EU 
 
This data sheet which is part of Type Certificate No. A16EU 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: General Atomics AeroTec Systems GmbH 
 Galileostraße 396 
 82131 Gauting 
 Germany 
 
Type Certificate Holder Record: DORNIER LUFTFAHRT GmbH 
 D-8031 Wessling 
 Federal Republic of Germany, transferred TC A16EU to Fairchild Dornier GmbH on 
June 1, 2000. 
 
Fairchild Dornier GmbH 
D-82230 Wessling, Germany, transferred TC A16EU to RUAG Aerospace Services 
GmbH on July 27, 2003. 
 
RUAG Aerospace Services GmbH transferred TC A16EU to General Atomics AeroTec 
Systems GmbH on September 28, 2021. 
 
 
I. Model Do 28D (Normal Category), approved July 31, 1967 
 Model Do 28D-1 (Normal Category), approved April 19, 1968 
 
 Engine 2 Lycoming IGSO-540 A1E 
  Bendix Injector RS10-FBI or Lycoming P/N 78417 
 
 Fuel 100/130 minimum grade aviation gasoline 
 
 Engine limits For takeoff, 5 minutes, 380 HP, 3400 rpm, 47 inch HG at S.L. 
  For continuous operation, 360 HP, 3200 rpm, 45 inch HG at S.L. 
 
 Propellers and propeller 2 Hartzell HC-B3W30-2B/W10151-8R 
   limits Diameter:  93 in., no cutoff permitted 
  Pitch settings at 30 in. station: 
   Low 16° 50' ± 15' 
   Feathered 85°       ± 30'

Page 2 of 11 A16EU 
 
 Airspeed limits (CAS) 
  Do 28 D Do 28 D-1 
 Knots m.p.h. Knots m.p.h. 
VNE  (never exceed) 180 207 180 207 
VNO  (maximum structural cruising) 143 165 143 165 
Maximum speed for cooling flaps 
  operation 
 
143 
 
165 
 
143 
 
165 
VP  (maneuvering) 115 133 117 113 
VFE  (flaps extended) 102 118 104 120 
VMC  (minimum control) 58 67 60 69 
 
 C.G. Range (+126.0) to (+141.0) at 6060 lbs. (+131.5) to (+141.0) at 8050 lbs.  All airplanes 
  except S/N 4001, 4002, and 4003. 
  (+126.0) to (+141.0) at 5950 lbs, (+131.5) to (141.0) at 7720 lbs. - S/N 4001, 4002 and  
  4003. 
  Straight line variation between points given. 
 
I. Model Do 28D, Do 28D-1 
 Empty weight C.G. range None 
 
 Datum A vertical line 118 inch forward of wing slat leading edge 
 
 Leveling means A water level on cabin floor rails 
 
 Maximum weights 8050 lb.  (See Note 1.) 
 
 Minimum crew 1 pilot 
 
 Number of seats Maximum 15 
 
 Maximum baggage 110 lbs. in fuselage nose hold (+35.5 in.) and 
  175 lbs. in the rear baggage hold (+275 in.) 
 
 Fuel capacity 232 U.S. gallons usable (+ 131.5 in.) 
 
 Oil capacity 3.3 U.S. gallons usable per engine (+ 105.5 in.) 
 
 Control surface movements Wing flaps Down 20° Up 52° 
  Ailerons Up 25° Down 25° 
  Elevator (no stabilizer) Up 22° Down 17° 
  Rudder Right 27.5° Left 27.5° 
 
 
II. Model Dornier 228-100 (Normal Category), approved May 11, 1984 
 Model Dornier 228-101 (Normal Category), approved February 28, 1985 
 Model Dornier 228-200 (Normal Category), approved May 11, 1984 
 Model Dornier 228-201 (Normal Category), approved February 28, 1985 
 Model Dornier 228-202 (Normal Category), approved September 10, 1986 
 
 Engines 2 Garrett AiResearch TPE 331-5-252D 
 
 Fuel Fuel grades:  See Pilot’s Operating Handbooks 
  Dornier 228-100/-101/-200/-201/-202 Section 2 Limitations. 
 
 Engine limits For takeoff and continuous operation, 715 SHP (533 KW). 
 
  
 Propellers and Propeller Limits For Dornier 228 Models - 100/-101/-200/-201 
  2 Hartzell HC-B4TN-5ML/LT 10574 
  or  “ “ 10574 K 
  or  “ “ 10574 B (length of deicing mat 17 inches) 
  or  “ “ 10574 B (length of deicing mat 21 inches)

Page 3 of 11 A16EU 
  or  “ “ 10574 A 
  or  “ “ 10574 AK 
  or  “ “ 10574 AB (length of deicing mat 17 inches) 
  or  “ “ 10574 AB (length of deicing mat 21 inches) 
  or  “ “ 10574 AS 
  or  “ “ 10574 ASK 
  or  “ “ 10574 ASB (length of deicing mat 17 inches) 
  or  “ “ 10574 ASB (length of deicing mat 21 inches) 
  or  “ “ 10574 FS 
  or  “ “ 10574 FSK 
  or  “ “ 10574 FSB (length of deicing mat 17 inches) 
  or  “ “ 10574 FSB (length of deicing mat 21 inches) 
 
 
II. Model Dornier 228-100, 228-101, 228-200, 228-201, 228-202    (cont’d) 
 Propellers and Propeller Limits For Dornier 228, Model -202 
   2 Hartzell HC-B4TN-5ML/LT 10574 AS 
  or  “ “ 10574 ASK 
  or  “ “ 10574 ASB (length of deicing mat 17 inches) 
  or  “ “ 10574 ASB (length of deicing mat 21 inches) 
  or  “ “ 10574 FS 
  or  “ “ 10574 FSK 
  or  “ “ 10574 FSB (length of deicing mat 17 inches) 
  or  “ “ 10574 FSB (length of deicing mat 21 inches) 
 
   The following limitations apply: 
   a) For all type of propellers: 
    1. Diameter limits are 106” maximum, 105” minimum. 
     (No further reduction permitted.) 
    2. All blades of the propeller of the individual airplanes must be of one type only. 
    3. Avoid sustained ground operation below 1050 (67%) RPM. 
 
   b) For all type of propellers except those with suffix “F”: 
    Regulations according to the FAA Airworthiness Directive No. 87-15-05, 
    R1, Amendment 39-5658, have to be considered. 
 
   c) For Dornier 228 Model -202 equipped with propeller with suffix “A”: 
    Avoid “power on” stalls above 60 percent torque. 
 
   d) Blade angle position with power lever in FI at 30 in. station: 
    1. For the Dornier Models 228-100/-101/-200/-201 is:  13° ± 20' 
    2. For the Dornier Models 228-202 and 228-201/-202 equipped with 
     keel (K) is:  15° ± 20'. 
      Refer also to Notes 1.b3 and 1.b4 respectively. 
 
 Airspeed Limits (CAS) 
 228-100 
Knots 
228-101 
Knots 
228-200 
Knots 
228-201 
Knots 
228-201(K) 
Knots 
228-202 
Knots 
228-202(K) 
Knots 
VMO (max. operating) 199 199 199 199 197 199 197 
VA (maneuvering) 141 144 140 140 143 147 146 
VFE (flaps extended)        
    Pos. 1 (5°) 149 149 149 149 149 149 149 
    Pos. 2 (20°) 128 128 128 128 129 128 129 
    Pos. DN (30° 128 128 128 x 128 x 129 x 128 x 129 x 
VLO (gear operating) 160 160 160 160 158 160 158 
VLE (gear extended) 160 160 160 160 158 160 158 
VMC (minimum  
  control) 
81 81   81   81   74   80   74 
 Airspeed Limits (CAS) x = with optionally installed trim coupling system (SCN C01 only) 
 (cont’d) 
  
 C.G. Range Refer to Pilot’s Operating Handbook applicable to the individual airplane.

Page 4 of 11 A16EU 
 Empty Weight C.G. Range None 
 
 Datum A vertical line 290.71 inches forward of the main jacking point under the fuselage. 
 
 Leveling Means A water level in cabin floor rails. 
 
     228-201 228-202 
  228-100 228-101 228-200 and-201 (K) and-202 (K) 
 Maximum Weight 12,500 lbs. 13,184 lbs. 12,500 lbs. 13,184 lbs. 13,669 lbs. 
 
I. Model Dornier 228-100, 228-101, 228-200, 228-201, 228-202 
 
 Minimum Crew 1 pilot 1 pilot 1 pilot 1 pilot 1 pilot 
  
 Maximum Operating Altitude 15,000 feet 15,000 feet 15,000 feet 15,000 feet 15,000 feet 
 
  The maximum operating altitude is 25,000 ft. if SCN No. DO8 (maximum allowable 
  airspeed indicator:  manufacturer:  Intercontinental Dynamics Corp.) is installed. 
 
 Maximum Number of 
   Passenger Seats     15     15     19     19     19 
 
 Maximum Baggage 
 In Fuselage Nose Hold 
   Station (inch) + 130.7 in. + 130.7 in. + 100.7 in. + 100.7 in. + 100.7 in. 
   Weight (lbs)    200 lbs.    200 lbs.    200 lbs.    200 lbs.    200 lbs. 
     265 lbsx    265 lbs.x    265 lbs.x    265 lbs.x    265 lbs.x 
  x = if SCN 2152 is installed 
 
 and in Rear Baggage Hold 
   Station (inch) + 487.4 in. + 487.4 in. + 503.9 in. + 503.9 in. + 503.9 in. 
   Weight (lbs.)    331 lbs.    331 lbs.    463 lbs.    463 lbs.    463 lbs. 
 
 Fuel Capacity 630.3 U.S. gallons usable (+ 312.4 in.) 
 
 Oil Tank Capacity 6.25, U.S. quarts per engine (+ 267.9 in.) 
 
 Control surface movements See Maintenance Manual DORNIER 228. 
 
III. Model Dornier 228-212 (Commuter Category), approved June 26, 1990  
 
 Engines 2 Garrett AiResearch TPE 331-5A-252D. 
 
 Fuel Fuel grades:  See Pilot’s Operating Handbook Dornier 228-212, Section 2 
 
 Engine limits For takeoff and continuous operation 776 SHP (579 KW). 
 
 Propeller and propeller limits 2 Hartzell HC-B4TN-5ML/LT 10574 FS 
  or 2 Hartzell HC-B4TN-5ML/LT 10574 FSB (length of deicer mat 21 inches) 
 
   The following limitations apply: 
   1. All blades of the propellers of the individual airplane must be of one type only. 
   2. Diameter limits are 106° maximum, 105° minimum. 
    (No further reduction permitted.) 
   3. Avoid sustained ground operation below 1050 (67%) RPM. 
   4. Blade angle position with power lever in FI at 30 in. 
    Station is 15°  ±  20’. 
 
 Airspeed Limits (CAS)    S/N 8176 thru 8190 S/N 8191 and up 
      Knots  Knots 
  VMO (max. operating)  197  220 
  VA (maneuvering)  149  149 
  VFE (flaps extended)

Page 5 of 11 A16EU 
   Pos. 1 (  5°)  149  158 
   Pos. 2 (20°)  129  129 
   Pos. DN (30°)  129x  129 
  VLO (gear operating)  158  158 
  VLE (gear extended)  158  158 
  VMC (minimum control)    75    75 
  x = with optionally installed trim coupling system (SCN C01) only. 
 
 C.G. Range Refer to Pilot’s Operating Handbook applicable to the individual airplane. 
 
 Empty Weight C.G. range None 
 
 Datum A vertical line 290.71 inches forward of the main jacking point under the fuselage. 
 Leveling Means A water level on cabin floor rails. 
 
 Maximum Weights    S/N 8176 thru 8190 S/N 8191 and up 
  for takeoff    14,110 lbs.  14,110 lbs. 
  Zero fuel up to 13,668 lbs TOW  12,324 lbs.  13,095 lbs. 
    up to 14,110 lbs TOW  11,905 lbs.  13,095 lbs. 
 
 Minimum Crew 1 pilot 
 
 Maximum operating altitude 15,000 feet 
  The maximum operating altitude is 25,000 ft. if SCN DO8 (maximum allowable  
  airspeed indicator:  manufacturer:  Intercontinental Dynamics Corp.) is installed. 
 
 Maximum number of 
   passenger seats 19 
 
 Maximum Baggage 
 in Fuselage Nose Hold 
   Station + 100.7 in. 
     265 lbs. 
 and in Rear Baggage Hold 
   Station + 503.9 in. 
   Weight    463 lbs. 
 
 Fuel Capacity 630.3 U.S. gallons usable (+312.4 in.) 
 
 Oil Capacity 6.25 U.S. quarts per engine (+267.9 in.) 
 
 Control surface movements See Airplane Manual Dornier 228. 
 
 
 
DATA APPLICABLE TO ALL MODELS 
 
 Serial numbers eligible See Import Requirements. (See Note 6) 
 
 Certification basis a) For Do 28D and Do 28D-1 
   FAR 23, including Amendments 23-1 through 23-3. 
   Date of application for type certificate:  June 13, 1966 
 
  b) For Dornier 228-100 and Dornier 228-200, under the provisions of FAR 21.29 
   FAR 23, effective February 1, 1965, including amendments 23-1 thru 23-23. 
   SFAR 41C Section (1a) which incorporates by reference FAR 135 Appendix A 
    in effect on September 26, 1978. 
   SFAR 27, effective February 1, 1974, including Amendments 27-1 through 27-4 
    (Fuel Venting).  See Note 4. 
   FAR 36, effective December 1, 1969, including Amendments 36-1 through 36-12. 
   Date of application for Amended Type Certificate:  December 3, 1979.

Page 6 of 11 A16EU 
  c) For Dornier 228-101, Dornier 228-201 and Dornier 228-202 under the provisions 
   FAR 21.29. 
   FAR 23, effective 1965, including amendment 23-1 through 23-23. 
   SFAR 41C effective September 13, 1982. 
   SFAR 27, effective February 1, 1974, including Amendments 27-1 through 27-4 
    (fuel venting), see Note 4. 
   FAR 36, effective December 1, 1969, including Amendments 36-1 through 36-12. 
   Date of application for Amended Type Certificate:  August 22, 1983. 
 
  d) For Dornier 228-212, under the provisions of FAR 21.29. 
   FAR 23, effective February 1, 1965, including Amendments 23-1 thru 23-34. 
   SFAR 27, effective February 1, 1974, including Amendments 27-1 thru 27-5 
   (Fuel Venting), see Note 4. 
   FAR 36, effective December 1, 1969, including Amendments 36-1 thru 36-16. 
   Date of application for Amended Type Certificate:  February 15, 1989. 
 
In addition, for the Dornier 228-212NG/228-212NXT version (created by the 
incorporation of General Atomics AeroTec Systems Major Change CN-228-247 and 
FAA supplemental type certificates (STCs) ST329CH-D (new engine) and 
SA03052NY (new propeller): 
 
23.1457 and 23.1459 at amendment 23-35; 
23.1322 and 23.1331 at amendment 23-43; 
23.1525 at amendment 23-45; 
23.867, 23.1303, 23.1309, 23.1311, 23.1321, 23.1323, 23.1329, 23.1351, 
23.1353, 23.1359, 23.1361, 23.1365, 23.1431 at amendment 23-49; 
23.1325, 23.1543, 23.1545 and 23.1555 at amendment 23-50; 
23.1308 at amendment 57; 
23.1306 at amendment 61, 
 
(The applicable certification bases for STCs ST329CH-D and SA03052NY are 
listed on their respective certificates.) 
 
The Dornier 228-212NG/228-212NXT version approval included approval of STOL 
Operation, General Atomics AeroTec Systems Change Notice CN-228-273. 
  
 
  The Luftfahrt Bundesamt originally type certificated this aircraft under its type certificate 
Numbers 2031, 2031a, 2031b and 2031c. The FAA validated this product under U.S. 
Type Certificate Number A16EU. Effective September 28, 2003, the European Aviation 
Safety Agency (EASA) began oversight of this product on behalf of Germany.  
 
The EASA type certificate for models Do 28D and Do28D-1 is EASA.A.360. 
The EASA type certificate for models Dornier 228-100, 228-101, 228-200, 228-201, 228-
202 and 228-212 is EASA.A.359. 
 
 
 Import Requirements The FAA can issue a U.S. airworthiness certificate based on an NAA Export Certificate 
of Airworthiness (Export C of A) signed by a representative of the Luftfahrt Bundesamt 
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. A16EU and to be in a condition for safe operation.’  (See Note 5 and Note 
6). 
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.

Page 7 of 11 A16EU 
Service Information Each of the documents listed below must state that it is approved by the European 
Aviation Safety Agency (EASA) or – for approvals made before September 28, 2003 – 
by the Luftfahrt Bundesamt.  
  • Service bulletins,  
  • Structural repair manuals,  
  • Vendor manuals,  
  • Aircraft flight manuals, and  
  • Overhaul and maintenance manuals.  
 
 The FAA accepts such documents and considers them FAA-approved unless one of
 the following conditions exists: 
 
• The documents change the limitations, performance, or procedures of the FAA 
approved manuals; or 
 
 •The documents make an acoustical or emissions changes to this product’s U.S. type 
certificate as defined in 14 CFR § 21.93.  
 
 The FAA uses the post type validation procedures to approve these documents.  The FAA 
may delegate on case-by-case to EASA to approve on behalf of the FAA for the U.S. type 
certificate.  If this is the case it will be noted on the document.  
 
 
 Equipment/ Basic required equipment as prescribed in the applicable airworthiness regulations (see 
 Airplane Flight Manual “Certification Basis”) must be installed in the aircraft for certification. 
 
  a) For Models Do 28D and Do 28D-1. 
   The approved equipment is marked with an “X” in the LBA-approved equipment 
   list dated 14 August 1968 in the approved AFM. 
 
   The airplane Flight Manual approved at the original issue for U.S. Type  
   Certification is dated November 6, 1967. 
 
  b) For Models Dornier Do 228-100 and Dornier 228-200 
   The installed equipment is marked with an “X” in the Equipment List in Section 6 
   in the LBA-approved AFM. 
 
 
   The Airplane Flight Manuals (Edition 1) for the Dornier Model 228-100 (7XXX) 
   or 228-200 (8XXX) approved at the original issue for U.S. type certification are 
   dated 15 November 1983, LBA approved April 4, 1984. 
 
   NOTE: “XXX” denotes aircraft serial numbers. 
    AFM consists of basic POH + Supplement 74. 
  
  c) For Models Dornier 228-101 
   The installed equipment is marked with an “X” in the Equipment List in 
   Section 6 of the LBA-approved “Edition 1” AFM. 
  c1) The Airplane Flight Manuals (Edition 1) for the Dornier Model 228-101 (7XXX) 
   with ICAO Annex 8 are LBA-approved October 15, 1984.  AFM consists of 
   basic POH + Supplement 42, 74, 74A. 
 
   
  c2) The Airplane Flight Manuals (Edition 1) for the Dornier Model 228-101 (7XXX) 
   without ICAO Annex 8 are LBA-approved December 11, 1984.  AFM consists of 
   basic POH + Supplements 42, 74, 74B. 
 
  d) For Models Dornier 228-201 and Dornier 228-202 
   The installed equipment is marked with an “X” in the “Airplane Master 
   Equipment List” in Section 6, part 2 of the LBA-approved AFM. 
 
  d1) The Airplane Flight Manual (Edition 2) for the Dornier Model 228-201 (8XXX)

Page 8 of 11 A16EU 
   with and without ICAO Annex 8 are LBA-approved February 8, 1989. 
 
  d2) The Airplane Flight Manuals (Edition 2) for the Dornier Model 228-201 (8XXX) 
   equipped with keel (K) with and without ICAO Annex 8 are LBA-approved 
   December 14, 1988. 
 
  d3) The Airplane Flight Manuals (Edition 2) for the Dornier Model 228-202 (8XXX) 
   with and without ICAO Annex 8 are LBA-approved February 8, 1989. 
 
 
  d4) The Airplane Flight Manuals (Edition 2) for the Dornier Model 228-202 (8XXX) 
   equipped with keel (K) with and without ICAO Annex 8 are LBA-approved 
   December 14, 1988. 
  
  NOTE (1): “XXX” denotes aircraft serial numbers. 
    228-201 with ICAO and 228-201 without ICAO are physically 
    identical except for flight manual requirements.   
    228-202 with ICAO and 228-202 without ICAO are physically 
    identical except for flight manual requirements. 
 
  NOTE (2): For model -201 and landing weights of 13,007 lbs. for main 
    landing gear S/N’s 1036 onwards the main landing gear must 
    comply with part numbers A-510 000 C000 and A-520 000 C000 
    or higher change index. 
 
  e) For Model Dornier 228-212 
   The installed equipment is marked with an “X” in the “Airplane Master Equipment 
   List” in Section 6, Part 2, of the LBA approved AFM. 
 
  e1) The Airplane Flight Manuals (Edition 1) for the Dornier Model 228-212 (8XXX) 
   commuter category valid for aircraft serial numbers S/N 8155 and S/N 8176 through 
   8190 are LBA-approved July 21, 1989. 
 
  e2) The Airplane Flight Manuals (Edition 1) for the Dornier Model 228-212 (8XXX) 
   Commuter Category valid for aircraft serial numbers S/N 8191 and up are 
   LBA-approved November 17, 1989.  
 
  NOTE: “XXX” denotes aircraft serial numbers. 
 
  There may be approved Airplane Flight Manuals (AFM) amendments of supplements 
  issued after the original type certificate, that are required to operate the airplane 
  when additional optional equipment is installed and/or when certain modifications 
  are embodied. 
  
  The airplane owner/operator should ensure that the correct LBA approved Airplane 
  Flight Manual (AFM) amendments or supplements are incorporated in the approved 
  AFM, for the approved model. 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
NOTES

Page 9 of 11 A16EU 
Note 1. Weight and Balance 
  Current weight and balance data together with a list of equipment included in the certificated empty weight, 
  and loading instructions, must be provided for each aircraft at the time of original certification. 
 
  a) For Do 28D and Do 28D-1 
   
  a1) The certificated empty weight and corresponding center of gravity locations must include unusable 
   fuel of 8 U.S. gallons (+ 131.5 in.) and undrainable system oil of 2.15 U.S. gallons (+ 105.5 in.). 
   
  a2) Serial numbers 4001, 4002 and 4003 eligible at a maximum weight of 7720 pounds. 
 
  a3) Do 28-1 airplanes of the following serial numbers are eligible at a maximum takeoff weight of  
   8160 pounds when equipped with Wing Serial Numbers shown in brackets: 
 
    4006(06), 4018(18), 4023(23), 4024(24), 4025(35), 
            4026(26), 4027(27), 4028(28), 4030(30), 4031(34), 
    4033(33), 4034(31), 4035(25), 4040(40), 4041(41), 
    4042(42), 4043(43), 4044(44), 4045(45), 4046(46), 
    4047(55), 4048(49), 4049(51), 4051(52), 4052(53), 
    4053(54), 4054(56), 4055(57), 4056(58), 4057(59), 4058(60), 4059(47) 
 
   Landing weight remains unchanged. 
 
  a4) Do 28 D-1 airplanes of the following serial numbers are eligible to a maximum takeoff weight 
   of 8160 pounds when equipped with wing serial numbers shown in brackets and Service 
   Bulletin No SB 2 044-1101 has been complied with: 
 
    4022(22), 4021(21) 
 
   Landing weight remains unchanged. 
 
  b) For Do 228-100/-101, Dornier 228-200/-201/-202, and Dornier 228-212. 
 
  b1) The certificated empty weight and corresponding center of gravity locations must include unusable 
   fuel of 14.4 U.S. gallons (+ 312.4 in.) and full system oil of 5.9 gallons (+ 267.9 in.) per airplane. 
 
  b2) Dornier 228-100/-200 airplanes can be changed to Models -101/-201 if they are modified 
   according to, and comply with the following Change Notice: 
   CN-228- 043-USA, “Increase of Maximum Takeoff Weight to 13,184 lbs.”  Also see Airplane 
   Master Equipment List/Airplane Flight Manual and Note 3. 
 
  b3) Dornier 228-200 and -201 airplanes can be changed to Model -202 if they are modified according 
   to, and comply with the following Change Notice: 
   CN-228- 164-USA, “Increase of Maximum Takeoff Weight to 13,669 lbs.”  Also see Airplane 
   Master Equipment List/Airplane Flight Manual and Note 3. 
 
  b4) Dornier 228-201 and -202 models can be modified and equipped with keels (k) if after 
   modification they comply with the following LBA Change Notice: 
   A-228- 174 “Retrofit measures to improve flight performance and rear center-of-gravity range 
   extended from 35% to 40%.” 
   Also see Airplane Master Equipment List/Airplane Flight Manual and Note 3. 
 
 
Note 2. Operation 
  a) Placards 
   All placards listed in the approved AFM must be installed in the appropriate locations.  Each 
   airplane has to be supplied with a placard that specifies the kind of operations to which the 
   operation of the individual airplane is limited by its installed equipment. 
   The following placard must be displayed on the instrument panel in full view of the pilot: 
 
  a1) For Do 28 D/D-1 
         “THIS AIRPLANE MUST BE OPERATED AS A NORMAL CATEGORY AIRPLANE IN 
           COMPLIANCE WITH THE OPERATING LIMITATIONS STATED IN THE FORM OF

Page 10 of 11 A16EU 
    PLACARDS MARKINGS AND MANUAL. 
 
    NO ACROBATIC MANEUVERS, INLCUDING SPINS, ARE APPROVED.” 
 
  a2) For Dornier 228-100/-101/-200/-201/-202 
    “THE MARKINGS AND PLACARDS INSTALLED IN THIS AIRPLANE CONTAIN 
    OPERATING LIMITATION WHICH MUST BE COMPLIED WITH WHEN OPERATING 
    THIS AIRPLANE IN THE NORMAL CATEGORY.” 
 
    “OTHER OPERATING LIMITATIONS WHICH MUST BE COMPLIED WITH WHEN 
    OPERATING THIS AIRPLANE IN THE NORMAL CATEGORY ARE CONTAINED IN  
    THE PILOT’S OPERATING HANDBOOK AND LBA-APPROVED AIRPLANE FLIGHT 
    MANUAL.” 
 
    “NO ACROBATIC MANEUVERS, INCLUDING SPINS, APPROVED.” 
 
  a3) For Dornier 228-212 
    “THE MARKINGS AND PLACARDS INSTALLED IN THIS AIRPLANE CONTAIN  
    OPERATING LIMITATION WHICH MUST BE COMPLIED WITH WHEN OPERATING THIS  
    AIRPLANE IN THE COMMUTER CATEGORY. 
 
    “OTHER OPERATING LIMITATIONS WHICH MUST BE COMPLIED WITH WHEN  
    OPERATING THIS AIRPLANE IN THE COMMUTER CATEGORY ARE CONTAINED IN 
    THE PILOT’S OPERATING HANDBOOK AND LBA-APPROVED AIRPLANE FLIGHT  
    MANUAL.” 
 
    “NO ACROBATIC MANEUVERS, INCLUDING SPINS, APPROVED.” 
 
  b) Certificate of Airworthiness for Dornier 228-101/-201/-202 
   If Dornier 228-101/-201/-202 aircraft are to be operated without ICAO Annex 8, the airworthiness 
   certificate shall be endorsed: “This airplane at weights in excess of 5,700 kg does not meet the 
   airworthiness requirements of ICAO, as prescribed by Annex 8 of the Convention of International 
   Civil Aviation.”  Also see Item Equipment/Airplane Flight Manual. 
 
 
Note 3. Airworthiness Limitations 
  Chapter 05 of the Dornier 228 Airplane Maintenance Manual, for the models Dornier 228-100/-101 and 
  Dornier 228-200/-201/-202/-212; which includes the Airworthiness Limitation Section 05-05-00, specifies 
  mandatory replacement times, structural inspection intervals, and related structural procedures, and 
  operation checks for continuous airworthiness.  This also fulfills the requirements of 14 CFR sections 
  21.29, 43.16, and 91.403 of FAA Regulations. 
 
  The Airworthiness Limitation Section 05-05-00 is FAA-approved and may not be changed without 
  FAA approval. 
 
 
Note 4. Fuel Venting and Exhaust Emission 
  For models Dornier 228-100/-101 and Dornier 228-200/-201/-202 compliance with SFAR 27 is achieved 
  when the installations described by Dornier Drawing No. A 685 200 AOOF is incorporated. 
 
 
Note 5. Modifications for U.S. Certification of Dornier 228-100/-101/-200/-201/-202 
  The following modifications have to be incorporated in aircraft of U.S. registry: 
 
  a) Modified stall warning system (option code CO9) 
  b) Modified electrical system (option code M10) 
  c) Dual pitch trim actuator (option code CO8) 
  d) Modified pax/cargo door (option code H28/H29) 
  e) Modified rear baggage door (option code F 06). 
 
  Modification a) and d) are production standard from XXX = 051 and up, modification b), c), and e) 
  are production standard from XXX = 081 and up.

Page 11 of 11 A16EU 
 
 
 
Note 6.  Aircraft manufactured by Hindustan Aeronautics Ltd. (HAL) with S/Ns 8I-xxxx are not covered under the   
  EASA Type certificate or this corresponding FAA validation TCDS and therefore are not eligible for an FAA 
Standard Certificate of Airworthiness.   
  
Aircraft assembled by Hindustan Aeronautics Ltd. (HAL) model 228-101 with S/N’s 7099, 7105, 7106, 
7113, and 7114 and model 228-201 with S/N’s 8052, 8055, 8060, 8064, 8067, 8072, 8075, 8081, 8082, 8089, 
8090, and 8098 are not covered under the EASA Type certificate or this corresponding FAA validation 
TCDS and therefore are not eligible for an FAA Standard Certificate of Airworthiness.   
  
The use of parts including spare parts from the Indian license production Hindustan Aeronautics Ltd. (HAL) 
is not recognized by General Atomics AeroTec Systems and are not permissible for Dornier 228 aircraft with 
FAA certification of airworthiness. These parts have part number with the letter “I” or “H” as a prefix (e.g. 
IA-xxxxxxAxxA or HA-xxxxxxAxxA). These parts should be treated as Suspected Unapproved Parts (SUP).  
 
.....END.....
```

## ADs (44, in force first)

- [AD 2025-07-01](https://openairdocs.org/ad/2025-07-01): Air Data Computer · Synthetic Vision Electronic Flight Information System (Arrow STC SR09595RC or ST01523WI). Effective May 15, 2025
- [AD 2021-19-06](https://openairdocs.org/ad/2021-19-06): Landing Gear System · General Atomics AeroTec Systems Dornier 228-212. Effective Oct 15, 2021
- [AD 2016-17-05](https://openairdocs.org/ad/2016-17-05): Engine Controls · RUAG Aerospace Services Dornier 228-100, Dornier 228-101, Dornier 228-200 and 3 more. Effective Sep 30, 2016
- [AD 2014-10-02](https://openairdocs.org/ad/2014-10-02): Time Limits · Dornier Luftfahrt Dornier 228-100, Dornier 228-101, Dornier 228-200 and 3 more. Effective Jul 28, 2014
- [AD 2014-04-02](https://openairdocs.org/ad/2014-04-02): Landing Gear · Dornier Luftfahrt Dornier 228-212. Effective Apr 1, 2014
- [AD 2011-03-05](https://openairdocs.org/ad/2011-03-05): Fuselage · Dornier Luftfahrt Dornier 228-100, Dornier 228-101, Dornier 228-200 and 3 more. Effective Mar 14, 2011
- [AD 2009-20-07](https://openairdocs.org/ad/2009-20-07): Landing gear · Dornier Luftfahrt Dornier 228-100, Dornier 228-101, Dornier 228-200 and 2 more. Effective Nov 3, 2009
- [AD 2009-12-16](https://openairdocs.org/ad/2009-12-16): Standard Practices/Structures · Dornier Luftfahrt Dornier 228-100, Dornier 228-101, Dornier 228-200 and 3 more. Effective Jul 17, 2009
- [AD 2009-07-09](https://openairdocs.org/ad/2009-07-09): Aileron trim actuator · Dornier Luftfahrt Dornier 228-100, Dornier 228-101, Dornier 228-200 and 3 more. Effective May 11, 2009
- [AD 2008-09-09](https://openairdocs.org/ad/2008-09-09): Control cables · Dornier Luftfahrt Dornier 228-200, Dornier 228-201, Dornier 228-202 and 1 more. Effective Jun 2, 2008
- [AD 2007-14-06](https://openairdocs.org/ad/2007-14-06): Isolation diode · Aerotechnic Vertiebs-u. Service Honeywell CAS67A ACAS II, Dornier 228-100, Dornier 228-101 and 3 more. Effective Aug 16, 2007
- [AD 2005-18-20](https://openairdocs.org/ad/2005-18-20): "FASTprop" propeller de-icers · Hartzell PHC-C3YF-1RF/F8468A(B,K)-8R constant speed propeller (STC SA00718LA or 17 others). Effective Oct 14, 2005
- [AD 2003-16-17](https://openairdocs.org/ad/2003-16-17): Cockpit and Cabin Auxiliary Heating Wiring · Dornier Luftfahrt Dornier 228-100, Dornier 228-101, Dornier 228-200 and 3 more. Effective Oct 6, 2003
- [AD 2001-25-09](https://openairdocs.org/ad/2001-25-09): Brake Housing Subassembly · Dornier Luftfahrt Dornier 228-212. Effective Jan 18, 2002
- [AD 2001-21-01](https://openairdocs.org/ad/2001-21-01): Horizontal Stabilizer Skin and Ribs · Dornier Luftfahrt Dornier 228-100, Dornier 228-101, Dornier 228-200 and 3 more. Effective Nov 30, 2001
- [AD 2001-04-04](https://openairdocs.org/ad/2001-04-04): Windshield Spray Nozzle · Dornier Luftfahrt Dornier 228-100, Dornier 228-101, Dornier 228-200 and 3 more. Effective Apr 6, 2001
- [AD 2000-06-02](https://openairdocs.org/ad/2000-06-02): Pneumatic Deicing Boots · Dornier Luftfahrt Dornier 228-100, Dornier 228-101, Dornier 228-200 and 3 more. Effective May 5, 2000
- [AD 98-11-16](https://openairdocs.org/ad/98-11-16): Landing Gear Warning System · Dornier Luftfahrt Dornier 228-100, Dornier 228-101, Dornier 228-200 and 3 more. Effective Jul 11, 1998
- [AD 98-06-13](https://openairdocs.org/ad/98-06-13): MLG Axle Housing Assembly · Dornier Luftfahrt Dornier 228-100, Dornier 228-101, Dornier 228-200 and 1 more. Effective Jun 15, 1998
- [AD 97-22-09](https://openairdocs.org/ad/97-22-09): Pilot s Operating Handbook - Power Levers · Dornier Luftfahrt Dornier 228-100, Dornier 228-101, Dornier 228-200 and 3 more. Effective Dec 5, 1997
- [AD 96-09-14](https://openairdocs.org/ad/96-09-14): AFM - Icing · Dornier Luftfahrt Dornier 228-100, Dornier 228-101, Dornier 228-200 and 3 more. Effective Jun 11, 1996
- [AD 94-19-06](https://openairdocs.org/ad/94-19-06): Crew Oxygen Masks · 328 Support Services 328-100, 328-300, 500 and 17 more. Effective Oct 6, 1994
- [AD 91-12-13](https://openairdocs.org/ad/91-12-13): Electric Trim System · Dornier Luftfahrt Dornier 228-100, Dornier 228-101, Dornier 228-200 and 3 more. Effective Jul 19, 1991
- [AD 91-12-14](https://openairdocs.org/ad/91-12-14): AC Power Supply · Dornier Luftfahrt Dornier 228-100, Dornier 228-101, Dornier 228-200 and 2 more. Effective Jul 19, 1991
- [AD 91-05-03](https://openairdocs.org/ad/91-05-03): Bonding Straps · Dornier Luftfahrt Dornier 228-100, Dornier 228-101, Dornier 228-200 and 3 more. Effective Mar 25, 1991
- [AD 90-21-06](https://openairdocs.org/ad/90-21-06): Engine Mount · Dornier Luftfahrt Do 28 D and Do 28 D-1. Effective Nov 13, 1990
- [AD 89-04-04](https://openairdocs.org/ad/89-04-04): Center of Gravity Station Guide Line · Dornier Luftfahrt Do 28 D-1. Effective Mar 10, 1989
- [AD 89-03-15](https://openairdocs.org/ad/89-03-15): Horizontal Tail Rivets · Dornier Luftfahrt Do 28 D and Do 28 D-1. Effective Mar 3, 1989
- [AD 77-14-17 R1](https://openairdocs.org/ad/77-14-17-R1): Fuel and Oil Hose · Dornier-Werke Do 27 Q-6, Do 28 A-1, Do 28 B-1 and 2 more. Effective Mar 22, 1985
- [AD 82-26-04](https://openairdocs.org/ad/82-26-04): Autopilot Actuators · Dornier Luftfahrt Do 28 D-1. Effective Dec 27, 1982
- [AD 79-13-06](https://openairdocs.org/ad/79-13-06): Engine Fire System · Dornier Luftfahrt Do 28 D. Effective Jul 11, 1979
- [AD 76-11-04](https://openairdocs.org/ad/76-11-04): Electrical Cable Insulation · Dornier Luftfahrt Do 28 D-1. Effective Jun 15, 1976
- [AD 76-10-08](https://openairdocs.org/ad/76-10-08): Elevator Trim Control · Dornier Luftfahrt Do 28 D and Do 28 D-1. Effective Jun 3, 1976
- [AD 71-13-05](https://openairdocs.org/ad/71-13-05): Landing Gear Wheel Forks · Dornier Luftfahrt Do 28 D-1. Effective Jun 23, 1971
- [AD 70-21-01](https://openairdocs.org/ad/70-21-01): Cabin Door Structure · Dornier Luftfahrt Do 28 D-1. Effective Nov 5, 1970
- [AD 70-19-03](https://openairdocs.org/ad/70-19-03): Jumper Wire Installation · Dornier Luftfahrt Do 28 D-1. Effective Sep 22, 1970
- [AD 70-12-10](https://openairdocs.org/ad/70-12-10): Elevator Trim Tab System · Dornier Luftfahrt Do 28 D-1. Effective Jun 11, 1970
- [AD 69-19-05](https://openairdocs.org/ad/69-19-05): Elevator Control · Dornier Luftfahrt Do 28 D-1. Effective Sep 15, 1969
- [AD 64-14-03](https://openairdocs.org/ad/64-14-03): Electrical Installation · Dornier-Werke Do 28 A-1, Do 28 B-1, Do 28 D and 1 more. Effective Jul 13, 1964
- [AD 2009-13-04](https://openairdocs.org/ad/2009-13-04) (historical): Engine controls · Dornier Luftfahrt Dornier 228-100, Dornier 228-101, Dornier 228-200 and 3 more. Effective Jul 24, 2009
- [AD 2008-08-15](https://openairdocs.org/ad/2008-08-15) (historical): Internal of the elevator and rudder · Dornier Luftfahrt Dornier 228-100, Dornier 228-101, Dornier 228-200 and 3 more. Effective May 27, 2008
- [AD 2007-11-03](https://openairdocs.org/ad/2007-11-03) (historical): Centre section of fuselage frame 19 · Dornier Luftfahrt Dornier 228-100, Dornier 228-101, Dornier 228-200 and 3 more. Effective Jun 26, 2007
- [AD 2007-02-13](https://openairdocs.org/ad/2007-02-13) (historical): Landing gear carbon brake assembly · Dornier Luftfahrt Dornier 228-212. Effective Mar 1, 2007
- [AD 2006-11-19](https://openairdocs.org/ad/2006-11-19) (historical): Flight deck overhead panels (locations 5VE and 6VE) · Dornier Luftfahrt Dornier 228-100, Dornier 228-101, Dornier 228-200 and 3 more. Effective Jul 14, 2006

## Registered aircraft by registry model (OpenAirDocs)

- [Dornier DORNIER 228-202](https://openairdocs.org/model/dornier-dornier-228-202): 11 aircraft (registry code 2992030)
- [Dornier DO 28 D-1](https://openairdocs.org/model/dornier-do-28-d-1): 1 aircraft (registry code 2991404)
- [Dornier Luftfahrt DO 228-212](https://openairdocs.org/model/dornier-luftfahrt-do-228-212): 1 aircraft (registry code 2992923)
- [Dornier DO 28 D](https://openairdocs.org/model/dornier-do-28-d): 0 aircraft (registry code 2991401)

## STCs approved under this data sheet (97, first 50)

- [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 SA12370NY](https://openairdocs.org/stc/SA12370NY): Installation of a Garmin G700 Avionics System. Bighorn Airways, Inc.
- [STC SA11158SC](https://openairdocs.org/stc/SA11158SC): Demonstration of aircraft tolerance to potential electromagnetic interference from certain Transmitting Potable Electronic Devices (T-PEDS). Liberty Partners Inc.
- [STC SA5879NM](https://openairdocs.org/stc/SA5879NM): Installation of floor proximity emergency escape path marking system.. Bruce Aerospace Inc.
- [STC SA02738CH](https://openairdocs.org/stc/SA02738CH): Installation of L-3 Communications Avionics Systems. Acron Aviation Inc.
- [STC SA09887AC](https://openairdocs.org/stc/SA09887AC): Installation of an Avionica MK-III mini Quick Access Recorder (QAR) and optional 4G or LTE Avionica
Cellular Module (avCM. Aircraft Systems and Manufacturing Inc.
- [STC SA01116DE](https://openairdocs.org/stc/SA01116DE): Installation of TB40 Main Ship Battery. Peregrine
- [STC SA04051CH](https://openairdocs.org/stc/SA04051CH): Certification of Automatic Dependent Surveillance - Broadcast (ADS-B) Out System with Rockwell Collins TDR-94/-94D Transponders. CMD Flight Solutions 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 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 SA02010WI](https://openairdocs.org/stc/SA02010WI): Installation of the Mid-Continent Instruments & Avionics MD23 FLEX Custom Function Display (CFD). Mid-Continent Instruments and Avionics
- [STC SA00076IB](https://openairdocs.org/stc/SA00076IB): Installation of Photo luminescent Safety Systems. STG AEROSPACE GERMANY GmbH
- [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 SA03819NY](https://openairdocs.org/stc/SA03819NY): Installation and maintenance of Oratex 6000 Covering and Coating System. Lanitz-Prena Folien Factory GmbH
- [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 SA02075SE](https://openairdocs.org/stc/SA02075SE): Installation of a Mid-Continent MD835( ) Lithium Ion Battery. Mid-Continent Instrument Co. Inc.
- [STC SA04514NY](https://openairdocs.org/stc/SA04514NY): Single/Dual Transponder System ADS-B Upgrade. Scandinavian Avionics Design ApS
- [STC SA02268CH](https://openairdocs.org/stc/SA02268CH): Installation of Airwolf Filter Corp. Air Oil Separator. Airwolf Filter Corporation
- [STC SA02677LA](https://openairdocs.org/stc/SA02677LA): Modification to upgrade the existing Mode S Transponder system by installing the ACSS NXT-700 Transponder with ADS-B Out and optionally install the ACSS NXG-900 GPS as the position source for ADS-B Out. Aviation Communication and Surveillance Systems (ACSS) LLC
- [STC SA02678LA](https://openairdocs.org/stc/SA02678LA): Modification to upgrade the existing Mode S Transponder system by installing the ACSS NXT-600 Transponder with ADS-B Out and optionally install the ACSS NXG-900 GPS as the position source for ADS-B Out. Aviation Communication and Surveillance Systems (ACSS) LLC
- [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 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 SA03973NY](https://openairdocs.org/stc/SA03973NY): Replacement of existing TCAS 7.0 by TCAS 7.1. Scandinavian Avionics Design ApS
- [STC SA00845DE](https://openairdocs.org/stc/SA00845DE): Installation of two Ferno Advanced Life Support Litters (ALSL) with equipment mounts and medical electrical power. Bighorn Airways Inc
- [STC SA00382BO](https://openairdocs.org/stc/SA00382BO): Installation of Globalstar Antenna and Cradle provisions to support a Globalstar GPS-1700 in non-composite airplanes. Avidyne Corporation
- [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 SA01734SE](https://openairdocs.org/stc/SA01734SE): Application of Stewart Systems synthetic fabric covering system to aircraft fuselage, wings, tail surfaces, control surfaces and related parts.. Andrew D. Humphrey
- [STC SA329CH-D](https://openairdocs.org/stc/SA329CH-D): Installation of AlliedSignal Engines Models TPE 331-10T-511D, TPE-331-10GT-511D, TPE 331-10GP-511D, or TPE 331-10P-511D. StandardAero Business Aviation Services, 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 SA01969SE](https://openairdocs.org/stc/SA01969SE): Installation of a Mid-Continent MD302 Standby Attitude Module. Mid-Continent Instruments and Avionics
- [STC SA00478CH](https://openairdocs.org/stc/SA00478CH): Installation of Cooper Superflite 102 Fabric.. Aviation Products Systems Inc.
- [STC SA02434SE](https://openairdocs.org/stc/SA02434SE): Installation of a Supplemental Lighting System. Aviation Specialties Unlimited Inc.
- [STC SA02283SE PAGE 2](https://openairdocs.org/stc/SA02283SE%20PAGE%202): 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 SA00674WI-D](https://openairdocs.org/stc/SA00674WI-D): Modification of Collins VHF-22A/VHF-22B VHF COMM Receiver Transmitter with CTL-22 Control Pro Line II 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.. Rockwell Collins Inc
- [STC SA02016SE-D](https://openairdocs.org/stc/SA02016SE-D): Installation of Garmin GTS 800, GTS 820 or GTS 850 Traffic System. Garmin International Inc
- [STC SA03052NY](https://openairdocs.org/stc/SA03052NY): Installation of Model MTV-27-1-E-C-F-R(G)/CFRL250-55b full feathering and reversing 5-bladed propellers. MT- Propeller Entwicklung GmbH
- [STC SA02392AK](https://openairdocs.org/stc/SA02392AK): Limit the maximum passenger seating capacity to 9. Bighorn Airways Inc
- [STC SA01636WI-D](https://openairdocs.org/stc/SA01636WI-D): Modification of Rockwell Collins, Inc. VHF-4000 and VHF-4000E installations. Rockwell Collins Inc
- [STC SA00681WI-D](https://openairdocs.org/stc/SA00681WI-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. Rockwell Collins Inc
- [STC SA00068SE](https://openairdocs.org/stc/SA00068SE): Installation of fuel flow/pressure instruments. (W/TSIO-360-MB1). Electronics International Inc.

All 97: https://openairdocs.org/tcds/A16EU/stcs.md

---
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