# TCDS A9EU: Aermacchi S.p.A.

- Type: Type certificate data sheet
- Status: Current
- Holder: Aermacchi S.p.A.
- Revision: 10
- Revised: March 11, 2022
- Product: Aircraft, Small Airplane
- Certification basis: Part 21, Part 23
- Registered aircraft: 25, by the registry models matched to it (OpenAirDocs)
- Data sheet PDF: https://openairdocs.org/files/sha256/e0/7f/e07f0e831152665b97d1b43005e7c9d6146d5a35187a311406c3b972e133ae17
- FAA DRS: https://drs.faa.gov/browse/excelExternalWindow/05EE900C79A5C1328625880500504CD6.0001
- Page: https://openairdocs.org/tcds/A9EU

## Models (7)

As the data sheet lists them.

- S.205 - 18/F
- S.208
- S.205 - 18/R
- S.205 - 22/R
- S.208A
- S.205 - 20/R
- S.205 - 20/F

## What the data sheet says

From the PDF's text layer, line by line; tables lose their columns. The PDF is the record.

```text
A9EU 
Revision10 
AERMACCHI S.p.A. 
S.205 - 18/F 
S.205 - 18/R 
S.205 - 20/F 
S.205 - 20/R 
S.205 - 22/R 
S.208 
S.208A 
 
March 11, 2022 
I. Model S.205 - 18/F, 4PCLM (Utility Category), Approved March 7, 1966. 
Model S.205 - 18/R, 4PCLM (Utility Category), Approved June 7, 1966. 
DEPARTMENT OF TRANSPORTATION 
FEDERAL AVIATION ADMINISTRATION 
 
 
TYPE CERTIFICATE DATA SHEET No. A9EU 
 
This data sheet which is a part of type certificate No. A9EU 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. AERMACCHI S.p.A. 
Via P. Foresio, 1 
21040 Venegono Superiore (VA) 
Italy 
 
 
 
(Model S.205 - 18/R same as Model S.205 - 18/F except for retractable landing gear) 
Engine. Lycoming O-360-A1A 
Fuel. 91-96 minimum grade aviation gasoline 
Engine Limits. For all operations, 2700 r.p.m. (180 hp.) See NOTE 2 (a)(3) 
Propeller and Propeller Limits. Hartzell HC-C2YK-1B/7666A-2 
Diameter: Maximum 74 in., minimum allowable for repairs 72 in. 
(no further reduction permitted) 
Pitch setting at 30 in. radius: Low 12 High 29

Airspeed Limits. Never exceed 201 m.p.h. 
 Maximum structural cruising 150 m.p.h. 
 Maneuvering 137 m.p.h. 
 Landing Gear Extended 109 m.p.h. (Model S.205 - 18/R) 
 Flaps extended 102 m.p.h. 

C.G. Range (Landing (+94.8) to (+102.2) at 2314 lb. or less 
Gear Extended) (+99.1) to (+102.2) at 2645 lb. 
Straight line variation between points given. 
 
Empty Weight C.G. Range. None 
 
Maximum Weight. 2645 lb. 
 
No. Seats. 2 (+87.2) 2 (+119.3) 
 
Maximum Baggage. 132 lb. (+147.6) 
 
Page No. 1 2 3 4 5 6 7 8  
Rev. No. 10 7 7 7 9 10 8 8

II. Model S.205 - 20/F and S.205 - 20/R, 4 PCLM (Normal Category), Approved June 7, 1966. 
III. Model S.205 - 22/R, 4PCLM (Normal Category), Approved June 7, 1966. 
Fuel Capacity. 55.5 gal. total; 55 gal. usable (2 wing tanks) (+99.9) 
See NOTE 1 for unusable fuel. 
 
Oil Capacity. 2 gal. (+31.5) (Unusable Oil - 2 qt.) 
See NOTE 1 for system oil 
 
 
 
(Model S.205 - 20/F same as Model S.205 - 18/F except for increased maximum weight and Power Plant Installation) 
(Model S.205 - 20/R same as Model S.205 - 20/F except for retractable landing gear). 
 
Engine. Lycoming IO-360-A1A 
 
Fuel. 100-130 minimum grade aviation gasoline 
Engine Limits. For all operations, 2700 r.p.m. (200 hp.) (See NOTE 2 (c)(1)) 
Propeller and Propeller Limits. Hartzell HC-C2YK-1B/7666A-2 
Diameter: Maximum 74 in., minimum allowable for repairs 72 in. 
(No further reduction permitted) 
Pitch setting at 30 in., radius: Low 14, High 29

Airspeed Limits. Never exceed 201 m.p.h. 
 Maximum structural cruising 150 m.p.h. 
 Maneuvering 137 m.p.h. 
 Landing gear extended 109 m.p.h. (Model S.205 - 20/R) 
 Flaps extended 102 m.p.h. 

C.G. Range (Landing Gear (+94.8) to (+102.2) at 2314 lb. or less 
Extended). (+99.1) to (+102.2) at 2866 lb. 
Straight line variation between points given. 
 
Empty C.G. Range. None 
 
Maximum Weight. 2866 lb. 
 
No. Seats. 2 (+87.2). 2 (+119.3) 
 
Maximum Baggage. 132 lb. (+147.6) 
 
Fuel Capacity. 55.5 gal. total; 55 gal. usable (2 wing tanks) (+99.9) 
See NOTE 1 for unusable fuel 
 
Oil Capacity. 2 gal. (+31.5) Unusable oil - 2 qt.) 
See NOTE 1 for system oil 
 
 
 
(Same as Model S.205 - 20/R except for Power Plant and Propeller installation, increased maximum weight, number 
of seats, increased maximum baggage). 
 
Engine. Franklin 6A-350-C1 
 
Fuel. 100-130 minimum grade aviation gasoline 
 
Engine Limits. For all operations, 2800 r.p.m. (220 hp.)

3 
 
 
Propeller and Propeller Limits. McCauley 2A31C21/84S-4 
Diameter: Maximum 80 in., minimum allowable for repairs 78 in. 
(No further reduction permitted) 
Pitch setting at 30 in. radius: Low 1120’, High 2050’ 
 
Or: 
Hartzell HC-C2YF-1B/8459-4 
Diameter: Maximum 80 in., minimum allowable for repairs 78 in. 
(No further reduction permitted) 
Pitch setting at 30 in. radius: Low 11, High 3030’ 
 
Airspeed Limits. Never exceed speed 201 m.p.h. 
Maximum structural cruising 150 m.p.h. 
Maneuvering 137 m.p.h. 
Landing gear extended 109 m.p.h. 
Flaps extended 102 m.p.h. 
 
C.G. Range (Landing Gear (+94.8) to (+102.2) at 2314 lb. or less 
Extended). (+99.1) to (+102.2) at 2976 lb. 
Straight line variation between points given. 
 
Empty Weight C.G. Range. None 
 
Maximum Weight. 2976 lb. 
 
No. Seats. 2 (+87.2). 2 (+119.3) (See NOTE 5 and 6) 
 
Maximum Baggage. 176 lb. (+147.6) (See NOTE 5) 
 
Fuel Capacity. 55.5 U.S. gal. total; 55 U.S. gal. usable (2 wing tanks) (+99.9) 
(See NOTE 1 for unusable fuel) (See NOTE 7 for wing tip tanks) 
 
Oil Capacity. 8.8 U.S. qt. (+31.5) (Unusable oil - 2 qt.) See NOTE 1 for system oil. 
A9EU 
 
 
 
 (Same as Model S.205 - 22/R except for powerplant and propeller installation. 
See NOTE 8 for conversion into S.208A model) 
 
Engine. Lycoming O-540-E4A5 
 
Fuel. 91-96 minimum grade aviation gasoline 
Engine Limits. For all operations, 2700 r.p.m. (260 hp.) (See NOTE 2(d)(1)) 
Propeller and Propeller Limits. Hartzell: HC-C2YK-1B/8467-8R 
Diameter: Maximum 76 in., minimum allowable for repairs 75 in. 
(No further reduction permitted) 
Pitch setting at 30 in., radius: Low 1530’, High 32 
Or: 
Hartzell HC-C2YK-1B/8477-8R 
Diameter: Maximum 76 in., (No reduction permitted) 
Pitch setting at 30 in. radius: Low 1530’, High 32
IV. Model S.208, 4 PCLM (Normal Category), Approved May 24, 1968.

V. Model S.208A, 5 PCLM (Normal Category), Approved June 17, 1974. 
Airspeed Limits. Never exceed speed 201 m.p.h. 
 Maximum structural cruising 150 m.p.h. 
 Maneuvering 137 m.p.h. 
 Landing gear extended 109 m.p.h. 
 Flap extended 102 m.p.h. 

C.G. Range (Landing Gear (+94.8) to (+102.2) at 2314 lb. or less 
Extended). (+99.1) to (+102.2) at 2976 lb. 
Straight line variation between points given. 
 
Empty Weight C.G. Range. None 
 
Maximum Weight. 2976 lb. 
 
No. of Seats. 2 (+87.2), 2 (+119.3). (See NOTE 5) 
 
Maximum Baggage. 176 lb. (+147.6). (See NOTE 5) 
 
Fuel Capacity. 55.5 U.S. gal. total; 55 U.S. gal. usable (2 wing tanks ) (+99.9) 
(See NOTE 1 for unusable fuel) (See NOTE 7 for wing tip tanks) 
 
Oil Capacity. 12 U.S. qt. (+31.5) (Unusable oil - 2.75 qt.) (See NOTE 1 for system oil) 
 
 
 
 
(Same as Model S.208 except for increased maximum weight, number of seats and increased maximum baggage). 
Engine. Lycoming O-540-E4A5 
Fuel. 91-96 minimum grade evaluation gasoline 
Engine Limits. For all operations, 2700 r.p.m. (260 hp.) (See NOTE 2(d)(1)). 
Propeller and Propeller Limits. Hartzell HC-C2YK-1B/8467-8R 
Diameter: Maximum 76 in. minimum allowable for repairs 75 in. 
(No further reduction permitted) 
Pitch setting at 30 in. radius: Low 1530’, High 32

Or: 
Hartzell HC-C2YK-1B/8477-8R 
Diameter: Maximum 76 in. (No reduction permitted) 
Pitch setting at 30 in. radius: Low 1530’, High 32

Airspeed Limits. Never exceed speed 209 m.p.h. 
Maximum structural cruising 166 m.p.h. 
Maneuvering 142 m.p.h. 
Landing gear and flap extended 115 m.p.h. 
 
C.G. Range (Landing Gear (+94.8) to (+102.2) at 2645 lb. or less 
Extended) (+101.2) to (+102.2) at 3318 lb. 
Straight line variation between points given. 
 
Empty Weight C.G. Range. None 
 
Maximum Weight. 3318 lb. 
 
No. Seats. 2 (+87.2), 2 (+118.1), 1(+147.6)

5 
 
 
Maximum Baggage. 220 lb. (+147.6). See NOTE 2(k) for placard 
 
Fuel Capacity. 86 U.S. gal. total 83.5 U.S. gal. usable 
(2 wing tanks of 27.8 U.S. gal. each (+99.9) 
(2 tip tanks of 15.2 U.S. gal. each (+101.7) 
(See NOTE 1 for unusable fuel). 
 
Oil Capacity. 12 U.S. qt. (+31.5) (Unusable oil - 2.75 qt.) (See NOTE 1 for system oil) 
 
 
DATA PERTINENT TO ALL MODELS 
A9EU 
 
Datum. 40.2 in. forward of center line of nose gear attachment bolts. 
 
Leveling Means. Three screws on baggage compartment bulkheads. 
 
Control Surface Movements. Wing flaps  Down 43  1
 Ailerons Up 22   1 Down 15  1
 Elevator Up 30  1 Down 20  1
 Rudder Right 25  1 Left 25   1
 Elevator Trim Tab Up 22   1 Down 26  1
 
Certification Basis. FAR - 21.29 - FAR 23 effective February 1, 1965, for models S.205 and S.208. 
FAR 23 effective February 1, 1965, including amendments 23-1, -4, -5, and -6 
for Model S.208A. 
Type Certificate No. A9EU issued March 7, 1966. 
Date of Application for Type Certificate June 30, 1965. 
 
The Ente Nazionale per l’Aviazone Civile (ENAC) originally type 
Certificated this aircraft under its Type Certificate Number A131. 
Effective September 28, 2003, the European Aviation Safety 
Agency (EASA) began oversight of this product under their 
Type certificate Number A131 on behalf of Italy. 
 
Serial Nos. Eligible. The Registro Aeronautico Italiano (R.A.I.) Certificate of Airworthiness endorsed as 
noted below under “Import Requirements” must be submitted for each individual aircraft 
for which certification is made. 
 
Equipment. The basic required equipment as prescribed in the applicable airworthiness regulations 
(See Certification Basis) must be installed in the aircraf for certification. In addition, the 
following items of equipment are required: 
 
(a) Pre-stall warning indicator, Safe Flight Instrument Corp. 164 S. 
(P/N NS5F026) (All models) .51b +67 
 
Equipment. (cont'd) (b) R.A.I. Approved Airplane Flight Manual 
(1) Flight Manual dated February 23, 1966 for Model S.205 - 18/F 
(2) Flight Manual dated April 14, 1966 for Model S.205 - 18/R 
(3) Flight Manual dated April 14, 1966 for Model S.205 - 20/F 
(4) Flight Manual dated April 14, 1966 for Model S.205 - 20/R 
(5) Flight Manual dated May 27, 1966 for Model S.205 - 22/R 
(6) Flight Manual dated March 5, 1968 for Model S.208. 
(7) Flight Manual dated January 18, 1973 for Model S.208A 
 
 
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 Ente Nazionale per 
l’Aviazone Civile (ENAC) 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 ENACs TC No A131 approved under 
U.S. Type Certificate No. A 9EU and to be in a condition for safe operation”. 
 
The U.S. airworthiness certification basis for aircraft type certificated under FAR Section 
21.29 and exported by the country of manufacture is FAR Sections 21.183(c) or .185(c). 
 
The U.S. airworthiness certification basis for aircraft type certificated under FAR Section 
21.29 exported from countries other than the country of manufacture (e.g., third party 
country) is FAR Sections 21.183(d) or 21.183(b). 
 
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 
 
 
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 Ente Nazionale per l’Aviazone Civile (ENAC) 
 
· 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 condition 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. 
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 time of original certification, and 
at all times thereafter. The certificated empty weight and corresponding center of gravity locations must 
include: 
 
- Unusable fuel 3.3. lbs. at (+99.9) (wing tanks) for all models. 
- Unusable fuel 12 lbs. at (+101.7) (tip tanks) for model S.205 - 22/R and S.208 when 
wing tip tanks are installed (See NOTE 7) and for model S.208A. 
System oil of 1 lb. at (+31.5) and unusable of 3.0 lb. at (+99.9) 
 
NOTE 2. The following placards must be displayed in front and in clear view of pilot: 
a) For Models S.205-18/F and S.205-18/R: 
(1) “THIS AIRPLANE MUST BE OPERATED AS A UTILITY 
CATEGORY AIRPLANE IN COMPLIANCE WITH THE 
OPERATING LIMITATIONS STATED IN THE FORM OF 
PLACARDS, MARKINGS AND THE FLIGHT MANUAL.” 
(2) “ACROBATIC MANEUVERS ARE LIMITED TO THE FOLLOWING: 
CHANDELLES 150 mph TIAS 
LAZY EIGHTS 160 mph TIAS

STEEP TURNS 125 mph TIAS 
STALLS (Except with stalls) SLOW DECELERATION”7 
 
 
(3) “AVOID CONTINUOUS OPERATIONS BETWEEN 2000 AND 2250 RPM”  
b) For Models S.205-20/F, S.205-20/R, S.208 and S.208A: 
(1) “THIS AIRPLANE MUST BE OPERATED AS A NORMAL 
CATEGORY AIRPLANE IN COMPLIANCE WITH THE OPERATING 
LIMITATIONS STATED IN THE FORM OF PLACARDS, MARKINGS 
AND THE FLIGHT MANUAL.” 
(2) “NO ACROBATIC MANEUVERS, INCLUDING SPINS, APPROVED” 
c) For Models S.205-20/F and S.205-20/R: 
(1) “AVOID CONTINUOUS OPERATION BETWEEN 2100 AND 2350 RPM” 
d) For Models S.208 and S.208A: (When Hartzell HC-C2YK-1B/8467-8R propeller is installed) 
(1) “AVOID CONTINUOUS OPERATION BETWEEN 2500 AND 2600 RPM 
ABOVE 25” HG. MANIFOLD PRESSURE.” 
e)   For Models S-205 -18/R; -20/R; -22/R and S.208: 
(1) “DO NOT LOWER LANDING GEAR ABOVE 109 MPH CAS”. 
f) For Models S.208A: 
(1) “DO NOT LOWER LANDING GEAR ABOVE 115 MPH CAS”. 
g) For Models S.205 and S.208: 
(1) “MAX MANEUVERING SPEED FOR FULL APPLICATION OF  
CONTROLS IS 137 MPH CAS. MAX CROSSWING VELOCITY:  15 
KNOTS”. 
(2) “USE WING TIP TANKS IN LEVEL FLIGHT ONLY”.  On 
Baggage Door: 
i)    For Models S.205-18/F; -18/R, -20/F and 20/R: 
(1) “MAX LOAD IN THIS COMPARTMENT : 132 LBS”. 
j) For Model S.205 -22/R and S.208: 
(1) “MAX LOAD IN THIS COMPARTMENT : 176 LBS”. 
k) For Model S.208A: 
(1) “MAX LOAD IN THIS COMPARTMENT (220 LBS) INCLUDES  THE 
BAGGAGE AND/OR FIFTH PASSENGER”. 
(2)  
NOTE 3. Each individual airplane will be supplied with a placard that specified the kinds of operations such as VFR or 
IFR, Day or Night, to which the operation of the airplane is limited by the equipment installed. 
 
NOTE 4. The aircraft must be assembled and inspected in accordance with Registro Aeronautico  
Italiano approved Report No. 77, dated June 19, 1967 and later RAI-approved revision, 
“SIAI S.205-22/R Aircraft Assembly and Test procedure at the Waco Plant”. 
 
NOTE 5. The fifth seat installation Drwg. No. 205-0-027-01 includes assemblies Part Nos. 205-2-038-01 (fifth seat at 
+ 147.6) and 205-2-041-101 and -102 (rear seat a + 118.1) as defined in the Technical Instruction No. 
205 I-3A. When the fifth seat is installed, the Appendix “2” of respective Flight Manuals must be followed 
and this placard must be installed in the baggage compartment: 
 
“THE MAXIMUM LOAD IN THIS COMPARTMENT (176 lbs.) INCLUDES THE 
BAGGAGE AND/OR FIFTH PASSENGER”. 
 
NOTE: 
On aircraft having the following Serial Nos., the fifth seat installation has been carried 
out by using two rear seats of fixed type with an arm of (+118.1): 
 
Model S.205-22/R: 373; 385; 4-142 to 4-158 inclusive; 
4-176 to 4-194 inclusive. 
Model S.208: 002; 003. 
 
 
NOTE 6. Installation of baggage compartment windows, as defined in Technical Instruction 
No. 205 I-8, is optional on S.205-22/R aircraft to be modified for the installation of fifth 
seat in the same compartment. 
NOTE 7. The wing tip tank installation, Dwg. 205-8-197, includes the assemblies, part No. 
205-8-193-01 and -02 (left and right wing tip tank) of 30.5 U.S. Gal. total capacity 
(15.25 gallons each tank) usable 28.5 U.S. Gal., at (+101.7), as defined in the Technical 
instruction No. 205 I-7. When the wing tip tanks are installed, the “Appendix 3” of

S.205-22/R and S.208 Flight Manual must be followed and this placard installed on the 
instrument panel, near to the fuel level indicator selector switch: 
“USE WING TIP TANKS IN LEVEL FLIGHT ONLY”. 
 
NOTE 8. The Model S.208 may be converted into S.208A: 
a. By modifying it in accordance with “Technical Instruction No. 208I-1” by using 
“Kit P/No. 208I-1”; 
b. By replacing the nameplate and the Flight Manual with those for Model S.208A; and, 
c. By accomplishing the modifications reported on NOTES 5 (see NOTE 9 for the S.208 
aircraft S/N 001) and 7, if they are not already installed. 
 
NOTE 9. The S.208 aircraft Serial No. 001 has been converted into S.208A without fifth seat 
installation with the rear seat, P/N 205-2-003, installed having an arm of (+119.3). 
In the baggage compartment is installed the placard: 
“MAX LOAD IN THIS COMPARTMENT : 220 LBS”. 
 
NOTE 10. As of January 1, 1997, AERMACCHI S.p.A. has acquired SIAI Marchetti S.r.L. 
 
 
 
- END -
```

## ADs (33, in force first)

- [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 2013-22-23 R1](https://openairdocs.org/ad/2013-22-23-R1): Powerplant · Aermacchi F.260, F.260B, F.260C and 5 more. Effective Jul 11, 2014
- [AD 2013-22-23](https://openairdocs.org/ad/2013-22-23): Powerplant · Aermacchi F.260, F.260B, F.260C and 5 more. Effective Dec 16, 2013
- [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 98-12-14](https://openairdocs.org/ad/98-12-14): Flap Cable Pulley Bracket · Aermacchi S.205 - 18/F, S.205 - 18/R, S.205 - 20/F and 4 more. Effective Jul 18, 1998
- [AD 98-08-04](https://openairdocs.org/ad/98-08-04): Landing Gear Rod Springs · Aermacchi S.208 and S.208A. Effective May 26, 1998
- [AD 98-08-06](https://openairdocs.org/ad/98-08-06): Flight Control Cables · Aermacchi S.205 - 18/F, S.205 - 18/R, S.205 - 20/F and 4 more. Effective May 26, 1998
- [AD 75-17-23 R2](https://openairdocs.org/ad/75-17-23-R2): Landing Gear Operating Mech. · Aermacchi S.205 - 18/F, S.205 - 18/R, S.205 - 20/F and 4 more. Effective Sep 27, 1985
- [AD 84-16-02](https://openairdocs.org/ad/84-16-02): Main Landing Gear Long Arm Cross-Member Inspection · Aermacchi S.205 - 18/F, S.205 - 18/R, S.205 - 20/F and 4 more. Effective Aug 23, 1984
- [AD 83-23-02 R1](https://openairdocs.org/ad/83-23-02-R1): Flap Hinges Attach Brackets · Aermacchi S.205 - 18/F, S.205 - 18/R, S.205 - 20/F and 4 more. Effective Apr 30, 1984
- [AD 83-08-07](https://openairdocs.org/ad/83-08-07): Propeller Control · Aermacchi F.260, F.260B, S.205 - 18/F and 5 more. Effective May 9, 1983
- [AD 83-07-10](https://openairdocs.org/ad/83-07-10): Butterfly Valve Attachment · Aermacchi S.205 - 20/F and S.205 - 20/R. Effective Apr 14, 1983
- [AD 83-07-20](https://openairdocs.org/ad/83-07-20): Exhaust System · Aermacchi S.205 - 22/R. Effective Apr 14, 1983
- [AD 71-17-04 R1](https://openairdocs.org/ad/71-17-04-R1): Main Gear Axle · Aermacchi S.205 - 18/F, S.205 - 18/R, S.205 - 20/F and 4 more. Effective Dec 27, 1982
- [AD 76-23-01](https://openairdocs.org/ad/76-23-01): Landing Gear Control Switch · Aermacchi F.260, F.260B, S.205 - 18/R and 4 more. Effective Nov 18, 1976
- [AD 76-09-06](https://openairdocs.org/ad/76-09-06): Aileron Control · Aermacchi S.205 - 18/F, S.205 - 18/R, S.205 - 20/F and 4 more. Effective May 10, 1976
- [AD 75-22-18](https://openairdocs.org/ad/75-22-18): Nose Landing Gear · Aermacchi S.205 - 18/F and S.205 - 20/F. Effective Nov 5, 1975
- [AD 75-22-20](https://openairdocs.org/ad/75-22-20): Landing Gear · Aermacchi S.205 - 18/R, S.205 - 20/R, S.205 - 22/R and 2 more. Effective Oct 30, 1975
- [AD 75-17-24](https://openairdocs.org/ad/75-17-24): Landing Gear Actuator Brackets · Aermacchi S.205 - 18/R, S.205 - 20/R, S.205 - 22/R and 2 more. Effective Aug 20, 1975
- [AD 73-11-07](https://openairdocs.org/ad/73-11-07): Frayed Aileron Control Cables · Aermacchi S.205 - 18/F, S.205 - 18/R, S.205 - 20/F and 4 more. Effective Jun 22, 1973
- [AD 73-11-08](https://openairdocs.org/ad/73-11-08): Landing Gear Link Pins and Bolts · Aermacchi S.205 - 18/F, S.205 - 18/R, S.205 - 20/F and 2 more. Effective Jun 22, 1973
- [AD 73-11-04](https://openairdocs.org/ad/73-11-04): Main Landing Gear Eye Bolt Seizure · Aermacchi S.205 - 18/R, S.205 - 20/R and S.205 - 22/R. Effective Jun 20, 1973
- [AD 72-16-04](https://openairdocs.org/ad/72-16-04): Nose Gear Drag Link · Aermacchi S.205 - 18/R, S.205 - 20/R and S.205 - 22/R. Effective Jul 25, 1972
- [AD 72-14-02](https://openairdocs.org/ad/72-14-02): Fuel or Fumes in Wings or Cabin · Aermacchi S.205 - 18/F, S.205 - 18/R, S.205 - 20/F and 4 more. Effective Jul 3, 1972
- [AD 72-03-02](https://openairdocs.org/ad/72-03-02): Wing Front Spar Attachment · Aermacchi S.205 - 18/F, S.205 - 18/R, S.205 - 20/F and 4 more. Effective Feb 25, 1972
- [AD 70-20-01](https://openairdocs.org/ad/70-20-01): Flap Locking Mechanism · Aermacchi S.205 - 22/R. Effective Sep 22, 1970
- [AD 69-19-07](https://openairdocs.org/ad/69-19-07): Engine and Elevator Controls · Aermacchi S.205 - 22/R. Effective Aug 17, 1970
- [AD 68-19-01](https://openairdocs.org/ad/68-19-01): Suction Gage Markings · Aermacchi S.205 - 22/R. Effective Oct 11, 1968
- [AD 68-19-02](https://openairdocs.org/ad/68-19-02): Cracks in Lower Fuselage · Aermacchi S.205 - 22/R. Effective Oct 11, 1968
- [AD 68-16-02](https://openairdocs.org/ad/68-16-02): Gear Position Indicator Switch · Aermacchi S.205 - 22/R. Effective Sep 7, 1968
- [AD 68-12-01](https://openairdocs.org/ad/68-12-01): Sealant at Firewall and Nose Wheel · Aermacchi S.205 - 22/R. Effective Jul 5, 1968
- [AD 68-08-06](https://openairdocs.org/ad/68-08-06): Nose Gear Brace · Aermacchi S.205 - 22/R. Effective May 17, 1968
- [AD 66-29-03](https://openairdocs.org/ad/66-29-03): Rear Spar Web · Aermacchi S.205 - 18/F, S.205 - 18/R, S.205 - 20/F and 2 more. Effective Nov 23, 1966

## Registered aircraft by registry model (OpenAirDocs)

- [Siai-Marchetti S.205/22R](https://openairdocs.org/model/siai-marchetti-s-205-22r): 22 aircraft (registry code 8120412)
- [Siai-Marchetti S 208](https://openairdocs.org/model/siai-marchetti-s-208): 1 aircraft (registry code 8121300)
- [Siai-Marchetti S.205-18R](https://openairdocs.org/model/siai-marchetti-s-205-18r): 1 aircraft (registry code 8120415)
- [Siai-Marchetti S.205-20F](https://openairdocs.org/model/siai-marchetti-s-205-20f): 1 aircraft (registry code 8120414)
- [Agusta S205-18F](https://openairdocs.org/model/agusta-s205-18f): 0 aircraft (registry code 0260500)
- [Agusta S205-18R](https://openairdocs.org/model/agusta-s205-18r): 0 aircraft (registry code 0260499)
- [Agusta S205-20F](https://openairdocs.org/model/agusta-s205-20f): 0 aircraft (registry code 0260497)
- [Agusta S205-20R](https://openairdocs.org/model/agusta-s205-20r): 0 aircraft (registry code 0260498)

## STCs approved under this data sheet (107, 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 SA04652CH](https://openairdocs.org/stc/SA04652CH): To allow use of 100R grade aviation fuel meeting Swift Fuel, LLC specification. Swift Fuels LLC
- [STC SA02636SE](https://openairdocs.org/stc/SA02636SE): Installation of Garmin GPS 175 Navigation System and GNX 375 Navigation System with ADS-B In/Out Transponder.. Garmin International Inc.
- [STC SA02019SE-D](https://openairdocs.org/stc/SA02019SE-D): Installation of Garmin Model GTN 625/635/650; 725/750 Navigation System. Garmin International Inc.
- [STC SA02511SE](https://openairdocs.org/stc/SA02511SE): Installation of replacement fuel quantity indicator sending unit(s). CiES 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 SA01757WI](https://openairdocs.org/stc/SA01757WI): To allow the use of UL91 or UL94 (minimum) grade aviation fuel. Swift Fuels LLC
- [STC SA04568CH](https://openairdocs.org/stc/SA04568CH): Installation of the uAvionix tailBeaconX, a tail mounted position light with integrated Automatic Dependent Surveillance - Broadcast (ADS-B) Out and 1090MHz Mode-S transponder functionality. uAvionix Corporation
- [STC SA02658SE](https://openairdocs.org/stc/SA02658SE): Installation of Garmin GI 275 Multi-Function Display System. Garmin International Inc.
- [STC SA02571SE](https://openairdocs.org/stc/SA02571SE): Installation of Garmin G500/G600 TXi Integrated Avionics System (Primary Flight Display, Multi-Function Display, and Engine Indicating System Display).. Garmin International Inc.
- [STC SA01899WI](https://openairdocs.org/stc/SA01899WI): Installation of Garmin G3X Touch Electronic Flight Instrument System. Garmin International Inc.
- [STC SA02019WI](https://openairdocs.org/stc/SA02019WI): Installation of the Trig Avionics TX56, TX56A, TX57, or TX57A VHF Nav-Com Radio.. Peregrine
- [STC SA01435LA](https://openairdocs.org/stc/SA01435LA): Installation of engines modified with Firewall Forward Technologies LLC modified camshaft. Centri-Lube Technologies LLC
- [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 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 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 SA09902AC](https://openairdocs.org/stc/SA09902AC): Installation of BendixKing KFD 900 Flight Display System. 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 SA10822SC](https://openairdocs.org/stc/SA10822SC): Installation of EFD1000 Primary Flight Display. Aspen Avionics Inc.
- [STC SA00401BO](https://openairdocs.org/stc/SA00401BO): Installation of a SkyTrax100B UAT receiver. Avidyne Corporation
- [STC SA00410BO](https://openairdocs.org/stc/SA00410BO): Installation of an AV-30-C Multi-Mode Indicator. uAvionix Corporation
- [STC SA01831WI](https://openairdocs.org/stc/SA01831WI): To allow the use of UL91 (minimum) grade aviation fuel. Petersen Aviation Inc
- [STC SA10236SC](https://openairdocs.org/stc/SA10236SC): Installation of a GDC 31 Roll Steering Converter. DAC International Inc
- [STC SA02268CH](https://openairdocs.org/stc/SA02268CH): Installation of Airwolf Filter Corp. Air Oil Separator. Airwolf Filter Corporation
- [STC SA01714WI](https://openairdocs.org/stc/SA01714WI): Installation of a Garmin transponders: (a) GTX 330/330D/33/33D with ADS-B Out functionality; (b) GTX 335/335R/345/345R with ADS-B Out and In functionality; or (c) GTX 335R/345R with ADS-B Out functionality in select airplanes installed with G950/G1000 systems.. Garmin International Inc
- [STC SA03286CH](https://openairdocs.org/stc/SA03286CH): Install an electronic engine ignition system. Electroair Acquisition Corporation
- [STC SA04032CH](https://openairdocs.org/stc/SA04032CH): Install rocker switch assemblies. Electroair Acquisition Corporation
- [STC SA04280CH](https://openairdocs.org/stc/SA04280CH): Install rocker switch assemblies on dual magneto configuration in accordance with Electroair Acquisition Corporation Installation Instructions as listed on AML No. SA04280CH, or later FAA approved revision.. 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 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 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 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 SA00433NY](https://openairdocs.org/stc/SA00433NY): Installation of Airwolf remote mounted engine oil filter model AFC-500 or AFC-600 on multi engine fixed wing light aircraft incorporating Franklin reciprocating engines of 450 horsepower or less.. Airwolf Filter Corporation
- [STC SA01933LA-D](https://openairdocs.org/stc/SA01933LA-D): Installation of Garmin Model 400W / 500W Series GPS-WAAS Navigation System. Garmin International Inc
- [STC 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 SA2586NM](https://openairdocs.org/stc/SA2586NM): Installation of J.P. Instruments temperature monitoring systems.. J P Instruments
- [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

All 107: https://openairdocs.org/tcds/A9EU/stcs.md

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