# TCDS A67EU: Extra Flugzeugproduktions- und Vertriebs- GmbH

- Type: Type certificate data sheet
- Status: Current
- Holder: Extra Flugzeugproduktions- und Vertriebs- GmbH
- Revision: 13
- Revised: February 17, 2022
- Product: Aircraft, Small Airplane
- Certification basis: Part 23
- Registered aircraft: 238, by the registry models matched to it (OpenAirDocs)
- Data sheet PDF: https://openairdocs.org/files/sha256/c3/1b/c31b6eae5ec5dd6f3301c8a3258a8893b99964ddf2401903eb19b5f35f11a080
- FAA DRS: https://drs.faa.gov/browse/excelExternalWindow/C23BA23B698D062E862587F3005AA63A.0001
- Page: https://openairdocs.org/tcds/A67EU

## Models (5)

As the data sheet lists them.

- EA 300/S
- EA 300
- EA 300/L
- EA 300/200
- EA 300/LC

## What the data sheet says

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

```text
DEPARTMENT OF TRANSPORTATION 
FEDERAL AVIATION ADMINISTRATION 
A67EU 
Revision 13 
EXTRA 
EA 300 
EA 300/S 
EA 300/L 
EA 300/200 
EA 300/LC 
February 17, 2022 
TYPE CERTIFICATE DATA SHEET No. A67EU 
This Data Sheet which is a part of Type Certificate No. A67EU 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 Extra Flugzeugproduktions- und Vertriebs- GmbH 
Flugplatz Dinslaken / Schwarze Heide 21 
D-46569 Hünxe 
Germany 
Type Certificate Holder Record Extra Flugzeugproduktions- und Vertriebs- GmbH 
Flugplatz Dinslaken / Schwarze Heide 21 
D-46569 Hünxe 
Germany 
Extra Flugzeugbau GmbH 
Flugplatz Dinslaken Schwarze Heide 
46569 Hünxe 
Federal Republic of Germany 
Transferred TC A67EU to 
Extra Flugzeugproduktions- und Vertriebs- GmbH 
on August 26, 2003. See Note 9. 
I. Model EA 300 (Normal, Acrobatic category), approved February 26, 1993. 
Differences. This model is not convertible to other listed models. 
Engine. 1 Textron Lycoming AEIO-540-L1B5 or AEIO-540-L1B5D 
(TCDS 1E4) 
Fuel. Avgas 100 or 100LL 
Engine Limits. Maximum take-off (5 min) 300 SHP/2700 rpm 
Continuous operation 270 SHP/2400 rpm 
Propeller and Propeller Limits. MT Propeller MTV-9-B-C/C200-15 or MTV-14-B-C/C190-17 
(TCDS P-24NE) (TCDS P3BO) 
Diameter 78.74 in. (2000 mm) 74.80 in. (1900 mm) 
Low Pitch 10.5º ± .2º 12.5º ± .2º 
High Pitch 34° ± 1° 34° - 1° 
Pitch Radius at 70 cm 66.5 cm 
Airspeed Limits (KCAS). Normal Cat. Acrobatic Cat. 
Vne 220 kt 220 kt 
Vno 140 kt 158 kt 
Va 140 kt 158 kt 
Center Gravity (C.G.) Range. Acrobatic Category Normal Category 
Page No. 1 2 3 4 5 6 7 8 9 10 11 12 
Rev. No. 13 12 10 10 9 11 11 13 11 11 11 11

Page 2 of 12 A67EU 
Category I Category II 
1808 lbs. or below at 1918 lbs. at 2095 lbs. 
(820 kg) (870 kg) (950 kg) 
Forward C.G. (aft of datum) 29.53 in. (750 mm) 30.12 in. (765 mm) 30.71 in. (780 mm) 
Rear C.G. (aft of datum 35.35 in. (898 mm) 34.84 in. (885 mm) 33.86 in. (860 mm) 
Straight line variation between points. 
Empty Weight C.G. Range. None. 
Maximum Weight. 1808 lbs (820 kg) - Acrobatic Category (Single Seat Operation/Acro I) 
1918 lbs (870 kg) - Acrobatic Category (Double Seat Operation/Acro II) 
2095 lbs (950 kg) - Normal Category 
Minimum Crew. 1 pilot (Rear Seat) 
Number of Seats. 2 (45.7 inches and 85.4 inches) 
Maximum Baggage. None 
Fuel Capacity. Fuselage Arm Wing Arm 
10.4 gals (38 liters) usable in acrobatic category or 
41.7 gals (158 liters) usable in normal category at 21.7 in. 20.5 in. 
50.7 gals (192 liters) usable in normal category 
(with LONG RANGE OPTION) at 21.7 in. 20.5 in. 
.53 gals (2 liters) unusable 
(See NOTE 1 for data on weight and balance) 
Oil Capacity. Minimum sump capacity for normal operation 2.25 gal 
Minimum sump capacity for acrobatic operation 3 gal 
Maximum sump capacity 4 gal at -23.4 in. 
(See NOTE 1 for data on weight and balance) 
Maximum Operational Altitude. 16000 ft 
Control Surface Movements. Aileron ± 30º 
Elevator ± 26º 
Trim tab ± 15º 
Rudder ± 30º 
For all control surfaces a tolerance of 2º is applied. 
II. Model EA 300/S (Normal, Acrobatic Category), approved October 28, 1993. 
Differences. This model is a single seat version and is not convertible to other listed models. 
Engine 1 Textron Lycoming AEIO-540-L1B5 or AEIO-540-L1B5D 
(TCDS 1E4) 
Fuel Avgas 100 or 100LL 
Engine Limits Maximum take-off (5 min) 300 SHP/2700 rpm 
Continuous operation 270 SHP/2400 rpm 
Propeller and Propeller Limits MT Propeller MTV-9-B-C/C200-15 or MTV-14-B-C/C190-17 
(TCDS P-24NE) (TCDS P3BO) 
Diameter 78.74 in. (2000 mm) 74.80 in. (1900 mm) 
Low Pitch 10.5º ± .2º 12.5º ± .2º 
High Pitch 34° ± 1° 34° -1° 
Pitch Radius at 70 cm 66.5 cm 
Airspeed Limits (KCAS) Normal Category Acrobatic Cat

Page 3 of 12 A67EU 
Vne 
Vno 
Va 
220 kt 
140 kt 
140 kt 
220 kt 
158 kt 
158 kt 
Center of Gravity (C.G.) Range All Weights 
Forward C.G. (aft of datum) 19.3 in. (489 mm) 
Rear C.G. (aft of datum) 28.1 in. (714 mm) 
Straight line variation between points. 
Empty Weight (C.G.) Range None. 
Maximum Weight 1808 lbs. (820 kg) - Acrobatic Category. 
2028 lbs. (920 kg) - Normal Category. 
Minimum Crew 1 pilot. 
Number of Seats 1 (71±4 inches). 
Maximum Baggage None. 
Fuel Capacity Fuselage Arm W
44.6 gals (169 liters) usable in normal category or 
12.9 gals (49 liters) usable in acrobatic category at 16.7 in. 
53.6 gals (203 liters) usable in normal category 
(with LONG RANGE OPTION) at 16.7 in. 
.53 gals (2 liters) unusable 
ing Arm 
13 in. 
13 in. 
(See NOTE 1 for data on weight and balance) 
Oil Capacity Minimum sump capacity for normal operation 
Minimum sump capacity for acrobatic operation 
Maximum sump capacity 
(See NOTE 1 for data on weight and balance) 
2.25 gal 
3 gal 
4 gal at -23.4 in. 
Maximum Operational Altitude 16000 ft 
Control Surface Movements Aileron ± 30° 
Elevator ± 26° 
Trim tab ± 15° 
Rudder ± 30° 
For all control surfaces a tolerance of 2° is applied. 
III. Model EA 300/L (Normal, Acrobatic Category), approved March 31, 1995. 
Differences This model features a lower wing position and is not convertible to other listed 
models. 
Engines 1 Textron Lycoming AEIO-540-L1B5 or AEIO-540-L1B5D (FAA TCDS 1E4) 
Optional: 1 Textron Lycoming AEIO-580-B1A (FAA TCDS E00004NY) 
Fuel Avgas 100 or 100LL 
Engine Limits AEIO-540-L1B5 or AEIO-540-L1B5D: 
Maximum take-off (5 min) 300 SHP/2700 rpm 
Continuous operation 270 SHP/2400 rpm 
Maximum take-off and maximum continuous: 300 SHP/2700 rpm (See Note 13)

Page 4 of 12 A67EU 
Engine Limits, cont’d. 
AEIO-580-B1A: 
Maximum take-off and maximum continuous: 315 SHP/2700 rpm 
Maximum take-off and maximum continuous: 303 SHP/2600 rpm (See Note 12) 
Propeller and Propeller Limits 
MT Propeller MTV-9-B-C/C200-15 
FAA TCDS P24NE 
MTV-14-B-C/C190-17 
(See Note 13); 
FAA TCDS P3BO 
MTV-9-B-C/C198-25 (See Note 12); 
FAA TCDS P24NE 
No. of Blades: 3 4 3 
Diameter 78.74 in. (2000 mm) 74.80 in. (1900 mm) 77.95 ± 0.20 in. (1980 mm ± 5 mm) 
Low Pitch 10.5º ± 0.2º 12.5º ± 0.2º 9.5º ± 0.2º 
High Pitch 34° ± 1° 34° - 1° 34º ± 1º 
Pitch Radius at 27.56 in (70 cm) 26.18 in (66.5 cm) 29.13 in. (74 cm) 
Airspeed Limits (KCAS) 
Vne 
Vno 
Va 
Normal Cat. 
220 kt 
140 kt 
140 kt 
Acrobatic Cat. 
220 kt 
158 kt 
158kt 
Center of Gravity (C.G.) Range 
Forward C.G. (aft of datum) 
Rear C.G. (aft of datum) 
All Weights 
26.4 in (671 mm) 
33.1 in (841 mm) 
Empty Weight (C.G.) Range None 
Maximum Weight 1808 lbs (820 kg) - Acrobatic Category (Single seat operation/Acro I) 
1918 lbs (870 kg) - Acrobatic Category (Double seat operation/Acro II) 
2095 lbs (950 kg) - Normal Category and Acrobatic Category (Double seat 
operation/Acro III) 
Empty Weight With AEIO-540-L1B5 and AEIO-540-L1B5D: 
1643 lbs (745 kg) Normal Category 
1607 lbs (729 kg) Raised Standard 
1588 lbs (720 kg) Long Range Option 
- Aerobatic Category: 
1546 lbs (701 kg) - Acrobatic Category (Single seat operation/Acro I) 
1512 lbs (686 kg) - Acrobatic Category Raised Standard 
1466 lbs (665 kg) - Acrobatic Category (Double seat operation/Acro II) 
1643 lbs (745 kg) - Acrobatic Category (Double seat operation/Acro III) 
With AEIO-580-B1A: 
1636 lbs (742 kg) Normal Category 
1607 lbs (729 kg) Raised Standard 
1588 lbs (720 kg) Long Range Option 
- Aerobatic Category: 
1540 lbs (698 kg) - Acrobatic Category (Single seat operation/Acro I) 
1512 lbs (686 kg) - Acrobatic Category Raised Standard 
1460 lbs (662 kg) - Acrobatic Category (Double seat operation/Acro II) 
1636 lbs (742 kg) - Acrobatic Category (Double seat operation/Acro III) 
Minimum Crew 1 pilot (Rear seat) 
Number of Seats 2 (38.4 inches and 82.5 inches aft of datum) 
Maximum Baggage None

Page 5 of 12 A67EU 
Fuel Capacity See Note 1 for data on weight and balance. 
Standard configuration: 
Total capacity: 45.1 gal (171 liters) 
- Wing tanks: 2 x 15.85 gal (60 liters) = 31.7 gal (120 liters); 
Moment arm: 19.8 in (0.51 m) 
- Center tank: 11.1 gal (42 liters); Moment arm: 11.9 in (0.32 m) 
- Acro tank: 2.4 gal (9 liters); Moment arm: 11.0 in (0.28 m) 
Usable fuel in the system: 43.7 gal (165.5 liters) 
Unusable fuel in the system: 1.4 gal (5.5 liters) 
Usable fuel in the center/acro tanks: 12.0 gal (45.5 liters) 
Unusable fuel in the center/acro tanks: 1.4 gal (5.5 liters) 
Long range configuration: 
Total capacity: 54.1 gal (205 liters) 
- Wing tanks: (2 x 20.34 gal (77 liters) = 40.68 gal (154 liters); 
Moment arm: 19.8 in (0.51 m) 
- Center tank: 11.1 gal (42 liters); Moment arm: 11.9 in (0.32 m) 
- Acro tank: 2.4 gal (9 liters); Moment arm: 11.0 in (0.28 m) 
Usable fuel in the system: 52.7 gal (199.5 liters) 
Unusable fuel in the system: 1.4 gal (5.5 liters) 
Usable fuel in the center/acro tanks: 12.0 gal (45.5 liters) 
Unusable fuel in the center/acro tanks: 1.4 gal (5.5 liters) 
Raised standard configuration (See Note 10): 
Total capacity: 49.9 gal (189 liters) 
- Wing tanks: (2 x 15.85 gal (60 liters) = 31.7 gal (120 liters) ; 
Moment arm: 19.8 in (0.51 m) 
- Center tank: 15.85 gal (60 liters); Moment arm: 11.9 in (0.32 m) 
- Acro tank: 2.4 gal (9 liters); Moment arm: 11.0 in (0.28 m) 
Usable fuel in the system: 49.4 gal (187 liters) 
Unusable fuel in the system: 0.5 gal (2 liters) 
Usable fuel in the center/acro tanks: 17.7 gal (67 liters) 
Unusable fuel in the center/acro tanks: 0.5 gal (2 liters) 
Oil Capacity With AEIO-540-L1B5 and AEIO-540-L1B5D: 
Minimum sump capacity for normal operation 
Minimum sump capacity for acrobatic operation 
Maximum sump capacity 
2.25 gal 
3 gal 
4 gal at -23.4 in. 
With AEIO-580-B1A: 
Minimum sump capacity 
Maximum sump capacity 
(See NOTE 1 for data on weight and balance) 
2.25 gal 
4 gal at -23.4 in. 
Maximum Operational Altitude 16000 ft (4877 m) 
Control Surface Movements Aileron ± 30° 
Elevator ± 26° 
Trim tab ± 15° 
Rudder ± 30° 
For all control surfaces a tolerance of 2° is applied. 
IV. Model EA 300/200 (Normal, Acrobatic Category) approved December 20, 1996. 
Differences. This model features revised structure and powerplant and is not convertible to 
other listed models. 
Engine. One (1) Textron Lycoming AEIO-360-A1E (TCDS 1E10) 
Fuel. Avgas 100 or 100LL

Page 6 of 12 A67EU 
Engine Limits. Maximum Takeoff (5 minutes) 
Continuous Operation 
200 SHP/2700 RPM 
185 SHP/2500 RPM 
Propeller and Propeller Limits MTV-12-B-C/C183-17e (TCDS P-25NE) 
3 blades 
Diameter 72.05 in (1830 mm) 
Pitch (R=64 cm): Low 12.5° ± .2°; High 30° ± 1° 
Airspeed Limits (KCAS). Normal Cat. Acrobatic Cat. 
Vne 220 220 
Vno 140 158 
Va 140 158 
Center of Gravity (C.G.) Range All Weights 
Forward C.G. (aft of datum) 28.8 in. (732 mm) 
Rear C.G. (aft of datum) 35 in. (891 mm) 
Straight line variation between points 
Empty Weight C.G. Range None 
Maximum Weight. 1549 lbs (700 kg) - Acrobatic Category (Single seat operation/Acro I) 
1770 lbs (800 kg) - Acrobatic Category (Double seat operation/Acro II) 
1858 lbs (840 kg) - Normal Category 
Minimum Crew 1 pilot (Rear seat) 
Number of Seats 2 (37 inches and 73 inches) 
Maximum Baggage None 
Fuel Capacity. Fuselage Arm Wing Arm 
8.5 gals (32 liters) usable (A) category or 
30.8 gals (117 liters) usable (N) category at 13.8 in 19.8 in. 
and 1.3 gals (5 liters) unusable in 
center, acro, and wing tanks 
48.8 gals (185 liters) usable in normal category 
(with LONG RANGE option) at 13.8 in 19.8 in 
(See NOTE 1 for data on weight and balance) 
Oil Capacity. (N) Category (A) Category 
Minimum sump 1 gal 1.5 gals 
Maximum sump 2 gals at -21in 2 gals at -21in 
(See NOTE 1 for data on weight and balance) 
Maximum Operational Altitude. 16000 ft. 
Control Surface Movements. Aileron ± 30° 
Elevator ± 22° 
Trim Tab ± 15° 
Rudder ± 30° 
V. Model EA 300/LC (Acrobatic Category), approved June 5, 2014. 
Differences This model is based on EA 300/L but features revised structure and is not 
convertible to other listed models. 
Engines 1 Textron Lycoming AEIO-580-B1A (FAA TCDS E00004NY) 
Fuel Avgas 100 or 100LL

Page 7 of 12 A67EU 
Engine Limits Maximum take-off and maximum continuous: 303 SHP/2600 RPM 
Propeller and Propeller Limits 
MT Propeller MTV-9-B-C/C198-25; 
FAA TCDS P24NE 
MTV-14-B-C/C190-130; 
FAA TCDS P3BO 
No. of Blades: 3 4 
Diameter 77.95 ± 0.20 in. (1980 mm ± 5 mm) 74.80 ± 0.20 in. (1900 mm ± 5 mm) 
Low Pitch 9.5º ± 0.2º 9º ± 0.2º 
High Pitch 34º ± 1º 34° - 1° 
Pitch Radius at 29.13 in. (74 cm) 27.95 in (71 cm) 
Airspeed Limits (KCAS) Acrobatic Cat. 
Vne 220 kt 
Vno 158 kt 
Va 158kt 
Center of Gravity (C.G.) Range 
Forward C.G. (aft of datum) 
Rear C.G. (aft of datum) 
All Weights 
26.4 in (671 mm) 
33.1 in (841 mm) 
Empty Weight (C.G.) Range None 
Maximum Weight 1808 lbs (820 kg) - Acrobatic Category (Single seat operation/Acro I) 
1918 lbs (870 kg) - Acrobatic Category (Double seat operation/Acro II) 
2095 lbs (950 kg) - Acrobatic Category (Double seat operation/Acro III) 
Empty Weight 1513 lbs (686 kg) - Acrobatic Category (Single seat operation/Acro I) 
1460 lbs (662 kg) - Acrobatic Category (Double seat operation/Acro II) 
1636 lbs (742 kg) - Acrobatic Category (Double seat operation/Acro III) 
Minimum Crew 1 pilot (Rear seat) 
Number of Seats 2 (38.4 inches and 82.5 inches aft of datum) 
Maximum Baggage None 
Fuel Capacity See Note 1 for data on weight and balance. 
Total capacity: 49.9 gal (189 liters) 
- Wing tanks: (2 x 15.85 gal (60 liters) = 31.7 gal (120 liters) ; 
Moment arm: 19.8 in (0.51 m) 
- Center tank: 15.85 gal (60 liters); Moment arm: 11.9 in (0.32 m) 
- Acro tank: 2.4 gal (9 liters); Moment arm: 11.0 in (0.28 m) 
Usable fuel in the system: 49.4 gal (187 liters) 
Unusable fuel in the system: 0.5 gal (2 liters) 
Usable fuel in the center/acro tanks: 17.7 gal (67 liters) 
Unusable fuel in the center/acro tanks: 0.5 gal (2 liters) 
Oil Capacity Minimum sump capacity 2.25 gal 
Maximum sump capacity 4 gal at -23.4 in. 
(See NOTE 1 for data on weight and balance) 
Maximum Operational Altitude 10000 ft (3048 m) 
Control Surface Movements Aileron 
Elevator 
Trim tab 
Rudder 
30°±2° upward 
25°±2° upward 
35°±2° upward 
30°±2° left 
30°±2° downward 
25°-2° downward 
27°±2° downward 
30°±2° right

Page 8 of 12 A67EU 
DATA PERTINENT TO ALL MODELS. 
Datum. Plane of Firewall. 
Leveling Means. Upper fuselage longeron. 
Serial Numbers Eligible. Each individual aircraft manufactured under this type certificate must be 
accompanied by an Export Certificate of Airworthiness as noted below under 
“Import Requirements” when an application for a U.S. airworthiness certificate 
is made. 
Model EA 300/SEA 300 serial numbers 35 to 67 (airplanes manufactured by 
Extra Flugzeugbau GmbH) and serial numbers 1068 and on (continuation of 
manufacture by Extra Flugzeugproduktions- und Vertriebs- GmbH.) 
(See NOTE 4) 
Model EA 300/S serial number 1 to 31 (airplanes manufactured by Extra 
Flugzeugbau GmbH) and serial numbers 1032 and on (continuation of 
manufacture by Extra Flugzeugproduktions- und Vertriebs- GmbH.) 
(See NOTE 5) 
Model EA 300/L serial number 1 to 167 (airplanes manufactured by Extra 
Flugzeugbau GmbH) and serial numbers 168 to 170, 1171, 172, 173, 1174 and 
on (continuation of manufacture by Extra Flugzeugproduktions- und Vertriebs-
GmbH.) (See Note 10.) 
Serial numbers 166 and 167 are under warranty of Extra Flugzeugproduktions-
und Vertriebs- GmbH although manufactured by Extra Flugzeugbau GmbH. 
Model EA 300 200 serial number 1 to 31 (airplanes manufactured by Extra 
Flugzeugbau GmbH) and serial numbers 1032 and on (continuation of 
manufacture by Extra Flugzeugproduktions- und Vertriebs- GmbH.) (All serial 
numbers must conform with requirements of the manufacturer’s Modification 
Instruction, Document No. UA-300-1-96, Issue A, December 17, 1996, or later 
approved revision.) (See Note 8.) 
Only model EA 300/L serial numbers 1282 and subsequent are eligible to be 
equipped with the AEIO-580-B1A engine. 
Model EA 300 LC serial number LC001, LC002, LC003 and on (airplanes 
manufactured by Extra Flugzeugproduktions- und Vertriebs- GmbH.) 
See type certificate holder record. 
Import Requirements For aircraft produced in Germany, the FAA can issue a U.S. airworthiness 
certificate based on a Lufthaft Bundesamt (LBA) Export Certificate of 
Airworthiness (Export C of A). The Export C of A should contain the 
following statement, “The [insert aircraft MODEL] covered by this certificate 
conforms to the type design approved under U.S. Type Certificate Number 
A67EU, and is found to be in a condition for safe operation.” 
Refer to the applicable bilateral agreement to verify eligibility for import into the 
United States of both new and used aircraft based on the scope of the agreement, to 
identify any required statements by the exporting authority on the export certificate 
of airworthiness (or equivalent document), and for procedures for coordinating 
exceptions to conformity statements on these documents. Refer to FAA Order 
8130.2, Airworthiness Certification of Aircraft, for requirements for issuance of an 
airworthiness certificate for imported aircraft. 
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,

Page 9 of 12 A67EU 
• Structural repair manuals, 
• Vendor manuals, 
• Aircraft flight manuals, and 
• Overhaul and maintenance manuals.The FAA accepts such documents 
and considers them FAA-approved unless oneof 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. 
Certification Basis 1. Model EA 300: TC Application Date: February 7, 1989 
Model EA 300/S: TC Application Date: April 30, 1993 
Model EA 300/L:  TC Application Date: November 28, 1994 
FAR 23 effective February 1, 1965, as amended through Amendment 
23-34 effective September 14, 1987; FAR 36 effective December 1, 
1969, as amended through Amendment 36-20 effective September 
16, 1992; and Special Conditions as published in Federal Register, 
FR Vol. 57, No. 175, September 9, 1992. For Revision 10 of this TCDS, the 
model EA-300/L amendment level to FAR 36 is Amendment 28, effective 
February 03, 2006. 
2. Model EA 300 200 (TC Application Date: July 22, 1996) 
FAR 23 effective February 1, 1965, as amended through Amendment 
23-34 effective September 14, 1987; Equivalent Level of Safety 
(ACE-96-6) dated December 4, 1996, for paragraphs 23.963(e), 23.1337(b), 
and 23.1553; FAR 36 effective December 1, 1969, amended through 
Amendment 36-21 effective December 28, 1995; and Special Conditions as 
published in Federal Register, FR Vol. 57, No. 175, September 9, 1992. 
3. Model EA 300/LC: TC Application Date: January 31, 2011 
14 CFR Part 23 effective February 1, 1965, including Amendment 23-1 through 
Amendment 23-34 effective September 14, 1987; 
14 CFR Part 36 effective December 1, 1969, including Amendment 36-1 
through Amendment 36-28 effective February 03, 2006; 
Equivalent Level of Safety as follows: 
(a) ACE-14-8: 14 CFR Section 23.207, Stall Warning 
(b) ACE-14-7: 14 CFR Section 23.777(d), Powerplant Controls Location 
(c) ACE-14-7: 14 CFR Section 23.781(b), Throttle Control Shape 
Special Condition 23-262-CE EA 300/LC; Acrobatic Category Aerodynamic 
Stability, dated May 7, 2014 
The Luftfahrt Bundesamt originally type certificated the aircraft EA 300, EA 
300/S, EA 300/L and EA 300/200 under its type certificate Number 1086. The 
FAA validated this product under U.S. Type Certificate Number A67EU. 
Effective September 28, 2003, the European Aviation Safety Agency (EASA) 
began oversight of this product on behalf of Germany. 
Equipment The basic required equipment as prescribed in the applicable 
airworthiness regulations (see Certification Basis) must be installed 
in the aircraft for airworthiness certification. In addition, the 
following items of equipment are required. 
1. Model EA 300: 
Pilot’s Operating Handbook and LBA approved Airplane

Page 10 of 12 A67EU 
Flight Manual dated October 30, 1990, Doc. No. EA-
03701, or later LBA or EASA approved revision, 
2. Model EA 300/S: 
Pilot’s Operating Handbook and LBA approved Airplane 
Flight Manual dated March 19, 1993, Doc. No. EA-
04701, or later LBA or EASA approved revision. 
3. Model EA 300/L: 
Pilot’s Operating Handbook and LBA approved Airplane 
Flight Manual dated January 31, 1995, Doc. No. EA-
06701, or later LBA or EASA approved revision. 
4. Model EA 300/200: 
Pilot’s Operating Handbook and LBA approved Airplane 
Flight Manual dated August 12, 1996, Doc. No. EA-
07701, or later LBA or EASA approved revision. 
5. Model EA 300/LC: 
Pilot’s Operating Handbook and FAA approved Airplane 
Flight Manual dated Februrary 19, 2014, Doc. No. EA-0E701US, 
or later EASA (in behalf of FAA) approved revision. 
The following optional equipment is available for the EA 300/L ex-factory: 
- Aspen Avionics model EFD1000 Electronic Flight Instrument System in accordance
with Extra Document ÄM-300-09-01. 
- Artex model ME406 series Emergency Locator Transmitter 
- Garmin GNC 420W COM/GPS 
NOTE 1. A current weight and balance report including list of equipment included in the 
certificated empty weight, and loading instructions when necessary, must be provided for 
each aircraft at the time of original airworthiness certification, and at all times thereafter. 
Model EA 300: 
The certificated empty weight and the corresponding center of gravity location must 
include full oil (29.92 lbs at -23.4 inches), and unusable fuel (3.18 lbs. at 21.7 inches) 
Model EA 300/S: 
The certificated empty weight and the corresponding center of gravity location must 
include full oil (29.92 lbs at -23.4 inches), and unusable fuel (3.12 lbs at 16.7 inches) 
Model EA 300/L: 
The certificated empty weight and the corresponding center of gravity location must 
include full oil (29.92 lbs at -23.4 inches), and unusable fuel (8.7 lbs or 3.2 lbs at 11.7 
inches; see fuel capacity) 
Model EA 300/200: 
The certificated empty weight and the corresponding center of gravity location must 
include full oil (14.96 lbs at -21inches), and unusable fuel (7.8 lbs at 13.8 inches) 
Model EA 300/LC: 
The certificated empty weight and the corresponding center of gravity location must 
include full oil (29.92 lbs at -23.4 inches), and unusable fuel (3.2 lbs at 11.7 inches; see 
fuel capacity) 
NOTE 2. Placards (Refer to Manufacturer’s Specifications for a complete listing): All 
required placards as listed in the approved Airplane Flight Manual must be 
installed in the appropriate locations. 
(1) The following placard must be displayed in clear view of the pilot: 
For EA 300, EA 300/S, EA 300/L and EA 300 200 -
(A) “THE MARKINGS AND PLACARDS INSTALLED IN THIS AIRPLANE

Page 11 of 12 A67EU 
CONTAIN OPERATING LIMITATIONS WHICH MUST BE COMPLIED WITH 
WHEN OPERATING THIS AIRPLANE IN THE ACROBATIC CATEGORY. OTHER 
LIMITATIONS WHICH MUST BE COMPLIED WITH WHEN OPERATING THIS 
AIRPLANE IN THE NORMAL CATEGORY ARE CONTAINED IN THE AIRPLANE 
FLIGHT MANUAL.” APPLICABLE RPM LIMITATIONS MUST BE OBSERVED. 
For EA 300/LC -
(A) “THE MARKINGS AND PLACARDS INSTALLED IN THIS AIRPLANE 
CONTAIN OPERATING LIMITATIONS WHICH MUST BE COMPLIED WITH 
WHEN OPERATING THIS AIRPLANE IN THE ACROBATIC CATEGORY. OTHER 
LIMITATIONS WHICH MUST BE COMPLIED WITH WHEN OPERATING THIS 
AIRPLANE IN THIS CATEGORY ARE CONTAINED IN THE AIRPLANE FLIGHT 
MANUAL.” 
(B) “THIS AIRPLANE IS CERTIFIED FOR VFR DAY OPERATION ONLY. 
OPERATION UNDER KNOWN ICING CONDITIONS PROHIBITED.” 
(2) Refer to the Airplane Flight Manual, Limitations section, for a listing of other 
required placards. 
NOTE 3. Model EA 300: 
Instructions for Continued Airworthiness and Service Life Limits of components 
include the Service Manual, and are contained in Doc. EA-03702. Revisions to 
Airworthiness Limitations must be approved by of the FAA. 
Model EA 300/S: 
Instructions for Continued Airworthiness and Service Life Limits of components 
include the Service Manual, and are contained in Doc. EA-04702. Revisions to 
Airworthiness Limitations must be approved by of the FAA. 
Model EA 300/L: 
Instructions for Continued Airworthiness and Service Life Limits of components 
include the Service Manual, and are contained in Doc. EA-06702. Revisions to 
Airworthiness Limitations must be approved by of the FAA. 
Model EA 300 200: 
Instructions for Continued Airworthiness and Service Life Limits of components 
include the Service Manual, and are contained in Doc. EA-07702. Revisions to 
Airworthiness Limitations must be approved by of the FAA. 
Model EA 300/LC: 
Instructions for Continued Airworthiness and Service Life Limits of components include 
the Maintenance Manual, and are contained in Doc. EA-0E702. Revisions to 
Airworthiness Limitations must be approved by of the FAA. 
All manufacturer’s service bulletins (and other manual material) which contain 
a statement that the document is approved by the exporting civil aviation authority 
(LBA or EASA) may be interpreted as FAA approved. These approvals pertain to the type 
design only. 
All service bulletins classified as Mandatory by the LBA or EASA are identified to that 
effect and are subject to an Airworthiness Directive issued by the FAA. 
NOTE 4. Model EA 300: 
Serial Nos. V1, 03, 05, 06, and 15 through 34 are eligible if modified in accordance 
with Extra Documents EA-03105 and AM-300-1-92. 
Service Life is limited to 300 flight hours for Serial Nos. V1, 03, 05, 06, and 15 through 
45 unless modified in accordance with Extra Service Bulletin No. 300-2-93, Rev. B, 
dated June 28, 1993.

Page 12 of 12 A67EU 
NOTE 5. Model EA 300/S: 
Service Life is limited to 300 flight hours for Serial Nos. 01 through 17 unless modified 
in accordance with Extra Service Bulletin No. 300-2-93, Rev. B, dated June 28, 1993. 
NOTE 6. Changing the color and the thickness of the surface coating is only permissible after prior 
approval by the manufacturer (refer to Extra document number EA-03205.19.) 
NOTE 7. Major structural repairs must be accomplished at FAA certified repair stations rated 
for composite aircraft structure work, in accordance with Extra repair methods approved 
by LBA or EASA and accepted by the FAA. 
NOTE 8 The fuel capacity of the wing tank and the maneuvering speed of S/N 01 and 02 differ 
from the model design: 
a) Maneuvering speed (Acrobatic Category): VA = 139 KIAS (VA = 140 KCAS) 
b) Wing and acro tank: 
Total fuel capacity: 41.2 gals (156 liters) 
Usable fuel capacity: 39.9 gals (151 liters) 
c) Operator's Instruction: 
Airplane Flight Manual Supplement EXTRA 300/200 Doc. No. EA-07701.2, 
LBA approved, approval date August 12, 1996 at the latest issue. 
NOTE 9 Extra Flugzeugproduktions- und Vertriebs- GmbH is the successor firm of Extra 
Flugzeugbau GmbH, which filed for insolvency on January 28, 2003. 
NOTE 10 EA 300/L serial numbers 168, 169, 170, and 173 manufactured by Extra 
Flugzeugproduktions- und Vertriebs- GmbH to be changed with FAA permission to 
1168, 1169, 1170, and 1173. 
NOTE 11 The center fuel tank with an increased capacity from 11.1 to 15.85 gal (42 to 60 liters) is 
available ex-factory only for the fuselage fuel tank system of the Model EA 300/L. It can 
not be combined with the increased fuel capacity of the wing fuel tank of the long range 
tank option. 
NOTE 12 Installation of the alternate propeller, MT Propeller model MTV-9-B-C/C198-25 is only 
approved in combination with the Lycoming eingine AEIO-580-B1A specified in Section 
III. When this combination is used, the exhaust silerncer system type Gomolzig EA300-
606000 must be installed and the aircraft must be limited to a reduced maximum take-off 
engine rotational speed of 2600 RPM. 
NOTE 13 Use of MT Propeller 4-blade model MTV-14-B-C/C190-17 must be combined with the 
exhaust silencer system type Gomolzig EA300-606500 or EA300-606000. When the MT 
Propeller 4-blade model MTV-14-B-C/C190-17 is installed on the Model EA 300/L, the 
maximum continuous engine rotational speed of 2700 RPM is allowed. 
NOTE 14 Model EA 300/L serial numbers 1 to 167 were manufactured by Extra Flugzeugbau 
GmbH. Serial numbers 168 through 170, 1171, 1172, 173, 1174 and on are manufactured 
by Extra Flugzeugproduktions- und Vertriebs- GmbH. 
NOTE 15 Model EA 300/L serial numbers 1 to 167 were manufactured by Extra Flugzeugbau 
GmbH. Serial numbers 168 through 170, 1171, 1172, 173, 1174 and on are manufactured 
by Extra Flugzeugproduktions- und Vertriebs- GmbH. 
.....END.....
```

## ADs (14, 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 2010-04-11](https://openairdocs.org/ad/2010-04-11): Fuselage · Extra Flugzeugproduktions- und Vertriebs- EA-300L and EA-300/200. Effective Mar 30, 2010
- [AD 2007-02-11](https://openairdocs.org/ad/2007-02-11): Upper longeron · Extra Flugzeugproduktions- und Vertriebs- EA-300, EA-300L, EA-300S and 1 more. Effective Feb 28, 2007
- [AD 2005-11-07](https://openairdocs.org/ad/2005-11-07): Bottom fuselage cover (belly fairing) and the firewall · Extra Flugzeugproduktions- und Vertriebs- EA-300, EA-300L, EA-300S and 1 more. Effective Jul 18, 2005
- [AD 2005-01-17](https://openairdocs.org/ad/2005-01-17): Upper longeron cutout-bridge · Extra Flugzeugproduktions- und Vertriebs- EA-300 and EA-300S. Effective Feb 28, 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 2003-17-02](https://openairdocs.org/ad/2003-17-02): Fuel selector valve · Extra Flugzeugproduktions- und Vertriebs- EA-300L, EA-300S and EA-300/200. Effective Oct 10, 2003
- [AD 98-24-07](https://openairdocs.org/ad/98-24-07): Rudder Pedal Footrest · Extra Flugzeugproduktions- und Vertriebs- EA-300, EA-300L and EA-300S. Effective Dec 28, 1998
- [AD 98-09-10](https://openairdocs.org/ad/98-09-10): Rudder Control Cables · Extra Flugzeugproduktions- und Vertriebs- EA-300 and EA-300S. Effective Jun 7, 1998
- [AD 98-06-03](https://openairdocs.org/ad/98-06-03): Elevator Mass Balance Assemblies · Extra Flugzeugproduktions- und Vertriebs- EA-300. Effective Apr 24, 1998
- [AD 98-04-01](https://openairdocs.org/ad/98-04-01): Canopy Latches · Extra Flugzeugproduktions- und Vertriebs- EA-300 and EA-300S. Effective Mar 24, 1998
- [AD 97-22-03](https://openairdocs.org/ad/97-22-03): Seat Belt Safety Cover · Extra Flugzeugproduktions- und Vertriebs- EA-300/200. Effective Nov 24, 1997
- [AD 2002-21-11](https://openairdocs.org/ad/2002-21-11) (historical): Horizontal stabilizer · Extra Flugzeugproduktions- und Vertriebs- EA-300S. Effective Dec 17, 2002
- [AD 98-03-14](https://openairdocs.org/ad/98-03-14) (historical): Upper Longeron Cutout Bridge · Extra Flugzeugproduktions- und Vertriebs- EA-300 and EA-300S. Effective Mar 16, 1998

## Registered aircraft by registry model (OpenAirDocs)

- [Extra Flugzeugbau EA 300/L](https://openairdocs.org/model/extra-flugzeugbau-ea-300-l): 125 aircraft (registry code 70218DG)
- [Extra Flugzeugproduktions-Und EA 300/LC](https://openairdocs.org/model/extra-flugzeugproduktions-und-ea-300-lc): 36 aircraft (registry code 70218DQ)
- [Extra Flugzeugproduktions EA 300/L](https://openairdocs.org/model/extra-flugzeugproduktions-ea-300-l): 32 aircraft (registry code 70218DN)
- [Extra Flugzeugbau EA-300](https://openairdocs.org/model/extra-flugzeugbau-ea-300): 22 aircraft (registry code 70218DI)
- [Extra Flugzeugbau EA 300/S](https://openairdocs.org/model/extra-flugzeugbau-ea-300-s): 13 aircraft (registry code 70218DE)
- [Extra Flugzeugbau EA300/200](https://openairdocs.org/model/extra-flugzeugbau-ea300-200): 9 aircraft (registry code 7021803)
- [Extra Flugzeugproduktions-Und EA300/L (EXTRA)](https://openairdocs.org/model/extra-flugzeugproduktions-und-ea300-l-extra): 1 aircraft (registry code 70218DS)
- [Extra Flugzeugproduktions-Und EA 300](https://openairdocs.org/model/extra-flugzeugproduktions-und-ea-300): 0 aircraft (registry code 70218DD)

## STCs approved under this data sheet (80, 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 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 SA01005DE](https://openairdocs.org/stc/SA01005DE): Installation of a EarthX ETX900-TSO Lithium battery. EarthX Inc.
- [STC SA04046CH PAGE 1](https://openairdocs.org/stc/SA04046CH%20PAGE%201): Installation of L-3 GENESIS  (TM) Electronic Standby Instrument System (ESI-500/MAG-500). Acron Aviation Inc.
- [STC SA04378CH](https://openairdocs.org/stc/SA04378CH): Installation of an engine modified per STC SE04349CH. SureFly Partners Ltd.
- [STC SA4503NM](https://openairdocs.org/stc/SA4503NM): Remove original cloth covering and install Ceconite covering. Ceconite Division of Poly-Fiber Inc.
- [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 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 SA03282CH](https://openairdocs.org/stc/SA03282CH): Installation of MT propeller model MTV-9-B/C/C200-25. McFarlane Aviation LLC
- [STC SA01967WI](https://openairdocs.org/stc/SA01967WI): Use of GAMI G100UL High Octane Unleaded Avgas. General Aviation Modifications Inc.
- [STC SA04776NY](https://openairdocs.org/stc/SA04776NY): The HIPEC Covering and Finishing System must be performed and maintained. HIPEC Aircraft Coatings Inc.
- [STC SA02444AK](https://openairdocs.org/stc/SA02444AK): Approval of the L-3 Communications NGT 9000/9000R ADS-B system installed. ADS-B Technologies LLC
- [STC SA01818WI](https://openairdocs.org/stc/SA01818WI): Installation of Garmin G5 Electronic Flight Instrument. Garmin International Inc.
- [STC 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 SA09920AC](https://openairdocs.org/stc/SA09920AC): Installation of a Hartzell Propeller Inc. model HC-C3YR-4BN/NC8302-7. Hartzell Propeller 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 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 SA04424AT](https://openairdocs.org/stc/SA04424AT): Installation of Continental Motors, Inc. (CMI) Shower-of-Sparks  Starting Vibrator Booster Systems. Continental Motors, Inc.
- [STC SA01835WI](https://openairdocs.org/stc/SA01835WI): Installation of Trig Avionics TY-96 or TY-97 VHF Communications Radio. Peregrine
- [STC SA00024NY](https://openairdocs.org/stc/SA00024NY): Installation of Airwolf remote mounted engine oil filter kit AFC-K007 on single or multi-engine fixed wing light aircraft incorporating Lycoming reciprocating engines of 450 horsepower or less.. Airwolf Filter Corporation
- [STC SA01933LA-D](https://openairdocs.org/stc/SA01933LA-D): Installation of Garmin Model 400W / 500W Series GPS-WAAS Navigation System. Garmin International Inc
- [STC 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 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 SA03861NY](https://openairdocs.org/stc/SA03861NY): Installation of Main Wheels and Brake System. Beringer Aero
- [STC SA00352BO PAGE 1](https://openairdocs.org/stc/SA00352BO%20PAGE%201): Installation of an Avidyne Corporation Mode A/C/S Transponder with ADS-B Out capability, Model AXP340 loaded with Version 3.13 software (or later FAA approved version),. Avidyne Corporation
- [STC SA02119SE PAGE 1](https://openairdocs.org/stc/SA02119SE%20PAGE%201): Installation of Garmin GDL 88 ADS-B UAT Transceiver System. Garmin International Inc
- [STC SA00478CH](https://openairdocs.org/stc/SA00478CH): Installation of Cooper Superflite 102 Fabric.. Aviation Products Systems Inc.
- [STC SA01229SE PAGE 1](https://openairdocs.org/stc/SA01229SE%20PAGE%201): Installation of GNS 480 (CNX80) GPS WAAS Navigator with integrated VHF Navigation and Communication radios. Garmin International Inc
- [STC SA02442AK PAGE 1](https://openairdocs.org/stc/SA02442AK%20PAGE%201): Approval of the L-3 Communications NGT 2000/2500 ADS-B system. ADS-B Technologies, LLC
- [STC SA01933LA-D PAGE 1](https://openairdocs.org/stc/SA01933LA-D%20PAGE%201): Installation of Garmin Model 400W / 500W Series GPS-WAAS Navigation
System. Garmin International Inc
- [STC SA02283SE PAGE 1](https://openairdocs.org/stc/SA02283SE%20PAGE%201): Installation of Electronics International Inc. Glass Panel Engine Monitor (with In Flight Data) CGR-30P. Electronics International Inc.
- [STC SA02402SE PAGE 1](https://openairdocs.org/stc/SA02402SE%20PAGE%201): Installation of Electronics International Inc. Glass Panel Engine Monitor (with In-Flight Data) CGR-30C. Electronics International Inc.
- [STC SA02717NY PAGE 1](https://openairdocs.org/stc/SA02717NY%20PAGE%201): Installation of VoiceFlight Systems LLC VFS101 Speech Recognition Module. VoiceFlight Systems LLC
- [STC SA02015SE-D](https://openairdocs.org/stc/SA02015SE-D): Installation of Garmin G500 Primary Flight Display (PFD) and Multifunction Display (MFD) System.. Garmin International Inc

All 80: https://openairdocs.org/tcds/A67EU/stcs.md

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