TCDS A67EU

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