TCDS A51CE

Page No. 1 2 3 4 5 6 7 Rev. No. 7 6 6 6 7 6 - DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION A51CE Revision 7 AQUILA Aviation GmbH AT01 AT01-100 July 29, 2021 TYPE CERTIFICATION DATA SHEET NO. A51CE This data sheet, which is part of Type Certificate No. A51CE prescribes conditions and limitations under which the product for which the type certification was issued meets the airworthiness requirements of the Federal Aviation Regulations. Type Certificate Holder AQUILA Aviation GmbH OT Schoenhagen Flugplatz 14959 Trebbin Germany Type Certificate Holder Record AQUILA – Aviation by Excellence AG change name to AQUILA Aviation GmbH on May 29, 2013 AQUILA Technische Entwicklungen GmbH Flugplatz D-14959 Schoenhagen Germany transferred TC A51CE to AQUILA – Aviation by Excellence AG on November 19, 2008. I. Model AQUILA AT01, (JAR-VLA), approved November 4, 2003 Engine One Rotax 912 S3, TCDS E00051EN Fuel See Pilot's Operating Manual/Airplane Flight Manual Oil API System “SF” or “SG” multi grade (See Airplane Flight Manual recommendations) Do not use aviation grade lubricants. Coolant See Pilot's Operating Manual/Airplane Flight Manual Engine Limits All operations, 5500 rpm (2260 propeller rpm), (92.5 hp, 69 kW) Propeller Mt-propeller, MTV-21-A/175-05 constant speed. TCDS P16BO Propeller Limits Diameter: Maximum 69.1 inches (1755 mm) Minimum 68.7 inches (1745 mm) Airspeed Limits VNE 165 KIAS 162 KCAS VA 112 KIAS 109 KCAS VNO 130 KIAS 128 KCAS VFE (TAKEOFF FLAPS) 90 KIAS 87 KCAS VFE (MAXIMUM FLAPS) 90 KIAS 87 KCAS C.G. Range 16.8 inches (427 mm) to 20.6 in (523 mm) aft of datum line. 2 of 6 A51CE Reference Datum Wing leading edge at wing root. Leveling Means Wedge 800:77 (5.5°) on top of fuselage cone at 31.5 inches (800mm) in front of horizontal tail leading edge Maximum Weight Takeoff and Landing 1653 pounds (750 kg) Minimum Crew 1 No. of Seats 2 adjustable seats at 17.9 inches (454 mm) to 23.3 inches (591 mm). Maximum Baggage Baggage compartment 88.2 lbs (40 kg) at 51.2 inches (1350 mm) aft of datum. Fuel Capacity 31.6 gallons (120 liters) total fuel in wing tanks. 29.0 gallons (109.6 liters) usable. Oil Capacity 3.2 quarts (3.0 liters) total in reservoir at 33.0 (838 mm) in front of datum 1.1 quarts (1.0 liters) usable Coolant Capacity 2.5 quarts (2.4 liters) total minimum 2.6 quarts (2.5 liters) total maximum in engine housing and cooler at 46.0 (1170 mm) in front of datum Maximum Operating Altitude 14500 feet Control Surface Movements Aileron trailing edge up 16° + 1.5° trailing edge down 11° + 1.0° Elevator trailing edge up 23° ± 1.5° trailing edge down 24° ± 1.5° Rudder left/right 29° ± 1.5° Wing flaps up 0° at stop of slotted flap take off 17° ± 1.5° landing 35° ± 1.5° Manufacturer’s Serial Numbers - AT01-101 up to AT01-182 (only manufactured by AQUILA Technische Entwicklungen GmbH in Germany.) - AT01-183 up to AT01-299 (only manufactured by AQUILA Aviation by Excellence AG in Germany.) Certification Basis Certificated under the Special Class provisions of 14 Code of Federal Regulations (CFR), Part 21.17(b) -- JAR-VLA thru amendment VLA/92/1 effective January 1, 1992 and Additional Requirements: Aquila GmbH Engine Mount Connection Design criteria and Winglets for the Aquila GmbH AT01 JAR-VLA Airplane, (final criteria issued 10-20-2003 and published in the Federal Register FR Doc. 03-28138 dated November 10, 2003) (68 FR 56809). 14 CFR Part 36 effective November 18, 1969, including Amendments 36-1 through 36-24 Additional Requirements for Night VFR option – Must have AQUILA modification/SB-AT01-010 incorporated for this Option: (See Note 7): The EASA Special Conditions are Special Conditions VLA 1, VLA 181, VLA 773, VLA 807, VLA 903, VLA 905, VLA 1107, VLA 1121, VLA 1143, VLA 1147, VLA 1322, VLA 1325, VLA 1331, VLA 1351, VLA 1353, VLA 1381, VLA 1383, VLA 1431, VLA 1547, VLA 1559 and VLA 1583. The FAA also adopted the corresponding EASA acceptable Means of Compliance (AMC) as shown in appendix 2 of the CRI A-01 for the 3 of 6 A51CE night VFR project. (final design criteria issued 8-12-2013 as published in the Federal Register FR Doc. 2013-20151 dated August 19, 2013) (78 FR 50313). Type Certificate No. A51CE was issued November 4, 2003. Date of Application for Type Certificate was December 3, 2001. The Luftfahrt Bundesamt originally type certificated this aircraft under its type certificate Number 1106. The FAA validated this product under U.S. Type Certificate Number A51CE. 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 airplane for certification. In addition, the following items of equipment are required: Pilot’s Operating Handbook and Airplane Flight Manual, document number AT01-1010-100-US, Rev. A.01 dated July 18, 2003 or later approved revision, must be carried. The list of basic required equipment for Day-VFR operation is contained in the Pilot’s Operating Handbook (POH) and Airplane Flight Manual (AFM). The required Night VFR operation equipment is in Pilot’s Operating Handbook and Airplane Flight Manual, document number AT01-1010-100-US, Rev. B.04 dated March 18, 2013 or later approved revision. Limitations (Reserved.) II. Model AQUILA AT01-100, (JAR-VLA), approved December 18, 2013 Engine One Rotax 912 S3, TCDS E00051EN Fuel See Pilot's Operating Manual/Airplane Flight Manual Oil API System “SF” or “SG” multi grade (See Airplane Flight Manual recommendations) Do not use aviation grade lubricants. Coolant See Pilot's Operating Manual/Airplane Flight Manual Engine Limits Maximum take off power, 5800 rpm (2385 propeller rpm), (98.6 hp, 73.5 kW) Maximum continuous power, 5500 rpm (2260 propeller rpm), (92.5 hp, 69 kW) Propeller Mt-propeller, MTV-21-A/170-05 constant speed 2-bladed. TCDS P16BO Propeller Limits Diameter: Maximum 67.1 inches (1705 mm) Minimum 66.7 inches (1695 mm) Airspeed Limits VNE 165 KIAS 162 KCAS VA 112 KIAS 109 KCAS VNO 130 KIAS 128 KCAS VFE (TAKEOFF FLAPS) 90 KIAS 87 KCAS VFE (MAXIMUM FLAPS) 90 KIAS 87 KCAS C.G. Range 16.8 inches (427 mm) to 20.6 in (523 mm) aft of datum line. Reference Datum Wing leading edge at wing root. Leveling Means Wedge 800:77 (5.5°) on top of fuselage cone at 31.5 inches (800mm) in front of horizontal tail leading edge Maximum Weight Takeoff and Landing 1653 pounds (750 kg) 4 of 6 A51CE Minimum Crew 1 No. of Seats 2 adjustable seats at 19.1 inches (484 mm) to 22.8 inches (581 mm). Maximum Baggage Baggage compartment 88.2 lbs (40 kg) at 51.2 inches (1300 mm) aft of datum. Fuel Capacity 31.6 gallons (120 liters) total fuel in wing tanks. 29.0 gallons (109. 6 liters) usable. Oil Capacity 3.2 quarts (3.0 liters) total in reservoir at 33.0 (838 mm) in front of datum 1.1 quarts (1.0 liters) usable Coolant Capacity 2.5 quarts (2.4 liters) total minimum 2.6 quarts (2.5 liters) total maximum in engine housing and cooler at 46.0 (1170 mm) in front of datum Maximum Operating Altitude 14500 feet Control Surface Movements Aileron trailing edge up 16° + 1.5° trailing edge down 11° + 1.0° Elevator trailing edge up 23° ± 1.5° trailing edge down 24° ± 1.5° Rudder left/right 29° ± 1.5° Wing flaps up 0° at stop of slotted flap take off 17° ± 1.5° landing 35° ± 1.5° Manufacturer’s Serial Numbers Model AT01-100 has three different serial number ranges that correspond to the EASA TCDS A.527 sub-models termed “variants”, which is a term not recognized by the FAA for part 23 airplanes. The Model AT01-100 will have one of these three serial number ranges (Note 8): S/N AT01-100A-300 and ff (subsequent), AT01-100B-300 and ff (subsequent), AT01- 100C-300 and ff (subsequent). Certification Basis Certificated under the Special Class provisions of 14 Code of Federal Regulations (CFR), Part 21.17(b) -- JAR-VLA thru amendment VLA/92/1 effective January 1, 1992 and Additional Requirements: AQUILA GmbH Engine Mount Connection Design criteria and Winglets for the AQUILA GmbH AT01 JAR-VLA Airplane, (final criteria issued 10-20-2003 and published in the Federal Register FR Doc. 03-28138 dated November 10, 2003) (68 FR 56809). 14 CFR Part 36 effective November 18, 1969, including Amendments 36-1 through 36-28 Additional Requirements for Night VFR option – If modification option is approved The EASA Special Conditions are Special Conditions VLA 1, VLA 181, VLA 773, VLA 807, VLA 903, VLA 905, VLA 1107, VLA 1121, VLA 1143, VLA 1147, VLA 1322, VLA 1325, VLA 1331, VLA 1351, VLA 1353, VLA 1381, VLA 1383, VLA 1431, VLA 1547, VLA 1559 and VLA 1583. The FAA also adopted the corresponding EASA acceptable Means of Compliance (AMC) as shown in appendix 2 of the CRI A-01 for the night VFR project. (final design criteria issued 8-12-2013 as published in the Federal Register FR Doc. 2013-20151 dated August 19, 2013) (78 FR 50313). Additional Requirements for Advanced Avionics for this model: 14 CFR part 23 § 23.1307 at amendment 23-49, “Miscellaneous Equipment”. 5 of 6 A51CE 14 CFR part 23 § 23.1311 at amendment 23-62, “Electronic Display Instrument Systems” 14 CFR part 23 § 23.1321 at amendment 23-49, “Arrangement and visibility” 14 CFR part 23 § 23.1359 at amendment 23-49, “Electrical System Fire Protection”. (final design criteria issued October 28, 2013 and published in the Federal Register November 15, 2013) (78 FR 68687): Date of Application for Amended Type Certificate was April 22, 2013. Equipment The basic required equipment as prescribed in the applicable airworthiness regulations (see Certification Basis) must be installed in the airplane for certification. In addition, the following items of equipment are required: Pilot’s Operating Handbook and Airplane Flight Manual, document number FM-AT01-1010-101 (variant AT01-100A), Rev. A.02 dated October 15, 2013 or FM- AT01-1010-102 (variant AT01-100B), Rev. A.02 dated October 15, 2013 or FM-AT01- 1010-103 (variant AT01-100C) Rev. A.02 dated October 15, 2013 must be carried. The list of basic required equipment for Day-VFR operation is contained in the Pilot’s Operating Handbook (POH) and Airplane Flight Manual (AFM). For NVFR-operation refer to AFM-Supplement AS-01 (variant AT01-100A), AS-05 (variant AT01-100B) and AS-06 (variant AT01-100C), Section 2, all dated October 15, 2013 or later approved Revision Limitations (Reserved.) DATA PERTINENT TO BOTH MODELS – AT01 and AT01-100 Import Requirements The FAA can issue a U.S. airworthiness certificate based on an NAA Export Certificate of Airworthiness (Export C of A) signed by a representative of the Luftfahrt Bundesamt on behalf of the European Community. The Export C of A should contain the following statement: ‘The aircraft covered by this certificate has been examined, tested, and found to comply with U.S. airworthiness regulations 14 CFR Part 21.17(b) approved under U.S. Type Certificate No. A51CE and 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, • Structural repair manuals, • Vendor manuals, • Aircraft flight manuals, and • Overhaul and maintenance manuals. The FAA accepts such documents and considers them FAA-approved unless one of the following conditions exists: 6 of 6 A51CE • 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. Available Documents for the Aquila AT01-100 are: Airplane Flight Manual: FM-AT01-1010-101 (variant AT01-100A), Rev. A.02 dated October 15, 2013 or later EASA approved revisions FM-AT01-1010-102 (variant AT01-100B), Rev. A.02 dated October 15, 2013 or later EASA approved revisions FM-AT01-1010-103 (variant AT01-100C), Rev. A.02 dated October 15, 2013 or later EASA approved revisions Airplane Maintenance Manual, MM-AT01-1020-110, Rev. A.03 dated October 24, 2013 or later EASA approved revisions. (Chapter 4 is FAA and EASA approved) NOTES: NOTE 1: Weight and Balance: 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 certification. The certificated empty weight and corresponding center of gravity location must include full oil and unusable fuel. NOTE 2: The placards specified in the LBA approved Pilot’s Operating Handbook must be displayed NOTE 3: Instructions for Continued Airworthiness and Service Life Limited components is included in the Aquila AT01 Maintenance Manual Section 4, "Airworthiness Limitations.' Revisions to Airworthiness Limitations cannot be made without EASA and FAA approval. Airframe life limit is 6,000 flight hours. NOTE 4: All external portions of the airplane structure exposed to sunlight must be painted white except for areas of markings and warning marks. Any deviation must be approved by the manufacturer. NOTE 5: This airplane cannot be converted for IFR operations or to a 14 CFR Part 23 airplane. NOTE 6: (left blank at this time) NOTE 7: Model AT01 that has Aquila modification defined by Service Bulletin (SB)-AT01-010 installed for Night VFR option must have AT01-1010-100-US, Rev. B.04 dated March 18, 2013 or later approved revision and AMM Doc No. MM-AT01-1020-100, revision 25, dated October 30, 2013 or later approved revision. NOTE 8: EASA TCDS variant A has S/Ns: AT01-100A-300 and subsequent and has traditional analog instruments or ASPEN EFD 1000 display. EASA TCDS variant B has S/Ns: AT01-100B-300 and subsequent and has Garmin G-500 with analog engine instruments. EASA TCDS variant C has S/Ns AT01-100C-300 and subsequent and has Garmin G- 500 with and Engine Monitoring System (EMS) MVP 50P. .....END.....