# TCDS A00121CE: BRM AERO s.r.o. - Type: Type certificate data sheet - Status: Current - Holder: BRM AERO s.r.o. - Revision: 0 - Revised: September 9, 2025 - Product: Aircraft, Small Airplane - Certification basis: Part 23, Part 21 - Data sheet PDF: https://openairdocs.org/files/sha256/fd/95/fd952233761f94806a1bfb42a7cf1df601cbec51feb1dd19fd43686978fb638f - FAA DRS: https://drs.faa.gov/browse/excelExternalWindow/DRSDOCID169387933320250909172510.0001 - Page: https://openairdocs.org/tcds/A00121CE ## Models (1) As the data sheet lists them. - Bristell B23 ## What the data sheet says From the PDF's text layer, line by line; tables lose their columns. The PDF is the record. ```text Page No. 1 2 3 4 5 6 Rev. No. 0 0 0 0 0 0 DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION A00121CE Revision 0 BRM Aero s.r.o. Bristell B23 September 09, 2025 TYPE CERTIFICATE DATA SHEET NO. A00121CE This data sheet, which is part of Type Certificate No. A00121CE 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 BRM AERO s.r.o. Letecká 255, 686 04 Kunovice Czech Republic Type Certificate Holder Record I. Bristell B23 (Normal Category) Approved Date September 9, 2025 Engine One BRP-Rotax GmbH & Co KG ROTAX 912 S3 piston engine FAA Type Certificate: E00051EN Fuel EN 228 Super and Super Plus (RON 95) ASTM D4814 (min. AKI 91) AVGAS UL91 AVGAS 100LL (ASTM D910) Maximum approved Ethanol content is 5% Engine Limits MCP: 69 kW at 5500 rpm Max. Take-off power: 73.5 kW at 5800 rpm (max. 5 min.) Oil As specified in the latest revision of Rotax Service Instructions SI-912-016 A00121CE Page 2 of 6 Propeller and One MT-Propeller Entwicklung GmbH MTV-34-1-A/175-200 Propeller Limits FAA Type Certificate: P00038BO Three blades, in-flight hydraulically adjustable Blade shape 51 Hub flange: Motor glider engines bolt 7/16" - 20 UNF, circle diameter 80 mm Diameter: 175 cm. No additional tolerance permitted. Static rpm at full throttle: Maximum: 2386 rpm Blade Fine Pitch Angle: 13° Blade Coarse Pitch Angle: 33° Blade Angle measured at 75% blade length. Airspeed Limits Never exceed (VNE) 157 KIAS Maneuvering (VA) 99 KIAS Max structural cruise (VNO) 136 KIAS Max flaps extended (VFE) 82 KIAS Center of Gravity Forward: 25% of MAC – 5.6225 ft. aft of datum (C.G). Range Aft: 34.5% of MAC – 6.04145 ft. aft of datum Empty Weight C.G. Range None. Datum Propeller flange on the engine Leveling Means Longitudinal: By spirit level across seat pan Lateral: By spirit level across fuselage top rivet row below canopy frame Refer to Aircraft Maintenance Manual ADxC-73-102-AMM for more detailed information. Maximum Weights Taxi 1653 lbs. (750 kg) Takeoff 1653 lbs. (750 kg.) Landing 1653 lbs. (750 kg.) Max. Zero wing load weight 1455 lbs. (660 kg.) Maximum weight at 25% 1322 lbs. (600 kg.) Maximum weight at 34.5% 1635 lbs. (750 kg.) Minimum Crew One pilot (pilot on left side) Number of Seats Two. Pilot seat 6.84 ft. aft of datum Passenger seat 6.84 ft. aft of datum A00121CE Page 3 of 6 Maximum Baggage Behind seats: Lower area 33.1 lbs. (15 kg.) 8.27 ft. aft of datum Upper area 2.2 lbs. (1 kg.) 9.18 ft. aft of datum Wing locker loading (per side): 44.1 lbs. (20 kg.) 6.64 ft. aft of datum Fuel Capacity Total Fuel Capacity 31.71 US gallons (120 liters) Total Fuel Each Tank 15.85 US gallons (60 liters) Mid-Fuel Weight Arm is 5.25 ft. Fuel arm varies dependent on fuel load. Total Usable Fuel 31.17 US gallons (118 liters) Total Unusable Fuel 0.53 US gallons (2 liters) Refer to flight manual for fuel distribution weight and balance data. See Note 1. Oil Capacity Total Capacity 0.95 US gallon (3.6 liters) Oil arm 34.45 in. (875 mm) aft of datum See Note 1 for data on system oil. Maximum Operation Altitude 14,000 feet AMSL Control Surface Elevator Up 19° Down min. 11°, max. 17° Movements Aileron Up 24° Down 16° Rudder Left 30° Right 30° Refer to Aircraft Maintenance Manual ADxC-73-102-AMM for more information on control surface movements. Flap Movement Take Off Flap 10° Landing Flap 25° Manufacturer's Serial Numbers 0170F and subsequent Serial Numbers with the letter “F” are the only aircraft eligible for United States standard airworthiness certificates per the US type certificate. A00121CE Page 4 of 6 Import Requirements A United States airworthiness certificate may be issued on the basis of an EASA Certificate of Airworthiness for Export signed by a representative of the Civil Aviation Authority of the Czech Republic, containing the following statement: “The aircraft covered by this certificate has been examined and found to comply with the Master Document List ADxC-73-102-MDL Revision A or later approved version, approved under US Type Certificate No. A00121CE and to be in a condition for safe operation”. The U.S. airworthiness certification basis for this aircraft type certificated under FAR § 21.29 and exported by the country of manufacture is FAR § 21.183 (c). 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 Per 21.50(b), Instructions for Continued Airworthiness (ICA) complying with FAR 23.1529, must be furnished before delivery of the first airplane or issuance of a US standard certificate of airworthiness, whichever occurs later. Certification Basis Type Certification under 14 CFR Section 21.29 and 21.183(c) including the following requirements: 1. 14 CFR Part 23, effective February 1, 1965, including amendment 23-1 through 23-64, “Airworthiness Standards: Normal Category Airplanes.” a. § 23.2005 Certification Level and Performance Level: Level 1, Low Speed b. The detailed design standards used as a means of compliance in accordance with § 23.2010 are documented in Aircraft Design Certification GmbH DDS summary Report No. BRM Aero Bristell B23 with ADxC-73-DC-102, Issue A, dated 14-08-2025. (NOTE 4) A00121CE Page 5 of 6 2. 14 CFR Part 36, effective December 1, 1969 with Amendments 36-1 through Amendment 36-32 “Noise Standards: Aircraft Type and Airworthiness Certification” 3. Equivalent Level of Safety findings (ELOS): None 4. Special Conditions: None 5. Exemptions: None 6. The aircraft is certified for Day-Night Visual Flight Rules (VFR) only 7. The airplane is not approved for ditching. 8. The airplane is not approved for flight into known icing conditions. Type Certificate A00121CE issued September 9, 2025. Date of application for FAA Type Certificate was February 18, 2021. The European Aviation Safety Agency (EASA) originally type certificated this aircraft under its type certificate number EASA.A.642 Production Basis No FAA production certification. Production under Czech Republic Production Organization Approval CZ.21G.0063. Equipment The basic required equipment as prescribed in the applicable airworthiness regulations (see Certification Basis) must be installed in the aircraft for certification. In addition, the approved (for FAA) Flight Manual Bristell B23 Document ADxC-73-102-AFM Rev. A2, dated August 27, 2025, or later approved revision must be carried. Service Information Service bulletins, structural repair manuals, vendor manuals, AFMs, and overhaul and maintenance manuals, which contain a statement that the document is approved by the European Union Aviation Safety Agency, are accepted by the FAA and are considered FAA approved. (These approvals pertain to the design data only). Available documents for the Bristell B23 model: Aircraft Flight Manual: • Bristell B23 Aircraft Flight Manual ADxC-73-102-AFM Rev. A2, dated August 27, 2025, or later approved revisions. (NOTE 2) A00121CE Page 6 of 6 Instructions for Continued Airworthiness (ICA): • Airplane Maintenance Manual (AMM) Document ADxC- 73-102-AMM Revision 1.0 dated August 19, 2025, or later approved revisions (Chapter 4 is FAA and EASA approved). (NOTE 3) NOTES NOTE 1 A current weight and balance report including a 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 the corresponding center of gravity location must include full oil (6.82 lbs. (3.09 kg.) at 34.45 in. 875 mm)) and unusable fuel (3.17 lbs. (1.44 kg.) at 5.25 ft. (1600 mm)). NOTE 2 Airplane operation must be in accordance with the EASA- approved Aircraft Flight Manual listed above. All placards listed in Section 2 of the FAA approved AFM must be displayed in the appropriate locations. Revisions to this Bristell B23 document may be approved by EASA on behalf of the FAA, unless they are changes to the limitation section. The limitation changes require direct FAA approval for the US version of the AFM. NOTE 3 Mandatory retirement lives, required inspections, and inspection intervals of components are contained in the Airworthiness Limitations Section (Chapter 4) of the Airplane Maintenance Manual ADxC-73-102-AMM Issue 1.0, dated August 19, 2025 or later approved revisions. The US versions of the Bristell B23 limitations may not be changed without EASA and direct FAA approval. NOTE 4 Aircraft Design Certification GmbH was the contracting EASA DOA that supported the FAA validation of the BRM Aero Bristell B23 type certificate. ...END.... ``` ## ADs None name its models. --- OpenAirDocs.org is an independent research project of [Contrail Labs](https://contraillabs.com/). It is not affiliated with the FAA or the NTSB. Source documents are U.S. government works in the public domain.