TCDS T00065IB

Page 1 2 3 4 5 Revision 1 - - - 1 DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION T00065IB Revision 1 DASSAULT AVIATION FALCON 6X November 28, 2023 TYPE CERTIFICATE DATA SHEET No. T00065IB This data sheet which is part of Type Certificate No. T00065IB prescribes conditions and limitations under which the product for which the Type Certificate was issued meets the airworthiness requirements of the US Federal Aviation Regulations. Type Certificate Holder Dassault Aviation 9 Rond Point Marcel Dassault 75008 PARIS FRANCE 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 21.185(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 21.183(d) or 21.185(b). Notwithstanding that the FAR referenced in the above paragraph does not specifically address or require a foreign civil airworthiness authority certification, such certification is the only practical way for an applicant to show, and the Federal Aviation Administration (FAA) to find conformity to the FAA-approved type design and conditions for safe operation. Additional guidance is contained in FAA Advisory Circular 21-23, Airworthiness Certification of Civil Aircraft, Engines, Propellers, and Related Products Imported into the United States. I. Model Falcon 6X (Transport Category) approved August 22, 2023 (a) Basic Model Definition Engines Two - PRATT & WHITNEY CANADA CORP. - Model PW812D Engine Type Certificate Data Sheet E00093N Fuel Kerosene JET A, JET A-1, JET Fuel No. 3 Kerosene low flash point TS-1, RT Kerosene high flash point JP-5 Engine Limits Static, Standard, Sea Level Take-off (5 min) 13,850 lb (6,161 daN) Maximum Continuous 12,989 lb (5,777 daN) T00065IB Page 2 of 5 For other limits refer to engine TC Data Sheet E00093EN or the FAA approved Airplane Flight Manual Airspeed Limits VMO/MMO = 350 KIAS / 0.9 Mach For other airspeed limits, refer to the FAA approved Airplane Flight Manual Center of Gravity (C.G.) Range Refer to the FAA approved Airplane Flight Manual Empty Weight C.G. Range None Datum 0 % of mean aerodynamic chord (MAC) is 492.9 in (12.5196 m) from the forward end of the aircraft nose cone. 25 % of mean aerodynamic chord (MAC) is 526.34 in (13.3690 m) from the forward end of the aircraft nose cone. Leveling Means Refer to Aircraft Maintenance Manual (AMM), part of Instructions for Continued Airworthiness (ICA) for level procedure. Maximum Weights Weights lb (kg) Take-off 77,500 (35,153) Landing 66,200 (30,028) Zero Fuel 45,900 (20,820) Minimum Crew 2 - Pilot and copilot Number of Seats The number of passengers shall not exceed 19 as determined by emergency exit requirements, nor shall the number of passengers exceed the number of seating accommodations approved for take-off and landing. (See note 4) Maximum Compartment Weights Refer to the Falcon 6X Weight and Balance Manual. (See note 1) Fuel Capacity Fuel capacities are defined in the FAA approved Flight Manual. Oil Capacity The oil capacity is defined in the applicable Engine Installation and Operating Manual. (See note 1) Maximum Operating Altitude Maximum Operating Altitude = 51,000 ft (15,544 m) Control Surface Movements Elevator Down 27.5° Up 30° Rudder Right 33° Left 33° Aileron Down 20° Up 35° Flaps Down 48° Flaperon Down 40° Up 5° Airbrakes Inboard up 40° Outboard up 35° Wing slats Down 30° Horizontal Stabilizer Down 3° Up 10.5° Manufacturers Serial Numbers Serial numbers 001 and up. T00065IB Page 3 of 5 Import Requirements 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. Certification Basis 1. 14 CFR part 25, effective February 1, 1965, including Amendments 25-1 through 25-146 in entirety. This includes the Optional Design Regulations used in the scope of compliance demonstration for ditching and icing conditions. 2. The following special conditions in accordance with 14 CFR part 11: (a) No. 25-599A-SC: Pilot Compartment View – Hydrophobic Coatings in Lieu of Windshield Wipers (b) No. 25-607A-SC: Limit Pilot Forces – Side Stick Controllers (c) No. 25-609A-SC: Design Roll Maneuver Condition (d) No. 25-710A-SC: Non-Rechargeable Lithium-Ion Batteries (e) No. 25-797-SC: Aircraft Electronic System Security Protection – External Sources (f) No. 25-798-SC: Design Speed Definition (g) No. 25-800-SC: Flight Envelope Protection – High Speed Limiting (h) No. 25-801-SC: Interactions of System and Structures (i) No. 25-802-SC: Flight Envelope Protection - General Limiting Requirements (j) No. 25-803-SC: Flight Envelope Protection: Icing and Non-Icing; High Incidence Protection Function (k) No. 25-804-SC: Control Surface Position Awareness (l) No. 25-805-SC: Side Stick Controllers – Controllability and Maneuverability (m) No. 25-807-SC: Electronic Flight Control System – Lateral Directional and Longitudinal Stability and Low Energy Awareness (n) No. 25-808-SC: Flight Envelope Protection – Pitch and Roll Limiting Functions (o) No. 25-809-SC: Operation without Normal Electrical Power (p) No. 25-810-SC: Dynamic Test Requirements for Multiple Occupant Side- Facing Seats with Inflatable Restraints (q) No. 25-812-SC: Aircraft Electronic System Security Protection – Internal Threats (r) No. 25-813-SC: Flight Envelope Protection – Normal Load Factor g Limiting 3. Equivalent Level of Safety Findings according to the provisions of 14 CFR 21.21(b)(1) for the following subjects: (a) § 25.671(c)(2): Flight Control System Failure Criteria (Memo TC00952IB- T-A-6) (b) § 25.783(h)(2): Servicing Doors (Memo TC00952IB-T-C-1) (c) § 25.811(e)(4)(i) & (iii): Inside Passenger Door Operational Arrow and “EXIT” verbiage Color (Memo TC00952IB-T-CI-05) (d) §25.811(d)(1),(d)(2),(d)(3): Overwing Emergency Exit Locator Sign (Memo TC00962IB-T-CI-01) (e) §§ 25.811(g), 25.812(b)(1): Graphical Exit Signs (Memo TC00952IB-T-CI- 03) (f) § 25. 934: Thrust Reverser Testing (Memo TC00953IB-T-CRI-E-20) T00065IB Page 4 of 5 (g) § 25.831(g): Ventilation System Failures – Cabin Temperature and Humidity (ELOS Memo TC00952IB-T-G-5-SE-20) (h) §§ 25.841(b), 25.843(b)(1): Combined Aircraft Pressurization Outflow and Positive Pressure Differential Relief Valve (Memo TC00952IB-T-SE-18) (i) § 25.841(a)&(b)(6): High Elevation Landing and Take-Off Capability (Memo TC00952IB-T-SE-17) (j) § 25.933(a)(1)(ii): Flight Critical Thrust Reverser (Memo TC00952IB-T-G- 5-P-7) (k) § 25.1145(a): Ignition Switches (Memo TC00952IB-T-CRI-E-09) (l) § 25.1193(e)(3): Engine and APU Cowling Fire Resistance (Memo TC00952IB-T-P-22) (m) §§ 25.1203(a), 25.1182(a): Engine Fire Detectors in Tailpipe (Memo TC00952IB-T-P-19) (n) §§ 25.1301, 25.1309: Equipment, Systems, and Installation Requirements: Use of ARAC Recommendations (Memo TC00952IB-T-SE-08) (o) § 25.1305(c)(3): Digital Display of Engine Parameters (Memo TC00952IB- T-G-5-P-5) (p) § 25.1383(b): Landing Lights Single Switch (Memo TC00952IB-T-SE-14) (q) § 25.1443(c): Minimum Mass Flow of Passenger Supplemental Oxygen (Memo TC00952IB-T-CRI-F-20) (r) §25.1459(a)(2): Use of Inertial Reference System (IRS) for Digital Flight Data Recorder (FDR) Vertical Acceleration (Memo TC00952IB-T-SE-5) 4. Exemptions for the following requirement: (a) Exemption No. 11163B, 14 CFR part 25, Section 25.809(a) Exit Arrangement (b) Exemption No. 18891, 14 CFR part 25, Section 25.813(e) Interior Doors (c) Time Limited Exemption No. 20368, 14 CFR part 25, Section 25.1322(b), (c)(2), and (e)(1) Flight Crew Alerting (d) Exemption No. 11328B, 14 CFR part 25, Section 25.1447(c) Equipment Standards for Oxygen Dispensing Units 5. Optional Design Regulations: (a) Ditching Sections 25.801, 25.1411(d), (e), (f), (g) and 25.1415 (b) Ice Protection Section 25.141 6. Environmental Standards 14 CFR part 36, Noise Standards: Aircraft Type Certification and Airworthiness Certification, effective December 1, 1969, including Amendments 36-1 through 36-31. 14 CFR part 34, Fuel Venting and Exhaust Emission Requirements for Turbine Engine Powered Airplanes, effective September 10, 1990, including Amendments 34-1 through 34-5A. 14 CFR part 26, effective December 10, 2007, including Amendments 26-1 through 26-6. Initial application for FAA TC was made on March 15, 2011. Updated reference application date is August 26, 2018. The European Aviation Safety Agency (EASA) originally type certificated this aircraft under its type certificate Number EASA.A.580. The FAA validated this product under U.S. Type Certificate Number T00065IB issued August 22, 2023. T00065IB Page 5 of 5 Production Basis Falcon 6X, all series and models, are produced in France under production approval FR.21G.0006 issued by the European Union Aviation Safety Agency, (EASA). Equipment The basic required equipment as prescribed in the applicable airworthiness regulations (see certification basis) must be installed on the aircraft for certification. See the Type Design aircraft configuration F6TC Std TC.26, stored in an electronic format under the virtual product management tool ENOVIA©. Service Information Each of the documents listed below that contain a statement that it is approved by the European Aviation Safety Agency (EASA) are accepted by the FAA and are considered FAA approved. Additionally, approvals issued by Dassault Aviation under the authority of EASA approved Design Organization DOA EASA.21J.051 are considered FAA approved. These approvals pertain to the type design only. • Dassault Aviation Service Bulletins, except as noted below, • Structural repair manuals, • Vendor manuals referenced in Dassault Aviation service bulletins • Aircraft flight manuals, • Repair Instructions. Note: Design changes that are contained in Dassault Aviation Service Bulletins and that are classified as Level 1 Major or Non-Basic in accordance with US/EASA Bilateral Aviation Safety Agreement Implementation Procedures/Technical Implementation Procedures for Airworthiness must be approved by the FAA. NOTES NOTE 1 - A current weight and balance report, including a list of equipment included in certificated empty weight, and loading instructions when necessary, must be provided for each aircraft at the time of original certification. The certificated basic empty weight and corresponding center of gravity location must include the total engine oil, hydraulic fluid and unusable fuel. Loading of the aircraft must be accomplished in a manner that always maintains the center of gravity within the specified limits considering crew and occupant movements as well as fuel consumption and transfer. NOTE 2 - Airplane operation must be in accordance with the Airplane Flight Manual. All placards required by either the AFM, the applicable operating rules, or the certification basis must be installed in the airplane. NOTE 3 - The Instructions for Continued Airworthiness (ICA), included in FIELD publication, meet the requirements of 14 CFR §§ 25.1529 and 1729, and part 25 Appendix H (Sections H25.2, H25.3 and H25.4 only), including information on description, operation, maintenance (troubleshooting, removal/replacement, cleaning, inspection, etc.), and scheduling, as well as an Airworthiness Limitations Section (ALS). NOTE 4 - Cabin interior and seating configuration must be approved. NOTE 5 - In accordance with the approved Type Design, the FALCON 6X meets the airworthiness requirements and are eligible to operate in “Reduced Vertical Separation Minimum” (RVSM) airspace. Continued airworthiness and operational approval aspects of RVSM must be constructed according to Advisory Circular (AC) 91-85B “Authorization of Aircraft and Operators for Flight in Reduced Vertical Separation Minimum Airspace.” ......END.....