TCDS A59NM

Page 1 2 3 4 5 6 7 8 9 10 Revision 10 2 6 2 8 5 2 9 10 6 DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION A59NM Revision 10 DASSAULT AVIATION FALCON 7X July 2, 2025 TYPE CERTIFICATE DATA SHEET No. A59NM This data sheet which is part of Type Certificate No. A59NM 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 b y 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 7X (Transport Category) approved April 27, 2007 (a) Basic Model Definition Engines 3 engines. PRATT & WHITNEY CANADA Corp. - Model PW307A (see NOTE 3b) Engine Limits Static, Standard, Sea Level Take-off (5 min) 6,405 lb (2,849 daN) 6,725 lb (2,910 daN) with M1000 Maximum Continuous 6,405 lb (2,849 daN) 6,725 lb (2,910 daN) with M1000 For other limits refer to engine TC Data Sheet E00071EN or the FAA approved Airplane Flight Manual Thrust Reversers Engine is approved for operation with thrust reverser p/n F7XC782140020 APU Honeywell Model 36-150 (FN) A59NM Page 2 of 10 Rev 8 APU Limits APU is usable for ground operation only. For other limits refer to the Airplane Flight Manual Airspeed Limits Unless otherwise stated, speeds are indicated airspeeds VMO at sea level .................................................................. 350 kts VMO straight line variation up to 10,000 ft ......................... 370 kts VMO from 10,000 ft to 28,000 ft ........................................ 370 kts MMO from 28,000 to 51,000 ft ............................................ 0.9 VA .......... maneuvering speed .................................................... 218 kts VFE SF1 ............................................................................ 200 kts SF2 ............................................................................ 190 kts SF3 ............................................................................. 180 kts Note : Above 20,000 ft, do not establish, nor maintain a configuration with the slats and the flaps extended VLO Landing gear operation .............................................. 200 kts MLO .................................................................................... 0,70 VLE Landing gear extended .............................................. 245 kts MLE .................................................................................... 0,75 VMCA minimum control speed in flight ................................ 80 kts (CAS) VMCG minimum control speed on ground ......................... 81.3 kts (CAS) Maximum Operating Altitude 51,000 ft (15,544 m) Mean Aerodynamic chord (MAC) Mean aerodynamic chord (MAC): 131.793 in (3,347.54 mm) And Datum Datum is 25% of mean aerodynamic chord (MAC) 479.646 in (12,183 mm) from the forward end of the aircraft nose cone. 501.646 in (12741 mm) with M1000 Leveling Means Aircraft is leveled in the longitudinal and lateral axis by means of a plumb bob and target in the left main landing gear bay Weight and CG Limitations Weight FWD limit Aft limit Kg lbs % MAC % MAC Minimum flight - Aft Minimum flight - Forward Maximum zero fuel Maximum landing Maximum for aft CG at 38.5 % Maximum takeoff Maximum ramp 14,696 15,694 18,597 28,304 25,890 31,751 31,842 32,400 34,600 41,000 62,400 57,076 70,000 70,200 N/A 26.0 19.5 19.5 19.5 19.05 19.5 38.5 N/A 38.5 37.35 38.5 33.65 31.5 A59NM Page 3 of 10 Rev 8 With modification M1000 installed Weight FWD limit Aft limit Kg lbs % MAC % MAC Minimum flight - Aft Minimum flight - Forward Maximum zero fuel Maximum landing Maximum for aft CG at 38.5 % Maximum takeoff Maximum ramp 14,696 15,694 18,597 28,304 25,890 33,112 33,203 32,400 34,600 41,000 62,400 57,076 73,000 73,200 N/A 26.6 19.5 19.5 19.5 19.54 19.62 38.5 N/A 38.5 37.35 38.5 27.73 27.00 For weight and balance calculation refer to the Falcon 7X Loading Manual (DGT 108840) / Falcon 7X-M1000 Loading Manual (DGT 147688) - (See note 1) Minimum Crew 2 - Pilot and copilot Maximum Passenger Seats 19 - limited by emergency exit requirements of Federal Aviation Regulations § 25.807(c). (See note 2) Ferry flight configuration (0 passenger provisions) is defined by Dassault modifications M0272 and M0163 Maximum Baggage Baggage compartment: 2004 lb (909 kg), not to exceed 61.4 lb/ft2 (300 kg per square meter) Exits Type Size 1 Passenger door I 0.800 x 1.72 m /(31.50 x 67.72 in) 1 Emergency exit III 0.534 x 0.916 m /(21.02 x 36.06 in) Dimensions With Modification M1000 Length 920.47 in 23.38 m 24.46 m Span 1031.89 in 26.21 m 26.28 m Height 312.20 in 7.93 m 7.93 m Gross wing area 761.008 ft2 70.7 m² 70.7 m Fuel Capacity Numbers in ( ) indicate capacity associated with modification M1000 USABLE FUEL Liters kg (*) US Gallons lbs (*) Left circuit 5944/(6359) 4773/(5106) 1570/(1680) 10522/(11257) Right circuit 5944/(6383) 4773/(5126) 1570/(1686) 10522/(11301) Center circuit 6154/(7108) 4942/(5708) 1626/(1878) 10896/(12583) Total usable 18042/(19850) 14488/(15940) 4766/(5244) 31940/(35141) UNUSABLE FUEL Drainable 65/(68) 52/(54) 17/(18) 115/(120) Undrainable 41/(48) 33/(39) 11/(13) 72/(85) A59NM Page 4 of 10 Rev 8 Total unusable 106/(116) 85/(93) 28/(31) 187/(205) * assuming a fuel density of 0,803 kg/liter Oil Capacity Liters kg (**) US gallons lbs (**) Max oil level Left engine 7.87 7.67 2.08 16.90 Right engine 7.87 7.67 2.08 16.90 Center engine 7.87 7.67 2.08 16.90 Total 23.61 23.01 6.24 50.70 Min oil level Left engine 6.23 6.07 1.64 13.38 Right engine 6.23 6.07 1.64 13.38 Center engine 6.23 6.07 1.64 13.38 Total 18.69 18.21 4.92 40.14 (*) Tank quantities do not include undrainable oil or residual oil in the Accessory Gearbox, oil filter bowl or air-cooled oil cooler (ACOC) (**) Based on specific gravity of 0.975 Approved Fuel, oils and additives : Refer to the Airplane Flight Manual. Control Surface Movements Elevator Down 25° Up 16° Rudder Right 29° Left 29° Aileron Up 25° Down 25° Flaps Down 40° Airbrakes Inboard up 50° Outboards up 30° Spoilers up 80° Wing slats Inboard down 20° Median down 35° Outboard down 35° Horizontal Stabilizer Down 12° Up 2° Serial Numbers Eligible Serial numbers 0001 through 0400. (b) Falcon 8X Definition (Approved June 27, 2016) The Falcon 8X does not correspond to a model designation. The Falcon 8X is only a commercial designation for stretch version of the Falcon 7X airplanes that incorporates modifications M1000 and M1254 (EASy III) installed at production. This Falcon 7X version incorporates Pratt & Whitney PW307D engines . M1000 is basic on all Falcon 7X aircraft starting with serial number 0401. 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 A59NM Page 5 of 10 Rev 8 to FAA Order 8130.2, Airworthiness Certification of Aircraft, for requirements for issuance of an airworthiness certificate for imported aircraft. Certification Basis (a) For Falcon 7X (basic model) 1. 14 CFR part 25, effective February 1, 1965, including Amendments 25 -1 through 25-111 in entirety 2. The following special conditions in accordance with 14 CFR part 11 : (a) No. 25-343-SC Pilot Compartment View – Hydrophobic Coatings in Lieu of Windshield Wipers (b) No. 25-346-SC Interaction of System and Structure (c) No. 25-346-SC Limit Pilot Forces (d) No. 25-346-SC High Intensity Radiated Fields (HIRF) Protection (e) No. 25-349-SC Side Stick Controllers (f) No. 25-349-SC Electronic Flight Control System: Lateral-Directional and Longitudinal Stability and Low Energy Awareness (g) No. 25-349-SC Electronic Flight Control System: Flight Control Surface Position Awareness (h) No. 25-349-SC Electronic Flight Control System: Flight Characteristics Compliance Via Handling Qualities Rating Method (HQRM) (i) No. 25-349-SC Flight Envelope Protection: General Limiting Requirements (j) No. 25-349-SC Flight Envelope Protection: High Incidence Protection Function (k) No. 25-349-SC Flight Envelope Protection: Normal Load Factor (G) Limiting (l) No. 25-349-SC Flight Envelope Protection: Pitch, Roll And High Speed Limiting Functions (m) No. 25-350-SC Sudden Engine Stoppage (n) No. 25-350-SC Operation Without Normal Electrical Power (o) No. 25-350-SC Dive Speed Definition with Speed Protection System (p) No. 25-351-SC Design Roll Maneuvering Conditions (q) No. 25-410-SC Enhanced Flight Visibility System (r) No. 25‐711‐SC, Non‐Rechargeable Lithium Batteries, effective to design changes applied for after January 18, 2018. See the applicability section of this special condition for more information on which design changes must meet it. NOTE: The FAA Special Conditions referenced above may be accessed at internet location: http://www.airweb.faa.gov/Regulatory_and_Guidance_Library/rgSC.nsf/MainFrame?Op enFrameSet 3. Equivalent Level of Safety Findings according to the provisions of 14 CFR 21.21(b)(1) for the following subjects: (a) Section 25.671: Control Systems - General (documented in TAD ELOS Memo TC0030IB-T-A-6) (b) Section 25.331(c)(2): Pitch Maneuver Conditions (documented in TAD ELOS Memo TC0030IB-T-A-8) (c) Section 25.811(d)(1), (d)(3): Emergency Exit Marking (documented in TAD ELOS Memo TC0030IB-T-C-2) A59NM Page 6 of 10 Rev 8 (d) Section 25.1305 Powerplant Instruments (documented in TAD ELOS Memo TC0030IB-T-P-5) (e) Section 25.933(a)(1)(ii) Reversing Systems (documented in TAD ELOS Memo TC0030IB-T-P-7) (f) Section 25.971(a),(b): Fuel Tank Sump (documented in TAD ELOS Memo TC0030IB-T-P-12) (g) Section 25.1549(b) – Powerplant and auxiliary power unit instruments (documented in TAD ELOS Memo TC0030IB-T-P-13) (h) Section 25.841(b)(6) – Pressurized Cabins (documented in TAD ELOS Memo TC0030IB-T-SE-13) (i) Section 25.831(g) - Ventilation (documented in TAD ELOS Memo TC0030IB-T-SE-20) (j) Section 25.1459(a)(2) – Flight Recorders (documented in TAD ELOS Memo TC0030IB-T-SE-22) (k) Section 25.809(b) - Emergency Exit Arrangement (documented in TAD ELOS Memorandum AT10010IB-T-CI-101) (l) Sections 25.809(b) and 25.813(c)(2)(ii) - Emergency Exit Access (documented in TAD ELOS Memorandum AT10010IB-T-CI-101) (m) Section 25.813(c)(2) “Emergency Exit Access” (documented in TAD ELOS Memo SP00843IB-T NOTE: The FAA Equivalent Level of Safety memos referenced above may be accessed at internet location: http://www.airweb.faa.gov/Regulatory_and_Guidance_Library/rgSC.nsf/MainFrame?Op enFrameSet 4. Exemptions for the following requirement: (a) Exemption No. 8792, 14 CFR part 25, Section 25.785(b) Side Facing Sofas (b) Exemption No. 9117, 14 CFR part 25, Section 25.901(c) Uncontrolled High Engine Thrust (c) Exemption No. 9148, 14 CFR part 25, Section 25.981(a)(3) Fuel Tank Ignition Prevention (d) Exemption No. 9506A, 14 CFR part 25, Section 25813(e) Emergency Exit Access NOTE: The FAA Exemptions referenced above may be accessed at internet location: http://www.airweb.faa.gov/Regulatory_and_Guidance_Library/rgEX.nsf/MainFrame?Op enFrameSet 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, amendment 36-26. 14 CFR part 34, effective September 10, 1990, including amendment 34 -3. (b) Falcon 7X airplanes incorporating M1000 (Falcon 8X definition) 1) The type certification basis, for the Model Falcon 7X M1000 project (commercially designated as the Model Falcon 8X), A59NM Page 7 of 10 Rev 8 is the original certification basis for the Model Falcon 7X shown above, plus the following: Section No. Title Amdt 25- System/Area 25.21(g) Proof of Compliance 135 Falcon 7X M1000 airplane in Icing (except 25.105(a), 25.111(c), and 25.121(b)(c)) 25.107(c),(g),(h) Take-off Speeds 121 Falcon 7X M1000 airplane 25.107(e) Take-off Speeds 135 Falcon 7X M1000 airplane 25.111(c) Take-off Path 115 Falcon 7X M1000 airplane 25.119 Landing Climb 121 Falcon 7X M1000 airplane 25.121(d) Climb 121 Falcon 7X M1000 airplane 25.123 En-route flight paths 121 Falcon 7X M1000 airplane 25.125 Landing 121 Falcon 7X M1000 airplane 25.143(c),(e),(f),(g),(h),(i) General 121 Falcon 7X M1000 airplane 25.143(j) General 129 Falcon 7X M1000 airplane 25.147(d) Directional and lateral control 115 Falcon 7X M1000 airplane 25.161(c) Trim 115 Falcon 7X M1000 airplane 25.207(b),(h),(i) Stall warning 129 Falcon 7X M1000 airplane 25.207(e),(f),(g) Stall warning 121 Falcon 7X M1000 airplane 25.237(a) Wind velocities 121 Falcon 7X M1000 airplane 25.253 High-speed characteristics 135 Falcon 7X M1000 airplane 25.571(a),(b) Damage- tolerance and fatigue evaluation of structure 132 T34 Section frames 12 to 12bis and frames 28bis to 29 25.613(b),(c),(d),(e),(f) Material strength properties and design values 112 T34 Section frames 12 to 12bis and frames 28bis to 29 25.677(b) Trim System 115 Horizontal Stabilizer 25.729(a),(b),(e),(f) Retracting Mechanism 136 Main Landing Gear A59NM Page 8 of 10 Rev 8 25.812(g) Emergency Lighting 116 Cabin, Winglet 25.812(h) Emergency Lighting 128 Cabin, Winglet 25.973 Fuel Tank Filler Connection 115 Wing Fuel Tanks 25.1322 (a), (e) Flight Crew Alerting 131 FalconEye System 2. Noise Standards 14 CFR part 36 as amended by Amendments 36-1 through 36-28. 3. Fuel Venting and Exhaust Emissions Standards 14 CFR Part 34 as amended by Amendments 34-1 through 34-5A. 4. Means of Compliance Issue Papers: In addition to the regulatory basis noted in the preceding sections, the FAA has established certain “means of compliance” in issue papers applicable to the Dassault Falcon 7X M1000 certification program. The means of compliance issue papers applicable for Falcon 7X initial pro duct, supplemented by the certification bases of all other affected F7X major changes up to the M1000 project time of application, are considered to be applicable for F7X M1000 project. The list of these issue papers is amended by the following means of compliance raised for the specified F7X M1000 project subject areas. Airframe IP A-01 Fuel Tanks Emergency Landing Conditions Cabin Safety At this time, no new Cabin Safety subjects identified as potential means of compliance Flight A Cover IP to CRI B-09 “Landing Distance On Smooth Wet Runways” is to be addressed by FAA Noise IP N-01 Noise Level Evaluation Requirement Propulsion At this time, no new Propulsion subjects identified as potential means of compliance Systems & Software At this time, no new Systems & Software subjects identified as potential means of compliance Dassault document DGT131264 identifies the complete agreed upon certification basis for the F7X M1000 project A59NM Page 9 of 10 Rev 8 (c) Falcon 7X or Falcon 8X airplanes incorporating M-OPT1238 (Starlink Antenna Provisions) 1) The type certification basis, for the Model Falcon 7X or Falcon 8X incorporating M-OPT1238 (Starlink Antenna Provisions), is the original certification basis for the Model Falcon 7X and Falcon 8X shown above, plus the following: 2) Equivalent Level of Safety Findings according to the provisions of 14 CFR 21.21(b)(1) for the following subjects: Section 25.251: Vibration and Buffeting (documented in ELOS Memo AT19534IB-T-ESF-B25.251-01) The European Aviation Safety Agency (EASA) originally type certificated this aircraft under its type certificate Number A.155. The FAA validated this product under U.S. Type Certificate Number A59NM issued April 27, 2007. Type Definition The type definition is defined by F7TC which is stored in an electronic format under the virtual product management tool ENOVIA/VPM©. The repository of the ENOVIA/VPM© database is located in Dassault Aviation facilities. (See note 5) Equipment The basic required equipment as prescribed in the applicable airworthiness regulations (see certification basis) must be installed on the aircraft for certification. The lists of all equipment as well as optional equipment approved by European Aircraft Safety Agency (EASA) are contained in the F7TC version stored in an electronic format under the virtual product management tool ENOVIA/VPM©. In addition, the aircraft must be operated in accordance with the FAA approved FALCON 7X Airplane Flight Manual, document DGT 105608. 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. • Dassault Aviation Service Bulletins, except as noted below, • Structural repair manuals, • Vendor manuals referenced in Dassault Aviation service bulletins • Aircraft flight manuals, • Repair Instructions. 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 certificate only such as changes to type design, repair/unrepair of damages. Note: Design changes that are contained in Dassault Aviation Service Bulletins and that are classified as Level 1 Major in accordance with US/France Bilateral Aviation Safety Agreement Implementation Procedures for Airworthiness must be approved by the FAA. FALCON 7X Operating and Service Instructions The aircraft must be operated according to the EASA approved Airplane Flight Manual DGT 105608 for the basic Falcon 7X. The aircraft must be operated according to the EASA approved Airplane Flight Manual DGT 147681 for the Falcon 7X M1000 airplanes (Falcon 8X). A59NM Page 10 of 10 Rev 8 Instructions for Continued Airworthiness and Airworthiness Limitations, included in FIELD publications, that consist of: • Airworthiness Limitation Section (Chapter 5-40 reference DGT 107838) • Maintenance Planning Document (Chapter 5): − Reference: DGT 125953 applicable to S/N 001to S/N 400 (modification M1000 not included) − Reference: DGSM 151456 applicable to S/N 401 and up (modification M1000 included) • Airplane Maintenance Manual • Fault Isolation Manual • Illustrated Parts Catalog (part list only) • Structural Repair Manual (Part 1) • Wiring Diagram Manual NOTES NOTE 1 - Weight and Balance (a) - A current weight and balance report must be carried in the aircraft at all times from the moment the aircraft is originally certified. (b) - Loading of the aircraft must be accomplished in a m anner that always maintains the center of gravity within the specified limits considering crew and passenger movements as well as fuel consumption and transfer. NOTE 2 - Cabin interior and seating configuration must be approved. NOTE 3 - Service Life Limits and required Maintenance/Inspections (a) Airframe components which are life limited, and associated retirement times, are presented in chapter 5.40.00 of the FALCON 7X Maintenance Manual, approved by EASA, and must be replaced as indicated therein. (b) PW307A engine life limits, established for critical rotating components, are published in the approved PW307A Airworthiness limitation manual 30P0422 (c) Required maintenance and inspections to maintain airworthiness based on involving reliability are presented in chapter 5.40.00 of the FALCON7X Maintenance Manuals approved by EASA. NOTE 4 - The FALCON 7X has been approved to operate in “Reduced Vertical Separation Minimum” (RVSM) airspace when the airplanes are operated in accordance with Airplane Flight Manual page 1-300-05. Continued airworthiness and operational approval aspects of RVSM must be constructed according to Advisory Circular (AC) 91-RVSM, titled “Approval of Aircraft and Operators for Flight in Airspace Above Flight Level (FL) 290 Where a 1,000 Foot Vertical Separation Minimum is Applied.” NOTE 5 - The use of electronic technology and alternative methods of data storage for the type definition of the FALCON 7X is managed in accordance with the procedures and documents defined in EASA CRI A-02 and Dassault document 00-113A-02, and is accepted by the FAA. NOTE 6 - The FAA has concluded that the occurrence of any uncontrollable high thrust failure condition, or any of the associated causal failures listed within Dassault Document DGT-DTC/CER 322496, may endanger the safe operation of an airplane. Consequently, the FAA recommends that operators be encouraged to report such failures in accordance with §§ 121.703(c), 125.409(c), and 135.415(c). NOTE 7 – An approved change to the AFM and ALS can be released either through a full revision of the manual or through a Change Project (CP) number bearing the same reference as the related manual. ......END.....