[Federal Register Volume 87, Number 13 (Thursday, January 20, 2022)]
[Rules and Regulations]
[Pages 3026-3027]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2022-00975]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 25
[Docket No. FAA-2014-1077; Special Conditions No. 25-609A-SC]
Special Conditions: Dassault Aviation Model Falcon 6X Airplane;
Design Roll Maneuver
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Final special conditions; amendment.
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SUMMARY: These amended special conditions are issued for the Dassault
Aviation (Dassault) Model Falcon 6X airplane. This airplane will have a
novel or unusual design feature when compared to the state of
technology envisioned in the airworthiness standards for transport-
category airplanes. This design feature is electronic flight controls
that affect maneuvering. The applicable airworthiness regulations do
not contain adequate or appropriate safety standards for this design
feature. These special conditions contain the additional safety
standards that the Administrator considers necessary to establish a
level of safety equivalent to that established by the existing
airworthiness standards.
DATES: This action is effective on Dassault on January 20, 2022.
FOR FURTHER INFORMATION CONTACT: Todd Martin, AIR-621, Materials and
Structural Properties Section, Technical Innovation Policy Branch,
Policy and Innovation Division, Federal Aviation Administration, 2200 S
216th Street,
[[Page 3027]]
Des Moines, Washington 98198-6547; telephone and fax 206-231-3210.
SUPPLEMENTARY INFORMATION:
Background
On July 1, 2012, Dassault Aviation applied for a type certificate
for their new Model Falcon 5X airplane. Those special conditions were
issued on February 17, 2016 (81 FR 7965). However, Dassault has decided
not to release an airplane under the model designation Falcon 5X,
instead choosing to change that model designation to Falcon 6X.
In February of 2018, due to engine supplier issues, Dassault
extended the type certificate application date for their Model Falcon
5X airplane under new Model Falcon 6X. This amendment to the original
special conditions reflects the model-name change. This airplane is a
twin-engine business jet with seating for 19 passengers and a maximum
takeoff weight of 77,460 pounds. The Dassault Model Falcon 6X airplane
design remains unchanged from the Model Falcon 5X in all material
respects other than different engines.
Type Certification Basis
Under the provisions of 14 CFR 21.17, Dassault must show that the
Model Falcon 6X airplane meets the applicable provisions of part 25, as
amended by Amendments 25-1 through 25-146.
If the Administrator finds that the applicable airworthiness
regulations (i.e., 14 CFR part 25) do not contain adequate or
appropriate safety standards for the Dassault Model Falcon 6X airplane
because of a novel or unusual design feature, special conditions are
prescribed under the provisions of Sec. 21.16.
Special conditions are initially applicable to the model for which
they are issued. Should the type certificate for that model be amended
later to include any other model that incorporates the same novel or
unusual design feature, these special conditions would also apply to
the other model under Sec. 21.101.
In addition to the applicable airworthiness regulations and special
conditions, the Dassault Model Falcon 6X airplane must comply with the
fuel-vent and exhaust-emission requirements of 14 CFR part 34, and the
noise-certification requirements of 14 CFR part 36.
The FAA issues special conditions, as defined in 14 CFR 11.19, in
accordance with Sec. 11.38, and they become part of the type
certification basis under Sec. 21.17(a)(2).
Novel or Unusual Design Features
The Dassault Model Falcon 6X airplane will incorporate the
following novel or unusual design feature:
An electronic flight-control system that provides control through
pilot inputs to the flight computer, thereby affecting maneuverability
of the airplane as compared to conventional control systems.
Discussion
Current part 25 airworthiness regulations account for control laws
for which aileron deflection is proportional to control-stick
deflection. They do not address nonlinearities or other effects on
aileron actuation that may be caused by electronic flight controls.
Because this type of system may affect flight loads, and therefore the
structural capability of the airplane, specific regulations are needed
to address these effects.
These special conditions contain the additional safety standards
that the Administrator considers necessary to establish a level of
safety equivalent to that established by the existing airworthiness
standards.
Discussion of Comments
The FAA issued Final special conditions, request for comment
Special Conditions No. 25-609-SC for the Dassault Model Falcon 5X
airplane, which was published in the Federal Register on February 17,
2016 (81 FR 7965). No comments were received, and the special
conditions are adopted as proposed, with amendments.
Applicability
As discussed above, these special conditions are applicable to the
Dassault Model Falcon 6X airplane. Should Dassault apply at a later
date for a change to the type certificate to include another model
incorporating the same novel or unusual design feature, these special
conditions would apply to that model as well.
Conclusion
This action affects only certain novel or unusual design features
on one model of airplane. It is not a rule of general applicability.
List of Subjects in 14 CFR Part 25
Aircraft, Aviation safety, Reporting and recordkeeping
requirements.
The authority citation for these special conditions is as follows:
Authority: 49 U.S.C. 106(f), 106(g), 40113, 44701, 44702,
44704.
The Special Conditions
Accordingly, pursuant to the authority delegated to me by the
Administrator, the following special conditions are issued as part of
the type certification basis for Dassault Model Falcon 6X airplanes.
In lieu of compliance to Sec. 25.349(a), the following conditions,
speeds, and cockpit roll-control motions (except as the motions may be
limited by pilot effort) must be considered in combination with an
airplane load factor of zero, and of two-thirds of the positive
maneuvering factor used in design. In determining the resulting
control-surface deflections, the torsional flexibility of the wing must
be considered in accordance with Sec. 25.301(b).
1. Conditions corresponding to steady rolling velocities must be
investigated. In addition, conditions corresponding to maximum angular
acceleration must be investigated for airplanes with engines or other
weight concentrations outboard of the fuselage. For the angular
acceleration conditions, zero rolling velocity may be assumed in the
absence of a rational time-history investigation of the maneuver.
2. At VA, sudden movement of the cockpit roll control up
to the limit is assumed. The position of the cockpit roll control must
be maintained until a steady roll rate is achieved, and then must be
returned suddenly to the neutral position.
3. At VC, the cockpit roll control must be moved
suddenly and maintained so as to achieve a roll rate not less than that
obtained in special condition 2, above.
4. At VD, the cockpit roll control must be moved
suddenly and maintained so as to achieve a roll rate not less than one-
third of that obtained in special condition 2, above.
Issued in Kansas City, Missouri, on January 13, 2022.
Patrick R. Mullen,
Manager, Technical Innovation Policy Branch, Policy and Innovation
Division, Aircraft Certification Service.
[FR Doc. 2022-00975 Filed 1-19-22; 8:45 am]
BILLING CODE 4910-13-P