Rule2022-16904
Special Conditions: Dassault Aviation Model Falcon 6X Airplane; Flight Envelope Protection: Normal Load-Factor (g) Limiting
Primary source
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Published
August 8, 2022
Effective
August 8, 2022
Issuing agencies
Transportation DepartmentFederal Aviation Administration
Abstract
These 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 an electronic flight-control system (EFCS) that incorporates full-time, normal load-factor limiting, designed to prevent the pilot from inadvertently or intentionally exceeding the positive or negative airplane limit load factor. 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.
Full Text
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<title>Federal Register, Volume 87 Issue 151 (Monday, August 8, 2022)</title>
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[Federal Register Volume 87, Number 151 (Monday, August 8, 2022)]
[Rules and Regulations]
[Pages 48084-48086]
From the Federal Register Online via the Government Publishing Office [<a href="http://www.gpo.gov">www.gpo.gov</a>]
[FR Doc No: 2022-16904]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 25
[Docket No. FAA-2021-0631; Special Conditions No. 25-813-SC]
Special Conditions: Dassault Aviation Model Falcon 6X Airplane;
Flight Envelope Protection: Normal Load-Factor (g) Limiting
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Final special conditions; request for comments.
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SUMMARY: These 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 an electronic flight-control system
(EFCS) that incorporates full-time, normal load-factor limiting,
designed to prevent the pilot from inadvertently or intentionally
exceeding the positive or negative airplane limit load factor. 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 August 8, 2022. Send
comments on or before September 22, 2022.
ADDRESSES: Send comments identified by Docket No. FAA-2021-0631 using
any of the following methods:
<bullet> Federal eRegulations Portal: Go to <a href="https://www.regulations.gov/">https://www.regulations.gov/</a> and follow the online instructions for sending
your comments electronically.
<bullet> Mail: Send comments to Docket Operations, M-30, U.S.
Department of Transportation (DOT), 1200 New Jersey Avenue SE, Room
W12-140, West Building Ground Floor, Washington, DC 20590-0001.
<bullet> Hand Delivery or Courier: Take comments to Docket
Operations in Room W12-140 of the West Building Ground Floor at 1200
New Jersey Avenue SE, Washington, DC, between 9 a.m. and 5 p.m., Monday
through Friday, except Federal holidays.
<bullet> Fax: Fax comments to Docket Operations at 202-493-2251.
Privacy: Except for Confidential Business Information (CBI) as
described in the following paragraph, and other information as
described in title 14, Code of Federal Regulations (14 CFR) 11.35, the
FAA will post all comments received without change to <a href="https://www.regulations.gov/">https://www.regulations.gov/</a>, including any personal information you provide.
The FAA will also post a report summarizing each substantive verbal
contact received about these special conditions.
Confidential Business Information: Confidential Business
Information (CBI) is commercial or financial information that is both
customarily and actually treated as private by its owner. Under the
Freedom of Information Act (FOIA) (5 U.S.C. 552), CBI is exempt from
public disclosure. If your comments responsive to these special
conditions contain commercial or financial information that is
customarily treated as private, that you actually treat as private, and
that is relevant or responsive to these special conditions, it is
important that you clearly designate the submitted comments as CBI.
Please mark each page of your submission containing CBI as ``PROPIN.''
The FAA will treat such marked submissions as confidential under the
FOIA, and the indicated comments will not be placed in the public
docket of these special conditions. Send submissions containing CBI to
Troy Brown, Performance and Environment Section,
[[Page 48085]]
AIR-625, Technical Innovation Policy Branch, Policy and Innovation
Division, Aircraft Certification Service, Federal Aviation
Administration, 1801 S Airport Rd., Wichita, KS 67209-2190; telephone
and fax 405-666-1050; email <a href="/cdn-cgi/l/email-protection#80f4f2eff9aee1aee2f2eff7eec0e6e1e1aee7eff6"><span class="__cf_email__" data-cfemail="6c181e0315420d420e1e031b022c0a0d0d420b031a">[email protected]</span></a>. Comments the FAA
receives, which are not specifically designated as CBI, will be placed
in the public docket for these special conditions.
Docket: Background documents or comments received may be read at
<a href="https://www.regulations.gov/">https://www.regulations.gov/</a> at any time. Follow the online
instructions for accessing the docket or go to Docket Operations in
Room W12-140 of the West Building Ground Floor at 1200 New Jersey
Avenue SE, Washington, DC, between 9 a.m. and 5 p.m., Monday through
Friday, except Federal holidays.
FOR FURTHER INFORMATION CONTACT: Troy Brown, Performance and
Environment Section, AIR-625, Technical Innovation Policy Branch,
Policy and Innovation Division, Aircraft Certification Service, Federal
Aviation Administration, 1801 S Airport Rd., Wichita, KS 67209-2190;
telephone and fax 405-666-1050; email <a href="/cdn-cgi/l/email-protection#2e5a5c4157004f004c5c4159406e484f4f00494158"><span class="__cf_email__" data-cfemail="c6b2b4a9bfe8a7e8a4b4a9b1a886a0a7a7e8a1a9b0">[email protected]</span></a>.
SUPPLEMENTARY INFORMATION:
The substance of these special conditions has been published in the
Federal Register for public comment in several prior instances with no
substantive comments received. Therefore, the FAA finds that, pursuant
to Sec. 11.38(b), new comments are unlikely, and notice and comment
prior to this publication are unnecessary.
Comments Invited
The FAA invites interested people to take part in this rulemaking
by sending written comments, data, or views. The most helpful comments
reference a specific portion of the special conditions, explain the
reason for any recommended change, and include supporting data.
The FAA will consider all comments received by the closing date for
comments. The FAA may change these special conditions based on the
comments received.
Background
On July 1, 2012, Dassault Aviation applied for a type certificate
for its new Model Falcon 5X airplane. 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 its Model Falcon 5X
airplane under new Model Falcon 6X. This airplane is a twin-engine
business jet with seating for 19 passengers, and has a maximum takeoff
weight of 77,460 pounds.
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 14 CFR part
25, as amended by amendments 25-1 through 25-146.
If the Administrator finds that the applicable airworthiness
regulations (e.g., 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 Aviation Model Falcon 6X airplane will incorporate the
following novel or unusual design feature:
An EFCS that incorporates full-time, normal load-factor limiting,
designed to prevent the pilot from inadvertently or intentionally
exceeding the positive or negative airplane limit load factor.
Discussion
The normal load-factor limit on the Model Falcon 6X is unique in
that traditional airplanes with conventional, mechanical-linkage
flight-control systems are limited, in the pitch axis, only by the
elevator surface area and deflection limit. The elevator control power
is normally derived for adequate controllability and maneuverability at
the most critical longitudinal pitching moment. The result is that for
conventional, mechanical-linkage airplanes, a significant portion of
the flight envelope maneuverability, in excess of limit structural
design values, is possible. With the normal load-factor limit engaged,
the Dassault Model Falcon 6X airplane will not exhibit this excess
maneuverability.
Part 25 does not specify requirements nor does any FAA policy
require the applicant to demonstrate maneuver control that impose any
handling qualities requirements beyond the design limit structural
loads. Nevertheless, some pilots are accustomed to the availability of
this excess maneuver capacity in case of extreme emergencies, such as
upset recoveries or collision avoidance.
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.
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 a certain novel or unusual design feature
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.
Authority Citation
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
0
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 addition to the requirements of Sec. 25.143(a), and in the
absence of other limiting factors, the following apply:
(a) The positive limiting load factor must not be less than:
(1) 2.5g for the electronic flight-control system (EFCS) normal
state with the high-lift devices retracted up to V<INF>MO</INF>/
M<INF>MO</INF>. The positive limiting load factor may be gradually
reduced down to 2.25g above V<INF>MO</INF>/M<INF>MO</INF>.
[[Page 48086]]
(2) 2.0g for the EFCS normal state with the high-lift devices
extended.
(b) The negative limiting load factor must be equal to or more
negative than:
(1) Minus 1.0g for the EFCS normal state with the high-lift devices
retracted.
(2) 0.0g for the EFCS normal state with high-lift devices extended.
(c) Maximum, reachable, positive load-factor wings level may be
limited by flight-control system characteristics or flight envelope
protections (other than load-factor protection) provided that:
(1) The required values are readily achievable in turns, and
(2) Wings level pitch-up responsiveness is satisfactory.
(d) Maximum achievable negative load factor may be limited by
flight-control system characteristics or flight envelope protections
(other than load-factor protection) provided that:
(1) Pitch-down responsiveness is satisfactory
(2) From level flight, 0g is readily achievable or, alternatively,
a satisfactory* trajectory change is readily achievable at operational
speeds.
* For the FAA to consider a trajectory change as satisfactory, the
applicant should propose and justify a pitch rate that provides
sufficient maneuvering capability in the most critical scenarios.
(e) Compliance demonstration with the above requirements may be
performed without ice accretion on the airframe.
Issued in Kansas City, Missouri, on August 2, 2022.
Patrick R. Mullen,
Manager, Technical Innovation Policy Branch, Policy and Innovation
Division, Aircraft Certification Service.
[FR Doc. 2022-16904 Filed 8-5-22; 8:45 am]
BILLING CODE 4910-13-P
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