[Federal Register Volume 75, Number 96 (Wednesday, May 19, 2010)]
[Rules and Regulations]
[Pages 27926-27927]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2010-11932]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 25

[Docket No. NM420; Special Conditions No. 25-406-SC]


Special Conditions: Dassault Aviation Falcon Model 2000EX; 
Autobraking System

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final special conditions.

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SUMMARY: These special conditions are issued for the Dassault Aviation 
Falcon Model 2000EX airplane. This airplane will have a novel or 
unusual design feature(s) associated with the autobraking system for 
use during landing. 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: Effective Date: June 18, 2010.

FOR FURTHER INFORMATION CONTACT: Todd Martin, FAA, Airframe/Cabin 
Safety, ANM-115, Transport Airplane Directorate, Aircraft Certification 
Service, 1601 Lind Avenue, SW., Renton, Washington, 98057-3356; 
telephone (425) 227-1178; facsimile (425) 227-1149.

SUPPLEMENTARY INFORMATION:

Background

    On July 1, 2008, Dassault Aviation applied for a change to Type 
Certificate (TC) No. A50NM to install an automatic braking system on 
the Falcon Model 2000EX airplane. This is a pilot-selectable function 
that allows earlier maximum braking at landing without pilot pedal 
input. When the autobrake system is armed before landing, it 
automatically commands maximum braking at main wheels touchdown. Normal 
procedures remain unchanged and call for manual braking after nose 
wheel touchdown.
    The current Federal Aviation Regulations do not contain adequate 
requirements to address the potentially higher structural loads that 
could result from this type of automatic braking system. Title 14, Code 
of Federal Regulations (14 CFR) 25.471 through 25.511 address ground 
handling loads, but do not contain a specific ``pitchover'' requirement 
addressing the loading on the nose gear, the nose gear surrounding 
structure, and the forward fuselage. The Dassault autobraking system, 
which applies maximum braking at the main wheels before the nose gear 
touches down, will cause a high nose gear sink rate, and potentially 
higher gear and airframe loads. Therefore, the FAA has determined that 
a special condition is needed. The special condition requires that the 
airplane be designed to withstand the loads resulting from maximum 
braking, taking into account the effects of the automatic braking 
system.

Type Certification Basis

    Under the provisions of 14 CFR 21.101, Dassault Aviation must show 
that the Falcon Model 2000EX, as changed, continues to meet the 
applicable provisions of the regulations incorporated by reference in 
TC No. A50NM or the applicable regulations in effect on the date of 
application for the change. The regulations incorporated by reference 
in the type certificate are commonly referred to as the ``original type 
certification basis.'' The regulations incorporated by reference in TC 
No. A50NM are as follows: Part 25 of 14 CFR as amended by Amendments 
25-1 through 25-69. In addition, Dassault Aviation has elected to 
comply with the following amendments:
    <bullet> Amendment 25-71 for Sec.  25.365(e).

[[Page 27927]]

    <bullet> Amendment 25-72 for Sec. Sec.  25.783(g) and 25.177.
    <bullet> Amendment 25-75 for Sec.  25.729(e).
    <bullet> Amendment 25-79 for Sec.  25.811(e)(2).
    <bullet> Amendment 25-80 for Sec.  25.1316.
    In addition, the certification basis includes certain special 
conditions, exemptions, or later amended sections of the applicable 
part that are not relevant to this proposed special condition.
    If the Administrator finds that the applicable airworthiness 
regulations (i.e., part 25) do not contain adequate or appropriate 
safety standards for the Falcon Model 2000EX because of a novel or 
unusual design feature, special conditions are prescribed under the 
provisions of Sec.  21.16.
    In addition to the applicable airworthiness regulations and special 
conditions, the Falcon Model 2000EX 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.  21.101.
    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, or should any other model already included on 
the same type certificate be modified to incorporate the same novel or 
unusual design feature, the special conditions would also apply to the 
other model under Sec.  21.101.

Novel or Unusual Design Features

    The Falcon Model 2000EX will incorporate the following novel or 
unusual design features:
    The airplane will be equipped with an automatic braking system, 
which is a pilot-selectable function that allows earlier maximum 
braking at landing without pilot pedal input. When the autobrake system 
is armed before landing, it automatically commands maximum braking at 
main wheels touchdown. This will cause a high nose gear sink rate, and 
potentially higher gear and airframe loads than would occur with a 
traditional braking system. Therefore, the FAA has determined that a 
special condition is needed.

Discussion

    The special condition defines a landing pitchover condition that 
takes into account the effects of the automatic braking system. The 
special condition defines the airplane configuration, speeds, and other 
parameters necessary to develop airframe and nose gear loads for this 
condition. The special condition requires that the airplane be designed 
to support the resulting limit and ultimate loads as defined in Sec.  
25.305.

Discussion of Comments

    Notice of proposed special conditions No. 25-09-13-SC for the 
Dassault Aviation Falcon Model 2000EX airplanes was published in the 
Federal Register on December 10, 2009. No comments were received, and 
the special conditions are adopted as proposed.

Applicability

    As discussed above, these special conditions are applicable to the 
Falcon Model 2000EX. Should Dassault Aviation apply at a later date for 
a change to the type certificate to include another model on the same 
type certificate incorporating the same novel or unusual design 
feature, the special conditions would apply to that model as well.

Conclusion

    This action affects only certain novel or unusual design features 
on one model of airplanes. 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(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 Aviation Falcon Model 2000EX 
airplanes.

Landing Pitchover Condition

    A landing pitchover condition must be addressed that takes into 
account the effect of the autobrake system. The airplane is assumed to 
be at the design maximum landing weight, or at the maximum weight 
allowed with the autobrake system on. The airplane is assumed to land 
in a tail-down attitude and at the speeds defined in Sec.  25.481. 
Following main gear contact, the airplane is assumed to rotate about 
the main gear wheels at the highest pitch rate allowed by the autobrake 
system. This is considered a limit load condition from which ultimate 
loads must also be determined. Loads must be determined for critical 
fuel and payload distributions and centers of gravity. Nose gear loads, 
as well as airframe loads, must be determined. The airplane must 
support these loads as described in Sec.  25.305.

    Issued in Renton, Washington, on May 12, 2010.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2010-11932 Filed 5-18-10; 8:45 am]
BILLING CODE 4910-13-P