Document ID: FAA-2017-0694-0003
Agency: faa
Document Type: Rule
Title: Airworthiness Directives: Dassault Aviation Airplanes
Posted Date: 2018-02-13T05:00Z

[Federal Register Volume 83, Number 30 (Tuesday, February 13, 2018)]
[Rules and Regulations]
[Pages 6120-6123]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2018-02748]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2017-0694; Product Identifier 2017-NM-007-AD; Amendment 
39-19192; AD 2018-03-19]
RIN 2120-AA64

Airworthiness Directives; Dassault Aviation Airplanes

AGENCY: Federal Aviation Administration (FAA), Department of 
Transportation (DOT).

ACTION: Final rule.

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SUMMARY: We are adopting a new airworthiness directive (AD) for certain

[[Page 6121]]

Dassault Aviation Model FALCON 7X airplanes. This AD was prompted by a 
report indicating that fuselage panels were manufactured with defects 
that could reduce panel fatigue limits. This AD requires a one-time 
inspection of the affected panels and repair if necessary, and for 
certain airplanes, installation of a stiffener. We are issuing this AD 
to address the unsafe condition on these products.

DATES: This AD is effective March 20, 2018.
    The Director of the Federal Register approved the incorporation by 
reference of a certain publication listed in this AD as of March 20, 
2018.

ADDRESSES: For service information identified in this final rule, 
contact Dassault Falcon Jet Corporation, Teterboro Airport, P.O. Box 
2000, South Hackensack, NJ 07606; telephone 201-440-6700; internet 
http://www.dassaultfalcon.com. You may view this referenced service 
information at the FAA, Transport Standards Branch, 1601 Lind Avenue 
SW, Renton, WA. For information on the availability of this material at 
the FAA, call 206-231-3195. It is also available on the internet at 
http://www.regulations.gov by searching for and locating Docket No. 
FAA-2017-0694.

Examining the AD Docket

    You may examine the AD docket on the internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2017-
0694; or in person at the Docket Management Facility between 9 a.m. and 
5 p.m., Monday through Friday, except Federal holidays. The AD docket 
contains this AD, the regulatory evaluation, any comments received, and 
other information. The street address for the Docket Office (telephone 
800-647-5527) is Docket Management Facility, U.S. Department of 
Transportation, Docket Operations, M-30, West Building Ground Floor, 
Room W12-140, 1200 New Jersey Avenue SE, Washington, DC 20590.

FOR FURTHER INFORMATION CONTACT: Tom Rodriguez, Aerospace Engineer, 
International Section, Transport Standards Branch, FAA, 1601 Lind 
Avenue SW, Renton, WA 98057-3356; telephone 425-227-1137; fax 425-227-
1149.

SUPPLEMENTARY INFORMATION:

Discussion

    We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR 
part 39 by adding an AD that would apply to certain Dassault Aviation 
Model FALCON 7X airplanes. The NPRM published in the Federal Register 
on July 14, 2017 (82 FR 32498) (``the NPRM''). The NPRM was prompted by 
a report indicating that fuselage panels were manufactured with defects 
that could reduce panel fatigue limits. The NPRM proposed to require a 
one-time inspection of the affected panels and corrective actions if 
necessary. We are issuing this AD to detect and correct discrepancies 
of certain fuselage lateral panels, which could lead to crack 
propagation and possible reduced structural integrity of the fuselage.
    The European Aviation Safety Agency (EASA), which is the Technical 
Agent for the Member States of the European Union, has issued EASA 
Airworthiness Directive 2016-0250, dated December 15, 2016 (referred to 
after this as the Mandatory Continuing Airworthiness Information, or 
``the MCAI''), to correct an unsafe condition for certain Dassault 
Aviation Model FALCON 7X airplanes. The MCAI states:

    A few pockets of fuselage Section T5 lateral panels were 
manufactured with defects in certain chemically-milled profiles. The 
technical investigation concluded that the fatigue limit of the 
affected panels might be reduced, depending on the defect 
characteristics.
    This condition, if not detected and corrected, could lead to 
crack propagation, possibly resulting in reduced structural 
integrity of the fuselage.
    To address this potential unsafe condition, DA published Service 
Bulletin (SB) F7X-042 providing inspection instructions.
    For the reasons described above, this [EASA] AD requires a one-
time [detailed] inspection of the chemically-milled profiles of the 
pockets of the Section T5 fuselage lateral panels and, depending on 
findings, accomplishment of applicable corrective action(s). This 
[EASA] AD also requires, for some aeroplanes, the installation of a 
stiffener on the forward pocket.

    Applicable corrective actions include repair, if necessary. You may 
examine the MCAI in the AD docket on the internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2017-
0694.

Comments

    We gave the public the opportunity to participate in developing 
this final rule. We received no comments on the NPRM or on the 
determination of the cost to the public.

Conclusion

    We reviewed the relevant data and determined that air safety and 
the public interest require adopting this AD as proposed, except for 
minor editorial changes. We have determined that these minor changes:
     Are consistent with the intent that was proposed in the 
NPRM for correcting the unsafe condition; and
     Do not add any additional burden upon the public than was 
already proposed in the NPRM.

Related Service Information Under 1 CFR Part 51

    We reviewed Dassault Service Bulletin 7X-042, Revision 1, dated May 
3, 2016. This service information describes the inspection of the 
chemically milled profiles of the pockets of the Section T5 fuselage 
lateral panels and the installation of a stiffener on the forward 
pocket on affected airplanes. This service information is reasonably 
available because the interested parties have access to it through 
their normal course of business or by the means identified in the 
ADDRESSES section.

Costs of Compliance

    We estimate that this AD affects 4 airplanes of U.S. registry.
    We estimate the following costs to comply with this AD:

                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
             Action                  Labor cost        Parts cost     Cost per product    Cost on U.S. operators
----------------------------------------------------------------------------------------------------------------
Panel inspections..............  Up to 10 work-                  $0  Up to $850........  Up to $3,400.
                                  hours x $85 per
                                  hour = $850.
Stiffener installation (up to 3  2 work-hours x $85           8,769  $8,939............  Up to $26,817.
 airplanes).                      per hour = $170.
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[[Page 6122]]

    According to the manufacturer, all of the costs of this AD may be 
covered under warranty, thereby reducing the cost impact on affected 
individuals. We do not control warranty coverage for affected 
individuals. As a result, we have included all costs in our cost 
estimate.

Authority for This Rulemaking

    Title 49 of the United States Code specifies the FAA's authority to 
issue rules on aviation safety. Subtitle I, section 106, describes the 
authority of the FAA Administrator. ``Subtitle VII: Aviation 
Programs,'' describes in more detail the scope of the Agency's 
authority.
    We are issuing this rulemaking under the authority described in 
``Subtitle VII, Part A, Subpart III, Section 44701: General 
requirements.'' Under that section, Congress charges the FAA with 
promoting safe flight of civil aircraft in air commerce by prescribing 
regulations for practices, methods, and procedures the Administrator 
finds necessary for safety in air commerce. This regulation is within 
the scope of that authority because it addresses an unsafe condition 
that is likely to exist or develop on products identified in this 
rulemaking action.
    This AD is issued in accordance with authority delegated by the 
Executive Director, Aircraft Certification Service, as authorized by 
FAA Order 8000.51C. In accordance with that order, issuance of ADs is 
normally a function of the Compliance and Airworthiness Division, but 
during this transition period, the Executive Director has delegated the 
authority to issue ADs applicable to transport category airplanes to 
the Director of the System Oversight Division.

Regulatory Findings

    We determined that this AD will not have federalism implications 
under Executive Order 13132. This AD will not have a substantial direct 
effect on the States, on the relationship between the national 
government and the States, or on the distribution of power and 
responsibilities among the various levels of government.
    For the reasons discussed above, I certify that this AD:
    1. Is not a ``significant regulatory action'' under Executive Order 
12866,
    2. Is not a ``significant rule'' under the DOT Regulatory Policies 
and Procedures (44 FR 11034, February 26, 1979),
    3. Will not affect intrastate aviation in Alaska, and
    4. Will not have a significant economic impact, positive or 
negative, on a substantial number of small entities under the criteria 
of the Regulatory Flexibility Act.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Incorporation by 
reference, Safety.

Adoption of the Amendment

    Accordingly, under the authority delegated to me by the 
Administrator, the FAA amends 14 CFR part 39 as follows:

PART 39--AIRWORTHINESS DIRECTIVES

0
1. The authority citation for part 39 continues to read as follows:

    Authority: 49 U.S.C. 106(g), 40113, 44701.

Sec.  39.13  [Amended]

0
2. The FAA amends Sec.  39.13 by adding the following new airworthiness 
directive (AD):

2018-03-19 Dassault Aviation: Amendment 39-19192; Docket No. FAA-
2017-0694; Product Identifier 2017-NM-007-AD.

(a) Effective Date

    This AD is effective March 20, 2018.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to Dassault Aviation Model FALCON 7X airplanes, 
certificated in any category, serial numbers (S/Ns) 2 through 19 
inclusive, except S/Ns 3 and 8.

(d) Subject

    Air Transport Association (ATA) of America Code 51, Structure.

(e) Reason

    This AD was prompted by a report indicating that a few pockets 
of fuselage Section T5 lateral panels were manufactured with defects 
that could reduce the fatigue limit of the affected panels. We are 
issuing this AD to detect and correct discrepancies of certain 
fuselage lateral panels, which could lead to crack propagation and 
possible reduced structural integrity of the fuselage.

(f) Compliance

    Comply with this AD within the compliance times specified, 
unless already done.

(g) Inspection

    Within 99 months or 4,100 flight cycles, whichever occurs first, 
after the effective date of this AD, do a detailed inspection to 
measure the pocket depth of the Section T5 fuselage lateral panels, 
in accordance with the Accomplishment Instructions of Dassault 
Service Bulletin 7X-042, Revision 1, dated May 3, 2016.

(h) Repair

    During the inspection required by paragraph (g) of this AD, if 
any discrepancy is found, as defined in Accomplishment Instructions 
of Dassault Service Bulletin 7X-042, Revision 1, dated May 3, 2016, 
before further flight, contact the FAA, the European Aviation Safety 
Agency (EASA), or Dassault Aviation's EASA Design Organization 
Approval (DOA) for approved repair instructions, and, within the 
compliance time specified in those instructions, accomplish the 
repair accordingly.

(i) Installation

    For airplanes having S/Ns 16, 17, and 19: Within 99 months or 
4,100 flight cycles, whichever occurs first, after the effective 
date of this AD, install a stiffener on the forward pocket of 
Section T5 fuselage lateral panels, in accordance with the 
Accomplishment Instructions of Dassault Service Bulletin 7X-042, 
Revision 1, dated May 3, 2016.

(j) Credit for Previous Actions

    This paragraph provides credit for actions required by 
paragraphs (g) and (i) of this AD, if those actions were performed 
before the effective date of this AD using Dassault Service Bulletin 
7X-042, dated January 3, 2011.

(k) Other FAA AD Provisions

    The following provisions also apply to this AD:
    (1) Alternative Methods of Compliance (AMOCs): The Manager, 
International Section, Transport Standards Branch, FAA, has the 
authority to approve AMOCs for this AD, if requested using the 
procedures found in 14 CFR 39.19. In accordance with 14 CFR 39.19, 
send your request to your principal inspector or local Flight 
Standards District Office, as appropriate. If sending information 
directly to the manager of the International Branch, send it to the 
attention of the person identified in paragraph (l)(2) of this AD. 
Information may be emailed to: [email protected]. 
Before using any approved AMOC, notify your appropriate principal 
inspector, or lacking a principal inspector, the manager of the 
local flight standards district office/certificate holding district 
office.
    (2) Contacting the Manufacturer: For any requirement in this AD 
to obtain corrective actions from a manufacturer, the action must be 
accomplished using a method approved by the Manager, International 
Section, Transport Standards Branch, FAA; or the EASA; or Dassault 
Aviation's EASA DOA. If approved by the DOA, the approval must 
include the DOA-authorized signature.

(l) Related Information

    (1) Refer to Mandatory Continuing Airworthiness Information 
(MCAI) EASA Airworthiness Directive 2016-0250, dated December 15, 
2016, for related information. This MCAI may be found in the AD 
docket on the internet at http://www.regulations.gov by searching 
for and locating Docket No. FAA-2017-0694.
    (2) For more information about this AD, contact Tom Rodriguez, 
Aerospace Engineer, International Section, Transport Standards 
Branch, FAA, 1601 Lind Avenue SW, Renton, WA 98057-3356; telephone 
425-227-1137; fax 425-227-1149.

[[Page 6123]]

    (3) Service information identified in this AD that is not 
incorporated by reference is available at the addresses specified in 
paragraphs (m)(3) and (m)(4) of this AD.

(m) Material Incorporated by Reference

    (1) The Director of the Federal Register approved the 
incorporation by reference (IBR) of the service information listed 
in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51.
    (2) You must use this service information as applicable to do 
the actions required by this AD, unless this AD specifies otherwise.
    (i) Dassault Service Bulletin 7X-042, Revision 1, dated May 3, 
2016.
    (ii) Reserved.
    (3) For service information identified in this AD, contact 
Dassault Falcon Jet Corporation, Teterboro Airport, P.O. Box 2000, 
South Hackensack, NJ 07606; telephone 201-440-6700; internet http://www.dassaultfalcon.com.
    (4) You may view this service information at the FAA, Transport 
Standards Branch, 1601 Lind Avenue SW, Renton, WA. For information 
on the availability of this material at the FAA, call 425-227-1221.
    (5) You may view this service information that is incorporated 
by reference at the National Archives and Records Administration 
(NARA). For information on the availability of this material at 
NARA, call 202-741-6030, or go to: http://www.archives.gov/federal-register/cfr/ibr-locations.html.

    Issued in Renton, Washington, on January 30, 2018.
Michael Kaszycki,
Acting Director, System Oversight Division, Aircraft Certification 
Service.
[FR Doc. 2018-02748 Filed 2-12-18; 8:45 am]
BILLING CODE 4910-13-P