Airworthiness Directives; Dassault Aviation Airplanes, 10535-10537 [2016-04295]
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Federal Register / Vol. 81, No. 40 / Tuesday, March 1, 2016 / Proposed Rules
the FAA proposes to amend 14 CFR part
39 as follows:
PART 39—AIRWORTHINESS
DIRECTIVES
1. The authority citation for part 39
continues to read as follows:
■
Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13
[Amended]
2. The FAA amends § 39.13 by adding
the following new airworthiness
directive (AD):
■
The Boeing Company: Docket No. FAA–
2016–3700; Directorate Identifier 2015–
NM–171–AD.
(i) Repair
If any crack is found during any inspection
required by this AD, before further flight,
repair using a method approved in
accordance with the procedures specified in
paragraph (j) of this AD.
(g) Initial Inspection
At the applicable time specified in
paragraph 1.E., ‘‘Compliance,’’ of Boeing
Alert Service Bulletin 757–53A0102, dated
October 8, 2015, except as required by
paragraph (h) of this AD: Do an external dual
frequency eddy current inspection or internal
high frequency eddy current inspection for
cracking of the lap splice, inner skin lower
fastener row, at S–14R, station (STA) 440
through STA 540, in accordance with the
Accomplishment Instructions of Boeing Alert
Service Bulletin 757–53A0102, dated October
8, 2015. Repeat either inspection thereafter at
the time specified in paragraph 1.E.,
‘‘Compliance,’’ of Boeing Alert Service
Bulletin 757–53A0102, dated October 8,
2015.
(j) Alternative Methods of Compliance
(AMOCs)
(1) The Manager, Los Angeles Aircraft
Certification Office (ACO), 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 ACO, send it to the
attention of the person identified in
paragraph (k) of this AD. Information may be
emailed to: 9-ANM-LAACO-AMOCRequests@faa.gov.
(2) 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.
(3) An AMOC that provides an acceptable
level of safety may be used for any repair,
modification, or alteration required by this
AD if it is approved by the Boeing
Commercial Airplanes ODA that has been
authorized by the Manager, Los Angeles
ACO, to make those findings. To be
approved, the repair method, modification
deviation, or alteration deviation must meet
the certification basis of the airplane, and the
approval must specifically refer to this AD.
(4) Except as required by paragraph (h) of
this AD: For service information that
contains steps that are labeled as Required
for Compliance (RC), the provisions of
paragraphs (j)(4)(i) and (j)(4)(ii) of this AD
apply.
(i) The steps labeled as RC, including
substeps under an RC step and any figures
identified in an RC step, must be done to
comply with the AD. An AMOC is required
for any deviations to RC steps, including
substeps and identified figures.
(ii) Steps not labeled as RC may be
deviated from using accepted methods in
accordance with the operator’s maintenance
or inspection program without obtaining
approval of an AMOC, provided the RC steps,
including substeps and identified figures, can
still be done as specified, and the airplane
can be put back in an airworthy condition.
(h) Service Information Exceptions
(1) Where Boeing Alert Service Bulletin
757–53A0102, dated October 8, 2015,
specifies a compliance time ‘‘after the
original issue date of this service bulletin,’’
this AD requires compliance within the
(k) Related Information
(1) For more information about this AD,
contact Eric Schrieber, Aerospace Engineer,
Airframe Branch, ANM–120L, FAA, Los
Angeles ACO, 3960 Paramount Boulevard,
Lakewood, California 90712–4137; phone:
(a) Comments Due Date
We must receive comments by April 15,
2016.
(b) Affected ADs
None.
(c) Applicability
This AD applies to all The Boeing
Company Model 757–200 and –200CB, series
airplanes, certificated in any category.
(d) Subject
Air Transport Association (ATA) of
America Code 53, Fuselage.
(e) Unsafe Condition
This AD was prompted by an evaluation by
the design approval holder (DAH) indicating
that the lap splices at stringer (S)–14R, lower
fastener row, are subject to widespread
fatigue damage (WFD). We are issuing this
AD to detect and correct cracking of the
fuselage skin lap splice. Such cracking could
result in reduced structural integrity of the
airplane.
(f) Compliance
Comply with this AD within the
compliance times specified, unless already
done.
asabaliauskas on DSK5VPTVN1PROD with PROPOSALS
specified compliance time after the effective
date of this AD.
(2) The Condition column of paragraph
1.E., ‘‘Compliance,’’ of Boeing Alert Service
Bulletin 757–53A0102, dated October 8,
2015, refers to total flight cycles and total
flight hours ‘‘as of the original issue date of
this service bulletin.’’ This AD, however,
applies to the airplanes with the specified
total flight cycles or total flight hours as of
the effective date of this AD.
VerDate Sep<11>2014
19:05 Feb 29, 2016
Jkt 238001
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10535
562–627–5348; fax: 562–627–5210; email:
eric.schrieber@faa.gov.
(2) For service information identified in
this AD, contact Boeing Commercial
Airplanes, Attention: Data & Services
Management, P.O. Box 3707, MC 2H–65,
Seattle, WA 98124–2207; telephone: 206–
544–5000, extension 1; fax: 206–766–5680;
Internet: https://www.myboeingfleet.com.
You may view this referenced service
information at the FAA, Transport Airplane
Directorate, 1601 Lind Avenue SW., Renton,
WA. For information on the availability of
this material at the FAA, call 425–227–1221.
Issued in Renton, Washington, on February
15, 2016.
Michael Kaszycki,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. 2016–03695 Filed 2–29–16; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2016–3987; Directorate
Identifier 2015–NM–165–AD]
RIN 2120–AA64
Airworthiness Directives; Dassault
Aviation Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
We propose to adopt a new
airworthiness directive (AD) for certain
Dassault Aviation Model FALCON 7X
airplanes. This proposed AD was
prompted by a report of improperly
drilled bores, located on upper and
lower stiffener joints to the web at a
certain frame. This proposed AD would
require a one-time inspection of the
bores, and repair if necessary. We are
proposing this AD to detect and correct
an unsatisfactory bore that can
adversely affect the structural integrity
of the airplane.
DATES: We must receive comments on
this proposed AD by April 15, 2016.
ADDRESSES: You may send comments,
using the procedures found in 14 CFR
11.43 and 11.45, by any of the following
methods:
• Federal eRulemaking Portal: Go to
https://www.regulations.gov. Follow the
instructions for submitting comments.
• Fax: 202–493–2251.
• Mail: U.S. Department of
Transportation, Docket Operations,
M–30, West Building Ground Floor,
Room W12–140, 1200 New Jersey
Avenue SE., Washington, DC 20590.
SUMMARY:
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10536
Federal Register / Vol. 81, No. 40 / Tuesday, March 1, 2016 / Proposed Rules
• Hand Delivery: U.S. Department of
Transportation, Docket Operations,
M–30, West Building Ground Floor,
Room W12–140, 1200 New Jersey
Avenue SE., Washington, DC, between 9
a.m. and 5 p.m., Monday through
Friday, except Federal holidays.
For service information identified in
this NPRM, contact Dassault Falcon Jet
Corporation, Teterboro Airport, P.O.
Box 2000, South Hackensack, NJ 07606;
telephone: 201–440–6700; Internet:
https://www.dassaultfalcon.com. You
may view this referenced service
information at the FAA, Transport
Airplane Directorate, 1601 Lind Avenue
SW., Renton, WA. For information on
the availability of this material at the
FAA, call 425–227–1221.
Examining the AD Docket
You may examine the AD docket on
the Internet at https://
www.regulations.gov by searching for
and locating Docket No. FAA–2016–
3987; 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 proposed AD, the
regulatory evaluation, any comments
received, and other information. The
street address for the Docket Operations
office (telephone 800–647–5527) is in
the ADDRESSES section. Comments will
be available in the AD docket shortly
after receipt.
FOR FURTHER INFORMATION CONTACT: Tom
Rodriguez, Aerospace Engineer,
International Branch, ANM–116,
Transport Airplane Directorate, FAA,
1601 Lind Avenue SW., Renton, WA
98057–3356; telephone 425–227–1137;
fax 425–227–1149.
SUPPLEMENTARY INFORMATION:
asabaliauskas on DSK5VPTVN1PROD with PROPOSALS
Comments Invited
We invite you to send any written
relevant data, views, or arguments about
this proposed AD. Send your comments
to an address listed under the
ADDRESSES section. Include ‘‘Docket No.
FAA–2016–3987; Directorate Identifier
2015–NM–165–AD’’ at the beginning of
your comments. We specifically invite
comments on the overall regulatory,
economic, environmental, and energy
aspects of this proposed AD. We will
consider all comments received by the
closing date and may amend this
proposed AD based on those comments.
We will post all comments we
receive, without change, to https://
www.regulations.gov, including any
personal information you provide. We
will also post a report summarizing each
substantive verbal contact we receive
about this proposed AD.
VerDate Sep<11>2014
19:05 Feb 29, 2016
Jkt 238001
Discussion
The European Aviation Safety Agency
(EASA), which is the Technical Agent
for the Member States of the European
Union, has issued Airworthiness
Directive 2015–0204, dated October 8,
2015, (referred to after this as the
Mandatory Continuing Airworthiness
Information, or ‘‘the MCAI’’), to correct
an unsafe condition for certain Dassault
Aviation FALCON 7X airplanes. The
MCAI states:
On the assembly line of Falcon 7X
airplanes, defects were detected on left hand
and right hand engine pylons. A quality
review revealed that bores located on upper
and lower stiffener joints to the web at pylon
Frame 41 were improperly drilled. Fettlings
of borings, for fixing diameter 4 mm and 5
mm, were found ovalized, too deep and
having irregular surface qualities under the
head of fixing. Dassault Aviation identified
the individual airplanes that are potentially
affected by this production deficiency.
This condition, if not detected and
corrected, would adversely affect the
structural integrity of the airplane.
To address this potential unsafe condition
Dassault Aviation published Service Bulletin
(SB) 7X–346 to provide corrective action
instructions.
For the reasons described above, this
[EASA] AD requires a one-time [detailed]
visual [and rototest] inspection for
unsatisfactory bores and, depending on
findings, repair of affected stiffener bores.
A bore is not satisfactory if it has any
surface defects greater than or equal to
0.5 mm or if any chamfer dimension or
edge distance value is not within the
dimensions specified in Dassault
Aviation Service Bulletin 7X–346, dated
April 24, 2015. You may examine the
MCAI in the AD docket on the Internet
at https://www.regulations.gov by
searching for and locating Docket No.
FAA–2016–3987.
Design Authority, we have been notified
of the unsafe condition described in the
MCAI and service information
referenced above. We are proposing this
AD because we evaluated all pertinent
information and determined an unsafe
condition exists and is likely to exist or
develop on other products of the same
type design.
Costs of Compliance
We estimate that this proposed AD
affects 55 airplanes of U.S. registry.
We also estimate that it would take
about 66 work-hours per product to
comply with the basic requirements of
this proposed AD. The average labor
rate is $85 per work-hour. Based on
these figures, we estimate the cost of
this proposed AD on U.S. operators to
be $308,550, or $5,610 per product.
In addition, we estimate that any
necessary follow-on actions would take
about 20 work-hours and require parts
costing $149, for a cost of $1,849 per
product. We have no way of
determining the number of aircraft that
might need this action.
According to the manufacturer, some
of the costs of this proposed 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.
Related Service Information Under
1 CFR Part 51
Dassault Aviation has issued Dassault
Service Bulletin 7X–346 dated April 24,
2015. The service information describes
procedures for a one-time inspection of
the bores on stiffeners at Frame 41 on
the engine pylons, and repair if
necessary.
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.
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.
FAA’s Determination and Requirements
of This Proposed AD
This product has been approved by
the aviation authority of another
country, and is approved for operation
in the United States. Pursuant to our
bilateral agreement with the State of
Regulatory Findings
We determined that this proposed AD
would not have federalism implications
under Executive Order 13132. This
proposed AD would not have a
substantial direct effect on the States, on
the relationship between the national
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Federal Register / Vol. 81, No. 40 / Tuesday, March 1, 2016 / Proposed Rules
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 this proposed regulation:
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.
The Proposed Amendment
Accordingly, under the authority
delegated to me by the Administrator,
the FAA proposes to amend 14 CFR part
39 as follows:
PART 39—AIRWORTHINESS
DIRECTIVES
1. The authority citation for part 39
continues to read as follows:
■
Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13
[Amended]
2. The FAA amends § 39.13 by adding
the following new airworthiness
directive (AD):
■
Dassault Aviation: Docket No. FAA–2016–
3987; Directorate Identifier 2015–NM–
165–AD.
(a) Comments Due Date
We must receive comments by April 15,
2016.
(b) Affected ADs
None.
asabaliauskas on DSK5VPTVN1PROD with PROPOSALS
(c) Applicability
This AD applies to Dassault Aviation
Model FALCON 7X airplanes, certificated in
any category, manufacturer serial numbers 1
through 221 inclusive, except serial numbers
182 and 220.
(d) Subject
Air Transport Association (ATA) of
America Code 53, Fuselage.
(e) Reason
This AD was prompted by a report of
improperly drilled bores, located on upper
and lower stiffener joints to the web at a
certain frame. We are issuing this AD to
detect and correct an unsatisfactory bore that
can adversely affect the structural integrity of
the airplane.
VerDate Sep<11>2014
19:05 Feb 29, 2016
Jkt 238001
(f) Compliance
Comply with this AD within the
compliance times specified, unless already
done.
(g) Inspect Bores
Within 4,000 flight cycles or 98 months,
whichever occurs first since date of issuance
of the original airworthiness certificate or
date of issuance of the original export
certificate of airworthiness, do a detailed
visual and rototest inspection of the bores,
located on upper and lower stiffener joints to
the web at pylon Frame 41, to determine if
the bores are not satisfactory, in accordance
with the Accomplishment Instructions of
Dassault Service Bulletin 7X–346, dated
April 24, 2015.
(h) Repair
If, during the inspection required by
paragraph (g) of this AD, it is determined that
any bore is not satisfactory: Before further
flight, repair affected bores, in accordance
with the Accomplishment Instructions of
Dassault Service Bulletin 7X–346, dated
April 24, 2015, except as required by
paragraph (i) of this AD.
(i) Exceptions
Where the Dassault Service Bulletin 7X–
346, dated April 24, 2015, specifies to contact
Dassault Aviation: Before further flight,
repair using a method approved by the
Manager, International Branch, ANM–116,
Transport Airplane Directorate, FAA; or the
European Aviation Safety Agency (EASA); or
Dassault Aviation’s EASA Design
Organization Approval (DOA).
(j) Other FAA AD Provisions
The following provisions also apply to this
AD:
(1) Alternative Methods of Compliance
(AMOCs): The Manager, International
Branch, ANM–116, Transport Airplane
Directorate, 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 International Branch, send it to ATTN:
Tom Rodriguez, Aerospace Engineer,
International Branch, ANM–116, Transport
Airplane Directorate, FAA, 1601 Lind
Avenue SW., Renton, WA 98057–3356;
telephone 425–227–1137; fax 425–227–1149.
Information may be emailed to: 9-ANM-116AMOC-REQUESTS@faa.gov. 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. The AMOC approval letter
must specifically reference this AD.
(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 Branch, ANM–
116, Transport Airplane Directorate, FAA; or
EASA; or Dassault Aviation’s EASA DOA. If
approved by the DOA, the approval must
include the DOA-authorized signature.
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10537
(k) Related Information
(1) Refer to Mandatory Continuing
Airworthiness Information (MCAI) EASA AD
2015–0204, dated October 8, 2015, for related
information. This MCAI may be found on the
Internet at https://www.regulations.gov by
searching for and locating Docket No. FAA–
2016–3987.
(2) 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: https://
www.dassaultfalcon.com. You may view this
service information at the FAA, Transport
Airplane Directorate, 1601 Lind Avenue SW.,
Renton, WA. For information on the
availability of this material at the FAA, call
425–227–1221.
Issued in Renton, Washington, on February
19, 2016.
Dorr M. Anderson,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. 2016–04295 Filed 2–29–16; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2016–3986; Directorate
Identifier 2015–NM–147–AD]
RIN 2120–AA64
Airworthiness Directives; The Boeing
Company Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
We propose to adopt a new
airworthiness directive (AD) for certain
The Boeing Company Model 747–400,
747–400D, and 747–400F series
airplanes. This proposed AD was
prompted by a determination that a
certain fastener type in the fuel tank
walls has insufficient bond to the
structure, and an electrical wiring short
could cause arcing to occur at the ends
of fasteners in the fuel tanks. This
proposed AD would require the
installation of new clamps and
polytetrafluoroethylene (TFE) sleeves on
the wire bundles of the front spars and
rear spars of the wings. This proposed
AD would also require inspecting the
existing TFE sleeves under the wire
bundle clamps for correct installation,
and replacement if necessary. We are
proposing this AD to prevent potential
ignition sources in the fuel tank in the
event of a lightning strike or highpowered short circuit, and consequent
fire or explosion.
SUMMARY:
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]]>Agencies
[Federal Register Volume 81, Number 40 (Tuesday, March 1, 2016)]
[Proposed Rules]
[Pages 10535-10537]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2016-04295]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2016-3987; Directorate Identifier 2015-NM-165-AD]
RIN 2120-AA64
Airworthiness Directives; Dassault Aviation Airplanes
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking (NPRM).
-----------------------------------------------------------------------
SUMMARY: We propose to adopt a new airworthiness directive (AD) for
certain Dassault Aviation Model FALCON 7X airplanes. This proposed AD
was prompted by a report of improperly drilled bores, located on upper
and lower stiffener joints to the web at a certain frame. This proposed
AD would require a one-time inspection of the bores, and repair if
necessary. We are proposing this AD to detect and correct an
unsatisfactory bore that can adversely affect the structural integrity
of the airplane.
DATES: We must receive comments on this proposed AD by April 15, 2016.
ADDRESSES: You may send comments, using the procedures found in 14 CFR
11.43 and 11.45, by any of the following methods:
Federal eRulemaking Portal: Go to https://www.regulations.gov. Follow the instructions for submitting comments.
Fax: 202-493-2251.
Mail: U.S. Department of Transportation, Docket
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New
Jersey Avenue SE., Washington, DC 20590.
[[Page 10536]]
Hand Delivery: U.S. Department of Transportation, Docket
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New
Jersey Avenue SE., Washington, DC, between 9 a.m. and 5 p.m., Monday
through Friday, except Federal holidays.
For service information identified in this NPRM, contact Dassault
Falcon Jet Corporation, Teterboro Airport, P.O. Box 2000, South
Hackensack, NJ 07606; telephone: 201-440-6700; Internet: https://www.dassaultfalcon.com. You may view this referenced service
information at the FAA, Transport Airplane Directorate, 1601 Lind
Avenue SW., Renton, WA. For information on the availability of this
material at the FAA, call 425-227-1221.
Examining the AD Docket
You may examine the AD docket on the Internet at https://www.regulations.gov by searching for and locating Docket No. FAA-2016-
3987; 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 proposed AD, the regulatory evaluation, any comments
received, and other information. The street address for the Docket
Operations office (telephone 800-647-5527) is in the ADDRESSES section.
Comments will be available in the AD docket shortly after receipt.
FOR FURTHER INFORMATION CONTACT: Tom Rodriguez, Aerospace Engineer,
International Branch, ANM-116, Transport Airplane Directorate, FAA,
1601 Lind Avenue SW., Renton, WA 98057-3356; telephone 425-227-1137;
fax 425-227-1149.
SUPPLEMENTARY INFORMATION:
Comments Invited
We invite you to send any written relevant data, views, or
arguments about this proposed AD. Send your comments to an address
listed under the ADDRESSES section. Include ``Docket No. FAA-2016-3987;
Directorate Identifier 2015-NM-165-AD'' at the beginning of your
comments. We specifically invite comments on the overall regulatory,
economic, environmental, and energy aspects of this proposed AD. We
will consider all comments received by the closing date and may amend
this proposed AD based on those comments.
We will post all comments we receive, without change, to https://www.regulations.gov, including any personal information you provide. We
will also post a report summarizing each substantive verbal contact we
receive about this proposed AD.
Discussion
The European Aviation Safety Agency (EASA), which is the Technical
Agent for the Member States of the European Union, has issued
Airworthiness Directive 2015-0204, dated October 8, 2015, (referred to
after this as the Mandatory Continuing Airworthiness Information, or
``the MCAI''), to correct an unsafe condition for certain Dassault
Aviation FALCON 7X airplanes. The MCAI states:
On the assembly line of Falcon 7X airplanes, defects were
detected on left hand and right hand engine pylons. A quality review
revealed that bores located on upper and lower stiffener joints to
the web at pylon Frame 41 were improperly drilled. Fettlings of
borings, for fixing diameter 4 mm and 5 mm, were found ovalized, too
deep and having irregular surface qualities under the head of
fixing. Dassault Aviation identified the individual airplanes that
are potentially affected by this production deficiency.
This condition, if not detected and corrected, would adversely
affect the structural integrity of the airplane.
To address this potential unsafe condition Dassault Aviation
published Service Bulletin (SB) 7X-346 to provide corrective action
instructions.
For the reasons described above, this [EASA] AD requires a one-
time [detailed] visual [and rototest] inspection for unsatisfactory
bores and, depending on findings, repair of affected stiffener
bores.
A bore is not satisfactory if it has any surface defects greater
than or equal to 0.5 mm or if any chamfer dimension or edge distance
value is not within the dimensions specified in Dassault Aviation
Service Bulletin 7X-346, dated April 24, 2015. You may examine the MCAI
in the AD docket on the Internet at https://www.regulations.gov by
searching for and locating Docket No. FAA-2016-3987.
Related Service Information Under 1 CFR Part 51
Dassault Aviation has issued Dassault Service Bulletin 7X-346 dated
April 24, 2015. The service information describes procedures for a one-
time inspection of the bores on stiffeners at Frame 41 on the engine
pylons, and repair if necessary.
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.
FAA's Determination and Requirements of This Proposed AD
This product has been approved by the aviation authority of another
country, and is approved for operation in the United States. Pursuant
to our bilateral agreement with the State of Design Authority, we have
been notified of the unsafe condition described in the MCAI and service
information referenced above. We are proposing this AD because we
evaluated all pertinent information and determined an unsafe condition
exists and is likely to exist or develop on other products of the same
type design.
Costs of Compliance
We estimate that this proposed AD affects 55 airplanes of U.S.
registry.
We also estimate that it would take about 66 work-hours per product
to comply with the basic requirements of this proposed AD. The average
labor rate is $85 per work-hour. Based on these figures, we estimate
the cost of this proposed AD on U.S. operators to be $308,550, or
$5,610 per product.
In addition, we estimate that any necessary follow-on actions would
take about 20 work-hours and require parts costing $149, for a cost of
$1,849 per product. We have no way of determining the number of
aircraft that might need this action.
According to the manufacturer, some of the costs of this proposed
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.
Regulatory Findings
We determined that this proposed AD would not have federalism
implications under Executive Order 13132. This proposed AD would not
have a substantial direct effect on the States, on the relationship
between the national
[[Page 10537]]
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 this proposed
regulation:
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.
The Proposed Amendment
Accordingly, under the authority delegated to me by the
Administrator, the FAA proposes to amend 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):
Dassault Aviation: Docket No. FAA-2016-3987; Directorate Identifier
2015-NM-165-AD.
(a) Comments Due Date
We must receive comments by April 15, 2016.
(b) Affected ADs
None.
(c) Applicability
This AD applies to Dassault Aviation Model FALCON 7X airplanes,
certificated in any category, manufacturer serial numbers 1 through
221 inclusive, except serial numbers 182 and 220.
(d) Subject
Air Transport Association (ATA) of America Code 53, Fuselage.
(e) Reason
This AD was prompted by a report of improperly drilled bores,
located on upper and lower stiffener joints to the web at a certain
frame. We are issuing this AD to detect and correct an
unsatisfactory bore that can adversely affect the structural
integrity of the airplane.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(g) Inspect Bores
Within 4,000 flight cycles or 98 months, whichever occurs first
since date of issuance of the original airworthiness certificate or
date of issuance of the original export certificate of
airworthiness, do a detailed visual and rototest inspection of the
bores, located on upper and lower stiffener joints to the web at
pylon Frame 41, to determine if the bores are not satisfactory, in
accordance with the Accomplishment Instructions of Dassault Service
Bulletin 7X-346, dated April 24, 2015.
(h) Repair
If, during the inspection required by paragraph (g) of this AD,
it is determined that any bore is not satisfactory: Before further
flight, repair affected bores, in accordance with the Accomplishment
Instructions of Dassault Service Bulletin 7X-346, dated April 24,
2015, except as required by paragraph (i) of this AD.
(i) Exceptions
Where the Dassault Service Bulletin 7X-346, dated April 24,
2015, specifies to contact Dassault Aviation: Before further flight,
repair using a method approved by the Manager, International Branch,
ANM-116, Transport Airplane Directorate, FAA; or the European
Aviation Safety Agency (EASA); or Dassault Aviation's EASA Design
Organization Approval (DOA).
(j) Other FAA AD Provisions
The following provisions also apply to this AD:
(1) Alternative Methods of Compliance (AMOCs): The Manager,
International Branch, ANM-116, Transport Airplane Directorate, 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 International Branch, send it to ATTN: Tom
Rodriguez, Aerospace Engineer, International Branch, ANM-116,
Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton,
WA 98057-3356; telephone 425-227-1137; fax 425-227-1149. Information
may be emailed to: 9-ANM-116-AMOC-REQUESTS@faa.gov. 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. The
AMOC approval letter must specifically reference this AD.
(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
Branch, ANM-116, Transport Airplane Directorate, FAA; or EASA; or
Dassault Aviation's EASA DOA. If approved by the DOA, the approval
must include the DOA-authorized signature.
(k) Related Information
(1) Refer to Mandatory Continuing Airworthiness Information
(MCAI) EASA AD 2015-0204, dated October 8, 2015, for related
information. This MCAI may be found on the Internet at https://www.regulations.gov by searching for and locating Docket No. FAA-
2016-3987.
(2) 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:
https://www.dassaultfalcon.com. You may view this service information
at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW.,
Renton, WA. For information on the availability of this material at
the FAA, call 425-227-1221.
Issued in Renton, Washington, on February 19, 2016.
Dorr M. Anderson,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2016-04295 Filed 2-29-16; 8:45 am]
BILLING CODE 4910-13-P
