Airworthiness Directives; Airbus Airplanes, 48021-48024 [2014-18461]
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Federal Register / Vol. 79, No. 158 / Friday, August 15, 2014 / Rules and Regulations
dated July 3, 2014: Retorque within 6,000
flight cycles or 7,500 flight hours, whichever
occurs first after replacement of the pylon
outboard and inboard lower link fittings
required by paragraph (h) of this AD, and
thereafter at intervals not to exceed 6,000
flight cycles or 7,500 flight hours, whichever
occurs first.
(ii) For airplanes identified as Group 3 in
Embraer Service Bulletin 190–54–0015, dated
July 3, 2014, and Model ERJ 190–100 STD,
–100 LR, –100 IGW, –200 STD, –200 LR, and
–200 IGW airplanes having serial numbers
19000586 and subsequent: Retorque within
6,000 flight cycles or 7,500 flight hours,
whichever occurs first after the effective date
of this AD, and thereafter at intervals not to
exceed 6,000 flight cycles or 7,500 flight
hours, whichever occurs first.
(2) For Model ERJ 190–100 ECJ airplanes:
Retorque as specified in paragraph (i)(2)(i) or
(i)(2)(ii) of this AD, as applicable, in
accordance with Parts III and IV of the
Accomplishment Instructions of Embraer
Service Bulletin 190LIN–54–0006, dated July
3, 2014.
(i) For airplanes identified as Groups 1 and
2 in Embraer Service Bulletin 190LIN–54–
0006, dated July 3, 2014: Retorque within
2,000 flight cycles or 7,500 flight hours,
whichever occurs first after replacement of
the pylon outboard and inboard lower link
fittings required by paragraph (h) of this AD,
and thereafter at intervals not to exceed 2,000
flight cycles or 7,500 flight hours, whichever
occurs first.
(ii) For airplanes identified as Group 3 in
Embraer Service Bulletin 190LIN–54–0006,
dated July 3, 2014, and Model ECJ airplanes
having serial numbers 19000572 and
subsequent: Retorque within 2,000 flight
cycles or 7,500 flight hours, whichever
occurs first after the effective date of this AD,
and thereafter at intervals not to exceed 2,000
flight cycles or 7,500 flight hours, whichever
occurs first.
(j) Parts Installation Prohibition
As of the effective date of this AD, no
person may install, at the inboard or
outboard lower link fitting on any airplane,
a lock assembly identified in Embraer Service
Bulletin 190–54–0013, dated November 27,
2012; or Embraer Service Bulletin 190LIN–
54–0004, dated December 20, 2012.
emcdonald on DSK67QTVN1PROD with RULES
(k) Credit for Previous Actions
This paragraph provides credit for the
actions specified in paragraph (g) of this AD,
if those actions were performed before the
effective date of this AD using the service
information specified in paragraphs (k)(1)
through (k)(5) of this AD, as applicable. This
service information is not incorporated by
reference in this AD.
(1) Embraer Alert Service Bulletin 190–54–
A015, dated June 23, 2014.
(2) Embraer Alert Service Bulletin 190–54–
A015, Revision 01, dated June 26, 2014.
(3) Embraer Alert Service Bulletin 190–54–
A015, Revision 02, dated June 27, 2014.
(4) Embraer Alert Service Bulletin 190LIN–
54–A006, dated June 23, 2014.
(5) Embraer Alert Service Bulletin 190LIN–
54–A006, Revision 01, dated June 26, 2014.
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(l) 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:
Kathrine Rask, Aerospace Engineer,
International Branch, ANM–116, Transport
Airplane Directorate, FAA; telephone 425–
227–2180; fax 425–227–1149. Information
may be emailed to 9-ANM-116-AMOCREQUESTS@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
ANAC; or ANAC’s authorized Designee. If
approved by the ANAC Designee, the
approval must include the Designee’s
authorized signature.
(m) Related Information
(1) Refer to Mandatory Continuing
Airworthiness Information (MCAI) Brazilian
Airworthiness Directive 2014–07–01, dated
July 10, 2014, for related information. You
may examine the MCAI on the Internet at
https://www.regulations.gov by searching for
and locating Docket No. FAA–2014–0531.
(2) Service information identified in this
AD that is not incorporated by reference is
available at the addresses specified in
paragraphs (n)(3) and (n)(4) of this AD.
(n) 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) Embraer Alert Service Bulletin 190–54–
A015, Revision 03, dated June 27, 2014.
(ii) Embraer Alert Service Bulletin 190LIN–
54–A006, Revision 02, dated June 27, 2014.
(iii) Embraer Service Bulletin 190–54–
0013, dated November 27, 2012.
(iv) Embraer Service Bulletin 190–54–0015,
dated July 3, 2014.
(v) Embraer Service Bulletin 190LIN–54–
0004, dated December 20, 2012.
(vi) Embraer Service Bulletin 190LIN–54–
0006, dated July 3, 2014.
(3) For service information identified in
this AD, contact Embraer S.A., Technical
Publications Section (PC 060), Av. Brigadeiro
˜
Faria Lima, 2170—Putim—12227–901 Sao
Jose dos Campos—SP—Brasil; telephone +55
PO 00000
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48021
12 3927–5852 or +55 12 3309–0732; fax +55
12 3927–7546; email distrib@embraer.com.br;
Internet https://www.flyembraer.com.
(4) 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.
(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 https://
www.archives.gov/federal-register/cfr/ibrlocations.html.
Issued in Renton, Washington, on August
6, 2014.
Victor Wicklund,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. 2014–19263 Filed 8–14–14; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2014–0121; Directorate
Identifier 2013–NM–151–AD; Amendment
39–17928; AD 2014–16–04]
RIN 2120–AA64
Airworthiness Directives; Airbus
Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
AGENCY:
We are superseding
Airworthiness Directive (AD) 2008–14–
17 for certain Airbus Model A330–200
and A340–300 series airplanes. AD
2008–14–17 required a high frequency
eddy current (HFEC) inspection,
corrective actions if necessary, and
modifications. This new AD requires the
same actions as those required by AD
2008–14–17, but with a reduced
compliance time. This AD was
prompted by a determination from a
fatigue and damage tolerance evaluation
that the compliance time needs to be
revised. We are issuing this AD to detect
and correct damage of the upper shell
structure at the skin and frame interface,
which could result in reduced structural
integrity of the airframe.
DATES: This AD becomes effective
September 19, 2014.
The Director of the Federal Register
approved the incorporation by reference
of a certain publication listed in this AD
as of September 19, 2014.
The Director of the Federal Register
approved the incorporation by reference
SUMMARY:
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48022
Federal Register / Vol. 79, No. 158 / Friday, August 15, 2014 / Rules and Regulations
of certain other publications listed in
this AD as of August 21, 2008 (73 FR
40958, July 17, 2008).
ADDRESSES: You may examine the AD
docket on the Internet at https://
www.regulations.gov/
#!docketDetail;D=FAA-2014-0121; or in
person at the 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.
For service information identified in
this AD, contact Airbus SAS,
Airworthiness Office—EAL, 1 Rond
Point Maurice Bellonte, 31707 Blagnac
Cedex, France; telephone +33 5 61 93 36
96; fax +33 5 61 93 45 80; email
airworthiness.A330-A340@airbus.com;
Internet https://www.airbus.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.
FOR FURTHER INFORMATION CONTACT:
Vladimir Ulyanov, Aerospace Engineer,
International Branch, ANM–116,
Transport Airplane Directorate, FAA,
1601 Lind Avenue SW., Renton, WA
98057–3356; telephone 425–227–1138;
fax 425–227–1149.
SUPPLEMENTARY INFORMATION:
Discussion
emcdonald on DSK67QTVN1PROD with RULES
We issued a notice of proposed
rulemaking (NPRM) to amend 14 CFR
part 39 to supersede AD 2008–14–17,
Amendment 39–15612 (73 FR 40958,
July 17, 2008). AD 2008–14–17 applied
to certain Airbus Model A330–200 and
A340–300 series airplanes. The NPRM
published in the Federal Register on
March 3, 2014 (79 FR 11717).
The European Aviation Safety Agency
(EASA), which is the Technical Agent
for the Member States of the European
Community, has issued EASA
Airworthiness Directive 2013–0158,
dated July 22, 2013 (referred to after this
as the Mandatory Continuing
Airworthiness Information, or ‘‘the
MCAI’’), to correct an unsafe condition
for certain Airbus Model A330–200 and
A340–300 series airplanes. The MCAI
states:
During fatigue tests (EF3) on an A340–600
aeroplane, multiple damage was found in the
upper side shell structure at skin and frame
(FR) 84 and 85 interface, from stringer 6 to
15 Left-Hand (LH) and Right Hand (RH). This
damage occurred between 58 341 and 72 891
simulated flight cycles (FC).
Due to the higher Design Service Goal and
different design (e.g. skin thickness) for
A330–200 and A340–300 aeroplanes, the
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damage assessment concluded that these
aeroplanes can potentially be impacted.
This condition, if not detected and
corrected, could result in reduced structural
integrity of the airframe.
Prompted by these findings, EASA issued
[an] AD * * * to require a one-time inspection
and a modification to improve the upper
shell structure.
EASA AD 2007–0269R1 [https://
ad.easa.europa.eu/blob/easa_ad_2007_
0269R1_superseded.pdf/AD_2007-0269R1_2,
which corresponds to FAA AD 2008–14–17,
Amendment 39–15612 (73 FR 40958)] was
issued to clarify the fact that the [EASA] AD
was not applicable to A340–300 aeroplanes
on which both Airbus Mod 44205 and Mod
45012 have been embodied in production.
Since that [EASA] AD was issued, in the
frame of a new fatigue and damage tolerance
evaluation, taking into account the aeroplane
utilization, the threshold and intervals were
reassessed. This reassessment concluded
that, in that specific case, the threshold for
modifying the aeroplane must be reduced.
For the reasons described above, this
[EASA] AD retains the requirements of EASA
AD 2007–0269R1, which is superseded, but
requires these actions within the new
thresholds.
You may examine the MCAI in the AD
docket on the Internet at https://
www.regulations.gov/
#!documentDetail;D=FAA-2014-01210002.
Comments
We gave the public the opportunity to
participate in developing this AD. We
received no comments on the NPRM (79
FR 11717, March 3, 2014) or on the
determination of the cost to the public.
‘‘Contacting the Manufacturer’’
Paragraph in This AD
Since late 2006, we have included a
standard paragraph titled ‘‘Airworthy
Product’’ in all MCAI ADs in which the
FAA develops an AD based on a foreign
authority’s AD.
We have become aware that some
operators have misunderstood or
misinterpreted the Airworthy Product
paragraph to allow the owner/operator
to use messages provided by the
manufacturer as approval of deviations
during the accomplishment of an ADmandated action. The Airworthy
Product paragraph does not approve
messages or other information provided
by the manufacturer for deviations to
the requirements of the AD-mandated
actions. The Airworthy Product
paragraph only addresses the
requirement to contact the manufacturer
for corrective actions for the identified
unsafe condition and does not cover
deviations from other AD requirements.
However, deviations to AD-required
actions are addressed in 14 CFR 39.17,
and anyone may request the approval
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for an alternative method of compliance
to the AD-required actions using the
procedures found in 14 CFR 39.19.
To address this misunderstanding and
misinterpretation of the Airworthy
Product paragraph, we have changed the
paragraph and retitled it ‘‘Contacting the
Manufacturer.’’ This paragraph now
clarifies that for any requirement in this
AD to obtain corrective actions from a
manufacturer, the actions must be
accomplished using a method approved
by the FAA, EASA, or Airbus’s EASA
DOA.
The Contacting the Manufacturer
paragraph also clarifies that, if approved
by the DOA, the approval must include
the DOA-authorized signature. The DOA
signature indicates that the data and
information contained in the document
are EASA-approved, which is also FAAapproved. Messages and other
information provided by the
manufacturer that do not contain the
DOA-authorized signature approval are
not EASA-approved, unless EASA
directly approves the manufacturer’s
message or other information.
This clarification does not remove
flexibility previously afforded by the
Airworthy Product paragraph.
Consistent with long-standing FAA
policy, such flexibility was never
intended for required actions. This is
also consistent with the
recommendation of the Airworthiness
Directive Implementation Aviation
Rulemaking Committee to increase
flexibility in complying with ADs by
identifying those actions in
manufacturers’ service instructions that
are ‘‘Required for Compliance’’ with
ADs. We continue to work with
manufacturers to implement this
recommendation. But once we
determine that an action is required, any
deviation from the requirement must be
approved as an alternative method of
compliance.
We also have decided not to include
a generic reference to either the
‘‘delegated agent’’ or ‘‘design approval
holder (DAH) with State of Design
Authority design organization
approval,’’ but instead we have
provided the specific delegation
approval granted by the State of Design
Authority for the DAH throughout this
AD.
Conclusion
We reviewed the available data and
determined that air safety and the
public interest require adopting this AD
with the changes described previously
and minor editorial changes. We have
determined that these minor changes:
• Are consistent with the intent that
was proposed in the NPRM (79 FR
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Federal Register / Vol. 79, No. 158 / Friday, August 15, 2014 / Rules and Regulations
11717, March 3, 2014) for correcting the
unsafe condition; and
• Do not add any additional burden
upon the public than was already
proposed in the NPRM (79 FR 11717,
March 3, 2014).
We also determined that these
changes will not increase the economic
burden on any operator or increase the
scope of this AD.
48023
Costs of Compliance
We estimate that this AD affects 7
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
Inspection and Modification [retained actions
from.
AD 2008–14–17, Amendment 39–15612 (73
FR 40958, July 17, 2008)].
300 work-hours × $85 per hour = $25,500 ....
$72,730
$98,230
$687,610
The new requirements of this AD add
no additional economic burden.
emcdonald on DSK67QTVN1PROD with RULES
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 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.
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List of Subjects in 14 CFR Part 39
(c) Applicability
This AD applies to the airplanes,
certificated in any category, identified in
paragraphs (c)(1) and (c)(2) of this AD.
(1) Airbus Model A330–201, –202, –203,
–223, and –243 airplanes, all manufacturer
serial numbers (MSNs), on which Airbus
Modification 44205 has been embodied in
production, except those on which Airbus
Modification 52974 or Modification 53223
has been embodied in production.
(2) Airbus Model A340–311, –312, and
–313 airplanes, all MSNs on which Airbus
Modification 44205 has been embodied in
production, except those on which Airbus
Modification 52974, Modification 53223, or
Modification 45012 has been embodied in
production.
Air transportation, Aircraft, Aviation
safety, Incorporation by reference,
Safety.
(d) Subject
Air Transport Association (ATA) of
America Code 53, Fuselage.
Adoption of the Amendment
(e) Reason
This AD was prompted by a determination
from a fatigue and damage tolerance
evaluation that the compliance time of the
high frequency eddy current (HFEC)
inspection for cracking, and modification of
the upper shell structure of the fuselage
needs to be revised. We are issuing this AD
to detect and correct damage of the upper
shell structure at the skin and frame
interface, which could result in reduced
structural integrity of the airframe.
Examining the AD Docket
You may examine the AD docket on
the Internet at https://
www.regulations.gov/#!docket
Detail;D=FAA–2014–0121; 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 Operations
office (telephone 800–647–5527) is in
the ADDRESSES section.
Accordingly, under the authority
delegated to me by the Administrator,
the FAA amends 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
removing Airworthiness Directive (AD)
2008–14–17, Amendment 39–15612 (73
FR 40958, July 17, 2008), and adding the
following new AD:
■
2014–16–04 Airbus: Amendment 39–17928.
Docket No. FAA–2014–0121; Directorate
Identifier 2013–NM–151–AD.
(a) Effective Date
This AD becomes effective September 19,
2014.
(b) Affected ADs
This AD replaces AD 2008–14–17,
Amendment 39–15612 (73 FR 40958, July 17,
2008).
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(f) Compliance
Comply with this AD within the
compliance times specified, unless already
done.
(g) Retained Inspection
This paragraph restates the requirements of
paragraph (f)(1) of AD 2008–14–17,
Amendment 39–15612 (73 FR 40958, July 17,
2008), with reduced compliance times and
revised service information. For Airbus
Model A330–200 series airplanes, as
identified in paragraph (c) of this AD, on
which Modification 45012 has been
embodied in production: Within the
applicable compliance times specified in
paragraphs (g)(1), (g)(2), (g)(3), and (g)(4) of
this AD, do the HFEC inspection for cracking,
and corrective actions as applicable; and
modify the upper shell structure of the
fuselage; in accordance with the
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Federal Register / Vol. 79, No. 158 / Friday, August 15, 2014 / Rules and Regulations
Accomplishment Instructions of Airbus
Service Bulletin A330–53–3152, Revision 3,
dated December 22, 2011. Do all applicable
corrective actions before further flight.
(1) For airplanes pre-modification 48827
with short range utilization: At the later of
the times specified in paragraph (g)(1)(i) or
(g)(1)(ii) of this AD.
(i) Prior to 24,400 total flight cycles or
85,400 total flight hours, whichever occurs
first.
(ii) Within 12 months after the effective
date of this AD without exceeding 25,400
total flight cycles.
(2) For airplanes pre-modification 48827
with long range utilization: At the later of the
times specified in paragraph (g)(2)(i) or
(g)(2)(ii) of this AD.
(i) Prior to 18,900 total flight cycles or
122,900 total flight hours, whichever occurs
first.
(ii) Within 12 months after the effective
date of this AD without exceeding 25,400
total flight cycles.
(3) For airplanes post-modification 48827
with short range utilization: At the later of
the times specified in paragraph (g)(3)(i) or
(g)(3)(ii) of this AD.
(i) Prior to 16,400 total flight cycles or
57,400 total flight hours, whichever occurs
first.
(ii) Within 12 months after the effective
date of this AD without exceeding 17,100
total flight cycles or 94,700 total flight hours,
whichever occurs first.
(4) For airplanes post-modification 48827
with long range utilization: At the later of the
times specified in paragraph (g)(4)(i) or
(g)(4)(ii) of this AD.
(i) Prior to 12,700 total flight cycles or
82,700 total flight hours, whichever occurs
first.
(ii) Within 12 months after the effective
date of this AD without exceeding 17,100
total flight cycles or 94,700 total flight hours,
whichever occurs first.
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(h) Retained Modification
This paragraph restates the requirements of
paragraph (f)(2) of AD 2008–14–17,
Amendment 39–15612 (73 FR 40958, July 17,
2008), with revised paragraph formatting. For
Airbus Model A330–200 and A340–300
series airplanes as identified in paragraph (c)
of this AD, on which Modification 45012 has
not been embodied in production: At the
later of the compliance times specified in
paragraphs (h)(1) and (h)(2) of this AD,
modify the upper shell structure of the
fuselage, in accordance with the
Accomplishment Instructions of Airbus
Service Bulletin A330–53–3157, or Airbus
Service Bulletin A340–53–4163, both dated
July 5, 2006, as applicable.
(1) For the airplanes identified in
paragraphs (h)(1)(i) and (h)(1)(ii) of this AD.
(i) For Model A330–200 series airplanes,
prior to 6,600 total flight cycles.
(ii) For Model A340–300 series airplanes,
prior to 14,000 total flight cycles.
(2) Within 90 days after August 21, 2008
(the effective date of AD 2008–14–17,
Amendment 39–15612 (73 FR 40958, July 17,
2008)).
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(i) Credit for Previous Actions
This paragraph provides credit for actions
required by paragraph (g) of this AD, if those
actions were performed before the effective
date of this AD using the service information
specified in paragraph (i)(1), (i)(2), or (i)(3) of
this AD.
(1) Airbus Service Bulletin A330–53–3152,
dated April 10, 2007, which was
incorporated by reference in AD 2008–14–17,
Amendment 39–15612 (73 FR 40958,
July 17, 2008).
(2) Airbus Service Bulletin A330–53–3152,
Revision 1, dated May 5, 2009, which is not
incorporated by reference in this AD.
(3) Airbus Service Bulletin A330–53–3152,
Revision 2, dated July 27, 2011, which is not
incorporated by reference in this AD.
(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:
Vladimir Ulyanov, Aerospace Engineer,
International Branch, ANM–116, Transport
Airplane Directorate, FAA, 1601 Lind
Avenue SW., Renton, WA 98057–3356;
telephone 425–227–1138; 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
the European Aviation Safety Agency
(EASA); or Airbus’s EASA Design
Organization Approval (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) European
Aviation Safety Agency Airworthiness
Directive 2013–0158, dated July 22, 2013, for
related information. You may examine the
MCAI in the AD docket on the Internet at
https://www.regulations.gov/
#!documentDetail;D=FAA-2014-0121-0002.
(2) Service information identified in this
AD that is not incorporated by reference in
this AD is available at the addresses specified
in paragraphs (l)(5) and (l)(6) of this AD.
(l) Material Incorporated by Reference
(1) The Director of the Federal Register
approved the incorporation by reference
(IBR) of the service information listed in this
PO 00000
Frm 00010
Fmt 4700
Sfmt 4700
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.
(3) The following service information was
approved for IBR on September 19, 2014.
(i) Airbus Service Bulletin A330–53–3152,
Revision 3, dated December 22, 2011.
(ii) Reserved.
(4) The following service information was
approved for IBR on August 21, 2008 (73 FR
40958, July 17, 2008).
(i) Airbus Service Bulletin A330–53–3157,
dated July 5, 2006.
(ii) Airbus Service Bulletin A340–53–4163,
dated July 5, 2006.
(5) For service information identified in
this AD, contact Airbus SAS, Airworthiness
Office—EAL, 1 Rond Point Maurice Bellonte,
31707 Blagnac Cedex, France; telephone +33
5 61 93 36 96; fax +33 5 61 93 45 80; email
airworthiness.A330–A340@airbus.com;
Internet https://www.airbus.com.
(6) 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.
(7) 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: https://
www.archives.gov/federal-register/cfr/ibrlocations.html.
Issued in Renton, Washington, on July 23,
2014.
John P. Piccola,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. 2014–18461 Filed 8–14–14; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2013–0468; Directorate
Identifier 2012–NM–147–AD; Amendment
39–17924; AD 2014–15–21]
RIN 2120–AA64
Airworthiness Directives; The Boeing
Company Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule.
AGENCY:
We are superseding
Airworthiness Directive (AD) 2006–26–
06 for certain The Boeing Company
Model 777–200 and –300 series
airplanes equipped with Rolls-Royce
engines. AD 2006–26–06 required
repetitive inspections to detect cracks of
the outer V-blades of the thrust reverser,
and corrective action if necessary. AD
SUMMARY:
E:\FR\FM\15AUR1.SGM
15AUR1
]]>Agencies
[Federal Register Volume 79, Number 158 (Friday, August 15, 2014)]
[Rules and Regulations]
[Pages 48021-48024]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2014-18461]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2014-0121; Directorate Identifier 2013-NM-151-AD;
Amendment 39-17928; AD 2014-16-04]
RIN 2120-AA64
Airworthiness Directives; Airbus Airplanes
AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
-----------------------------------------------------------------------
SUMMARY: We are superseding Airworthiness Directive (AD) 2008-14-17 for
certain Airbus Model A330-200 and A340-300 series airplanes. AD 2008-
14-17 required a high frequency eddy current (HFEC) inspection,
corrective actions if necessary, and modifications. This new AD
requires the same actions as those required by AD 2008-14-17, but with
a reduced compliance time. This AD was prompted by a determination from
a fatigue and damage tolerance evaluation that the compliance time
needs to be revised. We are issuing this AD to detect and correct
damage of the upper shell structure at the skin and frame interface,
which could result in reduced structural integrity of the airframe.
DATES: This AD becomes effective September 19, 2014.
The Director of the Federal Register approved the incorporation by
reference of a certain publication listed in this AD as of September
19, 2014.
The Director of the Federal Register approved the incorporation by
reference
[[Page 48022]]
of certain other publications listed in this AD as of August 21, 2008
(73 FR 40958, July 17, 2008).
ADDRESSES: You may examine the AD docket on the Internet at https://www.regulations.gov/#!docketDetail;D=FAA-2014-0121; or in person at the
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.
For service information identified in this AD, contact Airbus SAS,
Airworthiness Office--EAL, 1 Rond Point Maurice Bellonte, 31707 Blagnac
Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61 93 45 80;
email airworthiness.A330-A340@airbus.com; Internet https://www.airbus.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.
FOR FURTHER INFORMATION CONTACT: Vladimir Ulyanov, Aerospace Engineer,
International Branch, ANM-116, Transport Airplane Directorate, FAA,
1601 Lind Avenue SW., Renton, WA 98057-3356; telephone 425-227-1138;
fax 425-227-1149.
SUPPLEMENTARY INFORMATION:
Discussion
We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR
part 39 to supersede AD 2008-14-17, Amendment 39-15612 (73 FR 40958,
July 17, 2008). AD 2008-14-17 applied to certain Airbus Model A330-200
and A340-300 series airplanes. The NPRM published in the Federal
Register on March 3, 2014 (79 FR 11717).
The European Aviation Safety Agency (EASA), which is the Technical
Agent for the Member States of the European Community, has issued EASA
Airworthiness Directive 2013-0158, dated July 22, 2013 (referred to
after this as the Mandatory Continuing Airworthiness Information, or
``the MCAI''), to correct an unsafe condition for certain Airbus Model
A330-200 and A340-300 series airplanes. The MCAI states:
During fatigue tests (EF3) on an A340-600 aeroplane, multiple
damage was found in the upper side shell structure at skin and frame
(FR) 84 and 85 interface, from stringer 6 to 15 Left-Hand (LH) and
Right Hand (RH). This damage occurred between 58 341 and 72 891
simulated flight cycles (FC).
Due to the higher Design Service Goal and different design (e.g.
skin thickness) for A330-200 and A340-300 aeroplanes, the damage
assessment concluded that these aeroplanes can potentially be
impacted.
This condition, if not detected and corrected, could result in
reduced structural integrity of the airframe.
Prompted by these findings, EASA issued [an] AD * * * to require
a one-time inspection and a modification to improve the upper shell
structure.
EASA AD 2007-0269R1 [https://ad.easa.europa.eu/blob/easa_ad_2007_0269R1_superseded.pdf/AD_2007-0269R1_2, which corresponds
to FAA AD 2008-14-17, Amendment 39-15612 (73 FR 40958)] was issued
to clarify the fact that the [EASA] AD was not applicable to A340-
300 aeroplanes on which both Airbus Mod 44205 and Mod 45012 have
been embodied in production.
Since that [EASA] AD was issued, in the frame of a new fatigue
and damage tolerance evaluation, taking into account the aeroplane
utilization, the threshold and intervals were reassessed. This
reassessment concluded that, in that specific case, the threshold
for modifying the aeroplane must be reduced.
For the reasons described above, this [EASA] AD retains the
requirements of EASA AD 2007-0269R1, which is superseded, but
requires these actions within the new thresholds.
You may examine the MCAI in the AD docket on the Internet at https://www.regulations.gov/#!documentDetail;D=FAA-2014-0121-0002.
Comments
We gave the public the opportunity to participate in developing
this AD. We received no comments on the NPRM (79 FR 11717, March 3,
2014) or on the determination of the cost to the public.
``Contacting the Manufacturer'' Paragraph in This AD
Since late 2006, we have included a standard paragraph titled
``Airworthy Product'' in all MCAI ADs in which the FAA develops an AD
based on a foreign authority's AD.
We have become aware that some operators have misunderstood or
misinterpreted the Airworthy Product paragraph to allow the owner/
operator to use messages provided by the manufacturer as approval of
deviations during the accomplishment of an AD-mandated action. The
Airworthy Product paragraph does not approve messages or other
information provided by the manufacturer for deviations to the
requirements of the AD-mandated actions. The Airworthy Product
paragraph only addresses the requirement to contact the manufacturer
for corrective actions for the identified unsafe condition and does not
cover deviations from other AD requirements. However, deviations to AD-
required actions are addressed in 14 CFR 39.17, and anyone may request
the approval for an alternative method of compliance to the AD-required
actions using the procedures found in 14 CFR 39.19.
To address this misunderstanding and misinterpretation of the
Airworthy Product paragraph, we have changed the paragraph and retitled
it ``Contacting the Manufacturer.'' This paragraph now clarifies that
for any requirement in this AD to obtain corrective actions from a
manufacturer, the actions must be accomplished using a method approved
by the FAA, EASA, or Airbus's EASA DOA.
The Contacting the Manufacturer paragraph also clarifies that, if
approved by the DOA, the approval must include the DOA-authorized
signature. The DOA signature indicates that the data and information
contained in the document are EASA-approved, which is also FAA-
approved. Messages and other information provided by the manufacturer
that do not contain the DOA-authorized signature approval are not EASA-
approved, unless EASA directly approves the manufacturer's message or
other information.
This clarification does not remove flexibility previously afforded
by the Airworthy Product paragraph. Consistent with long-standing FAA
policy, such flexibility was never intended for required actions. This
is also consistent with the recommendation of the Airworthiness
Directive Implementation Aviation Rulemaking Committee to increase
flexibility in complying with ADs by identifying those actions in
manufacturers' service instructions that are ``Required for
Compliance'' with ADs. We continue to work with manufacturers to
implement this recommendation. But once we determine that an action is
required, any deviation from the requirement must be approved as an
alternative method of compliance.
We also have decided not to include a generic reference to either
the ``delegated agent'' or ``design approval holder (DAH) with State of
Design Authority design organization approval,'' but instead we have
provided the specific delegation approval granted by the State of
Design Authority for the DAH throughout this AD.
Conclusion
We reviewed the available data and determined that air safety and
the public interest require adopting this AD with the changes described
previously and minor editorial changes. We have determined that these
minor changes:
Are consistent with the intent that was proposed in the
NPRM (79 FR
[[Page 48023]]
11717, March 3, 2014) for correcting the unsafe condition; and
Do not add any additional burden upon the public than was
already proposed in the NPRM (79 FR 11717, March 3, 2014).
We also determined that these changes will not increase the
economic burden on any operator or increase the scope of this AD.
Costs of Compliance
We estimate that this AD affects 7 airplanes of U.S. registry.
We estimate the following costs to comply with this AD:
Estimated costs
----------------------------------------------------------------------------------------------------------------
Cost per Cost on U.S.
Action Labor cost Parts cost product operators
----------------------------------------------------------------------------------------------------------------
Inspection and Modification 300 work-hours x $85 $72,730 $98,230 $687,610
[retained actions from. per hour = $25,500.
AD 2008-14-17, Amendment 39-15612
(73 FR 40958, July 17, 2008)].
----------------------------------------------------------------------------------------------------------------
The new requirements of this AD add no additional economic burden.
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 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.
Examining the AD Docket
You may examine the AD docket on the Internet at https://www.regulations.gov/#!docketDetail;D=FAA-2014-0121; 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 Operations office (telephone 800-647-
5527) is in the ADDRESSES section.
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 removing Airworthiness Directive (AD)
2008-14-17, Amendment 39-15612 (73 FR 40958, July 17, 2008), and adding
the following new AD:
2014-16-04 Airbus: Amendment 39-17928. Docket No. FAA-2014-0121;
Directorate Identifier 2013-NM-151-AD.
(a) Effective Date
This AD becomes effective September 19, 2014.
(b) Affected ADs
This AD replaces AD 2008-14-17, Amendment 39-15612 (73 FR 40958,
July 17, 2008).
(c) Applicability
This AD applies to the airplanes, certificated in any category,
identified in paragraphs (c)(1) and (c)(2) of this AD.
(1) Airbus Model A330-201, -202, -203, -223, and -243 airplanes,
all manufacturer serial numbers (MSNs), on which Airbus Modification
44205 has been embodied in production, except those on which Airbus
Modification 52974 or Modification 53223 has been embodied in
production.
(2) Airbus Model A340-311, -312, and -313 airplanes, all MSNs on
which Airbus Modification 44205 has been embodied in production,
except those on which Airbus Modification 52974, Modification 53223,
or Modification 45012 has been embodied in production.
(d) Subject
Air Transport Association (ATA) of America Code 53, Fuselage.
(e) Reason
This AD was prompted by a determination from a fatigue and
damage tolerance evaluation that the compliance time of the high
frequency eddy current (HFEC) inspection for cracking, and
modification of the upper shell structure of the fuselage needs to
be revised. We are issuing this AD to detect and correct damage of
the upper shell structure at the skin and frame interface, which
could result in reduced structural integrity of the airframe.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(g) Retained Inspection
This paragraph restates the requirements of paragraph (f)(1) of
AD 2008-14-17, Amendment 39-15612 (73 FR 40958, July 17, 2008), with
reduced compliance times and revised service information. For Airbus
Model A330-200 series airplanes, as identified in paragraph (c) of
this AD, on which Modification 45012 has been embodied in
production: Within the applicable compliance times specified in
paragraphs (g)(1), (g)(2), (g)(3), and (g)(4) of this AD, do the
HFEC inspection for cracking, and corrective actions as applicable;
and modify the upper shell structure of the fuselage; in accordance
with the
[[Page 48024]]
Accomplishment Instructions of Airbus Service Bulletin A330-53-3152,
Revision 3, dated December 22, 2011. Do all applicable corrective
actions before further flight.
(1) For airplanes pre-modification 48827 with short range
utilization: At the later of the times specified in paragraph
(g)(1)(i) or (g)(1)(ii) of this AD.
(i) Prior to 24,400 total flight cycles or 85,400 total flight
hours, whichever occurs first.
(ii) Within 12 months after the effective date of this AD
without exceeding 25,400 total flight cycles.
(2) For airplanes pre-modification 48827 with long range
utilization: At the later of the times specified in paragraph
(g)(2)(i) or (g)(2)(ii) of this AD.
(i) Prior to 18,900 total flight cycles or 122,900 total flight
hours, whichever occurs first.
(ii) Within 12 months after the effective date of this AD
without exceeding 25,400 total flight cycles.
(3) For airplanes post-modification 48827 with short range
utilization: At the later of the times specified in paragraph
(g)(3)(i) or (g)(3)(ii) of this AD.
(i) Prior to 16,400 total flight cycles or 57,400 total flight
hours, whichever occurs first.
(ii) Within 12 months after the effective date of this AD
without exceeding 17,100 total flight cycles or 94,700 total flight
hours, whichever occurs first.
(4) For airplanes post-modification 48827 with long range
utilization: At the later of the times specified in paragraph
(g)(4)(i) or (g)(4)(ii) of this AD.
(i) Prior to 12,700 total flight cycles or 82,700 total flight
hours, whichever occurs first.
(ii) Within 12 months after the effective date of this AD
without exceeding 17,100 total flight cycles or 94,700 total flight
hours, whichever occurs first.
(h) Retained Modification
This paragraph restates the requirements of paragraph (f)(2) of
AD 2008-14-17, Amendment 39-15612 (73 FR 40958, July 17, 2008), with
revised paragraph formatting. For Airbus Model A330-200 and A340-300
series airplanes as identified in paragraph (c) of this AD, on which
Modification 45012 has not been embodied in production: At the later
of the compliance times specified in paragraphs (h)(1) and (h)(2) of
this AD, modify the upper shell structure of the fuselage, in
accordance with the Accomplishment Instructions of Airbus Service
Bulletin A330-53-3157, or Airbus Service Bulletin A340-53-4163, both
dated July 5, 2006, as applicable.
(1) For the airplanes identified in paragraphs (h)(1)(i) and
(h)(1)(ii) of this AD.
(i) For Model A330-200 series airplanes, prior to 6,600 total
flight cycles.
(ii) For Model A340-300 series airplanes, prior to 14,000 total
flight cycles.
(2) Within 90 days after August 21, 2008 (the effective date of
AD 2008-14-17, Amendment 39-15612 (73 FR 40958, July 17, 2008)).
(i) Credit for Previous Actions
This paragraph provides credit for actions required by paragraph
(g) of this AD, if those actions were performed before the effective
date of this AD using the service information specified in paragraph
(i)(1), (i)(2), or (i)(3) of this AD.
(1) Airbus Service Bulletin A330-53-3152, dated April 10, 2007,
which was incorporated by reference in AD 2008-14-17, Amendment 39-
15612 (73 FR 40958,
July 17, 2008).
(2) Airbus Service Bulletin A330-53-3152, Revision 1, dated May
5, 2009, which is not incorporated by reference in this AD.
(3) Airbus Service Bulletin A330-53-3152, Revision 2, dated July
27, 2011, which is not incorporated by reference in this AD.
(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: Vladimir
Ulyanov, Aerospace Engineer, International Branch, ANM-116,
Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton,
WA 98057-3356; telephone 425-227-1138; 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 the
European Aviation Safety Agency (EASA); or Airbus's EASA Design
Organization Approval (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) European Aviation Safety Agency Airworthiness Directive 2013-
0158, dated July 22, 2013, for related information. You may examine
the MCAI in the AD docket on the Internet at https://www.regulations.gov/#!documentDetail;D=FAA-2014-0121-0002.
(2) Service information identified in this AD that is not
incorporated by reference in this AD is available at the addresses
specified in paragraphs (l)(5) and (l)(6) of this AD.
(l) 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.
(3) The following service information was approved for IBR on
September 19, 2014.
(i) Airbus Service Bulletin A330-53-3152, Revision 3, dated
December 22, 2011.
(ii) Reserved.
(4) The following service information was approved for IBR on
August 21, 2008 (73 FR 40958, July 17, 2008).
(i) Airbus Service Bulletin A330-53-3157, dated July 5, 2006.
(ii) Airbus Service Bulletin A340-53-4163, dated July 5, 2006.
(5) For service information identified in this AD, contact
Airbus SAS, Airworthiness Office--EAL, 1 Rond Point Maurice
Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96;
fax +33 5 61 93 45 80; email airworthiness.A330-A340@airbus.com;
Internet https://www.airbus.com.
(6) 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.
(7) 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: https://www.archives.gov/federal-register/cfr/ibr-locations.html.
Issued in Renton, Washington, on July 23, 2014.
John P. Piccola,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2014-18461 Filed 8-14-14; 8:45 am]
BILLING CODE 4910-13-P
