Airworthiness Directives; Airbus Airplanes, 73092-73096 [2015-28886]
Download as PDF
<![CDATA[
73092
Federal Register / Vol. 80, No. 226 / Tuesday, November 24, 2015 / Rules and Regulations
V. Differences Between the Banks and
the Enterprises
Section 1313(f) of the Safety and
Soundness Act requires the Director to
consider the differences between the
Banks and the Enterprises whenever
promulgating regulations that affect the
Banks. In developing the amendments
to this rule, FHFA considered the
differences between the Banks and the
Enterprises, but also adhered to the
statutory mandate that the regulation be
‘‘consistent and comparable’’ with the
regulations of the other agencies. In
implementing the regulation, FHFA will
define scenarios for the regulated
entities, bearing in mind the key risk
exposures at each regulated entity.
In the final rule, FHFA requires
different timeframes for reporting stress
test results for the Enterprises versus the
Banks. For the Enterprises, FHFA sets
the dates for reporting stress test results
to the regulator, the FRB, and the public
in proximity to similar dates in the
other agencies’ rules for institutions
with over $50 billion in assets.
Reporting dates for all the Banks,
regardless of size, are set in proximity
to similar dates for institutions with less
than $50 billion in assets. As a result,
the Banks have over three additional
months to report results to FHFA, the
FRB, and the public.
VI. Paperwork Reduction Act
The final rule does not contain any
collections of information pursuant to
the Paperwork Reduction Act of 1995
(44 U.S.C. 3501, et seq.). Therefore,
FHFA has not submitted any
information to the Office of
Management and Budget for review.
mstockstill on DSK4VPTVN1PROD with RULES
List of Subjects in 12 CFR Part 1238
Administrative practice and
procedure, Capital, Federal Home Loan
Banks, Government-sponsored
enterprises, Regulated entities,
Reporting and recordkeeping
requirements, Stress test.
Authority and Issuance
For the reasons stated in the
preamble, and under the authority of 12
U.S.C. 4513, 4526, and 5365(i), FHFA
23:14 Nov 23, 2015
Jkt 238001
Authority: 12 U.S.C. 5365(i); 12 U.S.C.
4513, 4526, 4612; and 12 U.S.C. 1426.
stress test results for the severely
adverse scenario not earlier than
November 15 and not later than
November 30 of each year. The
summary may be published on the
regulated entity’s Web site or in any
other form that is reasonably accessible
to the public;
*
*
*
*
*
2. Amend § 1238.3 by revising
paragraphs (a)(1) and (b) to read as
follows:
Dated: November 11, 2015.
Melvin L. Watt,
Director, Federal Housing Finance Agency.
PART 1238—STRESS TESTING OF
REGULATED ENTITIES
1. The authority citation for part 1238
continues to read as follows:
■
■
§ 1238.3
[FR Doc. 2015–29861 Filed 11–23–15; 8:45 am]
Annual stress test.
(a) * * *
(1) Shall complete an annual stress
test of itself based on its data as of
December 31 of the preceding calendar
year;
*
*
*
*
*
(b) Scenarios provided by FHFA. In
conducting its annual stress tests under
this section, each regulated entity must
use scenarios provided by FHFA, which
shall be generally consistent with and
comparable to those established by the
FRB, that reflect a minimum of three
sets of economic and financial
conditions, including a baseline,
adverse, and severely adverse scenario.
Not later than 30 days after the FRB
publishes its scenarios, FHFA will issue
to all regulated entities a description of
the baseline, adverse, and severely
adverse scenarios that each regulated
entity shall use to conduct its annual
stress tests under this part.
■ 3. Amend § 1238.5 by revising
paragraph (a) to read as follows:
§ 1238.5 Required report to FHFA and the
FRB of stress test results and related
information.
VII. Regulatory Flexibility Act
The final rule applies only to the
regulated entities, which do not come
within the meaning of small entities as
defined in the Regulatory Flexibility Act
(see 5 U.S.C. 601(6)). Therefore, in
accordance with section 605(b) of the
Regulatory Flexibility Act (5 U.S.C.
605(b)), the General Counsel of FHFA
certifies that this final rule will not have
a significant economic impact on a
substantial number of small entities.
VerDate Sep<11>2014
amends part 1238 of title 12 of the Code
of Federal Regulations as follows:
(a) Report required for stress tests. On
or before May 20 of each year, the
Enterprises must report the results of
the stress tests required under § 1238.3
to FHFA, and to the FRB, in accordance
with paragraph (b) of this section; and
on or before August 31 of each year, the
Banks must report the results of the
stress tests required under § 1238.3 to
FHFA, and to the FRB, in accordance
with paragraph (b) of this section;
*
*
*
*
*
■ 4. Amend § 1238.7 by revising
paragraph (a) to read as follows:
§ 1238.7 Publication of results by
regulated entities.
(a) Public disclosure of results
required for stress tests of regulated
entities. The Enterprises must disclose
publicly a summary of the stress test
results for the severely adverse scenario
not earlier than August 1 and not later
than August 15 of each year. Each Bank
must disclose publicly a summary of the
PO 00000
Frm 00006
Fmt 4700
Sfmt 4700
BILLING CODE 8070–01–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2015–0490; Directorate
Identifier 2014–NM–018–AD; Amendment
39–18322; AD 2015–23–06]
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) 2008–22–
20 for certain Airbus Model A330–200,
A330–300, and A340–300 series
airplanes. AD 2008–22–20 required
repetitive high frequency eddy current
(HFEC) inspections for cracking, repair
if necessary, and modification of the
upper shell structure of the fuselage.
This new AD shortens certain
compliance times. This AD was
prompted by a determination from a
fatigue and damage tolerance evaluation
that the compliance times must be
reduced. We are issuing this AD to
prevent fatigue cracking of the upper
shell structure of the fuselage, which
could result in reduced structural
integrity of the airplane.
DATES: This AD becomes effective
December 29, 2015.
The Director of the Federal Register
approved the incorporation by reference
of certain publications listed in this AD
as of December 29, 2015.
The Director of the Federal Register
approved the incorporation by reference
of certain other publications listed in
this AD as of December 17, 2008 (73 FR
66747, November 12, 2008).
ADDRESSES: You may examine the AD
docket on the Internet at https://
www.regulations.gov/#!docketDetail;
SUMMARY:
E:\FR\FM\24NOR1.SGM
24NOR1
Federal Register / Vol. 80, No. 226 / Tuesday, November 24, 2015 / Rules and Regulations
mstockstill on DSK4VPTVN1PROD with RULES
D=FAA-2015-0490; 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. It is also
available on the Internet at https://
www.regulations.gov by searching for
and locating Docket No. FAA–2015–
0490.
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 2008–22–20,
Amendment 39–15717 (73 FR 66747,
November 12, 2008). AD 2008–22–20
applied to certain Airbus Model A330–
200, A330–300, and A340–300 series
airplanes. The NPRM published in the
Federal Register on March 17, 2015 (80
FR 13799). The NPRM was prompted by
a determination from a fatigue and
damage tolerance evaluation that the
compliance times must be reduced. The
NPRM also proposed to shorten certain
compliance times. We are issuing this
AD to prevent fatigue cracking of the
upper shell structure of the fuselage,
which could result in reduced structural
integrity of the airplane.
The European Aviation Safety Agency
(EASA), which is the Technical Agent
for the Member States of the European
Union, has issued EASA Airworthiness
Directive 2014–0012R1, dated January
24, 2014 (referred to after this as the
Mandatory Continuing Airworthiness
Information, or ‘‘the MCAI’’), to correct
an unsafe condition for certain Airbus
Model A330–200, A330–300, and A340–
300 series airplanes. The MCAI states:
During fatigue tests (EF3) on the A340–600,
damage was found in the longitudinal
doubler at the Vertical Tail Plane (VTP)
VerDate Sep<11>2014
23:14 Nov 23, 2015
Jkt 238001
attachment cut out between Frame (FR) 80
and FR86. This damage occurred between
58,341 and 72,891 simulated flight cycles
(FC).
Due to the higher Design Service Goal and
different design of the affected structural area
(e.g. doubler thickness) for A330–200/–300
and A340–300 airplane series, the damage
assessment concluded that these airplanes
may be also potentially affected.
This condition, if not detected and
corrected, could affect the structural integrity
of the upper shell structure between FR80
and FR86.
Prompted by these findings, EASA issued
AD 2007–0284 [(https://ad.easa.europa.eu/
blob/easa_ad_2007_0284_superseded.pdf/
AD_2007-0284_1)] to require implementation
of an inspection programme of this structural
area using a high frequency eddy current
(HFEC) method and a modification to
improve the upper shell structure.
Since that [EASA] AD was issued, in the
frame of a new fatigue and damage tolerance
evaluation, taking into account the airplane
utilisation, the inspection threshold and
intervals have been reassessed and the
conclusion was that the thresholds and
intervals for inspection, as well as the
threshold for modifying the airplane, must be
reduced.
For the reason described above, this
[EASA] AD retains the requirements of EASA
AD 2007–0284, which is superseded and
introduces redefined thresholds and
intervals.
This [EASA] AD is revised to clarify that,
under some conditions, accomplishment of a
repair constitutes terminating action for the
repetitive inspections. One of the outcome of
this clarification is the deletion of paragraph
(5) of this [EASA] AD.
You may examine the MCAI in the
AD docket on the Internet at https://
www.regulations.gov/#!documentDetail;
D=FAA-2015-0490-0002.
Comments
We gave the public the opportunity to
participate in developing this AD. The
following presents the comments
received on the NPRM (80 FR 13799,
March 17, 2015) and the FAA’s response
to each comment.
Support for the NPRM (80 FR 13799,
March 17, 2015)
An anonymous commenter agreed
with the safety benefit provided by the
NPRM (80 FR 13799, March 17, 2015).
Request for Revise Cost
Delta requested that we revise the
NPRM (80 FR 13799, March 17, 2015) to
relay the heavy impact of accomplishing
Airbus Service Bulletin A330–53–3160,
Revision 03, dated January 6, 2012.
Delta explained that the modification
specified in Airbus Service Bulletin
A330–53–3160, Revision 03, dated
January 6, 2012, requires removal of the
vertical stabilizer and the aft galley,
which can heavily impact the operation.
PO 00000
Frm 00007
Fmt 4700
Sfmt 4700
73093
Delta reasoned that it has consulted
with its maintenance organization and it
is estimated to take 400 work-hours
instead of 208 work-hours.
We disagree with the request to revise
this AD. We made the cost estimate
based on the information provided in
Airbus Service Bulletin A330–53–3160,
Revision 03, dated January 6, 2012. The
required work-hours defined in Airbus
Service Bulletin A330–53–3160,
Revision 03, dated January 6, 2012, are
based on the direct labor cost to do the
work. The need to remove and reinstall
the aft galley depends on the airplane
interior configuration and may differ
from operator to operator. We are unable
to determine all possible interior
configurations and thus determine the
maximum work-hours which may be
required for any specific configuration.
This estimate assumes that the work
will be done by experienced personnel,
and may need to be revised upwards to
suit an operator’s circumstances. The
estimate does not include the time to
prepare, plan, or inspect the work. We
have made no changes to this AD in this
regard.
Conclusion
We reviewed the available 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 (80 FR
13799, March 17, 2015) for correcting
the unsafe condition; and
• Do not add any additional burden
upon the public than was already
proposed in the NPRM (80 FR 13799,
March 17, 2015).
Related Service Information Under 1
CFR Part 51
Airbus has issued the following
service information.
• Airbus Service Bulletin A330–53–
3159, Revision 02, dated March 29,
2010, describes procedures for a
modification of the fuselage, which
includes inspections (e.g., eddy current
rotating probe test of fastener holes for
cracking, high frequency eddy current
(HFEC) inspections for cracking of the
upper shell structure of the fuselage,
and checks of the fastener position for
clearance) and applicable corrective
actions (e.g., repair and rework).
• Airbus Service Bulletin A330–53–
3160, Revision 03, dated January 6,
2012, describes procedures for
applicable actions, including an eddy
current rotating probe test for cracking
of the fastener holes and an HFEC
inspection for cracks in the upper shell
E:\FR\FM\24NOR1.SGM
24NOR1
73094
Federal Register / Vol. 80, No. 226 / Tuesday, November 24, 2015 / Rules and Regulations
mstockstill on DSK4VPTVN1PROD with RULES
of the fuselage (and including checks of
the fastener position for clearance and
applicable corrective actions (e.g., repair
and rework)), and a modification of the
airplane upper shell structure of the
fuselage between FR80 and FR86.
• Airbus Service Bulletin A330–53–
3168, Revision 02, dated December 21,
2011, describes procedures for a HFEC
inspection for cracking of the upper
shell structure of the fuselage between
FR80 and FR86.
• Airbus Service Bulletin A340–53–
4165, Revision 02, dated March 29,
2010, describes procedures for a
modification of the fuselage, which
includes inspections (e.g., eddy current
rotating probe test of fastener holes for
cracking, HFEC inspections for cracking
of the upper shell structure of the
fuselage, and checks of the fastener
position for clearance) and applicable
corrective actions (e.g., repair and
rework).
• Airbus Service Bulletin A340–53–
4172, Revision 01, dated July 8, 2009,
describes procedures for inspections
(e.g., rototest inspections of fastener
holes for cracking, HFEC inspections for
cracking of the upper shell structure of
the fuselage, and checks of the fastener
position for clearance) and modification
of the airplane upper shell structure
between FR80 and FR86 (including
applicable corrective actions (e.g., repair
and rework).
• Airbus Service Bulletin A340–53–
4174, Revision 02, dated December 21,
2011, describes procedures for a HFEC
inspection for cracking of the upper
shell structure of the fuselage between
FR80 and FR86.
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 of
this AD.
Costs of Compliance
We estimate that this AD affects 26
airplanes of U.S. registry. We also
estimate that it will take about 208
work-hours per product to comply with
the basic requirements (inspection and
modification) of this AD. The average
labor rate is $85 per work-hour.
Required parts will cost about $28,360
per product. Based on these figures, we
estimate the cost of this AD on U.S.
operators to be $1,197,040, or $46,040
per product.
We have received no definitive data
that will enable us to provide cost
estimates for the on-condition actions
specified in this AD.
According to the manufacturer, some
of the costs of this AD may be covered
under warranty, thereby reducing the
VerDate Sep<11>2014
23:14 Nov 23, 2015
Jkt 238001
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
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
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)
2008–22–20, Amendment 39–15717 (73
FR 66747, November 12, 2008), and
adding the following new AD:
■
2015–23–06 Airbus: Amendment 39–18322.
Docket No. FAA–2015–0490; Directorate
Identifier 2014–NM–018–AD.
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.
(a) Effective Date
Examining the AD Docket
(e) Reason
You may examine the AD docket on
the Internet at https://
www.regulations.gov/#!docket
Detail;D=FAA-2015-0490; 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
This AD was prompted by the results of a
fatigue and damage tolerance evaluation that
concluded existing compliance times must be
reduced. We are issuing this AD to prevent
fatigue cracking of the upper shell structure
of the fuselage, which could result in
reduced structural integrity of the airplane.
PO 00000
Frm 00008
Fmt 4700
Sfmt 4700
This AD becomes effective December 29,
2015.
(b) Affected ADs
This AD replaces AD 2008–22–20,
Amendment 39–15717 (73 FR 66747,
November 12, 2008).
(c) Applicability
This AD applies to Airbus Model A330–
201, –202, –203, –223, –243, –301, –302,
–303, –321, –322, –323, –341, –342, and –343
airplanes; and Model A340–311, –312, and
–313 airplanes; certificated in any category;
all manufacturer serial numbers on which
Airbus Modification 44205 has been
embodied in production, except those on
which Airbus Modification 52974 or 53223
has been embodied in production.
(d) Subject
Air Transport Association (ATA) of
America Code 53, Fuselage.
(f) Compliance
Comply with this AD within the
compliance times specified, unless already
done.
E:\FR\FM\24NOR1.SGM
24NOR1
Federal Register / Vol. 80, No. 226 / Tuesday, November 24, 2015 / Rules and Regulations
(h) Corrective Action for Airbus Model
A330–300 and A340–300 Airplanes, Except
Model A340–300 WV 027 Airplanes
mstockstill on DSK4VPTVN1PROD with RULES
(g) Inspection for Airbus Model A330–300
and A340–300 Airplanes, Except Model
A340–300 Weight Variant (WV) 027
Airplanes
For Model A330–300 and A340–300
airplanes, except Model A340–300 WV 027
airplanes: At the applicable time specified in
paragraph (g)(1) or (g)(2) of this AD, do a high
frequency eddy current (HFEC) inspection for
cracking of the upper shell structure between
frame (FR) 80 and FR86, in accordance with
the Accomplishment Instructions of Airbus
Service Bulletin A330–53–3168, Revision 02,
dated December 21, 2011; or Airbus Service
Bulletin A340–53–4174, Revision 02, dated
December 21, 2011; as applicable. Repeat the
inspection thereafter at the applicable time
specified in paragraph 1.E., ‘‘COMPLIANCE,’’
of Airbus Service Bulletin A330–53–3168,
Revision 02, dated December 21, 2011; or
Airbus Service Bulletin A340–53–4174,
Revision 02, dated December 21, 2011; as
applicable.
(1) For airplanes that, as of the effective
date of this AD, have not been inspected in
accordance with Airbus Service Bulletin
A330–53–3168; or Airbus Service Bulletin
A340–53–4174; as applicable: Inspect at the
later of the times specified in paragraphs
(g)(1)(i) and (g)(1)(ii) of this AD.
(i) Before reaching the applicable threshold
specified in paragraph 1.E., ‘‘COMPLIANCE,’’
of Airbus Service Bulletin A330–53–3168,
Revision 02, dated December 21, 2011; or
Airbus Service Bulletin A340–53–4174,
Revision 02, dated December 21, 2011; as
applicable for airplane model, configuration,
and utilization, since the airplane’s first
flight.
(ii) Within the threshold defined in
paragraph 1.E, ‘‘COMPLIANCE,’’ of Airbus
Service Bulletin A330–53–3168, Revision 01,
dated February 15, 2008; or Airbus Service
Bulletin A340–53–4174, Revision 01, dated
February 15, 2008; as applicable for airplane
model, configuration, and utilization since
the airplane’s first flight; or within 12 months
after the effective date of this AD; whichever
occurs first.
(2) For airplanes that, as of the effective
date of this AD, have been inspected in
accordance with Airbus Service Bulletin
A330–53–3168; or Airbus Service Bulletin
A340–53–4174; as applicable: Inspect at the
later of the times specified in paragraphs
(g)(2)(i) and (g)(2)(ii) of this AD.
(i) Within the applicable interval specified
in paragraph 1.E., ‘‘COMPLIANCE,’’ of
Airbus Service Bulletin A330–53–3168,
Revision 02, dated December 21, 2011; or
Airbus Service Bulletin A340–53–4174,
Revision 02, dated December 21, 2011; as
applicable; to be counted from the last
inspection.
(ii) Within 12 months after the effective
date of this AD without exceeding the
intervals defined in paragraph 1.E,
‘‘COMPLIANCE,’’ of Airbus Service Bulletin
A330–53–3168, Revision 01, dated February
15, 2008; or Airbus Service Bulletin A340–
53–4174, Revision 01, dated February 15,
2008; as applicable for airplane model,
configuration, and utilization to be counted
from the last inspection.
VerDate Sep<11>2014
23:14 Nov 23, 2015
Jkt 238001
If any crack is detected during any HFEC
inspection required by the introductory text
to paragraph (g) of this AD: 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
Airbus’s EASA Design Organization
Approval (DOA). Accomplishment of a repair
for a specific area, as required by this
paragraph, is terminating action for the
repetitive HFEC inspections required by the
introductory text to paragraph (g) of this AD,
as applicable, for that specific repaired area
only. The need and definition of subsequent
repetitive inspections (if any) for that specific
repaired area will be defined in the
applicable repair 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).
73095
(k) Inspection and Modification for Airbus
Model A340–300 Airplanes, Only WV 027
For Model A340–300 airplanes, WV 027
only: Before the accumulation of 14,200 total
flight cycles from the airplane’s first flight,
do all applicable inspections and modify the
airplane upper shell structure between FR80
and FR86; in accordance with the
Accomplishment Instructions of Airbus
Service Bulletin A340–53–4172, Revision 01,
dated July 8, 2009.
(l) Corrective Action for Airbus Model A330–
200 Airplanes; and Model A340–300
Airplanes, only WV 027
If any crack is detected during the
inspection required by the introductory text
to paragraph (j) of this AD, or paragraph (k)
of this AD, before further flight, repair using
a method approved by the Manager,
International Branch, ANM–116, Transport
Airplane Directorate, FAA; or EASA; or
Airbus’s EASA DOA; concurrently with
modification required by paragraph the
introductory text to paragraph (j) of this AD,
or paragraph (k) of this AD.
(j) Inspection and Modification for Airbus
Model A330–200 Airplanes
(m) Definition of ‘‘Threshold’’ and ‘‘Interval’’
(1) For the purposes of this AD, the term
‘‘Threshold,’’ as used in paragraph 1.E.,
‘‘COMPLIANCE,’’ of the service information
specified in paragraphs (m)(2)(i) through
(m)(2)(vi) of this AD means the total flight
cycles or flight hours accumulated since the
airplane’s first flight.
(2) For the purposes of this AD, the term
‘‘Interval’’ as used in paragraph 1.E.,
‘‘COMPLIANCE,’’ of the service information
specified in paragraphs (m)(2)(i) through
(m)(2)(vi) of this AD means the total flight
cycles or flight hours accumulated since the
last inspection, as applicable.
(i) Airbus Service Bulletin A330–53–3168,
dated September 19, 2007.
(ii) Airbus Service Bulletin A330–53–3168,
Revision 01, dated February 15, 2008.
(iii) Airbus Service Bulletin A330–53–
3168, Revision 02, dated December 21, 2011.
(iv) Airbus Service Bulletin A340–53–
4174, dated September 19, 2007.
(v) Airbus Service Bulletin A340–53–4174,
Revision 01, dated February 15, 2008.
(vi) Airbus Service Bulletin A340–53–
4174, Revision 02, dated December 21, 2011.
Within the compliance times specified in
paragraph (j)(1) or (j)(2) of this AD,
whichever occurs later: Do all applicable
actions, including an eddy current rotating
probe test and an HFEC inspection for cracks,
and modify the airplane upper shell structure
between FR80 and FR86; in accordance with
the Accomplishment Instructions of Airbus
Service Bulletin A330–53–3160, Revision 03,
dated January 6, 2012.
(1) Within the compliance times identified
in paragraph 1.E., ‘‘COMPLIANCE,’’ of
Airbus Service Bulletin A330–53–3160,
Revision 03, dated January 6, 2012, as
applicable for airplane configuration and
utilization since the airplane’s first flight.
(2) Within 12 months after the effective
date of this AD without exceeding the
threshold defined in paragraph 1.E,
‘‘COMPLIANCE,’’ of Airbus Service Bulletin
A330–53–3160, Revision 02, dated March 29,
2010, since the airplane’s first flight.
(n) Credit for Previous Actions
(1) For Model A330–300 and A340–300
airplanes, except Model A340–300 WV 027
airplanes: This paragraph provides credit for
the modification specified in paragraph (i) of
this AD, if those actions were performed
before the effective date of this AD using the
service information identified in paragraph
(n)(1)(i), (n)(1)(ii), (n)(1)(iii), or (n)(1)(iv) of
this AD, as applicable. This service
information is not incorporated by reference
in this AD.
(i) Airbus Service Bulletin A330–53–3159,
dated September 19, 2007.
(ii) Airbus Service Bulletin A330–53–3159,
Revision 01, dated June 15, 2009.
(iii) Airbus Service Bulletin A340–53–
4165, dated September 19, 2007.
(iv) Airbus Service Bulletin A340–53–
4165, Revision 01, dated June 17, 2009.
(2) For Model A330–200 airplanes: This
paragraph provides credit for the inspection
(i) Optional Terminating Action
For Airbus Model A330–300 and A340–
300 airplanes, except Model A340–300 WV
027 airplanes: Modification, which includes
inspections and applicable corrective actions,
in accordance with the Accomplishment
Instructions of Airbus Service Bulletin A330–
53–3159, Revision 02, dated March 29, 2010;
or Airbus Service Bulletin A340–53–4165,
Revision 02, dated March 29, 2010; as
applicable; terminates the repetitive HFEC
inspections required by the introductory text
to paragraph (g) of this AD, except where
Airbus Service Bulletin A330–53–3159,
Revision 02, dated March 29, 2010; or Airbus
Service Bulletin A340–53–4165, Revision 02,
dated March 29, 2010; as applicable;
specifies to contact the manufacturer, repair
using a method approved by the Manager,
International Branch, ANM–116, Transport
Airplane Directorate, FAA; or EASA; or
Airbus’s EASA DOA.
PO 00000
Frm 00009
Fmt 4700
Sfmt 4700
E:\FR\FM\24NOR1.SGM
24NOR1
73096
Federal Register / Vol. 80, No. 226 / Tuesday, November 24, 2015 / Rules and Regulations
and modification required by the
introductory text to paragraph (j) of this AD,
if those actions were performed before the
effective date of this AD using the service
information identified in paragraph (n)(2)(i),
(n)(2)(ii), or (n)(2)(iii) of this AD, as
applicable.
(i) Airbus Service Bulletin A330–53–3160,
dated July 9, 2007, which was incorporated
by reference in AD 2008–22–20, Amendment
39–15717 (73 FR 66747, November 12, 2008).
(ii) Airbus Service Bulletin A330–53–3160,
Revision 01, dated April 28, 2009, which is
not incorporated by reference in this AD.
(iii) Airbus Service Bulletin A330–53–
3160, Revision 02, dated March 29, 2010,
which is not incorporated by reference in this
AD.
(3) For Model A340–300 airplanes, WV 027
only: This paragraph provides credit for the
inspection and modification required by
paragraph (k) of this AD, if those actions
were performed before the effective date of
this AD using Airbus Service Bulletin A340–
53–4172, dated July 10, 2007, which is was
incorporated by reference in AD 2008–22–20,
Amendment 39–15717 (73 FR 66747,
November 12, 2008).
mstockstill on DSK4VPTVN1PROD with RULES
(o) 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-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: As of the
effective date of this AD, 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 EASA; or Airbus’s EASA DOA. If
approved by the DOA, the approval must
include the DOA-authorized signature.
(p) Related Information
(1) Refer to Mandatory Continuing
Airworthiness Information (MCAI) EASA
Airworthiness Directive 2014–0012R1, dated
January 24, 2014, for related information.
This MCAI may be found in the AD docket
on the Internet at https://www.regulations.gov
by searching for and locating Docket No.
FAA–2015–0490.
VerDate Sep<11>2014
23:14 Nov 23, 2015
Jkt 238001
(2) Service information identified in this
AD that is not incorporated by reference is
available at the addresses specified in
paragraphs (q)(3) and (q)(4) of this AD.
DEPARTMENT OF TRANSPORTATION
(q) Material Incorporated by Reference
14 CFR Part 39
(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 December 29, 2015.
(i) Airbus Service Bulletin A330–53–3159,
Revision 02, dated March 29, 2010.
(ii) Airbus Service Bulletin A330–53–3160,
Revision 03, dated January 6, 2012.
(iii) Airbus Service Bulletin A330–53–
3168, Revision 02, dated December 21, 2011.
(iv) Airbus Service Bulletin A340–53–
4165, Revision 02, dated March 29, 2010.
(v) Airbus Service Bulletin A340–53–4172,
Revision 01, dated July 8, 2009.
(vi) Airbus Service Bulletin A340–53–
4174, Revision 02, dated December 21, 2011.
(4) The following service information was
approved for IBR on December 17, 2008 (73
FR 66747, November 12, 2008).
(i) Airbus Service Bulletin A330–53–3168,
Revision 01, dated February 15, 2008.
(ii) Airbus Service Bulletin A340–53–4174,
Revision 01, dated February 15, 2008.
(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.
[Docket No. FAA–2015–0682; Directorate
Identifier 2014–NM–074–AD; Amendment
39–18329; AD 2015–23–12]
Issued in Renton, Washington, on October
30, 2015.
Michael Kaszycki,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. 2015–28886 Filed 11–23–15; 8:45 am]
BILLING CODE 4910–13–P
PO 00000
Frm 00010
Fmt 4700
Sfmt 4700
Federal Aviation Administration
RIN 2120–AA64
Airworthiness Directives; ATR—GIE
´
Avions de Transport Regional
Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
AGENCY:
We are adopting a new
airworthiness directive (AD) for all
ATR—GIE Avions de Transport
´
Regional Model ATR42 and ATR72
airplanes. This AD was prompted by
new occurrences of certain cracked
main landing gear (MLG) rear hinge
pins. This AD requires identifying the
serial number and part number of the
MLG rear hinge pins, and replacing pins
or the MLG if necessary. We are issuing
this AD to detect and correct cracked
rear hinge pins, which could lead to
MLG structural failure, possibly
resulting in collapse of the MLG and
consequent injury to the occupants of
the airplane.
DATES: This AD becomes effective
December 29, 2015. The Director of the
Federal Register approved the
incorporation by reference of certain
publications listed in this AD as of
December 29, 2015.
ADDRESSES: You may examine the AD
docket on the Internet at https://www.
regulations.gov/#!docketDetail;D=FAA2015-0682; 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 ATR—GIE Avions de
´
´
Transport Regional, 1, Allee Pierre
Nadot, 31712 Blagnac Cedex, France;
telephone +33 (0) 5 62 21 62 21; fax +33
(0) 5 62 21 67 18; email
continued.airworthiness@atr.fr; Internet
https://www.aerochain.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. It is also available
on the Internet at https://
www.regulations.gov by searching for
SUMMARY:
E:\FR\FM\24NOR1.SGM
24NOR1
]]>Agencies
[Federal Register Volume 80, Number 226 (Tuesday, November 24, 2015)]
[Rules and Regulations]
[Pages 73092-73096]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2015-28886]
=======================================================================
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2015-0490; Directorate Identifier 2014-NM-018-AD;
Amendment 39-18322; AD 2015-23-06]
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) 2008-22-20 for
certain Airbus Model A330-200, A330-300, and A340-300 series airplanes.
AD 2008-22-20 required repetitive high frequency eddy current (HFEC)
inspections for cracking, repair if necessary, and modification of the
upper shell structure of the fuselage. This new AD shortens certain
compliance times. This AD was prompted by a determination from a
fatigue and damage tolerance evaluation that the compliance times must
be reduced. We are issuing this AD to prevent fatigue cracking of the
upper shell structure of the fuselage, which could result in reduced
structural integrity of the airplane.
DATES: This AD becomes effective December 29, 2015.
The Director of the Federal Register approved the incorporation by
reference of certain publications listed in this AD as of December 29,
2015.
The Director of the Federal Register approved the incorporation by
reference of certain other publications listed in this AD as of
December 17, 2008 (73 FR 66747, November 12, 2008).
ADDRESSES: You may examine the AD docket on the Internet at https://www.regulations.gov/#!docketDetail;
[[Page 73093]]
D=FAA-2015-0490; 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. It is also available on the Internet at https://www.regulations.gov by searching for and locating Docket No. FAA-2015-
0490.
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 2008-22-20, Amendment 39-15717 (73 FR 66747,
November 12, 2008). AD 2008-22-20 applied to certain Airbus Model A330-
200, A330-300, and A340-300 series airplanes. The NPRM published in the
Federal Register on March 17, 2015 (80 FR 13799). The NPRM was prompted
by a determination from a fatigue and damage tolerance evaluation that
the compliance times must be reduced. The NPRM also proposed to shorten
certain compliance times. We are issuing this AD to prevent fatigue
cracking of the upper shell structure of the fuselage, which could
result in reduced structural integrity of the airplane.
The European Aviation Safety Agency (EASA), which is the Technical
Agent for the Member States of the European Union, has issued EASA
Airworthiness Directive 2014-0012R1, dated January 24, 2014 (referred
to after this as the Mandatory Continuing Airworthiness Information, or
``the MCAI''), to correct an unsafe condition for certain Airbus Model
A330-200, A330-300, and A340-300 series airplanes. The MCAI states:
During fatigue tests (EF3) on the A340-600, damage was found in
the longitudinal doubler at the Vertical Tail Plane (VTP) attachment
cut out between Frame (FR) 80 and FR86. This damage occurred between
58,341 and 72,891 simulated flight cycles (FC).
Due to the higher Design Service Goal and different design of
the affected structural area (e.g. doubler thickness) for A330-200/-
300 and A340-300 airplane series, the damage assessment concluded
that these airplanes may be also potentially affected.
This condition, if not detected and corrected, could affect the
structural integrity of the upper shell structure between FR80 and
FR86.
Prompted by these findings, EASA issued AD 2007-0284 [(https://ad.easa.europa.eu/blob/easa_ad_2007_0284_superseded.pdf/AD_2007-0284_1)] to require implementation of an inspection programme of
this structural area using a high frequency eddy current (HFEC)
method and a modification to improve the upper shell structure.
Since that [EASA] AD was issued, in the frame of a new fatigue
and damage tolerance evaluation, taking into account the airplane
utilisation, the inspection threshold and intervals have been
reassessed and the conclusion was that the thresholds and intervals
for inspection, as well as the threshold for modifying the airplane,
must be reduced.
For the reason described above, this [EASA] AD retains the
requirements of EASA AD 2007-0284, which is superseded and
introduces redefined thresholds and intervals.
This [EASA] AD is revised to clarify that, under some
conditions, accomplishment of a repair constitutes terminating
action for the repetitive inspections. One of the outcome of this
clarification is the deletion of paragraph (5) of this [EASA] AD.
You may examine the MCAI in the AD docket on the Internet at https://www.regulations.gov/#!documentDetail;D=FAA-2015-0490-0002.
Comments
We gave the public the opportunity to participate in developing
this AD. The following presents the comments received on the NPRM (80
FR 13799, March 17, 2015) and the FAA's response to each comment.
Support for the NPRM (80 FR 13799, March 17, 2015)
An anonymous commenter agreed with the safety benefit provided by
the NPRM (80 FR 13799, March 17, 2015).
Request for Revise Cost
Delta requested that we revise the NPRM (80 FR 13799, March 17,
2015) to relay the heavy impact of accomplishing Airbus Service
Bulletin A330-53-3160, Revision 03, dated January 6, 2012. Delta
explained that the modification specified in Airbus Service Bulletin
A330-53-3160, Revision 03, dated January 6, 2012, requires removal of
the vertical stabilizer and the aft galley, which can heavily impact
the operation. Delta reasoned that it has consulted with its
maintenance organization and it is estimated to take 400 work-hours
instead of 208 work-hours.
We disagree with the request to revise this AD. We made the cost
estimate based on the information provided in Airbus Service Bulletin
A330-53-3160, Revision 03, dated January 6, 2012. The required work-
hours defined in Airbus Service Bulletin A330-53-3160, Revision 03,
dated January 6, 2012, are based on the direct labor cost to do the
work. The need to remove and reinstall the aft galley depends on the
airplane interior configuration and may differ from operator to
operator. We are unable to determine all possible interior
configurations and thus determine the maximum work-hours which may be
required for any specific configuration. This estimate assumes that the
work will be done by experienced personnel, and may need to be revised
upwards to suit an operator's circumstances. The estimate does not
include the time to prepare, plan, or inspect the work. We have made no
changes to this AD in this regard.
Conclusion
We reviewed the available 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 (80 FR 13799, March 17, 2015) for correcting the unsafe condition;
and
Do not add any additional burden upon the public than was
already proposed in the NPRM (80 FR 13799, March 17, 2015).
Related Service Information Under 1 CFR Part 51
Airbus has issued the following service information.
Airbus Service Bulletin A330-53-3159, Revision 02, dated
March 29, 2010, describes procedures for a modification of the
fuselage, which includes inspections (e.g., eddy current rotating probe
test of fastener holes for cracking, high frequency eddy current (HFEC)
inspections for cracking of the upper shell structure of the fuselage,
and checks of the fastener position for clearance) and applicable
corrective actions (e.g., repair and rework).
Airbus Service Bulletin A330-53-3160, Revision 03, dated
January 6, 2012, describes procedures for applicable actions, including
an eddy current rotating probe test for cracking of the fastener holes
and an HFEC inspection for cracks in the upper shell
[[Page 73094]]
of the fuselage (and including checks of the fastener position for
clearance and applicable corrective actions (e.g., repair and rework)),
and a modification of the airplane upper shell structure of the
fuselage between FR80 and FR86.
Airbus Service Bulletin A330-53-3168, Revision 02, dated
December 21, 2011, describes procedures for a HFEC inspection for
cracking of the upper shell structure of the fuselage between FR80 and
FR86.
Airbus Service Bulletin A340-53-4165, Revision 02, dated
March 29, 2010, describes procedures for a modification of the
fuselage, which includes inspections (e.g., eddy current rotating probe
test of fastener holes for cracking, HFEC inspections for cracking of
the upper shell structure of the fuselage, and checks of the fastener
position for clearance) and applicable corrective actions (e.g., repair
and rework).
Airbus Service Bulletin A340-53-4172, Revision 01, dated
July 8, 2009, describes procedures for inspections (e.g., rototest
inspections of fastener holes for cracking, HFEC inspections for
cracking of the upper shell structure of the fuselage, and checks of
the fastener position for clearance) and modification of the airplane
upper shell structure between FR80 and FR86 (including applicable
corrective actions (e.g., repair and rework).
Airbus Service Bulletin A340-53-4174, Revision 02, dated
December 21, 2011, describes procedures for a HFEC inspection for
cracking of the upper shell structure of the fuselage between FR80 and
FR86.
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 of this
AD.
Costs of Compliance
We estimate that this AD affects 26 airplanes of U.S. registry. We
also estimate that it will take about 208 work-hours per product to
comply with the basic requirements (inspection and modification) of
this AD. The average labor rate is $85 per work-hour. Required parts
will cost about $28,360 per product. Based on these figures, we
estimate the cost of this AD on U.S. operators to be $1,197,040, or
$46,040 per product.
We have received no definitive data that will enable us to provide
cost estimates for the on-condition actions specified in this AD.
According to the manufacturer, some 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.
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-2015-0490; 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)
2008-22-20, Amendment 39-15717 (73 FR 66747, November 12, 2008), and
adding the following new AD:
2015-23-06 Airbus: Amendment 39-18322. Docket No. FAA-2015-0490;
Directorate Identifier 2014-NM-018-AD.
(a) Effective Date
This AD becomes effective December 29, 2015.
(b) Affected ADs
This AD replaces AD 2008-22-20, Amendment 39-15717 (73 FR 66747,
November 12, 2008).
(c) Applicability
This AD applies to Airbus Model A330-201, -202, -203, -223, -
243, -301, -302, -303, -321, -322, -323, -341, -342, and -343
airplanes; and Model A340-311, -312, and -313 airplanes;
certificated in any category; all manufacturer serial numbers on
which Airbus Modification 44205 has been embodied in production,
except those on which Airbus Modification 52974 or 53223 has been
embodied in production.
(d) Subject
Air Transport Association (ATA) of America Code 53, Fuselage.
(e) Reason
This AD was prompted by the results of a fatigue and damage
tolerance evaluation that concluded existing compliance times must
be reduced. We are issuing this AD to prevent fatigue cracking of
the upper shell structure of the fuselage, which could result in
reduced structural integrity of the airplane.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
[[Page 73095]]
(g) Inspection for Airbus Model A330-300 and A340-300 Airplanes, Except
Model A340-300 Weight Variant (WV) 027 Airplanes
For Model A330-300 and A340-300 airplanes, except Model A340-300
WV 027 airplanes: At the applicable time specified in paragraph
(g)(1) or (g)(2) of this AD, do a high frequency eddy current (HFEC)
inspection for cracking of the upper shell structure between frame
(FR) 80 and FR86, in accordance with the Accomplishment Instructions
of Airbus Service Bulletin A330-53-3168, Revision 02, dated December
21, 2011; or Airbus Service Bulletin A340-53-4174, Revision 02,
dated December 21, 2011; as applicable. Repeat the inspection
thereafter at the applicable time specified in paragraph 1.E.,
``COMPLIANCE,'' of Airbus Service Bulletin A330-53-3168, Revision
02, dated December 21, 2011; or Airbus Service Bulletin A340-53-
4174, Revision 02, dated December 21, 2011; as applicable.
(1) For airplanes that, as of the effective date of this AD,
have not been inspected in accordance with Airbus Service Bulletin
A330-53-3168; or Airbus Service Bulletin A340-53-4174; as
applicable: Inspect at the later of the times specified in
paragraphs (g)(1)(i) and (g)(1)(ii) of this AD.
(i) Before reaching the applicable threshold specified in
paragraph 1.E., ``COMPLIANCE,'' of Airbus Service Bulletin A330-53-
3168, Revision 02, dated December 21, 2011; or Airbus Service
Bulletin A340-53-4174, Revision 02, dated December 21, 2011; as
applicable for airplane model, configuration, and utilization, since
the airplane's first flight.
(ii) Within the threshold defined in paragraph 1.E,
``COMPLIANCE,'' of Airbus Service Bulletin A330-53-3168, Revision
01, dated February 15, 2008; or Airbus Service Bulletin A340-53-
4174, Revision 01, dated February 15, 2008; as applicable for
airplane model, configuration, and utilization since the airplane's
first flight; or within 12 months after the effective date of this
AD; whichever occurs first.
(2) For airplanes that, as of the effective date of this AD,
have been inspected in accordance with Airbus Service Bulletin A330-
53-3168; or Airbus Service Bulletin A340-53-4174; as applicable:
Inspect at the later of the times specified in paragraphs (g)(2)(i)
and (g)(2)(ii) of this AD.
(i) Within the applicable interval specified in paragraph 1.E.,
``COMPLIANCE,'' of Airbus Service Bulletin A330-53-3168, Revision
02, dated December 21, 2011; or Airbus Service Bulletin A340-53-
4174, Revision 02, dated December 21, 2011; as applicable; to be
counted from the last inspection.
(ii) Within 12 months after the effective date of this AD
without exceeding the intervals defined in paragraph 1.E,
``COMPLIANCE,'' of Airbus Service Bulletin A330-53-3168, Revision
01, dated February 15, 2008; or Airbus Service Bulletin A340-53-
4174, Revision 01, dated February 15, 2008; as applicable for
airplane model, configuration, and utilization to be counted from
the last inspection.
(h) Corrective Action for Airbus Model A330-300 and A340-300 Airplanes,
Except Model A340-300 WV 027 Airplanes
If any crack is detected during any HFEC inspection required by
the introductory text to paragraph (g) of this AD: 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 Airbus's EASA Design
Organization Approval (DOA). Accomplishment of a repair for a
specific area, as required by this paragraph, is terminating action
for the repetitive HFEC inspections required by the introductory
text to paragraph (g) of this AD, as applicable, for that specific
repaired area only. The need and definition of subsequent repetitive
inspections (if any) for that specific repaired area will be defined
in the applicable repair 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).
(i) Optional Terminating Action
For Airbus Model A330-300 and A340-300 airplanes, except Model
A340-300 WV 027 airplanes: Modification, which includes inspections
and applicable corrective actions, in accordance with the
Accomplishment Instructions of Airbus Service Bulletin A330-53-3159,
Revision 02, dated March 29, 2010; or Airbus Service Bulletin A340-
53-4165, Revision 02, dated March 29, 2010; as applicable;
terminates the repetitive HFEC inspections required by the
introductory text to paragraph (g) of this AD, except where Airbus
Service Bulletin A330-53-3159, Revision 02, dated March 29, 2010; or
Airbus Service Bulletin A340-53-4165, Revision 02, dated March 29,
2010; as applicable; specifies to contact the manufacturer, repair
using a method approved by the Manager, International Branch, ANM-
116, Transport Airplane Directorate, FAA; or EASA; or Airbus's EASA
DOA.
(j) Inspection and Modification for Airbus Model A330-200 Airplanes
Within the compliance times specified in paragraph (j)(1) or
(j)(2) of this AD, whichever occurs later: Do all applicable
actions, including an eddy current rotating probe test and an HFEC
inspection for cracks, and modify the airplane upper shell structure
between FR80 and FR86; in accordance with the Accomplishment
Instructions of Airbus Service Bulletin A330-53-3160, Revision 03,
dated January 6, 2012.
(1) Within the compliance times identified in paragraph 1.E.,
``COMPLIANCE,'' of Airbus Service Bulletin A330-53-3160, Revision
03, dated January 6, 2012, as applicable for airplane configuration
and utilization since the airplane's first flight.
(2) Within 12 months after the effective date of this AD without
exceeding the threshold defined in paragraph 1.E, ``COMPLIANCE,'' of
Airbus Service Bulletin A330-53-3160, Revision 02, dated March 29,
2010, since the airplane's first flight.
(k) Inspection and Modification for Airbus Model A340-300 Airplanes,
Only WV 027
For Model A340-300 airplanes, WV 027 only: Before the
accumulation of 14,200 total flight cycles from the airplane's first
flight, do all applicable inspections and modify the airplane upper
shell structure between FR80 and FR86; in accordance with the
Accomplishment Instructions of Airbus Service Bulletin A340-53-4172,
Revision 01, dated July 8, 2009.
(l) Corrective Action for Airbus Model A330-200 Airplanes; and Model
A340-300 Airplanes, only WV 027
If any crack is detected during the inspection required by the
introductory text to paragraph (j) of this AD, or paragraph (k) of
this AD, before further flight, repair using a method approved by
the Manager, International Branch, ANM-116, Transport Airplane
Directorate, FAA; or EASA; or Airbus's EASA DOA; concurrently with
modification required by paragraph the introductory text to
paragraph (j) of this AD, or paragraph (k) of this AD.
(m) Definition of ``Threshold'' and ``Interval''
(1) For the purposes of this AD, the term ``Threshold,'' as used
in paragraph 1.E., ``COMPLIANCE,'' of the service information
specified in paragraphs (m)(2)(i) through (m)(2)(vi) of this AD
means the total flight cycles or flight hours accumulated since the
airplane's first flight.
(2) For the purposes of this AD, the term ``Interval'' as used
in paragraph 1.E., ``COMPLIANCE,'' of the service information
specified in paragraphs (m)(2)(i) through (m)(2)(vi) of this AD
means the total flight cycles or flight hours accumulated since the
last inspection, as applicable.
(i) Airbus Service Bulletin A330-53-3168, dated September 19,
2007.
(ii) Airbus Service Bulletin A330-53-3168, Revision 01, dated
February 15, 2008.
(iii) Airbus Service Bulletin A330-53-3168, Revision 02, dated
December 21, 2011.
(iv) Airbus Service Bulletin A340-53-4174, dated September 19,
2007.
(v) Airbus Service Bulletin A340-53-4174, Revision 01, dated
February 15, 2008.
(vi) Airbus Service Bulletin A340-53-4174, Revision 02, dated
December 21, 2011.
(n) Credit for Previous Actions
(1) For Model A330-300 and A340-300 airplanes, except Model
A340-300 WV 027 airplanes: This paragraph provides credit for the
modification specified in paragraph (i) of this AD, if those actions
were performed before the effective date of this AD using the
service information identified in paragraph (n)(1)(i), (n)(1)(ii),
(n)(1)(iii), or (n)(1)(iv) of this AD, as applicable. This service
information is not incorporated by reference in this AD.
(i) Airbus Service Bulletin A330-53-3159, dated September 19,
2007.
(ii) Airbus Service Bulletin A330-53-3159, Revision 01, dated
June 15, 2009.
(iii) Airbus Service Bulletin A340-53-4165, dated September 19,
2007.
(iv) Airbus Service Bulletin A340-53-4165, Revision 01, dated
June 17, 2009.
(2) For Model A330-200 airplanes: This paragraph provides credit
for the inspection
[[Page 73096]]
and modification required by the introductory text to paragraph (j)
of this AD, if those actions were performed before the effective
date of this AD using the service information identified in
paragraph (n)(2)(i), (n)(2)(ii), or (n)(2)(iii) of this AD, as
applicable.
(i) Airbus Service Bulletin A330-53-3160, dated July 9, 2007,
which was incorporated by reference in AD 2008-22-20, Amendment 39-
15717 (73 FR 66747, November 12, 2008).
(ii) Airbus Service Bulletin A330-53-3160, Revision 01, dated
April 28, 2009, which is not incorporated by reference in this AD.
(iii) Airbus Service Bulletin A330-53-3160, Revision 02, dated
March 29, 2010, which is not incorporated by reference in this AD.
(3) For Model A340-300 airplanes, WV 027 only: This paragraph
provides credit for the inspection and modification required by
paragraph (k) of this AD, if those actions were performed before the
effective date of this AD using Airbus Service Bulletin A340-53-
4172, dated July 10, 2007, which is was incorporated by reference in
AD 2008-22-20, Amendment 39-15717 (73 FR 66747, November 12, 2008).
(o) 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: As of the effective date of
this AD, 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 EASA; or Airbus's EASA DOA. If
approved by the DOA, the approval must include the DOA-authorized
signature.
(p) Related Information
(1) Refer to Mandatory Continuing Airworthiness Information
(MCAI) EASA Airworthiness Directive 2014-0012R1, dated January 24,
2014, for related information. This MCAI may be found in the AD
docket on the Internet at https://www.regulations.gov by searching
for and locating Docket No. FAA-2015-0490.
(2) Service information identified in this AD that is not
incorporated by reference is available at the addresses specified in
paragraphs (q)(3) and (q)(4) of this AD.
(q) 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
December 29, 2015.
(i) Airbus Service Bulletin A330-53-3159, Revision 02, dated
March 29, 2010.
(ii) Airbus Service Bulletin A330-53-3160, Revision 03, dated
January 6, 2012.
(iii) Airbus Service Bulletin A330-53-3168, Revision 02, dated
December 21, 2011.
(iv) Airbus Service Bulletin A340-53-4165, Revision 02, dated
March 29, 2010.
(v) Airbus Service Bulletin A340-53-4172, Revision 01, dated
July 8, 2009.
(vi) Airbus Service Bulletin A340-53-4174, Revision 02, dated
December 21, 2011.
(4) The following service information was approved for IBR on
December 17, 2008 (73 FR 66747, November 12, 2008).
(i) Airbus Service Bulletin A330-53-3168, Revision 01, dated
February 15, 2008.
(ii) Airbus Service Bulletin A340-53-4174, Revision 01, dated
February 15, 2008.
(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 October 30, 2015.
Michael Kaszycki,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2015-28886 Filed 11-23-15; 8:45 am]
BILLING CODE 4910-13-P
