Airworthiness Directives; Airbus Airplanes, 1497-1502 [2015-32256]
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Federal Register / Vol. 81, No. 8 / Wednesday, January 13, 2016 / Rules and Regulations
KS 67209; phone: 316–946–4142; fax: 316–
946–4107; email: paul.devore@faa.gov.
(m) Material Incorporated by Reference
(1) The Director of the Federal Register
approved the incorporation by reference
(IBR) of the service information listed in this
paragraph under 5 U.S.C. 552(a) and 1 CFR
part 51.
(2) You must use this service information
as applicable to do the actions required by
this AD, unless the AD specifies otherwise.
(i) Advanced Aircraft Extinguishers Service
Bulletin TFA10–26–0020, Revision IR, dated
January 12, 2015.
(ii) Reserved.
(3) For service information identified in
this AD, contact Boeing Commercial
Airplanes, Attention: Data & Services
Management, P. O. Box 3707, MC 2H–65,
Seattle, WA 98124–2207; telephone 206–
544–5000, extension 1; fax 206–766–5680;
Internet https://www.myboeingfleet.com.
(4) You may view this service information
at 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
December 28, 2015.
Philip Forde,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. 2016–00004 Filed 1–12–16; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2015–0937; Directorate
Identifier 2014–NM–024–AD; Amendment
39–18348; AD 2015–25–10]
RIN 2120–AA64
Airworthiness Directives; Airbus
Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
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AGENCY:
We are superseding
Airworthiness Directive (AD) 2011–24–
05 for certain Airbus Model A330–201,
–202, –203, –223, –243, –301, –302,
–303, –321, –322, –323, –341, –342, and
–343 airplanes, and Model A340–200
and –300 series airplanes. AD 2011–24–
05 required repetitive inspections for
cracking of the hole(s) of the horizontal
SUMMARY:
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flange of the keel beam, and repair if
necessary. This new AD requires
changing the inspection compliance
times, and, for certain airplanes, adding
a one-time ultrasonic inspection for
cracking at a certain fastener hole. This
new AD also provides optional
terminating action for the repetitive
inspections. This AD was prompted by
a determination that the rototest
inspection and applicable corrective
actions of a certain fastener hole were
inadvertently omitted from the
requirements in AD 2011–24–05. We are
issuing this AD to detect and correct
cracking of the fastener holes, which
could result in rupture of the keel beam,
and consequent reduced structural
integrity of the airplane.
DATES: This AD becomes effective
February 17, 2016.
The Director of the Federal Register
approved the incorporation by reference
of certain publications listed in this AD
as of February 17, 2016.
The Director of the Federal Register
approved the incorporation by reference
of certain other publications listed in
this AD as of January 3, 2012 (76 FR
73496, November 29, 2011).
The Director of the Federal Register
approved the incorporation by reference
of certain other publications listed in
this AD as of September 13, 2007 (72 FR
44731, August 9, 2007).
ADDRESSES: You may examine the AD
docket on the Internet at https://
www.regulations.gov/
#!docketDetail;D=FAA-2015-0937; 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 final rule, 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–
0937.
FOR FURTHER INFORMATION CONTACT:
Vladimir Ulyanov, Aerospace Engineer,
International Branch, ANM–116,
Transport Airplane Directorate, FAA,
1601 Lind Avenue SW., Renton, WA
PO 00000
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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 2011–24–05,
Amendment 39–16869 (76 FR 73496,
November 29, 2011). AD 2011–24–05
applied to certain Airbus Model A330–
201, –202, –203, –223, –243, –301, –302,
–303, –321, –322, –323, –341, –342, and
–343 airplanes; and Model A340–200
and –300 series airplanes. The NPRM
published in the Federal Register on
May 4, 2015 (80 FR 25249).
The European Aviation Safety Agency
(EASA), which is the Technical Agent
for the Member States of the European
Union, has issued EASA Airworthiness
Directive 2014–0010R1, dated May 5,
2014 (referred to after this as the
Mandatory Continuing Airworthiness
Information, or ‘‘the MCAI’’), to correct
an unsafe condition for certain Airbus
Model A330–201, –202, –203, –223,
–243, –301, –302, –303, –321, –322,
–323, –341, –342, and –343 airplanes;
and Model A340–200 and –300 series
airplanes. The MCAI states:
During A330 and A340 aeroplanes fatigue
tests, cracks were detected on the RH [righthand] and LH [left-hand] sides between the
crossing area of the keel beam fitting and the
front spar of the Centre Wing Box (CWB).
This condition, if not detected and
corrected, could lead to keel beam rupture
which would affect the structural integrity of
the area.
Prompted by this potential unsafe
condition, EASA issued AD 2006–0315
[https://ad.easa.europa.eu/blob/easa_ad_
2006_0315.pdf/AD_2006-0315] (later revised
to R1) to require repetitive special detailed
inspections (SDI) [rotating probe inspection
for cracking] on the horizontal flange of the
keel beam in the area of first fastener hole aft
of Frame (FR) 40 in order to maintain the
structural integrity of the aeroplane.
After that [EASA] AD was issued, EASA
issued AD 2010–0024 [which corresponds to
FAA AD 2011–24–05, Amendment 39–16869
(76 FR 73496, November 29, 2011)], retaining
the inspection requirements of EASA AD
2006–0315R1 [https://ad.easa.europa.eu/blob/
easa_ad_2006_0315R1.pdf/AD_20060315R1], which was superseded, extending
the applicability to aeroplanes with Airbus
Mod 49202 embodied, and reducing the
inspection thresholds and intervals.
Since that [EASA] AD [2010–0024] was
issued, a new fatigue and damage tolerance
evaluation has been conducted by Airbus,
which concluded that due to the aeroplane
utilization, the current inspection threshold
and intervals have to be modified.
In addition, it was determined that the
rototest inspection of fastener hole Nr 6,
necessary to ensure that no crack was left
unrepaired at the time of fastener hole cold
working, was inadvertently not included in
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Revisions 01 and 02 of both Airbus Service
Bulletin (SB) A330–57–3098 and A340–57–
4106.
Prompted by these findings, EASA issued
AD 2014–0010 [https://ad.easa.europa.eu/
blob/easa_ad_2014-0010.pdf/AD_2014-0010],
retaining the requirements of EASA AD
2010–0024, which was superseded, and
redefined the inspection thresholds and
intervals [by reducing certain compliance
times], and added a one-time ultrasonic
inspection of fastener hold Nr 6 in the
junction keel beam fitting at FR40 on both LH
and RH side[s].
Following issuance of EASA AD 2014–
0010, it was identified that there was a need
for clarifications [of affected airplanes]
* * *.
The compliance times vary depending
on airplane utilization and
configuration. The earliest compliance
time for the initial rotating probe
inspections is the later of (1) before
10,400 total flight cycles or 67,800 total
flight hours, whichever occurs first; and
(2) within 24 months or 14,590 flight
cycles or 43,790 flight hours, whichever
occurs first. The latest compliance time
for the initial inspections is the later of
(1) before 20,800 total flight cycles or
67,900 total flight hours, whichever
occurs first; and (2) within 24 months or
21,180 flight cycles or 63,560 flight
hours, whichever occurs first. The
compliance times for the repetitive
intervals range between 7,800 flight
cycles or 50,900 flight hours and 10,700
flight cycles or 35,200 flight hours. The
compliance times for the one-time
ultrasonic inspection are the latest of (1)
21,000 flight cycles or 60,600 flight
hours and within 2,400 flight cycles or
24 months; or the latest of (2) 22,100
flight cycles and 64,400 flight hours, or
within 1,300 flight cycles or 24 months.
You may examine the MCAI in the
AD docket on the Internet at https://
www.regulations.gov/
#!documentDetail;D=FAA-2015-09370002.
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Comments
We gave the public the opportunity to
participate in developing this AD. We
received no comments on the NPRM (80
FR 25249, May 4, 2015) or on the
determination of the cost to the public.
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
25249, May 4, 2015) for correcting the
unsafe condition; and
• Do not add any additional burden
upon the public than was already
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proposed in the NPRM (80 FR 25249,
May 4, 2015).
Related Service Information Under 1
CFR Part 51
Airbus has issued the following
service information.
• Airbus Service Bulletin A330–57–
3081, Revision 05, dated November 13,
2012.
• Airbus Service Bulletin A330–57–
3090, Revision 01, dated June 15, 2011.
• Airbus Service Bulletin A330–57–
3098, dated August 30, 2007.
• Airbus Service Bulletin A330–57–
3098, Revision 02, June 15, 2011.
• Airbus Service Bulletin A330–57–
3098, Revision 03, dated September 24,
2012.
• Airbus Service Bulletin A330–57–
3117, dated January 25, 2013.
• Airbus Service Bulletin A340–57–
4089, Revision 05, dated November 13,
2012.
• Airbus Service Bulletin A340–57–
4098, Revision 01, dated June 15, 2011.
• Airbus Service Bulletin A340–57–
4106, dated August 30, 2007.
• Airbus Service Bulletin A340–57–
4106, Revision 02, dated June 15, 2011.
• Airbus Service Bulletin A340–57–
4106, Revision 03, dated September 24,
2012.
• Airbus Service Bulletin A340–57–
4126, dated January 25, 2013.
This service information describes
procedures for inspections for cracking
of the hole(s) of the horizontal flange of
the keel beam, and contacting the
manufacturer for repair instructions.
Additionally, this service information
describes procedures for a one-time
ultrasonic inspection for cracking at
fastener hole ‘‘Nr 6,’’ and provides
optional terminating action for the
repetitive inspections.
This service information is reasonably
available because the interested parties
have access to it through their normal
course of business or by the means
identified in the ADDRESSES section.
Costs of Compliance
We estimate that this AD affects 35
airplanes of U.S. registry.
The actions that were required by AD
2011–24–05, Amendment 39–16869 (76
FR 73496, November 29, 2011), and
retained in this AD take about 41 workhours per product, at an average labor
rate of $85 per work hour. Required
parts cost about $191 per product. Based
on these figures, the estimated cost of
the actions that were required by AD
2011–24–05 is $3,676 per product.
We also estimate that it takes about 23
work-hours per product to comply with
the basic requirements of this AD. The
average labor rate is $85 per work-hour.
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Based on these figures, we estimate the
cost of this AD on U.S. operators to be
$68,425, or $1,955 per product.
We have received no definitive data
that would enable us to provide a cost
estimate for the on-condition actions
specified in this AD.
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-2015-0937; 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
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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:
(f) Compliance
Comply with this AD within the
compliance times specified, unless already
done.
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)
2011–24–05, Amendment 39–16869 (76
FR 73496, November 29, 2011), and
adding the following new AD:
■
2015–25–10 Airbus: Amendment 39–18348.
Docket No. FAA–2015–0937; Directorate
Identifier 2014–NM–024–AD.
(a) Effective Date
This AD becomes effective February 17,
2016.
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(b) Affected ADs
This AD replaces AD 2011–24–05,
Amendment 39–16869 (76 FR 73496,
November 29, 2011).
(c) Applicability
(1) This AD applies to the airplanes
identified in paragraphs (c)(1)(i) and (c)(1)(ii)
of this AD, certificated in any category,
except as provided by paragraph (c)(2) of this
AD.
(i) Airbus Model A330–201, –202, –203,
–223, –243, –301, –302, –303, –321, –322,
–323, –341, –342, and –343 airplanes, all
serial numbers, except those on which
Airbus modification 55306 or 55792 has been
embodied in production.
(ii) Airbus Model A340–211, –212, –213,
–311, –312, and –313 airplanes, all serial
numbers, except those on which Airbus
modification 55306 or 55792 has been
embodied in production.
(2) This AD does not apply to Airbus
Model A340–211, –212, –213, –311, –312,
and –313 airplanes on which the repair
specified in Airbus Repair Drawing
R57115053, R57115051, or R57115047
(installation of titanium doubler on both
sides) has been accomplished. AD 2007–12–
08, Amendment 39–15086 (72 FR 31171,
June 6, 2007), applies to these airplanes.
(d) Subject
Air Transport Association (ATA) of
America Code 57, Wings.
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(e) Reason
This AD was prompted by reports of cracks
on the keel beam fitting and the front spar
of the center wing box. This AD was also
prompted by a determination that the rototest
inspection and applicable corrective actions
of fastener hole ‘‘Nr 6’’ were inadvertently
omitted from the requirements in AD 2011–
24–05, Amendment 39–16869 (76 FR 73496,
November 29, 2011). We are issuing this AD
to detect and correct cracking of the fastener
holes, which could result in rupture of the
keel beam, and consequent reduced
structural integrity of the airplane.
(g) Retained Non-Destructive Test (NDT)
Inspection
This paragraph restates the requirements of
paragraph (n) of AD 2011–24–05,
Amendment 39–16869 (76 FR 73496,
November 29, 2011), with new service
information and revised credit for certain
actions. At the applicable time in paragraph
(g)(1) or (g)(2) of this AD, do an NDT
inspection of the hole(s) of the horizontal
flange of the keel beam located on frame (FR)
40 datum on the right-hand (RH) and/or lefthand (LH) side of the fuselage, in accordance
with the Accomplishment Instructions of the
applicable service information specified in
paragraph (g)(3), (g)(4), (g)(5), or (g)(6) of this
AD. Accomplishing an inspection required
by paragraph (j) of this AD terminates the
inspections required by this paragraph.
(1) For airplanes on which an inspection
required by paragraph (h) of AD 2011–24–05,
Amendment 39–16869 (76 FR 73496,
November 29, 2011), has not been done as of
January 3, 2012 (the effective date of AD
2011–24–05): At the applicable time
specified in paragraph (g)(1)(i) or (g)(1)(ii) of
this AD.
(i) For all airplanes except those identified
in paragraph (g)(1)(ii) of this AD: Within the
‘‘Mandatory Threshold’’ (flight cycles or
flight hours) specified in table 1 of paragraph
1.E.(2) of Airbus Mandatory Service Bulletin
A330–57–3081, including Appendix 01,
Revision 04, dated May 31, 2011; or Airbus
Mandatory Service Bulletin A340–57–4089,
including Appendix 01, Revision 04, dated
May 31, 2011; as applicable; or within 3
months after January 3, 2012 (the effective
date AD 2011–24–05, Amendment 39–16869
(76 FR 73496, November 29, 2011));
whichever occurs later. The compliance
times for configurations 02 through 06
specified in the ‘‘Mandatory Threshold’’
column in table 1 of paragraph 1.E.,
‘‘Compliance,’’ are total flight cycles and
total flight hours.
(ii) For Model A330–201, –202, –203, –223,
–243, –301, –321, –322, –323, –341, –342,
and –343 airplanes, except those on which
Airbus modification 49202 has been
embodied in production, or Airbus Service
Bulletin A330–57–3090 has been embodied
in service; and Model A340–200 and –300
series airplanes, except those on which
Airbus modification 49202 has been
embodied in production or Airbus Service
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1499
Bulletin A340–57–4098 has been embodied
in service, and except Model A340–211,
–212, –213, –311, –312, and –313 airplanes
on which the repair specified in Airbus
Repair Drawing R57115053, R57115051, or
R57115047 has been accomplished: At the
earlier of the times specified in paragraphs
(g)(1)(ii)(A) and (g)(1)(ii)(B) of this AD.
(A) Within the ‘‘Mandatory Threshold’’
(flight cycles or flight hours) specified in
table 1 of paragraph 1.E.(2) of Airbus Service
Bulletin A340–57–4089, including Appendix
01, Revision 02, dated January 24, 2006; or
Airbus Service Bulletin A330–57–3081,
including Appendix 01, Revision 02, dated
January 24, 2006; depending on the
configuration of the aircraft model; or within
3 months after September 13, 2007 (the
effective date of AD 2007–16–02,
Amendment 39–15141 (72 FR 44731, August
9, 2007)), whichever occurs later. The
compliance times for Model A330 post-mod.
41652 and pre-mod. 44360, post-mod. 44360,
and pre-mod. 49202 (as specified in Airbus
Service Bulletin A330–57–3081, including
Appendix 01, Revision 02, dated January 24,
2006); and Model A340 post-mod. 41652,
post-mod. 43500 and pre-mod. 44360, postmod. 44360 and pre-mod. 49202, and weight
variant 027 (as specified in Airbus Service
Bulletin A340–57–4089, including Appendix
01, Revision 02, dated January 24, 2006);
specified in the ‘‘Mandatory Threshold’’
column in table 1 of paragraph 1.E.,
‘‘Compliance,’’ are total flight cycles and
total flight hours.
(B) Within the ‘‘Mandatory Threshold’’
(flight cycles or flight hours) specified in
table 1 of paragraph 1.E.(2) of Airbus
Mandatory Service Bulletin A330–57–3081,
including Appendix 01, Revision 04, dated
May 31, 2011; or Airbus Mandatory Service
Bulletin A340–57–4089, including Appendix
01, Revision 04, dated May 31, 2011; as
applicable; or within 3 months after January
3, 2012 (the effective date of AD 2011–24–05,
Amendment 39–16869 (76 FR 73496,
November 29, 2011)); whichever occurs later.
The compliance times for configurations 02
through 06 specified in the ‘‘Mandatory
Threshold’’ column in table 1 of paragraph
1.E., ‘‘Compliance,’’ are total flight cycles and
total flight hours.
(2) For airplanes on which an inspection
required by paragraph (h) of AD 2011–24–05,
Amendment 39–16869 (76 FR 73496,
November 29, 2011), has been done as of
January 3, 2012 (the effective date of AD
2011–24–05): At the earlier of the times
specified in paragraphs (g)(2)(i) and (g)(2)(ii)
of this AD.
(i) Within the ‘‘Mandatory Intervals’’ given
in table 1 of paragraph 1.E.(2) of Airbus
Service Bulletin A340–57–4089, including
Appendix 01, Revision 02, dated January 24,
2006; or Airbus Service Bulletin A330–57–
3081, including Appendix 01, Revision 02,
dated January 24, 2006; as applicable.
(ii) Within the applicable ‘‘Mandatory
Interval’’ specified in table 1 of Paragraph
1.E.(2) of Airbus Mandatory Service Bulletin
A330–57–3081, including Appendix 01,
Revision 04, dated May 31, 2011; or Airbus
Mandatory Service Bulletin A340–57–4089,
including Appendix 01, Revision 04, dated
May 31, 2011; as applicable; or within 3
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months after January 3, 2012 (the effective
date of AD 2011–24–05, Amendment 39–
16869 (76 FR 73496, November 29, 2011));
whichever occurs later.
(3) Airbus Mandatory Service Bulletin
A330–57–3081, including Appendix 01,
Revision 04, dated May 31, 2011.
(4) Airbus Service Bulletin A330–57–3081,
Revision 05, dated November 13, 2012.
(5) Airbus Mandatory Service Bulletin
A340–57–4089, including Appendix 01,
Revision 04, dated May 31, 2011.
(6) Airbus Service Bulletin A340–57–4089,
Revision 05, dated November 13, 2012.
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(h) Retained Repetitive Inspections
This paragraph restates the requirements of
paragraph (p) of AD 2011–24–05,
Amendment 39–16869 (76 FR 73496,
November 29, 2011). If no cracking is found
during any inspection required by paragraph
(g) of this AD, do the actions required by
paragraphs (h)(1) and (h)(2) of this AD.
(1) Before further flight: Install a new or
oversized fastener, as applicable; seal the
fastener; and do all other applicable actions;
in accordance with the Accomplishment
Instructions of the applicable service
information specified in paragraph (g)(3),
(g)(4), (g)(5), or (g)(6) of this AD.
(2) Repeat the inspection required by
paragraph (g) of this AD thereafter at
intervals not to exceed the ‘‘Mandatory
Intervals’’ specified in Paragraph 1.E.(2) of
Airbus Mandatory Service Bulletin A330–57–
3081, including Appendix 01, Revision 04,
dated May 31, 2011; or Airbus Mandatory
Service Bulletin A340–57–4089, including
Appendix 01, Revision 04, dated May 31,
2011; as applicable.
(i) Retained Corrective Action and Optional
Modification
(1) This paragraph restates the
requirements of paragraph (o) of AD 2011–
24–05, Amendment 39–16869 (76 FR 73496,
November 29, 2011), with revised method of
compliance language. If any cracking is
found during any inspection required by
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).
(2) This paragraph restates the
requirements of paragraph (r) of AD 2011–
24–05, Amendment 39–16869 (76 FR 73496,
November 29, 2011), with new service
information and revised method of
compliance language. Modifying the fastener
installation in the junction keel beam fitting
at FR 40, as specified in paragraph (i)(2)(i),
(i)(2)(ii), (i)(2)(iii), or (i)(2)(iv) of this AD, as
applicable, terminates the requirements of
paragraphs (g) and (h) of this AD; except, for
airplanes on which a crack was detected at
hole 5 before oversizing of the keel beam, in
accordance with step 3.B.(1)(b)3 of the
Accomplishment Instructions of Airbus
Service Bulletin A330–57–3098, dated
August 30, 2007; or Airbus Service Bulletin
A340–57–4106, dated August 30, 2007; or in
accordance with step 3.C.(2)(c) of the
Accomplishment Instructions of Airbus
VerDate Sep<11>2014
15:56 Jan 12, 2016
Jkt 238001
Service Bulletin A330–57–3098, Revision 03,
dated September 24, 2012, or Airbus Service
Bulletin A340–57–4106, Revision 03, dated
September 24, 2012; 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. In case of any
crack finding during any modification
specified in this paragraph: Where the
service information specifies to contact
Airbus, 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.
(i) Modification in accordance with Airbus
Service Bulletin A330–57–3098, dated
August 30, 2007, before January 3, 2012 (the
effective date of AD 2011–24–05,
Amendment 39–16869 (76 FR 73496,
November 29, 2011)).
(ii) Modification in accordance with Airbus
Service Bulletin A330–57–3098, Revision 03,
dated September 24, 2012, before the
effective date of this AD.
(iii) Modification in accordance with
Airbus Service Bulletin A340–57–4106,
dated August 30, 2007, before January 3,
2012 (the effective date of AD 2011–24–05,
Amendment 39–16869 (76 FR 73496,
November 29, 2011)).
(iv) Modification in accordance with
Airbus Service Bulletin A340–57–4106,
Revision 03, dated September 24, 2012,
before the effective date of this AD.
(j) New Repetitive Rotating Probe
Inspections
At the applicable times specified in
paragraphs (j)(1) and (j)(2) of this AD: Do a
rotating probe inspection for cracking of the
fastener hole(s) of the horizontal flange of the
keel beam located on FR 40 datum on the RH
and LH side of the fuselage, as applicable to
airplane type and depending on airplane
configuration and utilization, in accordance
with the Accomplishment Instructions of
Airbus Service Bulletin A330–57–3081,
Revision 05, dated November 13, 2012; or
Airbus Service Bulletin A340–57–4089,
Revision 05, dated November 13, 2012; as
applicable. Repeat the inspection thereafter
at intervals not to exceed the ‘‘Mandatory
Intervals’’ specified in Paragraph 1.E.(2) of
the Accomplishment Timescale of Airbus
Service Bulletin A330–57–3081, Revision 05,
dated November 13, 2012; or Airbus Service
Bulletin A340–57–4089, Revision 05, dated
November 13, 2012; as applicable.
Accomplishing an inspection required by
this paragraph terminates the inspections
required by paragraph (g) of this AD.
(1) For airplanes on which the inspection
required by paragraph (g) of this AD has not
been done as of the effective date of this AD:
Do the inspection before exceeding the
applicable compliance times specified in the
‘‘Mandatory Threshold’’ column of the tables
in paragraph 1.E.(2) of the Accomplishment
Timescale of Airbus Service Bulletin A330–
57–3081, Revision 05, dated November 13,
2012; or Airbus Service Bulletin A340–57–
4089, Revision 05, dated November 13, 2012;
as applicable; or within 12 months after the
effective date of this AD; whichever occurs
later.
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(2) For airplanes on which the inspection
required by paragraph (g) of this AD has been
done as of the effective date of this AD: Do
the inspection within the applicable
compliance times specified in the
‘‘Mandatory Interval’’ column of the tables in
paragraph 1.E.(2) of the Accomplishment
Timescale of Airbus Service Bulletin A330–
57–3081, Revision 05, dated November 13,
2012; or Airbus Service Bulletin A340–57–
4089, Revision 05, dated November 13, 2012;
as applicable; or within 12 months after the
effective date of this AD; whichever occurs
later.
(k) Credit for Previous Actions
(1) This paragraph provides credit for the
initial rotating probe inspection that is part
of the inspections required by paragraphs (g)
and (j)(1) of this AD, if those actions were
performed before the effective date of this AD
using the service information specified in
paragraph (k)(1)(i) or (k)(1)(ii) of this AD.
This service information was incorporated by
reference in AD 2011–24–05, Amendment
39–16869 (76 FR 73496, November 29, 2011).
(i) Airbus A330/A340 200–300 Technical
Disposition F57D03012810, Issue B, dated
August 18, 2003.
(ii) Airbus A330/A340 Technical
Disposition 582.0651/2002, Issue A, dated
October 17, 2002.
(2) This paragraph restates the credit for
the actions specified in paragraph (k) of AD
2011–24–05, Amendment 39–16869 (76 FR
73496, November 29, 2011), if those actions
were performed before January 3, 2012 (the
effective date of AD 2011–24–05), using the
service information specified in paragraphs
(k)(2)(i) through (k)(2)(viii) of this AD.
(i) Airbus Service Bulletin A330–57–3081,
dated October 30, 2003, which is not
incorporated by reference in this AD.
(ii) Airbus Service Bulletin A330–57–3081,
Revision 01, dated May 18, 2004, which is
not incorporated by reference in this AD.
(iii) Airbus Service Bulletin A330–57–
3081, Revision 02, including Appendix 01,
dated January 24, 2006, which was
incorporated by reference in AD 2007–12–08,
Amendment 39–15086 (72 FR 31171, June 6,
2007).
(iv) Airbus Mandatory Service Bulletin
A330–57–3081, Revision 03, dated July 31,
2009, which is not incorporated by reference
in this AD.
(v) Airbus Service Bulletin A340–57–4089,
dated October 30, 2003, which is not
incorporated by reference in this AD.
(vi) Airbus Service Bulletin A340–57–
4089, Revision 01, dated March 2, 2004,
which is not incorporated by reference in this
AD.
(vii) Airbus Service Bulletin A340–57–
4089, Revision 02, including Appendix 01,
dated January 24, 2006, which was
incorporated by reference in AD 2007–12–08,
Amendment 39–15086 (72 FR 31171, June 6,
2007).
(viii) Airbus Mandatory Service Bulletin
A340–57–4089, Revision 03, dated July 31,
2009.
(l) New One-Time Ultrasonic Inspection
For airplanes in Configuration 2, as defined
in the applicable service information
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identified in paragraph (l)(3), (l)(4), (l)(5), or
(l)(6) of this AD, on which the modification
has been done as of the effective date of this
AD in accordance with the Accomplishment
Instructions of the applicable service
information identified in paragraph (l)(3),
(l)(4), (l)(5), or (l)(6) of this AD; as applicable
to airplane type; and on which fastener hole
‘‘Nr 5’’ has been bushed before embodiment
of Airbus Service Bulletin A330–57–3098 or
Airbus Service Bulletin A340–57–4106, as
applicable; or on which a crack has been
found on fastener hole ‘‘Nr 5’’ during
embodiment of Airbus Service Bulletin
A330–57–3098 or Airbus Service Bulletin
A340–57–4106, as applicable: At the
applicable time specified in paragraph (l)(1)
or (l)(2) of this AD, do a one-time ultrasonic
inspection for cracking at fastener hole ‘‘Nr
6’’ in the junction keel beam fitting at FR 40
LH and RH sides, in accordance with the
Accomplishment Instructions of Airbus
Service Bulletin A330–57–3117, dated
January 25, 2013; or Airbus Service Bulletin
A340–57–4126, dated January 25, 2013; as
applicable.
(1) For Model A330–201, –202, –203, –223,
–243, –301, –321, –322, –323, –341, –342,
and –343 airplanes: At the later of the times
specified in paragraphs (l)(1)(i) and (l)(1)(ii)
of this AD.
(i) At the applicable time specified in
paragraph 1.E.(2), of the Accomplishment
Timescale of Airbus Service Bulletin A330–
57–3117, dated January 25, 2013.
(ii) Within 2,400 flight cycles or 24 months
after the effective date of this AD, whichever
occurs first.
(2) For Model A340–211, –212, –213, –311,
–312, and –313 airplanes: At the later of the
times specified in paragraphs (l)(2)(i) and
(l)(2)(ii) of this AD.
(i) At the applicable time specified in
paragraph 1.E.(2) of the Accomplishment
Timescale of Airbus Service Bulletin A340–
57–4126, dated January 25, 2013.
(ii) Within 1,300 flight cycles or 24 months
after the effective date of this AD, whichever
occurs first.
(3) Airbus Service Bulletin A330–57–3098,
excluding Appendix 1, Revision 01, dated
July 31, 2009.
(4) Airbus Service Bulletin A330–57–3098,
Revision 02, dated June 15, 2011.
(5) Airbus Service Bulletin A340–57–4106,
excluding Appendix 1, Revision 01, dated
July 31, 2009.
(6) Airbus Service Bulletin A340–57–4106,
Revision 02, dated June 15, 2011.
(m) Corrective Actions
(1) If no cracking is found during any
inspection required by paragraph (j) of this
AD, before further flight: Install new or
oversized fastener, as applicable; seal the
fastener; and do all other applicable
corrective actions; in accordance with the
Accomplishment Instructions of Airbus
Service Bulletin A330–57–3081, Revision 05,
dated November 13, 2012; or Airbus Service
Bulletin A340–57–4089, Revision 05, dated
November 13, 2012; as applicable. Thereafter,
repeat the inspection required by paragraph
(j) of this AD at intervals not to exceed the
‘‘Mandatory Intervals’’ specified in Paragraph
1.E.(2) of the Accomplishment Timescale of
VerDate Sep<11>2014
15:56 Jan 12, 2016
Jkt 238001
Airbus Service Bulletin A330–57–3081,
Revision 05, dated November 13, 2012; or
Airbus Service Bulletin A340–57–4089,
Revision 05, dated November 13, 2012; as
applicable.
(2) If any crack is found during any
inspection required by paragraph (j) or (l) 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. If approved by the
DOA, the approval must include the DOAauthorized signature.
(n) Airplanes Excluded From Certain
Requirements
(1) For airplanes on which a rototest was
done at fastener hole ‘‘Nr 6’’ before cold
working of the fastener hole during
accomplishment of the actions specified in
the applicable service information identified
in paragraph (n)(1)(i), (n)(1)(ii), (n)(1)(iii), or
(n)(1)(iv) of this AD: The ultrasonic
inspection specified in paragraph (l) of this
AD is not required.
(i) Airbus Service Bulletin A330–57–3098,
excluding Appendix 1, Revision 01, dated
July 31, 2009.
(ii) Airbus Service Bulletin A330–57–3098,
Revision 02, dated June 15, 2011.
(iii) Airbus Service Bulletin A340–57–
4106, excluding Appendix 1, Revision 01,
dated June 31, 2009.
(iv) Airbus Service Bulletin A340–57–
4106, Revision 02, dated June 15, 2011.
(2) For airplanes that have been modified
as of the effective date of this AD in
accordance with the Accomplishment
Instructions of the applicable service
information identified in paragraph (n)(1)(i),
(n)(1)(ii), (n)(1)(iii), or (n)(1)(iv) of this AD:
No action is required by this paragraph,
except as otherwise required by paragraph (l)
of this AD and, provided that if any crack
was found during any modification specified
in this paragraph and the service information
specified to contact Airbus, repair was done
before further flight using a method approved
by the Manager, International Branch, ANM–
116, Transport Airplane Directorate, FAA; or
EASA; or Airbus’s EASA DOA. If approved
by the DOA, the approval must include the
DOA-authorized signature.
(o) Optional Terminating Actions
(1) Modification of an airplane in
accordance with the Accomplishment
Instructions of the applicable service
information identified in paragraph (o)(1)(i),
(o)(1)(ii), (o)(1)(iii), (o)(1)(iv), (o)(1)(v), or
(o)(1)(vi) of this AD; as applicable to airplane
type and depending on airplane
configuration; terminates the requirements of
this AD, provided that in case of any crack
finding during any modification specified in
this paragraph, and the service information
specifies to contact Airbus, repair is done
before further flight, using a method
approved by the Manager, International
Branch, ANM–116, Transport Airplane
Directorate, FAA; or EASA; or Airbus’s EASA
DOA. If approved by the DOA, the approval
must include the DOA-authorized signature.
(i) Airbus Service Bulletin A330–57–3090,
dated March 27, 2006.
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Fmt 4700
Sfmt 4700
1501
(ii) Airbus Service Bulletin A330–57–3090,
Revision 01, dated June 15, 2011.
(iii) Airbus Service Bulletin A330–57–
3098, Revision 03, dated September 24, 2012.
(iv) Airbus Service Bulletin A340–57–
4098, dated March 27, 2006.
(v) Airbus Service Bulletin A340–57–4098,
Revision 01, dated June 15, 2011.
(vi) Airbus Service Bulletin A340–57–
4106, Revision 03, dated September 24, 2012.
(2) Accomplishment of the ultrasonic
inspection required by paragraph (l) of this
AD and all applicable corrective actions
required by paragraph (m) of this AD
terminate the requirements of this AD for
those airplanes.
(p) 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) AMOCs approved previously for AD
2011–24–05, Amendment 39–16869 (76 FR
73496, November 29, 2011), are approved as
AMOCs for the corresponding provisions of
this AD.
(3) 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
EASA; or Airbus’s EASA DOA. If approved
by the DOA, the approval must include the
DOA-authorized signature.
(q) Related Information
(1) Refer to Mandatory Continuing
Airworthiness Information (MCAI) EASA
Airworthiness Directive 2014–0010R1, dated
May 5, 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–
2015–0937–0002.
(2) Service information identified in this
AD that is not incorporated by reference in
this AD is available at the addresses specified
in paragraphs (r)(5) and (r)(6) of this AD.
(r) Material Incorporated by Reference
(1) The Director of the Federal Register
approved the incorporation by reference
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(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 February 17, 2016.
(i) Airbus Service Bulletin A330–57–3081,
Revision 05, dated November 13, 2012.
(ii) Airbus Service Bulletin A330–57–3090,
Revision 01, dated June 15, 2011.
(iii) Airbus Service Bulletin A330–57–
3098, dated August 30, 2007.
(iv) Airbus Service Bulletin A330–57–
3098, Revision 02, June 15, 2011.
(v) Airbus Service Bulletin A330–57–3098,
Revision 03, dated September 24, 2012.
(vi) Airbus Service Bulletin A330–57–
3117, dated January 25, 2013.
(vii) Airbus Service Bulletin A340–57–
4089, Revision 05, dated November 13, 2012.
(viii) Airbus Service Bulletin A340–57–
4098, Revision 01, dated June 15, 2011.
(ix) Airbus Service Bulletin A340–57–
4106, dated August 30, 2007.
(x) Airbus Service Bulletin A340–57–4106,
Revision 02, dated June 15, 2011.
(xi) Airbus Service Bulletin A340–57–
4106, Revision 03, dated September 24, 2012.
(xii) Airbus Service Bulletin A340–57–
4126, dated January 25, 2013.
(4) The following service information was
approved for IBR on January 3, 2012 (76 FR
73496, November 29, 2011).
(i) Airbus Mandatory Service Bulletin
A330–57–3081, including Appendix 01,
Revision 04, dated May 31, 2011.
(ii) Airbus Service Bulletin A330–57–3098,
Revision 01, excluding Appendix 1, dated
July 31, 2009.
(iii) Airbus Mandatory Service Bulletin
A340–57–4089, including Appendix 01,
Revision 04, dated May 31, 2011.
(iv) Airbus Service Bulletin A340–57–
4106, excluding Appendix 1, Revision 01,
dated July 31, 2009.
(5) The following service information was
approved for IBR on September 13, 2007 (72
FR 44731, August 9, 2007).
(i) Airbus Service Bulletin A330–57–3081,
Revision 02, including Appendix 01, dated
January 24, 2006.
(ii) Airbus Service Bulletin A340–57–4089,
Revision 02, including Appendix 01, dated
January 24, 2006.
(6) 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.
(7) 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.
VerDate Sep<11>2014
15:56 Jan 12, 2016
Jkt 238001
Issued in Renton, Washington, on
December 9, 2015.
Michael Kaszycki,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. 2015–32256 Filed 1–12–16; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2015–4213; Directorate
Identifier 2015–CE–022–AD; Amendment
39–18359; AD 2016–01–01]
RIN 2120–AA64
Airworthiness Directives; Piper
Aircraft, Inc. Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule.
AGENCY:
Discussion
We are adopting a new
airworthiness directive (AD) for certain
Piper Aircraft, Inc. Model PA–46–500TP
airplanes. This AD was prompted by a
report of the wing upper skin joints
being manufactured without sealant,
which allows water to enter and stay in
sealed, bonded stringers. This AD
requires inspecting the upper wing
surface for sealant; inspecting the wing
stringers for water intrusion; inspecting
for deformation and corrosion if
evidence of water intrusion exists; and
taking corrective actions as necessary.
We are issuing this AD to correct the
unsafe condition on these products.
DATES: This AD is effective February 17,
2016.
The Director of the Federal Register
approved the incorporation by reference
of a certain publication listed in this AD
as of February 17, 2016.
ADDRESSES: For service information
identified in this AD, contact Piper
Aircraft, Inc., Customer Service, 2926
Piper Drive, Vero Beach, Florida 32960;
telephone: (877) 879–0275; fax: none;
email: customer.service@piper.com;
Internet: www.piper.com. You may view
this referenced service information at
the FAA, Small Airplane Directorate,
901 Locust, Kansas City, Missouri
64106. For information on the
availability of this material at the FAA,
call (816) 329–4148. It is also available
on the Internet at https://
www.regulations.gov by searching for
locating Docket No. FAA–2015–4213.
SUMMARY:
Examining the AD Docket
You may examine the AD docket on
the Internet at https://
PO 00000
Frm 00022
Fmt 4700
Sfmt 4700
www.regulations.gov by searching for
and locating Docket No. FAA–2015–
4213; 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 address for the
Docket Office (telephone: 800–647–
5527) is Document Management
Facility, U.S. Department of
Transportation, Docket Operations, M–
30, West Building Ground Floor, Room
W12–140, 1200 New Jersey Avenue SE.,
Washington, DC 20590.
FOR FURTHER INFORMATION CONTACT:
Gregory ‘‘Keith’’ Noles, Aerospace
Engineer, FAA, Atlanta Aircraft
Certification Office, 1701 Columbia
Avenue, College Park, Georgia 30337;
telephone: (404) 474–5551; fax: (404)
474–5606; email: gregory.noles@faa.gov.
SUPPLEMENTARY INFORMATION:
We issued a notice of proposed
rulemaking (NPRM) to amend 14 CFR
part 39 by adding an AD that would
apply to certain Piper Aircraft, Inc.
Model PA–46–500TP airplanes. The
NPRM published in the Federal
Register on October 19, 2015 (80 FR
63151). The NPRM was prompted by a
report of wing upper skin joints on
Piper Aircraft, Inc. Model PA–46–500TP
airplanes being manufactured without
sealant, which allows water to enter and
stay in sealed, bonded stringers. The
NPRM proposed to require inspecting
the upper wing surface for sealant;
inspecting the wing stringers for water
intrusion; inspecting for deformation
and corrosion if evidence of water
intrusion exists; and taking corrective
actions as necessary. We are issuing this
AD to correct the unsafe condition on
these products.
Related Service Information Under 1
CFR Part 51
We reviewed Piper Aircraft, Inc.
Service Bulletin No. 1262B, dated April
23, 2015. The service bulletin provides
instructions for inspecting the upper
wing surface for sealant and sealing or
resealing (if necessary). This service
bulletin also provides instructions for
inspecting the wing stringers for water
intrusion, and, if water intrusion was
found as a result of the inspection,
inspecting for corrosion or deformation.
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 final rule.
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]]>Agencies
[Federal Register Volume 81, Number 8 (Wednesday, January 13, 2016)]
[Rules and Regulations]
[Pages 1497-1502]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2015-32256]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2015-0937; Directorate Identifier 2014-NM-024-AD;
Amendment 39-18348; AD 2015-25-10]
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) 2011-24-05 for
certain Airbus Model A330-201, -202, -203, -223, -243, -301, -302, -
303, -321, -322, -323, -341, -342, and -343 airplanes, and Model A340-
200 and -300 series airplanes. AD 2011-24-05 required repetitive
inspections for cracking of the hole(s) of the horizontal flange of the
keel beam, and repair if necessary. This new AD requires changing the
inspection compliance times, and, for certain airplanes, adding a one-
time ultrasonic inspection for cracking at a certain fastener hole.
This new AD also provides optional terminating action for the
repetitive inspections. This AD was prompted by a determination that
the rototest inspection and applicable corrective actions of a certain
fastener hole were inadvertently omitted from the requirements in AD
2011-24-05. We are issuing this AD to detect and correct cracking of
the fastener holes, which could result in rupture of the keel beam, and
consequent reduced structural integrity of the airplane.
DATES: This AD becomes effective February 17, 2016.
The Director of the Federal Register approved the incorporation by
reference of certain publications listed in this AD as of February 17,
2016.
The Director of the Federal Register approved the incorporation by
reference of certain other publications listed in this AD as of January
3, 2012 (76 FR 73496, November 29, 2011).
The Director of the Federal Register approved the incorporation by
reference of certain other publications listed in this AD as of
September 13, 2007 (72 FR 44731, August 9, 2007).
ADDRESSES: You may examine the AD docket on the Internet at https://www.regulations.gov/#!docketDetail;D=FAA-2015-0937; 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 final rule, 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-
0937.
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 2011-24-05, Amendment 39-16869 (76 FR 73496,
November 29, 2011). AD 2011-24-05 applied to certain Airbus Model A330-
201, -202, -203, -223, -243, -301, -302, -303, -321, -322, -323, -341,
-342, and -343 airplanes; and Model A340-200 and -300 series airplanes.
The NPRM published in the Federal Register on May 4, 2015 (80 FR
25249).
The European Aviation Safety Agency (EASA), which is the Technical
Agent for the Member States of the European Union, has issued EASA
Airworthiness Directive 2014-0010R1, dated May 5, 2014 (referred to
after this as the Mandatory Continuing Airworthiness Information, or
``the MCAI''), to correct an unsafe condition for certain Airbus Model
A330-201, -202, -203, -223, -243, -301, -302, -303, -321, -322, -323, -
341, -342, and -343 airplanes; and Model A340-200 and -300 series
airplanes. The MCAI states:
During A330 and A340 aeroplanes fatigue tests, cracks were
detected on the RH [right-hand] and LH [left-hand] sides between the
crossing area of the keel beam fitting and the front spar of the
Centre Wing Box (CWB).
This condition, if not detected and corrected, could lead to
keel beam rupture which would affect the structural integrity of the
area.
Prompted by this potential unsafe condition, EASA issued AD
2006-0315 [https://ad.easa.europa.eu/blob/easa_ad_2006_0315.pdf/AD_2006-0315] (later revised to R1) to require repetitive special
detailed inspections (SDI) [rotating probe inspection for cracking]
on the horizontal flange of the keel beam in the area of first
fastener hole aft of Frame (FR) 40 in order to maintain the
structural integrity of the aeroplane.
After that [EASA] AD was issued, EASA issued AD 2010-0024 [which
corresponds to FAA AD 2011-24-05, Amendment 39-16869 (76 FR 73496,
November 29, 2011)], retaining the inspection requirements of EASA
AD 2006-0315R1 [https://ad.easa.europa.eu/blob/easa_ad_2006_0315R1.pdf/AD_2006-0315R1], which was superseded,
extending the applicability to aeroplanes with Airbus Mod 49202
embodied, and reducing the inspection thresholds and intervals.
Since that [EASA] AD [2010-0024] was issued, a new fatigue and
damage tolerance evaluation has been conducted by Airbus, which
concluded that due to the aeroplane utilization, the current
inspection threshold and intervals have to be modified.
In addition, it was determined that the rototest inspection of
fastener hole Nr 6, necessary to ensure that no crack was left
unrepaired at the time of fastener hole cold working, was
inadvertently not included in
[[Page 1498]]
Revisions 01 and 02 of both Airbus Service Bulletin (SB) A330-57-
3098 and A340-57-4106.
Prompted by these findings, EASA issued AD 2014-0010 [https://ad.easa.europa.eu/blob/easa_ad_2014-0010.pdf/AD_2014-0010],
retaining the requirements of EASA AD 2010-0024, which was
superseded, and redefined the inspection thresholds and intervals
[by reducing certain compliance times], and added a one-time
ultrasonic inspection of fastener hold Nr 6 in the junction keel
beam fitting at FR40 on both LH and RH side[s].
Following issuance of EASA AD 2014-0010, it was identified that
there was a need for clarifications [of affected airplanes] * * *.
The compliance times vary depending on airplane utilization and
configuration. The earliest compliance time for the initial rotating
probe inspections is the later of (1) before 10,400 total flight cycles
or 67,800 total flight hours, whichever occurs first; and (2) within 24
months or 14,590 flight cycles or 43,790 flight hours, whichever occurs
first. The latest compliance time for the initial inspections is the
later of (1) before 20,800 total flight cycles or 67,900 total flight
hours, whichever occurs first; and (2) within 24 months or 21,180
flight cycles or 63,560 flight hours, whichever occurs first. The
compliance times for the repetitive intervals range between 7,800
flight cycles or 50,900 flight hours and 10,700 flight cycles or 35,200
flight hours. The compliance times for the one-time ultrasonic
inspection are the latest of (1) 21,000 flight cycles or 60,600 flight
hours and within 2,400 flight cycles or 24 months; or the latest of (2)
22,100 flight cycles and 64,400 flight hours, or within 1,300 flight
cycles or 24 months.
You may examine the MCAI in the AD docket on the Internet at https://www.regulations.gov/#!documentDetail;D=FAA-2015-0937-0002.
Comments
We gave the public the opportunity to participate in developing
this AD. We received no comments on the NPRM (80 FR 25249, May 4, 2015)
or on the determination of the cost to the public.
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 25249, May 4, 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 25249, May 4, 2015).
Related Service Information Under 1 CFR Part 51
Airbus has issued the following service information.
Airbus Service Bulletin A330-57-3081, Revision 05, dated
November 13, 2012.
Airbus Service Bulletin A330-57-3090, Revision 01, dated
June 15, 2011.
Airbus Service Bulletin A330-57-3098, dated August 30,
2007.
Airbus Service Bulletin A330-57-3098, Revision 02, June
15, 2011.
Airbus Service Bulletin A330-57-3098, Revision 03, dated
September 24, 2012.
Airbus Service Bulletin A330-57-3117, dated January 25,
2013.
Airbus Service Bulletin A340-57-4089, Revision 05, dated
November 13, 2012.
Airbus Service Bulletin A340-57-4098, Revision 01, dated
June 15, 2011.
Airbus Service Bulletin A340-57-4106, dated August 30,
2007.
Airbus Service Bulletin A340-57-4106, Revision 02, dated
June 15, 2011.
Airbus Service Bulletin A340-57-4106, Revision 03, dated
September 24, 2012.
Airbus Service Bulletin A340-57-4126, dated January 25,
2013.
This service information describes procedures for inspections for
cracking of the hole(s) of the horizontal flange of the keel beam, and
contacting the manufacturer for repair instructions. Additionally, this
service information describes procedures for a one-time ultrasonic
inspection for cracking at fastener hole ``Nr 6,'' and provides
optional terminating action for the repetitive inspections.
This service information is reasonably available because the
interested parties have access to it through their normal course of
business or by the means identified in the ADDRESSES section.
Costs of Compliance
We estimate that this AD affects 35 airplanes of U.S. registry.
The actions that were required by AD 2011-24-05, Amendment 39-16869
(76 FR 73496, November 29, 2011), and retained in this AD take about 41
work-hours per product, at an average labor rate of $85 per work hour.
Required parts cost about $191 per product. Based on these figures, the
estimated cost of the actions that were required by AD 2011-24-05 is
$3,676 per product.
We also estimate that it takes about 23 work-hours per product to
comply with the basic requirements of this AD. The average labor rate
is $85 per work-hour. Based on these figures, we estimate the cost of
this AD on U.S. operators to be $68,425, or $1,955 per product.
We have received no definitive data that would enable us to provide
a cost estimate for the on-condition actions specified in this AD.
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-2015-0937; 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
[[Page 1499]]
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)
2011-24-05, Amendment 39-16869 (76 FR 73496, November 29, 2011), and
adding the following new AD:
2015-25-10 Airbus: Amendment 39-18348. Docket No. FAA-2015-0937;
Directorate Identifier 2014-NM-024-AD.
(a) Effective Date
This AD becomes effective February 17, 2016.
(b) Affected ADs
This AD replaces AD 2011-24-05, Amendment 39-16869 (76 FR 73496,
November 29, 2011).
(c) Applicability
(1) This AD applies to the airplanes identified in paragraphs
(c)(1)(i) and (c)(1)(ii) of this AD, certificated in any category,
except as provided by paragraph (c)(2) of this AD.
(i) Airbus Model A330-201, -202, -203, -223, -243, -301, -302, -
303, -321, -322, -323, -341, -342, and -343 airplanes, all serial
numbers, except those on which Airbus modification 55306 or 55792
has been embodied in production.
(ii) Airbus Model A340-211, -212, -213, -311, -312, and -313
airplanes, all serial numbers, except those on which Airbus
modification 55306 or 55792 has been embodied in production.
(2) This AD does not apply to Airbus Model A340-211, -212, -213,
-311, -312, and -313 airplanes on which the repair specified in
Airbus Repair Drawing R57115053, R57115051, or R57115047
(installation of titanium doubler on both sides) has been
accomplished. AD 2007-12-08, Amendment 39-15086 (72 FR 31171, June
6, 2007), applies to these airplanes.
(d) Subject
Air Transport Association (ATA) of America Code 57, Wings.
(e) Reason
This AD was prompted by reports of cracks on the keel beam
fitting and the front spar of the center wing box. This AD was also
prompted by a determination that the rototest inspection and
applicable corrective actions of fastener hole ``Nr 6'' were
inadvertently omitted from the requirements in AD 2011-24-05,
Amendment 39-16869 (76 FR 73496, November 29, 2011). We are issuing
this AD to detect and correct cracking of the fastener holes, which
could result in rupture of the keel beam, and consequent reduced
structural integrity of the airplane.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(g) Retained Non-Destructive Test (NDT) Inspection
This paragraph restates the requirements of paragraph (n) of AD
2011-24-05, Amendment 39-16869 (76 FR 73496, November 29, 2011),
with new service information and revised credit for certain actions.
At the applicable time in paragraph (g)(1) or (g)(2) of this AD, do
an NDT inspection of the hole(s) of the horizontal flange of the
keel beam located on frame (FR) 40 datum on the right-hand (RH) and/
or left-hand (LH) side of the fuselage, in accordance with the
Accomplishment Instructions of the applicable service information
specified in paragraph (g)(3), (g)(4), (g)(5), or (g)(6) of this AD.
Accomplishing an inspection required by paragraph (j) of this AD
terminates the inspections required by this paragraph.
(1) For airplanes on which an inspection required by paragraph
(h) of AD 2011-24-05, Amendment 39-16869 (76 FR 73496, November 29,
2011), has not been done as of January 3, 2012 (the effective date
of AD 2011-24-05): At the applicable time specified in paragraph
(g)(1)(i) or (g)(1)(ii) of this AD.
(i) For all airplanes except those identified in paragraph
(g)(1)(ii) of this AD: Within the ``Mandatory Threshold'' (flight
cycles or flight hours) specified in table 1 of paragraph 1.E.(2) of
Airbus Mandatory Service Bulletin A330-57-3081, including Appendix
01, Revision 04, dated May 31, 2011; or Airbus Mandatory Service
Bulletin A340-57-4089, including Appendix 01, Revision 04, dated May
31, 2011; as applicable; or within 3 months after January 3, 2012
(the effective date AD 2011-24-05, Amendment 39-16869 (76 FR 73496,
November 29, 2011)); whichever occurs later. The compliance times
for configurations 02 through 06 specified in the ``Mandatory
Threshold'' column in table 1 of paragraph 1.E., ``Compliance,'' are
total flight cycles and total flight hours.
(ii) For Model A330-201, -202, -203, -223, -243, -301, -321, -
322, -323, -341, -342, and -343 airplanes, except those on which
Airbus modification 49202 has been embodied in production, or Airbus
Service Bulletin A330-57-3090 has been embodied in service; and
Model A340-200 and -300 series airplanes, except those on which
Airbus modification 49202 has been embodied in production or Airbus
Service Bulletin A340-57-4098 has been embodied in service, and
except Model A340-211, -212, -213, -311, -312, and -313 airplanes on
which the repair specified in Airbus Repair Drawing R57115053,
R57115051, or R57115047 has been accomplished: At the earlier of the
times specified in paragraphs (g)(1)(ii)(A) and (g)(1)(ii)(B) of
this AD.
(A) Within the ``Mandatory Threshold'' (flight cycles or flight
hours) specified in table 1 of paragraph 1.E.(2) of Airbus Service
Bulletin A340-57-4089, including Appendix 01, Revision 02, dated
January 24, 2006; or Airbus Service Bulletin A330-57-3081, including
Appendix 01, Revision 02, dated January 24, 2006; depending on the
configuration of the aircraft model; or within 3 months after
September 13, 2007 (the effective date of AD 2007-16-02, Amendment
39-15141 (72 FR 44731, August 9, 2007)), whichever occurs later. The
compliance times for Model A330 post-mod. 41652 and pre-mod. 44360,
post-mod. 44360, and pre-mod. 49202 (as specified in Airbus Service
Bulletin A330-57-3081, including Appendix 01, Revision 02, dated
January 24, 2006); and Model A340 post-mod. 41652, post-mod. 43500
and pre-mod. 44360, post-mod. 44360 and pre-mod. 49202, and weight
variant 027 (as specified in Airbus Service Bulletin A340-57-4089,
including Appendix 01, Revision 02, dated January 24, 2006);
specified in the ``Mandatory Threshold'' column in table 1 of
paragraph 1.E., ``Compliance,'' are total flight cycles and total
flight hours.
(B) Within the ``Mandatory Threshold'' (flight cycles or flight
hours) specified in table 1 of paragraph 1.E.(2) of Airbus Mandatory
Service Bulletin A330-57-3081, including Appendix 01, Revision 04,
dated May 31, 2011; or Airbus Mandatory Service Bulletin A340-57-
4089, including Appendix 01, Revision 04, dated May 31, 2011; as
applicable; or within 3 months after January 3, 2012 (the effective
date of AD 2011-24-05, Amendment 39-16869 (76 FR 73496, November 29,
2011)); whichever occurs later. The compliance times for
configurations 02 through 06 specified in the ``Mandatory
Threshold'' column in table 1 of paragraph 1.E., ``Compliance,'' are
total flight cycles and total flight hours.
(2) For airplanes on which an inspection required by paragraph
(h) of AD 2011-24-05, Amendment 39-16869 (76 FR 73496, November 29,
2011), has been done as of January 3, 2012 (the effective date of AD
2011-24-05): At the earlier of the times specified in paragraphs
(g)(2)(i) and (g)(2)(ii) of this AD.
(i) Within the ``Mandatory Intervals'' given in table 1 of
paragraph 1.E.(2) of Airbus Service Bulletin A340-57-4089, including
Appendix 01, Revision 02, dated January 24, 2006; or Airbus Service
Bulletin A330-57-3081, including Appendix 01, Revision 02, dated
January 24, 2006; as applicable.
(ii) Within the applicable ``Mandatory Interval'' specified in
table 1 of Paragraph 1.E.(2) of Airbus Mandatory Service Bulletin
A330-57-3081, including Appendix 01, Revision 04, dated May 31,
2011; or Airbus Mandatory Service Bulletin A340-57-4089, including
Appendix 01, Revision 04, dated May 31, 2011; as applicable; or
within 3
[[Page 1500]]
months after January 3, 2012 (the effective date of AD 2011-24-05,
Amendment 39-16869 (76 FR 73496, November 29, 2011)); whichever
occurs later.
(3) Airbus Mandatory Service Bulletin A330-57-3081, including
Appendix 01, Revision 04, dated May 31, 2011.
(4) Airbus Service Bulletin A330-57-3081, Revision 05, dated
November 13, 2012.
(5) Airbus Mandatory Service Bulletin A340-57-4089, including
Appendix 01, Revision 04, dated May 31, 2011.
(6) Airbus Service Bulletin A340-57-4089, Revision 05, dated
November 13, 2012.
(h) Retained Repetitive Inspections
This paragraph restates the requirements of paragraph (p) of AD
2011-24-05, Amendment 39-16869 (76 FR 73496, November 29, 2011). If
no cracking is found during any inspection required by paragraph (g)
of this AD, do the actions required by paragraphs (h)(1) and (h)(2)
of this AD.
(1) Before further flight: Install a new or oversized fastener,
as applicable; seal the fastener; and do all other applicable
actions; in accordance with the Accomplishment Instructions of the
applicable service information specified in paragraph (g)(3),
(g)(4), (g)(5), or (g)(6) of this AD.
(2) Repeat the inspection required by paragraph (g) of this AD
thereafter at intervals not to exceed the ``Mandatory Intervals''
specified in Paragraph 1.E.(2) of Airbus Mandatory Service Bulletin
A330-57-3081, including Appendix 01, Revision 04, dated May 31,
2011; or Airbus Mandatory Service Bulletin A340-57-4089, including
Appendix 01, Revision 04, dated May 31, 2011; as applicable.
(i) Retained Corrective Action and Optional Modification
(1) This paragraph restates the requirements of paragraph (o) of
AD 2011-24-05, Amendment 39-16869 (76 FR 73496, November 29, 2011),
with revised method of compliance language. If any cracking is found
during any inspection required by 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).
(2) This paragraph restates the requirements of paragraph (r) of
AD 2011-24-05, Amendment 39-16869 (76 FR 73496, November 29, 2011),
with new service information and revised method of compliance
language. Modifying the fastener installation in the junction keel
beam fitting at FR 40, as specified in paragraph (i)(2)(i),
(i)(2)(ii), (i)(2)(iii), or (i)(2)(iv) of this AD, as applicable,
terminates the requirements of paragraphs (g) and (h) of this AD;
except, for airplanes on which a crack was detected at hole 5 before
oversizing of the keel beam, in accordance with step 3.B.(1)(b)3 of
the Accomplishment Instructions of Airbus Service Bulletin A330-57-
3098, dated August 30, 2007; or Airbus Service Bulletin A340-57-
4106, dated August 30, 2007; or in accordance with step 3.C.(2)(c)
of the Accomplishment Instructions of Airbus Service Bulletin A330-
57-3098, Revision 03, dated September 24, 2012, or Airbus Service
Bulletin A340-57-4106, Revision 03, dated September 24, 2012; 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. In case of any crack finding during
any modification specified in this paragraph: Where the service
information specifies to contact Airbus, 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.
(i) Modification in accordance with Airbus Service Bulletin
A330-57-3098, dated August 30, 2007, before January 3, 2012 (the
effective date of AD 2011-24-05, Amendment 39-16869 (76 FR 73496,
November 29, 2011)).
(ii) Modification in accordance with Airbus Service Bulletin
A330-57-3098, Revision 03, dated September 24, 2012, before the
effective date of this AD.
(iii) Modification in accordance with Airbus Service Bulletin
A340-57-4106, dated August 30, 2007, before January 3, 2012 (the
effective date of AD 2011-24-05, Amendment 39-16869 (76 FR 73496,
November 29, 2011)).
(iv) Modification in accordance with Airbus Service Bulletin
A340-57-4106, Revision 03, dated September 24, 2012, before the
effective date of this AD.
(j) New Repetitive Rotating Probe Inspections
At the applicable times specified in paragraphs (j)(1) and
(j)(2) of this AD: Do a rotating probe inspection for cracking of
the fastener hole(s) of the horizontal flange of the keel beam
located on FR 40 datum on the RH and LH side of the fuselage, as
applicable to airplane type and depending on airplane configuration
and utilization, in accordance with the Accomplishment Instructions
of Airbus Service Bulletin A330-57-3081, Revision 05, dated November
13, 2012; or Airbus Service Bulletin A340-57-4089, Revision 05,
dated November 13, 2012; as applicable. Repeat the inspection
thereafter at intervals not to exceed the ``Mandatory Intervals''
specified in Paragraph 1.E.(2) of the Accomplishment Timescale of
Airbus Service Bulletin A330-57-3081, Revision 05, dated November
13, 2012; or Airbus Service Bulletin A340-57-4089, Revision 05,
dated November 13, 2012; as applicable. Accomplishing an inspection
required by this paragraph terminates the inspections required by
paragraph (g) of this AD.
(1) For airplanes on which the inspection required by paragraph
(g) of this AD has not been done as of the effective date of this
AD: Do the inspection before exceeding the applicable compliance
times specified in the ``Mandatory Threshold'' column of the tables
in paragraph 1.E.(2) of the Accomplishment Timescale of Airbus
Service Bulletin A330-57-3081, Revision 05, dated November 13, 2012;
or Airbus Service Bulletin A340-57-4089, Revision 05, dated November
13, 2012; as applicable; or within 12 months after the effective
date of this AD; whichever occurs later.
(2) For airplanes on which the inspection required by paragraph
(g) of this AD has been done as of the effective date of this AD: Do
the inspection within the applicable compliance times specified in
the ``Mandatory Interval'' column of the tables in paragraph 1.E.(2)
of the Accomplishment Timescale of Airbus Service Bulletin A330-57-
3081, Revision 05, dated November 13, 2012; or Airbus Service
Bulletin A340-57-4089, Revision 05, dated November 13, 2012; as
applicable; or within 12 months after the effective date of this AD;
whichever occurs later.
(k) Credit for Previous Actions
(1) This paragraph provides credit for the initial rotating
probe inspection that is part of the inspections required by
paragraphs (g) and (j)(1) of this AD, if those actions were
performed before the effective date of this AD using the service
information specified in paragraph (k)(1)(i) or (k)(1)(ii) of this
AD. This service information was incorporated by reference in AD
2011-24-05, Amendment 39-16869 (76 FR 73496, November 29, 2011).
(i) Airbus A330/A340 200-300 Technical Disposition F57D03012810,
Issue B, dated August 18, 2003.
(ii) Airbus A330/A340 Technical Disposition 582.0651/2002, Issue
A, dated October 17, 2002.
(2) This paragraph restates the credit for the actions specified
in paragraph (k) of AD 2011-24-05, Amendment 39-16869 (76 FR 73496,
November 29, 2011), if those actions were performed before January
3, 2012 (the effective date of AD 2011-24-05), using the service
information specified in paragraphs (k)(2)(i) through (k)(2)(viii)
of this AD.
(i) Airbus Service Bulletin A330-57-3081, dated October 30,
2003, which is not incorporated by reference in this AD.
(ii) Airbus Service Bulletin A330-57-3081, Revision 01, dated
May 18, 2004, which is not incorporated by reference in this AD.
(iii) Airbus Service Bulletin A330-57-3081, Revision 02,
including Appendix 01, dated January 24, 2006, which was
incorporated by reference in AD 2007-12-08, Amendment 39-15086 (72
FR 31171, June 6, 2007).
(iv) Airbus Mandatory Service Bulletin A330-57-3081, Revision
03, dated July 31, 2009, which is not incorporated by reference in
this AD.
(v) Airbus Service Bulletin A340-57-4089, dated October 30,
2003, which is not incorporated by reference in this AD.
(vi) Airbus Service Bulletin A340-57-4089, Revision 01, dated
March 2, 2004, which is not incorporated by reference in this AD.
(vii) Airbus Service Bulletin A340-57-4089, Revision 02,
including Appendix 01, dated January 24, 2006, which was
incorporated by reference in AD 2007-12-08, Amendment 39-15086 (72
FR 31171, June 6, 2007).
(viii) Airbus Mandatory Service Bulletin A340-57-4089, Revision
03, dated July 31, 2009.
(l) New One-Time Ultrasonic Inspection
For airplanes in Configuration 2, as defined in the applicable
service information
[[Page 1501]]
identified in paragraph (l)(3), (l)(4), (l)(5), or (l)(6) of this
AD, on which the modification has been done as of the effective date
of this AD in accordance with the Accomplishment Instructions of the
applicable service information identified in paragraph (l)(3),
(l)(4), (l)(5), or (l)(6) of this AD; as applicable to airplane
type; and on which fastener hole ``Nr 5'' has been bushed before
embodiment of Airbus Service Bulletin A330-57-3098 or Airbus Service
Bulletin A340-57-4106, as applicable; or on which a crack has been
found on fastener hole ``Nr 5'' during embodiment of Airbus Service
Bulletin A330-57-3098 or Airbus Service Bulletin A340-57-4106, as
applicable: At the applicable time specified in paragraph (l)(1) or
(l)(2) of this AD, do a one-time ultrasonic inspection for cracking
at fastener hole ``Nr 6'' in the junction keel beam fitting at FR 40
LH and RH sides, in accordance with the Accomplishment Instructions
of Airbus Service Bulletin A330-57-3117, dated January 25, 2013; or
Airbus Service Bulletin A340-57-4126, dated January 25, 2013; as
applicable.
(1) For Model A330-201, -202, -203, -223, -243, -301, -321, -
322, -323, -341, -342, and -343 airplanes: At the later of the times
specified in paragraphs (l)(1)(i) and (l)(1)(ii) of this AD.
(i) At the applicable time specified in paragraph 1.E.(2), of
the Accomplishment Timescale of Airbus Service Bulletin A330-57-
3117, dated January 25, 2013.
(ii) Within 2,400 flight cycles or 24 months after the effective
date of this AD, whichever occurs first.
(2) For Model A340-211, -212, -213, -311, -312, and -313
airplanes: At the later of the times specified in paragraphs
(l)(2)(i) and (l)(2)(ii) of this AD.
(i) At the applicable time specified in paragraph 1.E.(2) of the
Accomplishment Timescale of Airbus Service Bulletin A340-57-4126,
dated January 25, 2013.
(ii) Within 1,300 flight cycles or 24 months after the effective
date of this AD, whichever occurs first.
(3) Airbus Service Bulletin A330-57-3098, excluding Appendix 1,
Revision 01, dated July 31, 2009.
(4) Airbus Service Bulletin A330-57-3098, Revision 02, dated
June 15, 2011.
(5) Airbus Service Bulletin A340-57-4106, excluding Appendix 1,
Revision 01, dated July 31, 2009.
(6) Airbus Service Bulletin A340-57-4106, Revision 02, dated
June 15, 2011.
(m) Corrective Actions
(1) If no cracking is found during any inspection required by
paragraph (j) of this AD, before further flight: Install new or
oversized fastener, as applicable; seal the fastener; and do all
other applicable corrective actions; in accordance with the
Accomplishment Instructions of Airbus Service Bulletin A330-57-3081,
Revision 05, dated November 13, 2012; or Airbus Service Bulletin
A340-57-4089, Revision 05, dated November 13, 2012; as applicable.
Thereafter, repeat the inspection required by paragraph (j) of this
AD at intervals not to exceed the ``Mandatory Intervals'' specified
in Paragraph 1.E.(2) of the Accomplishment Timescale of Airbus
Service Bulletin A330-57-3081, Revision 05, dated November 13, 2012;
or Airbus Service Bulletin A340-57-4089, Revision 05, dated November
13, 2012; as applicable.
(2) If any crack is found during any inspection required by
paragraph (j) or (l) 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.
If approved by the DOA, the approval must include the DOA-authorized
signature.
(n) Airplanes Excluded From Certain Requirements
(1) For airplanes on which a rototest was done at fastener hole
``Nr 6'' before cold working of the fastener hole during
accomplishment of the actions specified in the applicable service
information identified in paragraph (n)(1)(i), (n)(1)(ii),
(n)(1)(iii), or (n)(1)(iv) of this AD: The ultrasonic inspection
specified in paragraph (l) of this AD is not required.
(i) Airbus Service Bulletin A330-57-3098, excluding Appendix 1,
Revision 01, dated July 31, 2009.
(ii) Airbus Service Bulletin A330-57-3098, Revision 02, dated
June 15, 2011.
(iii) Airbus Service Bulletin A340-57-4106, excluding Appendix
1, Revision 01, dated June 31, 2009.
(iv) Airbus Service Bulletin A340-57-4106, Revision 02, dated
June 15, 2011.
(2) For airplanes that have been modified as of the effective
date of this AD in accordance with the Accomplishment Instructions
of the applicable service information identified in paragraph
(n)(1)(i), (n)(1)(ii), (n)(1)(iii), or (n)(1)(iv) of this AD: No
action is required by this paragraph, except as otherwise required
by paragraph (l) of this AD and, provided that if any crack was
found during any modification specified in this paragraph and the
service information specified to contact Airbus, repair was done
before further flight using a method approved by the Manager,
International Branch, ANM-116, Transport Airplane Directorate, FAA;
or EASA; or Airbus's EASA DOA. If approved by the DOA, the approval
must include the DOA-authorized signature.
(o) Optional Terminating Actions
(1) Modification of an airplane in accordance with the
Accomplishment Instructions of the applicable service information
identified in paragraph (o)(1)(i), (o)(1)(ii), (o)(1)(iii),
(o)(1)(iv), (o)(1)(v), or (o)(1)(vi) of this AD; as applicable to
airplane type and depending on airplane configuration; terminates
the requirements of this AD, provided that in case of any crack
finding during any modification specified in this paragraph, and the
service information specifies to contact Airbus, repair is done
before further flight, using a method approved by the Manager,
International Branch, ANM-116, Transport Airplane Directorate, FAA;
or EASA; or Airbus's EASA DOA. If approved by the DOA, the approval
must include the DOA-authorized signature.
(i) Airbus Service Bulletin A330-57-3090, dated March 27, 2006.
(ii) Airbus Service Bulletin A330-57-3090, Revision 01, dated
June 15, 2011.
(iii) Airbus Service Bulletin A330-57-3098, Revision 03, dated
September 24, 2012.
(iv) Airbus Service Bulletin A340-57-4098, dated March 27, 2006.
(v) Airbus Service Bulletin A340-57-4098, Revision 01, dated
June 15, 2011.
(vi) Airbus Service Bulletin A340-57-4106, Revision 03, dated
September 24, 2012.
(2) Accomplishment of the ultrasonic inspection required by
paragraph (l) of this AD and all applicable corrective actions
required by paragraph (m) of this AD terminate the requirements of
this AD for those airplanes.
(p) 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) AMOCs approved previously for AD 2011-24-05, Amendment 39-
16869 (76 FR 73496, November 29, 2011), are approved as AMOCs for
the corresponding provisions of this AD.
(3) 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 EASA; or Airbus's EASA DOA. If
approved by the DOA, the approval must include the DOA-authorized
signature.
(q) Related Information
(1) Refer to Mandatory Continuing Airworthiness Information
(MCAI) EASA Airworthiness Directive 2014-0010R1, dated May 5, 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-2015-0937-0002.
(2) Service information identified in this AD that is not
incorporated by reference in this AD is available at the addresses
specified in paragraphs (r)(5) and (r)(6) of this AD.
(r) Material Incorporated by Reference
(1) The Director of the Federal Register approved the
incorporation by reference
[[Page 1502]]
(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
February 17, 2016.
(i) Airbus Service Bulletin A330-57-3081, Revision 05, dated
November 13, 2012.
(ii) Airbus Service Bulletin A330-57-3090, Revision 01, dated
June 15, 2011.
(iii) Airbus Service Bulletin A330-57-3098, dated August 30,
2007.
(iv) Airbus Service Bulletin A330-57-3098, Revision 02, June 15,
2011.
(v) Airbus Service Bulletin A330-57-3098, Revision 03, dated
September 24, 2012.
(vi) Airbus Service Bulletin A330-57-3117, dated January 25,
2013.
(vii) Airbus Service Bulletin A340-57-4089, Revision 05, dated
November 13, 2012.
(viii) Airbus Service Bulletin A340-57-4098, Revision 01, dated
June 15, 2011.
(ix) Airbus Service Bulletin A340-57-4106, dated August 30,
2007.
(x) Airbus Service Bulletin A340-57-4106, Revision 02, dated
June 15, 2011.
(xi) Airbus Service Bulletin A340-57-4106, Revision 03, dated
September 24, 2012.
(xii) Airbus Service Bulletin A340-57-4126, dated January 25,
2013.
(4) The following service information was approved for IBR on
January 3, 2012 (76 FR 73496, November 29, 2011).
(i) Airbus Mandatory Service Bulletin A330-57-3081, including
Appendix 01, Revision 04, dated May 31, 2011.
(ii) Airbus Service Bulletin A330-57-3098, Revision 01,
excluding Appendix 1, dated July 31, 2009.
(iii) Airbus Mandatory Service Bulletin A340-57-4089, including
Appendix 01, Revision 04, dated May 31, 2011.
(iv) Airbus Service Bulletin A340-57-4106, excluding Appendix 1,
Revision 01, dated July 31, 2009.
(5) The following service information was approved for IBR on
September 13, 2007 (72 FR 44731, August 9, 2007).
(i) Airbus Service Bulletin A330-57-3081, Revision 02, including
Appendix 01, dated January 24, 2006.
(ii) Airbus Service Bulletin A340-57-4089, Revision 02,
including Appendix 01, dated January 24, 2006.
(6) 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.
(7) 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 December 9, 2015.
Michael Kaszycki,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2015-32256 Filed 1-12-16; 8:45 am]
BILLING CODE 4910-13-P
