
[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]


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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.

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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 http://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 http://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 http://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 [http://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 [http://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 [http://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 http://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 http://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 http://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 http://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: http://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


