AD 2018-12-08

[Federal Register Volume 83, Number 138 (Wednesday, July 18, 2018)]
[Rules and Regulations]
[Pages 33821-33825]
From the Federal Register Online via the Government Publishing Office [<a href="http://www.gpo.gov">www.gpo.gov</a>]
[FR Doc No: 2018-13220]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2018-0111; Product Identifier 2017-NM-059-AD; Amendment 
39-19312; AD 2018-12-08]
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) 2017-07-07, 
which applied to certain Airbus Model A330-200, A330-300, A340-200, and 
A340-300 series airplanes. AD 2017-07-07 required repetitive 
inspections of certain fastener holes, and related investigative and 
corrective actions if necessary. This AD retains the requirements of AD 
2017-07-07 and expands the applicability. This AD was prompted by a 
report of cracking at fastener holes located at frame (FR) 40 on the 
lower shell panel junction. We are issuing this AD to address the 
unsafe condition on these products.

DATES: This AD is effective August 22, 2018.
    The Director of the Federal Register approved the incorporation by 
reference of certain publications listed in this AD as of August 22, 
2018.

ADDRESSES: 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: <a href="/cdn-cgi/l/email-protection#70111902071f020418191e1503035e314343405d31434440301119021205035e131f1d"><span class="__cf_email__" data-cfemail="4f2e263d38203d3b2726212a3c3c610e7c7c7f620e7c7b7f0f2e263d2d3a3c612c2022">[email&#160;protected]</span></a>; 
internet: <a href="http://www.airbus.com">http://www.airbus.com</a>. You may view this referenced service 
information at the FAA, Transport Standards Branch, 2200 South 216th 
St., Des Moines, WA. For information on the availability of this 
material at the FAA, call 206-231-3195. It is also available on the 
internet at <a href="http://www.regulations.gov">http://www.regulations.gov</a> by searching for and locating 
Docket No. FAA-2018-0111.

Examining the AD Docket

    You may examine the AD docket on the internet at <a href="http://www.regulations.gov">http://www.regulations.gov</a> by searching for and locating Docket No. FAA-2018-
0111; 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 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 20590.

FOR FURTHER INFORMATION CONTACT: Vladimir Ulyanov, Aerospace Engineer, 
International Section, Transport Standards Branch, FAA, 2200 South 
216th St., Des Moines, WA 98198; telephone and fax: 206-231-3229.

SUPPLEMENTARY INFORMATION:

Discussion

    We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR 
part 39 to supersede AD 2017-07-07, Amendment 39-18845 (82 FR 18547, 
April 20, 2017) (``AD 2017-07-07''). AD 2017-07-07 applied to certain 
Airbus Model A330-200, A330-300, A340-200, and A340-300 series 
airplanes with manufacturer serial numbers (MSN) 0176 through 0915 
inclusive. The NPRM published in the Federal Register on February 20, 
2018 (83 FR 7117). The NPRM was prompted by a report of cracking at 
fastener holes located at frame FR40 on the lower shell panel junction. 
The NPRM proposed to retain the requirements of AD 2017-07-07 and 
expand the applicability. We are issuing this AD to detect and correct 
cracking at FR40 on the lower shell panel junction; such cracking could 
lead to reduced structural integrity of the fuselage.
    The European Aviation Safety Agency (EASA), which is the Technical 
Agent for the Member States of the European Union, has issued EASA AD 
2017-0063, dated April 12, 2017 (referred to after this as the 
Mandatory Continuing Airworthiness Information, or ``the MCAI''), to 
correct an unsafe condition for certain Airbus Model A330-200, A330-
300, and A340-200 series airplanes, and Model A340-312 and -313 
airplanes. The MCAI states:

    During full scale fatigue test of the Frame (FR) 40 to fuselage 
skin panel junction, fatigue damage was found. Corrective actions 
consisted of in-service installation of an internal reinforcing 
strap on the related junction, as currently required by DGAC 
[Direction G[eacute]n[eacute]rale de l'Aviation Civile] France AD 
1999-448-126(B), which refers to Airbus Service Bulletin (SB) A340-
53-4104 Revision 02, and [DGAC] AD 2001-070(B), which refers to 
Airbus SB A330-53-3093 Revision 04; retrofit improvement of internal 
reinforcing strap fatigue life through recommended Airbus SB A330-
53-3145; and

[[Page 33822]]

introducing a design improvement in production through Airbus mod 
44360.
    After those actions were implemented, cracks were found on both 
left-hand (LH) and right-hand (RH) sides on internal strap, butt 
strap, keel beam fitting, or forward fitting FR40 flange. These 
findings were made during embodiment of a FR40 web repair on an A330 
aeroplane, and during keel beam replacement on an A340 aeroplane, 
where the internal strap was removed and a special detailed 
inspection (SDI) was performed on several holes.
    This condition, if not detected and corrected, could affect the 
structural integrity of the centre fuselage of the aeroplane.
    Prompted by these findings, Airbus issued SB A330-53-3215 and SB 
A340-53-4215, providing inspection instructions. Consequently, EASA 
issued AD 2014-0136 [which corresponds to FAA AD 2017-07-07] to 
require repetitive SDI (rototest) of 10 fastener holes located at 
the FR40 lower shell panel junction on both LH and RH sides and, 
depending on findings, accomplishment of applicable corrective 
action(s).
    Since that [EASA] AD was issued, prompted by the results of 
complementary fatigue analyses, it was determined that post-mod 
55792 aeroplanes could be also affected by crack initiation and 
propagation at this area of the fuselage. These analyses 
demonstrated that post-mod 55792 aeroplanes must follow the same 
maintenance program as aeroplanes in post-mod 55306 and pre-mod 
55792 configuration. Consequently, Airbus published SB A330-53-3215 
Revision 02 and SB A340-53-4215 Revision 02 to expand the 
Effectivity accordingly.
    For the reasons described above, this [EASA] AD retains the 
requirements of EASA AD 2014-0136, which is superseded, which now 
also apply to aeroplanes in post-mod 55792 configuration [the 
applicability identifies airplanes in post-mod 44360 configuration].

    AD 2017-07-07 includes Model A340-211 airplanes in its 
applicability. Airbus Model A340-211 airplanes are not identified in 
the applicability of this AD because those airplanes are not affected 
by the identified unsafe condition. All of those airplanes are in the 
pre-Airbus modification 44360 configuration. The MCAI also does not 
include Model A340-211 airplanes in its applicability.
    The compliance time ranges between 20,000 flight cycles or 65,400 
flight hours and 20,800 flight cycles or 68,300 flight hours, depending 
on airplane utilization and configuration. The repetitive inspection 
interval ranges between 14,000 flight cycles or 95,200 flight hours and 
24,600 flight cycles or 98,700 flight hours, depending on airplane 
utilization and configuration. You may examine the MCAI in the AD 
docket on the internet at <a href="http://www.regulations.gov">http://www.regulations.gov</a> by searching for 
and locating Docket No. FAA-2018-0111.

Comments

    We gave the public the opportunity to participate in developing 
this AD. We considered the comment received. Kenneth Ciallella 
supported the NPRM.

Explanation of Changes Made to This AD

    We have revised this AD to refer to Airbus Service Bulletin A330-
53-3215, Revision 03, dated January 22, 2018, as the appropriate source 
of service information for the required actions. This service 
information incorporates minor editorial changes which have no effect 
on airplanes that have incorporated prior revisions of this service 
information. We have revised table 1 to paragraph (g)(1) of this AD and 
paragraphs (g), (g)(1), (g)(2), (h), (h)(1), (h)(2), and (i) of this AD 
to specify Airbus Service Bulletin A330-53-3215, Revision 03, dated 
January 22, 2018, as the appropriate source of service information for 
accomplishing the required actions in those paragraphs.
    We have revised paragraph (j) of this AD to give credit for using 
Airbus Service Bulletin A330-53-3215, Revision 02, dated November 23, 
2016, to accomplish the required actions before the effective date of 
this AD.

Conclusion

    We reviewed the available data, including the comments received, 
and determined that air safety and the public interest require adopting 
this AD as proposed except for the changes described previously and 
minor editorial changes. We have determined that these minor changes:
    <bullet> Are consistent with the intent that was proposed in the 
NPRM for correcting the unsafe condition; and
    <bullet> Do not add any additional burden upon the public than was 
already proposed in the NPRM.

Related Service Information Under 1 CFR Part 51

    Airbus has issued Airbus Service Bulletin A330-53-3215, Revision 
03, dated January 22, 2018 (``A330-53-3215, R3'') and Airbus Service 
Bulletin A340-53-4215, Revision 02, dated November 23, 2016. This 
service information describes procedures for repetitive rototest 
inspections of certain fastener holes, and related investigative and 
corrective actions if necessary. These documents are distinct since 
they apply to different airplane models. 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 99 airplanes of U.S. registry. We 
estimate the following costs to comply with this AD:

                                      Estimated Costs for Required Actions
----------------------------------------------------------------------------------------------------------------
                                                                                    Cost per       Cost on U.S.
                          Labor cost                              Parts cost        product         operators
----------------------------------------------------------------------------------------------------------------
42 work-hours x $85 per hour = $3,570........................              $0           $3,570         $353,430
----------------------------------------------------------------------------------------------------------------

    We estimate the following costs to do any necessary repairs that 
would be required based on the results of the required inspections. We 
have no way of determining the number of aircraft that might need these 
repairs:

                 Estimated Costs of On-Condition Actions
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                                                             Cost per
              Labor cost                   Parts cost        product
------------------------------------------------------------------------
46 work-hours x $85 per hour = $3,910.          $2,358           $6,268
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[[Page 33823]]

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.
    This AD is issued in accordance with authority delegated by the 
Executive Director, Aircraft Certification Service, as authorized by 
FAA Order 8000.51C. In accordance with that order, issuance of ADs is 
normally a function of the Compliance and Airworthiness Division, but 
during this transition period, the Executive Director has delegated the 
authority to issue ADs applicable to transport category airplanes to 
the Director of the System Oversight Division.

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.

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) 
2017-07-07, Amendment 39-18845 (82 FR 18547, April 20, 2017), and 
adding the following new AD:

2018-12-08 Airbus: Amendment 39-19312; Docket No. FAA-2018-0111; 
Product Identifier 2017-NM-059-AD.

(a) Effective Date

    This AD is effective August 22, 2018.

(b) Affected ADs

    This AD replaces AD 2017-07-07, Amendment 39-18845 (82 FR 18547, 
April 20, 2017) (``AD 2017-07-07'').

(c) Applicability

    This AD applies to the airplanes, certificated in any category, 
identified in paragraphs (c)(1) and (c)(2) of this AD, all 
manufacturer serial numbers on which Airbus Modification 44360 has 
been embodied in production.
    (1) Airbus Model A330-201, -202, -203, -223, -243, -301, -302, -
303, -321, -322, -323, -341, -342, and -343 airplanes.
    (2) Airbus Model A340-212, -213, -312, and -313 airplanes.

(d) Subject

    Air Transport Association (ATA) of America Code 53, Fuselage.

(e) Reason

    This AD was prompted by a report of cracking at fastener holes 
located at frame (FR) 40 on the lower shell panel junction. We are 
issuing this AD to detect and correct cracking at FR40 on the lower 
shell panel junction; such cracking could lead to reduced structural 
integrity of the fuselage.

(f) Compliance

    Comply with this AD within the compliance times specified, 
unless already done.

(g) Compliance Times for the Actions Required by Paragraph (h) of This 
AD

    Accomplish the actions required by paragraph (h) of this AD at 
the times specified in paragraphs (g)(1) and (g)(2) of this AD, as 
applicable.
    (1) For airplanes having serial numbers 0176 through 0915 
inclusive: Within the compliance times defined in table 1 to 
paragraph (g)(1) of this AD, and, thereafter, at intervals not to 
exceed the compliance times defined in Airbus Service Bulletin A330-
53-3215, Revision 03, dated January 22, 2018 (``A330-53-3215, R3''); 
or Airbus Service Bulletin A340-53-4215, Revision 02, dated November 
23, 2016 (``A340-53-4215, R2''); as applicable, depending on 
airplane utilization and configuration. As of the effective date of 
this AD, where paragraph 1.E. ``Compliance,'' of A330-53-3215, R3 
specifies weight variant (WV) 050 in the condition column of table 
1, configuration 003, for the purposes of this AD, WV060 and WV080 
are also included.

[[Page 33824]]

[GRAPHIC] [TIFF OMITTED] TR18JY18.000

    (2) For all airplanes except those identified in paragraph 
(g)(1) of this AD: Before exceeding the applicable compliance time 
``threshold'' defined in paragraph 1.E., ``Compliance,'' of A330-53-
3215, R3; or A340-53-4215, R2; as applicable, depending on airplane 
utilization and configuration and to be counted from airplane first 
flight, and, thereafter, at intervals not to exceed the compliance 
times specified in paragraph 1.E., ``Compliance'' of A330-53-3215, 
R3; or A340-53-4215, R2; as applicable, depending on airplane 
utilization and configuration. Where paragraph 1.E. ``Compliance,'' 
of A330-53-3215, R3 specifies weight variant WV050 in the condition 
column of table 1, configuration 003, for the purposes of this AD, 
WV060 and WV080 are also included.

(h) Repetitive Inspections and Related Investigative and Corrective 
Actions

    At the applicable compliance times specified in paragraph (g) of 
this AD: Accomplish a special detailed inspection of the 10 fastener 
holes located at FR40 lower shell panel junction on both left-hand 
and right-hand sides, in accordance with the Accomplishment 
Instructions of A330-53-3215, R3; or A340-53-4215, R2; as 
applicable.
    (1) If, during any inspection required by the introductory text 
of paragraph (h) of this AD, any crack is detected, before further 
flight, accomplish all applicable related investigative and 
corrective actions, in accordance with the Accomplishment 
Instructions of A330-53-3215, R3; or A340-53-4215, R2; as 
applicable, except where A330-53-3215, R3; or A340-53-4215, R2; 
specifies to contact Airbus for repair instructions, and specifies 
that action as ``RC,'' this AD requires repair before further flight 
using a method approved by the Manager, International Section, 
Transport Standards Branch, FAA; or European Aviation Safety Agency 
(EASA); or Airbus's EASA Design Organization Approval (DOA). If 
approved by the DOA, the approval must include the DOA-authorized 
signature.
    (2) If, during any inspection required by the introductory text 
of paragraph (h) of this AD, the diameter of a fastener hole is 
found to be outside the tolerances of the transition fit as 
specified in A330-53-3215, R3; or A340-53-4215, R2; as applicable; 
and A330-53-3215, R3; or A340-53-4215, R2; specifies to contact 
Airbus for repair instructions, and specifies that action as ``RC,'' 
before further flight, repair using a method approved by the 
Manager, International Section, Transport Standards Branch, FAA; or 
EASA; or Airbus's EASA DOA. If approved by the DOA, the approval 
must include the DOA-authorized signature.
    (3) Accomplishment of corrective actions, as required by 
paragraph (h)(1) of this AD, does not constitute terminating action 
for the repetitive inspections required by the introductory text of 
paragraph (h) of this AD.
    (4) Accomplishment of a repair on an airplane, as required by 
paragraph (h)(2) of this AD, does not constitute terminating action 
for the repetitive inspections required by the introductory text of 
paragraph (h) of this AD for that airplane, unless the method 
approved by the Manager, International Section, Transport Standards 
Branch, FAA; or EASA; or Airbus's EASA DOA indicates otherwise.

(i) No Reporting Requirement

    Although A330-53-3215, R3 and A340-53-4215, R2, specify to 
submit certain information to the manufacturer, and specify that 
action as ``RC,'' this AD does not include that requirement.

(j) Credit for Previous Actions

    This paragraph provides credit for the inspections required by 
the introductory text of (h) of this AD and the related 
investigative and corrective actions required by paragraph (h)(1) of 
this AD, if those actions were performed before May 25, 2017 (the 
effective date of AD 2017-07-07), using Airbus Service Bulletin 
A330-53-3215, dated June 21, 2013; or Revision 01, dated April 17, 
2014; or Revision 02, dated November 23, 2016; or Airbus Service 
Bulletin A340-53-4215, dated June 21, 2013; or Revision 01, dated 
April 17, 2014; as applicable.

(k) Other FAA AD Provisions

    The following provisions also apply to this AD:
    (1) Alternative Methods of Compliance (AMOCs): The Manager, 
International Section, Transport Standards Branch, 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 Section, send it to the attention of 
the person identified in paragraph (l)(2) of this AD. Information 
may be emailed to: <a href="/cdn-cgi/l/email-protection#11283c505f5c3c2020273c505c5e523c4354404454424542517770703f767e67"><span class="__cf_email__" data-cfemail="b78e9af6f9fa9a8686819af6faf8f49ae5f2e6e2f2e4e3e4f7d1d6d699d0d8c1">[email&#160;protected]</span></a>. 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.
    (2) Contacting the Manufacturer: As of the effective date of 
this AD, for any requirement in this AD to obtain corrective actions 
from a manufacturer, the action must be accomplished using a method 
approved by the Manager, International Section, Transport Standards 
Branch, FAA; or EASA; or Airbus's EASA DOA. If approved by the DOA, 
the approval must include the DOA-authorized signature.
    (3) Required for Compliance (RC): Except as required by 
paragraphs (g)(1), (g)(2), (h)(1), (h)(2), and (i) of this AD: If 
any service information contains procedures or tests that are 
identified as RC, those procedures and tests must be done to comply 
with this AD; any procedures or tests that are not identified as RC 
are recommended. Those procedures and tests that are not identified 
as RC may be deviated from using accepted methods in accordance with 
the operator's maintenance or inspection program without obtaining 
approval of an AMOC, provided the procedures and tests identified as 
RC can be done and the airplane can be put back in an

[[Page 33825]]

airworthy condition. Any substitutions or changes to procedures or 
tests identified as RC require approval of an AMOC.

(l) Related Information

    (1) Refer to Mandatory Continuing Airworthiness Information 
(MCAI) EASA AD 2017-0063, dated April 12, 2017, for related 
information. This MCAI may be found in the AD docket on the internet 
at <a href="http://www.regulations.gov">http://www.regulations.gov</a> by searching for and locating Docket 
No. FAA-2018-0111.
    (2) For more information about this AD, contact Vladimir 
Ulyanov, Aerospace Engineer, International Section, Transport 
Standards Branch, FAA, 2200 South 216th St., Des Moines, WA 98198; 
telephone and fax: 206-231-3229.
    (3) Service information identified in this AD that is not 
incorporated by reference is available at the addresses specified in 
paragraphs (m)(3) and (m)(4) of this AD.

(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 this AD specifies otherwise.
    (i) Airbus Service Bulletin A330-53-3215, Revision 03, dated 
January 22, 2018.
    (ii) Airbus Service Bulletin A340-53-4215, Revision 02, dated 
November 23, 2016.
    (3) 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: <a href="/cdn-cgi/l/email-protection#9bfaf2e9ecf4e9eff3f2f5fee8e8b5daa8a8abb6daa8afabdbfaf2e9f9eee8b5f8f4f6"><span class="__cf_email__" data-cfemail="6b0a02191c04191f0302050e1818452a58585b462a585f5b2b0a0219091e1845080406">[email&#160;protected]</span></a>; 
internet: <a href="http://www.airbus.com">http://www.airbus.com</a>.
    (4) You may view this service information at the FAA, Transport 
Standards Branch, 2200 South 216th St., Des Moines, WA. For 
information on the availability of this material at the FAA, call 
206-231-3195.
    (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: <a href="http://www.archives.gov/federal-register/cfr/ibr-locations.html">http://www.archives.gov/federal-register/cfr/ibr-locations.html</a>.

    Issued in Des Moines, Washington, on June 6, 2018.
Michael Kaszycki,
Acting Director, System Oversight Division, Aircraft Certification 
Service.
[FR Doc. 2018-13220 Filed 7-17-18; 8:45 am]
 BILLING CODE 4910-13-P