AD 2018-25-06

[Federal Register Volume 83, Number 236 (Monday, December 10, 2018)]
[Rules and Regulations]
[Pages 63399-63402]
From the Federal Register Online via the Government Publishing Office [<a href="http://www.gpo.gov">www.gpo.gov</a>]
[FR Doc No: 2018-26474]



[[Page 63400]]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2018-0800; Product Identifier 2018-NM-107-AD; Amendment 
39-19517; AD 2018-25-06]
RIN 2120-AA64


Airworthiness Directives; Airbus SAS Airplanes

AGENCY: Federal Aviation Administration (FAA), Department of 
Transportation (DOT).

ACTION: Final rule.

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SUMMARY: We are adopting a new airworthiness directive (AD) for all 
Airbus SAS Model A330-223F and Model A330-243F airplanes. This AD was 
prompted by a report of cracking at fastener holes located at a certain 
frame on the lower shell panel junction. This AD requires repetitive 
special detailed inspections (rototest) of certain fastener holes 
located at the lower shell junction of a certain frame on both left-
hand (LH) and right-hand (RH) sides, and applicable related 
investigative and corrective actions. We are issuing this AD to address 
the unsafe condition on these products.

DATES: This AD is effective January 14, 2019.
    The Director of the Federal Register approved the incorporation by 
reference of a certain publication listed in this AD as of January 14, 
2019.

ADDRESSES: For service information identified in this final rule, 
contact Airbus SAS, Airworthiness Office--EAL, Rond-Point Emile 
Dewoitine No: 2, 31700 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#72131b00051d00061a1b1c1701015c334141425f3341464232131b001007015c111d1f"><span class="__cf_email__" data-cfemail="5a3b33282d35282e3233343f2929741b69696a771b696e6a1a3b3328382f2974393537">[email&#160;protected]</span></a>; 
internet <a href="http://www.airbus.com">http://www.airbus.com</a>. 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. 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-
0800.

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-
0800; or in person at Docket Operations between 9 a.m. and 5 p.m., 
Monday through Friday, except Federal holidays. The AD docket contains 
this final rule, the regulatory evaluation, any comments received, and 
other information. The address for Docket Operations (phone: 800-647-
5527) is 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 by adding an AD that would apply to all Airbus SAS Model A330-
223F and Model A330-243F airplanes. The NPRM published in the Federal 
Register on September 21, 2018 (83 FR 47850). The NPRM was prompted by 
a report of cracking at fastener holes located at a certain frame on 
the lower shell panel junction. The NPRM proposed to require repetitive 
special detailed inspections (rototest) of certain fastener holes 
located at the lower shell junction of a certain frame on both LH and 
RH sides, and applicable related investigative and corrective actions.
    We are issuing this AD to address 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 
Airworthiness Directive 2018-0146, dated July 12, 2018 (referred to 
after this as the Mandatory Continuing Airworthiness Information, or 
``the MCAI''), to correct an unsafe condition for all Airbus SAS Model 
A330-223F and Model A330- 243F airplanes. The MCAI states:

    During embodiment of a frame (FR) 40 web repair on an A330 
aeroplane, and during keel beam replacement on an A340 aeroplane, 
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.
    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 [service bulletin] 
A330-53-3215, providing inspection instructions, and EASA issued AD 
2014-0136 and, subsequently, AD 2017-0063 [which corresponds to FAA 
AD 2018-12-08, Amendment 39-19312 (83 FR 33821, July 18, 2018)] to 
require repetitive special detailed inspection (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).
    After those ADs were issued, it has been determined that A330 
Freighter aeroplanes are also affected by this potential unsafe 
condition. Consequently, Airbus published SB A330-53-3215 Revision 
03 to expand the Effectivity of that SB to these aeroplanes.
    For the reason described above, this [EASA] AD requires 
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) [which 
include oversizing, installing fasteners and repair; and 
accomplishment of applicable related investigative actions, which 
include a rototest inspection for cracking after oversizing].

    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-
0800.

Comments

    We gave the public the opportunity to participate in developing 
this final rule. We received no comments on the NPRM or on the 
determination of the cost to the public.

Conclusion

    We reviewed the relevant data and determined that air safety and 
the public interest require adopting this final rule as proposed, 
except for minor editorial changes. We have determined that these minor 
changes:
    <bullet> Are consistent with the intent that was proposed in the 
NPRM for addressing 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 Service Bulletin A330-53-3215, Revision 03, dated 
January 22, 2018. This service information describes procedures for 
repetitive rototest inspections of certain fastener holes, and related 
investigative and corrective actions if necessary. 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 5 airplanes of U.S. registry. We 
estimate the following costs to comply with this AD:

[[Page 63401]]



                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
            Labor cost                Parts cost           Cost per product           Cost on  U.S. operators
----------------------------------------------------------------------------------------------------------------
Up to 42 work-hours x $85 per hour              $0  Up to $3,570.................  Up to $17,850.
 = $3,570.
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    We estimate the following costs to do any necessary on-condition 
actions that would be required based on the results of any required 
actions. We have no way of determining the number of aircraft that 
might need these on-condition actions:

                 Estimated Costs of On-Condition Actions
------------------------------------------------------------------------
                                                               Cost per
                   Labor cost                     Parts cost    product
------------------------------------------------------------------------
46 work-hours x $85 per hour = $3,910...........     $3,690      $7,600
------------------------------------------------------------------------

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 and 
associated appliances to the Director of the System Oversight Division.

Regulatory Findings

    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 adding the following new airworthiness 
directive (AD):

2018-25-06 Airbus SAS: Amendment 39-19517; Docket No. FAA-2018-0800; 
Product Identifier 2018-NM-107-AD.

(a) Effective Date

    This AD is effective January 14, 2019.

(b) Affected ADs

    None.

(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.
    (1) Airbus SAS Model A330-223F airplanes.
    (2) Airbus SAS Model A330-243F airplanes.

(d) Subject

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

(e) Reason

    This AD was prompted by a report of cracking on both left-hand 
(LH) and right-hand (RH) sides on the internal strap, butt strap, 
keel beam fitting, or forward fitting frame (FR) 40 flange. We are 
issuing this AD to address 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 
before exceeding the compliance time ``threshold'' defined in 
paragraph 1.E., ``Compliance,'' of Airbus Service Bulletin A330-53-
3215, Revision 03, dated January 22, 2018 (``A330-53-3215, R3''), 
depending on airplane utilization and configuration and to be 
counted from airplane first flight, and, thereafter, at intervals 
not to exceed the compliance times defined in paragraph 1.E., 
``Compliance,'' of A330-53-3215, R3, depending on airplane 
utilization and configuration.

(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 LH and RH 
sides, in accordance with the Accomplishment Instructions of A330-
53-3215, R3.
    (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, except where A330-53-3215, R3 
specifies to contact Airbus for repair instructions, and specifies 
that action as Required for Compliance (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 SAS'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

[[Page 63402]]

fit as specified in A330-53-3215, R3, as applicable; and A330-53-
3215, R3; 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 SAS'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 SAS's EASA DOA indicates otherwise.

(i) No Reporting Requirement

    Although A330-53-3215, R3, specifies to submit certain 
information to the manufacturer, and specifies 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 paragraph (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 the effective date 
of this AD, 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.

(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#556c78141b18786464637814181a16780710040010060106153334347b323a23"><span class="__cf_email__" data-cfemail="82bbafc3cccfafb3b3b4afc3cfcdc1afd0c7d3d7c7d1d6d1c2e4e3e3ace5edf4">[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: 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 SAS's 
EASA DOA. If approved by the DOA, the approval must include the DOA-
authorized signature.
    (3) Required for Compliance (RC): Except as specified by 
paragraphs (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 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 2018-0146, dated July 12, 2018, 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-2018-0800.
    (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) [Reserved]
    (3) For service information identified in this AD, contact 
Airbus SAS, Airworthiness Office--EAL, Rond-Point Emile Dewoitine 
No: 2, 31700 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#adccc4dfdac2dfd9c5c4c3c8dede83ec9e9e9d80ec9e999dedccc4dfcfd8de83cec2c0"><span class="__cf_email__" data-cfemail="9efff7ece9f1eceaf6f7f0fbededb0dfadadaeb3dfadaaaedefff7ecfcebedb0fdf1f3">[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 November 23, 2018.
John P. Piccola,
Acting Director, System Oversight Division, Aircraft Certification 
Service.
[FR Doc. 2018-26474 Filed 12-7-18; 8:45 am]
 BILLING CODE 4910-13-P