AD 2018-25-06

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.

Final rule.

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

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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: 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.
(2) Contactingthe 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 http://www.regulations.gov 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 airworthiness.A330-A340@airbus.com; internet http://www.airbus.com.
(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: http://www.archives.gov/federal-register/cfr/ibr-locations.html.

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 http://www.regulations.gov 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:
Are consistent with the intent that was proposed in the NPRM for addressing the unsafe condition; and
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:

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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. ----------------------------------------------------------------------------------------------------------------

We estimate the following costs to do any necessary on-condition actions that would be required basedon 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 Order13132. 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.