Discussion
We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 by adding an AD that would apply to certain Airbus SAS Model A318 and A319 series airplanes, Model A320-211, -212, -214, -216, -231, -232, and -233 airplanes, and Model A321-111, -112, -131, -211, -212, - 213, -231, and -232 airplanes. The NPRM published in the Federal Register on December 11, 2018 (83 FR 63598). The NPRM was prompted by a report that taperloks used in a certain wing-to-fuselage junction were found to be non-compliant with the applicable specification, resulting in a loss of pre-tension in the fasteners. The NPRM proposed to require repetitive special detailed inspections of the center and outer wing box lower stiffeners and panels at a certain junction on the left- and right-hand sides for any cracking, and repair if necessary, as specified in, and in compliance with, EASA AD 2018-0218, dated October 11, 2018; corrected October 26, 2018 (``EASA AD2018-0218''). The NPRM also proposed, as specified in EASA AD 2018-0218, an optional modification, which would terminate the repetitive inspections.
We are issuing this AD to address the loss of pre-tension in the fasteners, which could affect the structural integrity of the airplane.
The EASA, which is the Technical Agent for the Member States of the European Union, has issued EASA AD 2018-0218 (also referred to as the Mandatory Continuing Airworthiness Information, or ``the MCAI''), to correct an unsafe condition for certain Airbus SAS Model A318 and A319 series airplanes, Model A320-211, -212, -214, -216, -231, -232, and - 233 airplanes, and Model A321-111, -112, -131, -211, -212, -213, -231, and -232 airplanes. The MCAI states:
Taperloks used in the wing-to-fuselage junction at Rib 1 were found to be non-compliant with the applicable specification, resulting in a loss of pre-tension in the fasteners.
This condition, if not detected and corrected, could affect the structural integrity of the aeroplane. To address this potential unsafe condition, Airbus issued SB A320-57-1129 and SB A320-57-1130, later revised twice, providing instructions for repetitive internal inspections of the lower stiffeners and for repetitive external inspections of the lower panels of the center and outer wing box at the level of Rib 1 junction. Consequently, EASA issued AD 2007-0067, later revised [which corresponds to FAA AD 2008-02-15, Amendment 39- 15345 (73 FR 4063, January 24, 2008) (``AD 2008-02-15'')], to require accomplishment of these inspections.
Since EASA AD 2007-0067R1 was issued, new events and the results of studies identified an aging effect on these parts. Prompted by these findings, Airbus revised SB A320-57-1129 (now at Revision 05) and A320-57-1130 (now at Revision 04), expanding the applicability, modifying the area to be inspected and updating the inspection intervals.
For the reasons stated above, this [EASA] AD retains the requirements of EASA AD 2007-0067R1, which is superseded, expands the Applicability, modifies the areas to be inspected and revises the inspection thresholds and intervals.
This [EASA] AD is republished to correct typographical errors in paragraph (2) and in Tables 1 and 3.
You may examine the MCAI in the AD docket on the internet at http://www.regulations.gov by searching for
[[Page 8806]]
and locating Docket No. FAA-2018-1007.
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 uponthe public than was already proposed in the NPRM.
Related IBR Material Under 1 CFR Part 51
EASA AD 2018-0218 describes procedures for repetitive special detailed inspections of the center and outer wing box lower stiffeners and panels at the level of rib 1 junction on the left- and right-hand sides for any cracking, and repair if necessary. EASA AD 2018-0218 also provides procedures for an optional modification, which would terminate the repetitive inspections. This material 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 and it is publicly available through the EASA website.
Costs of Compliance
We estimate that this AD affects 516 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 ---------------------------------------------------------------------------------------------------------------- 51 work-hours x $85 per hour = $4,335........................ $0 $4,335 $2,236,860 ----------------------------------------------------------------------------------------------------------------
We have received no definitive data that would enable us to provide cost estimates for the on-condition actions specified in this AD.
Estimated Costs for Optional Actions ----------------------------------------------------------------------------------------------------------------
Cost per
Labor cost Parts cost product ---------------------------------------------------------------------------------------------------------------- 244 work-hours x $85 per hour = $20,740....................................... $5,120 $25,860 ----------------------------------------------------------------------------------------------------------------
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 likelyto 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.