AD 2017-01-06

We are adopting a new airworthiness directive (AD) for certain Airbus Model A319-115, A319-132, A320-214, A320-232, A321-211, A321- 213, and A321-231 airplanes. This AD was prompted by a report of certain tie rod assemblies installed on the hinged fairing assembly of the main landing gear (MLG) with no cadmium plating on the rod end threads. This AD requires inspection and replacement of certain tie rod assemblies installed on the hinged fairing assembly of the MLG. 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:

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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):

2017-01-06 Airbus: Amendment 39-18773; Docket No. FAA-2016-9110; Directorate Identifier 2015-NM-196-AD.

(a) Effective Date

This AD is effective February 21, 2017.

(b) Affected ADs

None.

(c) Applicability

This AD applies to Airbus Model A319-115, A319-132, A320-214, A320-232, A321-211, A321-213, and A321-231 airplanes, certificated in any category, as identified in Airbus Service Bulletin A320-52- 1167, dated August 6, 2015.

(d) Subject

Air Transport Association (ATA) of America Code 52, Doors.(e) Reason

This AD was prompted by a report of certain tie rod assemblies installed on the hinged fairing assembly of the main landing gear (MLG) with no cadmium plating on the rod end threads. We are issuing this AD to detect and correct the absence of cadmium plating on the rod end threads of the tie rod assemblies. The absence of cadmium plating could lead to galvanic corrosion of the tie rod end threads, resulting in rod end failure, loss of a MLG door, and consequent damage to the airplane.

(f) Compliance

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

(g) Inspection and Corrective Action

Within 80 months after the airplane's first flight, do a detailed inspection of each tie rod assembly having a part number (P/N) D52840212000 or D52840212002 at the MLG hinged fairing for the presence of cadmium plating (gold colored threads), in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320-52-1167,dated August 6, 2015. If during the inspection any tie rod assembly is found that does not have cadmium plating, before further flight, replace the tie rod assembly with a serviceable part having the same part number and cadmium plating, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320-52- 1167, dated August 6, 2015.

(h) 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: Sanjay Ralhan, Aerospace Engineer, International Branch, ANM-116, Transport Airplane Directorate, FAA, 1601Lind Avenue SW., Renton, WA 98057- 3356; telephone 425-227-1405; 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) 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 Branch, ANM-116, Transport Airplane Directorate, FAA; or the 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.
(3) Required for Compliance (RC): If any service information contains procedures or tests that are identified as RC, those procedures and testsmust 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.

(i) Related Information

Refer to Mandatory Continuing Airworthiness Information (MCAI) EASA Airworthiness Directive 2015-0234, dated December 8, 2015, 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-2016-9110.

(j) 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 A320-52-1167, dated August 6, 2015.
(ii) Reserved.
(3) For service information identified in this AD, contact Airbus, Airworthiness Office--EIAS, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61 93 44 51; email account.airworth-eas@airbus.com; Internet http://www.airbus.com.
(4) 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.
(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 certain Airbus Model A319- 115, A319-132, A320-214, A320-232, A321-211, A321-213, and A321-231 airplanes. The NPRM published in the Federal Register on September 19, 2016 (81 FR 64083).
The European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Union, has issued EASA Airworthiness Directive 2015-0234, dated December 8, 2015 (referred to after this as the Mandatory Continuing Airworthiness Information, or ``the MCAI''), to correct an unsafe condition for certain Airbus Model A319-115, A319-132, A320-214, A320-232, A321-211, A321-213, and A321- 231 airplanes. The MCAI states:

A production quality issue was identified concerning tie rod assemblies, having Part Number (P/N) starting with D52840212000 or D52840212002, which are installed on the main landing gear (MLG) hingedfairing assembly. This quality issue affects the cadmium plating surface treatment which

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was inadvertently omitted from the rod end threads of the assembly. The absence of cadmium plating reduces the corrosion protection scheme.
This condition, if not detected and corrected, could lead to galvanic corrosion of the tie rod end threads, possibly resulting in rod end failure, loss of a MLG door, and consequent injury to persons on ground.
To address this unsafe condition, Airbus identified the affected [manufacturer serial number] MSN and issued [service bulletin] SB A320-52-1167 to provide inspection instructions.
For the reason described above, this [EASA] AD requires a one- time inspection of the affected MLG hinged fairing tie rod assemblies [for the presence of cadmium plating], and, depending on findings, replacement of the affected tie rod assembly.

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-2016- 9110.

Comments

We gave the public the opportunity to participate in developing this AD. 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 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 for correcting 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 A320-52-1167, dated August 6, 2015. The service information describes procedures for a detailed inspection for the presence of cadmium plating on tie rod assemblies having certain part numbers, and procedures for replacement of tie rod assemblies with nocadmium plating on the rod end threads. 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 20 airplanes of U.S. registry.
We estimate the following costs to comply with this AD:

Estimated Costs ----------------------------------------------------------------------------------------------------------------
Cost per Cost on U.S.
Action Labor cost Parts cost product operators ---------------------------------------------------------------------------------------------------------------- Inspection......................... 2 work-hours x $85 per hour = $0 $170 $3,400
$170. ----------------------------------------------------------------------------------------------------------------We estimate the following costs to do any necessary replacements that will be required based on the results of the inspection. We have no way of determining the number of airplanes that might need these replacements:

On-Condition Costs ----------------------------------------------------------------------------------------------------------------
Cost per
Action Labor cost Parts cost product ---------------------------------------------------------------------------------------------------------------- Replacement........................... 13 work-hours x $85 per hour = Not available........... $1,105
$1,105. ----------------------------------------------------------------------------------------------------------------

According to the manufacturer, some of the costs of this AD may be covered under warranty, thereby reducing the cost impact on affected individuals. We do not control warrantycoverage for affected individuals. As a result, we have included all available costs in our cost estimate.

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.

List of Subjects in 14 CFR Part 39

Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety.