AD 2016-07-12

We are adopting a new airworthiness directive (AD) for certain Airbus Model A318, A319, A320, and A321 series airplanes. This AD was prompted by reports of cracking of the aft fixed fairing (AFF) of the pylons due to fatigue damage of the structure. This AD requires repetitive inspections for damage and cracking of the AFF of the pylons, and repair if necessary. We are issuing this AD to detect and correct damage and cracking of the AFF of the pylons, which could result in detachment of a pylon and consequent reduced structural integrity of the airplane.

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):

2016-07-12 Airbus: Amendment 39-18457. Docket No. FAA-2015-6537; Directorate Identifier 2014-NM-154-AD.

(a) Effective Date

This AD becomes effective May 10, 2016.

(b) Affected ADs

None.

(c) Applicability

This AD applies to Airbus Model A318-111 and -112, airplanes; Model A319-111, -112, -113, -114, and -115 airplanes; Model A320- 211, -212, and -214 airplanes; and Model A321-111, -112, -211, -212, and -213 airplanes; certificated in any category; all manufacturer serial numbers on which Airbus Modification 33844 has been embodied in production.

(d) Subject

Air Transport Association (ATA) of America Code 54, Nacelles/ pylons.

(e) Reason

This AD was prompted by reports of cracking of the aft fixed fairing (AFF) of the pylons due to fatigue damage of the structure. We are issuing this AD to detect and correct damage and cracking of the AFF of the pylons, which could result in detachment of a pylon and consequent reduced structural integrity of the airplane.

(f) Compliance

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

(g) Repetitive Inspections

At the later of times specified in paragraphs (g)(1) and (g)(2), or (g)(1) and (g)(3) of this AD, as applicable: Do a detailed inspection for damage and cracking of the AFF of the pylons, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320-54-1027, dated April 10, 2014. Repeat the inspection thereafter at

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intervals not to exceed 2,500 flight cycles or 3,750 flight hours, whichever occurs first.
(1) For all airplanes: Before exceeding 5,000 flight cycles or 7,500 flight hours, whichever occurs first since the airplane's first flight.
(2) For airplanes on which the inspection specified in Airbus All Operators Transmission (AOT) A54N002-12 has been done as of the effective date of this AD: Within 2,500 flight cycles or 3,750 flight hours since the most recent accomplishment of maintenance planning data (MPD) Task ZL 371-01, or since doing the most recent inspection specified in Airbus AOT A54N002-12, whichever occurs first.
(3) For airplanes on which the inspection specified in Airbus AOT A54N002-12 has not been done as of the effective date of this AD: Within 750 flight cycles or 1,500 flight hours after the effective date of this AD, whichever occurs first.

(h) Repair

If any crack is found during any inspection required by paragraph (g) of this AD: Before further flight, repair in accordance with theAccomplishment Instructions of Airbus Service Bulletin A320-54-1027, dated April 10, 2014. Accomplishment of this repair does not terminate the repetitive inspections required by paragraph (g) of this AD.

(i) Other FAA AD Provisions

The following provisions also apply to this AD:
(1) Alternative Methods of Compliance (AMOCs): The Manager, International Branch, ANM-116, 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, 1601 Lind 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 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 deviatedfrom 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.

(j) Related Information

Refer to Mandatory Continuing Airworthiness Information (MCAI) EASA Airworthiness Directive 2014-0154, dated July 2, 2014, 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-2015-6537.

(k) 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 A320-54-1027, dated April 10, 2014.
(ii) Reserved.
(3) For Airbus 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 A318, A319, A320, and A321 series airplanes. The NPRM published in the Federal Register on November 30, 2015 (80 FR 74729) (``the NPRM'').
The European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Union, has issued EASA Airworthiness Directive 2014-0154, dated July 2, 2014 (referred to after this as the Mandatory Continuing Airworthiness Information, or ``the MCAI''), to correct an unsafe condition for certain Airbus Model A318, A319, A320, and A321 series airplanes. The MCAI states:

On aeroplanes equipped with post-mod 33844 CFM pylons, several operators have reported cracks on the Aft Fixed Fairing (AFF). After material analysis, it appears that

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the pylon AFF structure, especially on this configuration, is subject to fatigue constraint damage which could lead to pylon AFF cracks.
Further to these findings, Airbus released Alert Operators Transmission (AOT) A54N002-12 which provides instructions to inspect the pylon AFF, applicable only to aeroplanes incorporating Airbus production mod 33844 on CFM pylons. More recently, Airbus issued Service Bulletin (SB) A320-54-1027, superseding AOT A54N002-12.
This condition, if not detected and corrected, could lead to detachment of a pylon AFF from the aeroplane, possibly resulting in injuries to persons on the ground.
For the reasons described above, this [EASA] AD requires repetitive detailed inspections (DET) of the pylon AFF and, depending on findings, accomplishment of applicable corrective action(s).

Since the MCAI was issued, EASA has clarified that the detachment of a pylon AFF from the airplane could result in damage to the airplane; such damage could result in reduced structural integrity of the airplane.
You may examine the MCAI in theAD docket on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2015- 6537.

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.

Explanation of Change to the Proposed Applicability

We have removed Airbus Model A320-215 airplanes from the Applicability statement of this AD; this model is not type certificated in the U.S.

Conclusion

We reviewed the available data and determined that air safety and the public interest require adopting this AD with the change described previously, including 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 51Airbus has issued Service Bulletin A320-54-1027, dated April 10, 2014. This service information describes procedures for inspections for damage and cracking of the AFF of the pylons, and repair 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 69 airplanes of U.S. registry.
We also estimate that it takes about 4 work-hours per product to comply with the basic requirements of this AD. The average labor rate is $85 per work-hour. Based on these figures, we estimate the cost of this AD on U.S. operators to be $23,460, or $340 per product.
We have received no definitive data that would enable us to provide cost estimates for the on-condition actions specified in this AD.

Authority for This Rulemaking

Title 49 of the United States Code specifies the FAA'sauthority 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.