Document ID: FAA-2015-6537-0002
Agency: faa
Document Type: Rule
Title: Airworthiness Directives: Airbus Airplanes
Posted Date: 2016-04-05T04:00Z

[Federal Register Volume 81, Number 65 (Tuesday, April 5, 2016)]
[Rules and Regulations]
[Pages 19482-19484]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2016-07372]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2015-6537; Directorate Identifier 2014-NM-154-AD; 
Amendment 39-18457; AD 2016-07-12]
RIN 2120-AA64

Airworthiness Directives; Airbus 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 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.

DATES: This AD becomes effective May 10, 2016.
    The Director of the Federal Register approved the incorporation by 
reference of a certain publication listed in this AD as of May 10, 
2016.

ADDRESSES: For service information identified in this final rule, 
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. You may view this referenced 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. It is also available on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2015-
6537.

Examining the AD Docket

    You may examine the AD docket on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2015-
6537; or in person at the Docket Management Facility between 9 a.m. and 
5 p.m., Monday through Friday, except Federal holidays. The AD docket 
contains this AD, the regulatory evaluation, any comments received, and 
other information. The street address for the Docket Operations office 
(telephone 800-647-5527) is Docket Management Facility, U.S. Department 
of Transportation, Docket Operations, M-30, West Building Ground Floor, 
Room W12-140, 1200 New Jersey Avenue SE., Washington, DC.

FOR FURTHER INFORMATION CONTACT: 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.

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 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

[[Page 19483]]

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 the AD 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 51

    Airbus 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'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.

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

[[Page 19484]]

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 the Accomplishment 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 
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.

(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.

    Issued in Renton, Washington, on March 22, 2016.
Michael Kaszycki,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.

[FR Doc. 2016-07372 Filed 4-4-16; 8:45 am]
BILLING CODE 4910-13-P