[Federal Register Volume 80, Number 229 (Monday, November 30, 2015)]
[Proposed Rules]
[Pages 74729-74731]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2015-30218]


-----------------------------------------------------------------------

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2015-6537; Directorate Identifier 2014-NM-154-AD]
RIN 2120-AA64


Airworthiness Directives; Airbus Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

-----------------------------------------------------------------------

SUMMARY: We propose to adopt a new airworthiness directive (AD) for 
certain Airbus Model A318, A319, A320, and A321 series airplanes. This 
proposed AD was prompted by reports of cracking of the aft fixed 
fairing (AFF) of the pylons due to fatigue damage of the structure. 
This proposed AD would require repetitive inspections for damage and 
cracking of the AFF of the pylons, and repair if necessary. We are 
proposing 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: We must receive comments on this proposed AD by January 14, 
2016.

ADDRESSES: You may send comments, using the procedures found in 14 CFR 
11.43 and 11.45, by any of the following methods:
     Federal eRulemaking Portal: Go to http://www.regulations.gov. Follow the instructions for submitting comments.
     Fax: (202) 493-2251.
     Mail: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue SE., Washington, DC 20590.
     Hand Delivery: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue SE., Washington, DC, between 9 a.m. and 5 p.m., Monday 
through Friday, except Federal holidays.
    For service information identified in this proposed AD, contact 
Airbus, Airworthiness Office--EAS, 1 Rond Point Maurice Bellonte, 31707 
Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61 93 44 
51; email [email protected]; 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.

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 proposed AD, the regulatory evaluation, any comments 
received, and other information. The street address for the Docket 
Operations office (telephone (800) 647-5527) is in the ADDRESSES 
section. Comments will be available in the AD docket shortly after 
receipt.

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:

Comments Invited

    We invite you to send any written relevant data, views, or 
arguments about this proposed AD. Send your comments to an address 
listed under the ADDRESSES section. Include ``Docket No. FAA-2015-6537; 
Directorate Identifier 2014-NM-154-AD'' at the beginning of your 
comments. We specifically invite comments on the overall regulatory, 
economic, environmental, and energy aspects of this proposed AD. We 
will consider all comments received by the closing date and may amend 
this proposed AD based on those comments.
    We will post all comments we receive, without change, to http://www.regulations.gov, including any personal information you provide. We 
will also post a report summarizing each substantive verbal contact we 
receive about this proposed AD.

Discussion

    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 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).


[[Page 74730]]


    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 it in Docket No. 
FAA-2015-6537.

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 of this NPRM.

FAA's Determination and Requirements of This Proposed AD

    This product has been approved by the aviation authority of another 
country, and is approved for operation in the United States. Pursuant 
to our bilateral agreement with the State of Design Authority, we have 
been notified of the unsafe condition described in the MCAI and service 
information referenced above. We are proposing this AD because we 
evaluated all pertinent information and determined an unsafe condition 
exists and is likely to exist or develop on other products of the same 
type design.

Explanation of ``RC'' Procedures and Tests in Service Information

    The FAA worked in conjunction with industry, under the 
Airworthiness Directive Implementation Aviation Rulemaking Committee 
(ARC), to enhance the AD system. One enhancement was a new process for 
annotating which procedures and tests in the service information are 
required for compliance with an AD. Differentiating these procedures 
and tests from other tasks in the service information is expected to 
improve an owner's/operator's understanding of crucial AD requirements 
and help provide consistent judgment in AD compliance. The procedures 
and tests identified as Required for Compliance (RC) in any service 
information have a direct effect on detecting, preventing, resolving, 
or eliminating an identified unsafe condition.
    As specified in a NOTE under the Accomplishment Instructions of the 
specified service information, procedures and tests that are identified 
as RC in any service information must be done to comply with the 
proposed AD. However, procedures and 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 alternative method of compliance (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 will require approval of an AMOC.

Costs of Compliance

    We estimate that this proposed AD affects 69 airplanes of U.S. 
registry.
    We also estimate that it would take about 4 work-hours per product 
to comply with the basic requirements of this proposed AD. The average 
labor rate is $85 per work-hour. Based on these figures, we estimate 
the cost of this proposed 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 proposed 
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 proposed AD would not have federalism 
implications under Executive Order 13132. This proposed AD would 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 this proposed 
regulation:
    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.

The Proposed Amendment

    Accordingly, under the authority delegated to me by the 
Administrator, the FAA proposes to amend 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):

Airbus: Docket No. FAA-2015-6537; Directorate Identifier 2014-NM-
154-AD.

(a) Comments Due Date

    We must receive comments by January 14, 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, -214, and -215 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

[[Page 74731]]

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 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 document (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: [email protected]. 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

    (1) 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.
    (2) For service information identified in this AD, contact 
Airbus, Airworthiness Office--EAS, 1 Rond Point Maurice Bellonte, 
31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 
61 93 44 51; email [email protected]; Internet http://www.airbus.com. 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.

     Issued in Renton, Washington, on November 20, 2015.
Jeffrey E. Duven,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2015-30218 Filed 11-27-15; 8:45 am]
 BILLING CODE 4910-13-P