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[Federal Register Volume 81, Number 131 (Friday, July 8, 2016)]
[Rules and Regulations]
[Pages 44496-44499]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2016-15909]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2015-2964; Directorate Identifier 2014-NM-206-AD; 
Amendment 39-18584; AD 2016-14-03]
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 all 
Airbus Model A319, A320, and A321 series airplanes. This AD is intended 
to complete certain mandated programs intended to support the airplane 
reaching its limit of validity (LOV) of the engineering data that 
support the established structural maintenance program. This AD 
requires reinforcing the forward pressure bulkhead at a certain 
stringer on both the left-hand and right-hand sides, and doing related 
investigative and corrective actions if necessary. We are issuing this 
AD to prevent fatigue cracking of the forward pressure bulkhead, which 
could result in reduced structural integrity of the airplane.

DATES: This AD becomes effective August 12, 2016.
    The Director of the Federal Register approved the incorporation by 
reference of a certain publication listed in this AD as of August 12, 
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

[[Page 44497]]

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-2015-2964.

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-
2964; 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 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 20590.

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 all Airbus Model A319, 
A320, and A321 series airplanes. The NPRM published in the Federal 
Register on July 30, 2015 (80 FR 45457) (``the NPRM''). The NPRM was 
intended to complete certain mandated programs intended to support the 
airplane reaching its LOV of the engineering data that support the 
established structural maintenance program. The NPRM proposed to 
require reinforcing the forward pressure bulkhead at a certain stringer 
on both the left-hand and right-hand sides, and doing related 
investigative and corrective actions if necessary. We are issuing this 
AD to prevent fatigue cracking of the forward pressure bulkhead, which 
could result in reduced structural integrity of the airplane.
    The European Aviation Safety Agency (EASA), which is the Technical 
Agent for the Member States of the European Union, has issued EASA 
Airworthiness Directive 2014-0209, dated September 19, 2014 (referred 
to after this as the Mandatory Continuing Airworthiness Information, or 
``the MCAI''), to correct an unsafe condition on all Model A319, A320, 
and Model A321 series airplanes. The MCAI states:

    During the A320 fatigue test campaign for Extended Service Goal 
(ESG), it was determined that fatigue damage could develop on the 
forward pressure bulkhead at Frame (FR) 35 on left hand (LH) side 
and right hand (RH) side.
    This condition, if not detected and corrected, could affect the 
structural integrity of the aeroplane.
    To address this potential unsafe condition, a reinforcement 
modification was developed, which has been published through Airbus 
Service Bulletin (SB) A320-53-1268 for in-service application to 
allow aeroplanes to operate up to the new ESG limit.
    For the reasons described above, this [EASA] AD requires 
reinforcement of the centre fuselage forward pressure bulkhead at 
FR35.

    The forward pressure bulkhead reinforcement includes related 
investigative actions of measuring the diameters of certain fastener 
holes, and if they are not oversized, doing a rotating probe inspection 
for cracking of the fastener holes.
    Required corrective actions include cold expanding crack-free holes 
or repairing oversize or cracked holes by using a method approved by 
the FAA, EASA, or Airbus's EASA Design Organization Approval (DOA).
    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-
2964-0002.

Comments

    We gave the public the opportunity to participate in developing 
this AD. The following presents the comments received on the NPRM and 
the FAA's response to each comment.

Request To Reference Revised Service Information

    American Airlines requested that we reference Revision 03 of Airbus 
Service Bulletin A320-53-1268, dated May 7, 2015, as the appropriate 
source of service information.
    We agree with American Airlines' request. No additional work is 
specified by this revision for airplanes modified by any previous 
issue. We have revised paragraphs (g) and (h) of this AD to refer to 
Airbus Service Bulletin A320-53-1268, Revision 03, dated May 7, 2015; 
and revised paragraph (i) of this AD to also give credit for previous 
actions accomplished in accordance with Airbus Service Bulletin A320-
53-1268, Revision 02, dated July 15, 2014.

Request for Applicability Clarification

    United Airlines (UAL) stated that the effectivity of Airbus Service 
Bulletin A320-53-1268, Revision 02, dated July 15, 2014, does not match 
the NPRM applicability. UAL also stated that the NPRM applicability 
does not mention pre-modification 153832 airplanes, and that Airbus 
Service Bulletin A320-53-1268, Revision 02, dated July 15, 2014, is 
classified as Airbus Modification 153832.
    UAL stated that several alternative methods of compliance (AMOCs) 
may be needed because Airbus will add to the effectivity of Airbus 
Service Bulletin A320-53-1268, Revision 02, dated July 15, 2014, after 
operators purchase an extended design service goal from Airbus.
    We agree to clarify the applicability. The requirements of this AD 
apply to all airplanes identified in the applicability of the AD. If 
there is any conflict between the AD applicability and the service 
information effectivity, then the AD takes precedence. The 
applicability of this AD also matches the applicability of the 
corresponding MCAI AD.
    If operators are planning to operate the airplane beyond the LOV of 
engineering data approved for the original type design, the actions 
specified in this AD must be done in order to address the identified 
unsafe condition. We acknowledge that AMOCs may be needed to allow the 
use of future revisions of the service information. Therefore, we 
encourage operators to coordinate with Airbus for effective planning 
and compliance with the AD requirements if they intend to operate their 
fleet beyond its LOV. We have not changed this final rule in this 
regard.

Request for Terminating Action Clarification

    UAL questioned why there is no terminating action in the proposed 
AD. UAL stated that the reinforcement specified in this proposed AD is 
intended to prevent fatigue cracking of the forward pressure bulkhead 
but there is no reference to related inspection tasks or termination of 
existing Airworthiness Limitation Items (ALIs). UAL noted that, for 
example, ALI 533186 is applicable for pre-Mod 153832 (Airbus Service 
Bulletin A320-53-1268) airplanes. UAL stated this will cause confusion 
as to whether or not ALI inspections are required if there is no 
terminating action paragraph.
    In regard to UAL's question on terminating action, ALI inspections

[[Page 44498]]

must be accomplished on an airplane to be in compliance with the 
approved type design independent of the forward pressure bulkhead 
reinforcement required by this AD. Accomplishing the reinforcement does 
not preclude the need for ALI inspections.
    However, when the effectivity of an ALI inspection identifies pre-
modification airplanes, then it is not applicable to airplanes in a 
post-modification configuration. Thus, ALI inspections that are 
identified as pre-Mod 153832 (Airbus Service Bulletin A320-53-1268) do 
not affect airplanes on which the reinforcement specified in Airbus 
Service Bulletin A320-53-1268 has been done. We have not changed this 
AD in this regard.

Conclusion

    We reviewed the relevant data, considered the comments received, 
and determined that air safety and the public interest require adopting 
this AD with the changes described previously and 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.
    We also determined that these changes will not increase the 
economic burden on any operator or increase the scope of this AD.

Related Service Information Under 1 CFR Part 51

    Airbus has issued Service Bulletin A320-53-1268, Revision 03, dated 
May 7, 2015. The service information describes procedures for 
reinforcing the forward pressure bulkhead at frame 35, stringer 30, on 
both the left-hand and right-hand sides; and for doing repairs. 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 AD.

Costs of Compliance

    We estimate that this AD affects 48 airplanes of U.S. registry.
    We also estimate that it will take about 21 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 $85,680, or $1,785 per product.
    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 warranty coverage for affected 
individuals. As a result, we have included all 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.

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):

2016-14-03 Airbus: Amendment 39-18584. Docket No. FAA-2015-2964; 
Directorate Identifier 2014-NM-206-AD.

(a) Effective Date

    This AD becomes effective August 12, 2016.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to the Airbus airplanes, certificated in any 
category, identified in paragraphs (c)(1), (c)(2), and (c)(3) of 
this AD, all manufacturer serial numbers.
    (1) Airbus Model A319-111, -112, -113, -114, -115, -131, -132, 
and -133 airplanes.
    (2) Airbus Model A320-211, -212, -214, -231, -232, and -233 
airplanes.
    (3) Airbus Model A321-111, -112, -131, -211, -212, -213, -231, 
and -232 airplanes.

(d) Subject

    Air Transport Association (ATA) of America Code 53, Fuselage.

(e) Reason

    This AD is intended to complete certain mandated programs 
intended to support the airplane reaching its limit of validity 
(LOV) of the engineering data that support the established 
structural maintenance program. We are issuing this AD to prevent 
fatigue cracking of the forward pressure bulkhead, which could 
result in reduced structural integrity of the airplane.

(f) Compliance

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

(g) Reinforcement, Related Investigative Actions, and Corrective 
Actions

    Before the accumulation of 48,000 total flight cycles or 96,000 
total flight hours, whichever occurs first: Reinforce the forward 
pressure bulkhead at frame 35, stringer 30, on both the left-hand 
and right-hand sides; and do all applicable related investigative 
and corrective actions; in accordance with the Accomplishment 
Instructions of Airbus Service Bulletin A320-53-1268, Revision 03, 
dated May 7, 2015, except as provided by paragraph (h) of this AD. 
Do all applicable related investigative and corrective actions 
before further flight.

(h) Exception to Service Information Specifications

    Although Airbus Service Bulletin A320-53-1268, Revision 03, 
dated May 7, 2015, specifies to contact Airbus for repair

[[Page 44499]]

instructions, and specifies that action as ``RC'' (Required for 
Compliance), this AD requires repair before further flight 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).

(i) Credit for Previous Actions

    This paragraph provides credit for actions required by paragraph 
(g) of this AD, if those actions were performed before the effective 
date of this AD using any of the Airbus service information 
specified in paragraphs (i)(1) through (i)(3) of this AD. This 
service information is not incorporated by reference in this AD.
    (1) Airbus Service Bulletin A320-53-1268, dated January 8, 2013, 
which is not incorporated by reference in this AD.
    (2) Airbus Service Bulletin A320-53-1268, Revision 01, dated 
July 23, 2013, which is not incorporated by reference in this AD.
    (3) Airbus Service Bulletin A320-53-1268, Revision 02, dated 
July 15, 2014, which is not incorporated by reference in this AD.

(j) 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, 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 EASA; or 
Airbus's EASA DOA. If approved by the DOA, the approval must include 
the DOA-authorized signature.
    (3) Required for Compliance (RC): Except as required by 
paragraph (h) of this AD, 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.

(k) Related Information

    (1) Refer to Mandatory Continuing Airworthiness Information 
(MCAI) EASA AD 2014-0209, dated September 19, 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-2015-2964.
    (2) Service information identified in this AD that is not 
incorporated by reference is available at the addresses specified in 
paragraphs (l)(3) and (l)(4) of this AD.

(l) 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 A320-53-1268, Revision 03, dated May 
7, 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.

    Issued in Renton, Washington, on June 23, 2016.
Dorr M. Anderson,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2016-15909 Filed 7-7-16; 8:45 am]
BILLING CODE 4910-13-P
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