[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]]
[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. 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: [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 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 [email protected]; 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]
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