[Federal Register Volume 82, Number 204 (Tuesday, October 24, 2017)]
[Rules and Regulations]
[Pages 49091-49094]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2017-22949]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2016-6429; Product Identifier 2015-NM-117-AD; Amendment
39-19083; AD 2017-22-03]
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 superseding Airworthiness Directive (AD) 2015-05-02,
which applied to all Airbus Model
[[Page 49092]]
A318 and A319 series airplanes; Model A320-211, -212, -214, -231, -232,
and -233 airplanes; and Model A321-111, -112, -131, -211, -212, -213, -
231, and -232 airplanes. AD 2015-05-02 required revising the
maintenance or inspection program to incorporate new, more restrictive
airworthiness limitations. This new AD requires revising the
maintenance or inspection program to incorporate new or revised
structural inspection requirements and adds airplanes to the
applicability. This AD was prompted by an evaluation by the design
approval holder (DAH), which indicates that principal structural
elements and certain life-limited parts are subject to widespread
fatigue damage (WFD). We are issuing this AD to address the unsafe
condition on these products.
DATES: This AD is effective November 28, 2017.
The Director of the Federal Register approved the incorporation by
reference of certain publications listed in this AD as of November 28,
2017.
The Director of the Federal Register approved the incorporation by
reference of certain other publications listed in this AD as of March
2, 2015 (80 FR 3871, January 26, 2015).
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 [email protected]; Internet
http://www.airbus.com. You may view this referenced service information
at the FAA, Transport Standards Branch, 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-2016-
6429.
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-2016-
6429; 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 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 Section, Transport Standards Branch, FAA, 1601 Lind
Avenue SW., Renton, WA 98057-3356; telephone 425-227-1405; fax 425-227-
1149.
SUPPLEMENTARY INFORMATION:
Discussion
We issued a supplemental notice of proposed rulemaking (SNPRM) to
amend 14 CFR part 39 to supersede AD 2015-05-02, Amendment 39-18112 (80
FR 15152, March 23, 2015) (``AD 2015-05-02''). AD 2015-05-02 applied to
all Airbus Model A318 and A319 series airplanes; Model A320-211, -212,
-214, -231, -232, and -233 airplanes; and Model A321-111, -112, -131, -
211, -212, -213, -231, and -232 airplanes. The SNPRM published in the
Federal Register on May 19, 2017 (82 FR 22910) (``the SNPRM''). We
preceded the SNPRM with a notice of proposed rulemaking (NPRM) that
published in the Federal Register on May 11, 2016 (81 FR 29198) (``the
NPRM''). The NPRM was prompted by an evaluation by the DAH, which
indicates that principal structural elements and certain life limited
parts are subject to WFD. The NPRM proposed to require revising the
maintenance or inspection program, as applicable, to incorporate new or
revised structural inspection requirements. The SNPRM proposed to
require more restrictive airworthiness limitations and add Model A320-
251N and -271N airplanes to the applicability. We are issuing this AD
to prevent fatigue cracking, accidental damage, or corrosion in
principal structural elements, and WFD, 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 2016-0239, dated December 2, 2016 (referred to
after this as the Mandatory Continuing Airworthiness Information, or
``the MCAI''), to correct an unsafe condition. The MCAI states:
The airworthiness limitations for Airbus A320 family aeroplanes
are currently included in Airbus A318/A319/A320/A321 Airworthiness
Limitations Section (ALS) documents. The Damage Tolerant
Airworthiness Limitation Items are published in ALS Part 2, approved
by EASA.
The instructions contained in the ALS Part 2 have been
identified as mandatory actions for continued airworthiness. Failure
to comply with these instructions could result in an unsafe
condition.
Previously, EASA issued AD 2015-0083 to require accomplishment
of all maintenance tasks as described in ALS Part 2 at Revision 03.
Since that [EASA] AD was issued, Airbus issued Revision 04, and
later on Revision 05 of the ALS Part 2, including new and/or more
restrictive items, and new A320 models were certified.
For the reason described above, this [EASA] AD retains the
requirements of EASA AD 2015-0083, which is superseded, expands the
Applicability by adding the models A320-251N and A320-271N, requires
accomplishment of all maintenance tasks as described in the ALS Part
2, Revision 05 (hereafter referred to as `the ALS' in this [EASA]
AD), and provides specific compliance times for ALS task 572021-01-1
(Wide Spread Fatigue Damage related).
The required action is revising the maintenance or inspection
program to incorporate new or revised structural inspection
requirements. The unsafe condition is fatigue cracking, accidental
damage, or corrosion in principal structural elements, and WFD, which
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-2016-
6429.
Comments
We gave the public the opportunity to participate in developing
this AD. The following presents the comment received on the SNPRM and
the FAA's response to the comment.
Request To Reference Revised Service Information
American Airlines (AAL) requested that we revise the SNPRM to
incorporate Airbus A318/A319/A320/A321 ALS Part 1--Safe Life
Airworthiness Limitation Items (SL--ALI), Revision 05, dated April 6,
2017, including Variations 5.1 and 5.2; and Airbus A318/A319/A320/A321
ALS Part 2--Damage Tolerant Airworthiness Limitation Items (DT--ALI),
Revision 06, dated April 10, 2017.
We partially agree with AAL's request. We agree that operators
should use the latest service information, and we agree to account for
AAL's request in this AD. However, we do not agree to require the
revised service information in this final rule since it would expand
the scope, requiring additional notice and comment. We find that
delaying this action would be inappropriate in light of the identified
unsafe condition. We are considering further rulemaking to supersede
this final rule to require incorporating the revised service
information.
We have added paragraph (l)(1)(iii) to this AD to specify that the
previous
[[Page 49093]]
alternative methods of compliance (AMOCs) that are approved for AD
2015-05-02 are approved as AMOCs for the corresponding provisions of
paragraphs (i) and (j) of this AD. The previous AMOCs include Airbus
A318/A319/A320/A321 ALS Part 1--Safe Life Airworthiness Limitation
Items (SL--ALI), Revision 05, dated April 6, 2017, including Variations
5.1 and 5.2; and Airbus A318/A319/A320/A321 ALS Part 2--Damage Tolerant
Airworthiness Limitation Items (DT--ALI), Revision 06, dated April 10,
2017.
Conclusion
We reviewed the available data, including the comment received, and
determined that air safety and the public interest require adopting
this AD as proposed except for minor editorial changes. We have
determined that these minor changes:
Are consistent with the intent that was proposed in the
SNPRM for correcting the unsafe condition; and
Do not add any additional burden upon the public than was
already proposed in the SNPRM.
Related Service Information Under 1 CFR Part 51
Airbus has issued the following service information.
A318/A319/A320/A321 ALS Part 1--Safe Life Airworthiness
Limitation Items (SL--ALI), Revision 04, dated June 20, 2016. This
service information describes mandatory instructions and airworthiness
limitations for the ``safe-life'' structure.
A318/A319/A320/A321 ALS Part 2--Damage Tolerant
Airworthiness Limitation Items (DT--ALI), Revision 05, dated July 8,
2016. This service information describes mandatory instructions and
airworthiness limitations arising from fatigue and damage tolerance
evaluation of damage tolerant structural elements.
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 1,182 airplanes of U.S. registry.
The actions required by AD 2015-05-02, and retained in this AD,
take about 2 work-hours per product, at an average labor rate of $85
per work-hour. Based on these figures, the estimated cost of the
actions that are required by AD 2015-05-02 is $170 per product.
We also estimate that it will take about 2 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 $200,940, or $170 per product.
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.
This AD is issued in accordance with authority delegated by the
Executive Director, Aircraft Certification Service, as authorized by
FAA Order 8000.51C. In accordance with that order, issuance of ADs is
normally a function of the Compliance and Airworthiness Division, but
during this transition period, the Executive Director has delegated the
authority to issue ADs applicable to transport category airplanes to
the Director of the System Oversight Division.
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 removing Airworthiness Directive (AD)
2015-05-02, Amendment 39-18112 (80 FR 15152, March 23, 2015), and
adding the following new AD:
2017-22-03 Airbus Amendment 39-19083; Docket No. FAA-2016-6429;
Product Identifier 2015-NM-117-AD.
(a) Effective Date
This AD is effective November 28, 2017.
(b) Affected ADs
This AD replaces AD 2015-05-02, Amendment 39-18112 (80 FR 15152,
March 23, 2015) (``AD 2015-05-02'').
(c) Applicability
This AD applies to the Airbus airplanes identified in paragraphs
(c)(1) through (c)(4) of this AD, certificated in any category, with
an original certificate of airworthiness or original export
certificate of airworthiness issued on or before July 8, 2016.
(1) Model A318-111, -112, -121, and -122 airplanes.
(2) Model A319-111, -112, -113, -114, -115, -131, -132, and -133
airplanes.
(3) Model A320-211, -212, -214, -216, -231, -232, -233, -251N,
and -271N airplanes.
(4) Model A321-111, -112, -131, -211, -212, -213, -231, and -232
airplanes.
(d) Subject
Air Transport Association (ATA) of America Code 05, Periodic
Inspections.
(e) Reason
This AD was prompted by an evaluation by the design approval
holder which indicates that principal structural elements and
certain life-limited parts are subject to widespread fatigue damage
(WFD). We are issuing this AD to prevent fatigue cracking,
accidental damage, or corrosion in principal structural elements,
and WFD, which could result in reduced structural integrity of the
airplane.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
[[Page 49094]]
(g) Retained Maintenance or Inspection Program Revision, With No
Changes
This paragraph restates the requirements of paragraph (n) of AD
2015-05-02, with no changes. Within 30 days after March 2, 2015 (the
effective date of AD 2014-23-15, Amendment 39-18031 (80 FR 3871,
January 26, 2015) (``AD 2014-23-15'')), revise the maintenance or
inspection program, as applicable, to incorporate the Airworthiness
Limitation Items (ALIs) specified in paragraphs (g)(1) and (g)(2) of
this AD. The initial compliance time for accomplishing the actions
is at the applicable time identified in the ALIs specified in
paragraphs (g)(1) and (g)(2) of this AD; or within 4 months after
March 2, 2015 (the effective date of AD 2014-23-15); whichever
occurs later.
(1) Airbus A318/A319/A320/A321 Airworthiness Limitations Section
(ALS) Part 1--Safe Life Airworthiness Limitation Items, Revision 02,
dated May 13, 2011.
(2) Airbus A318/A319/A320/A321 ALS Part 2--Damage-Tolerant
Airworthiness Limitation Items (DT ALI), Revision 02, dated May 28,
2013.
(h) Retained Limitation: No Alternative Actions, Intervals, and/or
Critical Design Configuration Control Limitations (CDCCLs), With an
Exception
This paragraph restates the requirements of paragraph (o) of AD
2015-05-02, with an exception. Except as specified in paragraph (i)
or (j) of this AD, as applicable, after accomplishing the revision
required by paragraph (g) of this AD, no alternative actions (e.g.,
inspections), intervals, and/or CDCCLs may be used unless the
actions, intervals, and/or CDCCLs are approved as an alternative
method of compliance (AMOC) in accordance with the procedures
specified in paragraph (l)(1) of this AD.
(i) New Maintenance or Inspection Program Revision
Within 60 days after the effective date of this AD, revise the
maintenance or inspection program, as applicable, to incorporate the
ALIs specified in Airbus A318/A319/A320/A321 ALS Part 2--Damage
Tolerant Airworthiness Limitation Items (DT--ALI), Revision 05,
dated July 8, 2016. The initial compliance time for accomplishing
the actions is at the applicable time identified in the ALIs
specified in Airbus A318/A319/A320/A321 ALS Part 2--DT--ALI,
Revision 05, dated July 8, 2016, without exceeding the inspection
intervals in the ALIs specified in the service information
identified in paragraph (g)(2) of this AD. Accomplishing this action
terminates the requirements of paragraph (g)(2) of this AD.
(j) New Method of Compliance for Maintenance or Inspection Program
Revision
Revising the maintenance or inspection program, as applicable,
to incorporate the ALIs specified in Airbus A318/A319/A320/A321 ALS
Part 1--Safe Life Airworthiness Limitation Items (SL--ALI), Revision
04, dated June 20, 2016, is a method of compliance for the actions
required by paragraph (g)(1) of this AD. The initial compliance time
for accomplishing the actions is at the applicable time identified
in the ALIs specified in Airbus A318/A319/A320/A321 ALS Part 1--SL--
ALI, Revision 04, dated June 20, 2016, without exceeding the
inspection intervals in the ALIs specified in the service
information identified in paragraph (g)(1) of this AD. Accomplishing
this action terminates the requirements of paragraph (g)(1) of this
AD.
(k) New No Alternative Actions and/or Intervals
After accomplishing the revision required by paragraph (i) or
specified in paragraph (j) of this AD, no alternative actions (e.g.,
inspections) and/or intervals may be used unless the actions and/or
intervals are approved as an AMOC in accordance with the procedures
specified in paragraph (l)(1) of this AD.
(l) Other FAA AD Provisions
The following provisions also apply to this AD:
(1) Alternative Methods of Compliance (AMOCs): The Manager,
International Section, Transport Standards Branch, 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 Section, send it to the attention of
the person identified in paragraph (m)(2) of this AD. Information
may be emailed to: [email protected].
(i) 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.
(ii) AMOCs approved previously for AD 2015-05-02, are approved
as AMOCs for the corresponding provisions of paragraphs (g) and (h)
of this AD.
(iii) AMOCs approved previously for AD 2015-05-02, which are
included in the FAA AMOC letters specified in paragraphs
(l)(1)(iii)(A) and (l)(1)(iii)(B), are approved as AMOCs for the
corresponding provisions of paragraphs (i) and (j) of this AD.
(A) FAA AMOC letter ANM-116-17-002R1, dated November 14, 2016.
(B) FAA AMOC letter ANM-116-17-323, dated June 12, 2017.
(2) Contacting the Manufacturer: As of the effective date of
this AD, 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 Section, Transport Standards
Branch, 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.
(m) Related Information
(1) Refer to Mandatory Continuing Airworthiness Information
(MCAI) EASA Airworthiness Directive 2016-0239, dated December 2,
2016, 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-2016-6429.
(2) For more information about this AD, contact Sanjay Ralhan,
Aerospace Engineer, International Section, Transport Standards
Branch, FAA, 1601 Lind Avenue SW., Renton, WA 98057-3356; telephone
425-227-1405; fax 425-227-1149.
(n) 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.
(3) The following service information was approved for IBR on
November 28, 2017.
(i) Airbus A318/A319/A320/A321 Airworthiness Limitations Section
(ALS) Part 1--Safe Life--Airworthiness Limitation Items (SL--ALI),
Revision 04, dated June 20, 2016.
(ii) Airbus A318/A319/A320/A321 Airworthiness Limitations
Section (ALS) Part 2--Damage Tolerant Airworthiness Limitation Items
(DT--ALI), Revision 05, dated July 8, 2016.
(4) The following service information was approved for IBR on
March 2, 2015 (80 FR 3871, January 26, 2015).
(i) Airbus A318/A319/A320/A321 ALS Part 1--Safe Life
Airworthiness Limitation Items, Revision 02, dated May 13, 2011. The
revision level of this document is identified on only the title page
and in the Record of Revisions. The revision date is not identified
on the title page of this document.
(ii) Airbus A318/A319/A320/A321 ALS Part 2--Damage-Tolerant
Airworthiness Limitation Items (DT ALI), Revision 02, dated May 28,
2013. The revision date of this document is not identified on the
title page of this document.
(5) 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.
(6) You may view this service information at the FAA, Transport
Standards Branch, 1601 Lind Avenue SW., Renton, WA. For information
on the availability of this material at the FAA, call 425-227-1221.
(7) 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 October 11, 2017.
Jeffrey E. Duven,
Director, System Oversight Division, Aircraft Certification Service.
[FR Doc. 2017-22949 Filed 10-23-17; 8:45 am]
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