81 FR 21244 - Airworthiness Directives; Airbus Airplanes

DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration

Federal Register Volume 81, Issue 69 (April 11, 2016)

Page Range		21244-21246
FR Document		2016-07375
We are adopting a new airworthiness directive (AD) for certain 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 was prompted by fatigue testing that determined fatigue damage could appear on clips, shear webs, and angles at certain rear fuselage sections and certain frames. This AD requires replacing the clips, shear webs, and angles, including doing all applicable related investigative actions, and repair if necessary. We are issuing this AD to prevent fatigue damage on the clips, shear webs, and angles; such damage could affect the structural integrity of the airplane.
Federal Register, Volume 81 Issue 69 (Monday, April 11, 2016)
[Federal Register Volume 81, Number 69 (Monday, April 11, 2016)]
[Rules and Regulations]
[Pages 21244-21246]
From the Federal Register Online  [www.thefederalregister.org]
[FR Doc No: 2016-07375]


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

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2015-1277; Directorate Identifier 2014-NM-155-AD; 
Amendment 39-18459; AD 2016-07-14]
RIN 2120-AA64


Airworthiness Directives; Airbus Airplanes

AGENCY: Federal Aviation Administration (FAA), Department of 
Transportation (DOT).

ACTION: Final rule.

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

SUMMARY: We are adopting a new airworthiness directive (AD) for certain 
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 was 
prompted by fatigue testing that determined fatigue damage could appear 
on clips, shear webs, and angles at certain rear fuselage sections and 
certain frames. This AD requires replacing the clips, shear webs, and 
angles, including doing all applicable related investigative actions, 
and repair if necessary. We are issuing this AD to prevent fatigue 
damage on the clips, shear webs, and angles; such damage could affect 
the structural integrity of the airplane.

DATES: This AD becomes effective May 16, 2016.
    The Director of the Federal Register approved the incorporation by 
reference of a certain publication listed in this AD as of May 16, 
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 [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-
1277.

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-
1277; 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 in the ADDRESSES section.

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 A319, 
A320, and A321 series airplanes. The NPRM published in the Federal 
Register on May 8, 2015 (80 FR 26487) (``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 2014-0177, dated July 25, 2014 (referred to 
after this as the Mandatory Continuing Airworthiness Information, or 
``the MCAI''), to correct an unsafe condition for certain Airbus Model 
A319, A320, and A321 series airplanes. The MCAI states:

    During the A320 fatigue test campaign for Extended Service Goal 
(ESG), it was determined that fatigue damage could appear on the 
clips, shear webs and angles at rear fuselage section 19, on Frame 
(FR) 72 and FR74.
    This condition, if not detected and corrected, could affect the 
structural integrity of the aeroplane.
    To address this potential unsafe condition, Airbus developed a 
modification, which has been published through Airbus Service 
Bulletin (SB) A320-53-1266 for in-service application to allow 
aeroplanes to operate up to the new ESG limit.
    For the reasons described above, this [EASA] AD requires 
replacement of the affected clips, shear webs and angles at rear 
fuselage section 19, FR72 and FR74 [including all applicable related 
investigative actions and repair if any cracking is found].

    Related investigative actions include rotating probe testing for 
cracking of the fastener holes and high frequency eddy current 
inspections for cracking of the stringers. 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-2015-1277.

Actions Since NPRM was Issued

    Since the NPRM was issued, Airbus has issued Airbus Service 
Bulletin A320-53-1266, Revision 03, dated May 7, 2015. We have revised 
paragraph (g) of this AD to reference this revised service information. 
We have revised paragraph (i) of this AD to give credit for actions 
done before the effective date of this AD using the following service 
information.
     Airbus Service Bulletin A320-53-1266, dated January 11, 
2013.
     Airbus Service Bulletin A320-53-1266, Revision 01, dated 
June 20, 2013.
     Airbus Service Bulletin A320-53-1266, Revision 02, dated 
August 13, 2014.

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.

Support for the NPRM

    An anonymous commenter provided support for the NPRM.

Request To Omit Part Replacement Requirement

    United Airlines requested that we revise paragraph (h) of the 
proposed AD to omit the additional part replacement. United Airlines 
noted that paragraph (h) of the proposed AD states that the replacement 
of clips, shear webs, and angles must be accomplished again before 
30,000 flight cycles or 60,000 flight hours, whichever occurs first, if 
the replacement was accomplished before 30,000 flight cycles or 60,000 
flight hours, whichever occurred first from airplane's first flight. 
The commenter stated that this paragraph suggests that the installation 
of new parts does not constitute terminating action. The commenter 
expressed that paragraph (g) of the proposed AD has no repetitive 
requirement for replacement

[[Page 21245]]

of new parts if accomplished between 30,000 and 48,000 flight cycles or 
60,000 and 96,000 flight hours since the airplane's first flight. The 
commenter suggested that this requirement will encourage operators to 
replace the part when the airplane has accumulated more than 30,000 
total flight cycles and 60,000 total flight hours in order to avoid the 
possibility of additional part replacement. The commenter added that 
installation of new parts twice, increases the risk of damage during 
the part replacement.
    United Airlines stated further that the additional replacement in 
paragraph (h) of the proposed AD could potentially result in the 
requirement to replace the part twice before the threshold defined in 
paragraph (g) of the proposed AD. By way of example, the commenter 
stated that if the part replacement were accomplished before 18,000 
flight cycles and 36,000 flight hours since the airplane's first 
flight, the replacement would be required again before 48,000 flight 
cycles or 96,000 flight hours since the airplane's first flight. This 
scenario implies that the new parts reduce the fatigue life compared to 
an unmodified aircraft. United Airlines stated that it is not clear how 
the additional replacement in paragraph (h) of the proposed AD meets 
the intent of the NPRM. The replacement part modification prevents 
fatigue damage on the clips, shear webs, and angles to support 
operation reaching the LOV. However, there is no explanation in the AD 
that these new parts are life limited.
    We disagree to omit the additional part replacement required by 
paragraph (h) of this AD. We agree with United Airlines' assessment 
that this AD would require replacement of the clips, shear webs, and 
angles twice, if those parts are first replaced prior to 30,000 total 
flight cycles or 60,000 total flight hours, whichever occurs first. 
Replacement of clips, shear webs, and angles prior to 30,000 total 
flight cycles or 60,000 total flight hours may have been required due 
to reasons other than this AD. However, this AD does not require 
replacement of the parts before 30,000 total flight cycles or 60,000 
total flight hours. We have determined that if the parts are replaced 
before 30,000 total flight cycles or 60,000 total flight hours, 
whichever occurs first, a repeat replacement of those parts is 
necessary to support the airplane reaching its LOV of the engineering 
data.
    We also disagree that requiring replacement of the parts twice, 
will increase the risk of damage. The procedures specified in Airbus 
Service Bulletin A320-53-1266, Revision 03, dated May 7, 2015, for 
replacing clips, shear webs, and angles are appropriate for supporting 
the continued operational safety of the affected Airbus fleet and do 
not introduce additional risk to the structural integrity of the 
airplane. We have made no changes to 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 as proposed except for 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 Airbus Service Bulletin A320-53-1266, Revision 
03, dated May 7, 2015. The service information describes procedures for 
replacing clips, shear webs, and angles at rear fuselage section 19, 
FR72 and FR74. 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 44 airplanes of U.S. registry.
    We also estimate that it will take about 110 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 $411,400, or $9,350 per product.
    We have received no definitive data on the costs of required parts.

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):

2016-07-14 Airbus: Amendment 39-18459. Docket No. FAA-2015-1277; 
Directorate Identifier 2014-NM-155-AD.

(a) Effective Date

    This AD becomes effective May 16, 2016.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to the airplanes identified in paragraphs 
(c)(1), (c)(2), and (c)(3) of this AD, certificated in any category, 
all manufacturer serial numbers, except those on

[[Page 21246]]

which Airbus Modification 30975 has been embodied in production.
    (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 was prompted by fatigue testing that determined that 
fatigue damage could appear on clips, shear webs, and angles at 
certain rear fuselage sections and certain frames. This AD is 
intended to complete certain mandated programs intended to support 
the airplane reaching its limit of validity of the engineering data 
that support the established structural maintenance program. We are 
issuing this AD to prevent fatigue damage on the clips, shear webs, 
and angles, which could affect the structural integrity of the 
airplane.

(f) Compliance

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

(g) Replacement

    At the later of the times specified in paragraphs (g)(1) and 
(g)(2) of this AD: Replace the clips, shear webs, and angles at rear 
fuselage section 19, frame FR72 and FR74, and do all applicable 
related investigative actions before further flight, in accordance 
with the Accomplishment Instructions of Airbus Service Bulletin 
A320-53-1266, Revision 03, dated May 7, 2015. If any crack is found 
during any related investigative action required by this AD: Before 
further flight, repair 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).
    (1) Before exceeding 48,000 flight cycles or 96,000 flight 
hours, whichever occurs first since the airplane's first flight.
    (2) Within 30 days after the effective date of this AD.

(h) Additional Replacement for Certain Airplanes

    For airplanes on which the replacement of clips, shear webs, and 
angles specified in Airbus Service Bulletin A320-53-1266 is done 
before accumulating 30,000 flight cycles or 60,000 flight hours, 
whichever occurred first since the airplane's first flight: Within 
30,000 flight cycles or 60,000 flight hours, whichever occurs first 
after that replacement, do the replacement specified in paragraph 
(g) of this AD.

(i) Credit for Previous Actions

    Except as required by paragraph (h) of this AD: This paragraph 
provides credit for the replacement required by paragraph (g) of 
this AD, if those actions were performed before the effective date 
of this AD using the service information identified in paragraph 
(i)(1), (i)(2), or (i)(3) of this AD. This service information is 
not incorporated by reference in this AD.
    (1) Airbus Service Bulletin A320-53-1266, dated January 11, 
2013.
    (2) Airbus Service Bulletin A320-53-1266, Revision 01, dated 
June 20, 2013.
    (3) Airbus Service Bulletin A320-53-1266, Revision 02, dated 
August 13, 2014.

(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 the EASA; 
or Airbus's EASA DOA. If approved by the DOA, the approval must 
include the DOA-authorized signature.

(k) Related Information

    (1) Refer to Mandatory Continuing Airworthiness Information 
(MCAI) EASA Airworthiness Directive 2014-0177, dated July 25, 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-2015-1277.
    (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 A320-53-1266, 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 March 25, 2016.
Michael Kaszycki,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2016-07375 Filed 4-8-16; 8:45 am]
 BILLING CODE 4910-13-P
21244 Federal Register / Vol. 81, No. 69 / Monday, April 11, 2016 / Rules and Regulations

(5) You may view this service information account.airworth-eas@airbus.com; Bulletin (SB) A320–53–1266 for in-service
that is incorporated by reference at the Internet http://www.airbus.com. You application to allow aeroplanes to operate up
National Archives and Records may view this referenced service to the new ESG limit.
Administration (NARA). For information on For the reasons described above, this
information at the FAA, Transport [EASA] AD requires replacement of the
the availability of this material at NARA, call
202–741–6030, or go to: http:// Airplane Directorate, 1601 Lind Avenue affected clips, shear webs and angles at rear
www.archives.gov/federal-register/cfr/ibr- SW., Renton, WA. For information on fuselage section 19, FR72 and FR74
locations.html. the availability of this material at the [including all applicable related investigative
Issued in Renton, Washington, on March
FAA, call 425–227–1221. It is also actions and repair if any cracking is found].
25, 2016. available on the Internet at http:// Related investigative actions include
Michael Kaszycki,
www.regulations.gov by searching for rotating probe testing for cracking of the
and locating Docket No. FAA–2015– fastener holes and high frequency eddy
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
1277. current inspections for cracking of the
[FR Doc. 2016–07571 Filed 4–8–16; 8:45 am] Examining the AD Docket stringers. You may examine the MCAI
in the AD docket on the Internet at
BILLING CODE 4910–13–P You may examine the AD docket on http://www.regulations.gov by searching
the Internet at http:// for and locating Docket No. FAA–2015–
www.regulations.gov by searching for 1277.
DEPARTMENT OF TRANSPORTATION and locating Docket No. FAA–2015–
1277; or in person at the Docket Actions Since NPRM was Issued
Federal Aviation Administration
Management Facility between 9 a.m. Since the NPRM was issued, Airbus
and 5 p.m., Monday through Friday, has issued Airbus Service Bulletin
14 CFR Part 39
except Federal holidays. The AD docket A320–53–1266, Revision 03, dated May
[Docket No. FAA–2015–1277; Directorate contains this AD, the regulatory 7, 2015. We have revised paragraph (g)
Identifier 2014–NM–155–AD; Amendment evaluation, any comments received, and of this AD to reference this revised
39–18459; AD 2016–07–14] other information. The street address for service information. We have revised
RIN 2120–AA64 the Docket Operations office (telephone paragraph (i) of this AD to give credit for
800–647–5527) is in the ADDRESSES actions done before the effective date of
Airworthiness Directives; Airbus section. this AD using the following service
Airplanes FOR FURTHER INFORMATION CONTACT: information.
AGENCY: Federal Aviation Sanjay Ralhan, Aerospace Engineer, • Airbus Service Bulletin A320–53–
Administration (FAA), Department of International Branch, ANM–116, 1266, dated January 11, 2013.
Transportation (DOT). Transport Airplane Directorate, FAA, • Airbus Service Bulletin A320–53–
1601 Lind Avenue SW., Renton, WA 1266, Revision 01, dated June 20, 2013.
ACTION: Final rule.
98057–3356; telephone 425–227–1405; • Airbus Service Bulletin A320–53–
SUMMARY: We are adopting a new fax 425–227–1149. 1266, Revision 02, dated August 13,
airworthiness directive (AD) for certain 2014.
SUPPLEMENTARY INFORMATION:
Airbus Model A319, A320, and A321 Comments
series airplanes. This AD is intended to Discussion
complete certain mandated programs We gave the public the opportunity to
We issued a notice of proposed
intended to support the airplane participate in developing this AD. The
rulemaking (NPRM) to amend 14 CFR
reaching its limit of validity (LOV) of following presents the comments
part 39 by adding an AD that would
the engineering data that support the received on the NPRM and the FAA’s
apply to certain Airbus Model A319,
established structural maintenance response to each comment.
A320, and A321 series airplanes. The
program. This AD was prompted by NPRM published in the Federal Support for the NPRM
fatigue testing that determined fatigue Register on May 8, 2015 (80 FR 26487) An anonymous commenter provided
damage could appear on clips, shear (‘‘the NPRM’’). support for the NPRM.
webs, and angles at certain rear fuselage The European Aviation Safety Agency
sections and certain frames. This AD (EASA), which is the Technical Agent Request To Omit Part Replacement
requires replacing the clips, shear webs, for the Member States of the European Requirement
and angles, including doing all Union, has issued EASA Airworthiness United Airlines requested that we
applicable related investigative actions, Directive 2014–0177, dated July 25, revise paragraph (h) of the proposed AD
and repair if necessary. We are issuing 2014 (referred to after this as the to omit the additional part replacement.
this AD to prevent fatigue damage on Mandatory Continuing Airworthiness United Airlines noted that paragraph (h)
the clips, shear webs, and angles; such Information, or ‘‘the MCAI’’), to correct of the proposed AD states that the
damage could affect the structural an unsafe condition for certain Airbus replacement of clips, shear webs, and
integrity of the airplane. Model A319, A320, and A321 series angles must be accomplished again
DATES: This AD becomes effective May airplanes. The MCAI states: before 30,000 flight cycles or 60,000
16, 2016. During the A320 fatigue test campaign for flight hours, whichever occurs first, if
The Director of the Federal Register Extended Service Goal (ESG), it was the replacement was accomplished
approved the incorporation by reference determined that fatigue damage could appear before 30,000 flight cycles or 60,000
of a certain publication listed in this AD on the clips, shear webs and angles at rear flight hours, whichever occurred first
jstallworth on DSK7TPTVN1PROD with RULES

as of May 16, 2016. fuselage section 19, on Frame (FR) 72 and from airplane’s first flight. The
FR74. commenter stated that this paragraph
ADDRESSES: For service information
This condition, if not detected and
identified in this final rule, contact corrected, could affect the structural integrity
suggests that the installation of new
Airbus, Airworthiness Office—EIAS, 1 of the aeroplane. parts does not constitute terminating
Rond Point Maurice Bellonte, 31707 To address this potential unsafe condition, action. The commenter expressed that
Blagnac Cedex, France; telephone +33 5 Airbus developed a modification, which has paragraph (g) of the proposed AD has no
61 93 36 96; fax +33 5 61 93 44 51; email been published through Airbus Service repetitive requirement for replacement

VerDate Sep<11>2014 14:13 Apr 08, 2016 Jkt 238001 PO 00000 Frm 00022 Fmt 4700 Sfmt 4700 E:\FR\FM\11APR1.SGM 11APR1
Federal Register / Vol. 81, No. 69 / Monday, April 11, 2016 / Rules and Regulations 21245

of new parts if accomplished between shear webs, and angles are appropriate the Administrator finds necessary for
30,000 and 48,000 flight cycles or for supporting the continued safety in air commerce. This regulation
60,000 and 96,000 flight hours since the operational safety of the affected Airbus is within the scope of that authority
airplane’s first flight. The commenter fleet and do not introduce additional because it addresses an unsafe condition
suggested that this requirement will risk to the structural integrity of the that is likely to exist or develop on
encourage operators to replace the part airplane. We have made no changes to products identified in this rulemaking
when the airplane has accumulated this AD in this regard. action.
more than 30,000 total flight cycles and
60,000 total flight hours in order to Conclusion Regulatory Findings
avoid the possibility of additional part We reviewed the relevant data, We determined that this AD will not
replacement. The commenter added that considered the comments received, and have federalism implications under
installation of new parts twice, determined that air safety and the Executive Order 13132. This AD will
increases the risk of damage during the public interest require adopting this AD not have a substantial direct effect on
part replacement. as proposed except for minor editorial the States, on the relationship between
United Airlines stated further that the changes. We have determined that these the national government and the States,
additional replacement in paragraph (h) minor changes: or on the distribution of power and
of the proposed AD could potentially • Are consistent with the intent that responsibilities among the various
result in the requirement to replace the was proposed in the NPRM for levels of government.
part twice before the threshold defined correcting the unsafe condition; and For the reasons discussed above, I
in paragraph (g) of the proposed AD. By • Do not add any additional burden certify that this AD:
way of example, the commenter stated upon the public than was already 1. Is not a ‘‘significant regulatory
that if the part replacement were proposed in the NPRM. action’’ under Executive Order 12866;
accomplished before 18,000 flight cycles 2. Is not a ‘‘significant rule’’ under the
Related Service Information Under 1
and 36,000 flight hours since the DOT Regulatory Policies and Procedures
airplane’s first flight, the replacement CFR Part 51
(44 FR 11034, February 26, 1979);
would be required again before 48,000 Airbus has issued Airbus Service 3. Will not affect intrastate aviation in
flight cycles or 96,000 flight hours since Bulletin A320–53–1266, Revision 03, Alaska; and
the airplane’s first flight. This scenario dated May 7, 2015. The service 4. Will not have a significant
implies that the new parts reduce the information describes procedures for economic impact, positive or negative,
fatigue life compared to an unmodified replacing clips, shear webs, and angles on a substantial number of small entities
aircraft. United Airlines stated that it is at rear fuselage section 19, FR72 and under the criteria of the Regulatory
not clear how the additional FR74. This service information is Flexibility Act.
replacement in paragraph (h) of the reasonably available because the
proposed AD meets the intent of the interested parties have access to it List of Subjects in 14 CFR Part 39
NPRM. The replacement part through their normal course of business Air transportation, Aircraft, Aviation
modification prevents fatigue damage or by the means identified in the safety, Incorporation by reference,
on the clips, shear webs, and angles to ADDRESSES section. Safety.
support operation reaching the LOV.
However, there is no explanation in the Costs of Compliance Adoption of the Amendment
AD that these new parts are life limited. We estimate that this AD affects 44 Accordingly, under the authority
We disagree to omit the additional airplanes of U.S. registry. delegated to me by the Administrator,
part replacement required by paragraph We also estimate that it will take the FAA amends 14 CFR part 39 as
(h) of this AD. We agree with United about 110 work-hours per product to follows:
Airlines’ assessment that this AD would comply with the basic requirements of
require replacement of the clips, shear this AD. The average labor rate is $85 PART 39—AIRWORTHINESS
webs, and angles twice, if those parts per work-hour. Based on these figures, DIRECTIVES
are first replaced prior to 30,000 total we estimate the cost of this AD on U.S.
flight cycles or 60,000 total flight hours, operators to be $411,400, or $9,350 per ■ 1. The authority citation for part 39
whichever occurs first. Replacement of product. continues to read as follows:
clips, shear webs, and angles prior to We have received no definitive data Authority: 49 U.S.C. 106(g), 40113, 44701.
30,000 total flight cycles or 60,000 total on the costs of required parts.
flight hours may have been required due § 39.13 [Amended]
Authority for This Rulemaking
to reasons other than this AD. However, ■ 2. The FAA amends § 39.13 by adding
this AD does not require replacement of Title 49 of the United States Code the following new airworthiness
the parts before 30,000 total flight cycles specifies the FAA’s authority to issue directive (AD):
or 60,000 total flight hours. We have rules on aviation safety. Subtitle I,
determined that if the parts are replaced section 106, describes the authority of 2016–07–14 Airbus: Amendment 39–18459.
Docket No. FAA–2015–1277; Directorate
before 30,000 total flight cycles or the FAA Administrator. ‘‘Subtitle VII:
Identifier 2014–NM–155–AD.
60,000 total flight hours, whichever Aviation Programs,’’ describes in more
occurs first, a repeat replacement of detail the scope of the Agency’s (a) Effective Date
those parts is necessary to support the authority. This AD becomes effective May 16, 2016.
airplane reaching its LOV of the We are issuing this rulemaking under
(b) Affected ADs
jstallworth on DSK7TPTVN1PROD with RULES

engineering data. the authority described in ‘‘Subtitle VII,
We also disagree that requiring Part A, Subpart III, Section 44701: None.
replacement of the parts twice, will General requirements.’’ Under that (c) Applicability
increase the risk of damage. The section, Congress charges the FAA with This AD applies to the airplanes identified
procedures specified in Airbus Service promoting safe flight of civil aircraft in in paragraphs (c)(1), (c)(2), and (c)(3) of this
Bulletin A320–53–1266, Revision 03, air commerce by prescribing regulations AD, certificated in any category, all
dated May 7, 2015, for replacing clips, for practices, methods, and procedures manufacturer serial numbers, except those on

VerDate Sep<11>2014 16:42 Apr 08, 2016 Jkt 238001 PO 00000 Frm 00023 Fmt 4700 Sfmt 4700 E:\FR\FM\11APR1.SGM 11APR1
21246 Federal Register / Vol. 81, No. 69 / Monday, April 11, 2016 / Rules and Regulations

which Airbus Modification 30975 has been (i)(2), or (i)(3) of this AD. This service telephone +33 5 61 93 36 96; fax +33 5 61
embodied in production. information is not incorporated by reference 93 44 51; email account.airworth-eas@
(1) Airbus Model A319–111, –112, –113, in this AD. airbus.com; Internet http://www.airbus.com.
–114, –115, –131, –132, and –133 airplanes. (1) Airbus Service Bulletin A320–53–1266, (4) You may view this service information
(2) Airbus Model A320–211, –212, –214, dated January 11, 2013. at the FAA, Transport Airplane Directorate,
–231, –232, and –233 airplanes. (2) Airbus Service Bulletin A320–53–1266, 1601 Lind Avenue SW., Renton, WA. For
(3) Airbus Model A321–111, –112, –131, Revision 01, dated June 20, 2013. information on the availability of this
–211, –212, –213, –231, and –232 airplanes. (3) Airbus Service Bulletin A320–53–1266, material at the FAA, call 425–227–1221.
Revision 02, dated August 13, 2014. (5) You may view this service information
(d) Subject
(j) Other FAA AD Provisions that is incorporated by reference at the
Air Transport Association (ATA) of National Archives and Records
America Code 53, Fuselage. The following provisions also apply to this Administration (NARA). For information on
AD: the availability of this material at NARA, call
(e) Reason (1) Alternative Methods of Compliance 202–741–6030, or go to: http://
This AD was prompted by fatigue testing (AMOCs): The Manager, International www.archives.gov/federal-register/cfr/ibr-
that determined that fatigue damage could Branch, ANM–116, Transport Airplane locations.html.
appear on clips, shear webs, and angles at Directorate, FAA, has the authority to
certain rear fuselage sections and certain approve AMOCs for this AD, if requested Issued in Renton, Washington, on March
frames. This AD is intended to complete using the procedures found in 14 CFR 39.19. 25, 2016.
certain mandated programs intended to In accordance with 14 CFR 39.19, send your Michael Kaszycki,
support the airplane reaching its limit of request to your principal inspector or local Acting Manager, Transport Airplane
validity of the engineering data that support Flight Standards District Office, as Directorate, Aircraft Certification Service.
the established structural maintenance appropriate. If sending information directly
[FR Doc. 2016–07375 Filed 4–8–16; 8:45 am]
program. We are issuing this AD to prevent to the International Branch, send it to ATTN:
fatigue damage on the clips, shear webs, and Sanjay Ralhan, Aerospace Engineer, BILLING CODE 4910–13–P
angles, which could affect the structural International Branch, ANM–116, Transport
integrity of the airplane. Airplane Directorate, FAA, 1601 Lind
Avenue SW., Renton, WA 98057–3356; DEPARTMENT OF TRANSPORTATION
(f) Compliance telephone 425–227–1405; fax 425–227–1149.
Comply with this AD within the Information may be emailed to: 9-ANM-116- Federal Aviation Administration
compliance times specified, unless already AMOC-REQUESTS@faa.gov. Before using
done. any approved AMOC, notify your appropriate 14 CFR Part 39
principal inspector, or lacking a principal
(g) Replacement
inspector, the manager of the local flight [Docket No. FAA–2015–1426; Directorate
At the later of the times specified in standards district office/certificate holding Identifier 2013–NM–200–AD; Amendment
paragraphs (g)(1) and (g)(2) of this AD: district office. The AMOC approval letter 39–18462; AD 2016–07–17]
Replace the clips, shear webs, and angles at must specifically reference this AD.
rear fuselage section 19, frame FR72 and (2) Contacting the Manufacturer: For any RIN 2120–AA64
FR74, and do all applicable related requirement in this AD to obtain corrective
investigative actions before further flight, in actions from a manufacturer, the action must Airworthiness Directives; Airbus
accordance with the Accomplishment be accomplished using a method approved
Instructions of Airbus Service Bulletin A320– Airplanes
by the Manager, International Branch, ANM–
53–1266, Revision 03, dated May 7, 2015. If 116, Transport Airplane Directorate, FAA; or AGENCY: Federal Aviation
any crack is found during any related the EASA; or Airbus’s EASA DOA. If
investigative action required by this AD:
Administration (FAA), Department of
approved by the DOA, the approval must
Before further flight, repair using a method Transportation (DOT).
include the DOA-authorized signature.
approved by the Manager, International ACTION: Final rule.
Branch, ANM–116, Transport Airplane (k) Related Information
Directorate, FAA; or the European Aviation (1) Refer to Mandatory Continuing SUMMARY: We are superseding
Safety Agency (EASA); or Airbus’s EASA Airworthiness Information (MCAI) EASA Airworthiness Directive (AD) 97–20–07
Design Organization Approval (DOA). Airworthiness Directive 2014–0177, dated for certain Airbus Model A300 B4–600,
(1) Before exceeding 48,000 flight cycles or July 25, 2014, for related information. This B4–600R, and F4–600R series airplanes,
96,000 flight hours, whichever occurs first MCAI may be found in the AD docket on the and Model A300 C4–605R Variant F
since the airplane’s first flight. Internet at http://www.regulations.gov by
(2) Within 30 days after the effective date airplanes (collectively called Model
searching for and locating Docket No. FAA–
of this AD. 2015–1277. A300–600 series airplanes). AD 97–20–
(2) Service information identified in this 07 required repetitive inspections to
(h) Additional Replacement for Certain detect fatigue cracking in the left and
AD that is not incorporated by reference is
Airplanes
available at the addresses specified in right wings in the area where the top
For airplanes on which the replacement of paragraphs (l)(3) and (l)(4) of this AD. skin attaches to the center spar, and
clips, shear webs, and angles specified in repair or modification of this area if
Airbus Service Bulletin A320–53–1266 is (l) Material Incorporated by Reference
necessary. This new AD reduces the
done before accumulating 30,000 flight (1) The Director of the Federal Register
cycles or 60,000 flight hours, whichever approved the incorporation by reference inspection compliance time and
occurred first since the airplane’s first flight: (IBR) of the service information listed in this repetitive inspection intervals. This AD
Within 30,000 flight cycles or 60,000 flight paragraph under 5 U.S.C. 552(a) and 1 CFR was prompted by a determination that
hours, whichever occurs first after that part 51. the inspection compliance time and
replacement, do the replacement specified in (2) You must use this service information repetitive inspection interval must be
paragraph (g) of this AD. as applicable to do the actions required by reduced to allow timely detection of
jstallworth on DSK7TPTVN1PROD with RULES

this AD, unless this AD specifies otherwise. fatigue cracking in the left and right
(i) Credit for Previous Actions (i) Airbus Service Bulletin A320–53–1266, wings in the area where the top skin
Except as required by paragraph (h) of this Revision 03, dated May 7, 2015.
AD: This paragraph provides credit for the (ii) Reserved. attaches to the center spar. We are
replacement required by paragraph (g) of this (3) For service information identified in issuing this AD to detect and correct
AD, if those actions were performed before this AD, contact Airbus, Airworthiness this fatigue cracking, which could
the effective date of this AD using the service Office—EIAS, 1 Rond Point Maurice reduce the residual strength of the top
information identified in paragraph (i)(1), Bellonte, 31707 Blagnac Cedex, France; skin of the wings, and consequently

VerDate Sep<11>2014 14:13 Apr 08, 2016 Jkt 238001 PO 00000 Frm 00024 Fmt 4700 Sfmt 4700 E:\FR\FM\11APR1.SGM 11APR1
Document Created: 2016-04-09 00:11:46
Document Modified: 2016-04-09 00:11:46
Category		Regulatory Information
Collection		Federal Register
sudoc Class		AE 2.7: GS 4.107: AE 2.106:
Publisher		Office of the Federal Register, National Archives and Records Administration
Section		Rules and Regulations
Action		Final rule.
Dates		This AD becomes effective May 16, 2016.
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.
FR Citation		81 FR 21244
RIN Number		2120-AA64
CFR Associated		Air Transportation; Aircraft; Aviation Safety; Incorporation by Reference and Safety
81 FR 21244 - Airworthiness Directives; Airbus Airplanes

DEPARTMENT OF TRANSPORTATIONFederal Aviation Administration

Federal Register Volume 81, Issue 69 (April 11, 2016)

DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
