Airworthiness Directives; Airbus Airplanes, 52267-52269 [2014-20937]
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Federal Register / Vol. 79, No. 170 / Wednesday, September 3, 2014 / Proposed Rules
emcdonald on DSK67QTVN1PROD with PROPOSALS
if those actions were performed before April
23, 2008 (the effective date of AD 2008–06–
18, Amendment 39–15430 (73 FR 14670,
March 19, 2008)), using the applicable
service information identified in paragraphs
(i)(1)(i) through (i)(1)(iv) of this AD, which
are not incorporated by reference by this AD.
(i) Airbus Service Bulletin A300–57–0177,
Revision 03, dated May 29, 2006.
(ii) Airbus Service Bulletin A300–57–0177,
Revision 04, dated January 5, 2007.
(iii) Airbus Service Bulletin A300–57–
6029, Revision 04, dated May 29, 2006.
(iv) Airbus Service Bulletin A300–57–
6029, Revision 05, dated October 23, 2006.
(2) This paragraph provides credit for
actions required by paragraph (g) or (h) of
this AD, if those actions were performed
before the effective date of this AD, using
Airbus Service Bulletin A300–57–6029,
Revision 07, dated June 6, 2011, which is not
incorporated by reference by 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:
Dan Rodina, Aerospace Engineer,
International Branch, ANM–116, Transport
Airplane Directorate, FAA, 1601 Lind
Avenue SW., Renton, WA 98057–3356;
telephone 425–227–2125; fax 425–227–1149.
Information may be emailed to: 9-ANM-116AMOC-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. AMOCs
approved previously for AD 2008–06–18,
Amendment 39–15430 (73 FR 14670, March
19, 2008) are considered acceptable for this
AD.
(2) Contacting the Manufacturer: For any
requirement in this AD to obtain corrective
actions from a manufacturer, the action must
be accomplished using a method approved
by the Manager, International Branch, ANM–
116, Transport Airplane Directorate, FAA; or
the European Aviation Safety Agency
(EASA); or Airbus’s EASA Design
Organization Approval (DOA). If approved by
the DOA, the approval must include the
DOA-authorized signature.
(3) Reporting Requirements: A federal
agency may not conduct or sponsor, and a
person is not required to respond to, nor
shall a person be subject to a penalty for
failure to comply with a collection of
information subject to the requirements of
the Paperwork Reduction Act unless that
collection of information displays a current
valid OMB Control Number. The OMB
Control Number for this information
collection is 2120–0056. Public reporting for
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Jkt 232001
this collection of information is estimated to
be approximately 5 minutes per response,
including the time for reviewing instructions,
completing and reviewing the collection of
information. All responses to this collection
of information are mandatory. Comments
concerning the accuracy of this burden and
suggestions for reducing the burden should
be directed to the FAA at: 800 Independence
Ave. SW., Washington, DC 20591, Attn:
Information Collection Clearance Officer,
AES–200.
(k) Related Information
(1) Refer to Mandatory Continuing
Airworthiness Information (MCAI) European
Aviation Safety Agency Airworthiness
Directive 2012–0203, dated October 1, 2012,
for related information. This MCAI may be
found in the AD docket on the Internet at
https://www.regulations.gov by searching for
and locating Docket No. FAA–2014–0618.
(2) For service information identified in
this AD, contact Airbus SAS Airworthiness
Office—EAW, 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 https://www.airbus.com.
You may view this service information at the
FAA, Transport Airplane Directorate, 1601
Lind Avenue SW., Renton, WA. For
information on the availability of this
material at the FAA, call 425–227–1221.
Issued in Renton, Washington, on August
23, 2014.
Michael Kaszycki,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. 2014–20917 Filed 9–2–14; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2014–0589; Directorate
Identifier 2014–NM–069–AD]
RIN 2120–AA64
Airworthiness Directives; Airbus
Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
We propose to adopt a new
airworthiness directive (AD) for certain
Airbus Model A318–111 and –112
airplanes, Model A319, A320, and A321
series airplanes. This proposed AD was
prompted by reports of cracks on the
forward corner fittings of engine pylon
aft secondary structures. This proposed
AD would require repetitive inspections
of certain forward corner fittings of the
pylon aft secondary structures, and
corrective actions if necessary. This
SUMMARY:
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52267
proposed AD also provides optional
terminating action for the repetitive
inspections. We are proposing this AD
to detect and correct detachment of the
lower fairing attachment and/or loss of
the aft fixed fairing with the movable
fairing from the airplane in flight, which
could result in damage to the airplane.
DATES: We must receive comments on
this proposed AD by October 20, 2014.
ADDRESSES: You may send comments,
using the procedures found in 14 CFR
11.43 and 11.45, by any of the following
methods:
• Federal eRulemaking Portal: Go to
https://www.regulations.gov. Follow the
instructions for submitting comments.
• Fax: 202–493–2251.
• Mail: U.S. Department of
Transportation, Docket Operations, M–
30, West Building Ground Floor, Room
W12–140, 1200 New Jersey Avenue SE.,
Washington, DC 20590.
• Hand Delivery: U.S. Department of
Transportation, Docket Operations, M–
30, West Building Ground Floor, Room
W12–140, 1200 New Jersey Avenue SE.,
Washington, DC, between 9 a.m. and 5
p.m., Monday through Friday, except
Federal holidays.
For service information identified in
this proposed AD, contact Airbus,
Airworthiness Office—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 https://www.airbus.com. You
may view this referenced service
information at the FAA, Transport
Airplane Directorate, 1601 Lind Avenue
SW., Renton, WA. For information on
the availability of this material at the
FAA, call 425–227–1221.
Examining the AD Docket
You may examine the AD docket on
the Internet at https://
www.regulations.gov by searching for
and locating Docket No. FAA–2014–
0589; or in person at the Docket
Management Facility between 9 a.m.
and 5 p.m., Monday through Friday,
except Federal holidays. The AD docket
contains this proposed AD, the
regulatory evaluation, any comments
received, and other information. The
street address for the Docket Operations
office (telephone 800–647–5527) is in
the ADDRESSES section. Comments will
be available in the AD docket shortly
after receipt.
FOR FURTHER INFORMATION CONTACT:
Sanjay Ralhan, Aerospace Engineer,
International Branch, ANM–116,
Transport Airplane Directorate, FAA,
1601 Lind Avenue SW., Renton, WA
98057–3356; telephone 425–227–1405;
fax 425–227–1149.
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52268
Federal Register / Vol. 79, No. 170 / Wednesday, September 3, 2014 / Proposed Rules
SUPPLEMENTARY INFORMATION:
Comments Invited
We invite you to send any written
relevant data, views, or arguments about
this proposed AD. Send your comments
to an address listed under the
ADDRESSES section. Include ‘‘Docket No.
FAA–2014–0589; Directorate Identifier
2014–NM–069–AD’’ at the beginning of
your comments. We specifically invite
comments on the overall regulatory,
economic, environmental, and energy
aspects of this proposed AD. We will
consider all comments received by the
closing date and may amend this
proposed AD based on those comments.
We will post all comments we
receive, without change, to https://
www.regulations.gov, including any
personal information you provide. We
will also post a report summarizing each
substantive verbal contact we receive
about this proposed AD.
emcdonald on DSK67QTVN1PROD with PROPOSALS
Discussion
The European Aviation Safety Agency
(EASA), which is the Technical Agent
for the Member States of the European
Community, has issued EASA
Airworthiness Directive 2014–0064,
dated March 14, 2014 (referred to after
this as the Mandatory Continuing
Airworthiness Information, or ‘‘the
MCAI’’), to correct an unsafe condition
for certain Model A318–111 and –112
airplanes, Model A319 series airplanes,
Model A320 series airplanes, and Model
A321 series airplanes. The MCAI states:
Several operators of A320 family
aeroplanes have reported finding cracks on
the forward corner fittings of engine pylon aft
secondary structures, on the lateral face
(lateral panel side). In some cases, these
cracks had propagated onto the forward face
(Rib 11 side). Investigation results have
highlighted that these cracks are initiated by
stress corrosion.
This condition, if not detected and
corrected, could lead to loss (i.e. detachment
from the aeroplane) of the lower fairing
attachment at Rib 10, and/or loss of the aft
fixed fairing with the movable fairing,
possibly resulting in * * * [damage to the
airplane].
For the reasons described above, this
[EASA] AD requires repetitive detailed
inspections (DI) of the right hand (RH) Part
Number (P/N) D54530014201 and left hand
(LH) P/N D54530014200 corner fittings of
engine pylon aft secondary structures (premod 38067 or pre-Airbus Service Bulletin
(SB) A320–54–1019) to detect cracks or
deformation in the splicing area with corner
fitting between Ribs 11–12 and, depending
on findings, replacement of the corner
fittings.
This [EASA] AD also recognizes that
replacement of the corner fittings with
improved parts (as per Airbus SB A320–54–
1019) constitutes a terminating action for the
repetitive DI required by this [EASA] AD.
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Jkt 232001
You may examine the MCAI in the
AD docket on the Internet at https://
www.regulations.gov by searching for
and locating Docket No. FAA–2014–
0589.
Relevant Service Information
Airbus has issued Service Bulletin
A320–54–1019, Revision 01, dated April
10, 2008; and Service Bulletin A320–
54–1022, Revision 02, dated July 12,
2013. The actions described in this
service information are intended to
correct the unsafe condition identified
in the MCAI.
FAA’s Determination and Requirements
of This Proposed AD
This product has been approved by
the aviation authority of another
country, and is approved for operation
in the United States. Pursuant to our
bilateral agreement with the State of
Design Authority, we have been notified
of the unsafe condition described in the
MCAI and service information
referenced above. We are proposing this
AD because we evaluated all pertinent
information and determined an unsafe
condition exists and is likely to exist or
develop on other products of these same
type designs.
Costs of Compliance
We estimate that this proposed AD
affects 851 airplanes of U.S. registry.
We also estimate that it would take
about 30 work-hours per product to
comply with the basic requirements of
this proposed AD. The average labor
rate is $85 per work-hour. Based on
these figures, we estimate the cost of
this proposed AD on U.S. operators to
be $2,170,050, or $2,550 per product.
In addition, we estimate the optional
terminating modification would take
about 60 work-hours and require parts
costing about $932 per product, for a
cost of $6,032 per product.
We have received no definitive data
that would enable us to provide cost
estimates for the on-condition actions
specified in this proposed AD.
According to the manufacturer, some
of the costs of this proposed 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
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detail the scope of the Agency’s
authority.
We are issuing this rulemaking under
the authority described in ‘‘Subtitle VII,
Part A, Subpart III, Section 44701:
General requirements.’’ Under that
section, Congress charges the FAA with
promoting safe flight of civil aircraft in
air commerce by prescribing regulations
for practices, methods, and procedures
the Administrator finds necessary for
safety in air commerce. This regulation
is within the scope of that authority
because it addresses an unsafe condition
that is likely to exist or develop on
products identified in this rulemaking
action.
Regulatory Findings
We determined that this proposed AD
would not have federalism implications
under Executive Order 13132. This
proposed AD would not have a
substantial direct effect on the States, on
the relationship between the national
Government and the States, or on the
distribution of power and
responsibilities among the various
levels of government.
For the reasons discussed above, I
certify this proposed regulation:
1. Is not a ‘‘significant regulatory
action’’ under Executive Order 12866;
2. Is not a ‘‘significant rule’’ under the
DOT Regulatory Policies and Procedures
(44 FR 11034, February 26, 1979);
3. Will not affect intrastate aviation in
Alaska; and
4. Will not have a significant
economic impact, positive or negative,
on a substantial number of small entities
under the criteria of the Regulatory
Flexibility Act.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation
safety, Incorporation by reference,
Safety.
The Proposed Amendment
Accordingly, under the authority
delegated to me by the Administrator,
the FAA proposes to amend 14 CFR part
39 as follows:
PART 39—AIRWORTHINESS
DIRECTIVES
1. The authority citation for part 39
continues to read as follows:
■
Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13
[Amended]
2. Amend § 39.13 by adding the
following new airworthiness directive
(AD):
■
Airbus: Docket No. FAA–2014–0589;
Directorate Identifier 2014–NM–069–AD.
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Federal Register / Vol. 79, No. 170 / Wednesday, September 3, 2014 / Proposed Rules
(a) Comments Due Date
We must receive comments by October 20,
2014.
(b) Affected ADs
None.
(c) Applicability
This AD applies to the Airbus airplanes
identified in paragraphs (c)(1) through (c)(4)
of this AD, certificated in any category,
except for airplanes on which Airbus
Modification 33844, or Modification 33847,
as applicable, has been embodied in
production.
(1) Airbus Model A318–111 and –112
airplanes.
(2) Airbus Model A319–111, –112, –113,
–114, –115, –131, –132, and –133 airplanes.
(3) Airbus Model A320–211, –212, –214,
–231, –232, and –233 airplanes.
(4) Airbus Model A321–111, –112, –131,
–211, –212, –213, –231, and –232 airplanes.
(d) Subject
Air Transport Association (ATA) of
America Code 54, Nacelles/pylons.
(e) Reason
This AD was prompted by reports of cracks
on the forward corner fittings of engine pylon
aft secondary structures. We are issuing this
AD to detect and correct detachment of the
lower fairing attachment and/or loss of the aft
fixed fairing with the movable fairing from
the airplane in flight, which could result in
damage to the airplane.
emcdonald on DSK67QTVN1PROD with PROPOSALS
(f) Compliance
Comply with this AD within the
compliance times specified, unless already
done.
(g) Repetitive Inspections
At the latest of the times specified in
paragraphs (g)(1), (g)(2), and (g)(3) of this AD:
Do a detailed inspection for cracking of
forward corner fittings having part number
(P/N) D54530014201 (right-hand (RH)) and
P/N D54530014200 (left-hand (LH)) of the
pylon aft secondary structures, in accordance
with the Accomplishment Instructions of
Airbus Service Bulletin A320–54–1022,
Revision 02, dated July 12, 2013, except as
provided by paragraph (j) of this AD. Repeat
the inspection thereafter at intervals not to
exceed 15,000 flight cycles or 22,500 flight
hours, whichever occurs first.
Accomplishment of the actions required by
paragraph (i) of this AD terminates the
actions required by this paragraph.
(1) Within 15,000 flight cycles or 22,500
flight hours, whichever occurs first since first
flight of the airplane.
(2) Within 5,000 flight cycles or 7,500
flight hours after the effective date of this AD,
without exceeding 40,750 flight cycles or
60,750 flight hours, whichever occurs first
since first flight of the airplane.
(3) Within 750 flight cycles or 750 flight
hours, whichever occurs first after the
effective date of this AD.
(h) Related Investigative and Corrective
Actions
If any crack is found on the corner fittings
of a pylon during any inspection required by
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16:15 Sep 02, 2014
Jkt 232001
paragraph (g) of this AD: Before further flight,
do a detailed inspection for cracking of the
lower and medium spars, in accordance with
the Accomplishment Instructions of Airbus
Service Bulletin A320–54–1022, Revision 02,
dated July 12, 2013.
(1) If any damage is found: 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).
(2) If no damage is found: Within 5,000
flight cycles or 7,500 flight hours, whichever
occurs first after the detailed inspection
specified in paragraph (h) of this AD, modify
the airplane, in accordance with the
Accomplishment Instructions of Service
Bulletin A320–54–1019, Revision 01, dated
April 10, 2008.
(i) Optional Terminating Action
Modification of an airplane by installation
of corner fittings having P/N
D0041092120000 RH and P/N
D0041092120100 LH on both pylons, in
accordance with the Accomplishment
Instructions of Airbus Service Bulletin A320–
54–1019, Revision 01, dated April 10, 2008,
constitutes terminating action for the
repetitive inspections required by paragraph
(g) of this AD.
(j) Parts Installation Exception
Airplanes on which Airbus Modification
38067 (installation of new corner fittings) has
been embodied in production, and airplanes
already modified in service as described in
Airbus Service Bulletin A320–54–1019, are
not affected by the requirements of paragraph
(g) of this AD, provided that no corner
fittings having P/N D54530014201 RH or
P/N D54530014200 LH have been installed
since first flight of the airplane, or since
modification, as applicable.
(k) Parts Installation Prohibition
(1) As of the effective date of this AD, for
airplanes on which Airbus Modification
38067 has been embodied in production on
both pylons, and for airplanes previously
modified in service as described in Airbus
Service Bulletin A320–54–1019: Do not
install any corner fittings having P/N
D54530014201 RH or P/N D54530014200 LH.
(2) After modification as required by
paragraph (h) of this AD, or after optional
modification as specified in paragraph (i) of
this AD, as applicable: Do not install any
corner fittings having P/N D54530014201 RH
or P/N D54530014200 LH.
(l) Credit for Previous Actions
This paragraph provides credit for actions
required by paragraphs (g) and (h) of this AD,
if those actions were performed before the
effective date of this AD using Airbus Service
Bulletin A320–54–1022, dated July 7, 2009;
or Airbus Service Bulletin A320–54–1022,
Revision 01, dated September 29, 2011;
which are not incorporated by reference in
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-116AMOC-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
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.
(n) Related Information
(1) Refer to Mandatory Continuing
Airworthiness Information (MCAI) EASA
Airworthiness Directive 2014–0064, dated
March 14, 2014, for related information. This
MCAI may be found in the AD docket on the
Internet at https://www.regulations.gov by
searching for and locating Docket No. FAA–
2014–0589.
(2) 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 https://www.airbus.com.
You may view this service information at the
FAA, Transport Airplane Directorate, 1601
Lind Avenue SW., Renton, WA. For
information on the availability of this
material at the FAA, call 425–227–1221.
Issued in Renton, Washington, on August
22, 2014.
Kevin Hull,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. 2014–20937 Filed 9–2–14; 8:45 am]
BILLING CODE 4910–13–P
(m) Other FAA AD Provisions
The following provisions also apply to this
AD:
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52269
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]]>Agencies
[Federal Register Volume 79, Number 170 (Wednesday, September 3, 2014)]
[Proposed Rules]
[Pages 52267-52269]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2014-20937]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2014-0589; Directorate Identifier 2014-NM-069-AD]
RIN 2120-AA64
Airworthiness Directives; Airbus Airplanes
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking (NPRM).
-----------------------------------------------------------------------
SUMMARY: We propose to adopt a new airworthiness directive (AD) for
certain Airbus Model A318-111 and -112 airplanes, Model A319, A320, and
A321 series airplanes. This proposed AD was prompted by reports of
cracks on the forward corner fittings of engine pylon aft secondary
structures. This proposed AD would require repetitive inspections of
certain forward corner fittings of the pylon aft secondary structures,
and corrective actions if necessary. This proposed AD also provides
optional terminating action for the repetitive inspections. We are
proposing this AD to detect and correct detachment of the lower fairing
attachment and/or loss of the aft fixed fairing with the movable
fairing from the airplane in flight, which could result in damage to
the airplane.
DATES: We must receive comments on this proposed AD by October 20,
2014.
ADDRESSES: You may send comments, using the procedures found in 14 CFR
11.43 and 11.45, by any of the following methods:
Federal eRulemaking Portal: Go to https://www.regulations.gov. Follow the instructions for submitting comments.
Fax: 202-493-2251.
Mail: U.S. Department of Transportation, Docket
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New
Jersey Avenue SE., Washington, DC 20590.
Hand Delivery: U.S. Department of Transportation, Docket
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New
Jersey Avenue SE., Washington, DC, between 9 a.m. and 5 p.m., Monday
through Friday, except Federal holidays.
For service information identified in this proposed AD, contact
Airbus, Airworthiness Office--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 https://www.airbus.com. You may view this referenced service information at the
FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA.
For information on the availability of this material at the FAA, call
425-227-1221.
Examining the AD Docket
You may examine the AD docket on the Internet at https://www.regulations.gov by searching for and locating Docket No. FAA-2014-
0589; or in person at the Docket Management Facility between 9 a.m. and
5 p.m., Monday through Friday, except Federal holidays. The AD docket
contains this proposed AD, the regulatory evaluation, any comments
received, and other information. The street address for the Docket
Operations office (telephone 800-647-5527) is in the ADDRESSES section.
Comments will be available in the AD docket shortly after receipt.
FOR FURTHER INFORMATION CONTACT: Sanjay Ralhan, Aerospace Engineer,
International Branch, ANM-116, Transport Airplane Directorate, FAA,
1601 Lind Avenue SW., Renton, WA 98057-3356; telephone 425-227-1405;
fax 425-227-1149.
[[Page 52268]]
SUPPLEMENTARY INFORMATION:
Comments Invited
We invite you to send any written relevant data, views, or
arguments about this proposed AD. Send your comments to an address
listed under the ADDRESSES section. Include ``Docket No. FAA-2014-0589;
Directorate Identifier 2014-NM-069-AD'' at the beginning of your
comments. We specifically invite comments on the overall regulatory,
economic, environmental, and energy aspects of this proposed AD. We
will consider all comments received by the closing date and may amend
this proposed AD based on those comments.
We will post all comments we receive, without change, to https://www.regulations.gov, including any personal information you provide. We
will also post a report summarizing each substantive verbal contact we
receive about this proposed AD.
Discussion
The European Aviation Safety Agency (EASA), which is the Technical
Agent for the Member States of the European Community, has issued EASA
Airworthiness Directive 2014-0064, dated March 14, 2014 (referred to
after this as the Mandatory Continuing Airworthiness Information, or
``the MCAI''), to correct an unsafe condition for certain Model A318-
111 and -112 airplanes, Model A319 series airplanes, Model A320 series
airplanes, and Model A321 series airplanes. The MCAI states:
Several operators of A320 family aeroplanes have reported
finding cracks on the forward corner fittings of engine pylon aft
secondary structures, on the lateral face (lateral panel side). In
some cases, these cracks had propagated onto the forward face (Rib
11 side). Investigation results have highlighted that these cracks
are initiated by stress corrosion.
This condition, if not detected and corrected, could lead to
loss (i.e. detachment from the aeroplane) of the lower fairing
attachment at Rib 10, and/or loss of the aft fixed fairing with the
movable fairing, possibly resulting in * * * [damage to the
airplane].
For the reasons described above, this [EASA] AD requires
repetitive detailed inspections (DI) of the right hand (RH) Part
Number (P/N) D54530014201 and left hand (LH) P/N D54530014200 corner
fittings of engine pylon aft secondary structures (pre-mod 38067 or
pre-Airbus Service Bulletin (SB) A320-54-1019) to detect cracks or
deformation in the splicing area with corner fitting between Ribs
11-12 and, depending on findings, replacement of the corner
fittings.
This [EASA] AD also recognizes that replacement of the corner
fittings with improved parts (as per Airbus SB A320-54-1019)
constitutes a terminating action for the repetitive DI required by
this [EASA] AD.
You may examine the MCAI in the AD docket on the Internet at https://www.regulations.gov by searching for and locating Docket No. FAA-2014-
0589.
Relevant Service Information
Airbus has issued Service Bulletin A320-54-1019, Revision 01, dated
April 10, 2008; and Service Bulletin A320-54-1022, Revision 02, dated
July 12, 2013. The actions described in this service information are
intended to correct the unsafe condition identified in the MCAI.
FAA's Determination and Requirements of This Proposed AD
This product has been approved by the aviation authority of another
country, and is approved for operation in the United States. Pursuant
to our bilateral agreement with the State of Design Authority, we have
been notified of the unsafe condition described in the MCAI and service
information referenced above. We are proposing this AD because we
evaluated all pertinent information and determined an unsafe condition
exists and is likely to exist or develop on other products of these
same type designs.
Costs of Compliance
We estimate that this proposed AD affects 851 airplanes of U.S.
registry.
We also estimate that it would take about 30 work-hours per product
to comply with the basic requirements of this proposed AD. The average
labor rate is $85 per work-hour. Based on these figures, we estimate
the cost of this proposed AD on U.S. operators to be $2,170,050, or
$2,550 per product.
In addition, we estimate the optional terminating modification
would take about 60 work-hours and require parts costing about $932 per
product, for a cost of $6,032 per product.
We have received no definitive data that would enable us to provide
cost estimates for the on-condition actions specified in this proposed
AD.
According to the manufacturer, some of the costs of this proposed
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 proposed AD would not have federalism
implications under Executive Order 13132. This proposed AD would not
have a substantial direct effect on the States, on the relationship
between the national Government and the States, or on the distribution
of power and responsibilities among the various levels of government.
For the reasons discussed above, I certify this proposed
regulation:
1. Is not a ``significant regulatory action'' under Executive Order
12866;
2. Is not a ``significant rule'' under the DOT Regulatory Policies
and Procedures (44 FR 11034, February 26, 1979);
3. Will not affect intrastate aviation in Alaska; and
4. Will not have a significant economic impact, positive or
negative, on a substantial number of small entities under the criteria
of the Regulatory Flexibility Act.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.
The Proposed Amendment
Accordingly, under the authority delegated to me by the
Administrator, the FAA proposes to amend 14 CFR part 39 as follows:
PART 39--AIRWORTHINESS DIRECTIVES
0
1. The authority citation for part 39 continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
Sec. 39.13 [Amended]
0
2. Amend Sec. 39.13 by adding the following new airworthiness
directive (AD):
Airbus: Docket No. FAA-2014-0589; Directorate Identifier 2014-NM-
069-AD.
[[Page 52269]]
(a) Comments Due Date
We must receive comments by October 20, 2014.
(b) Affected ADs
None.
(c) Applicability
This AD applies to the Airbus airplanes identified in paragraphs
(c)(1) through (c)(4) of this AD, certificated in any category,
except for airplanes on which Airbus Modification 33844, or
Modification 33847, as applicable, has been embodied in production.
(1) Airbus Model A318-111 and -112 airplanes.
(2) Airbus Model A319-111, -112, -113, -114, -115, -131, -132,
and -133 airplanes.
(3) Airbus Model A320-211, -212, -214, -231, -232, and -233
airplanes.
(4) Airbus Model A321-111, -112, -131, -211, -212, -213, -231,
and -232 airplanes.
(d) Subject
Air Transport Association (ATA) of America Code 54, Nacelles/
pylons.
(e) Reason
This AD was prompted by reports of cracks on the forward corner
fittings of engine pylon aft secondary structures. We are issuing
this AD to detect and correct detachment of the lower fairing
attachment and/or loss of the aft fixed fairing with the movable
fairing from the airplane in flight, which could result in damage to
the airplane.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(g) Repetitive Inspections
At the latest of the times specified in paragraphs (g)(1),
(g)(2), and (g)(3) of this AD: Do a detailed inspection for cracking
of forward corner fittings having part number (P/N) D54530014201
(right-hand (RH)) and P/N D54530014200 (left-hand (LH)) of the pylon
aft secondary structures, in accordance with the Accomplishment
Instructions of Airbus Service Bulletin A320-54-1022, Revision 02,
dated July 12, 2013, except as provided by paragraph (j) of this AD.
Repeat the inspection thereafter at intervals not to exceed 15,000
flight cycles or 22,500 flight hours, whichever occurs first.
Accomplishment of the actions required by paragraph (i) of this AD
terminates the actions required by this paragraph.
(1) Within 15,000 flight cycles or 22,500 flight hours,
whichever occurs first since first flight of the airplane.
(2) Within 5,000 flight cycles or 7,500 flight hours after the
effective date of this AD, without exceeding 40,750 flight cycles or
60,750 flight hours, whichever occurs first since first flight of
the airplane.
(3) Within 750 flight cycles or 750 flight hours, whichever
occurs first after the effective date of this AD.
(h) Related Investigative and Corrective Actions
If any crack is found on the corner fittings of a pylon during
any inspection required by paragraph (g) of this AD: Before further
flight, do a detailed inspection for cracking of the lower and
medium spars, in accordance with the Accomplishment Instructions of
Airbus Service Bulletin A320-54-1022, Revision 02, dated July 12,
2013.
(1) If any damage is found: 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).
(2) If no damage is found: Within 5,000 flight cycles or 7,500
flight hours, whichever occurs first after the detailed inspection
specified in paragraph (h) of this AD, modify the airplane, in
accordance with the Accomplishment Instructions of Service Bulletin
A320-54-1019, Revision 01, dated April 10, 2008.
(i) Optional Terminating Action
Modification of an airplane by installation of corner fittings
having P/N D0041092120000 RH and P/N D0041092120100 LH on both
pylons, in accordance with the Accomplishment Instructions of Airbus
Service Bulletin A320-54-1019, Revision 01, dated April 10, 2008,
constitutes terminating action for the repetitive inspections
required by paragraph (g) of this AD.
(j) Parts Installation Exception
Airplanes on which Airbus Modification 38067 (installation of
new corner fittings) has been embodied in production, and airplanes
already modified in service as described in Airbus Service Bulletin
A320-54-1019, are not affected by the requirements of paragraph (g)
of this AD, provided that no corner fittings having P/N D54530014201
RH or P/N D54530014200 LH have been installed since first flight of
the airplane, or since modification, as applicable.
(k) Parts Installation Prohibition
(1) As of the effective date of this AD, for airplanes on which
Airbus Modification 38067 has been embodied in production on both
pylons, and for airplanes previously modified in service as
described in Airbus Service Bulletin A320-54-1019: Do not install
any corner fittings having P/N D54530014201 RH or P/N D54530014200
LH.
(2) After modification as required by paragraph (h) of this AD,
or after optional modification as specified in paragraph (i) of this
AD, as applicable: Do not install any corner fittings having P/N
D54530014201 RH or P/N D54530014200 LH.
(l) Credit for Previous Actions
This paragraph provides credit for actions required by
paragraphs (g) and (h) of this AD, if those actions were performed
before the effective date of this AD using Airbus Service Bulletin
A320-54-1022, dated July 7, 2009; or Airbus Service Bulletin A320-
54-1022, Revision 01, dated September 29, 2011; which are not
incorporated by reference in this AD.
(m) 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 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.
(n) Related Information
(1) Refer to Mandatory Continuing Airworthiness Information
(MCAI) EASA Airworthiness Directive 2014-0064, dated March 14, 2014,
for related information. This MCAI may be found in the AD docket on
the Internet at https://www.regulations.gov by searching for and
locating Docket No. FAA-2014-0589.
(2) 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 https://www.airbus.com. You may view this service information at the FAA,
Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA.
For information on the availability of this material at the FAA,
call 425-227-1221.
Issued in Renton, Washington, on August 22, 2014.
Kevin Hull,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2014-20937 Filed 9-2-14; 8:45 am]
BILLING CODE 4910-13-P
