Airworthiness Directives; Airbus Airplanes, 52263-52267 [2014-20917]
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Federal Register / Vol. 79, No. 170 / Wednesday, September 3, 2014 / Proposed Rules
(j) Other FAA AD Provisions
DEPARTMENT OF TRANSPORTATION
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:
Todd Thompson, Aerospace Engineer,
International Branch, ANM–116, Transport
Airplane Directorate, FAA, 1601 Lind
Avenue SW., Renton, WA 98057–3356;
telephone 425–227–1175; 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 BAE Systems (Operations)
Limited’s EASA Design Organization
Approval (DOA). If approved by the DOA,
the approval must include the DOAauthorized signature.
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(k) Related Information
(1) Refer to Mandatory Continuing
Airworthiness Information (MCAI) EASA
Airworthiness Directive 2013–0207, dated
September 9, 2013, 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–2014–0621.
(2) For service information identified in
this AD, contact BAE Systems (Operations)
Limited, Customer Information Department,
Prestwick International Airport, Ayrshire,
KA9 2RW, Scotland, United Kingdom;
telephone +44 1292 675207; fax +44 1292
675704; email RApublications@
baesystems.com; Internet https://
www.baesystems.com/Businesses/
RegionalAircraft/index.htm. 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.
Issued in Renton, Washington, on August
25, 2014.
Michael Kaszycki,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. 2014–20943 Filed 9–2–14; 8:45 am]
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Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2014–0618; Directorate
Identifier 2012–NM–171–AD]
RIN 2120–AA64
Airworthiness Directives; Airbus
Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
We propose to supersede
Airworthiness Directive (AD) 2008–06–
18, for all Airbus Model A300 B4–600,
B4–600R, and F4–600R series airplanes,
and Model A300 C4–605R Variant F
airplanes (collectively called Model
A300–600 series airplanes) and Model
A300 series airplanes. AD 2008–06–18
currently requires repetitive inspections
for any cracking of the wing lower skin
panel and associated internal support
structure, and if necessary, corrective
actions such as modifying the lower
panel inboard of rib 9 aft of the rear spar
and repairing cracks. Since we issued
AD 2008–06–18, we have received a
report that information from an analysis
and fleet survey show a need for
reduced compliance times and intervals.
This proposed AD would continue to
require the existing requirements, and
would reduce some compliance times.
We are proposing this AD to detect and
correct cracking, which could lead to
reduced structural integrity of the
airplane.
SUMMARY:
We must receive comments on
this proposed AD by October 20, 2014.
ADDRESSES: You may send comments 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 SAS
Airworthiness Office—EAW, 1 Rond
Point Maurice Bellonte, 31707 Blagnac
Cedex, France; telephone +33 5 61 93 36
DATES:
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52263
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; or in person at the
Docket Operations office 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: 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.
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–2014–0618; Directorate Identifier
2012–NM–171–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
On March 7, 2008, we issued AD
2008–06–18, Amendment 39–15430 (73
FR 14670, March 19, 2008). AD 2008–
06–18 requires actions intended to
address an unsafe condition on all
Airbus Model A300 B4–600, B4–600R,
and F4–600R series airplanes, and
Model A300 C4–605R Variant F
airplanes (collectively called Model
A300–600 series airplanes) and Model
A300 series airplanes.
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Since we issued AD 2008–06–18,
Amendment 39–15430 (73 FR 14670,
March 19, 2008), we have received a
report that information from an analysis
and fleet survey show a need for
reduced compliance times and intervals.
The European Aviation Safety Agency
(EASA), which is the Technical Agent
for the Member States of the European
Community, has issued EASA
Airworthiness Directive 2012–0203,
dated October 1, 2012 (referred to after
this as the Mandatory Continuing
Airworthiness Information, or ‘‘the
MCAI’’), to correct an unsafe condition
for all Airbus Model A300 B4–600, B4–
600R, and F4–600R series airplanes, and
Model A300 C4–605R Variant F
airplanes (collectively called Model
A300–600 series airplanes) and Model
A300 series airplanes. The MCAI states:
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During routine maintenance, cracks were
found in the wing bottom skin and in the
associated internal support structure on an
A300 aeroplane aft of the rear spar and
inboard of rib 9. Initially, cracks were found
in the skin only, starting from a fastener close
to the forward outboard corner of access
panel 575FB/675FB. Subsequently, cases
were reported of cracks being found in the
skin support strap and the stiffener.
This condition, if not detected and
corrected, could affect the structural integrity
of the aeroplane.
To address this unsafe condition, EASA
issued AD 2006–0282 [https://
ad.easa.europa.eu/ad/2006-0282] [which
corresponds with FAA AD 2008–06–18,
Amendment 39–15430 (73 FR 14670, March
19, 2008)] to require repetitive inspections of
the wing lower skin panel and associated
internal support structure aft of the rear spar
and inboard of rib 9.
Since that [EASA] AD was issued, the
results of a fleet survey and updated Fatigue
and Damage Tolerance analysis, which were
performed in order to substantiate the second
A300 and A300–600 Extended Service Goal
(ESG2) exercise, revealed that the inspection
threshold and interval had to be reduced to
allow timely detection of cracks and the
accomplishment of an applicable corrective
action.
Prompted by these findings, Airbus issued
Revision 05 of Airbus Service Bulletin (SB)
A300–57–0177 and Revision 07 of Airbus SB
A300–57–6029.
For the reasons described above, this
[EASA] AD retains the requirements of EASA
AD 2006–0282, which is superseded, but
requires the accomplishment of those actions
within reduced thresholds and intervals.
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–
0618.
Relevant Service Information
Airbus has issued Service Bulletin
A300–57–6029, Revision 08, dated April
25, 2013. The compliance times for the
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initial inspections range approximately
from 160 flight cycles or 270 flight
hours, whichever occurs first, to 49,300
flight cycles or 98,700 flight hours,
whichever occurs first, depending on
the model and configuration. The
repetitive intervals range from 30 flight
cycles or 40 flight hours, whichever
occurs first, to 3,800 flight cycles or
7,700 flight hours, whichever occurs
first, depending on the model and
configuration. 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 the same
type design.
Changes to AD 2008–06–18,
Amendment 39–15430 (73 FR 14670,
March 19, 2008)
This proposed AD would retain all
requirements of AD 2008–06–18,
Amendment 39–15430 (73 FR 14670,
March 19, 2008). Since AD 2008–06–18
was issued, the AD format has been
revised, and certain paragraphs have
been rearranged. As a result, the
corresponding paragraph identifiers
have changed in this proposed AD, as
listed in the following table:
REVISED PARAGRAPH IDENTIFIERS
Requirement in
AD 2008–06–18,
Amendment 39–
15430 (73 FR 14670,
March 19, 2008
Corresponding
requirement in this
proposed AD
paragraph (f)
paragraph (g)
Paragraph (f)(3) of AD 2008–06–18,
Amendment 39–15430 (73 FR 14670,
March 19, 2008), contains a
typographical error. That error resulted
in a reference to paragraph ‘‘(e)(f)(ii)’’ of
AD 2008–06–18. The correct reference is
to paragraph (f)(3)(ii) of AD 2008–06–18.
Since the AD format has been revised
and certain paragraphs have been
rearranged, the reference is now to
paragraph (g)(3)(ii) of the proposed AD.
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‘‘Contacting the Manufacturer’’
Paragraph in This Proposed AD
Since late 2006, we have included a
standard paragraph titled ‘‘Airworthy
Product’’ in all MCAI ADs in which the
FAA develops an AD based on a foreign
authority’s AD.
The MCAI or referenced service
information in an FAA AD often directs
the owner/operator to contact the
manufacturer for corrective actions,
such as a repair. Briefly, the Airworthy
Product paragraph allowed owners/
operators to use corrective actions
provided by the manufacturer if those
actions were FAA-approved. In
addition, the paragraph stated that any
actions approved by the State of Design
Authority (or its delegated agent) are
considered to be FAA-approved.
In an NPRM having Directorate
Identifier 2012–NM–101–AD (78 FR
78285, December 26, 2013), we
proposed to prevent the use of repairs
that were not specifically developed to
correct the unsafe condition, by
requiring that the repair approval
provided by the State of Design
Authority or its delegated agent
specifically refer to the FAA AD. This
change was intended to clarify the
method of compliance and to provide
operators with better visibility of repairs
that are specifically developed and
approved to correct the unsafe
condition. In addition, we proposed to
change the phrase ‘‘its delegated agent’’
to include a design approval holder
(DAH) with State of Design Authority
design organization approval (DOA), as
applicable, to refer to a DAH authorized
to approve required repairs for the
proposed AD.
One commenter to the NPRM having
Directorate Identifier 2012–NM–101–AD
(78 FR 78285, December 26, 2013) stated
the following: ‘‘The proposed wording,
being specific to repairs, eliminates the
interpretation that Airbus messages are
acceptable for approving minor
deviations (corrective actions) needed
during accomplishment of an AD
mandated Airbus service bulletin.’’
This comment has made the FAA
aware that some operators have
misunderstood or misinterpreted the
Airworthy Product paragraph to allow
the owner/operator to use messages
provided by the manufacturer as
approval of deviations during the
accomplishment of an AD-mandated
action. The Airworthy Product
paragraph does not approve messages or
other information provided by the
manufacturer for deviations to the
requirements of the AD-mandated
actions. The Airworthy Product
paragraph only addresses the
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requirement to contact the manufacturer
for corrective actions for the identified
unsafe condition and does not cover
deviations from other AD requirements.
However, deviations to AD-required
actions are addressed in 14 CFR 39.17,
and anyone may request the approval
for an alternative method of compliance
to the AD-required actions using the
procedures found in 14 CFR 39.19.
To address this misunderstanding and
misinterpretation of the Airworthy
Product paragraph, we have changed the
paragraph and retitled it ‘‘Contacting the
Manufacturer.’’ This paragraph now
clarifies that for any requirement in this
proposed AD to obtain corrective
actions from a manufacturer, the actions
must be accomplished using a method
approved by the FAA, the European
Aviation Safety Agency (EASA), or
Airbus’s EASA DOA.
The Contacting the Manufacturer
paragraph also clarifies that, if approved
by the DOA, the approval must include
the DOA-authorized signature. The DOA
signature indicates that the data and
information contained in the document
are EASA-approved, which is also FAAapproved. Messages and other
information provided by the
manufacturer that do not contain the
DOA-authorized signature approval are
not EASA-approved, unless EASA
directly approves the manufacturer’s
message or other information.
This clarification does not remove
flexibility previously afforded by the
Airworthy Product paragraph.
Consistent with long-standing FAA
policy, such flexibility was never
intended for required actions. This is
also consistent with the
recommendation of the Airworthiness
Directive Implementation Aviation
Rulemaking Committee to increase
flexibility in complying with ADs by
identifying those actions in
manufacturers’ service instructions that
are ‘‘Required for Compliance’’ with
ADs. We continue to work with
manufacturers to implement this
recommendation. But once we
determine that an action is required, any
deviation from the requirement must be
approved as an alternative method of
compliance.
We also have decided not to include
a generic reference to either the
‘‘delegated agent’’ or ‘‘design approval
holder (DAH) with State of Design
Authority design organization
approval,’’ but instead we have
provided the specific delegation
approval granted by the State of Design
Authority for the DAH throughout this
proposed AD.
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Costs of Compliance
We estimate that this proposed AD
affects 162 airplanes of U.S. registry.
The actions that are required by AD
2008–06–18, Amendment 39–15430 (73
FR 14670, March 19, 2008), and retained
in this proposed AD take about 2 workhours 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 2008–
06–18 is $170 per product.
We also estimate that it would take
about 2 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 $27,540, or $170 per product.
In addition, we estimate that any
necessary follow-on actions would take
about 12 work-hours and require parts
costing $10,000, for a cost of $11,020
per product. We have no way of
determining the number of aircraft that
might need these actions.
Paperwork Reduction Act
A federal agency may not conduct or
sponsor, and a person is not required to
respond to, nor shall a person be subject
to 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 control
number for the collection of information
required by this AD is 2120–0056. The
paperwork cost associated with this AD
has been detailed in the Costs of
Compliance section of this document
and includes time for reviewing
instructions, as well as completing and
reviewing the collection of information.
Therefore, all reporting associated with
this AD is 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.
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.
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
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§ 39.13
[Amended]
2. The FAA amends § 39.13 by
removing Airworthiness Directive (AD)
2008–06–18, Amendment 39–15430 (73
FR 14670, March 19, 2008), and adding
the following new AD:
■
Airbus: Docket No. FAA–2014–0618;
Directorate Identifier 2012–NM–171–AD.
(a) Comments Due Date
We must receive comments by October 20,
2014.
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(b) Affected ADs
This AD replaces AD 2008–06–18,
Amendment 39–15430 (73 FR 14670, March
19, 2008).
(c) Applicability
This AD applies to the airplanes identified
in paragraphs (c)(1) through (c)(5) of this AD,
certificated in any category, all certified
models, all serial numbers.
(1) Airbus Model A300 B2–1A, B2–1C,
B2K–3C, B2–203, B4–2C, B4–103, and B4–
203 airplanes.
(2) Airbus Model A300 B4–601, B4–603,
B4–620, and B4–622 airplanes.
(3) Airbus Model A300 B4–605R and B4–
622R airplanes.
(4) Airbus Model A300 F4–605R and F4–
622R airplanes.
(5) Airbus Model A300 C4–605R Variant F
airplanes.
(d) Subject
Air Transport Association (ATA) of
America Code 57, Wings.
(e) Reason
This AD was prompted by a report that
information from an analysis and fleet survey
show a need for reduced compliance times
and intervals. We are issuing this AD to
detect and correct cracking, which could lead
to reduced structural integrity of the airplane.
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(f) Compliance
You are responsible for having the actions
required by this AD performed within the
compliance times specified, unless the
actions have already been done.
(g) Retained Actions and Compliance Times
With Revised Service Information
This paragraph restates the requirements of
paragraph (f) of AD 2008–06–18, Amendment
39–15430 (73 FR 14670, March 19, 2008),
with revised service information. Unless
already done, do the following actions.
(1) Except as provided by paragraphs
(g)(1)(i), (g)(1)(ii), (g)(1)(iii), (g)(1)(iv), and (h)
of this AD: At the threshold specified in
paragraph 1.E.(2) of Airbus Service Bulletin
A300–57–0177, Revision 05, dated March 23,
2007 (for Model A300 series airplanes);
Airbus Service Bulletin A300–57–6029,
Revision 06, dated March 23, 2007 (for Model
A300–600 series airplanes); or Airbus Service
Bulletin A300–57–6029, Revision 08, dated
April 25, 2013 (for Model A300–600 series
airplanes); as applicable; perform the
inspection of the wing lower skin panel and
associated internal support structure aft of
the rear spar and inboard of rib 9 and apply
applicable corrective measures in accordance
with Airbus Service Bulletin A300–57–0177,
Revision 05, dated March 23, 2007 (for Model
A300 series airplanes); or Airbus Service
Bulletin A300–57–6029, Revision 06, dated
March 23, 2007 (for Model A300–600 series
airplanes); or Airbus Service Bulletin A300–
57–6029, Revision 08, dated April 25, 2013
(for Model A300–600 series airplanes); as
applicable. All applicable corrective
measures must be done at the applicable
times specified in paragraph 1.E.(2) and the
Accomplishment Instructions of Airbus
Service Bulletin A300–57–0177, Revision 05,
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dated March 23, 2007 (for Model A300 series
airplanes); Airbus Service Bulletin A300–57–
6029, Revision 06, dated March 23, 2007 (for
Model A300–600 series airplanes); or Airbus
Service Bulletin A300–57–6029, Revision 08,
dated April 25, 2013 (for Model A300–600
series airplanes); as applicable.
Accomplishing the requirements of
paragraph (h) of this AD terminates the
requirements of this paragraph for Model
A300–600 airplanes.
(i) Where the tables in paragraph 1.E.(2),
‘‘Accomplishment Timescale,’’ of Airbus
Service Bulletin A300–57–0177, Revision 05,
dated March 23, 2007; A300–57–6029,
Revision 06, dated March 23, 2007; specify
a grace period for doing the actions, this AD
requires that the actions be done within the
specified grace period relative to April 23,
2008 (the effective date of AD 2008–06–18,
Amendment 39–15430 (73 FR 14670, March
19, 2008)).
(ii) Where the tables in paragraph
1.E.(2)(e), ‘‘Config 04,’’ of Airbus Service
Bulletin A300–57–0177, Revision 05, dated
March 23, 2007, specify an inspection
interval but not an initial threshold, this AD
requires that the actions be done within the
specified interval after inspecting in
accordance with Table 1A or 1B, as
applicable, for Configuration 01 airplanes
described in the service bulletin and
thereafter at the inspection interval specified
in the tables in paragraph 1.E.(2)(e), ‘‘Config
04,’’ of Airbus Service Bulletin A300–57–
0177, Revision 05, dated March 23, 2007.
(iii) Where the tables in paragraph
1.E.(2)(f), ‘‘Config 05,’’ of Airbus Service
Bulletin A300–57–6029, Revision 06, dated
March 23, 2007, specify an inspection
interval but not an initial threshold, this AD
requires that the actions be done within the
specified interval after inspecting in
accordance with Table 1A, or 1B, as
applicable, for configuration 01 of Airbus
Service Bulletin A300–57–6029, Revision 06,
dated March 23, 2007, and thereafter at the
inspection interval specified in the tables in
paragraph 1.E.(2)(f), ‘‘Config 05,’’ of Airbus
Service Bulletin A300–57–6029, Revision 06,
dated March 23, 2007.
(iv) All crack lengths specified in Airbus
Service Bulletin A300–57–0177, Revision 05,
dated March 23, 2007; and A300–57–6029,
Revision 06, dated March 23, 2007, are
considered ‘‘not to exceed’’ lengths.
(2) Repeat the inspection at the intervals
in, and according to the instructions defined
in, Airbus Service Bulletin A300–57–0177,
Revision 05, dated March 23, 2007 (for Model
A300 series airplanes); Airbus Service
Bulletin A300–57–6029, Revision 06, dated
March 23, 2007 (for Model A300–600 series
airplanes); or Airbus Service Bulletin A300–
57–6029, Revision 08, dated April 25, 2013
(for Model A300–600 series airplanes); as
applicable; except where Airbus Service
Bulletin A300–57–0177, Revision 05, dated
March 23, 2007, specifies repetitive
inspections for cracking if Airbus Service
Bulletin A300–57–022 has not been
embodied, this AD requires doing repetitive
inspections for cracking if Airbus Service
Bulletin A300–57–0222 (modification
11178H5410) has not been embodied.
(3) Report to Airbus the first inspection
results, whatever they may be, at the
PO 00000
Frm 00028
Fmt 4702
Sfmt 4702
applicable time specified in paragraph
(g)(3)(i) or (g)(3)(ii) of this AD.
(i) If the inspection was done after April
23, 2008 (the effective date of AD 2008–06–
18, Amendment 39–15430 (73 FR 14670,
March 19, 2008)), submit the report within 30
days after the inspection.
(ii) If the inspection was accomplished
prior to April 23, 2008 (the effective date of
AD 2008–06–18, Amendment 39–15430 (73
FR 14670, March 19, 2008)), submit the
report within 30 days after April 23, 2008.
(h) New Requirement of This AD: New
Compliance Times for Model A300–600
Airplanes
For Model A300–600 airplanes, do the
actions specified in paragraphs (h)(1) through
(h)(3) of this AD at the applicable times
specified in those paragraphs.
(1) Except as provided by paragraphs
(h)(1)(i) and (h)(1)(ii) of this AD: Within the
compliance times specified in Airbus Service
Bulletin A300–57–6029, Revision 08, dated
April 25, 2013, perform the inspection of the
wing lower skin panels and associated
internal support structures aft of the rear spar
and inboard of rib 9, in accordance with the
Accomplishment Instructions of Airbus
Service Bulletin A300–57–6029, Revision 08,
dated April 25, 2013. Thereafter, repeat these
inspections at intervals specified in Airbus
Service Bulletin A300–57–6029, Revision 08,
dated April 25, 2013. Accomplishment of the
actions required by this paragraph terminates
the requirements of paragraph (g) of this AD
for Model A300–600 airplanes.
(i) Where the tables in paragraph 1.E.(2),
‘‘Accomplishment Timescale,’’ of Airbus
Service Bulletin A300–57–6029, Revision 08,
dated April 25, 2013, specify a grace period
for doing the actions for airplanes that have
exceeded the thresholds, this AD requires, for
all airplanes, that the actions be done within
the specified grace period after the effective
date of this AD or before the specified
thresholds, whichever occurs later.
(ii) Where Airbus Service Bulletin A300–
57–6029, Revision 08, dated April 25, 2013,
specifies to ‘‘contact Airbus’’ before further
flight, this AD requires repairing using a
method approved by the Manager,
International Branch, ANM–116, Transport
Airplane Directorate, FAA; or European
Aviation Safety Agency (EASA); or Airbus’s
EASA Design Organization Approval (DOA);
and accomplishing those actions before
further flight. If approved by the DOA, the
approval must include the DOA-authorized
signature.
(2) If, during any inspection as required by
paragraph (h)(1) of this AD, discrepancies are
detected, before next flight, accomplish the
applicable corrective actions, in accordance
with the Accomplishment Instructions of
Airbus Service Bulletin A300–57–6029,
Revision 08, dated April 25, 2013.
(3) Corrective actions, as required by
paragraph (h)(2) of this AD, do not constitute
terminating action for the repetitive
inspection requirements of paragraph (h)(1)
of this AD.
(i) Credit for Previous Actions
(1) This paragraph provides credit for
actions required by paragraph (g) of this AD,
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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
VerDate Mar<15>2010
16:15 Sep 02, 2014
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:
PO 00000
Frm 00029
Fmt 4702
Sfmt 4702
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.
E:\FR\FM\03SEP1.SGM
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]]>Agencies
[Federal Register Volume 79, Number 170 (Wednesday, September 3, 2014)]
[Proposed Rules]
[Pages 52263-52267]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2014-20917]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2014-0618; Directorate Identifier 2012-NM-171-AD]
RIN 2120-AA64
Airworthiness Directives; Airbus Airplanes
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking (NPRM).
-----------------------------------------------------------------------
SUMMARY: We propose to supersede Airworthiness Directive (AD) 2008-06-
18, for all Airbus Model A300 B4-600, B4-600R, and F4-600R series
airplanes, and Model A300 C4-605R Variant F airplanes (collectively
called Model A300-600 series airplanes) and Model A300 series
airplanes. AD 2008-06-18 currently requires repetitive inspections for
any cracking of the wing lower skin panel and associated internal
support structure, and if necessary, corrective actions such as
modifying the lower panel inboard of rib 9 aft of the rear spar and
repairing cracks. Since we issued AD 2008-06-18, we have received a
report that information from an analysis and fleet survey show a need
for reduced compliance times and intervals. This proposed AD would
continue to require the existing requirements, and would reduce some
compliance times. We are proposing this AD to detect and correct
cracking, which could lead to reduced structural integrity of the
airplane.
DATES: We must receive comments on this proposed AD by October 20,
2014.
ADDRESSES: You may send comments 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 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 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; or in person at the Docket Operations office
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: 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.
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-2014-0618;
Directorate Identifier 2012-NM-171-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
On March 7, 2008, we issued AD 2008-06-18, Amendment 39-15430 (73
FR 14670, March 19, 2008). AD 2008-06-18 requires actions intended to
address an unsafe condition on all Airbus Model A300 B4-600, B4-600R,
and F4-600R series airplanes, and Model A300 C4-605R Variant F
airplanes (collectively called Model A300-600 series airplanes) and
Model A300 series airplanes.
[[Page 52264]]
Since we issued AD 2008-06-18, Amendment 39-15430 (73 FR 14670,
March 19, 2008), we have received a report that information from an
analysis and fleet survey show a need for reduced compliance times and
intervals.
The European Aviation Safety Agency (EASA), which is the Technical
Agent for the Member States of the European Community, has issued EASA
Airworthiness Directive 2012-0203, dated October 1, 2012 (referred to
after this as the Mandatory Continuing Airworthiness Information, or
``the MCAI''), to correct an unsafe condition for all Airbus Model A300
B4-600, B4-600R, and F4-600R series airplanes, and Model A300 C4-605R
Variant F airplanes (collectively called Model A300-600 series
airplanes) and Model A300 series airplanes. The MCAI states:
During routine maintenance, cracks were found in the wing bottom
skin and in the associated internal support structure on an A300
aeroplane aft of the rear spar and inboard of rib 9. Initially,
cracks were found in the skin only, starting from a fastener close
to the forward outboard corner of access panel 575FB/675FB.
Subsequently, cases were reported of cracks being found in the skin
support strap and the stiffener.
This condition, if not detected and corrected, could affect the
structural integrity of the aeroplane.
To address this unsafe condition, EASA issued AD 2006-0282
[https://ad.easa.europa.eu/ad/2006-0282] [which corresponds with FAA
AD 2008-06-18, Amendment 39-15430 (73 FR 14670, March 19, 2008)] to
require repetitive inspections of the wing lower skin panel and
associated internal support structure aft of the rear spar and
inboard of rib 9.
Since that [EASA] AD was issued, the results of a fleet survey
and updated Fatigue and Damage Tolerance analysis, which were
performed in order to substantiate the second A300 and A300-600
Extended Service Goal (ESG2) exercise, revealed that the inspection
threshold and interval had to be reduced to allow timely detection
of cracks and the accomplishment of an applicable corrective action.
Prompted by these findings, Airbus issued Revision 05 of Airbus
Service Bulletin (SB) A300-57-0177 and Revision 07 of Airbus SB
A300-57-6029.
For the reasons described above, this [EASA] AD retains the
requirements of EASA AD 2006-0282, which is superseded, but requires
the accomplishment of those actions within reduced thresholds and
intervals.
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-
0618.
Relevant Service Information
Airbus has issued Service Bulletin A300-57-6029, Revision 08, dated
April 25, 2013. The compliance times for the initial inspections range
approximately from 160 flight cycles or 270 flight hours, whichever
occurs first, to 49,300 flight cycles or 98,700 flight hours, whichever
occurs first, depending on the model and configuration. The repetitive
intervals range from 30 flight cycles or 40 flight hours, whichever
occurs first, to 3,800 flight cycles or 7,700 flight hours, whichever
occurs first, depending on the model and configuration. 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 the same
type design.
Changes to AD 2008-06-18, Amendment 39-15430 (73 FR 14670, March 19,
2008)
This proposed AD would retain all requirements of AD 2008-06-18,
Amendment 39-15430 (73 FR 14670, March 19, 2008). Since AD 2008-06-18
was issued, the AD format has been revised, and certain paragraphs have
been rearranged. As a result, the corresponding paragraph identifiers
have changed in this proposed AD, as listed in the following table:
Revised Paragraph Identifiers
------------------------------------------------------------------------
Requirement in AD 2008-06-18,
Amendment 39-15430 (73 FR 14670, Corresponding requirement in this
March 19, 2008 proposed AD
------------------------------------------------------------------------
paragraph (f) paragraph (g)
------------------------------------------------------------------------
Paragraph (f)(3) of AD 2008-06-18, Amendment 39-15430 (73 FR 14670,
March 19, 2008), contains a typographical error. That error resulted in
a reference to paragraph ``(e)(f)(ii)'' of AD 2008-06-18. The correct
reference is to paragraph (f)(3)(ii) of AD 2008-06-18. Since the AD
format has been revised and certain paragraphs have been rearranged,
the reference is now to paragraph (g)(3)(ii) of the proposed AD.
``Contacting the Manufacturer'' Paragraph in This Proposed AD
Since late 2006, we have included a standard paragraph titled
``Airworthy Product'' in all MCAI ADs in which the FAA develops an AD
based on a foreign authority's AD.
The MCAI or referenced service information in an FAA AD often
directs the owner/operator to contact the manufacturer for corrective
actions, such as a repair. Briefly, the Airworthy Product paragraph
allowed owners/operators to use corrective actions provided by the
manufacturer if those actions were FAA-approved. In addition, the
paragraph stated that any actions approved by the State of Design
Authority (or its delegated agent) are considered to be FAA-approved.
In an NPRM having Directorate Identifier 2012-NM-101-AD (78 FR
78285, December 26, 2013), we proposed to prevent the use of repairs
that were not specifically developed to correct the unsafe condition,
by requiring that the repair approval provided by the State of Design
Authority or its delegated agent specifically refer to the FAA AD. This
change was intended to clarify the method of compliance and to provide
operators with better visibility of repairs that are specifically
developed and approved to correct the unsafe condition. In addition, we
proposed to change the phrase ``its delegated agent'' to include a
design approval holder (DAH) with State of Design Authority design
organization approval (DOA), as applicable, to refer to a DAH
authorized to approve required repairs for the proposed AD.
One commenter to the NPRM having Directorate Identifier 2012-NM-
101-AD (78 FR 78285, December 26, 2013) stated the following: ``The
proposed wording, being specific to repairs, eliminates the
interpretation that Airbus messages are acceptable for approving minor
deviations (corrective actions) needed during accomplishment of an AD
mandated Airbus service bulletin.''
This comment has made the FAA aware that some operators have
misunderstood or misinterpreted the Airworthy Product paragraph to
allow the owner/operator to use messages provided by the manufacturer
as approval of deviations during the accomplishment of an AD-mandated
action. The Airworthy Product paragraph does not approve messages or
other information provided by the manufacturer for deviations to the
requirements of the AD-mandated actions. The Airworthy Product
paragraph only addresses the
[[Page 52265]]
requirement to contact the manufacturer for corrective actions for the
identified unsafe condition and does not cover deviations from other AD
requirements. However, deviations to AD-required actions are addressed
in 14 CFR 39.17, and anyone may request the approval for an alternative
method of compliance to the AD-required actions using the procedures
found in 14 CFR 39.19.
To address this misunderstanding and misinterpretation of the
Airworthy Product paragraph, we have changed the paragraph and retitled
it ``Contacting the Manufacturer.'' This paragraph now clarifies that
for any requirement in this proposed AD to obtain corrective actions
from a manufacturer, the actions must be accomplished using a method
approved by the FAA, the European Aviation Safety Agency (EASA), or
Airbus's EASA DOA.
The Contacting the Manufacturer paragraph also clarifies that, if
approved by the DOA, the approval must include the DOA-authorized
signature. The DOA signature indicates that the data and information
contained in the document are EASA-approved, which is also FAA-
approved. Messages and other information provided by the manufacturer
that do not contain the DOA-authorized signature approval are not EASA-
approved, unless EASA directly approves the manufacturer's message or
other information.
This clarification does not remove flexibility previously afforded
by the Airworthy Product paragraph. Consistent with long-standing FAA
policy, such flexibility was never intended for required actions. This
is also consistent with the recommendation of the Airworthiness
Directive Implementation Aviation Rulemaking Committee to increase
flexibility in complying with ADs by identifying those actions in
manufacturers' service instructions that are ``Required for
Compliance'' with ADs. We continue to work with manufacturers to
implement this recommendation. But once we determine that an action is
required, any deviation from the requirement must be approved as an
alternative method of compliance.
We also have decided not to include a generic reference to either
the ``delegated agent'' or ``design approval holder (DAH) with State of
Design Authority design organization approval,'' but instead we have
provided the specific delegation approval granted by the State of
Design Authority for the DAH throughout this proposed AD.
Costs of Compliance
We estimate that this proposed AD affects 162 airplanes of U.S.
registry.
The actions that are required by AD 2008-06-18, Amendment 39-15430
(73 FR 14670, March 19, 2008), and retained in this proposed 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 2008-06-18 is $170 per product.
We also estimate that it would take about 2 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 $27,540, or $170
per product.
In addition, we estimate that any necessary follow-on actions would
take about 12 work-hours and require parts costing $10,000, for a cost
of $11,020 per product. We have no way of determining the number of
aircraft that might need these actions.
Paperwork Reduction Act
A federal agency may not conduct or sponsor, and a person is not
required to respond to, nor shall a person be subject to 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 control
number for the collection of information required by this AD is 2120-
0056. The paperwork cost associated with this AD has been detailed in
the Costs of Compliance section of this document and includes time for
reviewing instructions, as well as completing and reviewing the
collection of information. Therefore, all reporting associated with
this AD is 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.
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. The FAA amends Sec. 39.13 by removing Airworthiness Directive (AD)
2008-06-18, Amendment 39-15430 (73 FR 14670, March 19, 2008), and
adding the following new AD:
Airbus: Docket No. FAA-2014-0618; Directorate Identifier 2012-NM-
171-AD.
(a) Comments Due Date
We must receive comments by October 20, 2014.
[[Page 52266]]
(b) Affected ADs
This AD replaces AD 2008-06-18, Amendment 39-15430 (73 FR 14670,
March 19, 2008).
(c) Applicability
This AD applies to the airplanes identified in paragraphs (c)(1)
through (c)(5) of this AD, certificated in any category, all
certified models, all serial numbers.
(1) Airbus Model A300 B2-1A, B2-1C, B2K-3C, B2-203, B4-2C, B4-
103, and B4-203 airplanes.
(2) Airbus Model A300 B4-601, B4-603, B4-620, and B4-622
airplanes.
(3) Airbus Model A300 B4-605R and B4-622R airplanes.
(4) Airbus Model A300 F4-605R and F4-622R airplanes.
(5) Airbus Model A300 C4-605R Variant F airplanes.
(d) Subject
Air Transport Association (ATA) of America Code 57, Wings.
(e) Reason
This AD was prompted by a report that information from an
analysis and fleet survey show a need for reduced compliance times
and intervals. We are issuing this AD to detect and correct
cracking, which could lead to reduced structural integrity of the
airplane.
(f) Compliance
You are responsible for having the actions required by this AD
performed within the compliance times specified, unless the actions
have already been done.
(g) Retained Actions and Compliance Times With Revised Service
Information
This paragraph restates the requirements of paragraph (f) of AD
2008-06-18, Amendment 39-15430 (73 FR 14670, March 19, 2008), with
revised service information. Unless already done, do the following
actions.
(1) Except as provided by paragraphs (g)(1)(i), (g)(1)(ii),
(g)(1)(iii), (g)(1)(iv), and (h) of this AD: At the threshold
specified in paragraph 1.E.(2) of Airbus Service Bulletin A300-57-
0177, Revision 05, dated March 23, 2007 (for Model A300 series
airplanes); Airbus Service Bulletin A300-57-6029, Revision 06, dated
March 23, 2007 (for Model A300-600 series airplanes); or Airbus
Service Bulletin A300-57-6029, Revision 08, dated April 25, 2013
(for Model A300-600 series airplanes); as applicable; perform the
inspection of the wing lower skin panel and associated internal
support structure aft of the rear spar and inboard of rib 9 and
apply applicable corrective measures in accordance with Airbus
Service Bulletin A300-57-0177, Revision 05, dated March 23, 2007
(for Model A300 series airplanes); or Airbus Service Bulletin A300-
57-6029, Revision 06, dated March 23, 2007 (for Model A300-600
series airplanes); or Airbus Service Bulletin A300-57-6029, Revision
08, dated April 25, 2013 (for Model A300-600 series airplanes); as
applicable. All applicable corrective measures must be done at the
applicable times specified in paragraph 1.E.(2) and the
Accomplishment Instructions of Airbus Service Bulletin A300-57-0177,
Revision 05, dated March 23, 2007 (for Model A300 series airplanes);
Airbus Service Bulletin A300-57-6029, Revision 06, dated March 23,
2007 (for Model A300-600 series airplanes); or Airbus Service
Bulletin A300-57-6029, Revision 08, dated April 25, 2013 (for Model
A300-600 series airplanes); as applicable. Accomplishing the
requirements of paragraph (h) of this AD terminates the requirements
of this paragraph for Model A300-600 airplanes.
(i) Where the tables in paragraph 1.E.(2), ``Accomplishment
Timescale,'' of Airbus Service Bulletin A300-57-0177, Revision 05,
dated March 23, 2007; A300-57-6029, Revision 06, dated March 23,
2007; specify a grace period for doing the actions, this AD requires
that the actions be done within the specified grace period relative
to April 23, 2008 (the effective date of AD 2008-06-18, Amendment
39-15430 (73 FR 14670, March 19, 2008)).
(ii) Where the tables in paragraph 1.E.(2)(e), ``Config 04,'' of
Airbus Service Bulletin A300-57-0177, Revision 05, dated March 23,
2007, specify an inspection interval but not an initial threshold,
this AD requires that the actions be done within the specified
interval after inspecting in accordance with Table 1A or 1B, as
applicable, for Configuration 01 airplanes described in the service
bulletin and thereafter at the inspection interval specified in the
tables in paragraph 1.E.(2)(e), ``Config 04,'' of Airbus Service
Bulletin A300-57-0177, Revision 05, dated March 23, 2007.
(iii) Where the tables in paragraph 1.E.(2)(f), ``Config 05,''
of Airbus Service Bulletin A300-57-6029, Revision 06, dated March
23, 2007, specify an inspection interval but not an initial
threshold, this AD requires that the actions be done within the
specified interval after inspecting in accordance with Table 1A, or
1B, as applicable, for configuration 01 of Airbus Service Bulletin
A300-57-6029, Revision 06, dated March 23, 2007, and thereafter at
the inspection interval specified in the tables in paragraph
1.E.(2)(f), ``Config 05,'' of Airbus Service Bulletin A300-57-6029,
Revision 06, dated March 23, 2007.
(iv) All crack lengths specified in Airbus Service Bulletin
A300-57-0177, Revision 05, dated March 23, 2007; and A300-57-6029,
Revision 06, dated March 23, 2007, are considered ``not to exceed''
lengths.
(2) Repeat the inspection at the intervals in, and according to
the instructions defined in, Airbus Service Bulletin A300-57-0177,
Revision 05, dated March 23, 2007 (for Model A300 series airplanes);
Airbus Service Bulletin A300-57-6029, Revision 06, dated March 23,
2007 (for Model A300-600 series airplanes); or Airbus Service
Bulletin A300-57-6029, Revision 08, dated April 25, 2013 (for Model
A300-600 series airplanes); as applicable; except where Airbus
Service Bulletin A300-57-0177, Revision 05, dated March 23, 2007,
specifies repetitive inspections for cracking if Airbus Service
Bulletin A300-57-022 has not been embodied, this AD requires doing
repetitive inspections for cracking if Airbus Service Bulletin A300-
57-0222 (modification 11178H5410) has not been embodied.
(3) Report to Airbus the first inspection results, whatever they
may be, at the applicable time specified in paragraph (g)(3)(i) or
(g)(3)(ii) of this AD.
(i) If the inspection was done after April 23, 2008 (the
effective date of AD 2008-06-18, Amendment 39-15430 (73 FR 14670,
March 19, 2008)), submit the report within 30 days after the
inspection.
(ii) If the inspection was accomplished prior to April 23, 2008
(the effective date of AD 2008-06-18, Amendment 39-15430 (73 FR
14670, March 19, 2008)), submit the report within 30 days after
April 23, 2008.
(h) New Requirement of This AD: New Compliance Times for Model A300-600
Airplanes
For Model A300-600 airplanes, do the actions specified in
paragraphs (h)(1) through (h)(3) of this AD at the applicable times
specified in those paragraphs.
(1) Except as provided by paragraphs (h)(1)(i) and (h)(1)(ii) of
this AD: Within the compliance times specified in Airbus Service
Bulletin A300-57-6029, Revision 08, dated April 25, 2013, perform
the inspection of the wing lower skin panels and associated internal
support structures aft of the rear spar and inboard of rib 9, in
accordance with the Accomplishment Instructions of Airbus Service
Bulletin A300-57-6029, Revision 08, dated April 25, 2013.
Thereafter, repeat these inspections at intervals specified in
Airbus Service Bulletin A300-57-6029, Revision 08, dated April 25,
2013. Accomplishment of the actions required by this paragraph
terminates the requirements of paragraph (g) of this AD for Model
A300-600 airplanes.
(i) Where the tables in paragraph 1.E.(2), ``Accomplishment
Timescale,'' of Airbus Service Bulletin A300-57-6029, Revision 08,
dated April 25, 2013, specify a grace period for doing the actions
for airplanes that have exceeded the thresholds, this AD requires,
for all airplanes, that the actions be done within the specified
grace period after the effective date of this AD or before the
specified thresholds, whichever occurs later.
(ii) Where Airbus Service Bulletin A300-57-6029, Revision 08,
dated April 25, 2013, specifies to ``contact Airbus'' before further
flight, this AD requires repairing using a method approved by the
Manager, International Branch, ANM-116, Transport Airplane
Directorate, FAA; or European Aviation Safety Agency (EASA); or
Airbus's EASA Design Organization Approval (DOA); and accomplishing
those actions before further flight. If approved by the DOA, the
approval must include the DOA-authorized signature.
(2) If, during any inspection as required by paragraph (h)(1) of
this AD, discrepancies are detected, before next flight, accomplish
the applicable corrective actions, in accordance with the
Accomplishment Instructions of Airbus Service Bulletin A300-57-6029,
Revision 08, dated April 25, 2013.
(3) Corrective actions, as required by paragraph (h)(2) of this
AD, do not constitute terminating action for the repetitive
inspection requirements of paragraph (h)(1) of this AD.
(i) Credit for Previous Actions
(1) This paragraph provides credit for actions required by
paragraph (g) of this AD,
[[Page 52267]]
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-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. 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
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
