Airworthiness Directives; Airbus Airplanes, 78285-78290 [2013-30893]
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78285
Proposed Rules
Federal Register
Vol. 78, No. 248
Thursday, December 26, 2013
This section of the FEDERAL REGISTER
contains notices to the public of the proposed
issuance of rules and regulations. The
purpose of these notices is to give interested
persons an opportunity to participate in the
rule making prior to the adoption of the final
rules.
NUCLEAR REGULATORY
COMMISSION
10 CFR Part 72
[NRC–2012–0052]
RIN 3150–AJ12
List of Approved Spent Fuel Storage
Casks: HI–STORM 100 Cask System;
Amendment No. 9
Nuclear Regulatory
Commission.
ACTION: Proposed rule; correction and
extension of comment period.
AGENCY:
The U.S. Nuclear Regulatory
Commission (NRC) is correcting a
proposed rule that appeared in the
Federal Register on December 6, 2013,
and is extending the public comment
period. The document proposed to
amend the NRC’s spent fuel storage
regulations by revising the Holtec
International HI–STORM 100 Cask
System listing within the ‘‘List of
Approved Spent Fuel Storage Casks’’ to
include Amendment No. 9 to Certificate
of Compliance (CoC) No. 1014. This
action is necessary to correct the NRC’s
Agencywide Documents Access and
Management System (ADAMS)
accession numbers for the CoC and the
ADAMS document package containing
the CoC, the Safety Evaluation Report
(SER), and the Technical Specifications
(TSs) for this amendment; and to extend
the public comment period.
DATES: The comment period for the
proposed rule published December 6,
2013, at 78 FR 73456, is extended.
Comments are due by January 27, 2014.
ADDRESSES: Please refer to Docket ID
NRC–2012–0052 when contacting the
NRC about the availability of
information for this action. You may
access publicly-available information
related to this action by any of the
following methods:
• Federal Rulemaking Web site: Go to
https://www.regulations.gov and search
for Docket ID NRC–2012–0052. Address
questions about NRC dockets to Carol
Gallagher, telephone: 301–287–3422,
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SUMMARY:
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email: Carol.Gallagher@nrc.gov. For
technical questions, contact the
individual listed in the FOR FURTHER
INFORMATION CONTACT section of this
document.
• NRC’s Agencywide Documents
Access and Management System
(ADAMS): You may access publicly
available documents online in the NRC
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select ‘‘ADAMS Public Documents’’ and
then select ‘‘Begin Web-based ADAMS
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please contact the NRC’s Public
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FOR FURTHER INFORMATION CONTACT:
Naiem S. Tanious, Office of Federal and
State Materials and Environmental
Management Programs, U.S. Nuclear
Regulatory Commission, Washington,
DC 20555–0001, telephone: 301–415–
6103, email: Naiem.Tanious@nrc.gov.
SUPPLEMENTARY INFORMATION:
effective date will be delayed from
February 19, 2014, to March 11, 2014.
Corrections
AGENCY:
The NRC is correcting the ADAMS
accession numbers for the CoC and the
ADAMS document package containing
the CoC, SER, and the TSs for this
amendment because the documents
referenced by accession numbers in the
proposed rule the NRC published on
December 6, 2013 (78 FR 73456; Fr. Doc.
2013–29160), do not clearly display the
proposed changes to the documents.
In Fr. Doc. 2013–29160, on page
73456, in the second column, second
line from the bottom of the page,
‘‘ML120530246’’ is corrected to read
‘‘ML13351A224.’’ On page 73456, in the
third column, second line from the top
of the page, ‘‘ML120530271’’ is
corrected to read ‘‘ML13351A205.’’
In the Rules and Regulations section
of this issue of the Federal Register, the
NRC is publishing a document to correct
and delay the effective date of the direct
final rule (78 FR 73379; December 6,
2013). Specifically, ADAMS accession
numbers for the CoC, the SER, and the
ADAMS document package containing
the CoC, the SER, and the TSs for this
amendment will be corrected and the
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Extension of Comment Period
The public comment period is being
extended from January 6, 2014, to
January 27, 2014, to provide the public
the opportunity to review all
information related to the rulemaking.
Dated at Rockville, Maryland, this 19th day
of December, 2013.
For the Nuclear Regulatory Commission.
Leslie Terry,
Acting Chief, Rules, Announcements, and
Directives Branch, Division of Administrative
Services, Office of Administration.
[FR Doc. 2013–30864 Filed 12–24–13; 8:45 am]
BILLING CODE 7590–01–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2013–1064; Directorate
Identifier 2012–NM–101–AD]
RIN 2120–AA64
Airworthiness Directives; Airbus
Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking
(NPRM).
We propose to supersede
airworthiness directive (AD) 2005–23–
08 that applies to certain Airbus Model
A300 B4–605R and B4–622R airplanes;
Model A300 F4–605R airplanes; and
Model A300 C4–605R Variant F
airplanes. AD 2005–23–08 required
repetitive inspections to detect cracks of
certain attachment holes, installation of
new fasteners, follow-on inspections or
repair if necessary, and modification of
the angle fittings of fuselage frame FR47.
Since we issued AD 2005–23–08, we
have received reports of cracks found on
the horizontal flange of the Frame 47
internal corner angle fitting while
accomplishing the modification
required by AD 2005–23–08. This
proposed AD would add new repetitive
ultrasonic inspections for cracks of the
center wing box lower panel; and repair
if necessary. This proposed AD also
removes certain airplanes from the
applicability. We are proposing this AD
to detect and correct fatigue cracking of
SUMMARY:
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Federal Register / Vol. 78, No. 248 / Thursday, December 26, 2013 / Proposed Rules
the forward fitting of fuselage frame
FR47, which could result in reduced
structural integrity of the frame.
DATES: We must receive comments on
this proposed AD by February 10, 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—
EAW (Airworthiness Office), 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 review copies of the 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.
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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 MCAI,
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.
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FAA–2013–1064; Directorate Identifier
2012–NM–101–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.
fitting web (vertical face) related to SB A300–
57–6049 and internal lower angle fitting
modification programme related to SB A300–
57–6050 remain unchanged.
For the reasons explained above, this new
[EASA] AD retains the requirements of DGAC
France AD F–2004–159, which is
superseded, and requires additional
repetitive [ultrasonic] inspections [for cracks]
of the CWB lower panel through the
ultrasonic method and, depending on
findings, [repair, e.g.,] re-installation of
removed fasteners in transition fit instead of
interference.
This [EASA] AD has been republished to
correct a typographical error * * *.
Discussion
On October 31, 2005, we issued AD
2005–23–08, Amendment 39–14366 (70
FR 69056, November 14, 2005). That AD
required actions intended to address an
unsafe condition on certain Model A300
B4–601, B4–603, B4–620, and B4–622
airplanes; Model A300 B4–605R and
B4–622R airplanes; Model A300 F4–
605R airplanes; and Model A300 C4–
605R Variant F airplanes.
Since we issued AD 2005–23–08,
Amendment 39–14366 (70 FR 69056,
November 14, 2005), the European
Aviation Safety Agency (EASA), which
is the Technical Agent for the Member
States of the European Community, has
issued EASA Airworthiness Directive
2012–0092, dated May 25, 2012;
correction dated June 4, 2012 (referred
to after this as the Mandatory
Continuing Airworthiness Information,
or ‘‘the MCAI’’), to correct an unsafe
condition for the specified products.
The MCAI states:
The repetitive interval for the new
ultrasonic inspection is either 1,260
flight cycles or 2,720 flight hours,
whichever occurs first; or 1,360 flight
cycles or 2,200 flight hours, whichever
occurs first; depending on average flight
time of the airplane. You may obtain
further information by examining the
MCAI in the AD docket.
Prompted by cracks found on the Frame 47
angle fitting, DGAC France published AD
2000–533–328 [(https://ad.easa.europa.eu/ad/
F-2000-533-328R1)] to require [a] repetitive
inspection programme for fuselage frame 47.
If not detected and corrected, these cracks
could affect the structural integrity of the
Centre Wing Box (CWB) of the aeroplane.
Subsequent to the publication of a new
repetitive inspection programme for fuselage
frame 47 at certain fasteners of the CWB
angle fitting, DGAC France issued AD F–
2004–159 [(https://ad.easa.europa.eu/ad/F2004-159)] [which corresponds to AD 2005–
23–08, Amendment 39–14366 (70 FR 69056,
November 14, 2005)], superseding AD 2000–
533–328.
After DGAC France AD F–2004–159 was
issued, cracks were reportedly found on the
horizontal flange of the Frame 47 internal
corner angle fitting during accomplishment
of routine maintenance structural inspection
and modification in accordance with Airbus
SB A300–57–6050.
Prompted by these findings, Airbus
reviewed and amended the inspection
programme for the internal lower angle
fitting flange (horizontal face). The
inspection programme for the lower angle
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Relevant Service Information
Airbus has issued Mandatory Service
Bulletins A300–57–6049, Revision 07,
dated December 22, 2006, and A300–
57–6086, Revision 05, dated January 30,
2012. 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.
Difference Between This Proposed AD
and the MCAI or Service Information
Although the MCAI and service
information specify to contact the
manufacturer for instructions to repair
certain conditions, this proposed AD
would require repairing those
conditions using a method approved by
the Manager, International Branch,
ANM–116, Transport Airplane
Directorate, FAA; or the EASA (or its
delegated agent; or the Design Approval
Holder with EASA’s design organization
approval), as applicable.
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Explanation of Changes to AD 2005–23–
08, Amendment 39–14366 (70 FR
69056, November 14, 2005)
In many FAA transport ADs, when
the service information specifies to
contact the manufacturer for further
instructions if certain discrepancies are
found, we typically include in the AD
a requirement to accomplish the action
using a method approved by either the
FAA or the State of Design Authority (or
its delegated agent).
We have recently been notified that
certain laws in other countries do not
allow such delegation of authority, but
some countries do recognize design
approval organizations. In addition, we
have become aware that some U.S.
operators have used repair instructions
that were previously approved by a
State of Design Authority or a Design
Approval Holder (DAH) as a method of
compliance with this provision in FAA
ADs. Frequently, in these cases, the
previously approved repair instructions
come from the airplane structural repair
manual or the DAH repair approval
statements that were not specifically
developed to address the unsafe
condition corrected by the AD. Using
repair instructions that were not
specifically approved for a particular
AD creates the potential for doing
repairs that were not developed to
address the unsafe condition identified
by the MCAI AD, the FAA AD, or the
applicable service information, which
could result in the unsafe condition not
being fully corrected.
To prevent the use of repairs that
were not specifically developed to
correct the unsafe condition, this
proposed AD would require that the
repair approval specifically refer to the
FAA AD. This change is 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
78287
condition. In addition, we use the
phrase ‘‘its delegated agent, or by the
DAH with State of Design Authority
design organization approval, as
applicable’’ in this proposed AD to refer
to an DAH authorized to approve
required repairs for this proposed AD.
Explanation of Change to Applicability
AD 2005–23–08, Amendment 39–
14366 (70 FR 69056, November 14,
2005), includes Airbus Model A300 B4–
601 airplanes in the applicability.
However, this proposed AD does not
include Model A300 B4–601 airplanes
because these airplanes are no longer in
service.
Costs of Compliance
We estimate that this proposed AD
affects about 65 products of U.S.
registry.
We estimate the following costs to
comply with this proposed AD:
ESTIMATED COSTS
Average labor
rate per hour
Action
Work hours
Inspection [retained action from existing AD] AD
2005-23-08, Amendment 39-14366 (70 FR
69056, November 14, 2005).
Inspection [retained action from existing AD] AD
2005–23–08, Amendment 39–14366 (70 FR
69056, November 14, 2005).
Modification [retained action from existing AD]
AD 2005–23–08, Amendment 39–14366 (70
FR 69056, November 14, 2005).
New ultrasonic inspection ....................................
13 .................................
$85
30 .................................
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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
17:18 Dec 24, 2013
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Cost per airplane
$0 .................................
$1,105.
85
Between $6,637 and
$19,091.
Between 65 and 365 ....
85
$3,370 ..........................
Between $9,187 and
$21,641, per inspection cycle.
Between $8,895 and
$34,395.
35 .................................
85
Between $11,750 and
$18,720.
Between $14,725 and
$21,695 per inspection cycle.
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.
We have received no definitive data
that would enable us to provide cost
estimates for the on-condition actions
specified in this proposed AD.
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Parts
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.
Authority for This Rulemaking
Regulatory Findings
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
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);
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Federal Register / Vol. 78, No. 248 / Thursday, December 26, 2013 / Proposed Rules
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.
We prepared a regulatory evaluation
of the estimated costs to comply with
this proposed AD and placed it in the
AD docket.
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. The FAA amends § 39.13 by
removing airworthiness directive (AD)
2005–23–08, Amendment 39–14366 (70
FR 69056, November 14, 2005) and
adding the following new AD:
■
Airbus: Docket No. FAA–2013–1064;
Directorate Identifier 2012–NM–101–AD.
(a) Comments Due Date
We must receive comments by February
10, 2014.
(b) Affected ADs
This AD supersedes AD 2005–23–08,
Amendment 39–14366 (70 FR 69056,
November 14, 2005).
(c) Applicability
This AD applies to Airbus Model B4–603,
B4–620, and B4–622 airplanes; Model A300
B4–605R and B4–622R airplanes; Model
A300 F4–605R airplanes; and Model A300
C4–605R Variant F airplanes; certificated in
any category; except airplanes on which
Airbus Modification 12171 or 12249 has been
embodied in production, or on which Airbus
Service Bulletin A300–57–6069 has been
embodied in service.
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(d) Subject
Air Transport Association (ATA) of
America Code 57: Wings.
(e) Reason
This AD was prompted by reports of cracks
found on the horizontal flange of the Frame
47 internal corner angle fitting while
accomplishing the modification required by
AD 2005–23–08, Amendment 39–14366 (70
FR 69056, November 14, 2005). We are
issuing this AD to detect and correct fatigue
cracking of the forward fitting of fuselage
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frame FR47, which could result in reduced
structural integrity of the frame.
(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 Inspections for Attachment
Holes on the Internal Angles of the Wing
Center Box, and Corrective Action
This paragraph restates the requirements of
paragraphs (f), (g), and (h) of AD 2005–23–
08, Amendment 39–14366 (70 FR 69056,
November 14, 2005), with revised service
information. Perform a rotating probe
inspection to detect cracking of the
applicable attachment holes on the left and
right internal angles of the wing center box
in accordance with the Accomplishment
Instructions of Airbus Service Bulletin A300–
57–6049, Revision 06, dated July 15, 2004; or
Airbus Mandatory Service Bulletin A300–57–
6049, Revision 07, dated December 22, 2006.
Do the inspection at the applicable time
specified by paragraph 1.E.(2),
Accomplishment Timescale, of Airbus
Service Bulletin A300–57–6049, Revision 06,
dated July 15, 2004; except as required by
paragraph (j) of this AD. Repeat the rotating
probe inspection specified in this paragraph
thereafter at intervals not to exceed the
applicable interval specified in Airbus
Mandatory Service Bulletin A300–57–6049,
Revision 06, dated July 15, 2004, except that
all touch-and-go landings must be counted in
determining the total number of flight cycles
between consecutive inspections. As of the
effective date of this AD, only Airbus
Mandatory Service Bulletin A300–57–6049,
Revision 07, dated December 22, 2006, may
be used to accomplish the actions required
by this paragraph.
(1) If no cracking is found during any
inspection required by paragraph (g) of this
AD: Prior to further flight, install new
fasteners in accordance with the
Accomplishment Instructions of Airbus
Service Bulletin A300–57–6049, Revision 06,
dated July 15, 2004; or Airbus Mandatory
Service Bulletin A300–57–6049, Revision 07,
dated December 22, 2006. As of the effective
date of this AD, only Airbus Mandatory
Service Bulletin A300–57–6049, Revision 07,
dated December 22, 2006, may be used to
accomplish the actions required by this
paragraph.
(2) If any cracking is found during any
inspection required by paragraph (g) of this
AD: Prior to further flight, perform applicable
corrective actions (including reaming,
drilling, drill-stopping holes, chamfering,
performing follow-on inspections, and
installing new or oversize fasteners) in
accordance with the Accomplishment
Instructions of Airbus Service Bulletin A300–
57–6049, Revision 06, dated July 15, 2004; or
Airbus Mandatory Service Bulletin A300–57–
6049, Revision 07, dated December 22, 2006;
except as required by paragraph (k) of this
AD. As of the effective date of this AD, only
Airbus Mandatory Service Bulletin A300–57–
6049, Revision 07, dated December 22, 2006,
may be used to accomplish the actions
required by this paragraph.
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(h) Retained Inspections for Attachment
Holes in the Horizontal Flange of the
Internal Corner Angle Fitting of Fuselage
Frame FR47, and Corrective Action
This paragraph restates the requirements of
paragraphs (i), (j), and (k) of AD 2005–23–08,
Amendment 39–14366 (70 FR 69056,
November 14, 2005), with revised service
information. Perform a rotating probe
inspection to detect cracking of the
applicable attachment holes in the horizontal
flange of the internal corner angle fitting of
fuselage frame FR47, in accordance with the
Accomplishment Instructions of Airbus
Service Bulletin A300–57–6086, Revision 01,
dated April 2, 2002; or Airbus Mandatory
Service Bulletin A300–57–6086, Revision 05,
dated January 30, 2012. Do the inspection at
the applicable time specified in paragraph
1.E., Compliance, of Airbus Service Bulletin
A300–57–6086, Revision 01, dated April 2,
2002, except as provided by paragraph (j) of
this AD; or within 1,500 flight cycles after
July 8, 2002 (the effective date of AD 2002–
11–04, amendment 39–12765 (67 FR 38193,
June 3, 2002)); whichever occurs later. Repeat
the rotating probe inspection specified in this
paragraph thereafter at intervals not to
exceed the applicable interval specified in
Airbus Service Bulletin A300–57–6086,
dated June 6, 2000, except that all touch-andgo landings must be counted in determining
the total number of flight cycles between
consecutive inspections. As of the effective
date of this AD, only Airbus Mandatory
Service Bulletin A300–57–6086, Revision 05,
dated January 30, 2012, may be used to
accomplish the actions required by this
paragraph.
(1) If no cracking is found during any
inspection required by paragraph (h) of this
AD: Prior to further flight, install new
fasteners in accordance with the
Accomplishment Instructions of Airbus
Service Bulletin A300–57–6086, Revision 01,
dated April 2, 2002; or Airbus Mandatory
Service Bulletin A300–57–6086, Revision 05,
dated January 30, 2012. As of the effective
date of this AD, only Airbus Mandatory
Service Bulletin A300–57–6086, Revision 05,
dated January 30, 2012, may be used to
accomplish the actions required by this
paragraph.
(2) If any cracking is found during any
inspection required by paragraph (h) of this
AD: Prior to further flight, perform applicable
corrective actions (including inspecting hole
T if any cracking is found at hole G, reaming
the holes, and installing oversize fasteners) in
accordance with the Accomplishment
Instructions of Airbus Service Bulletin A300–
57–6086, Revision 01, dated April 2, 2002; or
Airbus Mandatory Service Bulletin A300–57–
6086, Revision 05, dated January 30, 2012;
except as required by paragraph (k) of this
AD. As of the effective date of this AD, only
Airbus Mandatory Service Bulletin A300–57–
6086, Revision 05, dated January 30, 2012,
may be used to accomplish the actions
required by this paragraph.
(i) Retained Modification of Angle Fittings of
the Wing Center Box
This paragraph restates the requirements of
paragraph (l) of AD 2005–23–08, Amendment
39–14366 (70 FR 69056, November 14, 2005).
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Federal Register / Vol. 78, No. 248 / Thursday, December 26, 2013 / Proposed Rules
Modify the left and right internal angle
fittings of the wing center box. The
modification includes performing a rotating
probe inspection to detect cracking, repairing
cracks, cold expanding holes, and installing
medium interference fitting bolts. Perform
the modification in accordance with the
Accomplishment Instructions of Airbus
Service Bulletin A300–57–6050, Revision 03,
dated May 31, 2001; and at the applicable
time specified by paragraph 1.B.(4),
Accomplishment Timescale, of Airbus
Service Bulletin A300–57–6050, Revision 03,
dated May 31, 2001; except as required by
paragraphs (j) and (k) of this AD.
(j) Retained Compliance Time Exception to
Service Information Specified in Paragraphs
(g), (h), and (i) of This AD
This paragraph restates the requirements of
paragraph (m) of AD 2005–23–08,
Amendment 39–14366 (70 FR 69056,
November 14, 2005). Where the service
information specified in paragraphs (g), (h),
and (i) of this AD specify a grace period
relative to receipt of the service bulletin, this
AD requires compliance within the
applicable grace period following December
19, 2005, (the effective date of AD 2005–23–
08), if the threshold has been exceeded.
tkelley on DSK3SPTVN1PROD with PROPOSALS
(k) Retained Corrective Action Exception to
Service Information Specified in Paragraphs
(g), (h), and (i) of This AD
This paragraph restates the requirements of
paragraph (n) of AD 2005–23–08,
Amendment 39–14366 (70 FR 69056,
November 14, 2005). If any crack is detected
during any inspection required by paragraph
(g), (h), or (i) of this AD, and the applicable
service information specifies to contact the
manufacturer for disposition of certain
corrective actions: Prior to further flight,
repair in accordance with a method approved
by the Manager, International Branch, ANM–
116, Transport Airplane Directorate, FAA; or
´ ´
the Direction Generale de l’Aviation Civile
(DGAC) (or its delegated agent).
(l) Credit for Previous Actions
(1) This paragraph restates the credit
provided by paragraph (o) of AD 2005–23–08,
Amendment 39–14366 (70 FR 69056,
November 14, 2005): This paragraph provides
credit for actions required by paragraph (h)
of this AD, if those actions were performed
before December 19. 2005, (the effective date
of AD 2005–23–08) using Airbus Service
Bulletin A300–57–6086, dated June 6, 2000.
(2) This paragraph restates the credit
provided by paragraph (p) of AD 2005–23–
08, Amendment 39–14366 (70 FR 69056,
November 14, 2005): This paragraph provides
credit for the modification required by
paragraph (i) of this AD, if the modification
was performed before December 19, 2005,
(the effective date of AD 2005–23–08) using
Airbus Service Bulletin A300–57–6050,
Revision 02, dated February 10, 2000.
(m) New Requirements of This AD:
Repetitive Ultrasonic Inspections and
Corrective Action
(1) For airplanes on which Airbus Service
Bulletin A300–57–6050, Revision 03, dated
May 31, 2001, has not been done, or on
which Airbus Modification 10155 has been
VerDate Mar<15>2010
17:18 Dec 24, 2013
Jkt 232001
done: Perform an ultrasonic inspection for
cracking of the left- and right-hand aft bottom
panel of the center wing box (CWB) in
accordance with the Accomplishment
Instructions of Airbus Mandatory Service
Bulletin A300–57–6086, Revision 05, dated
January 30, 2012. Do the inspection at the
later of the times specified in paragraphs
(m)(1)(i) and (m)(1)(ii) of this AD. If any
cracking is found, before further flight, repair
using a method approved by the Manager,
International Branch, ANM–116, Transport
Airplane Directorate, FAA; or EASA (or its
delegated agent, or the Design Approval
Holder with EASA’s design organization
approval, as applicable. For a repair method
to be approved, the repair approval must
specifically refer to this AD. Repeat the
inspection thereafter at intervals not to
exceed the applicable interval specified in
paragraph 1.E.(2), Accomplishment
Timescale, of Airbus Mandatory Service
Bulletin A300–57–6086, Revision 05, dated
January 30, 2012.
(i) Within 13,400 flight cycles or 34,600
flight hours after the first flight of the
airplane, whichever occurs first.
(ii) Within 650 flight cycles or 8 months
after the effective date of this AD, whichever
occurs first.
(2) For airplanes on which Airbus Service
Bulletin A300–57–6050, Revision 03, dated
May 31, 2001, has been done: Perform an
ultrasonic inspection for cracking of the leftand right-hand aft bottom panel of the center
wing box (CWB), in accordance with the
Accomplishment Instructions of Airbus
Mandatory Service Bulletin A300–57–6086,
Revision 05, dated January 30, 2012. Do the
inspection at the later of the times specified
in paragraphs (m)(2)(i) and (m)(2)(ii) of this
AD. If any cracking is found, before further
flight repair using a method approved by the
Manager, International Branch, ANM–116,
Transport Airplane Directorate, FAA; or
EASA (or its delegated agent, or the Design
Approval Holder with EASA’s design
organization approval), as applicable. For a
repair method to be approved, the repair
approval must specifically refer to this AD.
Repeat the inspection thereafter at intervals
not to exceed the applicable interval
specified in paragraph 1.E.(2),
Accomplishment Timescale, of Airbus
Mandatory Service Bulletin A300–57–6086,
Revision 05, dated January 30, 2012.
(i) Within 13,400 flight cycles or 34,600
flight hours after accomplishing Airbus
Service Bulletin A300–57–6050, whichever
occurs first.
(ii) Within 650 flight cycles or 8 months
after the effective date of this AD, whichever
occurs first.
(n) New Reporting Requirement
Submit a report of the findings (both
positive and negative) of the inspection
required by paragraph (m) of this AD to the
Design Approval Holder, at the applicable
time specified in paragraph (n)(1) or (n)(2) of
this AD. The report must include the
inspection results, a description of any
discrepancies found, the airplane serial
number, and the number of flight cycles and
flight hours on the airplane. The inspection
report form in Appendix 01 of Airbus
PO 00000
Frm 00005
Fmt 4702
Sfmt 4702
78289
Mandatory Service Bulletin A300–57–6086,
Revision 05, dated January 30, 2012, may be
used.
(1) If the inspection was done on or after
the effective date of this AD: Submit the
report within 30 days after the inspection.
(2) If the inspection was done before the
effective date of this AD: Submit the report
within 30 days after the effective date of this
AD.
(o) 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: 9ANM-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 in
accordance with AD 2005–23–08,
Amendment 39–14366 (70 FR 69056,
November 14, 2005), are approved as AMOCs
for the corresponding provision of this AD.
(2) Airworthy Product: For any requirement
in this AD to obtain corrective actions from
a manufacturer, use these actions if they are
FAA-approved. Corrective actions are
considered FAA-approved if they were
approved by the State of Design Authority (or
its delegated agent, or the Design Approval
Holder with a State of Design Authority’s
design organization approval), as applicable.
For a repair method to be approved, the
repair approval must specifically refer to this
AD. You are required to ensure the product
is airworthy before it is returned to service.
(p) Related Information
(1) Refer to Mandatory Continuing
Airworthiness Information EASA
Airworthiness Directive 2012–0092, dated
May 25, 2012: Correction dated June 4, 2012,
for related information. This MCAI may be
found in the AD docket on the Internet at
https://www.regulations.gov.
(2) For service information identified in
this AD, contact Airbus SAS—EAW
(Airworthiness Office), 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.
(3) You may review copies of the
referenced service information at the FAA,
Transport Airplane Directorate, 1601 Lind
Avenue SW., Renton, WA. For information
E:\FR\FM\26DEP1.SGM
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78290
Federal Register / Vol. 78, No. 248 / Thursday, December 26, 2013 / Proposed Rules
on the availability of this material at the
FAA, call 425–227–1221.
Issued in Renton, Washington, on
December 17, 2013.
Jeffrey E. Duven,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. 2013–30893 Filed 12–24–13; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
Examining the AD Docket
[Docket No. FAA–2008–1088; Directorate
Identifier 2008–NE–15–AD]
RIN 2120–AA64
Airworthiness Directives; Dowty
Propellers
Federal Aviation
Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
We propose to revise
airworthiness directive (AD) 2008–21–
07 that applies to certain Dowty
Propellers model R408/6–123–F/17
propellers. AD 2008–21–07 requires
initial and repetitive inspections of the
blade bonded metallic leading edge (L/
E) guards for correct bonding until they
accumulate more than 1,200 flight hours
(FH) time in service. Since we issued
AD 2008–21–07, Dowty Propellers has
introduced updated service bulletins
that identify terminating action to the
requirements of AD 2008–21–07. This
proposed AD would maintain the
inspection and replacement
requirements of AD 2008–21–07,
provide an optional terminating action
to those requirements, and add a new
part number to the list of affected parts.
We are proposing this AD to prevent the
loss of the bonded metallic L/E guard of
the propeller, which could result in
damage to the propeller or to the
airplane, or injury to personnel.
DATES: We must receive comments on
this proposed AD by February 24, 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.
tkelley on DSK3SPTVN1PROD with PROPOSALS
SUMMARY:
VerDate Mar<15>2010
17:18 Dec 24, 2013
Jkt 232001
• Hand Delivery: Deliver to Mail
address above between 9 a.m. and 5
p.m., Monday through Friday, except
Federal holidays.
For service information identified in
this AD, contact Dowty Propellers,
Anson Business Park, Cheltenham Road
East, Gloucester GL2 9QN, UK; phone
44 (0) 1452 716000; fax 44 (0) 1452
716001. You may view this service
information at the FAA, Engine &
Propeller Directorate, 12 New England
Executive Park, Burlington, MA. For
information on the availability of this
material at the FAA, call 781–238–7125.
You may examine the AD docket on
the Internet at https://
www.regulations.gov by searching for
and locating Docket No. FAA–2008–
1088; 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
mandatory continuing airworthiness
information, the regulatory evaluation,
any comments received, and other
information. The street address for the
Docket Office (phone: 800–647–5527) is
in the ADDRESSES section. Comments
will be available in the AD docket
shortly after receipt.
FOR FURTHER INFORMATION CONTACT:
Michael Schwetz, Aerospace Engineer,
Boston Aircraft Certification Office,
FAA, Engine & Propeller Directorate, 12
New England Executive Park,
Burlington, MA 01803; phone: 781–
238–7761; fax: 781–238–7170; email:
michael.schwetz@faa.gov.
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–2008–1088; Directorate Identifier
2008–NE–15–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 because of 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.
PO 00000
Frm 00006
Fmt 4702
Sfmt 4702
Discussion
On October 3, 2008, we issued AD
2008–21–07, Amendment 39–15691 (73
FR 61346, October 16, 2008), (‘‘AD
2008–21–07’’), for all Dowty Propellers
model R408/6–123–F/17 propellers. AD
2008–21–07 requires initial and
repetitive inspections of the blade
bonded metallic L/E guards for correct
bonding until they accumulate more
than 1,200 FH time in service. AD 2008–
21–07 resulted from three in-service
occurrences of blades losing the bonded
metallic L/E guard. We issued AD 2008–
21–07 to prevent the loss of the bonded
metallic L/E guard of the propeller,
which could result in damage to the
propeller or to the airplane, or injury to
personnel.
Actions Since Existing AD Was Issued
Since we issued AD 2008–21–07,
Dowty Propellers has introduced
updated service bulletins that identify
terminating action to the repetitive
inspection requirements of AD 2008–
21–07. Dowty has also informed us of
the need to add blade part number
697071278–18 to the list of affected
parts. Also since we issued AD 2008–
21–07, the European Aviation Safety
Agency (EASA) has issued AD 2007–
0223R4, dated September 30, 2013,
which requires repetitive inspections of
the affected propellers and clarifies
terminating action.
Relevant Service Information
We reviewed Dowty Propellers Alert
Service Bulletin (ASB) No. D8400–61–
A69, Revision 1, dated September 18,
2007. The ASB describes procedures for
initial and repetitive inspections of
blade bonded metallic L/E guards, and
repair or replacement of blades that fail
inspection. We also reviewed Service
Bulletin (SB) No. D8400–61–70,
Revision 3, dated June 3, 2013, and SB
No. D8400–61–83, Revision 4, dated
June 3, 2013, which provide optional
terminating action for the repetitive
inspection requirement of this proposed
AD.
FAA’s Determination
We are proposing this AD because we
evaluated all the relevant information
and determined the unsafe condition
described previously is likely to exist or
develop in other products of the same
type design.
Proposed AD Requirements
This proposed AD would maintain
the initial and repetitive inspections of
the propeller blade bonded metallic L/
E guards required by AD 2008–21–07
(73 FR 61346, October 16, 2008). This
proposed AD would also provide an
E:\FR\FM\26DEP1.SGM
26DEP1
]]>Agencies
[Federal Register Volume 78, Number 248 (Thursday, December 26, 2013)]
[Proposed Rules]
[Pages 78285-78290]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2013-30893]
=======================================================================
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2013-1064; Directorate Identifier 2012-NM-101-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) 2005-23-
08 that applies to certain Airbus Model A300 B4-605R and B4-622R
airplanes; Model A300 F4-605R airplanes; and Model A300 C4-605R Variant
F airplanes. AD 2005-23-08 required repetitive inspections to detect
cracks of certain attachment holes, installation of new fasteners,
follow-on inspections or repair if necessary, and modification of the
angle fittings of fuselage frame FR47. Since we issued AD 2005-23-08,
we have received reports of cracks found on the horizontal flange of
the Frame 47 internal corner angle fitting while accomplishing the
modification required by AD 2005-23-08. This proposed AD would add new
repetitive ultrasonic inspections for cracks of the center wing box
lower panel; and repair if necessary. This proposed AD also removes
certain airplanes from the applicability. We are proposing this AD to
detect and correct fatigue cracking of
[[Page 78286]]
the forward fitting of fuselage frame FR47, which could result in
reduced structural integrity of the frame.
DATES: We must receive comments on this proposed AD by February 10,
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--EAW (Airworthiness Office), 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 review copies of the 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 MCAI, 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-2013-1064;
Directorate Identifier 2012-NM-101-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 October 31, 2005, we issued AD 2005-23-08, Amendment 39-14366
(70 FR 69056, November 14, 2005). That AD required actions intended to
address an unsafe condition on certain Model A300 B4-601, B4-603, B4-
620, and B4-622 airplanes; Model A300 B4-605R and B4-622R airplanes;
Model A300 F4-605R airplanes; and Model A300 C4-605R Variant F
airplanes.
Since we issued AD 2005-23-08, Amendment 39-14366 (70 FR 69056,
November 14, 2005), the European Aviation Safety Agency (EASA), which
is the Technical Agent for the Member States of the European Community,
has issued EASA Airworthiness Directive 2012-0092, dated May 25, 2012;
correction dated June 4, 2012 (referred to after this as the Mandatory
Continuing Airworthiness Information, or ``the MCAI''), to correct an
unsafe condition for the specified products. The MCAI states:
Prompted by cracks found on the Frame 47 angle fitting, DGAC
France published AD 2000-533-328 [(https://ad.easa.europa.eu/ad/F-2000-533-328R1)] to require [a] repetitive inspection programme for
fuselage frame 47. If not detected and corrected, these cracks could
affect the structural integrity of the Centre Wing Box (CWB) of the
aeroplane.
Subsequent to the publication of a new repetitive inspection
programme for fuselage frame 47 at certain fasteners of the CWB
angle fitting, DGAC France issued AD F-2004-159 [(https://ad.easa.europa.eu/ad/F-2004-159)] [which corresponds to AD 2005-23-
08, Amendment 39-14366 (70 FR 69056, November 14, 2005)],
superseding AD 2000-533-328.
After DGAC France AD F-2004-159 was issued, cracks were
reportedly found on the horizontal flange of the Frame 47 internal
corner angle fitting during accomplishment of routine maintenance
structural inspection and modification in accordance with Airbus SB
A300-57-6050.
Prompted by these findings, Airbus reviewed and amended the
inspection programme for the internal lower angle fitting flange
(horizontal face). The inspection programme for the lower angle
fitting web (vertical face) related to SB A300-57-6049 and internal
lower angle fitting modification programme related to SB A300-57-
6050 remain unchanged.
For the reasons explained above, this new [EASA] AD retains the
requirements of DGAC France AD F-2004-159, which is superseded, and
requires additional repetitive [ultrasonic] inspections [for cracks]
of the CWB lower panel through the ultrasonic method and, depending
on findings, [repair, e.g.,] re-installation of removed fasteners in
transition fit instead of interference.
This [EASA] AD has been republished to correct a typographical
error * * *.
The repetitive interval for the new ultrasonic inspection is either
1,260 flight cycles or 2,720 flight hours, whichever occurs first; or
1,360 flight cycles or 2,200 flight hours, whichever occurs first;
depending on average flight time of the airplane. You may obtain
further information by examining the MCAI in the AD docket.
Relevant Service Information
Airbus has issued Mandatory Service Bulletins A300-57-6049,
Revision 07, dated December 22, 2006, and A300-57-6086, Revision 05,
dated January 30, 2012. 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.
Difference Between This Proposed AD and the MCAI or Service Information
Although the MCAI and service information specify to contact the
manufacturer for instructions to repair certain conditions, this
proposed AD would require repairing those conditions using a method
approved by the Manager, International Branch, ANM-116, Transport
Airplane Directorate, FAA; or the EASA (or its delegated agent; or the
Design Approval Holder with EASA's design organization approval), as
applicable.
[[Page 78287]]
Explanation of Changes to AD 2005-23-08, Amendment 39-14366 (70 FR
69056, November 14, 2005)
In many FAA transport ADs, when the service information specifies
to contact the manufacturer for further instructions if certain
discrepancies are found, we typically include in the AD a requirement
to accomplish the action using a method approved by either the FAA or
the State of Design Authority (or its delegated agent).
We have recently been notified that certain laws in other countries
do not allow such delegation of authority, but some countries do
recognize design approval organizations. In addition, we have become
aware that some U.S. operators have used repair instructions that were
previously approved by a State of Design Authority or a Design Approval
Holder (DAH) as a method of compliance with this provision in FAA ADs.
Frequently, in these cases, the previously approved repair instructions
come from the airplane structural repair manual or the DAH repair
approval statements that were not specifically developed to address the
unsafe condition corrected by the AD. Using repair instructions that
were not specifically approved for a particular AD creates the
potential for doing repairs that were not developed to address the
unsafe condition identified by the MCAI AD, the FAA AD, or the
applicable service information, which could result in the unsafe
condition not being fully corrected.
To prevent the use of repairs that were not specifically developed
to correct the unsafe condition, this proposed AD would require that
the repair approval specifically refer to the FAA AD. This change is
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 use the
phrase ``its delegated agent, or by the DAH with State of Design
Authority design organization approval, as applicable'' in this
proposed AD to refer to an DAH authorized to approve required repairs
for this proposed AD.
Explanation of Change to Applicability
AD 2005-23-08, Amendment 39-14366 (70 FR 69056, November 14, 2005),
includes Airbus Model A300 B4-601 airplanes in the applicability.
However, this proposed AD does not include Model A300 B4-601 airplanes
because these airplanes are no longer in service.
Costs of Compliance
We estimate that this proposed AD affects about 65 products of U.S.
registry.
We estimate the following costs to comply with this proposed AD:
Estimated Costs
----------------------------------------------------------------------------------------------------------------
Average labor
Action Work hours rate per hour Parts Cost per airplane
----------------------------------------------------------------------------------------------------------------
Inspection [retained action from 13................. $85 $0................. $1,105.
existing AD] AD
2005[dash]23[dash]08, Amendment
39[dash]14366 (70 FR 69056,
November 14, 2005).
Inspection [retained action from 30................. 85 Between $6,637 and Between $9,187 and
existing AD] AD 2005-23-08, $19,091. $21,641, per
Amendment 39-14366 (70 FR 69056, inspection cycle.
November 14, 2005).
Modification [retained action Between 65 and 365. 85 $3,370............. Between $8,895 and
from existing AD] AD 2005-23-08, $34,395.
Amendment 39-14366 (70 FR 69056,
November 14, 2005).
New ultrasonic inspection........ 35................. 85 Between $11,750 and Between $14,725 and
$18,720. $21,695 per
inspection cycle.
----------------------------------------------------------------------------------------------------------------
We have received no definitive data that would enable us to provide
cost estimates for the on-condition actions specified in this proposed
AD.
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);
[[Page 78288]]
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.
We prepared a regulatory evaluation of the estimated costs to
comply with this proposed AD and placed it in the AD docket.
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)
2005-23-08, Amendment 39-14366 (70 FR 69056, November 14, 2005) and
adding the following new AD:
Airbus: Docket No. FAA-2013-1064; Directorate Identifier 2012-NM-
101-AD.
(a) Comments Due Date
We must receive comments by February 10, 2014.
(b) Affected ADs
This AD supersedes AD 2005-23-08, Amendment 39-14366 (70 FR
69056, November 14, 2005).
(c) Applicability
This AD applies to Airbus Model B4-603, B4-620, and B4-622
airplanes; Model A300 B4-605R and B4-622R airplanes; Model A300 F4-
605R airplanes; and Model A300 C4-605R Variant F airplanes;
certificated in any category; except airplanes on which Airbus
Modification 12171 or 12249 has been embodied in production, or on
which Airbus Service Bulletin A300-57-6069 has been embodied in
service.
(d) Subject
Air Transport Association (ATA) of America Code 57: Wings.
(e) Reason
This AD was prompted by reports of cracks found on the
horizontal flange of the Frame 47 internal corner angle fitting
while accomplishing the modification required by AD 2005-23-08,
Amendment 39-14366 (70 FR 69056, November 14, 2005). We are issuing
this AD to detect and correct fatigue cracking of the forward
fitting of fuselage frame FR47, which could result in reduced
structural integrity of the frame.
(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 Inspections for Attachment Holes on the Internal Angles of
the Wing Center Box, and Corrective Action
This paragraph restates the requirements of paragraphs (f), (g),
and (h) of AD 2005-23-08, Amendment 39-14366 (70 FR 69056, November
14, 2005), with revised service information. Perform a rotating
probe inspection to detect cracking of the applicable attachment
holes on the left and right internal angles of the wing center box
in accordance with the Accomplishment Instructions of Airbus Service
Bulletin A300-57-6049, Revision 06, dated July 15, 2004; or Airbus
Mandatory Service Bulletin A300-57-6049, Revision 07, dated December
22, 2006. Do the inspection at the applicable time specified by
paragraph 1.E.(2), Accomplishment Timescale, of Airbus Service
Bulletin A300-57-6049, Revision 06, dated July 15, 2004; except as
required by paragraph (j) of this AD. Repeat the rotating probe
inspection specified in this paragraph thereafter at intervals not
to exceed the applicable interval specified in Airbus Mandatory
Service Bulletin A300-57-6049, Revision 06, dated July 15, 2004,
except that all touch-and-go landings must be counted in determining
the total number of flight cycles between consecutive inspections.
As of the effective date of this AD, only Airbus Mandatory Service
Bulletin A300-57-6049, Revision 07, dated December 22, 2006, may be
used to accomplish the actions required by this paragraph.
(1) If no cracking is found during any inspection required by
paragraph (g) of this AD: Prior to further flight, install new
fasteners in accordance with the Accomplishment Instructions of
Airbus Service Bulletin A300-57-6049, Revision 06, dated July 15,
2004; or Airbus Mandatory Service Bulletin A300-57-6049, Revision
07, dated December 22, 2006. As of the effective date of this AD,
only Airbus Mandatory Service Bulletin A300-57-6049, Revision 07,
dated December 22, 2006, may be used to accomplish the actions
required by this paragraph.
(2) If any cracking is found during any inspection required by
paragraph (g) of this AD: Prior to further flight, perform
applicable corrective actions (including reaming, drilling, drill-
stopping holes, chamfering, performing follow-on inspections, and
installing new or oversize fasteners) in accordance with the
Accomplishment Instructions of Airbus Service Bulletin A300-57-6049,
Revision 06, dated July 15, 2004; or Airbus Mandatory Service
Bulletin A300-57-6049, Revision 07, dated December 22, 2006; except
as required by paragraph (k) of this AD. As of the effective date of
this AD, only Airbus Mandatory Service Bulletin A300-57-6049,
Revision 07, dated December 22, 2006, may be used to accomplish the
actions required by this paragraph.
(h) Retained Inspections for Attachment Holes in the Horizontal Flange
of the Internal Corner Angle Fitting of Fuselage Frame FR47, and
Corrective Action
This paragraph restates the requirements of paragraphs (i), (j),
and (k) of AD 2005-23-08, Amendment 39-14366 (70 FR 69056, November
14, 2005), with revised service information. Perform a rotating
probe inspection to detect cracking of the applicable attachment
holes in the horizontal flange of the internal corner angle fitting
of fuselage frame FR47, in accordance with the Accomplishment
Instructions of Airbus Service Bulletin A300-57-6086, Revision 01,
dated April 2, 2002; or Airbus Mandatory Service Bulletin A300-57-
6086, Revision 05, dated January 30, 2012. Do the inspection at the
applicable time specified in paragraph 1.E., Compliance, of Airbus
Service Bulletin A300-57-6086, Revision 01, dated April 2, 2002,
except as provided by paragraph (j) of this AD; or within 1,500
flight cycles after July 8, 2002 (the effective date of AD 2002-11-
04, amendment 39-12765 (67 FR 38193, June 3, 2002)); whichever
occurs later. Repeat the rotating probe inspection specified in this
paragraph thereafter at intervals not to exceed the applicable
interval specified in Airbus Service Bulletin A300-57-6086, dated
June 6, 2000, except that all touch-and-go landings must be counted
in determining the total number of flight cycles between consecutive
inspections. As of the effective date of this AD, only Airbus
Mandatory Service Bulletin A300-57-6086, Revision 05, dated January
30, 2012, may be used to accomplish the actions required by this
paragraph.
(1) If no cracking is found during any inspection required by
paragraph (h) of this AD: Prior to further flight, install new
fasteners in accordance with the Accomplishment Instructions of
Airbus Service Bulletin A300-57-6086, Revision 01, dated April 2,
2002; or Airbus Mandatory Service Bulletin A300-57-6086, Revision
05, dated January 30, 2012. As of the effective date of this AD,
only Airbus Mandatory Service Bulletin A300-57-6086, Revision 05,
dated January 30, 2012, may be used to accomplish the actions
required by this paragraph.
(2) If any cracking is found during any inspection required by
paragraph (h) of this AD: Prior to further flight, perform
applicable corrective actions (including inspecting hole T if any
cracking is found at hole G, reaming the holes, and installing
oversize fasteners) in accordance with the Accomplishment
Instructions of Airbus Service Bulletin A300-57-6086, Revision 01,
dated April 2, 2002; or Airbus Mandatory Service Bulletin A300-57-
6086, Revision 05, dated January 30, 2012; except as required by
paragraph (k) of this AD. As of the effective date of this AD, only
Airbus Mandatory Service Bulletin A300-57-6086, Revision 05, dated
January 30, 2012, may be used to accomplish the actions required by
this paragraph.
(i) Retained Modification of Angle Fittings of the Wing Center Box
This paragraph restates the requirements of paragraph (l) of AD
2005-23-08, Amendment 39-14366 (70 FR 69056, November 14, 2005).
[[Page 78289]]
Modify the left and right internal angle fittings of the wing center
box. The modification includes performing a rotating probe
inspection to detect cracking, repairing cracks, cold expanding
holes, and installing medium interference fitting bolts. Perform the
modification in accordance with the Accomplishment Instructions of
Airbus Service Bulletin A300-57-6050, Revision 03, dated May 31,
2001; and at the applicable time specified by paragraph 1.B.(4),
Accomplishment Timescale, of Airbus Service Bulletin A300-57-6050,
Revision 03, dated May 31, 2001; except as required by paragraphs
(j) and (k) of this AD.
(j) Retained Compliance Time Exception to Service Information Specified
in Paragraphs (g), (h), and (i) of This AD
This paragraph restates the requirements of paragraph (m) of AD
2005-23-08, Amendment 39-14366 (70 FR 69056, November 14, 2005).
Where the service information specified in paragraphs (g), (h), and
(i) of this AD specify a grace period relative to receipt of the
service bulletin, this AD requires compliance within the applicable
grace period following December 19, 2005, (the effective date of AD
2005-23-08), if the threshold has been exceeded.
(k) Retained Corrective Action Exception to Service Information
Specified in Paragraphs (g), (h), and (i) of This AD
This paragraph restates the requirements of paragraph (n) of AD
2005-23-08, Amendment 39-14366 (70 FR 69056, November 14, 2005). If
any crack is detected during any inspection required by paragraph
(g), (h), or (i) of this AD, and the applicable service information
specifies to contact the manufacturer for disposition of certain
corrective actions: Prior to further flight, repair in accordance
with a method approved by the Manager, International Branch, ANM-
116, Transport Airplane Directorate, FAA; or the Direction
G[eacute]n[eacute]rale de l'Aviation Civile (DGAC) (or its delegated
agent).
(l) Credit for Previous Actions
(1) This paragraph restates the credit provided by paragraph (o)
of AD 2005-23-08, Amendment 39-14366 (70 FR 69056, November 14,
2005): This paragraph provides credit for actions required by
paragraph (h) of this AD, if those actions were performed before
December 19. 2005, (the effective date of AD 2005-23-08) using
Airbus Service Bulletin A300-57-6086, dated June 6, 2000.
(2) This paragraph restates the credit provided by paragraph (p)
of AD 2005-23-08, Amendment 39-14366 (70 FR 69056, November 14,
2005): This paragraph provides credit for the modification required
by paragraph (i) of this AD, if the modification was performed
before December 19, 2005, (the effective date of AD 2005-23-08)
using Airbus Service Bulletin A300-57-6050, Revision 02, dated
February 10, 2000.
(m) New Requirements of This AD: Repetitive Ultrasonic Inspections and
Corrective Action
(1) For airplanes on which Airbus Service Bulletin A300-57-6050,
Revision 03, dated May 31, 2001, has not been done, or on which
Airbus Modification 10155 has been done: Perform an ultrasonic
inspection for cracking of the left- and right-hand aft bottom panel
of the center wing box (CWB) in accordance with the Accomplishment
Instructions of Airbus Mandatory Service Bulletin A300-57-6086,
Revision 05, dated January 30, 2012. Do the inspection at the later
of the times specified in paragraphs (m)(1)(i) and (m)(1)(ii) of
this AD. If any cracking is found, before further flight, repair
using a method approved by the Manager, International Branch, ANM-
116, Transport Airplane Directorate, FAA; or EASA (or its delegated
agent, or the Design Approval Holder with EASA's design organization
approval, as applicable. For a repair method to be approved, the
repair approval must specifically refer to this AD. Repeat the
inspection thereafter at intervals not to exceed the applicable
interval specified in paragraph 1.E.(2), Accomplishment Timescale,
of Airbus Mandatory Service Bulletin A300-57-6086, Revision 05,
dated January 30, 2012.
(i) Within 13,400 flight cycles or 34,600 flight hours after the
first flight of the airplane, whichever occurs first.
(ii) Within 650 flight cycles or 8 months after the effective
date of this AD, whichever occurs first.
(2) For airplanes on which Airbus Service Bulletin A300-57-6050,
Revision 03, dated May 31, 2001, has been done: Perform an
ultrasonic inspection for cracking of the left- and right-hand aft
bottom panel of the center wing box (CWB), in accordance with the
Accomplishment Instructions of Airbus Mandatory Service Bulletin
A300-57-6086, Revision 05, dated January 30, 2012. Do the inspection
at the later of the times specified in paragraphs (m)(2)(i) and
(m)(2)(ii) of this AD. If any cracking is found, before further
flight repair using a method approved by the Manager, International
Branch, ANM-116, Transport Airplane Directorate, FAA; or EASA (or
its delegated agent, or the Design Approval Holder with EASA's
design organization approval), as applicable. For a repair method to
be approved, the repair approval must specifically refer to this AD.
Repeat the inspection thereafter at intervals not to exceed the
applicable interval specified in paragraph 1.E.(2), Accomplishment
Timescale, of Airbus Mandatory Service Bulletin A300-57-6086,
Revision 05, dated January 30, 2012.
(i) Within 13,400 flight cycles or 34,600 flight hours after
accomplishing Airbus Service Bulletin A300-57-6050, whichever occurs
first.
(ii) Within 650 flight cycles or 8 months after the effective
date of this AD, whichever occurs first.
(n) New Reporting Requirement
Submit a report of the findings (both positive and negative) of
the inspection required by paragraph (m) of this AD to the Design
Approval Holder, at the applicable time specified in paragraph
(n)(1) or (n)(2) of this AD. The report must include the inspection
results, a description of any discrepancies found, the airplane
serial number, and the number of flight cycles and flight hours on
the airplane. The inspection report form in Appendix 01 of Airbus
Mandatory Service Bulletin A300-57-6086, Revision 05, dated January
30, 2012, may be used.
(1) If the inspection was done on or after the effective date of
this AD: Submit the report within 30 days after the inspection.
(2) If the inspection was done before the effective date of this
AD: Submit the report within 30 days after the effective date of
this AD.
(o) 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 in accordance with AD 2005-23-08, Amendment 39-
14366 (70 FR 69056, November 14, 2005), are approved as AMOCs for
the corresponding provision of this AD.
(2) Airworthy Product: For any requirement in this AD to obtain
corrective actions from a manufacturer, use these actions if they
are FAA-approved. Corrective actions are considered FAA-approved if
they were approved by the State of Design Authority (or its
delegated agent, or the Design Approval Holder with a State of
Design Authority's design organization approval), as applicable. For
a repair method to be approved, the repair approval must
specifically refer to this AD. You are required to ensure the
product is airworthy before it is returned to service.
(p) Related Information
(1) Refer to Mandatory Continuing Airworthiness Information EASA
Airworthiness Directive 2012-0092, dated May 25, 2012: Correction
dated June 4, 2012, for related information. This MCAI may be found
in the AD docket on the Internet at https://www.regulations.gov.
(2) For service information identified in this AD, contact
Airbus SAS--EAW (Airworthiness Office), 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.
(3) You may review copies of the referenced service information
at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW.,
Renton, WA. For information
[[Page 78290]]
on the availability of this material at the FAA, call 425-227-1221.
Issued in Renton, Washington, on December 17, 2013.
Jeffrey E. Duven,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2013-30893 Filed 12-24-13; 8:45 am]
BILLING CODE 4910-13-P
