Airworthiness Directives; Airbus Airplanes, 65879-65885 [2014-26356]
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Federal Register / Vol. 79, No. 215 / Thursday, November 6, 2014 / Rules and Regulations
applicant than the terms and conditions
that are generally applicable to
residential real property loans offered
by the same lender to other borrowers
in comparable circumstances.
(iii) A covered employee who seeks or
obtains a real property loan from a
national bank, Federal savings
association or a subsidiary of a national
bank or Federal savings association or
whose spouse or minor child obtains a
real property loan under the
requirements of paragraph (b)(4)(ii)
above must observe from the time of the
initial application any recusal
established under OCC ethics policy.
(5) Pre-existing credit. (i) This section
does not prohibit a covered OCC
employee, or spouse or minor child of
a covered OCC employee from retaining
a loan or extension of credit from a
national bank or Federal savings
association on its original terms, and
subject to any recusal established under
OCC ethics policy, if the loan or
extension of credit:
(A) Was incurred prior to employment
by the OCC;
(B) Was obtained from a lender that
was not supervised by the OCC at the
time it was obtained; or
(C) Is held by a national bank or
Federal savings association or
subsidiary thereof as the result of the
sale or transfer of a loan to the national
bank or Federal savings association or
the conversion or merger of the lender
into a national bank or Federal savings
association.
(ii) Any renewal or renegotiation of a
pre-existing loan or extension of credit
will be treated as a new loan subject to
the prohibitions in paragraph (b)(1) of
this section.
*
*
*
*
*
(d) Prohibited recommendations.
Employees of the OCC shall not make
recommendations or suggestions,
directly or indirectly, concerning the
acquisition or sale or other divestiture of
securities of any commercial bank
(including both national and statechartered banks), Federal savings
association, state savings association,
affiliate of these institutions (including
bank holding companies, savings and
loan holding companies, and any nonbank subsidiaries of either type of
holding company), or foreign bank that
owns a commercial bank or savings
association in the United States.
(e) Prohibited purchase of assets. No
employee of the OCC, or spouse or
minor child of an OCC employee, shall
purchase, directly or indirectly, an asset
(i.e. real property, automobiles,
furniture, or similar items) from a
national bank or Federal savings
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association or an affiliate of a national
bank or a Federal savings association,
including a bank or savings and loan
holding company, unless it is sold at a
public auction or by other means which
ensure that the selling price is the
asset’s fair market value.
(f) Outside employment—(1)
Prohibition on Outside Employment. No
covered OCC employee shall perform
services for compensation for any bank,
savings association or a bank or savings
association affiliate, or for any officer,
director or employee of, or for any
person connected in any capacity with
a bank, savings association or bank or
savings association affiliate.
(2) * * *
(i) An OCC examiner; and
*
*
*
*
*
§ 3101.109
■
§ 3101.110
■
[Removed]
6. Remove § 3101.110.
§ 3101.111
■
[Removed]
5. Remove § 3101.109.
[Removed]
7. Remove reserved § 3101.111.
Dated: October 14, 2014.
By the Department of the Treasury.
Christopher J. Meade,
General Counsel.
Dated: October 24, 2014.
By the Office of Government Ethics.
Walter M. Shaub,
Director.
[FR Doc. 2014–26173 Filed 11–5–14; 8:45 am]
BILLING CODE 4810–25–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 25
[Docket No. FAA–2013–0894; Special
Conditions No. 25–532–SC]
Special Conditions: Airbus A350–900
Series Airplane; Interaction of Systems
and Structures
Federal Aviation
Administration (FAA), DOT.
ACTION: Final special conditions, request
for comments; correction.
65879
FOR FURTHER INFORMATION CONTACT:
Todd Martin, FAA, Airframe/Cabin
Safety, ANM–115, Transport Airplane
Directorate, Aircraft Certification
Service, 1601 Lind Avenue SW.,
Renton, Washington, 98057–3356;
telephone (425) 227–1178; facsimile
(425) 227–1320.
SUPPLEMENTARY INFORMATION: The final
special conditions document designated
as ‘‘Docket No. FAA–2013–0894; Notice
No. 25–13–16–SC’’ was published in the
Federal Register on December 20, 2013
(78 FR 76980). The document issued
special conditions pertaining to
interaction of systems and structures on
Airbus A350–900 series airplanes.
As published, the document
contained two errors: One referring to
the document’s special conditions stage,
‘‘Notice no.,’’ instead of ‘‘Special
Conditions No.;’’ and one in the special
conditions number itself, 25–13–16–SC
(a notice number), instead of 25–532–SC
(the assigned final special conditions
number).
Because this error and correction do
not affect the regulatory content of the
special conditions, the special
conditions are not being re-published.
Correction
In the final special conditions, request
for comments document [FR Doc. 2013–
30235, Filed 12–19–13; 8:45 a.m.]
published on December 20, 2013 (78 FR
76980), make the following correction:
On page 76980, in the first column, in
the heading, correct ‘‘Notice No. 25–13–
16–SC’’ to read ‘‘Special Conditions No.
25–532–SC’’.
Issued in Renton, Washington, on October
31, 2014.
Michael Kaszycki,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. 2014–26341 Filed 11–5–14; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
AGENCY:
This document corrects errors
that appeared in final special conditions
docket no. FAA–2013–0894, which was
published in the Federal Register on
December 20, 2013 (78 FR 76980). The
errors are in the document’s special
conditions stage (notice vs. final) and
special conditions number.
DATES: This action is effective
November 6, 2014.
SUMMARY:
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14 CFR Part 39
[Docket No. FAA–2013–1064; Directorate
Identifier 2012–NM–101–AD; Amendment
39–17991; AD 2014–20–18]
RIN 2120–AA64
Airworthiness Directives; Airbus
Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
AGENCY:
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Federal Register / Vol. 79, No. 215 / Thursday, November 6, 2014 / Rules and Regulations
We are superseding
Airworthiness Directive (AD) 2005–23–
08 for 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.
This new AD adds new repetitive
ultrasonic inspections for cracks of the
center wing box lower panel; and repair
if necessary. This new AD also removes
certain airplanes from the applicability.
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. 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.
DATES: This AD becomes December 11,
2014.
The Director of the Federal Register
approved the incorporation by reference
of certain publications listed in this AD
as of December 11, 2014.
The Director of the Federal Register
approved the incorporation by reference
of certain other publications listed in
this AD as of December 19, 2005 (70 FR
69056, November 14, 2005).
The Director of the Federal Register
approved the incorporation by reference
of a certain other publication listed in
this AD as of July 8, 2002 (67 FR 38193,
June 3, 2002).
ADDRESSES: You may examine the AD
docket on the Internet at https://
www.regulations.gov/
#!docketDetail;D=FAA-2013-1064; or in
person at the Docket Management
Facility, U.S. Department of
Transportation, Docket Operations, M–
30, West Building Ground Floor, Room
W12–140, 1200 New Jersey Avenue SE.,
Washington, DC.
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. 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.
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SUMMARY:
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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:
FOR FURTHER INFORMATION CONTACT:
Discussion
We issued a notice of proposed
rulemaking (NPRM) to amend 14 CFR
part 39 to supersede AD 2005–23–08,
Amendment 39–14366 (70 FR 69056,
November 14, 2005). AD 2005–23–08
applied to 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. The NPRM
published in the Federal Register on
December 26, 2013 (78 FR 78285).
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/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
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]
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of the CWB lower panel through the
ultrasonic method and, depending on
findings, [e.g., repair] 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 examine
the MCAI in the AD docket on the
Internet at https://www.regulations.gov/
#!documentDetail;D=FAA-2013-10640002.
Comments
We gave the public the opportunity to
participate in developing this AD. The
following presents the comments
received on the NPRM (78 FR 78285,
December 26, 2013) and the FAA’s
response to each comment.
Requests To Remove Requirement To
Refer to This AD in Repair Approvals
Airlines for America, Inc. (A4A), on
behalf of seven affected member
airlines, requested that we revise
paragraphs (m)(1), (m)(2), and (o)(2) of
the NPRM (78 FR 78285, December 26,
2013) to remove the requirement to
include the AD reference in repair
approvals. The commenters have made
this request because the proposed
requirement is overly broad and would
add significant cost and complexity to
their operations. The commenters were
concerned that this proposed
requirement would set a precedent for
how repairs are approved, and could
negatively affect all U.S. operators of
foreign-manufactured airplanes.
We concur with the commenters’
request to remove from this AD the
requirement that repair approvals must
specifically refer to this 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 the NPRM (78 FR 78285, December
26, 2013), we proposed to prevent the
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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 this 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 ‘‘the Design Approval Holder
(DAH) with a State of Design
Authority’s design organization
approval (DOA)’’ to refer to a DAH
authorized to approve required repairs
for the proposed AD.
One commenter to the NPRM (78 FR
78285, December 26, 2013), United
Parcel Service (UPS), 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
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
that paragraph and retitled it
‘‘Contacting the Manufacturer.’’ This
paragraph now clarifies that for any
requirement in this AD to obtain
corrective actions from a manufacturer,
the actions must be accomplished using
a method approved by the FAA, 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
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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 afforded previously 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 AD
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.
Other commenters pointed out that in
many cases the foreign manufacturer’s
service bulletin and the foreign
authority’s MCAI may have been issued
some time before the FAA AD.
Therefore, the DOA may have provided
U.S. operators with an approved repair,
developed with full awareness of the
unsafe condition, before the FAA AD is
issued. Under these circumstances, to
comply with the FAA AD, the operator
would be required to go back to the
manufacturer’s DOA and obtain a new
approval document, adding time, and
expense to the compliance process with
no safety benefit.
Based on these comments, we
removed from this AD the requirement
that the DAH-provided repair
specifically refer to this AD. Before
adopting such a requirement in the
future, the FAA will coordinate with
affected DAHs and verify they are
prepared to implement means to ensure
that their repair approvals consider the
unsafe condition addressed in the AD.
Any such requirements will be adopted
through the normal AD rulemaking
process, including notice-and-comment
procedures, when appropriate.
We have also decided not to include
a generic reference to either the
‘‘delegated agent’’ or the ‘‘DAH with
State of Design Authority design
organization approval’’ for new
requirements, but instead we will
provide the specific delegation approval
granted by the State of Design Authority
for the DAH.
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65881
Request To Revise Costs of Compliance
One commenter, FedEx, requested
assurance that two inspections (the
rotating probe of the attachment holes of
the horizontal flange of the internal
corner angle fitting, and the ultrasonic
inspection of the aft bottom panel of the
center wing box) specified in the NPRM
(78 FR 78285, December 26, 2013) are to
be conducted as two separate
inspections at two separate thresholds
and intervals. FedEx observed that both
inspections are contained in the same
service information, and that these two
inspections appear to be combined in
the Costs of Compliance paragraph of
the NPRM. FedEx requested that the
estimated costs be presented separately
for the two inspection actions, and
added that the Costs of Compliance
paragraph should specify 4 work-hours
for the new ultrasonic inspection.
We agree to clarify the Costs of
Compliance paragraph. There are two
inspection actions (rotating probe and
ultrasonic inspections) identified in
Airbus Service Bulletin A300–57–6086,
Revision 05, dated January 30, 2012,
and these are listed separately in the
Costs of Compliance paragraph. The
second row of the table in the Costs of
Compliance paragraph should reflect
the costs for the rotating probe
inspections identified in Airbus Service
Bulletin A300–57–6086, Revision 05,
dated January 30, 2012; we have revised
the second row of the table in the Costs
of Compliance paragraph accordingly.
We have also revised the fourth row of
the table in the Costs of Compliance
paragraph to refer to Airbus Service
Bulletin A300–57–6086, Revision 05,
dated January 30, 2012, to reflect costs
for the new ultrasonic inspection.
In addition, we agree with FedEx that
the ultrasonic inspection takes 4 workhours, as specified in Airbus Service
Bulletin A300–57–6086, Revision 05,
dated January 30, 2012. In addition,
Airbus Service Bulletin A300–57–6086,
Revision 05, dated January 30, 2012,
specifies 12 work-hours for access and
close procedures. Therefore, we have
revised the work-hours for the
ultrasonic inspection specified in the
fourth row of the table in the Costs of
Compliance paragraph from 35 to 16
work-hours.
Conclusion
We reviewed the available data,
including the comments received, and
determined that air safety and the
public interest require adopting this AD
with the changes described previously
and minor editorial changes. We have
determined that these changes:
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• Are consistent with the intent that
was proposed in the NPRM (78 FR
78285, December 26, 2013) for
correcting the unsafe condition; and
• Do not add any additional burden
upon the public than was already
proposed in the NPRM (78 FR 78285,
December 26, 2013).
We also determined that these
changes will not increase the economic
burden on any operator or increase the
scope of this AD.
Costs of Compliance
We estimate that this AD affects 65
airplanes of U.S. registry.
We estimate the following costs to
comply with this AD:
ESTIMATED COSTS
Average
labor rate
per hour
Action
Work hours
Inspection for attachment holes on internal angles [retained action from AD 2005–23–08,
Amendment 39–14366 (70 FR 69056, November 14, 2005)].
Rotating probe inspections for attachment holes
in the horizontal flange (specified in Airbus
Service Bulletin A300–57–6086, Revision 05,
dated January 30, 2012) [retained action
from AD 2005–23–08, Amendment 39–14366
(70 FR 69056, November 14, 2005)].
Modification [retained action from AD 2005–23–
08, Amendment 39–14366 (70 FR 69056,
November 14, 2005)].
New ultrasonic inspections of the aft bottom
panel of the center wing box (specified in Airbus Service Bulletin A300–57–6086, Revision
05, dated January 30, 2012).
13 .................................
$85
30 .................................
We have received no definitive data
that would enable us to provide cost
estimates for the on-condition actions
specified in this AD.
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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
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
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Parts
Cost per airplane
$0 .................................
$1,105.
85
Between $6,637 and
$19,091.
Between $9,187 and
$21,641 per inspection
cycle.
Between 65 and 365 ...
85
$3,370 ..........................
Between $8,895 and
$34,395.
16 .................................
85
Between $11,750 and
$18,720.
Between $13,110 and
$20,080 per inspection
cycle.
detail the scope of the Agency’s
authority.
We are issuing this rulemaking under
the authority described in ‘‘Subtitle VII,
Part A, Subpart III, Section 44701:
General requirements.’’ Under that
section, Congress charges the FAA with
promoting safe flight of civil aircraft in
air commerce by prescribing regulations
for practices, methods, and procedures
the Administrator finds necessary for
safety in air commerce. This regulation
is within the scope of that authority
because it addresses an unsafe condition
that is likely to exist or develop on
products identified in this rulemaking
action.
Regulatory Findings
We determined that this AD will not
have federalism implications under
Executive Order 13132. This AD will
not have a substantial direct effect on
the States, on the relationship between
the national government and the States,
or on the distribution of power and
responsibilities among the various
levels of government.
For the reasons discussed above, I
certify that this AD:
1. Is not a ‘‘significant regulatory
action’’ under Executive Order 12866;
2. Is not a ‘‘significant rule’’ under the
DOT Regulatory Policies and Procedures
(44 FR 11034, February 26, 1979);
3. Will not affect intrastate aviation in
Alaska; and
4. Will not have a significant
economic impact, positive or negative,
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on a substantial number of small entities
under the criteria of the Regulatory
Flexibility Act.
Examining the AD Docket
You may examine the AD docket on
the Internet at https://
www.regulations.gov/
#!docketDetail;D=FAA-2013-1064; or in
person at the Docket Management
Facility between 9 a.m. and 5 p.m.,
Monday through Friday, except Federal
holidays. The AD docket contains this
AD, the regulatory evaluation, any
comments received, and other
information. The street address for the
Docket Operations office (telephone
800–647–5527) is in the ADDRESSES
section.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation
safety, Incorporation by reference,
Safety.
Adoption of the Amendment
Accordingly, under the authority
delegated to me by the Administrator,
the FAA amends 14 CFR part 39 as
follows:
PART 39—AIRWORTHINESS
DIRECTIVES
1. The authority citation for part 39
continues to read as follows:
■
Authority: 49 U.S.C. 106(g), 40113, 44701.
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§ 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:
■
2014–20–18 Airbus: Amendment 39–17991.
Docket No. FAA–2013–1064; Directorate
Identifier 2012–NM–101–AD.
(a) Effective Date
This AD becomes effective December 11,
2014.
(b) Affected ADs
This AD replaces 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.
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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 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 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
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thereafter at intervals not to exceed the
applicable interval specified in Airbus
Service Bulletin A300–57–6049, Revision 06,
dated July 15, 2004, except that all touchand-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 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 Service
Bulletin A300–57–6049, Revision 07, dated
December 22, 2006. As of the effective date
of this AD, only Airbus 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 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 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 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
PO 00000
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Fmt 4700
Sfmt 4700
65883
the total number of flight cycles between
consecutive inspections. As of the effective
date of this AD, only Airbus 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 Service
Bulletin A300–57–6086, Revision 05, dated
January 30, 2012. As of the effective date of
this AD, only Airbus 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 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
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).
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.
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Federal Register / Vol. 79, No. 215 / Thursday, November 6, 2014 / Rules and Regulations
(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).
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(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 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 the European Aviation
Safety Agency (EASA); or Airbus’s EASA
Design Organization Approval (DOA). Repeat
the inspection thereafter at intervals not to
exceed the applicable interval specified in
paragraph 1.E.(2), Accomplishment
Timescale, of Airbus 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
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15:26 Nov 05, 2014
Jkt 235001
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
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 the European
Aviation Safety Agency (EASA); or Airbus’s
EASA Design Organization Approval (DOA).
Repeat the inspection thereafter at intervals
not to exceed the applicable interval
specified in paragraph 1.E.(2),
Accomplishment Timescale, of Airbus
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 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.
(i) Before using any approved AMOC,
notify your appropriate principal inspector,
or lacking a principal inspector, the manager
of the local flight standards district office/
certificate holding district office. The AMOC
PO 00000
Frm 00012
Fmt 4700
Sfmt 4700
approval letter must specifically reference
this AD.
(ii) 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) Contacting the Manufacturer: As of the
effective date of this AD, for any requirement
in this AD to obtain corrective actions from
a manufacturer, the action must be
accomplished using a method approved by
the Manager, International 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.
(p) Related Information
(1) Refer to Mandatory Continuing
Airworthiness Information (MCAI) 2012–
0092, dated May 25, 2012; Correction dated
June 4, 2012; for related information. You
may examine the MCAI in the AD docket on
the Internet at https://www.regulations.gov/
#!documentDetail;D=FAA-2013-10640002.
(2) Service information identified in this
AD that is not incorporated by reference is
available at the addresses specified in
paragraphs (q)(5) and (q)(6) of this AD.
(q) Material Incorporated by Reference
(1) The Director of the Federal Register
approved the incorporation by reference
(IBR) of the service information listed in this
paragraph under 5 U.S.C. 552(a) and 1 CFR
part 51.
(2) You must use this service information
as applicable to do the actions required by
this AD, unless this AD specifies otherwise.
(3) The following service information was
approved for IBR on December 11, 2014.
(i) Airbus Service Bulletin A300–57–6049,
Revision 07, dated December 22, 2006.
(ii) Airbus Service Bulletin A300–57–6086,
Revision 05, dated January 30, 2012.
(4) The following service information was
approved for IBR on December 19, 2005 (70
FR 69056, November 14, 2005).
(i) Airbus Service Bulletin A300–57–6049,
excluding Appendix 01, Revision 06, dated
July 15, 2004.
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Federal Register / Vol. 79, No. 215 / Thursday, November 6, 2014 / Rules and Regulations
(ii) Airbus Service Bulletin A300–57–6050,
Revision 03, dated May 31, 2001. This
document contains the effective pages
specified in paragraphs (q)(4)(ii)(A),
(q)(4)(ii)(B), (q)(4)(ii)(C), and (q)(4)(ii)(D) of
this AD.
(A) Pages 1, 4, 10A through 11, 75, and 76
are identified as Revision 03, dated May 31,
2001.
(B) Pages 2, 8, 9, 17 through 32, 41, 42, 57,
58, 61 through 63, and 77 are identified as
Revision 02, dated February 10, 2000.
(C) Pages 3, 5 through 7, 10, 12, 33, 34, 37,
38, 47, 59, and 60 are identified as Revision
01, dated May 31, 1999.
(D) Pages 13 through 16, 35, 36, 39, 40, 43
through 46, 48 through 56, and 64 through
74 are identified as original, dated September
9, 1994.
(iii) Airbus Service Bulletin A300–57–
6086, Revision 01, dated April 2, 2002.
(5) The following service information was
approved for IBR on July 8, 2002 (67 FR
38193, June 3, 2002).
(i) Airbus Service Bulletin A300–57–6086,
dated June 6, 2000.
(ii) Reserved.
(6) 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.airwortheas@airbus.com; Internet https://
www.airbus.com.
(7) 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.
(8) You may view this service information
that is incorporated by reference at the
National Archives and Records
Administration (NARA). For information on
the availability of this material at NARA, call
202–741–6030, or go to: https://
www.archives.gov/federal-register/cfr/ibrlocations.html.
Issued in Renton, Washington, on
September 24, 2014.
Michael Kaszycki,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. 2014–26356 Filed 11–5–14; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2014–0288; Directorate
Identifier 2013–NM–101–AD; Amendment
39–18009; AD 2014–22–04]
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RIN 2120–AA64
Airworthiness Directives; The Boeing
Company Airplanes
Federal Aviation
Administration (FAA), DOT.
AGENCY:
VerDate Sep<11>2014
15:26 Nov 05, 2014
Jkt 235001
ACTION:
Final rule.
We are adopting a new
airworthiness directive (AD) for certain
The Boeing Company Model DC–9–10,
DC–9–20, and DC–9–30 series airplanes.
This AD was prompted by an evaluation
by the design approval holder (DAH)
indicating that the improved (shotpeened) aft fuselage non-ventral
pressure bulkhead tee is subject to
widespread fatigue damage (WFD). This
AD requires repetitive inspections for
cracking of the improved (shot-peened)
non-ventral aft pressure bulkhead tees,
and replacement if necessary. We are
issuing this AD to detect and correct
fatigue cracking of the improved (shotpeened) non-ventral aft pressure
bulkhead tees connecting the bulkhead
web to the fuselage, which could result
in reduced structural integrity and rapid
decompression of the airplane.
DATES: This AD is effective December
11, 2014.
The Director of the Federal Register
approved the incorporation by reference
of a certain publication listed in this AD
as of December 11, 2014.
ADDRESSES: For service information
identified in this AD, contact Boeing
Commercial Airplanes, Attention: Data
& Services Management, 3855
Lakewood Boulevard, MC D800–0019,
Long Beach, CA 90846–0001; telephone
206–544–5000, extension 2; fax 206–
766–5683; Internet https://
www.myboeingfleet.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.
SUMMARY:
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–
0288; or in person at the Docket
Management Facility between 9 a.m.
and 5 p.m., Monday through Friday,
except Federal holidays. The AD docket
contains this AD, the regulatory
evaluation, any comments received, and
other information. The address for the
Docket Office (phone: 800–647–5527) is
Docket Management Facility, U.S.
Department of Transportation, Docket
Operations, M–30, West Building
Ground Floor, Room W12–140, 1200
New Jersey Avenue SE., Washington,
DC 20590.
FOR FURTHER INFORMATION CONTACT: Eric
Schrieber, Aerospace Engineer,
Airframe Branch, ANM–120L, FAA, Los
PO 00000
Frm 00013
Fmt 4700
Sfmt 4700
65885
Angeles Aircraft Certification Office,
3960 Paramount Boulevard, Lakewood,
CA 90712–4137; phone: 562–627–5348;
fax: 562–627–5210; email:
eric.schrieber@faa.gov.
SUPPLEMENTARY INFORMATION:
Discussion
We issued a notice of proposed
rulemaking (NPRM) to amend 14 CFR
part 39 by adding an AD that would
apply to certain The Boeing Company
Model DC–9–10, DC–9–20, and DC–9–
30 series airplanes. The NPRM
published in the Federal Register on
May 29, 2014 (79 FR 30753). The NPRM
was prompted by an evaluation by the
DAH indicating that the improved (shotpeened) aft fuselage non-ventral
pressure bulkhead tee is subject to WFD.
The NPRM proposed to require
repetitive inspections for cracking of the
improved (shot-peened) non-ventral aft
pressure bulkhead tees, and
replacement if necessary. We are issuing
this AD to detect and correct fatigue
cracking of the improved (shot-peened)
non-ventral aft pressure bulkhead tees
connecting the bulkhead web to the
fuselage, which could result in reduced
structural integrity and rapid
decompression of the airplane.
Comments
We gave the public the opportunity to
participate in developing this AD. We
have considered the comment received.
Boeing supported the NPRM (79 FR
30753, May 29, 2014).
Conclusion
We reviewed the relevant data,
considered the comment received, and
determined that air safety and the
public interest require adopting this AD
as proposed except for minor editorial
changes. We have determined that these
minor changes:
• Are consistent with the intent that
was proposed in the NPRM (79 FR
30753, May 29, 2014) for correcting the
unsafe condition; and
• Do not add any additional burden
upon the public than was already
proposed in the NPRM (79 FR 30753,
May 29, 2014).
Costs of Compliance
We estimate that this AD affects 48
airplanes of U.S. registry.
We estimate the following costs to
comply with this AD:
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]]>Agencies
[Federal Register Volume 79, Number 215 (Thursday, November 6, 2014)]
[Rules and Regulations]
[Pages 65879-65885]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2014-26356]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2013-1064; Directorate Identifier 2012-NM-101-AD;
Amendment 39-17991; AD 2014-20-18]
RIN 2120-AA64
Airworthiness Directives; Airbus Airplanes
AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
-----------------------------------------------------------------------
[[Page 65880]]
SUMMARY: We are superseding Airworthiness Directive (AD) 2005-23-08 for
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. This new AD adds new repetitive ultrasonic
inspections for cracks of the center wing box lower panel; and repair
if necessary. This new AD also removes certain airplanes from the
applicability. 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. 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.
DATES: This AD becomes December 11, 2014.
The Director of the Federal Register approved the incorporation by
reference of certain publications listed in this AD as of December 11,
2014.
The Director of the Federal Register approved the incorporation by
reference of certain other publications listed in this AD as of
December 19, 2005 (70 FR 69056, November 14, 2005).
The Director of the Federal Register approved the incorporation by
reference of a certain other publication listed in this AD as of July
8, 2002 (67 FR 38193, June 3, 2002).
ADDRESSES: You may examine the AD docket on the Internet at https://www.regulations.gov/#!docketDetail;D=FAA-2013-1064; or in person at the
Docket Management Facility, U.S. Department of Transportation, Docket
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New
Jersey Avenue SE., Washington, DC.
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. 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.
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:
Discussion
We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR
part 39 to supersede AD 2005-23-08, Amendment 39-14366 (70 FR 69056,
November 14, 2005). AD 2005-23-08 applied to 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. The NPRM published in the Federal Register on December 26,
2013 (78 FR 78285).
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, [e.g., repair] 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 examine the
MCAI in the AD docket on the Internet at https://www.regulations.gov/#!documentDetail;D=FAA-2013-1064-0002.
Comments
We gave the public the opportunity to participate in developing
this AD. The following presents the comments received on the NPRM (78
FR 78285, December 26, 2013) and the FAA's response to each comment.
Requests To Remove Requirement To Refer to This AD in Repair Approvals
Airlines for America, Inc. (A4A), on behalf of seven affected
member airlines, requested that we revise paragraphs (m)(1), (m)(2),
and (o)(2) of the NPRM (78 FR 78285, December 26, 2013) to remove the
requirement to include the AD reference in repair approvals. The
commenters have made this request because the proposed requirement is
overly broad and would add significant cost and complexity to their
operations. The commenters were concerned that this proposed
requirement would set a precedent for how repairs are approved, and
could negatively affect all U.S. operators of foreign-manufactured
airplanes.
We concur with the commenters' request to remove from this AD the
requirement that repair approvals must specifically refer to this 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 the NPRM (78 FR 78285, December 26, 2013), we proposed to
prevent the
[[Page 65881]]
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
this 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 ``the Design Approval Holder (DAH) with a
State of Design Authority's design organization approval (DOA)'' to
refer to a DAH authorized to approve required repairs for the proposed
AD.
One commenter to the NPRM (78 FR 78285, December 26, 2013), United
Parcel Service (UPS), 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 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 that paragraph and
retitled it ``Contacting the Manufacturer.'' This paragraph now
clarifies that for any requirement in this AD to obtain corrective
actions from a manufacturer, the actions must be accomplished using a
method approved by the FAA, 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 afforded previously
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 AD 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.
Other commenters pointed out that in many cases the foreign
manufacturer's service bulletin and the foreign authority's MCAI may
have been issued some time before the FAA AD. Therefore, the DOA may
have provided U.S. operators with an approved repair, developed with
full awareness of the unsafe condition, before the FAA AD is issued.
Under these circumstances, to comply with the FAA AD, the operator
would be required to go back to the manufacturer's DOA and obtain a new
approval document, adding time, and expense to the compliance process
with no safety benefit.
Based on these comments, we removed from this AD the requirement
that the DAH-provided repair specifically refer to this AD. Before
adopting such a requirement in the future, the FAA will coordinate with
affected DAHs and verify they are prepared to implement means to ensure
that their repair approvals consider the unsafe condition addressed in
the AD. Any such requirements will be adopted through the normal AD
rulemaking process, including notice-and-comment procedures, when
appropriate.
We have also decided not to include a generic reference to either
the ``delegated agent'' or the ``DAH with State of Design Authority
design organization approval'' for new requirements, but instead we
will provide the specific delegation approval granted by the State of
Design Authority for the DAH.
Request To Revise Costs of Compliance
One commenter, FedEx, requested assurance that two inspections (the
rotating probe of the attachment holes of the horizontal flange of the
internal corner angle fitting, and the ultrasonic inspection of the aft
bottom panel of the center wing box) specified in the NPRM (78 FR
78285, December 26, 2013) are to be conducted as two separate
inspections at two separate thresholds and intervals. FedEx observed
that both inspections are contained in the same service information,
and that these two inspections appear to be combined in the Costs of
Compliance paragraph of the NPRM. FedEx requested that the estimated
costs be presented separately for the two inspection actions, and added
that the Costs of Compliance paragraph should specify 4 work-hours for
the new ultrasonic inspection.
We agree to clarify the Costs of Compliance paragraph. There are
two inspection actions (rotating probe and ultrasonic inspections)
identified in Airbus Service Bulletin A300-57-6086, Revision 05, dated
January 30, 2012, and these are listed separately in the Costs of
Compliance paragraph. The second row of the table in the Costs of
Compliance paragraph should reflect the costs for the rotating probe
inspections identified in Airbus Service Bulletin A300-57-6086,
Revision 05, dated January 30, 2012; we have revised the second row of
the table in the Costs of Compliance paragraph accordingly. We have
also revised the fourth row of the table in the Costs of Compliance
paragraph to refer to Airbus Service Bulletin A300-57-6086, Revision
05, dated January 30, 2012, to reflect costs for the new ultrasonic
inspection.
In addition, we agree with FedEx that the ultrasonic inspection
takes 4 work-hours, as specified in Airbus Service Bulletin A300-57-
6086, Revision 05, dated January 30, 2012. In addition, Airbus Service
Bulletin A300-57-6086, Revision 05, dated January 30, 2012, specifies
12 work-hours for access and close procedures. Therefore, we have
revised the work-hours for the ultrasonic inspection specified in the
fourth row of the table in the Costs of Compliance paragraph from 35 to
16 work-hours.
Conclusion
We reviewed the available data, including the comments received,
and determined that air safety and the public interest require adopting
this AD with the changes described previously and minor editorial
changes. We have determined that these changes:
[[Page 65882]]
Are consistent with the intent that was proposed in the
NPRM (78 FR 78285, December 26, 2013) for correcting the unsafe
condition; and
Do not add any additional burden upon the public than was
already proposed in the NPRM (78 FR 78285, December 26, 2013).
We also determined that these changes will not increase the
economic burden on any operator or increase the scope of this AD.
Costs of Compliance
We estimate that this AD affects 65 airplanes of U.S. registry.
We estimate the following costs to comply with this AD:
Estimated Costs
----------------------------------------------------------------------------------------------------------------
Average
Action Work hours labor rate Parts Cost per airplane
per hour
----------------------------------------------------------------------------------------------------------------
Inspection for attachment 13.............. $85 $0............. $1,105.
holes on internal angles
[retained action from AD
2005-23-08, Amendment 39-
14366 (70 FR 69056, November
14, 2005)].
Rotating probe inspections 30.............. 85 Between $6,637 Between $9,187 and $21,641 per
for attachment holes in the and $19,091. inspection cycle.
horizontal flange (specified
in Airbus Service Bulletin
A300-57-6086, Revision 05,
dated January 30, 2012)
[retained action from AD
2005-23-08, Amendment 39-
14366 (70 FR 69056, November
14, 2005)].
Modification [retained action Between 65 and 85 $3,370......... Between $8,895 and $34,395.
from AD 2005-23-08, 365.
Amendment 39-14366 (70 FR
69056, November 14, 2005)].
New ultrasonic inspections of 16.............. 85 Between $11,750 Between $13,110 and $20,080 per
the aft bottom panel of the and $18,720. inspection cycle.
center wing box (specified
in Airbus Service Bulletin
A300-57-6086, Revision 05,
dated January 30, 2012).
----------------------------------------------------------------------------------------------------------------
We have received no definitive data that would enable us to provide
cost estimates for the on-condition actions specified in this 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 AD will not have federalism implications
under Executive Order 13132. This AD will not have a substantial direct
effect on the States, on the relationship between the national
government and the States, or on the distribution of power and
responsibilities among the various levels of government.
For the reasons discussed above, I certify that this AD:
1. Is not a ``significant regulatory action'' under Executive Order
12866;
2. Is not a ``significant rule'' under the DOT Regulatory Policies
and Procedures (44 FR 11034, February 26, 1979);
3. Will not affect intrastate aviation in Alaska; and
4. Will not have a significant economic impact, positive or
negative, on a substantial number of small entities under the criteria
of the Regulatory Flexibility Act.
Examining the AD Docket
You may examine the AD docket on the Internet at https://www.regulations.gov/#!docketDetail;D=FAA-2013-1064; or in person at the
Docket Management Facility between 9 a.m. and 5 p.m., Monday through
Friday, except Federal holidays. The AD docket contains this AD, the
regulatory evaluation, any comments received, and other information.
The street address for the Docket Operations office (telephone 800-647-
5527) is in the ADDRESSES section.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.
Adoption of the Amendment
Accordingly, under the authority delegated to me by the
Administrator, the FAA amends 14 CFR part 39 as follows:
PART 39--AIRWORTHINESS DIRECTIVES
0
1. The authority citation for part 39 continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
[[Page 65883]]
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:
2014-20-18 Airbus: Amendment 39-17991. Docket No. FAA-2013-1064;
Directorate Identifier 2012-NM-101-AD.
(a) Effective Date
This AD becomes effective December 11, 2014.
(b) Affected ADs
This AD replaces 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
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 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 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 Service Bulletin A300-57-6049, Revision 07, dated
December 22, 2006. As of the effective date of this AD, only Airbus
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 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 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 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
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 Service Bulletin A300-57-6086, Revision 05, dated
January 30, 2012. As of the effective date of this AD, only Airbus
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 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
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).
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.
[[Page 65884]]
(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 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 the European Aviation Safety Agency
(EASA); or Airbus's EASA Design Organization Approval (DOA). Repeat
the inspection thereafter at intervals not to exceed the applicable
interval specified in paragraph 1.E.(2), Accomplishment Timescale,
of Airbus 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 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 the European Aviation
Safety Agency (EASA); or Airbus's EASA Design Organization Approval
(DOA). Repeat the inspection thereafter at intervals not to exceed
the applicable interval specified in paragraph 1.E.(2),
Accomplishment Timescale, of Airbus 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
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.
(i) Before using any approved AMOC, notify your appropriate
principal inspector, or lacking a principal inspector, the manager
of the local flight standards district office/certificate holding
district office. The AMOC approval letter must specifically
reference this AD.
(ii) 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) Contacting the Manufacturer: As of the effective date of
this AD, for any requirement in this AD to obtain corrective actions
from a manufacturer, the action must be accomplished using a method
approved by the Manager, International 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.
(p) Related Information
(1) Refer to Mandatory Continuing Airworthiness Information
(MCAI) 2012-0092, dated May 25, 2012; Correction dated June 4, 2012;
for related information. You may examine the MCAI in the AD docket
on the Internet at https://www.regulations.gov/#!documentDetail;D=FAA-2013-10640002.
(2) Service information identified in this AD that is not
incorporated by reference is available at the addresses specified in
paragraphs (q)(5) and (q)(6) of this AD.
(q) Material Incorporated by Reference
(1) The Director of the Federal Register approved the
incorporation by reference (IBR) of the service information listed
in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51.
(2) You must use this service information as applicable to do
the actions required by this AD, unless this AD specifies otherwise.
(3) The following service information was approved for IBR on
December 11, 2014.
(i) Airbus Service Bulletin A300-57-6049, Revision 07, dated
December 22, 2006.
(ii) Airbus Service Bulletin A300-57-6086, Revision 05, dated
January 30, 2012.
(4) The following service information was approved for IBR on
December 19, 2005 (70 FR 69056, November 14, 2005).
(i) Airbus Service Bulletin A300-57-6049, excluding Appendix 01,
Revision 06, dated July 15, 2004.
[[Page 65885]]
(ii) Airbus Service Bulletin A300-57-6050, Revision 03, dated
May 31, 2001. This document contains the effective pages specified
in paragraphs (q)(4)(ii)(A), (q)(4)(ii)(B), (q)(4)(ii)(C), and
(q)(4)(ii)(D) of this AD.
(A) Pages 1, 4, 10A through 11, 75, and 76 are identified as
Revision 03, dated May 31, 2001.
(B) Pages 2, 8, 9, 17 through 32, 41, 42, 57, 58, 61 through 63,
and 77 are identified as Revision 02, dated February 10, 2000.
(C) Pages 3, 5 through 7, 10, 12, 33, 34, 37, 38, 47, 59, and 60
are identified as Revision 01, dated May 31, 1999.
(D) Pages 13 through 16, 35, 36, 39, 40, 43 through 46, 48
through 56, and 64 through 74 are identified as original, dated
September 9, 1994.
(iii) Airbus Service Bulletin A300-57-6086, Revision 01, dated
April 2, 2002.
(5) The following service information was approved for IBR on
July 8, 2002 (67 FR 38193, June 3, 2002).
(i) Airbus Service Bulletin A300-57-6086, dated June 6, 2000.
(ii) Reserved.
(6) 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.
(7) 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.
(8) You may view this service information that is incorporated
by reference at the National Archives and Records Administration
(NARA). For information on the availability of this material at
NARA, call 202-741-6030, or go to: https://www.archives.gov/federal-register/cfr/ibr-locations.html.
Issued in Renton, Washington, on September 24, 2014.
Michael Kaszycki,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2014-26356 Filed 11-5-14; 8:45 am]
BILLING CODE 4910-13-P
