[Federal Register Volume 78, Number 248 (Thursday, December 26, 2013)]
[Proposed Rules]
[Pages 78285-78290]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2013-30893]
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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).
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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 http://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 [email protected]; Internet http://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 http://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 http://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 [(http://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 [(http://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: [email protected]. Before using any
approved AMOC, notify your appropriate principal inspector, or
lacking a principal inspector, the manager of the local flight
standards district office/certificate holding district office. The
AMOC approval letter must specifically reference this AD. 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 http://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 [email protected];
Internet http://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