[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