[Federal Register Volume 80, Number 108 (Friday, June 5, 2015)]
[Proposed Rules]
[Pages 32058-32061]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2015-13335]



[[Page 32058]]

-----------------------------------------------------------------------

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2015-1426; Directorate Identifier 2013-NM-200-AD]
RIN 2120-AA64


Airworthiness Directives; Airbus Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

-----------------------------------------------------------------------

SUMMARY: We propose to supersede Airworthiness Directive (AD) 97-20-07, 
for certain Airbus Model A300 B4-600, B4-600R, and F4-600R series 
airplanes, and Model A300 C4-605R Variant F airplanes (collectively 
called Model A300-600 series airplanes). AD 97-20-07 requires 
repetitive inspections to detect fatigue cracking in the left and right 
wings in the area where the top skin attaches to the center spar, and 
repair or modification of this area if necessary. Since we issued AD 
97-20-07, we have determined that the inspection compliance time and 
repetitive inspection interval must be reduced to allow timely 
detection of cracking in the left and right wings in the area where the 
top skin attaches to the center spar. This proposed AD would reduce the 
inspection compliance time and repetitive inspection intervals. We are 
proposing this AD to detect and correct this cracking, which could 
reduce the residual strength of the top skin of the wings, and 
consequently affect the structural integrity of the airframe.

DATES: We must receive comments on this proposed AD by July 20, 2015.

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, Airworthiness Office--EAW, 1 Rond Point Maurice Bellonte, 
31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61 
93 44 51; email [email protected]; Internet http://www.airbus.com. You may view this referenced service information at the 
FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. 
For information on the availability of this material at the FAA, call 
425-227-1221.

Examining the AD Docket

    You may examine the AD docket on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2015-
1426; or in person at the Docket Management Facility between 9 a.m. and 
5 p.m., Monday through Friday, except Federal holidays. The AD docket 
contains this proposed AD, the regulatory evaluation, any comments 
received, and other information. The street address for the Docket 
Operations office (telephone (800) 647-5527) is in the ADDRESSES 
section. Comments will be available in the AD docket shortly after 
receipt.

FOR FURTHER INFORMATION CONTACT: 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-2015-1426; 
Directorate Identifier 2013-NM-200-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 September 17, 1997, we issued AD 97-20-07, Amendment 39-10145 
(62 FR 50251, September 25, 1997). AD 97-20-07 requires actions 
intended to address an unsafe condition on the products listed above. 
Since we issued AD 97-20-07, we have determined that the inspection 
compliance time and repetitive inspection interval must be reduced to 
allow timely detection of cracking in the left and right wings in the 
area where the top skin attaches to the center spar.
    The European Aviation Safety Agency (EASA), which is the Technical 
Agent for the Member States of the European Union, has issued EASA 
Airworthiness Directive 2013-0221, dated September 19, 2013 (referred 
to after this as the Mandatory Continuing Airworthiness Information, or 
``the MCAI''), to correct an unsafe condition for certain Airbus Model 
A300 B4-600, B4-600R, and F4-600R series airplanes, and Model A300 C4-
605R Variant F airplanes (collectively called Model A300-600 series 
airplanes). The MCAI states:

    During fatigue tests conducted in the early 1990's, cracks were 
found on the top skin of the wing at the centre spar joint between 
ribs 1 and 7.
    Consequently, Airbus developed production mod. 10089 and issued 
Service Bulletin (SB) A300-57-6041, involving installation of a 
reinforcing plate on the affected area. Despite this improvement, 
subsequent cases of cracks were reported by operators.
    This condition, if not detected and corrected, could adversely 
affect the structural integrity of the aeroplane.
    To address this potential unsafe condition, Airbus issued SB 
A300-57-6044 and DGAC [Direction G[eacute]n[eacute]rale de 
l'Aviation Civile] France issued AD 95-086-180 (later revised twice) 
to require repetitive inspections of the affected area and, 
depending on findings, accomplishment of applicable corrective 
action(s).
    Since [DGAC] AD 1995-086-180(B)R2 [which corresponds to FAA AD 
97-20-07, Amendment 39-10145 (62 FR 50251, September 25, 1997)] was 
issued, a fleet survey and updated Fatigue and Damage Tolerance 
Analyses were performed in order to substantiate the second A300-600 
Extended Service Goal (ESG2) exercise. The results of these analyses 
have shown that the inspection thresholds and intervals must be 
reduced to allow timely detection of these cracks and accomplishment 
of an applicable corrective action.
    Prompted by these findings, Airbus issued SB A300-57-6044 
Revision 04 [dated August 19, 2011].
    For the reasons described above, this [EASA] AD retains the 
requirements of DGAC France AD 1995-086-180(B)R2, which is 
superseded, but requires the repetitive inspections to be 
accomplished at reduced thresholds and intervals and, depending on 
findings, corrective actions.

    You may examine the MCAI in the AD docket on the Internet at http://www.regulations.gov by searching for and locating it in Docket No. 
FAA-2015-1426.

[[Page 32059]]

Related Service Information Under 1 CFR Part 51

    Airbus has issued Service Bulletin A300-57-6044, Revision 04, 
including Appendix 01, dated August 19, 2011. The service information 
describes procedures for inspections to detect fatigue cracking in the 
left and right wings in the area where the top skin attaches to the 
center spar, and repair or modification of this area. The actions 
described in this service information are intended to correct the 
unsafe condition identified in the MCAI. This service information is 
reasonably available because the interested parties have access to it 
through their normal course of business or by the means identified in 
the ADDRESSES section of this NPRM.

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.

Costs of Compliance

    We estimate that this proposed AD affects 47 airplanes of U.S. 
registry.
    The actions that are required by AD 97-20-07, Amendment 39-10145 
(62 FR 50251, September 25, 1997), and retained in this proposed AD 
take about 3 work-hours per product, at an average labor rate of $85 
per work-hour. Based on these figures, the estimated cost of the 
actions that were required by AD 97-20-07 is $255 per product.
    We also estimate that it would take about 5 work-hours per product 
to comply with the basic requirements of this proposed AD. The average 
labor rate is $85 per work-hour. Based on these figures, we estimate 
the cost of this proposed AD on U.S. operators to be $19,975, or $425 
per product.
    We have received no definitive data that would enable us to provide 
cost estimates for the on-condition actions specified in this proposed 
AD.

Authority for This Rulemaking

    Title 49 of the United States Code specifies the FAA's authority to 
issue rules on aviation safety. Subtitle I, section 106, describes the 
authority of the FAA Administrator. ``Subtitle VII: Aviation 
Programs,'' describes in more detail the scope of the Agency's 
authority.
    We are issuing this rulemaking under the authority described in 
``Subtitle VII, Part A, Subpart III, Section 44701: General 
requirements.'' Under that section, Congress charges the FAA with 
promoting safe flight of civil aircraft in air commerce by prescribing 
regulations for practices, methods, and procedures the Administrator 
finds necessary for safety in air commerce. This regulation is within 
the scope of that authority because it addresses an unsafe condition 
that is likely to exist or develop on products identified in this 
rulemaking action.

Regulatory Findings

    We determined that this proposed AD would not have federalism 
implications under Executive Order 13132. This proposed AD would not 
have a substantial direct effect on the States, on the relationship 
between the national Government and the States, or on the distribution 
of power and responsibilities among the various levels of government.
    For the reasons discussed above, I certify this proposed 
regulation:
    1. Is not a ``significant regulatory action'' under Executive Order 
12866;
    2. Is not a ``significant rule'' under the DOT Regulatory Policies 
and Procedures (44 FR 11034, February 26, 1979);
    3. Will not affect intrastate aviation in Alaska; and
    4. Will not have a significant economic impact, positive or 
negative, on a substantial number of small entities under the criteria 
of the Regulatory Flexibility Act.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Incorporation by 
reference, Safety.

The Proposed Amendment

    Accordingly, under the authority delegated to me by the 
Administrator, the FAA proposes to amend 14 CFR part 39 as follows:

PART 39--AIRWORTHINESS DIRECTIVES

0
1. The authority citation for part 39 continues to read as follows:

    Authority: 49 U.S.C. 106(g), 40113, 44701.


Sec.  39.13  [Amended]

0
2. The FAA amends Sec.  39.13 by removing Airworthiness Directive (AD) 
97-20-07, Amendment 39-10145 (62 FR 50251, September 25, 1997), and 
adding the following new AD:

Airbus: Docket No. FAA-2015-1426; Directorate Identifier 2013-NM-
200-AD.

(a) Comments Due Date

    We must receive comments by July 20, 2015.

(b) Affected ADs

    This AD replaces AD 97-20-07, Amendment 39-10145 (62 FR 50251, 
September 25, 1997).

(c) Applicability

    This AD applies to the Airbus airplanes identified in paragraphs 
(c)(1) through (c)(4) of this AD, certificated in any category, all 
manufacturer serial numbers except those on which Airbus 
Modification 10160 has been done in production.
    (1) Airbus Model A300 B4-601, B4-603, B4-620, and B4-622 
airplanes.
    (2) Airbus Model A300 B4-605R and B4-622R airplanes.
    (3) Airbus Model A300 F4-605R and F4-622R airplanes.
    (4) Airbus Model A300 C4-605R Variant F airplanes.

(d) Subject

    Air Transport Association (ATA) of America Code 57, Wings.

(e) Reason

    This AD was prompted by a determination that the inspection 
compliance time and repetitive inspection interval must be reduced 
to allow timely detection of cracking in the left and right wings in 
the area where the top skin attaches to the center spar. We are 
issuing this AD to detect and correct this cracking, which could 
reduce the residual strength of the top skin of the wings, and 
consequently affect the structural integrity of the airframe.

(f) Compliance

    Comply with this AD within the compliance times specified, 
unless already done.

(g) Retained Repetitive Inspections and Corrective Actions With Revised 
Service information

    This paragraph restates the requirements of paragraph (a) of AD 
97-20-07, Amendment 39-10145 (62 FR 50251, September 25, 1997), with 
revised service information. For airplanes on which Airbus 
Modification 10089 has not been installed: Prior to the accumulation 
of 18,000 total landings, or within 1,500 landings after October 30, 
1997 (the effective date of AD 97-20-07), whichever occurs later, 
conduct either a detailed visual inspection or a high frequency eddy 
current (HFEC) inspection to detect fatigue cracking in the left and 
right wings in the area where the top skin attaches to the center 
spar between ribs 1 and 7, in accordance with Airbus Service 
Bulletin A300-57-6044, Revision 02, dated September 6, 1995, 
including Appendix 1; or Airbus Service Bulletin A300-57-6044, 
Revision 04, including Appendix 01, dated August 19, 2011. As of the 
effective date of this AD, use only Airbus Service Bulletin A300-57-
6044, Revision 04, including Appendix 01, dated August 19, 2011. 
Accomplishment of the inspection required by paragraph (i) of this 
AD terminates the inspection requirements of this paragraph.

[[Page 32060]]

    (1) If no cracking is detected, conduct repetitive inspections 
thereafter at the following intervals:
    (i) If the immediately preceding inspection was conducted using 
detailed visual techniques, conduct the next inspection within 5,000 
landings.
    (ii) If the immediately preceding inspection was conducted using 
HFEC techniques, conduct the next inspection within 9,500 landings.
    (2) If any cracking is detected or suspected during any detailed 
visual inspection required by paragraph (g), (g)(1), or (g)(3)(i) of 
this AD, prior to further flight, confirm this finding and the 
length of this cracking by conducting an HFEC inspection, in 
accordance with Airbus Service Bulletin A300-57-6044, Revision 02, 
dated September 6, 1995, including Appendix 01; or Airbus Service 
Bulletin A300-57-6044, Revision 04, including Appendix 01, dated 
August 19, 2011. As of the effective date of this AD, use only 
Airbus Service Bulletin A300-57-6044, Revision 04, including 
Appendix 01, dated August 19, 2011. If no cracking is confirmed 
during the HFEC inspection, accomplish the repetitive inspection 
required by paragraph (g)(1)(ii) of this AD at the time specified in 
that paragraph.
    (3) If any cracking is detected or confirmed during any HFEC 
inspection required by paragraph (g), (g)(1), or (g)(2) of this AD:
    (i) If the cracking is 75 millimeters (mm) or less per rib bay, 
prior to further flight, repair in accordance with Airbus Service 
Bulletin A300-57-6044, Revision 02, dated September 6, 1995, 
including Appendix 01; or Airbus Service Bulletin A300-57-6044, 
Revision 04, including Appendix 01, dated August 19, 2011. As of the 
effective date of this AD, use only Airbus Service Bulletin A300-57-
6044, Revision 04, including Appendix 01, dated August 19, 2011. 
Thereafter, conduct repetitive detailed visual inspections of the 
repaired area at intervals not to exceed 50 landings, in accordance 
with Airbus Service Bulletin A300-57-6044, Revision 02, dated 
September 6, 1995, including Appendix 01; or Airbus Service Bulletin 
A300-57-6044, Revision 04, including Appendix 01, dated August 19, 
2011. As of the effective date of this AD, use only Airbus Service 
Bulletin A300-57-6044, Revision 04, including Appendix 01, dated 
August 19, 2011.
    (ii) If the cracking exceeds 75 mm per rib bay, prior to further 
flight, install Airbus Modification 10089, in accordance with Airbus 
Service Bulletin A300-57-6044, Revision 02, dated September 6, 1995, 
including Appendix 01; or Airbus Service Bulletin A300-57-6044, 
Revision 04, including Appendix 01, dated August 19, 2011. As of the 
effective date of this AD, use only Airbus Service Bulletin A300-57-
6044, Revision 04, including Appendix 01, dated August 19, 2011. 
Thereafter, conduct a low frequency eddy current inspection in 
accordance with the requirements of paragraph (h) of this AD.

    Note 1 to paragraph (g) of this AD: Airbus Service Bulletin 
A300-57-6044, Revision 02, dated September 6, 1995, including 
Appendix 01 references Airbus Service Bulletin A300-57-6041, 
Revision 04, dated November 16, 1995, as an additional source of 
guidance for installing Airbus Modification 10089.

(h) Retained Repetitive Inspections and Corrective Actions for Certain 
Airplanes with Revised Service Information and Repair Instructions

    This paragraph restates the requirements of paragraph (b) of AD 
97-20-07, Amendment 39-10145 (62 FR 50251, September 25, 1997), with 
revised service information and repair instructions. For airplanes 
on which Airbus Modification 10089 has been installed: Prior to the 
accumulation of 22,000 total landings after this modification has 
been installed, or within 1,500 landings after October 30, 1997 (the 
effective date of AD 97-20-07), whichever occurs later, conduct a 
low frequency eddy current (LFEC) inspection to detect fatigue 
cracking in the inboard and rear edges of the top skin reinforcing 
plates, in accordance with Airbus Service Bulletin A300-57-6044, 
Revision 02, dated September 6, 1995, including Appendix 01; or 
Airbus Service Bulletin A300-57-6044, Revision 04, including 
Appendix 01, dated August 19, 2011. As of the effective date of this 
AD, use only Airbus Service Bulletin A300-57-6044, Revision 04, 
including Appendix 01, dated August 19, 2011. Accomplishment of the 
inspection required by paragraph (k) of this AD terminates the 
inspection requirements of this paragraph.
    (1) If no cracking is detected, repeat this inspection 
thereafter at intervals not to exceed 11,000 landings.
    (2) If any cracking is detected, prior to further flight, repair 
in accordance with a method approved by the Manager, Standardization 
Branch, ANM-113, FAA, Transport Airplane Directorate. As of the 
effective date of this AD, 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). Thereafter, repeat 
this inspection at intervals not to exceed 11,000 landings.

(i) New Requirement of This AD: Initial Inspections

    For airplanes on which Airbus Modification 10089 has not been 
installed: At the applicable time specified in paragraphs (i)(1) and 
(i)(2) of this AD, do either a detailed visual inspection or an HFEC 
inspection to detect fatigue cracking in the left and right wings in 
the area where the top skin attaches to the center spar between ribs 
1 and 7, in accordance with the Accomplishment Instructions of 
Airbus Service Bulletin A300-57-6044, Revision 04, including 
Appendix 01, dated August 19, 2011. Accomplishment of the inspection 
required by this paragraph terminates the inspection requirements of 
paragraph (g) of this AD.
    (1) For airplanes whose flight time average is equal to or more 
than 1.5 hours, at the later of the times specified in paragraphs 
(i)(1)(i) and (i)(1)(ii) of this AD.
    (i) Before the accumulation of 14,000 total flight cycles or 
30,300 total flight hours, whichever occurs first.
    (ii) Within 1,500 flight cycles or 3,200 flight hours after the 
effective date of this AD, whichever occurs first.
    (2) For airplanes whose flight time average is less than 1.5 
hours, at the later of the times specified in paragraphs (i)(2)(i) 
and (i)(2)(ii) of this AD.
    (i) Before the accumulation of 15,100 total flight cycles or 
22,700 total flight hours, whichever occurs first.
    (ii) Within 1,600 flight cycles or 2,500 flight hours after the 
effective date of this AD, whichever occurs first.

(j) New Requirement of This AD: Repetitive Inspections

    Repeat the inspections specified in paragraph (i) of this AD 
thereafter at the applicable interval specified in paragraphs (j)(1) 
and (j)(2) of this AD.
    (1) For airplanes whose flight time average is equal to or more 
than 1.5 hours, at the applicable interval specified in paragraphs 
(j)(1)(i) and (j)(1)(ii) of this AD.
    (i) For a detailed inspection, at intervals not to exceed 3,900 
flight cycles or 8,400 flight hours, whichever occurs first.
    (ii) For an HFEC inspection, at intervals not to exceed 7,400 
flight cycles or 16,000 flight hours, whichever occurs first.
    (2) For airplanes whose flight time average is less than 1.5 
hours at the applicable interval specified in paragraphs (j)(2)(i) 
and (j)(2)(ii) of this AD.
    (i) For a detailed inspection, at intervals not to exceed 4,200 
flight cycles or 6,300 flight hours, whichever occurs first.
    (ii) For an HFEC inspection, at intervals not to exceed 8,000 
flight cycles or 11,900 flight hours, whichever occurs first.

(k) New Requirement of This AD: Initial Inspection for Certain 
Airplanes

    For airplanes on which Airbus Modification 10089 has been 
installed: At the applicable time specified in paragraphs (k)(1) and 
(k)(2) of this AD, do an LFEC inspection to detect fatigue cracking 
in the inboard and rear edges of the top skin reinforcing plates, in 
accordance with the Accomplishment Instructions of Airbus Service 
Bulletin A300-57-6044, Revision 04, including Appendix 01, dated 
August 19, 2011. Accomplishment of the inspection required by this 
paragraph terminates the inspection requirements of paragraph (h) of 
this AD.
    (1) For airplanes whose flight time average is equal to or more 
than 1.5 hours, at the later of the times specified in paragraphs 
(k)(1)(i) and (k)(1)(ii) of this AD.
    (i) Before the accumulation of 17,000 total flight cycles or 
37,100 total flight hours, whichever occurs first.
    (ii) Within 1,500 flight cycles or 3,200 flight hours after the 
effective date of this AD, whichever occurs first.
    (2) For airplanes whose flight time average is less than 1.5 
hours, at the later of the times specified in paragraphs (k)(2)(i) 
and (k)(2)(ii) of this AD.
    (i) Before the accumulation of 18,500 total flight cycles or 
27,800 total flight hours, whichever occurs first.
    (ii) Within 1,600 flight cycles or 2,500 flight hours after the 
effective date of this AD, whichever occurs first.

[[Page 32061]]

(l) New Requirement of This AD: Repetitive Inspections for Certain 
Airplanes

    Repeat the inspection specified in paragraph (k) of this AD 
thereafter at the applicable interval specified in paragraphs (l)(1) 
and (l)(2) of this AD.
    (1) For airplanes whose flight time average is equal to or more 
than 1.5 hours, at intervals not to exceed 8,500 flight cycles or 
18,500 flight hours, whichever occurs first.
    (2) For airplanes whose flight time average is less than 1.5 
hours, at intervals not to exceed 9,200 flight cycles or 13,700 
flight hours, whichever occurs first.

(m) New Requirement of This AD: Corrective Actions

    (1) If any cracking is detected or suspected during any detailed 
visual inspection required by paragraph (i) or (j) of this AD: 
Before further flight, confirm this finding and the length of this 
cracking by conducting an HFEC inspection, in accordance with the 
Accomplishment Instructions of Airbus Service Bulletin A300-57-6044, 
Revision 04, including Appendix 01, dated August 19, 2011, except as 
specified in paragraph (o) of this AD. If no cracking is confirmed 
during the HFEC inspection, accomplish the applicable repetitive 
inspections required by paragraphs (j) and (l) of this AD at the 
applicable time specified in those paragraphs.
    (2) If any cracking is found during any HFEC inspection required 
by paragraph (i), (j), (k) or (l) of this AD: Before further flight, 
do the applicable actions specified in paragraphs (m)(2)(i) and 
(m)(2)(ii) of this AD.
    (i) If the cracking is 75 mm or less per each rib bay: Before 
further flight, repair the cracking, in accordance with the 
Accomplishment Instructions of Airbus Service Bulletin A300-57-6044, 
Revision 04, including Appendix 01, dated August 19, 2011, except as 
specified in paragraph (o) of this AD. Do repetitive detailed visual 
inspections of the repaired area thereafter at intervals not to 
exceed 50 flight cycles or 110 flight hours, whichever occurs first, 
in accordance with the Accomplishment Instructions of Airbus Service 
Bulletin A300-57-6044, Revision 04, including Appendix 01, dated 
August 19, 2011. Within 250 flight cycles or 550 flight hours, 
whichever occurs first after doing the temporary repair, do a 
permanent repair of the repaired area, in accordance with the 
Accomplishment Instructions of Airbus Service Bulletin A300-57-6044, 
Revision 04, including Appendix 01, dated August 19, 2011.
    (ii) If the cracking exceeds 75 mm per any rib bay: Before 
further flight, install Airbus Modification 10089, in accordance 
with the Accomplishment Instructions of Airbus Service Bulletin 
A300-57-6044, Revision 04, including Appendix 01, dated August 19, 
2011. Do an LFEC inspection thereafter at the intervals specified in 
paragraph (l) of this AD.
    (3) If any cracking is found during any inspection required by 
this AD at fastener holes 1A, 1, or 2: Before further flight, repair 
the cracking, in accordance with the Accomplishment Instructions of 
Airbus Service Bulletin A300-57-6044, Revision 04, including 
Appendix 01, dated August 19, 2011.

(n) Credit for Previous Actions

    This paragraph provides credit for actions required by 
paragraphs (i) through (l) of this AD, if those actions were 
performed before the effective date of this AD using Airbus Service 
Bulletin A300-57-6044, Revision 03, dated April 7, 1999, including 
Appendix 01, which is not incorporated by reference in this AD.

(o) Exception to Service Information Specification

    Although Airbus Service Bulletin A300-57-6044, Revision 04, 
including Appendix 01, dated August 19, 2011, specifies to submit 
information to Airbus, this AD does not require that submission.

(p) 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.
    (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 EASA; or Airbus's EASA DOA. If 
approved by the DOA, the approval must include the DOA-authorized 
signature.

(q) Related Information

    (1) Refer to Mandatory Continuing Airworthiness Information 
(MCAI) EASA Airworthiness Directive 2013-0221, dated September 19, 
2013, for related information. This MCAI may be found in the AD 
docket on the Internet at http://www.regulations.gov by searching 
for and locating Docket No. FAA-2015-1426.
    (2) For service information identified in this AD, contact 
Airbus SAS, Airworthiness Office--EAW, 1 Rond Point Maurice 
Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; 
fax +33 5 61 93 44 51; email [email protected]; 
Internet http://www.airbus.com. You may view this service 
information at the FAA, Transport Airplane Directorate, 1601 Lind 
Avenue SW., Renton, WA. For information on the availability of this 
material at the FAA, call 425-227-1221.


    Issued in Renton, Washington, on May 19, 2015.
Dionne Palmero,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.

[FR Doc. 2015-13335 Filed 6-4-15; 8:45 am]
 BILLING CODE 4910-13-P