
[Federal Register Volume 80, Number 93 (Thursday, May 14, 2015)]
[Proposed Rules]
[Pages 27607-27611]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2015-11554]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2015-1417; Directorate Identifier 2013-NM-159-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) 2004-20-
14, for all Airbus Model A300 B4-2C, B4-103, and B4-203 airplanes; and 
all Model A300 B4-600, B4-600R, and F4-600R series airplanes. AD 2004-
20-14 requires repetitive inspections to detect cracking of the splice 
fitting at fuselage frame (FR) 47 between stringers 24 and 26 (left- 
and right-hand sides), and corrective actions if necessary. Since we 
issued AD 2004-20-14, we have determined that the inspection compliance 
time and repetitive inspection interval must be reduced to allow timely 
detection of cracks in the splice fitting at fuselage FR 47. This 
proposed AD would reduce the inspection compliance time and repetitive 
inspection intervals, and add Model A300 C4-605R Variant F airplanes to 
the applicability. We are proposing this AD to detect and correct 
cracking of the splice fitting at fuselage FR 47, which could result in 
reduced structural integrity of the airplane.

DATES: We must receive comments on this proposed AD by June 29, 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 account.airworth-eas@airbus.com; 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.

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 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-2015-1417; 
Directorate Identifier 2013-NM-159-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 30, 2004, we issued AD 2004-20-14, Amendment 39-13819 
(69 FR 60809, October 13, 2004), which superseded AD 2001-03-14, 
Amendment 39-12118 (66 FR 10957, February 21, 2001). AD 2004-20-14 
requires actions intended to address an unsafe condition on all Airbus 
Model A300 B4-2C, B4-103, and B4-203 airplanes; and all Model A300 B4-
600, B4-600R, and F4-600R series airplanes. Since we issued AD 2004-20-
14, Amendment 39-13819 (69 FR 60809, October 13, 2004), we have 
determined that the inspection compliance time and repetitive 
inspection interval must be reduced to allow timely detection of cracks 
in the splice fitting at fuselage FR 47, and that Model A300 C4-605R 
Variant F airplanes must be added to the applicability.
    The European Aviation Safety Agency (EASA), which is the Technical 
Agent for the Member States of the European Union, has issued EASA 
Airworthiness Directive 2013-0184R1, dated August 22, 2013 (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:

    In order to prevent crack development in the fastener holes at 
Frame (FR) 47 splicing joint on A300 aeroplanes, Airbus developed 
modification (Mod) 5890 for aeroplanes in production and issued 
corresponding Service Bulletin (SB) A300-53-0199 for aeroplanes in 
service.
    Subsequently, cracks were found on FR47 splice fitting between 
stringers (STRG) 24 and 26 on A300 aeroplanes previously modified by 
SB A300-53-0199.
    This condition, if not detected and corrected, could reduce the 
structural integrity of the aeroplane.
    To address this potential unsafe condition, DGAC [Direction 
G[eacute]n[eacute]rale de l'Aviation Civile] France issued AD 2002-
184 http://ad.easa.europa.eu/blob/2002184tb_superseded.pdf/AD_F-2002-184_2 [which corresponds to FAA AD 2004-20-14, Amendment 39-
13819 (69 FR 60809, October 13, 2004)], superseding [DGAC France] AD 
85-152-069 and [DGAC France] AD 1999-515-298 [which corresponds to 
FAA AD 2001-03-14, Amendment 39-12118 (66 FR 10957, February 21, 
2001)], to require repetitive High Frequency Eddy Current (HFEC) 
rotating probe inspections of the splice fitting between STRG 24 and 
26 and,

[[Page 27608]]

depending on findings, corrective action(s). DGAC France AD 2002-
184(B) expanded the applicability to A300-600 aeroplanes, which have 
the same design.
    Since that [DGAC France] AD was issued, a fleet survey and 
updated Fatigue and Damage Tolerance analyses have been performed in 
order to substantiate the second A300-600 Extended Service Goal 
(ESG2) exercise. The results of these analyses have determined that 
the inspection threshold and intervals for A300-600 aeroplanes must 
be reduced to allow timely detection of these cracks and the 
accomplishment of an applicable corrective action.
    For the reasons described above, [EASA] AD 2013-0184 retains the 
requirements of DGAC France AD 2002-184, which is superseded, but 
requires accomplishment of the actions for A300-600 aeroplanes 
within the new thresholds and intervals introduced with Revision 05 
of Airbus SB [service bulletin] A300-53-6123 [dated August 1, 2011] 
.
    This [EASA] AD was revised to correct the splices Part Numbers 
(P/N) in Table 4 of Appendix 1 of this [EASA] AD. Also, reference is 
now made to Airbus SB A300-53-6123 Revision 06 [dated September 28, 
2011], which corrected this mistake compared to Revision 05.

    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-2015-1417.

Related Service Information Under 1 CFR Part 51

    Airbus has issued the following service bulletins:
     Airbus Service Bulletin A300-53-6123, Revision 06, 
including Inspection Report, dated September 28, 2011. This service 
bulletin describes procedures for inspection for cracking of the splice 
fitting at fuselage FR 47 between stringers 24 and 26, and corrective 
actions.
     Airbus Service Bulletin A300-53-0350, Revision 03, 
including Appendix 03, dated July 26, 2007. This service bulletin 
describes procedures for inspection to detect cracking of the splice 
fitting at fuselage FR 47 between stringers 24 and 26, and corrective 
actions.
    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 72 airplanes of U.S. 
registry.
    We also estimate that it would take up to 14 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 $85,680, or $1,190 
per product.
    In addition, we estimate that any necessary follow-on actions would 
take up to 204 work-hours and require parts costing up to $37,000, for 
a cost of up to $54,340 per product. We have no way of determining the 
number of aircraft that might need these actions.

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.
    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) 
2004-20-14, Amendment 39-13819 (69 FR 60809, October 13, 2004), and 
adding the following new AD:

Airbus: Docket No. FAA-2015-1417; Directorate Identifier 2013-NM-
159-AD.

(a) Comments Due Date

    We must receive comments by June 29, 2015.

(b) Affected ADs

    This AD replaces AD 2004-20-14, Amendment 39-13819 (69 FR 60809, 
October 13, 2004).

(c) Applicability

    This AD applies to the Airbus airplanes identified in paragraphs 
(c)(1) through (c)(5) of this AD, certificated in any category, all 
manufacturer serial numbers.
    (1) Airbus Model A300 B4-2C, B4-103, and B4-203 airplanes.
    (2) Airbus Model A300 B4-601, B4-603, B4-620, and B4-622 
airplanes.
    (3) Airbus Model A300 B4-605R and B4-622R airplanes.
    (4) Airbus Model A300 F4-605R and F4-622R airplanes.
    (5) Airbus Model A300 C4-605R Variant F airplanes.

(d) Subject

    Air Transport Association (ATA) of America Code 53, Fuselage.

[[Page 27609]]

(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 cracks in the splice fitting at 
fuselage frame (FR) 47. We are issuing this AD to detect and correct 
cracking of the splice fitting at fuselage FR 47, which could result 
in reduced structural integrity of the airplane.

(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 Repetitive Inspections for Airplanes Defined in Airbus 
Service Bulletin A300-53-0350, Revision 02, Dated November 12, 2002, 
With New Service Information

    This paragraph restates the requirements of paragraph (a) of AD 
2004-20-14, Amendment 39-13819 (69 FR 60809, October 13, 2004), with 
new service information. For airplanes defined in Airbus Service 
Bulletin A300-53-0350, Revision 02, dated November 12, 2002: Do a 
high frequency eddy current (HFEC) inspection to detect cracking of 
the splice fitting at fuselage FR 47 between stringers 24 and 26 
(left- and right-hand sides), at the applicable times specified in 
paragraph (g)(1) or (g)(2) of this AD. Repeat the inspection 
thereafter at the earlier of the flight-cycle/flight-hour intervals 
specified in the applicable column in Table 2 of Figure 1 and Sheet 
1 of the Accomplishment Instructions of Airbus Service Bulletin 
A300-53-0350, Revision 02, excluding Appendix 01, dated November 12, 
2002. Do the inspections in accordance with Airbus Service Bulletin 
A300-53-0350, Revision 02, excluding Appendix 01, dated November 12, 
2002; or Revision 03, excluding Appendix 01, dated July 26, 2007. As 
of the effective date of this AD, use only Airbus Service Bulletin 
A300-53-0350, Revision 03, excluding Appendix 01, dated July 26, 
2007.
    (1) For airplanes that have accumulated 20,000 or more total 
flight cycles as of November 17, 2004 (the effective date of AD 
2004-20-14, Amendment 39-13819 (69 FR 60809, October 13, 2004)): Do 
the initial inspection at the later of the times specified in 
paragraphs (g)(1)(i) and (g)(1)(ii) of this AD.
    (i) At the earlier of the flight-cycle/flight-hour intervals 
after November 17, 2004 (the effective date of AD 2004-20-14, 
Amendment 39-13819 (69 FR 60809, October 13, 2004)), as specified in 
the applicable column in Table 1 of Figure 1 and Sheet 1 of the 
Accomplishment Instructions of Airbus Service Bulletin A300-53-0350, 
Revision 02, excluding Appendix 01, dated November 12, 2002.
    (ii) Within 750 flight cycles or 1,500 flight hours after 
November 17, 2004 (the effective date of AD 2004-20-14, Amendment 
39-13819 (69 FR 60809, October 13, 2004)), whichever is first.
    (2) For airplanes that have accumulated fewer than 20,000 total 
flight cycles as of November 17, 2004 (the effective date of AD 
2004-20-14, Amendment 39-13819 (69 FR 60809, October 13, 2004)): Do 
the initial inspection at the later of the times specified in 
paragraphs (g)(2)(i) and (g)(2)(ii) of this AD.
    (i) At the earlier of the flight-cycle/flight-hour intervals 
after November 17, 2004 (the effective date of AD 2004-20-14, 
Amendment 39-13819 (69 FR 60809, October 13, 2004)), as specified in 
the applicable column in Table 1 of Figure 1 and Sheet 1 of the 
Accomplishment Instructions of Airbus Service Bulletin A300-53-0350, 
Revision 02, excluding Appendix 01, dated November 12, 2002.
    (ii) Within 1,800 flight cycles or 3,000 flight hours after 
November 17, 2004 (the effective date of AD 2004-20-14, Amendment 
39-13819 (69 FR 60809, October 13, 2004)), whichever is first.

(h) Retained Repetitive Inspections for Airplanes Defined in Airbus 
Service Bulletin A300-53-6123, Revision 02, Dated November 12, 2002, 
With New Service Information

    This paragraph restates the requirements of paragraph (b) of AD 
2004-20-14, Amendment 39-13819 (69 FR 60809, October 13, 2004), with 
new service information. For airplanes defined in Airbus Service 
Bulletin A300-53-6123, Revision 02, dated November 12, 2002: Do the 
HFEC inspection required by paragraph (g) of this AD at the 
applicable times specified in paragraph (h)(1) or (h)(2) of this AD. 
Repeat the inspection thereafter at the earlier of the flight-cycle/
flight-hour intervals specified in the applicable column in Table 2 
of Figure 1 and Sheet 1 of the Accomplishment Instructions of Airbus 
Service Bulletin A300-53-6123, Revision 02, excluding Appendix 01, 
dated November 12, 2002. Do the inspections in accordance with the 
Accomplishment Instructions of Airbus Service Bulletin A300-53-6123, 
Revision 02, excluding Appendix 01, dated November 12, 2002, 
excluding Appendix 01; or Revision 06, dated September 28, 2011. 
Accomplishment of the actions required by paragraph (j) of this AD 
terminates the requirements of this paragraph.
    (1) For airplanes that have accumulated 10,000 or more total 
flight cycles as of November 17, 2004 (the effective date of AD 
2004-20-14, Amendment 39-13819 (69 FR 60809, October 13, 2004)): Do 
the initial inspection within 750 flight cycles or 1,900 flight 
hours after November 17, 2004, whichever is first.
    (2) For airplanes that have accumulated fewer than 10,000 total 
flight cycles as of November 17, 2004 (the effective date of AD 
2004-20-14, Amendment 39-13819 (69 FR 60809, October 13, 2004)): Do 
the initial inspection at the later of the times specified in 
paragraphs (h)(2)(i) and (h)(2)(ii) of this AD.
    (i) At the earlier of the flight-cycle/flight-hour intervals 
after November 17, 2004 (the effective date of AD 2004-2-14, 
Amendment 39-13819 (69 FR 60809, October 13, 2004)), as specified in 
the applicable column in Table 1 of Figure 1 and Sheet 1 of the 
Accomplishment Instructions of Airbus Service Bulletin A300-53-6123, 
Revision 02, excluding Appendix 01, dated November 12, 2002.
    (ii) Within 1,500 flight cycles or 3,800 flight hours after 
November 17, 2004 (the effective date of AD 2004-20-14, Amendment 
39-13819 (69 FR 60809, October 13, 2004)), whichever is first.

(i) Retained Repair, With Revised Repair Instructions

    This paragraph restates the requirements of paragraph (c) of AD 
2004-20-14, Amendment 39-13819 (69 FR 60809, October 13, 2004), with 
revised repair instructions. Repair any cracking found during any 
inspection required by paragraphs (g) and (h) this AD before further 
flight, in accordance with Airbus Service Bulletin A300-53-0350, 
Revision 02, excluding Appendix 01, dated November 12, 2002; or 
Airbus Service Bulletin A300-53-6123, Revision 02, excluding 
Appendix 01, dated November 12, 2002; as applicable. Where Airbus 
Service Bulletin A300-53-0350, Revision 02, excluding Appendix 01, 
dated November 12, 2002; or Airbus Service Bulletin A300-53-6123, 
Revision 02, excluding Appendix 01, dated November 12, 2002; specify 
to contact Airbus in case of certain crack findings, this AD 
requires that a repair be accomplished before further flight using a 
method approved by the Manager, International Branch, ANM-116, FAA, 
Transport Airplane Directorate; or the Direction 
G[eacute]n[eacute]rale de l'Aviation Civile (DGAC) (or its delegated 
agent); or the European Aviation Safety Agency (EASA); or Airbus's 
EASA Design Organization Approval (DOA).

(j) New Requirement of This AD: Repetitive Inspections

    For airplanes identified in paragraphs (c)(2) through (c)(5) of 
this AD: At the applicable time specified in paragraph (j)(1) or 
(j)(2) of this AD: Remove the fasteners and accomplish an HFEC 
rotating probe inspection for cracking of the splice fitting between 
stringer 24 and 26, in accordance with the Accomplishment 
Instructions of Airbus Service Bulletin A300-53-6123, Revision 06, 
excluding Inspection Report, dated September 28, 2011. Repeat the 
inspection thereafter at the applicable intervals specified in 
paragraphs (k)(1) through (k)(4) of this AD. If no cracking is 
found: Before further flight after each inspection, install new 
fasteners, in accordance with the Accomplishment Instructions of 
Airbus Service Bulletin A300-53-6123, Revision 06, excluding 
Inspection Report, dated September 28, 2011. Accomplishment of the 
initial inspection required by this paragraph terminates the 
requirements of paragraph (h) of this AD for that airplane.
    (1) For airplanes on which Airbus Modification 5890, or the 
actions specified in Airbus Service Bulletin A300-53-6131, have not 
been done: At the applicable time specified in paragraphs (j)(1)(i) 
and (j)(1)(ii) of this AD.
    (i) For airplanes that have an average flight time (AFT) that is 
more than 1.5 hours: At the later of the times specified in 
paragraphs (j)(1)(i)(A) and (j)(1)(i)(B) of this AD.
    (A) Before the accumulation of 2,500 total flight cycles or 
5,500 total flight hours, whichever occurs first.

[[Page 27610]]

    (B) Within 800 flight cycles or 1,750 flight hours, whichever 
occurs first after the effective date of this AD.
    (ii) For airplanes that have an AFT that is equal to or less 
than 1.5 hours: At the later of the times specified in paragraphs 
(j)(1)(ii)(A) and (j)(1)(ii)(B) of this AD.
    (A) Before the accumulation of 2,700 total flight cycles or 
4,100 total flight hours, whichever occurs first.
    (B) Within 800 flight cycles or 1,750 flight hours, whichever 
occurs first after the effective date of this AD.
    (2) For airplanes that have accomplished Airbus Modification 
5890, or have accomplished the actions specified in Airbus Service 
Bulletin A300-53-6131: At the applicable time specified in paragraph 
(j)(2)(i) or (j)(2)(ii) of this AD.
    (i) For airplanes that have an AFT that is more than 1.5 hours: 
At the later of the times specified in paragraphs (j)(2)(i)(A) and 
(j)(2)(i)(B) of this AD.
    (A) Before the accumulation of 6,800 total flight cycles or 
14,700 total flight hours, whichever occurs first.
    (B) Within 800 flight cycles or 1,750 flight hours, whichever 
occurs first after the effective date of this AD.
    (ii) For airplanes that have an AFT that is equal to or less 
than 1.5 hours: At the later of the times specified in paragraphs 
(j)(2)(ii)(A) and (j)(2)(ii)(B) of this AD.
    (A) Before the accumulation of 7,300 total flight cycles or 
11,000 total flight hours, whichever occurs first.
    (B) Within 800 flight cycles or 1,750 flight hours, whichever 
occurs first after the effective date of this AD.

(k) New Requirement of This AD: Repetitive Inspection Intervals for 
Actions Specified in Paragraph (j) of This AD

    For airplanes identified in paragraphs (c)(2) through (c)(5) of 
this AD: Repeat the inspection required by paragraph (j) of this AD 
at the applicable time specified in paragraphs (k)(1) through (k)(4) 
of this AD.
    (1) For airplanes that have an AFT of more than 1.5 hours and 
meet the applicable conditions specified in paragraphs (k)(1)(i) 
through (k)(1)(iv) of this AD: Inspect at intervals not to exceed 
800 flight cycles or 1,750 flight hours, whichever occurs first.
    (i) Airplanes on which Airbus Modification 5890 has not been 
accomplished.
    (ii) Airplanes on which the actions specified in Airbus Service 
Bulletin A300-53-6131 have not been accomplished.
    (iii) Airplanes on which Airbus Modification 5890 has been 
accomplished and have splice part number (P/N) A53834139-202/-203 
installed.
    (iv) Airplanes on which the actions specified in Airbus Service 
Bulletin A300-53-6131 have been accomplished and have splice P/N 
A53834139-202/-203 installed.
    (2) For airplanes that have an AFT that is equal to or less than 
1.5 hours and meet the applicable conditions specified in paragraphs 
(k)(2)(i) through (k)(2)(iv) of this AD: Inspect at intervals not to 
exceed 800 flight cycles or 1,750 flight hours.
    (i) Airplanes on which Airbus Modification 5890 has not been 
accomplished.
    (ii) Airplanes on which the actions specified in Airbus Service 
Bulletin A300-53-6131 have not been accomplished.
    (iii) Airplanes on which Airbus Modification 5890 has been 
accomplished and have splice P/N A53834139-202/-203 installed.
    (iv) Airplanes on which the actions described in Airbus Service 
Bulletin A300-53-6131 have been accomplished and have splice P/N 
A53834139-202/-203 installed.
    (3) For airplanes that have an AFT of more than 1.5 hours and 
meet the applicable conditions specified in paragraphs (k)(3)(i) and 
(k)(3)(ii) of this AD: Inspect at intervals not to exceed 800 flight 
cycles or 1,750 flight hours.
    (i) Airplanes on which Airbus Modification 5890 has been 
accomplished and have splice P/N A53812635-200/-201/-202/-203 
installed.
    (ii) Airplanes on which the actions specified in Airbus Service 
Bulletin A300-53-6131 have been accomplished and have splice P/N 
A53812635-200/-201/-202/-203 installed.
    (4) For the airplanes that have an AFT that is equal to or less 
than 1.5 hours and meet the applicable conditions specified in 
paragraphs (k)(4)(i) and (k)(4)(ii) of this AD: Inspect at intervals 
not to exceed 800 flight cycles or 1,750 flight hours.
    (i) Airplanes on which Airbus Modification 5890 has been 
accomplished and have splice P/N A53812635-200/-201/-202/-203 
installed.
    (ii) Airplanes on which the actions specified in Airbus Service 
Bulletin A300-53-6131 have been accomplished and have splice P/N 
A53812635-200/-201/-202/-203 installed.

(l) New Requirement of This AD: Corrective Actions

    If, during any inspection required by paragraph (j) or (k) of 
this AD, any cracks are found: Before further flight, do the 
applicable corrective actions, in accordance with the Accomplishment 
Instructions of Airbus Service Bulletin A300-53-6123, Revision 06, 
excluding Inspection Report, dated September 28, 2011; except as 
provided by paragraph (m) of this AD.

(m) New Requirement of This AD: Exception to Service Information

    If any crack is found during any inspection required by 
paragraph (j) or (k) of this AD and Airbus Service Bulletin A300-53-
6123, Revision 06, excluding Inspection Report, dated September 28, 
2011; or Airbus Service Bulletin A300-53-0350, Revision 03, dated 
July 26, 2007; specifies to contact Airbus: Before further flight, 
repair the crack using a method approved by the Manager, 
International Branch, ANM-116, Transport Airplane Directorate, FAA; 
or the EASA; or Airbus's EASA DOA.

(n) Credit for Previous Actions

    This paragraph provides credit for actions required by 
paragraphs (j) and (l) of this AD, if those actions were performed 
before the effective date of this AD using the applicable service 
information specified in paragraphs (n)(1) through (n)(7) of this 
AD.
    (1) Airbus Service Bulletin A300-53-0350, Revision 01, dated 
December 18, 2001, which is not incorporated by reference in this 
AD.
    (2) Airbus Service Bulletin A300-53-0350, Revision 02, excluding 
Appendix 01, dated November 12, 2002, which is incorporated by 
reference in AD 2004-20-14, Amendment 39-13819 (69 FR 60809, October 
13, 2004).
    (3) Airbus Service Bulletin A300-53-6123, Revision 01, dated 
December 18, 2001, which is not incorporated by reference in this 
AD.
    (4) Airbus Service Bulletin A300-53-6123, Revision 02, excluding 
Appendix 01, dated November 12, 2002, which is incorporated by 
reference in AD 2004-20-14, Amendment 39-13819 (69 FR 60809, October 
13, 2004).
    (5) Airbus Service Bulletin A300-53-6123, Revision 03, dated 
August 20, 2004, which is not incorporated by reference in this AD.
    (6) Airbus Service Bulletin A300-53-6123, Revision 04, dated 
April 25, 2008, which is not incorporated by reference in this AD.
    (7) Airbus Service Bulletin A300-53-6123, Revision 05, dated 
August 1, 2011, which is not incorporated by reference in 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, FAA, has the authority to approve AMOCs for 
this AD, if requested using the procedures found in 14 CFR 39.19. In 
accordance with 14 CFR 39.19, send your request to your principal 
inspector or local Flight Standards District Office, as appropriate. 
If sending information directly to the International Branch, send it 
to ATTN: Dan Rodina, Aerospace Engineer, International Branch, ANM-
116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., 
Renton, WA 98057-3356; telephone 425-227-2125; fax 425-227-1149. 
Information may be emailed to: 9-ANM-116-AMOC-REQUESTS@faa.gov. 
Before using any approved AMOC, notify your appropriate principal 
inspector, or lacking a principal inspector, the manager of the 
local flight standards district office/certificate holding district 
office. The AMOC approval letter must specifically reference this 
AD.
    (2) Contacting the Manufacturer: As of the effective date of 
this AD, for any requirement in this AD to obtain corrective actions 
from a manufacturer, the action must be accomplished using a method 
approved by the Manager, International Branch, ANM-116, Transport 
Airplane Directorate, FAA; or the EASA; or Airbus's EASA DOA. If 
approved by the DOA, the approval must include the DOA-authorized 
signature.

(p) Related Information

    (1) Refer to Mandatory Continuing Airworthiness Information 
(MCAI) Airworthiness Directive 2013-0184R1, dated August 22, 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-2015-1417.
    (2) For service information identified in this AD, contact 
Airbus SAS, Airworthiness Office--EAW, 1 Rond Point Maurice 
Bellonte, 31707 Blagnac Cedex, France;

[[Page 27611]]

telephone +33 5 61 93 36 96; fax +33 5 61 93 44 51; email 
account.airworth-eas@airbus.com; 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 April 30, 2015.
Michael Kaszycki,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2015-11554 Filed 5-13-15; 8:45 am]
 BILLING CODE 4910-13-P


