
[Federal Register Volume 81, Number 23 (Thursday, February 4, 2016)]
[Rules and Regulations]
[Pages 5889-5893]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2016-00379]



[[Page 5889]]

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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; 
Amendment 39-18369; AD 2016-01-10]
RIN 2120-AA64


Airworthiness Directives; Airbus Airplanes

AGENCY: Federal Aviation Administration (FAA), Department of 
Transportation (DOT).

ACTION: Final rule.

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SUMMARY: We are superseding Airworthiness Directive (AD) 2004-20-14, 
for all Airbus Model A300 B4-2C, B4-103, and B4-203 airplanes; and all 
Airbus Model A300 B4-600, B4-600R, and F4-600R series airplanes. AD 
2004-20-14 required 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. This 
new AD reduces the inspection compliance time and repetitive inspection 
intervals, and adds Airbus Model A300 C4-605R Variant F airplanes to 
the applicability. 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 FR 47. We are issuing this AD to detect and correct cracking 
of the splice fitting at fuselage FR 47; such cracking could result in 
reduced structural integrity of the airplane.

DATES: This AD becomes effective March 10, 2016.
    The Director of the Federal Register approved the incorporation by 
reference of certain publications listed in this AD as of March 10, 
2016.
    The Director of the Federal Register approved the incorporation by 
reference of certain other publications listed in this AD as of 
November 17, 2004 (69 FR 60809, October 13, 2004).

ADDRESSES: You may examine the AD docket on the Internet at http://www.regulations.gov/#!docketDetail;D=FAA-2015-1417; or in person at the 
Docket Management Facility, U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue SE., Washington, DC.
    For service information identified in this final rule, 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 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. It is also available on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2015-
1417.

FOR FURTHER INFORMATION CONTACT: Dan Rodina, Aerospace Engineer, 
International Branch, ANM-116, Transport Airplane Directorate, FAA, 
1601 Lind Avenue SW., Renton, WA 98057-3356; telephone 425-227-2125; 
fax 425-227-1149.

SUPPLEMENTARY INFORMATION: 

Discussion

    We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR 
part 39 to supersede AD 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 applied to all Model 
A300 B4-600, B4-600R, and F4-600R (collectively called Model A300-600) 
series airplanes; and all Model A300 B4 series airplanes. The NPRM 
published in the Federal Register on May 14, 2015 (80 FR 27607). The 
NPRM 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 FR 47. The NPRM 
proposed to continue to require repetitive inspections to detect 
cracking of the splice fitting at fuselage FR 47 between stringers 24 
and 26 (left- and right-hand sides), and corrective actions if 
necessary. The NPRM also proposed to reduce the inspection compliance 
time and repetitive inspection intervals, and add Model A300 C4-605R 
Variant F airplanes to the applicability. We are issuing this AD to 
detect and correct cracking of the splice fitting at fuselage FR 47; 
such cracking could result in reduced structural integrity of the 
airplane.
    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 all Model A300 B4-
600, B4-600R, and F4-600R (collectively called Model A300-600) series 
airplanes; all Model A300 B4 series airplanes; and all Model A300 C4-
605R Variant F airplanes. 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, 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/#!documentDetail;D=FAA-2015-1417-0002.

[[Page 5890]]

Comments

    We gave the public the opportunity to participate in developing 
this AD. The following presents the comments received on the NPRM (80 
FR 27607, May 14, 2015) and the FAA's response to each comment.

Request To Revise Compliance Times To Match Service Information

    United Parcel Service (UPS) and FedEx Express requested that we 
revise the compliance times in paragraph (k) of the proposed AD (80 FR 
27607, May 14, 2015) to match the compliance times in Airbus Service 
Bulletin A300-53-6123, Revision 06, dated September 28, 2011, and EASA 
AD 2013-0184R1, dated August 22, 2013.
    We agree with the commenters' requests to revise the compliance 
times in paragraph (k) of this AD to reflect the compliance times in 
EASA AD 2013-0184R1, dated August 22, 2013. We have revised paragraph 
(k) of this AD accordingly. The changes extend the inspection interval 
and do not add an additional burden on operators.

Request To Retain Inspection Intervals in AD 2004-20-14, Amendment 39-
13819 (69 FR 60809, October 13, 2004)

    UPS requested that we revise paragraph (k) of the proposed AD (80 
FR 27607, May 14, 2015) to retain the inspection intervals in AD 2004-
20-14, Amendment 39-13819 (69 FR 60809, October 13, 2004), until the 
airplanes have reached their design service goal (DSG). UPS stated that 
acceleration of the inspection interval on airplanes that have less 
than 33 percent of the original DSG does not enhance safety. UPS 
explained that the proposed inspection interval reduction introduces 
additional opportunities for fastener hole damage due to the inspection 
process, thus increasing the risk for subsequent fatigue damage.
    We disagree with the commenter's request. Since AD 2004-20-14, 
Amendment 39-13819 (69 FR 60809, October 13, 2004), was issued, Airbus 
conducted a fleet survey and an analysis to extend the DSG. In 
consideration of this information, we determined that the inspection 
interval and thresholds needed to be reduced to support timely 
detection of cracks. The Airbus analysis for the extension of the DSG 
and other data was used to determine the compliance thresholds and 
intervals for this AD. We have not changed this AD in this regard.

Request To Revise Repetitive Inspection Interval

    FedEx Express requested that we revise the flight-cycle compliance 
time in paragraph (k)(1) of the proposed AD (80 FR 27607, May 14, 2015) 
from 2,000 flight cycles to 2,200 flight cycles so that the inspections 
can consistently be performed at the same interval as a C-check. FedEx 
Express stated that it considers the 2,200-flight-cycle interval to be 
conservative. FedEx Express submitted service experience from the 
previous inspections showing relatively few findings.
    We do not agree with the commenter's request. The inspections are 
dependent upon various configurations and average flight times (AFTs). 
The commenter did not identify the applicable configuration for the 
requested 2,200-flight-cycle interval. Operators may request approval 
of a different interval under the provisions of paragraph (o)(1) of 
this AD if sufficient specific information is submitted to substantiate 
that the compliance time will provide an acceptable level of safety. We 
have not changed this AD in this regard.

Request To Remove Average Flight Time Classifications

    UPS request that we revise the compliance times to remove the AFT 
classifications. UPS stated that it considers that the inspection 
interval difference with regard to the AFT adds a level of compliance 
complication that does not enhance fleet safety.
    We disagree with the commenter's request. The compliance time 
thresholds and intervals using AFTs were developed by Airbus using 
fleet experience and analysis. Once we issue this AD, the commenter may 
request approval of a different interval under the provisions of 
paragraph (o)(1) of this AD. Sufficient data must be submitted to 
substantiate that the compliance time will provide an acceptable level 
of safety. We have not changed this AD in this regard.

Conclusion

    We reviewed the available data, including the comments received, 
and determined that air safety and the public interest require adopting 
this AD with the changes described previously and minor editorial 
changes. We have determined that these changes:
     Are consistent with the intent that was proposed in the 
NPRM (80 FR 27607, May 14, 2015) for correcting the unsafe condition; 
and
     Do not add any additional burden upon the public than was 
already proposed in the NPRM (80 FR 27607, May 14, 2015).

Related Service Information Under 1 CFR Part 51

    Airbus has issued the following service information:
     Airbus Service Bulletin A300-53-0350, Revision 03, 
including Appendix 03, dated July 26, 2007. This service bulletin 
describes procedures for inspections to detect cracking of the splice 
fitting at fuselage FR 47 between stringers 24 and 26, and corrective 
actions.
     Airbus Service Bulletin A300-53-6123, Revision 06, dated 
September 28, 2011. This service bulletin describes procedures for 
inspections for cracking of the splice fitting at fuselage FR 47 
between stringers 24 and 26, and corrective actions.
    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.

Costs of Compliance

    We estimate that this AD affects 72 airplanes of U.S. registry.
    We also estimate that it will take up to 14 work-hours per product 
to comply with the basic requirements of this AD. The average labor 
rate is $85 per work hour. Based on these figures, we estimate the cost 
of this AD on U.S. operators to be $85,680, or $1,190 per product.
    In addition, we estimate that any necessary follow-on actions will 
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.

[[Page 5891]]

Regulatory Findings

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

Examining the AD Docket

    You may examine the AD docket on the Internet at http://www.regulations.gov/#!docketDetail;D=FAA-2015-1417; or in person at the 
Docket Management Facility between 9 a.m. and 5 p.m., Monday through 
Friday, except Federal holidays. The AD docket contains this AD, the 
regulatory evaluation, any comments received, and other information. 
The street address for the Docket Operations office (telephone 800-647-
5527) is in the ADDRESSES section.

List of Subjects in 14 CFR Part 39

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

Adoption of the Amendment

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

PART 39--AIRWORTHINESS DIRECTIVES

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

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


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:

2016-01-10 Airbus: Amendment 39-18369; Docket No. FAA-2015-1417; 
Directorate Identifier 2013-NM-159-AD.

(a) Effective Date

    This AD becomes effective March 10, 2016.

(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.

(e) Reason

    This AD was prompted by a determination that the inspection 
compliance time and repetitive inspection interval specified in AD 
2004-20-14, Amendment 39-13819 (69 FR 60809, October 13, 2004), 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; such 
cracking could result in reduced structural integrity of the 
airplane.

(f) Compliance

    Comply with this AD within the compliance times specified, 
unless already 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; or 
Revision 06, dated September 28, 2011. Accomplishment of the actions

[[Page 5892]]

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; 
specifies 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, 
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, 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.
    (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 
2,000 flight cycles or 4,300 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 2,100 flight cycles or 3,200 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 1,600 
flight cycles or 3,500 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 1,700 flight cycles or 2,600 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 crack is found: Before further flight, do the 
applicable corrective actions, in accordance with the Accomplishment 
Instructions of Airbus

[[Page 5893]]

Service Bulletin A300-53-6123, Revision 06, 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, 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)(6) 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 was 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 03, dated 
August 20, 2004, which is not incorporated by reference in this AD.
    (5) Airbus Service Bulletin A300-53-6123, Revision 04, dated 
April 25, 2008, which is not incorporated by reference in this AD.
    (6) 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, ANM-116, Transport Airplane Directorate, FAA, 
has the authority to approve AMOCs for this AD, if requested using 
the procedures found in 14 CFR 39.19. In accordance with 14 CFR 
39.19, send your request to your principal inspector or local Flight 
Standards District Office, as appropriate. If sending information 
directly to the International Branch, send it to ATTN: Dan Rodina, 
Aerospace Engineer, International Branch, ANM-116, Transport 
Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057-
3356; telephone 425-227-2125; fax 425-227-1149. Information may be 
emailed to: 9-ANM-116-AMOC-REQUESTS@faa.gov. 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) Service information identified in this AD that is not 
incorporated by reference is available at the addresses specified in 
paragraphs (q)(5) and (q)(6) of this AD.

(q) Material Incorporated by Reference

    (1) The Director of the Federal Register approved the 
incorporation by reference (IBR) of the service information listed 
in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51.
    (2) You must use this service information as applicable to do 
the actions required by this AD, unless this AD specifies otherwise.
    (3) The following service information was approved for IBR on 
March 10, 2016.
    (i) Airbus Service Bulletin A300-53-0350, Revision 03, dated 
July 26, 2007.
    (ii) Airbus Service Bulletin A300-53-6123, Revision 06, dated 
September 28, 2011.
    (4) The following service information was approved for IBR on 
November 17, 2004 (69 FR 60809, October 13, 2004).
    (i) Airbus Service Bulletin A300-53-6123, Revision 02, excluding 
Appendix 01, dated November 12, 2002.
    (ii) Reserved.
    (5) 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 account.airworth-eas@airbus.com; 
Internet http://www.airbus.com.
    (6) 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.
    (7) You may view this service information that is incorporated 
by reference at the National Archives and Records Administration 
(NARA). For information on the availability of this material at 
NARA, call 202-741-6030, or go to: http://www.archives.gov/federal-register/cfr/ibr-locations.html.

    Issued in Renton, Washington, on December 31, 2015.
Phil Forde,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2016-00379 Filed 2-3-16; 8:45 am]
BILLING CODE 4910-13-P


