AD 2016-07-17

[Federal Register Volume 81, Number 69 (Monday, April 11, 2016)]
[Rules and Regulations]
[Pages 21246-21250]
From the Federal Register Online via the Government Publishing Office [<a href="http://www.gpo.gov">www.gpo.gov</a>]
[FR Doc No: 2016-07574]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2015-1426; Directorate Identifier 2013-NM-200-AD; 
Amendment 39-18462; AD 2016-07-17]
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) 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 required 
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. This new AD reduces 
the inspection compliance time and repetitive inspection intervals. 
This AD was prompted by a determination that the inspection compliance 
time and repetitive inspection interval must be reduced to allow timely 
detection of fatigue 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 fatigue cracking, which could reduce the 
residual strength of the top skin of the wings, and consequently

[[Page 21247]]

affect the structural integrity of the airframe.

DATES: This AD becomes effective May 16, 2016.
    The Director of the Federal Register approved the incorporation by 
reference of a certain publication listed in this AD as of May 16, 
2016.
    The Director of the Federal Register approved the incorporation by 
reference of a certain other publication listed in this AD as of 
October 30, 1997 (62 FR 50251, September 25, 1997).

ADDRESSES: 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 <a href="/cdn-cgi/l/email-protection#6c0d0f0f03190218420d051e1b031e180441090d1f2c0d051e0e191f420f0301"><span class="__cf_email__" data-cfemail="dfbebcbcb0aab1abf1beb6ada8b0adabb7f2babeac9fbeb6adbdaaacf1bcb0b2">[email&#160;protected]</span></a>; Internet 
<a href="http://www.airbus.com">http://www.airbus.com</a>. 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 <a href="http://www.regulations.gov">http://www.regulations.gov</a> by searching for and locating Docket No. FAA-2015-
1426.

Examining the AD Docket

    You may examine the AD docket on the Internet at <a href="http://www.regulations.gov">http://www.regulations.gov</a> 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 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.

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 97-20-07, Amendment 39-10145 (62 FR 50251, 
September 25, 1997) (``AD 97-20-07''). AD 97-20-07 applied to 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 NPRM published in the Federal Register on 
June 5, 2015 (80 FR 32058) (``the NPRM''). The NPRM was prompted by a 
determination that the inspection compliance time and repetitive 
inspection interval must be reduced to allow timely detection of 
fatigue cracking in the left and right wings in the area where the top 
skin attaches to the center spar. The NPRM proposed to continue to 
require 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. The NPRM 
also proposed to reduce the inspection compliance time and repetitive 
inspection intervals. We are issuing this AD to detect and correct this 
fatigue cracking, which could reduce the residual strength of the top 
skin of the wings, and consequently affect the structural integrity of 
the airframe.
    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 * * * [an airworthiness directive] 
(later revised twice) to require repetitive inspections of the 
affected area and, depending on findings, accomplishment of 
applicable corrective action(s).
    Since [the French] * * * [airworthiness directive] [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 [the French AD] * * * 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 <a href="http://www.regulations.gov">http://www.regulations.gov</a> by searching for and locating Docket No. FAA-2015-
1426.

Comments

    We gave the public the opportunity to participate in developing 
this AD. We received no comments on the NPRM or on the determination of 
the cost to the public.

Changes Made to This Final Rule

    Paragraph (m)(2) of the proposed AD inadvertently included the 
corrective action for the low frequency eddy current (LFEC) inspections 
for cracking specified in paragraphs (k) and (l) of the proposed AD; 
however, the corrective action in paragraph (m)(2) of this AD applies 
only to the new high frequency eddy current (HFEC) inspections required 
by this AD. We have revised paragraph (m)(2) of this AD to specify the 
corrective action for the HFEC inspections for cracking specified in 
paragraphs (i), (j), and (m)(1) of this AD. We have added new paragraph 
(m)(4) of this AD to specify the corrective actions for the LFEC 
inspections specified in paragraphs (k) and (l) of this AD.

Conclusion

    We reviewed the available data 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:
    <bullet> Are consistent with the intent that was proposed in the 
NPRM for correcting the unsafe condition; and
    <bullet> Do not add any additional burden upon the public than was 
already proposed in the NPRM.

Related Service Information Under 1 CFR Part 51

    Airbus has issued Service Bulletin A300-57-6044, Revision 04, dated 
August 19, 2011, including Appendix 01, Revision 04, 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. This service information is reasonably available

[[Page 21248]]

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 47 airplanes of U.S. registry.
    The actions required by AD 97-20-07, and retained in this 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 will take about 5 work-hours per product 
to comply with the new 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 $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 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 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.

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) 
97-20-07, Amendment 39-10145 (62 FR 50251, September 25, 1997), and 
adding the following new AD:

2016-07-17 Airbus: Amendment 39-18462. Docket No. FAA-2015-1426; 
Directorate Identifier 2013-NM-200-AD.

(a) Effective Date

    This AD becomes effective May 16, 2016.

(b) Affected ADs

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

(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 fatigue 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 fatigue 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, 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 2, dated September 6, 
1995, including Appendix 1, Revision 1, dated November 25, 1994; or 
Airbus Service Bulletin A300-57-6044, Revision 04, dated August 19, 
2011, including Appendix 01, Revision 04, dated August 19, 2011. As 
of the effective date of this AD, use only Airbus Service Bulletin 
A300-57-6044, Revision 04, dated August 19, 2011, including Appendix 
01, Revision 04, dated August 19, 2011. Accomplishment of the 
inspection required by paragraph (i) of this AD terminates the 
inspection requirements of this paragraph.
    (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 inspection 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 the introductory text of paragraph 
(g), paragraph (g)(1), or paragraph (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 2, dated September 6, 1995, 
including Appendix 1, Revision 1, dated November 25, 1994; or Airbus 
Service Bulletin A300-57-6044, Revision 04, dated August 19, 2011, 
including Appendix 01, Revision 04, dated August 19, 2011. As of the 
effective date of this AD, use only Airbus Service Bulletin A300-57-
6044, Revision 04, dated August 19, 2011, including Appendix 01, 
Revision 04, 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.

[[Page 21249]]

    (3) If any cracking is detected or confirmed during any HFEC 
inspection required by the introductory text of paragraph (g), 
paragraph (g)(1), or paragraph (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 2, dated September 6, 1995, 
including Appendix 1, Revision 1, dated November 25, 1994; or Airbus 
Service Bulletin A300-57-6044, Revision 04, dated August 19, 2011, 
including Appendix 01, Revision 04, dated August 19, 2011. As of the 
effective date of this AD, use only Airbus Service Bulletin A300-57-
6044, Revision 04, dated August 19, 2011, including Appendix 01, 
Revision 04, 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 2, dated September 6, 1995, including Appendix 1, 
Revision 1, dated November 25, 1994; or Airbus Service Bulletin 
A300-57-6044, Revision 04, dated August 19, 2011, including Appendix 
01, Revision 04, dated August 19, 2011. As of the effective date of 
this AD, use only Airbus Service Bulletin A300-57-6044, Revision 04, 
dated August 19, 2011, including Appendix 01, Revision 04, 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 2, dated September 6, 1995, 
including Appendix 1, Revision 1, dated November 25, 1994; or Airbus 
Service Bulletin A300-57-6044, Revision 04, dated August 19, 2011, 
including Appendix 01, Revision 04, dated August 19, 2011. As of the 
effective date of this AD, use only Airbus Service Bulletin A300-57-
6044, Revision 04, dated August 19, 2011, including Appendix 01, 
Revision 04, dated August 19, 2011. Thereafter, conduct a low 
frequency eddy current (LFEC) 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 2, dated September 6, 1995, including 
Appendix 1, Revision 1, dated November 25, 1994, references Airbus 
Service Bulletin A300-57-6041, Revision 4, 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, 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 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 2, 
dated September 6, 1995, including Appendix 1, Revision 1, dated 
November 25, 1994; or Airbus Service Bulletin A300-57-6044, Revision 
04, dated August 19, 2011, including Appendix 01, Revision 04, dated 
August 19, 2011. As of the effective date of this AD, use only 
Airbus Service Bulletin A300-57-6044, Revision 04, dated August 19, 
2011, including Appendix 01, Revision 04, 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, Transport Airplane Directorate, FAA. 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, dated August 19, 
2011, including Appendix 01, Revision 04, 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 visual 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 visual 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, dated August 19, 2011, including 
Appendix 01, Revision 04, 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.

(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 
inspection required by paragraph (i) or (j) of this AD: Before 
further flight, confirm this finding and the length of

[[Page 21250]]

this cracking by conducting an HFEC inspection, in accordance with 
the Accomplishment Instructions of Airbus Service Bulletin A300-57-
6044, Revision 04, dated August 19, 2011, including Appendix 01, 
Revision 04, 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), or (m)(1) 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, dated August 19, 2011, including Appendix 01, Revision 
04, dated August 19, 2011, except as specified in paragraph (o) of 
this AD. Do repetitive detailed 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, 
dated August 19, 2011, including Appendix 01, Revision 04, 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, dated August 19, 2011, including Appendix 01, Revision 
04, 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, dated August 19, 2011, including Appendix 
01, Revision 04, 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 hole 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, dated August 19, 
2011, including Appendix 01, Revision 04, dated August 19, 2011.
    (4) If any cracking is found during any LFEC inspection required 
by paragraph (k) or (l) of this AD: Before further flight, repair 
using a method approved by the Manager, International Branch, ANM-
116, Transport Airplane Directorate, FAA; or EASA; or Airbus's EASA 
DOA.

(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, Revision 03, dated April 7, 1999, which is not 
incorporated by reference in this AD.

(o) Exception to Service Information Specification

    Although Airbus Service Bulletin A300-57-6044, Revision 04, 
dated August 19, 2011, including Appendix 01, Revision 04, 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: <a href="/cdn-cgi/l/email-protection#edd4c0aca3a0c0dcdcdbc0aca0a2aec0bfa8bcb8a8beb9bead8b8c8cc38a829b"><span class="__cf_email__" data-cfemail="6f56422e2122425e5e59422e22202c423d2a3e3a2a3c3b3c2f090e0e41080019">[email&#160;protected]</span></a>. 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 <a href="http://www.regulations.gov">http://www.regulations.gov</a> by searching 
for and locating Docket No. FAA-2015-1426.
    (2) Service information identified in this AD that is not 
incorporated by reference is available at the addresses specified in 
paragraphs (r)(5) and (r)(6) of this AD.

(r) 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 
May 16, 2016
    (i) Airbus Service Bulletin A300-57-6044, Revision 04, dated 
August 19, 2011, including Appendix 01, Revision 04, dated August 
19, 2011.
    (ii) Reserved.
    (4) The following service information was approved for IBR on 
October 30, 1997 (62 FR 50251, September 25, 1997).
    (i) Airbus Service Bulletin A300-57-6044, Revision 2, dated 
September 6, 1995, including Appendix 1, Revision 1, dated November 
25, 1994. Pages 1 through 8 of this document are identified as 
Revision 2, dated September 6, 1995; pages 9 and 10 are identified 
as original, dated March 1, 1993. Page 1 of Appendix 1 is identified 
as Revision 1, dated November 25, 1994; and pages 2 through 6 are 
identified as original, dated March 1, 1993.
    (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 <a href="/cdn-cgi/l/email-protection#244547474b514a500a454d56534b56504c0941455764454d564651570a474b49"><span class="__cf_email__" data-cfemail="b7d6d4d4d8c2d9c399d6dec5c0d8c5c3df9ad2d6c4f7d6dec5d5c2c499d4d8da">[email&#160;protected]</span></a>; 
Internet <a href="http://www.airbus.com">http://www.airbus.com</a>.
    (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: <a href="http://www.archives.gov/federal-register/cfr/ibr-locations.html">http://www.archives.gov/federal-register/cfr/ibr-locations.html</a>.

    Issued in Renton, Washington, on March 24, 2016.
Michael Kaszycki,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2016-07574 Filed 4-8-16; 8:45 am]
 BILLING CODE 4910-13-P