Document ID: FAA-2015-4813-0001
Agency: faa
Document Type: Proposed Rule
Title: Airworthiness Directives: Airbus Airplanes
Posted Date: 2015-11-17T05:00Z

[Federal Register Volume 80, Number 221 (Tuesday, November 17, 2015)]
[Proposed Rules]
[Pages 71751-71755]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2015-28892]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2015-4813; Directorate Identifier 2013-NM-161-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) 99-16-01, 
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 99-16-01 currently requires 
repetitive inspections of certain bolt holes where parts of the main 
landing gear (MLG) are attached to the wing rear spar, and repair if 
necessary. Since we issued AD-99-16-01, we have determined that the 
risk of cracking in the rear spar is higher than initially determined. 
This proposed AD would add airplanes to the applicability, reduce the 
compliance times and repetitive intervals for the inspections, and 
change the inspection procedures. We are proposing this AD to detect 
and correct cracking of the rear spar of the wing, which could result 
in reduced structural integrity of the airplane.

DATES: We must receive comments on this proposed AD by January 4, 2016.

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 referenced service information at the 
FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. 
For information on the availability of this material at the FAA, call 
425-227-1221.

Examining the AD Docket

    You may examine the AD docket on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2015-
4813; or in person at the Docket Management Facility between 9 a.m. and 
5 p.m., Monday through Friday, except Federal holidays. The AD docket 
contains this proposed AD, the regulatory evaluation, any comments 
received, and other information. The street address for the Docket 
Operations office (telephone 800-647-5527) is in the ADDRESSES section. 
Comments will be available in the AD docket shortly after receipt.

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

SUPPLEMENTARY INFORMATION:

Comments Invited

    We invite you to send any written relevant data, views, or 
arguments about this proposed AD. Send your comments to an address 
listed under the ADDRESSES section. Include ``Docket No. FAA-2015-4813; 
Directorate Identifier 2013-NM-161-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 July 21, 1999, we issued AD 99-16-01, Amendment 39-11236 (64 FR 
40743, July 28, 1999). AD 99-16-01 requires actions intended to address 
an unsafe condition on 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).
    Since we issued AD 99-16-01, Amendment 39-11236 (64 FR 40743,

[[Page 71752]]

July 28, 1999), a fleet survey and updated fatigue and damage tolerance 
analyses have shown that the threshold for the initial inspections and 
the intervals for the repetitive inspections need to be reduced.
    The European Aviation Safety Agency (EASA), which is Technical 
Agent for the Member States of the European Union, has issued EASA 
Airworthiness Directive 2013-0180, dated August 9, 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:

    During full-scale fatigue testing, cracks were found on the rear 
spar from certain bolt holes at the attachment of the Main Landing 
gear (MLG) forward pick-up fitting and the MLG Rib 5 aft.
    This condition, if not detected and corrected, could reduce the 
structural integrity of the aeroplane.
    DGAC [Direction G[eacute]n[eacute]rale de l'Aviation Civile] 
France issued * * * [an AD] (later revised) to require High 
Frequency Eddy Current (HFEC) or Ultrasonic (U/S) inspections of 
certain fastener holes where the MLG forward pick-up fitting and MLG 
Rib 5 aft are attached to the rear spar.
    Since DGAC France * * * [issued a revised AD, which corresponded 
to FAA AD 99-16-01, Amendment 39-11236 (64 FR 40743, July 28, 1999), 
which superseded FAA AD 95-20-02, Amendment 39-9380 (60 FR 52618, 
October 10, 1995)] * * *, 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 shown that the 
threshold and interval must be reduced to allow timely detection of 
these cracks and accomplishment of an applicable corrective action.
    For the reasons described above, this [EASA] AD retains the 
requirements of [the revised DGAC France AD], which is superseded, 
but reduces the related compliance times.

The new, reduced threshold for the initial inspection ranges between 
8,900 total flight cycles/20,000 total flight hours, and 34,600 total 
flight cycles/77,800 total flight hours, depending on the modification. 
The grace periods (750 or 1,500 landings) for airplanes that have 
exceeded the specified thresholds are unchanged from those provided in 
AD 99-16-01, Amendment 39-11236 (64 FR 40743, July 28, 1999). The new, 
reduced intervals for the repetitive inspections range between 4,000 
flight cycles/9,000 flight hours (whichever occurs first), and 8,900 
flight cycles/20,000 flight hours (whichever occurs first), depending 
on the modification. You may examine the MCAI in the AD docket on the 
Internet at http://www.regulations.gov by searching for and locating 
Docket No. FAA-2015-4813.

Clarification of Terminating Action for Certain Paragraphs

    We have determined that if the inspection in paragraph 
(g)(4)(ii)(B)(2) of the proposed AD was done it would terminate the 
repetitive inspections specified in paragraph (g)(2) of this proposed 
AD. We have revised paragraph (g)(3)(i) of this proposed AD to include 
accomplishment of the inspection in paragraph (g)(4)(ii)(B)(2) as a 
terminating action. We have also determined that if the inspection in 
paragraph (g)(4)(ii)(B)(1) of the proposed AD was done it would 
terminate the repetitive inspections specified in paragraph (g)(2) of 
this proposed AD. We have revised paragraph (g)(3)(ii) of this proposed 
AD to include accomplishment of the inspection in paragraph 
(g)(4)(ii)(B)(1) of this AD as a terminating action.

Related Service Information Under 1 CFR Part 51

    Airbus has issued Service Bulletin A300-57-6017, Revision 04, 
including Appendix 1, dated February 4, 2011. This service information 
describes procedures for repetitive inspections of certain bolt holes 
where parts of the MLG are attached to the wing rear spar, and repair. 
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.

Changes to AD 99-16-01, Amendment 39-11236 (64 FR 40743, July 28, 1999)

    This proposed AD would retain all the requirements of AD 99-16-01, 
Amendment 39-11236 (64 FR 40743, July 28, 1999). Since AD 99-16-01 was 
issued, the AD format has been revised, and certain paragraphs have 
been rearranged. As a result, the corresponding paragraph identifiers 
have been redesignated in this proposed AD, as listed in the following 
table:

                      Revised Paragraph Identifiers
------------------------------------------------------------------------
    Requirement in AD 99-16-01,
 Amendment 39-11236 (64 FR 40743,     Corresponding requirement in this
          July 28, 1999)                         proposed AD
------------------------------------------------------------------------
 paragraph (a)                       paragraph (g)(1)
 paragraph (b)                       paragraph (g)(2)
 paragraph (c)                       paragraph (g)(3)
 paragraph (d)                       paragraph (g)(4)
 paragraph (e)                       paragraph (g)(5)
 paragraph (f)                       paragraph (g)(6)
------------------------------------------------------------------------

    Certain notes that appeared in AD 99-16-01, Amendment 39-11236 (64 
FR 40743, July 28, 1999), were either removed due to the revised AD 
format or converted to regulatory text in this proposed AD.
     Notes 1, 6, and 7 of AD 99-16-01 have been removed from 
this proposed AD. Due to the revised AD format, certain information in 
these notes is now included in the AD template.
     The content of Note 2 of AD 99-16-01 is regulatory in 
nature; therefore, we have included that information in paragraph 
(k)(1) of this proposed AD.
     The content of Note 3 of AD 99-16-01 has been redesignated 
as Note 1 to paragraph (g) in this proposed AD.
     The content of Note 4 of AD 99-16-01 is regulatory in 
nature; therefore, we have included that information in paragraph 
(g)(2)(ii) of this proposed AD.
     The content of Note 5 of AD 99-16-01 is regulatory in 
nature; therefore, we have included that information in paragraph 
(k)(3) of this proposed AD.

Costs of Compliance

    We estimate that this proposed AD affects 71 airplanes of U.S. 
registry.
    The actions required by AD 99-16-01, Amendment 39-11236 (64 FR 
40743, July 28, 1999), and retained in this proposed AD, take about 226 
work-hours per product, at an average labor rate of $85 per work-hour. 
Required parts cost about $0 per product. Based on these figures, the 
estimated cost of the actions that are required by AD 99-16-01 is 
$19,210 per product, per inspection cycle.
    We also estimate that it would take about 226 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 
$1,363,910, or $19,210 per product.
    We have received no definitive data that would enable us to provide 
cost estimates for the on-condition actions specified in this proposed 
AD.

[[Page 71753]]

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) 
99-16-01, Amendment 39-11236 (64 FR 40743, July 28, 1999), and adding 
the following new AD:

Airbus: Docket No. FAA-2015-4813; Directorate Identifier 2013-NM-
161-AD.

(a) Comments Due Date

    We must receive comments by January 4, 2016.

(b) Affected ADs

    This AD replaces AD 99-16-01, Amendment 39-11236 (64 FR 40743, 
July 28, 1999).

(c) Applicability

    This AD applies to Airbus Model A300 B4-601, B4-603, B4-620, and 
B4-622 airplanes; Model A300 B4-605R and B4-622R airplanes; Model 
A300 F4-605R airplanes; and Model A300 C4-605R Variant F airplanes; 
certificated in any category; all manufacturer serial numbers.

(d) Subject

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

(e) Reason

    This AD was prompted by the results of a full-scale fatigue test 
when cracking was found on the rear spar of the wing, and the 
subsequent determination that the risk of such cracking is higher 
than initially determined. We are issuing this AD to detect and 
correct cracking of the rear spar of the wing, which 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 Inspections and Corrective Actions

    This paragraph restates the requirements of paragraphs (a), (b), 
(c), (d), (e), and (f) of AD 99-16-01, Amendment 39-11236 (64 FR 
40743, July 28, 1999), with revised service information and reduced 
thresholds and repetitive intervals, for Airbus Model A300 B4-600, 
B4-600R, and F4-600R series airplanes, and Model A300 C4-605R 
Variant F airplanes; manufacturer serial numbers (MSNs) 252 through 
553 inclusive; except those airplanes on which Airbus Modification 
07601 has been accomplished prior to delivery.
    (1) Perform a high frequency eddy current (HFEC) rototest 
inspection to detect cracks in certain bolt holes where the main 
landing gear (MLG) forward pick-up fitting and MLG rib 5 aft are 
attached to the rear spar, in accordance with Airbus Service 
Bulletin A300-57-6017, Revision 01, including Appendix 1, dated July 
25, 1994; or Airbus Service Bulletin A300-57-6017, Revision 04, 
including Appendix 1, dated February 24, 2011. As of the effective 
date of this AD, only Airbus Service Bulletin A300-57-6017, Revision 
04, including Appendix 1, dated February 24, 2011, may be used for 
the actions required by this paragraph.
    (i) For airplanes that have accumulated 17,300 total landings or 
less as of November 9, 1995 (the effective date of AD 99-16-01, 
Amendment 39-11236 (64 FR 40743, July 28, 1999)): Inspect prior to 
the accumulation of 17,300 total landings, or within 1,500 landings 
after November 9, 1995, whichever occurs later.
    (ii) For airplanes that have accumulated 17,301 or more total 
landings, but less than 19,300 total landings as of November 9, 1995 
(the effective date of AD 99-16-01, Amendment 39-11236 (64 FR 40743, 
July 28, 1999)): Inspect within 1,500 landings after November 9, 
1995.
    (iii) For airplanes that have accumulated 19,300 or more total 
landings as of November 9, 1995 (the effective date of AD 99-16-01, 
Amendment 39-11236 (64 FR 40743, July 28, 1999)): Inspect within 750 
landings after November 9, 1995 (the effective date of AD 99-16-01, 
Amendment 39-11236 (64 FR 40743, July 28, 1999)):
    (2) If no crack is found during the inspection required by 
paragraph (g)(1) of this AD, repeat that inspection thereafter at 
the time specified in either paragraph (g)(2)(i) or (g)(2)(ii) of 
this AD, as applicable.
    (i) For airplanes on which Airbus Modification 07716 (as 
specified in Airbus Service Bulletin A300-57-6020) has not been 
accomplished, inspect at the time specified in paragraph 
(g)(2)(i)(A) or (g)(2)(i)(B) of this AD, as applicable.
    (A) For airplanes having MSNs 465 through 553 inclusive: Repeat 
the inspection at intervals not to exceed 13,000 landings, until the 
inspection required by paragraph (g)(4)(ii)(A)(1) of this AD has 
been accomplished.
    (B) For airplanes having MSN 252 through 464 inclusive: Repeat 
the inspection at intervals not to exceed 8,400 landings, until the 
inspection required by paragraph (g)(4)(ii)(A)(2) of this AD has 
been accomplished.
    (ii) For airplanes on which Airbus Modification 07716 has been 
accomplished, inspect at the time specified in either paragraph 
(g)(2)(ii)(A) or (g)(2)(ii)(B) of this AD, as applicable.
    (A) For airplanes having MSNs 465 through 553 inclusive: Repeat 
the inspection at intervals not to exceed 11,800 landings, until the 
inspection required by paragraph (g)(4)(i)(B) of this AD has been 
accomplished.
    (B) For airplanes having MSNs 252 through 464 inclusive: Repeat 
the inspection within 10,700 landings following the initial 
inspection required by paragraph (g)(1) of this AD, and thereafter 
at intervals not to exceed 7,500 landings, until the inspection 
required by paragraph (g)(4)(ii)(B)(2) has been accomplished.
    (3) If any crack is found during the inspection required by 
either paragraph (g)(1) or (g)(2) of this AD, prior to further 
flight,

[[Page 71754]]

accomplish the requirements of either paragraph (g)(3)(i) or 
(g)(3)(ii) of this AD, as applicable.
    (i) For airplanes on which Airbus Modification 07716 has not 
been accomplished: Oversize the bolt hole by \1/32\ inch and repeat 
the HFEC inspection required by paragraph (g)(1) of this AD, in 
accordance with Airbus Service Bulletin 300-57-6017, Revision 01, 
including Appendix 1, dated July 25, 1994. After accomplishing the 
oversizing and HFEC inspection, repeat the inspection, as required 
by paragraph (g)(2) of this AD, at the applicable schedule specified 
in that paragraph, until the inspection required by paragraph 
(g)(4)(ii)(B)(1) or (g)(4)(ii)(B)(2) of this AD has been 
accomplished.
    (A) If no cracking is detected, install the second oversize bolt 
in accordance with Airbus Service Bulletin 300-57-6017, Revision 01, 
including Appendix 1, dated July 25, 1994.
    (B) If any cracking is detected, repair in accordance with a 
method approved by the Manager, International Branch, ANM-116, FAA, 
Transport Airplane Directorate.
    (ii) For airplanes on which Airbus Modification 07716 has been 
accomplished: Repair in accordance with a method approved by the 
Manager, International Branch, ANM-116. After repair, repeat the 
inspections as required by paragraph (g)(2) of this AD at the 
applicable schedule specified in that paragraph, until the 
inspection required by paragraph (g)(4)(ii)(B)(1) or 
(g)(4)(ii)(B)(2) of this AD has been accomplished.
    (4) Perform an ultrasonic inspection to detect cracks in certain 
bolt holes where the MLG forward pick-up fitting and MLG rib 5 aft 
are attached to the rear spar, in accordance with Airbus Service 
Bulletin A300-57-6017, Revision 03, dated November 19, 1997; or 
Revision 04, including Appendix 1, dated February 24, 2011; at the 
time specified in paragraph (g)(4)(i) or (g)(4)(ii) of this AD, as 
applicable. As of the effective date of this AD, only Airbus Service 
Bulletin A300-57-6017, Revision 04, including Appendix 1, dated 
February 24, 2011, may be used for the actions in this paragraph.
    (i) For airplanes not inspected prior to September 1, 1999 (the 
effective date of AD 99-16-01, Amendment 39-11236 (64 FR 40743, July 
28, 1999)), as specified in Airbus Service Bulletin A300-57-6017, 
dated November 22, 1993; or Revision 01, including Appendix 1, dated 
July 25, 1994: Inspect at the time specified in paragraph 
(g)(4)(i)(A), (g)(4)(i)(B), or (g)(4)(i)(C) of this AD, as 
applicable. Accomplishment of this inspection terminates the 
requirements of paragraph (g)(1) of this AD.
    (A) For airplanes that have accumulated 17,300 total landings or 
fewer as of the effective date of this AD: Inspect prior to the 
accumulation of 17,300 total landings, or within 1,500 landings 
after September 1, 1999 (the effective date of AD 99-16-01, 
Amendment 39-11236 (64 FR 40743, July 28, 1999)), whichever occurs 
later.
    (B) For airplanes that have accumulated 17,301 total landings or 
more but fewer than 19,300 total landings as of September 1, 1999 
(the effective date of AD 99-16-01, Amendment 39-11236 (64 FR 40743, 
July 28, 1999)): Inspect within 1,500 landings after September 1, 
1999 (the effective date of AD 99-16-01).
    (C) For airplanes that have accumulated 19,300 total landings or 
more as of September 1, 1999 (the effective date of AD 99-16-01, 
Amendment 39-11236 (64 FR 40743, July 28, 1999)): Inspect within 750 
landings after September 1, 1999 (the effective date of AD 99-16-
01).
    (ii) For airplanes on which an HFEC inspection was performed 
prior to September 1, 1999 (the effective date of AD 99-16-01, 
Amendment 39-11236 (64 FR 40743, July 28, 1999)), in accordance with 
the requirements of paragraph (g)(1) of this AD, or in accordance 
with Airbus Service Bulletin A300-57-6017, dated November 22, 1993: 
Inspect at the time specified in paragraph (g)(4)(ii)(A) or 
(g)(4)(ii)(B) of this AD, as applicable.
    (A) If no cracking was detected during any HFEC inspection 
accomplished prior to September 1, 1999 (the effective date of AD 
99-16-01, Amendment 39-11236 (64 FR 40743, July 28, 1999)), and if 
Airbus Modification 07716 has not been accomplished: Inspect at the 
time specified in paragraph (g)(4)(ii)(A)(1) or (g)(4)(ii)(A)(2) of 
this AD, as applicable.
    (1) For airplanes having MSNs 465 through 553 inclusive: Inspect 
within 13,000 landings after the most recent HFEC inspection, and 
thereafter at intervals not to exceed 8,900 landings. Accomplishment 
of this inspection constitutes terminating action for the repetitive 
inspection requirement of paragraph (g)(2)(i)(A) of this AD.
    (2) For airplanes having MSNs 252 through 464 inclusive: Inspect 
within 8,400 landings after the most recent HFEC inspection, and 
thereafter at intervals not to exceed 5,500 landings. Accomplishment 
of this inspection constitutes terminating action for the repetitive 
inspection requirement of paragraph (g)(2)(i)(B) of this AD.
    (B) If any cracking was detected during any HFEC inspection 
performed prior to the effective date of this AD, regardless of the 
method of repair, or if Airbus Modification 07716 has been 
accomplished: Inspect at the time specified in paragraph 
(g)(4)(ii)(B)(1) or (g)(4)(ii)(B)(2) of this AD, as applicable.
    (1) For airplanes having MSNs 465 through 553 inclusive: Inspect 
within 11,800 landings after the most recent HFEC inspection, and 
thereafter at intervals not to exceed 8,200 landings. Accomplishment 
of this inspection constitutes terminating action for the repetitive 
inspection requirement of paragraph (g)(3)(i) or (g)(3)(ii) of this 
AD, as applicable.
    (2) For airplanes having MSNs 252 through 464 inclusive: Inspect 
within 10,700 landings after the initial inspection in accordance 
with paragraph (g)(1) of this AD, or within 7,500 landings after the 
most recent HFEC inspection, whichever occurs later, and thereafter 
at intervals not to exceed 4,900 landings. Accomplishment of this 
inspection constitutes terminating action for the repetitive 
inspection requirement of paragraph (g)(3)(i) or (g)(3)(ii) of this 
AD, as applicable.
    (5) If no cracking is detected during the ultrasonic inspection 
required by paragraph (g)(4)(i) of this AD, repeat that inspection 
thereafter at the time specified in paragraph (g)(5)(i) or 
(g)(5)(ii) of this AD, as applicable, until the initial ultrasonic 
inspection required by paragraph (h) of this AD is done.
    (i) For airplanes having MSNs 465 through 553 inclusive: Repeat 
the inspection at intervals not to exceed 8,900 landings.
    (ii) For airplanes having MSNs 232 through 464 inclusive: Repeat 
the inspection at intervals not to exceed 5,500 landings.
    (6) If any cracking is detected during any inspection performed 
in accordance with the requirements of paragraph (g)(4) or (g)(5) of 
this AD: Prior to further flight, repair in accordance with a method 
approved by the Manager, International Branch, ANM-116; or the 
Direction G[eacute]n[eacute]rale de l'Aviation Civile (or its 
delegated agent); or the European Aviation Safety Agency (EASA); or 
Airbus's EASA Design Organization Approval (DOA).
    Note 1 to paragraph (g) of this AD: Airbus Service Bulletin 
A300-57-6017, Revision 01, including Appendix 1, dated July 25, 
1994; and Airbus Service Bulletin A300-57-6017, Revision 04, 
including Appendix 1, dated February 24, 2011; also reference Airbus 
Service Bulletin A300-57-6020, dated November 22, 1993, as an 
additional source of service information for installation of 
oversize studs in the bolt holes.

(h) New Repetitive Inspections

    At the applicable times specified in paragraph 1.B.(5), 
``Accomplishment Timescale,'' of Airbus Service Bulletin A300-57-
6017, Revision 04, including Appendix 1, dated February 24, 2011: Do 
ultrasonic inspections to detect cracks in the MLG attachment 
fitting holes on the wing rear spar, in accordance with the 
Accomplishment Instructions of Airbus Service Bulletin A300-57-6017, 
Revision 04, including Appendix 1, dated February 24, 2011. Repeat 
the inspections thereafter at the applicable intervals specified in 
paragraph 1.B.(5), ``Accomplishment Timescale,'' of Airbus Service 
Bulletin A300-57-6017, Revision 04, including Appendix 1, dated 
February 24, 2011. For airplanes modified as specified in Airbus 
Service Bulletin A300-57-6073, the initial inspection threshold is 
counted from the completion date of the modification. Clarification 
of compliance time terminology used in table 1, ``Structural 
Inspection Program,'' of Airbus Service Bulletin A300-57-6017, 
Revision 04, including Appendix 1, dated February 24, 2011, is 
provided in paragraphs (h)(1) through (h)(4) of this AD. 
Accomplishment of the initial inspection terminates the repetitive 
inspections required by paragraph (g)(5) of this AD.
    (1) For pre-Airbus Modification 07716 or pre-Airbus Modification 
11440 airplanes:
    (i) The term ``flight cycles'' in the ``Inspection Threshold'' 
column is total flight cycles accumulated by the airplane.
    (ii) The term ``flight hours'' in the ``Inspection Threshold'' 
column is total flight hours accumulated by the airplane.
    (2) For post-Airbus Modification 07716 airplanes:
    (i) The term ``flight cycles'' in the ``Inspection Threshold'' 
column is total flight cycles accumulated by the airplane.

[[Page 71755]]

    (ii) The term ``flight hours'' in the ``Inspection Threshold'' 
column is total flight hours accumulated by the airplane.
    (3) For post-Airbus Modification 11440 (Airbus Service Bulletin 
A300-57-6073) airplanes:
    (i) The term ``flight cycles'' in the ``Inspection Threshold'' 
column is flight cycles accumulated by the airplane after the 
modification was done.
    (ii) The term ``flight hours'' in the ``Inspection Threshold'' 
column is flight hours accumulated by the airplane after the 
modification was done.
    (4) For post-Airbus Modification 07601 airplanes:
    (i) The term ``flight cycles'' in the ``Inspection Threshold'' 
column is total flight cycles accumulated by the airplane.
    (ii) The term ``flight hours'' in the ``Inspection Threshold'' 
column is total flight hours accumulated by the airplane.

(i) Repairs

    If any crack is found during any inspection required by 
paragraph (h) of this AD: Before further flight, 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).

(j) Repair Not Terminating Action

    Accomplishment of any repair as required by paragraph (i) of 
this AD is not terminating action for the repetitive inspections 
required by paragraph (g) or (h) of this AD.

(k) Credit for Previous Actions

    This paragraph provides credit for actions required by 
paragraphs (g) and (h) of this AD, if those actions were performed 
before the effective date of this AD using any of the following 
service information:
    (1) Airbus Service Bulletin A300-57-6017, dated November 22, 
1993, which is not incorporated by reference in this AD.
    (2) Airbus Service Bulletin A300-57-6017, Revision 01, including 
Appendix 1, dated July 25, 1994, which was incorporated by reference 
in AD 95-20-02, Amendment 39-9380 (60 FR 52618, October 10, 1995).
    (3) Airbus Service Bulletin A300-57-6017, Revision 02, dated 
January 14, 1997, including Appendix 1, dated July 25, 1994, which 
is not incorporated by reference in this AD.
    (4) Airbus Service Bulletin A300-57-6017, Revision 03, dated 
November 19, 1997, including Appendix 1, which was incorporated by 
reference in AD 99-16-01, Amendment 39-11236 (64 FR 40743, July 28, 
1999).

(l) 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.
    (i) 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.
    (ii) AMOCs approved previously for AD 99-16-01, Amendment 39-
11236 (64 FR 40743, July 28, 1999), are approved as AMOCs for the 
corresponding provisions of 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.

(m) Related Information

    (1) Refer to Mandatory Continuing Airworthiness Information 
(MCAI) EASA Airworthiness Directive 2013-0180, dated August 9, 2013, 
for related information. This MCAI may be found in the AD docket on 
the Internet at http://www.regulations.gov searching for and 
locating Docket No. FAA-2015-4813.
    (2) For service information identified in this AD, contact 
Airbus SAS, Airworthiness Office--EAW, 1 Rond Point Maurice 
Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; 
fax +33 5 61 93 44 51; email 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 November 4, 2015.
Dionne Palermo,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2015-28892 Filed 11-16-15; 8:45 am]
 BILLING CODE 4910-13-P