[Federal Register Volume 79, Number 234 (Friday, December 5, 2014)]
[Rules and Regulations]
[Pages 72127-72132]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2014-28477]



[[Page 72127]]

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

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2013-1066; Directorate Identifier 2013-NM-021-AD; 
Amendment 39-18029; AD 2014-23-13]
RIN 2120-AA64


Airworthiness Directives; Airbus Airplanes

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

ACTION: Final rule.

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

SUMMARY: We are superseding Airworthiness Directive (AD) 2000-12-12, 
for certain Airbus Model A300, A300-600, and A310 series airplanes. AD 
2000-12-12 required inspecting to detect cracks in the lower spar axis 
of the nacelle pylon between ribs 9 and 10, and repair if necessary. AD 
2000-12-12 also provided for optional modification of the pylon, which 
terminated the inspections for Model A300 series airplanes. This new AD 
reduces the initial and repetitive inspection compliance times. This AD 
was prompted by reports of cracking of the lower pylon spar after 
accomplishing the existing modification. We are issuing this AD to 
detect and correct fatigue cracking, which could result in reduced 
structural integrity of the lower spar of the nacelle pylon.

DATES: This AD becomes effective January 9, 2015.
    The Director of the Federal Register approved the incorporation by 
reference of certain publications listed in this AD as of January 9, 
2015.
    The Director of the Federal Register approved the incorporation by 
reference of a certain other publication listed in this AD as of July 
28, 2000 (65 FR 39072, June 23, 2000).
    The Director of the Federal Register approved the incorporation by 
reference of certain other publications listed in this AD as of June 
12, 1995 (60 FR 25604, May 12, 1995).

ADDRESSES: You may examine the AD docket on the Internet at http://www.regulations.gov/#!docketDetail;D=FAA-2013-1066; 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 AD, contact Airbus SAS, 
Airworthiness Office--EAW, 1 Rond Point Maurice Bellonte, 31707 Blagnac 
Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61 93 44 51; 
email [email protected]; Internet http://www.airbus.com. 
You may view this referenced service information at the FAA, Transport 
Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For information 
on the availability of this material at the FAA, call 425-227-1221.

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 2000-12-12, Amendment 39-11790 (65 FR 39072, 
June 23, 2000). AD 2000-12-12 applied to certain Airbus Model A300, 
A300-600, and A310 series airplanes. The NPRM published in the Federal 
Register on December 30, 2013 (78 FR 79333).
    The European Aviation Safety Agency (EASA), which is the Technical 
Agent for the Member States of the European Community, has issued EASA 
Airworthiness Directive 2013-0016, dated September 17, 2013 (referred 
to after this as the Mandatory Continuing Airworthiness Information, or 
``the MCAI''), to correct an unsafe condition for certain Airbus Model 
A300, A300-600, and A310 series airplanes. The MCAI states:

    Cracks were found between ribs 9 and 10 in the lower pylon spar 
of A310 aeroplanes equipped with Pratt & Whitney (PW) engines.
    For A310, A300 and A300-600 aeroplanes and, in order to prevent 
crack initiation, the implementation of a first inspection programme 
of this area was required by DGAC [Direction G[eacute]n[eacute]rale 
de l'Aviation Civile] France AD 1992-049-130(B) [which corresponds 
to certain actions in FAA AD 2000-12-12, Amendment 39-11790 (65 FR 
39072, June 23, 2000)], currently at Revision 4.
    General Electric (GE) and PW pylons on A300 aeroplanes are also 
affected, due to similar design.
    After that [DGAC] AD was issued, prompted by new findings, a 
specific inspection programme for A310 aeroplanes was introduced and 
required by DGAC France AD 1999-237-285(B) [which corresponds to 
certain actions in FAA AD 2000-12-12, Amendment 39-11790 (65 FR 
39072, June 23, 2000)], which was subsequently superseded by EASA AD 
2008-0008 [http://ad.easa.europa.eu/blob/easa_ad_2008_0008_superseded.pdf/AD_2008-0008_1], which introduced 
new thresholds and intervals in the frame of the A310 extended 
service goal exercise.
    Some cracks, which were discovered after the implementation of 
the preventive modification, prompted Airbus to perform a new 
Fatigue and Damage Tolerance analysis with a refined model of the 
area with and without repair or preventive reinforcement before 
crack appearance. Based on the results of this analysis, Airbus 
revised the related Service Bulletins to introduce more restrictive 
thresholds and intervals for curative and preventive repair 
configuration.
    EASA issued AD 2013-0014 [http://ad.easa.europa.eu/blob/easa_ad_2013_0214.pdf/AD_2013-0014_1], which superseded DGAC France 
AD 1992-049-130(B) and EASA AD 2008-0008, to mandate a new 
inspection programme [including related investigative and corrective 
actions].
    After EASA AD 2013-0014 was issued, further analysis allowed to 
identify one A300 aeroplane model and one retrofitted A300 MSN 
[manufacturer serial number] missing in the applicability chapter.
    For the reason described above, this [EASA] AD retains the 
requirements of EASA AD 2013-0014, which is superseded, and 
clarifies the Applicability section and adds one A300 model and one 
A300 MSN.

    The unsafe condition is fatigue cracking, which could result in 
reduced structural integrity of the lower spar of the nacelle pylon. 
Related investigative actions include additional eddy current and 
liquid penetrant inspections for cracking. Corrective actions include 
repairing cracking. For certain cracking lengths, repairs are described 
as reinforcing the lower spar with a doubler. You may examine the MCAI 
in the AD docket on the Internet at http://www.regulations.gov/#!documentDetail;D=FAA-2013-1066-0002.

Comments

    We gave the public the opportunity to participate in developing 
this AD. The following presents the comments received on the NPRM (78 
FR 79333, December 30, 2013) and the FAA's response to each comment.

``Contacting the Manufacturer'' Paragraph in This AD

    United Parcel Service (UPS) requested that we revise the NPRM (78 
FR 79333, December 30, 2013) to remove the requirement to include the 
AD reference in repair approvals. UPS noted its concerns that the 
proposal would require development of a unique Airbus process for U.S. 
operators; that it could have significant financial and administrative 
impacts to existing customer support agreements and different AD 
records requirements within an operator's fleet; that it will increase 
requests for approval of alternative methods of compliance

[[Page 72128]]

(AMOC) and result in delayed return to service; and that it creates a 
new requirement that did not exist when the superseded AD was written.
    We concur with the commenter's request to remove from this AD the 
requirement that repair approvals must specifically refer to this AD.
    Since late 2006, we have included a standard paragraph titled 
``Airworthy Product'' in all MCAI ADs in which the FAA develops an AD 
based on a foreign authority's AD. The MCAI or referenced service 
information in an FAA AD often directs the owner/operator to contact 
the manufacturer for corrective actions, such as a repair. Briefly, the 
Airworthy Product paragraph allowed owners/operators to use corrective 
actions provided by the manufacturer if those actions were FAA-
approved. In addition, the paragraph stated that any actions approved 
by the State of Design Authority (or its delegated agent) are 
considered to be FAA-approved.
    In the NPRM (78 FR 79333, December 30, 2013), we proposed to 
prevent the use of repairs that were not specifically developed to 
correct the unsafe condition, by requiring that the repair approval 
provided by the State of Design Authority or its delegated agent 
specifically refer to this FAA AD. This change was intended to clarify 
the method of compliance and to provide operators with better 
visibility of repairs that are specifically developed and approved to 
correct the unsafe condition. In addition, we proposed to change the 
phrase ``its delegated agent'' to include a design approval holder 
(DAH) with State of Design Authority design organization approval 
(DOA), as applicable, to refer to a DAH authorized to approve required 
repairs for the proposed AD.
    UPS specifically stated the following in its comments to the NPRM 
(78 FR 79333, December 30, 2013): ``The proposed wording, being 
specific to repairs, eliminates the interpretation that Airbus messages 
are acceptable for approving minor deviations (corrective actions) 
needed during accomplishment of an AD mandated Airbus service 
bulletin.''
    This comment has made the FAA aware that some operators have 
misunderstood or misinterpreted the Airworthy Product paragraph to 
allow the owner/operator to use messages provided by the manufacturer 
as approval of deviations during the accomplishment of an AD-mandated 
action. The Airworthy Product paragraph does not approve messages or 
other information provided by the manufacturer for deviations to the 
requirements of the AD-mandated actions. The Airworthy Product 
paragraph only addresses the requirement to contact the manufacturer 
for corrective actions for the identified unsafe condition and does not 
cover deviations from other AD requirements. However, deviations to AD-
required actions are addressed in 14 CFR 39.17, and anyone may request 
the approval for an alternative method of compliance to the AD-required 
actions using the procedures found in 14 CFR 39.19.
    To address this misunderstanding and misinterpretation of the 
Airworthy Product paragraph, we have changed that paragraph and 
retitled it ``Contacting the Manufacturer.'' This paragraph now 
clarifies that for any requirement in this AD to obtain corrective 
actions from a manufacturer, the actions must be accomplished using a 
method approved by the FAA, EASA, or Airbus's EASA DOA.
    The Contacting the Manufacturer paragraph also clarifies that, if 
approved by the DOA, the approval must include the DOA-authorized 
signature. The DOA signature indicates that the data and information 
contained in the document are EASA-approved, which is also FAA-
approved. Messages and other information provided by the manufacturer 
that do not contain the DOA-authorized signature approval are not EASA-
approved, unless EASA directly approves the manufacturer's message or 
other information.
    This clarification does not remove flexibility afforded previously 
by the Airworthy Product paragraph. Consistent with long-standing FAA 
policy, such flexibility was never intended for required actions. This 
is also consistent with the recommendation of the Airworthiness 
Directive Implementation Aviation Rulemaking Committee to increase 
flexibility in complying with ADs by identifying those actions in 
manufacturers' service instructions that are ``Required for 
Compliance'' with ADs. We continue to work with manufacturers to 
implement this recommendation. But once we determine that an action is 
required, any deviation from the requirement must be approved as an 
alternative method of compliance.
    Commenters to an NPRM having Directorate Identifier 2012-NM-101-AD 
(78 FR 78285, December 26, 2013) pointed out that in many cases the 
foreign manufacturer's service bulletin and the foreign authority's 
MCAI may have been issued some time before the FAA AD. Therefore, the 
DOA may have provided U.S. operators with an approved repair, developed 
with full awareness of the unsafe condition, before the FAA AD is 
issued. Under these circumstances, to comply with the FAA AD, the 
operator would be required to go back to the manufacturer's DOA and 
obtain a new approval document, adding time and expense to the 
compliance process with no safety benefit.
    Based on these comments, we removed from this AD the requirement 
that the DAH-provided repair specifically refer to this AD. Before 
adopting such a requirement, the FAA will coordinate with affected DAHs 
and verify they are prepared to implement means to ensure that their 
repair approvals consider the unsafe condition addressed in the AD. Any 
such requirements will be adopted through the normal AD rulemaking 
process, including notice-and-comment procedures, when appropriate.
    We also have decided to revise the language in paragraphs (g)(3), 
(g)(4), (h)(3), (h)(4), (i)(3), and (i)(4) of this AD to retain 
references to repair approvals done by the DGAC (or its delegated 
agent) from AD 2000-12-12, Amendment 39-11790 (65 FR 39072, June 23, 
2000), as well as including references to EASA and the specific 
delegation approval granted by EASA for the DAH. Further, we revised 
paragraphs (n)(2) and (n)(3) of this AD to remove references to the 
``delegated agent'' and the ``DAH with State of Design Authority design 
organization approval'' and instead provided the specific delegation 
approval granted by the State of Design Authority for the DAH.

Conclusion

    We reviewed the relevant 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 minor changes:
     Are consistent with the intent that was proposed in the 
NPRM (78 FR 79333, December 30, 2013) for correcting the unsafe 
condition; and
     Do not add any additional burden upon the public than was 
already proposed in the NPRM (78 FR 79333, December 30, 2013).
    We also determined that these changes will not increase the 
economic burden on any operator or increase the scope of this AD.

Costs of Compliance

    We estimate that this AD affects 91 airplanes of U.S. registry.
    The actions required by AD 2000-12-12, Amendment 39-11790 (65 FR 
39072, June 23, 2000), and retained in

[[Page 72129]]

this AD take about 4 work-hours per product, at an average labor rate 
of $85 per work-hour. Based on these figures, the estimated cost of the 
actions required by AD 2000-12-12 is $340 per product.
    We also estimate that it would take about 12 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 $92,820, or $1,020 per product.
    In addition, we estimate that any necessary follow-on actions would 
take about 60 work-hours and require parts costing $1,680, for a cost 
of $6,780 per product. We have no way of determining the number of 
aircraft that might need these actions.

Authority for This Rulemaking

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

Regulatory Findings

    We determined that this 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-2013-1066; 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) 
2000-12-12, Amendment 39-11790 (65 FR 39072, June 23, 2000), and adding 
the following new AD:

2014-23-13 Airbus: Amendment 39-18029. Docket No. FAA-2013-1066; 
Directorate Identifier 2013-NM-021-AD.

(a) Effective Date

    This AD becomes effective January 9, 2015.

(b) Affected ADs

    This AD replaces AD 2000-12-12, Amendment 39-11790 (65 FR 39072, 
June 23, 2000).

(c) Applicability

    This AD applies to the Airbus airplanes identified in paragraphs 
(c)(1) through (c)(4) of this AD, certificated in any category.
    (1) Airbus Model A300 B2-203, B2K-3C, B4-103, B4-203, and B4-2C 
airplanes on which Airbus Modification 2434 has been embodied in 
production.
    (2) Airbus Model A300 airplane having manufacturer serial number 
125, on the left hand side pylon only.
    (3) Airbus Model A300 B4-620, B4-622R, and B4-622 airplanes, 
except for airplanes on which Airbus Modification 10149 has been 
embodied in production.
    (4) Airbus Model A310-221, -222, -322, -324, and -325 airplanes, 
except for airplanes on which Airbus Modification 10149 has been 
embodied in production.

(d) Subject

    Air Transport Association (ATA) of America Code 54, Nacelles/
pylons.

(e) Reason

    This AD was prompted by reports of cracking of the lower pylon 
spar after accomplishing an existing modification. We are issuing 
this AD to detect and correct fatigue cracking, which could result 
in reduced structural integrity of the lower spar of the nacelle 
pylon.

(f) Compliance

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

(g) Retained Inspection and Corrective Action for Certain Model A300 
Series Airplanes

    This paragraph restates the requirements of paragraph (a) of AD 
2000-12-12, Amendment 39-11790 (65 FR 39072, June 23, 2000), with 
additional sources for repair approvals. For Model A300 B4-2C, B2K-
3C, B2-203, B4-103, and B4-203 series airplanes: Prior to the 
accumulation of 9,000 total landings, or within 500 landings after 
June 12, 1995 (the effective date of AD 95-10-03, Amendment 39-9220 
(60 FR 25604, May 12, 1995)), whichever occurs later, perform an 
internal eddy current inspection to detect cracks in the lower spar 
axis of the pylon between ribs 9 and 10, in accordance with Airbus 
Service Bulletin A300-54-071, dated November 12, 1991; or Revision 
1, dated October 15, 1993. Accomplishment of an inspection required 
by paragraph (k), (l), or (m) of this AD terminates the inspection 
requirements of this paragraph.
    (1) If no crack is found, repeat the inspection thereafter at 
intervals not to exceed 2,500 landings.
    (2) If any crack is found that is less than or equal to 30 
millimeters (mm): Perform subsequent inspections and repair in 
accordance with the methods and times specified in Airbus Service 
Bulletin A300-54-071, dated November 12, 1991; or Revision 1, dated 
October 15, 1993.
    (3) If any crack is found that is greater than 30 mm, but less 
than 100 mm: Before further flight, repair using a method approved 
by the Manager, International Branch, ANM-116, Transport Airplane 
Directorate, FAA; 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).
    (4) If any crack is found that is greater than or equal to 100 
mm: Before further flight, repair using a method approved by the 
Manager, International Branch, ANM-116, Transport Airplane 
Directorate, FAA; or the DGAC (or its delegated agent); or the EASA; 
or Airbus's EASA DOA.
    (5) Accomplishment of the modification specified in Airbus 
Service Bulletin A300-54-0079, dated October 15, 1993, constitutes 
terminating action for the inspections required by paragraph (g) of 
this AD.

[[Page 72130]]

(h) Retained Inspection and Corrective Action for Model A300-600 Series 
Airplanes

    This paragraph restates the requirements of paragraph (b) of AD 
2000-12-12, Amendment 39-11790 (65 FR 39072, June 23, 2000), with 
additional sources for repair approvals. For Model A300-600, B4-620, 
C4-620, B4-622R, and B4-622 series airplanes: Except as provided by 
paragraph (h)(5) of this AD, prior to the accumulation of 4,000 
total landings, or within 500 landings after June 12, 1995 (the 
effective date of AD 95-10-03, Amendment 39-9220 (60 FR 25604, May 
12, 1995)), whichever occurs later, perform an internal eddy current 
inspection to detect cracks in the lower spar axis of the pylon 
between ribs 9 and 10, in accordance with Airbus Service Bulletin 
A300-54-6011, dated November 12, 1991, as amended by Airbus Service 
Bulletin Change Notice O.A., dated July 10, 1992; or Revision 1, 
dated October 15, 1993. Accomplishment of an inspection required by 
paragraph (k), (l), or (m) of this AD terminates the inspection 
requirements of this paragraph.
    (1) If no crack is found, repeat the inspection thereafter at 
intervals not to exceed 2,500 landings.
    (2) If any crack is found that is less than or equal to 30 mm: 
Perform subsequent inspections and repair in accordance with the 
methods and times specified in Airbus Service Bulletin A300-54-6011, 
dated November 12, 1991, as amended by Airbus Service Bulletin 
Change Notice O.A., dated July 10, 1992; or Revision 1, dated 
October 15, 1993.
    (3) If any crack is found that is greater than 30 mm, but less 
than 100 mm: Before further flight, repair using a method approved 
by the Manager, International Branch, ANM-116, Transport Airplane 
Directorate, FAA; or the DGAC (or its delegated agent); or the EASA; 
or Airbus's EASA DOA.
    (4) If any crack is found that is greater than or equal to 100 
mm: Before further flight, repair using a method approved by the 
Manager, International Branch, ANM-116, Transport Airplane 
Directorate, FAA; or the DGAC (or its delegated agent); or the EASA; 
or Airbus's EASA DOA.
    (5) Accomplishment of the modification specified in Airbus 
Service Bulletin A300-54-6019, dated October 15, 1993, increases the 
threshold and repetitive interval of the inspections required by 
paragraph (h) of this AD to the threshold and interval specified in 
paragraph 2.D. of the Accomplishment Instructions of Airbus Service 
Bulletin A300-54-6011, Revision 1, dated October 15, 1993.

(i) Retained Inspection and Corrective Action for Model A310 Series 
Airplanes

    This paragraph restates the requirements of paragraph (c) of AD 
2000-12-12, Amendment 39-11790 (65 FR 39072, June 23, 2000), with 
additional sources for repair approvals. For Model A310-221, -222, -
322, -324, and -325 series airplanes: Perform an internal eddy 
current inspection to detect cracks in the lower spar axis of the 
pylon between ribs 9 and 10, in accordance with Airbus Service 
Bulletin A310-54-2016, dated November 12, 1991; or Revision 1, dated 
October 15, 1993; or Revision 02, dated June 11, 1999; at the time 
specified in paragraph (j) of this AD. Accomplishment of an 
inspection required by paragraph (k), (l), or (m) of this AD 
terminates the inspection requirements of this paragraph.
    (1) If no crack is found, repeat the inspection thereafter at 
intervals not to exceed 2,500 landings.
    (2) If any crack is found that is less than or equal to 30 mm: 
Perform subsequent inspections and repair in accordance with the 
methods and times specified in Airbus Service Bulletin A310-54-2016, 
dated November 12, 1991; or Revision 1, dated October 15, 1993; or 
Revision 02, dated June 11, 1999.
    (3) If any crack is found that is greater than 30 mm, but less 
than 100 mm: Before further flight, repair using a method approved 
by the Manager, International Branch, ANM-116, Transport Airplane 
Directorate, FAA; or the DGAC (or its delegated agent); or the EASA; 
or Airbus's EASA DOA.
    (4) If any crack is found that is greater than or equal to 100 
mm: Before further flight, repair using a method approved by the 
Manager, International Branch, ANM-116, Transport Airplane 
Directorate, FAA; or the DGAC (or its delegated agent); or the EASA; 
or Airbus's EASA DOA.
    (5) Accomplishment of the modification specified in Airbus 
Service Bulletin A310-54-2022, dated October 15, 1993; or Revision 
01, dated March 16, 1999; increases the threshold and repetitive 
interval of the inspections required by paragraph (i) of this AD to 
the threshold and interval specified in paragraph 2.D. of the 
Accomplishment Instructions of Airbus Service Bulletin A310-54-2016, 
Revision 02, dated June 11, 1999.

(j) Retained Compliance Time for Paragraph (i) of This AD

    This paragraph restates the requirements of paragraph (d) of AD 
2000-12-12, Amendment 39-11790 (65 FR 39072, June 23, 2000), with no 
changes. Perform the initial inspection required by paragraph (i) of 
this AD at the earlier of the times specified by paragraphs (j)(1) 
and (j)(2) of this AD.
    (1) Prior to the accumulation of 25,000 total landings, or 
within 500 landings after June 12, 1995 (the effective date of AD 
95-10-03, Amendment 39-9220 (60 FR 25604, May 12, 1995), whichever 
occurs later.
    (2) At the applicable time specified by paragraph (j)(2)(i), 
(j)(2)(ii), or (j)(2)(iii) of this AD.
    (i) For airplanes that have accumulated fewer than 10,000 
landings as of July 28, 2000 (the effective date of AD 2000-12-12, 
Amendment 39-11790 (65 FR 39072, June 23, 2000)): Perform the 
inspection prior to the accumulation of 3,800 total landings, or 
within 1,500 landings after July 28, 2000, whichever occurs later.
    (ii) For airplanes that have accumulated 10,000 total landings 
or more, but fewer than 20,000 total landings, as of July 28, 2000 
(the effective date of AD 2000-12-12, Amendment 39-11790 (65 FR 
39072, June 23, 2000)): Perform the inspection within 1,000 landings 
after July 28, 2000.
    (iii) For airplanes that have accumulated 20,000 total landings 
or more as of July 28, 2000 (the effective date of AD 2000-12-12, 
Amendment 39-11790 (65 FR 39072, June 23, 2000)): Perform the 
inspection within 500 landings after July 28, 2000.

(k) New Repetitive Inspections for Cracking

    (1) For airplanes identified in paragraph (k)(2) of this AD: 
Except as provided by paragraphs (n)(1) and (n)(4) of this AD, at 
the applicable compliance time specified in paragraph 1.E.(2), 
``Compliance,'' of the applicable service bulletin specified in 
paragraph (k)(1)(i), (k)(1)(ii), or (k)(1)(iii) of this AD, or 
within 100 flight cycles after the effective date of this AD, 
whichever occurs later, do an eddy current inspection or liquid 
penetrant inspection for cracking of the lower spar of the pylon 
between ribs 9 and 10; and do all applicable related investigative 
and corrective actions; in accordance with the Accomplishment 
Instructions of the applicable service bulletin specified in 
paragraph (k)(1)(i), (k)(1)(ii), or (k)(1)(iii) of this AD, except 
as required by paragraphs (n)(2) and (n)(3) of this AD. Do all 
applicable related investigative and corrective actions before 
further flight. Repeat the inspection of the lower spar of the pylon 
between ribs 9 and 10 thereafter at intervals not to exceed the 
applicable interval specified in paragraph 1.E.(2), ``Compliance,'' 
of the applicable service bulletin specified in paragraph (k)(1)(i), 
(k)(1)(ii), or (k)(1)(iii) of this AD. Accomplishment of corrective 
actions required by this paragraph terminates the repetitive 
inspections required by this paragraph. Accomplishment of an 
inspection required by this paragraph terminates the inspection 
requirements of paragraphs (g), (h), and (i) of this AD. 
Accomplishment of the optional modification specified in the 
applicable service bulletin specified in paragraph (k)(1)(i), 
(k)(1)(ii), or (k)(1)(iii) of this AD terminates the repetitive 
inspections required by this paragraph.
    (i) Airbus Service Bulletin A300-54-0071, Revision 04, dated 
April 11, 2013 (for Model A300 B2-203, B2K-3C, B4-103, B4-203, and 
B4-2C airplanes).
    (ii) Airbus Service Bulletin A310-54-2016, Revision 06, dated 
January 16, 2013 (for Model A310-221, -222, -322, -324, and -325 
airplanes).
    (iii) Airbus Service Bulletin A300-54-6011, Revision 03, dated 
June 23, 2011 (for Model A300 B4-620, B4-622R, and B4-622 
airplanes).
    (2) For airplanes that have not been modified or repaired with a 
doubler as specified in the applicable service bulletin specified in 
paragraph (k)(2)(i), (k)(2)(ii), or (k)(2)(iii) of this AD, do the 
inspections required by paragraph (k)(1) of this AD.
    (i) Airbus Service Bulletin A300-54-0079 (for Model A300 B2-203, 
B2K-3C, B4-103, B4-203, and B4-2C airplanes).
    (ii) Airbus Service Bulletin A310-54-2022 (for Model A310-221, -
222, -322, -324, and -325 airplanes).
    (iii) Airbus Service Bulletin A300-54-6019 (for Model A300 B4-
620, B4-622R, and B4-622 airplanes).

(l) New Repetitive Inspections for Post-Repair Airplanes

    For airplanes that have been repaired with a doubler as 
specified in the applicable Airbus service bulletin specified in

[[Page 72131]]

paragraph (k)(1)(i), (k)(1)(ii), or (k)(1)(iii) of this AD: At the 
applicable time specified in paragraph 1.E.(2), ``Compliance,'' in 
the applicable service bulletin specified in paragraph (k)(1)(i), 
(k)(1)(ii), or (k)(1)(iii) of this AD, except as specified in 
paragraphs (n)(1) and (n)(4) of this AD, do an eddy current 
inspection or liquid penetrant inspection for cracking of the lower 
spar of the pylon between ribs 9 and 10, and do all applicable 
corrective actions, in accordance with the Accomplishment 
Instructions of the applicable service bulletin specified in 
paragraph (k)(1)(i), (k)(1)(ii), or (k)(1)(iii) of this AD, except 
as required by paragraph (n)(2) of this AD. Do all applicable 
corrective actions before further flight. Repeat the inspection of 
the lower spar of the pylon between ribs 9 and 10 thereafter at 
intervals not to exceed the applicable interval specified in 
paragraph 1.E.(2), ``Compliance,'' of the applicable service 
bulletin specified in paragraph (k)(1)(i), (k)(1)(ii), or 
(k)(1)(iii) of this AD. Accomplishment of an inspection required by 
this paragraph terminates the inspection requirements of paragraphs 
(g), (h), and (i) of this AD.

(m) New Repetitive Inspections for Post-Modification Airplanes

    For airplanes that have been modified as specified in the 
applicable Airbus service bulletin specified in paragraph (k)(1)(i), 
(k)(1)(ii), or (k)(1)(iii) of this AD: At the applicable time 
specified in paragraph 1.E.(2), ``Compliance,'' in the applicable 
service bulletin specified in paragraph (k)(1)(i), (k)(1)(ii), or 
(k)(1)(iii) of this AD, except as specified in paragraph (n)(1) and 
(n)(4) of this AD: Do an eddy current inspection or liquid penetrant 
inspection for cracking of the lower spar of the pylon between ribs 
9 and 10; and do all applicable corrective actions; in accordance 
with the Accomplishment Instructions of the applicable service 
bulletin specified in paragraph (k)(1)(i), (k)(1)(ii), or 
(k)(1)(iii) of this AD, except as required by paragraph (n)(2) of 
this AD. Do all applicable corrective actions before further flight. 
Repeat the inspection of the lower spar of the pylon between ribs 9 
and 10 thereafter at intervals not to exceed the applicable interval 
specified in paragraph 1.E.(2), ``Compliance,'' of the applicable 
service bulletin specified in paragraph (k)(1)(i), (k)(1)(ii), or 
(k)(1)(iii) of this AD. Accomplishment of an inspection required by 
this paragraph terminates the inspection requirements of paragraphs 
(g), (h), and (i) of this AD.

(n) New Service Bulletin Exceptions

    (1) Where the service bulletins specified in paragraphs 
(k)(1)(i), (k)(1)(ii), and (k)(1)(iii) of this AD specify a 
compliance time ``from the publication date,'' this AD requires 
compliance within the specified compliance time after the effective 
date of this AD.
    (2) If any crack is detected during any inspection required by 
paragraph (k), (l), or (m) of this AD, and the service bulletin 
specified in paragraph (k)(1)(i), (k)(1)(ii), or (k)(1)(iii) of this 
AD specifies to contact the manufacturer: Before further flight, 
repair 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.
    (3) Where the service bulletins specified in paragraphs 
(k)(1)(i), (k)(1)(ii), and (k)(1)(iii) of this AD specify to contact 
the manufacturer for inspection requirements: Inspect 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.
    (4) Where the ``Threshold'' column in the tables in paragraph 
1.E., ``Compliance,'' of the service bulletins specified in 
paragraphs (k)(1)(i), (k)(1)(ii), and (k)(1)(iii) of this AD 
specifies a compliance time in flight cycles/flight hours, this AD 
requires compliance within the corresponding time in total flight 
cycles/total flight hours; except that for tables for post-repair 
and post-modification airplanes, this AD requires compliance within 
the corresponding time after accomplishing the repair or 
modification.

(o) Credit for Previous Actions

    This paragraph provides credit for actions required by paragraph 
(k) of this AD, if those actions were performed before the effective 
date of this AD using the applicable service bulletin specified in 
paragraphs (o)(1) through (o)(4) of this AD.
    (1) Airbus Service Bulletin A300-54-071, Revision 02, dated 
August 25, 2000 (for Model A300 B2-203, B2K-3C, B4-103, B4-203, and 
B4-2C airplanes), which is not incorporated by reference in this AD.
    (2) Airbus Service Bulletin A300-54-0071, Revision 03, dated 
October 5, 2012 (for Model A300 B2-203, B2K-3C, B4-103, B4-203, and 
B4-2C airplanes), which is not incorporated by reference in this AD.
    (3) Airbus Service Bulletin A310-54-2016, Revision 04, dated 
November 16, 2007; or Airbus Service Bulletin A310-54-2016, Revision 
05, dated October 5, 2012 (for Model A310-221, -222, -322, -324, and 
-325 airplanes); which are not incorporated by reference in this AD.
    (4) Airbus Service Bulletin A300-54-6011, Revision 02, dated 
August 25, 2000 (for Model A300 B4-620, B4-622R, and B4-622 
airplanes), which is not incorporated by reference in this AD.

(p) Other FAA AD Provisions

    The following provisions also apply to this AD:
    (1) Alternative Methods of Compliance (AMOCs): The Manager, 
International Branch, FAA, has the authority to approve AMOCs for 
this AD, if requested using the procedures found in 14 CFR 39.19. In 
accordance with 14 CFR 39.19, send your request to your principal 
inspector or local Flight Standards District Office, as appropriate. 
If sending information directly to the International Branch, send it 
to ATTN: Dan Rodina, Aerospace Engineer, International Branch, ANM-
116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., 
Renton, WA 98057-3356; telephone 425-227-2125; fax 425-227-1149. 
Information may be emailed to: [email protected].
    (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 2000-12-12, Amendment 39-
11790 (65 FR 39072, June 23, 2000), 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 the 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) European Aviation Safety Agency Airworthiness Directive 2013-
0216, dated September 17, 2013, for related information. You may 
examine the MCAI in the AD docket on the Internet at http://www.regulations.gov/#!documentDetail;D=FAA-2013-1066-0002.
    (2) Service information identified in this AD that is not 
incorporated by reference in this AD is available at the addresses 
specified in paragraphs (r)(6) and (r)(7) 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 
January 9, 2015.
    (i) Airbus Service Bulletin A300-54-0071, Revision 04, dated 
April 11, 2013.
    (ii) Airbus Service Bulletin A310-54-2016, Revision 06, dated 
January 16, 2013.
    (iii) Airbus Service Bulletin A300-54-6011, Revision 03, dated 
June 23, 2011.
    (4) The following service information was approved for IBR on 
July 28, 2000 (65 FR 39072, June 23, 2000).
    (i) Airbus Service Bulletin A310-54-2016, Revision 02, dated 
June 11, 1999.
    (ii) Reserved.
    (5) The following service information was approved for IBR on 
June 12, 1995 (60 FR 25604, May 12, 1995).
    (i) Airbus Service Bulletin A300-54-071, dated November 12, 
1991.
    (ii) Airbus Service Bulletin A300-54-071, Revision 1, dated 
October 15, 1993.
    (iii) Airbus Service Bulletin A300-54-6011, dated November 12, 
1991.
    (iv) Airbus Service Bulletin Change Notice O.A., A300-54-6011, 
dated July 10, 1992.
    (v) Airbus Service Bulletin A300-54-6011, Revision 1, dated 
October 15, 1993. (Pages 1 through 10 and 12 through 19 of this 
document are identified as Revision 1, dated October 15, 1993; page 
11 is dated November 12, 1991.)

[[Page 72132]]

    (vi) Airbus Service Bulletin A300-54-6019, dated October 15, 
1993.
    (6) For service information identified in this AD, contact 
Airbus SAS, Airworthiness Office--EAW, 1 Rond Point Maurice 
Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; 
fax +33 5 61 93 44 51; email [email protected]; 
Internet http://www.airbus.com.
    (7) 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.
    (8) 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 November 6, 2014.
Jeffrey E. Duven,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2014-28477 Filed 12-4-14; 8:45 am]
BILLING CODE 4910-13-P