```

[Federal Register Volume 77, Number 89 (Tuesday, May 8, 2012)]
[Rules and Regulations]
[Pages 26937-26943]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2012-9189]

=======================================================================
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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2011-1066; Directorate Identifier 2011-NM-050-AD; 
Amendment 39-16917; AD 2012-01-05]
RIN 2120-AA64

Airworthiness Directives; Airbus Airplanes

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

ACTION: Final rule.

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

SUMMARY: We are superseding an existing airworthiness directive (AD) 
for certain Airbus Model A300 B2-1C, B2K-3C, B2-203, B4-2C, B4-103, and 
B4-203 airplanes; and Model A300 B4-601, B4-603, B4-620, B4-622, B4-
605R, B4-622R, and F4-605R airplanes. That AD currently requires 
repetitive inspections for cracking in Gear Rib 5 of the main landing 
gear (MLG) attachment fittings at the lower flange, and repair if 
necessary; and provides an optional spot-facing modification around 
certain fastener holes, which would terminate certain repetitive 
inspections. This new AD mandates the optional spot-facing 
modification. This AD was prompted by new cases of cracks discovered 
during scheduled maintenance checks. We are issuing this AD to prevent 
cracking of the Gear Rib 5 right-hand and left-hand attachment fitting 
at the lower flanges of the MLG, which could result in failed bolts 
penetrating through the rear spar and into a fuel tank, consequent fuel 
loss, and reduced structural integrity of the airplane.

DATES: This AD becomes effective June 12, 2012.
    The Director of the Federal Register approved the incorporation by 
reference of certain publications listed in this AD as of June 12, 
2012.
    The Director of the Federal Register approved the incorporation by 
reference of certain other publications listed in this AD as of January 
5, 2011 (75 FR 74610, December 1, 2010).
    The Director of the Federal Register approved the incorporation by 
reference of certain other publications listed in this AD as of July 
18, 2006 (71 FR 33994, June 13, 2006).
    The Director of the Federal Register approved the incorporation by 
reference of certain other publications listed in this AD as of April 
12, 2000 (65 FR 12077, March 8, 2000).
    The Director of the Federal Register approved the incorporation by 
reference of certain other publications listed in this AD as of October 
20, 1999 (64 FR 49966, September 15, 1999).

ADDRESSES: You may examine the AD docket on the Internet at http://www.regulations.gov or in person at the U.S. Department of 
Transportation, Docket Operations, M-30, West Building Ground Floor, 
Room W12-140, 1200 New Jersey Avenue SE., Washington, DC.

FOR FURTHER INFORMATION CONTACT: Dan Rodina, Aerospace Engineer, 
International Branch, ANM-116, Transport Airplane Directorate, FAA, 
1601 Lind Avenue SW., Renton, Washington 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 include an AD that would apply to the specified products. 
That NPRM was published in the Federal Register on October 11, 2011 (76 
FR 62673), and proposed to supersede AD 2010-23-26, Amendment 39-16516 
(75 FR 74610, December 1, 2010). That NPRM proposed to correct an 
unsafe condition for the specified products. The MCAI states:

    Following the occurrence of cracks on the MLG [main landing 
gear] Rib 5 RH [right-hand] and LH [left-hand] attachment fitting 
lower flanges, DGAC [Direction G[eacute]n[eacute]rale de l'Aviation 
Civile] France AD 2003-318(B) was issued to require repetitive 
inspections and, as terminating action, the embodiment of Airbus 
Service Bulletins (SB) A300-57-0235 and A300-57-6088 * * *.
    Subsequently, new cases of cracks were discovered during 
scheduled maintenance checks by operators of A300B4 and A300-600 
type aeroplanes on which the terminating action SB's were embodied. 
This condition, if not corrected, could affect the structural 
integrity of those aeroplanes.
    To address and correct this condition, Airbus developed an 
inspection programme for aeroplanes modified in accordance with SB 
A300-57-0235 or A300-57-6088. This inspection programme was required 
to be implemented by DGAC France AD F-2005-113, original issue and 
later revision 1 [parallel to part of FAA AD 2006-12-13, Amendment 
39-14639 (71 FR 33994, June 13, 2006)].
    A new EASA [European Aviation Safety Agency] AD 2008-0111, 
superseding DGAC France AD F-2005-113R1, was issued to reduce the 
applicability. For aeroplanes already compliant with DGAC France AD 
F-2005-113R1, no further action was required.
    Since EASA AD 2008-0111 issuance, Airbus reviewed the inspection 
programmes of SB A300-57A0246 and SB A300-57A6101 to introduce 
repetitive inspections including a new inspection technique for 
holes 47 and 54 and to reduce inspections threshold and intervals 
from 700 Flight Cycles (FC) to 400 FC until a revised terminating 
action is made available.
    For the reasons stated above, EASA AD 2009-0081 superseded EASA 
AD 2008-0111 and required operators to comply with the new 
inspection programme introduced in Revisions 3 of Airbus SB A300-
57A0246 and Airbus SB A300-57A6101.
    EASA AD 2009-0081 R1 [which corresponds to FAA AD 2010-23-26, 
Amendment 39-16516 (75 FR 74610, December 1, 2010)] has been 
published to introduce an optional terminating action which 
consisted of spot-facing the sensitive holes of the MLG Rib 5 (LH 
and RH) bottom flanges.
    Later discussions with Airbus have demonstrated the necessity to 
require the spot-facing modification as a final solution (no longer 
optional). This new [EASA] AD retains the inspection requirements of 
EASA AD 2009-0081 R1, which is superseded, and requires the spot-
facing of sensitive holes of the MLG Rib 5 (LH and RH) bottom 
flanges as terminating action.

Required actions include repairing discrepancies (e.g., cracking or a 
second oversize or greater fastener hole). You may obtain further 
information by examining the MCAI in the AD docket.

Comments

    We gave the public the opportunity to participate in developing 
this AD. We considered the comment received. The

[[Page 26938]]

commenter supports the NPRM (76 FR 62673, October 11, 2011).

Explanation of Changes Made to This AD

    We have made the following changes to this AD. These changes have 
not changed the intent of any provisions specified in this AD.
     Revised certain headers throughout this AD.
     Redesignated Notes 1, 2, and 3 of the NPRM (76 FR 62673, 
October 11, 2011) as paragraphs (g)(3), (q)(1), and (q)(2) of this AD, 
respectively.
     Redesignated paragraph (n) of the NPRM (76 FR 62673, 
October 11, 2011) as paragraph (q)(3) of this AD, and redesignated 
subsequent paragraphs accordingly.
     We have revised paragraphs (g), (i), (o)(1), (o)(3), 
(o)(4), and (o)(5) of this AD to clarify the specific actions for which 
the specified service information is required.
     We have revised the headings of Tables 1, 2, 3, 4, 5, and 
6 of this AD to clarify the purpose of the content in those tables.
     We have revised the wording in paragraphs (q)(1), (q)(2), 
(q)(3), and (q)(4) of this AD (Notes 2 and 3 and paragraphs (n) and (r) 
of the NPRM (76 FR 62673, October 11, 2011), respectively); this change 
has not changed the intent of these paragraphs.

Conclusion

    We reviewed the available data, including the comment received, and 
determined that air safety and the public interest require adopting the 
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 (76 FR 62673, October 11, 2011) for correcting the unsafe 
condition; and
     Do not add any additional burden upon the public than was 
already proposed in the NPRM (76 FR 62673, October 11, 2011).

Costs of Compliance

    We estimate that this AD will affect about 155 products of U.S. 
registry.
    The actions that are required by AD 2010-23-26, Amendment 39-16516 
(75 FR 74610, December 1, 2010), and retained in this AD take about 79 
work-hours per product, at an average labor rate of $85 per work hour. 
Required parts cost about $10,270 per product. Based on these figures, 
the estimated cost of the currently required actions is $16,985 per 
product.
    We estimate that it will take about 100 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 the AD on U.S. operators to be $1,317,500, or $8,500 per product.

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 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); and
    3. 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 AD and placed it in the AD docket.

Examining the AD Docket

    You may examine the AD docket on the Internet at http://www.regulations.gov; or in person at the Docket Operations office 
between 9 a.m. and 5 p.m., Monday through Friday, except Federal 
holidays. The AD docket contains the NPRM (76 FR 62673, October 11, 
2011), 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.

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 Amendment 39-16516 (75 FR 
74610, December 1, 2010) and adding the following new AD:

2012-01-05 Airbus: Amendment 39-16917. Docket No. FAA-2011-1066; 
Directorate Identifier 2011-NM-050-AD.

(a) Effective Date

    This airworthiness directive (AD) becomes effective June 12, 
2012.

(b) Affected ADs

    This AD supersedes AD 2010-23-26, Amendment 39-16516 (75 FR 
74610, December 1, 2010).

(c) Applicability

    This AD applies to the airplanes, certificated in any category, 
identified in paragraphs (c)(1) and (c)(2) of this AD; except 
airplanes on which Airbus Modification 11912 or 11932 has been 
installed.
    (1) Airbus Model A300 B2-1C, B2K-3C, B2-203, B4-2C, B4-103, and 
B4-203 airplanes.
    (2) Airbus Model A300 B4-601, B4-603, B4-620, B4-622, B4-605R, 
B4-622R, and F4-605R airplanes.

(d) Subject

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

(e) Reason

    This AD was prompted by new cases of cracks discovered during 
scheduled maintenance checks. We are issuing this AD to prevent 
cracking of the Gear Rib 5 right-hand and left-hand attachment 
fitting at the lower flanges of the main landing gear (MLG), which 
could result in failed bolts penetrating through the rear spar and 
into a fuel tank, consequent fuel loss, and reduced structural 
integrity of the airplane.

(f) Compliance

    You are responsible for having the actions required by this AD 
performed within the

[[Page 26939]]

compliance times specified, unless the actions have already been 
done.

(g) Retained Repetitive Inspections

    This paragraph restates the requirements of paragraph (g) of AD 
2010-23-26, Amendment 39-16516 (75 FR 74610, December 1, 2010). 
Perform a detailed inspection and a high-frequency eddy current 
(HFEC) inspection to detect cracks in Gear Rib 5 of the MLG 
attachment fittings at the lower flange, in accordance with the 
Accomplishment Instructions of any applicable service bulletin 
listed in table 1 and table 2 of this AD, at the time specified in 
paragraph (g)(1) or (g)(2) of this AD. After April 12, 2000 (the 
effective date of AD 2000-05-07, Amendment 39-11616 (65 FR 12077, 
March 8, 2000)), the service bulletins listed in table 2 of this AD 
must be used to accomplish the actions required by this paragraph. 
Repeat the inspections thereafter at intervals not to exceed 1,500 
flight cycles, until the actions specified in paragraph (i), (j), or 
(l) of this AD are accomplished.

                     Table 1--Revision 01 of Service Bulletins for Paragraph (g) of This AD
----------------------------------------------------------------------------------------------------------------
                                        Airbus Service Bulletin--
                Model--                                              Revision--               Dated--
----------------------------------------------------------------------------------------------------------------
A300 B4[dash]601, B4[dash]603,          A300[dash]57[dash]6087...              01  March 11, 1998.
 B4[dash]620, B4[dash]622,
 B4[dash]605R, B4[dash]622R and
 F4[dash]605R airplanes.
A300 B2[dash]1C, B2K-3C, B2[dash]203,   A300-57-0234.............              01  March 11, 1998.
 B4[dash]2C, B4[dash]103, and
 B4[dash]203 airplanes.
----------------------------------------------------------------------------------------------------------------

                   Table 2--Other Revisions of Service Bulletins for Paragraph (g) of This AD
----------------------------------------------------------------------------------------------------------------
                                        Airbus Service
              Model--                     Bulletin--             Revision--                   Dated--
----------------------------------------------------------------------------------------------------------------
A300 B4[dash]601, B4[dash]603,      A300[dash]57A6087....  02, including          June 24, 1999.
 B4[dash]620, B4[dash]622,                                  Appendix 01.
 B4[dash]605R, B4[dash]622R, and
 F4[dash]605R airplanes.
                                                           03, including          May 19, 2000.
                                                            Appendix 01.
                                                           04, including          February 19, 2002.
                                                            Appendix 01.
                                                           05, including          March 10, 2008.
                                                            Appendix 01.
----------------------------------------------------------------------------------------------------------------
A300 B2[dash]1C, B2K-3C,            A300[dash]57A0234....  02                     June 24, 1999.
 B2[dash]203, B4[dash]2C,
 B4[dash]103, and B4[dash]203
 airplanes.
                                                           03, including          September 2, 1999.
                                                            Appendix 01.
                                                           04, including          May 19, 2000.
                                                            Appendix 01.
                                                           05, including          February 19, 2002.
                                                            Appendix 01.
----------------------------------------------------------------------------------------------------------------

    (1) For airplanes that have accumulated 20,000 or more total 
flight cycles as of March 9, 1998 (the effective date of AD 98-03-
06, Amendment 39-10298 (63 FR 5224, February 2, 1998)): Inspect 
within 500 flight cycles after March 9, 1998.
    (2) For airplanes that have accumulated less than 20,000 total 
flight cycles as of March 9, 1998 (the effective date of AD 98-03-
06, Amendment 39-10298 (63 FR 5224, February 2, 1998)): Inspect 
prior to the accumulation of 18,000 total flight cycles, or within 
1,500 flight cycles after March 9, 1998, whichever occurs later.
    (3) For the purposes of this AD, a detailed inspection is 
defined as: ``An intensive visual examination of a specific 
structural area, system, installation, or assembly to detect damage, 
failure, or irregularity. Available lighting is normally 
supplemented with a direct source of good lighting at intensity 
deemed appropriate by the inspector. Inspection aids such as mirror, 
magnifying lenses, etc., may be used. Surface cleaning and elaborate 
access procedures may be required.''

(h) Retained Repair for Any Crack Found During Inspections Required by 
Paragraph (g) of This AD

    This paragraph restates the requirements of paragraph (h) of AD 
2010-23-26, Amendment 39-16516 (75 FR 74610, December 1, 2010). If 
any crack is detected during any inspection required by paragraph 
(g) of this AD, prior to further flight, accomplish the requirements 
of paragraph (h)(1) or (h)(2) of this AD, as applicable.
    (1) If a crack is detected at one hole only, and the crack does 
not extend out of the spotface of the hole, repair in accordance 
with the Accomplishment Instructions of the applicable service 
bulletin in table 2 of this AD.
    (2) If a crack is detected at more than one hole, or if any 
crack at any hole extends out of the spotface of the hole, repair in 
accordance with a method approved by the Manager, International 
Branch, ANM-116, Transport Airplane Directorate, FAA, or the 
European Aviation Safety Agency (EASA) (or its delegated agent).

(i) Retained Terminating Modification for Repetitive Inspections 
Required by Paragraphs (g) and (j) of This AD

    This paragraph restates the requirements of paragraph (i) of AD 
2010-23-26, Amendment 39-16516 (75 FR 74610, December 1, 2010). 
Except as required by paragraph (l) of this AD, prior to the 
accumulation of 21,000 total flight cycles, or within 2 years after 
October 20, 1999 (the effective date of AD 99-19-26, Amendment 39-
11313 (64 FR 49966, September 15, 1999)), whichever occurs later: 
Modify Gear Rib 5 of the MLG attachment fittings at the lower flange 
in accordance with the Accomplishment Instructions of the applicable 
service bulletin in table 3 of this AD. After July 18, 2006 (the 
effective date of AD 2006-12-13, Amendment 39-14639 (71 FR 33994, 
June 13, 2006)), Airbus Service Bulletin A300-57-6088, Revision 04, 
dated December 3, 2003 (for Model A300 B4-601, B4-603, B4-620, B4-
622, B4-605R, B4-622R, and F4-605R airplanes); and Airbus Service 
Bulletin A300-57-0235, Revision 04, dated March 13, 2003, or 
Revision 05, dated December 3, 2003 (for Model A300 B2-1C, B2K-3C, 
B2-203, B4-2C, B4-103, and B4-203 airplanes); must be used to 
accomplish the actions required by this paragraph. Accomplishment of 
this modification constitutes terminating action for the repetitive 
inspection requirements of paragraphs (g) and (j) of this AD.

          Table 3--Service Bulletins for Terminating Modification Required by Paragraph (i) of This AD
----------------------------------------------------------------------------------------------------------------
                                        Airbus Service
              Model--                     Bulletin--             Revision--                   Dated--
----------------------------------------------------------------------------------------------------------------
A300 B4-601, B4-603, B4-620, B4-    A300-57-6088.........  01, including          February 1, 1999.
 622, B4-605R, B4-622R, and F4-                             Appendix 01.
 605R airplanes.
                                                           02                     September 5, 2002.

[[Page 26940]]

 
                                                           04                     December 3, 2003.
----------------------------------------------------------------------------------------------------------------
A300 B2-1C, B2K-3C, B2-203, B4-2C,  A300-57-0235.........  01, including          February 1, 1999.
 B4-103, and B4-203 airplanes.                              Appendix 01.
                                                           03                     September 5, 2002.
                                                           04                     March 13, 2003.
                                                           05                     December 3, 2003.
----------------------------------------------------------------------------------------------------------------

(j) Retained Additional Repetitive Inspections

    This paragraph restates the requirements of paragraph (j) of AD 
2010-23-26, Amendment 39-16516 (75 FR 74610, December 1, 2010). For 
airplanes on which the modification specified in paragraph (i) or 
(l) of this AD has not been done before July 18, 2006 (the effective 
date of AD 2006-12-13, Amendment 39-14639 (71 FR 33994, June 13, 
2006)), perform a detailed and an HFEC inspection to detect cracks 
of the lower flange of Gear Rib 5 of the MLG at holes 43, 47, 48, 
49, 50, 52, and 54, in accordance with the applicable service 
bulletin listed in table 4 of this AD. Perform the inspections at 
the applicable time specified in paragraph (j)(1), (j)(2), (j)(3), 
or (j)(4) of this AD. Repeat the inspections thereafter at intervals 
not to exceed 700 flight cycles until the terminating modification 
required by paragraph (l) of this AD is accomplished. Accomplishment 
of the inspections per paragraph (j) of this AD terminates the 
inspection requirements of paragraph (g) of this AD.

           Table 4--Service Bulletins for Repetitive Inspections Required by Paragraph (j) of This AD
----------------------------------------------------------------------------------------------------------------
                                        Airbus Service
              Model--                     Bulletin--             Revision--                   Dated--
----------------------------------------------------------------------------------------------------------------
A300 B4-601, B4-603, B4-620, B4-    A300-57A6087.........  04, including          February 19, 2002.
 622, B4-605R, B4-622R, and F4-                             Appendix 01.
 605R airplanes.
                                                           05, including          March 10, 2008.
                                                            Appendix 01
----------------------------------------------------------------------------------------------------------------
A300 B2-1C, B2K-3C, B2-203, B4-2C,  A300-57A0234.........  05, including          February 19, 2002.
 B4-103, and B4-203 airplanes.                              Appendix 01.
----------------------------------------------------------------------------------------------------------------

    (1) For Model A300 B2-1C, B2K-3C, B2-203, B4-2C, B4-103, and B4-
203 airplanes; and Model A300 B4-601, B4-603, B4-620, B4-622, B4-
605R, B4-622R, and F4-605R airplanes that have accumulated 18,000 or 
more total flight cycles as of July 18, 2006 (the effective date of 
AD 2006-12-13, Amendment 39-14639 (71 FR 33994, June 13, 2006)): 
Within 700 flight cycles after July 18, 2006.
    (2) For Model A300 B2-1C, B2K-3C, and B2-203 airplanes that have 
accumulated less than 18,000 total flight cycles as of July 18, 2006 
(the effective date of AD 2006-12-13, Amendment 39-14639 (71 FR 
33994, June 13, 2006)): Prior to the accumulation of 18,000 total 
flight cycles, or within 700 flight cycles after July 18, 2006, 
whichever occurs later.
    (3) For Model A300 B4-2C, B4-103, and B4-203 airplanes that have 
accumulated less than 18,000 total flight cycles as of July 18, 2006 
(the effective date of AD 2006-12-13, Amendment 39-14639 (71 FR 
33994, June 13, 2006)): Prior to the accumulation of 14,500 total 
flight cycles, or within 700 flight cycles after July 18, 2006, 
whichever occurs later.
    (4) For Model A300 B4-601, B4-603, B4-620, B4-622, B4-605R, B4-
622R, and F4-605R airplanes that have accumulated less than 18,000 
total flight cycles as of July 18, 2006 (the effective date of AD 
2006-12-13, Amendment 39-14639 (71 FR 33994, June 13, 2006)): Prior 
to the accumulation of 11,600 total flight cycles, or within 700 
flight cycles after July 18, 2006, whichever occurs later.

(k) Retained Crack Repair

    This paragraph restates the requirements of paragraph (k) of AD 
2010-23-26, Amendment 39-16516 (75 FR 74610, December 1, 2010). If 
any crack is detected during any inspection required by paragraph 
(j) of this AD, prior to further flight, accomplish the requirements 
of paragraphs (k)(1) and (k)(2) of this AD, as applicable.
    (1) If a crack is detected at only one hole, and the crack does 
not extend out of the spotface of the hole, repair in accordance 
with Airbus Service Bulletin A300-57A0234, Revision 05, including 
Appendix 01, dated February 19, 2002 (for Model A300 B2-1C, B2K-3C, 
B2-203, B4-2C, B4-103, and B4-203 airplanes); or A300-57A6087, 
Revision 04, including Appendix 01, dated February 19, 2002, or 
A300-57A6087, Revision 05, including Appendix 01, dated March 10, 
2008 (for Model A300 B4-601, B4-603, B4-620, B4-622, B4-605R, B4-
622R, and F4-605R airplanes).
    (2) If a crack is detected at more than one hole, or if any 
crack at any hole extends out of the spotface of the hole, repair in 
accordance with a method approved by the Manager, International 
Branch, ANM-116, or the EASA (or its delegated agent).

(l) Retained Terminating Modification for Repetitive Inspections 
Required by Paragraphs (g) and (j) of This AD for Certain Airplanes

    This paragraph restates the requirements of paragraph (l) of AD 
2010-23-26, Amendment 39-16516 (75 FR 74610, December 1, 2010). For 
airplanes on which the terminating modification in paragraph (i) of 
this AD has not been accomplished before July 18, 2006 (the 
effective date of AD 2006-12-13, Amendment 39-14639 (71 FR 33994, 
June 13, 2006)): At the earlier of the times specified in paragraphs 
(l)(1) and (l)(2) of this AD, modify Gear Rib 5 of the MLG 
attachment fittings at the lower flange. Except as provided by 
paragraph (m) of this AD, do the modification in accordance with the 
applicable service bulletin identified in table 5 of this AD. This 
action terminates the repetitive inspections requirements of 
paragraphs (g) and (j) of this AD.
    (1) Prior to the accumulation of 21,000 total flight cycles, or 
within 2 years after October 20, 1999 (the effective date of AD 99-
19-26, Amendment 39-11313 (64 FR 49966, September 15, 1999)), 
whichever is later.
    (2) Within 16 months after July 18, 2006 (the effective date of 
AD 2006-12-13, Amendment 39-14639 (71 FR 33994, June 13, 2006)).

[[Page 26941]]

          Table 5--Service Bulletins for Terminating Modification Required by Paragraph (l) of This AD
----------------------------------------------------------------------------------------------------------------
                                         Airbus Service
              Model--                      Bulletin--              Revision--                  Dated--
----------------------------------------------------------------------------------------------------------------
A300 B4-601, B4-603, B4-620, B4-     A300-57-6088..........  04                     December 3, 2003.
 622, B4-605R, B4-622R and F4-605R
 airplanes.
----------------------------------------------------------------------------------------------------------------
A300 B2-1C, B2K-3C, B2-203, B4-2C,   A300-57-0235..........  04                     March 13, 2003.
 B4-103, and B4-203 airplanes.
                                                             05                     December 3, 2003.
----------------------------------------------------------------------------------------------------------------

(m) Retained Modification

    This paragraph restates the requirements of paragraph (m) of AD 
2010-23-26, Amendment 39-16516 (75 FR 74610, December 1, 2010). 
Where the applicable service bulletin specified in paragraph (l) of 
this AD specifies to contact Airbus for modification instructions; 
or if there is a previously installed repair at any of the affected 
fastener holes; or if a crack is found when accomplishing the 
modification: Prior to further flight, modify in accordance with a 
method approved by the Manager, International Branch, ANM-116, or 
the EASA (or its delegated agent).

(n) Retained Exception for No Reporting

    This paragraph restates the requirements of paragraph (o) of AD 
2010-23-26, Amendment 39-16516 (75 FR 74610, December 1, 2010). 
Although the service bulletins identified in tables 1, 2, 3, 4, 5, 
and 6 of this AD specify to submit certain information to the 
manufacturer, this AD does not include such a requirement.

(o) Retained Requirements With Revised Service Information

    This paragraph restates the requirements of paragraph (p) of AD 
2010-23-26, Amendment 39-16516 (75 FR 74610, December 1, 2010). 
Unless already done, do the following actions.
    (1) At the applicable time specified in paragraph (o)(2) of this 
AD, perform a detailed inspection for cracking at the locations 
specified in paragraphs (o)(1)(i), (o)(1)(ii), and (o)(1)(iii) of 
this AD, in accordance with the Accomplishment Instructions of 
Airbus Mandatory Service Bulletin A300-57A0246, Revision 03, 
including Appendices 1 and 2, dated March 11, 2009, or Revision 04, 
including Appendices 1 and 2, dated September 9, 2009 (for Model 
A300 B2-1C, B2K-3C, B2-203, B4-2C, B4-103, and B4-203 airplanes); or 
Airbus Mandatory Service Bulletin A300-57A6101, Revision 03, 
including Appendices 1 and 2, dated March 11, 2009, or Revision 04, 
including Appendices 1 and 2, dated September 9, 2009 (for Model 
A300 B4-601, B4-603, B4-620, B4-622, B4-605R, B4-622R and F4-605R 
airplanes). As of the effective date of this AD Revision 04 of these 
service bulletins must be used to accomplish the actions required by 
this paragraph.
    (i) The bottom flange and vertical web in the area between the 
wing rear spar/gear Rib 5 attachment and the forward reaction-rod 
pick-up lug.
    (ii) On the inboard side, around the fastener holes at locations 
43, 47 to 50, 52, and 54.
    (iii) On the outboard side, the lower flange, the vertical web 
and around the fastener holes at locations 43, 47 to 50, 52 and 54.
    (2) Do the inspection required by paragraph (o)(1) of this AD at 
the later of the times in paragraphs (o)(2)(i) and (o)(2)(ii) of 
this AD.
    (i) Within 400 flight cycles after the accomplishment of the 
actions required by paragraph (i) or (l) of this AD, as applicable.
    (ii) Within 400 flight cycles or 4 months after January 5, 2011 
(the effective date of AD 2010-23-26, Amendment 39-16516 (75 FR 
74610, December 1, 2010)), whichever occurs first.
    (3) If no cracking is detected during the inspection required by 
paragraph (o)(1) of this AD, before further flight, perform a 
fluorescent penetrant inspection (FPI) at holes location 47 and 54, 
in the right-hand and left-hand MLG Rib 5 attachment fitting lower 
flange, in accordance with the Accomplishment Instructions of Airbus 
Mandatory Service Bulletin A300-57A0246, Revision 03, including 
Appendices 1 and 2, dated March 11, 2009, or Revision 04, including 
Appendices 1 and 2, dated September 9, 2009 (for Model A300 B2-1C, 
B2K-3C, B2-203, B4-2C, B4-103, and B4-203 airplanes); or Airbus 
Mandatory Service Bulletin A300-57A6101, Revision 03, including 
Appendices 1 and 2, dated March 11, 2009, or Revision 04, including 
Appendices 1 and 2, dated September 9, 2009 (for Model A300 B4-601, 
B4-603, B4-620, B4-622, B4-605R, B4-622R and F4-605R airplanes). As 
of the effective date of this AD, Airbus Mandatory Service Bulletin 
A300-57A0246, Revision 04, including Appendices 1 and 2, dated 
September 9, 2009; or Airbus Mandatory Service Bulletin A300-
57A6101, Revision 04, including Appendices 1 and 2, dated September 
9, 2009; as applicable; must be used to accomplish the actions 
required by this paragraph.
    (4) Thereafter, at intervals not to exceed 400 flight cycles, 
repeat the detailed and FPI inspections, in accordance with the 
Accomplishment Instructions of Airbus Mandatory Service Bulletin 
A300-57A0246, Revision 03, including Appendices 1 and 2, dated March 
11, 2009, or Revision 04, including Appendices 1 and 2, dated 
September 9, 2009 (for Model A300 B2-1C, B2K-3C, B2-203, B4-2C, B4-
103, and B4-203 airplanes); or Airbus Mandatory Service Bulletin 
A300-57A6101, Revision 03, including Appendices 1 and 2, dated March 
11, 2009, or Revision 04, including Appendices 1 and 2, dated 
September 9, 2009 (for Model A300 B4-601, B4-603, B4-620, B4-622, 
B4-605R, B4-622R and F4-605R airplanes); until the terminating 
action required by paragraph (p) of this AD has been accomplished. 
As of the effective date of this AD, Airbus Mandatory Service 
Bulletin A300-57A0246, Revision 04, including Appendices 1 and 2, 
dated September 9, 2009; or Airbus Mandatory Service Bulletin A300-
57A6101, Revision 04, including Appendices 1 and 2, dated September 
9, 2009; as applicable; must be used to accomplish the actions 
required by this paragraph.
    (5) If any crack is detected during any of the inspections 
required by paragraphs (o)(1), (o)(3), and (o)(4) of this AD, and 
Airbus Mandatory Service Bulletin A300-57A0246, Revision 03, 
including Appendices 1 and 2, dated March 11, 2009, or Revision 04, 
including Appendices 1 and 2, dated September 9, 2009 (for Model 
A300 B2-1C, B2K-3C, B2-203, B4-2C, B4-103, and B4-203 airplanes); or 
Airbus Mandatory Service Bulletin A300-57A6101, Revision 03, 
including Appendices 1 and 2, dated March 11, 2009, or Revision 04, 
including Appendices 1 and 2, dated September 9, 2009 (for Model 
A300 B4-601, B4-603, B4-620, B4-622, B4-605R, B4-622R and F4-605R 
airplanes); recommends contacting Airbus for appropriate action: 
Before further flight, contact Airbus for a repair solution, and do 
the repair; or repair the cracking using a method approved by the 
Manager, International Branch, ANM-116, Transport Airplane 
Directorate, FAA, or EASA (or its delegated agent).

(p) New Terminating Action

    Within 30 months after the effective date of this AD: Modify the 
spot-faces around all the fastener holes at locations 43, 47 to 50, 
52, and 54 (except for spot-faces of holes which have been 
previously repaired) on the bottom flange MLG ribs, in accordance 
with the Accomplishment Instructions of Airbus Mandatory Service 
Bulletin A300-57-0254, Revision 01, including Appendix 1, dated June 
14, 2011 (for Model A300 B2-1C, B2K-3C, B2-203, B4-2C, B4-103, and 
B4-203 airplanes); or Airbus Mandatory Service Bulletin A300-57-
6110, Revision 01, including Appendix 1, dated June 6, 2011 A300 B4-
601, B4-603, B4-620, B4-622, B4-605R, B4-622R and F4-605R airplanes 
(for Model A300 B4-601, B4-603, B4-620, B4-622, B4-605R, B4-622R and 
F4-605R airplanes). Accomplishing this modification terminates the 
repetitive inspection requirements of paragraph (o)(4) of this AD.

(q) Credit for Previous Actions

    (1) This paragraph provides credit for initial detailed and HFEC 
inspections, as

[[Page 26942]]

required by the introductory text of paragraph (g) of this AD, if 
those inspections were performed before April 12, 2000 (the 
effective date of AD 2000-05-07, Amendment 39-11616 (65 FR 12077, 
March 8, 2000)), using Airbus Service Bulletin A300-57A0234 (for 
Model A300 B2-1C, B2K-3C, B2-203, B4-2C, B4-103, and B4-203 
airplanes) or A300-57A6087, both dated August 5, 1997 (for Model 
A300 B4-601, B4-603, B4-620, B4-622, B4-605R, B4-622R, and F4-605R 
airplanes).
    (2) This paragraph provides credit for a modification, as 
required by paragraph (i) of this AD, if the modification was 
performed before April 12, 2000 (the effective date of AD 2000-05-
07, Amendment 39-11616 (65 FR 12077, March 8, 2000)), using Airbus 
Service Bulletin A300-57-6088, dated August 5, 1998 (for Model A300 
B4-601, B4-603, B4-620, B4-622, B4-605R, B4-622R and F4-605R 
airplanes); or Airbus Service Bulletin A300-57-0235, dated August 5, 
1998 (for Model A300 B2-1C, B2K-3C, B2-203, B4-2C, B4-103, and B4-
203 airplanes).
    (3) This paragraph provides credit for the actions required by 
paragraphs (i) and (l) of this AD, if those actions were performed 
before July 18, 2006 (the effective date of AD 2006-12-13, Amendment 
39-14639 (71 FR 33994, June 13, 2006)), using the applicable service 
information listed in table 6 of this AD.

                              Table 6--Previous Issues of Certain Service Bulletins
----------------------------------------------------------------------------------------------------------------
                                        Airbus Service
              Model--                     Bulletin--             Revision--                   Dated--
----------------------------------------------------------------------------------------------------------------
A300 B2-1C, B2K-3C, B2-203, B4-2C,  A300-57-0235.........  02, including          September 27, 1999.
 B4-103, and B4-203 airplanes.                              Appendix 01.
                                                           03                     September 5, 2002.
----------------------------------------------------------------------------------------------------------------
A300 B4-601, B4-603, B4-620, B4-    A300-57-6088.........  02...................  September 5, 2000.
 622, B4-605R, B4-622R and F4-605R
 airplanes.
                                                           03...................  March 13, 2003.
----------------------------------------------------------------------------------------------------------------

     (4) This paragraph provides credit for a modification of the 
spot-faces, as specified in paragraph (p) of this AD, if the 
modification was performed before the effective date of this AD 
using Airbus Mandatory Service Bulletin A300-57-0254, dated June 4, 
2010 (for Model A300 B2-1C, B2K-3C, B2-203, B4-2C, B4-103, and B4-
203 airplanes); or Airbus Mandatory Service Bulletin A300-57-6110, 
dated June 7, 2010 (for Model A300 B4-601, B4-603, B4-620, B4-622, 
B4-605R, B4-622R and F4-605R airplanes).

(r) Other FAA AD Provisions

    The following provisions also apply to this AD:
    (1) Alternative Methods of Compliance (AMOCs): The Manager, 
International Branch, ANM-116, 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, Washington 98057-3356; telephone (425) 
227-2125; fax (425) 227-1149. Information may be emailed to: 9-ANM-116-AMOC-REQUESTS@faa.gov. Before using any approved AMOC, notify 
your appropriate principal inspector, or lacking a principal 
inspector, the manager of the local flight standards district 
office/certificate holding district office. The AMOC approval letter 
must specifically reference this AD. AMOCs approved previously in 
accordance with AD 2000-05-07, Amendment 39-11616 (65 FR 12077, 
March 8, 2000); AD 2006-12-13, Amendment 39-14639 (71 FR 33994, June 
13, 2006); and AD 2010-23-26, Amendment 39-16516 (75 FR 74610, 
December 1, 2010); are approved as AMOCs for the corresponding 
provisions of this AD.
    (2) Airworthy Product: For any requirement in this AD to obtain 
corrective actions from a manufacturer or other source, use these 
actions if they are FAA-approved. Corrective actions are considered 
FAA-approved if they are approved by the State of Design Authority 
(or their delegated agent). You are required to assure the product 
is airworthy before it is returned to service.

(s) Related Information

    Refer to MCAI EASA Airworthiness Directive 2011-0029, dated 
February 24, 2011, and the service information specified in 
paragraphs (s)(1) through (s)(23) of this AD, for related 
information.
    (1) Airbus Service Bulletin A300-57-0234, Revision 01, dated 
March 11, 1998.
    (2) Airbus Service Bulletin A300-57A0234, Revision 02, dated 
June 24, 1999.
    (3) Airbus Service Bulletin A300-57A0234, Revision 03, including 
Appendix 01, dated September 2, 1999.
    (4) Airbus Service Bulletin A300-57A0234, Revision 04, including 
Appendix 01, dated May 19, 2000.
    (5) Airbus Service Bulletin A300-57A0234, Revision 05, including 
Appendix 01, dated February 19, 2002.
    (6) Airbus Service Bulletin A300-57-0235, Revision 01, including 
Appendix 01, dated February 1, 1999.
    (7) Airbus Service Bulletin A300-57-0235, Revision 03, dated 
September 5, 2002.
    (8) Airbus Service Bulletin A300-57-0235, Revision 04, dated 
March 13, 2003.
    (9) Airbus Service Bulletin A300-57-0235, Revision 05, dated 
December 3, 2003.
    (10) Airbus Mandatory Service Bulletin A300-57A0246, Revision 
03, including Appendices 1 and 2, dated March 11, 2009.
    (11) Airbus Mandatory Service Bulletin A300-57A0246, Revision 
04, including Appendices 1 and 2, dated September 9, 2009.
    (12) Airbus Mandatory Service Bulletin A300-57-0254, Revision 
01, including Appendix 1, dated June 14, 2011.
    (13) Airbus Service Bulletin A300-57-6087, Revision 01, dated 
March 11, 1998.
    (14) Airbus Service Bulletin A300-57A6087, Revision 02, 
including Appendix 01, dated June 24, 1999.
    (15) Airbus Service Bulletin A300-57A6087, Revision 03, 
including Appendix 01, dated May 19, 2000.
    (16) Airbus Service Bulletin A300-57A6087, Revision 04, 
including Appendix 01, dated February 19, 2002.
    (17) Airbus Service Bulletin A300-57A6087, Revision 05, 
including Appendix 01, dated March 10, 2008.
    (18) Airbus Service Bulletin A300-57-6088, Revision 01, 
including Appendix 01, dated February 1, 1999.
    (19) Airbus Service Bulletin A300-57-6088, Revision 02, dated 
September 5, 2002.
    (20) Airbus Service Bulletin A300-57-6088, Revision 04, dated 
December 3, 2003.
    (21) Airbus Mandatory Service Bulletin A300-57A6101, Revision 
03, including Appendices 1 and 2, dated March 11, 2009.
    (22) Airbus Mandatory Service Bulletin A300-57A6101, Revision 
04, including Appendices 1 and 2, dated September 9, 2009.
    (23) Airbus Mandatory Service Bulletin A300-57-6110, Revision 
01, including Appendix 1, dated June 6, 2011.

(t) Material Incorporated by Reference

    (1) You must use the following service information to do the 
actions required by this AD, unless the AD specifies otherwise. The 
Director of the Federal Register approved the incorporation by 
reference (IBR) of the following service information under 5 U.S.C. 
552(a) and 1 CFR part 51 on the date specified.
    (2) The following service information was approved for IBR on 
June 12, 2012:
    (i) Airbus Mandatory Service Bulletin A300-57-0254, Revision 01, 
including Appendix 1, dated June 14, 2011.
    (ii) Airbus Mandatory Service Bulletin A300-57-6110, Revision 
01, including Appendix 1, dated June 6, 2011.
    (3) The following service information was approved for IBR 
January 5, 2011 (75 FR 74610, December 1, 2010):

[[Page 26943]]

    (i) Airbus Mandatory Service Bulletin A300-57A0246, Revision 03, 
including Appendices 1 and 2, dated March 11, 2009.
    (ii) Airbus Mandatory Service Bulletin A300-57A0246, Revision 
04, including Appendices 1 and 2, dated September 9, 2009.
    (iii) Airbus Mandatory Service Bulletin A300-57A6101, Revision 
03, including Appendices 1 and 2, dated March 11, 2009.
    (iv) Airbus Mandatory Service Bulletin A300-57A6101, Revision 
04, including Appendices 1 and 2, dated September 9, 2009.
    (v) Airbus Service Bulletin A300-57A6087, Revision 05, including 
Appendix 01, dated March 10, 2008. (Appendix 01 of this document was 
incorrectly identified as ``Appendix 05'' in the document citation 
specified in table 8 of AD 2010-23-26, Amendment 39-16516 (75 FR 
74610, December 1, 2010); all other references to Appendix 01 of 
this document in AD 2010-23-26 were correct.)
    (4) The following service information was approved for IBR July 
18, 2006 (71 FR 33994, June 13, 2006):
    (i) Airbus Service Bulletin A300-57A0234, Revision 04, including 
Appendix 01, dated May 19, 2000.
    (ii) Airbus Service Bulletin A300-57A0234, Revision 05, 
including Appendix 01, dated February 19, 2002.
    (iii) Airbus Service Bulletin A300-57A6087, Revision 03, 
including Appendix 01, dated May 19, 2000.
    (iv) Airbus Service Bulletin A300-57A6087, Revision 04, 
including Appendix 01, dated February 19, 2002.
    (v) Airbus Service Bulletin A300-57-0235, Revision 03, dated 
September 5, 2002.
    (vi) Airbus Service Bulletin A300-57-0235, Revision 04, dated 
March 13, 2003.
    (vii) Airbus Service Bulletin A300-57-0235, Revision 05, dated 
December 3, 2003.
    (viii) Airbus Service Bulletin A300-57-6088, Revision 02, dated 
September 5, 2002.
    (ix) Airbus Service Bulletin A300-57-6088, Revision 04, dated 
December 3, 2003.
    (5) The following service information was approved for IBR on 
April 12, 2000 (65 FR 12077, March 8, 2000):
    (i) Airbus Service Bulletin A300-57A0234, Revision 02, dated 
June 24, 1999.
    (ii) Airbus Service Bulletin A300-57A0234, Revision 03, 
including Appendix 01, dated September 2, 1999.
    (iii) Airbus Service Bulletin A300-57A6087, Revision 02, 
including Appendix 01, dated June 24, 1999.
    (6) The following service information was approved for IBR on 
October 20, 1999 (64 FR 49966, September 15, 1999).
    (i) Airbus Service Bulletin A300-57-0234, Revision 01, dated 
March 11, 1998.
    (ii) Airbus Service Bulletin A300-57-0235, Revision 01, 
including Appendix 01, dated February 1, 1999.
    (iii) Airbus Service Bulletin A300-57-6087, Revision 01, dated 
March 11, 1998.
    (iv) Airbus Service Bulletin A300-57-6088, Revision 01, 
including Appendix 01, dated February 1, 1999.
    (7) For service information identified in this AD, contact 
Airbus SAS--EAW (Airworthiness Office), 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.
    (8) You may review copies of the service information at the FAA, 
Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, 
Washington. For information on the availability of this material at 
the FAA, call 425-227-1221.
    (9) You may also review copies of the service information that 
is incorporated by reference at the National Archives and Records 
Administration (NARA). For information on the availability of this 
material at an NARA facility, call 202-741-6030, or go to http://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html.

    Issued in Renton, Washington, on January 6, 2012.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2012-9189 Filed 5-7-12; 8:45 am]
BILLING CODE 4910-13-P
```