[Federal Register Volume 75, Number 230 (Wednesday, December 1, 2010)]
[Rules and Regulations]
[Pages 74610-74616]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2010-28589]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2009-1067; Directorate Identifier 2009-NM-071-AD;
Amendment 39-16516; AD 2010-23-26]
RIN 2120-AA64
Airworthiness Directives; 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
AGENCY: Federal Aviation Administration, Department of Transportation.
ACTION: Final rule.
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SUMMARY: We are superseding an existing airworthiness directive (AD)
for the products listed above. This AD results from mandatory
continuing airworthiness information (MCAI) originated by an aviation
authority of another country to identify and correct an unsafe
condition on an aviation product. The MCAI describes the unsafe
condition as:
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) [parallel to part of FAA AD 2006-12-
13] was issued to require repetitive inspections and, as terminating
action * * *[.]
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 * * * [was]
embodied. This condition, if not corrected, could affect the
structural integrity of those aeroplanes.
* * * * *
We are issuing this AD to require actions to correct the unsafe
condition on these products.
DATES: This AD becomes effective January 5, 2011.
The Director of the Federal Register approved the incorporation by
reference of certain publications listed in this AD as of January 5,
2011.
On 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.
On 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.
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 November 18, 2009
(74 FR 59483), and proposed to supersede AD 2006-12-13, Amendment 39-
14639 (71 FR 33994, June 13, 2006). 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) [parallel to part of FAA AD 2006-12-
13] 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].
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, AD 2009-0081 superseded EASA AD
2008-0111 and required operators to comply with the new inspection
programme introduced in
[[Page 74611]]
Revisions 3 of Airbus SB A300-57A0246 and Airbus SB A300-57A6101.
This AD is revised to introduce an optional terminating action
which consists of spot-facing the sensitive holes of the MLG Rib 5
(LH and RH) bottom flanges.
Required actions include contacting Airbus for repair instructions, if
necessary, and doing the repair. 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.
Request To Revise Proposed Costs of Compliance
FedEx Express commented that the NPRM would affect 57 of its
airplanes. FedEx Express states that the inspections do not require any
special inspection techniques, training, or tooling, and that it has
scheduled the proposed inspections although it has not yet inspected
any airplanes. FedEx Express also states that the inspection interval
is sufficient, but if cracks are found, significant downtime will be
required.
From these comments, we infer that FedEx Express is requesting that
we revise the Costs of Compliance section of the NPRM. We do not agree
with the request. We recognize that, in accomplishing the requirements
of any AD, operators might incur ``incidental'' costs in addition to
the ``direct'' costs that are reflected in the cost analysis presented
in the AD preamble. However, the cost analysis in AD rulemaking actions
typically does not include incidental costs. We have, however, reviewed
the figures that we have used over the past several years to calculate
costs to operators. To account for various inflationary costs in the
airline industry, we find it necessary to increase the labor rate used
in these calculations from $80 per work hour to $85 per work hour. The
cost impact information, below, reflects this increase in the specified
hourly rate. We have also corrected the calculations used in
determining the cost to operators.
Explanation of Change to the NPRM
Paragraph (p)(5) of the NPRM specifies contacting Airbus for a
repair solution and doing the repair. The European Aviation Safety
Agency (EASA) has assumed responsibility for the airplane models
subject to this AD. Therefore, we have revised paragraph (p)(5) of this
AD to add a provision for making repairs using a method approved by
either the Manager of the International Branch, ANM-116, Transport
Airplane Directorate, FAA or the EASA (or its delegated agent).
Explanation of Change to AD
We have revised paragraphs (j) and (k) of this AD; and Tables 1, 2,
3, 4, and 5 of this AD to remove Airbus Model A300 B2-1A, F4-622R, and
C4-605R Variant F airplanes. We have determined that these airplanes
were inadvertently carried over from the paragraph callouts of the
previous AD into the NPRM. These airplanes are not subject to the
identified unsafe condition and therefore are not affected by this AD.
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. We also determined that these
changes will not increase the economic burden on any operator or
increase the scope of the AD.
Differences Between This AD and the MCAI or Service Information
We have reviewed the MCAI and related service information and, in
general, agree with their substance. But we might have found it
necessary to use different words from those in the MCAI to ensure the
AD is clear for U.S. operators and is enforceable. In making these
changes, we do not intend to differ substantively from the information
provided in the MCAI and related service information.
We might also have required different actions in this AD from those
in the MCAI in order to follow our FAA policies. Any such differences
are highlighted in a NOTE within the AD.
Costs of Compliance
We estimate that this AD will affect about 155 products of U.S.
registry.
The actions that are required by AD 2006-12-13 and retained in this
AD take about 76 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 $16,730 per product.
We estimate that it will take about 3 work-hours per product to
comply with the new basic requirements of this AD. The average labor
rate is $85 per work-hour. Based on these figures, we estimate the cost
of this AD to the U.S. operators to be $39,525 or $255 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, 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.
[[Page 74612]]
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.
Adoption of the Amendment
0
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 39-14639 (71 FR
33994, June 13, 2006) and adding the following new AD:
2010-23-26 Airbus: Amendment 39-16516. Docket No. FAA-2009-1067;
Directorate Identifier 2009-NM-071-AD.
Effective Date
(a) This airworthiness directive (AD) becomes effective January
5, 2011.
Affected ADs
(b) This AD supersedes AD 2006-12-13, Amendment 39-14639.
Applicability
(c) 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.
Subject
(d) Air Transport Association (ATA) of America Code 57: Wings.
Reason
(e) The mandatory continuing airworthiness information (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) [parallel to part of FAA AD 2006-12-
13] 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].
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, 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.
This AD is revised to introduce an optional terminating action
which consists of spot-facing the sensitive holes of the MLG Rib 5
(LH and RH) bottom flanges.
Required actions include contacting Airbus for repair instructions,
if necessary, and doing the repair.
Restatement of Requirements of AD 2000-05-07
(f) You are responsible for having the actions required by this
AD performed within the compliance times specified, unless the
actions have already been done.
Repetitive Inspections
(g) Perform a detailed inspection and a high-frequency eddy
current (HFEC) inspection to detect cracks in Gear Rib 5 of the main
landing gear (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),
only the service bulletins listed in Table 2 of this AD may be used.
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
----------------------------------------------------------------------------------------------------------------
Airbus Service Revision
Model-- Bulletin-- level-- Dated--
----------------------------------------------------------------------------------------------------------------
A300 B4-601, B4-603, B4-620, B4-622, A300-57-6087 01 March 11, 1998.
B4-605R, B4-622R and F4-605R
airplanes.
A300 B2-1C, B2K-3C, B2-203, B4-2C, B4- A300-57-0234 01 March 11, 1998.
103, and B4-203 airplanes.
----------------------------------------------------------------------------------------------------------------
Table 2--Other Revisions of Service Bulletins
----------------------------------------------------------------------------------------------------------------
Airbus Service
Model-- Bulletin-- Revision level-- Dated--
----------------------------------------------------------------------------------------------------------------
A300 B4-601, B4-603, B4-620, B4- A300-57A6087 02, including June 24, 1999.
622, B4-605R, B4-622R, and F4- Appendix 01.
605R airplanes.
................ 03, including May 19, 2000.
Appendix 01.
................ 04, including February 19, 2002.
Appendix 01.
................ 05, including March 10, 2008.
Appendix 01.
A300 B2-1C, B2K-3C, B2-203, B4-2C, A300-57A0234 02................... June 24, 1999.
B4-103, and B4-203 airplanes.
................ 03, including September 2, 1999.
Appendix 01.
................ 04, including May 19, 2000.
Appendix 01.
................ 05, including February 19, 2002.
Appendix 01.
----------------------------------------------------------------------------------------------------------------
[[Page 74613]]
(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): 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: Inspect prior to the accumulation
of 18,000 total flight cycles, or within 1,500 flight cycles after
March 9, 1998, whichever occurs later.
Note 1: 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.''
Note 2: Accomplishment of the initial detailed and HFEC
inspections prior to April 12, 2000, in accordance with Airbus
Service Bulletin A300-57A0234 or A300-57A6087, both dated August 5,
1997, as applicable, is considered acceptable for compliance with
the initial inspections required by paragraph (g) of this AD.
Repair for Any Crack Found During Inspections Required by Paragraph (g)
of This AD
(h) 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).
Terminating Modification for Repetitive Inspections Required by
Paragraphs (g) and (j) of This AD
(i) 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), 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), only Revision 04 of Airbus Service Bulletin A300-57-
6088, and Revisions 04 and 05 of Airbus Service Bulletin A300-57-
0235 may be used. 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
----------------------------------------------------------------------------------------------------------------
Airbus Service
Model-- Bulletin-- Revision level-- 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.
................ 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.
----------------------------------------------------------------------------------------------------------------
Note 3: Accomplishment of the modification required by paragraph
(i) of this AD prior to April 12, 2000, in accordance with Airbus
Service Bulletin A300-57-6088 or A300-57-0235, both dated August 5,
1998; as applicable; is acceptable for compliance with the
requirements of that paragraph.
Restatement of Requirements of AD 2006-12-13
Additional Repetitive Inspections
(j) 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),
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
----------------------------------------------------------------------------------------------------------------
Airbus Service
Model-- Bulletin-- Revision level-- 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: 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: 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: Prior to the accumulation of 14,500 total flight cycles, or
within 700 flight cycles after July 18, 2006, whichever occurs
later.
[[Page 74614]]
(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: Prior to the accumulation
of 11,600 total flight cycles, or within 700 flight cycles after
July 18, 2006, whichever occurs later.
Crack Repair
(k) 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, dated March 10, 2008 (for Model A300 B4-
601, B4-603, B4-620, B4-622, B4-605R, B4-622R, and F4-605R
airplanes); as applicable.
(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).
Terminating Modification for Repetitive Inspections Required by
Paragraphs (g) and (j) of This AD for Certain Airplanes
(l) For airplanes on which the terminating modification in
paragraph (i) of this AD has not been accomplished before July 18,
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 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, whichever is later.
(2) Within 16 months after July 18, 2006.
Table 5--Service Bulletins for Terminating Modification
----------------------------------------------------------------------------------------------------------------
Airbus Service
Model-- Bulletin-- Revision level-- 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) 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).
Actions Accomplished per Previous Issues of Service Bulletins
(n) Actions accomplished before July 18, 2006, in accordance
with the service bulletins listed in Table 6 of this AD, are
considered acceptable for compliance with the corresponding action
specified in paragraphs (g) through (m) of this AD.
Table 6--Previous Issues of Service Bulletins
----------------------------------------------------------------------------------------------------------------
Airbus Service Bulletin-- Revision level-- Dated--
----------------------------------------------------------------------------------------------------------------
A300-57-0235.......................... 02, including Appendix 01..... September 27, 1999.
03............................ September 5, 2002.
A300-57-6088.......................... 02............................ September 5, 2000.
03............................ March 13, 2003.
----------------------------------------------------------------------------------------------------------------
No Reporting
(o) 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.
New Requirements of This AD:
Actions and Compliance
(p) Unless already done, do the following actions.
(1) At the applicable time specified in paragraph (p)(2) of this
AD, perform a detailed inspection for cracking at the locations
specified in paragraphs (p)(1)(i), (p)(1)(ii), and (p)(1)(iii) of
this AD, in accordance with the Accomplishment Instructions of
Airbus Mandatory Service Bulletin A300-57A0246, Revision 03, dated
March 11, 2009; or Revision 04, dated September 9, 2009; or Airbus
Mandatory Service Bulletin A300-57A6101, Revision 03, dated March
11, 2009; or Revision 04, dated September 9, 2009; as applicable.
(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 (p)(1) of this AD at
the later of the times in paragraphs (p)(2)(i) and (p)(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 the effective
date of this AD, whichever occurs first.
(3) If no cracking is detected during the inspection required by
paragraph (p)(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, dated March
11, 2009; or Revision 04, dated September 9, 2009; or Airbus
Mandatory Service Bulletin A300-57A6101, Revision 03, dated March
11, 2009; or Revision 04, dated September 9, 2009; as applicable.
(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, dated March 11, 2009; or Revision 04,
dated September 9, 2009; or Airbus Mandatory Service Bulletin A300-
[[Page 74615]]
57A6101, Revision 03, dated March 11, 2009; or Revision 04, dated
September 9, 2009; as applicable.
(5) If any crack is detected during any of the inspections
required by paragraphs (p)(1), (p)(3), and (p)(4) of this AD, and
Airbus Mandatory Service Bulletin A300-57A0246, Revision 03, dated
March 11, 2009; or Revision 04, dated September 9, 2009; or Airbus
Mandatory Service Bulletin A300-57A6101, Revision 03, dated March
11, 2009; or Revision 04, dated September 9, 2009; 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.
(q) Spot-facing the sensitive holes on the bottom flange MLG
ribs, in accordance with the Accomplishment Instructions of Airbus
Mandatory Service Bulletin A300-57-0254, dated June 4, 2010, or
Airbus Mandatory Service Bulletin A300-57-6110, dated June 7, 2010;
as applicable; terminates the repetitive inspection requirements of
paragraph (p)(4) of this AD.
FAA AD Differences
Note 4: This AD differs from the MCAI and/or service information
as follows: No differences.
Other FAA AD Provisions
(r) 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. Send information 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. Before using any approved AMOC
on any airplane to which the AMOC applies, notify your principal
maintenance inspector (PMI) or principal avionics inspector (PAI),
as appropriate, or lacking a principal inspector, your local Flight
Standards District Office. The AMOC approval letter must
specifically reference 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.
Related Information
(s) Refer to MCAI EASA Airworthiness Directive 2009-0081R1,
dated July 30, 2010, and the service information specified in Table
7 of this AD, for related information.
Table 7--Related Service Information
----------------------------------------------------------------------------------------------------------------
Airbus-- Revision-- Dated--
----------------------------------------------------------------------------------------------------------------
Mandatory Service Bulletin A300- 03, including Appendices 1 and March 11, 2009.
57A0246. 2.
04, including Appendices 1 and September 9, 2009.
2.
Mandatory Service Bulletin A300-57- 0, including Appendix 1....... June 4, 2010.
0254.
Mandatory Service Bulletin A300- 03, including Appendixes 1 and March 11, 2009.
57A6101. 2.
04, including Appendices 1 and September 9, 2009.
2.
Mandatory Service Bulletin A300-57- 0, including Appendix 1....... June 7, 2010.
6110.
Service Bulletin A300-57A0234......... 02............................ June 24, 1999.
03, including Appendix 01..... September 2, 1999.
04, including Appendix 01..... May 19, 2000.
05, including Appendix 01..... February 19, 2002.
Service Bulletin A300-57A6087......... 02, including Appendix 01..... June 24, 1999.
03, including Appendix 01..... May 19, 2000.
04, including Appendix 01..... February 19, 2002.
05, including Appendix 01..... March 10, 2008.
Service Bulletin A300-57-0235......... 04............................ March 13, 2003.
05............................ December 3, 2003.
Service Bulletin A300-57-6088......... 04............................ December 3, 2003.
----------------------------------------------------------------------------------------------------------------
Material Incorporated by Reference
(t) You must use the service information specified in Table 8 of
this AD to do the actions required by this AD, as applicable, unless
the AD specifies otherwise.
Table 8--All Material Incorporated by Reference
----------------------------------------------------------------------------------------------------------------
Airbus-- Revision-- Dated--
----------------------------------------------------------------------------------------------------------------
Mandatory Service Bulletin A300- 03, including Appendices 1 and March 11, 2009.
57A0246. 2.
04, including Appendices 1 and September 9, 2009.
2.
Mandatory Service Bulletin A300-57- 0, including Appendix 1....... June 4, 2010.
0254.
Mandatory Service Bulletin A300- 03, including Appendices 1 and March 11, 2009.
57A6101. 2.
04, including Appendices 1 and September 9, 2009.
2.
Mandatory Service Bulletin A300-57- 0, including Appendix 1....... June 7, 2010.
6110.
Service Bulletin A300-57A0234......... 02............................ June 24, 1999.
03, including Appendix 01..... September 2, 1999.
04, including Appendix 01..... May 19, 2000.
05, including Appendix 01..... February 19, 2002.
Service Bulletin A300-57A6087......... 02, including Appendix 01..... June 24, 1999.
03, including Appendix 01..... May 19, 2000.
04, including Appendix 01..... February 19, 2002.
05, including Appendix 05..... March 10, 2008.
Service Bulletin A300-57-0235......... 04............................ March 13, 2003.
05............................ December 3, 2003.
Service Bulletin A300-57-6088......... 04............................ December 3, 2003.
----------------------------------------------------------------------------------------------------------------
[[Page 74616]]
(1) The Director of the Federal Register approved the
incorporation by reference of the service information contained in
Table 9 of this AD under 5 U.S.C. 552(a) and 1 CFR part 51.
Table 9--New Material Incorporated by Reference
----------------------------------------------------------------------------------------------------------------
Airbus-- Revision-- Dated--
----------------------------------------------------------------------------------------------------------------
Mandatory Service Bulletin A300- 03, including Appendices 1 and March 11, 2009.
57A0246. 2.
04, including Appendices 1 and September 9, 2009.
2.
Mandatory Service Bulletin A300-57- Original...................... June 4, 2010.
0254.
Mandatory Service Bulletin A300- 05, including Appendix 1...... March 10, 2008.
57A6087.
Mandatory Service Bulletin A300- 03, including Appendices 1 and March 11, 2009.
57A6101. 2.
04, including Appendices 1 and September 9, 2009.
2.
Mandatory Service Bulletin A300-57- 0, including Appendix 1....... June 7, 2010.
6110.
----------------------------------------------------------------------------------------------------------------
(2) The Director of the Federal Register previously approved
the incorporation by reference of the service information specified
in Table 10 of this AD on July 18, 2006 (71 FR 33994, June 13,
2006).
Table 10--Material Previously Incorporated by Reference in AD 2006-12-13
----------------------------------------------------------------------------------------------------------------
Airbus-- Revision-- Dated--
----------------------------------------------------------------------------------------------------------------
Service Bulletin A300-57A0234......... 04, including Appendix 01..... May 19, 2000.
05, including Appendix 01..... February 19, 2002.
Service Bulletin A300-57A6087......... 03, including Appendix 01..... May 19, 2000.
04, including Appendix 01..... February 19, 2002.
Service Bulletin A300-57-0235......... 04............................ March 13, 2003.
05............................ December 3, 2003.
Service Bulletin A300-57-6088......... 04............................ December 3, 2003.
----------------------------------------------------------------------------------------------------------------
(3) The Director of the Federal Register previously approved
the incorporation by reference of the service information specified
in Table 11 of this AD on April 12, 2000 (65 FR 12077, March 8,
2000).
Table 11--Material Previously Incorporated by Reference in AD 2000-05-07
----------------------------------------------------------------------------------------------------------------
Airbus-- Revision-- Dated--
----------------------------------------------------------------------------------------------------------------
Service Bulletin A300-57A0234......... 02............................ June 24, 1999.
03, including Appendix 01..... September 2, 1999.
Service Bulletin A300-57A6087......... 02, including Appendix 01..... June 24, 1999.
----------------------------------------------------------------------------------------------------------------
(4) 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; e-mail [email protected];
Internet http://www.airbus.com.
(5) 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.
(6) 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 NARA, 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 November 3, 2010.
Dionne Palermo,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2010-28589 Filed 11-30-10; 8:45 am]
BILLING CODE 4910-13-P