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, 74610-74616 [2010-28589]
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74610
Federal Register / Vol. 75, No. 230 / Wednesday, December 1, 2010 / Rules and Regulations
(3) Reporting Requirements: For any
reporting requirement in this AD, a federal
agency may not conduct or sponsor, and a
person is not required to respond to, nor
shall a person be subject to a penalty for
failure to comply with a collection of
information subject to the requirements of
the Paperwork Reduction Act unless that
collection of information displays a current
valid OMB Control Number. The OMB
Control Number for this information
collection is 2120–0056. Public reporting for
this collection of information is estimated to
be approximately 5 minutes per response,
including the time for reviewing instructions,
completing and reviewing the collection of
information. All responses to this collection
of information are mandatory. Comments
concerning the accuracy of this burden and
suggestions for reducing the burden should
be directed to the FAA at: 800 Independence
Ave., SW., Washington, DC 20591, Attn:
Information Collection Clearance Officer,
AES–200.
Related Information
WReier-Aviles on DSKGBLS3C1PROD with RULES
(h) Refer to MCAI European Aviation
Safety Agency (EASA) AD No. 2010–0099,
´ ´
dated May 26, 2010; and Societe Nouvelle
Centrair Service Bulletin No. 101–29, dated
July 30, 2009, for related information.
Material Incorporated by Reference
´ ´
(i) You must use Societe Nouvelle Centrair
Service Bulletin No. 101–29, dated July 30,
2009, to do the actions required by this AD,
unless the AD specifies otherwise.
(1) The Director of the Federal Register
approved the incorporation by reference of
this service information under 5 U.S.C.
552(a) and 1 CFR part 51.
(2) For service information identified in
´ ´
this AD, contact Societe Nouvelle
CENTRAIR, Aerodome—36300 Le Blanc,
France; telephone: +33 (0)254 370796; fax:
+33 (0)54. 374864; Internet: https://
www.societe.com.
(3) You may review copies of the service
information incorporated by reference for
this AD at the FAA, Central Region, Office of
the Regional Counsel, 901 Locust, Kansas
City, Missouri 64106. For information on the
availability of this material at the Central
Region, call (816) 329–3768.
(4) You may also review copies of the
service information incorporated by reference
for this AD 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: https://www.archives.gov/federal_register/
code_of_federal_regulations/ibr_
locations.html.
Issued in Kansas City, Missouri, on
November 17, 2010.
Patrick R. Mullen,
Acting Manager, Small Airplane Directorate,
Aircraft Certification Service.
[FR Doc. 2010–29461 Filed 11–30–10; 8:45 am]
BILLING CODE 4910–13–P
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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
Federal Aviation
Administration, Department of
Transportation.
ACTION: Final rule.
AGENCY:
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:
SUMMARY:
Following the occurrence of cracks on the
MLG [main landing gear] rib 5 RH [righthand] and LH [left-hand] attachment fitting
´ ´
lower flanges, DGAC [Direction Generale 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 https://
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Fmt 4700
Sfmt 4700
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 [righthand] and LH [left-hand] attachment fitting
´ ´
lower flanges, DGAC [Direction Generale 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
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Federal Register / Vol. 75, No. 230 / Wednesday, December 1, 2010 / Rules and Regulations
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 spotfacing 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.
WReier-Aviles on DSKGBLS3C1PROD with RULES
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
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14:39 Nov 30, 2010
Jkt 223001
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 workhour. Based on these figures, we
estimate the cost of this AD to the U.S.
operators to be $39,525 or $255 per
product.
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74611
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 https://
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.
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74612
Federal Register / Vol. 75, No. 230 / Wednesday, December 1, 2010 / Rules and Regulations
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation
safety, Incorporation by reference,
Safety.
Adoption of the Amendment
Subject
(d) Air Transport Association (ATA) of
America Code 57: Wings.
Accordingly, under the authority
delegated to me by the Administrator,
the FAA amends 14 CFR part 39 as
follows:
■
PART 39—AIRWORTHINESS
DIRECTIVES
1. The authority citation for part 39
continues to read as follows:
■
Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13
(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.
[Amended]
2. The FAA amends § 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.
Reason
(e) The mandatory continuing
airworthiness information (MCAI) states:
Following the occurrence of cracks on the
MLG [main landing gear] rib 5 RH [righthand] and LH [left-hand] attachment fitting
´ ´
lower flanges, DGAC [Direction Generale 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 spotfacing 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
Bulletin—
Model—
A300 B4–601, B4–603, B4–620, B4–622, B4–605R, B4–622R and F4–605R airplanes.
A300 B2–1C, B2K–3C, B2–203, B4–2C, B4–103, and B4–203 airplanes ............
Revision
level—
Dated—
A300–57–6087
01
March 11, 1998.
A300–57–0234
01
March 11, 1998.
TABLE 2—OTHER REVISIONS OF SERVICE BULLETINS
Airbus Service
Bulletin—
Model—
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A300 B2–1C, B2K–3C, B2–203, B4–2C, B4–103, and B4–
203 airplanes.
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Dated—
A300–57A6087
02, including Appendix 01 ..............
June 24, 1999.
A300–57A0234
03, including Appendix 01 ..............
04, including Appendix 01 ..............
05, including Appendix 01 ..............
02 ....................................................
May 19, 2000.
February 19, 2002.
March 10, 2008.
June 24, 1999.
03, including Appendix 01 ..............
04, including Appendix 01 ..............
05, including Appendix 01 ..............
A300 B4–601, B4–603, B4–620, B4–622, B4–605R, B4–
622R, and F4–605R airplanes.
Revision level—
September 2, 1999.
May 19, 2000.
February 19, 2002.
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Federal Register / Vol. 75, No. 230 / Wednesday, December 1, 2010 / Rules and Regulations
(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
74613
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.
Transport Airplane Directorate, FAA, or the
European Aviation Safety Agency (EASA) (or
its delegated agent).
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,
(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.
Terminating Modification for Repetitive
Inspections Required by Paragraphs (g) and
(j) of This AD
TABLE 3—SERVICE BULLETINS FOR TERMINATING MODIFICATION
Airbus Service
Bulletin—
Model—
February 1, 1999.
02 ....................................................
04 ....................................................
01, including Appendix 01 ..............
September 5, 2002.
December 3, 2003.
February 1, 1999.
03 ....................................................
04 ....................................................
05 ....................................................
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.
01, including Appendix 01 ..............
A300–57–0235
A300 B2–1C, B2K–3C, B2–203, B4–2C, B4–103, and B4–
203 airplanes.
Dated—
A300–57–6088
A300 B4–601, B4–603, B4–620, B4–622, B4–605R, B4–
622R, and F4–605R airplanes.
Revision level—
September 5, 2002.
March 13, 2003.
December 3, 2003.
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
Bulletin—
Model—
Revision level—
Dated—
A300–57A6087
04, including Appendix 01 ..............
February 19, 2002.
A300 B2–1C, B2K–3C, B2–203, B4–2C, B4–103, and B4–
203 airplanes.
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A300 B4–601, B4–603, B4–620, B4–622, B4–605R, B4–
622R, and F4–605R airplanes.
A300–57A0234
05, including Appendix 01 ..............
05, including Appendix 01 ..............
March 10, 2008.
February 19, 2002.
(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.
VerDate Mar<15>2010
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(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.
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(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.
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(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
Bulletin—
Model—
04 ....................................................
December 3, 2003.
A300–57–0235
04 ....................................................
March 13, 2003.
05 ....................................................
(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
Dated—
A300–57–6088
A300 B4–601, B4–603, B4–620, B4–622, B4–605R, B4–
622R and F4–605R airplanes.
A300 B2–1C, B2K–3C, B2–203, B4–2C, B4–103, and B4–
203 airplanes.
Revision level—
December 3, 2003.
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 .................................................
03 .......................................................................................
02 .......................................................................................
03 .......................................................................................
September 27, 1999.
September 5, 2002.
September 5, 2000.
March 13, 2003.
A300–57–6088 ...................................................................
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:
WReier-Aviles on DSKGBLS3C1PROD with RULES
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,
VerDate Mar<15>2010
14:39 Nov 30, 2010
Jkt 223001
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.
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(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–
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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)
74615
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 A300–57A0246 .......................
03, including Appendices 1 and 2 .....................................
04, including Appendices 1 and 2 .....................................
0, including Appendix 1 .....................................................
03, including Appendixes 1 and 2 .....................................
04, including Appendices 1 and 2 .....................................
0, including Appendix 1 .....................................................
02 .......................................................................................
03, including Appendix 01 .................................................
04, including Appendix 01 .................................................
05, including Appendix 01 .................................................
02, including Appendix 01 .................................................
03, including Appendix 01 .................................................
04, including Appendix 01 .................................................
05, including Appendix 01 .................................................
04 .......................................................................................
05 .......................................................................................
04 .......................................................................................
March 11, 2009.
September 9, 2009.
June 4, 2010.
March 11, 2009.
September 9, 2009.
June 7, 2010.
June 24, 1999.
September 2, 1999.
May 19, 2000.
February 19, 2002.
June 24, 1999.
May 19, 2000.
February 19, 2002.
March 10, 2008.
March 13, 2003.
December 3, 2003.
December 3, 2003.
Mandatory Service Bulletin A300–57–0254 .......................
Mandatory Service Bulletin A300–57A6101 .......................
Mandatory Service Bulletin A300–57–6110 .......................
Service Bulletin A300–57A0234 .........................................
Service Bulletin A300–57A6087 .........................................
Service Bulletin A300–57–0235 .........................................
Service Bulletin A300–57–6088 .........................................
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 A300–57A0246 .......................
03, including Appendices 1 and 2 .....................................
04, including Appendices 1 and 2 .....................................
0, including Appendix 1 .....................................................
03, including Appendices 1 and 2 .....................................
04, including Appendices 1 and 2 .....................................
0, including Appendix 1 .....................................................
02 .......................................................................................
03, including Appendix 01 .................................................
04, including Appendix 01 .................................................
05, including Appendix 01 .................................................
02, including Appendix 01 .................................................
03, including Appendix 01 .................................................
04, including Appendix 01 .................................................
05, including Appendix 05 .................................................
04 .......................................................................................
05 .......................................................................................
04 .......................................................................................
March 11, 2009.
September 9, 2009.
June 4, 2010.
March 11, 2009.
September 9, 2009.
June 7, 2010.
June 24, 1999.
September 2, 1999.
May 19, 2000.
February 19, 2002.
June 24, 1999.
May 19, 2000.
February 19, 2002.
March 10, 2008.
March 13, 2003.
December 3, 2003.
December 3, 2003.
Mandatory Service Bulletin A300–57–0254 .......................
Mandatory Service Bulletin A300–57A6101 .......................
WReier-Aviles on DSKGBLS3C1PROD with RULES
Mandatory Service Bulletin A300–57–6110 .......................
Service Bulletin A300–57A0234 .........................................
Service Bulletin A300–57A6087 .........................................
Service Bulletin A300–57–0235 .........................................
Service Bulletin A300–57–6088 .........................................
VerDate Mar<15>2010
14:39 Nov 30, 2010
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Federal Register / Vol. 75, No. 230 / Wednesday, December 1, 2010 / Rules and Regulations
(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 A300–57A0246 .......................
03, including Appendices 1 and 2 .....................................
04, including Appendices 1 and 2 .....................................
Original ...............................................................................
05, including Appendix 1 ...................................................
03, including Appendices 1 and 2 .....................................
04, including Appendices 1 and 2 .....................................
0, including Appendix 1 .....................................................
March 11, 2009.
September 9, 2009.
June 4, 2010.
March 10, 2008.
March 11, 2009.
September 9, 2009.
June 7, 2010.
Mandatory Service Bulletin A300–57–0254 .......................
Mandatory Service Bulletin A300–57A6087 .......................
Mandatory Service Bulletin A300–57A6101 .......................
Mandatory Service Bulletin A300–57–6110 .......................
(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 .................................................
05, including Appendix 01 .................................................
03, including Appendix 01 .................................................
04, including Appendix 01 .................................................
04 .......................................................................................
05 .......................................................................................
04 .......................................................................................
May 19, 2000.
February 19, 2002.
May 19, 2000.
February 19, 2002.
March 13, 2003.
December 3, 2003.
December 3, 2003.
Service Bulletin A300–57A6087 .........................................
Service Bulletin A300–57–0235 .........................................
Service Bulletin A300–57–6088 .........................................
(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 .......................................................................................
03, including Appendix 01 .................................................
02, including Appendix 01 .................................................
June 24, 1999.
September 2, 1999.
June 24, 1999.
WReier-Aviles on DSKGBLS3C1PROD with RULES
Service Bulletin A300–57A6087 .........................................
(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 account.airwortheas@airbus.com; Internet https://
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: https://www.archives.gov/federal_register/
code_of_federal_regulations/
ibr_locations.html.
VerDate Mar<15>2010
14:39 Nov 30, 2010
Jkt 223001
Issued in Renton, Washington, on
November 3, 2010.
Dionne Palermo,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
DEPARTMENT OF TRANSPORTATION
[FR Doc. 2010–28589 Filed 11–30–10; 8:45 am]
[Docket No. FAA–2007–28348; Directorate
Identifier 2007–NM–060–AD; Amendment
39–16530; AD 2010–24–11]
BILLING CODE 4910–13–P
PO 00000
Federal Aviation Administration
14 CFR Part 39
RIN 2120–AA64
Airworthiness Directives; The Boeing
Company Model 737–600, –700, –700C,
–800, and –900 Series Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
AGENCY:
The FAA is adopting a new
airworthiness directive (AD) for certain
Model 737–600, –700, –700C, –800, and
–900 series airplanes. This AD requires
sealing the fasteners on the front and
SUMMARY:
Frm 00010
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01DER1
]]>Agencies
[Federal Register Volume 75, Number 230 (Wednesday, December 1, 2010)]
[Rules and Regulations]
[Pages 74610-74616]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2010-28589]
=======================================================================
-----------------------------------------------------------------------
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.
-----------------------------------------------------------------------
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 https://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 https://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--
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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.
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(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 account.airworth-eas@airbus.com;
Internet https://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: https://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
