Airworthiness Directives; Airbus Airplanes, 26937-26943 [2012-9189]
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Federal Register / Vol. 77, No. 89 / Tuesday, May 8, 2012 / Rules and Regulations
originating from the official
establishment has entered commerce, if
the official establishment believes or has
reason to believe that this has
happened. The official establishment
must inform the District Office of the
type, amount, origin, and destination of
the adulterated or misbranded product.
§ 418.3 Preparation and maintenance of
written recall procedures.
Each official establishment must
prepare and maintain written
procedures for the recall of any meat,
meat food, poultry, or poultry product
produced and shipped by the official
establishment. These written procedures
must specify how the official
establishment will decide whether to
conduct a product recall, and how the
establishment will effect the recall,
should it decide that one is necessary.
§ 418.4
Records.
All records, including records
documenting procedures required by
this part, must be available for official
review and copying.
Done in Washington, DC, on May 1, 2012.
Alfred V. Almanza,
Administrator.
[FR Doc. 2012–10917 Filed 5–7–12; 8:45 am]
BILLING CODE 3410–DM–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2011–1066; Directorate
Identifier 2011–NM–050–AD; Amendment
39–16917; AD 2012–01–05]
RIN 2120–AA64
Airworthiness Directives; Airbus
Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
AGENCY:
We are superseding an
existing airworthiness directive (AD) for
certain Airbus Model A300 B2–1C,
B2K–3C, B2–203, B4–2C, B4–103, and
B4–203 airplanes; and Model A300 B4–
601, B4–603, B4–620, B4–622, B4–605R,
B4–622R, and F4–605R airplanes. That
AD currently requires repetitive
inspections for cracking in Gear Rib 5 of
the main landing gear (MLG) attachment
fittings at the lower flange, and repair if
necessary; and provides an optional
spot-facing modification around certain
fastener holes, which would terminate
certain repetitive inspections. This new
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SUMMARY:
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AD mandates the optional spot-facing
modification. This AD was prompted by
new cases of cracks discovered during
scheduled maintenance checks. We are
issuing this AD to prevent cracking of
the Gear Rib 5 right-hand and left-hand
attachment fitting at the lower flanges of
the MLG, which could result in failed
bolts penetrating through the rear spar
and into a fuel tank, consequent fuel
loss, and reduced structural integrity of
the airplane.
DATES: This AD becomes effective June
12, 2012.
The Director of the Federal Register
approved the incorporation by reference
of certain publications listed in this AD
as of June 12, 2012.
The Director of the Federal Register
approved the incorporation by reference
of certain other publications listed in
this AD as of January 5, 2011 (75 FR
74610, December 1, 2010).
The Director of the Federal Register
approved the incorporation by reference
of certain other publications listed in
this AD as of July 18, 2006 (71 FR
33994, June 13, 2006).
The Director of the Federal Register
approved the incorporation by reference
of certain other publications listed in
this AD as of April 12, 2000 (65 FR
12077, March 8, 2000).
The Director of the Federal Register
approved the incorporation by reference
of certain other publications listed in
this AD as of October 20, 1999 (64 FR
49966, September 15, 1999).
ADDRESSES: You may examine the AD
docket on the Internet at 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 October 11, 2011 (76 FR
62673), and proposed to supersede AD
2010–23–26, Amendment 39–16516 (75
FR 74610, December 1, 2010). That
NPRM proposed to correct an unsafe
condition for the specified products.
The MCAI states:
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26937
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)
was issued to require repetitive inspections
and, as terminating action, the embodiment
of Airbus Service Bulletins (SB) A300–57–
0235 and A300–57–6088 * * *.
Subsequently, new cases of cracks were
discovered during scheduled maintenance
checks by operators of A300B4 and A300–
600 type aeroplanes on which the
terminating action SB’s were embodied. This
condition, if not corrected, could affect the
structural integrity of those aeroplanes.
To address and correct this condition,
Airbus developed an inspection programme
for aeroplanes modified in accordance with
SB A300–57–0235 or A300–57–6088. This
inspection programme was required to be
implemented by DGAC France AD F–2005–
113, original issue and later revision 1
[parallel to part of FAA AD 2006–12–13,
Amendment 39–14639 (71 FR 33994, June
13, 2006)].
A new EASA [European Aviation Safety
Agency] AD 2008–0111, superseding DGAC
France AD F–2005–113R1, was issued to
reduce the applicability. For aeroplanes
already compliant with DGAC France AD F–
2005–113R1, no further action was required.
Since EASA AD 2008–0111 issuance,
Airbus reviewed the inspection programmes
of SB A300–57A0246 and SB A300–57A6101
to introduce repetitive inspections including
a new inspection technique for holes 47 and
54 and to reduce inspections threshold and
intervals from 700 Flight Cycles (FC) to 400
FC until a revised terminating action is made
available.
For the reasons stated above, EASA AD
2009–0081 superseded EASA AD 2008–0111
and required operators to comply with the
new inspection programme introduced in
Revisions 3 of Airbus SB A300–57A0246 and
Airbus SB A300–57A6101.
EASA AD 2009–0081 R1 [which
corresponds to FAA AD 2010–23–26,
Amendment 39–16516 (75 FR 74610,
December 1, 2010)] has been published to
introduce an optional terminating action
which consisted of spot-facing the sensitive
holes of the MLG Rib 5 (LH and RH) bottom
flanges.
Later discussions with Airbus have
demonstrated the necessity to require the
spot-facing modification as a final solution
(no longer optional). This new [EASA] AD
retains the inspection requirements of EASA
AD 2009–0081 R1, which is superseded, and
requires the spot-facing of sensitive holes of
the MLG Rib 5 (LH and RH) bottom flanges
as terminating action.
Required actions include repairing
discrepancies (e.g., cracking or a second
oversize or greater fastener hole). You
may obtain further information by
examining the MCAI in the AD docket.
Comments
We gave the public the opportunity to
participate in developing this AD. We
considered the comment received. The
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commenter supports the NPRM (76 FR
62673, October 11, 2011).
Explanation of Changes Made to This
AD
We have made the following changes
to this AD. These changes have not
changed the intent of any provisions
specified in this AD.
• Revised certain headers throughout
this AD.
• Redesignated Notes 1, 2, and 3 of
the NPRM (76 FR 62673, October 11,
2011) as paragraphs (g)(3), (q)(1), and
(q)(2) of this AD, respectively.
• Redesignated paragraph (n) of the
NPRM (76 FR 62673, October 11, 2011)
as paragraph (q)(3) of this AD, and
redesignated subsequent paragraphs
accordingly.
• We have revised paragraphs (g), (i),
(o)(1), (o)(3), (o)(4), and (o)(5) of this AD
to clarify the specific actions for which
the specified service information is
required.
• We have revised the headings of
Tables 1, 2, 3, 4, 5, and 6 of this AD to
clarify the purpose of the content in
those tables.
• We have revised the wording in
paragraphs (q)(1), (q)(2), (q)(3), and
(q)(4) of this AD (Notes 2 and 3 and
paragraphs (n) and (r) of the NPRM (76
FR 62673, October 11, 2011),
respectively); this change has not
changed the intent of these paragraphs.
Conclusion
We reviewed the available data,
including the comment received, and
determined that air safety and the
public interest require adopting the AD
with the changes described previously—
and minor editorial changes. We have
determined that these minor changes:
• Are consistent with the intent that
was proposed in the NPRM (76 FR
62673, October 11, 2011) for correcting
the unsafe condition; and
• Do not add any additional burden
upon the public than was already
proposed in the NPRM (76 FR 62673,
October 11, 2011).
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Costs of Compliance
We estimate that this AD will affect
about 155 products of U.S. registry.
The actions that are required by AD
2010–23–26, Amendment 39–16516 (75
FR 74610, December 1, 2010), and
retained in this AD take about 79 workhours per product, at an average labor
rate of $85 per work hour. Required
parts cost about $10,270 per product.
Based on these figures, the estimated
cost of the currently required actions is
$16,985 per product.
We estimate that it will take about 100
work-hours per product to comply with
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the new basic requirements of this AD.
The average labor rate is $85 per workhour. Based on these figures, we
estimate the cost of the AD on U.S.
operators to be $1,317,500, or $8,500 per
product.
Authority for This Rulemaking
Title 49 of the United States Code
specifies the FAA’s authority to issue
rules on aviation safety. Subtitle I,
section 106, describes the authority of
the FAA Administrator. ‘‘Subtitle VII:
Aviation Programs,’’ describes in more
detail the scope of the Agency’s
authority.
We are issuing this rulemaking under
the authority described in ‘‘Subtitle VII,
Part A, Subpart III, Section 44701:
General requirements.’’ Under that
section, Congress charges the FAA with
promoting safe flight of civil aircraft in
air commerce by prescribing regulations
for practices, methods, and procedures
the Administrator finds necessary for
safety in air commerce. This regulation
is within the scope of that authority
because it addresses an unsafe condition
that is likely to exist or develop on
products identified in this rulemaking
action.
Regulatory Findings
We determined that this AD will not
have federalism implications under
Executive Order 13132. This AD will
not have a substantial direct effect on
the States, on the relationship between
the national government and the States,
or on the distribution of power and
responsibilities among the various
levels of government.
For the reasons discussed above, I
certify this AD:
1. Is not a ‘‘significant regulatory
action’’ under Executive Order 12866;
2. Is not a ‘‘significant rule’’ under the
DOT Regulatory Policies and Procedures
(44 FR 11034, February 26, 1979); and
3. Will not have a significant
economic impact, positive or negative,
on a substantial number of small entities
under the criteria of the Regulatory
Flexibility Act.
We prepared a regulatory evaluation
of the estimated costs to comply with
this AD and placed it in the AD docket.
Examining the AD Docket
You may examine the AD docket on
the Internet at 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 (76 FR 62673,
October 11, 2011), the regulatory
evaluation, any comments received, and
other information. The street address for
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the Docket Operations office (telephone
(800) 647–5527) is in the ADDRESSES
section. Comments will be available in
the AD docket shortly after receipt.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation
safety, Incorporation by reference,
Safety.
Adoption of the Amendment
Accordingly, under the authority
delegated to me by the Administrator,
the FAA amends 14 CFR part 39 as
follows:
PART 39—AIRWORTHINESS
DIRECTIVES
1. The authority citation for part 39
continues to read as follows:
■
Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13
[Amended]
2. The FAA amends § 39.13 by
removing Amendment 39–16516 (75 FR
74610, December 1, 2010) and adding
the following new AD:
■
2012–01–05 Airbus: Amendment 39–16917.
Docket No. FAA–2011–1066; Directorate
Identifier 2011–NM–050–AD.
(a) Effective Date
This airworthiness directive (AD) becomes
effective June 12, 2012.
(b) Affected ADs
This AD supersedes AD 2010–23–26,
Amendment 39–16516 (75 FR 74610,
December 1, 2010).
(c) Applicability
This AD applies to the airplanes,
certificated in any category, identified in
paragraphs (c)(1) and (c)(2) of this AD; except
airplanes on which Airbus Modification
11912 or 11932 has been installed.
(1) Airbus Model A300 B2–1C, B2K–3C,
B2–203, B4–2C, B4–103, and B4–203
airplanes.
(2) Airbus Model A300 B4–601, B4–603,
B4–620, B4–622, B4–605R, B4–622R, and
F4–605R airplanes.
(d) Subject
Air Transport Association (ATA) of
America Code 57: Wings.
(e) Reason
This AD was prompted by new cases of
cracks discovered during scheduled
maintenance checks. We are issuing this AD
to prevent cracking of the Gear Rib 5 righthand and left-hand attachment fitting at the
lower flanges of the main landing gear
(MLG), which could result in failed bolts
penetrating through the rear spar and into a
fuel tank, consequent fuel loss, and reduced
structural integrity of the airplane.
(f) Compliance
You are responsible for having the actions
required by this AD performed within the
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compliance times specified, unless the
actions have already been done.
(g) Retained Repetitive Inspections
This paragraph restates the requirements of
paragraph (g) of AD 2010–23–26,
Amendment 39–16516 (75 FR 74610,
December 1, 2010). Perform a detailed
inspection and a high-frequency eddy current
(HFEC) inspection to detect cracks in Gear
Rib 5 of the MLG attachment fittings at the
lower flange, in accordance with the
Accomplishment Instructions of any
applicable service bulletin listed in table 1
and table 2 of this AD, at the time specified
in paragraph (g)(1) or (g)(2) of this AD. After
April 12, 2000 (the effective date of AD
2000–05–07, Amendment 39–11616 (65 FR
12077, March 8, 2000)), the service bulletins
listed in table 2 of this AD must be used to
accomplish the actions required by this
paragraph. Repeat the inspections thereafter
at intervals not to exceed 1,500 flight cycles,
until the actions specified in paragraph (i),
(j), or (l) of this AD are accomplished.
TABLE 1—REVISION 01 OF SERVICE BULLETINS FOR PARAGRAPH (g) OF THIS AD
Model—
Airbus Service Bulletin—
Revision—
Dated—
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
A300-57-6087 .................................
01
March 11, 1998.
A300–57–0234 ...............................
01
March 11, 1998.
TABLE 2—OTHER REVISIONS OF SERVICE BULLETINS FOR PARAGRAPH (g) OF THIS AD
Model—
Airbus Service Bulletin—
B4-605R,
A300 B2-1C, B2K–3C, B2-203, B4-2C, B4-103, and
B4-203 airplanes.
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(1) For airplanes that have accumulated
20,000 or more total flight cycles as of March
9, 1998 (the effective date of AD 98–03–06,
Amendment 39–10298 (63 FR 5224, February
2, 1998)): Inspect within 500 flight cycles
after March 9, 1998.
(2) For airplanes that have accumulated
less than 20,000 total flight cycles as of
March 9, 1998 (the effective date of AD 98–
03–06, Amendment 39–10298 (63 FR 5224,
February 2, 1998)): Inspect prior to the
accumulation of 18,000 total flight cycles, or
within 1,500 flight cycles after March 9,
1998, whichever occurs later.
(3) For the purposes of this AD, a detailed
inspection is defined as: ‘‘An intensive visual
examination of a specific structural area,
system, installation, or assembly to detect
damage, failure, or irregularity. Available
lighting is normally supplemented with a
direct source of good lighting at intensity
deemed appropriate by the inspector.
Inspection aids such as mirror, magnifying
lenses, etc., may be used. Surface cleaning
and elaborate access procedures may be
required.’’
A300-57A6087 ......................
02, including Appendix 01 ....
June 24, 1999.
May 19, 2000.
February 19, 2002.
March 10, 2008.
02
June 24, 1999.
03, including Appendix 01 ....
04, including Appendix 01 ....
05, including Appendix 01 ....
B4-622,
Dated—
03, including Appendix 01 ....
04, including Appendix 01 ....
05, including Appendix 01 ....
A300 B4-601, B4-603, B4-620,
B4-622R, and F4-605R airplanes.
Revision—
September 2, 1999.
May 19, 2000.
February 19, 2002.
A300-57A0234 ......................
(h) Retained Repair for Any Crack Found
During Inspections Required by Paragraph
(g) of This AD
This paragraph restates the requirements of
paragraph (h) of AD 2010–23–26,
Amendment 39–16516 (75 FR 74610,
December 1, 2010). If any crack is detected
during any inspection required by paragraph
(g) of this AD, prior to further flight,
accomplish the requirements of paragraph
(h)(1) or (h)(2) of this AD, as applicable.
(1) If a crack is detected at one hole only,
and the crack does not extend out of the
spotface of the hole, repair in accordance
with the Accomplishment Instructions of the
applicable service bulletin in table 2 of this
AD.
(2) If a crack is detected at more than one
hole, or if any crack at any hole extends out
of the spotface of the hole, repair in
accordance with a method approved by the
Manager, International Branch, ANM–116,
Transport Airplane Directorate, FAA, or the
European Aviation Safety Agency (EASA) (or
its delegated agent).
(i) Retained Terminating Modification for
Repetitive Inspections Required by
Paragraphs (g) and (j) of This AD
This paragraph restates the requirements of
paragraph (i) of AD 2010–23–26, Amendment
39–16516 (75 FR 74610, December 1, 2010).
Except as required by paragraph (l) of this
AD, prior to the accumulation of 21,000 total
flight cycles, or within 2 years after October
20, 1999 (the effective date of AD 99–19–26,
Amendment 39–11313 (64 FR 49966,
September 15, 1999)), whichever occurs later:
Modify Gear Rib 5 of the MLG attachment
fittings at the lower flange in accordance
with the Accomplishment Instructions of the
applicable service bulletin in table 3 of this
AD. After July 18, 2006 (the effective date of
AD 2006–12–13, Amendment 39–14639 (71
FR 33994, June 13, 2006)), Airbus Service
Bulletin A300–57–6088, Revision 04, dated
December 3, 2003 (for Model A300 B4–601,
B4–603, B4–620, B4–622, B4–605R, B4–
622R, and F4–605R airplanes); and Airbus
Service Bulletin A300–57–0235, Revision 04,
dated March 13, 2003, or Revision 05, dated
December 3, 2003 (for Model A300 B2–1C,
B2K–3C, B2–203, B4–2C, B4–103, and B4–
203 airplanes); must be used to accomplish
the actions required by this paragraph.
Accomplishment of this modification
constitutes terminating action for the
repetitive inspection requirements of
paragraphs (g) and (j) of this AD.
TABLE 3—SERVICE BULLETINS FOR TERMINATING MODIFICATION REQUIRED BY PARAGRAPH (i) OF THIS AD
Model—
Airbus Service Bulletin—
Revision—
Dated—
A300 B4–601, B4–603, B4–620, B4–622, B4–605R, B4–
622R, and F4–605R airplanes.
A300–57–6088 .....................
01, including Appendix 01 ....
February 1, 1999.
02
September 5, 2002.
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TABLE 3—SERVICE BULLETINS FOR TERMINATING MODIFICATION REQUIRED BY PARAGRAPH (i) OF THIS AD—Continued
Model—
Airbus Service Bulletin—
Revision—
Dated—
04
December 3, 2003.
01, including Appendix 01 ....
February 1, 1999.
03
04
05
September 5, 2002.
March 13, 2003.
December 3, 2003.
effective date of AD 2006–12–13,
Amendment 39–14639 (71 FR 33994, June
13, 2006)), perform a detailed and an HFEC
inspection to detect cracks of the lower
flange of Gear Rib 5 of the MLG at holes 43,
47, 48, 49, 50, 52, and 54, in accordance with
the applicable service bulletin listed in table
4 of this AD. Perform the inspections at the
applicable time specified in paragraph (j)(1),
(j)(2), (j)(3), or (j)(4) of this AD. Repeat the
inspections thereafter at intervals not to
exceed 700 flight cycles until the terminating
modification required by paragraph (l) of this
AD is accomplished. Accomplishment of the
inspections per paragraph (j) of this AD
terminates the inspection requirements of
paragraph (g) of this AD.
A300 B2–1C, B2K–3C, B2–203, B4–2C, B4–103, and B4–
203 airplanes.
(j) Retained Additional Repetitive
Inspections
This paragraph restates the requirements of
paragraph (j) of AD 2010–23–26, Amendment
39–16516 (75 FR 74610, December 1, 2010).
For airplanes on which the modification
specified in paragraph (i) or (l) of this AD has
not been done before July 18, 2006 (the
A300–57–0235 .....................
TABLE 4—SERVICE BULLETINS FOR REPETITIVE INSPECTIONS REQUIRED BY PARAGRAPH (j) OF THIS AD
Model—
Airbus Service Bulletin—
Revision—
Dated—
A300 B4–601, B4–603, B4–620, B4–622, B4–605R, B4–
622R, and F4–605R airplanes.
A300–57A6087 .....................
04, including Appendix 01 ....
February 19, 2002.
05, including Appendix 01
March 10, 2008.
05, including Appendix 01 ....
February 19, 2002.
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A300 B2–1C, B2K–3C, B2–203, B4–2C, B4–103, and B4–
203 airplanes.
(1) For Model A300 B2–1C, B2K–3C, B2–
203, B4–2C, B4–103, and B4–203 airplanes;
and Model A300 B4–601, B4–603, B4–620,
B4–622, B4–605R, B4–622R, and F4–605R
airplanes that have accumulated 18,000 or
more total flight cycles as of July 18, 2006
(the effective date of AD 2006–12–13,
Amendment 39–14639 (71 FR 33994, June
13, 2006)): Within 700 flight cycles after July
18, 2006.
(2) For Model A300 B2–1C, B2K–3C, and
B2–203 airplanes that have accumulated less
than 18,000 total flight cycles as of July 18,
2006 (the effective date of AD 2006–12–13,
Amendment 39–14639 (71 FR 33994, June
13, 2006)): Prior to the accumulation of
18,000 total flight cycles, or within 700 flight
cycles after July 18, 2006, whichever occurs
later.
(3) For Model A300 B4–2C, B4–103, and
B4–203 airplanes that have accumulated less
than 18,000 total flight cycles as of July 18,
2006 (the effective date of AD 2006–12–13,
Amendment 39–14639 (71 FR 33994, June
13, 2006)): Prior to the accumulation of
14,500 total flight cycles, or within 700 flight
cycles after July 18, 2006, whichever occurs
later.
(4) For Model A300 B4–601, B4–603, B4–
620, B4–622, B4–605R, B4–622R, and F4–
605R airplanes that have accumulated less
than 18,000 total flight cycles as of July 18,
2006 (the effective date of AD 2006–12–13,
Amendment 39–14639 (71 FR 33994, June
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A300–57A0234 .....................
13, 2006)): Prior to the accumulation of
11,600 total flight cycles, or within 700 flight
cycles after July 18, 2006, whichever occurs
later.
(l) Retained Terminating Modification for
Repetitive Inspections Required by
Paragraphs (g) and (j) of This AD for Certain
Airplanes
(k) Retained Crack Repair
This paragraph restates the requirements of
paragraph (k) of AD 2010–23–26,
Amendment 39–16516 (75 FR 74610,
December 1, 2010). If any crack is detected
during any inspection required by paragraph
(j) of this AD, prior to further flight,
accomplish the requirements of paragraphs
(k)(1) and (k)(2) of this AD, as applicable.
(1) If a crack is detected at only one hole,
and the crack does not extend out of the
spotface of the hole, repair in accordance
with Airbus Service Bulletin A300–57A0234,
Revision 05, including Appendix 01, dated
February 19, 2002 (for Model A300 B2–1C,
B2K–3C, B2–203, B4–2C, B4–103, and B4–
203 airplanes); or A300–57A6087, Revision
04, including Appendix 01, dated February
19, 2002, or A300–57A6087, Revision 05,
including Appendix 01, dated March 10,
2008 (for Model A300 B4–601, B4–603, B4–
620, B4–622, B4–605R, B4–622R, and F4–
605R airplanes).
(2) If a crack is detected at more than one
hole, or if any crack at any hole extends out
of the spotface of the hole, repair in
accordance with a method approved by the
Manager, International Branch, ANM–116, or
the EASA (or its delegated agent).
This paragraph restates the requirements of
paragraph (l) of AD 2010–23–26, Amendment
39–16516 (75 FR 74610, December 1, 2010).
For airplanes on which the terminating
modification in paragraph (i) of this AD has
not been accomplished before July 18, 2006
(the effective date of AD 2006–12–13,
Amendment 39–14639 (71 FR 33994, June
13, 2006)): At the earlier of the times
specified in paragraphs (l)(1) and (l)(2) of this
AD, modify Gear Rib 5 of the MLG
attachment fittings at the lower flange.
Except as provided by paragraph (m) of this
AD, do the modification in accordance with
the applicable service bulletin identified in
table 5 of this AD. This action terminates the
repetitive inspections requirements of
paragraphs (g) and (j) of this AD.
(1) Prior to the accumulation of 21,000
total flight cycles, or within 2 years after
October 20, 1999 (the effective date of AD
99–19–26, Amendment 39–11313 (64 FR
49966, September 15, 1999)), whichever is
later.
(2) Within 16 months after July 18, 2006
(the effective date of AD 2006–12–13,
Amendment 39–14639 (71 FR 33994, June
13, 2006)).
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Federal Register / Vol. 77, No. 89 / Tuesday, May 8, 2012 / Rules and Regulations
TABLE 5—SERVICE BULLETINS FOR TERMINATING MODIFICATION REQUIRED BY PARAGRAPH (l) OF THIS AD
Model—
Airbus Service Bulletin—
Revision—
Dated—
A300 B4–601, B4–603, B4–620, B4–622, B4–605R, B4–622R and F4–
605R airplanes.
A300–57–6088 ...............................
04
December 3,
2003.
A300 B2–1C, B2K–3C, B2–203, B4–2C, B4–103, and B4–203 airplanes.
A300–57–0235 ...............................
04
March 13, 2003.
05
December 3,
2003.
(m) Retained Modification
This paragraph restates the requirements of
paragraph (m) of AD 2010–23–26,
Amendment 39–16516 (75 FR 74610,
December 1, 2010). Where the applicable
service bulletin specified in paragraph (l) of
this AD specifies to contact Airbus for
modification instructions; or if there is a
previously installed repair at any of the
affected fastener holes; or if a crack is found
when accomplishing the modification: Prior
to further flight, modify in accordance with
a method approved by the Manager,
International Branch, ANM–116, or the
EASA (or its delegated agent).
mstockstill on DSK4VPTVN1PROD with RULES
(n) Retained Exception for No Reporting
This paragraph restates the requirements of
paragraph (o) of AD 2010–23–26,
Amendment 39–16516 (75 FR 74610,
December 1, 2010). Although the service
bulletins identified in tables 1, 2, 3, 4, 5, and
6 of this AD specify to submit certain
information to the manufacturer, this AD
does not include such a requirement.
(o) Retained Requirements With Revised
Service Information
This paragraph restates the requirements of
paragraph (p) of AD 2010–23–26,
Amendment 39–16516 (75 FR 74610,
December 1, 2010). Unless already done, do
the following actions.
(1) At the applicable time specified in
paragraph (o)(2) of this AD, perform a
detailed inspection for cracking at the
locations specified in paragraphs (o)(1)(i),
(o)(1)(ii), and (o)(1)(iii) of this AD, in
accordance with the Accomplishment
Instructions of Airbus Mandatory Service
Bulletin A300–57A0246, Revision 03,
including Appendices 1 and 2, dated March
11, 2009, or Revision 04, including
Appendices 1 and 2, dated September 9,
2009 (for Model A300 B2–1C, B2K–3C, B2–
203, B4–2C, B4–103, and B4–203 airplanes);
or Airbus Mandatory Service Bulletin A300–
57A6101, Revision 03, including Appendices
1 and 2, dated March 11, 2009, or Revision
04, including Appendices 1 and 2, dated
September 9, 2009 (for Model A300 B4–601,
B4–603, B4–620, B4–622, B4–605R, B4–622R
and F4–605R airplanes). As of the effective
date of this AD Revision 04 of these service
bulletins must be used to accomplish the
actions required by this paragraph.
(i) The bottom flange and vertical web in
the area between the wing rear spar/gear Rib
5 attachment and the forward reaction-rod
pick-up lug.
(ii) On the inboard side, around the
fastener holes at locations 43, 47 to 50, 52,
and 54.
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Jkt 226001
(iii) On the outboard side, the lower flange,
the vertical web and around the fastener
holes at locations 43, 47 to 50, 52 and 54.
(2) Do the inspection required by
paragraph (o)(1) of this AD at the later of the
times in paragraphs (o)(2)(i) and (o)(2)(ii) of
this AD.
(i) Within 400 flight cycles after the
accomplishment of the actions required by
paragraph (i) or (l) of this AD, as applicable.
(ii) Within 400 flight cycles or 4 months
after January 5, 2011 (the effective date of AD
2010–23–26, Amendment 39–16516 (75 FR
74610, December 1, 2010)), whichever occurs
first.
(3) If no cracking is detected during the
inspection required by paragraph (o)(1) of
this AD, before further flight, perform a
fluorescent penetrant inspection (FPI) at
holes location 47 and 54, in the right-hand
and left-hand MLG Rib 5 attachment fitting
lower flange, in accordance with the
Accomplishment Instructions of Airbus
Mandatory Service Bulletin A300–57A0246,
Revision 03, including Appendices 1 and 2,
dated March 11, 2009, or Revision 04,
including Appendices 1 and 2, dated
September 9, 2009 (for Model A300 B2–1C,
B2K–3C, B2–203, B4–2C, B4–103, and B4–
203 airplanes); or Airbus Mandatory Service
Bulletin A300–57A6101, Revision 03,
including Appendices 1 and 2, dated March
11, 2009, or Revision 04, including
Appendices 1 and 2, dated September 9,
2009 (for Model A300 B4–601, B4–603, B4–
620, B4–622, B4–605R, B4–622R and F4–
605R airplanes). As of the effective date of
this AD, Airbus Mandatory Service Bulletin
A300–57A0246, Revision 04, including
Appendices 1 and 2, dated September 9,
2009; or Airbus Mandatory Service Bulletin
A300–57A6101, Revision 04, including
Appendices 1 and 2, dated September 9,
2009; as applicable; must be used to
accomplish the actions required by this
paragraph.
(4) Thereafter, at intervals not to exceed
400 flight cycles, repeat the detailed and FPI
inspections, in accordance with the
Accomplishment Instructions of Airbus
Mandatory Service Bulletin A300–57A0246,
Revision 03, including Appendices 1 and 2,
dated March 11, 2009, or Revision 04,
including Appendices 1 and 2, dated
September 9, 2009 (for Model A300 B2–1C,
B2K–3C, B2–203, B4–2C, B4–103, and B4–
203 airplanes); or Airbus Mandatory Service
Bulletin A300–57A6101, Revision 03,
including Appendices 1 and 2, dated March
11, 2009, or Revision 04, including
Appendices 1 and 2, dated September 9,
2009 (for Model A300 B4–601, B4–603, B4–
620, B4–622, B4–605R, B4–622R and F4–
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605R airplanes); until the terminating action
required by paragraph (p) of this AD has been
accomplished. As of the effective date of this
AD, Airbus Mandatory Service Bulletin
A300–57A0246, Revision 04, including
Appendices 1 and 2, dated September 9,
2009; or Airbus Mandatory Service Bulletin
A300–57A6101, Revision 04, including
Appendices 1 and 2, dated September 9,
2009; as applicable; must be used to
accomplish the actions required by this
paragraph.
(5) If any crack is detected during any of
the inspections required by paragraphs (o)(1),
(o)(3), and (o)(4) of this AD, and Airbus
Mandatory Service Bulletin A300–57A0246,
Revision 03, including Appendices 1 and 2,
dated March 11, 2009, or Revision 04,
including Appendices 1 and 2, dated
September 9, 2009 (for Model A300 B2–1C,
B2K–3C, B2–203, B4–2C, B4–103, and B4–
203 airplanes); or Airbus Mandatory Service
Bulletin A300–57A6101, Revision 03,
including Appendices 1 and 2, dated March
11, 2009, or Revision 04, including
Appendices 1 and 2, dated September 9,
2009 (for Model A300 B4–601, B4–603, B4–
620, B4–622, B4–605R, B4–622R and F4–
605R airplanes); recommends contacting
Airbus for appropriate action: Before further
flight, contact Airbus for a repair solution,
and do the repair; or repair the cracking
using a method approved by the Manager,
International Branch, ANM–116, Transport
Airplane Directorate, FAA, or EASA (or its
delegated agent).
(p) New Terminating Action
Within 30 months after the effective date
of this AD: Modify the spot-faces around all
the fastener holes at locations 43, 47 to 50,
52, and 54 (except for spot-faces of holes
which have been previously repaired) on the
bottom flange MLG ribs, in accordance with
the Accomplishment Instructions of Airbus
Mandatory Service Bulletin A300–57–0254,
Revision 01, including Appendix 1, dated
June 14, 2011 (for Model A300 B2–1C, B2K–
3C, B2–203, B4–2C, B4–103, and B4–203
airplanes); or Airbus Mandatory Service
Bulletin A300–57–6110, Revision 01,
including Appendix 1, dated June 6, 2011
A300 B4–601, B4–603, B4–620, B4–622, B4–
605R, B4–622R and F4–605R airplanes (for
Model A300 B4–601, B4–603, B4–620, B4–
622, B4–605R, B4–622R and F4–605R
airplanes). Accomplishing this modification
terminates the repetitive inspection
requirements of paragraph (o)(4) of this AD.
(q) Credit for Previous Actions
(1) This paragraph provides credit for
initial detailed and HFEC inspections, as
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required by the introductory text of
paragraph (g) of this AD, if those inspections
were performed before April 12, 2000 (the
effective date of AD 2000–05–07,
Amendment 39–11616 (65 FR 12077, March
8, 2000)), using Airbus Service Bulletin
A300–57A0234 (for Model A300 B2–1C,
B2K–3C, B2–203, B4–2C, B4–103, and B4–
203 airplanes) or A300–57A6087, both dated
August 5, 1997 (for Model A300 B4–601, B4–
603, B4–620, B4–622, B4–605R, B4–622R,
and F4–605R airplanes).
(2) This paragraph provides credit for a
modification, as required by paragraph (i) of
this AD, if the modification was performed
before April 12, 2000 (the effective date of
AD 2000–05–07, Amendment 39–11616 (65
FR 12077, March 8, 2000)), using Airbus
Service Bulletin A300–57–6088, dated
August 5, 1998 (for Model A300 B4–601, B4–
603, B4–620, B4–622, B4–605R, B4–622R and
F4–605R airplanes); or Airbus Service
Bulletin A300–57–0235, dated August 5,
1998 (for Model A300 B2–1C, B2K–3C, B2–
203, B4–2C, B4–103, and B4–203 airplanes).
(3) This paragraph provides credit for the
actions required by paragraphs (i) and (l) of
this AD, if those actions were performed
before July 18, 2006 (the effective date of AD
2006–12–13, Amendment 39–14639 (71 FR
33994, June 13, 2006)), using the applicable
service information listed in table 6 of this
AD.
TABLE 6—PREVIOUS ISSUES OF CERTAIN SERVICE BULLETINS
Model—
Airbus Service Bulletin—
Revision—
Dated—
A300 B2–1C, B2K–3C, B2–203, B4–2C, B4–103, and B4–
203 airplanes.
A300–57–0235 .....................
02, including Appendix 01 ....
03
September 27,
1999.
September 5, 2002.
02 ..........................................
September 5, 2000.
03 ..........................................
March 13, 2003.
A300 B4–601, B4–603, B4–620, B4–622, B4–605R, B4–
622R and F4–605R airplanes.
mstockstill on DSK4VPTVN1PROD with RULES
(4) This paragraph provides credit for a
modification of the spot-faces, as specified in
paragraph (p) of this AD, if the modification
was performed before the effective date of
this AD using Airbus Mandatory Service
Bulletin A300–57–0254, dated June 4, 2010
(for Model A300 B2–1C, B2K–3C, B2–203,
B4–2C, B4–103, and B4–203 airplanes); or
Airbus Mandatory Service Bulletin A300–57–
6110, dated June 7, 2010 (for Model A300
B4–601, B4–603, B4–620, B4–622, B4–605R,
B4–622R and F4–605R airplanes).
(r) Other FAA AD Provisions
The following provisions also apply to this
AD:
(1) Alternative Methods of Compliance
(AMOCs): The Manager, International
Branch, ANM–116, FAA, has the authority to
approve AMOCs for this AD, if requested
using the procedures found in 14 CFR 39.19.
In accordance with 14 CFR 39.19, send your
request to your principal inspector or local
Flight Standards District Office, as
appropriate. If sending information directly
to the International Branch, send it to ATTN:
Dan Rodina, Aerospace Engineer,
International Branch, ANM–116, Transport
Airplane Directorate, FAA, 1601 Lind
Avenue SW., Renton, Washington 98057–
3356; telephone (425) 227–2125; fax (425)
227–1149. Information may be emailed to: 9ANM-116-AMOC-REQUESTS@faa.gov.
Before using any approved AMOC, notify
your appropriate principal inspector, or
lacking a principal inspector, the manager of
the local flight standards district office/
certificate holding district office. The AMOC
approval letter must specifically reference
this AD. AMOCs approved previously in
accordance with AD 2000–05–07,
Amendment 39–11616 (65 FR 12077, March
8, 2000); AD 2006–12–13, Amendment 39–
14639 (71 FR 33994, June 13, 2006); and AD
2010–23–26, Amendment 39–16516 (75 FR
74610, December 1, 2010); are approved as
AMOCs for the corresponding provisions of
this AD.
(2) Airworthy Product: For any requirement
in this AD to obtain corrective actions from
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16:28 May 07, 2012
Jkt 226001
A300–57–6088 .....................
a manufacturer or other source, use these
actions if they are FAA-approved. Corrective
actions are considered FAA-approved if they
are approved by the State of Design Authority
(or their delegated agent). You are required
to assure the product is airworthy before it
is returned to service.
(s) Related Information
Refer to MCAI EASA Airworthiness
Directive 2011–0029, dated February 24,
2011, and the service information specified
in paragraphs (s)(1) through (s)(23) of this
AD, for related information.
(1) Airbus Service Bulletin A300–57–0234,
Revision 01, dated March 11, 1998.
(2) Airbus Service Bulletin A300–57A0234,
Revision 02, dated June 24, 1999.
(3) Airbus Service Bulletin A300–57A0234,
Revision 03, including Appendix 01, dated
September 2, 1999.
(4) Airbus Service Bulletin A300–57A0234,
Revision 04, including Appendix 01, dated
May 19, 2000.
(5) Airbus Service Bulletin A300–57A0234,
Revision 05, including Appendix 01, dated
February 19, 2002.
(6) Airbus Service Bulletin A300–57–0235,
Revision 01, including Appendix 01, dated
February 1, 1999.
(7) Airbus Service Bulletin A300–57–0235,
Revision 03, dated September 5, 2002.
(8) Airbus Service Bulletin A300–57–0235,
Revision 04, dated March 13, 2003.
(9) Airbus Service Bulletin A300–57–0235,
Revision 05, dated December 3, 2003.
(10) Airbus Mandatory Service Bulletin
A300–57A0246, Revision 03, including
Appendices 1 and 2, dated March 11, 2009.
(11) Airbus Mandatory Service Bulletin
A300–57A0246, Revision 04, including
Appendices 1 and 2, dated September 9,
2009.
(12) Airbus Mandatory Service Bulletin
A300–57–0254, Revision 01, including
Appendix 1, dated June 14, 2011.
(13) Airbus Service Bulletin A300–57–
6087, Revision 01, dated March 11, 1998.
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(14) Airbus Service Bulletin A300–
57A6087, Revision 02, including Appendix
01, dated June 24, 1999.
(15) Airbus Service Bulletin A300–
57A6087, Revision 03, including Appendix
01, dated May 19, 2000.
(16) Airbus Service Bulletin A300–
57A6087, Revision 04, including Appendix
01, dated February 19, 2002.
(17) Airbus Service Bulletin A300–
57A6087, Revision 05, including Appendix
01, dated March 10, 2008.
(18) Airbus Service Bulletin A300–57–
6088, Revision 01, including Appendix 01,
dated February 1, 1999.
(19) Airbus Service Bulletin A300–57–
6088, Revision 02, dated September 5, 2002.
(20) Airbus Service Bulletin A300–57–
6088, Revision 04, dated December 3, 2003.
(21) Airbus Mandatory Service Bulletin
A300–57A6101, Revision 03, including
Appendices 1 and 2, dated March 11, 2009.
(22) Airbus Mandatory Service Bulletin
A300–57A6101, Revision 04, including
Appendices 1 and 2, dated September 9,
2009.
(23) Airbus Mandatory Service Bulletin
A300–57–6110, Revision 01, including
Appendix 1, dated June 6, 2011.
(t) Material Incorporated by Reference
(1) You must use the following service
information to do the actions required by this
AD, unless the AD specifies otherwise. The
Director of the Federal Register approved the
incorporation by reference (IBR) of the
following service information under 5 U.S.C.
552(a) and 1 CFR part 51 on the date
specified.
(2) The following service information was
approved for IBR on June 12, 2012:
(i) Airbus Mandatory Service Bulletin
A300–57–0254, Revision 01, including
Appendix 1, dated June 14, 2011.
(ii) Airbus Mandatory Service Bulletin
A300–57–6110, Revision 01, including
Appendix 1, dated June 6, 2011.
(3) The following service information was
approved for IBR January 5, 2011 (75 FR
74610, December 1, 2010):
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08MYR1
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Federal Register / Vol. 77, No. 89 / Tuesday, May 8, 2012 / Rules and Regulations
(i) Airbus Mandatory Service Bulletin
A300–57A0246, Revision 03, including
Appendices 1 and 2, dated March 11, 2009.
(ii) Airbus Mandatory Service Bulletin
A300–57A0246, Revision 04, including
Appendices 1 and 2, dated September 9,
2009.
(iii) Airbus Mandatory Service Bulletin
A300–57A6101, Revision 03, including
Appendices 1 and 2, dated March 11, 2009.
(iv) Airbus Mandatory Service Bulletin
A300–57A6101, Revision 04, including
Appendices 1 and 2, dated September 9,
2009.
(v) Airbus Service Bulletin A300–57A6087,
Revision 05, including Appendix 01, dated
March 10, 2008. (Appendix 01 of this
document was incorrectly identified as
‘‘Appendix 05’’ in the document citation
specified in table 8 of AD 2010–23–26,
Amendment 39–16516 (75 FR 74610,
December 1, 2010); all other references to
Appendix 01 of this document in AD 2010–
23–26 were correct.)
(4) The following service information was
approved for IBR July 18, 2006 (71 FR 33994,
June 13, 2006):
(i) Airbus Service Bulletin A300–57A0234,
Revision 04, including Appendix 01, dated
May 19, 2000.
(ii) Airbus Service Bulletin A300–
57A0234, Revision 05, including Appendix
01, dated February 19, 2002.
(iii) Airbus Service Bulletin A300–
57A6087, Revision 03, including Appendix
01, dated May 19, 2000.
(iv) Airbus Service Bulletin A300–
57A6087, Revision 04, including Appendix
01, dated February 19, 2002.
(v) Airbus Service Bulletin A300–57–0235,
Revision 03, dated September 5, 2002.
(vi) Airbus Service Bulletin A300–57–
0235, Revision 04, dated March 13, 2003.
(vii) Airbus Service Bulletin A300–57–
0235, Revision 05, dated December 3, 2003.
(viii) Airbus Service Bulletin A300–57–
6088, Revision 02, dated September 5, 2002.
(ix) Airbus Service Bulletin A300–57–
6088, Revision 04, dated December 3, 2003.
(5) The following service information was
approved for IBR on April 12, 2000 (65 FR
12077, March 8, 2000):
(i) Airbus Service Bulletin A300–57A0234,
Revision 02, dated June 24, 1999.
(ii) Airbus Service Bulletin A300–
57A0234, Revision 03, including Appendix
01, dated September 2, 1999.
(iii) Airbus Service Bulletin A300–
57A6087, Revision 02, including Appendix
01, dated June 24, 1999.
(6) The following service information was
approved for IBR on October 20, 1999 (64 FR
49966, September 15, 1999).
(i) Airbus Service Bulletin A300–57–0234,
Revision 01, dated March 11, 1998.
(ii) Airbus Service Bulletin A300–57–0235,
Revision 01, including Appendix 01, dated
February 1, 1999.
(iii) Airbus Service Bulletin A300–57–
6087, Revision 01, dated March 11, 1998.
(iv) Airbus Service Bulletin A300–57–
6088, Revision 01, including Appendix 01,
dated February 1, 1999.
(7) For service information identified in
this AD, contact Airbus SAS—EAW
(Airworthiness Office), 1 Rond Point Maurice
VerDate Mar<15>2010
16:28 May 07, 2012
Jkt 226001
26943
Bellonte, 31707 Blagnac Cedex, France;
telephone +33 5 61 93 36 96; fax +33 5 61
93 44 51; email account.airwortheas@airbus.com; Internet https://
www.airbus.com.
(8) You may review copies of the service
information at the FAA, Transport Airplane
Directorate, 1601 Lind Avenue SW., Renton,
Washington. For information on the
availability of this material at the FAA, call
425–227–1221.
(9) You may also review copies of the
service information that is incorporated by
reference at the National Archives and
Records Administration (NARA). For
information on the availability of this
material at an NARA facility, call 202–741–
6030, or go to https://www.archives.gov/
federal_register/code_of_federal_regulations/
ibr_locations.html.
ADDRESSES:
Issued in Renton, Washington, on January
6, 2012.
Ali Bahrami,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
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 this AD, the regulatory
evaluation, any comments received, and
other information. The street address for
the Docket Operations office (phone:
800–647–5527) is the same as the Mail
address provided in the ADDRESSES
section. Comments will be available in
the AD docket shortly after receipt.
FOR FURTHER INFORMATION CONTACT: Paul
Craig, Aerospace Engineer, Los Angeles
Aircraft Certification Office, FAA, 3960
Paramount Blvd., Suite 100, Lakewood,
CA 90712; phone: 562–627–5252; fax:
562–627–5210; email:
paul.craig@faa.gov.
[FR Doc. 2012–9189 Filed 5–7–12; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2012–0417; Directorate
Identifier 2012–NE–11–AD; Amendment 39–
17045; AD 2012–09–10]
RIN 2120–AA64
Airworthiness Directives; Pratt &
Whitney Canada Turboprop Engines
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule; request for
comments.
AGENCY:
PO 00000
Frm 00033
Fmt 4700
Sfmt 4700
Examining the AD Docket
SUPPLEMENTARY INFORMATION:
Discussion
We are adopting a new
airworthiness directive (AD) for certain
Pratt & Whitney Canada PT6A–38, –41,
–42, –42A, –61, –64, –66, –66B, –110,
–112, –114, –114A, –121, –135, and
–135A series turboprop engines. This
AD requires removal from service of
certain part manufacturer approval
(PMA) replacement Timken Alcor
Aerospace Technologies, Inc. (TAATI)
first stage sun gears and planet gears
installed in the reduction gearbox. This
AD was prompted by failures of certain
first stage sun gears manufactured by
TAATI. We are issuing this AD to
prevent failure of the sun gear and
planet gears which will result in an
engine in-flight shut down, possible
uncontained engine failure, aircraft
damage, and serious injuries.
DATES: This AD becomes effective May
23, 2012.
We must receive comments on this
AD by June 22, 2012.
SUMMARY:
You may send comments by
any of the following methods:
• Federal eRulemaking Portal: Go to
https://www.regulations.gov and follow
the instructions for sending your
comments electronically.
• Mail: U.S. Department of
Transportation, 1200 New Jersey
Avenue SE., West Building Ground
Floor, Room W12–140, Washington, DC
20590–0001.
• Hand Delivery: Deliver to Mail
address above between 9 a.m. and 5
p.m., Monday through Friday, except
Federal holidays.
• Fax: 202–493–2251.
We received two reports of sun gears,
part number (P/N) E3028456, and
installed in reduction gearboxes, failing
during operation. We also received one
report of a sun gear, P/N E3037304,
showing premature wear and broken
gear teeth during inspection. All three
gear failures occurred between 60 and
127 hours of operation time-since-new.
These conditions, if not corrected, could
result in failure of the sun gear and
planet gears in the propeller reduction
gearbox assembly, which will result in
an engine in-flight shut down, possible
uncontained engine failure, aircraft
damage, and serious injuries. We
determined that the affected PMA
replacement TAATI first stage sun gears
and planet gears listed in this AD,
would have been installed after
December 22, 2008. The affected parts
are listed as follows:
First stage sun gears P/N E3028456,
all serial numbers (S/Ns), and the
associated planet gears.
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]]>Agencies
[Federal Register Volume 77, Number 89 (Tuesday, May 8, 2012)]
[Rules and Regulations]
[Pages 26937-26943]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2012-9189]
=======================================================================
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2011-1066; Directorate Identifier 2011-NM-050-AD;
Amendment 39-16917; AD 2012-01-05]
RIN 2120-AA64
Airworthiness Directives; Airbus Airplanes
AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
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SUMMARY: We are superseding an existing airworthiness directive (AD)
for certain Airbus Model A300 B2-1C, B2K-3C, B2-203, B4-2C, B4-103, and
B4-203 airplanes; and Model A300 B4-601, B4-603, B4-620, B4-622, B4-
605R, B4-622R, and F4-605R airplanes. That AD currently requires
repetitive inspections for cracking in Gear Rib 5 of the main landing
gear (MLG) attachment fittings at the lower flange, and repair if
necessary; and provides an optional spot-facing modification around
certain fastener holes, which would terminate certain repetitive
inspections. This new AD mandates the optional spot-facing
modification. This AD was prompted by new cases of cracks discovered
during scheduled maintenance checks. We are issuing this AD to prevent
cracking of the Gear Rib 5 right-hand and left-hand attachment fitting
at the lower flanges of the MLG, which could result in failed bolts
penetrating through the rear spar and into a fuel tank, consequent fuel
loss, and reduced structural integrity of the airplane.
DATES: This AD becomes effective June 12, 2012.
The Director of the Federal Register approved the incorporation by
reference of certain publications listed in this AD as of June 12,
2012.
The Director of the Federal Register approved the incorporation by
reference of certain other publications listed in this AD as of January
5, 2011 (75 FR 74610, December 1, 2010).
The Director of the Federal Register approved the incorporation by
reference of certain other publications listed in this AD as of July
18, 2006 (71 FR 33994, June 13, 2006).
The Director of the Federal Register approved the incorporation by
reference of certain other publications listed in this AD as of April
12, 2000 (65 FR 12077, March 8, 2000).
The Director of the Federal Register approved the incorporation by
reference of certain other publications listed in this AD as of October
20, 1999 (64 FR 49966, September 15, 1999).
ADDRESSES: You may examine the AD docket on the Internet at 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 October 11, 2011 (76
FR 62673), and proposed to supersede AD 2010-23-26, Amendment 39-16516
(75 FR 74610, December 1, 2010). That NPRM proposed to correct an
unsafe condition for the specified products. The MCAI states:
Following the occurrence of cracks on the MLG [main landing
gear] Rib 5 RH [right-hand] and LH [left-hand] attachment fitting
lower flanges, DGAC [Direction G[eacute]n[eacute]rale de l'Aviation
Civile] France AD 2003-318(B) was issued to require repetitive
inspections and, as terminating action, the embodiment of Airbus
Service Bulletins (SB) A300-57-0235 and A300-57-6088 * * *.
Subsequently, new cases of cracks were discovered during
scheduled maintenance checks by operators of A300B4 and A300-600
type aeroplanes on which the terminating action SB's were embodied.
This condition, if not corrected, could affect the structural
integrity of those aeroplanes.
To address and correct this condition, Airbus developed an
inspection programme for aeroplanes modified in accordance with SB
A300-57-0235 or A300-57-6088. This inspection programme was required
to be implemented by DGAC France AD F-2005-113, original issue and
later revision 1 [parallel to part of FAA AD 2006-12-13, Amendment
39-14639 (71 FR 33994, June 13, 2006)].
A new EASA [European Aviation Safety Agency] AD 2008-0111,
superseding DGAC France AD F-2005-113R1, was issued to reduce the
applicability. For aeroplanes already compliant with DGAC France AD
F-2005-113R1, no further action was required.
Since EASA AD 2008-0111 issuance, Airbus reviewed the inspection
programmes of SB A300-57A0246 and SB A300-57A6101 to introduce
repetitive inspections including a new inspection technique for
holes 47 and 54 and to reduce inspections threshold and intervals
from 700 Flight Cycles (FC) to 400 FC until a revised terminating
action is made available.
For the reasons stated above, EASA AD 2009-0081 superseded EASA
AD 2008-0111 and required operators to comply with the new
inspection programme introduced in Revisions 3 of Airbus SB A300-
57A0246 and Airbus SB A300-57A6101.
EASA AD 2009-0081 R1 [which corresponds to FAA AD 2010-23-26,
Amendment 39-16516 (75 FR 74610, December 1, 2010)] has been
published to introduce an optional terminating action which
consisted of spot-facing the sensitive holes of the MLG Rib 5 (LH
and RH) bottom flanges.
Later discussions with Airbus have demonstrated the necessity to
require the spot-facing modification as a final solution (no longer
optional). This new [EASA] AD retains the inspection requirements of
EASA AD 2009-0081 R1, which is superseded, and requires the spot-
facing of sensitive holes of the MLG Rib 5 (LH and RH) bottom
flanges as terminating action.
Required actions include repairing discrepancies (e.g., cracking or a
second oversize or greater fastener hole). You may obtain further
information by examining the MCAI in the AD docket.
Comments
We gave the public the opportunity to participate in developing
this AD. We considered the comment received. The
[[Page 26938]]
commenter supports the NPRM (76 FR 62673, October 11, 2011).
Explanation of Changes Made to This AD
We have made the following changes to this AD. These changes have
not changed the intent of any provisions specified in this AD.
Revised certain headers throughout this AD.
Redesignated Notes 1, 2, and 3 of the NPRM (76 FR 62673,
October 11, 2011) as paragraphs (g)(3), (q)(1), and (q)(2) of this AD,
respectively.
Redesignated paragraph (n) of the NPRM (76 FR 62673,
October 11, 2011) as paragraph (q)(3) of this AD, and redesignated
subsequent paragraphs accordingly.
We have revised paragraphs (g), (i), (o)(1), (o)(3),
(o)(4), and (o)(5) of this AD to clarify the specific actions for which
the specified service information is required.
We have revised the headings of Tables 1, 2, 3, 4, 5, and
6 of this AD to clarify the purpose of the content in those tables.
We have revised the wording in paragraphs (q)(1), (q)(2),
(q)(3), and (q)(4) of this AD (Notes 2 and 3 and paragraphs (n) and (r)
of the NPRM (76 FR 62673, October 11, 2011), respectively); this change
has not changed the intent of these paragraphs.
Conclusion
We reviewed the available data, including the comment received, and
determined that air safety and the public interest require adopting the
AD with the changes described previously--and minor editorial changes.
We have determined that these minor changes:
Are consistent with the intent that was proposed in the
NPRM (76 FR 62673, October 11, 2011) for correcting the unsafe
condition; and
Do not add any additional burden upon the public than was
already proposed in the NPRM (76 FR 62673, October 11, 2011).
Costs of Compliance
We estimate that this AD will affect about 155 products of U.S.
registry.
The actions that are required by AD 2010-23-26, Amendment 39-16516
(75 FR 74610, December 1, 2010), and retained in this AD take about 79
work-hours per product, at an average labor rate of $85 per work hour.
Required parts cost about $10,270 per product. Based on these figures,
the estimated cost of the currently required actions is $16,985 per
product.
We estimate that it will take about 100 work-hours per product to
comply with the new basic requirements of this AD. The average labor
rate is $85 per work-hour. Based on these figures, we estimate the cost
of the AD on U.S. operators to be $1,317,500, or $8,500 per product.
Authority for This Rulemaking
Title 49 of the United States Code specifies the FAA's authority to
issue rules on aviation safety. Subtitle I, section 106, describes the
authority of the FAA Administrator. ``Subtitle VII: Aviation
Programs,'' describes in more detail the scope of the Agency's
authority.
We are issuing this rulemaking under the authority described in
``Subtitle VII, Part A, Subpart III, Section 44701: General
requirements.'' Under that section, Congress charges the FAA with
promoting safe flight of civil aircraft in air commerce by prescribing
regulations for practices, methods, and procedures the Administrator
finds necessary for safety in air commerce. This regulation is within
the scope of that authority because it addresses an unsafe condition
that is likely to exist or develop on products identified in this
rulemaking action.
Regulatory Findings
We determined that this AD will not have federalism implications
under Executive Order 13132. This AD will not have a substantial direct
effect on the States, on the relationship between the national
government and the States, or on the distribution of power and
responsibilities among the various levels of government.
For the reasons discussed above, I certify this AD:
1. Is not a ``significant regulatory action'' under Executive Order
12866;
2. Is not a ``significant rule'' under the DOT Regulatory Policies
and Procedures (44 FR 11034, February 26, 1979); and
3. Will not have a significant economic impact, positive or
negative, on a substantial number of small entities under the criteria
of the Regulatory Flexibility Act.
We prepared a regulatory evaluation of the estimated costs to
comply with this AD and placed it in the AD docket.
Examining the AD Docket
You may examine the AD docket on the Internet at 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 (76 FR 62673, October 11,
2011), the regulatory evaluation, any comments received, and other
information. The street address for the Docket Operations office
(telephone (800) 647-5527) is in the ADDRESSES section. Comments will
be available in the AD docket shortly after receipt.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.
Adoption of the Amendment
Accordingly, under the authority delegated to me by the
Administrator, the FAA amends 14 CFR part 39 as follows:
PART 39--AIRWORTHINESS DIRECTIVES
0
1. The authority citation for part 39 continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
Sec. 39.13 [Amended]
0
2. The FAA amends Sec. 39.13 by removing Amendment 39-16516 (75 FR
74610, December 1, 2010) and adding the following new AD:
2012-01-05 Airbus: Amendment 39-16917. Docket No. FAA-2011-1066;
Directorate Identifier 2011-NM-050-AD.
(a) Effective Date
This airworthiness directive (AD) becomes effective June 12,
2012.
(b) Affected ADs
This AD supersedes AD 2010-23-26, Amendment 39-16516 (75 FR
74610, December 1, 2010).
(c) Applicability
This AD applies to the airplanes, certificated in any category,
identified in paragraphs (c)(1) and (c)(2) of this AD; except
airplanes on which Airbus Modification 11912 or 11932 has been
installed.
(1) Airbus Model A300 B2-1C, B2K-3C, B2-203, B4-2C, B4-103, and
B4-203 airplanes.
(2) Airbus Model A300 B4-601, B4-603, B4-620, B4-622, B4-605R,
B4-622R, and F4-605R airplanes.
(d) Subject
Air Transport Association (ATA) of America Code 57: Wings.
(e) Reason
This AD was prompted by new cases of cracks discovered during
scheduled maintenance checks. We are issuing this AD to prevent
cracking of the Gear Rib 5 right-hand and left-hand attachment
fitting at the lower flanges of the main landing gear (MLG), which
could result in failed bolts penetrating through the rear spar and
into a fuel tank, consequent fuel loss, and reduced structural
integrity of the airplane.
(f) Compliance
You are responsible for having the actions required by this AD
performed within the
[[Page 26939]]
compliance times specified, unless the actions have already been
done.
(g) Retained Repetitive Inspections
This paragraph restates the requirements of paragraph (g) of AD
2010-23-26, Amendment 39-16516 (75 FR 74610, December 1, 2010).
Perform a detailed inspection and a high-frequency eddy current
(HFEC) inspection to detect cracks in Gear Rib 5 of the MLG
attachment fittings at the lower flange, in accordance with the
Accomplishment Instructions of any applicable service bulletin
listed in table 1 and table 2 of this AD, at the time specified in
paragraph (g)(1) or (g)(2) of this AD. After April 12, 2000 (the
effective date of AD 2000-05-07, Amendment 39-11616 (65 FR 12077,
March 8, 2000)), the service bulletins listed in table 2 of this AD
must be used to accomplish the actions required by this paragraph.
Repeat the inspections thereafter at intervals not to exceed 1,500
flight cycles, until the actions specified in paragraph (i), (j), or
(l) of this AD are accomplished.
Table 1--Revision 01 of Service Bulletins for Paragraph (g) of This AD
----------------------------------------------------------------------------------------------------------------
Airbus Service Bulletin--
Model-- Revision-- Dated--
----------------------------------------------------------------------------------------------------------------
A300 B4[dash]601, B4[dash]603, A300[dash]57[dash]6087... 01 March 11, 1998.
B4[dash]620, B4[dash]622,
B4[dash]605R, B4[dash]622R and
F4[dash]605R airplanes.
A300 B2[dash]1C, B2K-3C, B2[dash]203, A300-57-0234............. 01 March 11, 1998.
B4[dash]2C, B4[dash]103, and
B4[dash]203 airplanes.
----------------------------------------------------------------------------------------------------------------
Table 2--Other Revisions of Service Bulletins for Paragraph (g) of This AD
----------------------------------------------------------------------------------------------------------------
Airbus Service
Model-- Bulletin-- Revision-- Dated--
----------------------------------------------------------------------------------------------------------------
A300 B4[dash]601, B4[dash]603, A300[dash]57A6087.... 02, including June 24, 1999.
B4[dash]620, B4[dash]622, Appendix 01.
B4[dash]605R, B4[dash]622R, and
F4[dash]605R airplanes.
03, including May 19, 2000.
Appendix 01.
04, including February 19, 2002.
Appendix 01.
05, including March 10, 2008.
Appendix 01.
----------------------------------------------------------------------------------------------------------------
A300 B2[dash]1C, B2K-3C, A300[dash]57A0234.... 02 June 24, 1999.
B2[dash]203, B4[dash]2C,
B4[dash]103, and B4[dash]203
airplanes.
03, including September 2, 1999.
Appendix 01.
04, including May 19, 2000.
Appendix 01.
05, including February 19, 2002.
Appendix 01.
----------------------------------------------------------------------------------------------------------------
(1) For airplanes that have accumulated 20,000 or more total
flight cycles as of March 9, 1998 (the effective date of AD 98-03-
06, Amendment 39-10298 (63 FR 5224, February 2, 1998)): Inspect
within 500 flight cycles after March 9, 1998.
(2) For airplanes that have accumulated less than 20,000 total
flight cycles as of March 9, 1998 (the effective date of AD 98-03-
06, Amendment 39-10298 (63 FR 5224, February 2, 1998)): Inspect
prior to the accumulation of 18,000 total flight cycles, or within
1,500 flight cycles after March 9, 1998, whichever occurs later.
(3) For the purposes of this AD, a detailed inspection is
defined as: ``An intensive visual examination of a specific
structural area, system, installation, or assembly to detect damage,
failure, or irregularity. Available lighting is normally
supplemented with a direct source of good lighting at intensity
deemed appropriate by the inspector. Inspection aids such as mirror,
magnifying lenses, etc., may be used. Surface cleaning and elaborate
access procedures may be required.''
(h) Retained Repair for Any Crack Found During Inspections Required by
Paragraph (g) of This AD
This paragraph restates the requirements of paragraph (h) of AD
2010-23-26, Amendment 39-16516 (75 FR 74610, December 1, 2010). If
any crack is detected during any inspection required by paragraph
(g) of this AD, prior to further flight, accomplish the requirements
of paragraph (h)(1) or (h)(2) of this AD, as applicable.
(1) If a crack is detected at one hole only, and the crack does
not extend out of the spotface of the hole, repair in accordance
with the Accomplishment Instructions of the applicable service
bulletin in table 2 of this AD.
(2) If a crack is detected at more than one hole, or if any
crack at any hole extends out of the spotface of the hole, repair in
accordance with a method approved by the Manager, International
Branch, ANM-116, Transport Airplane Directorate, FAA, or the
European Aviation Safety Agency (EASA) (or its delegated agent).
(i) Retained Terminating Modification for Repetitive Inspections
Required by Paragraphs (g) and (j) of This AD
This paragraph restates the requirements of paragraph (i) of AD
2010-23-26, Amendment 39-16516 (75 FR 74610, December 1, 2010).
Except as required by paragraph (l) of this AD, prior to the
accumulation of 21,000 total flight cycles, or within 2 years after
October 20, 1999 (the effective date of AD 99-19-26, Amendment 39-
11313 (64 FR 49966, September 15, 1999)), whichever occurs later:
Modify Gear Rib 5 of the MLG attachment fittings at the lower flange
in accordance with the Accomplishment Instructions of the applicable
service bulletin in table 3 of this AD. After July 18, 2006 (the
effective date of AD 2006-12-13, Amendment 39-14639 (71 FR 33994,
June 13, 2006)), Airbus Service Bulletin A300-57-6088, Revision 04,
dated December 3, 2003 (for Model A300 B4-601, B4-603, B4-620, B4-
622, B4-605R, B4-622R, and F4-605R airplanes); and Airbus Service
Bulletin A300-57-0235, Revision 04, dated March 13, 2003, or
Revision 05, dated December 3, 2003 (for Model A300 B2-1C, B2K-3C,
B2-203, B4-2C, B4-103, and B4-203 airplanes); must be used to
accomplish the actions required by this paragraph. Accomplishment of
this modification constitutes terminating action for the repetitive
inspection requirements of paragraphs (g) and (j) of this AD.
Table 3--Service Bulletins for Terminating Modification Required by Paragraph (i) of This AD
----------------------------------------------------------------------------------------------------------------
Airbus Service
Model-- Bulletin-- Revision-- Dated--
----------------------------------------------------------------------------------------------------------------
A300 B4-601, B4-603, B4-620, B4- A300-57-6088......... 01, including February 1, 1999.
622, B4-605R, B4-622R, and F4- Appendix 01.
605R airplanes.
02 September 5, 2002.
[[Page 26940]]
04 December 3, 2003.
----------------------------------------------------------------------------------------------------------------
A300 B2-1C, B2K-3C, B2-203, B4-2C, A300-57-0235......... 01, including February 1, 1999.
B4-103, and B4-203 airplanes. Appendix 01.
03 September 5, 2002.
04 March 13, 2003.
05 December 3, 2003.
----------------------------------------------------------------------------------------------------------------
(j) Retained Additional Repetitive Inspections
This paragraph restates the requirements of paragraph (j) of AD
2010-23-26, Amendment 39-16516 (75 FR 74610, December 1, 2010). For
airplanes on which the modification specified in paragraph (i) or
(l) of this AD has not been done before July 18, 2006 (the effective
date of AD 2006-12-13, Amendment 39-14639 (71 FR 33994, June 13,
2006)), perform a detailed and an HFEC inspection to detect cracks
of the lower flange of Gear Rib 5 of the MLG at holes 43, 47, 48,
49, 50, 52, and 54, in accordance with the applicable service
bulletin listed in table 4 of this AD. Perform the inspections at
the applicable time specified in paragraph (j)(1), (j)(2), (j)(3),
or (j)(4) of this AD. Repeat the inspections thereafter at intervals
not to exceed 700 flight cycles until the terminating modification
required by paragraph (l) of this AD is accomplished. Accomplishment
of the inspections per paragraph (j) of this AD terminates the
inspection requirements of paragraph (g) of this AD.
Table 4--Service Bulletins for Repetitive Inspections Required by Paragraph (j) of This AD
----------------------------------------------------------------------------------------------------------------
Airbus Service
Model-- Bulletin-- Revision-- Dated--
----------------------------------------------------------------------------------------------------------------
A300 B4-601, B4-603, B4-620, B4- A300-57A6087......... 04, including February 19, 2002.
622, B4-605R, B4-622R, and F4- Appendix 01.
605R airplanes.
05, including March 10, 2008.
Appendix 01
----------------------------------------------------------------------------------------------------------------
A300 B2-1C, B2K-3C, B2-203, B4-2C, A300-57A0234......... 05, including February 19, 2002.
B4-103, and B4-203 airplanes. Appendix 01.
----------------------------------------------------------------------------------------------------------------
(1) For Model A300 B2-1C, B2K-3C, B2-203, B4-2C, B4-103, and B4-
203 airplanes; and Model A300 B4-601, B4-603, B4-620, B4-622, B4-
605R, B4-622R, and F4-605R airplanes that have accumulated 18,000 or
more total flight cycles as of July 18, 2006 (the effective date of
AD 2006-12-13, Amendment 39-14639 (71 FR 33994, June 13, 2006)):
Within 700 flight cycles after July 18, 2006.
(2) For Model A300 B2-1C, B2K-3C, and B2-203 airplanes that have
accumulated less than 18,000 total flight cycles as of July 18, 2006
(the effective date of AD 2006-12-13, Amendment 39-14639 (71 FR
33994, June 13, 2006)): Prior to the accumulation of 18,000 total
flight cycles, or within 700 flight cycles after July 18, 2006,
whichever occurs later.
(3) For Model A300 B4-2C, B4-103, and B4-203 airplanes that have
accumulated less than 18,000 total flight cycles as of July 18, 2006
(the effective date of AD 2006-12-13, Amendment 39-14639 (71 FR
33994, June 13, 2006)): Prior to the accumulation of 14,500 total
flight cycles, or within 700 flight cycles after July 18, 2006,
whichever occurs later.
(4) For Model A300 B4-601, B4-603, B4-620, B4-622, B4-605R, B4-
622R, and F4-605R airplanes that have accumulated less than 18,000
total flight cycles as of July 18, 2006 (the effective date of AD
2006-12-13, Amendment 39-14639 (71 FR 33994, June 13, 2006)): Prior
to the accumulation of 11,600 total flight cycles, or within 700
flight cycles after July 18, 2006, whichever occurs later.
(k) Retained Crack Repair
This paragraph restates the requirements of paragraph (k) of AD
2010-23-26, Amendment 39-16516 (75 FR 74610, December 1, 2010). If
any crack is detected during any inspection required by paragraph
(j) of this AD, prior to further flight, accomplish the requirements
of paragraphs (k)(1) and (k)(2) of this AD, as applicable.
(1) If a crack is detected at only one hole, and the crack does
not extend out of the spotface of the hole, repair in accordance
with Airbus Service Bulletin A300-57A0234, Revision 05, including
Appendix 01, dated February 19, 2002 (for Model A300 B2-1C, B2K-3C,
B2-203, B4-2C, B4-103, and B4-203 airplanes); or A300-57A6087,
Revision 04, including Appendix 01, dated February 19, 2002, or
A300-57A6087, Revision 05, including Appendix 01, dated March 10,
2008 (for Model A300 B4-601, B4-603, B4-620, B4-622, B4-605R, B4-
622R, and F4-605R airplanes).
(2) If a crack is detected at more than one hole, or if any
crack at any hole extends out of the spotface of the hole, repair in
accordance with a method approved by the Manager, International
Branch, ANM-116, or the EASA (or its delegated agent).
(l) Retained Terminating Modification for Repetitive Inspections
Required by Paragraphs (g) and (j) of This AD for Certain Airplanes
This paragraph restates the requirements of paragraph (l) of AD
2010-23-26, Amendment 39-16516 (75 FR 74610, December 1, 2010). For
airplanes on which the terminating modification in paragraph (i) of
this AD has not been accomplished before July 18, 2006 (the
effective date of AD 2006-12-13, Amendment 39-14639 (71 FR 33994,
June 13, 2006)): At the earlier of the times specified in paragraphs
(l)(1) and (l)(2) of this AD, modify Gear Rib 5 of the MLG
attachment fittings at the lower flange. Except as provided by
paragraph (m) of this AD, do the modification in accordance with the
applicable service bulletin identified in table 5 of this AD. This
action terminates the repetitive inspections requirements of
paragraphs (g) and (j) of this AD.
(1) Prior to the accumulation of 21,000 total flight cycles, or
within 2 years after October 20, 1999 (the effective date of AD 99-
19-26, Amendment 39-11313 (64 FR 49966, September 15, 1999)),
whichever is later.
(2) Within 16 months after July 18, 2006 (the effective date of
AD 2006-12-13, Amendment 39-14639 (71 FR 33994, June 13, 2006)).
[[Page 26941]]
Table 5--Service Bulletins for Terminating Modification Required by Paragraph (l) of This AD
----------------------------------------------------------------------------------------------------------------
Airbus Service
Model-- Bulletin-- Revision-- Dated--
----------------------------------------------------------------------------------------------------------------
A300 B4-601, B4-603, B4-620, B4- A300-57-6088.......... 04 December 3, 2003.
622, B4-605R, B4-622R and F4-605R
airplanes.
----------------------------------------------------------------------------------------------------------------
A300 B2-1C, B2K-3C, B2-203, B4-2C, A300-57-0235.......... 04 March 13, 2003.
B4-103, and B4-203 airplanes.
05 December 3, 2003.
----------------------------------------------------------------------------------------------------------------
(m) Retained Modification
This paragraph restates the requirements of paragraph (m) of AD
2010-23-26, Amendment 39-16516 (75 FR 74610, December 1, 2010).
Where the applicable service bulletin specified in paragraph (l) of
this AD specifies to contact Airbus for modification instructions;
or if there is a previously installed repair at any of the affected
fastener holes; or if a crack is found when accomplishing the
modification: Prior to further flight, modify in accordance with a
method approved by the Manager, International Branch, ANM-116, or
the EASA (or its delegated agent).
(n) Retained Exception for No Reporting
This paragraph restates the requirements of paragraph (o) of AD
2010-23-26, Amendment 39-16516 (75 FR 74610, December 1, 2010).
Although the service bulletins identified in tables 1, 2, 3, 4, 5,
and 6 of this AD specify to submit certain information to the
manufacturer, this AD does not include such a requirement.
(o) Retained Requirements With Revised Service Information
This paragraph restates the requirements of paragraph (p) of AD
2010-23-26, Amendment 39-16516 (75 FR 74610, December 1, 2010).
Unless already done, do the following actions.
(1) At the applicable time specified in paragraph (o)(2) of this
AD, perform a detailed inspection for cracking at the locations
specified in paragraphs (o)(1)(i), (o)(1)(ii), and (o)(1)(iii) of
this AD, in accordance with the Accomplishment Instructions of
Airbus Mandatory Service Bulletin A300-57A0246, Revision 03,
including Appendices 1 and 2, dated March 11, 2009, or Revision 04,
including Appendices 1 and 2, dated September 9, 2009 (for Model
A300 B2-1C, B2K-3C, B2-203, B4-2C, B4-103, and B4-203 airplanes); or
Airbus Mandatory Service Bulletin A300-57A6101, Revision 03,
including Appendices 1 and 2, dated March 11, 2009, or Revision 04,
including Appendices 1 and 2, dated September 9, 2009 (for Model
A300 B4-601, B4-603, B4-620, B4-622, B4-605R, B4-622R and F4-605R
airplanes). As of the effective date of this AD Revision 04 of these
service bulletins must be used to accomplish the actions required by
this paragraph.
(i) The bottom flange and vertical web in the area between the
wing rear spar/gear Rib 5 attachment and the forward reaction-rod
pick-up lug.
(ii) On the inboard side, around the fastener holes at locations
43, 47 to 50, 52, and 54.
(iii) On the outboard side, the lower flange, the vertical web
and around the fastener holes at locations 43, 47 to 50, 52 and 54.
(2) Do the inspection required by paragraph (o)(1) of this AD at
the later of the times in paragraphs (o)(2)(i) and (o)(2)(ii) of
this AD.
(i) Within 400 flight cycles after the accomplishment of the
actions required by paragraph (i) or (l) of this AD, as applicable.
(ii) Within 400 flight cycles or 4 months after January 5, 2011
(the effective date of AD 2010-23-26, Amendment 39-16516 (75 FR
74610, December 1, 2010)), whichever occurs first.
(3) If no cracking is detected during the inspection required by
paragraph (o)(1) of this AD, before further flight, perform a
fluorescent penetrant inspection (FPI) at holes location 47 and 54,
in the right-hand and left-hand MLG Rib 5 attachment fitting lower
flange, in accordance with the Accomplishment Instructions of Airbus
Mandatory Service Bulletin A300-57A0246, Revision 03, including
Appendices 1 and 2, dated March 11, 2009, or Revision 04, including
Appendices 1 and 2, dated September 9, 2009 (for Model A300 B2-1C,
B2K-3C, B2-203, B4-2C, B4-103, and B4-203 airplanes); or Airbus
Mandatory Service Bulletin A300-57A6101, Revision 03, including
Appendices 1 and 2, dated March 11, 2009, or Revision 04, including
Appendices 1 and 2, dated September 9, 2009 (for Model A300 B4-601,
B4-603, B4-620, B4-622, B4-605R, B4-622R and F4-605R airplanes). As
of the effective date of this AD, Airbus Mandatory Service Bulletin
A300-57A0246, Revision 04, including Appendices 1 and 2, dated
September 9, 2009; or Airbus Mandatory Service Bulletin A300-
57A6101, Revision 04, including Appendices 1 and 2, dated September
9, 2009; as applicable; must be used to accomplish the actions
required by this paragraph.
(4) Thereafter, at intervals not to exceed 400 flight cycles,
repeat the detailed and FPI inspections, in accordance with the
Accomplishment Instructions of Airbus Mandatory Service Bulletin
A300-57A0246, Revision 03, including Appendices 1 and 2, dated March
11, 2009, or Revision 04, including Appendices 1 and 2, dated
September 9, 2009 (for Model A300 B2-1C, B2K-3C, B2-203, B4-2C, B4-
103, and B4-203 airplanes); or Airbus Mandatory Service Bulletin
A300-57A6101, Revision 03, including Appendices 1 and 2, dated March
11, 2009, or Revision 04, including Appendices 1 and 2, dated
September 9, 2009 (for Model A300 B4-601, B4-603, B4-620, B4-622,
B4-605R, B4-622R and F4-605R airplanes); until the terminating
action required by paragraph (p) of this AD has been accomplished.
As of the effective date of this AD, Airbus Mandatory Service
Bulletin A300-57A0246, Revision 04, including Appendices 1 and 2,
dated September 9, 2009; or Airbus Mandatory Service Bulletin A300-
57A6101, Revision 04, including Appendices 1 and 2, dated September
9, 2009; as applicable; must be used to accomplish the actions
required by this paragraph.
(5) If any crack is detected during any of the inspections
required by paragraphs (o)(1), (o)(3), and (o)(4) of this AD, and
Airbus Mandatory Service Bulletin A300-57A0246, Revision 03,
including Appendices 1 and 2, dated March 11, 2009, or Revision 04,
including Appendices 1 and 2, dated September 9, 2009 (for Model
A300 B2-1C, B2K-3C, B2-203, B4-2C, B4-103, and B4-203 airplanes); or
Airbus Mandatory Service Bulletin A300-57A6101, Revision 03,
including Appendices 1 and 2, dated March 11, 2009, or Revision 04,
including Appendices 1 and 2, dated September 9, 2009 (for Model
A300 B4-601, B4-603, B4-620, B4-622, B4-605R, B4-622R and F4-605R
airplanes); recommends contacting Airbus for appropriate action:
Before further flight, contact Airbus for a repair solution, and do
the repair; or repair the cracking using a method approved by the
Manager, International Branch, ANM-116, Transport Airplane
Directorate, FAA, or EASA (or its delegated agent).
(p) New Terminating Action
Within 30 months after the effective date of this AD: Modify the
spot-faces around all the fastener holes at locations 43, 47 to 50,
52, and 54 (except for spot-faces of holes which have been
previously repaired) on the bottom flange MLG ribs, in accordance
with the Accomplishment Instructions of Airbus Mandatory Service
Bulletin A300-57-0254, Revision 01, including Appendix 1, dated June
14, 2011 (for Model A300 B2-1C, B2K-3C, B2-203, B4-2C, B4-103, and
B4-203 airplanes); or Airbus Mandatory Service Bulletin A300-57-
6110, Revision 01, including Appendix 1, dated June 6, 2011 A300 B4-
601, B4-603, B4-620, B4-622, B4-605R, B4-622R and F4-605R airplanes
(for Model A300 B4-601, B4-603, B4-620, B4-622, B4-605R, B4-622R and
F4-605R airplanes). Accomplishing this modification terminates the
repetitive inspection requirements of paragraph (o)(4) of this AD.
(q) Credit for Previous Actions
(1) This paragraph provides credit for initial detailed and HFEC
inspections, as
[[Page 26942]]
required by the introductory text of paragraph (g) of this AD, if
those inspections were performed before April 12, 2000 (the
effective date of AD 2000-05-07, Amendment 39-11616 (65 FR 12077,
March 8, 2000)), using Airbus Service Bulletin A300-57A0234 (for
Model A300 B2-1C, B2K-3C, B2-203, B4-2C, B4-103, and B4-203
airplanes) or A300-57A6087, both dated August 5, 1997 (for Model
A300 B4-601, B4-603, B4-620, B4-622, B4-605R, B4-622R, and F4-605R
airplanes).
(2) This paragraph provides credit for a modification, as
required by paragraph (i) of this AD, if the modification was
performed before April 12, 2000 (the effective date of AD 2000-05-
07, Amendment 39-11616 (65 FR 12077, March 8, 2000)), using Airbus
Service Bulletin A300-57-6088, dated August 5, 1998 (for Model A300
B4-601, B4-603, B4-620, B4-622, B4-605R, B4-622R and F4-605R
airplanes); or Airbus Service Bulletin A300-57-0235, dated August 5,
1998 (for Model A300 B2-1C, B2K-3C, B2-203, B4-2C, B4-103, and B4-
203 airplanes).
(3) This paragraph provides credit for the actions required by
paragraphs (i) and (l) of this AD, if those actions were performed
before July 18, 2006 (the effective date of AD 2006-12-13, Amendment
39-14639 (71 FR 33994, June 13, 2006)), using the applicable service
information listed in table 6 of this AD.
Table 6--Previous Issues of Certain Service Bulletins
----------------------------------------------------------------------------------------------------------------
Airbus Service
Model-- Bulletin-- Revision-- Dated--
----------------------------------------------------------------------------------------------------------------
A300 B2-1C, B2K-3C, B2-203, B4-2C, A300-57-0235......... 02, including September 27, 1999.
B4-103, and B4-203 airplanes. Appendix 01.
03 September 5, 2002.
----------------------------------------------------------------------------------------------------------------
A300 B4-601, B4-603, B4-620, B4- A300-57-6088......... 02................... September 5, 2000.
622, B4-605R, B4-622R and F4-605R
airplanes.
03................... March 13, 2003.
----------------------------------------------------------------------------------------------------------------
(4) This paragraph provides credit for a modification of the
spot-faces, as specified in paragraph (p) of this AD, if the
modification was performed before the effective date of this AD
using Airbus Mandatory Service Bulletin A300-57-0254, dated June 4,
2010 (for Model A300 B2-1C, B2K-3C, B2-203, B4-2C, B4-103, and B4-
203 airplanes); or Airbus Mandatory Service Bulletin A300-57-6110,
dated June 7, 2010 (for Model A300 B4-601, B4-603, B4-620, B4-622,
B4-605R, B4-622R and F4-605R airplanes).
(r) Other FAA AD Provisions
The following provisions also apply to this AD:
(1) Alternative Methods of Compliance (AMOCs): The Manager,
International Branch, ANM-116, FAA, has the authority to approve
AMOCs for this AD, if requested using the procedures found in 14 CFR
39.19. In accordance with 14 CFR 39.19, send your request to your
principal inspector or local Flight Standards District Office, as
appropriate. If sending information directly to the International
Branch, send it to ATTN: Dan Rodina, Aerospace Engineer,
International Branch, ANM-116, Transport Airplane Directorate, FAA,
1601 Lind Avenue SW., Renton, Washington 98057-3356; telephone (425)
227-2125; fax (425) 227-1149. Information may be emailed to: 9-ANM-116-AMOC-REQUESTS@faa.gov. Before using any approved AMOC, notify
your appropriate principal inspector, or lacking a principal
inspector, the manager of the local flight standards district
office/certificate holding district office. The AMOC approval letter
must specifically reference this AD. AMOCs approved previously in
accordance with AD 2000-05-07, Amendment 39-11616 (65 FR 12077,
March 8, 2000); AD 2006-12-13, Amendment 39-14639 (71 FR 33994, June
13, 2006); and AD 2010-23-26, Amendment 39-16516 (75 FR 74610,
December 1, 2010); are approved as AMOCs for the corresponding
provisions of this AD.
(2) Airworthy Product: For any requirement in this AD to obtain
corrective actions from a manufacturer or other source, use these
actions if they are FAA-approved. Corrective actions are considered
FAA-approved if they are approved by the State of Design Authority
(or their delegated agent). You are required to assure the product
is airworthy before it is returned to service.
(s) Related Information
Refer to MCAI EASA Airworthiness Directive 2011-0029, dated
February 24, 2011, and the service information specified in
paragraphs (s)(1) through (s)(23) of this AD, for related
information.
(1) Airbus Service Bulletin A300-57-0234, Revision 01, dated
March 11, 1998.
(2) Airbus Service Bulletin A300-57A0234, Revision 02, dated
June 24, 1999.
(3) Airbus Service Bulletin A300-57A0234, Revision 03, including
Appendix 01, dated September 2, 1999.
(4) Airbus Service Bulletin A300-57A0234, Revision 04, including
Appendix 01, dated May 19, 2000.
(5) Airbus Service Bulletin A300-57A0234, Revision 05, including
Appendix 01, dated February 19, 2002.
(6) Airbus Service Bulletin A300-57-0235, Revision 01, including
Appendix 01, dated February 1, 1999.
(7) Airbus Service Bulletin A300-57-0235, Revision 03, dated
September 5, 2002.
(8) Airbus Service Bulletin A300-57-0235, Revision 04, dated
March 13, 2003.
(9) Airbus Service Bulletin A300-57-0235, Revision 05, dated
December 3, 2003.
(10) Airbus Mandatory Service Bulletin A300-57A0246, Revision
03, including Appendices 1 and 2, dated March 11, 2009.
(11) Airbus Mandatory Service Bulletin A300-57A0246, Revision
04, including Appendices 1 and 2, dated September 9, 2009.
(12) Airbus Mandatory Service Bulletin A300-57-0254, Revision
01, including Appendix 1, dated June 14, 2011.
(13) Airbus Service Bulletin A300-57-6087, Revision 01, dated
March 11, 1998.
(14) Airbus Service Bulletin A300-57A6087, Revision 02,
including Appendix 01, dated June 24, 1999.
(15) Airbus Service Bulletin A300-57A6087, Revision 03,
including Appendix 01, dated May 19, 2000.
(16) Airbus Service Bulletin A300-57A6087, Revision 04,
including Appendix 01, dated February 19, 2002.
(17) Airbus Service Bulletin A300-57A6087, Revision 05,
including Appendix 01, dated March 10, 2008.
(18) Airbus Service Bulletin A300-57-6088, Revision 01,
including Appendix 01, dated February 1, 1999.
(19) Airbus Service Bulletin A300-57-6088, Revision 02, dated
September 5, 2002.
(20) Airbus Service Bulletin A300-57-6088, Revision 04, dated
December 3, 2003.
(21) Airbus Mandatory Service Bulletin A300-57A6101, Revision
03, including Appendices 1 and 2, dated March 11, 2009.
(22) Airbus Mandatory Service Bulletin A300-57A6101, Revision
04, including Appendices 1 and 2, dated September 9, 2009.
(23) Airbus Mandatory Service Bulletin A300-57-6110, Revision
01, including Appendix 1, dated June 6, 2011.
(t) Material Incorporated by Reference
(1) You must use the following service information to do the
actions required by this AD, unless the AD specifies otherwise. The
Director of the Federal Register approved the incorporation by
reference (IBR) of the following service information under 5 U.S.C.
552(a) and 1 CFR part 51 on the date specified.
(2) The following service information was approved for IBR on
June 12, 2012:
(i) Airbus Mandatory Service Bulletin A300-57-0254, Revision 01,
including Appendix 1, dated June 14, 2011.
(ii) Airbus Mandatory Service Bulletin A300-57-6110, Revision
01, including Appendix 1, dated June 6, 2011.
(3) The following service information was approved for IBR
January 5, 2011 (75 FR 74610, December 1, 2010):
[[Page 26943]]
(i) Airbus Mandatory Service Bulletin A300-57A0246, Revision 03,
including Appendices 1 and 2, dated March 11, 2009.
(ii) Airbus Mandatory Service Bulletin A300-57A0246, Revision
04, including Appendices 1 and 2, dated September 9, 2009.
(iii) Airbus Mandatory Service Bulletin A300-57A6101, Revision
03, including Appendices 1 and 2, dated March 11, 2009.
(iv) Airbus Mandatory Service Bulletin A300-57A6101, Revision
04, including Appendices 1 and 2, dated September 9, 2009.
(v) Airbus Service Bulletin A300-57A6087, Revision 05, including
Appendix 01, dated March 10, 2008. (Appendix 01 of this document was
incorrectly identified as ``Appendix 05'' in the document citation
specified in table 8 of AD 2010-23-26, Amendment 39-16516 (75 FR
74610, December 1, 2010); all other references to Appendix 01 of
this document in AD 2010-23-26 were correct.)
(4) The following service information was approved for IBR July
18, 2006 (71 FR 33994, June 13, 2006):
(i) Airbus Service Bulletin A300-57A0234, Revision 04, including
Appendix 01, dated May 19, 2000.
(ii) Airbus Service Bulletin A300-57A0234, Revision 05,
including Appendix 01, dated February 19, 2002.
(iii) Airbus Service Bulletin A300-57A6087, Revision 03,
including Appendix 01, dated May 19, 2000.
(iv) Airbus Service Bulletin A300-57A6087, Revision 04,
including Appendix 01, dated February 19, 2002.
(v) Airbus Service Bulletin A300-57-0235, Revision 03, dated
September 5, 2002.
(vi) Airbus Service Bulletin A300-57-0235, Revision 04, dated
March 13, 2003.
(vii) Airbus Service Bulletin A300-57-0235, Revision 05, dated
December 3, 2003.
(viii) Airbus Service Bulletin A300-57-6088, Revision 02, dated
September 5, 2002.
(ix) Airbus Service Bulletin A300-57-6088, Revision 04, dated
December 3, 2003.
(5) The following service information was approved for IBR on
April 12, 2000 (65 FR 12077, March 8, 2000):
(i) Airbus Service Bulletin A300-57A0234, Revision 02, dated
June 24, 1999.
(ii) Airbus Service Bulletin A300-57A0234, Revision 03,
including Appendix 01, dated September 2, 1999.
(iii) Airbus Service Bulletin A300-57A6087, Revision 02,
including Appendix 01, dated June 24, 1999.
(6) The following service information was approved for IBR on
October 20, 1999 (64 FR 49966, September 15, 1999).
(i) Airbus Service Bulletin A300-57-0234, Revision 01, dated
March 11, 1998.
(ii) Airbus Service Bulletin A300-57-0235, Revision 01,
including Appendix 01, dated February 1, 1999.
(iii) Airbus Service Bulletin A300-57-6087, Revision 01, dated
March 11, 1998.
(iv) Airbus Service Bulletin A300-57-6088, Revision 01,
including Appendix 01, dated February 1, 1999.
(7) For service information identified in this AD, contact
Airbus SAS--EAW (Airworthiness Office), 1 Rond Point Maurice
Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96;
fax +33 5 61 93 44 51; email account.airworth-eas@airbus.com;
Internet https://www.airbus.com.
(8) You may review copies of the service information at the FAA,
Transport Airplane Directorate, 1601 Lind Avenue SW., Renton,
Washington. For information on the availability of this material at
the FAA, call 425-227-1221.
(9) You may also review copies of the service information that
is incorporated by reference at the National Archives and Records
Administration (NARA). For information on the availability of this
material at an NARA facility, call 202-741-6030, or go to https://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html.
Issued in Renton, Washington, on January 6, 2012.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2012-9189 Filed 5-7-12; 8:45 am]
BILLING CODE 4910-13-P
