Airworthiness Directives; Airbus Model A300 Airplanes; and Model A300 B4-600, B4-600R, and F4-600R Series Airplanes, and Model C4-605R Variant F Airplanes (Collectively Called A300-600 Series Airplanes), 2803-2807 [E7-25503]
Download as PDF
<![CDATA[
Federal Register / Vol. 73, No. 11 / Wednesday, January 16, 2008 / Rules and Regulations
replace the specified bolts with new bolts
with the new part numbers in all MLG
assemblies following PILATUS AIRCRAFT
LTD. PC–12 Service Bulletin No: 32–020,
Rev. No. 1, dated November 22, 2007.
(3) As of February 20, 2008 (the effective
date of this AD), do not install any of the
special bolts that have serial numbers that
start with the letters AT or have the supplier
code AT on Models PC–12, PC–12/45, and
PC–12/47 airplanes as indicated in PILATUS
AIRCRAFT LTD. PC–12 Service Bulletin No:
32–020, Rev. No. 1, dated November 22,
2007. MLG assemblies, special bolts, and
modifications kits, as referenced in
paragraphs (c)(1), (c)(2), and (c)(3) of this AD,
delivered from PILATUS AIRCRAFT LTD. on
or after December 31, 2006, will not
incorporate the unsafe condition.
FAA AD Differences
Note: This AD differs from the MCAI and/
or service information as follows: No
differences.
Other FAA AD Provisions
(g) The following provisions also apply to
this AD:
(1) Alternative Methods of Compliance
(AMOCs): The Manager, Standards Office,
FAA, has the authority to approve AMOCs
for this AD, if requested using the procedures
found in 14 CFR 39.19. Send information to
ATTN: Doug Rudolph, Aerospace Engineer,
FAA, Small Airplane Directorate, 901 Locust,
Room 301, Kansas City, Missouri 64106;
telephone: (816) 329–4059; fax: (816) 329–
4090. Before using any approved AMOC on
any airplane to which the AMOC applies,
notify your appropriate principal inspector
(PI) in the FAA Flight Standards District
Office (FSDO), or lacking a PI, your local
FSDO.
(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 FAAapproved 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.
(3) Reporting Requirements: For any
reporting requirement in this AD, under the
provisions of the Paperwork Reduction Act
(44 U.S.C. 3501 et. seq.), the Office of
Management and Budget (OMB) has
approved the information collection
requirements and has assigned OMB Control
Number 2120–0056.
ebenthall on PRODPC61 with RULES
Related Information
(h) Refer to Federal Office of Civil Aviation
(FOCA) AD HB–2007–382, dated August 27,
2007; and PILATUS AIRCRAFT LTD. PC–12
Service Bulletin No: 32–020, Rev. No. 1,
dated November 22, 2007, for related
information.
Material Incorporated by Reference
(i) You must use PILATUS AIRCRAFT
LTD. PC–12 Service Bulletin No: 32–020,
Rev. No. 1, dated November 22, 2007, to do
the actions required by this AD, unless the
AD specifies otherwise.
(1) The Director of the Federal Register
approved the incorporation by reference of
VerDate Aug<31>2005
15:01 Jan 15, 2008
Jkt 214001
this service information under 5 U.S.C.
552(a) and 1 CFR part 51.
(2) For service information identified in
this AD, contact PILATUS AIRCRAFT LTD.,
Customer Support Manager, CH–6371
STANS, Switzerland; telephone: +41 41 619
6208; fax: +41 41 619 7311; e-mail:
SupportPC12@pilatus-aircraft.com.
(3) You may review copies at the FAA,
Central Region, Office of the Regional
Counsel, 901 Locust, Room 506, Kansas City,
Missouri 64106; or at the National Archives
and Records Administration (NARA). For
information on the availability of this
material at NARA, call 202–741–6030, or go
to: https://www.archives.gov/federal-register/
cfr/ibr-locations.html.
Issued in Kansas City, Missouri, on January
8, 2008.
John Colomy,
Acting Manager, Small Airplane Directorate,
Aircraft Certification Service.
[FR Doc. E8–479 Filed 1–15–08; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2007–27926; Directorate
Identifier 2006–NM–050–AD; Amendment
39–15316; AD 2007–26–14]
RIN 2120–AA64
Airworthiness Directives; Airbus Model
A300 Airplanes; and Model A300 B4–
600, B4–600R, and F4–600R Series
Airplanes, and Model C4–605R Variant
F Airplanes (Collectively Called A300–
600 Series Airplanes)
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
AGENCY:
SUMMARY: The FAA is superseding an
existing airworthiness directive (AD),
which applies to all Airbus Model A300
B2 and B4 series airplanes; and all
Model A300 B4–600, B4–600R, and F4–
600R (collectively called A300–600)
series airplanes. That AD currently
requires repetitive inspections to detect
cracking of the upper radius of the
forward fitting of frame 47, and repair
if necessary. This new AD retains those
requirements, but reduces inspection
thresholds and repetitive intervals, and
adds related investigative and corrective
actions. This AD also provides an
optional terminating action for the
repetitive inspections only for airplanes
with cracking that is within certain
limits, and a post-repair inspection
program following the optional
terminating action. This AD results from
reports of additional cracking in
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Fmt 4700
Sfmt 4700
2803
airplanes that were inspected in
accordance with the existing AD. We are
issuing this AD to detect and correct
fatigue cracking of the left and right
upper radius at frame 47, which could
propagate and result in reduced
structural integrity of the airplane.
DATES: This AD becomes effective
February 20, 2008.
The Director of the Federal Register
approved the incorporation by reference
of certain publications listed in the AD
as of February 20, 2008.
On May 1, 2003 (68 FR 14894, March
27, 2003), the Director of the Federal
Register approved the incorporation by
reference of certain publications listed
in the AD.
ADDRESSES: For service information
identified in this AD, contact Airbus,
1 Rond Point Maurice Bellonte, 31707
Blagnac Cedex, France.
Examining the AD Docket
You may examine the AD docket on
the Internet at https://
www.regulations.gov; or in person at the
Docket Management Facility between
9 a.m. and 5 p.m., Monday through
Friday, except Federal holidays. The AD
docket contains this AD, the regulatory
evaluation, any comments received, and
other information. The address for the
Docket Office (telephone 800–647–5527)
is the Document Management Facility,
U.S. Department of Transportation,
Docket Operations, M–30, West
Building Ground Floor, Room W12–140,
1200 New Jersey Avenue, SE.,
Washington, DC 20590.
FOR FURTHER INFORMATION CONTACT:
Thomas Stafford, Aerospace Engineer,
International Branch, ANM–116, FAA,
Transport Airplane Directorate, 1601
Lind Avenue, SW., Renton, Washington
98057–3356; telephone (425) 227–1622;
fax (425) 227–1149.
SUPPLEMENTARY INFORMATION:
Discussion
The FAA issued a notice of proposed
rulemaking (NPRM) to amend 14 CFR
part 39 to include an AD that
supersedes AD 2003–06–04, amendment
39–13091 (68 FR 14894, March 27,
2003). The existing AD applies to all
Airbus Model A300 B2 and B4 series
airplanes; and all Model A300 B4–600,
B4–600R, and F4–600R (collectively
called A300–600) series airplanes. That
NPRM was published in the Federal
Register on April 20, 2007 (72 FR
19818). That NPRM proposed to
continue to require repetitive
inspections to detect cracking of the
upper radius of the forward fitting of
frame 47, and repair if necessary. That
NPRM also proposed to reduce
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Federal Register / Vol. 73, No. 11 / Wednesday, January 16, 2008 / Rules and Regulations
inspection thresholds and repetitive
intervals, and to add related
investigative and corrective actions.
That NPRM also proposed to provide an
optional terminating action for the
repetitive inspections only for airplanes
with cracking that is within certain
limits.
Comments
We provided the public the
opportunity to participate in the
development of this AD. We have
considered the comments that have
been received on the NPRM.
Request To Clarify Requirements of
Paragraph (l) of the NPRM
Air Transport Association (ATA), on
behalf of its member American Airlines
(AA), and supported by Airbus, points
out that paragraph (l)(2) of the NPRM
specifies performing repetitive
inspections on airplanes with cracks
‘‘30 millimeters (mm) (1.181 inch) or
less in length.’’ AA believes that the
length should be 50 mm. AA explains
that Table 2 (Figure 1, Sheet 1) of Airbus
Service Bulletin A300–53–6029,
Revision 08, dated October 19, 2005 (for
Model A300–600 series airplanes),
allows repetitive inspections for cracks
equal to or less than 50 mm. AA also
points out that the table titled ‘‘Related
Investigative and Corrective Actions
Following Eddy Current Inspection’’ in
the ‘‘Relevant Service Information’’
section of the NPRM states that
repetitive inspections are applicable for
cracks equal to or less than 50 mm in
size.
We agree that paragraph (l)(2) of the
NPRM needs to be clarified. Therefore,
we have revised paragraph (l)(2) of the
AD to clarify the crack size that applies
to each model.
Request To Apply Certain Actions Only
to Airplanes With Known Cracks
ATA, on behalf of its member AA,
states that paragraph (m), ‘‘Abnormal
Load Events,’’ of the NPRM should
apply only to airplanes with known
cracks. Airbus supports this statement.
AA explains that Figure 1, Sheet 1, of
Airbus Service Bulletin A300–53–6029,
Revision 08, requires the inspections
only if a crack exists. AA also points out
that the table titled ‘‘Related
Investigative and Corrective Actions
Following Eddy Current Inspection’’ in
the ‘‘Relevant Service Information’’
section of the NPRM states that the
inspection is for an ‘‘abnormal load
event on an airplane with any crack
finding.’’
We agree with the commenters for the
reasons stated by the commenters.
Paragraph (m) of the AD should apply
only to airplanes with known cracks.
We have revised paragraph (m) of this
AD to state that it applies only to
airplanes on which any crack was found
during any inspection required by this
AD.
Request To Refer to Latest Revision of
Service Bulletin
Airbus states that Airbus Service
Bulletin A300–53–6144, dated July 16,
2004, which we referred to in the NPRM
as the appropriate source of service
information for accomplishing the
optional terminating action, has now
been revised. Airbus requests that we
refer to Airbus Service Bulletin A300–
53–6144, Revision 01, dated October 15,
2007.
We agree with the request to refer to
Revision 01 of Airbus Service Bulletin
A300–53–6144. The procedures in
Revision 01 and the original issue are
essentially the same. Revision 01 revises
the effectivity of the service bulletin, but
states that no additional work is
required for airplanes modified in
accordance with the previous issue. We
have revised paragraph (n) of this AD to
refer to Revision 01 of the service
bulletin. We have also revised
paragraph (r) of this AD to give credit
to operators that have accomplished the
actions in accordance with the previous
issue of the service bulletin.
Request To Revise Contact Information
Airbus requests that we revise the
address for submitting reports of
inspection findings in paragraph (q) of
the NPRM. We have revised paragraph
(q) of the AD to include the information
provided by Airbus.
Explanation of Clarifications
We have clarified paragraph (m) of the
AD by replacing the ‘‘or’’ with an ‘‘and’’
in the statement ‘‘Do the actions in
paragraph (m)(1), (m)(2), or (m)(3), as
applicable * * *’’ An ‘‘and’’ in this case
more clearly conveys the intent of the
paragraph because it is possible that
operators might need to do more than
one of those actions.
We have also revised paragraph (s)(2)
of the AD to clarify the appropriate
procedure for notifying the principal
inspector before using any approved
AMOC on any airplane to which the
AMOC applies.
Conclusion
We have carefully reviewed the
available data, including the comments
that have been received, and determined
that air safety and the public interest
require adopting the AD with the
changes described previously. We have
determined that these changes will
neither increase the economic burden
on any operator nor increase the scope
of the AD.
Costs of Compliance
There are about 163 U.S.-registered
airplanes that are affected by this AD.
The following table provides the
estimated costs for U.S. operators to
comply with this AD. The average labor
rate is $80 per work hour.
ESTIMATED COSTS
Work
hours
Action
Parts
Cost per airplane
Fleet cost
$117,360, per inspection
cycle.
$13,040, per inspection cycle.
Actions required by AD 2003–06–04 ............................
9
$0
$720, per inspection cycle ......
Inspection (new action) .................................................
1
$0
$80, per inspection cycle ........
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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
VerDate Aug<31>2005
15:01 Jan 15, 2008
Jkt 214001
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
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Frm 00012
Fmt 4700
Sfmt 4700
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
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Federal Register / Vol. 73, No. 11 / Wednesday, January 16, 2008 / Rules and Regulations
products identified in this rulemaking
action.
Regulatory Findings
We have determined that this AD will
not have federalism implications under
Executive Order 13132. This AD will
not have a substantial direct effect on
the States, on the relationship between
the national government and the States,
or on the distribution of power and
responsibilities among the various
levels of government.
For the reasons discussed above, I
certify that this AD:
(1) Is not a ‘‘significant regulatory
action’’ under Executive Order 12866;
(2) Is not a ‘‘significant rule’’ under
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.
See the ADDRESSES section for a location
to examine the regulatory evaluation.
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:
I
PART 39—AIRWORTHINESS
DIRECTIVES
1. The authority citation for part 39
continues to read as follows:
I
Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13
[Amended]
2. The Federal Aviation
Administration (FAA) amends § 39.13
by removing amendment 39–13091 (68
FR 14894, March 27, 2003) and by
adding the following new airworthiness
directive (AD):
I
2007–26–14 Airbus: Amendment 39–15316.
Docket No. FAA–2007–27926;
Directorate Identifier 2006–NM–050–AD.
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Effective Date
(a) This AD becomes effective February 20,
2008.
Affected ADs
(b) This AD supersedes AD 2003–06–04.
Applicability
(c) This AD applies to all Airbus Model
A300 airplanes; and all Model A300 B4–601,
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15:01 Jan 15, 2008
Jkt 214001
B4–603, B4–620, B4–622, B4–605R, B4–
622R, F4–605R, F4–622R, and C4–605R
Variant F airplanes; certificated in any
category.
Unsafe Condition
(d) This AD results from reports of
additional cracking in airplanes that were
inspected in accordance with AD 2003–06–
04. We are issuing this AD to detect and
correct fatigue cracking of the left and right
upper radius at frame 47, which could
propagate and result in reduced structural
integrity of the airplane.
Compliance
(e) You are responsible for having the
actions required by this AD performed within
the compliance times specified, unless the
actions have already been done.
Requirements of AD 2003–06–04
Model A300–600: Inspection
(f) For Model A300–600 series airplanes:
At the earlier of the times specified by
paragraphs (f)(1) and (f)(2) of this AD,
perform an eddy current inspection to detect
cracking of the upper radius of the left and
right forward fitting of frame 47, in
accordance with Airbus Service Bulletin
A300–53–6029, Revision 02, dated November
7, 1994; Revision 05, including Appendix 01,
dated April 11, 2001; or Revision 08,
including Appendix 01, dated October 19,
2005. After the effective date of this AD, only
Revision 08 of the service bulletin may be
used.
(1) Before the accumulation of 17,300 total
flight cycles, or within one year after October
16, 1996 (the effective date of AD 96–18–18,
amendment 39–9744), whichever occurs
later.
(2) At the later of the times specified by
paragraphs (f)(2)(i) and (f)(2)(ii) of this AD.
(i) Before the accumulation of 10,000 total
flight cycles or 26,000 total flight hours,
whichever occurs first.
(ii) Within 750 flight cycles or 1,900 flight
hours, whichever occurs first after May 1,
2003 (the effective date of AD 2003–06–04).
Model A300–600: Follow-On (Repetitive)
Inspections
(g) For Model A300–600 series airplanes on
which no cracking is found during any
inspection required by paragraph (f) of this
AD, repeat the inspection required by
paragraph (f) of this AD at the applicable
times specified in paragraphs (g)(1) and (g)(2)
of this AD until the inspection required by
paragraph (j) of this AD is done.
(1) If the initial inspection was
accomplished before May 1, 2003, repeat the
inspection at the later of the times specified
in paragraphs (g)(1)(i) and (g)(1)(ii) of this
AD. Thereafter, repeat the inspection at
intervals not to exceed 6,100 flight cycles or
15,600 flight hours, whichever occurs first.
(i) Re-inspect within 6,100 flight cycles
after the initial inspection.
(ii) Re-inspect within 750 flight cycles or
1,900 flight hours, whichever occurs first
after May 1, 2003.
(2) If the initial inspection was not
accomplished before May 1, 2003, repeat the
inspection thereafter at intervals not to
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Fmt 4700
Sfmt 4700
2805
exceed 6,100 flight cycles or 15,600 flight
hours, whichever occurs first.
Model A300–600: Corrective Action
(h) For Model A300–600 series airplanes
on which any cracking is found during any
inspection required by paragraph (f) of this
AD: Before further flight, contact the
Manager, International Branch, ANM–116,
Transport Airplane Directorate, FAA; or the
´ ´
Direction Generale de l’Aviation Civile
(DGAC) (or its delegated representative); or
the European Aviation Safety Agency (EASA)
(or its delegated agent); for instructions
regarding repair or for an applicable reinspection interval, in accordance with
Airbus Service Bulletin A300–53–6029,
Revision 05, including Appendix 01, dated
April 11, 2001; or Revision 08, including
Appendix 01, dated October 19, 2005. After
the effective date of this AD, only Revision
08 may be used. Repair and/or re-inspection
accomplished before May 1, 2003, in
accordance with a method approved by the
Manager, International Branch, ANM–116, is
acceptable for compliance with the
requirements of paragraph (h) of this AD.
Model A300 B2 and B4: Repetitive
Inspections and Follow-On Actions
(i) For Model A300 B2 and B4 series
airplanes: At the applicable time specified in
paragraph (i)(1), (i)(2), or (i)(3) of this AD,
perform repetitive eddy current inspections
to detect cracking of the upper radius of the
forward fitting of frame 47, left and right
sides, per Airbus Service Bulletin A300–53–
0246, Revision 03, including Appendix 01,
dated April 11, 2001; or Revision 06,
including Appendix 01, dated October 19,
2005. After the effective date of this AD, only
Revision 06 may be used. Accomplishing this
requirement terminates the corresponding
inspection requirement of the A300
Supplemental Structural Inspection
Document (SSID) for Model A300 B2 and B4
series airplanes. (That SSID is mandated by
AD 96–13–11, amendment 39–9679.)
(1) For Model A300 B2 series airplanes:
Perform the initial inspection at the later of
the times specified by paragraphs (i)(1)(i) and
(i)(1)(ii) of this AD. Repeat the inspection
thereafter at intervals not to exceed 10,400
flight cycles or 13,300 flight hours,
whichever occurs first, until the inspection
required by paragraph (j) of this AD is done.
(i) Before the accumulation of 16,500 total
flight cycles or 21,000 total flight hours,
whichever occurs first.
(ii) Within 1,000 flight cycles or 1,300
flight hours after May 1, 2003, whichever
occurs first.
(2) For Model A300 B4–100 series
airplanes: Perform the initial inspection at
the later of the times specified by paragraphs
(i)(2)(i) and (i)(2)(ii) of this AD. Repeat the
inspection thereafter at intervals not to
exceed 8,500 flight cycles or 16,400 flight
hours, whichever occurs first, until the
inspection required by paragraph (j) of this
AD is done.
(i) Before the accumulation of 10,300 total
flight cycles or 19,800 total flight hours,
whichever occurs first.
(ii) Within 750 flight cycles or 1,500 flight
hours after May 1, 2003, whichever occurs
first.
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Federal Register / Vol. 73, No. 11 / Wednesday, January 16, 2008 / Rules and Regulations
(3) For Model A300 B4–200 series
airplanes: Perform the initial inspection at
the later of the times specified by paragraphs
(i)(3)(i) and (i)(3)(ii) of this AD. Repeat the
inspection thereafter at intervals not to
exceed 7,000 flight cycles or 13,600 flight
hours, whichever occurs first, until the
inspection required by paragraph (j) of this
AD is done.
(i) Before the accumulation of 11,000 total
flight cycles or 21,200 total flight hours,
whichever occurs first.
(ii) Within 750 flight cycles or 1,500 flight
hours after May 1, 2003, whichever occurs
first.
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New Requirements of This AD
Inspections and Corrective Actions
(j) At the applicable time in paragraph (k)
or (l) of this AD: Except as provided by
paragraphs (n) and (p) of this AD, do an eddy
current inspection to detect cracking of the
upper radius of the forward fitting of frame
47, and do all applicable related investigative
and corrective actions, by accomplishing all
the applicable actions specified in the
Accomplishment Instructions of the
applicable service bulletin specified in
paragraph (j)(1) or (j)(2) of this AD. Do all
applicable investigative and corrective
actions before further flight. Where the
service bulletins specify to contact Airbus for
repair instructions: Before further flight,
repair using a method approved by either the
Manager, International Branch, ANM–116; or
the EASA (or its delegated agent). Doing the
inspections required by this paragraph
terminates the inspections required by
paragraphs (f), (g), and (i) of this AD.
(1) For Airbus Model A300 airplanes:
Airbus Service Bulletin A300–53–0246,
Revision 06, including Appendix 01, dated
October 19, 2005.
(2) For Airbus Model A300 B4–601, B4–
603, B4–620, B4–622, B4–605R, B4–622R,
F4–605R, F4–622R, and C4–605R Variant F
airplanes: Airbus Service Bulletin A300–53–
6029, Revision 08, including Appendix 01,
dated October 19, 2005.
(k) For airplanes on which the inspection
required by paragraph (f), (g), or (i) of this
AD, as applicable, has not been done prior
to the effective date of this AD: Do the initial
inspection required by paragraph (j) of this
AD before the accumulation of 10,000 total
flight cycles, or within 1,400 flight cycles
after the effective date of this AD, whichever
occurs later. Repeat the inspection thereafter
at the applicable interval specified in Figure
1, Sheet 1, of the Accomplishment
Instructions of the applicable service
bulletin.
(l) For airplanes on which the inspection
required by paragraph (f), (g), or (i) of this
AD, as applicable, has been done prior to the
effective date of this AD: Inspect at the
applicable times specified in paragraph (l)(1)
or (l)(2) of this AD. Repeat the inspection
thereafter at the applicable interval specified
in Figure 1, Sheet 1, of the Accomplishment
Instructions of the applicable service
bulletin.
(1) For airplanes on which no cracking was
found during any inspection required by this
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15:01 Jan 15, 2008
Jkt 214001
AD: Do the next inspection at the earlier of
the times specified in paragraphs (l)(1)(i) and
(l)(1)(ii) of this AD.
(i) At the next repetitive interval specified
in the applicable service bulletin specified in
paragraph (j)(1) or (j)(2) of this AD, or within
1,400 flight cycles after the effective date of
this AD, whichever occurs later.
(ii) At the next repetitive interval specified
in paragraph (g) or (i) of this AD, as
applicable.
(2) For airplanes on which any crack was
found during any inspection required by this
AD, and the crack is the size specified in
paragraph (l)(2)(i), (l)(2)(ii), or (l)(2)(iii) of
this AD: Do the next inspection at the
applicable times specified in paragraph
(l)(2)(i), (l)(2)(ii), or (l)(2)(iii) of this AD, as
applicable.
(i) For Airbus Model A300 airplanes on
which the crack is 30 millimeters (mm)
(1.181 inch) or less in length: At the next
repetitive interval specified in the service
bulletin specified in paragraph (j)(1) of this
AD, or within 500 flight cycles after the
effective date of this AD, whichever occurs
later.
(ii) For Airbus Model A300 airplanes on
which the crack is greater than 30
millimeters (mm) (1.181 inch) in length, but
less than or equal to 50 mm in length (1.97
inch): At the next repetitive interval specified
in paragraph (l) of this AD (Figure 1, Sheet
1, of the Accomplishment Instructions of the
applicable service bulletin).
(iii) For Airbus Model A300 B4–601, B4–
603, B4–620, B4–622, B4–605R, B4–622R,
F4–605R, F4–622R, and C4–605R Variant F
airplanes on which the crack is 50 mm (1.97
inch) or less in length: At the next repetitive
interval specified in the service bulletin
specified in paragraph (j)(2) of this AD;
without, however, exceeding the previous
inspection interval specified in paragraph (g)
of this AD.
Abnormal Load Events
(m) For airplanes on which any crack was
found during any inspection required by this
AD and on which any abnormal load event
occurs after the effective date of this AD: Do
the actions in paragraphs (m)(1), (m)(2), and
(m)(3) of this AD, as applicable, at the time
specified in the applicable paragraph.
(1) Within 3 months after the event, or at
the next applicable repetitive interval
required by paragraph (k) or (l) of this AD,
whichever occurs first: Do the next repetitive
inspection required by paragraph (j) of this
AD.
(2) Before further flight following any
additional abnormal load event that occurs
following the first event but before the next
repetitive inspection required by paragraph
(k) or (l) of this AD: Contact the Manager,
International Branch, ANM–116, or the
EASA (or its delegated agent), for further
instructions.
(3) Within 3 months after any abnormal
load event: Report the event to Airbus in
accordance with the requirements of
paragraph (q) of this AD.
PO 00000
Frm 00014
Fmt 4700
Sfmt 4700
Optional Terminating Action (Repair) for
Certain Cracks
(n) Repairing any crack greater than 30 mm
but less than or equal to 50 mm in size, in
accordance with the Accomplishment
Instructions of Airbus Service Bulletin A300–
53–0370, including Appendix 01, dated July
16, 2004; or Airbus Service Bulletin A300–
53–6144, Revision 01, including Appendix
01, dated July October 15, 2007; as
applicable; terminates the repetitive
inspection requirements of paragraph (k) or
(l) of this AD for that area only. Where the
service bulletins specify to contact Airbus for
repair instructions: Repair the crack using a
method approved by either the Manager,
International Branch, ANM–116; or the
EASA (or its delegated agent).
Repetitive Inspections Following Optional
Terminating Action
(o) Within 6 months after repair in
accordance with paragraph (n) of this AD:
Submit a post-repair inspection program for
monitoring the repair to the Manager,
International Branch, ANM–116, for
approval.
Repair of Any Crack Greater than 50 mm in
Size
(p) If any crack that is greater than 50 mm
in size is found during any inspection
required by paragraph (j), (k), or (l) of this
AD: Before further flight, repair according to
a method approved by the Manager,
International Branch, ANM–116.
Reporting Requirement
(q) At the applicable time specified in
paragraph (q)(1) or (q)(2) of this AD: Submit
a report of all results of each inspection
required by this AD to Airbus, 1 Rond Point
Maurice Bellonte, 31707 Blagnac Cedex,
France, Attention: Davide Cavazzini, fax 33–
5–61–93–36–14. The report must include the
inspection results, a description of any
discrepancies found, the airplane serial
number, and the number of landings and
flight hours on the airplane. Information
collection requirements contained in this AD
have been approved by the Office of
Management and Budget (OMB) under the
provisions of the Paperwork Reduction Act
(44 U.S.C. 3501 et seq.) and have been
assigned OMB Control Number 2120–0056.
(1) For airplanes on which the inspection
is accomplished after the effective date of
this AD: Submit the report within 30 days
after performing the inspection.
(2) For airplanes on which the inspection
has been accomplished before the effective
date of this AD: Submit the report within 30
days after the effective date of this AD.
Actions Accomplished in Accordance With
Previous Issues of Service Bulletins
(r) Actions done before the effective date of
this AD in accordance with the service
bulletins listed in Table 1 of this AD are
acceptable for compliance with the
corresponding requirements of paragraphs (i),
(j), and (n) of this AD.
E:\FR\FM\16JAR1.SGM
16JAR1
2807
Federal Register / Vol. 73, No. 11 / Wednesday, January 16, 2008 / Rules and Regulations
TABLE 1.—PREVIOUS ISSUES OF SERVICE BULLETINS
Airbus Service
Bulletin
Model
A300 airplanes .................................................................................................
Revision level
Date
Alternative Methods of Compliance
(AMOCs)
(s)(1) The Manager, International Branch,
ANM–116, has the authority to approve
AMOCs for this AD, if requested in
accordance with the procedures found in 14
CFR 39.19.
(2) To request a different method of
compliance or a different compliance time
for this AD, follow the procedures in 14 CFR
03
04
05
05
..............................
..............................
..............................
..............................
April 11, 2001.
November 12, 2002.
January 19, 2004.
April 11, 2001.
A300–53–6029
A300–53–6029
A300–53–6144
A300 B4–601, B4–603, B4–620, B4–622, B4–605R, B4–622R, F4–605R,
F4–622R, and C4–605R Variant F airplanes.
A300–53–0246
A300–53–0246
A300–53–0246
A300–53–6029
06 ..............................
07 ..............................
Original ......................
November 12, 2002.
January 19, 2004.
July 16, 2004.
39.19. Before using any approved AMOC on
any airplane to which the AMOC applies,
notify your appropriate principal inspector
(PI) in the FAA Flight Standards District
Office (FSDO), or lacking a PI, your local
FSDO.
(3) AMOCs approved previously in
accordance with AD 2003–06–04 are
approved as AMOCs with this AD until
paragraph (j) of this AD is accomplished.
Related Information
(t) French airworthiness directive F–2006–
016, dated January 18, 2006, also addresses
the subject of this AD.
Material Incorporated by Reference
(u) You must use the service information
listed in Table 2 of this AD to perform the
actions that are required by this AD, unless
the AD specifies otherwise.
TABLE 2.—ALL MATERIAL INCORPORATED BY REFERENCE
Airbus Service Bulletin
Revision level
A300–53–0246, including Appendix 01 ...........................................................................................
A300–53–0246, including Appendix 01 ...........................................................................................
A300–53–0370, including Appendix 01 ...........................................................................................
A300–53–6029 .................................................................................................................................
A300–53–6029, including Appendix 01 ...........................................................................................
A300–53–6029, including Appendix 01 ...........................................................................................
A300–53–6144, including Appendix 01 ...........................................................................................
03 ..............................
06 ..............................
Original ......................
02 ..............................
05 ..............................
08 ..............................
Original ......................
(1) The Director of the Federal Register
approved the incorporation by reference of
the documents listed in Table 3 of this AD
Date
April 11, 2001.
October 19, 2005.
July 16, 2004.
November 7, 1994.
April 11, 2001.
October 19, 2005.
July 16, 2004.
in accordance with 5 U.S.C. 552(a) and 1 CFR
part 51.
TABLE 3.—NEW MATERIAL INCORPORATED BY REFERENCE
Airbus Service Bulletin
A300–53–0246,
A300–53–0370,
A300–53–6029,
A300–53–6144,
including
including
including
including
Appendix
Appendix
Appendix
Appendix
01
01
01
01
Revision level
...........................................................................................
...........................................................................................
...........................................................................................
...........................................................................................
(2) On May 1, 2003 (68 FR 14894, March
27, 2003), the Director of the Federal Register
06 ..............................
Original ......................
08 ..............................
Original ......................
Date
October 19, 2005.
July 16, 2004.
October 19, 2005.
July 16, 2004.
approved the incorporation by reference of
the documents listed in Table 4 of this AD.
TABLE 4.—MATERIAL INCORPORATED BY REFERENCE IN PREVIOUS AD
Revision level
A300–53–0246, including Appendix 01 ...........................................................................................
A300–53–6029, including Appendix 01 ...........................................................................................
ebenthall on PRODPC61 with RULES
Airbus Service Bulletin
03 ..............................
05 ..............................
(3) On October 16, 1996 (61 FR 47808,
September 11, 1996), the Director of the
Federal Register approved the incorporation
by reference of Airbus Service Bulletin
A300–53–6029, Revision 02, dated November
7, 1994.
(4) Contact Airbus, 1 Rond Point Maurice
Bellonte, 31707 Blagnac Cedex, France, for a
copy of this service information. You may
Issued in Renton, Washington, on
December 19, 2007.
Ali Bahrami,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. E7–25503 Filed 1–15–08; 8:45 am]
VerDate Aug<31>2005
15:01 Jan 15, 2008
Jkt 214001
review copies at the FAA, Transport Airplane
Directorate, 1601 Lind Avenue, SW., Renton,
Washington; or at the National Archives and
Records Administration (NARA). For
information on the availability of this
material at NARA, call 202–741–6030, or go
to: https://www.archives.gov/federal-register/
cfr/ibr-locations.html.
PO 00000
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Fmt 4700
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BILLING CODE 4910–13–P
E:\FR\FM\16JAR1.SGM
16JAR1
Date
April 11, 2001.
April 11, 2001.
]]>Agencies
[Federal Register Volume 73, Number 11 (Wednesday, January 16, 2008)]
[Rules and Regulations]
[Pages 2803-2807]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E7-25503]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2007-27926; Directorate Identifier 2006-NM-050-AD;
Amendment 39-15316; AD 2007-26-14]
RIN 2120-AA64
Airworthiness Directives; Airbus Model A300 Airplanes; and Model
A300 B4-600, B4-600R, and F4-600R Series Airplanes, and Model C4-605R
Variant F Airplanes (Collectively Called A300-600 Series Airplanes)
AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
-----------------------------------------------------------------------
SUMMARY: The FAA is superseding an existing airworthiness directive
(AD), which applies to all Airbus Model A300 B2 and B4 series
airplanes; and all Model A300 B4-600, B4-600R, and F4-600R
(collectively called A300-600) series airplanes. That AD currently
requires repetitive inspections to detect cracking of the upper radius
of the forward fitting of frame 47, and repair if necessary. This new
AD retains those requirements, but reduces inspection thresholds and
repetitive intervals, and adds related investigative and corrective
actions. This AD also provides an optional terminating action for the
repetitive inspections only for airplanes with cracking that is within
certain limits, and a post-repair inspection program following the
optional terminating action. This AD results from reports of additional
cracking in airplanes that were inspected in accordance with the
existing AD. We are issuing this AD to detect and correct fatigue
cracking of the left and right upper radius at frame 47, which could
propagate and result in reduced structural integrity of the airplane.
DATES: This AD becomes effective February 20, 2008.
The Director of the Federal Register approved the incorporation by
reference of certain publications listed in the AD as of February 20,
2008.
On May 1, 2003 (68 FR 14894, March 27, 2003), the Director of the
Federal Register approved the incorporation by reference of certain
publications listed in the AD.
ADDRESSES: For service information identified in this AD, contact
Airbus, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France.
Examining the AD Docket
You may examine the AD docket on the Internet at https://
www.regulations.gov; or in person at the Docket Management Facility
between 9 a.m. and 5 p.m., Monday through Friday, except Federal
holidays. The AD docket contains this AD, the regulatory evaluation,
any comments received, and other information. The address for the
Docket Office (telephone 800-647-5527) is the Document Management
Facility, U.S. Department of Transportation, Docket Operations, M-30,
West Building Ground Floor, Room W12-140, 1200 New Jersey Avenue, SE.,
Washington, DC 20590.
FOR FURTHER INFORMATION CONTACT: Thomas Stafford, Aerospace Engineer,
International Branch, ANM-116, FAA, Transport Airplane Directorate,
1601 Lind Avenue, SW., Renton, Washington 98057-3356; telephone (425)
227-1622; fax (425) 227-1149.
SUPPLEMENTARY INFORMATION:
Discussion
The FAA issued a notice of proposed rulemaking (NPRM) to amend 14
CFR part 39 to include an AD that supersedes AD 2003-06-04, amendment
39-13091 (68 FR 14894, March 27, 2003). The existing AD applies to all
Airbus Model A300 B2 and B4 series airplanes; and all Model A300 B4-
600, B4-600R, and F4-600R (collectively called A300-600) series
airplanes. That NPRM was published in the Federal Register on April 20,
2007 (72 FR 19818). That NPRM proposed to continue to require
repetitive inspections to detect cracking of the upper radius of the
forward fitting of frame 47, and repair if necessary. That NPRM also
proposed to reduce
[[Page 2804]]
inspection thresholds and repetitive intervals, and to add related
investigative and corrective actions. That NPRM also proposed to
provide an optional terminating action for the repetitive inspections
only for airplanes with cracking that is within certain limits.
Comments
We provided the public the opportunity to participate in the
development of this AD. We have considered the comments that have been
received on the NPRM.
Request To Clarify Requirements of Paragraph (l) of the NPRM
Air Transport Association (ATA), on behalf of its member American
Airlines (AA), and supported by Airbus, points out that paragraph
(l)(2) of the NPRM specifies performing repetitive inspections on
airplanes with cracks ``30 millimeters (mm) (1.181 inch) or less in
length.'' AA believes that the length should be 50 mm. AA explains that
Table 2 (Figure 1, Sheet 1) of Airbus Service Bulletin A300-53-6029,
Revision 08, dated October 19, 2005 (for Model A300-600 series
airplanes), allows repetitive inspections for cracks equal to or less
than 50 mm. AA also points out that the table titled ``Related
Investigative and Corrective Actions Following Eddy Current
Inspection'' in the ``Relevant Service Information'' section of the
NPRM states that repetitive inspections are applicable for cracks equal
to or less than 50 mm in size.
We agree that paragraph (l)(2) of the NPRM needs to be clarified.
Therefore, we have revised paragraph (l)(2) of the AD to clarify the
crack size that applies to each model.
Request To Apply Certain Actions Only to Airplanes With Known Cracks
ATA, on behalf of its member AA, states that paragraph (m),
``Abnormal Load Events,'' of the NPRM should apply only to airplanes
with known cracks. Airbus supports this statement. AA explains that
Figure 1, Sheet 1, of Airbus Service Bulletin A300-53-6029, Revision
08, requires the inspections only if a crack exists. AA also points out
that the table titled ``Related Investigative and Corrective Actions
Following Eddy Current Inspection'' in the ``Relevant Service
Information'' section of the NPRM states that the inspection is for an
``abnormal load event on an airplane with any crack finding.''
We agree with the commenters for the reasons stated by the
commenters. Paragraph (m) of the AD should apply only to airplanes with
known cracks. We have revised paragraph (m) of this AD to state that it
applies only to airplanes on which any crack was found during any
inspection required by this AD.
Request To Refer to Latest Revision of Service Bulletin
Airbus states that Airbus Service Bulletin A300-53-6144, dated July
16, 2004, which we referred to in the NPRM as the appropriate source of
service information for accomplishing the optional terminating action,
has now been revised. Airbus requests that we refer to Airbus Service
Bulletin A300-53-6144, Revision 01, dated October 15, 2007.
We agree with the request to refer to Revision 01 of Airbus Service
Bulletin A300-53-6144. The procedures in Revision 01 and the original
issue are essentially the same. Revision 01 revises the effectivity of
the service bulletin, but states that no additional work is required
for airplanes modified in accordance with the previous issue. We have
revised paragraph (n) of this AD to refer to Revision 01 of the service
bulletin. We have also revised paragraph (r) of this AD to give credit
to operators that have accomplished the actions in accordance with the
previous issue of the service bulletin.
Request To Revise Contact Information
Airbus requests that we revise the address for submitting reports
of inspection findings in paragraph (q) of the NPRM. We have revised
paragraph (q) of the AD to include the information provided by Airbus.
Explanation of Clarifications
We have clarified paragraph (m) of the AD by replacing the ``or''
with an ``and'' in the statement ``Do the actions in paragraph (m)(1),
(m)(2), or (m)(3), as applicable * * *'' An ``and'' in this case more
clearly conveys the intent of the paragraph because it is possible that
operators might need to do more than one of those actions.
We have also revised paragraph (s)(2) of the AD to clarify the
appropriate procedure for notifying the principal inspector before
using any approved AMOC on any airplane to which the AMOC applies.
Conclusion
We have carefully reviewed the available data, including the
comments that have been received, and determined that air safety and
the public interest require adopting the AD with the changes described
previously. We have determined that these changes will neither increase
the economic burden on any operator nor increase the scope of the AD.
Costs of Compliance
There are about 163 U.S.-registered airplanes that are affected by
this AD. The following table provides the estimated costs for U.S.
operators to comply with this AD. The average labor rate is $80 per
work hour.
Estimated Costs
--------------------------------------------------------------------------------------------------------------------------------------------------------
Work
Action hours Parts Cost per airplane Fleet cost
--------------------------------------------------------------------------------------------------------------------------------------------------------
Actions required by AD 2003-06-04.... 9 $0 $720, per inspection cycle................... $117,360, per inspection cycle.
Inspection (new action).............. 1 $0 $80, per inspection cycle.................... $13,040, per inspection cycle.
--------------------------------------------------------------------------------------------------------------------------------------------------------
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
[[Page 2805]]
products identified in this rulemaking action.
Regulatory Findings
We have determined that this AD will not have federalism
implications under Executive Order 13132. This AD will not have a
substantial direct effect on the States, on the relationship between
the national government and the States, or on the distribution of power
and responsibilities among the various levels of government.
For the reasons discussed above, I certify that this AD:
(1) Is not a ``significant regulatory action'' under Executive
Order 12866;
(2) Is not a ``significant rule'' under 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. See the ADDRESSES
section for a location to examine the regulatory evaluation.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.
Adoption of the Amendment
0
Accordingly, under the authority delegated to me by the Administrator,
the FAA amends 14 CFR part 39 as follows:
PART 39--AIRWORTHINESS DIRECTIVES
0
1. The authority citation for part 39 continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
Sec. 39.13 [Amended]
0
2. The Federal Aviation Administration (FAA) amends Sec. 39.13 by
removing amendment 39-13091 (68 FR 14894, March 27, 2003) and by adding
the following new airworthiness directive (AD):
2007-26-14 Airbus: Amendment 39-15316. Docket No. FAA-2007-27926;
Directorate Identifier 2006-NM-050-AD.
Effective Date
(a) This AD becomes effective February 20, 2008.
Affected ADs
(b) This AD supersedes AD 2003-06-04.
Applicability
(c) This AD applies to all Airbus Model A300 airplanes; and all
Model A300 B4-601, B4-603, B4-620, B4-622, B4-605R, B4-622R, F4-
605R, F4-622R, and C4-605R Variant F airplanes; certificated in any
category.
Unsafe Condition
(d) This AD results from reports of additional cracking in
airplanes that were inspected in accordance with AD 2003-06-04. We
are issuing this AD to detect and correct fatigue cracking of the
left and right upper radius at frame 47, which could propagate and
result in reduced structural integrity of the airplane.
Compliance
(e) You are responsible for having the actions required by this
AD performed within the compliance times specified, unless the
actions have already been done.
Requirements of AD 2003-06-04
Model A300-600: Inspection
(f) For Model A300-600 series airplanes: At the earlier of the
times specified by paragraphs (f)(1) and (f)(2) of this AD, perform
an eddy current inspection to detect cracking of the upper radius of
the left and right forward fitting of frame 47, in accordance with
Airbus Service Bulletin A300-53-6029, Revision 02, dated November 7,
1994; Revision 05, including Appendix 01, dated April 11, 2001; or
Revision 08, including Appendix 01, dated October 19, 2005. After
the effective date of this AD, only Revision 08 of the service
bulletin may be used.
(1) Before the accumulation of 17,300 total flight cycles, or
within one year after October 16, 1996 (the effective date of AD 96-
18-18, amendment 39-9744), whichever occurs later.
(2) At the later of the times specified by paragraphs (f)(2)(i)
and (f)(2)(ii) of this AD.
(i) Before the accumulation of 10,000 total flight cycles or
26,000 total flight hours, whichever occurs first.
(ii) Within 750 flight cycles or 1,900 flight hours, whichever
occurs first after May 1, 2003 (the effective date of AD 2003-06-
04).
Model A300-600: Follow-On (Repetitive) Inspections
(g) For Model A300-600 series airplanes on which no cracking is
found during any inspection required by paragraph (f) of this AD,
repeat the inspection required by paragraph (f) of this AD at the
applicable times specified in paragraphs (g)(1) and (g)(2) of this
AD until the inspection required by paragraph (j) of this AD is
done.
(1) If the initial inspection was accomplished before May 1,
2003, repeat the inspection at the later of the times specified in
paragraphs (g)(1)(i) and (g)(1)(ii) of this AD. Thereafter, repeat
the inspection at intervals not to exceed 6,100 flight cycles or
15,600 flight hours, whichever occurs first.
(i) Re-inspect within 6,100 flight cycles after the initial
inspection.
(ii) Re-inspect within 750 flight cycles or 1,900 flight hours,
whichever occurs first after May 1, 2003.
(2) If the initial inspection was not accomplished before May 1,
2003, repeat the inspection thereafter at intervals not to exceed
6,100 flight cycles or 15,600 flight hours, whichever occurs first.
Model A300-600: Corrective Action
(h) For Model A300-600 series airplanes on which any cracking is
found during any inspection required by paragraph (f) of this AD:
Before further flight, contact the Manager, International Branch,
ANM-116, Transport Airplane Directorate, FAA; or the Direction
G[eacute]n[eacute]rale de l'Aviation Civile (DGAC) (or its delegated
representative); or the European Aviation Safety Agency (EASA) (or
its delegated agent); for instructions regarding repair or for an
applicable re-inspection interval, in accordance with Airbus Service
Bulletin A300-53-6029, Revision 05, including Appendix 01, dated
April 11, 2001; or Revision 08, including Appendix 01, dated October
19, 2005. After the effective date of this AD, only Revision 08 may
be used. Repair and/or re-inspection accomplished before May 1,
2003, in accordance with a method approved by the Manager,
International Branch, ANM-116, is acceptable for compliance with the
requirements of paragraph (h) of this AD.
Model A300 B2 and B4: Repetitive Inspections and Follow-On Actions
(i) For Model A300 B2 and B4 series airplanes: At the applicable
time specified in paragraph (i)(1), (i)(2), or (i)(3) of this AD,
perform repetitive eddy current inspections to detect cracking of
the upper radius of the forward fitting of frame 47, left and right
sides, per Airbus Service Bulletin A300-53-0246, Revision 03,
including Appendix 01, dated April 11, 2001; or Revision 06,
including Appendix 01, dated October 19, 2005. After the effective
date of this AD, only Revision 06 may be used. Accomplishing this
requirement terminates the corresponding inspection requirement of
the A300 Supplemental Structural Inspection Document (SSID) for
Model A300 B2 and B4 series airplanes. (That SSID is mandated by AD
96-13-11, amendment 39-9679.)
(1) For Model A300 B2 series airplanes: Perform the initial
inspection at the later of the times specified by paragraphs
(i)(1)(i) and (i)(1)(ii) of this AD. Repeat the inspection
thereafter at intervals not to exceed 10,400 flight cycles or 13,300
flight hours, whichever occurs first, until the inspection required
by paragraph (j) of this AD is done.
(i) Before the accumulation of 16,500 total flight cycles or
21,000 total flight hours, whichever occurs first.
(ii) Within 1,000 flight cycles or 1,300 flight hours after May
1, 2003, whichever occurs first.
(2) For Model A300 B4-100 series airplanes: Perform the initial
inspection at the later of the times specified by paragraphs
(i)(2)(i) and (i)(2)(ii) of this AD. Repeat the inspection
thereafter at intervals not to exceed 8,500 flight cycles or 16,400
flight hours, whichever occurs first, until the inspection required
by paragraph (j) of this AD is done.
(i) Before the accumulation of 10,300 total flight cycles or
19,800 total flight hours, whichever occurs first.
(ii) Within 750 flight cycles or 1,500 flight hours after May 1,
2003, whichever occurs first.
[[Page 2806]]
(3) For Model A300 B4-200 series airplanes: Perform the initial
inspection at the later of the times specified by paragraphs
(i)(3)(i) and (i)(3)(ii) of this AD. Repeat the inspection
thereafter at intervals not to exceed 7,000 flight cycles or 13,600
flight hours, whichever occurs first, until the inspection required
by paragraph (j) of this AD is done.
(i) Before the accumulation of 11,000 total flight cycles or
21,200 total flight hours, whichever occurs first.
(ii) Within 750 flight cycles or 1,500 flight hours after May 1,
2003, whichever occurs first.
New Requirements of This AD
Inspections and Corrective Actions
(j) At the applicable time in paragraph (k) or (l) of this AD:
Except as provided by paragraphs (n) and (p) of this AD, do an eddy
current inspection to detect cracking of the upper radius of the
forward fitting of frame 47, and do all applicable related
investigative and corrective actions, by accomplishing all the
applicable actions specified in the Accomplishment Instructions of
the applicable service bulletin specified in paragraph (j)(1) or
(j)(2) of this AD. Do all applicable investigative and corrective
actions before further flight. Where the service bulletins specify
to contact Airbus for repair instructions: Before further flight,
repair using a method approved by either the Manager, International
Branch, ANM-116; or the EASA (or its delegated agent). Doing the
inspections required by this paragraph terminates the inspections
required by paragraphs (f), (g), and (i) of this AD.
(1) For Airbus Model A300 airplanes: Airbus Service Bulletin
A300-53-0246, Revision 06, including Appendix 01, dated October 19,
2005.
(2) For Airbus Model A300 B4-601, B4-603, B4-620, B4-622, B4-
605R, B4-622R, F4-605R, F4-622R, and C4-605R Variant F airplanes:
Airbus Service Bulletin A300-53-6029, Revision 08, including
Appendix 01, dated October 19, 2005.
(k) For airplanes on which the inspection required by paragraph
(f), (g), or (i) of this AD, as applicable, has not been done prior
to the effective date of this AD: Do the initial inspection required
by paragraph (j) of this AD before the accumulation of 10,000 total
flight cycles, or within 1,400 flight cycles after the effective
date of this AD, whichever occurs later. Repeat the inspection
thereafter at the applicable interval specified in Figure 1, Sheet
1, of the Accomplishment Instructions of the applicable service
bulletin.
(l) For airplanes on which the inspection required by paragraph
(f), (g), or (i) of this AD, as applicable, has been done prior to
the effective date of this AD: Inspect at the applicable times
specified in paragraph (l)(1) or (l)(2) of this AD. Repeat the
inspection thereafter at the applicable interval specified in Figure
1, Sheet 1, of the Accomplishment Instructions of the applicable
service bulletin.
(1) For airplanes on which no cracking was found during any
inspection required by this AD: Do the next inspection at the
earlier of the times specified in paragraphs (l)(1)(i) and
(l)(1)(ii) of this AD.
(i) At the next repetitive interval specified in the applicable
service bulletin specified in paragraph (j)(1) or (j)(2) of this AD,
or within 1,400 flight cycles after the effective date of this AD,
whichever occurs later.
(ii) At the next repetitive interval specified in paragraph (g)
or (i) of this AD, as applicable.
(2) For airplanes on which any crack was found during any
inspection required by this AD, and the crack is the size specified
in paragraph (l)(2)(i), (l)(2)(ii), or (l)(2)(iii) of this AD: Do
the next inspection at the applicable times specified in paragraph
(l)(2)(i), (l)(2)(ii), or (l)(2)(iii) of this AD, as applicable.
(i) For Airbus Model A300 airplanes on which the crack is 30
millimeters (mm) (1.181 inch) or less in length: At the next
repetitive interval specified in the service bulletin specified in
paragraph (j)(1) of this AD, or within 500 flight cycles after the
effective date of this AD, whichever occurs later.
(ii) For Airbus Model A300 airplanes on which the crack is
greater than 30 millimeters (mm) (1.181 inch) in length, but less
than or equal to 50 mm in length (1.97 inch): At the next repetitive
interval specified in paragraph (l) of this AD (Figure 1, Sheet 1,
of the Accomplishment Instructions of the applicable service
bulletin).
(iii) For Airbus Model A300 B4-601, B4-603, B4-620, B4-622, B4-
605R, B4-622R, F4-605R, F4-622R, and C4-605R Variant F airplanes on
which the crack is 50 mm (1.97 inch) or less in length: At the next
repetitive interval specified in the service bulletin specified in
paragraph (j)(2) of this AD; without, however, exceeding the
previous inspection interval specified in paragraph (g) of this AD.
Abnormal Load Events
(m) For airplanes on which any crack was found during any
inspection required by this AD and on which any abnormal load event
occurs after the effective date of this AD: Do the actions in
paragraphs (m)(1), (m)(2), and (m)(3) of this AD, as applicable, at
the time specified in the applicable paragraph.
(1) Within 3 months after the event, or at the next applicable
repetitive interval required by paragraph (k) or (l) of this AD,
whichever occurs first: Do the next repetitive inspection required
by paragraph (j) of this AD.
(2) Before further flight following any additional abnormal load
event that occurs following the first event but before the next
repetitive inspection required by paragraph (k) or (l) of this AD:
Contact the Manager, International Branch, ANM-116, or the EASA (or
its delegated agent), for further instructions.
(3) Within 3 months after any abnormal load event: Report the
event to Airbus in accordance with the requirements of paragraph (q)
of this AD.
Optional Terminating Action (Repair) for Certain Cracks
(n) Repairing any crack greater than 30 mm but less than or
equal to 50 mm in size, in accordance with the Accomplishment
Instructions of Airbus Service Bulletin A300-53-0370, including
Appendix 01, dated July 16, 2004; or Airbus Service Bulletin A300-
53-6144, Revision 01, including Appendix 01, dated July October 15,
2007; as applicable; terminates the repetitive inspection
requirements of paragraph (k) or (l) of this AD for that area only.
Where the service bulletins specify to contact Airbus for repair
instructions: Repair the crack using a method approved by either the
Manager, International Branch, ANM-116; or the EASA (or its
delegated agent).
Repetitive Inspections Following Optional Terminating Action
(o) Within 6 months after repair in accordance with paragraph
(n) of this AD: Submit a post-repair inspection program for
monitoring the repair to the Manager, International Branch, ANM-116,
for approval.
Repair of Any Crack Greater than 50 mm in Size
(p) If any crack that is greater than 50 mm in size is found
during any inspection required by paragraph (j), (k), or (l) of this
AD: Before further flight, repair according to a method approved by
the Manager, International Branch, ANM-116.
Reporting Requirement
(q) At the applicable time specified in paragraph (q)(1) or
(q)(2) of this AD: Submit a report of all results of each inspection
required by this AD to Airbus, 1 Rond Point Maurice Bellonte, 31707
Blagnac Cedex, France, Attention: Davide Cavazzini, fax 33-5-61-93-
36-14. The report must include the inspection results, a description
of any discrepancies found, the airplane serial number, and the
number of landings and flight hours on the airplane. Information
collection requirements contained in this AD have been approved by
the Office of Management and Budget (OMB) under the provisions of
the Paperwork Reduction Act (44 U.S.C. 3501 et seq.) and have been
assigned OMB Control Number 2120-0056.
(1) For airplanes on which the inspection is accomplished after
the effective date of this AD: Submit the report within 30 days
after performing the inspection.
(2) For airplanes on which the inspection has been accomplished
before the effective date of this AD: Submit the report within 30
days after the effective date of this AD.
Actions Accomplished in Accordance With Previous Issues of Service
Bulletins
(r) Actions done before the effective date of this AD in
accordance with the service bulletins listed in Table 1 of this AD
are acceptable for compliance with the corresponding requirements of
paragraphs (i), (j), and (n) of this AD.
[[Page 2807]]
Table 1.--Previous Issues of Service Bulletins
----------------------------------------------------------------------------------------------------------------
Airbus Service
Model Bulletin Revision level Date
----------------------------------------------------------------------------------------------------------------
A300 airplanes.................. A300-53-0246 03........................... April 11, 2001.
A300-53-0246 04........................... November 12, 2002.
A300-53-0246 05........................... January 19, 2004.
A300 B4-601, B4-603, B4-620, B4- A300-53-6029 05........................... April 11, 2001.
622, B4-605R, B4-622R, F4-605R,
F4-622R, and C4-605R Variant F
airplanes.
A300-53-6029 06........................... November 12, 2002.
A300-53-6029 07........................... January 19, 2004.
A300-53-6144 Original..................... July 16, 2004.
----------------------------------------------------------------------------------------------------------------
Alternative Methods of Compliance (AMOCs)
(s)(1) The Manager, International Branch, ANM-116, has the
authority to approve AMOCs for this AD, if requested in accordance
with the procedures found in 14 CFR 39.19.
(2) To request a different method of compliance or a different
compliance time for this AD, follow the procedures in 14 CFR 39.19.
Before using any approved AMOC on any airplane to which the AMOC
applies, notify your appropriate principal inspector (PI) in the FAA
Flight Standards District Office (FSDO), or lacking a PI, your local
FSDO.
(3) AMOCs approved previously in accordance with AD 2003-06-04
are approved as AMOCs with this AD until paragraph (j) of this AD is
accomplished.
Related Information
(t) French airworthiness directive F-2006-016, dated January 18,
2006, also addresses the subject of this AD.
Material Incorporated by Reference
(u) You must use the service information listed in Table 2 of
this AD to perform the actions that are required by this AD, unless
the AD specifies otherwise.
Table 2.--All Material Incorporated by Reference
----------------------------------------------------------------------------------------------------------------
Airbus Service Bulletin Revision level Date
----------------------------------------------------------------------------------------------------------------
A300-53-0246, including Appendix 01.... 03................................. April 11, 2001.
A300-53-0246, including Appendix 01.... 06................................. October 19, 2005.
A300-53-0370, including Appendix 01.... Original........................... July 16, 2004.
A300-53-6029........................... 02................................. November 7, 1994.
A300-53-6029, including Appendix 01.... 05................................. April 11, 2001.
A300-53-6029, including Appendix 01.... 08................................. October 19, 2005.
A300-53-6144, including Appendix 01.... Original........................... July 16, 2004.
----------------------------------------------------------------------------------------------------------------
(1) The Director of the Federal Register approved the
incorporation by reference of the documents listed in Table 3 of
this AD in accordance with 5 U.S.C. 552(a) and 1 CFR part 51.
Table 3.--New Material Incorporated by Reference
----------------------------------------------------------------------------------------------------------------
Airbus Service Bulletin Revision level Date
----------------------------------------------------------------------------------------------------------------
A300-53-0246, including Appendix 01.... 06................................. October 19, 2005.
A300-53-0370, including Appendix 01.... Original........................... July 16, 2004.
A300-53-6029, including Appendix 01.... 08................................. October 19, 2005.
A300-53-6144, including Appendix 01.... Original........................... July 16, 2004.
----------------------------------------------------------------------------------------------------------------
(2) On May 1, 2003 (68 FR 14894, March 27, 2003), the Director
of the Federal Register approved the incorporation by reference of
the documents listed in Table 4 of this AD.
Table 4.--Material Incorporated by Reference in Previous AD
----------------------------------------------------------------------------------------------------------------
Airbus Service Bulletin Revision level Date
----------------------------------------------------------------------------------------------------------------
A300-53-0246, including Appendix 01.... 03................................. April 11, 2001.
A300-53-6029, including Appendix 01.... 05................................. April 11, 2001.
----------------------------------------------------------------------------------------------------------------
(3) On October 16, 1996 (61 FR 47808, September 11, 1996), the
Director of the Federal Register approved the incorporation by
reference of Airbus Service Bulletin A300-53-6029, Revision 02,
dated November 7, 1994.
(4) Contact Airbus, 1 Rond Point Maurice Bellonte, 31707 Blagnac
Cedex, France, for a copy of this service information. You may
review copies at the FAA, Transport Airplane Directorate, 1601 Lind
Avenue, SW., Renton, Washington; or at the National Archives and
Records Administration (NARA). For information on the availability
of this material at NARA, call 202-741-6030, or go to: https://
www.archives.gov/federal-register/cfr/ibr-locations.html.
Issued in Renton, Washington, on December 19, 2007.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. E7-25503 Filed 1-15-08; 8:45 am]
BILLING CODE 4910-13-P
