Airworthiness Directives; Airbus Model A321-100 Series Airplanes, 8792-8796 [06-1504]
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constitute satisfactory evidence of such
assumption for purposes of section 8(q).
(e) Issuance of an order. The
Executive Secretary, upon request from
the Director of the Division of
Supervision and Consumer Protection
and with the concurrence of the General
Counsel, or their respective designees,
shall issue an order terminating the
insured status of the transferring
insured depository institution as of the
date of receipt by the FDIC of
satisfactory evidence of such
assumption, pursuant to section 8(q) of
the FDI Act and this regulation.
Generally, no order shall be issued,
under this paragraph, and insured status
shall be cancelled by operation of law:
(1) If the charter of the transferring
institution has been cancelled, revoked,
rescinded, or otherwise terminated by
operation of applicable state or federal
statutes or regulations, or by action of
the chartering authority for the
transferring institution essentially
contemporaneously, that is, generally
within five business days after all
deposits have been assumed; or
(2) If the transferring institution is an
insured depository institution in default
and for which the FDIC has been
appointed receiver.
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§ 307.3 Notice to depositors when insured
status is voluntarily terminated and
deposits are not assumed.
(a) Notice required. An insured
depository institution that has obtained
authority from the FDIC to terminate its
insured status under sections 8(a), 8(p)
or 18(i)(3) of the FDI Act without its
deposit liabilities being assumed by one
or more insured depository institutions
shall provide to each of its depositors,
at the depositor’s last known address of
record on the books of the institution,
prior written notification of the date the
institution’s insured status shall
terminate.
(b) Prior approval of notice. The
insured depository institution shall
provide the appropriate Regional
Director of the FDIC’s Division of
Supervision and Consumer Protection,
as defined in 12 CFR 303.2(g), a copy of
the proposed notice for approval. After
being approved, the notice shall be
provided to depositors by the insured
depository institution at the time and in
the manner specified by the appropriate
Regional Director.
(c) Form of notice. The notice to
depositors required by paragraph (a) of
this section shall be provided on the
official letterhead of the insured
depository institution, shall bear the
signature of a duly authorized officer,
and, unless otherwise specified by the
appropriate Regional Director, may
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follow the form of the notice contained
in Appendix B of this part.
(d) Other requirements possible. The
FDIC may require the insured
depository institution to take such other
actions as the FDIC considers necessary
and appropriate for the protection of
depositors.
Appendix A to Part 307—Transferring
Institution Letterhead
[Date]
[Name and Address of appropriate FDIC
Regional Director]
SUBJECT: Certification of Total Assumption
of Deposits
This certification is being provided
pursuant to 12 U.S.C. 1818(q) and 12 CFR
307.2. On [state the date the deposit
assumption took effect], [state the name of
the depository institution assuming the
deposit liabilities] assumed all of the deposits
of [state the name and location of the
transferring institution whose deposits were
assumed]. [If applicable, state the date and
method by which the transferring
institution’s authority to engage in banking
was or will be terminated.] Please contact the
undersigned, at [telephone number], if
additional information is needed.
Sincerely,
By:
[Name and Title of Authorized
Representative]
Appendix B to Part 307—Institution
Letterhead
[Date]
[Name and Address of Depositor]
SUBJECT: Notice to Depositor of Voluntary
Termination of Insured Status
The insured status of [name of insured
depository institution], under the provisions
of the Federal Deposit Insurance Act, will
terminate as of the close of business on [state
the date] (‘‘termination date’’). Insured
deposits in the [name of insured depository
institution] on the termination date, less all
withdrawals from such deposits made
subsequent to that date, will continue to be
insured by the Federal Deposit Insurance
Corporation, to the extent provided by law,
until [state the date]. The Federal Deposit
Insurance Corporation will not insure any
new deposits or additions to existing
deposits made by you after the termination
date.
This Notice is being provided pursuant to
12 CFR 307.3.
Please contact [name of institution official
in charge of depositor inquiries], at [name
and address of insured depository
institution] if additional information is
needed regarding this Notice or the insured
status of your account(s).
Sincerely,
By:
[Name and Title of Authorized
Representative]
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By order of the Board of Directors, at
Washington, DC, on this 10th day of
February, 2006.
Federal Deposit Insurance Corporation.
Robert Feldman,
Executive Secretary.
[FR Doc. 06–1568 Filed 2–17–06; 8:45 am]
BILLING CODE 6714–01–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2006–23935; Directorate
Identifier 2005–NM–060–AD; Amendment
39–14492; AD 2006–04–11]
RIN 2120–AA64
Airworthiness Directives; Airbus Model
A321–100 Series Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule; request for
comments.
AGENCY:
SUMMARY: The FAA is superseding an
existing airworthiness directive (AD),
which applies to certain Airbus Model
A321–111, –112, and –131 series
airplanes. That AD currently requires
repetitive inspections to detect fatigue
cracking in the area surrounding certain
attachment holes of the forward pintle
fittings of the main landing gear (MLG)
and the actuating cylinder anchorage
fittings on the inner rear spar; and
repair, if necessary. The existing AD
also provides for optional terminating
action for the repetitive inspections.
This AD adds inspections of three
additional mounting holes and revises
the thresholds for the currently required
inspections. This AD results from
manufacturer analysis of the fatigue and
damage tolerance of the area
surrounding certain mounting holes of
the MLG. We are issuing this AD to
detect and correct fatigue cracking on
the inner rear spar of the wings, which
could result in reduced structural
integrity of the airplane.
DATES: This AD becomes effective
March 8, 2006.
The Director of the Federal Register
approved the incorporation by reference
of certain publications listed in the AD
as of March 8, 2006.
The incorporation by reference of
Airbus Service Bulletin A320–57–1101,
Revision 02, dated October 25, 2001, as
listed in the regulations, was approved
previously by the Director of the Federal
Register as of April 21, 2004 (69 FR
17906, April 6, 2004).
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The incorporation by reference of
Airbus Service Bulletin A320–57–1101,
dated July 24, 1997, as listed in the
regulations, was approved previously by
the Director of the Federal Register as of
December 18, 1998 (63 FR 66753,
December 3, 1998).
We must receive comments on this
AD by April 24, 2006.
ADDRESSES: Use one of the following
addresses to submit comments on this
AD.
• DOT Docket Web site: Go to
https://dms.dot.gov and follow the
instructions for sending your comments
electronically.
• Government-wide rulemaking Web
site: Go to https://www.regulations.gov
and follow the instructions for sending
your comments electronically.
• Mail: Docket Management Facility;
U.S. Department of Transportation, 400
Seventh Street, SW., Nassif Building,
Room PL–401, Washington, DC 20590.
• Fax: (202) 493–2251.
• Hand Delivery: Room PL–401 on
the plaza level of the Nassif Building,
400 Seventh Street, SW., Washington,
DC, between 9 a.m. and 5 p.m., Monday
through Friday, except Federal holidays.
Contact Airbus, 1 Rond Point Maurice
Bellonte, 31707 Blagnac Cedex, France,
for service information identified in this
AD.
FOR FURTHER INFORMATION CONTACT: Dan
Rodina, Aerospace Engineer,
International Branch, ANM–116, FAA,
Transport Airplane Directorate, 1601
Lind Avenue, SW., Renton, Washington
98055–4056; telephone (425) 227–2125;
fax (425) 227–1149.
SUPPLEMENTARY INFORMATION:
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Discussion
On March 25, 2004, we issued AD
2004–07–15, amendment 39–13559 (69
FR 17906, April 6, 2004), for certain
Airbus Model A321–111, –112, and
–131 series airplanes. That AD requires
repetitive inspections to detect fatigue
cracking in the area surrounding certain
attachment holes of the forward pintle
fittings of the main landing gear (MLG)
and the actuating cylinder anchorage
fittings on the inner rear spar; and
repair, if necessary. That AD also
provided for optional terminating action
for the repetitive inspections. That AD
resulted from a fleet survey by the
manufacturer. We issued that AD to
detect and correct fatigue cracking on
the inner rear spar of the wings, which
could result in reduced structural
integrity of the airplane.
Actions Since Existing AD Was Issued
Since we issued AD 2004–07–15,
Airbus conducted further analysis of the
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fatigue and damage tolerance of the
mounting holes of the inner rear spar of
the wing. The results of the analysis
revealed that three more mounting holes
require inspection and that it is
necessary to decrease the thresholds of
the repetitive inspections already
required by AD 2004–07–15.
Relevant Service Information
Airbus has issued Service Bulletin
(SB) A320–57–1101, Revision 04, dated
November 22, 2004. (AD 2004–07–15
refers to Airbus SB A320–57–1101,
dated July 24, 1997; and Revision 02,
dated October 25, 2001; as appropriate
sources of service information for the
actions required by that AD.) SB A320–
57–1101, Revision 04, describes
procedures for performing repetitive
ultrasonic inspections for fatigue
cracking in the area around certain
mounting holes on the inner rear spar of
the wings. The thresholds specified in
SB A320–57–1101, Revision 04, have
been reduced from those specified in SB
A320–57–1101, Revision 02; and from
those thresholds specified in Airbus SB
A320–57–1101, Revision 03, dated July
30, 2003, which added three additional
mounting holes to the area subject to the
repetitive inspections. The Direction
´ ´
Generale de l’Aviation Civile (DGAC),
which is the airworthiness authority for
France, mandated SB A320–57–1101,
Revision 03, and issued French
airworthiness directive F–2004–166,
dated October 13, 2004, to ensure the
continued airworthiness of these
airplanes in France. Airbus SB A320–
57–1101, Revision 04—which was
released after the issuance of French
airworthiness directive F–2004–166—is
also acceptable for accomplishing the
requirements of this AD.
We have reviewed later revisions of
Airbus SB A320–57–1100, dated July
28, 1997, which is designated as the
appropriate source of information for
accomplishing the optional terminating
action specified in paragraph (b) of AD
2004–07–15. Those later revisions are
Airbus SB A320–57–1100, Revision 01,
dated June 4, 1999; Revision 02, dated
October 25, 2001; and Revision 03,
dated January 16, 2003. Though not
specified in AD 2004–07–15, SB A320–
57–1100 includes Appendix 01 only,
while SB A320–57–1100, Revisions 01,
02, and 03 include Appendices 01 and
02. Any revision of SB A320–57–1100 is
considered an acceptable source of
service information for accomplishing
the optional terminating action
specified in paragraph (b) of AD 2004–
07–15, which is restated as paragraph
(g) of this AD.
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FAA’s Determination and Requirements
of This AD
This airplane model is manufactured
in France and is type certificated for
operation in the United States under the
provisions of section 21.29 of the
Federal Aviation Regulations (14 CFR
21.29) and the applicable bilateral
airworthiness agreement. Pursuant to
this bilateral airworthiness agreement,
the DGAC has kept the FAA informed
of the situation described above. We
have examined the DGAC’s findings,
evaluated all pertinent information, and
determined that we need to issue an AD
for products of this type design that are
certificated for operation in the United
States.
We are issuing this AD to supersede
AD 2004–07–15. This new AD
continues to require repetitive
inspections to detect fatigue cracking in
the area surrounding certain attachment
holes of the forward pintle fittings of the
MLG and the actuating cylinder
anchorage fittings on the inner rear spar;
and repair, if necessary; and additional
inspections and repairs, if necessary; as
specified in the service information
described previously; except as
discussed under ‘‘Difference Between
French Airworthiness Directive and
This AD’’ and ‘‘Differences Between
This AD and Service Information.’’
Difference Between French
Airworthiness Directive and This AD
The applicability of French
airworthiness directive F–2004–166
excludes airplanes on which Airbus SB
A320–57–1100 was accomplished in
service. However, we have not excluded
those airplanes in the applicability of
this AD; rather, this AD includes a
requirement to accomplish the actions
specified in SB A320–57–1101, Revision
04, and provides for doing SB A320–57–
1100 as an optional terminating action
for the actions in SB A320–57–1101.
This requirement will ensure that the
actions specified in SB A320–57–1101,
Revision 04, are accomplished on all
affected airplanes. Operators must
continue to operate the airplane in the
configuration required by this AD
unless an alternative method of
compliance (AMOC) is approved.
Differences Between This AD and
Service Information
Airbus SB A320–57–1101, Revision
04, does not describe any method or
service information to be used to repair
any crack discovered during any
inspection specified by the service
information. Therefore, this AD requires
operators to use a repair method that we
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or the DGAC (or its delegated agent)
approve.
Although the service bulletins
describe procedures for reporting
inspection findings to Airbus, this AD
does not require such a report.
average labor rate of $65 per work hour.
The cost of required parts would be
approximately $17,540 per airplane.
Based on these figures, the cost impact
of the optional terminating action would
be $51,340 per airplane.
Explanation of Change to Applicability
We have revised the applicability of
the existing AD to identify model
designations as published in the most
recent type certificate data sheet for the
affected models.
FAA’s Determination of the Effective
Date
Change to Existing AD
This AD would retain certain
requirements of AD 2004–07–15. Since
AD 2004–07–15 was issued, the AD
format has been revised, and certain
paragraphs have been rearranged. As a
result, the corresponding paragraph
identifiers have changed in this AD, as
listed in the following table:
REVISED PARAGRAPH IDENTIFIERS
Corresponding
requirement in
this proposed
AD
Requirement in
AD 2004–07–15
Paragraph
Paragraph
Paragraph
Paragraph
Paragraph
Paragraph
(a) ......................
(b) ......................
(c) ......................
(d) ......................
(e) ......................
(f) .......................
Paragraph
Paragraph
Paragraph
Paragraph
Paragraph
Paragraph
(f).
(g).
(h).
(i).
(j).
(m).
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Clarification of AMOC Paragraph
We have revised this action to clarify
the appropriate procedure for notifying
the principal inspector before using any
approved AMOC on any airplane to
which the AMOC applies.
Costs of Compliance
None of the airplanes affected by this
action are on the U.S. Register. All
airplanes included in the applicability
of this AD currently are operated by
non-U.S. operators under foreign
registry; therefore, they are not directly
affected by this AD action. However, we
consider that this AD is necessary to
ensure that the unsafe condition is
addressed in the event that any of these
subject airplanes are imported and
placed on the U.S. Register in the future.
If an affected airplane is imported and
placed on the U.S. Register in the future,
it would require approximately 22 work
hours to accomplish the required
actions at an average labor rate of $65
per work hour. Based on these figures,
the cost impact of this AD would be
$1,430 per airplane.
If an operator elects to accomplish the
optional terminating action provided by
this AD, it would take approximately
520 work hours to accomplish, at an
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No airplane affected by this AD is
currently on the U.S. Register.
Therefore, providing notice and
opportunity for public comment is
unnecessary before this AD is issued,
and this AD may be made effective in
less than 30 days after it is published in
the Federal Register.
Comments Invited
This AD is a final rule that involves
requirements that affect flight safety and
was not preceded by notice and an
opportunity for public comment;
however, we invite you to submit any
relevant written data, views, or
arguments regarding this AD. Send your
comments to an address listed in the
ADDRESSES section. Include ‘‘Docket No.
FAA–2006–23935; Directorate Identifier
2005–NM–060–AD’’ at the beginning of
your comments. We specifically invite
comments on the overall regulatory,
economic, environmental, and energy
aspects of the AD that might suggest a
need to modify it.
We will post all comments we
receive, without change, to https://
dms.dot.gov, including any personal
information you provide. We will also
post a report summarizing each
substantive verbal contact with FAA
personnel concerning this AD. Using the
search function of that Web site, anyone
can find and read the comments in any
of our dockets, including the name of
the individual who sent the comment
(or signed the comment on behalf of an
association, business, labor union, etc.).
You may review the DOT’s complete
Privacy Act Statement in the Federal
Register published on April 11, 2000
(65 FR 19477–78), or you may visit
https://dms.dot.gov.
Examining the Docket
You may examine the AD docket on
the Internet at https://dms.dot.gov, or in
person at the Docket Management
Facility office between 9 a.m. and 5
p.m., Monday through Friday, except
Federal holidays. The Docket
Management Facility office (telephone
(800) 647–5227) is located on the plaza
level of the Nassif Building at the DOT
street address stated in the ADDRESSES
section. Comments will be available in
the AD docket shortly after the Docket
Management System receives them.
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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
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 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 the regulation:
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.
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
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Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13
[Amended]
2. The Federal Aviation
Administration (FAA) amends § 39.13
by removing amendment 39–13559 (69
FR 17906, April 6, 2004) and by adding
the following new airworthiness
directive (AD):
I
2006–04–11 Airbus: Amendment 39–14492.
Docket No. FAA–2006–23935;
Directorate Identifier 2005–NM–060–AD.
Effective Date
(a) This AD becomes effective March 8,
2006.
Affected ADs
(b) This AD supersedes AD 2004–07–15.
Applicability
(c) This AD applies to Airbus Model A321–
111, –112, and –131 airplanes, certificated in
any category; all manufacturer serial numbers
(MSN), except MSN 364 and 365; and except
for those airplanes that have received Airbus
Modification 24977 in production.
Unsafe Condition
(d) This AD results from manufacturer
analysis of the fatigue and damage tolerance
of the area surrounding certain mounting
holes of the main landing gear (MLG). The
FAA is issuing this AD to detect and correct
fatigue cracking on the inner rear spar of the
wings, which could 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.
Restatement of Requirements of AD 2004–
07–15
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Repetitive Inspections and Corrective Actions
(f) Prior to the accumulation of 20,000 total
flight cycles, or within 120 days after
December 18, 1998 (the effective date of AD
98–25–05, amendment 39–10928), whichever
occurs later, perform an ultrasonic inspection
to detect fatigue cracking in the area
surrounding certain attachment holes of the
forward pintle fittings of the MLG and the
actuating cylinder anchorage fittings on the
inner rear spar, in accordance with Airbus
Service Bulletin A320–57–1101, dated July
24, 1997; or Revision 02, dated October 25,
2001.
(1) If no cracking is detected, prior to
further flight, repair the sealant in the
inspected areas and repeat the ultrasonic
inspections thereafter at intervals not to
exceed 7,700 flight cycles, until paragraph
(g), (i), or (k) of this AD is accomplished.
(2) If any cracking is detected, prior to
further flight, repair in accordance with a
method approved by either the Manager,
International Branch, ANM–116, Transport
Airplane Directorate, FAA; or the Direction
Generale de l’Aviation Civile (DGAC) (or its
delegated agent).
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Optional Terminating Action
(g) Accomplishment of visual and eddy
current inspections to detect cracking in the
area surrounding certain attachment holes of
the forward pintle fittings of the MLG and the
actuating cylinder anchorage fittings on the
inner rear spar; follow-on corrective actions,
as applicable; and rework of the attachment
holes; in accordance with Airbus Service
Bulletin A320–57–1100, including Appendix
01, dated July 28, 1997; or Revision 03,
including Appendices 01 and 02, dated
January 16, 2003; constitutes terminating
action for the repetitive inspection
requirements of this AD. Actions
accomplished in accordance with Airbus
Service Bulletin A320–57–1100, Revision 01,
including Appendices 01 and 02, dated June
4, 1999; or Revision 02, including
Appendices 01 and 02, dated October 25,
2001; are considered acceptable for
compliance with the optional terminating
action specified in this paragraph. If any
cracking is detected during accomplishment
of any inspection described in the service
bulletin, and the service bulletin specifies to
contact Airbus for appropriate action: Prior to
further flight, repair in accordance with a
method approved by either the Manager,
International Branch, ANM–116; or the
DGAC (or its delegated agent).
Repetitive Inspections for Airplanes Not
Previously Inspected Per Paragraph (f)
(h) For airplanes on which the initial
inspection required by paragraph (f) of this
AD has not been accomplished as of April 21,
2004 (the effective date of AD 2004–07–15):
Accomplish the inspection required by
paragraph (f) of this AD, at the earlier of the
times specified in paragraphs (h)(1) and
(h)(2) of this AD. If no cracking is found,
repeat the inspection thereafter at intervals
not to exceed 5,500 flight cycles or 10,200
flight hours, whichever occurs first, until
paragraph (g) or (k) of this AD is
accomplished. Accomplishment of this
paragraph eliminates the need to accomplish
repetitive inspections at the intervals
required by paragraph (f)(1) of this AD.
(1) Prior to the accumulation of 20,000
total flight cycles.
(2) Prior to the accumulation of 37,300
total flight hours, or within 120 days after
April 21, 2004, whichever occurs later.
Repetitive Inspections for Airplanes
Previously Inspected Per Paragraph (f)
(i) For airplanes on which the initial
inspection required by paragraph (f) of this
AD has been accomplished as of April 21,
2004, and no cracking was found: Do the next
inspection at the earlier of the times specified
in paragraphs (i)(1) and (i)(2) of this AD, and
repeat the inspection thereafter at intervals
not to exceed 5,500 flight cycles or 10,200
flight hours, whichever occurs first, until
paragraph (g) or (k) of this AD is
accomplished. Accomplishment of this
paragraph terminates the repetitive
inspections required by paragraph (f)(1) of
this AD.
(1) Within 7,700 flight cycles since the
most recent inspection.
(2) At the later of the times specified in
paragraph (i)(2)(i) or (i)(2)(ii) of this AD:
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8795
(i) Within 5,500 flight cycles or 10,200
flight hours since the most recent inspection,
whichever occurs first.
(ii) Within 120 days after April 21, 2004.
Existing Repair
(j) If any cracking is detected during any
inspection required by paragraph (h) or (i) of
this AD: Prior to further flight, repair in
accordance with a method approved by
either the Manager, International Branch,
ANM–116; or the DGAC (or its delegated
agent).
New Requirements of This AD
Initial and Repetitive Inspections
(k) Within the applicable compliance times
specified by paragraph (k)(1), (k)(2), or (k)(3)
of this AD, perform an ultrasonic inspection
for cracking of the attachment holes of the
MLG pintle fittings in the inner rear spar in
accordance with the Accomplishment
Instructions of Airbus Service Bulletin A320–
57–1101, Revision 03, dated July 30, 2003; or
Revision 04, dated November 22, 2004. If no
cracking is found, repeat the inspection
thereafter at intervals not to exceed 5,500
flight cycles or 10,200 flight hours,
whichever occurs first, until paragraph (g) of
this AD is accomplished. Accomplishment of
this paragraph terminates the repetitive
inspections required by paragraphs (f)(1), (h),
and (i) of this AD.
(1) For airplanes that have never been
inspected in accordance with Airbus Service
Bulletin A320–57–1101, dated July 24, 1997;
or Revision 02, dated October 25, 2001:
Before the accumulation of 20,000 total flight
cycles or 37,300 total flight hours, whichever
occurs first; or within 120 days after the
effective date of this AD; whichever occurs
later.
(2) For airplanes previously inspected in
accordance with Airbus Service Bulletin
A320–57–1101, dated July 24, 1997; or
Revision 02, dated October 25, 2001, that
have accumulated less than 18,900 total
flight cycles or 35,300 total flight hours as of
the effective date of this AD: Within 5,500
flight cycles or 10,200 flight hours,
whichever occurs first, after the previous
inspection performed in accordance with
Airbus Service Bulletin A320–57–1101,
Revision 02, dated October 25, 2001; or
within 120 days after the effective date of this
AD; whichever occurs later.
(3) For airplanes previously inspected in
accordance with Airbus Service Bulletin
A320–57–1101, dated July 24, 1997; or
Revision 02, dated October 25, 2001, that
have accumulated 18,900 or more flight
cycles or 35,300 or more flight hours as of the
effective date of this AD: Before the
accumulation of 24,400 total flight cycles or
45,600 total flight hours, whichever occurs
first; or within 120 days after the effective
date of this AD; whichever occurs later.
New Repair
(l) If any crack is detected during any
inspection required by paragraph (k) of this
AD: Prior to further flight, repair in
accordance with a method approved by
either the Manager, International Branch,
ANM–116; or the DGAC (or its delegated
agent).
E:\FR\FM\21FER1.SGM
21FER1
8796
Federal Register / Vol. 71, No. 34 / Tuesday, February 21, 2006 / Rules and Regulations
No Reporting Requirement
(m) Although Airbus Service Bulletin
A320–57–1101, Revision 02, dated October
25, 2001; and Revision 04, dated November
22, 2004; describe procedures for reporting
inspection findings to Airbus, this AD does
not require such a report.
Alternative Methods of Compliance
(AMOCs)
(n)(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) Before using any AMOC approved in
accordance with 14 CFR 39.19 on any
airplane to which the AMOC applies, notify
the appropriate principal inspector in the
FAA Flight Standards Certificate Holding
District Office.
Related Information
(o) French airworthiness directive F–2004–
166, dated October 13, 2004, also addresses
the subject of this AD.
Material Incorporated by Reference
(p) You must use the service information
specified in Table 1 of this AD to perform the
actions that are required by this AD, unless
the AD specifies otherwise.
TABLE 1.—ALL MATERIAL INCORPORATED BY REFERENCE
Airbus service bulletin
Revision level
A320–57–1100, including Appendix 01 ...............................................................
A320–57–1100, including Appendices 01 and 02 ...............................................
A320–57–1101 .....................................................................................................
A320–57–1101 .....................................................................................................
A320–57–1101 .....................................................................................................
A320–57–1101 .....................................................................................................
Original ..................................................
03 ..........................................................
Original ..................................................
02 ..........................................................
03 ..........................................................
04 ..........................................................
The optional terminating action specified
in paragraph (g) of this AD should be done
Date
July 28, 1997.
January 16, 2003.
July 24, 1997.
October 25, 2001.
July 30, 2003.
November 22, 2004.
in accordance with the service bulletins
specified in Table 2 of this AD.
TABLE 2.—OPTIONAL SERVICE BULLETINS
Airbus service bulletin
Revision level
A320–57–1100, including Appendix 01 ...............................................................
A320–57–1100, including Appendices 01 and 02 ...............................................
Original ..................................................
03 ..........................................................
(1) The Director of the Federal Register
approved the incorporation by reference of
the service bulletins specified in Table 3 of
Date
July 28, 1997.
January 16, 2003.
this AD, in accordance with 5 U.S.C. 552(a)
and 1 CFR part 51.
TABLE 3.—NEW MATERIAL INCORPORATED BY REFERENCE
Revision level
A320–57–1100, including Appendix 01 ...............................................................
A320–57–1100, including Appendices 01 and 02 ...............................................
A320–57–1101 .....................................................................................................
A320–57–1101 .....................................................................................................
rmajette on PROD1PC67 with RULES1
Airbus service bulletin
Original ..................................................
03 ..........................................................
03 ..........................................................
04 ..........................................................
(2) The incorporation by reference of
Airbus Service Bulletin A320–57–1101,
Revision 02, dated October 25, 2001, was
approved previously by the Director of the
Federal Register as of April 21, 2004 (69 FR
17906, April 6, 2004).
(3) The incorporation by reference of
Airbus Service Bulletin A320–57–1101,
dated July 24, 1997, was approved previously
by the Director of the Federal Register as of
December 18, 1998 (63 FR 66753, December
3, 1998).
(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 Docket Management
Facility, U.S. Department of Transportation,
400 Seventh Street SW., room PL–401, Nassif
Building, Washington, DC; on the Internet at
https://dms.dot.gov; or at the National
Archives and Records Administration
(NARA). For information on the availability
of this material at the NARA, call (202) 741–
6030, or go to https://www.archives.gov/
VerDate Aug<31>2005
13:33 Feb 17, 2006
Jkt 208001
Date
July 28, 1997.
January 16, 2003.
July 30, 2003.
November 22, 2004.
federal_register/code_of_federal_regulations/
ibr_locations.html.
DEPARTMENT OF TRANSPORTATION
Issued in Renton, Washington, on February
9, 2006.
Kalene C. Yanamura,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. 06–1504 Filed 2–17–06; 8:45 am]
Federal Aviation Administration
BILLING CODE 4910–13–P
PO 00000
14 CFR Part 97
[Docket No. 30481; Amdt. No. 3155]
Standard Instrument Approach
Procedures; Miscellaneous
Amendments
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule.
AGENCY:
SUMMARY: This amendment amends
Standard Instrument Approach
Procedures (SIAPs) for operations at
certain airports. These regulatory
actions are needed because of changes
occurring in the National Airspace
System, such as the commissioning of
Frm 00008
Fmt 4700
Sfmt 4700
E:\FR\FM\21FER1.SGM
21FER1
Agencies
[Federal Register Volume 71, Number 34 (Tuesday, February 21, 2006)]
[Rules and Regulations]
[Pages 8792-8796]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 06-1504]
=======================================================================
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2006-23935; Directorate Identifier 2005-NM-060-AD;
Amendment 39-14492; AD 2006-04-11]
RIN 2120-AA64
Airworthiness Directives; Airbus Model A321-100 Series Airplanes
AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule; request for comments.
-----------------------------------------------------------------------
SUMMARY: The FAA is superseding an existing airworthiness directive
(AD), which applies to certain Airbus Model A321-111, -112, and -131
series airplanes. That AD currently requires repetitive inspections to
detect fatigue cracking in the area surrounding certain attachment
holes of the forward pintle fittings of the main landing gear (MLG) and
the actuating cylinder anchorage fittings on the inner rear spar; and
repair, if necessary. The existing AD also provides for optional
terminating action for the repetitive inspections. This AD adds
inspections of three additional mounting holes and revises the
thresholds for the currently required inspections. This AD results from
manufacturer analysis of the fatigue and damage tolerance of the area
surrounding certain mounting holes of the MLG. We are issuing this AD
to detect and correct fatigue cracking on the inner rear spar of the
wings, which could result in reduced structural integrity of the
airplane.
DATES: This AD becomes effective March 8, 2006.
The Director of the Federal Register approved the incorporation by
reference of certain publications listed in the AD as of March 8, 2006.
The incorporation by reference of Airbus Service Bulletin A320-57-
1101, Revision 02, dated October 25, 2001, as listed in the
regulations, was approved previously by the Director of the Federal
Register as of April 21, 2004 (69 FR 17906, April 6, 2004).
[[Page 8793]]
The incorporation by reference of Airbus Service Bulletin A320-57-
1101, dated July 24, 1997, as listed in the regulations, was approved
previously by the Director of the Federal Register as of December 18,
1998 (63 FR 66753, December 3, 1998).
We must receive comments on this AD by April 24, 2006.
ADDRESSES: Use one of the following addresses to submit comments on
this AD.
DOT Docket Web site: Go to https://dms.dot.gov and follow
the instructions for sending your comments electronically.
Government-wide rulemaking Web site: Go to https://
www.regulations.gov and follow the instructions for sending your
comments electronically.
Mail: Docket Management Facility; U.S. Department of
Transportation, 400 Seventh Street, SW., Nassif Building, Room PL-401,
Washington, DC 20590.
Fax: (202) 493-2251.
Hand Delivery: Room PL-401 on the plaza level of the
Nassif Building, 400 Seventh Street, SW., Washington, DC, between 9
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
Contact Airbus, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex,
France, for service information identified in this AD.
FOR FURTHER INFORMATION CONTACT: Dan Rodina, Aerospace Engineer,
International Branch, ANM-116, FAA, Transport Airplane Directorate,
1601 Lind Avenue, SW., Renton, Washington 98055-4056; telephone (425)
227-2125; fax (425) 227-1149.
SUPPLEMENTARY INFORMATION:
Discussion
On March 25, 2004, we issued AD 2004-07-15, amendment 39-13559 (69
FR 17906, April 6, 2004), for certain Airbus Model A321-111, -112, and
-131 series airplanes. That AD requires repetitive inspections to
detect fatigue cracking in the area surrounding certain attachment
holes of the forward pintle fittings of the main landing gear (MLG) and
the actuating cylinder anchorage fittings on the inner rear spar; and
repair, if necessary. That AD also provided for optional terminating
action for the repetitive inspections. That AD resulted from a fleet
survey by the manufacturer. We issued that AD to detect and correct
fatigue cracking on the inner rear spar of the wings, which could
result in reduced structural integrity of the airplane.
Actions Since Existing AD Was Issued
Since we issued AD 2004-07-15, Airbus conducted further analysis of
the fatigue and damage tolerance of the mounting holes of the inner
rear spar of the wing. The results of the analysis revealed that three
more mounting holes require inspection and that it is necessary to
decrease the thresholds of the repetitive inspections already required
by AD 2004-07-15.
Relevant Service Information
Airbus has issued Service Bulletin (SB) A320-57-1101, Revision 04,
dated November 22, 2004. (AD 2004-07-15 refers to Airbus SB A320-57-
1101, dated July 24, 1997; and Revision 02, dated October 25, 2001; as
appropriate sources of service information for the actions required by
that AD.) SB A320-57-1101, Revision 04, describes procedures for
performing repetitive ultrasonic inspections for fatigue cracking in
the area around certain mounting holes on the inner rear spar of the
wings. The thresholds specified in SB A320-57-1101, Revision 04, have
been reduced from those specified in SB A320-57-1101, Revision 02; and
from those thresholds specified in Airbus SB A320-57-1101, Revision 03,
dated July 30, 2003, which added three additional mounting holes to the
area subject to the repetitive inspections. The Direction
G[eacute]n[eacute]rale de l'Aviation Civile (DGAC), which is the
airworthiness authority for France, mandated SB A320-57-1101, Revision
03, and issued French airworthiness directive F-2004-166, dated October
13, 2004, to ensure the continued airworthiness of these airplanes in
France. Airbus SB A320-57-1101, Revision 04--which was released after
the issuance of French airworthiness directive F-2004-166--is also
acceptable for accomplishing the requirements of this AD.
We have reviewed later revisions of Airbus SB A320-57-1100, dated
July 28, 1997, which is designated as the appropriate source of
information for accomplishing the optional terminating action specified
in paragraph (b) of AD 2004-07-15. Those later revisions are Airbus SB
A320-57-1100, Revision 01, dated June 4, 1999; Revision 02, dated
October 25, 2001; and Revision 03, dated January 16, 2003. Though not
specified in AD 2004-07-15, SB A320-57-1100 includes Appendix 01 only,
while SB A320-57-1100, Revisions 01, 02, and 03 include Appendices 01
and 02. Any revision of SB A320-57-1100 is considered an acceptable
source of service information for accomplishing the optional
terminating action specified in paragraph (b) of AD 2004-07-15, which
is restated as paragraph (g) of this AD.
FAA's Determination and Requirements of This AD
This airplane model is manufactured in France and is type
certificated for operation in the United States under the provisions of
section 21.29 of the Federal Aviation Regulations (14 CFR 21.29) and
the applicable bilateral airworthiness agreement. Pursuant to this
bilateral airworthiness agreement, the DGAC has kept the FAA informed
of the situation described above. We have examined the DGAC's findings,
evaluated all pertinent information, and determined that we need to
issue an AD for products of this type design that are certificated for
operation in the United States.
We are issuing this AD to supersede AD 2004-07-15. This new AD
continues to require repetitive inspections to detect fatigue cracking
in the area surrounding certain attachment holes of the forward pintle
fittings of the MLG and the actuating cylinder anchorage fittings on
the inner rear spar; and repair, if necessary; and additional
inspections and repairs, if necessary; as specified in the service
information described previously; except as discussed under
``Difference Between French Airworthiness Directive and This AD'' and
``Differences Between This AD and Service Information.''
Difference Between French Airworthiness Directive and This AD
The applicability of French airworthiness directive F-2004-166
excludes airplanes on which Airbus SB A320-57-1100 was accomplished in
service. However, we have not excluded those airplanes in the
applicability of this AD; rather, this AD includes a requirement to
accomplish the actions specified in SB A320-57-1101, Revision 04, and
provides for doing SB A320-57-1100 as an optional terminating action
for the actions in SB A320-57-1101. This requirement will ensure that
the actions specified in SB A320-57-1101, Revision 04, are accomplished
on all affected airplanes. Operators must continue to operate the
airplane in the configuration required by this AD unless an alternative
method of compliance (AMOC) is approved.
Differences Between This AD and Service Information
Airbus SB A320-57-1101, Revision 04, does not describe any method
or service information to be used to repair any crack discovered during
any inspection specified by the service information. Therefore, this AD
requires operators to use a repair method that we
[[Page 8794]]
or the DGAC (or its delegated agent) approve.
Although the service bulletins describe procedures for reporting
inspection findings to Airbus, this AD does not require such a report.
Explanation of Change to Applicability
We have revised the applicability of the existing AD to identify
model designations as published in the most recent type certificate
data sheet for the affected models.
Change to Existing AD
This AD would retain certain requirements of AD 2004-07-15. Since
AD 2004-07-15 was issued, the AD format has been revised, and certain
paragraphs have been rearranged. As a result, the corresponding
paragraph identifiers have changed in this AD, as listed in the
following table:
Revised Paragraph Identifiers
------------------------------------------------------------------------
Corresponding requirement in
Requirement in AD 2004-07-15 this proposed AD
------------------------------------------------------------------------
Paragraph (a)........................... Paragraph (f).
Paragraph (b)........................... Paragraph (g).
Paragraph (c)........................... Paragraph (h).
Paragraph (d)........................... Paragraph (i).
Paragraph (e)........................... Paragraph (j).
Paragraph (f)........................... Paragraph (m).
------------------------------------------------------------------------
Clarification of AMOC Paragraph
We have revised this action to clarify the appropriate procedure
for notifying the principal inspector before using any approved AMOC on
any airplane to which the AMOC applies.
Costs of Compliance
None of the airplanes affected by this action are on the U.S.
Register. All airplanes included in the applicability of this AD
currently are operated by non-U.S. operators under foreign registry;
therefore, they are not directly affected by this AD action. However,
we consider that this AD is necessary to ensure that the unsafe
condition is addressed in the event that any of these subject airplanes
are imported and placed on the U.S. Register in the future.
If an affected airplane is imported and placed on the U.S. Register
in the future, it would require approximately 22 work hours to
accomplish the required actions at an average labor rate of $65 per
work hour. Based on these figures, the cost impact of this AD would be
$1,430 per airplane.
If an operator elects to accomplish the optional terminating action
provided by this AD, it would take approximately 520 work hours to
accomplish, at an average labor rate of $65 per work hour. The cost of
required parts would be approximately $17,540 per airplane. Based on
these figures, the cost impact of the optional terminating action would
be $51,340 per airplane.
FAA's Determination of the Effective Date
No airplane affected by this AD is currently on the U.S. Register.
Therefore, providing notice and opportunity for public comment is
unnecessary before this AD is issued, and this AD may be made effective
in less than 30 days after it is published in the Federal Register.
Comments Invited
This AD is a final rule that involves requirements that affect
flight safety and was not preceded by notice and an opportunity for
public comment; however, we invite you to submit any relevant written
data, views, or arguments regarding this AD. Send your comments to an
address listed in the ADDRESSES section. Include ``Docket No. FAA-2006-
23935; Directorate Identifier 2005-NM-060-AD'' at the beginning of your
comments. We specifically invite comments on the overall regulatory,
economic, environmental, and energy aspects of the AD that might
suggest a need to modify it.
We will post all comments we receive, without change, to https://
dms.dot.gov, including any personal information you provide. We will
also post a report summarizing each substantive verbal contact with FAA
personnel concerning this AD. Using the search function of that Web
site, anyone can find and read the comments in any of our dockets,
including the name of the individual who sent the comment (or signed
the comment on behalf of an association, business, labor union, etc.).
You may review the DOT's complete Privacy Act Statement in the Federal
Register published on April 11, 2000 (65 FR 19477-78), or you may visit
https://dms.dot.gov.
Examining the Docket
You may examine the AD docket on the Internet at https://
dms.dot.gov, or in person at the Docket Management Facility office
between 9 a.m. and 5 p.m., Monday through Friday, except Federal
holidays. The Docket Management Facility office (telephone (800) 647-
5227) is located on the plaza level of the Nassif Building at the DOT
street address stated in the ADDRESSES section. Comments will be
available in the AD docket shortly after the Docket Management System
receives them.
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 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 the regulation:
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. 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:
[[Page 8795]]
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 39-13559 (69 FR 17906, April 6, 2004) and by adding
the following new airworthiness directive (AD):
2006-04-11 Airbus: Amendment 39-14492. Docket No. FAA-2006-23935;
Directorate Identifier 2005-NM-060-AD.
Effective Date
(a) This AD becomes effective March 8, 2006.
Affected ADs
(b) This AD supersedes AD 2004-07-15.
Applicability
(c) This AD applies to Airbus Model A321-111, -112, and -131
airplanes, certificated in any category; all manufacturer serial
numbers (MSN), except MSN 364 and 365; and except for those
airplanes that have received Airbus Modification 24977 in
production.
Unsafe Condition
(d) This AD results from manufacturer analysis of the fatigue
and damage tolerance of the area surrounding certain mounting holes
of the main landing gear (MLG). The FAA is issuing this AD to detect
and correct fatigue cracking on the inner rear spar of the wings,
which could 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.
Restatement of Requirements of AD 2004-07-15
Repetitive Inspections and Corrective Actions
(f) Prior to the accumulation of 20,000 total flight cycles, or
within 120 days after December 18, 1998 (the effective date of AD
98-25-05, amendment 39-10928), whichever occurs later, perform an
ultrasonic inspection to detect fatigue cracking in the area
surrounding certain attachment holes of the forward pintle fittings
of the MLG and the actuating cylinder anchorage fittings on the
inner rear spar, in accordance with Airbus Service Bulletin A320-57-
1101, dated July 24, 1997; or Revision 02, dated October 25, 2001.
(1) If no cracking is detected, prior to further flight, repair
the sealant in the inspected areas and repeat the ultrasonic
inspections thereafter at intervals not to exceed 7,700 flight
cycles, until paragraph (g), (i), or (k) of this AD is accomplished.
(2) If any cracking is detected, prior to further flight, repair
in accordance with a method approved by either the Manager,
International Branch, ANM-116, Transport Airplane Directorate, FAA;
or the Direction Generale de l'Aviation Civile (DGAC) (or its
delegated agent).
Optional Terminating Action
(g) Accomplishment of visual and eddy current inspections to
detect cracking in the area surrounding certain attachment holes of
the forward pintle fittings of the MLG and the actuating cylinder
anchorage fittings on the inner rear spar; follow-on corrective
actions, as applicable; and rework of the attachment holes; in
accordance with Airbus Service Bulletin A320-57-1100, including
Appendix 01, dated July 28, 1997; or Revision 03, including
Appendices 01 and 02, dated January 16, 2003; constitutes
terminating action for the repetitive inspection requirements of
this AD. Actions accomplished in accordance with Airbus Service
Bulletin A320-57-1100, Revision 01, including Appendices 01 and 02,
dated June 4, 1999; or Revision 02, including Appendices 01 and 02,
dated October 25, 2001; are considered acceptable for compliance
with the optional terminating action specified in this paragraph. If
any cracking is detected during accomplishment of any inspection
described in the service bulletin, and the service bulletin
specifies to contact Airbus for appropriate action: Prior to further
flight, repair in accordance with a method approved by either the
Manager, International Branch, ANM-116; or the DGAC (or its
delegated agent).
Repetitive Inspections for Airplanes Not Previously Inspected Per
Paragraph (f)
(h) For airplanes on which the initial inspection required by
paragraph (f) of this AD has not been accomplished as of April 21,
2004 (the effective date of AD 2004-07-15): Accomplish the
inspection required by paragraph (f) of this AD, at the earlier of
the times specified in paragraphs (h)(1) and (h)(2) of this AD. If
no cracking is found, repeat the inspection thereafter at intervals
not to exceed 5,500 flight cycles or 10,200 flight hours, whichever
occurs first, until paragraph (g) or (k) of this AD is accomplished.
Accomplishment of this paragraph eliminates the need to accomplish
repetitive inspections at the intervals required by paragraph (f)(1)
of this AD.
(1) Prior to the accumulation of 20,000 total flight cycles.
(2) Prior to the accumulation of 37,300 total flight hours, or
within 120 days after April 21, 2004, whichever occurs later.
Repetitive Inspections for Airplanes Previously Inspected Per
Paragraph (f)
(i) For airplanes on which the initial inspection required by
paragraph (f) of this AD has been accomplished as of April 21, 2004,
and no cracking was found: Do the next inspection at the earlier of
the times specified in paragraphs (i)(1) and (i)(2) of this AD, and
repeat the inspection thereafter at intervals not to exceed 5,500
flight cycles or 10,200 flight hours, whichever occurs first, until
paragraph (g) or (k) of this AD is accomplished. Accomplishment of
this paragraph terminates the repetitive inspections required by
paragraph (f)(1) of this AD.
(1) Within 7,700 flight cycles since the most recent inspection.
(2) At the later of the times specified in paragraph (i)(2)(i)
or (i)(2)(ii) of this AD:
(i) Within 5,500 flight cycles or 10,200 flight hours since the
most recent inspection, whichever occurs first.
(ii) Within 120 days after April 21, 2004.
Existing Repair
(j) If any cracking is detected during any inspection required
by paragraph (h) or (i) of this AD: Prior to further flight, repair
in accordance with a method approved by either the Manager,
International Branch, ANM-116; or the DGAC (or its delegated agent).
New Requirements of This AD
Initial and Repetitive Inspections
(k) Within the applicable compliance times specified by
paragraph (k)(1), (k)(2), or (k)(3) of this AD, perform an
ultrasonic inspection for cracking of the attachment holes of the
MLG pintle fittings in the inner rear spar in accordance with the
Accomplishment Instructions of Airbus Service Bulletin A320-57-1101,
Revision 03, dated July 30, 2003; or Revision 04, dated November 22,
2004. If no cracking is found, repeat the inspection thereafter at
intervals not to exceed 5,500 flight cycles or 10,200 flight hours,
whichever occurs first, until paragraph (g) of this AD is
accomplished. Accomplishment of this paragraph terminates the
repetitive inspections required by paragraphs (f)(1), (h), and (i)
of this AD.
(1) For airplanes that have never been inspected in accordance
with Airbus Service Bulletin A320-57-1101, dated July 24, 1997; or
Revision 02, dated October 25, 2001: Before the accumulation of
20,000 total flight cycles or 37,300 total flight hours, whichever
occurs first; or within 120 days after the effective date of this
AD; whichever occurs later.
(2) For airplanes previously inspected in accordance with Airbus
Service Bulletin A320-57-1101, dated July 24, 1997; or Revision 02,
dated October 25, 2001, that have accumulated less than 18,900 total
flight cycles or 35,300 total flight hours as of the effective date
of this AD: Within 5,500 flight cycles or 10,200 flight hours,
whichever occurs first, after the previous inspection performed in
accordance with Airbus Service Bulletin A320-57-1101, Revision 02,
dated October 25, 2001; or within 120 days after the effective date
of this AD; whichever occurs later.
(3) For airplanes previously inspected in accordance with Airbus
Service Bulletin A320-57-1101, dated July 24, 1997; or Revision 02,
dated October 25, 2001, that have accumulated 18,900 or more flight
cycles or 35,300 or more flight hours as of the effective date of
this AD: Before the accumulation of 24,400 total flight cycles or
45,600 total flight hours, whichever occurs first; or within 120
days after the effective date of this AD; whichever occurs later.
New Repair
(l) If any crack is detected during any inspection required by
paragraph (k) of this AD: Prior to further flight, repair in
accordance with a method approved by either the Manager,
International Branch, ANM-116; or the DGAC (or its delegated agent).
[[Page 8796]]
No Reporting Requirement
(m) Although Airbus Service Bulletin A320-57-1101, Revision 02,
dated October 25, 2001; and Revision 04, dated November 22, 2004;
describe procedures for reporting inspection findings to Airbus,
this AD does not require such a report.
Alternative Methods of Compliance (AMOCs)
(n)(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) Before using any AMOC approved in accordance with 14 CFR
39.19 on any airplane to which the AMOC applies, notify the
appropriate principal inspector in the FAA Flight Standards
Certificate Holding District Office.
Related Information
(o) French airworthiness directive F-2004-166, dated October 13,
2004, also addresses the subject of this AD.
Material Incorporated by Reference
(p) You must use the service information specified in Table 1 of
this AD to perform the actions that are required by this AD, unless
the AD specifies otherwise.
Table 1.--All Material Incorporated by Reference
----------------------------------------------------------------------------------------------------------------
Airbus service bulletin Revision level Date
----------------------------------------------------------------------------------------------------------------
A320-57-1100, including Appendix 01...... Original.................... July 28, 1997.
A320-57-1100, including Appendices 01 and 03.......................... January 16, 2003.
02.
A320-57-1101............................. Original.................... July 24, 1997.
A320-57-1101............................. 02.......................... October 25, 2001.
A320-57-1101............................. 03.......................... July 30, 2003.
A320-57-1101............................. 04.......................... November 22, 2004.
----------------------------------------------------------------------------------------------------------------
The optional terminating action specified in paragraph (g) of
this AD should be done in accordance with the service bulletins
specified in Table 2 of this AD.
Table 2.--Optional Service Bulletins
----------------------------------------------------------------------------------------------------------------
Airbus service bulletin Revision level Date
----------------------------------------------------------------------------------------------------------------
A320-57-1100, including Appendix 01...... Original.................... July 28, 1997.
A320-57-1100, including Appendices 01 and 03.......................... January 16, 2003.
02.
----------------------------------------------------------------------------------------------------------------
(1) The Director of the Federal Register approved the
incorporation by reference of the service bulletins specified 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
----------------------------------------------------------------------------------------------------------------
A320-57-1100, including Appendix 01...... Original.................... July 28, 1997.
A320-57-1100, including Appendices 01 and 03.......................... January 16, 2003.
02.
A320-57-1101............................. 03.......................... July 30, 2003.
A320-57-1101............................. 04.......................... November 22, 2004.
----------------------------------------------------------------------------------------------------------------
(2) The incorporation by reference of Airbus Service Bulletin
A320-57-1101, Revision 02, dated October 25, 2001, was approved
previously by the Director of the Federal Register as of April 21,
2004 (69 FR 17906, April 6, 2004).
(3) The incorporation by reference of Airbus Service Bulletin
A320-57-1101, dated July 24, 1997, was approved previously by the
Director of the Federal Register as of December 18, 1998 (63 FR
66753, December 3, 1998).
(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 Docket Management Facility, U.S. Department of
Transportation, 400 Seventh Street SW., room PL-401, Nassif
Building, Washington, DC; on the Internet at https://dms.dot.gov; or
at the National Archives and Records Administration (NARA). For
information on the availability of this material at the NARA, call
(202) 741-6030, or go to https://www.archives.gov/federal_register/
code_of_federal_regulations/ibr_locations.html.
Issued in Renton, Washington, on February 9, 2006.
Kalene C. Yanamura,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 06-1504 Filed 2-17-06; 8:45 am]
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