Airworthiness Directives; Airbus Model A321-100 Series Airplanes, 32807-32811 [06-5121]
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32807
Federal Register / Vol. 71, No. 109 / Wednesday, June 7, 2006 / Rules and Regulations
this rule, as stated above, this rule
merely implements language which
Congress has enacted and complies with
the court’s final judgment and order.
AMS is committed to compliance
with the Government Paperwork
Elimination Act (GPEA), which requires
Government agencies in general to
provide the public the option of
submitting information or transacting
business electronically to the maximum
extent possible.
USDA has not identified any relevant
Federal rules that duplicate, overlap, or
conflict with this rule.
No additional collection or
recordkeeping requirements are
imposed on the public by this rule.
Accordingly, OMB clearance is not
required by § 305(h) of the Paperwork
Reduction Act of 1995, 44 U.S.C. 3501,
et seq., or OMB’s implementing
regulation at 5 CFR part 1320.
Further, given the Congressional
amendments, and the court’s final
judgment and order, good cause exists
under 5 U.S.C. 533 for not postponing
the effective date of this rule, except
§ 205.606, until 30 days after
publication in the Federal Register.
List of Subjects in 7 CFR Part 205
Administrative practice and
procedure, Agriculture, Animals,
Archives and records, Imports, Labeling,
Organically produced products, Plants,
Reporting and recordkeeping
requirements, Seals and insignia, Soil
conservation.
I For the reasons set forth in the
preamble, 7 CFR part 205, is amended
as follows:
PART 205—NATIONAL ORGANIC
PROGRAM
1. The authority citation for 7 CFR
part 205 continues to read as follows:
I
Authority: 7 U.S.C. 6501–6522.
2. Section 205.236 (a)(2) is revised to
read as follows:
I
§ 205.236
Origin of Livestock.
(a) * * *
(2) Dairy animals. Milk or milk
products must be from animals that
have been under continuous organic
management beginning no later than 1
year prior to the production of the milk
or milk products that are to be sold,
labeled, or represented as organic,
Except,
(i) That, crops and forage from land,
included in the organic system plan of
a dairy farm, that is in the third year of
organic management may be consumed
by the dairy animals of the farm during
the 12-month period immediately prior
to the sale of organic milk and milk
products; and
(ii) That, when an entire, distinct herd
is converted to organic production, the
producer may, provided no milk
produced under this subparagraph
enters the stream of commerce labeled
as organic after June 9, 2007: (a) For the
first 9 months of the year, provide a
minimum of 80-percent feed that is
either organic or raised from land
included in the organic system plan and
managed in compliance with organic
crop requirements; and (b) Provide feed
in compliance with § 205.237 for the
final 3 months.
(iii) Once an entire, distinct herd has
been converted to organic production,
all dairy animals shall be under organic
management from the last third of
gestation.
*
*
*
*
*
I 3. Section 205.606 is revised to read
as follows:
§ 205.606 Nonorganically produced
agricultural products allowed as ingredients
in or on processed products labeled as
organic.
Only the following nonorganically
produced agricultural products may be
used as ingredients in or on processed
products labeled as ‘‘organic,’’ only in
accordance with any restrictions
specified in this section, and only when
the product is not commercially
available in organic form.
(a) Cornstarch (native)
(b) Gums—water extracted only (arabic,
guar, locust bean, carob bean)
(c) Kelp—for use only as a thickener and
dietary supplement
(d) Lecithin—unbleached
(e) Pectin (high-methoxy)
Dated: June 2, 2006.
Barry L. Carpenter,
Acting Administrator, Agricultural Marketing
Service.
[FR Doc. 06–5203 Filed 6–5–06; 9:14 am]
BILLING CODE 3410–02–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2006–24953; Directorate
Identifier 2006–NM–084–AD; Amendment
39–14628; AD 2006–04–11 R1]
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 revising an
existing airworthiness directive (AD)
that applies to certain Airbus Model
A321–111, –112, and –131 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. That AD also provides for
optional terminating action for the
repetitive inspections, adds inspections
of three additional mounting holes, and
revises the thresholds for the currently
required inspections. 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. This new AD
retains the requirements and revises the
applicability of that AD. This AD results
from the discovery of a typographical
error in the applicability of that AD,
which could cause the unsafe condition
on an affected airplane to remain
uncorrected. 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: Effective June 22, 2006.
The incorporation by reference of the
publications specified in the following
table, as listed in the regulations, was
approved previously by the Director of
the Federal Register as of March 8, 2006
(71 FR 8792, February 21, 2006).
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MATERIAL INCORPORATED BY REFERENCE
Revision
level
Airbus service bulletin
A320–57–1100, including Appendix 01 ..............................................................................................................
A320–57–1100, including Appendices 01 and 02 ..............................................................................................
A320–57–1101 ....................................................................................................................................................
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03
03
Date
July 28, 1997.
January 16, 2003.
July 30, 2003.
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Federal Register / Vol. 71, No. 109 / Wednesday, June 7, 2006 / Rules and Regulations
MATERIAL INCORPORATED BY REFERENCE—Continued
Revision
level
Airbus service bulletin
A320–57–1101 ....................................................................................................................................................
04
Date
November 22, 2004.
1 Original.
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).
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 August 7, 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,
Transport Airplane Directorate, FAA,
1601 Lind Avenue, SW., Renton,
Washington 98055–4056; telephone
(425) 227–2125; fax (425) 227–1149.
SUPPLEMENTARY INFORMATION:
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Discussion
On February 9, 2006, we issued AD
2006–04–11, amendment 39–14492 (71
FR 8792, February 21, 2006), for certain
Airbus Model A321–111, –112, and
–131 airplanes. That AD requires
repetitive inspections to detect fatigue
cracking in the area surrounding certain
attachment holes of the forward pintle
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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
provides for optional terminating action
for the repetitive inspections, adds
inspections of three additional
mounting holes, and revises the
thresholds for the currently required
inspections. That AD resulted from
manufacturer analysis of the fatigue and
damage tolerance of the area
surrounding certain mounting holes of
the MLG. 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 2006–04–11,
amendment 39–14492, a typographical
error was discovered in the applicability
of that AD, which could cause the
unsafe condition on an affected airplane
to remained uncorrected. The
applicability of that AD states, ‘‘all
manufacturer serial numbers (MSN),
except MSN 364 and 365.’’ The correct
reference should have been, ‘‘all
manufacturer serial numbers (MSN),
except MSN 364 and 385.’’
Clarification of No Reporting
Requirement
Airbus Service Bulletin A320–57–
1101, Revision 03, dated July 30, 2003,
which also describes procedures for
reporting inspection findings to Airbus,
was inadvertently omitted from
paragraph (m) of AD 2006–04–11, which
specifies that we do not require reports
of inspection findings. We have revised
paragraph (m) of this AD to include
Service Bulletin A320–57–1101,
Revision 3.
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,
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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.
This new AD revises the applicability
of AD 2006–04–11 by correcting the
reference, ‘‘all manufacturer serial
numbers (MSN), except MSN 364 and
365,’’ to read ‘‘all manufacturer serial
numbers (MSN), except MSN 364 and
385.’’ This new AD also retains the
requirements of AD 2006–04–11.
Costs of Compliance
The revisions made to this AD add no
additional economic burden. The
current costs for this AD are repeated for
the convenience of affected operators, as
follows:
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
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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 the address listed under
the ADDRESSES section. Include ‘‘Docket
No. FAA–2006–24953; Directorate
Identifier 2006–NM–084–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.
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.
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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.
List of Subjects in 14 CFR Part 39
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
I
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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:
Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13
[Amended]
2. The Federal Aviation
Administration (FAA) amends § 39.13
by removing amendment 39–14492 (71
FR 8792, February 21, 2006), and adding
the following new airworthiness
directive (AD):
I
AD 2006–04–11 R1 Airbus: Amendment
39–14628. Docket No. FAA–2006–24953;
Directorate Identifier 2006–NM–084–AD.
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32809
Effective Date
(a) This AD becomes effective June 22,
2006.
Affected ADs
(b) This AD revises AD 2006–04–11.
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 385; 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 European
Aviation Safety Agency (EASA) (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
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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
EASA (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 EASA (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).
No Reporting Requirement
(m) Although Airbus Service Bulletin
A320–57–1101, Revision 02, dated October
25, 2001; Revision 03, dated July 30, 2003;
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
Revision
level
Airbus service bulletin
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 .....................................................................................................................................................
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1 Original.
The optional terminating action specified
in paragraph (g) of this AD should be done
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in accordance with the service bulletins
specified in Table 2 of this AD.
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03
(1)
02
03
04
Date
July 28, 1997.
January 16, 2003.
July 24, 1997.
October 25, 2001.
July 30, 2003.
November 22, 2004.
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TABLE 2.—OPTIONAL SERVICE BULLETINS
Revision
level
Airbus service bulletin
(1)
03
A320–57–1100, including Appendix 01 ................................................................................................................
A320–57–1100, including Appendices 01 and 02 ................................................................................................
Date
July 28, 1997.
January 16, 2003.
1 Original.
(1) The incorporation by reference of the
service information specified in Table 3 of
this AD was approved previously by the
Director of the Federal Register as of March
8, 2006 (71 FR 8792, February 21, 2006).
TABLE 3.—NEW MATERIAL INCORPORATED BY REFERENCE
Revision
level
Airbus service bulletin
A320–57–1100, including Appendix 01 ..............................................................................................................
A320–57–1100, including Appendices 01 and 02 ..............................................................................................
A320–57–1101 ....................................................................................................................................................
A320–57–1101 ....................................................................................................................................................
(1)
03
03
04
Date
July 28, 1997.
January 16, 2003.
July 30, 2003.
November 22, 2004.
1 Original.
(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 May 26,
2006.
Jeffrey E. Duven,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. 06–5121 Filed 6–6–06; 8:45 am]
sroberts on PROD1PC70 with RULES
BILLING CODE 4910–13–P
VerDate Aug<31>2005
19:09 Jun 06, 2006
Jkt 208001
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2005–22628; Directorate
Identifier 2005–NM–056–AD; Amendment
39–14631; AD 2006–12–06]
RIN 2120–AA64
Airworthiness Directives; Boeing
Model 737–300, –400, –500, –700, and
–800 Series Airplanes; Model 747–400
and –400F Series Airplanes; Model
757–200 Series Airplanes; Model 767–
300 Series Airplanes; and Model 777–
300 Series Airplanes Equipped With
Certain Driessen or Showa Galleys or
Driessen Closets
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
AGENCY:
SUMMARY: The FAA is adopting a new
airworthiness directive (AD) for certain
Boeing transport category airplanes.
This AD requires inspecting to
determine if certain galleys and closets
are installed, and replacing the spiral
wire wrapping of the electrical cables of
the galleys and closets with new spiral
wire wrapping if necessary. This AD
results from testing and reports from the
manufacturer indicating unacceptable
flammability properties of wire
wrapping installed in certain galleys
and closets. We are issuing this AD to
prevent fire propagation or smoke in the
cabin area due to electrical arcing or
sparking and ignition of the spiral wire
wrapping.
PO 00000
Frm 00009
Fmt 4700
Sfmt 4700
This AD becomes effective July
12, 2006.
The Director of the Federal Register
approved the incorporation by reference
of certain publications listed in the AD
as of July 12, 2006.
ADDRESSES: You may examine the AD
docket on the Internet at https://
dms.dot.gov or in person at the Docket
Management Facility, U.S. Department
of Transportation, 400 Seventh Street,
SW., Nassif Building, Room PL–401,
Washington, DC.
Contact Boeing Commercial
Airplanes, P.O. Box 3707, Seattle,
Washington 98124–2207, for service
information identified in this AD.
FOR FURTHER INFORMATION CONTACT:
Robert Kaufman, Aerospace Engineer,
Cabin Safety and Environmental
Systems Branch, ANM–150S, FAA,
Seattle Aircraft Certification Office,
1601 Lind Avenue, SW., Renton,
Washington 98055–4056; telephone
(425) 917–6433; fax (425) 917–6590.
SUPPLEMENTARY INFORMATION:
DATES:
Examining the Docket
You may examine the airworthiness
directive (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 street address stated in the
ADDRESSES section.
Discussion
The FAA issued a notice of proposed
rulemaking (NPRM) to amend 14 CFR
part 39 to include an AD that would
E:\FR\FM\07JNR1.SGM
07JNR1
]]>Agencies
[Federal Register Volume 71, Number 109 (Wednesday, June 7, 2006)]
[Rules and Regulations]
[Pages 32807-32811]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 06-5121]
=======================================================================
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2006-24953; Directorate Identifier 2006-NM-084-AD;
Amendment 39-14628; AD 2006-04-11 R1]
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 revising an existing airworthiness directive (AD)
that applies to certain Airbus Model A321-111, -112, and -131
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. That AD also provides for optional terminating
action for the repetitive inspections, adds inspections of three
additional mounting holes, and revises the thresholds for the currently
required inspections. 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. This new AD retains the
requirements and revises the applicability of that AD. This AD results
from the discovery of a typographical error in the applicability of
that AD, which could cause the unsafe condition on an affected airplane
to remain uncorrected. 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: Effective June 22, 2006.
The incorporation by reference of the publications specified in the
following table, as listed in the regulations, was approved previously
by the Director of the Federal Register as of March 8, 2006 (71 FR
8792, February 21, 2006).
Material Incorporated by Reference
------------------------------------------------------------------------
Revision
Airbus service bulletin level Date
------------------------------------------------------------------------
A320-57-1100, including (\1\) July 28, 1997.
Appendix 01.
A320-57-1100, including 03 January 16, 2003.
Appendices 01 and 02.
A320-57-1101................... 03 July 30, 2003.
[[Page 32808]]
A320-57-1101................... 04 November 22, 2004.
------------------------------------------------------------------------
\1\ Original.
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).
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 August 7, 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, Transport Airplane Directorate, FAA,
1601 Lind Avenue, SW., Renton, Washington 98055-4056; telephone (425)
227-2125; fax (425) 227-1149.
SUPPLEMENTARY INFORMATION:
Discussion
On February 9, 2006, we issued AD 2006-04-11, amendment 39-14492
(71 FR 8792, February 21, 2006), for certain Airbus Model A321-111, -
112, and -131 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 provides for optional terminating
action for the repetitive inspections, adds inspections of three
additional mounting holes, and revises the thresholds for the currently
required inspections. That AD resulted from manufacturer analysis of
the fatigue and damage tolerance of the area surrounding certain
mounting holes of the MLG. 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 2006-04-11, amendment 39-14492, a typographical
error was discovered in the applicability of that AD, which could cause
the unsafe condition on an affected airplane to remained uncorrected.
The applicability of that AD states, ``all manufacturer serial numbers
(MSN), except MSN 364 and 365.'' The correct reference should have
been, ``all manufacturer serial numbers (MSN), except MSN 364 and
385.''
Clarification of No Reporting Requirement
Airbus Service Bulletin A320-57-1101, Revision 03, dated July 30,
2003, which also describes procedures for reporting inspection findings
to Airbus, was inadvertently omitted from paragraph (m) of AD 2006-04-
11, which specifies that we do not require reports of inspection
findings. We have revised paragraph (m) of this AD to include Service
Bulletin A320-57-1101, Revision 3.
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.
This new AD revises the applicability of AD 2006-04-11 by
correcting the reference, ``all manufacturer serial numbers (MSN),
except MSN 364 and 365,'' to read ``all manufacturer serial numbers
(MSN), except MSN 364 and 385.'' This new AD also retains the
requirements of AD 2006-04-11.
Costs of Compliance
The revisions made to this AD add no additional economic burden.
The current costs for this AD are repeated for the convenience of
affected operators, as follows:
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
[[Page 32809]]
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 the
address listed under the ADDRESSES section. Include ``Docket No. FAA-
2006-24953; Directorate Identifier 2006-NM-084-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:
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 39-14492 (71 FR 8792, February 21, 2006), and adding
the following new airworthiness directive (AD):
AD 2006-04-11 R1 Airbus: Amendment 39-14628. Docket No. FAA-2006-
24953; Directorate Identifier 2006-NM-084-AD.
Effective Date
(a) This AD becomes effective June 22, 2006.
Affected ADs
(b) This AD revises AD 2006-04-11.
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 385; 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 European Aviation Safety Agency (EASA) (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
[[Page 32810]]
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 EASA (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 EASA (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).
No Reporting Requirement
(m) Although Airbus Service Bulletin A320-57-1101, Revision 02,
dated October 25, 2001; Revision 03, dated July 30, 2003; 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
------------------------------------------------------------------------
Revision
Airbus service bulletin level Date
------------------------------------------------------------------------
A320-57-1100, including Appendix (\1\) July 28, 1997.
01.
A320-57-1100, including 03 January 16, 2003.
Appendices 01 and 02.
A320-57-1101.................... (\1\) July 24, 1997.
A320-57-1101.................... 02 October 25, 2001.
A320-57-1101.................... 03 July 30, 2003.
A320-57-1101.................... 04 November 22, 2004.
------------------------------------------------------------------------
\1\ Original.
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.
[[Page 32811]]
Table 2.--Optional Service Bulletins
----------------------------------------------------------------------------------------------------------------
Revision
Airbus service bulletin level Date
----------------------------------------------------------------------------------------------------------------
A320-57-1100, including Appendix 01...................... (\1\) July 28, 1997.
A320-57-1100, including Appendices 01 and 02............. 03 January 16, 2003.
----------------------------------------------------------------------------------------------------------------
\1\ Original.
(1) The incorporation by reference of the service information
specified in Table 3 of this AD was approved previously by the
Director of the Federal Register as of March 8, 2006 (71 FR 8792,
February 21, 2006).
Table 3.--New Material Incorporated by Reference
----------------------------------------------------------------------------------------------------------------
Revision
Airbus service bulletin level Date
----------------------------------------------------------------------------------------------------------------
A320-57-1100, including Appendix 01..................... (\1\) July 28, 1997.
A320-57-1100, including Appendices 01 and 02............ 03 January 16, 2003.
A320-57-1101............................................ 03 July 30, 2003.
A320-57-1101............................................ 04 November 22, 2004.
----------------------------------------------------------------------------------------------------------------
\1\ Original.
(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 May 26, 2006.
Jeffrey E. Duven,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 06-5121 Filed 6-6-06; 8:45 am]
BILLING CODE 4910-13-P
