Airworthiness Directives; Airbus Model A330-200, A330-300, A340-200, and A340-300 Series Airplanes, 67441-67445 [E6-19535]
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Federal Register / Vol. 71, No. 225 / Wednesday, November 22, 2006 / Rules and Regulations
credit union’s members or may threaten
to impair public confidence in any
credit union, by written notice served
upon such party, suspend him or her
from office, or prohibit him or her from
further participation in any manner in
the affairs of any credit union, or both.
A copy of the notice of suspension or
prohibition shall also be served upon
the credit union of which the subject of
the order is, or most recently was, an
institution-affiliated party.
7. Section 747.304 is revised to read
as follows:
I
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[FR Doc. E6–19703 Filed 11–21–06; 8:45 am]
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14 CFR Part 39
[Docket No. 2001–NM–381–AD; Amendment
39–14832; AD 2006–24–03]
RIN 2120–AA64
Airworthiness Directives; Airbus Model
A330–200, A330–300, A340–200, and
A340–300 Series Airplanes
Federal Aviation
Administration, DOT.
ACTION: Final rule.
(a) In the event that a judgment of
conviction or an agreement to enter a
pretrial diversion or other similar
program is entered against the
institution-affiliated party, and at such
time as the judgment, if any, is not
subject to further appellate review, the
NCUA Board may, if continued service
or participation by such party may pose
a threat to the interests of any credit
union’s members or may threaten to
impair public confidence in any credit
union, issue and serve upon the
individual an order removing him or her
from office or prohibiting him or her
from further participation in any
manner in the conduct of the affairs of
any credit union except with the
consent of the NCUA Board. A copy of
such order will also be served upon the
credit union of which the subject of the
order is, or most recently was, an
institution-affiliated party.
(b) The NCUA Board may issue such
order with respect to an individual who
is an institution-affiliated party at a
credit union at the time of the offense
without regard to whether such
individual is an institution-affiliated
party at any credit union at the time the
order is considered or issued by the
Board or whether the credit union at
which the individual was an institutionaffiliated party at the time of the offense
remains in existence at the time the
order is considered or issued by the
board.
(c) A finding of not guilty or other
disposition of the charge will not
preclude the Board from thereafter
instituting proceedings, pursuant to the
provisions of section 206(g) of the Act
(12 U.S.C. 1786(g)) and subpart A of this
part, to remove such director, committee
member, officer, or other person from
office or to prohibit his or her further
participation in the affairs of the credit
union.
VerDate Aug<31>2005
Federal Aviation Administration
AGENCY:
§ 747.304 Removal or permanent
prohibition.
BILLING CODE 7535–01–P
DEPARTMENT OF TRANSPORTATION
SUMMARY: This amendment adopts a
new airworthiness directive (AD),
applicable to certain Airbus Model
A330–200, A330–300, A340–200, and
A340–300 series airplanes. This AD
requires repetitive inspections for
discrepancies of the grease and gear
teeth of the radial variable differential
transducer of the nose wheel steering
gearbox; or repetitive inspections for
damage of the chrome on the bearing
surface of the nose landing gear (NLG)
main fitting barrel; as applicable. And,
for airplanes with any discrepancy or
damage, this AD requires an additional
inspection or corrective actions. This
AD also adds a terminating action. The
actions specified by this AD are
intended to prevent incorrect operation
or jamming of the nose wheel steering,
which could cause reduced
controllability of the airplane on the
ground. This action is intended to
address the identified unsafe condition.
DATES: Effective December 27, 2006.
The incorporation by reference of
certain publications listed in the
regulations is approved by the Director
of the Federal Register as of December
27, 2006.
ADDRESSES: The service information
referenced in this AD may be obtained
from Airbus, 1 Rond Point Maurice
Bellonte, 31707 Blagnac Cedex, France.
This information may be examined at
the Federal Aviation Administration
(FAA), Transport Airplane Directorate,
Rules Docket, 1601 Lind Avenue, SW.,
Renton, Washington.
FOR FURTHER INFORMATION CONTACT: Tim
Backman, Aerospace Engineer,
International Branch, ANM–116, FAA,
Transport Airplane Directorate, 1601
Lind Avenue, SW., Renton, Washington
98057–3356; telephone (425) 227–2797;
fax (425) 227–1149.
SUPPLEMENTARY INFORMATION: A
proposal to amend part 39 of the Federal
Aviation Regulations (14 CFR part 39) to
include an airworthiness directive (AD)
that is applicable to certain Airbus
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67441
Model A330–200, A330–300, A340–200,
and A340–300 series airplanes was
published as a supplemental notice of
proposed rulemaking (NPRM) in the
Federal Register on August 8, 2006 (71
FR 44937). That action proposed to
require repetitive inspections for
discrepancies of the grease and gear
teeth of the radial variable differential
transducer of the nose wheel steering
gearbox; or repetitive inspections for
damage of the chrome on the bearing
surface of the nose landing gear (NLG)
main fitting barrel; as applicable. And,
for airplanes with any discrepancy or
damage, that action proposed to require
an additional inspection or corrective
actions. That action also proposed to
add a terminating action and remove
certain airplanes from the applicability.
Comments
Interested persons have been afforded
an opportunity to participate in the
making of this amendment. Due
consideration has been given to the
comment received.
Request To Change Incorporation of
Certain Information
The Modification and Replacement
Parts Association (MARPA) states that,
typically, airworthiness directives are
based on service information originating
with the type certificate holder or its
suppliers. MARPA adds that
manufacturer service documents are
privately authored instruments
generally having copyright protection
against duplication and distribution.
MARPA notes that when a service
document is incorporated by reference
into a public document, such as an
airworthiness directive, it loses its
private, protected status and becomes a
public document. MARPA adds that if
a service document is used as a
mandatory element of compliance, it
should not simply be referenced, but
should be incorporated into the
regulatory document; by definition,
public laws must be public, which
means they cannot rely upon private
writings. MARPA adds that
incorporated-by-reference service
documents should be made available to
the public by publication in the Docket
Management System (DMS), keyed to
the action that incorporates them.
MARPA notes that the stated purpose of
the incorporation-by-reference method
is brevity, to keep from expanding the
Federal Register needlessly by
publishing documents already in the
hands of the affected individuals;
traditionally, ‘‘affected individuals’’
means aircraft owners and operators,
who are generally provided service
information by the manufacturer.
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67442
Federal Register / Vol. 71, No. 225 / Wednesday, November 22, 2006 / Rules and Regulations
incorporates by reference the documents
necessary for the accomplishment of the
requirements mandated by this AD.
Further, we point out that while
documents that are incorporated by
reference do become public information,
they do not lose their copyright
protection. For that reason, we advise
the public to contact the manufacturer
to obtain copies of the referenced
service information.
Additionally, we do not publish
service documents in DMS. We are
currently reviewing our practice of
publishing proprietary service
information. Once we have thoroughly
examined all aspects of this issue, and
have made a final determination, we
will consider whether our current
practice needs to be revised. However,
we consider that to delay this AD action
for that reason would be inappropriate,
since we have determined that an
unsafe condition exists and that the
requirements in this AD must be
accomplished to ensure continued
safety. Therefore, we have not changed
the AD in this regard.
method approved by either the FAA or
´ ´
the Direction Generale de l’Aviation
Civile (DGAC) (or its delegated agent).
The European Aviation Safety Agency
(EASA), which is the airworthiness
authority for the European Union, has
assumed responsibility for the airplane
models subject to this AD. Therefore, we
have revised paragraph (e)(2) of this AD
to specify making repairs using a
method approved by the FAA, the
DGAC (or its delegated agent), or the
EASA (or its delegated agent).
Model designations have been added
to Table 2 of paragraph (g)(2) of the
supplemental NPRM for clarification.
Explanation of Changes to the
Supplemental NPRM
Paragraph (e)(2) of the supplemental
NPRM specifies making repairs using a
MARPA adds that a new class of
affected individuals has emerged, since
the majority of aircraft maintenance is
now performed by specialty shops
instead of aircraft owners and operators.
MARPA notes that this new class
includes maintenance and repair
organizations, component servicing and
repair shops, parts purveyors and
distributors, and organizations
manufacturing or servicing alternatively
certified parts [under part 21 of the
Federal Aviation Regulations (14 CFR
part 21), § 21.303 (parts manufacturer
approval)]. MARPA adds that the
concept of brevity is now nearly archaic
as documents exist more frequently in
electronic format than on paper.
Therefore, MARPA asks that the service
documents deemed essential to the
accomplishment of the supplemental
NPRM be incorporated by reference into
the regulatory instrument, and
published in the DMS.
We do not agree that documents
should be incorporated by reference
during the NPRM phase of rulemaking.
The Office of the Federal Register (OFR)
requires that documents that are
necessary to accomplish the
requirements of the AD be incorporated
by reference during the final rule phase
of rulemaking. This final rule
Cost Impact
Conclusion
We have carefully reviewed the
available data, including the comment
received, and we have determined that
air safety and the public interest require
the adoption of the rule with the change
previously described. This change will
neither increase the economic burden
on any operator nor increase the scope
of the AD.
The following table provides the
estimated costs for U.S. operators to
comply with this AD.
ESTIMATED COSTS
Action
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Radial variable differential
transducer inspection, per
inspection cycle.
Chrome inspection, per inspection cycle.
Modification (Service Bulletin
A330–32–3164 or A340–
32–4204).
Rotating sleeve grease system
modification (Service Bulletin A330–32–3192 or
A340–32–4227).
15:05 Nov 21, 2006
Parts
Cost per airplane
Number of
U.S.-registered
airplanes
Fleet cost
6
$80
None ..............
$480 ...............
11
$5,280.
13
80
None ..............
$1,040 ............
15
$15,600.
15
80
$10,244 to
$11,337.
$11,444 to
$12,537.
12
$137,328 to $150,444.
15
80
Unknown ........
From $1,200 ..
23
From $27,600.
The cost impact figures discussed
above are based on assumptions that no
operator has yet accomplished any of
the requirements of this AD action, and
that no operator would accomplish
those actions in the future if this AD
were not adopted. The cost impact
figures discussed in AD rulemaking
actions represent only the time
necessary to perform the specific actions
actually required by the AD. These
figures typically do not include
incidental costs, such as the time
required to gain access and close up,
planning time, or time necessitated by
other administrative actions.
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Average labor
rate per hour
Work hours
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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
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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 Impact
The regulations adopted herein 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
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Federal Register / Vol. 71, No. 225 / Wednesday, November 22, 2006 / Rules and Regulations
levels of government. Therefore, it is
determined that this final rule does not
have federalism implications under
Executive Order 13132.
For the reasons discussed above, I
certify that this action (1) is not a
‘‘significant regulatory action’’ under
Executive Order 12866; (2) is not a
‘‘significant rule’’ under DOT
Regulatory Policies and Procedures (44
FR 11034, February 26, 1979); and (3)
will not have a significant economic
impact, positive or negative, on a
substantial number of small entities
under the criteria of the Regulatory
Flexibility Act. A final evaluation has
been prepared for this action and it is
contained in the Rules Docket. A copy
of it may be obtained from the Rules
Docket at the location provided under
the caption ADDRESSES.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation
safety, Incorporation by reference,
Safety.
Adoption of the Amendment
Accordingly, pursuant to the authority
delegated to me by the Administrator,
the Federal Aviation Administration
amends part 39 of the Federal Aviation
Regulations (14 CFR part 39) as follows:
I
PART 39—AIRWORTHINESS
DIRECTIVES
1. The authority citation for part 39
continues to read as follows:
I
Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13
[Amended]
2. Section 39.13 is amended by adding
the following new airworthiness
directive:
I
2006–24–03 Airbus: Amendment 39–14832.
Docket 2001–NM–381–AD.
Applicability: The following airplanes,
certificated in any category, except those
modified in production by both Airbus
Modifications 51381 and 53073:
Model A330–201, –202, –203, –223, and –243
airplanes
Model A330–301, –302, –303, –321, –322,
–323, –341, –342, and –343 airplanes
Model A340–211, –212, and –213 airplanes
Model A340–311, –312, and –313 airplanes
Compliance: Required as indicated, unless
accomplished previously.
To prevent incorrect operation or jamming
of the nose wheel steering (NWS), which
could cause reduced controllability of the
airplane on the ground, accomplish the
following:
Inspections: Airplanes Without Modification
51381
(a) For airplanes that were not modified in
production by Airbus Modification 51381: Do
the inspection specified in either paragraph
(a)(1) or (a)(2) of this AD, in accordance with
the required service bulletin identified in
67443
Table 1 of this AD, as applicable. The
required compliance time is specified in
paragraph (b) of this AD.
(1) Inspect for discrepancies of the grease
by sending it to a laboratory for analysis, and
do a detailed inspection for discrepancies of
the gear teeth of the radial variable
differential transducer (RVDT) driving ring
and the gears in the RVDT gearboxes. If there
are no discrepancies (such as metallic
particles in the grease, abnormal wear of the
gear teeth, or missing rubber sealant at the
mating face between the main fitting and the
RVDT gearbox), repeat the inspection as
specified in paragraph (c) of this AD. If there
is any discrepancy, do the inspection in
paragraph (a)(2) of this AD within 3 months
after the inspection specified in paragraph
(a)(1) of this AD.
(2) Do a detailed inspection for damage of
the chrome on the bearing surface of the nose
landing gear (NLG) main fitting barrel under
the NWS rotating sleeve. If there is no
damage (such as flaking, corrosion, or
blistering), repeat the inspection as specified
in paragraph (c) of this AD. If there is any
damage, before further flight, do the
corrective action in paragraph (e) of this AD.
Note 1: For the purposes of this AD, a
detailed inspection is defined as: ‘‘An
intensive visual examination of a specific
structural area, system, installation, or
assembly to detect damage, failure, or
irregularity. Available lighting is normally
supplemented with a direct source of good
lighting at intensity deemed appropriate by
the inspector. Inspection aids such as mirror,
magnifying lenses, etc., may be used. Surface
cleaning and elaborate access procedures
may be required.’’
TABLE 1.—INSPECTION SERVICE BULLETINS
Airbus
Service
Bulletin
Airplane models
Approved revision level (for actions done
before the effective date of the AD)
Required revision level
A330–32–
3134.
Revision 04, including Appendix 01,
dated April 3, 2006.
A340–200 and –300 series airplanes .......
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A330–200 and –300 series airplanes .......
A340–32–
4172.
Revision 04, including Appendix 01,
dated April 3, 2006.
(b) For airplanes identified in paragraph (a)
of this AD: Do the initial inspection specified
in paragraph (a) of this AD at the latest of the
following times:
(1) Within 60 months after the date that the
new NLG was installed on the airplane.
(2) Within 60 months after the last major
NLG overhaul accomplished before the
effective date of this AD.
(3) Within 700 flight hours after the
effective date of this AD.
(c) For airplanes identified in paragraph (a)
of this AD: Repeat either inspection specified
in paragraph (a)(1) or (a)(2) of this AD at
intervals not to exceed the applicable interval
specified in paragraph (c)(1) or (c)(2) of this
AD, until the requirements of paragraph (g)
of this AD are done.
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(1) If the most recent inspection was the
inspection specified in paragraph (a)(1) of
this AD, then the next inspection must be
done within 8 months.
(2) If the most recent inspection was the
inspection specified in paragraph (a)(2) of
this AD, then the next inspection must be
done within 18 months.
Repetitive Inspections: Airplanes With
Modification 51381
(d) For airplanes modified in production
by Airbus Modification 51381: Perform a
detailed inspection for damage of the chrome
on the bearing surface of the NLG main
fitting barrel under the NWS rotating sleeve.
Do the inspection at the later of the times
specified in paragraphs (d)(1) and (d)(2) of
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Original, dated September 11, 2001.
Revision 01, dated November 29, 2001.
Revision 02, dated August 8, 2003.
Revision 03, dated May 11, 2005.
Original, dated September 11, 2001.
Revision 01, dated November 29, 2001.
Revision 02, dated August 8, 2003.
Revision 03, dated May 11, 2005.
this AD in accordance with the applicable
required Airbus service bulletin identified in
Table 1 of this AD. Repeat the inspection
thereafter at intervals not to exceed 18
months, until the requirements of paragraph
(g) of this AD have been done.
(1) Within 60 months after the date that the
new NLG was installed on the airplane.
(2) Within 60 months after the last major
NLG overhaul accomplished before the
effective date of this AD.
Follow-on Investigative and Corrective
Actions
(e) For all airplanes: If any damage or
discrepancy is found during any inspection
required by this AD, do the corrective action
before further flight in accordance with the
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Federal Register / Vol. 71, No. 225 / Wednesday, November 22, 2006 / Rules and Regulations
applicable required Airbus service bulletin
identified in Table 1 of this AD, with the
following exceptions:
(1) If discrepancies are found during any
inspection specified in paragraph (a)(1) of
this AD, the inspection in paragraph (a)(2) of
this AD is required within 3 months.
(2) Where the service bulletin recommends
contacting Messier-Dowty for appropriate
action. Repair before further flight in
accordance with a method approved by the
Manager, International Branch, ANM–116,
FAA, Transport Airplane Directorate; the
Direction Gonorale de l’Aviation Civile (or its
delegated agent); or the European Aviation
Safety Agency (or its delegated agent).
Note 2: Airbus Service Bulletins A330–32–
3134 and A340–32–4172, both Revision 04,
both dated April 3, 2006, refer to MessierDowty Special Inspection Service Bulletins
D23285–32–037, Revision 2, dated May 23,
2002; and D23285–32–044, dated January 12,
2004; as additional sources of service
information for the inspections.
Credit for Prior Accomplishment
(f) Actions done before the effective date of
this AD in accordance with an applicable
Approved Revision Level of the service
bulletin identified in Table 1 of this AD are
acceptable for compliance with the
corresponding requirements of paragraphs
(a), (d), and (e) of this AD.
Modification
(g) For all airplanes: At the applicable time
specified in paragraph (g)(1) or (g)(2) of this
AD, modify the NLG as specified in Table 2
of this AD, as applicable.
(1) For NLGs overhauled before the
effective date of this AD: At the later of the
times specified in paragraphs (g)(1)(i) and
(g)(1)(ii) of this AD:
(i) Within 60 months since the NLG was
overhauled or 180 months since the NLG was
new, whichever occurs first.
(ii) Within 6 months after the effective date
of this AD.
(2) For NLGs not overhauled before the
effective date of this AD: Within 120 months
since the NLG was new, or within 6 months
after the effective date of this AD, whichever
occurs later.
TABLE 2.—MODIFICATION
For airplanes—
Modify the NLG in accordance with—
For Model A330 airplanes without Airbus Modifications 51381 and
53073 done in production.
51381 but not Air-
Airbus Service Bulletin A330–32–3164, dated June 27, 2003, or Revision 01, dated March 21, 2006; and A330–32–3192, dated December 8, 2005.
Airbus Service Bulletins A340–32–4204, dated June 27, 2003, or Revision 01, dated March 21, 2006; and A340–32–4227, dated December 8, 2005.
Airbus Service Bulletin A330–32–3192, dated December 8, 2005.
51381 but not Air-
Airbus Service Bulletin A340–32–4227, dated December 8, 2005.
53073 but not Air-
Airbus
sion
Airbus
sion
For Model A340 airplanes without Airbus Modifications 51381 and
53073 done in production.
For Model A330 airplanes with Airbus Modification
bus Modification 53073 done in production.
For Model A340 airplanes with Airbus Modification
bus Modification 53073 done in production.
For Model A330 airplanes with Airbus Modification
bus Modification 51381 done in production.
For Model A340 airplanes with Airbus Modification
bus Modification 51381 done in production.
Terminating Action
(h) Accomplishment of both NLG
modifications specified in paragraph (g) of
this AD terminates the repetitive inspection
requirements of this AD.
Note 3: Airbus Service Bulletins A330–32–
3164 and A340–32–4204 refer to MessierDowty Service Bulletin D23285–32–042,
dated June 19, 2003, as an additional source
of service information for the modification.
Note 4: Airbus Service Bulletins A330–32–
3192 and A340–32–4227 refer to MessierDowty Service Bulletin D23581–32–047,
dated December 1, 2005, as an additional
source of service information for the
modification.
Reporting
(i) Certain service bulletins specify to
submit a report to the manufacturer. This AD
53073 but not Air-
Service Bulletin A330–32–3164, dated June 27, 2003, or Revi01, dated March 21, 2006.
Service Bulletin A340–32–4204, dated June 27, 2003, or Revi01, dated March 21, 2006.
does not require a report, unless the grease
analysis required by paragraph (a)(1) of this
AD is done at a lab chosen by the operator,
which requires the results to be evaluated by
Messier-Dowty.
Alternative Methods of Compliance
(j)(1) In accordance with 14 CFR 39.19, the
Manager, International Branch, ANM–116, is
authorized to approve alternative methods of
compliance for this AD.
(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.
Note 5: The subject of this AD is addressed
in French airworthiness directives F–2005–
209 and F–2005–210, both dated December
21, 2005.
Incorporation by Reference
(k) Unless otherwise specified in this AD,
the actions must be done in accordance with
the applicable service bulletins identified in
Table 3 of this AD. This incorporation by
reference was approved by the Director of the
Federal Register in accordance with 5 U.S.C.
552(a) and 1 CFR part 51. To get copies of
this service information, contact Airbus, 1
Rond Point Maurice Bellonte, 31707 Blagnac
Cedex, France. To inspect copies of this
service information, go to the FAA, Transport
Airplane Directorate, 1601 Lind Avenue,
SW., Renton, Washington; or to 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.
TABLE 3.—MATERIAL INCORPORATED BY REFERENCE
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Airbus Service Bulletin
Revision level
A330–32–3134, including Appendix 01 ...........................................................................................
A330–32–3164 .................................................................................................................................
A330–32–3164 .................................................................................................................................
A330–32–3192 .................................................................................................................................
A340–32–4172, including Appendix 01 ...........................................................................................
A340–32–4204 .................................................................................................................................
A340–32–4204 .................................................................................................................................
A340–32–4227 .................................................................................................................................
Revision 04 ...............
Original ......................
Revision 01 ................
Original ......................
Revision 04 ...............
Original ......................
Revision 01 ................
Original ......................
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Date
April 3, 2006.
June 27, 2003.
March 21, 2006.
December 8, 2005.
April 3, 2006.
June 27, 2003.
March 21, 2006.
December 8, 2005.
Federal Register / Vol. 71, No. 225 / Wednesday, November 22, 2006 / Rules and Regulations
Effective Date
(l) This amendment becomes effective on
December 27, 2006.
Issued in Renton, Washington, on
November 8, 2006.
Kalene C. Yanamura,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. E6–19535 Filed 11–21–06; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2006–24877; Directorate
Identifier 2005–NM–253–AD; Amendment
39–14831; AD 2006–24–02]
RIN 2120–AA64
Airworthiness Directives; Boeing
Model 747–100, 747–100B, 747–200B,
747–200C, 747–200F, 747SR, and
747SP Series Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
mstockstill on PROD1PC61 with RULES
AGENCY:
SUMMARY: The FAA is superseding an
existing airworthiness directive (AD),
which applies to certain Boeing Model
747 series airplanes. That AD currently
requires repetitive inspections to detect
cracks at certain stringer fastener
locations; and repair, if necessary. For
certain airplanes, that AD requires a
modification in certain areas where
reports indicate that cracking was
prevalent. This modification terminates
the repetitive inspections only for those
areas, and is also an option for other
airplanes affected by the existing AD.
This new AD requires an additional
inspection of areas that may have
Alodine-coated rivets installed, and
repair if necessary. This AD results from
a report of cracking discovered in a skin
lap joint that was previously inspected
using the eddy current method. We are
issuing this AD to prevent rapid
decompression of the airplane due to
disbonding and subsequent cracking of
the skin panels.
DATES: This AD becomes effective
December 27, 2006.
The Director of the Federal Register
approved the incorporation by reference
of certain publications listed in the AD
as of December 27, 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,
VerDate Aug<31>2005
15:05 Nov 21, 2006
Jkt 211001
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: Ivan
Li, Aerospace Engineer, Airframe
Branch, ANM–120S, FAA, Seattle
Aircraft Certification Office, 1601 Lind
Avenue, SW., Renton, Washington
98057–3356; telephone (425) 917–6437;
fax (425) 917–6590.
SUPPLEMENTARY INFORMATION:
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
supersedes AD 90–26–10, amendment
39–6836 (55 FR 51401, December 14,
1990). The existing AD applies to
certain Boeing Model 747 series
airplanes. That NPRM was published in
the Federal Register on May 25, 2006
(71 FR 30074). That NPRM proposed to
continue to require repetitive
inspections to detect cracks at certain
stringer fastener locations, and repair if
necessary. For certain airplanes, that
NPRM proposed to continue to require
modification in certain areas where
reports indicate that cracking was
prevalent. This modification terminates
the repetitive inspections only for those
areas, and is also an option for other
airplanes affected by the existing AD.
That NPRM also proposed to require an
additional inspection of areas that may
have Alodine-coated rivets installed,
and repair if necessary.
Comments
We provided the public the
opportunity to participate in the
development of this AD. We have
considered the comments that have
been received on the NPRM.
Support for the NPRM
Boeing supports the NPRM.
Request To Recognize Overlapping
Inspections
The Air Transport Association, on
behalf of one of its members, Northwest
PO 00000
Frm 00015
Fmt 4700
Sfmt 4700
67445
Airlines, requests that we recognize that
a service bulletin currently in
development could result in
overlapping inspections and cause
duplication of efforts. Northwest
Airlines states that it has been advised
by Boeing that the service bulletin in
development will recommend external
detailed inspections and/or external
surface high frequency eddy current
inspections in a good portion of the
region affected by the NPRM. This new
service bulletin resulted from a recent
report of skin cracking in section 41.
We partially agree with the
commenters. We agree that it is
important to avoid duplication of effort.
However, because the service bulletin
that the commenters mention has not
been issued, we have not issued an
NPRM for the subject of that service
bulletin. When the service bulletin is
issued, we will review it and any
forthcoming proposed rule in an effort
to prevent duplication of tasks. We
consider that to delay this AD action
would be inappropriate, since we have
determined that an unsafe condition
exists and that replacement of certain
parts must be accomplished to ensure
continued safety. We have not changed
the AD in this regard.
Explanation of Editorial Changes
We have clarified the Summary
section of this AD to state that this new
AD requires ‘‘an additional inspection’’
rather than a one-time inspection at a
reduced threshold. The new inspection
required by this AD is ‘‘additional’’ and,
therefore, we are not reducing a
threshold in the previous AD.
We have also removed the words, ‘‘at
intervals not to exceed 150 flight
cycles’’ from paragraph (k)(1)(i) of this
AD because it duplicates information
already in paragraph (k)(1) of this AD,
and may cause confusion.
Conclusion
We have carefully reviewed the
available data, including the comments
received, and determined that air safety
and the public interest require adopting
the AD with the changes described
previously. We have determined that
these changes will neither increase the
economic burden on any operator nor
increase the scope of the AD.
Costs of Compliance
The following table provides the
estimated costs for U.S. operators to
comply with this AD. There are about
132 airplanes of the affected design in
the worldwide fleet. This AD affects
about 59 airplanes of U.S. registry. The
average labor rate is $80 per work hour.
E:\FR\FM\22NOR1.SGM
22NOR1
]]>Agencies
[Federal Register Volume 71, Number 225 (Wednesday, November 22, 2006)]
[Rules and Regulations]
[Pages 67441-67445]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E6-19535]
=======================================================================
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 2001-NM-381-AD; Amendment 39-14832; AD 2006-24-03]
RIN 2120-AA64
Airworthiness Directives; Airbus Model A330-200, A330-300, A340-
200, and A340-300 Series Airplanes
AGENCY: Federal Aviation Administration, DOT.
ACTION: Final rule.
-----------------------------------------------------------------------
SUMMARY: This amendment adopts a new airworthiness directive (AD),
applicable to certain Airbus Model A330-200, A330-300, A340-200, and
A340-300 series airplanes. This AD requires repetitive inspections for
discrepancies of the grease and gear teeth of the radial variable
differential transducer of the nose wheel steering gearbox; or
repetitive inspections for damage of the chrome on the bearing surface
of the nose landing gear (NLG) main fitting barrel; as applicable. And,
for airplanes with any discrepancy or damage, this AD requires an
additional inspection or corrective actions. This AD also adds a
terminating action. The actions specified by this AD are intended to
prevent incorrect operation or jamming of the nose wheel steering,
which could cause reduced controllability of the airplane on the
ground. This action is intended to address the identified unsafe
condition.
DATES: Effective December 27, 2006.
The incorporation by reference of certain publications listed in
the regulations is approved by the Director of the Federal Register as
of December 27, 2006.
ADDRESSES: The service information referenced in this AD may be
obtained from Airbus, 1 Rond Point Maurice Bellonte, 31707 Blagnac
Cedex, France. This information may be examined at the Federal Aviation
Administration (FAA), Transport Airplane Directorate, Rules Docket,
1601 Lind Avenue, SW., Renton, Washington.
FOR FURTHER INFORMATION CONTACT: Tim Backman, Aerospace Engineer,
International Branch, ANM-116, FAA, Transport Airplane Directorate,
1601 Lind Avenue, SW., Renton, Washington 98057-3356; telephone (425)
227-2797; fax (425) 227-1149.
SUPPLEMENTARY INFORMATION: A proposal to amend part 39 of the Federal
Aviation Regulations (14 CFR part 39) to include an airworthiness
directive (AD) that is applicable to certain Airbus Model A330-200,
A330-300, A340-200, and A340-300 series airplanes was published as a
supplemental notice of proposed rulemaking (NPRM) in the Federal
Register on August 8, 2006 (71 FR 44937). That action proposed to
require repetitive inspections for discrepancies of the grease and gear
teeth of the radial variable differential transducer of the nose wheel
steering gearbox; or repetitive inspections for damage of the chrome on
the bearing surface of the nose landing gear (NLG) main fitting barrel;
as applicable. And, for airplanes with any discrepancy or damage, that
action proposed to require an additional inspection or corrective
actions. That action also proposed to add a terminating action and
remove certain airplanes from the applicability.
Comments
Interested persons have been afforded an opportunity to participate
in the making of this amendment. Due consideration has been given to
the comment received.
Request To Change Incorporation of Certain Information
The Modification and Replacement Parts Association (MARPA) states
that, typically, airworthiness directives are based on service
information originating with the type certificate holder or its
suppliers. MARPA adds that manufacturer service documents are privately
authored instruments generally having copyright protection against
duplication and distribution. MARPA notes that when a service document
is incorporated by reference into a public document, such as an
airworthiness directive, it loses its private, protected status and
becomes a public document. MARPA adds that if a service document is
used as a mandatory element of compliance, it should not simply be
referenced, but should be incorporated into the regulatory document; by
definition, public laws must be public, which means they cannot rely
upon private writings. MARPA adds that incorporated-by-reference
service documents should be made available to the public by publication
in the Docket Management System (DMS), keyed to the action that
incorporates them. MARPA notes that the stated purpose of the
incorporation-by-reference method is brevity, to keep from expanding
the Federal Register needlessly by publishing documents already in the
hands of the affected individuals; traditionally, ``affected
individuals'' means aircraft owners and operators, who are generally
provided service information by the manufacturer.
[[Page 67442]]
MARPA adds that a new class of affected individuals has emerged, since
the majority of aircraft maintenance is now performed by specialty
shops instead of aircraft owners and operators. MARPA notes that this
new class includes maintenance and repair organizations, component
servicing and repair shops, parts purveyors and distributors, and
organizations manufacturing or servicing alternatively certified parts
[under part 21 of the Federal Aviation Regulations (14 CFR part 21),
Sec. 21.303 (parts manufacturer approval)]. MARPA adds that the
concept of brevity is now nearly archaic as documents exist more
frequently in electronic format than on paper. Therefore, MARPA asks
that the service documents deemed essential to the accomplishment of
the supplemental NPRM be incorporated by reference into the regulatory
instrument, and published in the DMS.
We do not agree that documents should be incorporated by reference
during the NPRM phase of rulemaking. The Office of the Federal Register
(OFR) requires that documents that are necessary to accomplish the
requirements of the AD be incorporated by reference during the final
rule phase of rulemaking. This final rule incorporates by reference the
documents necessary for the accomplishment of the requirements mandated
by this AD. Further, we point out that while documents that are
incorporated by reference do become public information, they do not
lose their copyright protection. For that reason, we advise the public
to contact the manufacturer to obtain copies of the referenced service
information.
Additionally, we do not publish service documents in DMS. We are
currently reviewing our practice of publishing proprietary service
information. Once we have thoroughly examined all aspects of this
issue, and have made a final determination, we will consider whether
our current practice needs to be revised. However, we consider that to
delay this AD action for that reason would be inappropriate, since we
have determined that an unsafe condition exists and that the
requirements in this AD must be accomplished to ensure continued
safety. Therefore, we have not changed the AD in this regard.
Explanation of Changes to the Supplemental NPRM
Paragraph (e)(2) of the supplemental NPRM specifies making repairs
using a method approved by either the FAA or the Direction
G[eacute]n[eacute]rale de l'Aviation Civile (DGAC) (or its delegated
agent). The European Aviation Safety Agency (EASA), which is the
airworthiness authority for the European Union, has assumed
responsibility for the airplane models subject to this AD. Therefore,
we have revised paragraph (e)(2) of this AD to specify making repairs
using a method approved by the FAA, the DGAC (or its delegated agent),
or the EASA (or its delegated agent).
Model designations have been added to Table 2 of paragraph (g)(2)
of the supplemental NPRM for clarification.
Conclusion
We have carefully reviewed the available data, including the
comment received, and we have determined that air safety and the public
interest require the adoption of the rule with the change previously
described. This change will neither increase the economic burden on any
operator nor increase the scope of the AD.
Cost Impact
The following table provides the estimated costs for U.S. operators
to comply with this AD.
Estimated Costs
--------------------------------------------------------------------------------------------------------------------------------------------------------
Number of U.S.-
Action Work hours Average labor Parts Cost per airplane registered Fleet cost
rate per hour airplanes
--------------------------------------------------------------------------------------------------------------------------------------------------------
Radial variable differential 6 $80 None.............. $480............. 11 $5,280.
transducer inspection, per
inspection cycle.
Chrome inspection, per 13 80 None.............. $1,040........... 15 $15,600.
inspection cycle.
Modification (Service Bulletin 15 80 $10,244 to $11,337 $11,444 to 12 $137,328 to $150,444.
A330-32-3164 or A340-32-4204). $12,537.
Rotating sleeve grease system 15 80 Unknown........... From $1,200...... 23 From $27,600.
modification (Service Bulletin
A330-32-3192 or A340-32-4227).
--------------------------------------------------------------------------------------------------------------------------------------------------------
The cost impact figures discussed above are based on assumptions
that no operator has yet accomplished any of the requirements of this
AD action, and that no operator would accomplish those actions in the
future if this AD were not adopted. The cost impact figures discussed
in AD rulemaking actions represent only the time necessary to perform
the specific actions actually required by the AD. These figures
typically do not include incidental costs, such as the time required to
gain access and close up, planning time, or time necessitated by other
administrative actions.
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 Impact
The regulations adopted herein 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
[[Page 67443]]
levels of government. Therefore, it is determined that this final rule
does not have federalism implications under Executive Order 13132.
For the reasons discussed above, I certify that this action (1) is
not a ``significant regulatory action'' under Executive Order 12866;
(2) is not a ``significant rule'' under DOT Regulatory Policies and
Procedures (44 FR 11034, February 26, 1979); and (3) will not have a
significant economic impact, positive or negative, on a substantial
number of small entities under the criteria of the Regulatory
Flexibility Act. A final evaluation has been prepared for this action
and it is contained in the Rules Docket. A copy of it may be obtained
from the Rules Docket at the location provided under the caption
ADDRESSES.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.
Adoption of the Amendment
0
Accordingly, pursuant to the authority delegated to me by the
Administrator, the Federal Aviation Administration amends part 39 of
the Federal Aviation Regulations (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. Section 39.13 is amended by adding the following new airworthiness
directive:
2006-24-03 Airbus: Amendment 39-14832. Docket 2001-NM-381-AD.
Applicability: The following airplanes, certificated in any
category, except those modified in production by both Airbus
Modifications 51381 and 53073:
Model A330-201, -202, -203, -223, and -243 airplanes
Model A330-301, -302, -303, -321, -322, -323, -341, -342, and -343
airplanes
Model A340-211, -212, and -213 airplanes
Model A340-311, -312, and -313 airplanes
Compliance: Required as indicated, unless accomplished
previously.
To prevent incorrect operation or jamming of the nose wheel
steering (NWS), which could cause reduced controllability of the
airplane on the ground, accomplish the following:
Inspections: Airplanes Without Modification 51381
(a) For airplanes that were not modified in production by Airbus
Modification 51381: Do the inspection specified in either paragraph
(a)(1) or (a)(2) of this AD, in accordance with the required service
bulletin identified in Table 1 of this AD, as applicable. The
required compliance time is specified in paragraph (b) of this AD.
(1) Inspect for discrepancies of the grease by sending it to a
laboratory for analysis, and do a detailed inspection for
discrepancies of the gear teeth of the radial variable differential
transducer (RVDT) driving ring and the gears in the RVDT gearboxes.
If there are no discrepancies (such as metallic particles in the
grease, abnormal wear of the gear teeth, or missing rubber sealant
at the mating face between the main fitting and the RVDT gearbox),
repeat the inspection as specified in paragraph (c) of this AD. If
there is any discrepancy, do the inspection in paragraph (a)(2) of
this AD within 3 months after the inspection specified in paragraph
(a)(1) of this AD.
(2) Do a detailed inspection for damage of the chrome on the
bearing surface of the nose landing gear (NLG) main fitting barrel
under the NWS rotating sleeve. If there is no damage (such as
flaking, corrosion, or blistering), repeat the inspection as
specified in paragraph (c) of this AD. If there is any damage,
before further flight, do the corrective action in paragraph (e) of
this AD.
Note 1: For the purposes of this AD, a detailed inspection is
defined as: ``An intensive visual examination of a specific
structural area, system, installation, or assembly to detect damage,
failure, or irregularity. Available lighting is normally
supplemented with a direct source of good lighting at intensity
deemed appropriate by the inspector. Inspection aids such as mirror,
magnifying lenses, etc., may be used. Surface cleaning and elaborate
access procedures may be required.''
Table 1.--Inspection Service Bulletins
----------------------------------------------------------------------------------------------------------------
Approved revision level
Airbus Service (for actions done
Airplane models Bulletin Required revision level before the effective
date of the AD)
----------------------------------------------------------------------------------------------------------------
A330-200 and -300 series airplanes... A330-32-3134........... Revision 04, including Original, dated
Appendix 01, dated September 11, 2001.
April 3, 2006. Revision 01, dated
November 29, 2001.
Revision 02, dated
August 8, 2003.
Revision 03, dated May
11, 2005.
A340-200 and -300 series airplanes... A340-32-4172........... Revision 04, including Original, dated
Appendix 01, dated September 11, 2001.
April 3, 2006. Revision 01, dated
November 29, 2001.
Revision 02, dated
August 8, 2003.
Revision 03, dated May
11, 2005.
----------------------------------------------------------------------------------------------------------------
(b) For airplanes identified in paragraph (a) of this AD: Do the
initial inspection specified in paragraph (a) of this AD at the
latest of the following times:
(1) Within 60 months after the date that the new NLG was
installed on the airplane.
(2) Within 60 months after the last major NLG overhaul
accomplished before the effective date of this AD.
(3) Within 700 flight hours after the effective date of this AD.
(c) For airplanes identified in paragraph (a) of this AD: Repeat
either inspection specified in paragraph (a)(1) or (a)(2) of this AD
at intervals not to exceed the applicable interval specified in
paragraph (c)(1) or (c)(2) of this AD, until the requirements of
paragraph (g) of this AD are done.
(1) If the most recent inspection was the inspection specified
in paragraph (a)(1) of this AD, then the next inspection must be
done within 8 months.
(2) If the most recent inspection was the inspection specified
in paragraph (a)(2) of this AD, then the next inspection must be
done within 18 months.
Repetitive Inspections: Airplanes With Modification 51381
(d) For airplanes modified in production by Airbus Modification
51381: Perform a detailed inspection for damage of the chrome on the
bearing surface of the NLG main fitting barrel under the NWS
rotating sleeve. Do the inspection at the later of the times
specified in paragraphs (d)(1) and (d)(2) of this AD in accordance
with the applicable required Airbus service bulletin identified in
Table 1 of this AD. Repeat the inspection thereafter at intervals
not to exceed 18 months, until the requirements of paragraph (g) of
this AD have been done.
(1) Within 60 months after the date that the new NLG was
installed on the airplane.
(2) Within 60 months after the last major NLG overhaul
accomplished before the effective date of this AD.
Follow-on Investigative and Corrective Actions
(e) For all airplanes: If any damage or discrepancy is found
during any inspection required by this AD, do the corrective action
before further flight in accordance with the
[[Page 67444]]
applicable required Airbus service bulletin identified in Table 1 of
this AD, with the following exceptions:
(1) If discrepancies are found during any inspection specified
in paragraph (a)(1) of this AD, the inspection in paragraph (a)(2)
of this AD is required within 3 months.
(2) Where the service bulletin recommends contacting Messier-
Dowty for appropriate action. Repair before further flight in
accordance with a method approved by the Manager, International
Branch, ANM-116, FAA, Transport Airplane Directorate; the Direction
Gonorale de l'Aviation Civile (or its delegated agent); or the
European Aviation Safety Agency (or its delegated agent).
Note 2: Airbus Service Bulletins A330-32-3134 and A340-32-4172,
both Revision 04, both dated April 3, 2006, refer to Messier-Dowty
Special Inspection Service Bulletins D23285-32-037, Revision 2,
dated May 23, 2002; and D23285-32-044, dated January 12, 2004; as
additional sources of service information for the inspections.
Credit for Prior Accomplishment
(f) Actions done before the effective date of this AD in
accordance with an applicable Approved Revision Level of the service
bulletin identified in Table 1 of this AD are acceptable for
compliance with the corresponding requirements of paragraphs (a),
(d), and (e) of this AD.
Modification
(g) For all airplanes: At the applicable time specified in
paragraph (g)(1) or (g)(2) of this AD, modify the NLG as specified
in Table 2 of this AD, as applicable.
(1) For NLGs overhauled before the effective date of this AD: At
the later of the times specified in paragraphs (g)(1)(i) and
(g)(1)(ii) of this AD:
(i) Within 60 months since the NLG was overhauled or 180 months
since the NLG was new, whichever occurs first.
(ii) Within 6 months after the effective date of this AD.
(2) For NLGs not overhauled before the effective date of this
AD: Within 120 months since the NLG was new, or within 6 months
after the effective date of this AD, whichever occurs later.
Table 2.--Modification
------------------------------------------------------------------------
Modify the NLG in accordance
For airplanes-- with--
------------------------------------------------------------------------
For Model A330 airplanes without Airbus Airbus Service Bulletin A330-32-
Modifications 51381 and 53073 done in 3164, dated June 27, 2003, or
production. Revision 01, dated March 21,
2006; and A330-32-3192, dated
December 8, 2005.
For Model A340 airplanes without Airbus Airbus Service Bulletins A340-
Modifications 51381 and 53073 done in 32-4204, dated June 27, 2003,
production. or Revision 01, dated March
21, 2006; and A340-32-4227,
dated December 8, 2005.
For Model A330 airplanes with Airbus Airbus Service Bulletin A330-32-
Modification 51381 but not Airbus 3192, dated December 8, 2005.
Modification 53073 done in production.
For Model A340 airplanes with Airbus Airbus Service Bulletin A340-32-
Modification 51381 but not Airbus 4227, dated December 8, 2005.
Modification 53073 done in production.
For Model A330 airplanes with Airbus Airbus Service Bulletin A330-32-
Modification 53073 but not Airbus 3164, dated June 27, 2003, or
Modification 51381 done in production. Revision 01, dated March 21,
2006.
For Model A340 airplanes with Airbus Airbus Service Bulletin A340-32-
Modification 53073 but not Airbus 4204, dated June 27, 2003, or
Modification 51381 done in production. Revision 01, dated March 21,
2006.
------------------------------------------------------------------------
Terminating Action
(h) Accomplishment of both NLG modifications specified in
paragraph (g) of this AD terminates the repetitive inspection
requirements of this AD.
Note 3: Airbus Service Bulletins A330-32-3164 and A340-32-4204
refer to Messier-Dowty Service Bulletin D23285-32-042, dated June
19, 2003, as an additional source of service information for the
modification.
Note 4: Airbus Service Bulletins A330-32-3192 and A340-32-4227
refer to Messier-Dowty Service Bulletin D23581-32-047, dated
December 1, 2005, as an additional source of service information for
the modification.
Reporting
(i) Certain service bulletins specify to submit a report to the
manufacturer. This AD does not require a report, unless the grease
analysis required by paragraph (a)(1) of this AD is done at a lab
chosen by the operator, which requires the results to be evaluated
by Messier-Dowty.
Alternative Methods of Compliance
(j)(1) In accordance with 14 CFR 39.19, the Manager,
International Branch, ANM-116, is authorized to approve alternative
methods of compliance for this AD.
(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.
Note 5: The subject of this AD is addressed in French
airworthiness directives F-2005-209 and F-2005-210, both dated
December 21, 2005.
Incorporation by Reference
(k) Unless otherwise specified in this AD, the actions must be
done in accordance with the applicable service bulletins identified
in Table 3 of this AD. This incorporation by reference was approved
by the Director of the Federal Register in accordance with 5 U.S.C.
552(a) and 1 CFR part 51. To get copies of this service information,
contact Airbus, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex,
France. To inspect copies of this service information, go to the
FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton,
Washington; or to 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.
Table 3.--Material Incorporated by Reference
----------------------------------------------------------------------------------------------------------------
Airbus Service Bulletin Revision level Date
----------------------------------------------------------------------------------------------------------------
A330-32-3134, including Appendix 01... Revision 04........................ April 3, 2006.
A330-32-3164.......................... Original........................... June 27, 2003.
A330-32-3164.......................... Revision 01........................ March 21, 2006.
A330-32-3192.......................... Original........................... December 8, 2005.
A340-32-4172, including Appendix 01... Revision 04........................ April 3, 2006.
A340-32-4204.......................... Original........................... June 27, 2003.
A340-32-4204.......................... Revision 01........................ March 21, 2006.
A340-32-4227.......................... Original........................... December 8, 2005.
----------------------------------------------------------------------------------------------------------------
[[Page 67445]]
Effective Date
(l) This amendment becomes effective on December 27, 2006.
Issued in Renton, Washington, on November 8, 2006.
Kalene C. Yanamura,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. E6-19535 Filed 11-21-06; 8:45 am]
BILLING CODE 4910-13-P
