Airworthiness Directives; Airbus Model A330-200 and A330-300 Series Airplanes, and Airbus Model A340-200 and A340-300 Series Airplanes, 38062-38064 [06-5943]
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38062
Federal Register / Vol. 71, No. 128 / Wednesday, July 5, 2006 / Rules and Regulations
The Director of the Federal Register
approved the incorporation by reference of
these documents in accordance with 5 U.S.C.
552(a) and 1 CFR part 51. 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 June 23,
2006.
Kalene C. Yanamura,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. 06–5944 Filed 7–3–06; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 2002–NM–247–AD; Amendment
39–14673; AD 2006–14–02]
RIN 2120–AA64
Airworthiness Directives; Airbus Model
A330–200 and A330–300 Series
Airplanes, and Airbus Model A340–200
and A340–300 Series Airplanes
Federal Aviation
Administration, DOT.
ACTION: Final rule.
jlentini on PROD1PC65 with RULES
AGENCY:
SUMMARY: This amendment adopts a
new airworthiness directive (AD),
applicable to certain Airbus Model
A330–200 and A330–300 series
airplanes; and Airbus Model A340–200
and A340–300 series airplanes. This AD
requires lubrication of the upper and
lower shortening mechanism (SM) link
of the main landing gear, and
consequent detection of resistance or
blockage of the greaseway. Depending
upon the resistance finding and upon
whether or not the airplane has a certain
modification, this AD also requires
various other actions including
unblocking the greaseway;
accomplishing all necessary repairs;
performing various inspections; and
accomplishing the eventual replacement
of the SM8 pin, if necessary. This action
is necessary to prevent failure of the
landing gear lengthening system, which
could result in reduced controllability
of the airplane on the ground during
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19:23 Jul 03, 2006
Jkt 208001
landing. This action is intended to
address the identified unsafe condition.
DATES: Effective August 9, 2006.
The incorporation by reference of
certain publications listed in the
regulations is approved by the Director
of the Federal Register as of August 9,
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: Dan
Rodina, Aerospace Engineer,
International Branch, ANM–116, FAA,
Transport Airplane Directorate, 1601
Lind Avenue, SW., Renton, Washington
98055–4056; telephone (425) 227–2125;
fax (425) 227–1149.
SUPPLEMENTARY INFORMATION: 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 series airplanes; Airbus
Model A340–300 series airplanes; and
Airbus Model A340–541 airplanes was
published in the Federal Register on
April 1, 2004 (69 FR 17088). That action
proposed to require lubrication of the
upper and lower shortening mechanism
(SM) link of the main landing gear, and
consequent detection of resistance or
blockage of the greaseway. Depending
upon the resistance finding and upon
whether or not the airplane has a certain
modification, that action also proposed
to require various other actions
including unblocking the greaseway;
accomplishing all necessary repairs;
performing various inspections; and
accomplishing the eventual replacement
of the SM8 pin, if necessary.
Comments
Interested persons have been afforded
an opportunity to participate in the
making of this amendment. Due
consideration has been given to the
comments received.
Support for the Proposed AD
US Airways expresses support for the
proposed AD. Northwest Airlines notes
that it does not operate any airplanes
affected by the proposed AD.
Request To Remove Certain Airplanes
From Applicability
Airbus notes that the applicability of
the proposed AD should not include
Airbus Model A340–541 airplanes.
Airbus states that Model A340–541
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airplanes do not have SM8 pins that are
affected by the actions in this proposed
AD.
We agree. Airbus Model A340–541
airplanes are not included in either the
French airworthiness directives or the
all-operators telexes (AOTs) that are
referenced in the proposed AD. We
included the Airbus Model A340–541
inadvertently in our proposed AD. We
have revised the final rule to exclude
this airplane model.
Request To Revise Compliance Time in
Paragraph (e)(1) of the Proposed AD
Airbus also observes that the
proposed AD includes in paragraph
(e)(1) the requirement to make all
necessary repairs and unblock any
blocked greaseway ‘‘before further
flight.’’ Airbus suggests that we may
have misunderstood the intent of the
French airworthiness directives and the
AOTs, and requests that we change this
compliance time to agree with the time
in those documents. Instead of ‘‘before
further flight,’’ Airbus states that the
compliance time should be ‘‘within 700
flight hours.’’
We agree. We have changed paragraph
(e)(1) of the final rule to state that
operators should comply with the
actions in that paragraph ‘‘within 700
flight hours after the general visual
inspection’’ rather than ‘‘before further
flight.’’ We have determined that
extending the compliance time will not
adversely affect safety.
Requests To Revise Compliance Time in
Paragraph (e)(2) of the Proposed AD
Air Transportation Association, on
behalf of U.S. Airways, expresses
concern over the facilities needed to
perform the ‘‘tall’’ airplane jacking that
must be done to accomplish the SM8
pin replacement. U.S. Airways notes
that this jacking procedure must be
accomplished indoors and requires
equipment and a facility capable of
handling the abnormal jacking height.
U.S. Airways recommends that we
revise paragraph (e)(2) of the proposed
AD to allow 180 flight cycles for
operators to plan for the pin
replacement after a finding in
accordance with paragraph (e) of the
proposed AD. ATA supports the
observation and recommends that we
adopt U.S. Airways’ recommendation.
We partially agree. We agree with the
commenters that a grace period should
be added. We disagree with the
proposed 180 flight cycles. Instead, we
have changed paragraph (e)(2) of the
final rule to require that the actions in
paragraph (e)(2) be performed ‘‘within
20 flight cycles after the general visual
inspection’’ to match the intent of the
E:\FR\FM\05JYR1.SGM
05JYR1
Federal Register / Vol. 71, No. 128 / Wednesday, July 5, 2006 / Rules and Regulations
French airworthiness directives and the
AOTs.
Explanation of Further Changes to
Applicability
We have revised the applicability of
the proposed AD to identify model
designations as published in the most
recent type certificate data sheet for the
affected models.
We also have made minor editorial
changes to clarify the applicability and
paragraph (b)(1) of this AD, as follows.
We changed the phrases ‘‘original
Airworthiness Certificate’’ to ‘‘original
French standard Airworthiness
Certificate,’’ and ‘‘Export Certificate of
Airworthiness’’ to ‘‘original Export
Certificate of Airworthiness. We also
removed an unnecessary phrase,
‘‘whichever occurs later,’’ from the
applicability. In addition, we revised
paragraph (b)(1) of this AD to remove an
unnecessary phrase—‘‘whichever occurs
first.’’
Furthermore, we inadvertently
excluded Airbus Model A340–200 series
airplanes from the applicability of the
NPRM. Both French airworthiness
directive 2002–265(B) R2, dated January
8, 2003, and Airbus AOT 323A4189,
dated March 26, 2002, are applicable to
both A340–200 and A340–300 series
airplanes. Since there are no affected
A340–200 series airplanes on the U.S.
register, we find that this correction
does not expand the scope of the NPRM.
We have revised the final rule to
include the Model A340–200 series
airplanes.
Clarification of Editorial Changes to AD
We have clarified paragraphs (b), (c),
(e), and (f) of the AD to reference
specific paragraphs of the AOT that are
necessary for accomplishing the
specified actions.
Clarification of Alternative Method of
Compliance (AMOC) Paragraph
We have revised this action to clarify
the appropriate procedure for notifying
the principal inspector before using any
approved AMOC on any airplane to
which the AMOC applies.
jlentini on PROD1PC65 with RULES
Conclusion
After careful review of the available
data, including the comments noted
above, we have determined that air
safety and the public interest require the
adoption of the rule with the changes
previously described. We have
determined that these changes will
neither increase the economic burden
on any operator nor increase the scope
of the AD.
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19:23 Jul 03, 2006
Jkt 208001
Cost Impact
We estimate that 9 Model A330 series
airplanes of U.S. registry will be affected
by this AD, that it will take
approximately 1 work hour per airplane
to accomplish the proposed lubrication,
and that the average labor rate is $65 per
work hour. Based on these figures, the
cost impact of the AD on U.S. operators
is estimated to be $585, or $65 per
airplane.
The cost impact figure discussed
above is 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.
Currently, there are no affected Model
A340 airplanes on the U.S. Register.
However, if an affected airplane is
imported and placed on the U.S.
Register in the future, it would take
approximately 1 work hour per airplane
to accomplish the proposed lubrication
at an average labor rate of $65 per work
hour. Based on these figures, we
estimate the cost of the lubrication
required by this AD for these airplanes
to be $65 per airplane.
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
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38063
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. 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
2006–14–02 Airbus: Amendment 39–14673.
Docket 2002–NM–247–AD.
Applicability: Model A330–201, –202,
–203, –223, –243, –301, –321, –322, –323,
–341, –342, and –343 airplanes; and Model
A340–211, –212, –213, –311, –312, and –313
airplanes, certificated in any category; having
a date of issuance of the original French
standard Airworthiness Certificate or the date
of issuance of the original Export Certificate
of Airworthiness of May 24, 2002, or earlier.
Compliance: Required as indicated, unless
accomplished previously.
To prevent failure of the landing gear
lengthening system, which could result in
reduced controllability of the airplane on the
ground during landing, accomplish the
following:
All Operators Telex Reference
(a) The term ‘‘all operators telex,’’ or
‘‘AOT,’’ as used in this AD, means the Short-
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05JYR1
38064
Federal Register / Vol. 71, No. 128 / Wednesday, July 5, 2006 / Rules and Regulations
Term Action section of the following AOTs,
as applicable:
(1) For Model A330–201, –202, –203, –223,
–243, –301, –321, –322, –323, –341, –342,
and –343 airplanes: Airbus A330 AOT
32A3151, dated March 26, 2002; and
(2) For Model A340–211, –212, –213, –311,
–312, and –313 airplanes: Airbus A340 AOT
32A4189, dated March 26, 2002.
jlentini on PROD1PC65 with RULES
Lubrication
(b) At the later of the compliance times in
paragraphs (b)(1) and (b)(2) of this AD:
Lubricate the upper and lower shortening
mechanism (SM) link of the main landing
gear in accordance with paragraph 4.2.1 of
the applicable AOT.
(1) Within 6 months after the date of
issuance of the original French standard
Airworthiness Certificate or the date of
issuance of the original Export Certificate of
Airworthiness.
(2) Within 700 flight hours or 60 days after
the effective date of this AD, whichever
occurs first.
(c) If, during the lubrication required by
paragraph (b) of this AD, any corrective
actions are required, do paragraph (c)(1) or
(c)(2) of this AD, as applicable.
(1) If Airbus Modification 46904 has been
accomplished, the corrective actions must be
performed in accordance with paragraphs
4.2.2 and 4.3 of the applicable AOT.
(2) If Airbus Modification 46904 has not
been accomplished, do the applicable
inspection and all necessary corrective
actions in accordance with paragraph 4.3 of
the applicable AOT.
(d) If, during the lubrication required by
paragraph (b) of this AD, there is noticeable
resistance or blockage of the greaseway:
Before further flight, do the applicable
inspection and all necessary corrective
actions in paragraphs (e) and (f) of this AD.
Inspections and Corrective Action
(e) For airplanes on which Airbus
Modification 46904 has been incorporated
that have a discrepant greaseway per
paragraph (d) of this AD; and for airplanes on
which Airbus Modification 46904 has not
been incorporated that do not have a
discrepant greaseway: Before further flight
following the lubrication required by
paragraph (b) of this AD, do a general visual
inspection for clearance of the end caps of
the SM8 pin, and the presence of the split
pin, the nut, the end caps, and the bolts; in
accordance with paragraph 4.2.2 of the
applicable AOT.
(1) If the combined gap of both end caps
to the outer flanges of the bushes in the lower
SM is less than 0.75 mm: Within 700 flight
hours after the general visual inspection,
make all necessary repairs and unblock any
blocked greaseway, in accordance with
paragraphs 4.2.2 and 4.3 of the applicable
AOT.
(2) If the inspection required by paragraph
(e) of this AD reveals a migration of the SM8
pin end caps to a gap of 0.75 mm to 3.0 mm:
Within 20 flight cycles after the general
visual inspection, unblock any blocked
greaseway in accordance with paragraph 4.3
of the applicable AOT, and repeat the
inspection required by paragraph (e) of this
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19:23 Jul 03, 2006
Jkt 208001
AD at intervals not to exceed 20 flight cycles
until the action in paragraph (e)(3) is
accomplished.
(3) If the inspection required by paragraph
(e) of this AD reveals a migration of the SM8
pin end caps to a gap of 3.0 mm or greater:
Before further flight, remove the SM8 pin,
and perform a general visual inspection of
the SM upper link, SM lower link, and SM8
pin for damage or blockage, and make all
necessary repairs before further flight in
accordance with paragraph 4.3 of the
applicable AOT.
Note 1: For the purposes of this AD, a
general visual inspection is defined as: ‘‘A
visual examination of an interior or exterior
area, installation, or assembly to detect
obvious damage, failure, or irregularity. This
level of inspection is made from within
touching distance unless otherwise specified.
A mirror may be necessary to enhance visual
access to all exposed surfaces in the
inspection area. This level of inspection is
made under normally available lighting
conditions such as daylight, hangar lighting,
flashlight, or drop light and may require
removal or opening of access panels or doors.
Stands, ladders, or platforms may be required
to gain proximity to the area being checked.’’
Detailed Inspections and Corrective Actions
(f) If no noticeable resistance or blockage
of the greaseway is noted during the
lubrication required by paragraph (b) of this
AD: Within 700 flight hours after the
effective date of this AD, do a detailed
inspection of the SM8 pin for damage or
corrosion; unblock any blocked greaseway;
and replace any damaged or corroded pin
with a new part; in accordance with
paragraph 4.2.2 of the applicable AOT.
Note 2: 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.’’
No Reporting Requirements
(g) Although the AOTs referenced in this
AD specify to report inspection results to the
manufacturer, this AD does not include such
a requirement.
Alternative Methods of Compliance
(h)(1) In accordance with 14 CFR 39.19, the
Manager, International Branch, ANM–116,
Transport Airplane Directorate, FAA, is
authorized to approve alternative methods of
compliance (AMOCs) for this AD.
(2) Before using any AMOC approved in
accordance with § 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 3: The subject of this AD is addressed
in French airworthiness directives 2002–
262(B) R1, and 2002–265(B) R2, both dated
January 8, 2003.
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Incorporation by Reference
(i) Unless otherwise specified in this AD,
the actions must be done in accordance with
Airbus A330 All Operators Telex 32A3151,
dated March 26, 2002; and Airbus A340 All
Operators Telex 32A4189, dated March 26,
2002; as applicable. 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.
Effective Date
(j) This amendment becomes effective on
August 9, 2006.
Issued in Renton, Washington, on June 22,
2006.
Kalene C. Yanamura,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. 06–5943 Filed 7–3–06; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 97
[Docket No. 30501; Amdt. No. 3173]
Standard Instrument Approach
Procedures; Miscellaneous
Amendments
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule.
AGENCY:
SUMMARY: This amendment amends
Standard Instrument Approach
Procedures (SIAPs) for operations at
certain airports. These regulatory
actions are needed because of changes
occurring in the National Airspace
System, such as the commissioning of
new navigational facilities, addition of
new obstacles, or changes in air traffic
requirements. These changes are
designed to provide safe and efficient
use of the navigable airspace and to
promote safe flight operations under
instrument flight rules at the affected
airports.
DATES: This rule is effective July 5,
2006. The compliance date for each
SIAP is specified in the amendatory
provisions.
The incorporation by reference of
certain publications listed in the
E:\FR\FM\05JYR1.SGM
05JYR1
Agencies
[Federal Register Volume 71, Number 128 (Wednesday, July 5, 2006)]
[Rules and Regulations]
[Pages 38062-38064]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 06-5943]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 2002-NM-247-AD; Amendment 39-14673; AD 2006-14-02]
RIN 2120-AA64
Airworthiness Directives; Airbus Model A330-200 and A330-300
Series Airplanes, and Airbus Model 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 and A330-300 series
airplanes; and Airbus Model A340-200 and A340-300 series airplanes.
This AD requires lubrication of the upper and lower shortening
mechanism (SM) link of the main landing gear, and consequent detection
of resistance or blockage of the greaseway. Depending upon the
resistance finding and upon whether or not the airplane has a certain
modification, this AD also requires various other actions including
unblocking the greaseway; accomplishing all necessary repairs;
performing various inspections; and accomplishing the eventual
replacement of the SM8 pin, if necessary. This action is necessary to
prevent failure of the landing gear lengthening system, which could
result in reduced controllability of the airplane on the ground during
landing. This action is intended to address the identified unsafe
condition.
DATES: Effective August 9, 2006.
The incorporation by reference of certain publications listed in
the regulations is approved by the Director of the Federal Register as
of August 9, 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: Dan Rodina, Aerospace Engineer,
International Branch, ANM-116, FAA, Transport Airplane Directorate,
1601 Lind Avenue, SW., Renton, Washington 98055-4056; telephone (425)
227-2125; fax (425) 227-1149.
SUPPLEMENTARY INFORMATION: 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 series
airplanes; Airbus Model A340-300 series airplanes; and Airbus Model
A340-541 airplanes was published in the Federal Register on April 1,
2004 (69 FR 17088). That action proposed to require lubrication of the
upper and lower shortening mechanism (SM) link of the main landing
gear, and consequent detection of resistance or blockage of the
greaseway. Depending upon the resistance finding and upon whether or
not the airplane has a certain modification, that action also proposed
to require various other actions including unblocking the greaseway;
accomplishing all necessary repairs; performing various inspections;
and accomplishing the eventual replacement of the SM8 pin, if
necessary.
Comments
Interested persons have been afforded an opportunity to participate
in the making of this amendment. Due consideration has been given to
the comments received.
Support for the Proposed AD
US Airways expresses support for the proposed AD. Northwest
Airlines notes that it does not operate any airplanes affected by the
proposed AD.
Request To Remove Certain Airplanes From Applicability
Airbus notes that the applicability of the proposed AD should not
include Airbus Model A340-541 airplanes. Airbus states that Model A340-
541 airplanes do not have SM8 pins that are affected by the actions in
this proposed AD.
We agree. Airbus Model A340-541 airplanes are not included in
either the French airworthiness directives or the all-operators telexes
(AOTs) that are referenced in the proposed AD. We included the Airbus
Model A340-541 inadvertently in our proposed AD. We have revised the
final rule to exclude this airplane model.
Request To Revise Compliance Time in Paragraph (e)(1) of the Proposed
AD
Airbus also observes that the proposed AD includes in paragraph
(e)(1) the requirement to make all necessary repairs and unblock any
blocked greaseway ``before further flight.'' Airbus suggests that we
may have misunderstood the intent of the French airworthiness
directives and the AOTs, and requests that we change this compliance
time to agree with the time in those documents. Instead of ``before
further flight,'' Airbus states that the compliance time should be
``within 700 flight hours.''
We agree. We have changed paragraph (e)(1) of the final rule to
state that operators should comply with the actions in that paragraph
``within 700 flight hours after the general visual inspection'' rather
than ``before further flight.'' We have determined that extending the
compliance time will not adversely affect safety.
Requests To Revise Compliance Time in Paragraph (e)(2) of the Proposed
AD
Air Transportation Association, on behalf of U.S. Airways,
expresses concern over the facilities needed to perform the ``tall''
airplane jacking that must be done to accomplish the SM8 pin
replacement. U.S. Airways notes that this jacking procedure must be
accomplished indoors and requires equipment and a facility capable of
handling the abnormal jacking height. U.S. Airways recommends that we
revise paragraph (e)(2) of the proposed AD to allow 180 flight cycles
for operators to plan for the pin replacement after a finding in
accordance with paragraph (e) of the proposed AD. ATA supports the
observation and recommends that we adopt U.S. Airways' recommendation.
We partially agree. We agree with the commenters that a grace
period should be added. We disagree with the proposed 180 flight
cycles. Instead, we have changed paragraph (e)(2) of the final rule to
require that the actions in paragraph (e)(2) be performed ``within 20
flight cycles after the general visual inspection'' to match the intent
of the
[[Page 38063]]
French airworthiness directives and the AOTs.
Explanation of Further Changes to Applicability
We have revised the applicability of the proposed AD to identify
model designations as published in the most recent type certificate
data sheet for the affected models.
We also have made minor editorial changes to clarify the
applicability and paragraph (b)(1) of this AD, as follows. We changed
the phrases ``original Airworthiness Certificate'' to ``original French
standard Airworthiness Certificate,'' and ``Export Certificate of
Airworthiness'' to ``original Export Certificate of Airworthiness. We
also removed an unnecessary phrase, ``whichever occurs later,'' from
the applicability. In addition, we revised paragraph (b)(1) of this AD
to remove an unnecessary phrase--``whichever occurs first.''
Furthermore, we inadvertently excluded Airbus Model A340-200 series
airplanes from the applicability of the NPRM. Both French airworthiness
directive 2002-265(B) R2, dated January 8, 2003, and Airbus AOT
323A4189, dated March 26, 2002, are applicable to both A340-200 and
A340-300 series airplanes. Since there are no affected A340-200 series
airplanes on the U.S. register, we find that this correction does not
expand the scope of the NPRM. We have revised the final rule to include
the Model A340-200 series airplanes.
Clarification of Editorial Changes to AD
We have clarified paragraphs (b), (c), (e), and (f) of the AD to
reference specific paragraphs of the AOT that are necessary for
accomplishing the specified actions.
Clarification of Alternative Method of Compliance (AMOC) Paragraph
We have revised this action to clarify the appropriate procedure
for notifying the principal inspector before using any approved AMOC on
any airplane to which the AMOC applies.
Conclusion
After careful review of the available data, including the comments
noted above, we have determined that air safety and the public interest
require the adoption of the rule with the changes previously described.
We have determined that these changes will neither increase the
economic burden on any operator nor increase the scope of the AD.
Cost Impact
We estimate that 9 Model A330 series airplanes of U.S. registry
will be affected by this AD, that it will take approximately 1 work
hour per airplane to accomplish the proposed lubrication, and that the
average labor rate is $65 per work hour. Based on these figures, the
cost impact of the AD on U.S. operators is estimated to be $585, or $65
per airplane.
The cost impact figure discussed above is 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.
Currently, there are no affected Model A340 airplanes on the U.S.
Register. However, if an affected airplane is imported and placed on
the U.S. Register in the future, it would take approximately 1 work
hour per airplane to accomplish the proposed lubrication at an average
labor rate of $65 per work hour. Based on these figures, we estimate
the cost of the lubrication required by this AD for these airplanes to
be $65 per airplane.
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 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:
2006-14-02 Airbus: Amendment 39-14673. Docket 2002-NM-247-AD.
Applicability: Model A330-201, -202, -203, -223, -243, -301, -
321, -322, -323, -341, -342, and -343 airplanes; and Model A340-211,
-212, -213, -311, -312, and -313 airplanes, certificated in any
category; having a date of issuance of the original French standard
Airworthiness Certificate or the date of issuance of the original
Export Certificate of Airworthiness of May 24, 2002, or earlier.
Compliance: Required as indicated, unless accomplished
previously.
To prevent failure of the landing gear lengthening system, which
could result in reduced controllability of the airplane on the
ground during landing, accomplish the following:
All Operators Telex Reference
(a) The term ``all operators telex,'' or ``AOT,'' as used in
this AD, means the Short-
[[Page 38064]]
Term Action section of the following AOTs, as applicable:
(1) For Model A330-201, -202, -203, -223, -243, -301, -321, -
322, -323, -341, -342, and -343 airplanes: Airbus A330 AOT 32A3151,
dated March 26, 2002; and
(2) For Model A340-211, -212, -213, -311, -312, and -313
airplanes: Airbus A340 AOT 32A4189, dated March 26, 2002.
Lubrication
(b) At the later of the compliance times in paragraphs (b)(1)
and (b)(2) of this AD: Lubricate the upper and lower shortening
mechanism (SM) link of the main landing gear in accordance with
paragraph 4.2.1 of the applicable AOT.
(1) Within 6 months after the date of issuance of the original
French standard Airworthiness Certificate or the date of issuance of
the original Export Certificate of Airworthiness.
(2) Within 700 flight hours or 60 days after the effective date
of this AD, whichever occurs first.
(c) If, during the lubrication required by paragraph (b) of this
AD, any corrective actions are required, do paragraph (c)(1) or
(c)(2) of this AD, as applicable.
(1) If Airbus Modification 46904 has been accomplished, the
corrective actions must be performed in accordance with paragraphs
4.2.2 and 4.3 of the applicable AOT.
(2) If Airbus Modification 46904 has not been accomplished, do
the applicable inspection and all necessary corrective actions in
accordance with paragraph 4.3 of the applicable AOT.
(d) If, during the lubrication required by paragraph (b) of this
AD, there is noticeable resistance or blockage of the greaseway:
Before further flight, do the applicable inspection and all
necessary corrective actions in paragraphs (e) and (f) of this AD.
Inspections and Corrective Action
(e) For airplanes on which Airbus Modification 46904 has been
incorporated that have a discrepant greaseway per paragraph (d) of
this AD; and for airplanes on which Airbus Modification 46904 has
not been incorporated that do not have a discrepant greaseway:
Before further flight following the lubrication required by
paragraph (b) of this AD, do a general visual inspection for
clearance of the end caps of the SM8 pin, and the presence of the
split pin, the nut, the end caps, and the bolts; in accordance with
paragraph 4.2.2 of the applicable AOT.
(1) If the combined gap of both end caps to the outer flanges of
the bushes in the lower SM is less than 0.75 mm: Within 700 flight
hours after the general visual inspection, make all necessary
repairs and unblock any blocked greaseway, in accordance with
paragraphs 4.2.2 and 4.3 of the applicable AOT.
(2) If the inspection required by paragraph (e) of this AD
reveals a migration of the SM8 pin end caps to a gap of 0.75 mm to
3.0 mm: Within 20 flight cycles after the general visual inspection,
unblock any blocked greaseway in accordance with paragraph 4.3 of
the applicable AOT, and repeat the inspection required by paragraph
(e) of this AD at intervals not to exceed 20 flight cycles until the
action in paragraph (e)(3) is accomplished.
(3) If the inspection required by paragraph (e) of this AD
reveals a migration of the SM8 pin end caps to a gap of 3.0 mm or
greater: Before further flight, remove the SM8 pin, and perform a
general visual inspection of the SM upper link, SM lower link, and
SM8 pin for damage or blockage, and make all necessary repairs
before further flight in accordance with paragraph 4.3 of the
applicable AOT.
Note 1: For the purposes of this AD, a general visual inspection
is defined as: ``A visual examination of an interior or exterior
area, installation, or assembly to detect obvious damage, failure,
or irregularity. This level of inspection is made from within
touching distance unless otherwise specified. A mirror may be
necessary to enhance visual access to all exposed surfaces in the
inspection area. This level of inspection is made under normally
available lighting conditions such as daylight, hangar lighting,
flashlight, or drop light and may require removal or opening of
access panels or doors. Stands, ladders, or platforms may be
required to gain proximity to the area being checked.''
Detailed Inspections and Corrective Actions
(f) If no noticeable resistance or blockage of the greaseway is
noted during the lubrication required by paragraph (b) of this AD:
Within 700 flight hours after the effective date of this AD, do a
detailed inspection of the SM8 pin for damage or corrosion; unblock
any blocked greaseway; and replace any damaged or corroded pin with
a new part; in accordance with paragraph 4.2.2 of the applicable
AOT.
Note 2: 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.''
No Reporting Requirements
(g) Although the AOTs referenced in this AD specify to report
inspection results to the manufacturer, this AD does not include
such a requirement.
Alternative Methods of Compliance
(h)(1) In accordance with 14 CFR 39.19, the Manager,
International Branch, ANM-116, Transport Airplane Directorate, FAA,
is authorized to approve alternative methods of compliance (AMOCs)
for this AD.
(2) Before using any AMOC approved in accordance with Sec.
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 3: The subject of this AD is addressed in French
airworthiness directives 2002-262(B) R1, and 2002-265(B) R2, both
dated January 8, 2003.
Incorporation by Reference
(i) Unless otherwise specified in this AD, the actions must be
done in accordance with Airbus A330 All Operators Telex 32A3151,
dated March 26, 2002; and Airbus A340 All Operators Telex 32A4189,
dated March 26, 2002; as applicable. 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.
Effective Date
(j) This amendment becomes effective on August 9, 2006.
Issued in Renton, Washington, on June 22, 2006.
Kalene C. Yanamura,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 06-5943 Filed 7-3-06; 8:45 am]
BILLING CODE 4910-13-P