[Federal Register: July 5, 2006 (Volume 71, Number 128)]
[Rules and Regulations]
[Page 38062-38064]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr05jy06-5]
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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.
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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 http://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