[Federal Register: April 1, 2004 (Volume 69, Number 63)]
[Proposed Rules]
[Page 17088-17091]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr01ap04-23]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 2002-NM-247-AD]
RIN 2120-AA64
Airworthiness Directives; Airbus Model A330 Series Airplanes;
Airbus Model A340-300 Series Airplanes; and Airbus Model A340-541
Airplanes
AGENCY: Federal Aviation Administration, DOT.
ACTION: Notice of proposed rulemaking (NPRM).
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SUMMARY: This document proposes the adoption of a new 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. This proposal would 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, this proposal would
require various other actions including unblocking the greaseway;
accomplishing any 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: Comments must be received by May 3, 2004.
ADDRESSES: Submit comments in triplicate to the Federal Aviation
Administration (FAA), Transport Airplane Directorate, ANM-114,
Attention: Rules Docket No. 2002-NM-247-AD, 1601 Lind Avenue, SW.,
Renton, Washington 98055-4056.
[[Page 17089]]
Comments may be inspected at this location between 9 a.m. and 3 p.m.,
Monday through Friday, except Federal holidays. Comments may be
submitted via fax to (425) 227-1232. Comments may also be sent via the
Internet using the following address: 9-anm-nprmcomment@faa.gov.
Comments sent via fax or the Internet must contain ``Docket No. 2002-
NM-247-AD'' in the subject line and need not be submitted in
triplicate. Comments sent via the Internet as attached electronic files
must be formatted in Microsoft Word 97 or 2000 or ASCII text.
The service information referenced in the proposed rule may be
obtained from Airbus, 1 Rond Point Maurice Bellonte, 31707 Blagnac
Cedex, France. This information may be examined at the FAA, Transport
Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington.
FOR FURTHER INFORMATION CONTACT: Gary Lium, Aerospace Engineer,
International Branch, ANM-116, FAA, Transport Airplane Directorate,
1601 Lind Avenue, SW., Renton, Washington 98055-4056; telephone (425)
227-1112; fax (425) 227-1149.
SUPPLEMENTARY INFORMATION:
Comments Invited
Interested persons are invited to participate in the making of the
proposed rule by submitting such written data, views, or arguments as
they may desire. Communications shall identify the Rules Docket number
and be submitted in triplicate to the address specified above. All
communications received on or before the closing date for comments,
specified above, will be considered before taking action on the
proposed rule. The proposals contained in this action may be changed in
light of the comments received.
Submit comments using the following format:
Organize comments issue-by-issue. For example,
discuss a request to change the compliance time and a request to change
the service bulletin reference as two separate issues.
For each issue, state what specific change to
the proposed AD is being requested.
Include justification (e.g., reasons or data)
for each request.
Comments are specifically invited on the overall regulatory,
economic, environmental, and energy aspects of the proposed rule. All
comments submitted will be available, both before and after the closing
date for comments, in the Rules Docket for examination by interested
persons. A report summarizing each FAA-public contact concerned with
the substance of this proposal will be filed in the Rules Docket.
Commenters wishing the FAA to acknowledge receipt of their comments
submitted in response to this action must submit a self-addressed,
stamped postcard on which the following statement is made: ``Comments
to Docket Number 2002-NM-247-AD.'' The postcard will be date stamped
and returned to the commenter.
Availability of NPRMs
Any person may obtain a copy of this NPRM by submitting a request
to the FAA, Transport Airplane Directorate, ANM-114, Attention: Rules
Docket No. 2002-NM-247-AD, 1601 Lind Avenue, SW., Renton, Washington
98055-4056.
Discussion
The Direction G[eacute]n[eacute]rale de l'Aviation Civile (DGAC),
which is the airworthiness authority for France, notified the FAA that
an unsafe condition may exist on certain Airbus Model A330 series
airplanes; Airbus Model A340-300 series airplanes; and Airbus Model
A340-541 airplanes. The DGAC advises that on approach, after landing
gear extension, the crew of an Airbus Model A330 series airplane
received a warning of ``Landing Gear LH Lengthening Fault,'' and an
advisory message to keep the landing gear lever down. An inspection of
the landing gear after the airplane landed showed that the left-hand
(LH) main landing gear (MLG) was completely compressed. Investigation
found that the LH shortening mechanism (SM) proximity sensor was not in
the proper position, which was caused by the failure of the connecting
link. The link failure was caused by corrosion on the non-nickel
underchrome SM8 pin due to poor lubrication. This condition, if not
corrected, could result in failure of the landing gear lengthening
system, which could cause reduced controllability of the airplane on
the ground during landing.
Explanation of Relevant Service Information
Airbus has issued All Operators Telex (AOT) 32A3151, dated March
26, 2002; and AOT 32A4189, dated March 26, 2002. These AOTs describe
procedures for lubricating the upper and lower SM links and consequent
detection of discrepancies (resistance or blockage) in the greaseway.
For airplanes on which Airbus Modification 46904 has been
incorporated, that have a discrepant greaseway, or for airplanes on
which Airbus Modification 46904 has not been incorporated (whether or
not it has a discrepant greaseway); the AOTs describe procedures for
performing a detailed inspection of the SM8 pin for damage or
corrosion, unblocking any blocked greaseway, and replacing any damaged
or corroded pin with a new part.
For airplanes on which Airbus Modification 46904 has not been
incorporated, that have a discrepant greaseway, the AOTs describe
additional procedures for performing a general visual inspection of the
SM8 end caps to determine the presence and correct installation of
certain parts, and to measure the gap of the end caps to the outer
flanges of the bushes in the lower SM link; unblocking the blocked
greaseway and making any necessary repairs; and repeating the general
visual inspection, if necessary, until the affected part is repaired.
The DGAC classified these AOTs as mandatory and issued French
airworthiness directive 2002-262(B) R1, dated January 8, 2003; and
French airworthiness directive 2002-265(B) R2, dated January 8, 2003;
to ensure the continued airworthiness of these airplanes in France.
FAA's Conclusions
These airplane models are manufactured in France and are type
certificated for operation in the United States under the provisions of
section 21.29 of the Federal Aviation Regulations (14 CFR 21.29) and
the applicable bilateral airworthiness agreement. Pursuant to this
bilateral airworthiness agreement, the DGAC has kept the FAA informed
of the situation described above. The FAA has examined the findings of
the DGAC, reviewed all available information, and determined that AD
action is necessary for products of this type design that are
certificated for operation in the United States.
Explanation of Requirements of Proposed Rule
Since an unsafe condition has been identified that is likely to
exist or develop on other airplanes of the same type design registered
in the United States, the proposed AD would require accomplishment of
the actions specified in the AOTs described previously, except as
discussed below.
Difference Between the AOTs and the Proposed AD
Although the AOTs specify to report inspection results to the
manufacturer, this AD does not include such a requirement.
[[Page 17090]]
Interim Action
We consider this proposed AD interim action. If final action is
later identified, we may consider further rulemaking then.
Cost Impact
The FAA estimates that 9 Model A330 airplanes of U.S. registry
would be affected by this proposed AD, that it would 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 lubrication proposed by this AD on U.S.
operators of these airplanes 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 proposed 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 proposed by this AD for these airplanes to
be $65 per airplane.
Regulatory Impact
The regulations proposed herein would 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 proposal would not have federalism implications
under Executive Order 13132.
For the reasons discussed above, I certify that this proposed
regulation (1) is not a ``significant regulatory action'' under
Executive Order 12866; (2) is not a ``significant rule'' under the DOT
Regulatory Policies and Procedures (44 FR 11034, February 26, 1979);
and (3) if promulgated, 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 copy of the draft
regulatory evaluation prepared for this action is contained in the
Rules Docket. A copy of it may be obtained by contacting the Rules
Docket at the location provided under the caption ADDRESSES.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Safety.
The Proposed Amendment
Accordingly, pursuant to the authority delegated to me by the
Administrator, the Federal Aviation Administration proposes to amend
part 39 of the Federal Aviation Regulations (14 CFR part 39) as
follows:
PART 39--AIRWORTHINESS DIRECTIVES
1. The authority citation for part 39 continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
Sec. 39.13 [Amended]
2. Section 39.13 is amended by adding the following new airworthiness
directive:
Airbus: Docket 2002-NM-247-AD.
Applicability: Model A330 series airplanes; Model A340-300
series airplanes; and Model A340-541 airplanes; having a date of
issuance of the original Airworthiness Certificate or the date of
issuance of the Export Certificate of Airworthiness (whichever
occurs later) of May 24, 2002, or earlier; certificated in any
category.
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-Term Action section of the following AOTs,
as applicable:
(1) For Model A330 series airplanes: Airbus AOT 32A3151, dated
March 26, 2002; and
(2) For Model A340 series airplanes, and Model A340-541
airplanes: Airbus 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 the
applicable AOT.
(1) Within 6 months after the date of issuance of the original
Airworthiness Certificate or the date of issuance of the Export
Certificate of Airworthiness, whichever occurs first.
(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, there is no noticeable resistance or blockage of the greaseway,
do paragraph (c)(1) or (c)(2) of this AD, as applicable.
(1) If Airbus Modification 46904 has been accomplished, no
further action is required by this AD.
(2) If Airbus Modification 46904 has not been accomplished, do
the applicable inspection and any necessary corrective action in
paragraph (e) of this AD.
(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 any
necessary corrective action 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: Before further
flight, make any necessary repairs and unblock the any blocked
greaseway, in accordance with 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: Before further flight, unblock any blocked greaseway, and
repeat the inspection required by paragraph (e) of this AD at
intervals not to exceed 20 flight cycles until paragraph (e)(3) of
this AD 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 any necessary repairs
before further flight in accordance with 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 droplight 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.''
[[Page 17091]]
Detailed Inspections and Corrective Actions
(f) If 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 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 specifies to report
inspection results to the manufacturer, this AD does not include
such a requirement.
Alternative Methods of Compliance
(h) In accordance with 14 CFR 39.19, the Manager, International
Branch, ANM-116, FAA, Transport Airplane Directorate is authorized
to approve alternative methods of compliance for this AD.
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.
Issued in Renton, Washington, on March 19, 2004.
Kevin M. Mullin,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 04-7357 Filed 3-31-04; 8:45 am]
BILLING CODE 4910-13-P