[Federal Register: June 16, 2004 (Volume 69, Number 115)]
[Proposed Rules]
[Page 33592-33595]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr16jn04-27]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 2001-NM-381-AD]
RIN 2120-AA64
Airworthiness Directives; Airbus Model A330, A340-200, and A340-
300 Series Airplanes
AGENCY: Federal Aviation Administration, DOT.
ACTION: Notice of proposed rulemaking (NPRM).
-----------------------------------------------------------------------
SUMMARY: This document proposes the adoption of a new airworthiness
directive (AD) that is applicable to all Airbus Model A330, A340-200,
and A340-300 series airplanes. This proposal would require repetitive
detailed inspections for discrepancies of the grease and gear teeth of
the radial variable differential transducer of the nose wheel steering
gearbox; or repetitive detailed inspections for damage of the chrome on
the bearing surface of the nose landing gear (NLG) main fitting barrel;
as applicable. For airplanes on which any discrepancy or damage is
found, this proposal would require either an additional inspection or
corrective actions, as applicable. This action is necessary 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: Comments must be received by July 16, 2004.
ADDRESSES: Submit comments in triplicate to the Federal Aviation
Administration (FAA), Transport Airplane Directorate, ANM-114,
Attention: Rules Docket No. 2001-NM-381-AD, 1601 Lind Avenue, SW.,
Renton, Washington 98055-4056. 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. 2001-NM-381-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: Tim Backman, Aerospace Engineer,
International Branch, ANM-116, FAA, Transport Airplane Directorate,
1601 Lind Avenue, SW., Renton, Washington 98055-4056; telephone (425)
227-2797; 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:
[[Page 33593]]
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 2001-NM-381-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. 2001-NM-381-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 all Airbus Model A330, A340-200, and
A340-300 series airplanes. The DGAC advises that an operator of a Model
A340 airplane reported the failure of the nose wheel steering (NWS)
system. An investigation found abnormal wear of the gear teeth of the
radial variable differential transducer (RVDT) gearbox, which led to
incorrect driving of the command channel and monitoring-channel
feedback sensors. Subsequent analyses of grease samples taken from the
RVDT gearbox showed the presence of significant quantities of water in
the grease, which, when frozen, could have jammed the gearboxes. The
investigation also found chrome flaking and extensive corrosion of the
nose landing gear (NLG) main fitting barrel under the NWS rotating
sleeve.
The investigators concluded that abrasion from metallic particles
in the grease caused the wear of the gear teeth. These metallic
particles came from the corroded areas of the NLG main fitting barrel,
and had been carried into the system by grease that was used during the
normal lubrication of the rotating sleeve. The investigators also
concluded that water entered the gearbox through the seal between the
steering collar and the NLG main fitting; improvement of this seal is
the subject of Airbus Modification 51318 (Airbus Service Bulletins
A330-32-3164 and A340-32-4204).
Wear of the gear teeth of the RVDT caused by the metallic particles
from corrosion in the grease, and jamming of the gearbox caused by
water freezing in the grease, could result in incorrect operation or
jamming of the NWS, which could cause reduced controllability of the
airplane on the ground.
The subject area on certain Model A330 series airplanes is almost
identical to that on the affected Model A340-200, and A340-300 series
airplanes. Therefore, those Model A330 series airplanes may be subject
to the unsafe condition revealed on the Model A340-200, and A340-300
series airplanes.
Explanation of Relevant Service Information
Airbus has issued the following service bulletins:
For Model A330 series airplanes: Airbus Service Bulletin
A330-32-3134, Revision 02, excluding Appendix 01, dated August 8, 2003;
and
For Model A340-200 and A340-300 series airplanes: Airbus
Service Bulletin A340-32-4172, Revision 02, excluding Appendix 01,
dated August 8, 2003.
For certain airplanes, these service bulletins specify that
operators may choose between two different inspections. Depending on
the inspection choice, the service bulletins recommend different
repetitive intervals. The service bulletins also state that operators
may alternate between the inspection choices as long as the interval
until the next inspection is the interval described for the last
inspection performed.
The first inspection choice for airplanes without the Airbus
Modification is repetitive inspections of the grease and gear teeth of
the RVDT driving ring and the gears in the RVDT gearboxes to find
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. If there are discrepancies, the
service bulletins describe procedures for inspecting the chrome on the
bearing surface of the NLG main fitting barrel under the NWS rotating
sleeve for damage such as flaking, corrosion, or blistering.
The second inspection choice for airplanes without the Airbus
Modification is repetitive inspections of the chrome on the bearing
surface of the NLG main fitting barrel under the NWS rotating sleeve
for damages such as flaking, corrosion, or blistering.
For certain other airplanes, the service bulletins recommend only
the inspection of the chrome on the bearing surface of the NLG main
fitting barrel, which is described in the paragraph above.
For all airplanes on which discrepancies and/or damage are found,
the service bulletins specify that operators should take corrective
actions. The corrective actions are included in the two Messier-Dowty
service bulletins listed below. These corrective actions include
degreasing bare base metal and protecting the metal with cadmium Cd10
or a complete paint scheme, restoring the rubber sealant, and/or
contacting Messier-Dowty for disposition.
For certain airplanes: Messier-Dowty Special Inspection
Service Bulletin D23285-32-037, dated November 8, 2001.
For certain other airplanes airplanes: Messier-Dowty
Special Inspection Service Bulletin D23285-32-044, dated January 12,
2004.
Both Airbus service bulletins refer to the Messier-Dowty service
bulletins as additional sources of service information for
accomplishment of the inspections and any applicable corrective
actions.
The DGAC classified the Airbus service bulletins as mandatory and
issued French airworthiness directives 2001-503(B) R3, dated October 1,
2003; and 2001-504(B) R4, dated October 1, 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
Sec. 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.
[[Page 33594]]
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 service bulletins described previously,
except as discussed below.
Differences Among the Proposed Rule, Service Bulletins, and the French
Airworthiness Directive
Operators should note that, although the Messier-Dowty service
bulletins specify that the manufacturer may be contacted for
disposition of certain repair conditions, this proposal would require
the repair of those conditions to be accomplished per a method approved
by either the FAA, or the DGAC (or its delegated agent). In light of
the type of repair that would be required to address the identified
unsafe condition, and in consonance with existing bilateral
airworthiness agreements, the FAA has determined that, for this
proposed AD, a repair approved by either the FAA or the DGAC would be
acceptable for compliance with this proposed AD.
Operators should also note that, although the Messier-Dowty service
bulletins specify to submit reporting forms to the manufacturer, this
proposed AD does not include such a requirement.
The French airworthiness directives do not give a compliance time
for inspecting the chrome on the bearing surface of the NLG main
fitting barrel for airplanes without Airbus Modification 51318 that
have discrepancies of the grease and gear teeth of the RVDT driving
ring and the gears in the RVDT gearboxes. This proposed AD would
require that operators inspect the chrome within 3 months after the
RVDT inspection.
The French airworthiness directives and the service bulletins do
not define the type of inspections to be performed. This proposed AD
calls the inspections ``detailed inspections.'' Note 1 of this proposed
AD defines this inspection.
Cost Impact
We estimate that 16 airplanes of U.S. registry would be affected by
this proposed AD.
For operators of airplanes without Airbus Modification 51318, who
choose to do the inspection of the grease and gear teeth of the RVDT
gearbox, we estimate that it would take approximately 2 work hours per
airplane to accomplish the proposed inspection and that the average
labor rate is $65 per work hour. Based on these figures, the cost
impact of this action on U.S. operators is estimated to be $130 per
airplane, per inspection cycle.
For operators of airplanes with Airbus Modification 51381, or for
operators of airplanes without Airbus Modification 51381 who choose to
do the proposed inspection of the chrome on the bearing surface of the
NLG main fitting barrel, we estimate that it would take approximately 8
work hours per airplane to accomplish the inspection, and that the
average labor rate is $65 per work hour. Based on these figures, the
cost impact of the proposed AD on U.S. operators is estimated to be
$520 per airplane, per inspection cycle.
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.
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 2001-NM-381-AD.
Applicability: All Model A330, A340-200, and A340-300 series
airplanes; certificated in any category.
Compliance: Required as indicated, unless accomplished
previously.
To prevent incorrect operation or jamming of the nose wheel
steering, which could cause reduced controllability of the airplane
on the ground, accomplish the following:
Service Bulletin Reference
(a) The following information pertains to the service bulletin
referenced in this AD:
(1) The term ``service bulletin,'' as used in this AD, means the
Accomplishment Instructions of the following service bulletins, as
applicable:
(i) For the inspections specified in paragraphs (c) and (d) of
this AD: For Model A330 series airplanes, Airbus Service Bulletin
A330-32-3134, Revision 02, excluding Appendix 01, dated August 8,
2003; and for Model A340-200 and A340-300 series airplanes, Airbus
Service Bulletin A340-32-4172, Revision 02, excluding Appendix 01,
dated August 8, 2003; and
(ii) For further information about the inspections required by
paragraphs (c) and (d) of this AD, and for the corrective actions
specified in paragraph (e) of this AD: Messier-Dowty Special
Inspection Service Bulletin D23285-32-037, dated November 8, 2001
(for airplanes without Airbus Modification 51381); and Messier-Dowty
Special Inspection Service Bulletin D23285-32-044, dated January 12,
2004 (for airplanes with Airbus Modification 51381).
(2) Actions accomplished before the effective date of this AD
per the Airbus service bulletins listed in Table 1 of this AD are
considered acceptable for compliance with the corresponding action
specified in this AD.
[[Page 33595]]
Table 1.--Previous Issues of Service Bulletins
----------------------------------------------------------------------------------------------------------------
Model Service bulletin Revision level Date
----------------------------------------------------------------------------------------------------------------
A330........................... A330-32-3134 Original Issue......... September 11, 2001.
A330........................... A330-32-3134 01..................... November 29, 2001.
A340-200 and A340-300.......... A340-32-4172 Original Issue......... September 11, 2001.
A340-200 and A340-300.......... A340-32-4172 01..................... November 29, 2001.
----------------------------------------------------------------------------------------------------------------
Initial Inspection and Related Investigative Action
(b) For airplanes without Airbus Modification 51381: At the
latest of the times in paragraphs (b)(1), (b)(2), and (b)(3) of this
AD, do the applicable initial inspection in paragraph (d) of this
AD.
(1) Within 60 months after the date that the nose landing gear
(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 with Airbus Modification 51381: At the latest
of the times in paragraphs (c)(1), (c)(2), and (c)(3) of this AD, do
the applicable initial inspection in paragraph (d) of this AD.
(1) Within 60 months after the date that the 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 60 months after the date that Airbus Modification
51381 was installed on the airplane.
(d) For airplanes without Airbus Modification 51318, do the
inspection in either paragraph (d)(1) or (d)(2) of this AD,
including any applicable related investigative action. For airplanes
with Airbus Modification 51318, do the inspection in paragraph
(d)(2) of this AD. Do the inspection at the applicable time in
paragraph (b) or (c) of this AD, in accordance with the applicable
service bulletin.
(1) Do a detailed inspection for discrepancies of the grease and
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 per paragraph (e) of this AD. If there are discrepancies,
within 3 months after the inspection, do the inspection in paragraph
(d)(2) of this AD.
(2) Do a detailed inspection for damage of the chrome on the
bearing surface of the NLG main fitting barrel under the NWS
rotating sleeve. If there is no damage (such as flaking, corrosion,
or blistering), repeat the inspection per paragraph (e) of this AD.
If there is damage, do the corrective action in paragraph (f) 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.''
Repetitive Inspections
(e) Repeat the applicable inspection required by paragraph (d)
of this AD at the applicable interval in paragraph (e)(1) or (e)(2)
of this AD until paragraph (f) of this AD is accomplished.
(1) If the most recent inspection performed is the inspection in
paragraph (d)(1) of this AD, then repeat the selected inspection at
intervals not to exceed 8 months.
(2) If the most recent inspection performed is the inspection in
paragraph (d)(2) of this AD, then repeat the selected inspection at
intervals not to exceed 18 months.
Corrective Actions
(f) Except as provided by paragraph (d)(1) of this AD, for
airplanes on which any damage or discrepancy is found during any
inspection required by paragraph (d) or (e) of this AD: Prior to
further flight, do the corrective action in accordance with the
applicable service bulletin. Where the service bulletin recommends
contacting Messier-Dowty for appropriate action: Before further
flight, repair per a method approved by either the Manager,
International Branch, ANM-116, FAA, Transport Airplane Directorate;
or the Direction G[eacute]n[eacute]rale de l'Aviation Civile (DGAC)
(or its delegated agent).
No Reporting Requirements
(g) Where the Messier-Dowty service bulletins specify to submit
a reporting form 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, is authorized to approve alternative methods of
compliance for this AD.
Note 2: The subject of this AD is addressed in French
airworthiness directives 2001-503(B) R3, dated October 1, 2003; and
2001-504(B) R4, dated October 1, 2003.
Issued in Renton, Washington, on June 7, 2004.
Kalene C. Yanamura,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 04-13562 Filed 6-15-04; 8:45 am]
BILLING CODE 4910-13-U