[Federal Register Volume 69, Number 115 (Wednesday, June 16, 2004)]
[Proposed Rules]
[Pages 33592-33595]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 04-13562]


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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).

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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: 
[email protected]. 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
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             Model                   Service bulletin          Revision level                   Date
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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