[Federal Register: May 29, 2003 (Volume 68, Number 103)]
[Proposed Rules]
[Page 31991-31994]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr29my03-24]
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Proposed Rules
Federal Register
________________________________________________________________________
This section of the FEDERAL REGISTER contains notices to the public of
the proposed issuance of rules and regulations. The purpose of these
notices is to give interested persons an opportunity to participate in
the rule making prior to the adoption of the final rules.
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[[Page 31991]]
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 2001-NM-187-AD]
RIN 2120-AA64
Airworthiness Directives; Airbus Model A330 and A340 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 and A340
series airplanes. This proposal would require, among other actions, a
detailed inspection of the rudder travel limitation unit for proper
adjustment, measurement of the desynchronization of rudder servo-
controls, installation of rigging placards for rudder servo-controls,
and follow-on and corrective actions, if necessary. This action is
necessary to prevent desynchronization of the rudder servo-controls,
which could result in high load factors on the rudder servo-controls,
and consequent reduced structural integrity of the attachment fittings
for the rudder servo-controls. This action is intended to address the
identified unsafe condition.
DATES: Comments must be received by June 30, 2003.
ADDRESSES: Submit comments in triplicate to the Federal Aviation
Administration (FAA), Transport Airplane Directorate, ANM-114,
Attention: Rules Docket No. 2001-NM-187-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-187-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 for Windows or
ASCII text.
The service information referenced in the proposed rule may be
obtained from Airbus Industrie, 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: 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:
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:
[sbull] 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.
[sbull] For each issue, state what specific change to the proposed
AD is being requested.
[sbull] 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-187-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-187-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 and A340 series
airplanes. The DGAC advises that it has received several reports of
abnormal stiff application of the rudder pedal in flight and during
ground tests. Investigation revealed cracks on the attachment fittings
for the blue rudder servo-controls and on the spherical bearing of the
tail lock for the blue rudder servo-controls. Also, the actuating
spring rod of the blue rudder servo-controls was found to be shorter
than the actuating spring rods of the yellow and green rudder servo-
controls, which resulted in desynchronization of the rudder servo-
controls. The high load factors induced by the desynchronization caused
the cracks on the attachment fittings for the servo-controls and
spherical bearing. The desynchronization was caused by deviation from
the procedures for adjusting actuating spring rods of the rudder servo-
controls. This condition, if not corrected, could result in high load
factors on the rudder servo-controls, and consequent reduced structural
integrity of the attachment fittings for the rudder servo-controls.
Explanation of Relevant Service Information
Airbus has issued Service Bulletin A330-27-3084 (for Model A330
series airplanes); and Service Bulletin A340-27-4088 (for Model A340
series airplanes); both dated March 28, 2001. These service bulletins
describe
[[Page 31992]]
procedures for performing a detailed inspection of the rudder travel
limitation unit (RTLU) for proper adjustment, and measuring
desynchronization of the rudder servo-controls. The inspection of the
RTLU includes installing rigging pins on the bellcrank and right and
left input levers and, if necessary, adjusting the length of the
applicable adjustable rod. Measurement of the rudder servo-controls for
desynchronization includes disconnecting the control rod from the
bellcrank; installing a rigging pin on the bellcrank assembly of the
lower servo-controls; pressurizing and depressurizing the blue, yellow,
and green hydraulic systems at the appropriate times; recording the
results; if desynchronization is found, determining if the value is
within the acceptable limits specified in the service bulletins;
replacing or adjusting the actuating spring rods and affected rudder
servo-controls; and returning replaced rudder servo-controls with the
highest load factors to the manufacturer; as applicable.
For airplanes on which any rudder servo-control has been replaced
per Service Bulletin A330-27-3084 or Service Bulletin A340-27-4088,
Airbus has also issued Service Bulletin A330-55-3028 (for Model A330
series airplanes); and Service Bulletin A340-55-4026 (for Model A340
series airplanes); including Appendix 01; dated May 28, 2001. These
service bulletins describe procedures for a detailed or high frequency
eddy current inspection of the attachment fittings of desynchronized
rudder servo-controls for cracks. The service bulletins describe
procedures for follow-on actions (including additional detailed
inspections in the area of the fasteners and attachment fittings;
additional high frequency eddy current inspections; cold expansion of
specific fastener holes; drilling/reaming and cleaning of specific
fastener holes; rotating probe inspections; and wet installation of
pins, collars, and oversize fasteners) depending on airplane
configuration; as applicable; and repetitive inspections. The service
bulletins also state that if any crack is found, operators should
contact Airbus for repair instructions.
For certain Model A330 series airplanes, Airbus Service Bulletin
A330-27-3084 recommends concurrent accomplishment of Airbus Service
Bulletin A330-27-3082, dated March 28, 2001. Service Bulletin A330-27-
3082 describes procedures for installing rigging placards for the
rudder servo-controls (including bonding placards to the appropriate
areas and coating them with lacquer).
For certain Model A340 series airplanes, Airbus Service Bulletin
A340-27-4088 recommends concurrent accomplishment of Airbus Service
Bulletin A340-27-4086, dated March 28, 2001. Service Bulletin A340-27-
4086 describes procedures for installing rigging placards for the
rudder servo-controls (including bonding placards to the appropriate
areas and coating them with lacquer).
Accomplishment of the actions specified in these service bulletins
is intended to adequately address the identified unsafe condition. The
DGAC classified these service bulletins as mandatory and issued French
airworthiness directives 2001-156(B) and 2001-157(B), both dated May 2,
2001, in order to assure 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 applicable service bulletins described
previously, except as discussed below.
Differences Between Foreign Airworthiness Directives, Service
Bulletins, and Proposed AD
Operators should note that although French airworthiness directives
2001-156(B) and 2001-157(B); and Airbus Service Bulletins A330-55-3028
(for Model A330 series airplanes) and A340-55-4026 (for Model A340
series airplanes); include instructions for reporting inspection
results and returning desynchronized rudder servo-controls with the
highest load factors to Airbus, this proposed AD would not require
those actions.
Operators should also note that, although Airbus Service Bulletins
A330-55-3028 and A340-55-4026 specify that the manufacturer may be
contacted for certain repair instructions, this proposal would require
the repair be accomplished in accordance with 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 (or its delegated agent) would
be acceptable for compliance with this proposed AD.
Cost Impact
The FAA estimates that 9 Model A330 series airplanes of U.S.
registry would be affected by this proposed AD, that it would take 6
work hours per airplane to accomplish the proposed inspection and
measurement, and 1 work hour per airplane to accomplish the proposed
installation of the rigging placards, and that the average labor rate
is $60 per work hour. Required rigging placards would be provided to
the operators at no cost. Based on these figures, the cost impact of
the proposed AD on U.S. operators is estimated to be $3,780, or $420
per airplane.
The cost impact figures discussed above are 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 proposed 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 Airbus Model A340 series airplanes on the
U.S. Register. However, should an affected airplane be imported and
placed on the U.S. Register in the future, it would require 6 work
hours per airplane to accomplish the proposed inspection and
measurement, and 1 work hour per airplane to accomplish the proposed
installation of the rigging placards, at an average labor rate of $60
per work hour. Required placards would be provided to the operators at
no cost. Based on these figures, the cost impact of the proposed AD for
Model A340 operators would be $420 per airplane.
[[Page 31993]]
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-187-AD.
Applicability: Model A330 and A340 series airplanes,
certificated in any category; except those airplanes modified in
production in accordance with Airbus Modification 48110.
Note 1: This AD applies to each airplane identified in the
preceding applicability provision, regardless of whether it has been
otherwise modified, altered, or repaired in the area subject to the
requirements of this AD. For airplanes that have been modified,
altered, or repaired so that the performance of the requirements of
this AD is affected, the owner/operator must request approval for an
alternative method of compliance in accordance with paragraph (e) of
this AD. The request should include an assessment of the effect of
the modification, alteration, or repair on the unsafe condition
addressed by this AD; and, if the unsafe condition has not been
eliminated, the request should include specific proposed actions to
address it.
Compliance: Required as indicated, unless accomplished
previously.
To prevent desynchronization of the rudder servo-controls, which
could result in high load factors on the rudder servo-controls, and
consequent reduced structural integrity of the attachment fittings
for the rudder servo-controls, accomplish the following:
Inspection of Rudder Travel Limitation Unit
(a) Within 16 months after the effective date of this AD:
Perform a one-time detailed inspection of the rudder travel
limitation unit (RTLU) (including installing rigging pins on the
bellcrank and the right and left input levers) for proper
adjustment, per the Accomplishment Instructions specified in Airbus
Service Bulletin A330-27-3084 (for Model A330 series airplanes); or
Airbus Service Bulletin A340-27-4088 (for Model A340 series
airplanes); both dated March 28, 2001; as applicable. Although the
service bulletins reference a reporting requirement, such reporting
is not required by this AD.
(1) If it is possible to install rigging pins on both input
levers, the RTLU is properly adjusted and no further action is
required by this paragraph.
(2) If it is not possible to install the rigging pins on either
input lever, before further flight, adjust the length of the
appropriate adjustable rod, per the Accomplishment Instructions
specified in the applicable service bulletin.
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.''
Measurement of Rudder Servo-Controls Desynchronization and Corrective
Action if Necessary
(b) Within 16 months after the effective date of this AD:
Measure the desynchronization value (value D) of the rudder servo-
controls and, depending on the measurement, before further flight,
perform the applicable corrective actions (e.g., replacement and/or
adjustment of the spring rod and/or the rudder servo-controls); per
the Accomplishment Instructions specified in Airbus Service Bulletin
A330-27-3084 (for Model A330 series airplanes); or Airbus Service
Bulletin A340-27-4088 (for Model A340 series airplanes); both dated
March 28, 2001; as applicable. Operators should note that although
these service bulletins request that desynchronized rudder servo-
controls with the highest load factors be returned to the
manufacturer, that action is not required by this AD.
(c) If any rudder servo-control was replaced per the
requirements of paragraph (b) of this AD, do paragraphs (c)(1) and
(c)(2) of this AD.
(1) Before further flight, perform either a detailed inspection
or a high frequency eddy current (HFEC) inspection for cracks in the
attachment fittings of the desynchronized rudder servo-controls, and
perform the applicable follow-on and corrective actions (e.g., cold
expansion of affected fastener holes, drilling/reaming of affected
holes, and rotating probe inspections), per the Accomplishment
Instructions specified in Airbus Service Bulletin A330-55-3028 (for
Model A330 series airplanes); or Airbus Service Bulletin A340-55-
4026 (for Model A340 series airplanes); excluding Appendix 01; dated
May 28, 2001; as applicable; except where the service bulletin
specifies to contact the manufacturer for repair instructions,
repair per a method approved by the Manager, International Branch,
ANM-116, FAA.
(2) Repeat the inspection required by paragraph (c)(1) of this
AD at the following intervals:
(i) If the immediately preceding inspection was conducted using
detailed inspection techniques, conduct the next inspection within
300 flight cycles; or
(ii) If the immediately preceding inspection was conducted using
HFEC techniques, conduct the next inspection within 6,000 flight
cycles.
Concurrent Requirements
(d) Concurrently with the requirements of paragraphs (a) and (b)
of this AD, install appropriate rigging placards for the rudder
servo-controls, per Airbus Service Bulletin A330-27-3082 (for Model
A330 series airplanes); or Airbus Service Bulletin A340-27-4086 (for
Model A340 series airplanes); both dated March 28, 2001; as
applicable.
Alternative Methods of Compliance
(e) An alternative method of compliance or adjustment of the
compliance time that provides an acceptable level of safety may be
used if approved by the Manager, International Branch, ANM-116,
Transport Airplane Directorate, FAA. Operators shall submit their
requests through an appropriate FAA Principal Maintenance Inspector,
who may add comments and then send it to the Manager, International
Branch, ANM-116.
Note 3: Information concerning the existence of approved
alternative methods of compliance with this AD, if any, may be
obtained from the International Branch, ANM-116.
Special Flight Permits
(f) Special flight permits may be issued in accordance with
sections 21.197 and 21.199 of the Federal Aviation Regulations (14
CFR 21.197 and 21.199) to operate the airplane to a location where
the requirements of this AD can be accomplished.
Note 4: The subject of this AD is addressed in French
airworthiness directives 2001-156(B) and 2001-157(B), both dated May
2, 2001.
[[Page 31994]]
Issued in Renton, Washington, on May 21, 2003.
Vi L. Lipski,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 03-13389 Filed 5-28-03; 8:45 am]
BILLING CODE 4910-13-P