[Federal Register: September 5, 2003 (Volume 68, Number 172)]
[Rules and Regulations]
[Page 52688-52690]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr05se03-4]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 2001-NM-187-AD; Amendment 39-13293; AD 2003-18-02]
RIN 2120-AA64
Airworthiness Directives; Airbus Model A330 and A340 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 and A340 series airplanes, that
requires, 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: Effective October 10, 2003.
The incorporation by reference of certain publications listed in
the regulations is approved by the Director of the Federal Register as
of October 10, 2003.
ADDRESSES: The service information referenced in this AD may be
obtained from Airbus Industrie, 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; or at the Office of
the Federal Register, 800 North Capitol Street, NW., suite 700,
Washington, DC.
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 and A340
series airplanes was published in the Federal Register on May 29, 2003
(68 FR 31991). That action proposed to 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.
Interested persons have been afforded an opportunity to participate
in the making of this amendment. Due consideration has been given to
the comments received.
Request To Extend Compliance Time
Two commenters request that the compliance time of the proposed AD
be extended from 16 months to 18 months. One of the commenters is the
operator of the nine U.S.-registered Airbus Model A330 airplanes
affected by the proposed AD. Extension of the compliance time to 18
months would match the Airbus C-check interval. The second commenter
supports the comments of the first commenter and offers no additional
comment.
The FAA does not agree with the commenters' request to extend the
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compliance time. The operator has completed the required inspection on
five of its nine airplanes. The operator plans to inspect the remaining
four airplanes in its fleet at the next C-check, scheduled to begin in
late 2003. Of the five airplanes already inspected, the operator
indicates that it has found two airplanes with desynchronized servo-
controls. Based upon those inspection results the FAA finds that it may
be possible for the remaining airplanes to also have desynchronized
servo-controls. Such desynchronized servo-controls could cause cracks
on the rudder servo-control bearing and attachment, leading to reduced
structural integrity of the rudder servo-control attachment fitting.
Therefore, we do not consider that an extension is appropriate.
Operators always have the option to request approval of an alternative
method of compliance if it provides an equivalent level of safety. No
change to the final rule is necessary regarding this issue.
Conclusion
After careful review of the available data, including the comments
noted above, the FAA has determined that air safety and the public
interest require the adoption of the rule as proposed.
Changes to 14 CFR Part 39/Effect on the AD
On July 10, 2002, the FAA issued a new version of 14 CFR part 39
(67 FR 47997, July 22, 2002), which governs the FAA's airworthiness
directives system. The regulation now includes material that relates to
altered products, special flight permits, and alternative methods of
compliance. However, for clarity and consistency in this final rule, we
have retained the language of the NPRM regarding that material.
Change to Labor Rate Estimate
We have reviewed the figures we have used over the past several
years to calculate AD costs to operators. To account for various
inflationary costs in the airline industry, we find it necessary to
increase the labor rate used in these calculations from $60 per work
hour to $65 per work hour. The cost impact information, below, reflects
this increase in the specified hourly labor rate.
Cost Impact
The FAA estimates that 9 Airbus Model A330 series airplanes of U.S.
registry will be affected by this AD, that it will take approximately 6
work hours per airplane to accomplish the required inspection and
measurement, and 1 work hour per airplane to accomplish the required
installation of the rigging placards, and that the average labor rate
is $65 per work hour. Required rigging placards will be provided to the
operators at no cost. Based on these figures, the cost impact of the AD
on U.S. operators is estimated to be $4,095, or $455 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 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 required inspection and
measurement, and 1 work hour per airplane to accomplish the required
installation of the rigging placards, at an average labor rate of $65
per work hour. Required placards would be provided to the operators at
no cost. Based on these figures, the cost impact of the AD for Model
A340 operators would be $455 per airplane.
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:
2003-18-02 Airbus: Amendment 39-13293. 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
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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); both excluding Appendix 01;
both 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 Permit
(f) Special flight permits may be issued in accordance with
Sec. Sec. 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.
Incorporation by Reference
(g) The actions shall be done in accordance with Airbus Service
Bulletin A330-27-3082, dated March 28, 2001; Airbus Service Bulletin
A330-27-3084, dated March 28, 2001; Airbus Service Bulletin A330-55-
3028, excluding Appendix 01, dated May 28, 2001; Airbus Service
Bulletin A340-27-4086, dated March 28, 2001; Airbus Service Bulletin
A340-27-4088, dated March 28, 2001; and Airbus Service Bulletin
A340-55-4026, excluding Appendix 01, dated May 28, 2001; 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. Copies may be obtained from Airbus Industrie, 1
Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France. Copies may
be inspected at the FAA, Transport Airplane Directorate, 1601 Lind
Avenue, SW., Renton, Washington; or at the Office of the Federal
Register, 800 North Capitol Street, NW., suite 700, Washington, DC.
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.
Effective Date
(h) This amendment becomes effective on October 10, 2003.
Issued in Renton, Washington, on August 27, 2003.
Neil D. Schalekamp,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 03-22495 Filed 9-4-03; 8:45 am]
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