[Federal Register Volume 68, Number 172 (Friday, September 5, 2003)]
[Rules and Regulations]
[Pages 52688-52690]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 03-22495]


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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

[[Page 52689]]

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

[[Page 52690]]

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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