[Federal Register Volume 69, Number 216 (Tuesday, November 9, 2004)]
[Rules and Regulations]
[Pages 64836-64839]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 04-24625]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2002-NM-246-AD; Amendment 39-13854; AD 2004-22-26]
RIN 2120-AA64


Airworthiness Directives; Airbus Model A330, A340-200, and A340-
300 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, A340-200, and A340-300 series 
airplanes. This AD requires repetitive inspections for evidence of 
corrosion and sheared attachment bolts of the sensor struts at flap 
track 4 on the left and right sides of the airplane; related

[[Page 64837]]

investigative and corrective actions as necessary; and a terminating 
action for the repetitive inspections, by requiring the eventual 
replacement of all sensor struts with new, improved sensor struts that 
are less sensitive to corrosion. The actions specified by this AD are 
intended to prevent loss of the sensor strut function, resulting in the 
inability to detect flap drive disconnection at flap track stations 4 
and 5, which could lead to separation of the outboard flap from the 
airplane, and consequent reduced controllability of the airplane. This 
action is intended to address the identified unsafe condition.

DATES: Effective December 14, 2004.
    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of December 14, 2004.

ADDRESSES: The service information referenced in this AD may be 
obtained from Airbus, 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 National Archives 
and Records Administration (NARA). For information on the availability 
of this material at NARA, call (202) 741-6030, or go to: http://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html.

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: 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, A340-
200, and A340-300 series airplanes, was published as a supplemental 
notice of proposed rulemaking (NPRM) in the Federal Register on 
September 2, 2004 (69 FR 53658). That action proposed to require 
repetitive inspections for evidence of corrosion and sheared attachment 
bolts of the sensor struts at flap track 4 on the left and right sides 
of the airplane; related investigative and corrective actions as 
necessary; and a terminating action for the repetitive inspections, by 
requiring the eventual replacement of all sensor struts with new, 
improved sensor struts that are less sensitive to corrosion. That 
action also proposed to change the threshold for the initial inspection 
and reduce the compliance time for the terminating action of the 
original NPRM.

Comments

    Interested persons have been afforded an opportunity to participate 
in the making of this amendment. No comments were submitted in response 
to the proposal or the FAA's determination of the cost to the public.

Change to This Final Rule

    The date of the original issue of Airbus Service Bulletin A330-27-
3091 has been corrected in paragraph (e) of this AD. The date on the 
actual original issue of the service bulletin is February 6, 2002. The 
revision history in Revisions 01, 02, and 03 of the service bulletin, 
and the dates on those revisions, indicate that the date of the 
original issue of the service bulletin is February 2, 2002. The wrong 
date was inadvertently cited in the NPRM and supplemental NPRM.

Conclusion

    We have determined that air safety and the public interest require 
the adoption of the rule with the change described previously. This 
change will neither increase the economic burden on any operator not 
increase the scope of the AD.

Cost Impact

    We estimate that 9 Airbus Model A330 airplanes of U.S. registry 
will be affected by this AD.
    It will take 1 work hour per airplane to accomplish the repetitive 
inspections, at an average labor rate of $65 per work hour. Based on 
these figures, the cost impact of the inspections on U.S. operators is 
estimated to be $585, or $65 per airplane, per inspection cycle.
    If required, it will take approximately 3 work hours per airplane 
to accomplish the replacement of discrepant sensor struts and 
attachment bolts, at an average labor rate of $65 per work hour. The 
cost for required parts will be nominal. Based on these figures, the 
cost impact of the replacement of sensor struts will be $195 per 
airplane.
    It will take approximately 2 work hours per airplane to accomplish 
the installation of the new, improved sensor struts, at an average 
labor rate of $65 per work hour. The cost of required parts will be 
$8,400. Based on these figures, the cost impact of the installation on 
U.S. operators is estimated to be $76,770, or $8,530 per airplane.
    The cost impact figures discussed above are 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 will take approximately 1 
work hour per airplane to accomplish the inspection, at an average 
labor rate of $65 per work hour. Based on these figures, the cost 
impact of the inspection for Model A340 operators will be $65 per 
airplane, per inspection cycle.
    Should an Airbus Model A340 series airplane be imported and placed 
on the U.S. Register in the future and have affected sensor struts and 
attachment bolts replaced, it will take approximately 3 work hours, at 
an average labor rate of $65 per work hour. The cost for required parts 
will be nominal. Based on these figures, the cost impact of the 
replacement of sensor struts for Model A340 operators will be $195 per 
airplane.
    Should an Airbus Model A340 series airplane be imported and placed 
on the U.S. Register in the future and have new, improved sensor struts 
installed, it would take approximately 2 work hours, at an average 
labor rate of $65 per work hour. The cost for required parts will be 
$8,400. Based on these figures, the cost impact of the installation for 
Model A340 operators would be $8,530 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

[[Page 64838]]

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:

2004-22-26 Airbus: Amendment 39-13854. Docket 2002-NM-246-AD.

    Applicability: Model A330 series airplanes; and Model A340-200 
and A340-300 series airplanes; certificated in any category; except 
those airplanes on which Airbus Modification 48579 was incorporated 
in production.
    Compliance: Required as indicated, unless accomplished 
previously.
    To prevent loss of the sensor strut function, resulting in the 
inability to detect flap drive disconnection at flap track stations 
4 and 5, which could lead to separation of the outboard flap from 
the airplane, and consequent reduced controllability of the 
airplane; accomplish the following:

Inspection

    (a) At the latest of the times specified in paragraphs (a)(1), 
(a)(2), and (a)(3) of this AD: Do an inspection, by applying hand 
force to the piston of the sensor struts and moving the sensor 
struts longitudinally, for evidence of corrosion in the sensor 
struts at flap track 4, on the left and right sides of the airplane, 
by doing all the applicable actions specified in the Accomplishment 
Instructions of Airbus Service Bulletin A330-27-3091, Revision 03 
(for Model A330 series airplanes); or Service Bulletin A340-27-4097, 
Revision 03 (for Model A340-200 and -300 series airplanes); both 
dated January 16, 2004; as applicable. If the longitudinal travel 
range is 60.0 millimeters (2.36 inches) or more: Repeat the 
inspection thereafter at intervals not to exceed 18 months, until 
the requirements of paragraph (d) of this AD are accomplished.
    (1) Within 18 months since the date of issuance of the original 
Airworthiness Certificate or the date of issuance of the original 
Export Certificate of Airworthiness, whichever occurs first.
    (2) Within 2,800 flight hours after the effective date of this 
AD.
    (3) Within 6 months after the effective date of this AD.

Related Investigative and Corrective Actions

    (b) If the result of the inspection required by paragraph (a) of 
this AD is a longitudinal travel range of less than 60.0 mm (2.36 
inches): Before further flight, remove all affected sensor struts, 
and measure the axial force of any affected sensor struts, by doing 
all of the applicable actions per the Accomplishment Instructions of 
Airbus Service Bulletin A330-27-3091, Revision 03 (for Model A330 
series airplanes); or Service Bulletin A340-27-4097, Revision 03 
(for Model A340-200 and -300 series airplanes); both dated January 
16, 2004; as applicable.
    (1) If the axial force F is less than or equal to 50 daN (112.41 
lbf.): Clean and re-install the sensor struts per the Accomplishment 
Instructions of the applicable service bulletin. Repeat the 
inspection required by paragraph (a) of this AD thereafter at 
intervals not to exceed 18 months, until the requirements of 
paragraph (d) of this AD are accomplished.
    (2) If the axial force F is more than 50 daN (112.41 lbf.): 
Before further flight, do a detailed inspection for cracking and/or 
deformation of the adjacent structure and attachment parts per the 
Accomplishment Instructions of the applicable service bulletin.
    (i) If no cracking and/or deformation is found: Re-install the 
sensor struts and within 25 flight cycles after the inspection 
required by paragraph (b) of this AD, replace the sensor struts and 
attachment bolts per the Accomplishment Instructions of the 
applicable service bulletin. Repeat the inspection required by 
paragraph (a) of this AD thereafter at intervals not to exceed 18 
months, until the requirements of paragraph (d) of this AD are 
accomplished.
    (ii) If any cracking and/or deformation is found: Before further 
flight, repair any cracked or deformed structure and attachment 
parts 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 (or its 
delegated agent); and replace the sensor struts and attachment bolts 
per the Accomplishment Instructions of the applicable service 
bulletin. Repeat the inspection required by paragraph (a) of this AD 
thereafter at intervals not to exceed 18 months, until the 
requirements of paragraph (d) of this AD are accomplished.

    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.''

Concurrent Requirements

    (c) The actions required by paragraphs (a) and (b) of this AD 
must be done before or concurrently with the requirements of 
paragraph (d) of this AD. Replacement of any sensor strut with a 
sensor strut having part number (P/N) F5757492600000, during 
accomplishment of paragraph (b) of this AD, is acceptable for 
compliance with paragraph (d) of this AD, for that strut.

Terminating Action

    (d) Within 30 months after the effective date of this AD: 
Replace all existing sensor struts with new, improved sensor struts 
having P/N F5757492600000 per the Accomplishment Instructions of 
Airbus Service Bulletin A330-27-3092 (for Model A330 series 
airplanes); or Service Bulletin A340-27-4098 (for Model A340-200 and 
-300 series airplanes); both dated February 14, 2003; as applicable. 
Accomplishment of this replacement constitutes terminating action 
for the repetitive inspections required by paragraphs (a) and (b) of 
this AD.

Actions Done per Previous Issue of Service Bulletins

    (e) Accomplishment of the specified actions before the effective 
date of this AD per Airbus Service Bulletin A330-27-3091, dated 
February 6, 2002, Revision 01, dated May 17, 2002, or Revision 02, 
dated September 5, 2002; or A340-27-4097, dated February 6, 2002, 
Revision 01, dated May 17, 2002, or Revision 02, dated September 5, 
2002; as applicable; is considered acceptable for compliance with 
the applicable requirements of paragraphs (a) and (b) of this AD.

Submission of Information Not Required

    (f) Although the service bulletins specify to send inspection 
results to the manufacturer, that action is not required by this AD.

Alternative Methods of Compliance

    (g) In accordance with 14 CFR 39.19, the Manager, International 
Branch, ANM-116, FAA, Transport Airplane Directorate, is authorized 
to approve alternative methods of compliance for this AD.

Incorporation by Reference

    (h) Unless otherwise specified in this AD, the actions shall be 
done in accordance with the applicable Airbus service bulletins 
listed in Table 1 of this AD.

          Table 1.--Service Bulletins Incorporated by Reference
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     Airbus service bulletin       Revision level           Date
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A330-27-3091....................  03.............  Jan. 16, 2004.
A330-27-3092....................  Original.......  Feb. 14, 2003.
A340-27-4097....................  03.............  Jan. 16, 2004.
A340-27-4098....................  Original.......  Feb. 14, 2003.
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    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, 1 Rond Point Maurice 
Bellonte, 31707 Blagnac Cedex, France. Copies may be

[[Page 64839]]

inspected at the FAA, Transport Airplane Directorate, 1601 Lind 
Avenue, SW., Renton, Washington; or at the National Archives and 
Records Administration (NARA). For information on the availability 
of this material at NARA, call (202) 741-6030, or go to: http://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html.

    Note 2: The subject of this AD is addressed in French 
airworthiness directives F-2003-425 and F-2003-426, both dated 
December 10, 2003.

Effective Date

    (i) This amendment becomes effective on December 14, 2004.

    Issued in Renton, Washington, on October 26, 2004.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 04-24625 Filed 11-8-04; 8:45 am]
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