[Federal Register Volume 70, Number 29 (Monday, February 14, 2005)]
[Rules and Regulations]
[Pages 7384-7386]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 05-2581]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2003-NM-16-AD; Amendment 39-13970; AD 2005-03-14]
RIN 2120-AA64


Airworthiness Directives; Airbus Model A300 B2 and B4 Series 
Airplanes

AGENCY: Federal Aviation Administration (FAA), Department of 
Transportation (DOT).

ACTION: Final rule.

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SUMMARY: This amendment supersedes an existing airworthiness directive 
(AD) that applies to all Airbus Model A300 B2 and B4 series airplanes. 
The existing AD currently requires determining the part and amendment 
number of the variable lever arm (VLA) of the rudder control system to 
verify the parts were installed using the correct standard, and 
corrective actions if necessary. For certain VLAs, this new AD requires 
repetitive inspections of the VLA and corrective action if necessary. 
This new AD also provides a terminating action for the repetitive 
inspections. Furthermore, this new AD reduces the applicability of 
affected airplanes. The actions specified by this AD are intended to 
prevent failure of both spring boxes of certain VLAs due to corrosion 
damage, which could result in loss of rudder control and consequent 
reduced controllability of the airplane. This action is intended to 
address the identified unsafe condition.

DATES: Effective March 21, 2005.
    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of March 21, 2005.
    The incorporation by reference of a certain other publication as 
listed in the regulations was approved previously by the Director of 
the Federal Register as of November 13, 2001 (66 FR 54416, October 29, 
2001).

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 the 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: The FAA proposed to amend part 39 of the 
Federal Aviation Regulations (14 CFR part 39) with an AD to supersede 
AD 2001-22-02, amendment 39-12481 (66 FR 54416, October 29, 2001). The 
existing AD applies to all Airbus Model A300 B2 and B4 series 
airplanes. The proposed AD was published as a supplemental notice of 
proposed

[[Page 7385]]

rulemaking (NPRM) in the Federal Register on October 5, 2004 (69 FR 
59557). The supplemental NPRM proposed to continue to require 
determining the part and amendment number of the variable lever arm 
(VLA) of the rudder control system to verify the parts were installed 
using the correct standard, and corrective actions if necessary. The 
supplemental NPRM also proposed to require repetitive inspections for 
damage, and replacement with a new VLA if necessary. The supplemental 
NPRM also proposed to reduce the applicability of affected airplanes 
and to mandate a terminating modification of the VLA, which would end 
the repetitive inspections.

Comments

    Interested persons have been afforded an opportunity to participate 
in the making of this amendment. Due consideration has been given to 
the comment received.

Request To Clarify Affected Part Numbers

    The commenter requests that paragraph (b) of the proposed AD be 
revised to specify that the referenced part numbers are for VLA spring 
boxes. The commenter states that the supplemental NPRM gives the 
impression of addressing a VLA assembly with P/Ns other than 418473-20 
or 418473-200. The commenter notes that the referenced P/Ns are 
actually for the VLA spring boxes, not the VLA assembly. The P/Ns of 
the VLA assemblies are ``40720 with amendments other than 6,'' as 
described in Airbus Service Bulletin A300-27-0196, Revision 01, dated 
November 13, 2002 (which was referenced in the supplemental NPRM as the 
appropriate source of service information for accomplishment of the 
inspections and corrective actions). The commenter contends that unless 
the P/Ns are clearly identified, operators may be confused regarding 
the applicability of paragraph (b) of the supplemental NPRM.
    We agree with the commenter's request to clarify the affected part 
numbers. Paragraph (b) of this AD has been revised accordingly.

Conclusion

    After careful review of the available data, including the comment 
noted above, we have determined that air safety and the public interest 
require the adoption of the rule with the change described previously. 
We have determined that this change will neither increase the economic 
burden on any operator nor increase the scope of the AD.

Cost Impact

    About 33 airplanes of U.S. registry will be affected by this AD.
    The actions that are currently required by AD 2001-22-02, and 
retained in this AD, take about 1 work hour per airplane to accomplish, 
at an average labor rate of $65 per work hour. Based on these figures, 
the cost impact of the currently required actions on U.S. operators is 
estimated to be $65 per airplane.
    The new inspection required by this AD will take about 1 work hour 
per airplane to accomplish, at an average labor rate of $65 per work 
hour. Based on these figures, the cost impact of the new inspections on 
U.S. operators is estimated to be $2,145, or $65 per airplane, per 
inspection cycle.
    The new modification required by this AD will take about 4 hours 
per airplane to accomplish, at an average labor rate of $65 per work 
hour. Required parts cost will be minimal. Based on these figures, the 
cost impact of the new modification on U.S. operators is $8,580, or 
$260 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.

Authority for This Rulemaking

    Title 49 of the United States Code specifies the FAA's authority to 
issue rules on aviation safety. Subtitle I, section 106, describes the 
authority of the FAA Administrator. Subtitle VII, Aviation Programs, 
describes in more detail the scope of the Agency's authority.
    We are issuing this rulemaking under the authority described in 
subtitle VII, part A, subpart III, section 44701, ``General 
requirements.'' Under that section, Congress charges the FAA with 
promoting safe flight of civil aircraft in air commerce by prescribing 
regulations for practices, methods, and procedures the Administrator 
finds necessary for safety in air commerce. This regulation is within 
the scope of that authority because it addresses an unsafe condition 
that is likely to exist or develop on products identified in this 
rulemaking action.

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 removing amendment 39-12481 (66 FR 
54416, October 29, 2001), and by adding a new airworthiness directive 
(AD), amendment 39-13970, to read as follows:

2005-03-14 Airbus: Docket 2003-NM-16-AD. Amendment 39-13970. 
Supersedes AD 2002-08-13, Amendment 39-12481.
    Applicability: Model A300 B2 and B4 series airplanes, 
certificated in any category; except those airplanes modified by 
Airbus Modification 12656.
    Compliance: Required as indicated, unless accomplished 
previously.

[[Page 7386]]

    To prevent failure of both spring boxes of certain VLAs due to 
corrosion damage, which could result in loss of rudder control and 
consequent reduced controllability of the airplane, accomplish the 
following:

Restatement of the Requirements of AD 2001-22-02

    (a) Within 10 days after November 13, 2001 (the effective date 
of AD 2001-22-02, amendment 39-12481): Determine the part and 
amendment numbers of the VLA of the rudder control system to verify 
the parts were installed using the correct standard, in accordance 
with Airbus All Operators Telex (AOT) A300-27A0196, dated September 
20, 2001; or in accordance with the Accomplishment Instructions of 
Airbus Service Bulletin A300-27-0196, Revision 01, dated November 
13, 2002.
    (1) If the part and amendment numbers shown are not correct, as 
specified in the AOT or the service bulletin, before further flight, 
do a detailed inspection of the VLA tie rod for damage (bent or 
ruptured rod) in accordance with the AOT or the service bulletin.
    (i) If the tie rod is damaged, replace the VLA with a new VLA in 
accordance with the AOT or the service bulletin. Such replacement 
ends the requirements of this paragraph.
    (ii) If the tie rod is not damaged, no further action is 
required by this paragraph.
    (2) If the part and amendment numbers shown are correct, no 
further action is required by this paragraph.

    Note 1: For the purposes of this AD, a detailed inspection is: 
``An intensive examination of a specific item, installation, or 
assembly to detect damage, failure, or irregularity. Available 
lighting is normally supplemented with a direct source of good 
lighting at an intensity deemed appropriate. Inspection aids such as 
mirror, magnifying lenses, etc., may be necessary. Surface cleaning 
and elaborate procedures may be required.''

New Requirements of This AD

    (b) For airplanes having VLA spring boxes with any part number 
(P/N) other than 418473-20 or 418473-200: Within 500 flight hours 
after the effective date of this AD, do a detailed inspection of the 
tie rod for damage (bent or ruptured rod), by accomplishing all of 
the applicable actions specified in the Accomplishment Instructions 
of Airbus Service Bulletin A300-27-0196, Revision 01, dated November 
13, 2002. Repeat the inspection thereafter at intervals not to 
exceed 1,000 flight hours, until paragraph (f) of this AD has been 
accomplished.

Replacement or Repair

    (c) If any damage is found to the VLA or the rudder control 
system during any inspection required by paragraph (a)(1) or (b) of 
this AD, before further flight, replace the VLA with a new VLA 
(including a follow-up test) by accomplishing all of the applicable 
actions specified in the Accomplishment Instructions of Airbus 
Service Bulletin A300-27-0196, Revision 01, dated November 13, 2002.

No Reporting/Parts Return Requirements

    (d) Although Airbus Service Bulletin A300-27-0196, Revision 01, 
dated November 13, 2002, describes procedures for submitting certain 
information to the manufacturer, and for returning certain parts to 
the manufacturer, this AD does not require those actions.

Terminating Modification

    (e) Within 24 months after the effective date of this AD: Modify 
the applicable VLA, as required by either paragraph (e)(1) or (e)(2) 
of this AD, by accomplishing all of the applicable actions specified 
in the Accomplishment Instructions of Airbus Service Bulletin A300-
27-0198, dated December 1, 2003. Accomplishing this modification 
ends the repetitive inspections required by paragraph (b) of this 
AD.
    (1) For any VLA having a spring box with P/N 418473-20 or 
418473-200: Install a new identification plate and re-identify the 
VLA.
    (2) For any VLA having a spring box with P/N 418473 or 418473-
100: Modify the spring box and re-identify the VLA.

    Note 2: Airbus Service Bulletin A300-27-0198, dated December 1, 
2003, references Goodrich Actuation Systems Service Bulletin 27-21-
1H, Revision 3, dated December 8, 2003, as an additional source of 
service information for accomplishing the modification.

Alternative Methods of Compliance

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

Incorporation by Reference

    (g) Unless otherwise specified in this AD, the actions must be 
done in accordance with the service information in Table 1 of this 
AD. Copies may be obtained from Airbus, 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 National Archives and Records 
Administration (NARA). For information on the availability of this 
material at the NARA, call (202) 741-6030, or go to http://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html.

                                  Table 1.--Material Incorporated by Reference
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        Airbus service information                   Revision level                           Date
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All Operators Telex A300-27A0196.........  Original..........................  Sept. 20, 2001.
Service Bulletin A300-27-0196, excluding   01................................  Nov. 13, 2002.
 Appendix 01.
Service Bulletin A300-27-0198............  Original..........................  Dec. 1, 2003.
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    (1) The incorporation by reference of Airbus Service Bulletin 
A300-27-0196, excluding Appendix 01, Revision 01, dated November 13, 
2002; and Airbus Service Bulletin A300-27-0198, dated December 1, 
2003; is approved by the Director of the Federal Register in 
accordance with 5 U.S.C. 552(a) and 1 CFR part 51.
    (2) The incorporation by reference of Airbus All Operators Telex 
A300-27A0196, dated September 20, 2001, was approved previously by 
the Director of the Federal Register as of November 13, 2001 (66 FR 
54416, October 29, 2001).

    Note 3: The subject of this AD is addressed in French 
airworthiness directive F-2004-091(B), dated June 23, 2004.

Effective Date

    (h) This amendment becomes effective on March 21, 2005.

    Issued in Renton, Washington, on January 31, 2005.
Kalene C. Yanamura,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 05-2581 Filed 2-11-05; 8:45 am]
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