Airworthiness Directives; Airbus Model A300, A310, and A300-600 Series Airplanes

[Federal Register Volume 65, Number 23 (Thursday, February 3, 2000)]
[Rules and Regulations]
[Pages 5243-5245]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 00-2083]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 99-NM-247-AD; Amendment 39-11542; AD 2000-02-24]
RIN 2120-AA64


Airworthiness Directives; Airbus Model A300, A310, and A300-600 
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 A300, A310, and A300-600 series 
airplanes, that requires either replacement of the spring rod 
assemblies of the rudder servo controls with improved spring rod 
assemblies; or modification of the existing spring rod assemblies. For 
certain airplanes, this amendment requires a one-time visual inspection 
to determine whether certain parts of the spring rod assemblies of the 
rudder servo controls are installed; and corrective actions, if 
necessary. This amendment is prompted by issuance of mandatory 
continuing airworthiness information by a foreign civil airworthiness 
authority. The actions specified by this AD are intended to prevent 
corrosion of the spring rod assemblies of the rudder servo controls, 
which could result in the jamming of the rudder servo controls and 
consequent reduced controllability of the airplane.

DATES: Effective March 9, 2000.
    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of March 9, 2000.

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: Norman B. Martenson, Manager, 
International Branch, ANM-116, FAA, Transport Airplane Directorate, 
1601 Lind Avenue, SW., Renton, Washington 98055-4056; telephone (425) 
227-2110; 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 A300, A310, 
and A300-600 series airplanes was published in the Federal Register on 
November 4, 1999 (64 FR 60138). That action proposed to require either 
replacement of the spring rod assemblies of the rudder servo controls 
with improved spring rod assemblies; or modification of the existing 
spring rod assemblies. For certain airplanes, that action proposed to 
require a one-time visual inspection to determine whether certain parts 
of

[[Page 5244]]

the spring rod assemblies of the rudder servo controls are installed; 
and corrective actions, if necessary.
    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.

French Airworthiness Directive Revision

    Since issuance of the proposed AD, the Direction Gonorale de 
l'Aviation Civile (DGAC), which is the airworthiness authority for 
France, has revised the corresponding French airworthiness directive. 
The DGAC issued 1999-240-288(B) R1, dated December 15, 1999, to provide 
operators with an exhaustive list of appropriate part numbers (P/N) for 
rudder servo control input spring rod assemblies. The FAA has reviewed 
this information and has determined that paragraphs (b)(1) and (b)(2) 
of the proposed AD should be revised to include an additional part 
number. These paragraphs specify acceptable spring rod assemblies as 
those having either P/N A2727086500400 or A2727086500600. However, P/N 
A2727114900000 also is acceptable for installation. Paragraphs (b)(1) 
and (b)(2) of the AD have been revised to include this P/N.

Conclusion

    After careful review of the available data, the FAA has determined 
that air safety and the public interest require the adoption of the 
rule with the change described previously. The FAA has determined that 
this change will neither increase the economic burden on any operator 
nor increase the scope of the AD.

Cost Impact

    The FAA estimates that 156 airplanes of U.S. registry will be 
affected by this AD.
    If an operator elects to replace the spring rod assemblies: It will 
take approximately 4 work hours per airplane to accomplish the 
replacement, at an average labor rate of $60 per work hour. Required 
parts will cost approximately $3,720 per airplane. Based on these 
figures, the cost impact of the replacement on U.S. operators is 
estimated to be $3,960 per airplane.
    If an operator elects to modify the spring rod assemblies: It will 
take approximately 7 work hours per airplane to accomplish the 
modification, at an average labor rate of $60 per work hour. Required 
parts will cost approximately $294 per airplane. Based on these 
figures, the cost impact of the modification on U.S. operators is 
estimated to be $714 per airplane.
    If an operator is required to accomplish the one-time inspection: 
It will take approximately 1 work hour per airplane to accomplish that 
inspection, at an average labor rate of $60 per work hour. Based on 
these figures, the cost impact of the inspection on U.S. operators is 
estimated to be $60 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.

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

    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

    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:

2000-02-24  Airbus Industrie: Amendment 39-11542. Docket 99-NM-247-
AD.

    Applicability: Model A300, A310, and A300-600 series airplanes; 
certificated in any category; except those airplanes on which Airbus 
Modification 10438 has been installed, or on which Airbus Service 
Bulletin A300-27-0182, Revision 2, A300-27-6023, Revision 2, or 
A300-27-2065, Revision 2, each dated June 30, 1999, has been 
accomplished.


    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 (d) 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 corrosion of the spring rod assemblies of the rudder 
servo controls, which could result in the jamming of the rudder 
servo controls and consequent reduced controllability of the 
airplane, accomplish the following:
    (a) For airplanes on which the spring rod assemblies of the 
rudder servo controls have not been modified in accordance with 
Airbus Service Bulletin A300-27-182, dated March 16, 1995, or 
Revision 1, dated November 21, 1996 (for Model A300 series 
airplanes); A310-27-2065, dated March 16, 1995, or Revision 1, dated 
March 10, 1997 (for Model A310 series airplanes); or A300-27-6023, 
dated March 16, 1995, or Revision 1, dated March 10, 1997 (for Model 
A300-600 series airplanes); as applicable; as of the effective date 
of this AD: Within 1 year after the effective date of this AD, 
accomplish the actions specified in either paragraph (a)(1) or 
(a)(2) in accordance with Airbus Service Bulletin A300-27-182, 
Revision 2 (for Model A300 series airplanes); or A310-27-2065, 
Revision 2 (for Model A310 series airplanes); or A300-27-6023, 
Revision 2 (for Model A300-600 series airplanes); each dated June 
30, 1999; as applicable.
    (1) Replace the spring rod assemblies with improved spring rod 
assemblies; or

[[Page 5245]]

    (2) Modify the existing spring rod assemblies and re-identify 
all modified spring rod assemblies.
    (b) For airplanes on which the spring rod assemblies of the 
rudder servo controls have been modified in accordance with Airbus 
Service Bulletin A300-27-182, dated March 16, 1995, or Revision 1, 
dated November 21, 1996 (for Model A300 series airplanes); or A310-
27-2065, dated March 16, 1995, or Revision 1, dated March 10, 1997 
(for Model A310 series airplanes); or A300-27-6023, dated March 16, 
1995, or Revision 1, dated March 10, 1997 (for Model A300-600 series 
airplanes); as applicable; as of the effective date of this AD: 
Within 1 year after the effective date of this AD, perform a one-
time visual inspection to verify that all spring rod assemblies of 
the rudder servo controls have the same part numbers, in accordance 
with Airbus Service Bulletin A300-27-182, Revision 2 (for Model A300 
series airplanes); or A310-27-2065, Revision 2 (for Model A310 
series airplanes); or A300-27-6023, Revision 2 (for Model A300-600 
series airplanes); each dated June 30, 1999; as applicable.
    (1) If all three spring rod assemblies have P/N A2727086500400, 
A2727086500600, or A2727114900000, no further action is required by 
this AD.
    (2) If any spring rod assembly has a P/N other than P/N 
A2727086500400, A2727086500600, or A2727114900000, prior to further 
flight, re-identify all spring rod assemblies to the P/N specified 
in the applicable service bulletin, in accordance with the 
applicable service bulletin.
    (c) As of the effective date of this AD, no person shall install 
on any airplane a spring rod assembly having P/N A2727086500200.

Alternative Methods of Compliance

    (d) 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, FAA, 
Transport Airplane Directorate. 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 2:  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

    (e) Special flight permits may be issued in accordance with 
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

    (f) The actions shall be done in accordance with Airbus Service 
Bulletin A300-27-182, Revision 2, dated June 30, 1999; Airbus 
Service Bulletin A310-27-2065, Revision 2, dated June 30, 1999; or 
Airbus Service Bulletin A300-27-6023, Revision 2, dated June 30, 
1999; as applicable. Airbus Service Bulletin A300-27-6023, Revision 
2, dated June 30, 1999, contains the following list of effective 
pages:

------------------------------------------------------------------------
                                  Date shown on
    Revision level page No.            page            Shown on page
------------------------------------------------------------------------
1-6, 8-12, 17.................  2................  June 30, 1999.
7, 13-16......................  Original.........  March 16, 1995.
------------------------------------------------------------------------

    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 3: The subject of this AD is addressed in French 
airworthiness directives 1999-240-288(B), dated June 30, 1999, and 
1999-240-288(B) R1, dated December 15, 1999.

    (g) This amendment becomes effective on March 9, 2000.

    Issued in Renton, Washington, on January 25, 2000.
Donald L. Riggin,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 00-2083 Filed 2-2-00; 8:45 am]
BILLING CODE 4910-13-U

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