[Federal Register Volume 63, Number 122 (Thursday, June 25, 1998)]
[Rules and Regulations]
[Pages 34580-34581]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 98-16491]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 97-NM-257-AD; Amendment 39-10624; AD 98-13-33]
RIN 2120-AA64


Airworthiness Directives; Airbus Model A300, A300-600, and A310 
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 all Airbus Model A300, A300-600, and A310 series 
airplanes, that requires repetitive tests to detect desynchronization 
of the rudder servo actuators, and adjustment or replacement of the 
spring rods of the rudder servo actuators, if necessary. For certain 
airplanes, this AD also requires repetitive inspections to detect 
cracking of the rudder attachments, and repair, if necessary; or 
modification of the rudder attachments. This proposal is prompted by 
issuance of mandatory continuing airworthiness information by a foreign 
civil airworthiness authority. The actions specified by the proposed AD 
are intended to detect and correct desynchronization of the rudder 
servo actuators, which could result in reduced structural integrity of 
the rudder attachments and reduced controllability of the airplane.

DATES: Effective July 30, 1998.
    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of July 30, 1998.

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 all Airbus Model A300, A300-600, 
and A310 series airplanes was published in the Federal Register on 
March 6, 1998 (63 FR 11169). That action proposed to require repetitive 
tests to detect desynchronization of the rudder servo actuators, and 
adjustment or replacement of the spring rods of the rudder servo 
actuators, if necessary. For certain airplanes, this AD also requires 
repetitive inspections to detect cracking of the rudder attachments, 
and repair, if necessary; or modification of the rudder attachments.
    Interested persons have been afforded an opportunity to participate 
in the making of this amendment. Due consideration has been given to 
the comments received.

Revise the Cost Information

    The Air Transport Association (ATA) of America, on behalf of one of 
its members, requests that the cost estimate presented in the proposal 
be revised. The ATA states that the data contained in the proposal does 
not take into consideration the costs required for actions that may be 
required as a result of certain inspection findings.
    The FAA does not concur that the cost estimate information should 
be revised. The economic analysis of the AD is limited only to the cost 
of actions that are actually required by the rule. It does not consider 
the costs of ``on condition'' actions, such as adjustments or 
replacement of parts if a discrepancy is detected during a required 
inspection. Such ``on condition'' actions would be required to be 
accomplished--regardless of AD direction--in order to correct an 
identified unsafe condition, and to ensure operation of that airplane 
in an airworthy condition, as required by the Federal Aviation 
Regulations.

Conclusion

    After careful review of the available data, including the comment 
noted above, the FAA has determined that air safety and the public 
interest require the adoption of the rule as proposed.

Cost Impact

    The FAA estimates that 103 Airbus Model A300, A300-600, and A310 
series airplanes of U.S. registry will be affected by this proposed AD, 
that it will take approximately 1 work hour per airplane to accomplish 
the proposed test, and that the average labor rate is $60 per work 
hour. Based on these figures, the cost impact of the AD on U.S. 
operators is estimated to be $60 per airplane, per test cycle.
    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.

Regulatory Impact

    The regulations adopted herein will not have substantial direct 
effects 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, in 
accordance with Executive Order 12612, it is determined that this final 
rule does not have sufficient federalism implications to warrant the 
preparation of a Federalism Assessment.
    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.

[[Page 34581]]

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:

98-13-33  Airbus Industrie: Amendment 39-10624. Docket 97-NM-257-AD.

    Applicability: All Model A300, A300-600, and A310 series 
airplanes, certificated in any category.

    Note 1: This AD applies to each airplane identified in the 
preceding applicability provision, regardless of whether it has been 
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 detect and correct desynchronization of the rudder servo 
actuators, which could result in reduced structural integrity of the 
rudder attachments and reduced controllability of the airplane, 
accomplish the following:
    (a) Prior to accumulation of 1,300 total flight hours, or within 
500 flight hours after the effective date of this AD, whichever 
occurs later, and thereafter at intervals not to exceed 1,300 flight 
hours: Perform a test to detect desynchronization of the rudder 
servo actuators in accordance with Airbus Service Bulletin A300-27-
0188, Revision 2, dated October 1, 1997 (for Model A300 series 
airplanes); A300-27-6036, Revision 2, dated October 1, 1997 (for 
Model A300-600 series airplanes); or A310-27-2082, Revision 2, dated 
October 1, 1997 (for Model A310 series airplanes); as applicable. If 
any desynchronization (rudder movement) is detected, prior to 
further flight, either adjust or replace, as applicable, the spring 
rod of the affected rudder servo actuator in accordance with the 
applicable service bulletin.

    Note 2: A test to detect desynchronization of the rudder servo 
actuators, if accomplished prior to the effective date of this AD in 
accordance with Airbus Service Bulletin A300-27-0188, dated October 
24, 1996, or Revision 1, dated November 5, 1996 (for Model A300 
series airplanes); A300-27-6036, dated October 24, 1996, or Revision 
1, dated November 5, 1996 (for Model A300-600 series airplanes); or 
A310-27-2082, dated October 24, 1996, or Revision 1, dated November 
5, 1996 (for Model A310 series airplanes); is considered acceptable 
for compliance with the initial test required by paragraph (a) of 
this AD.

    (b) Except as provided by paragraph (c) of this AD, if any 
desynchronization (rudder movement) greater than the limit specified 
in Paragraph B of the Accomplishment Instructions of the applicable 
service bulletin is detected during any test required by paragraph 
(a), prior to further flight, accomplish either paragraph (b)(1) or 
(b)(2) of this AD, in accordance with Airbus Service Bulletin A300-
55-0044, dated October 22, 1996 (for Model A300 series airplanes); 
A300-55-6023, dated October 22, 1996 (for Model A300-600 series 
airplanes); or A310-55-2026, dated October 22, 1996 (for Model A310 
series airplanes); as applicable.
    (1) Conduct a visual inspection, high frequency eddy current 
inspection, or ultrasonic inspection, as applicable, to detect 
cracking of the rudder attachments; and repeat the inspection 
thereafter, as applicable, at the intervals specified in the 
applicable service bulletin. Or
    (2) Modify the rudder attachments to cold expand the rivet 
holes.
    (c) If any crack is found during any inspection or modification 
required by paragraph (b) of this AD, and the applicable service 
bulletin specifies to contact Airbus for an appropriate action: 
Prior to further flight, repair the affected structure in accordance 
with a method approved by the Manager, International Branch, ANM-
116, FAA, Transport Airplane Directorate, or in accordance with a 
method approved by the Direction Generale de l'Aviation Civile 
(DGAC), which is the airworthiness authority for France.
    (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. 
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.

    (e) Special flight permits may be issued in accordance with 
sections 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.
    (f) Except as provided in paragraph (c) of this AD, the 
repetitive inspections and repair shall be done in accordance with 
Airbus Service Bulletin A300-55-0044, dated October 22, 1996; Airbus 
Service Bulletin A300-55-6023, dated October 22, 1996; or Airbus 
Service Bulletin A310-55-2026, dated October 22, 1996, as 
applicable. Testing for desynchronization shall be done in 
accordance with Airbus Service Bulletin A300-27-0188, Revision 2, 
dated October 1, 1997; Airbus Service Bulletin A300-27-6036, 
Revision 2, dated October 1, 1997; or Airbus Service Bulletin A310-
27-2082, Revision 2, dated October 1, 1997, 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 directive 96-242-208(B) R2, dated November 19, 1997.

    (g) This amendment becomes effective on July 30, 1998.

    Issued in Renton, Washington, on June 16, 1998.
Darrell M. Pederson,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 98-16491 Filed 6-24-98; 8:45 am]
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