[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]
BILLING CODE 4910-13-U
