[Federal Register Volume 63, Number 44 (Friday, March 6, 1998)]
[Proposed Rules]
[Pages 11169-11171]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 98-5606]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 97-NM-257-AD]
RIN 2120-AA64
Airworthiness Directives; Airbus Model A300, A300-600, and A310
Series Airplanes
AGENCY: Federal Aviation Administration, DOT.
ACTION: Notice of proposed rulemaking (NPRM).
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SUMMARY: This document proposes the adoption of a new airworthiness
directive (AD) that is applicable to all Airbus Model A300, A300-600,
and A310 series airplanes. This proposal would 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 proposal would
also require 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: Comments must be received by April 6, 1998.
ADDRESSES: Submit comments in triplicate to the Federal Aviation
Administration (FAA), Transport Airplane Directorate, ANM-114,
Attention: Rules Docket No. 97-NM-257-AD, 1601 Lind Avenue, SW.,
Renton, Washington 98055-4056. Comments may be inspected at this
location between 9:00 a.m. and 3:00 p.m., Monday through Friday, except
Federal holidays.
The service information referenced in the proposed rule may be
obtained from Airbus Industrie, 1 Rond Point Maurice Bellonte, 31707
Blagnac Cedex, France. This information may be examined at the FAA,
Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton,
Washington.
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:
Comments Invited
Interested persons are invited to participate in the making of the
proposed rule by submitting such written data, views, or arguments as
they may desire. Communications shall identify the Rules Docket number
and be submitted in triplicate to the address specified above. All
communications received on or before the closing date for comments,
specified above, will be considered before taking action on the
proposed rule. The proposals contained in this notice may be changed in
light of the comments received.
Comments are specifically invited on the overall regulatory,
economic, environmental, and energy aspects of the proposed rule. All
comments submitted will be available, both before and after the closing
date for comments, in the Rules Docket for examination by interested
persons. A report summarizing each FAA-public contact concerned with
the substance of this proposal will be filed in the Rules Docket.
Commenters wishing the FAA to acknowledge receipt of their comments
submitted in response to this notice must submit a self-addressed,
stamped postcard on which the following statement is made: ``Comments
to Docket Number 97-NM-257-AD.'' The postcard will be date stamped and
returned to the commenter.
Availability of NPRMs
Any person may obtain a copy of this NPRM by submitting a request
to the
[[Page 11170]]
FAA, Transport Airplane Directorate, ANM-114, Attention: Rules Docket
No. 97-NM-257-AD, 1601 Lind Avenue, SW., Renton, Washington 98055-4056.
Discussion
The Direction Generale de l'Aviation Civile (DGAC), which is the
airworthiness authority for France, notified the FAA that an unsafe
condition may exist on all Airbus Model A300, A300-600, and A310 series
airplanes. The DGAC advises that it has received reports of
desynchronization of the rudder servo actuators, and consequent
structural fatigue damage to the rudder servo actuator attachments due
to opposing servo actuator forces. The DGAC also advises that
desynchronization of the rudder servo actuators could affect aircraft
handling qualities, if the desynchronization is combined with an engine
failure and the loss of the related hydraulic system. Subsequent
investigation revealed that the desynchronization was caused primarily
by malfunction of the spring rods of the rudder servo actuators. Such
desynchronization, if not detected and corrected in a timely manner,
could result in reduced structural integrity of the rudder attachments
and reduced controllability of the airplane.
Explanation of Relevant Service Information
Airbus has issued Service Bulletins A300-27-0188, Revision 2 (for
Model A300 series airplanes), A300-27-6036, Revision 2 (for Model A300-
600 series airplanes), and A310-27-2082, Revision 2 (for Model A310
series airplanes); all dated October 1, 1997. These service bulletins
describe procedures for repetitive tests to detect desynchronization of
the rudder servo actuators, and adjustment or replacement of spring
rods of the rudder servo actuators, if necessary.
Airbus has also issued Service Bulletins A300-55-0044 (for Model
A300 series airplanes), A300-55-6023 (for Model A300-600 series
airplanes), and A310-55-2026 (for Model A310 series airplanes); all
dated October 22, 1996. If desynchronization beyond certain limits is
detected during accomplishment of the repetitive tests described
previously, these service bulletins describe procedures for repetitive
inspections to detect cracking of the rudder attachments, or
modification of the rudder attachments to cold expand the rivet holes.
The DGAC classified these service bulletins as mandatory and issued
French airworthiness directive 96-242-208(B) R2, dated November 19,
1997, in order to assure the continued airworthiness of these airplanes
in France.
FAA's Conclusions
These airplane models are manufactured in France and are type
certificated for operation in the United States under the provisions of
section 21.29 of the Federal Aviation Regulations (14 CFR 21.29) and
the applicable bilateral airworthiness agreement. Pursuant to this
bilateral airworthiness agreement, the DGAC has kept the FAA informed
of the situation described above. The FAA has examined the findings of
the DGAC, reviewed all available information, and determined that AD
action is necessary for products of this type design that are
certificated for operation in the United States.
Explanation of Requirements of Proposed Rule
Since an unsafe condition has been identified that is likely to
exist or develop on other airplanes of the same type design registered
in the United States, the proposed AD would require accomplishment of
the actions specified in the service bulletins described previously,
except as noted below.
Differences Between Proposed Rule and Service Bulletin
Operators should note that, although the service bulletins specify
that the manufacturer may be contacted for disposition of certain crack
conditions, this proposal would require the repair of those conditions
to be accomplished in accordance with a method approved by the FAA or
the DGAC.
Cost Impact
The FAA estimates that 103 Airbus Model A300, A300-600, and A310
series airplanes of U.S. registry would be affected by this proposed
AD, that it would 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 proposed
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 proposed 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 proposed herein would 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
proposal would not have sufficient federalism implications to warrant
the preparation of a Federalism Assessment.
For the reasons discussed above, I certify that this proposed
regulation (1) is not a ``significant regulatory action'' under
Executive Order 12866; (2) is not a ``significant rule'' under the DOT
Regulatory Policies and Procedures (44 FR 11034, February 26, 1979);
and (3) if promulgated, 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 copy of the draft
regulatory evaluation prepared for this action is contained in the
Rules Docket. A copy of it may be obtained by contacting the Rules
Docket at the location provided under the caption ADDRESSES.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Safety.
The Proposed Amendment
Accordingly, pursuant to the authority delegated to me by the
Administrator, the Federal Aviation Administration proposes to amend
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:
Airbus Industrie: 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.
[[Page 11171]]
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.
Note 4: The subject of this AD is addressed in French
airworthiness directive 96-242-208(B) R2, dated November 19, 1997.
Issued in Renton, Washington, on February 26, 1998.
Darrell M. Pederson,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 98-5606 Filed 3-5-98; 8:45 am]
BILLING CODE 4910-13-U
