[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