AD 98-13-33 SUPERSEDED

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.

Final rule.

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 andcorrect 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 G n rale 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 NorthCapitol 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.

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 estimatepresented 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.

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.
39.13 [Amended]
2. Section 39.13 is amended by adding the following new airworthiness directive:

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.

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.