Airworthiness directives: Airbus,

[Federal Register: November 4, 1999 (Volume 64, Number 213)]

[Proposed Rules]

[Page 60138-60140]

From the Federal Register Online via GPO Access [wais.access.gpo.gov]

[DOCID:fr04no99-21]

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 99-NM-247-AD]

RIN 2120-AA64

Airworthiness Directives; Airbus Model A300, A310, and A300-600 Series Airplanes

AGENCY: Federal Aviation Administration, DOT.

ACTION: Notice of proposed rulemaking (NPRM).

SUMMARY: This document proposes the adoption of a new airworthiness directive (AD) that is applicable to certain Airbus Model A300, A310, and A300-600 series airplanes. This proposal would require either replacement of the spring rod assemblies of the rudder servo controls with improved spring rod assemblies; or modification of the existing spring rod assemblies. For certain airplanes, this proposed AD would require a one-time visual inspection to determine whether certain parts of the spring rod assemblies of the rudder servo controls are installed; and corrective actions, if necessary. 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 prevent corrosion of the spring rod assemblies of the rudder servo controls, which could result in the jamming of the rudder servo controls and consequent reduced controllability of the airplane.

DATES: Comments must be received by December 6, 1999.

ADDRESSES: Submit comments in triplicate to the Federal Aviation Administration (FAA), Transport Airplane Directorate, ANM-114, Attention: Rules Docket No. 99-NM-247-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 filedin 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 99-NM-247-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 FAA, Transport Airplane Directorate, ANM-114, Attention: Rules Docket No. 99-NM-247-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 certain Airbus Model A300, A310, and A300-600 series airplanes. The DGAC advises that it has received reports of jammed spring rods of the rudder servo controls. Investigation revealed that the internal mechanism parts of the spring rod assemblies of the rudder servo controls were heavily corroded and the drain holes were clogged. Such corrosion, if not corrected, could result in the jamming of the rudder servo controls

[[Page 60139]]

and consequent reduced controllability of the airplane.

Explanation of Relevant Service Information

The manufacturer has issued Airbus Service Bulletins A300-27-182, Revision 2 (for Model A300 series airplanes); A310-27-2065, Revision 2 (for Model A310 series airplanes); and A300-27-6023, Revision 2 (for Model A300-600 series airplanes); each dated June 30, 1999. These service bulletins describe procedures for either replacement of the spring rod assemblies of rudder servo controls with improved spring rod assemblies, or modification of the existing spring rod assemblies of the rudder servo controls. The modification involves enlarging the drain holes of the spring rod assembly housing, replacing the retainers, and removing the lubrication between the retainer spring and rod body. If a modified spring rod assembly is installed, the modification also includes re-identification of the modified spring rod assembly to the correct part number.

For certain airplanes, the service bulletins describe procedures for a one-time visual inspection to determine whether certain part numbers of the spring rod assemblies of the rudder servo controls are installed; and corrective actions, if necessary. The corrective actions involve re-identifying all spring rod assemblies to the part number specified in the service bulletin.

Accomplishment of the actions specified in the service bulletins is intended to adequately address the identified unsafe condition. The DGAC classified these service bulletins as mandatory and issued French airworthiness directive 1999-240-288(B), dated June 30, 1999, 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 bulletin described previously.

Cost Impact

The FAA estimates that 156 airplanes of U.S. registry would be affected by this proposed AD.

If an operator elects to replace the spring rod assemblies: It would take approximately 4 work hours per airplane to accomplish the proposed replacement, at an average labor rate of $60 per work hour. Required parts would cost approximately $3,720 per airplane. Based on these figures, the cost impact of the modification proposed by this AD on U.S. operators is estimated to be $3,960 per airplane.

If an operator elects to modify the spring rod assemblies: It would take approximately 7 work hours per airplane to accomplish the proposed modification, at an average labor rate of $60 per work hour. Required parts would cost approximately $294 per airplane. Based on these figures, the cost impact of the proposed AD on U.S. operators is estimated to be $714 per airplane.

If an operator is required to accomplish the one-time inspection: It would take approximately 1 work hour per airplane to accomplish that proposed inspection, at an average labor rate of $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.

The cost impact figures discussed above are 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 99-NM-247-AD.

    Applicability: Model A300, A310, and A300-600 series airplanes except those airplanes on which Airbus Modification 10438 has been installed, or Airbus Service Bulletins A300-27-0182, Revision 2, A300-27-6023, Revision 2, or A300-27-2065, Revision 2, each dated June 30, 1999, has been accomplished; certificated in any category.

    Note 1: This AD applies to each airplane identified in the preceding applicability provision, regardless of whether it has been otherwise 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 prevent corrosion of the spring rod assemblies of the rudder servo controls,

    [[Page 60140]]

    which could result in the jamming of the rudder servo controls and consequent reduced controllability of the airplane, accomplish the following:

    (a) For airplanes on which the spring rod assemblies of the rudder servo controls have not been modified in accordance with Airbus Service Bulletin A300-27-182, dated March 16, 1995, or Revision 1, dated November 21, 1996 (for Model A300 series airplanes); A310-27-2065, dated March 16, 1995, or Revision 1, dated March 10, 1997 (for Model A310 series airplanes); or A300-27-6023, dated March 16, 1995, or Revision 1, dated March 10, 1997 (for Model A300-600 series airplanes); as applicable; as of the effective date of this AD: Within 1 year after the effective date of this AD, accomplish the actions specified in either paragraph (a)(1) or (a)(2) in accordance with Airbus Service Bulletin A300-27-182, Revision 2 (for Model A300 series airplanes); or A310-27-2065, Revision 2 (for Model A310 series airplanes); or A300-27-6023, Revision 2 (for Model A300-600 series airplanes); each dated June 30, 1999; as applicable.

    (1) Replace the spring rod assemblies with improved spring rod assemblies; or

    (2) Modify the existing spring rod assemblies and re-identify all modified spring rod assemblies.

    (b) For airplanes on which the spring rod assemblies of the rudder servo controls have been modified in accordance with Airbus Service Bulletin A300-27-182, dated March 16, 1995, or Revision 1, dated November 21, 1996 (for Model A300 series airplanes); or A310- 27-2065, dated March 16, 1995, or Revision 1, dated March 10, 1997 (for Model A310 series airplanes); or A300-27-6023, dated March 16, 1995, or Revision 1, dated March 10, 1997 (for Model A300-600 series airplanes); as applicable; as of the effective date of this AD: Within 1 year after the effective date of this AD, perform a one- time visual inspection to verify that all spring rod assemblies of the rudder servo controls have the same part numbers, in accordance with Airbus Service Bulletin A300-27-182, Revision 2 (for Model A300 series airplanes); or A310-27-2065, Revision 2 (for Model A310 series airplanes); or A300-27-6023, Revision 2 (for Model A300-600 series airplanes); each dated June 30, 1999; as applicable.

    (1) If all three spring rod assemblies have either P/N A2727086500400 or A2727086500600, no further action is required by this AD.

    (2) If any spring rod assembly has a part number other than P/N A2727086500400 or A2727086500600, prior to further flight, re- identify all spring rod assemblies to the part number specified in the applicable service bulletin, in accordance with the applicable service bulletin.

    (c) As of the effective date of this AD, no person shall install on any airplane a spring rod assembly having P/N A2727086500200.

    Alternative Methods of Compliance

    (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, FAA, Transport Airplane Directorate. 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 2: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the International Branch, ANM-116.

    Special Flight Permits

    (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 3: The subject of this AD is addressed in French airworthiness directive 1999-240-288(B), dated June 30, 1999.

    Issued in Renton, Washington, on October 29, 1999. D.L. Riggin, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service.

    [FR Doc. 99-28847Filed11-3-99; 8:45 am]

    BILLING CODE 4910-13-U

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