AD 98-21-32

This amendment supersedes an existing airworthiness directive (AD), applicable to all Airbus Model A300, A310, and A300-600 series airplanes, that currently requires performing a ram air turbine (RAT) extension test; removing and disassembling the RAT uplock mechanism; performing an inspection to detect corrosion of the RAT uplock mechanism, and replacement with a new assembly, if necessary; and cleaning all the parts of the RAT control shaft and its bearing component parts. This amendment requires modification of the RAT unlocking control unit, which constitutes terminating action for the repetitive tests and inspections. This amendment also limits the applicability of the existing AD. This amendment is prompted by issuance of mandatory continuing airworthiness information by a foreign civil airworthiness authority. The actions specified by this AD are intended to prevent corrosion of the RAT uplock pin/shaft and needle, which could result in failure of the RAT to deployand consequent loss of emergency hydraulic power to the flight controls in the event that power is lost in both engines.

Final rule.

98-21-32 AIRBUS INDUSTRIE: Amendment 39-10840. Docket 98-NM-187-AD. Supersedes AD 97-22-06, Amendment 39-10177.

Applicability: Model A300, A310, and A300-600 series airplanes on which Airbus Modification 11527 has not 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 ram air turbine (RAT) uplock pin/shaft and needle, which could result in failure of the RAT to deploy and consequent loss of emergency hydraulic power to the flight controls in the event that power is lost in both engines, accomplish the following:

RESTATEMENT OF THE REQUIREMENTS OF AD 97-22-06:

(a) Within 30 months since the date of manufacture, or within 3 months after December 2, 1997 (the effective date of AD 97-22-06, amendment 39-10177), whichever occurs later, accomplish the requirements of paragraphs (a)(1) and (a)(2) of this AD. Thereafter, repeat these actions at intervals not to exceed 30 months.

(1) Perform a RAT extension test on the ground, in accordance with the procedures specified in the Airplane Maintenance Manual.

(2) Disassemble and remove the uplock mechanism of the RAT and perform a visual inspection of the uplock mechanism to detect corrosion, in accordance with Airbus Service Bulletin A300-29-0108, dated April 1, 1996 (for Model A300 series airplanes); A310-29-2076, dated April 1, 1996 (for Model A310 series airplanes); or A300-29-6037, dated April 1, 1996 (for Model A300-600 series airplanes); as applicable.

NOTE 2: For the purposes of this AD, the RAT uplock mechanism includes both the lever assembly and uplock unit.

(i) If no corrosion is detected: Prior to further flight, clean and lubricate the uplock mechanism and its associated parts, reinstall the assembly, and perform a retraction/extension/retraction of the RAT, in accordance with the applicable service bulletin.

(ii) If any corrosion is detected in any part of the uplock mechanism, prior to further flight, accomplish either paragraph (a)(2)(ii)(A) or (a)(2)(ii)(B) of this AD in accordance with the applicable service bulletin.

(A) Replace the uplock mechanism with a new part and perform a retraction/extension/retraction of the RAT, in accordance with the applicable service bulletin. Or

(B) Clean and lubricate the uplock mechanism and its associated parts. Within 30 days following accomplishment of this cleaning and lubrication, replace the uplock mechanism with a new part and perform a retraction/extension/retraction of the RAT.

(b) Initial accomplishment of the actions required by paragraph (a) of this AD that have been performed in accordance with Airbus All Operator Telex 29-16, Revision 01, dated January 10, 1996, is considered acceptable for compliance with the initial RAT extension test and an initial visual inspection as required by paragraph (a) of this AD. However, the first repetitive inspection, as required by paragraph (a) of this AD, must be performed within 30 months after that RAT extension test and visual inspection were conducted, and repeated thereafter at intervals not to exceed 30 months.

NEW REQUIREMENTS OF THIS AD:

(c) Within 30 monthsafter the effective date of this AD, modify the RAT unlocking control unit in accordance with Airbus Service Bulletin A300-29-0109 (for Model A300 series airplanes); A310-29-2077 (for Model A310 series airplanes); or A300-29-6038 (for Model A300- 600 series airplanes); all dated January 27, 1997; as applicable. Accomplishment of this modification constitutes terminating action for the repetitive test and inspection requirements of this AD.

(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 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 by paragraph (a)(1) of this AD, the actions shall be done in accordance with Airbus Service Bulletin A300-29-0108, dated April 1, 1996; Airbus Service Bulletin A310-29-2076, dated April 1, 1996; Airbus Service Bulletin A300-29-6037, dated April 1, 1996; Airbus Service Bulletin A300-29-0109, dated January 27, 1997; Airbus Service Bulletin A310-29-2077, dated January 27, 1997; and Airbus Service Bulletin A300-29-6038; dated January 27, 1997; as applicable.

(1) The incorporation by reference of Airbus Service Bulletin A300-29- 0109, dated January 27, 1997; Airbus Service Bulletin A310-29-2077, dated January 27, 1997; and Airbus Service Bulletin A300-29-6038; dated January 27, 1997; is approved by the Director of the Federal Register in accordance with 5 U.S.C. 552(a) and 1 CFR part 51.

(2) The incorporation by reference of Airbus Service Bulletin A300-29- 0108, dated April 1, 1996; Airbus Service Bulletin A310-29-2076, dated April 1, 1996; and Airbus Service Bulletin A300-29-6037, dated April 1, 1996; was approved previously by the Director of the Federal Register as of December 2, 1997 (62 FR 55726, October 28, 1997).

(3) 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 95-163- 182(B)R3, dated May 7, 1997.

(g) This amendment becomes effective on November 20, 1998.

A proposal to amend part 39 of the Federal Aviation Regulations (14 CFR part 39) by superseding AD 97-22-06, amendment 39-10177 (62 FR 55726, October 28, 1997), which is applicable to all Airbus Model A300, A310, and A300-600 series airplanes, was published in the Federal Register on August 13, 1998 (63 FR 43349). The action proposed to continue to require performing a ram air turbine (RAT) extension test; removing and disassembling the RAT uplock mechanism; performing an inspection to detect corrosion of the RAT uplock mechanism, and replacement with a new assembly, if necessary; and cleaning all the parts of the RAT control shaft and its bearing component parts. The action also proposed to require modification of the RAT unlocking control unit, which constitutes terminating action for the repetitive tests and inspections. Additionally, the action proposed to limit the applicability of the existing AD.

Comments
Interested persons have been afforded an opportunity to participate in the making of this amendment. Due consideration has been given to the single comment received.

The commenter supports the proposed rule.

Explanation of Correction Made to this Final Rule
In paragraph (a) of the proposed rule, the FAA inadvertently referenced Airbus Service Bulletins A300-29-0108, dated April 1, 1996; A310-29-2076, dated April 1, 1996; and A300-29-6037, dated April 1, 1996; for accomplishment of the action required by paragraph (a)(1) of the NPRM. However, the Airplane Maintenance Manual is the correct reference for accomplishment of the action required by paragraph (a)(1). Paragraph (a) of this final rule has been revised accordingly.

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 with the change previously described. The FAA has determined that this change will neither increase the economic burden on any operator nor increase the scope of the AD.

Cost Impact
There are approximately 126 Model A300, A310, and A300-600 series airplanes of U.S. registry that will be affected by this AD.

The actions that are currently required by AD 97-22-06, and retained in this AD, take approximately 10 work hours per airplane to accomplish, at an average labor rate of $60 per work hour. Required parts will be provided by the manufacturer at no cost to the operators. Based on these figures, the cost impact of the previously required actions on U.S. operators is estimated to be $75,600, or $600 per airplane.

The new modification that is required in this AD action will take approximately 9 work hours per airplane to accomplish, at an average labor rate of $60 per work hour. Required parts will cost approximately $1,972 per airplane. Based on these figures, the cost impact of the modification required by this AD on U.S. operators is estimated to be $316,512, or $2,512 per airplane.

The cost impact figures discussed above are 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 asignificant 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 removing amendment 39-10177 (62 FR 55726, October 28, 1997), and by adding a new airworthiness directive (AD), amendment 39-10840, to read as follows: