AD 98-14-16

This amendment adopts a new airworthiness directive (AD), applicable to certain Airbus Model A300 series airplanes. This action requires repetitive inspections to detect cracks in the forward canted frames between fuselage frames 47a and 48 from stringer (STGR) 41 to STGR 43; and temporary repair, or replacement of the forward canted frame with a new frame, if necessary. This amendment is prompted by issuance of mandatory continuing airworthiness information by a foreign civil airworthiness authority. The actions specified in this AD are intended to detect and correct cracking in the forward canted frames, which could result in failure of the forward canted frame, and consequent reduced structural integrity of the airplane.

Final rule; request for comments.

98-14-16 AIRBUS INDUSTRIE: Amendment 39-10649. Docket 98-NM-31-AD.

Applicability: Model A300 series airplanes, certificated in any category, as listed below:
B2-1C, all serial numbers;
B2K-3C, all serial numbers;
B2-203, all serial numbers;
B4-203 having manufacturer's serial number 255; and
B4-2C having manufacturer's serial number 256.

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 (e) 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 and correct cracking in the forward canted frames, which could result in failure of the forward canted frame, and consequent reduced structural integrity of the airplane, accomplish the following:

(a) Perform an eddy current inspection to detect cracking in the forward canted frame between fuselage frames 47a and 48 from stringer 41 to stringer 43, in accordance with Airbus Service Bulletin A300-53-0314, dated January 14, 1997; at the time specified in paragraph (a)(1), (a)(2), (a)(3), or (a)(4) of this AD, as applicable. If no crack is detected, repeat the inspection thereafter at intervals not to exceed 2,100 flight cycles.

(1) For airplanes that have accumulated less than 11,000 flight cycles as of the effective date of this AD: Perform the inspection prior to the accumulation of 11,000 total flight cycles, or within 2,000 flight cycles after the effective date of this AD, whichever occurs later.

(2) For airplanes that have accumulated 11,000 or more total flight cycles, but less than 14,000 total flight cycles, as of the effective date of this AD: Perform the inspection within 2,000 flight cycles after the effective date of this AD.

(3) For airplanes that have accumulated 14,000 or more total flight cycles as of the effective date of this AD: Perform the inspection within 1,000 flight cycles after the effective date of this AD.

(4) For airplanes on which the forward canted frame has been replaced with a basic frame (A53833393-200, -201, -202, -203, -206, or -207): Perform the inspection prior to the accumulation of 11,000 total flight cycles since the frame replacement date, or within 2,100 flight cycles after the effective date of this AD, whichever occurs later.

(b) Except as provided by paragraph (d) of this AD, if any crack is detected during any inspection required by paragraph (a) of this AD, prior to further flight, accomplish the requirements of either paragraph (b)(1) or (b)(2) of this AD, in accordance with Airbus Service Bulletin A300-53-0314, dated January 14, 1997. Thereafter, inspect in accordance with the requirements of paragraph (c) of this AD.

(1) Replace the forward canted frame with a new forward canted frame. Or

(2) Perform the temporary repair and, within 1,600 flight cycles after accomplishment of the temporary repair, replace the forward canted frame with a new forward canted frame.

(c) Prior to accumulation of 24,600 flight cycles after replacement of the forward canted frame with a new forward canted frame, and thereafter at intervals not to exceed 3,200 flight cycles: Perform an eddy current inspection to detect cracking of the new forward canted frame in accordance with the requirements of paragraph (a) of this AD.

(d) For airplanes having manufacturer's serial number 32: If any crack is detected during any inspection required by paragraph (a) of this AD, prior to further flight, repair the crack in accordance with a method approved by either the Manager, International Branch, ANM-116, Transport Airplane Directorate, FAA, or the Direction G n rale de l'Aviation Civile (DGAC) (or its delegated agent).

(e) 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 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.

(f) 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.

(g) The actions shall be done in accordance with Airbus Service Bulletin A300-53-0314, dated January 14, 1997. 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 North Capitol Street, NW., suite 700, Washington, DC.

NOTE 3: The subject of this AD is addressed in French airworthiness directive 97-063- 214(B), dated February 26, 1997.

(h) This amendment becomes effective on July 24, 1998.

The Direction G n rale 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 series airplanes. The DGAC advises that it has been informed of several reported cases of fatigue cracking between frame 47a to 48 on the forward canted frame from stringer (STGR) 41 to STGR 43. These cracks were found on airplanes that had accumulated between 20,900 and 24,000 flight cycles. This condition, if not corrected, could result in failure of the forward canted frame, and consequent reduced structural integrity of the airplane.

Explanation of Relevant Service Information
Airbus has issued Service Bulletin A300-53-0314, dated January 14, 1997, which describes procedures for repetitive eddy current inspections to detect cracking in the forward canted frames between fuselage frames 47a and 48 from STGR 41 to STGR 43; and temporary repair, or replacement of the forward canted frame with a new forward canted frame, if necessary. Following accomplishment of the replacement, the service bulletin recommends accomplishment of the eddy current inspections at an extended threshold and interval. Accomplishment of the actions specified in the service bulletin is intended to adequately address the identified unsafe condition.

The DGAC classified this service bulletin as mandatory and issued French airworthiness directive 97-063-214(B), dated February 26, 1997, in order to assure the continued airworthiness of these airplanes in France.

FAA's Conclusions
This airplane model is manufactured in France and is type certificated for operation in the United States under the provisions of section 21.29 of the Federal Aviation Regulations (14 CFR 21.19) 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 the 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, this AD is being issued to detect and correct cracking in the forward canted frames, which could result in failure of the forward canted frame, and consequent reduced structural integrity of the airplane. This AD requires accomplishment of the actions specified in the service bulletin described previously, except as discussed below.

Difference Between This AD and Related Service Information
Operators should note that, although the service bulletin specifies that the manufacturer may be contacted for disposition of certain repair conditions, this AD would require the repair of those conditions to be accomplished in accordance with a method approved by the FAA or the DGAC (or its delegated agent). In light of the type of repair that would be required to address the identified unsafe condition, and in consonance with existing bilateral airworthiness agreements, the FAA has determined that, for this AD, a repair approved by either the FAA or the DGAC would be acceptable for compliance with this AD.

Cost Impact
None of the airplanes affected by this action are on the U.S. Register. All airplanes included in the applicability of this rule currently are operated by non-U.S. operators under foreign registry; therefore, they are not directly affected by this AD action. However, the FAA considers that this rule is necessary to ensure that the unsafe condition is addressed in the event that any of these subject airplanes are imported and placed on the U.S. Register in the future.

Should an affected airplane be imported and placed on the U.S. Register in the future, it would requireapproximately 3 work hours to accomplish the required inspection, at an average labor rate of $60 per work hour. Based on these figures, the cost impact of this AD would be $180 per airplane, per inspection cycle.

Determination of Rule's Effective Date
Since this AD action does not affect any airplane that is currently on the U.S. register, it has no adverse economic impact and imposes no additional burden on any person. Therefore, prior notice and public procedures hereon are unnecessary and the amendment may be made effective in less than 30 days after publication in the Federal Register.

Comments Invited
Although this action is in the form of a final rule and was not preceded by notice and opportunity for public comment, comments are invited on this rule. Interested persons are invited to comment on this 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 under the caption "ADDRESSES." All communications received on or before the closing date for comments will be considered, and this rule may be amended in light of the comments received. Factual information that supports the commenter's ideas and suggestions is extremely helpful in evaluating the effectiveness of the AD action and determining whether additional rulemaking action would be needed.

Comments are specifically invited on the overall regulatory, economic, environmental, and energy aspects of the rule that might suggest a need to modify the 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 that summarizes each FAA-public contact concerned with the substance of this AD will be filed in the Rules Docket.

Commenters wishing the FAA to acknowledge receipt of their comments submitted in response to this rule must submit a self-addressed, stamped postcard on which the following statement is made: "Comments to Docket Number 98-NM-31-AD." The postcard will be date stamped and returned to the commenter.

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 entitiesunder 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: