AD 99-27-09

This amendment adopts a new airworthiness directive (AD), applicable to certain Airbus Model A300 B4-203 series airplanes. This action requires repetitive inspections of the attachment bolts of the brake bar on the main landing gear (MLG) to detect missing or damaged bolts, and replacement with new bolts, 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 prevent detachment of the brake bar from the MLG strut, which could result in failure of the main landing gear to extend.

Final rule; request for comments.

99-27-09 AIRBUS INDUSTRIE: Amendment 39-11490. Docket 99-NM-327-AD. Issued December 23, 1999.
Applicability: Model A300 B4-203 series airplanes, certificated in any category, equipped with La Guardia main landing gears (MLG) and Messier Bugatti steel brakes.
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 (b) 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 toaddress it.
Compliance: Required as indicated, unless accomplished previously.
To prevent detachment of the brake bar from the MLG strut, which could result in failure of the MLG to extend, accomplish the following:
(a) Within 500 flight hours after the effective date of this AD, perform a detailed visual inspection to detect missing brake bar attachment bolts on the left and right MLG, in accordance with Airbus Service Bulletin A300-32-0430, dated January 29, 1999.
(1) If no attachment bolt is missing, prior to further flight, remove the attachment bolts, and perform a detailed visual inspection to detect damage, as specified by Figure 1 of the service bulletin. Accomplish the actions in accordance with the service bulletin.
(i) If no damage is detected, repeat the detailed visual inspection required by paragraph (a) of this AD thereafter at intervals not to exceed 500 flight hours.(ii) If any damage is detected, prior to further flight, replace the two attachment bolts with new bolts in accordance with the service bulletin. Repeat the detailed visual inspection required by paragraph (a) of this AD thereafter at intervals not to exceed 500 flight hours.
(2) If any attachment bolt is missing, prior to further flight, replace the two attachment bolts with new bolts, in accordance with the service bulletin. Repeat the detailed visual inspection required by paragraph (a) of this AD thereafter at intervals not to exceed 500 flight hours.
NOTE 2: For the purposes of this AD, a detailed visual inspection is defined as: "An intensive visual examination of a specific structural area, system, installation, or assembly to detect damage, failure, or irregularity. Available lighting is normally supplemented with a direct source of good lighting at intensity deemed appropriate by the inspector. Inspectionaids such as mirror, magnifying lenses, etc., may be used. Surface cleaning and elaborate access procedures may be required."
Alternative Methods of Compliance
(b) 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.
Special Flight Permits
(c) 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.
Incorporation by Reference
(d) The actions shall be done in accordance with Airbus Service Bulletin A300-32-0430, dated January 29, 1999. 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 4: The subject of this AD is addressed in French airworthiness directive 1999-284-290(B), dated July 13, 1999.

(e) This amendment becomes effective on January 19, 2000.

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 A300 B4-203 series airplanes. The DGAC advises that three cases of brake bar (rod) loss after fracture of retaining bolts have been reported by operators of Model A300 series airplanes equipped with La Guardia landing gears and Messier Bugatti steel brakes. In three other cases, there was no bar separation but retaining bolts were found damaged. The reason for these anomalies is not known at this time. However, such discrepancies, if not corrected, could result in failure of the main landing gear (MLG) to extend.
Explanation of Relevant Service Information
Airbus has issued Service Bulletin A300-32-0430, dated January 29, 1999, which describes procedures for repetitive detailed visual inspections of the attachment bolts on the brake bar of the MLG to detect damaged or missing bolts, and replacement of any damaged or missing bolt with a new bolt. The service bulletin describes damage critieria and procedures for determining when the brake bar attachment bolts need to be replaced. 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 1999-284-290(B), dated July 13, 1999, 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 allavailable 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 prevent detachment of the brake bar from the main landing gear strut, which could result in failure of the main landing gear to extend. This AD requires accomplishment of the actions specified in the service bulletin described previously, except as discussed below.
Differences Between the Rule and the Service Information
The manufacturer s service bulletin recommends repetitive inspections to begin at the next "A" check with an "A"-check repetitive interval. The DGAC has established an initial inspection time of 500 flight hours and a repetitive inspection interval of 500 flight hours. In developing an appropriate compliance time for this action, the FAA considered the safety implications, the compliance time of the DGAC, and normal maintenance schedules for timely accomplishment of the inspections. Consequently, the FAA concurs with the DGAC s mandated compliance time.
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 require approximately 2 work hours to accomplish the required inspection, at an average labor rate of $60 per work hour. Based onthese figures, the cost impact of this AD would be $120 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 forcomments 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 99-NM-327-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 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: