[Federal Register Volume 65, Number 2 (Tuesday, January 4, 2000)]
[Rules and Regulations]
[Pages 211-213]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 00-8]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 99-NM-327-AD; Amendment 39-11490; AD 99-27-09]
RIN 2120-AA64


Airworthiness Directives; Airbus Model A300 B4-203 Series 
Airplanes

AGENCY: Federal Aviation Administration, DOT.

ACTION: Final rule; request for comments.

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SUMMARY: 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.

DATES: Effective January 19, 2000.
    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of January 19, 2000.
    Comments for inclusion in the Rules Docket must be received on or 
before February 3, 2000.

ADDRESSES: Submit comments in triplicate to the Federal Aviation 
Administration (FAA), Transport Airplane Directorate, ANM-114, 
Attention: Rules Docket No. 99-NM-327-AD, 1601 Lind Avenue, SW., 
Renton, Washington 98055-4056.
    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 FAA, Transport Airplane 
Directorate, 1601 Lind Avenue, SW., Renton, Washington; or at the 
Office of

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the Federal Register, 800 North Capitol Street, NW., suite 700, 
Washington, DC.

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: 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 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 
criteria 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 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 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 on these 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 
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 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)

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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.


Sec. 39.13  [Amended]

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

99-27-09 Airbus Industrie: Amendment 39-11490. Docket 99-NM-327-AD.
    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 to 
address 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. Inspection aids 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.

    Issued in Renton, Washington, on December 23, 1999.
Vi L. Lipski,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 00-8 Filed 1-3-00; 8:45 am]
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