Airworthiness Directives; Airbus Model A300 B4-203 Series Airplanes

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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