Airworthiness Directives; Airbus Model A300 and A300-600 Series Airplanes

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 99-NM-337-AD]

RIN 2120-AA64

Airworthiness Directives; Airbus Model A300 and A300-600 Series

Airplanes

AGENCY: Federal Aviation Administration, DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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SUMMARY: This document proposes the supersedure of an existing

airworthiness directive (AD), applicable to certain Airbus Model A300

and A300-600 series airplanes, that currently requires repetitive

inspections to detect cracks in Gear Rib 5 of the main landing gear

(MLG) attachment fittings at the lower flange, and repair, if

necessary. That AD also requires modification of Gear Rib 5 of the MLG

attachment fittings, which constitutes terminating action for the

repetitive inspections. This action would expand the current inspection

area for certain airplanes. This proposal is prompted by issuance of

mandatory continuing airworthiness information by a foreign civil

airworthiness authority. The actions specified by the proposed AD are

intended to prevent fatigue cracking of the MLG attachment fittings,

which could result in reduced structural integrity of the airplane.

DATES: Comments must be received by January 31, 2000.

ADDRESSES: Submit comments in triplicate to the Federal Aviation

Administration (FAA), Transport Airplane Directorate, ANM-114,

Attention: Rules Docket No. 99-NM-337-AD, 1601 Lind Avenue, SW.,

Renton, Washington 98055-4056. Comments may be inspected at this

location between 9:00 a.m. and 3:00 p.m., Monday through Friday, except

Federal holidays.

The service information referenced in the proposed rule 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.

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:

Comments Invited

Interested persons are invited to participate in the making of the

proposed 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 above. All

communications received on or before the closing date for comments,

specified above, will be considered before taking action on the

proposed rule. The proposals contained in this notice may be changed in

light of the comments received.

Comments are specifically invited on the overall regulatory,

economic, environmental, and energy aspects of the proposed rule. All

comments

[[Page 73440]]

submitted will be available, both before and after the closing date for

comments, in the Rules Docket for examination by interested persons. A

report summarizing each FAA-public contact concerned with the substance

of this proposal will be filed in the Rules Docket.

Commenters wishing the FAA to acknowledge receipt of their comments

submitted in response to this notice must submit a self-addressed,

stamped postcard on which the following statement is made: ``Comments

to Docket Number 99-NM-337-AD.'' The postcard will be date stamped and

returned to the commenter.

Availability of NPRMs

Any person may obtain a copy of this NPRM by submitting a request

to the FAA, Transport Airplane Directorate, ANM-114, Attention: Rules

Docket No. 99-NM-337-AD, 1601 Lind Avenue, SW., Renton, Washington

98055-4056.

Discussion

On September 2, 1999, the FAA issued AD 99-19-26, amendment 39-

11313 (64 FR 49966, September 15, 1999), applicable to certain Airbus

Model A300 and A300-600 series airplanes, to require repetitive

inspections to detect cracks in Gear Rib 5 of the main landing gear

(MLG) attachment fittings at the lower flange, and repair, if

necessary. That AD also requires modification of Gear Rib 5 of the MLG

attachment fittings, which constitutes terminating action for the

repetitive inspections. That action was prompted by issuance of

mandatory continuing airworthiness information by a foreign civil

airworthiness authority. The requirements of that AD are intended to

prevent fatigue cracking of the MLG attachment fittings, which could

result in reduced structural integrity of the airplane.

Explanation of Relevant Service Information

Since the issuance of AD 99-19-26, the manufacturer has issued

Airbus Service Bulletins A300-57A0234, Revision 03, including Appendix

01, dated September 2, 1999 (for Model A300 series airplanes); and

A300-57A6087, Revision 02, including Appendix 01, dated June 24, 1999

(for Model A300-600 series airplanes). These service bulletins expand

the current inspection area for accomplishing the repetitive detailed

visual and high frequency eddy current inspections to include holes 43,

48, 49, 50, 52, and 54 of Gear Rib 5 of the main landing gear (MLG)

attachment fittings at the lower flange.

The Direction Generale de l'Aviation Civile (DGAC), which is the

airworthiness authority for France, classified these service bulletins

as mandatory and issued French airworthiness directive 1998-151-247(B)

R2, dated June 16, 1999, in order to assure the continued airworthiness

of these airplanes in France.

FAA's Conclusions

These airplane models are manufactured in France and are type

certificated for operation in the United States under the provisions of

section 21.29 of the Federal Aviation Regulations (14 CFR 21.29) 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 Proposed 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, the proposed AD would supersede AD 99-19-26 to

continue to require repetitive inspections to detect cracks in Gear Rib

5 of the main landing gear (MLG) attachment fittings at the lower

flange, and repair, if necessary. It also would continue to require

modification of Gear Rib 5 of the MLG attachment fittings, which

constitutes terminating action for the repetitive inspections. This

proposed AD would expand the current inspection area for certain

airplanes. The inspections would be required to be accomplished in

accordance with the service bulletins described previously.

Cost Impact

There are approximately 164 airplanes of U.S. registry that would

be affected by this proposed AD.

The modification that is currently required by AD 99-19-26, and

retained in this proposed AD takes approximately 62 work hours per

airplane to accomplish, at an average labor rate of $60 per work hour.

Required parts cost approximately $10,270 per airplane. Based on these

figures, the cost impact of the currently required inspections on U.S.

operators is estimated to be $2,294,360, or $13,990 per airplane.

The new expanded inspections that are proposed in this AD action

would take approximately 6 work hours per airplane to accomplish, at an

average labor rate of $60 per work hour. Based on these figures, the

cost impact of the proposed requirements of this AD on U.S. operators

is estimated to be $59,040, or $360 per airplane.

The cost impact figures discussed above are based on assumptions

that no operator has yet accomplished any of the current or proposed

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 proposed herein would 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

proposal would not have sufficient federalism implications to warrant

the preparation of a Federalism Assessment.

For the reasons discussed above, I certify that this proposed

regulation (1) is not a ``significant regulatory action'' under

Executive Order 12866; (2) is not a ``significant rule'' under the DOT

Regulatory Policies and Procedures (44 FR 11034, February 26, 1979);

and (3) if promulgated, 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 copy of the draft

regulatory evaluation prepared for this action is contained in the

Rules Docket. A copy of it may be obtained by contacting the Rules

Docket at the location provided under the caption ADDRESSES.

List of Subjects in 14 CFR Part 39

Air transportation, Aircraft, Aviation safety, Safety.

The Proposed Amendment

Accordingly, pursuant to the authority delegated to me by the

Administrator, the Federal Aviation Administration proposes to amend

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.

[[Page 73441]]

Sec. 39.13 [Amended]

2. Section 39.13 is amended by removing amendment 39-11313 (64 FR

49966, September 15, 1999), and by adding a new airworthiness directive

(AD), to read as follows:

Airbus Industrie: Docket 99-NM-337-AD. Supersedes AD 99-19-26,

amendment 39-11313.

Applicability: Model A300 series airplanes, as listed in Airbus

Service Bulletin A300-57-0234, Revision 01, dated March 11, 1998;

and Model A300-600 series airplanes, as listed in Airbus Service

Bulletin A300-57-6087, Revision 01, dated March 11, 1998; except

airplanes on which Airbus Modification 11912 has been installed in

production, or on which Airbus Modification 11932 has 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)(1)

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 fatigue cracking of the main landing gear (MLG)

attachment fittings, which could result in reduced structural

integrity of the airplane, accomplish the following:

Repetitive Inspections

(a) Perform a detailed visual and a high frequency eddy current

(HFEC) inspection to detect cracks in Gear Rib 5 of the MLG

attachment fittings at the lower flange, in accordance with Airbus

Service Bulletin A300-57-6087, Revision 01, dated March 11, 1998

(for Model A300-600 series airplanes); or A300-57-0234, Revision 01,

dated March 11, 1998 (for Model A300 series airplanes); as

applicable; at the time specified in paragraph (a)(1) or (a)(2) of

this AD, as applicable. After the effective date of this AD, only

Airbus Service Bulletin A300-57A0234, Revision 02, dated June 24,

1999, or Revision 03, including Appendix 01, dated September 2, 1999

(for Model A300 series airplanes); or A300-57A6087, Revision 02,

including Appendix 01, dated June 24, 1999 (for Model A300-600

series airplanes); as applicable; shall be used. Repeat the

inspections thereafter at intervals not to exceed 1,500 flight

cycles.

Detailed Visual Inspection

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.''

(1) For airplanes that have accumulated 20,000 or more total

flight cycles as of March 9, 1998: Inspect within 500 flight cycles

after March 9, 1998.

(2) For airplanes that have accumulated less than 20,000 total

flight cycles as of March 9, 1998: Inspect prior to the accumulation

of 18,000 total flight cycles, or within 1,500 flight cycles after

March 9, 1998, whichever occurs later.

Note 3: Accomplishment of the initial detailed visual and HFEC

inspections in accordance with Airbus Service Bulletin A300-57A0234

or A300-57A6057, both dated August 1, 1997, as applicable, is

considered acceptable for compliance with the initial inspections

required by paragraph (a) of this AD.

Repair

(b) If any crack is detected during any inspection required by

this AD, prior to further flight, accomplish the requirements of

paragraphs (b)(1) or (b)(2) of this AD, as applicable.

(1) If a crack is detected at one hole only, and the crack does

not extend out of the spotface of the hole, repair in accordance

with Airbus Service Bulletin A300-57A0234, Revision 02, dated June

24, 1999, or Revision 03, including Appendix 01, dated September 2,

1999 (for Model A300 series airplanes); or A300-57A6087, Revision

02, including Appendix 01, dated June 24, 1999 (for Model A300-600

series airplanes); as applicable.

(2) If a crack is detected at more than one hole, or if any

crack at any hole extends out of the spotface of the hole, repair in

accordance with a method approved by the Manager, International

Branch, ANM-116, FAA, Transport Airplane Directorate, or the

Direction Generale de l'Aviation Civile (or its delegated agent).

Terminating Modification

(c) Prior to the accumulation of 21,000 total flight cycles, or

within 2 years after October 20, 1999 (the effective date of AD 99-

19-26, amendment 39-11313), whichever occurs later: Modify Gear Rib

5 of the MLG attachment fittings at the lower flange in accordance

with Airbus Service Bulletin A300-57-6088, Revision 01, including

Appendix 01 (for Model A300-600 series airplanes), or A300-57-0235,

Revision 01, including Appendix 01 (for Model A300 series

airplanes), all dated February 1, 1999, as applicable.

Accomplishment of this modification constitutes terminating action

for the repetitive inspection requirements of this AD.

Note 4: Accomplishment of the modification required by paragraph

(d) of this AD prior to the effective date of this AD in accordance

with Airbus Service Bulletin A300-57-6088 or A300-57-0235, both

dated August 1, 1998; as applicable; is acceptable for compliance

with the requirements of that paragraph.

Alternative Methods of Compliance

(d)(1) 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.

(d)(2) Alternative methods of compliance, approved previously in

accordance with AD 99-19-26, amendment 39-11313, are approved as

alternative methods of compliance with this AD.

Note 5: 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

(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.

Note 6: The subject of this AD is addressed in French

airworthiness directive 1998-151-247(B), dated June 16, 1999.

Issued in Renton, Washington, on December 23, 1999.

Vi L. Lipski,

Acting Manager, Transport Airplane Directorate, Aircraft Certification

Service.

[FR Doc. 99-33949 Filed 12-29-99; 8:45 am]

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