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

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 98-NM-106-AD; Amendment 39-11074; AD 99-06-10]

RIN 2120-AA64

Airworthiness Directives; Airbus Model A300 and A300-600 Series

Airplanes

AGENCY: Federal Aviation Administration, DOT.

ACTION: Final rule.

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SUMMARY: This amendment adopts a new airworthiness directive (AD),

applicable to certain Airbus Model A300 and A300-600 series airplanes,

that requires replacement of the rivets that attach the pressurized

floor panel to gantries 4 and 5 with new titanium alloy bolts. This

amendment also requires, for certain airplanes, repetitive inspections

to detect discrepancies of the rivets; and corrective actions, if

necessary. This amendment is prompted by the issuance of mandatory

continuing airworthiness information by a foreign civil airworthiness

authority. The actions specified by this AD are intended to prevent

failure of the rivets that attach the pressurized floor panel to

gantries 4 and 5, which could result in the loss of the floor panel and

consequent rapid decompression of the airplane.

DATES: Effective April 16, 1999.

The incorporation by reference of certain publications listed in

the regulations is approved by the Director of the Federal Register as

of April 16, 1999.

ADDRESSES: 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 Federal

Aviation Administration (FAA), Transport Airplane Directorate, Rules

Docket, 1601 Lind Avenue, SW., Renton, Washington; or at the Office of

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: A proposal to amend part 39 of the Federal

Aviation Regulations (14 CFR part 39) to include an airworthiness

directive (AD) that is applicable to certain Airbus Model A300 and

A300-600 series airplanes was published in the Federal Register on

December 9, 1998 (63 FR 67813). That action proposed to require

replacement of the rivets that attach the pressurized floor panel to

gantries 4 and 5 with new titanium alloy bolts. That action also

proposed to require, for certain airplanes, repetitive inspections to

detect discrepancies of the rivets; and corrective actions, if

necessary.

Interested persons have been afforded an opportunity to participate

in the making of this amendment. Due consideration has been given to

the comment received.

Request to Limit Applicability

One commenter, the manufacturer, requests that the applicability of

the proposed AD be revised to exclude airplanes on which Airbus

Modification 11522 has been accomplished. The commenter states that,

following development of the retrofit solution defined as Airbus

Modification 11523

[[Page 12243]]

(reference Airbus Service Bulletins A300-53-0331 and A300-53-6107, both

dated March 18, 1997), a similar production solution defined as

Modification 11522 was developed, and has been installed on airplanes

in production since mid-1996. The FAA concurs that airplanes on which

Airbus Modification 11522 has been installed in production are not

subject to the requirements of this AD, and has revised the final rule

accordingly.

Service Bulletin Revisions

Since issuance of the proposed AD, the manufacturer has issued

Airbus Service Bulletins A300-53-0331, Revision 01, and A300-53-6107,

Revision 01, both dated November 5, 1998. The FAA has reviewed these

revisions and has determined that, in addition to certain

nonsubstantive changes, references to certain nuts were corrected, and

a cleaning agent material was revised. Since these changes do not add

any additional burden to operators, paragraphs (a) and (b) of the final

rule have been revised to cite Revision 01 of these service bulletins

as the appropriate source of service information. For operators that

may have previously accomplished the required actions in accordance

with the original service bulletins, a Note has been added to the final

rule to give credit for those actions.

Conclusion

After careful review of the available data, including the comment

noted above, the FAA has determined that air safety and the public

interest require the adoption of the rule with the changes described

previously. The FAA has determined that these changes will neither

increase the economic burden on any operator nor increase the scope of

the AD.

Cost Impact

The FAA estimates that 24 Airbus Model A300 series airplanes of

U.S. registry will be affected by this AD. It will take approximately

26 work hours per airplane to accomplish the required replacement, at

an average labor rate of $60 per work hour. Required parts will cost

between $3,160 and $3,520 per airplane, depending on the service kit

purchased. Based on these figures, the cost impact of the replacement

required by this AD on U.S. operators is estimated to be as low as

$4,720 per airplane or as high as $5,080 per airplane.

The FAA estimates that 61 Airbus Model A300-600 series airplanes of

U.S. registry will be affected by this AD. It will take approximately

26 work hours per airplane to accomplish the required replacement, at

an average labor rate of $60 per work hour. Required parts will cost

between $3,530 and $3,550 per airplane, depending on the service kit

purchased. Based on these figures, the cost impact of the replacement

required by this AD on U.S. operators is estimated to be as low as

$5,090 per airplane or as high as $5,110 per airplane.

The cost impact figures discussed above are based on assumptions

that no operator has yet accomplished any of the requirements of this

AD action, and that no operator would accomplish those actions in the

future if this AD were not adopted.

Should an operator be required to accomplish the inspection

required by this AD, it will take approximately 1 work hour to

accomplish, at an average labor rate of $60 per work hour. Based on

this figure, the cost impact of the inspection required by this AD on

U.S. operators is estimated to be $60 per airplane, per inspection

cycle.

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.

Sec. 39.13 [Amended]

2. Section 39.13 is amended by adding the following new

airworthiness directive:

99-06-10 Airbus Industrie: Amendment 39-11074. Docket 98-NM-106-AD.

Applicability: Model A300 and A300-600 series airplanes on which

Airbus Modification 11523 (reference Airbus Service Bulletins A300-

53-0331 and A300-53-6107, both dated March 18, 1997) has not been

accomplished, or on which Airbus Modification 11522 has not been

installed in production; 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 (c) 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 failure of the rivets that attach the pressurized

floor panel to gantries 4 and 5, which could result in the loss of

the floor panel and consequent rapid decompression of the airplane,

accomplish the following:

(a) Accomplish paragraph (a)(1), or paragraphs (a)(2) and

(a)(3), of this AD at the times specified in those paragraphs in

accordance with Airbus Service Bulletin A300-53-0331, Revision 01

(for Airbus Model A300 series airplanes); or A300-53-6107, Revision

01 (for Airbus Model A300-600 series airplanes), both dated November

5, 1998; as applicable.

(1) Replace the rivets that attach the pressurized floor panel

to gantries 4 and 5 with new titanium alloy bolts, at the applicable

time specified in paragraph (a)(1)(i), (a)(1)(ii), (a)(1)(iii), or

(a)(1)(iv) of this AD.

(i) For Airbus Model A300-600 series airplanes, replace the

rivets prior to the accumulation of 7,150 total flight cycles.

(ii) For Airbus Model A300 B4-203 series airplanes, replace the

rivets prior to the accumulation of 10,000 total flight cycles.

(iii) For Airbus Model A300 B4-2C and B4-103 series airplanes,

replace the rivets prior to the accumulation of 12,300 total flight

cycles.

[[Page 12244]]

(iv) For Airbus Model A300 B2-1C, B2-203, and B2K-3C series

airplanes, replace the rivets prior to the accumulation of 14,600

total flight cycles.

(2) Perform a detailed visual inspection to detect any broken or

discrepant rivets that attach the pressurized floor panel to

gantries 4 and 5, at the applicable time specified in paragraph

(a)(2)(i), (a)(2)(ii), (a)(2)(iii), or (a)(2)(iv) of this AD. Repeat

the inspection thereafter at intervals not to exceed 350 flight

cycles until accomplishment of the action required by paragraph

(a)(3) of this AD.

(i) For Airbus Model A300-600 series airplanes, inspect the

rivets prior to the accumulation of 7,500 total flight cycles, or

within 350 flight cycles after the effective date of this AD,

whichever occurs later.

(ii) For Airbus Model A300 B4-203 series airplanes, inspect the

rivets prior to the accumulation of 10,350 total flight cycles, or

within 350 flight cycles after the effective date of this AD,

whichever occurs later.

(iii) For Airbus Model A300 B4-2C and B4-103 series airplanes,

inspect the rivets prior to the accumulation of 12,650 total flight

cycles, or within 350 flight cycles after the effective date of this

AD, whichever occurs later.

(iv) For Airbus Model A300 B2-1C, B2-203, and B2K-3C series

airplanes, inspect the rivets prior to the accumulation of 14,950

total flight cycles, or within 350 flight cycles after the effective

date of this AD, whichever occurs later.

(3) Within 3,000 flight cycles after the effective date of this

AD, replace the rivets that attach the pressurized floor panel to

gantries 4 and 5 with new titanium alloy bolts in accordance with

the applicable service bulletin. Accomplishment of this replacement

constitutes terminating action for the repetitive inspections.

(b) If any discrepant or broken rivet is detected during any

inspection specified in paragraph (a)(2) of this AD, prior to

further flight, accomplish either paragraph (b)(1) or (b)(2) of this

AD, as applicable, in accordance with Airbus Service Bulletin A300-

53-0331, Revision 01 (for Airbus Model A300 series airplanes); or

A300-53-6107, Revision 01 (for Airbus Model A300-600 series

airplanes), both dated November 5, 1998; as applicable.

(1) If less than 15 discrepant or broken rivets are detected,

prior to further flight, replace the discrepant or broken rivets

with serviceable rivets and continue the repetitive inspections, in

accordance with the applicable service bulletin, until

accomplishment of the action required by paragraph (a)(3) of this

AD.

(2) If 15 or more discrepant or broken rivets are detected,

prior to further flight, replace all the rivets that attach the

pressurized floor panel to gantries 4 and 5 with new titanium alloy

bolts, in accordance with the applicable service bulletin.

Accomplishment of this replacement constitutes terminating action

for the repetitive inspections required by this AD.

Note 2: Accomplishment of the actions required by paragraphs (a)

and (b) of this AD in accordance with Airbus Service Bulletin A300-

53-0331, dated March 18, 1997 (for Airbus Model A300 series

airplanes); or Airbus Service Bulletin A300-53-6107, dated March 18,

1997 (for Airbus Model A300-600 series airplanes), prior to the

effective date of this AD, is acceptable for compliance with those

paragraphs.

(c) 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.

(d) 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.

(e) The actions shall be done in accordance with Airbus Service

Bulletin A300-53-0331, Revision 01, dated November 5, 1998, or

Airbus Service Bulletin A300-53-6107, Revision 01, dated November 5,

1998. 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 97-176-229(B), dated August 13, 1997.

(f) This amendment becomes effective on April 16, 1999.

Issued in Renton, Washington, on March 4, 1999.

Darrell M. Pederson,

Acting Manager, Transport Airplane Directorate, Aircraft Certification

Service.

[FR Doc. 99-5993 Filed 3-11-99; 8:45 am]

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