[Federal Register Volume 64, Number 48 (Friday, March 12, 1999)]
[Rules and Regulations]
[Pages 12242-12244]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 99-5993]


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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]
BILLING CODE 4910-13-P