[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]
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