[Federal Register Volume 61, Number 173 (Thursday, September 5, 1996)]
[Rules and Regulations]
[Pages 46703-46704]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 96-22144]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 95-NM-249-AD; Amendment 39-9730; AD 96-18-06]
RIN 2120-AA64
Airworthiness Directives; Airbus Model A320-111, -211, and -231
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 A320-111, -211, and -231 series
airplanes, that requires visual inspections to detect cracks of the
fittings of the pressurized floor at frame 36, and renewal of the zone
protective finish or replacement of fittings with new fittings, if
necessary. This amendment is prompted by a report of fatigue cracking
found on the pressurized floor fitting at frame 36 under the lower
surface panel. The actions specified by this AD are intended to prevent
such fatigue cracking, which could result in failure of a floor fitting
and subsequent depressurization of the fuselage.
DATES: Effective October 10, 1996.
The incorporation by reference of certain publications listed in
the regulations is approved by the Director of the Federal Register as
of October 10, 1996.
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: Tim Backman, Aerospace Engineer,
Standardization Branch, ANM-113, FAA, Transport Airplane Directorate,
1601 Lind Avenue, SW., Renton, Washington 98055-4056; telephone (206)
227-2797; fax (206) 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 A320-111, -
211, and -231 series airplanes was published in the Federal Register on
April 19, 1996 (61 FR 17257). That action proposed to require visual
inspection(s) to detect cracks of the six fittings of the pressurized
floor at frame 36 under the lower surface panel, and renewing the zone
protective finish or replacement of the fittings with new fittings, if
necessary.
Interested persons have been afforded an opportunity to participate
in the making of this amendment. Due consideration has been given to
the two comments received.
Both commenters support the proposed rule.
New Service Information
Airbus has issued Revision 1 of Service Bulletin A320-57-1028,
dated April 19, 1996. This revision is essentially identical in its
technical content as the original version, which was cited in the
proposal as the appropriate source of service information. The
Direction Generale de l'Aviation Civile (DGAC), which is the
airworthiness authority for France, has classified this revised service
bulletin as mandatory. Accordingly, this final rule has been revised to
reference Revision 1 of the service bulletin. It has also been revised
to note that any of the required actions that were performed in
accordance with the originally issued service bulletin prior to the
effective date of the final rule are considered acceptable for
compliance with this AD.
Conclusion
After careful review of the available data, including the comments
noted above, the FAA has determined that air safety and the public
interest require the adoption of the rule with the change previously
described. The FAA has determined that this change will neither
increase the economic burden on any operator nor increase the scope of
the AD.
Cost Impact
The FAA estimates that 22 Airbus Model A320-111, -211, and -231
series airplanes of U.S. registry will be affected by this AD, that it
will take approximately 3 work hours per airplane to accomplish the
required actions, and that the average labor rate is $60 per work hour.
Based on these figures, the cost impact of the AD on U.S. operators is
estimated to be $3,960, or $180 per airplane, per inspection cycle.
The cost impact figure discussed above is 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.
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.
[[Page 46704]]
Sec. 39.13 [Amended]
2. Section 39.13 is amended by adding the following new
airworthiness directive:
96-18-06 Airbus Industrie: Amendment 39-9730. Docket 95-NM-249-AD.
Applicability: Model A320-111, -211, and -231 series airplanes;
manufacturer's serial numbers 002 through 008 inclusive, 010 through
014 inclusive, 016 through 078 inclusive, and 080 through 104
inclusive; on which Airbus Modification 21282P01497 (reference
Airbus Service Bulletin A320-57-1029) has not been installed;
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 fatigue cracking on the pressurized floor fitting at
frame 36 under the lower surface panel, which could result in
failure of a fitting and subsequent depressurization of the
fuselage, accomplish the following:
Note 2: Inspections and replacement(s) that were performed prior
to the effective date of this AD in accordance with Airbus Service
Bulletin A320-57-1028, dated April 12, 1996, are considered
acceptable for compliance with this AD.
(a) Prior to the accumulation of 16,000 total landings, or
within 6 months after the effective date of this AD, whichever
occurs later, perform a visual inspection to detect cracks of the 6
fittings of the pressurized floor at frame 36 under the lower
surface panel, in accordance with Airbus Service Bulletin A320-57-
1028, Revision 1, dated April 19, 1996.
(1) If no cracking is found, prior to further flight, renew the
zone protective finish in accordance with the service bulletin.
Repeat the visual inspection thereafter at intervals not to exceed
12,000 landings.
(2) If only 1 of the 6 fittings is found to be cracked and that
crack is less than or equal to 0.59 inch (15 mm) in length, prior to
further flight, replace the cracked fitting with a new fitting in
accordance with the service bulletin. Thereafter, prior to the
accumulation of 500 landings following accomplishment of this
replacement, replace the remaining 5 fittings with new fittings in
accordance with the service bulletin.
(3) If only 1 of the 6 fittings is found to be cracked and that
crack is greater than 0.59 inch (15 mm) in length, prior to further
flight, replace all six fittings with new fittings in accordance
with the service bulletin.
(4) If 2 or more fittings are found to be cracked, prior to
further flight, replace all 6 fittings with new fittings in
accordance with the service bulletin.
(b) Replacement of all 6 fittings with new fittings in
accordance with Airbus Service Bulletin A320-57-1028, Revision 1,
dated April 19, 1996, constitutes terminating action for the
inspection requirements of this AD.
(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, Standardization Branch, ANM-113,
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,
Standardization Branch, ANM-113.
Note 3: Information concerning the existence of approved
alternative methods of compliance with this AD, if any, may be
obtained from the Standardization Branch, ANM-113.
(d) The actions shall be done in accordance with Airbus Service
Bulletin A320-57-1028, Revision 1, dated April 19, 1996, which
contains the following list of effective pages:
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Revision level
Page number shown on page Date shown on page
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1-3............................ 1.............. Apr. 19, 1996.
4-15........................... Original....... Aug. 12, 1991.
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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.
(e) This amendment becomes effective on October 10, 1996.
Issued in Renton, Washington, on August 23, 1996.
Darrell M. Pederson,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 96-22144 Filed 9-4-96; 8:45 am]
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