[Federal Register Volume 63, Number 114 (Monday, June 15, 1998)]
[Rules and Regulations]
[Pages 32608-32609]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 98-15679]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 97-NM-194-AD; Amendment 39-10586; AD 98-12-33]
RIN 2120-AA64
Airworthiness Directives; Airbus Model A320 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 series airplanes, that requires
repetitive inspections to detect fatigue cracking on the connecting
angle between frame 56 and the right-hand frame support at stringer 38;
and replacement of the connecting angle, if necessary. This amendment
also provides for an optional terminating action for the repetitive
inspections.
This amendment is prompted by issuance of mandatory continuing
airworthiness information by a foreign civil airworthiness authority.
The actions specified by this AD are intended to detect and correct
fatigue cracking on the connecting angle, which could result in reduced
structural integrity of the airplane.
DATES: Effective July 20, 1998.
The incorporation by reference of certain publications listed in
the regulations is approved by the Director of the Federal Register as
of July 20, 1998.
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 A320 series
airplanes was published in the Federal Register on April 14, 1998 (63
FR 18156). That action proposed to require repetitive inspections to
detect fatigue cracking on the connecting angle between frame 56 and
the right-hand frame support at stringer 38; and replacement of the
connecting angle, if necessary. That action also proposed to provide
for an optional terminating action for the repetitive inspections.
Comments
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.
The commenters support the proposed rule.
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 as proposed.
Cost Impact
The FAA estimates that 5 airplanes of U.S. registry will be
affected by this AD. It will take approximately 1 work hour per
airplane to accomplish the required inspection, 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
$300, or $60 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.
Should an operator elect to perform the optional terminating
replacement provided by this AD, it would take approximately 3 work
hours per airplane to accomplish the modification, at an average labor
rate of $60 per work hour. Required parts would cost $136 or $153 per
airplane, depending on the service kit purchased. Based on these
figures, the cost impact of the optional terminating modification
provided by this AD on U.S. operators is estimated to be as low as
$1,580, or $316 per airplane, and as high as $1,665, or $333 per
airplane.
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
[[Page 32609]]
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:
98-12-33 Airbus Industrie: Amendment 39-10586. Docket 97-NM-194-AD.
Applicability: Model A320 series airplanes, on which Airbus
Modification 20941 (reference Airbus Service Bulletin A320-53-1011,
dated December 9, 1994) has not 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 (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 detect and correct fatigue cracking on the connecting angle
between frame 56 and the right-hand frame support at stringer 38,
which could result in reduced structural integrity of the airplane,
accomplish the following:
(a) Prior to the accumulation of 20,000 total flight cycles, or
within 1,000 flight cycles after the effective date of this AD,
whichever occurs later, perform a visual inspection for fatigue
cracking on the connecting angle between frame 56 and the right-hand
frame support at stringer 38, in accordance with Airbus Service
Bulletin A320-53-1084, Revision 1, dated November 28, 1995.
(1) If no cracking is detected, accomplish either paragraph
(a)(1)(i) or (a)(1)(ii) of this AD.
(i) Prior to further flight, replace the connecting angle
between frame 56 and the right-hand frame support at stringer 38
with a new part, in accordance with Airbus Service Bulletin A320-53-
1011, dated December 9, 1994; or
(ii) Repeat the visual inspection thereafter at intervals not to
exceed 12,000 flight cycles.
(2) If any cracking is detected, prior to further flight,
replace the connecting angle between frame 56 and the right-hand
frame support at stringer 38 with a new part, in accordance with
Airbus Service Bulletin A320-53-1011, dated December 9, 1994.
(b) Accomplishment of the replacement of the connecting angle
constitutes terminating action for the repetitive 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, 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 2: 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 the following
Airbus service bulletins, which contain the specified effective
pages:
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Service bulletin referenced and Revision level shown on
date Page No. shown on page page Date shown on page
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A320-53-1084, Revision 1, 1, 2..................... 1....................... Nov. 28, 1995.
November 28, 1995. 3-11..................... Original................ Dec. 9, 1994.
A320-53-1011, December 9, 1994... 1-11..................... Original................ Dec. 9, 1994.
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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.
Note 3: The subject of this AD is addressed in French
airworthiness directive 96-237-090(B), dated October 23, 1996, and
Erratum to French airworthiness directive 96-237-090(B), dated
February 26, 1997.
(f) This amendment becomes effective on July 20, 1998.
Issued in Renton, Washington, on June 5, 1998.
Darrell M. Pederson,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 98-15679 Filed 6-12-98; 8:45 am]
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