[Federal Register Volume 63, Number 39 (Friday, February 27, 1998)]
[Rules and Regulations]
[Pages 9934-9935]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 98-4400]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 97-NM-152-AD; Amendment 39-10360; AD 98-04-49]
RIN 2120-AA64
Airworthiness Directives; Airbus Model A320-111, -211, -212, -
214, -231, -232, and -233 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 all Airbus Model A320-111, -211, -212, -214, -231, -232,
and -233 series airplanes, that requires repetitive ultrasonic
inspections to detect fatigue cracking in the wing/fuselage joint
cruciform fittings, and corrective actions, if necessary. 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 cracks
on the wing/fuselage joint cruciform fittings, which could result in
reduced structural integrity of the wing/fuselage.
DATES: Effective April 3, 1998.
The incorporation by reference of certain publications listed in
the regulations is approved by the Director of the Federal Register as
of April 3, 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 all Airbus Model A320-111, -211, -
212, -214, -231, -232, and -233 series airplanes was published in the
Federal Register on December 1, 1997 (62 FR 63476). That action
proposed to require repetitive ultrasonic inspections to detect fatigue
cracking in the wing/fuselage joint cruciform fittings, and corrective
actions, if necessary.
Comments
Interested persons have been afforded an opportunity to participate
in the making of this amendment. Due consideration has been given to
the comments received.
All of 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 132 airplanes of U.S. registry will be
affected by this AD, that it will take approximately 8 work hours per
airplane to accomplish the required inspection, at an average labor
rate of $60 per work hour. Based on these figures, the cost impact of
the inspection required by this AD on U.S. operators is estimated to be
$63,360, or $480 per airplane.
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.
Sec. 39.13 [Amended]
2. Section 39.13 is amended by adding the following new
airworthiness directive:
98-04-49 Airbus Industrie: Amendment 39-10360. Docket 97-NM-152-AD.
Applicability: Model A320-111, -211, -212, -214, -231, -232, and
-233 series airplanes, all serial numbers, certificated in any
category.
Note 1: This AD applies to each airplane identified in the
preceding applicability provision, regardless of whether it has been
modified, altered, or repaired in the area subject to the
requirements of this AD. For airplanes that have been modified,
altered, or
[[Page 9935]]
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 (b) 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 cracks on the wing/fuselage joint
cruciform fittings, which could result in reduced structural
integrity of the wing/fuselage, accomplish the following:
(a) Prior to the accumulation of 28,000 total landings, or
within 60 days after the effective date of this AD, whichever occurs
later, perform an ultrasonic inspection to detect fatigue cracking
in the wing/fuselage joint cruciform fittings, in accordance with
Airbus Service Bulletin A320-57-1051, Revision 01, dated March 21,
1996.
(1) If no cracking is detected, repeat the inspection thereafter
at intervals not to exceed 20,000 landings.
(2) If any crack is detected, prior to further flight, repair it
in accordance with the service bulletin. Thereafter, repeat the
inspection at the times specified in paragraph (a)(2)(i) or
(a)(2)(ii) of this AD, as applicable.
(i) If the crack that was detected and repaired was greater than
2.5 mm: Repeat the inspection prior to the accumulation of 32,000
landings since accomplishment of the repair; and thereafter at
intervals not to exceed 32,000 landings.
(ii) If the crack that was detected and repaired was less than
or equal to 2.5 mm: Repeat the inspection prior to the accumulation
of 28,000 landings since accomplishment of the repair; and
thereafter at intervals not to exceed 20,000 landings.
(b) 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 request
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.
(c) 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.
(d) The actions shall be done in accordance with Airbus Service
Bulletin A320-57-1051, Revision 01, dated March 21, 1996, which
contains the specified effective pages:
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Revision level Date shown on
Page No. shown on page page
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1-29, 31-37, 39-40............... 1................. Mar. 21, 1996.
30, 38........................... Original.......... Mar. 30, 1993.
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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 96-299-094(B), dated December 18, 1996.
(e) This amendment becomes effective on April 3, 1998.
Issued in Renton, Washington, on February 13, 1998.
Stewart R. Miller,
Acting Manager, Transport Airplane Directorate, Aircraft Certification.
Service.
[FR Doc. 98-4400 Filed 2-26-98; 8:45 am]
BILLING CODE 4910-13-U
