[Federal Register Volume 63, Number 122 (Thursday, June 25, 1998)]
[Rules and Regulations]
[Pages 34556-34558]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 98-16053]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 97-NM-250-AD; Amendment 39-10602; AD 98-13-14]
RIN 2120-AA64
Airworthiness Directives; Airbus Model A320 Series Airplanes
AGENCY: Federal Aviation Administration, DOT.
ACTION: Final rule.
-----------------------------------------------------------------------
SUMMARY: This amendment adopts a new airworthiness directive (AD),
applicable to certain Airbus Model A320 series airplanes, that requires
repetitive rotating probe inspections of fastener holes and/or the
adjacent tooling hole of a former junction of the aft fuselage, and
corrective action, if necessary. This amendment also provides for
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 prevent reduced structural
integrity of the aft fuselage caused by fatigue cracking of the former
junction at frame 68.
DATES: Effective July 30, 1998.
[[Page 34557]]
The incorporation by reference of certain publications listed in
the regulations is approved by the Director of the Federal Register as
of July 30, 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 20, 1998 (63
FR 19421). That action proposed to require repetitive rotating probe
inspections of fastener holes and/or the adjacent tooling hole of a
former junction of the aft fuselage, and corrective action, if
necessary. That action also provided for 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 10 Airbus Model A320 series airplanes of
U.S. registry will be affected by this AD.
Should an operator be required to accomplish the inspection of the
fastener holes and the adjacent tooling hole, it will take
approximately 8 work hours per airplane to accomplish this inspection,
at an average labor rate of $60 per work hour. Based on these figures,
the cost impact of this inspection required by this AD on U.S.
operators is estimated to be $480 per airplane, per inspection cycle.
Should an operator be required to accomplish the inspection of only
the tooling hole, it will take approximately 3 work hours per airplane
to accomplish this inspection, at an average labor rate of $60 per work
hour. Based on these figures, the cost impact of this inspection
required by this AD on U.S. operators is estimated to be $180 per
airplane, per inspection cycle.
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 elect to accomplish the optional terminating
action specified in this AD, it would take approximately 9 work hours
to cold work the fastener holes and tooling hole, or 3 work hours to
cold work (only) the tooling hole. The average labor rate is $60 per
work hour. Based on these figures, the cost impact of the optional
terminating action would be $540 per airplane for cold working the
fastener hole and tooling holes, or $180 per airplane for cold working
(only) the tooling hole.
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:
98-13-14 Airbus Industrie: Amendment 39-10602. Docket 97-NM-250-AD.
Applicability: Model A320 series airplanes, as listed in Airbus
Service Bulletins A320-53-1089 and A320-53-1090, both dated November
22, 1995; on which Airbus Modifications 21780 and 21781 (reference
Airbus Service Bulletin A320-53-1090) have 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 (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 cracking of the former junction at
frame 68, which could result in reduced structural integrity of the
aft fuselage, accomplish the following:
(a) Prior to the accumulation of 20,000 total flight cycles, or
within 500 flight cycles after the effective date of this AD,
whichever occurs later, perform a rotating probe inspection for
fatigue cracking of the fastener holes and/or the adjacent tooling
hole, as applicable, of the right- and left-hand former junctions at
frame 68, in accordance with Airbus Service Bulletin A320-53-1089,
dated November 22, 1995.
(1) If no crack is detected, accomplish either paragraph
(a)(1)(i) or (a)(1)(ii) of this AD.
(i) Repeat the inspection thereafter at intervals not to exceed
20,000 flight cycles.
Or
[[Page 34558]]
(ii) Prior to further flight following the accomplishment of the
inspection required by paragraph (a) of this AD, cold work the
fastener holes and/or the adjacent tooling hole of the right- and
left-hand former junctions at frame 68, as applicable, in accordance
with Airbus Service Bulletin A320-53-1090, dated November 22, 1995.
Accomplishment of this cold working constitutes terminating action
for the repetitive inspections required by this AD.
(2) If any crack is detected, prior to further flight, repair it
in accordance with a method approved by the Manager, International
Branch, ANM-116, FAA, Transport Airplane Directorate.
(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.
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.
(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) Except as provided by paragraph (a)(2) of this AD, the
actions shall be done in accordance with Airbus Service Bulletin
A320-53-1089, dated November 22, 1995 and Airbus Service Bulletin
A320-53-1090, dated November 22, 1995. 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 96-298-093(B)R1, dated January 29, 1997.
(e) This amendment becomes effective on July 30, 1998.
Issued in Renton, Washington, on June 11, 1998.
Darrell M. Pederson,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 98-16053 Filed 6-24-98; 8:45 am]
BILLING CODE 4910-13-U
