[Federal Register Volume 63, Number 186 (Friday, September 25, 1998)]
[Rules and Regulations]
[Pages 51279-51281]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 98-25473]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 97-NM-192-AD; Amendment 39-10797; AD 98-20-30]
RIN 2120-AA64
Airworthiness Directives; Airbus Model A320 Series Airplanes
Equipped With a Bulk Cargo Door
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 series airplanes equipped with a
bulk cargo door, that requires repetitive inspections to detect fatigue
cracking of the upper frame flanges; and repair, if necessary. This
amendment also requires modification of the upper frame flanges of the
bulk cargo door, which constitutes 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 fatigue cracking of the upper frame flanges, which could
result in reduced structural integrity of the airplane.
DATES: Effective October 30, 1998.
The incorporation by reference of certain publications listed in
the regulations is approved by the Director of the Federal Register as
of October 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 all Airbus Model A320 series
airplanes equipped with a bulk cargo door was published in the Federal
Register on August 7, 1998 (63
[[Page 51280]]
FR 42286). That action proposed to require repetitive inspections to
detect fatigue cracking of the upper frame flanges; and repair, if
necessary. That action also proposed to require modification of the
upper frame flanges of the bulk cargo door, which constitutes
terminating action for the repetitive inspections.
Comments
Interested persons have been afforded an opportunity to participate
in the making of this amendment. No comments were submitted in response
to the proposal or the FAA's determination of the cost to the public.
Conclusion
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 8 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 these figures, the cost impact of the inspection required by
this AD on U.S. operators is estimated to be $480, or $60 per airplane,
per inspection cycle.
It will take approximately 4 work hours per airplane to accomplish
the required modification, at an average labor rate of $60 per work
hour. Based on these figures, the cost impact of the modification
required by this AD on U.S. operators is estimated to be $1,920, or
$240 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.
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:
98-20-30 Airbus Industrie: Amendment 39-10797. Docket 97-NM-192-AD.
Applicability: Model A320 series airplanes, equipped with a bulk
cargo door (Airbus Modification 20029), 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 of the upper frame flanges, 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 1,200 flight cycles after the effective date of this AD,
whichever occurs later: Perform a high frequency eddy current
inspection to detect fatigue cracking of the upper frame flanges, in
accordance with Airbus Service Bulletin A320-53-1022, Revision 1,
dated June 18, 1992.
(1) If no cracking is detected, accomplish either paragraph
(a)(1)(i) or (a)(1)(ii) of this AD.
(i) Repeat the eddy current inspection thereafter at intervals
not to exceed 1,200 flight cycles until accomplishment of the
requirements of paragraph (b) of this AD. Or
(ii) Prior to further flight, modify the upper frame flanges, in
accordance with Airbus Service Bulletin A320-53-1021, Revision 1,
dated April 13, 1992. This modification constitutes terminating
action for the requirements of this AD.
(2) If any cracking is detected, prior to further flight, repair
in accordance with Airbus Service Bulletin A320-53-1021, Revision 1,
dated April 13, 1992.
Accomplishment of the repair constitutes terminating action for
the requirements of this AD.
(b) Prior to the accumulation of 26,000 total flight cycles, or
within 6,000 flight cycles after the effective date of this AD,
whichever occurs later: Perform a high frequency eddy current
inspection to detect fatigue cracking of the upper frame flanges, in
accordance with Airbus Service Bulletin A320-53-1021, Revision 1,
dated April 13, 1992.
(1) If no cracking is detected, prior to further flight, modify
the upper frame flanges, in accordance with the service bulletin.
Accomplishment of this modification constitutes terminating action
for the requirements of this AD.
(2) If any cracking is detected, prior to further flight, repair
in accordance with the service bulletin. Accomplishment of the
repair constitutes terminating action for the 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
Secs. 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 inspections, repairs, and modification shall be done in
accordance with the following Airbus service bulletins, which
contain the specified effective pages:
[[Page 51281]]
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Service bulletin referenced Page number shown Revision level shown on
and date on page page Date shown on page
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A320-53-1022,................ 1-6 1.......................... June 18, 1992.
Revision 1,.................. ......................... .................................
June 18, 1992................ 7, 8 Original................... October 17, 1991.
A320-53-1021,................ 1, 4-24 1.......................... April 13, 1992
Revision 1,.................. .........................
April 13, 1992............... 2, 3 Original................... October 17, 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.
Note 3: The subject of this AD is addressed in French
airworthiness directive 96-238-091(B), dated October 23, 1996.
(f) This amendment becomes effective on October 30, 1998.
Issued in Renton, Washington, on September 17, 1998.
Darrell M. Pederson,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 98-25473 Filed 9-24-98; 8:45 am]
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