[Federal Register Volume 63, Number 171 (Thursday, September 3, 1998)]
[Rules and Regulations]
[Pages 46876-46878]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 98-23604]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 98-NM-01-AD; Amendment 39-10732; AD 98-18-16]
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 supersedes an existing airworthiness directive
(AD), applicable to certain Airbus Model A320-111, -211, -212, and -231
series airplanes, that currently requires reinforcement of the tail
section of the fuselage at frames 68 and 69. This amendment adds a
requirement for reinforcement of the tail section of the fuselage at
frames 65 to 67. This action also revises the applicability of the
existing AD. This amendment is prompted by reports indicating that the
tail section has struck the runway during takeoffs and landings. The
actions specified by this AD are intended to prevent structural damage
to the tail section when it strikes the runway, which could result in
depressurization of the fuselage during flight.
DATES: Effective October 8, 1998.
The incorporation by reference of Airbus Service Bulletin A320-53-
1110, Revision 1, dated November 27, 1995, and Airbus Service Bulletin
A320-53-1131, dated July 24, 1997, as listed in the regulations, is
approved by the Director of the Federal Register as of October 8, 1998.
The incorporation by reference of Airbus Service Bulletin A320-53-
1110, dated August 28, 1995, was approved previously by the Director of
the Federal Register as of May 15, 1997 (62 FR 17532, April 10, 1997).
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) by superseding AD 97-08-04,
amendment 39-9992 (62 FR 17532, April 10, 1997), which is applicable to
certain Airbus Model A320-111, -211, -212, and -231 series airplanes,
was published in the Federal Register on July 9, 1998 (63 FR 37078).
The action proposed to supersede AD 97-08-04 to continue to require
reinforcement of the tail section of the fuselage at frames 68 and 69.
It also proposed to add a requirement for reinforcement of the tail
section of the fuselage at frames 65 to 67. The action also proposed to
revise the applicability of the existing AD.
[[Page 46877]]
Comments
Interested persons have been afforded an opportunity to participate
in the making of this amendment. Due consideration has been given to
the single comment received.
The commenter supports the proposed rule.
Conclusion
After careful review of the available data, including the comment
noted above, the FAA has determined that air safety and the public
interest require the adoption of the rule as proposed.
Cost Impact
There are approximately 118 airplanes of U.S. registry that will be
affected by this AD.
The actions that are currently required by AD 97-08-04, and
retained in this AD, take approximately 196 work hours per airplane to
accomplish, at an average labor rate of $60 per work hour. Required
parts will be provided by the manufacturer at no cost to the operators.
Based on these figures, the cost impact of the currently required
actions on U.S. operators is estimated to be $1,387,680, or $11,760 per
airplane.
The new actions that are required by this new AD will take
approximately 488 work hours per airplane to accomplish, at an average
labor rate of $60 per work hour. Required parts will be provided by the
manufacturer at no cost to the operators. Based on these figures, the
cost impact of the new requirements of this AD on U.S. operators is
estimated to be $3,455,040, or $29,280 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 removing amendment 39-9992 (62 FR
17532, April 10, 1997), and by adding a new airworthiness directive
(AD), amendment 39-10732, to read as follows:
98-18-16 Airbus Industrie: Amendment 39-10732. Docket 98-NM-01-AD.
Supersedes AD 97-08-04, Amendment 39-9992.
Applicability: Model A320 series airplanes on which Airbus
Modification 22764 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 (d) 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 structural damage to the tail section when it strikes
the runway, which could result in depressurization of the fuselage
during flight, accomplish the following:
Restatement of Requirement of AD 97-08-04
(a) For airplanes listed in Airbus Service Bulletin A320-53-
1110, dated August 28, 1995: Within 6 years after May 15, 1997 (the
effective date of AD 97-08-04, amendment 39-9992), modify the
fuselage by reinforcing frames 68 and 69 in accordance with Airbus
Service Bulletin A320-53-1110, dated August 28, 1995; or Revision 1,
dated November 27, 1995.
New Requirements of this AD
(b) For airplanes other than those identified in paragraph (a)
of this AD: Within 5 years after the effective date of this AD,
modify the fuselage by reinforcing frames 68 and 69 in accordance
with Airbus Service Bulletin A320-53-1110, dated August 28, 1995, or
Revision 1, dated November 27, 1995.
(c) For all airplanes: Within 5 years after the effective date
of this AD, modify the fuselage by reinforcing frames 65 to 67 in
accordance with Airbus Service Bulletin A320-53-1131, dated July 24,
1997.
(d) 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.
(e) 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.
(f) The modifications shall be done in accordance with Airbus
Service Bulletin A320-53-1131, dated July 24, 1997; Airbus Service
Bulletin A320-53-1110, dated August 28, 1995; and Airbus Service
Bulletin A320-53-1110, Revision 1, dated November 27, 1995, which
contains the following list of effective pages:
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Revision level shown
Page No. on page Date shown on page
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1-8, 10-13, 15-20, 23-40, Original............ August 28, 1995.
42, 44-45.
[[Page 46878]]
9, 14, 21-22, 41, 43........ Revision 1.......... November 27, 1995.
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(1) The incorporation by reference of Airbus Service Bulletin
A320-53-1110, Revision 1, dated November 27, 1995, and Airbus
Service Bulletin A320-53-1131, dated July 24, 1997, is approved by
the Director of the Federal Register in accordance with 5 U.S.C.
552(a) and 1 CFR part 51.
(2) The incorporation by reference of Airbus Service Bulletin
A320-53-1110, dated August 28, 1995, was approved previously by the
Director of the Federal Register as of May 15, 1997 (62 FR 17532,
April 10, 1997).
(3) 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 97-315-109(B), dated October 22, 1997.
(g) This amendment becomes effective on October 8, 1998.
Issued in Renton, Washington, on August 26, 1998.
Vi L. Lipski,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 98-23604 Filed 9-2-98; 8:45 am]
BILLING CODE 4910-13-U
