[Federal Register Volume 62, Number 69 (Thursday, April 10, 1997)]
[Rules and Regulations]
[Pages 17532-17534]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 97-9009]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 96-NM-93-AD; Amendment 39-9992; AD 97-08-04]
RIN 2120-AA64
Airworthiness Directives; Airbus Model A320-111, -211, -212, and
-231 Series Airplanes
AGENCY: Federal Aviation Administration, DOT.
ACTION: Final rule.
-----------------------------------------------------------------------
SUMMARY: This amendment adopts a new airworthiness directive (AD),
applicable to certain Airbus Model A320-111, -211, -212, and -231
series airplanes, that requires reinforcement of the tail section of
the fuselage at frames 68 and 69. 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; that
[[Page 17533]]
condition, if not detected, could result in depressurization of the
fuselage during flight.
DATES: Effective May 15, 1997.
The incorporation by reference of certain publications listed in
the regulations is approved by the Director of the Federal Register as
of May 15, 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: Charles Huber, Aerospace Engineer,
Standardization Branch, ANM-113, FAA, Transport Airplane Directorate,
1601 Lind Avenue, SW., Renton, Washington 98055-4056; telephone (206)
227-2589; fax (206) 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 A320-111, -
211, -212, and -231 series airplanes was published in the Federal
Register on October 23, 1996 (61 FR 54960). That action proposed to
require modification of the tail section of the airplane by
reinforcement of the fuselage at frames 68 and 69.
Interested persons have been afforded an opportunity to participate
in the making of this amendment. Due consideration has been given to
the comments received.
Support for the Proposal
One commenter supports the proposed AD.
Request to Extend the Compliance Time
One commenter requests that the compliance time for the
modification be extended from the proposed 4 years to 6 years. This
commenter points out that further analysis conducted by Airbus has
indicated that additional fuselage frames, beyond those addressed by
the proposal, may also be affected. Airbus has indicated that it will
release a new Service Bulletin A320-53-1131, which will contain
procedures that include modification of these additional frames. In
anticipation of the imminent release of this service information, the
commenter requests that the compliance time of the proposed AD be
extended in order to allow the rework of all affected areas to be
performed at the same time.
The FAA concurs with the commenter's request to extend the
compliance time. The FAA acknowledges that Airbus will soon release a
new service bulletin to address other affected fuselage frames. In
addition, the Direction Generale de l'Aviation Civile (DGAC), which is
the airworthiness authority for France, has already issued French
airworthiness directive (CN) 96-009-074(B)R1, which provides for a
compliance time of 6 years for modification of the fuselage frames
addressed in Airbus Service Bulletin A320-53-1110.
The FAA also acknowledges that, due to the magnitude of both the
modification required by this AD action, as well as the modification of
the additional frames that may be included in the new service bulletin,
performing both modifications at the same time will decrease the chance
for human error to occur and, thus, enhance safety.
Once the new service bulletin is released and reviewed, the FAA may
consider additional rulemaking for accomplishment of the pertinent
modifications identified in Airbus Service Bulletin A320-53-1131.
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 with the change previously
described. The FAA has determined that this change will neither
increase the economic burden on any operator nor increase the scope of
the AD.
Cost Impact
The FAA estimates that 97 Airbus Model A320-111, -211, -212, and -
231 series airplanes of U.S. registry will be affected by this AD, that
it will take approximately 196 work hours per airplane to accomplish
the required actions, and that the average labor rate is $60 per work
hour. Required parts will be provided by the manufacturer at no cost to
operators. Based on these figures, the cost impact of the AD on U.S.
operators is estimated to be $1,140,720, or $11,760 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:
97-08-04 Airbus Industrie: Amendment 39-9992. Docket 96-NM-93-AD.
Applicability: Model A320-111, -211, -212, and -231 series
airplanes, as listed in Airbus Service Bulletin A320-53-1110, dated
August 28, 1995; 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
[[Page 17534]]
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 prevent structural damage to the tail section of the airplane
when it strikes the runway which, if undetected, could result in
depressurization of the fuselage during flight, accomplish the
following:
(a) Within 6 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.
(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, Standardization Branch, ANM-113,
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,
Standardization Branch, ANM-113.
Note 2: Information concerning the existence of approved
alternative methods of compliance with this AD, if any, may be
obtained from the Standardization Branch, ANM-113.
(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 A320-53-1110, dated August 28, 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.
(e) This amendment becomes effective on May 15, 1997.
Issued in Renton, Washington, on April 2, 1997.
Darrell M. Pederson,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 97-9009 Filed 4-9-97; 8:45 am]
BILLING CODE 4910-13-U
