[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]


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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.

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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