AD Amdt-39-10732

[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 [<a href="http://www.gpo.gov">www.gpo.gov</a>]
[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:

------------------------------------------------------------------------
                              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