AD Amdt-39-10602

[Federal Register Volume 63, Number 122 (Thursday, June 25, 1998)]
[Rules and Regulations]
[Pages 34556-34558]
From the Federal Register Online via the Government Publishing Office [<a href="http://www.gpo.gov">www.gpo.gov</a>]
[FR Doc No: 98-16053]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 97-NM-250-AD; Amendment 39-10602; AD 98-13-14]
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 adopts a new airworthiness directive (AD), 
applicable to certain Airbus Model A320 series airplanes, that requires 
repetitive rotating probe inspections of fastener holes and/or the 
adjacent tooling hole of a former junction of the aft fuselage, and 
corrective action, if necessary. This amendment also provides for 
optional 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 reduced structural 
integrity of the aft fuselage caused by fatigue cracking of the former 
junction at frame 68.
DATES: Effective July 30, 1998.

[[Page 34557]]

    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of July 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 certain Airbus Model A320 series 
airplanes was published in the Federal Register on April 20, 1998 (63 
FR 19421). That action proposed to require repetitive rotating probe 
inspections of fastener holes and/or the adjacent tooling hole of a 
former junction of the aft fuselage, and corrective action, if 
necessary. That action also provided for optional terminating action 
for the repetitive inspections.

Comments

    Interested persons have been afforded an opportunity to participate 
in the making of this amendment. Due consideration has been given to 
the two comments received.
    The commenters support the proposed rule.

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 as proposed.

Cost Impact

    The FAA estimates that 10 Airbus Model A320 series airplanes of 
U.S. registry will be affected by this AD.
    Should an operator be required to accomplish the inspection of the 
fastener holes and the adjacent tooling hole, it will take 
approximately 8 work hours per airplane to accomplish this inspection, 
at an average labor rate of $60 per work hour. Based on these figures, 
the cost impact of this inspection required by this AD on U.S. 
operators is estimated to be $480 per airplane, per inspection cycle.
    Should an operator be required to accomplish the inspection of only 
the tooling hole, it will take approximately 3 work hours per airplane 
to accomplish this inspection, at an average labor rate of $60 per work 
hour. Based on these figures, the cost impact of this inspection 
required by this AD on U.S. operators is estimated to be $180 per 
airplane, per inspection cycle.
    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.
    Should an operator elect to accomplish the optional terminating 
action specified in this AD, it would take approximately 9 work hours 
to cold work the fastener holes and tooling hole, or 3 work hours to 
cold work (only) the tooling hole. The average labor rate is $60 per 
work hour. Based on these figures, the cost impact of the optional 
terminating action would be $540 per airplane for cold working the 
fastener hole and tooling holes, or $180 per airplane for cold working 
(only) the tooling hole.

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:

98-13-14 Airbus Industrie: Amendment 39-10602. Docket 97-NM-250-AD.

    Applicability: Model A320 series airplanes, as listed in Airbus 
Service Bulletins A320-53-1089 and A320-53-1090, both dated November 
22, 1995; on which Airbus Modifications 21780 and 21781 (reference 
Airbus Service Bulletin A320-53-1090) have 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 (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 detect and correct fatigue cracking of the former junction at 
frame 68, which could result in reduced structural integrity of the 
aft fuselage, accomplish the following:
    (a) Prior to the accumulation of 20,000 total flight cycles, or 
within 500 flight cycles after the effective date of this AD, 
whichever occurs later, perform a rotating probe inspection for 
fatigue cracking of the fastener holes and/or the adjacent tooling 
hole, as applicable, of the right- and left-hand former junctions at 
frame 68, in accordance with Airbus Service Bulletin A320-53-1089, 
dated November 22, 1995.
    (1) If no crack is detected, accomplish either paragraph 
(a)(1)(i) or (a)(1)(ii) of this AD.
    (i) Repeat the inspection thereafter at intervals not to exceed 
20,000 flight cycles.

Or


[[Page 34558]]


    (ii) Prior to further flight following the accomplishment of the 
inspection required by paragraph (a) of this AD, cold work the 
fastener holes and/or the adjacent tooling hole of the right- and 
left-hand former junctions at frame 68, as applicable, in accordance 
with Airbus Service Bulletin A320-53-1090, dated November 22, 1995. 
Accomplishment of this cold working constitutes terminating action 
for the repetitive inspections required by this AD.
    (2) If any crack is detected, prior to further flight, repair it 
in accordance with a method approved by the Manager, International 
Branch, ANM-116, FAA, Transport Airplane Directorate.
    (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, International Branch, ANM-116. 
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.

    (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) Except as provided by paragraph (a)(2) of this AD, the 
actions shall be done in accordance with Airbus Service Bulletin 
A320-53-1089, dated November 22, 1995 and Airbus Service Bulletin 
A320-53-1090, dated November 22, 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.

    Note 3: The subject of this AD is addressed in French 
airworthiness directive 96-298-093(B)R1, dated January 29, 1997.

    (e) This amendment becomes effective on July 30, 1998.

    Issued in Renton, Washington, on June 11, 1998.
Darrell M. Pederson,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 98-16053 Filed 6-24-98; 8:45 am]
BILLING CODE 4910-13-U