[Federal Register Volume 62, Number 100 (Friday, May 23, 1997)]
[Rules and Regulations]
[Pages 28324-28325]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 97-12857]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 96-NM-106-AD; Amendment 39-10030; AD 97-11-01]
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 
an initial inspection of fastener holes on certain outer frames of the 
fuselage to detect fatigue cracking, and modification of this area by 
cold expanding these holes and installing oversized fasteners. This 
amendment is prompted by a report from the manufacturer indicating 
that, during full-scale fatigue testing of the test article, fatigue 
cracking was detected in the area where the center fuselage joins the 
wing. The actions specified by this AD are intended to prevent fatigue 
cracking and consequent reduced structural integrity of this area, 
which could lead to rapid depressurization of the fuselage.

DATES: Effective June 27, 1997.
    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of June 27, 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: Tim Backman, Aerospace Engineer, 
Standardization Branch, ANM-113, FAA, Transport Airplane Directorate, 
1601 Lind Avenue, SW., Renton, Washington 98055-4056; telephone (425) 
227-2797; 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 February 20, 1997 
(62 FR 7727). That action proposed to require an initial eddy current 
rotation probe inspection to detect fatigue cracking in certain 
fastener holes in the area where the center fuselage joins the wing, 
and a modification to improve the resistance of this area to fatigue 
cracking.
    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.
    Both 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 24 Airbus Model A320 series airplanes of 
U.S. registry will be affected by this AD.
    It will take approximately 25 work hours per airplane to accomplish 
the required actions, at an average labor rate of $60 per work hour. 
Required parts will cost approximately $557 per airplane. Based on 
these figures, the cost impact of the AD on U.S. operators is estimated 
to be $49,368, or $2,057 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

[[Page 28325]]

``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:

97-11-01  Airbus Industrie: Amendment 39-10030. Docket 96-NM-106-AD.

    Applicability: Model A320 series airplanes as listed in Airbus 
Service Bulletin A320-53-1026, dated August 5, 1994; on which 
modifications 21281P1495 and 21680P1818 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 (e) 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 fatigue cracking in the area where the center 
fuselage joins the wing, which could reduce the structural integrity 
of this area and consequently result in rapid decompression of the 
fuselage, accomplish the following:
    (a) Prior to the accumulation of 16,000 total landings, or 
within 6 months after the effective date of this AD, whichever 
occurs later, perform an eddy current rotating probe inspection to 
detect fatigue cracking in the fastener holes of the outer frame 
flanges of left and right fuselage frames 37 through 41, adjacent to 
Stringer 23, in accordance with Airbus Service Bulletin A320-53-
1026, dated August 5, 1994.

    Note 2: Prior to the effective date of this AD, accomplishment 
of any modification in accordance with Airbus Service Bulletin A320-
53-1025, dated August 5, 1994, is considered acceptable for 
compliance with the modification requirements of paragraphs (b), 
(c)(1)(i), (c)(2) and (d) of this AD.

    (b) If the inspection required by paragraph (a) of this AD 
detects no cracking in any hole: Prior to the accumulation of 6,000 
landings after this inspection, modify each hole in accordance with 
Paragraph 2.B.(5) of Airbus Service Bulletin A320-53-1025, Revision 
1, dated November 24, 1994. Thereafter, no further action is 
required by this AD.
    (c) If the inspection required by paragraph (a) of this AD 
detects any cracking in no more than one hole per frame cap, 
accomplish the requirements of paragraphs (c)(1) and (c)(2) of this 
AD:
    (1) Prior to further flight, repair this cracked hole and 
conduct another rotating probe inspection of this hole to detect 
cracking, in accordance with Paragraph 2.B.(6) of Airbus Service 
Bulletin A320-53-1025, Revision 1, dated November 24, 1994.
    (i) If no cracking of this repaired hole is detected: Prior to 
further flight, modify this hole in accordance with Paragraph 
2.B.(6)(c) of this service bulletin. Thereafter, no further action 
with regard to this hole is required by this AD.
    (ii) If any cracking of this repaired hole is detected: Prior to 
further flight, repair this hole in a manner approved by the 
Manager, Standardization Branch, ANM-113, FAA, Transport Airplane 
Directorate. Thereafter, no further action with regard to this hole 
is required by this AD.
    (2) Prior to the accumulation of 6,000 landings after the 
inspection required by paragraph (a) of this AD; modify all other 
holes in accordance with Paragraph 2.B.(5) of Airbus Service 
Bulletin A320-53-1025, Revision 1, dated November 24, 1994. 
Thereafter, no further action is required by this AD with respect to 
these holes.
    (d) If the inspection required by paragraph (a) of this AD 
detects any cracking in more than one hole per frame cap, or if this 
inspection detects any cracking in any frame: Prior to further 
flight, repair the discrepant area in a manner approved by the 
Manager, Standardization Branch, ANM-113; and modify all other holes 
in accordance with Paragraph 2.B.(5) of Airbus Service Bulletin 
A320-53-1025, Revision 1, dated November 24, 1994. Thereafter, no 
further action is required by this AD.
    (e) 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. 
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 3: Information concerning the existence of approved 
alternative methods of compliance with this AD, if any, may be 
obtained from the Standardization Branch, ANM-113.

    (f) 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.
    (g) The actions shall be done in accordance with Airbus Service 
Bulletin A320-53-1026, dated August 5, 1994; and Airbus Service 
Bulletin A320-53-1025, Revision 1, dated November 24, 1994. Airbus 
Service Bulletin A320-53-1025, Revision 1, dated November 24, 1994, 
contains the following list of effective pages:

------------------------------------------------------------------------
                                  Revision level                        
            Page No.              shown on page     Date shown on page  
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1-12, 17.......................  1..............  November 24, 1994.    
13-16, 18, 19..................  Original.......  August 5, 1994.       
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    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.
    (h) This amendment becomes effective on June 27, 1997.

    Issued in Renton, Washington, on May 12, 1997.
Darrell M. Pederson,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 97-12857 Filed 5-22-97; 8:45 am]
BILLING CODE 4910-13-U