[Federal Register Volume 61, Number 245 (Thursday, December 19, 1996)]
[Rules and Regulations]
[Pages 66884-66885]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 96-31112]


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DEPARTMENT OF TRANSPORTATION
14 CFR Part 39

[Docket No. 96-NM-47-AD; Amendment 39-9847; AD 96-25-05]
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 repetitive inspections to detect cracks 
of the rear bracket attached to the outboard rib of the shroud boxes 
and the surfaces of the lugs adjacent to the bushes, and replacement, 
if necessary. This amendment also requires replacement of the outboard 
aft brackets of the shroud boxes with modified brackets that have 
floating boxes, which terminates the repetitive inspections. This 
amendment is prompted by a report that the lug of the rear outboard 
bracket failed due to fatigue. The actions specified by this AD are 
intended to prevent fatigue-related cracking in the subject lug, and 
the consequent failure of this lug; this condition could result in the 
loss of the shroud box and, consequently, lead to reduced 
controllability of the airplane.

DATES: Effective January 27, 1997.
    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of January 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: 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 August 26, 1996 (61 FR 43687). That action proposed to 
require repetitive visual inspections to detect cracks of the rear 
bracket attached to the outboard rib of the shroud boxes and the 
surfaces of the lugs adjacent to the bushes, and replacement, if 
necessary. That action also proposed to require replacement of the 
outboard aft brackets of the shroud boxes with modified brackets with 
floating boxes, which constitutes terminating action for the repetitive 
inspection requirements.
    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

    The FAA estimates that 70 Airbus Model A320-111, -211, -212, and -
231 series airplanes of U.S. registry will be affected by this AD.
    It will take approximately 1 work hour per airplane to accomplish 
the required inspection, at an average labor rate of $60 per work hour. 
Based on these figures, the cost impact of the inspection required by 
this AD on U.S. operators is estimated to be $4,200, or $60 per 
airplane, per inspection cycle.
    It will take approximately 35 work hours per airplane to accomplish 
the required modification, at an average

[[Page 66885]]

labor rate of $60 per work hour. Required parts will cost approximately 
$2,170 per airplane. Based on these figures, the cost impact of the 
modification required by this AD on U.S. operators is estimated to be 
$298,900, or $4,270 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 adding the following new 
airworthiness directive:
96-25-05 Airbus Industrie: Amendment 39-9847. Docket 96-NM-47-AD.

    Applicability: Model A320-111, -211, -212, and -231 series 
airplanes, as listed in Airbus Service Bulletin A320-57-1034, 
Revision 2, dated September 8, 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 owner/operator must request approval for an 
alternative method of compliance in accordance with paragraph (c) 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-related cracking in the shroud box attachment 
lug, which could result in the loss of the shroud box and, 
consequently, lead to reduced controllability of the airplane, 
accomplish the following:
    (a) Prior to the accumulation of 17,000 total landings, or 
within 12 months after the effective date of this AD, whichever 
occurs later, perform a detailed visual inspection to detect cracks 
of the rear bracket attached to the outboard rib of the shroud boxes 
and the surfaces of the lugs adjacent to the bushes, in accordance 
with Airbus Service Bulletin A320-57-1034, Revision 2, dated 
September 8, 1995.

    Note 2: Inspections accomplished prior to the effective date of 
this amendment in accordance with Airbus Service Bulletin A320-57-
1034, Revision 1, dated August 24, 1992, are considered acceptable 
for compliance with the requirements of paragraph (a) of this AD.
    (1) If no crack is detected, repeat the visual inspection 
thereafter at intervals specified in paragraph (a)(1)(i) or 
(a)(1)(ii), as applicable.
    (i) For Model A320-100 series airplanes: Repeat at intervals not 
to exceed 6,000 landings.
    (ii) For Model A320-200 series airplanes: Repeat at intervals 
not to exceed 4,800 landings.
    (2) If any crack is detected, prior to further flight, replace 
the bracket with a modified bracket, in accordance with Airbus 
Service Bulletin A320-57-1035, Revision 4, dated February 22, 1994. 
Accomplishment of this replacement terminates the requirements of 
this AD for that bracket.
    (b) Within 4 years following accomplishment of paragraph (a) of 
this AD, replace the outboard aft brackets of the shroud boxes with 
modified brackets that have floating boxes, in accordance with 
Airbus Service Bulletin A320-57-1035, Revision 4, dated February 22, 
1994. Accomplishment of this replacement constitutes terminating 
action for the repetitive inspections requirements of paragraph (a) 
of this AD.
    (c) 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 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.

    (d) 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.
    (e) The inspections shall be done in accordance with Airbus 
Service Bulletin A320-57-1034, Revision 2, dated September 8, 1995. 
The replacement shall be done in accordance with Airbus Service 
Bulletin A320-57-1035, Revision 4, dated February 22, 1994, which 
contains the following list of effective pages:

------------------------------------------------------------------------
                                   Revision                             
                                    level                               
            Page No.               shown on       Date shown on page    
                                     page                               
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1, 2, 10........................          4  February 22, 1994.         
3-9, 11-16......................          3  January 11, 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.

     (f) This amendment becomes effective on January 23, 1997.

    Issued in Renton, Washington, on December 2, 1996.
Darrell M. Pederson,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 96-31112 Filed 12-18-96; 8:45 am]
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