[Federal Register Volume 61, Number 61 (Thursday, March 28, 1996)]
[Proposed Rules]
[Pages 13789-13791]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 96-7548]



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DEPARTMENT OF TRANSPORTATION
14 CFR Part 39

[Docket No. 95-NM-208-AD]


Airworthiness Directives; Airbus Model A320-111, -211, and -231 
Series Airplanes

AGENCY: Federal Aviation Administration, DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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SUMMARY: This document proposes the adoption of a new airworthiness 
directive (AD) that is applicable to certain Airbus Model A320-111, -
211, and -231 series airplanes. This proposal would require repetitive 
high frequency eddy current inspections to detect cracks around the 
fasteners of the lower forward corners of the sliding window frames, 
and repair, if necessary. This proposal would also require installation 
of a modification for each affected fastener hole, which would 
terminate the repetitive inspections. This proposal is prompted by the 
results of full-scale fatigue tests which indicated that fatigue 
cracking occurred on the lower forward corner of the sliding window 
frames at frame 4. The actions specified by the proposed AD are 
intended to prevent such fatigue cracking, which could result in rapid 
depressurization of the airplane.

DATES: Comments must be received by May 6, 1996.

ADDRESSES: Submit comments in triplicate to the Federal Aviation 
Administration (FAA), Transport Airplane Directorate, ANM-103, 
Attention: Rules Docket No. 95-NM-208-AD, 1601 Lind Avenue, SW., 
Renton, Washington 98055-4056. Comments may be inspected at this 
location between 9:00 a.m. and 3:00 p.m., Monday through Friday, except 
Federal holidays.
    The service information referenced in the proposed rule may be 
obtained from Airbus Industrie, 1 Rond Point Maurice Bellonte, 31707 
Blagnac Cedex, France. This information may be examined at the FAA, 
Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, 
Washington.

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 (206) 
227-2797; fax (206) 227-1149.

SUPPLEMENTARY INFORMATION:

Comments Invited

    Interested persons are invited to participate in the making of the

[[Page 13790]]
proposed rule by submitting such written data, views, or arguments as 
they may desire. Communications shall identify the Rules Docket number 
and be submitted in triplicate to the address specified above. All 
communications received on or before the closing date for comments, 
specified above, will be considered before taking action on the 
proposed rule. The proposals contained in this notice may be changed in 
light of the comments received.
    Comments are specifically invited on the overall regulatory, 
economic, environmental, and energy aspects of the proposed rule. All 
comments submitted will be available, both before and after the closing 
date for comments, in the Rules Docket for examination by interested 
persons. A report summarizing each FAA-public contact concerned with 
the substance of this proposal will be filed in the Rules Docket.
    Commenters wishing the FAA to acknowledge receipt of their comments 
submitted in response to this notice must submit a self-addressed, 
stamped postcard on which the following statement is made: ``Comments 
to Docket Number 95-NM-208-AD.'' The postcard will be date stamped and 
returned to the commenter.

Availability of NPRMs

    Any person may obtain a copy of this NPRM by submitting a request 
to the FAA, Transport Airplane Directorate, ANM-103, Attention: Rules 
Docket No. 95-NM-208-AD, 1601 Lind Avenue, SW., Renton, Washington 
98055-4056.

Discussion

    The Direction Generale de l'Aviation Civile (DGAC), which is the 
airworthiness authority for France, recently notified the FAA that an 
unsafe condition may exist on certain Airbus Model A320-111, -211, and 
-231 series airplanes. The DGAC advises that, during full-scale fatigue 
tests on a Model A320 series airplane test article, fatigue cracking 
was found on the lower forward corner of the sliding window frames at 
frame 4. Fatigue cracking on the lower forward corner of the sliding 
window frames at frame 4, if not detected and corrected in a timely 
manner, could result in rapid depressurization of the airplane.
    Airbus has issued Service Bulletin A320-53-1082, Revision 1, dated 
November 9, 1994, which describes procedures for a high frequency eddy 
current inspection to detect cracks around the five fasteners of the 
lower forward corners of the sliding window frames at frame 4. For 
cases where no cracks are detected during inspection, the service 
bulletin describes procedures for either conducting repetitive 
inspections, or installing Modification 23685P3199. The service 
bulletin also permits further flight with cracking around the five 
fasteners.
    Airbus has also issued Service Bulletin A320-53-1044, dated 
February 8, 1994, which describes procedures for installation of 
Modification 23685P3199. The modification entails cold working each of 
the five fastener holes on each side and installing a tension bolt. 
Accomplishment of the modification on each of the 5 fasteners on each 
side would eliminate the need for the repetitive inspections.
    The DGAC classified these service bulletins as mandatory and issued 
French airworthiness directive 94-166-056(B), dated July 20, 1994, in 
order to assure the continued airworthiness of these airplanes in 
France.
    This airplane model is manufactured in France and is type 
certificated for operation in the United States under the provisions of 
section 21.29 of the Federal Aviation Regulations (14 CFR 21.29) and 
the applicable bilateral airworthiness agreement. Pursuant to this 
bilateral airworthiness agreement, the DGAC has kept the FAA informed 
of the situation described above. The FAA has examined the findings of 
the DGAC, reviewed all available information, and determined that AD 
action is necessary for products of this type design that are 
certificated for operation in the United States.
    Since an unsafe condition has been identified that is likely to 
exist or develop on other airplanes of the same type design, the 
proposed AD would require high frequency eddy current inspection(s) to 
detect cracks around the 5 fasteners of the lower forward corners of 
the sliding window frames at frame 4. For cases where no cracks are 
detected during inspection, the proposed AD would require installation 
of Modification 23685P3199, which would constitute terminating action 
for the repetitive inspection requirements. The actions would be 
required to be accomplished in accordance with the procedures of the 
service bulletins described previously.
    Operators should note that, unlike the procedures described in the 
referenced service bulletin, this proposed AD would not permit further 
flight with cracking detected around any of the 5 fasteners of the 
lower forward corner of the sliding window frame at frame 4. The FAA 
has determined that, due to the safety implications and consequences 
associated with such cracking, all cracks that are found must be 
repaired prior to further flight. The repair would be required to be 
accomplished in accordance with a method approved by the FAA.
    The FAA estimates that 21 airplanes of U.S. registry would be 
affected by this proposed AD, that it would take approximately 5 work 
hours per airplane to accomplish the proposed actions, and that the 
average labor rate is $60 per work hour. Based on these figures, the 
cost impact of the proposed AD on U.S. operators is estimated to be 
$6,300, or $300 per airplane, per inspection cycle.
    The cost impact figure discussed above is based on assumptions that 
no operator has yet accomplished any of the proposed requirements of 
this AD action, and that no operator would accomplish those actions in 
the future if this AD were not adopted.
    The regulations proposed herein would 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 
proposal would not have sufficient federalism implications to warrant 
the preparation of a Federalism Assessment.
    For the reasons discussed above, I certify that this proposed 
regulation (1) is not a ``significant regulatory action'' under 
Executive Order 12866; (2) is not a ``significant rule'' under the DOT 
Regulatory Policies and Procedures (44 FR 11034, February 26, 1979); 
and (3) if promulgated, 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 copy of the draft 
regulatory evaluation prepared for this action is contained in the 
Rules Docket. A copy of it may be obtained by contacting the Rules 
Docket at the location provided under the caption ADDRESSES.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Safety.

The Proposed Amendment

    Accordingly, pursuant to the authority delegated to me by the 
Administrator, the Federal Aviation Administration proposes to amend 
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:


[[Page 13791]]

    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:

Airbus Industrie: Docket 95-NM-208-AD.

    Applicability: Model A320-111, -211, and -231 series airplanes; 
manufacturer's serial numbers 002 through 008 inclusive, 010 through 
014 inclusive, 016 through 078 inclusive, and 080 through 098 
inclusive; certificated in any category.

    Note 1: This AD applies to each airplane identified in the 
preceding applicability provision, regardless of whether it has been 
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 are 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 cracking on the lower forward corner of the 
sliding window frames at frame 4, which could result in rapid 
depressurization of the airplane, accomplish the following:
    (a) Prior to the accumulation of 15,000 total landings, or 3 
months after the effective date of this AD, whichever occurs first, 
perform a high frequency eddy current inspection to detect cracks 
around the 5 fasteners of the lower forward corners of the sliding 
window frames at frame 4, in accordance with the procedures of 
Airbus Service Bulletin A320-53-1082, Revision 1, dated November 9, 
1994.
    (1) If no cracks are detected, repeat the inspection thereafter 
at intervals not to exceed 15,000 landings.
    (2) If any crack is detected, prior to further flight, repair it 
in accordance with a method approved by the Manager, Standardization 
Branch, ANM-113, FAA, Transport Airplane Directorate.
    (b) Prior to the accumulation of 30,000 total landings, or 5 
years after the effective date of this AD, whichever occurs later, 
accomplish Airbus Modification 23685P3199 for each fastener hole, in 
accordance with Airbus Service Bulletin A320-53-1044, dated February 
8, 1994. Accomplishment of the modification constitutes terminating 
action for the repetitive inspection 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. 
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.

    (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.

    Issued in Renton, Washington, on March 22, 1996.
Darrell M. Pederson,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 96-7548 Filed 3-27-96; 8:45 am]
BILLING CODE 4910-13-P