[Federal Register Volume 61, Number 146 (Monday, July 29, 1996)]
[Rules and Regulations]
[Pages 39315-39317]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 96-18771]


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


DEPARTMENT OF TRANSPORTATION
14 CFR Part 39

[Docket No. 95-NM-208-AD; Amendment 39-9699; AD 96-15-09]
RIN 2120-AA64


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

AGENCY: Federal Aviation Administration, DOT.

ACTION: Final rule.

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

SUMMARY: This amendment adopts a new airworthiness directive (AD), 
applicable to certain Airbus Model A320-111, -211, and -231 series 
airplanes, that requires repetitive high

[[Page 39316]]

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 amendment also requires the installation 
of a modification for each affected fastener hole, which terminates the 
repetitive inspections. This amendment 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 this AD are intended to prevent such 
fatigue cracking, which could result in rapid depressurization of the 
airplane.

DATES: Effective September 3, 1996.
    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of September 3, 1996.

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 (206) 
227-2797; 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, and -231 series airplanes was published in the Federal Register on 
March 28, 1996 (61 FR 13789). That action proposed to 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. That action also proposed to require 
the installation of a modification for each affected fastener hole, 
which would terminate the repetitive inspections.
    Interested persons have been afforded an opportunity to participate 
in the making of this amendment. Due consideration has been given to 
the comments received.

Support for the Proposal

    One commenter supports the proposal.

Request To Revise Proposed Compliance Time

    One commenter requests that the compliance time for the inspection 
specified in proposed paragraph (a) be revised. The commenter points 
out that the proposal specifies that the initial inspection is to be 
accomplished prior to the accumulation of 15,000 total landings, or 
within 3 months after the effective date of the final rule, whichever 
occurs first. ``The commenter requests that this compliance time be 
changed to ``* * * whichever occurs later.'' Since the threshold for 
the proposed action is at 15,000 total flight cycles, the 3-month 
``grace period'' should follow rather than precede the threshold.
    The FAA concurs. The compliance language that appeared in the 
proposal was in error; it should have contained the phrase ``* * * 
whichever occurs later,'' rather than ``* * * whichever occurs first.'' 
The FAA has revised the final rule accordingly.

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 with the change previously 
described. The FAA has determined that this change will neither 
increase the economic burden on any operator nor increase the scope of 
the AD.

Cost Impact

    The FAA estimates that 21 airplanes of U.S. registry will be 
affected by this AD, that it will take approximately 5 work hours per 
airplane to accomplish the required actions, and that the average labor 
rate is $60 per work hour. Based on these figures, the cost impact of 
the inspection requirements of this AD on U.S. operators is estimated 
to be $6,300, or $300 per airplane, per inspection cycle.
    The modification will take approximately 10 work hours to 
accomplish, at an average labor rate of $60 per work hour. Required 
parts will cost approximately $311 per airplane. Based on these 
figures, the cost impact of the modification requirements of this AD on 
U.S. operators is estimated to be $19,131, or $911 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:

96-15-09 Airbus Industrie: Amendment 39-9699. 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

[[Page 39317]]

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 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 
within 3 months after the effective date of this AD, whichever 
occurs later, 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 
within 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.
    (e) The inspection shall be done in accordance with Airbus 
Service Bulletin A320-53-1082, Revision 1, dated November 9, 1994, 
which contains the following list of effective pages:

------------------------------------------------------------------------
    Page No.-         Revision level shown on page    Date shown on page
------------------------------------------------------------------------
1, 3.............  1 -..............................  November 9, 1994. 
2, 4-19-.........  Original.........................  February 8, 1994. 
------------------------------------------------------------------------

    The modification shall be done in accordance with Airbus Service 
Bulletin A320-53-1044, dated February 8, 1994. The incorporation by 
reference of these documents 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 September 3, 1996.

    Issued in Renton, Washington, on July 18, 1996.
Stewart R. Miller,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 96-18771 Filed 7-26-96; 8:45 am]
BILLING CODE 4910-13-U