[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