[Federal Register Volume 60, Number 178 (Thursday, September 14, 1995)]
[Rules and Regulations]
[Pages 47677-47678]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 95-21946]
========================================================================
Rules and Regulations
Federal Register
________________________________________________________________________
This section of the FEDERAL REGISTER contains regulatory documents
having general applicability and legal effect, most of which are keyed
to and codified in the Code of Federal Regulations, which is published
under 50 titles pursuant to 44 U.S.C. 1510.
The Code of Federal Regulations is sold by the Superintendent of Documents.
Prices of new books are listed in the first FEDERAL REGISTER issue of each
week.
========================================================================
Federal Register / Vol. 60, No. 178 / Thursday, September 14, 1995 /
Rules and Regulations
[[Page 47677]]
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 95-NM-03-AD; Amendment 39-9355; AD 95-18-08]
Airworthiness Directives; Airbus Model A300-600 Series Airplanes
AGENCY: Federal Aviation Administration, DOT.
ACTION: Final rule.
-----------------------------------------------------------------------
SUMMARY: This amendment adopts a new airworthiness directive (AD),
applicable to all Airbus Model A300-600 series airplanes, that requires
repetitive inspections to detect cracks in the bottom skin of the wing
in the area of the cut out for the pylon rear attachment fitting, and
repair, if necessary. This amendment is prompted by a report indicating
that, during full-scale fatigue testing, a crack was found in the
bottom skin of the wing at the cut out for the aft pylon attachment
fitting due to fatigue-related stress. The actions specified by this AD
are intended to prevent such fatigue-related cracking, which could
result in reduced structural integrity of the wing.
DATES: Effective October 16, 1995.
The incorporation by reference of certain publications listed in
the regulations is approved by the Director of the Federal Register as
of October 16, 1995.
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 all Airbus Model A300-600 series
airplanes was published in the Federal Register on May 2, 1995 (60 FR
21470). That action proposed to require repetitive detailed visual
inspections to detect cracks in the bottom skin of the wing in the area
of the cut out for the pylon rear attachment fitting, and repair, if
necessary.
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.
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.
The FAA estimates that 35 airplanes of U.S. registry will be
affected by this AD, that it will take approximately 6 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 total cost
impact of the AD on U.S. operators is estimated to be $12,600, or $360
per airplane.
The total 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. -
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 USC 106(g), 40101, 40113, 44701.
Sec. 39.13 [Amended]
2. Section 39.13 is amended by adding the following new
airworthiness directive:
95-18-08 Airbus Industrie: Amendment 39-9355. Docket 95-NM-03-AD.
Applicability: All Model A300-600 series airplanes, 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 is affected, the owner/operator must use the authority
provided in paragraph (b) of this AD to request approval from the
FAA. This approval may address either no action, if the current
configuration eliminates the unsafe condition; or different actions
necessary to address the unsafe condition described in this AD. Such
a request should include an assessment of the effect of the changed
configuration on the unsafe condition
[[Page 47678]]
addressed by this AD. In no case does the presence of any modification,
alteration, or repair remove any airplane from the applicability of
this AD.
Compliance: Required as indicated, unless accomplished
previously.
To prevent reduced structural integrity of the wing, accomplish
the following:
(a) Prior to the accumulation of 24,000 total flight cycles
since date of manufacture of the airplane, or within 750 flight
cycles after the effective date of the AD, whichever occurs later,
perform a detailed visual inspection to detect cracks in the bottom
skin of the wing in the area of the cut out for the pylon rear
attachment fitting, in accordance with Airbus Service Bulletin A300-
57-6028, Revision 3, dated September 13, 1994. Repeat the inspection
thereafter at intervals not to exceed 9,000 flight cycles. If any
crack is detected, prior to further flight, repair the wing bottom
skin in accordance with a method approved by the Manager,
Standardization Branch, ANM-113, FAA, Transport Airplane
Directorate.
(b) 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 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.
(c) Special flight permits may be issued in accordance with
Secs. 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.
(d) The inspection shall be done in accordance with Airbus
Service Bulletin A300-57-6028, Revision 3, dated September 13, 1994,
which contains the specified effective pages:
------------------------------------------------------------------------
Revision
level
Page No. shown on Date shown on page
page-
------------------------------------------------------------------------
-1-6-................................... 3- Sept. 13, 1994. -
7-9-.................................... 2- Feb. 22, 1994.
------------------------------------------------------------------------
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.
-(e) This amendment becomes effective on October 16, 1995.
Issued in Renton, Washington, on August 29, 1995.
Darrell M. Pederson,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 95-21946 Filed 9-13-95; 8:45 am]
BILLING CODE 4910-13-U
