[Federal Register Volume 60, Number 98 (Monday, May 22, 1995)]
[Rules and Regulations]
[Pages 27005-27007]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 95-11907]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 94-NM-193-AD; Amendment 39-9231; AD 95-10-14]
Airworthiness Directives; Airbus Model A300, A310, and A300-600
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 all Airbus Model A300, A310, and A300-600 series
airplanes, that requires repetitive mechanical and electrical
inspections to detect chafing of electrical wiring; and repair or
replacement of discrepant parts, and repositioning the looms. This
amendment is prompted by reports of wire chafing in the forward avionic
compartment. The actions specified by this AD are intended to prevent
such chafing, which may lead to a short in the electrical circuits at
the 104VU panel; this condition could result in unwanted
depressurization, loss of wing de-icing, and loss of in-flight engine
restart capability.
DATES: Effective June 21, 1995.
The incorporation by reference of certain publications listed in
the regulations is approved by the Director of the Federal Register as
of June 21, 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: Stephen Slotte, Aerospace Engineer,
Standardization Branch, ANM-113, FAA, Transport Airplane Directorate,
1601 Lind Avenue, SW., Renton, Washington 98055-4056; telephone (206)
227-2797; fax (206) 227-1320.
[[Page 27006]] 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, A310, and A300-600 series airplanes was published in the Federal
Register on January 4, 1995 (60 FR 384). That action proposed to
require repetitive mechanical and electrical inspections to detect
discrepancies; and repair or replacement of discrepant parts, and
repositioning the looms.
Interested persons have been afforded an opportunity to participate
in the making of this amendment. Due consideration has been given to
the comments received.
Two commenters support the proposed rule.
One commenter requests that the proposal be revised to include
removal of the avionics bay ladder as an optional terminating action
for the repetitive inspections. The commenter states that removing the
avionics bay ladder will prevent future chafing. The commenter states
that it has removed the avionics bay ladder in accordance with the
Airplane Maintenance Manual and will request an alternative method of
compliance. The FAA does not concur with the commenter's request to
revise the final rule. The FAA does not consider it appropriate to
include various provisions in an AD applicable to a single operator's
unique configuration of an affected airplane. Paragraph (b) of this AD
provides for the approval of an alternative method of compliance to
address these types of unique configurations.
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.
This is considered to be interim action. The manufacturer has
advised that it currently is developing a modification that will
positively address the unsafe condition addressed by this AD. Once this
modification is developed, approved, and available, the FAA may
consider additional rulemaking.
The FAA estimates that 69 airplanes of U.S. registry will be
affected by this AD, that it will take approximately 1 work hour 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 $4,140, or $60
per airplane, per inspection cycle.
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 U.S.C. App. 1354(a), 1421 and 1423; 49 U.S.C.
106(g); and 14 CFR 11.89.
Sec. 39.13 [Amended]
2. Section 39.13 is amended by adding the following new
airworthiness directive:
95-10-14 Airbus Industrie: Amendment 39-9231. Docket 94-NM-193-AD.
Applicability: All Model A300, A310, and 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) 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 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 unwanted depressurization, loss of wing de-icing, and
loss of in-flight engine restart capability, accomplish the
following:
(a) Within 600 flight hours or 6 months after the effective date
of this AD, whichever occurs first, accomplish paragraphs (a)(1) and
(a)(2) of this AD.
(1) Perform mechanical inspections to detect discrepancies, in
accordance with paragraph 4.2.1. of Airbus All Operators Telex AOT
24-05, Revision 1, dated June 7, 1994. Repeat the inspection
thereafter at intervals not to exceed 1,050 flight hours. If any
discrepancy is detected, prior to further flight, repair or replace
discrepant parts, and perform an electrical inspection in accordance
with the AOT.
(2) Perform an electrical inspection to detect discrepancies, in
accordance with paragraph 4.2.2. of Airbus All Operators Telex AOT
24-05, Revision 1, dated June 7, 1994. Repeat the inspection
thereafter at intervals not to exceed 18 months. If any discrepancy
is detected, prior to further flight, repair or replace discrepant
parts, and reposition the looms, in accordance with the AOT.
-(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
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.
(d) The inspections, repair, and replacement shall be done in
accordance with Airbus All Operators Telex AOT 24-05, Revision 1,
dated June 7, 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
[[Page 27007]] 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 June 21, 1995.
Issued in Renton, Washington, on May 9, 1995.
Darrell M. Pederson,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 95-11907 Filed 5-19-95; 8:45 am]
BILLING CODE 4910-13-U
