[Federal Register Volume 59, Number 241 (Friday, December 16, 1994)]
[Unknown Section]
[Page 0]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 94-30943]
[[Page Unknown]]
[Federal Register: December 16, 1994]
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DEPARTMENT OF TRANSPORTATION
14 CFR Part 39
[Docket No. 94-NM-191-AD]
Airworthiness Directives; Airbus Model A310 and A300-600 Series
Airplanes Equipped With SOGERMA-SOCEA Pilot, Co-Pilot, and Third
Occupant Seats
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 A310 and
A300-600 series airplanes. This proposal would require repetitive
inspections to detect distortion and/or cracks on the attachment
brackets of the backrest recline control locks of certain seats. This
proposal would also require replacement of cracked or distorted
brackets and their associated attachment fittings with new parts, which
would terminate the repetitive inspection requirements. This proposal
is prompted by a report of failure of the bracket of the backrest
recline control lock on a seat due to fatigue-related cracking. The
actions specified by the proposed AD are intended to prevent such
fatigue-related cracking and/or distortion, which could result in
failure of the seat backrest attach fittings, which may lead to the
uncommanded 50 deg. angle recline of the pilot or co-pilot seat, and,
subsequently, the temporary inability of the pilots to control the
airplane.
DATES: Comments must be received by January 27, 1995.
ADDRESSES: Submit comments in triplicate to the Federal Aviation
Administration (FAA), Transport Airplane Directorate, ANM-103,
Attention: Rules Docket No. 94-NM-191-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: 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.
SUPPLEMENTARY INFORMATION:
Comments Invited -
Interested persons are invited to participate in the making of the
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 94-NM-191-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. 94-NM-191-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 A310 and A300-600
series airplanes equipped with certain SOGERMA-SOCEA pilot, co-pilot,
and third occupant seats. The DGAC advises that a report has been
received of failure of the bracket of the backrest recline control lock
on a seat after the airplane accumulated 21,762 total flight hours.
Investigation has revealed that the cause of this failure has been
attributed to fatigue-related cracking. Fatigue cracks and/or
distortion of the bracket of the backrest recline control lock, if not
detected and corrected in a timely manner, could result in failure of
the seat backrest attach fittings, and the subsequent uncommanded 50
angle recline of the pilot or co-pilot seat; this situation could lead
to the temporary inability of the pilots to control the airplane. -
SOGERMA-SOCEA has issued Service Bulletin 25-229, dated November
26, 1993, which describes procedures for repetitive detailed visual
inspections to detect distortion and/or cracks on the attachment
brackets of the backrest recline control locks. This service bulletin
also describes procedures for replacement of both of the brackets and
their associated attachment fittings with new parts, which would
eliminate the need for the repetitive inspections. The DGAC classified
this service bulletin as mandatory and issued French airworthiness
directive 94-188-162(B), dated August 17, 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 registered
in the United States, the proposed AD would require repetitive detailed
visual inspections to detect distortion and/or cracks on the attachment
brackets of the seat backrest recline control locks. This proposed AD
would also require replacement of both of the brackets and their
associated attachment fittings with new parts; this replacement would
constitute terminating action for repetitive inspection requirements.
The actions would be required to be accomplished in accordance with the
service bulletin described previously. -
As a result of recent communications with the Air Transport
Association (ATA) of America, the FAA has learned that, in general,
some operators may misunderstand the legal effect of AD's on airplanes
that are identified in the applicability provision of the AD, but that
have been altered or repaired in the area addressed by the AD. The FAA
points out that all airplanes identified in the applicability provision
of an AD are legally subject to the AD. If an airplane has been altered
or repaired in the affected area in such a way as to affect compliance
with the AD, the owner or operator is required to obtain FAA approval
for an alternative method of compliance with the AD, in accordance with
the paragraph of each AD that provides for such approvals. A note has
been included in this notice to clarify this requirement. -
The FAA estimates that 49 airplanes of U.S. registry would be
affected by this proposed AD, that it would take approximately 4 work
hours per airplane to accomplish the proposed actions, and that the
average labor rate is $60 per work hour. Required parts would be
supplied by the manufacturer at no cost to the operators. Based on
these figures, the total cost impact of the proposed AD on U.S.
operators is estimated to be $11,760, or $240 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 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:
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:
Airbus Industrie: Docket 94-NM-191-AD.
Applicability: Model A310 and A300-600 series airplanes equipped
with SOGERMA-SOCEA pilot, co-pilot, and third occupant seats; as
listed in SOGERMA-SOCEA Service Bulletin 25-229, dated November 26,
1993; 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 fatigue cracks and/or distortion in the seat bracket
of the backrest recline control lock, which could result in failure
of the seat backrest attach fittings, the uncommanded 50 deg. angle
recline of the pilot or co-pilot seat, and, subsequently, lead to
the temporary inability of the pilots to control the airplane,
accomplish the following:
(a) Prior to the accumulation of 10,000 total flight hours or
within 500 flight hours after the effective date of this AD,
whichever occurs later, perform a detailed visual inspection to
detect distortion and/or cracks on the attachment brackets of the
backrest recline control locks of certain seats, in accordance with
SOGERMA-SOCEA Service Bulletin 25-229, dated November 26, 1993.
(1) If no bracket is distorted or cracked, repeat the inspection
thereafter at intervals not to exceed 5,000 flight hours.
(2) If any bracket is distorted or cracked, prior to further
flight, replace both of the brackets and their associated attachment
fittings with new parts, in accordance with the service bulletin.
Accomplishment of this replacement constitutes terminating action
for the repetitive inspection requirements of this AD.
(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.
Issued in Renton, Washington, on December 12, 1994.
Darrell M. Pederson,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 94-30943 Filed 12-15-94; 8:45 am]
BILLING CODE 4910-13-P
