[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