Airworthiness Directives; Airbus Model A310 and A300-600 Series Airplanes Equipped With SOGERMA-SOCEA Pilot, Co-Pilot, and Third Occupant Seats

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]

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