[Federal Register Volume 59, Number 211 (Wednesday, November 2, 1994)]
[Proposed Rules]
[Page 0]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 94-27153]
[[Page Unknown]]
[Federal Register: November 2, 1994]
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DEPARTMENT OF TRANSPORTATION
14 CFR Part 39
[Docket No. 94-NM-148-AD]
Airworthiness Directives; Airbus Model A320 Series Airplanes
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 A320 series
airplanes. This proposal would require inspections to determine proper
adjustment of the gap tolerances of the seat track joints at frame 64,
and correction of discrepancies. This proposal would also require
eventual repositioning or replacing the seat tracks on all affected
airplanes, which would terminate the requirement of repetitively
removing or repositioning the seat tracks. This proposal is prompted by
in-service inspection reports, which have revealed that a gap between
the forward and aft seat track at frame 64 could exceed the tolerance
limit due to a method used on the assembly line to control the position
of the seat track. The actions specified by the proposed AD are
intended to ensure that the gap tolerances of the seat track joints do
not exceed the tolerance limit and subsequently lead to separation of
the passenger seats from the seat track under emergency landing
conditions.
DATES: Comments must be received by December 29, 1994.
ADDRESSES: Submit comments in triplicate to the Federal Aviation
Administration (FAA), Transport Airplane Directorate, ANM-103,
Attention: Rules Docket No. 94-NM-148-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-148-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-148-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 A320 series
airplanes. The DGAC advises that in-service inspection reports have
revealed that the gap between the forward and aft seat track at frame
64 (left- and right-hand) could be exceeding the 2.8 mm (.11 inch)
tolerance limit. Investigation revealed that the cause has been
attributed to the method used on the assembly line to control the
position of the seat track. This method is inadequate in monitoring the
gap between the forward and aft seat track of the passenger seats at
frame 64. Incorrectly installed seat tracks, if not corrected, could
result in a gap that exceeds the tolerance limit, and could
subsequently lead to separation of the passenger seats from the seat
track under emergency landing conditions.
Airbus has issued All Operator Telex (AOT) 53-01, dated August 27,
1992, which describes procedures for:
1. Performing a one-time visual inspection to determine if a seat
fitting having an x-plunger behind a z-stud is installed at the seat
track joint at frame 64;
2. Measuring the gap between the forward and aft seat tracks, if
any seat fitting having an x-plunger is installed;
3. Applying sealing material at the seat tracks, if the gap is less
than or equal to 2.8 mm; and
4. Removing or repositioning the seat, if the gap is greater than
2.8 mm.
Airbus has also issued Service Bulletin A320-53-1088, dated May 10,
1993, which describes procedures for repositioning or replacing the
seat tracks.
The DGAC classified the AOT and service bulletin as mandatory and
issued French Airworthiness Directive 93-081-042(B), dated May 26,
1993, 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 a one-time visual
inspection to determine if a seat fitting having an x-plunger behind a
z-stud is installed at the seat track joint at frame 64, and correction
of discrepancies. The proposed AD would also require repositioning or
replacing the seat tracks, which would terminate the requirement of
repetitively removing or repositioning the seat tracks. The actions
would be required to be accomplished in accordance with the service
bulletin described previously. If any cabin equipment other than
passenger seats is installed at frame 64, the correction would be
required to be accomplished in accordance with a method approved by the
FAA.
The FAA estimates that 85 airplanes of U.S. registry would be
affected by this proposed AD.
It would take approximately 7 work hours per airplane to accomplish
the proposed inspection at an average labor rate is $55 per work hour.
Based on these figures, the total cost impact of the inspection
proposed by this AD on U.S. operators is estimated to be $32,725, or
$385 per airplane.
It would take approximately 54 work hours per airplane to
accomplish the proposed modification at an average labor rate of $55
per work hour. Required parts would be supplied by the manufacturer at
no cost to the operators. Based on these figures, the total impact of
the modification proposed by this AD on U.S. operators is estimated to
be $252,450, or $2,970.
Based on above figures, the total cost impact of the proposed
inspection and modification on U.S. operators is estimated to be
$285,175, or $3,355/per airplane.
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-148-AD.
Applicability: Model A320 series airplanes; manufacturer's
serial numbers 002 through 008 inclusive, 010 through 014 inclusive,
016 through 078 inclusive, 080 through 122 inclusive, 124 through
179 inclusive, 183 through 194 inclusive, 196 through 228 inclusive,
230 through 251 inclusive, and 253 through 255 inclusive;
certificated in any category.
Compliance: Required as indicated, unless accomplished
previously.
To prevent separation of the passenger seats from the seat track
during an emergency landing, accomplish the following:
(a) Within 450 flight cycles after the effective date of this
AD, perform a visual inspection to determine if a seat fitting
having an x-plunger behind a z-stud is installed at the seat track
joint at frame 64, in accordance with Airbus All Operator Telex
(AOT) 53-01, dated August 27, 1992.
(b) If such a seat fitting is installed, prior to further
flight, measure the gap between the forward and aft seat tracks in
accordance with the Airbus AOT 53-01, dated August 27, 1992.
(1) If the gap is less than or equal to 2.8 mm, prior to further
flight, apply sealing material at the seat tracks, in accordance
with the AOT.
(2) If the gap is greater than 2.8 mm, prior to further flight,
accomplish the requirements of either paragraph (b)(2)(i) or
(b)(2)(ii) of this AD, as applicable.
(i) For airplanes equipped with passenger seats at frame 64:
Accomplish either paragraph (b)(2)(i)(A) or (b)(2)(i)(B) of this AD:
(A) Remove or reposition the seat in accordance with Airbus AOT
53-01, dated August 27, 1992. Thereafter, repeat the removal or
repositioning whenever the cabin configuration is changed until the
accomplishment of paragraph (c) of this AD. Or
(B) Reposition or replace the seat tracks in accordance with
Airbus Service Bulletin A320-53-1088, dated May 10, 1993. Such
repositioning or replacement constitutes terminating action for the
requirements of this AD.
(ii) For airplanes equipped with equipment other than passenger
seats at frame 64: Prior to further flight, correct the discrepancy
in accordance with a method approved by the Manager, Standardization
Branch, ANM-113, FAA, Transport Airplane Directorate.
(c) Within 30 months after the effective date of this AD,
reposition or replace the seat tracks, in accordance with Airbus
Service Bulletin A320-53-1088, dated May 10, 1993. Accomplishment of
this repositioning or replacement constitutes terminating action for
the requirements of this AD.
(d) 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: Information concerning the existence of approved
alternative methods of compliance with this AD, if any, may be
obtained from the Standardization Branch, ANM-113.
(e) 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.
Issued in Renton, Washington, on October 27, 1994.
Darrell M. Pederson,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 94-27153 Filed 11-1-94; 8:45 am]
BILLING CODE 4910-13-U
