[Federal Register Volume 63, Number 86 (Tuesday, May 5, 1998)]
[Proposed Rules]
[Pages 24762-24764]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 98-11890]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 98-NM-10-AD]
RIN 2120-AA64
Airworthiness Directives; McDonnell Douglas Model DC-9-80 Series
Airplanes and Model MD-90-30 and MD-88 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 all McDonnell Douglas Model DC-9-
80 series airplanes and Model MD-90-30 and MD-88 airplanes. This
proposal would require a one-time inspection of the harness assembly of
the tailcone emergency evacuation slide to determine the diameter of
the swaged balls; reidentification of the harness assembly; and
reinstallation or replacement of the assembly with a new assembly, if
necessary. This proposal is prompted by a failed deployment of the
tailcone emergency evacuation slide during a system test conducted by
the manufacturer. The actions specified by the proposed AD are intended
to prevent failure of the tailcone emergency evacuation slide to deploy
automatically due to incorrect diameter of the swaged balls on the wire
rope of the harness assembly.
DATES: Comments must be received by June 19, 1998.
ADDRESSES: Submit comments in triplicate to the Federal Aviation
Administration (FAA), Transport Airplane Directorate, ANM-114,
Attention: Rules Docket No. 98-NM-10-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 The Boeing Company, Douglas Products Division, 3855
Lakewood Boulevard, Long Beach, California 90846, Attention: Technical
Publications Business Administration, Dept. C1-L51 (2-60). This
information may be examined at the FAA, Transport Airplane Directorate,
1601 Lind Avenue, SW., Renton, Washington; or at the FAA, Transport
Airplane Directorate, Los Angeles Aircraft Certification Office, 3960
Paramount Boulevard, Lakewood, California.
FOR FURTHER INFORMATION CONTACT: Alan Sinclair, Aerospace Engineer,
Systems and Equipment Branch, ANM-130L, FAA, Transport Airplane
Directorate, Los Angeles Aircraft Certification Office, 3960 Paramount
Boulevard, Lakewood, California 90712-4137; telephone (562) 627-5338;
fax (562) 627-5210.
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 98-NM-10-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-114, Attention: Rules
Docket No. 98-NM-10-AD, 1601 Lind Avenue, SW., Renton, Washington
98055-4056.
[[Page 24763]]
Discussion
During an FAA-required system test of the tailcone emergency
evacuation slide conducted by the manufacturer, the slide failed to
deploy automatically. Reports indicate that the swaged ball on the
deployment harness of the slide pulled off the wire rope, thus
preventing the automatic deployment of the slide. An analysis of this
incident revealed that the swaged ball on the harness assembly had
pulled off the wire rope due to incorrect diameter of the swaged ball.
This condition, if not corrected, could result in failure of the
tailcone emergency evacuation slide to deploy automatically.
Explanation of Relevant Service Information
The FAA has reviewed and approved McDonnell Douglas Alert Service
Bulletins MD80-25A364 [for Model DC-9-81 (MD-81), DC-9-82 (MD-82), DC-
9-83 (MD-83), and DC-9-87 (MD-87) series airplanes, and Model MD-88
airplanes]; and MD90-25A030 (for Model MD-90-30 airplanes); both dated
October 30, 1997; which describe procedures for a one-time inspection
of the harness assembly (container deployment harness) of the tailcone
emergency evacuation slide to determine the diameter of the swaged
balls; reidentification of the harness assembly; and reinstallation or
replacement of the assembly with a new assembly, if necessary. For
airplanes on which the diameter of the swaged ball is within specified
limits, the alert service bulletins describe procedures for
reinstallation of the reidentified harness assembly. However, for
airplanes on which the diameter of the swaged ball is outside specified
limits, the alert service bulletins describe procedures for replacement
of the harness assembly with a new harness assembly. Accomplishment of
the actions specified in the service bulletins is intended to
adequately address the identified unsafe condition.
Explanation of Requirements of Proposed Rule
Since an unsafe condition has been identified that is likely to
exist or develop on other products of this same type design, the
proposed AD would require accomplishment of the actions specified in
the alert service bulletins described previously.
Cost Impact
There are approximately 943 airplanes of the affected design in the
worldwide fleet. The FAA estimates that 570 airplanes of U.S. registry
would be affected by this proposed AD, that it would take approximately
2 work hours per airplane to accomplish the proposed action and that
the average labor rate is $60 per work hour. Based on these figures,
the cost impact of the proposed AD on U.S. operators is estimated to be
$68,400, or $120 per airplane.
The 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.
Regulatory Impact
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. 106(g), 40113, 44701.
Sec. 39.13 [Amended]
2. Section 39.13 is amended by adding the following new
airworthiness directive:
McDonnell Douglas: Docket 98-NM-10-AD.
Applicability: All Model DC-9-81 (MD-81), DC-9-82 (MD-82), DC-9-
83 (MD-83), and DC-9-87 (MD-87) series airplanes; and Model MD-88
and MD-90-30 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 request approval for an
alternative method of compliance in accordance with paragraph (c) of
this AD. The request should include an assessment of the effect of
the modification, alteration, or repair on the unsafe condition
addressed by this AD; and, if the unsafe condition has not been
eliminated, the request should include specific proposed actions to
address it.
Compliance: Required as indicated, unless accomplished
previously.
To prevent failure of the tailcone emergency evacuation slide to
deploy automatically due to incorrect diameter of the swaged balls
on the wire rope of the harness assembly, accomplish the following:
(a) Within 180 days after the effective date of this AD, perform
a one-time inspection of the harness assembly of the tailcone
emergency evacuation slide to determine the diameter of the swaged
balls; in accordance with McDonnell Douglas Alert Service Bulletin
MD80-25A364 [for Model DC-9-81 (MD-81), DC-9-82 (MD-82), DC-9-83
(MD-83), and DC-9-87 (MD-87) series airplanes, and Model MD-88
airplanes]; or MD90-25A030 (for Model MD-90-30 airplanes); both
dated October 30, 1997.
(1) If the swaged balls are within the limits specified in the
applicable alert service bulletin, prior to further flight,
reidentify and reinstall the harness assembly in accordance with the
applicable alert service bulletin.
(2) If the swaged balls are outside the limits specified in the
applicable alert service bulletin, prior to further flight, replace
the harness assembly having part number (P/N) 8370024-3 with a new
harness assembly having P/N 8370024-9 or 8370024-3H, as applicable,
in accordance with the applicable alert service bulletin.
(b) As of the effective date of this AD, no person shall install
a harness assembly (P/N) 8370024-3, on any airplane.
(c) 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, Los Angeles Aircraft Certification
Office (ACO), 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, Los Angeles ACO.
Note 2: Information concerning the existence of approved
alternative methods of
[[Page 24764]]
compliance with this AD, if any, may be obtained from the Los
Angeles ACO.
(d) 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 April 29, 1998.
John J. Hickey,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 98-11890 Filed 5-4-98; 8:45 am]
BILLING CODE 4910-13-U