[Federal Register Volume 63, Number 113 (Friday, June 12, 1998)]
[Proposed Rules]
[Pages 32154-32156]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 98-15675]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 98-NM-73-AD]
RIN 2120-AA64
Airworthiness Directives; McDonnell Douglas Model DC-10-10, -15,
-30, and -40 Series Airplanes
AGENCY: Federal Aviation Administration, DOT.
ACTION: Notice of proposed rulemaking (NPRM).
-----------------------------------------------------------------------
SUMMARY: This document proposes the adoption of a new airworthiness
directive (AD) that is applicable to certain McDonnell Douglas Model
DC-10-10, -15, -30, and -40 series airplanes. This proposal would
require installation of a new protector cap in all fuel tank boost/
transfer pump housings. This proposal is prompted by reports of
inoperative fuel boost/transfer pumps due to arcing or burning of the
electrical connector. The actions specified by the proposed AD are
intended to prevent damage to the fuel tank boost/transfer pump
housings in case of an electrical connector malfunction, which could
result in increased risk of a fuel tank explosion or fire.
DATES: Comments must be received by July 27, 1998.
ADDRESSES: Submit comments in triplicate to the Federal Aviation
Administration (FAA), Transport Airplane Directorate, ANM-114,
Attention: Rules Docket No. 98-NM-73-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: Roscoe Van Dyke, Aerospace Engineer,
Propulsion Branch, ANM-140L, FAA, Transport Airplane Directorate, Los
Angeles Aircraft Certification Office, 3960 Paramount Boulevard,
Lakewood, California 90712-4137; telephone (562) 627-5254; 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
[[Page 32155]]
must submit a self-addressed, stamped postcard on which the following
statement is made: ``Comments to Docket Number 98-NM-73-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-73-AD, 1601 Lind Avenue, SW., Renton, Washington
98055-4056.
Discussion
As part of its long-term, continued operational safety program, the
FAA has been conducting an ongoing, comprehensive review of large
transport category airplanes with respect to designs and service
histories associated with fuel tank-related problems. In particular,
the FAA is focusing on all potential fuel tank ignition sources.
While some of the more recent investigations have focused on
electrical power wiring in the fuel tanks, this proposed AD focuses on
the electrical connectors inside the pump housings and the associated
damage to the fuel pump housings that can be created when arcing occurs
between pins on worn connectors.
The FAA has reviewed past reports of inoperative fuel boost/
transfer pumps on McDonnell Douglas Model DC-10 series airplanes. Some
of the failures have been attributed to arcing or burning of the
electrical connectors of these pumps, which, in some cases, resulted in
damage to the fuel pump housings. The pump electrical connector is
located inside the pump housing, which is located in the fuel tank. If
the arcing burns through the pump housing, it could ignite fuel vapors.
(No reports of burn-throughs of the housing have been received,
however.)
Based on this review, the FAA has determined that installation of a
protector cap in all fuel pump housings is necessary to prevent the
possibility of damage to the pump housing in case of an electrical
connector malfunction. This condition, if not corrected, could result
in increased risk of a fuel tank explosion or fire.
Explanation of Relevant Service Information
The FAA has reviewed and approved McDonnell Douglas DC-10 Service
Bulletin 28-97, dated May 10, 1982, and Revision 1, dated October 8,
1985, which describes procedures for installation of a new protector
cap in all fuel tank boost/transfer pump housings. Accomplishment of
the action specified in the service bulletin 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 service bulletin described previously.
Cost Impact
There are approximately 188 airplanes of the affected design in the
worldwide fleet. The FAA estimates that 151 airplanes of U.S. registry
would be affected by this proposed AD.
For airplanes identified as Group I in the referenced service
bulletin, it would take approximately 12 work hours per airplane to
accomplish the proposed modification, at an average labor rate of $60
per work hour. Required parts would cost approximately $3,400 per
airplane. Based on these figures, the cost impact of the modification
proposed by this AD on U.S. operators of Group I airplanes is estimated
to be $4,120 per airplane.
For airplanes identified as Group II in the referenced service
bulletin, it would take approximately 15 work hours per airplane to
accomplish the proposed modification, at an average labor rate of $60
per work hour. Required parts would cost approximately $4,100 per
airplane. Based on these figures, the cost impact of the modification
proposed by this AD on U.S. operators of Group II airplanes is
estimated to be $5,000 per airplane.
For airplanes identified as Group III in the referenced service
bulletin, it would take approximately 17 work hours per airplane to
accomplish the proposed modification, at an average labor rate of $60
per work hour. Required parts would cost approximately $4,800 per
airplane. Based on these figures, the cost impact of the modification
proposed by this AD on U.S. operators of Group III airplanes is
estimated to be $5,820 per airplane.
The cost impact figures discussed above are 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-73-AD.
Applicability: Model DC-10-10, -15, -30, and -40 series
airplanes, as listed in McDonnell Douglas DC-10 Service Bulletin 28-
97, Revision 1, dated October 8, 1985; 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 (b) of
this AD. The request should include an assessment of the effect of
the modification, alteration, or
[[Page 32156]]
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 damage to the fuel tank boost/transfer pump housings
in case of an electrical connector malfunction, which could result
in increased risk of a fuel tank explosion or fire, accomplish the
following:
(a) Within 24 months after the effective date of this AD,
install a new protector cap in all fuel tank boost/transfer pump
housings in accordance with McDonnell Douglas DC-10 Service Bulletin
28-97, dated May 10, 1982, or Revision 1, dated October 8, 1985.
(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, 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 compliance with this AD, if any, may be
obtained from the Los Angeles ACO.
(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 June 5, 1998.
Darrell M. Pederson,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 98-15675 Filed 6-11-98; 8:45 am]
BILLING CODE 4910-13-U