[Federal Register Volume 59, Number 103 (Tuesday, May 31, 1994)]
[Unknown Section]
[Page 0]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 94-13011]
[[Page Unknown]]
[Federal Register: May 31, 1994]
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DEPARTMENT OF TRANSPORTATION
14 CFR Part 39
[Docket No. 94-NM-64-AD; Amendment 39-8922; AD 94-11-06]
Airworthiness Directives; McDonnell Douglas Model MD-11 and MD-
11F Series Airplanes
AGENCY: Federal Aviation Administration, DOT.
ACTION: Final rule; request for comments.
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SUMMARY: This amendment adopts a new airworthiness directive (AD) that
is applicable to certain McDonnell Douglas Model MD-11 and MD-11F
series airplanes. This action requires modification of the external
power feeder cable clamping installation. This amendment is prompted by
reports of damage to the external power feeder cables located under the
forward cargo compartment floor, which was caused by excessive cable
length and/or maintenance personnel stepping on the cables. The actions
specified in this AD are intended to prevent arcing from occurring
under the forward cargo compartment floor as a result of damaged
external power feeder cables, a situation that could lead to a fire at
this location.
DATES: Effective June 15, 1994.
The incorporation by reference of certain publications listed in
the regulations is approved by the Director of the Federal Register as
of June 15, 1994.
Comments for inclusion in the Rules Docket must be received on or
before August 1, 1994.
ADDRESSES: Submit comments in triplicate to the Federal Aviation
Administration (FAA), Transport Airplane Directorate, ANM-103,
Attention: Rules Docket No. 94-NM-64-AD, 1601 Lind Avenue, SW., Renton,
Washington 98055-4056.
The service information referenced in this AD may be obtained from
McDonnell Douglas Corporation, P.O. Box 1771, Long Beach, California
90801-1771, Attention: business Unit Manager, Technical Administrative
support, Dept. L51, M.C. 2-98. This information may be examined at the
FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton,
Washington; or at the FAA, Los Angeles Aircraft Certification Office,
Transport Airplane Directorate, 3229 East Spring Street, Long Beach,
California; or at the Office of the Federal Register, 800 North Capitol
Street, NW., suite 700, Washington, DC.
FOR FURTHER INFORMATION CONTACT: Brett Portwood, Aerospace Engineer,
Systems & Equipment Branch, ANM-130L, Los Angeles Aircraft
Certification Office, FAA, Transport Airplane Directorate, 3229 East
Spring Street, Long Beach, California 90806-2425; telephone (310) 988-
5347; fax (310) 988-5210.
SUPPLEMENTARY INFORMATION: One operator of McDonnell Douglas Model MD-
11 series airplanes recently reported that, during fueling and loading
of cargo, smoke was observed in the forward lower cargo compartment of
one airplane. The forward cargo door was open and no cargo compartment
smoke warning was noted in the cockpit. Maintenance personnel directed
a fire extinguisher into the cargo compartment air outlet at
approximately station Y=635. The airport fire department was notified
and assisted in extinguishing all smoke. No injuries were reported.
Investigation of this incident revealed heat damage under the cargo
floor from station Y=602 to station Y=695, between longerons 48 left-
hand side to 43 right-hand side. Insulation blankets at these locations
were replaced. Vertical supports, part numbers (P/N) ADA0033-2,
suffered possible heat damage and were replaced. Certain wiring located
near the aircraft centerline, station Y=602 to Y=615, was discolored
and replaced. Paint on the lower fuselage in three locations was
slightly darkened. The airplane was repaired prior to return to
service.
Approximately one month later, a second incident occurred on this
same airplane in which, prior to flight, a burning smell was noticed in
the First Class passenger seating area at about the same time that
electrical power was being applied to the airplane. Subsequently, the
airplane would not accept external power. Investigation revealed that
the external power cables had chafed and arced to the fuselage frame at
station Y=655. The metalized covering of one blanket at this location
from the airplane centerline to one yard left of centerline was
missing, and the blanket insulation had burn spots. The cables and
blankets were replaced on this airplane.
Investigation of these incidents by McDonnell Douglas revealed that
the damage to the external power feeder cables located under the
forward cargo compartment floor could have been caused by excessive
cable length and/or maintenance personnel stepping on the cable. Damage
to the cables, such as chafing, can lead to arcing at the subject
location. This condition, if not corrected, could result in a fire
under the forward cargo compartment floor.
The FAA has reviewed and approved McDonnell Douglas Service
Bulletin 24-78, dated May 10, 1994, that describes procedures for
replacing one cable clamp support (standoff) with a new bracket at
station Y=655, and replacing six nylon cable clamps with new metal
clamps having rubber cushions at station Y=635. Modifying the external
power feeder cable clamping installation will minimize the possibility
of damage and chafing of the cables, and thereby minimize the
possibility of arcing and potential resultant fire. The manufacturer
has advised that this installation will be incorporated prior to
delivery on airplanes having manufacturer's serial numbers 559, 560,
562, and subsequent.
Since an unsafe condition has been identified that is likely to
exist or develop on other Model MD-11 and MD-11F series airplanes of
the same type design, this AD is being issued to prevent arcing from
occurring under the forward cargo compartment floor as a result of
damaged external power feeder cables, a situation that could lead to a
fire at this location. This AD requires modification of the external
power feeder cable clamping installation. The actions are required to
be accomplished in accordance with the service bulletin described
previously.
Since a situation exists that requires the immediate adoption of
this regulation, it is found that notice and opportunity for prior
public comment hereon are impracticable, and that good cause exists for
making this amendment effective in less than 30 days.
Comments Invited
Although this action is in the form of a final rule that involves
requirements affecting flight safety and, thus, was not preceded by
notice and an opportunity for public comment, comments are invited on
this rule. Interested persons are invited to comment on this 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 under the caption ADDRESSES. All
communications received on or before the closing date for comments will
be considered, and this rule may be amended in light of the comments
received. Factual information that supports the commenter's ideas and
suggestions is extremely helpful in evaluating the effectiveness of the
AD action and determining whether additional rulemaking action would be
needed.
Comments are specifically invited on the overall regulatory,
economic, environmental, and energy aspects of the rule that might
suggest a need to modify the 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 that
summarizes each FAA-public contact concerned with the substance of this
AD 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-64-AD.'' The postcard will be date stamped and
returned to the commenter.
The regulations adopted herein will 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 final
rule does not have sufficient federalism implications to warrant the
preparation of a Federalism Assessment.
The FAA has determined that this regulation is an emergency
regulation that must be issued immediately to correct an unsafe
condition in aircraft, and is not a ``significant regulatory action''
under Executive Order 12866. It has been determined further that this
action involves an emergency regulation under DOT Regulatory Policies
and Procedures (44 FR 11034, February 26, 1979). If it is determined
that this emergency regulation otherwise would be significant under DOT
Regulatory Policies and Procedures, a final regulatory evaluation will
be prepared and placed in the Rules Docket. A copy of it, if filed, may
be obtained from the Rules Docket at the location provided under the
caption ADDRESSES.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.
Adoption of the Amendment
Accordingly, pursuant to the authority delegated to me by the
Administrator, the Federal Aviation Administration amends 14 CFR part
39 of the Federal Aviation Regulations 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:
94-11-06 McDonnell Douglas: Amendment 39-8922. Docket 94-NM-64-AD.
Applicability: Model MD-11 and MD-11F series airplanes, as
listed in McDonnell Douglas Service Bulletin 24-78, dated May 10,
1994, certificated in any category.
Compliance: Required as indicated, unless accomplished
previously. To prevent arcing from occurring under the forward cargo
compartment floor as a result of damaged external power feeder
cables, a situation that could lead to a fire at this location,
accomplish the following:
(a) Within 90 days after the effective date of this AD, modify
the external power feeder cable clamping installation in accordance
with McDonnell Douglas Service Bulletin 24-78, dated May 10, 1994.
(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: 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.
(d) The modification shall be done in accordance with McDonnell
Douglas Service Bulletin 24-78, dated May 10, 1994. This
incorporation by reference was approved by the Director of the
Federal Register in accordance with 5 U.S.C. 552(a) and 1 CFR Part
51. Copies may be obtained from McDonnell Douglas Corporation, P.O.
Box 1771, Long Beach, California 90801-1771, Attention: business
Unit Manager, Technical Administrative support, Dept. L51, M.C. 2-
98. Copies may be inspected at the FAA, Transport Airplane
Directorate, 1601 Lind Avenue, SW., Renton, Washington; or at the
FAA, Los Angeles Aircraft Certification Office, Transport Airplane
Directorate, 3229 East Spring Street, Long Beach, California; or at
the Office of the Federal Register, 800 North Capitol Street, NW.,
suite 700, Washington, DC.
(e) This amendment becomes effective on June 15, 1994.
Issued in Renton, Washington, on May 23, 1994.
Darrell M. Pederson,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 94-13011 Filed 5-27-94; 8:45 am]
BILLING CODE 4910-13-U
