[Federal Register Volume 64, Number 243 (Monday, December 20, 1999)]
[Rules and Regulations]
[Pages 71001-71003]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 99-32192]
[[Page 71001]]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 99-NM-262-AD; Amendment 39-11463; AD 99-26-03]
RIN 2120-AA64
Airworthiness Directives; McDonnell Douglas Model MD-11 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 series
airplanes. This action requires repetitive general visual inspections
of the power feeder cables, terminal strip, fuseholder, and fuses of
the galley load control unit (GLCU) within the No. 3 bay electrical
power center to detect damage; and corrective actions, if necessary.
This amendment is prompted by an incident of no power to the aft
galleys and two incidents of sparking sounds coming from the G3 galley
due to damage of the No. 3 and 4 wire assembly terminal lugs and
overheating of the power feeder cables on the G3 GLCU. The actions
specified in this AD are intended to prevent such damage due to the
accumulated effects over time from overheating of the power feeder
cables on the G3 GLCU, which could result in smoke and fire in the G3
galley.
DATES: Effective January 4, 2000.
The incorporation by reference of certain publications listed in
the regulations is approved by the Director of the Federal Register as
of January 4, 2000.
Comments for inclusion in the Rules Docket must be received on or
before February 18, 2000.
ADDRESSES: Submit comments in triplicate to the Federal Aviation
Administration (FAA), Transport Airplane Directorate, ANM-114,
Attention: Rules Docket No. 99-NM-262-AD, 1601 Lind Avenue, SW.,
Renton, Washington 98055-4056.
The service information referenced in this AD may be obtained from
Boeing Commercial Aircraft Group, Long Beach 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; 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 and Equipment Branch, ANM-130L, FAA, Transport Airplane
Directorate, Los Angeles Aircraft Certification Office, 3960 Paramount
Boulevard, Lakewood, California 90712-4137; telephone (562) 627-5350;
fax (562) 627-5210.
SUPPLEMENTARY INFORMATION: As part of its practice of re-examining all
aspects of the service experience of a particular aircraft whenever an
accident occurs, the FAA has become aware of one occurrence of no power
to the aft galleys and two occurrences of sparking sounds coming from
the G3 galley. These incidents occurred on McDonnell Douglas Model MD-
11 series airplanes equipped with a certain 120 kilo volts alternating
current (KVA) galley option. The No. 3 and 4 wire assembly of the
galley load control unit (GLCU) had 2 terminal lugs discolored and one
terminal strip with overheated power feeder cables and studs on the
fuseholder. The damage was attributed to the accumulative effects over
time from overheating due to galley current loads on wires improperly
sized for the application. This condition, if not corrected, could
result in damage to the wire assembly terminal lugs and power feeder
cable of the G3 GLCU, which could result in smoke and fire in the G3
galley.
This incident is not considered to be related to an accident that
occurred off the coast of Nova Scotia involving a McDonnell Douglas
Model MD-11 series airplane. The cause of that accident is still under
investigation.
Other Related Rulemaking
The FAA, in conjunction with Boeing and operators of Model MD-11
series airplanes, is continuing to review all aspects of the service
history of those airplanes to identify potential unsafe conditions and
to take appropriate corrective actions. This AD is one of a series of
actions identified during that process. The process is continuing and
the FAA may consider additional rulemaking actions as further results
of the review become available.
Explanation of Relevant Service Information
The FAA has reviewed and approved McDonnell Douglas Alert Service
Bulletin MD11-24A160, Revision 01, dated November 11, 1999, which
describes procedures for repetitive general visual inspections of the
power feeder cables, terminal strip, fuseholder, and fuses of the GLCU
within the No. 3 bay electrical power center; and corrective actions,
if necessary. The corrective actions include replacement of power
feeder cables, fuseholder, and/or fuses, as applicable. Accomplishment
of the actions specified in the service bulletin is intended to
adequately address the identified unsafe condition.
The FAA also has reviewed and approved McDonnell Douglas Alert
Service Bulletin MD11-24A160, dated August 30, 1999, which describes
the same procedures as Revision 01 of the service bulletin. However,
the inspection is only accomplished once, rather than repetitively.
Therefore, this service bulletin is also provided as a source of
accomplishment instructions for the required general visual inspections
and corrective actions.
Explanation of the Requirements of the Rule
Since an unsafe condition has been identified that is likely to
exist or develop on other airplanes of the same type design, this AD is
being issued to prevent damage to the wire assembly terminal lugs and
power feeder cables due to the accumulated effects over time from
overheating of the power feeder cables on the G3 GLCU. This AD requires
accomplishment of the actions specified in the service bulletin
described previously.
Interim Action
This is considered to be interim action until final action is
identified, at which time the FAA may consider further rulemaking.
Determination of Rule's Effective Date
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
[[Page 71002]]
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 rule must submit a self-addressed,
stamped postcard on which the following statement is made: ``Comments
to Docket Number 99-NM-262-AD.'' The postcard will be date stamped and
returned to the commenter.
Regulatory Impact
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 that it 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 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:
99-26-03 McDonnell Douglas: Amendment 39-11463. Docket 99-NM-262-
AD.
Applicability: Model MD-11 series airplanes, as listed in
McDonnell Douglas Alert Service Bulletin MD11-24A160, Revision 01,
dated November 11, 1999; 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 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 wire assembly terminal lugs and power
feeder cables due to the accumulated effects over time from
overheating of the power feeder cable on the G3 galley load control
unit (GLCU), which could result in smoke and fire in the G3 galley,
accomplish the following:
(a) Within 60 days after the effective date of this AD, perform
a general visual inspection of the power feeder cables, terminal
strip, fuseholder, and fuses of the GLCU within the No. 3 bay
electrical power center to detect damage (i.e., discoloration of
affected parts or loose attachments) in accordance with McDonnell
Douglas Alert Service Bulletin MD11-24A160, dated August 30, 1999;
or Revision 01, dated November 11, 1999.
Note 2: For the purposes of this AD, a general visual inspection
is defined as: ``A visual examination of an interior or exterior
area, installation, or assembly to detect obvious damage, failure,
or irregularity. This level of inspection is made under normally
available lighting conditions such as daylight, hangar lighting,
flashlight, or drop-light, and may require removal or opening of
access panels or doors. Stands, ladders, or platforms may be
required to gain proximity to the area being checked.''
(1) If no damage is detected during any inspection required by
this AD, repeat the general visual inspection thereafter at
intervals not to exceed 600 flight hours.
(2) If any damage is detected during any inspection required by
this AD, prior to further flight, replace the power feeder cables,
fuseholder, and/or fuses, as applicable, in accordance with the
service bulletin. Repeat the general visual inspection thereafter at
intervals not to exceed 600 flight hours.
Alternative Methods of Compliance
(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 3: Information concerning the existence of approved
alternative methods of compliance with this AD, if any, may be
obtained from the Los Angeles ACO.
Special Flight Permits
(c) 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.
Incorporation by Reference
(d) The actions shall be done in accordance with McDonnell
Douglas Alert Service Bulletin MD11-24A160, dated August 30, 1999;
or McDonnell Douglas Alert Service Bulletin MD11-24A160, Revision
01, dated November 11, 1999. 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
Boeing Commercial Aircraft Group, Long Beach Division, 3855 Lakewood
Boulevard, Long Beach, California 90846, Attention: Technical
Publications Business Administration, Dept. C1-L51 (2-0). Copies may
be inspected 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; or at the Office of the
Federal Register, 800 North Capitol Street, NW., suite 700,
Washington, DC.
(e) This amendment becomes effective on January 4, 2000.
[[Page 71003]]
Issued in Renton, Washington, on December 7, 1999.
D.L. Riggin,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 99-32192 Filed 12-17-99; 8:45 am]
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