[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]



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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.


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    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]
BILLING CODE 4910-13-P