AD 2002-17-06

[Federal Register Volume 67, Number 169 (Friday, August 30, 2002)]
[Rules and Regulations]
[Pages 55716-55718]
From the Federal Register Online via the Government Publishing Office [<a href="http://www.gpo.gov">www.gpo.gov</a>]
[FR Doc No: 02-22127]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2002-NM-195-AD; Amendment 39-12872; AD 2002-17-06]
RIN 2120-AA64


Airworthiness Directives; McDonnell Douglas Model MD-11 Airplanes

AGENCY: Federal Aviation Administration, DOT.

ACTION: Final rule; request for comments.

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SUMMARY: This amendment supersedes an existing airworthiness directive 
(AD), applicable to certain McDonnell Douglas Model MD-11 airplanes, 
that currently 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. That AD 
also currently requires replacement of the electrical wiring of the 
galley in the electrical power center in bays 1, 2, and 3 with larger 
gage cable assemblies, which terminates the repetitive inspections. 
This amendment removes the replacement requirement and reinstates the 
repetitive inspections and corrective actions if necessary. This 
amendment is prompted by information from the airplane manufacturer 
that accomplishment of the replacement required by the existing AD 
could result in additional wire chafing damage in the electrical power 
center (EPC) due to insufficient clearance from structure. The actions 
specified in this AD are intended to prevent such chafing, and 
consequent arcing and smoke and fire in the EPC, and to prevent damage 
to the wire assembly terminal lugs and overheating of the power feeder 
cables on the No. 3 and No. 4 galley load control unit, which could 
result in smoke and fire in the center accessory compartment.

DATES: Effective September 16, 2002.
    The incorporation by reference of certain publications, as listed 
in the regulations, was approved previously by the Director of the 
Federal Register as of January 4, 2000 (64 FR 71001, December 20, 
1999).
    Comments for inclusion in the Rules Docket must be received on or 
before October 29, 2002.

ADDRESSES: Submit comments in triplicate to the Federal Aviation 
Administration (FAA), Transport Airplane Directorate, ANM-114, 
Attention: Rules Docket No. 2002-NM-195-AD, 1601 Lind Avenue, SW., 
Renton, Washington 98055-4056. Comments may be inspected at this 
location between 9 a.m. and 3 p.m., Monday through Friday, except 
Federal holidays. Comments may be submitted via fax to (425) 227-1232. 
Comments may also be sent via the Internet using the following address: 
<a href="/cdn-cgi/l/email-protection#053c28646b68286c6477666a6868606b71456364642b626a73"><span class="__cf_email__" data-cfemail="0c35216d626121656d7e6f6361616962784c6a6d6d226b637a">[email&#160;protected]</span></a>. Comments sent via fax or the Internet must 
contain ``Docket No. 2002-NM-195-AD'' in the subject line and need not 
be submitted in triplicate. Comments sent via the Internet as attached 
electronic files must be formatted in Microsoft Word 97 for Windows or 
ASCII text.
    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: Data and Service 
Management, Dept. C1-L5A (D800-0024). 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, 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: Technical Information: Brett Portwood, 
Aerospace Engineer, Systems and Equipment Branch, ANM-130L, FAA, Los 
Angeles Aircraft Certification Office, 3960 Paramount Boulevard, 
Lakewood, California 90712-4137; telephone (562) 627-5350; fax (562) 
627-5210.
    Other Information: Sandi Carli, Airworthiness Directive Technical 
Writer/Editor; telephone (425) 687-4243, fax (425) 227-1232. Questions 
or comments may also be sent via the Internet using the following 
address: <a href="/cdn-cgi/l/email-protection#6d1e0c030904430e0c1f01042d0b0c0c430a021b"><span class="__cf_email__" data-cfemail="91e2f0fff5f8bff2f0e3fdf8d1f7f0f0bff6fee7">[email&#160;protected]</span></a>. Questions or comments sent via the 
Internet as attached electronic files must be formatted in Microsoft 
Word 97 for Windows or ASCII text.

SUPPLEMENTARY INFORMATION: On July 2, 2002, the FAA issued AD 2002-14-
05, amendment 39-12805 (67 FR 47640, July 19, 2002), applicable to 
certain McDonnell Douglas Model MD-11 airplanes, to require 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. That AD also requires replacement of the

[[Page 55717]]

electrical wiring of the galley in the electrical power center in bays 
1, 2, and 3 with larger gage cable assemblies, which terminates the 
repetitive inspections. That action was prompted by the FAA's 
determination that further rulemaking action was necessary to mandate 
the terminating action. The actions required by that AD are intended to 
prevent damage to the wire assembly terminal lugs and overheating of 
the power feeder cables on the No. 3 and 4 GLCU, which could result in 
smoke and fire in the center accessory compartment.

Actions Since Issuance of Previous AD

    Since the issuance of AD 2002-14-05, the airplane manufacturer has 
informed the FAA that accomplishment of the replacement specified in 
Boeing Service Bulletin MD11-24-184, dated February 22, 2001, which is 
required by paragraph (c) of that AD, could result in additional wire 
chafing damage in the electrical power center (EPC) due to insufficient 
clearance from structure. Such chafing, if not corrected, could cause 
arcing and consequent smoke and fire in the electrical power center. 
Boeing also has informed us that it is planning to revise Boeing 
Service Bulletin MD11-24-184.

FAA's Determination

    In light of the identified unsafe condition, we have determined 
that the replacement required by paragraph (c) of AD 2002-14-05 is no 
longer acceptable as terminating action for the repetitive inspections 
required by paragraphs (a) and (b) of that AD, and that those 
repetitive inspections must continue to be done, until a new 
terminating action is developed, approved, and available.

Explanation of Relevant Service Information

    We previously 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, with new parts.
    We also previously 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.
    Accomplishment of the actions specified in the service bulletins is 
intended to adequately address the identified unsafe condition.

Explanation of Requirements of Rule

    Since an unsafe condition has been identified that is likely to 
exist or develop on other airplanes of this same type design, this AD 
supersedes AD 2002-14-05 to require 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 to 
detect damage; and corrective actions, if necessary. The actions will 
be required to be accomplished in accordance with the service bulletins 
described previously.

Interim Action

    This is considered to be interim action. The airplane manufacturer 
has advised that it currently is developing a replacement that will 
address the unsafe condition addressed by this AD. Once this 
replacement is developed, approved, and available, we may consider 
additional 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 
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.
    Submit comments using the following format:
    <bullet> Organize comments issue-by-issue. For example, discuss a 
request to change the compliance time and a request to change the 
service bulletin reference as two separate issues.
    <bullet> For each issue, state what specific change to the AD is 
being requested.
    <bullet> Include justification (e.g., reasons or data) for each 
request.
    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 2002-NM-195-AD.'' The postcard will be date stamped 
and returned to the commenter.

Regulatory Impact

    The regulations adopted herein will not have a substantial direct 
effect 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, it 
is determined that this final rule does not have federalism 
implications under Executive Order 13132.
    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.

[[Page 55718]]

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 removing amendment 39-12805 (67 FR 
47640, July 19, 2002), and by adding a new airworthiness directive 
(AD), amendment 39-12872, to read as follows:

2002-17-06  McDonnell Douglas: Amendment 39-12872. Docket 2002-NM-
195-AD. Supersedes AD 2002-14-05, Amendment 39-12805.

    Applicability: Model MD-11 airplanes, as listed in Boeing 
Service Bulletin MD11-24-184, dated February 22, 2001; 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 (d) 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 chafing damage to the wire assembly, and consequent 
arcing and smoke and fire in the electrical power center, and to 
prevent damage to the wire assembly terminal lugs and overheating of 
the power feeder cables on the No. 3 and No. 4 galley load control 
unit (GLCU), which could result in smoke and fire in the center 
accessory compartment, accomplish the following:

Initial Inspection

    (a) Do 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), per McDonnell Douglas Alert 
Service Bulletin MD11-24A160, dated August 30, 1999; or Revision 01, 
dated November 11, 1999; at the applicable time specified in 
paragraph (a)(1) or (a)(2) of this AD.
    (1) For airplanes on which the replacement required by paragraph 
(c) of AD 2002-14-05, amendment 39-12805, has been done: Inspect 
within 60 days after the effective date of this AD.
    (2) For airplanes on which the replacement required by paragraph 
(c) of AD 2002-14-05 has NOT been done: Inspect within 600 flight 
hours from the last inspection required by AD 2002-14-05, or within 
60 days after the effective date of this AD, whichever occurs later.

    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 from within 
touching distance unless otherwise specified. A mirror may be 
necessary to enhance visual access to all exposed surfaces in the 
inspection area. This level of inspection is made under normally 
available lighting conditions such as daylight, hangar lighting, 
flashlight, or droplight 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.''

No Damage Detected: Repetitive Inspections

    (b) If no damage is detected during any inspection required by 
this AD, repeat the general visual inspection every 600 flight 
hours.

Damage Detected: Replacement and Repetitive Inspections

    (c) If any damage is detected during any inspection required by 
this AD, before further flight, replace the power feeder cables, 
fuseholder, and/or fuses, as applicable, with new parts, per 
McDonnell Douglas Alert Service Bulletin MD11-24A160, dated August 
30, 1999; or Revision 01, dated November 11, 1999. Repeat the 
general visual inspection every 600 flight hours.

Alternative Methods of Compliance

    (d) 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. 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

    (e) 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.

Incorporation by Reference

    (f) 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. The incorporation by reference of those 
documents was approved previously by the Director of the Federal 
Register as of January 4, 2000 (64 FR 71001, December 20, 1999). 
Copies may be obtained from Boeing Commercial Aircraft Group, Long 
Beach Division, 3855 Lakewood Boulevard, Long Beach, California 
90846, Attention: Data and Service Management, Dept. C1-L5A (D800-
0024). 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, 3960 Paramount 
Boulevard, Lakewood, California; or at the Office of the Federal 
Register, 800 North Capitol Street, NW., Suite 700, Washington, DC.

Effective Date

    (g) This amendment becomes effective on September 16, 2002.

    Issued in Renton, Washington, on August 23, 2002.
Vi L. Lipski,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 02-22127 Filed 8-29-02; 8:45 am]
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