[Federal Register Volume 68, Number 166 (Wednesday, August 27, 2003)]
[Proposed Rules]
[Pages 51523-51526]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 03-21872]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2003-NM-68-AD]
RIN 2120-AA64


Airworthiness Directives; McDonnell Douglas Model MD-11 Airplanes

AGENCY: Federal Aviation Administration, DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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SUMMARY: This document proposes the supersedure of 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 (EPC) to detect damage; and 
corrective actions, if necessary. For certain airplanes, this action 
would require replacement of the electrical wiring of the galley in the 
EPC. For certain other airplanes, this action would require an 
inspection to detect damage of the electrical wiring of the galley in 
the EPC; corrective actions if necessary; modification of the wiring 
support; and removal of spare fuses; as applicable. These new actions 
would terminate the repetitive inspection requirements. This action 
also limits the applicability of the existing AD. This proposal is 
prompted by the FAA's determination that additional rulemaking is 
necessary. The actions specified by the proposed AD are intended to 
prevent chafing damage to the wire assembly, 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 GLCU, which could result in smoke and fire in the center 
accessory compartment.

DATES: Comments must be received by October 14, 2003.

ADDRESSES: Submit comments in triplicate to the Federal Aviation 
Administration (FAA), Transport Airplane Directorate, ANM-114, 
Attention: Rules Docket No. 2003-NM-68-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

[[Page 51524]]

the following address: [email protected]. Comments sent via fax 
or the Internet must contain ``Docket No. 2003-NM-68-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 or 2000 or ASCII text.
    The service information referenced in the proposed rule 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.

FOR FURTHER INFORMATION CONTACT: 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.

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 action may be changed in 
light of the comments received.
    Submit comments using the following format:
    [sbull] 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.
    [sbull] For each issue, state what specific change to the proposed 
AD is being requested.
    [sbull] 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 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 action must submit a self-addressed, 
stamped postcard on which the following statement is made: ``Comments 
to Docket Number 2003-NM-68-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. 2003-NM-68-AD, 1601 Lind Avenue, SW., Renton, Washington 
98055-4056.

Discussion

    On August 23, 2002, the FAA issued AD 2002-17-06, amendment 39-
12872 (67 FR 55716, August 30, 2002), applicable to certain McDonnell 
Douglas Model MD-11 airplanes, to supersede AD 2002-14-05, amendment 
39-12805 (67 FR 47640, July 19, 2002) 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 (EPC) to detect damage; and 
corrective actions, if necessary. That action was prompted by 
information from the airplane manufacturer that accomplishment of the 
replacement required by AD 2002-14-05 could result in additional wire 
chafing damage in the EPC due to insufficient clearance from structure. 
The requirements of that 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 GLCU, which could result in smoke and 
fire in the center accessory compartment.

Actions Since Issuance of Previous Rule

    In the preamble of AD 2002-17-06, the FAA indicated that the 
actions required by that AD were considered ``interim action,'' and 
that further rulemaking action would be considered once the airplane 
manufacturer developed a replacement that addresses the identified 
unsafe condition and once we approved that replacement. We now have 
determined that further rulemaking is indeed necessary, and this 
proposed AD follows from that determination.

Explanation of Relevant Service Information

    We have reviewed and approved Revision 02 of Boeing Service 
Bulletin MD-11-24-184, dated January 7, 2003. Revision 02 of the 
service bulletin incorporates engineering data released subsequent to 
Revision 01 of the service bulletin (referenced in AD 2002-17-06 as the 
appropriate source of service information for the required actions) to 
provide additional details for ensuring proper wire clamping and 
support. Revision 02 also removes airplanes from the effectivity. 
Accomplishment of the actions 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 supersede AD 2002-17-06 to continue to require 
repetitive general visual inspections of the power feeder cables, 
terminal strip, fuseholder, and fuses of the GLCU within the No. 3 bay 
EPC to detect damage; and corrective actions, if necessary. The 
proposed AD would also require accomplishment of the actions specified 
in Revision 02 of the service bulletin described previously, which 
would terminate the repetitive inspection requirements.

Explanation of Change to Applicability

    The applicability of the proposed AD references Boeing Service 
Bulletin MD11-24-184, Revision 02, dated January 7, 2003, as the 
appropriate source of service information for determining the affected 
airplanes (AD 2002-17-06 referenced Revision 01 of the service 
bulletin). The service bulletin reflects the most current listing of 
airplanes subject to the requirements of this proposed AD.

Changes to 14 CFR Part 39/Effect on the AD

    On July 10, 2002, we issued a new version of 14 CFR part 39 (67 FR 
47997, July 22, 2002), which governs our AD system. The regulation now 
includes material that relates to altered products, special flight 
permits, and alternative methods of compliance (AMOC). Because we have 
now included this material in part 39, for purposes of this proposed 
AD, it is only necessary to identify the office authorized to approved 
AMOCs and previously approved AMOCs that are acceptable for compliance 
with the applicable requirements of this proposed AD.

[[Page 51525]]

Cost Impact

    There are approximately 112 airplanes of the affected design in the 
worldwide fleet. The FAA estimates that 32 airplanes of U.S. registry 
would be affected by this proposed AD.
    The inspection that is currently required by AD 2002-17-06 and 
retained in this AD takes approximately 1 work hour per airplane to 
accomplish, at an average labor rate of $65 per work hour. Based on 
these figures, the cost impact of the currently required inspection on 
U.S. operators is estimated to be $2,080, or $65 per airplane, per 
inspection cycle.
    Table 1 of this proposed AD shows the estimated cost impact of the 
new actions for airplanes affected by this proposed AD. The average 
labor rate is $65 per work hour. Table 1 is as follows:

                                             Table 1.--Cost Estimate
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                                           For group 1 airplanes                   For group 2 airplanes
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              Task                  Work                       Cost per     Work                       Cost per
                                   hours    Required parts     airplane    hours    Required parts     airplane
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Replacement.....................       18  $15,276.........      $16,446       19  $17,261.........      $18,496
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                                             Group 3 airplanes                     For group 4 airplanes
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              Task                  Work                       Cost per     Work                       Cost per
                                   hours    Required parts     airplane    hours    Required parts     airplane
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Inspection......................        1  None............          $65        1  None............          $65
Modification....................        2  $190............         $320        1  $9..............          $74
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    The cost impact figures discussed above are based on assumptions 
that no operator has yet accomplished any of the current or proposed 
requirements of this AD action, and that no operator would accomplish 
those actions in the future if this AD were not adopted. The cost 
impact figures discussed in AD rulemaking actions represent only the 
time necessary to perform the specific actions actually required by the 
AD. These figures typically do not include incidental costs, such as 
the time required to gain access and close up, planning time, or time 
necessitated by other administrative actions. The manufacturer may 
cover the cost of replacement parts associated with this proposed AD, 
subject to warranty conditions. Manufacturer warranty remedies may also 
be available for labor costs associated with this proposed AD. As a 
result, the costs attributable to the proposed AD may be less than 
stated above.

Regulatory Impact

    The regulations proposed herein would 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 proposal would not have federalism implications 
under Executive Order 13132.
    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 removing amendment 39-12872 (67 FR 
55716, August 30, 2002), and by adding a new airworthiness directive 
(AD), to read as follows:

McDonnell Douglas: Docket 2003-NM-68-AD. Supersedes AD 2002-17-06, 
Amendment 39-12872.

    Applicability: Model MD-11 airplanes, as listed in Boeing 
Service Bulletin MD11-24-184, Revision 02, dated January 7, 2003; 
certificated in any category.
    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 (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 (GLCU), which could result in smoke and fire in the 
center accessory compartment; accomplish the following:

Certain Requirements of AD 2002-17-06, Amendment 39-12872

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 EPC 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 September 16, 2002 (the effective date AD 2002-
17-06, amendment 39-12872).
    (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 September 16, 2002, whichever occurs later.

    Note: 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

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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 
paragraph (a) of 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 
paragraph (a) of 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.

New Requirements of This AD

Group 1 and Group 2 Airplanes: Replacement of Electrical Wiring

    (d) For Group 1 and Group 2 airplanes identified in Boeing Service 
Bulletin MD11-24-184, Revision 02, dated January 7, 2003: Within 12 
months after the effective date of this AD, replace the electrical 
wiring of the galley in the EPC in bays 1, 2, and 3, per the service 
bulletin. Accomplishment of the replacement terminates the requirements 
of paragraphs (a) through (c) of this AD.

Group 3 and Group 4 Airplanes: Inspection for Damage, Modification 
of Wiring Support, Removal of Fuses; and Corrective Action; As 
Applicable

    (e) For Group 3 and Group 4 airplanes identified in Boeing 
Service Bulletin MD11-24-184, Revision 02, dated January 7, 2003: 
Within 12 months after the effective date of this AD, do the actions 
specified in paragraphs (e)(1), (e)(2), and (e)(3) of this AD per 
the service bulletin. Accomplishment of the applicable actions in 
those paragraphs terminates the requirements of paragraphs (a) 
through (c) of this AD.
    (1) Do a general visual inspection to detect damage of the 
electrical wiring of the galley in the EPC in bays 1, 2, and 3. If 
any damage is detected, before further flight, repair or replace 
damaged wiring with new or serviceable wiring per the service 
bulletin.
    (2) Modify wiring support in bay 1.
    (3) Remove spare fuses and modify wiring support in bays 2 and 
3.

Alternative Methods of Compliance

    (f)(1) In accordance with 14 CFR 39.19, the Manager, Los Angeles 
Aircraft Certification Office (ACO), FAA, is authorized to approve 
alternative methods of compliance for this AD.
    (2) Alternative methods of compliance, approved previously per 
AD 2002-17-06, amendment 39-12872, are approved as alternative 
methods of compliance with paragraphs (a) through (c) of this AD.

    Issued in Renton, Washington, on August 20, 2003.
Kyle L. Olsen,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 03-21872 Filed 8-26-03; 8:45 am]
BILLING CODE 4910-13-P