[Federal Register Volume 68, Number 233 (Thursday, December 4, 2003)]
[Rules and Regulations]
[Pages 67792-67794]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 03-30112]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2003-NM-68-AD; Amendment 39-13380; AD 2003-24-11]
RIN 2120-AA64


Airworthiness Directives; McDonnell Douglas Model MD-11 Airplanes

AGENCY: Federal Aviation Administration, DOT.

ACTION: Final rule.

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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 (EPC) to detect damage; and corrective actions, if necessary. 
For certain airplanes, this amendment requires replacement of the 
electrical wiring of the galley in the EPC. For certain other 
airplanes, this amendment requires 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 terminate the repetitive 
inspection requirements. This amendment also limits the applicability 
of the existing AD. This amendment is prompted by the FAA's 
determination that additional rulemaking is necessary. The actions 
specified by this 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. This action is 
intended to address the identified unsafe condition.

DATES: Effective January 8, 2004.
    The incorporation by reference of a certain publication, as listed 
in the regulations is approved by the Director of the Federal Register 
as of January 8, 2004.
    The incorporation by reference of certain other 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).

ADDRESSES: The service information referenced in this AD may be 
obtained from Boeing Commercial Airplane 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 Federal Aviation Administration (FAA), Transport 
Airplane Directorate, Rules Docket, 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: 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: A proposal to amend part 39 of the Federal 
Aviation Regulations (14 CFR part 39) by superseding AD 2002-17-06, 
amendment 39-12872 (67 FR 55716, August 30, 2002), which is applicable 
to certain McDonnell Douglas Model MD-11 airplanes, was published in 
the Federal Register on August 27, 2003 (68 FR 51523). The action 
proposed to continue 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. For certain airplanes, that action proposed to require 
replacement of the electrical wiring of the galley in the EPC. For 
certain other airplanes, that action proposed to 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. Those new actions would 
terminate the repetitive inspection requirements. That action also 
proposed to limit the applicability of the existing AD.

Comments

    Interested persons have been afforded an opportunity to participate 
in the making of this amendment. No comments were submitted in response 
to the proposal or the FAA's determination of the cost to the public.

Conclusion

    The FAA has determined that air safety and the public interest 
require the adoption of the rule as proposed.

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 
will be affected by this 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 AD shows the estimated cost impact of the new 
actions for airplanes affected by this AD. The average labor rate is 
$65 per work hour. Table 1 is as follows:

[[Page 67793]]



                                             Table 1.--Cost Estimate
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                                        For group 1 airplanes                     For group 2 airplanes
                             -----------------------------------------------------------------------------------
            Task                              Required      Cost per                    Required      Cost per
                               Work  hours      parts       airplane     Work  hours      parts       airplane
----------------------------------------------------------------------------------------------------------------
Replacement.................           18       $15,276       $16,446            19       $17,261       $18,496
----------------------------------------------------------------------------------------------------------------


 
                                        For group 3 airplanes                     For group 4 airplanes
                             -----------------------------------------------------------------------------------
            Task                              Required      Cost per                    Required      Cost per
                               Work  hours      parts       airplane     Work  hours      parts       airplane
----------------------------------------------------------------------------------------------------------------
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 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 AD, subject to warranty 
conditions. Manufacturer warranty remedies may also be available for 
labor costs associated with this AD. As a result, the cost attributable 
to this AD may be less than stated above.

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.
    For the reasons discussed above, I certify that this action (1) is 
not a ``significant regulatory action'' under Executive Order 12866; 
(2) is not a ``significant rule'' under DOT Regulatory Policies and 
Procedures (44 FR 11034, February 26, 1979); and (3) 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 final evaluation has been prepared for this action 
and it is contained in the Rules Docket. A copy of it 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

0
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

0
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]

0
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), amendment 39-13380, to read as follows:

2003-24-11 McDonnell Douglas: Amendment 39-13380. 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 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.

[[Page 67794]]

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.

Incorporation by Reference

    (g) 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; and Boeing Service Bulletin MD11-24-
184, Revision 02, dated January 7, 2003; as applicable.
    (1) The incorporation by reference of Boeing Service Bulletin 
MD11-24-184, Revision 02, dated January 7, 2003, is approved by the 
Director of the Federal Register, in accordance with 5 U.S.C. 552(a) 
and 1 CFR part 51.
    (2) The incorporation by reference of McDonnell Douglas Alert 
Service Bulletin MD11-24A160, dated August 30, 1999; and McDonnell 
Douglas Alert Service Bulletin MD11-24A160, Revision 01, dated 
November 11, 1999; was approved previously by the Director of the 
Federal Register as of January 4, 2000 (64 FR 71001, December 20, 
1999).
    (3) Copies may be obtained from Boeing Commercial Airplane 
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

    (h) This amendment becomes effective on January 8, 2004.

    Issued in Renton, Washington, on November 26, 2003.
Kalene C. Yanamura,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 03-30112 Filed 12-3-03; 8:45 am]
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