[Federal Register: December 4, 2003 (Volume 68, Number 233)]
[Rules and Regulations]
[Page 67792-67794]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr04de03-3]
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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
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Task Required Cost per Required Cost per
Work hours parts airplane Work hours parts airplane
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Replacement................. 18 $15,276 $16,446 19 $17,261 $18,496
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For group 3 airplanes For group 4 airplanes
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Task Required Cost per Required Cost per
Work hours parts airplane Work hours 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 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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