[Federal Register: January 20, 2004 (Volume 69, Number 12)]
[Rules and Regulations]
[Page 2659-2661]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr20ja04-5]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 2001-NM-161-AD; Amendment 39-13430; AD 2004-01-16]
RIN 2120-AA64
Airworthiness Directives; McDonnell Douglas Model MD-11 and -11F
Airplanes
AGENCY: Federal Aviation Administration, DOT.
[[Page 2660]]
ACTION: Final rule.
-----------------------------------------------------------------------
SUMMARY: This amendment adopts a new airworthiness directive (AD),
applicable to certain McDonnell Douglas Model MD-11 and -11F airplanes,
that requires revising the wire connection stackups for the terminal
strip of the generator feeder tail compartment of the auxiliary power
unit (APU), and removing a nameplate, as applicable. For certain
airplanes, this AD also requires replacing the terminal strips and
revising the terminal hardware stackup for the feeder of the center
cargo loading system. This action is necessary to prevent arcing damage
to the terminal strips and damage to the adjacent structure, which
could result in smoke and/or fire in the center and/or aft cargo
compartments. This action is intended to address the identified unsafe
condition.
DATES: Effective February 24, 2004.
The incorporation by reference of certain publications listed in
the regulations is approved by the Director of the Federal Register as
of February 24, 2004.
ADDRESSES: 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 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; 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) to include an airworthiness
directive (AD) that is applicable to certain McDonnell Douglas Model
MD-11 and -11F airplanes was published in the Federal Register on July
24, 2003 (68 FR 43693). That action proposed to require revising the
wire connection stackups for the terminal strip of the generator feeder
tail compartment of the auxiliary power unit (APU), and removing a
nameplate, as applicable. For certain airplanes, that action also
proposed to require replacing the terminal strips and revising the
terminal hardware stackup for the feeder of the center cargo loading
system.
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.
Editorial Clarification
The FAA has revised the spelling of a word from ``namplate'' to
``nameplate'' in this AD.
Conclusion
The FAA has determined that air safety and the public interest
require the adoption of the rule with the change described previously.
The FAA has determined that this change will neither increase the
economic burden on any operator nor increase the scope of this AD.
Cost Impact
There are approximately 154 Model MD-11 and -11F airplanes of the
affected design in the worldwide fleet. We estimate that 67 airplanes
of U.S. registry will be affected by this AD, that it will take
approximately between 1 and 2 work hours per airplane (depending on the
airplane configuration) to accomplish the required actions, and that
the average labor rate is $65 per work hour. Required parts will cost
approximately $102 per airplane. Based on these figures, the cost
impact of the AD on U.S. operators is estimated to between $11,189 and
$15,544, or between $167 and $232 per airplane (depending on the
airplane configuration).
The cost impact figure discussed above is 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. However, for affected airplanes
within the period under the warranty agreement, we have been advised
that the manufacturer has committed previously to its customers that it
will bear the cost of replacement parts. We also have been advised that
manufacturer warranty remedies are available for labor costs associated
with accomplishing the actions required by this AD. Therefore, the
future economic cost impact of this AD may be less than the cost impact
figure indicated above.
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.
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 adding the following new airworthiness
directive:
2004-01-16 McDonnell Douglas: Amendment 39-13430. Docket 2001-NM-
161-AD.
Applicability: Model MD-11 and -11F airplanes, as listed in
McDonnell Douglas Alert Service Bulletin MD11-24A173,
[[Page 2661]]
Revision 02, dated May 2, 2002; certificated in any category.
Compliance: Required as indicated, unless accomplished
previously.
To prevent arcing damage to the terminal strips and damage to
the adjacent structure, which could result in smoke and/or fire in
the center and/or aft cargo compartments, accomplish the following:
For Group 1 and Group 2 Airplanes: Revise Wire Connection Stackups,
Remove Nameplate, and Inspect for Damage
(a) For Group 1 and Group 2 airplanes listed in McDonnell
Douglas Alert Service Bulletin MD11-24A173, Revision 02, dated May
2, 2002: Within 18 months after the effective date of this AD, do
the actions specified in paragraphs (a)(1) and (a)(2) of this AD per
the service bulletin. Although the service bulletin references a
reporting requirement in paragraph 4, ``Appendix,'' such reporting
is not required by this AD.
(1) Revise the wire connection stackups for the terminal strip
of the generator feeder tail compartment of the auxiliary power unit
(APU), and remove the nameplate, as applicable.
(2) Do a general visual inspection to detect arcing damage of
the surrounding structure, adjacent system components, and
electrical cables in the center cargo and aft cargo compartments.
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 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.''
For Group 2 Airplanes: Replace Terminal Strips, Revise Terminal
Hardware Stackup, Remove Nameplate, and Inspect for Damage
(b) For Group 2 airplanes listed in McDonnell Douglas Alert
Service Bulletin MD11-24A173, Revision 02, dated May 2, 2002: Within
18 months after the effective date of this AD, do the actions
specified in paragraphs (b)(1) and (b)(2) of this AD per the service
bulletin. Although the service bulletin references a reporting
requirement in paragraph 4, ``Appendix,'' such reporting is not
required by this AD.
(1) Replace the terminal strips and revise the terminal hardware
stackup for the feeder of the center cargo loading system, and
remove the nameplate, as applicable.
(2) Do a general visual inspection to detect arcing damage of
the surrounding structure, adjacent system components, and
electrical cables in the center cargo and aft cargo compartments.
Corrective Action if Necessary
(c) If any damage is detected during any inspection required by
paragraph (a) or (b) of this AD, before further flight, repair
damage or replace the damaged part with a new part, per McDonnell
Douglas Alert Service Bulletin MD11-24A173, Revision 02, dated May
2, 2002. If the type of structural material that has been damaged is
not covered in the structural repair manual, repair per a method
approved by the Manager, Los Angeles Aircraft Certification Office
(ACO), FAA. Although the service bulletin references a reporting
requirement in paragraph 4, ``Appendix,'' such reporting is not
required by this AD.
Alternative Methods of Compliance
(d) In accordance with 14 CFR 39.19, the Manager, Los Angeles
ACO, FAA, is authorized to approve alternative methods of compliance
for this AD.
Incorporation by Reference
(e) Unless otherwise specified in this AD, the actions shall be
done in accordance with McDonnell Douglas Alert Service Bulletin
MD11-24A173, Revision 02, dated May 2, 2002. 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:
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
(f) This amendment becomes effective on February 24, 2004.
Issued in Renton, Washington, on January 2, 2004.
Kevin M. Mullin,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 04-761 Filed 1-16-04; 8:45 am]
BILLING CODE 4910-13-P