[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