[Federal Register: October 17, 2003 (Volume 68, Number 201)]
[Rules and Regulations]               
[Page 59709-59711]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr17oc03-3]                         

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2001-NM-57-AD; Amendment 39-13340; AD 2003-21-05]
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 a one-time detailed visual inspection of the 
wire bundle installation behind the first observer's station to detect 
damaged or chafed wires; and corrective action, if necessary. This 
amendment requires a new inspection of the wire bundle installation 
behind the first observer's station to detect damaged or chafed wires; 
repair if necessary; installation of a grommet around the lower edge of 
the feed-through; replacement of the support bracket with a new 
bracket; and relocation of the support clamp of the wire bundle; as 
applicable. The actions specified by this AD are intended to prevent 
the wire bundle contained in the feed-through from contacting the 
bottom of the feed-through, which could cause cable chafing, electrical 
arcing, and smoke or fire in the cockpit. This action is intended to 
address the identified unsafe condition.

DATES: Effective November 21, 2003.
    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of November 21, 2003.

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 FAA, 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, Transport Airplane 
Directorate, 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

[[Page 59710]]

Aviation Regulations (14 CFR part 39) by superseding AD 2000-03-13, 
amendment 39-11572 (65 FR 8028, February 17, 2000), which is applicable 
to certain McDonnell Douglas Model MD-11 airplanes, was published as a 
supplemental notice of proposed rulemaking (NPRM) in the Federal 
Register on July 24, 2003 (68 FR 43686). The action proposed to require 
a new inspection of the wire bundle installation behind the first 
observer's station to detect damaged or chafed wires; repair if 
necessary; installation of a grommet around the lower edge of the feed-
through; replacement of the support bracket with a new bracket; and 
relocation of the support clamp of the wire bundle; as applicable. The 
action also specified new corrective actions.

Comments

    Interested persons have been afforded an opportunity to participate 
in the making of this amendment. No comments were submitted in response 
to the supplemental NPRM 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.

Changes to 14 CFR Part 39/Effect on the Proposed AD

    On July 10, 2002, the FAA issued a new version of 14 CFR part 39 
(67 FR 47997, July 22, 2002), which governs the FAA's airworthiness 
directives system. The regulation now includes material that relates to 
altered products, special flight permits, and alternative methods of 
compliance (AMOCs). Because we have now included this material in part 
39, only the office authorized to approve AMOCs is identified in each 
individual AD.

Change to Labor Rate Estimate

    We have reviewed the figures we have used over the past several 
years to calculate AD costs to operators. To account for various 
inflationary costs in the airline industry, we find it necessary to 
increase the labor rate used in these calculations from $60 per work 
hour to $65 per work hour. The cost impact information, below, reflects 
this increase in the specified hourly labor rate.

Cost Impact

    There are approximately 193 airplanes of the affected design in the 
worldwide fleet. The FAA estimates that 62 airplanes of U.S. registry 
will be affected by this AD.
    The actions that are required by this AD will take approximately 2 
work hours per airplane to accomplish, at an average labor rate of $65 
per work hour. Required parts will cost approximately $407 per 
airplane. Based on these figures, the cost impact of the requirements 
of this AD on U.S. operators is estimated to be $33,294, or $537 per 
airplane.
    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. 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 costs 
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 39-11572 (65 FR 8028, 
February 17, 2000), and by adding a new airworthiness directive (AD), 
amendment 39-13340, to read as follows:

2003-21-05 McDonnell Douglas: Amendment 39-13340. Docket 2001-NM-57-
AD. Supersedes AD 2000-03-13, Amendment 39-11572.

    Applicability: Model MD-11 airplanes, as listed in Boeing Alert 
Service Bulletin MD11-24A041, Revision 03, dated September 11, 2002; 
certificated in any category.

    Note 1: This AD applies to each airplane identified in the 
preceding applicability provision, regardless of whether it has been 
modified, altered, or repaired in the area subject to the 
requirements of this AD. For airplanes that have been modified, 
altered, or repaired so that the performance of the requirements of 
this AD is affected, the owner/operator must request approval for an 
alternative method of compliance in accordance with paragraph (d)(1) 
of this AD. The request should include an assessment of the effect 
of the modification, alteration, or repair on the unsafe condition 
addressed by this AD; and, if the unsafe condition has not been 
eliminated, the request should include specific proposed actions to 
address it.

    Compliance: Required as indicated, unless accomplished 
previously.
    To prevent the wire bundle contained in the feed-through from 
contacting the bottom of the feed-through, which could cause cable 
chafing, electrical arcing, and smoke or fire in the cockpit, 
accomplish the following:

Inspection

    (a) Within 1 year after the effective date of this AD, do a one-
time detailed inspection of the wire bundle installation behind the 
first observer's station to detect damaged or chafed wires, per 
Boeing Alert Service Bulletin MD11-24A041, Revision 03, dated 
September 11, 2002.

    Note 2: For the purposes of this AD, a detailed inspection is 
defined as: ``An intensive visual examination of a specific 
structural area, system, installation, or assembly to detect damage, 
failure, or irregularity. Available lighting is normally 
supplemented with a direct source of good lighting at intensity 
deemed appropriate by the inspector. Inspection aids such as mirror,

[[Page 59711]]

magnifying lenses, etc., may be used. Surface cleaning and elaborate 
access procedures may be required.''

Condition 1: No Damaged or Chafed Wire

    (b) If no damaged or chafed wire is detected during the detailed 
inspection required by paragraph (a) of this AD, before further 
flight, revise the wire bundle support clamp installation, per 
Boeing Alert Service Bulletin MD11-24A041, Revision 03, dated 
September 11, 2002.

Condition 2: Any Damaged or Chafed Wire

    (c) If any damaged or chafed wire is detected during the 
detailed inspection required by paragraph (a) of this AD, before 
further flight, repair wiring, and revise the wire bundle support 
clamp installation, per Boeing Alert Service Bulletin MD11-24A041, 
Revision 03, dated September 11, 2002.

Alternative Methods of Compliance

    (d)(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 (AMOCs) for this AD.

    Note 3: Information concerning the existence of approved 
alternative methods of compliance with this AD, if any, may be 
obtained from the Los Angeles ACO.

    (2) Alternative methods of compliance, approved previously in 
accordance with AD 2000-03-13, amendment 39-11572, are approved as 
alternative methods of compliance with this AD.

Incorporation by Reference

    (e) The actions shall be done in accordance with Boeing Alert 
Service Bulletin MD11-24A041, Revision 03, dated September 11, 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). 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; 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 November 21, 2003.

    Issued in Renton, Washington, on October 9, 2003.
Ali Bahrami,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 03-26116 Filed 10-16-03; 8:45 am]

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