[Federal Register Volume 66, Number 163 (Wednesday, August 22, 2001)]
[Rules and Regulations]
[Pages 44041-44042]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 01-20936]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2000-NM-189-AD; Amendment 39-12400; AD 2001-17-09]
RIN 2120-AA64


Airworthiness Directives; McDonnell Douglas Model MD-11 Series 
Airplanes

AGENCY: Federal Aviation Administration, DOT.

ACTION: Final rule.

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SUMMARY: This amendment adopts a new airworthiness directive (AD), 
applicable to certain McDonnell Douglas Model MD-11 series airplanes, 
that requires an inspection of the upper avionics circuit breaker panel 
at the main observer's station to detect damage of the wires and to 
verify the correct routing of the wire bundles; corrective actions, if 
necessary; and installation of a new clamp, spacer, and sta-straps. 
This action is necessary to prevent chafing in the upper avionics 
circuit breaker panel of the main observer's station, which could 
result in arcing and consequent smoke and/or fire in the cockpit. This 
action is intended to address the identified unsafe condition.

DATES: Effective September 26, 2001.
    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of September 26, 2001.

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 
90712-4137; 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) to include an airworthiness 
directive (AD) that is applicable to certain McDonnell Douglas Model 
MD-11 series airplanes was published in the Federal Register on 
February 20, 2001 (66 FR 10851). That action proposed to require an 
inspection of the upper avionics circuit breaker panel at the main 
observer's station to detect damage of the wires and to verify the 
correct routing of the wire bundles; corrective actions, if necessary; 
and installation of a new clamp, spacer, and sta-straps.

Comments

    Interested persons have been afforded an opportunity to participate 
in the making of this amendment. Due consideration has been given to 
the comments received.

Address Change for Obtaining Service Information

    The airplane manufacturer states that the referenced department 
name, number, and mail code of the address for obtaining service 
information are incorrect in the proposed AD. The correct address is 
Boeing Commercial Aircraft Group, Long Beach Division, 3855 Lakewood 
Boulevard, Long Beach, California 90846, Attention: Data and Service 
Management, Dept. C1-L5A (D800-0024). The airplane manufacturer 
requests that the proposed AD be revised accordingly. The FAA agrees 
and has revised this address in the final rule. 1

Revise Requirements of Paragraph (a)(1)(ii) of Proposed AD

    One commenter requests that the requirements for adjusting the wire 
routing (i.e., loosening of clamps and replacing sta-straps) specified 
in paragraph (a)(1)(ii) of the proposed AD be deleted, and that a 
requirement to install individual spacers or sleeves be added. The 
commenter states that the adjustment cannot be done according to the 
drawings as recommended in the referenced service bulletin without a 
big expenditure of work. The commenter also states that the adjustment 
may cause disruption of the wire bundles and introduce new 
possibilities for wire chafing.
    The FAA does not agree. We find that adjusting the wire routing, as 
required by paragraph (a)(1)(ii) of the AD, further minimizes the 
possibility of wire damage and adequately addresses the identified 
unsafe condition. However, under the provision of paragraph (b) of the 
final rule, we may consider requests for approval of an alternative 
method of compliance if sufficient data are submitted to substantiate 
that such a design change would provide an acceptable level of safety.

Conclusion

    After careful review of the available data, including the comments 
noted above, the FAA has determined that air safety and the public 
interest require the adoption of the rule with the change previously 
described. The FAA has determined that this change will neither 
increase the economic burden on any operator nor increase the scope of 
the AD.

[[Page 44042]]

Cost Impact

    There are approximately 185 Model MD-11 series airplanes of the 
affected design in the worldwide fleet. The FAA estimates that 59 
airplanes of U.S. registry will be affected by this AD, that it will 
take approximately 5 work hours per airplane to accomplish the required 
actions, and that the average labor rate is $60 per work hour. Required 
parts will be supplied by the airplane manufacturer at no cost to the 
operators. Based on these figures, the cost impact of the AD on U.S. 
operators is estimated to be $17,700, or $300 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.

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

    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

    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]

    2. Section 39.13 is amended by adding the following new 
airworthiness directive:

2001-17-09  McDonnell Douglas: Amendment 39-12400. Docket 2000-NM-
189-AD.

    Applicability: Model MD-11 series airplanes, as listed in Boeing 
Alert Service Bulletin MD11-24A179, Revision 01, dated October 31, 
2000; 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 (b) 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 chafing in the upper avionics circuit breaker panel 
of the main observer's station, which could result in arcing and 
consequent smoke and/or fire in the cockpit, accomplish the 
following:

Inspection, Installation, and Corrective Actions, If Necessary

    (a) Within 6 months after the effective date of this AD, do the 
action(s) specified in paragraphs (a)(1) and (a)(2) of this AD per 
Boeing Alert Service Bulletin MD11-24A179, Revision 01, dated 
October 31, 2000.
    (1) A general visual inspection of the upper avionics circuit 
breaker panel at the main observer's station to detect damage of the 
wires and to verify the correct routing of the wire bundles.

    Note 2: 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.''

    (i) If any damaged wire is found, before further flight, repair 
it or replace it with new wiring.
    (ii) If any incorrect wire routing is found, before further 
flight, loosen clamps and replace the sta-straps with new sta-
straps.
    (2) Install a new clamp to the AES9101 wire bundle and wire 
support bar, and install a new spacer and sta-straps.

    Note 3: Accomplishment of the actions specified in Boeing Alert 
Service Bulletin MD11-24A179, dated August 10, 2000, before the 
effective date of this AD, is considered acceptable for compliance 
with the requirements of this AD.

Alternative Methods of Compliance

    (b) An alternative method of compliance or adjustment of the 
compliance time that provides an acceptable level of safety may be 
used if approved by the Manager, Los Angeles Aircraft Certification 
Office (ACO), FAA. Operators shall submit their requests through an 
appropriate FAA Principal Maintenance Inspector, who may add 
comments and then send it to the Manager, Los Angeles ACO.

    Note 4: Information concerning the existence of approved 
alternative methods of compliance with this AD, if any, may be 
obtained from the Los Angeles ACO.

Special Flight Permits

    (c) Special flight permits may be issued in accordance with 
sections 21.197 and 21.199 of the Federal Aviation Regulations (14 
CFR 21.197 and 21.199) to operate the airplane to a location where 
the requirements of this AD can be accomplished.

Incorporation by Reference

    (d) The actions shall be done in accordance with Boeing Alert 
Service Bulletin MD11-24A179, Revision 01, including Appendix A, 
dated October 31, 2000. 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

    (e) This amendment becomes effective on September 26, 2001.

    Issued in Renton, Washington, on August 14, 2001.
Vi L. Lipski,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 01-20936 Filed 8-21-01; 8:45 am]
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