AD 2001-24-21

[Federal Register Volume 66, Number 239 (Wednesday, December 12, 2001)]
[Rules and Regulations]
[Pages 64121-64124]
From the Federal Register Online via the Government Publishing Office [<a href="http://www.gpo.gov">www.gpo.gov</a>]
[FR Doc No: 01-30197]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2001-NM-96-AD; Amendment 39-12538; AD 2001-24-21]
RIN 2120-AA64


Airworthiness Directives; McDonnell Douglas Model DC-10 Series 
Airplanes, and Model MD-10-10F and -30F Series Airplanes

AGENCY: Federal Aviation Administration, DOT.

ACTION: Final rule.

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SUMMARY: This amendment supersedes an existing airworthiness directive 
(AD), applicable to all McDonnell Douglas Model DC-10 series airplanes, 
that currently requires a one-time detailed visual inspection to 
determine if wire segments of the wire bundle routed through the feed 
through on the aft side of the flight engineer's station are damaged or 
chafed, and corrective actions, if necessary. This amendment also 
requires revising the wire bundle support clamp installation at the 
flight engineer's station. This action is necessary to prevent chafing 
of the wire bundle located behind the flight engineer's panel caused by 
the wire bundle coming in contact with the lower edge of the feed 
through and consequent electrical arcing, which could result in smoke 
and fire in the cockpit. This action is intended to address the 
identified unsafe condition.

DATES: Effective January 16, 2002.
    The incorporation by reference of Boeing Alert Service Bulletin 
DC10-24A149, Revision 02, dated April 5, 2001, as listed in the 
regulations, is approved by the Director of the Federal Register as of 
January 16, 2002.
    The incorporation by reference of McDonnell Douglas Alert Service 
Bulletin DC10-24A149, Revision 01, dated July 28, 1999, as listed in 
the regulations, was approved previously by the Director of the Federal 
Register as of June 21, 2000 (65 FR 31253, May 17, 2000).

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,

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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: Natalie Phan-Tran, Aerospace Engineer, 
Systems and Equipment Branch, ANM-130L, FAA, Los Angeles Aircraft 
Certification Office, 3960 Paramount Boulevard, Lakewood, California 
90712-4137; telephone (562) 627-5343; fax (562) 627-5210.

SUPPLEMENTARY INFORMATION: A proposal to amend part 39 of the Federal 
Aviation Regulations (14 CFR part 39) by superseding AD 2000-10-03, 
amendment 39-11727 (65 FR 31253, May 17, 2000), which is applicable to 
certain McDonnell Douglas Model DC-10 series airplanes, and Model MD-
10-10F and -30F series airplanes was published in the Federal Register 
on July 23, 2001 (66 FR 38188). The action proposed to continue to 
require a one-time detailed visual inspection to determine if wire 
segments of the wire bundle routed through the feed through on the aft 
side of the flight engineer's station are damaged or chafed, and 
corrective actions, if necessary. The action also proposed to require 
revising the wire bundle support clamp installation at the flight 
engineer's station.

Comment Received

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

Request To Withdraw Proposed AD

    The commenter requests that the proposed AD be withdrawn. The 
commenter states that it recently inspected the subject harness 
installation per AD 2000-10-03 on airplanes with a minimum of 13 years 
in service and a maximum of 29 years in service. The inspections 
revealed no chafed or damaged wires or broken support clamps. 
Therefore, the commenter concludes that the requirements of the 
proposed AD are unnecessary.
    The FAA does not agree. As discussed in the preamble of the 
proposed AD, we determined that the revision of the wire bundle support 
clamp installation required by AD 2000-10-03 for certain airplanes does 
not adequately address the identified unsafe condition. In addition, we 
determined that all affected airplanes must incorporate this new, 
improved support clamp, because the procedures specified in McDonnell 
Douglas Alert Service Bulletin DC10-24A149, Revision 01, dated July 28, 
1999 (which was referenced in AD 2000-10-03 as the appropriate source 
of service information), do not prevent electrical arcing or chafing 
even if no chafed or damaged wire bundles located behind the flight 
engineer's panel were found during the required one-time inspection. 
Therefore, we find that the requirements of this AD are warranted to 
adequately address the identified unsafe condition.

Request To Revise Compliance Time

    If the AD is issued as proposed, the commenter requests that the 
compliance time for the proposed revision of the wire bundle support 
clamp installation be revised from 1 year to 18 months. The commenter 
states that the work scope of the proposed AD is best suited for ``a 
planned multiple-day maintenance visit.''
    The FAA does not agree. In developing an appropriate compliance 
time for this action, we considered not only those safety issues in 
developing an appropriate compliance time for this action, but the 
recommendations of the manufacturer, and the practical aspect of 
accomplishing the required revision within an interval of time that 
parallels normal scheduled maintenance for the majority of affected 
operators. In consideration of all of these factors, we determined that 
the compliance time, as proposed, represents an appropriate interval in 
which the required revision can be accomplished in a timely manner 
within the fleet and still maintain an adequate level of safety.
    In addition, the FAA finds that operators of affected airplanes on 
the U.S. Register should have already accomplished the one-time 
inspection required by paragraph (a) of this AD (the effective date for 
compliance was June 21, 2001) which is a restatement of the 
requirements of AD 2000-10-03). Operators are given credit for work 
previously performed by means of the phrase in the ``Compliance'' 
section of the AD that states, ``Required as indicated, unless 
accomplished previously.'' Therefore, operators should be able to 
accomplish the additional work of revising the wire bundle support 
clamp installation required by paragraph (b) of this AD within the 1-
year compliance time during regularly scheduled maintenance intervals. 
However, under the provisions of paragraph (c) of this AD, we may 
approve requests for adjustments to the compliance time if data are 
submitted to substantiate that such an adjustment would provide an 
acceptable level of safety.

Request To Revise Work Hours

    The commenter disagrees with the FAA's estimate of two work hours 
to accomplish the revision of the wire bundle support clamp 
installation in the Cost Impact section of the proposed AD. The 
commenter estimates four work hours per airplane, because of the 
confined space and numerous wire bundles in the area of the 
modification.
    The FAA does not concur. We used the work hours specified in Boeing 
Alert Service Bulletin DC10-24A149, Revision 02, dated April 5, 2001 
(which is referenced in the AD as the appropriate source of service 
information for accomplishment of the required modification). We note 
that the economic analysis of this AD represents the time necessary to 
perform only the actions actually required by this AD. We recognize 
that, in accomplishing the requirements of any AD, operators may incur 
``incidental'' costs in addition to the ``direct'' costs. As indicated 
in the preamble of the notice of proposed rulemaking (NPRM), the cost 
analysis in AD rulemaking actions typically does not include incidental 
costs, such as the time required to gain access and close up; planning 
time; or time necessitated by other administrative actions. Because 
incidental costs may vary significantly from operator to operator, they 
are almost impossible to calculate. Therefore, no change to the final 
rule is necessary.

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 as proposed.

Cost Impact

    There are approximately 412 Model DC-10 series airplanes and Model 
MD-10-10F and -30F series airplanes of the affected design in the 
worldwide fleet. The FAA estimates that 300 airplanes of U.S. registry 
will be affected by this AD.
    The actions that are currently required by AD 2000-10-03, and 
retained in this AD, take approximately 1 work hour per airplane to 
accomplish, at an average labor rate of $60 per work hour. Based on 
these figures, the cost impact of the currently required actions on 
U.S. operators is estimated to be $18,000, or $60 per airplane.
    The new actions that are required in this AD action will take 
approximately 2 work hours per airplane to accomplish, at an average 
labor rate of $60 per work hour. Based on these

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figures, the cost impact of the new requirements of this AD on U.S. 
operators is estimated to be $36,000, or $120 per airplane.
    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.

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 removing amendment 39-11727 (65 FR 
31253, May 17, 2000), and by adding a new airworthiness directive (AD), 
amendment 39-12538, to read as follows:

2001-24-21  McDonnell Douglas: Amendment 39-12538. Docket 2001-NM-
96-AD. Supersedes AD 2000-10-03, Amendment 39-11727.

    Applicability: Model DC-10 series airplanes, and Model MD-10-10F 
and -30F series airplanes; as listed in Boeing Alert Service 
Bulletin DC10-24A149, Revision 02, dated April 5, 2001; 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 (c) 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 of the wire bundle located behind the flight 
engineer's panel caused by the wire bundle coming in contact with 
the lower edge of the feed through and consequent electrical arcing, 
which could result in smoke and fire in the cockpit, accomplish the 
following:

Restatement of Certain Requirements of
AD 2000-10-03

Inspection and Repair, If Necessary

    (a) Within 1 year after June 21, 2000 (the effective date of AD 
2000-10-03, amendment 39-11727), perform a one-time detailed visual 
inspection to determine if the wire segments of the wire bundle 
routed through the feed through on the aft side of the flight 
engineer's station are damaged or chafed, in accordance with 
McDonnell Douglas Alert Service Bulletin DC10-24A149, Revision 01, 
dated July 28, 1999, or Boeing Alert Service Bulletin DC10-24A149, 
Revision 02, dated April 5, 2001. If any damaged or chafed wire is 
found, prior to further flight, repair in accordance with the alert 
service bulletin.

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

New Actions Required by this AD

Revision of Wire Bundle Support Clamp Installation

    (b) Within 1 year after the effective date of this AD, revise 
the wire bundle support clamp installation at the flight engineer's 
station, per Boeing Alert Service Bulletin DC10-24A149, Revision 02, 
dated April 5, 2001.

Alternative Methods of Compliance

    (c) 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 3: 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

    (d) 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

    (e) The actions shall be done in accordance with McDonnell 
Douglas Alert Service Bulletin DC10-24A149, Revision 01, dated July 
28, 1999; or Boeing Alert Service Bulletin DC10-24A149, Revision 02, 
dated April 5, 2001; as applicable.
    (1) The incorporation by reference of Boeing Alert Service 
Bulletin DC10-24A149, Revision 02, dated April 5, 2001, 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 DC10-24A149, Revision 01, dated July 28, 1999, was 
approved previously by the Director of the Federal Register as of 
June 21, 2000 (65 FR 31253, May 17, 2000).
    (3) 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 January 16, 2002.


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    Issued in Renton, Washington, on November 28, 2001.
Vi L. Lipski,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 01-30197 Filed 12-11-01; 8:45 am]
BILLING CODE 4910-13-U