[Federal Register Volume 69, Number 177 (Tuesday, September 14, 2004)]
[Rules and Regulations]
[Pages 55323-55326]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 04-20406]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2002-NM-283-AD; Amendment 39-13794; AD 2004-18-15]
RIN 2120-AA64


Airworthiness Directives; McDonnell Douglas Model DC-10-10, DC-
10-10F, DC-10-15, DC-10-30, DC-10-30F, DC-10-30F (KC10A and KDC-10), 
DC-10-40, DC-10-40F, MD-10-10F, and MD-10-30F Airplanes

AGENCY: Federal Aviation Administration, DOT.

ACTION: Final rule.

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SUMMARY: This amendment supersedes an existing airworthiness directive 
(AD), applicable to McDonnell Douglas transport category airplanes 
listed above, that currently requires a one-time detailed 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. That AD also requires 
revising the wire bundle support clamp installation at the flight 
engineer's station. For certain airplanes, this amendment requires a 
new revision of the wire bundle support clamp installation, and 
modification of a certain wire bundle. This amendment also reduces the 
applicability in the existing AD. The actions specified by this AD are 
intended 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 October 19, 2004.
    The incorporation by reference of certain publications, as listed 
in the regulations, is approved by the Director of the Federal Register 
as of October 19, 2004.
    The incorporation by reference of Boeing Alert Service Bulletin 
DC10-24A149, Revision 02, dated April 5, 2001, as listed in the 
regulations, was approved previously by the Director of the Federal 
Register as of January 16, 2002 (66 FR 64121, December 12, 2001).
    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,

[[Page 55324]]

Washington; or at the FAA, Los Angeles Aircraft Certification Office, 
3960 Paramount Boulevard, Lakewood, California; or at the National 
Archives and Records Administration (NARA). For information on the 
availability of this material at NARA, call (202) 741-6030, or go to: 
http://www.archives.gov/federal_register/code_of_federal_-
regulations/ibr--locations.html.

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 2001-24-21, 
amendment 39-12538 (66 FR 64121, December 12, 2001), which is 
applicable to all McDonnell Douglas Model DC-10 series airplanes and 
Model MD-10-10F and -30F series airplanes, was published in the Federal 
Register on October 2, 2003 (68 FR 56796). The action proposed to 
continue to require a one-time detailed 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. That action also proposed to continue 
to require revising the wire bundle support clamp installation at the 
flight engineer's station. For certain airplanes, that action proposed 
to require a new revision of the wire bundle support clamp 
installation, and modification of a certain wire bundle. That action 
also proposed to remove certain airplanes from the applicability in the 
existing AD.

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 from a single commenter.

Request To Withdraw the Proposed AD

    The commenter asks that the proposed AD be withdrawn from 
consideration. The commenter reiterates the requirements of the 
proposed AD and states that the newly proposed rule would require yet 
another replacement of the same clamp support bracket for the subject 
wire bundle. The commenter strongly objects to the proposed AD, and 
notes that its airplanes were inspected per the requirements of AD 
2001-24-21, and no chafed or damaged wires were found. The commenter 
adds that it has no recorded failures of the wire bundle support 
bracket, and has replaced the bracket as specified in Boeing Alert 
Service Bulletin DC10-24A149, Revision 02, dated April 5, 2001 
(referenced in the existing AD as the appropriate source of service 
information for accomplishment of the required actions). The commenter 
also adds that the proposed AD is unnecessary and states it is 
concerned that the succession of service bulletin revisions and 
superseded ADs adds confusion to compliance requirements, and creates 
an unnecessary risk of non-compliance.
    We do not agree. As we explained in the preamble of the proposed 
AD, we have determined that the procedures for revising the wire bundle 
support clamp installation required by AD 2001-24-21 do not adequately 
address the identified unsafe condition for certain airplanes. In 
addition, the procedures specified in Revision 02 of Boeing Alert 
Service Bulletin DC10-24A149 (referenced in AD 2001-24-21 for 
accomplishment of the required actions) do not prevent electrical 
arcing or chafing, even if no chafed or damaged wire bundles were found 
during the inspection. Since we issued that AD, we have determined that 
the required bracket installation is inadequate because the bracket 
interferes with existing potting inserts. The procedures for revising 
the wire bundle support clamp installation at the flight engineer's 
station described in Revision 02 of Boeing Alert Service Bulletin DC10-
24A149 have been changed by the issuance of two new revisions. These 
changes are included in the procedures specified in Boeing Alert 
Service Bulletins DC10-24A149, Revision 03, dated September 19, 2002; 
and Revision 04, dated March 26, 2003. Revision 03 adds procedures for 
the installation and relocation of a new bracket when revising the wire 
bundle support clamp installation, and revision of the wire bundle 
support clamp installation at the first observer's station for Group 3 
airplanes. Revision 04 adds procedures for modification of Groups 1 and 
2 airplanes on which wire bundle run (RDZ) is installed, and was 
changed as specified in Revision 03 of the alert service bulletin. In 
light of the above information, we have determined that issuance of the 
final rule is necessary.

Request To Extend Compliance Time

    The commenter asks that the compliance time of one year for the 
revision of the wire bundle support clamp installation be extended to 
18 months. The commenter notes that, since recent inspections of the 
subject area were done in accordance with the previously issued AD, the 
wire chafing condition that initially prompted the rulemaking has 
already been addressed; therefore, if any unsafe condition was found by 
any operator, it has already been corrected. The commenter adds that, 
due to this fact, allowing an 18-month compliance time for the latest 
correction to the bracket installation would in no way jeopardize the 
airworthiness or the level of safety of affected airplanes. We infer 
that the commenter is also requesting that the compliance time to 
accomplish the modification, per paragraph (d) of the proposed rule, be 
extended to 18 months.
    We agree that the compliance time may be extended to 18 months. We 
have coordinated the extension of the compliance time with the 
manufacturer and determined that extending the compliance time will not 
adversely affect the operational safety of the fleet. We have revised 
paragraphs (c) and (d) of the final rule to reflect the 18-month 
compliance time.

Request To Change Cost Impact Section

    The commenter disagrees with the estimate of 2.5 work hours for 
accomplishment of the bracket replacement. The commenter states that, 
due to confined work space and numerous wire bundles in the area of the 
modification, maintenance personnel estimate 4 work hours for 
accomplishment of the actions. The commenter asks that the work hours 
be changed before the proposed AD is issued.
    We do not agree, as we have reiterated the work hours specified in 
Revision 04 of the referenced alert service bulletin. The number of 
work hours necessary to accomplish the actions, specified in the cost 
impact information, was provided by the manufacturer based on the best 
data available to date. The cost analysis in AD rulemaking actions 
typically does not include additional costs, such as the cost for 
unforeseen work hours used when working in a confined work space with 
numerous wire bundles in the work area. Because such work hours may 
vary significantly from operator to operator, depending on the airplane 
configuration, they are almost impossible to calculate. No change to 
the final rule is necessary in this regard.

Conclusion

    We have carefully reviewed the available data, including the 
comments noted above, and have determined that

[[Page 55325]]

air safety and the public interest require adopting the AD as proposed.

Cost Impact

    There are approximately 412 airplanes of the affected design in the 
worldwide fleet. The FAA estimates that 298 airplanes of U.S. registry 
will be affected by this AD.
    The inspection that is currently required by AD 2001-24-21, takes 
about 1 work hour per airplane to accomplish, at an average labor rate 
of $65 per work hour. Based on these figures, the cost impact of the 
currently required actions on U.S. operators is estimated to be $65 per 
airplane.
    The revision of the wire bundle support clamp installation that is 
currently required by AD 2001-24-21 takes about 2 work hours per 
airplane to accomplish, at an average labor rate of $65 per work hour. 
Based on these figures, the cost impact of the currently required 
actions on U.S. operators is estimated to be $130 per airplane.
    For Groups 1, 2, and 3 airplanes: It will take about 2 work hours 
per airplane to do the new revision of the wire bundle support clamp 
installation, at an average labor rate of $65 per work hour. Required 
parts cost is minimal. Based on these figures, the cost impact of the 
installation is estimated to be $38,740, or $130 per airplane.
    For Group 4 airplanes: It will take about 1 work hour per airplane 
to do the new modification of the wire bundle, at an average labor rate 
of $65 per work hour. Required parts cost is minimal. Based on these 
figures, the cost impact of the modification is estimated to be 
$19,370, or $65 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

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 39-12538 (66 FR 
64121, December 12, 2001), and by adding a new airworthiness directive 
(AD), amendment 39-13794, to read as follows:

2004-18-15 McDonnell Douglas: Amendment 39-13794. Docket 2002-NM-
283-AD. Supersedes AD 2001-24-21, Amendment 39-12538.

    Applicability: Model DC-10-10, DC-10-10F, DC-10-15, DC-10-30, 
DC-10-30F, DC-10-30F (KC10A and KDC-10), DC-10-40, DC-10-40F, MD-10-
10F, and MD-10-30F airplanes; as listed in Boeing Alert Service 
Bulletin DC10-24A149, Revision 04, dated March 26, 2003; 
certificated in any category.
    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 Requirements of AD 2001-24-21

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 
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; Revision 03, dated September 19, 
2002; or Revision 04, dated March 26, 2003. If any damaged or chafed 
wire is found, prior to further flight, repair in accordance with 
the alert service bulletin.

    Note 1: 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.''

Revision of Wire Bundle Support Clamp Installation

    (b) Within 1 year after January 16, 2002 (the effective date of 
AD 2001-24-21, amendment 39-12538), revise the wire bundle support 
clamp installation at the flight engineer's station, in accordance 
with Boeing Alert Service Bulletin DC10-24A149, Revision 02, dated 
April 5, 2001.

New Requirements of This AD

New Revision of Wire Bundle Support Clamp Installation

    (c) Within 18 months after the effective date of this AD, do the 
applicable actions specified in paragraph (c)(1), (c)(2), or (c)(3) 
of this AD, in accordance with Boeing Alert Service Bulletin DC10-
24A149, Revision 04, dated March 26, 2003.
    (1) For Group 1 airplanes, as defined in Boeing Alert Service 
Bulletin DC10-24A149, Revision 04, dated March 26, 2003: Revise the 
wire bundle support clamp installation at the flight engineer's 
station.
    (2) For Group 2 airplanes, as defined in Boeing Alert Service 
Bulletin DC10-24A149, Revision 04, dated March 26, 2003: Revise the 
wire bundle support clamp installation at the flight engineer's 
station.
    (3) For Group 3 airplanes, as defined in Boeing Alert Service 
Bulletin DC10-24A149, Revision 04, dated March 26, 2003: Revise the 
wire bundle support clamp installation at the first observer's 
station.

Modification

    (d) For Group 4 airplanes, as defined in Boeing Alert Service 
Bulletin DC10-24A149, Revision 04, dated March 26, 2003: Within 18 
months after the effective date of this AD, modify the wire bundle 
in accordance with the Accomplishment Instructions of Boeing

[[Page 55326]]

Alert Service Bulletin DC10-24A149, Revision 04, dated March 26, 
2003.

Alternative Methods of Compliance

    (e) In accordance with 14 CFR 39.19, the Manager, Los Angeles 
Aircraft Certification Office, FAA, is authorized to approve 
alternative methods of compliance for this AD.

Incorporation by Reference

    (f) The actions must be done in accordance with the applicable 
service bulletin listed in Table 1 of this AD.

         Table 1.--Service Information Incorporated by Reference
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                                 Revision
     Service information          level                 Date
------------------------------------------------------------------------
McDonnell Douglas Alert                 01  July 28, 1999.
 Service Bulletin DC10-24A149.
Boeing Alert Service Bulletin           02  April 5, 2001.
 DC10-24A149.
Boeing Alert Service Bulletin           03  September 19, 2002.
 DC10-24A149.
Boeing Alert Service Bulletin           04  March 26, 2003.
 DC10-24A149.
------------------------------------------------------------------------

    (1) The incorporation by reference of Boeing Alert Service 
Bulletin DC10-24A149, Revision 03, dated September 19, 2002; and 
Boeing Alert Service Bulletin DC10-24A149, Revision 04, dated March 
26, 2003; 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 Boeing Alert Service 
Bulletin DC10-24A149, Revision 02, dated April 5, 2001, was approved 
previously by the Director of the Federal Register as of January 16, 
2002 (66 FR 64121, December 12, 2001).
    (3) 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).
    (4) 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 National 
Archives and Records Administration (NARA). For information on the 
availability of this material at NARA, call (202) 741-6030, or go 
to: http://www.archives.gov/federal_register/code_of_federal_ 
regulations/ibr--locations.html.

Effective Date

    (g) This amendment becomes effective on October 19, 2004.

    Issued in Renton, Washington, on August 31, 2004.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 04-20406 Filed 9-13-04; 8:45 am]
BILLING CODE 4910-13-P