[Federal Register Volume 67, Number 3 (Friday, January 4, 2002)]
[Proposed Rules]
[Pages 550-552]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 02-209]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2001-NM-121-AD]
RIN 2120-AA64


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

AGENCY: Federal Aviation Administration, DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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SUMMARY: This document proposes the adoption of a new airworthiness 
directive (AD) that is applicable to McDonnell Douglas Model DC-10-10, 
-10F, -15, -30, -30F (KC-10A and KDC-10), -40, and -40F series 
airplanes; and Model MD-10-10F and MD-10-30F series airplanes. This 
proposal would require an inspection of the parallel power feeder 
cables of the number 2 generator for chafing or structure damage; 
repositioning of the cables; and repair, if necessary. This action is 
necessary to prevent wire chafing of the parallel power feeder cables 
of the number 2 generator, which, if not corrected, could result in 
electrical arcing and damage to adjacent structure, and consequent 
smoke and/or fire in the aft door panel area. This action is intended 
to address the identified unsafe condition.

DATES: Comments must be received by February 19, 2002.

ADDRESSES: Submit comments in triplicate to the Federal Aviation 
Administration (FAA), Transport Airplane Directorate, ANM-114, 
Attention: Rules Docket No. 2001-NM-121-AD, 1601 Lind Avenue, SW., 
Renton, Washington 98055-4056. Comments may be inspected at this 
location between 9 a.m. and 3 p.m., Monday through Friday, except 
Federal holidays. Comments may be submitted via fax to (425) 227-1232. 
Comments may also be sent via the Internet using the following address: 
[email protected]. Comments sent via fax or the Internet must 
contain ``Docket No. 2001-NM-121-AD'' in the subject line and need not 
be submitted in triplicate. Comments sent via the Internet as attached 
electronic files must be formatted in Microsoft Word 97 for Windows or 
ASCII text.
    The service information referenced in the proposed rule 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.

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:

Comments Invited

    Interested persons are invited to participate in the making of the 
proposed rule by submitting such written data, views, or arguments as 
they may desire. Communications shall identify the Rules Docket number 
and be submitted in triplicate to the address specified above. All 
communications received on or before the closing date for comments, 
specified above, will be considered before taking action on the 
proposed rule. The proposals contained in this action may be changed in 
light of the comments received.
    Submit comments using the following format:
     Organize comments issue-by-issue. For example, discuss a 
request to change the compliance time and a request to change the 
service bulletin reference as two separate issues.
     For each issue, state what specific change to the proposed 
AD is being requested.
     Include justification (e.g., reasons or data) for each 
request.
    Comments are specifically invited on the overall regulatory, 
economic, environmental, and energy aspects of the proposed rule. All 
comments submitted will be available, both before and after the closing 
date for comments, in the Rules Docket for examination by interested 
persons. A report summarizing each FAA-public contact concerned with 
the substance of this proposal will be filed in the Rules Docket.
    Commenters wishing the FAA to acknowledge receipt of their comments 
submitted in response to this action must submit a self-addressed, 
stamped postcard on which the following statement is made: ``Comments 
to Docket Number 2001-NM-121-AD.'' The postcard will be date stamped 
and returned to the commenter.

Availability of NPRMs

    Any person may obtain a copy of this NPRM by submitting a request 
to the FAA, Transport Airplane Directorate, ANM-114, Attention: Rules 
Docket No. 2001-NM-121-AD, 1601 Lind Avenue, SW., Renton, Washington 
98055-4056.

Discussion

    The FAA has received a report of a fault alert of the electrical 
power generator system with smoke in the right aft galley area on a 
McDonnell Douglas Model MD-11 series airplane. The affected airplane 
had accumulated 28,867 total flight hours and 4,878 total flight 
cycles. Investigation revealed that the parallel power feeder cable of 
the number 2 Integrated Drive Generator (IDG) was burned through 30 
percent due to chafing on the aft track of door R4. The parallel power 
feeder cables on Model MD-11 and DC-10 series airplanes, and Model MD-
10-10F and MD-10-30F series airplanes are routed the same at the aft 
track of door R4. Wire chafing of the parallel power feeder cables of 
the number 2 generator, if not corrected, could result in electrical 
arcing and damage to adjacent structure, and consequent smoke and/or 
fire in the aft door panel area.

Other Relevant Rulemaking

    On August 14, 2001, the FAA issued AD 2001-17-08, amendment 39-
12399 (66 FR 44043, August 22, 2001), which applies to certain 
McDonnell Douglas Model MD-11 series airplanes. That AD is intended to 
prevent chafing and

[[Page 551]]

arcing of the parallel feeder cables of the number 2 IDG, which could 
result in smoke and/or fire in the right aft galley area. The AD 
requires a general visual inspection to detect chafing or damage of the 
parallel power feeder cables of the number 2 IDG; repairing any chafed 
cable and damaged structure; and repositioning the parallel power 
feeder cables of the number 2 IDG.

Explanation of Relevant Service Information

    The FAA has reviewed and approved Boeing Alert Service Bulletin 
DC10-24A170, Revision 01, dated September 25, 2001, which describes 
procedures for a one-time general visual inspection of the parallel 
power feeder cables of the number 2 generator for chafing and structure 
damage; repositioning of the cables; and repair, if necessary. 
Accomplishment of the actions specified in the alert service bulletin 
is intended to adequately address the identified unsafe condition.

Explanation of Requirements of Proposed Rule

    Since an unsafe condition has been identified that is likely to 
exist or develop on other products of this same type design, the 
proposed AD would require accomplishment of the actions specified in 
the alert service bulletin described previously.

Cost Impact

    There are approximately 231 Model DC-10-10, -10F, -15, -30, -30F 
(KC-10A and KDC-10), -40, and -40F series airplanes; and Model MD-10-
10F and MD-10-30F series airplanes of the affected design in the 
worldwide fleet. The FAA estimates that 157 airplanes of U.S. registry 
would be affected by this proposed AD.
    It would take approximately 1 work hour per airplane to accomplish 
the proposed inspection, at an average labor rate of $60 per work hour. 
Based on these figures, the cost impact of the inspection proposed by 
this AD on U.S. operators is estimated to be $9,420, or $60 per 
airplane.
    It would take approximately 2 work hours per airplane to accomplish 
the proposed repositioning of cables, at an average labor rate of $60 
per work hour. Required parts would cost approximately $646 per 
airplane. Based on these figures, the cost impact of the repositioning 
of cables proposed by this AD on U.S. operators is estimated to be 
$120,262, or $766 per airplane.
    The cost impact figures discussed above are based on assumptions 
that no operator has yet accomplished any of the proposed requirements 
of this AD action, and that no operator would accomplish those actions 
in the future if this proposed 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 proposed herein would 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 proposal would not have federalism implications 
under Executive Order 13132.
    For the reasons discussed above, I certify that this proposed 
regulation (1) is not a ``significant regulatory action'' under 
Executive Order 12866; (2) is not a ``significant rule'' under the DOT 
Regulatory Policies and Procedures (44 FR 11034, February 26, 1979); 
and (3) if promulgated, 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 copy of the draft 
regulatory evaluation prepared for this action is contained in the 
Rules Docket. A copy of it may be obtained by contacting the Rules 
Docket at the location provided under the caption ADDRESSES.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Safety.

The Proposed Amendment

    Accordingly, pursuant to the authority delegated to me by the 
Administrator, the Federal Aviation Administration proposes to amend 
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:

McDonnell Douglas: Docket 2001-NM-121-AD.

    Applicability: Model DC-10-10, -10F, -15, -30, -30F (KC-10A and 
KDC-10), -40, and -40F series airplanes; and Model MD-10-10F and MD-
10-30F series airplanes, certificated in any category; as identified 
in Boeing Alert Service Bulletin DC10-24A170, Revision 01, dated 
September 25, 2001.

    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 wire chafing of the parallel power feeder cables of 
the number 2 generator, which, if not corrected, could result in 
electrical arcing and damage to adjacent structure, and consequent 
smoke and/or fire in the aft door panel area, accomplish the 
following:

Inspection and Follow-On Actions

    (a) Within 6 months after the effective date of this AD, do a 
one-time general visual inspection of the parallel power feeder 
cables of the number 2 generator for chafing and structure damage, 
per Boeing Alert Service Bulletin DC10-24A170, Revision 01, dated 
September 25, 2001.
    (1) Condition 1. If no chafing or structure damage is found: At 
the next scheduled maintenance visit, but no later than 6 months 
after the effective date of this AD, reposition the cables per the 
alert service bulletin.
    (2) Condition 2. If any chafing or structure damage is found: 
Prior to further flight, repair the cable and damaged adjacent 
structure, as applicable, and reposition the cables, per the alert 
service bulletin.

    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.''

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.


[[Page 552]]


    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 Permit

    (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.

    Issued in Renton, Washington, on December 21, 2001.
Vi L. Lipski,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 02-209 Filed 1-3-02; 8:45 am]
BILLING CODE 4910-13-P