AD 2003-08-03

[Federal Register Volume 68, Number 74 (Thursday, April 17, 2003)]
[Rules and Regulations]
[Pages 18852-18854]
From the Federal Register Online via the Government Publishing Office [<a href="http://www.gpo.gov">www.gpo.gov</a>]
[FR Doc No: 03-8894]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2001-NM-99-AD; Amendment 39-13114; AD 2003-08-03]
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 adopts a new airworthiness directive (AD), 
applicable to certain McDonnell Douglas airplane models. This amendment 
requires repetitive inspections for chafing or potential chafing of the 
wiring for the throttle control module (TCM) on the center pedestal in 
the flight deck compartment, corrective actions if necessary, an 
inspection of the TCM to determine its part number and configuration, 
and modification of the TCM. Doing this modification terminates the 
repetitive inspections. The actions specified by this AD are intended 
to prevent chafing

[[Page 18853]]

of wiring inside the TCM, fuel shutoff lever lights, and/or aft 
pedestal lightplates due to degradation of protective sleeving, which 
could result in electrical arcing and failure of the auto throttle/
speed control system and consequent smoke and/or fire in the cockpit.

DATES: Effective May 22, 2003.
    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of May 22, 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 Federal Aviation Administration (FAA), Transport 
Airplane Directorate, Rules Docket, 1601 Lind Avenue, SW., Renton, 
Washington; 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) to include an airworthiness 
directive (AD) that is applicable to certain 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, 
was published as a supplemental notice of proposed rulemaking (NPRM) in 
the Federal Register on January 3, 2003 (68 FR 305). That action 
proposed to require an inspection of the throttle control module (TCM) 
on the center pedestal in the flight deck compartment to determine its 
part number and configuration, modification of the TCM, repetitive 
inspections for chafing or potential chafing of the TCM wiring, and 
corrective actions if necessary.

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.

Support for the Proposal

    The Air Transport Association of America (ATA) states that its 
members support the intent of the proposal. In a comment attached to 
the ATA's comment, one ATA member states that it appreciates the FAA's 
decision in the supplemental NPRM to extend the compliance time for the 
proposed actions to 5 years.

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 401 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 of the affected design in the 
worldwide fleet. The FAA estimates that 321 airplanes of U.S. registry 
will be affected by this AD.
    We estimate that it will take approximately 2 work hours per 
airplane to perform the required inspections, at an average labor rate 
of $60 per work hour. Based on these figures, the cost impact of the 
inspections required by this AD on U.S. operators is estimated to be 
$38,520, or $120 per airplane, per inspection cycle.
    It will take approximately 15 work hours per airplane to accomplish 
the required modification at an average labor rate of $60 per work 
hour. Required parts will cost approximately $1,712 per airplane. Based 
on these figures, the cost impact of the modification required by this 
AD on U.S. operators is estimated to be $838,452, or $2,612 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

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 adding the following new airworthiness 
directive:

2003-08-03 McDonnell Douglas: Amendment 39-13114. Docket 2001-NM-99-
AD.

    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 DC10-76A048, Revision 01, dated January 29, 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

[[Page 18854]]

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) 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 wiring inside the throttle control module, 
fuel shutoff lever lights, and/or aft pedestal lightplates due to 
degradation of protective sleeving, which could result in electrical 
arcing and failure of the auto throttle/speed control system and 
consequent smoke and/or fire in the cockpit, accomplish the 
following:

Repetitive Inspections for Chafing

    (a) Within 18 months after the effective date of this AD, 
perform a general visual inspection for chafing or potential chafing 
of the wiring of the throttle control module located on the center 
pedestal in the flight compartment, per Boeing Alert Service 
Bulletin (ASB) DC10-76A049, excluding the Appendix and Evaluation 
Form, dated January 29, 2002. Thereafter, repeat the inspection at 
intervals not to exceed 18 months, until the actions specified in 
paragraph (c) of this AD are accomplished.

    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 from within 
touching distance unless otherwise specified. A mirror may be 
necessary to enhance visual access to all exposed surfaces in the 
inspection area. This level of inspection is made under normally 
available lighting conditions such as daylight, hangar lighting, 
flashlight, or droplight 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.''

Corrective Actions for Chafing or Potential Chafing

    (b) If any evidence of chafing or potential chafing is found 
during any inspection required by paragraph (a) of this AD, before 
further flight, repair the chafed wires or reposition wires, as 
applicable, per Boeing ASB DC10-76A049, excluding the Appendix and 
Evaluation Form, dated January 29, 2002.

Inspection and Modification

    (c) Within 5 years after the effective date of this AD, do the 
actions specified in paragraphs (c)(1) and (c)(2) of this AD, per 
Boeing ASB DC10-76A048, excluding the Evaluation Form, dated August 
6, 2001; or Revision 01, excluding the Evaluation Form, dated 
January 29, 2002.
    (1) Do an inspection of the throttle control module on the 
center pedestal in the flight deck compartment to determine its part 
number and configuration, which will identify the group 
applicability information.
    (2) Modify the throttle control module on the center pedestal in 
the flight deck compartment per the applicable figure in the service 
bulletin. Accomplishment of the modification constitutes terminating 
action for the requirements of paragraph (a) of this AD.

Alternative Methods of Compliance

    (d) 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

    (e) 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

    (f) The actions shall be done in accordance with Boeing Alert 
Service Bulletin DC10-76A048, excluding the Evaluation Form, dated 
August 6, 2001, or Boeing Alert Service Bulletin DC10-76A048, 
Revision 01, excluding the Evaluation Form, dated January 29, 2002; 
and Boeing Alert Service Bulletin DC10-76A049, excluding the 
Appendix and Evaluation Form, dated January 29, 2002; as applicable. 
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; 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

    (g) This amendment becomes effective on May 22, 2003.

    Issued in Renton, Washington, on April 7, 2003.
Ali Bahrami,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 03-8894 Filed 4-16-03; 8:45 am]
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