[Federal Register Volume 65, Number 147 (Monday, July 31, 2000)]
[Rules and Regulations]
[Pages 46571-46573]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 00-18750]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 99-NM-215-AD; Amendment 39-11836; AD 2000-15-07]
RIN 2120-AA64


Airworthiness Directives; McDonnell Douglas Model DC-10 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 DC-10 series airplanes, 
that requires a one-time detailed visual inspection of the galley power 
feeder cables and fuselage structure at a certain station to detect 
chafing or arcing damage to the cables and structure or to detect 
arcing damage to the insulation blankets; and corrective actions, if 
necessary. This AD also requires installation of spacers between the 
galley power feeder cable clamps and fuselage structure. This amendment 
is prompted by reports indicating that the galley power feeder cables 
chafed against a certain fuselage frame in the forward lower cargo 
compartment, which resulted in electrical arcing. The actions specified 
by this AD are intended to prevent such chafing and arcing due to 
insufficient clearance between the cables and the airplane structure, 
which could result in smoke and fire in the forward lower cargo 
compartment.

DATES: Effective September 4, 2000.
    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of September 4, 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: 
Technical Publications Business Administration, Dept. C1-L51 (2-60). 
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, Transport Airplane Directorate, 
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, Transport Airplane 
Directorate, 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 series airplanes was published in the Federal Register on January 
26, 2000 (65 FR 4182). That action proposed to require a one-time 
detailed visual inspection of the galley power feeder cables and 
fuselage structure at a certain station to detect chafing or arcing 
damage to the cables and structure or to detect arcing damage to the 
insulation blankets; and corrective actions, if necessary. That action 
also proposed to require installation of spacers between the galley 
power feeder cable clamps and fuselage structure.

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 Proposed Rule

    Several commenters support the proposed rule.

Request To Extend Compliance Time

    One commenter requests that the compliance time from accomplishing 
the detailed visual inspection be extended from the proposed 6 months 
to 18 months. The commenter states that the inspection should be 
accomplished during a heavy maintenance visit to ensure that proper 
access can be obtained, all discrepancies are identified, and that any 
on-condition repairs can be performed in the proper maintenance 
environment.
    The FAA does not concur. In developing an appropriate compliance 
time for this inspection, the FAA considered not only the degree of 
urgency associated with addressing the subject unsafe condition, but 
the manufacturer's recommendation as to an appropriate compliance time, 
the availability of required parts, and the practical aspect of 
accomplishing the inspection within an interval of time that parallels 
the normal scheduled maintenance for the majority of affected 
operators. In light of these items, the FAA has determined that 6 
months for

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compliance is appropriate. However, under the provisions of paragraph 
(b) of the final rule, the FAA 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 Hour Estimate

    One commenter requests that the work hour estimate for 
accomplishing the proposed inspection be revised from 2 work hours to 4 
work hours. The commenter states that the proposed inspection alone 
will require 4 work hours. The commenter notes that any on-condition 
repairs will add additional time to this inspection, and that any 
structural repairs that may be needed will significantly increase the 
hours necessary to accomplish the requirements of the proposed AD.
    The FAA does not concur. The work hour estimate (i.e., 2 work 
hours) in the proposed AD reflects the time necessary to accomplish the 
required inspection (1 work hour) and installation of spacers (1 work 
hour). The FAA used the work hours specified in McDonnell Douglas Alert 
Service Bulletin DC10-24A162, dated July 28, 1999 (which is referenced 
in the AD as the appropriate source of service information for 
accomplishment of the required inspection and installation). In 
addition, the economic analysis of the AD is limited only to the cost 
of actions actually required by the rule. It does not consider the 
costs of ``on condition'' actions, such as repairing a crack if one is 
detected during a required inspection (``repair, if necessary''). Such 
``on-condition'' repair actions would be required to be accomplished--
regardless of AD direction--in order to correct an unsafe condition 
identified in an airplane and to ensure operation of that airplane in 
an airworthy condition, as required by the Federal Aviation 
Regulations. 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 168 Model DC-10 series airplanes of the 
affected design in the worldwide fleet. The FAA estimates that 103 
airplanes of U.S. registry will be affected by this AD, that it will 
take approximately 2 work hours per airplane to accomplish the required 
actions, and that the average labor rate is $60 per work hour. Based on 
these figures, the cost impact of the AD on U.S. operators is estimated 
to be $12,360, or $120 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.

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:

2000-15-07  McDonnell Douglas: Amendment 39-11836. Docket 99-NM-215-
AD.

    Applicability: Model DC-10 series airplanes, as listed in 
McDonnell Douglas Alert Service Bulletin DC10-24A162, dated July 28, 
1999; 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 and arcing of the galley power feeder cables 
against the airplane structure due to insufficient clearance between 
the cables and the airplane structure, which could result in smoke 
and fire in the forward lower cargo compartment, accomplish the 
following:

Inspection, Installation of Spacers, and Corrective Actions, If 
Necessary

    (a) Within 6 months after the effective date of this AD, perform 
a detailed visual inspection of the galley external power feeder 
cables and fuselage structure at station Y=635.000 to detect chafing 
or arcing damage to the cables and structure or to detect arcing 
damage to the insulation blankets, in accordance with McDonnell 
Douglas Alert Service Bulletin DC10-24A162, dated July 28, 1999.

    Note 2: For the purposes of this AD, a detailed visual 
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.''

    (1) If any damage or chafing is detected, prior to further 
flight, accomplish the actions specified in paragraphs (a)(1)(i), 
(a)(1)(ii), (a)(1)(iii), and (a)(1)(iv) of this AD, as applicable, 
in accordance with Condition 2 of the Accomplishment Instructions of 
the service bulletin.
    (i) Repair or replace the chafed cables with new cables.
    (ii) Repair the damaged frame.
    (iii) Replace the damaged insulation blanket with a new blanket; 
however, insulation blankets made of metallized 
polyethyleneteraphthalate (MPET) may not be used.
    (iv) Install spacers between the galley power feeder cable 
clamps and fuselage structure.
    (2) If no damage or chafing is detected, prior to further 
flight, install spacers between

[[Page 46573]]

the galley power feeder cable clamps and fuselage structure in 
accordance with Condition 1 of the Accomplishment Instructions of 
the service bulletin.

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, Transport Airplane Directorate. 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

    (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 McDonnell 
Douglas Alert Service Bulletin DC10-24A162, dated July 28, 1999. 
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: Technical Publications Business Administration, 
Dept. C1-L51 (2-60). Copies may be inspected at the FAA, Transport 
Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington; or 
at the FAA, Transport Airplane Directorate, 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 4, 2000.


    Issued in Renton, Washington, on July 19, 2000.
Donald L. Riggin,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 00-18750 Filed 7-28-00; 8:45 am]
BILLING CODE 4910-13-U