[Federal Register Volume 65, Number 147 (Monday, July 31, 2000)]
[Rules and Regulations]
[Pages 46573-46575]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 00-18749]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 99-NM-214-AD; Amendment 39-11835; AD 2000-15-06]
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 general visual inspection of electrical power feeder 
cables, airplane structure, and insulation blankets at a certain 
fuselage station to detect chafing and arcing damage, and corrective 
actions, if necessary; and installation of a standoff and clamp. This 
amendment is prompted by an incident in which the power feeder cables 
in the cabin electrical system were found to be chafed and arced 
against a fuselage frame due to insufficient clearance between the 
cables and airplane structure. The actions specified by this AD are 
intended to prevent such chafing and arcing, which could cause smoke 
and fire in the overhead of the main cabin.

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 and KC-10A (military) airplanes was published in 
the Federal Register on January 26, 2000 (65 FR 4184). That action 
proposed to require a general visual inspection of electrical power 
feeder cables, airplane structure, and insulation blankets at a certain 
fuselage station to detect chafing and arcing damage, and corrective 
actions, if necessary; and installation of a standoff and clamp.

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 AD

    One commenter supports the proposed AD.

Request To Revise the Applicability

    One commenter requests that the effectivity of McDonnell Douglas 
Alert Service Bulletin DC10-24A163, dated July 28, 1999 (which was 
referenced in the applicability of the proposed AD as the appropriate 
source of service information for determining the affected 
manufacturer's fuselage numbers of the affected airplanes), be revised 
to exclude freighter airplanes N1852U through N1854U inclusive, and 
N1859U. The commenter states that the service bulletin is not 
applicable to freighter airplanes.
    The FAA concurs. The cabin power feeder cables at station 
Y=1099.00, which is the subject area of the identified unsafe condition 
of this AD, were not installed on McDonnell Douglas Model DC-10 series 
airplanes that have been converted from a passenger to a cargo-carrying 
(``freighter'') configuration, and Model DC-10-10F, -30F (KC-10A and 
KDC-10 military), and -40F series airplanes. Therefore, the FAA has 
revised the applicability of the final rule accordingly.

Request To Extend Compliance Time

    One commenter requests that the compliance time for accomplishing 
the general visual inspection be extended from the proposed 6 months to 
18 months. The commenter states that the

[[Page 46574]]

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 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 the Work Hours Specified in the Cost Estimate

    One commenter requests that the work hour figure specified in the 
Cost Impact section of the proposed AD be revised from 1 work hour to 5 
work hours, which includes 3 hours to gain access, 1 hour to inspect, 
and 1 hour to install the clamp. The commenter states that the work 
hours will be even greater than 5 if any on-condition repairs are 
needed.
    The FAA does not concur. The cost impact information, below, 
describes only the ``direct'' costs of the specific actions required by 
this AD. The work hours specified in the AD represent the time 
necessary to perform only the actions actually required by this AD. The 
FAA recognizes that, in accomplishing the requirements of any AD, 
operators may incur ``incidental'' costs in addition to the ``direct'' 
costs. The cost analysis in AD rulemaking actions, however, 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.
    In addition, the FAA notes that 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'' 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 with the changes previously 
described. The FAA has determined that these changes will neither 
increase the economic burden on any operator nor increase the scope of 
the AD.

Cost Impact

    There are approximately 160 Model DC-10 series airplanes of the 
affected design in the worldwide fleet. The FAA estimates that 80 
airplanes of U.S. registry will be affected by this AD.
    It will take approximately 1 work hour per airplane to accomplish 
the required inspection, at an average labor rate of $60 per work hour. 
Based on these figures, the cost impact of the inspection required by 
this AD on U.S. operators is estimated to be $4,800, or $60 per 
airplane.
    It will take approximately 1 work hour per airplane to accomplish 
the required installation, at an average labor rate of $60 per work 
hour. Based on these figures, the cost impact of the installation 
required by this AD on U.S. operators is estimated to be $4,800, or $60 
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 adding the following new 
airworthiness directive:

2000-15-06  McDonnell Douglas: Amendment 39-11835. Docket 99-NM-214-
AD.

    Applicability: Model DC-10 series airplanes, as listed in 
McDonnell Douglas Alert Service Bulletin DC10-24A163, dated July 28, 
1999; certificated in any category; except those airplanes that have 
been converted from a passenger to a cargo-carrying (``freighter'') 
configuration, and Model DC-10-10F, -30F (KC-10A and KDC-10 
military), and -40F series airplanes.

    Note 1: This AD applies to each airplane identified in the 
preceding applicability provision, regardless of whether it has been 
otherwise 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.

[[Page 46575]]

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 arcing of the power feeder cables against the 
fuselage structure, which could cause smoke and fire in the overhead 
of the main cabin, accomplish the following:

Inspection

    (a) Within 6 months after the effective date of this AD, perform 
a general visual inspection of the power feeder cables in the cabin 
electrical system, airplane structure, and insulation blankets at 
station Y=1099.000 between longerons 9 and 10 (right side) for 
evidence of chafing and arcing damage, in accordance with McDonnell 
Douglas Alert Service Bulletin DC10-24A163, dated July 28, 1999.

    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.''

Condition 1  Corrective Action

    (1) If no chafing or damage to the power feeder cables, 
structure, or insulation blankets is detected: Prior to further 
flight, install a standoff and clamp at station Y=1093.000, longeron 
10, in accordance with Condition 1 of the Work Instructions of the 
service bulletin.

Condition 2  Corrective Action

    (2) If any chafed power feeder cable is detected, and if no 
damage to adjacent structure or insulation blankets is detected: 
Prior to further flight, repair or replace the power feeder cables 
in the cabin electrical system with new power feeder cables; and 
install a standoff and clamp at station Y=1093.000, longeron 10, in 
accordance with Condition 2 of the Work Instructions of the service 
bulletin.

Condition 3  Corrective Action

    (3) If any chafed power feeder cable is detected, and if any 
damage to the adjacent structure and/or insulation blankets is 
detected: Prior to further flight, accomplish the actions specified 
in paragraphs (a)(3)(i), (a)(3)(ii), (a)(3)(iii), and (a)(3)(iv) of 
this AD, as applicable, in accordance with Condition 3 of the Work 
Instructions of the service bulletin.
    (i) Repair or replace the damaged power feeder cables in the 
cabin electrical system with new power feeder cables.
    (ii) Repair or replace the damaged structure with new structure.
    (iii) Repair or replace the damaged insulation blankets with new 
insulation blankets; however, insulation blankets made of metallized 
polyethyleneteraphthalate (MPET) may not be used.
    (iv) Install a standoff and clamp at station Y=1093.000, 
longeron 10.

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 DC10-24A163, 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. 00-18749 Filed 7-28-00; 8:45 am]
BILLING CODE 4910-13-U