AD 2000-07-19

[Federal Register Volume 65, Number 73 (Friday, April 14, 2000)]
[Rules and Regulations]
[Pages 20327-20329]
From the Federal Register Online via the Government Publishing Office [<a href="http://www.gpo.gov">www.gpo.gov</a>]
[FR Doc No: 00-8815]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 99-NM-268-AD; Amendment 39-11673; AD 2000-07-19]
RIN 2120-AA64


Airworthiness Directives; McDonnell Douglas Model MD-11 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 MD-11 series airplanes, 
that requires a detailed visual inspection of the external power feeder 
cables in the forward cargo compartment between certain stations to 
detect chafing or damage; repair, if necessary; and installation of 
spiral wrap. This amendment is prompted by reports of failure of the 
external power feeder cable due to being chafed during maintenance. The 
actions specified by this AD are intended to prevent chafing and damage 
to external ground power feeder cables, which could result in 
electrical arcing and consequent structural damage and smoke and fire 
in the forward cargo compartment.

DATES: Effective May 19, 2000.
    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of May 19, 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: Brett Portwood, 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) 627-5350; 
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 
MD-11 series airplanes was published in the Federal Register on 
February 1, 2000 (65 FR 4790). That action proposed to require a 
detailed visual inspection of the external power feeder cables in the 
forward cargo compartment between certain stations to detect chafing or 
damage; repair, if necessary; and installation of spiral wrap.

Comments

    Interested persons have been afforded an opportunity to participate 
in the making of this amendment. Due consideration has been given to 
the single comment received.
    The commenter supports the proposed rule.

Explanation of Revised Alert Service Bulletin

    Since issuance of the NPRM, the FAA has reviewed and approved 
Revision 02 of McDonnell Douglas Alert Service Bulletin MD11-24A008, 
dated March

[[Page 20328]]

27, 2000. The inspection and corrective action procedures in Revision 
02 are identical that those specified in Revision 01 of the alert 
service bulletin, which was referenced in the proposed AD as the 
appropriate source of service information. Revision 02 of the alert 
service bulletin reverses the order of the groups of affected airplanes 
and removes one airplane from the effectivity listing.
    As a result of the revised alert service bulletin, the FAA has 
revised the final rule to reference Revision 02 of the alert service 
bulletin as the appropriate source of service information for 
accomplishing the actions required by this AD and for determining the 
applicability of the AD. The FAA also has revised the final rule by 
including a new note that gives operators credit for accomplishing the 
actions required by this AD in accordance with Revision 01 of the alert 
service. In addition, the FAA has revised the Cost Impact section of 
the AD to reflect the appropriate cost information for the revised 
airplane groups.

Conclusion

    After careful review of the available data, including the comment 
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 38 airplanes of the affected design in the 
worldwide fleet. The FAA estimates that 14 airplanes (11 airplanes 
identified as Group 1 and 3 airplanes identified as Group 2) of U.S. 
registry will be affected by this AD.
    For Group 2 airplanes, the FAA estimates that it will take 
approximately 1 work hour per airplane to accomplish the required 
inspection, and approximately 2 work hours per airplane to accomplish 
the required installation of spiral wrap, and that the average labor 
rate is $60 per work hour. Required parts will cost approximately $140 
per airplane. Based on these figures, the cost impact of the AD on U.S. 
operators of Group 2 airplanes is estimated to be $960, or $320 per 
airplane.
    For Group 1 airplanes, the FAA estimates that it will take 
approximately 2 work hours per airplane to accomplish the required 
inspection, and approximately 3 work hours per airplane to accomplish 
the required installation of spiral wrap. Required parts will cost 
approximately $140 per airplane. Based on these figures, the cost 
impact of the AD on U.S. operators of Group 1 airplanes is estimated to 
be $4,840, or $440 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.

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:

2000-07-19  McDonnell Douglas: Amendment 39-11673. Docket 99-NM-268-
AD.

    Applicability: Model MD-11 series airplanes, as listed in 
McDonnell Douglas Alert Service Bulletin MD11-24A008, Revision 02, 
dated March 27, 2000; 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 damage to external ground power feeder 
cables, which could result in electrical arcing and consequent 
structural damage and smoke and fire in the forward cargo 
compartment, accomplish the following:

Inspection and Modification

    (a) Within 12 months after the effective date of this AD, 
perform a detailed visual inspection of the external ground power 
feeder cables in the forward cargo compartment between stations 
Y=879.000 and Y=1019.000 left of centerline to detect chafing or 
damage, in accordance with McDonnell Douglas Alert Service Bulletin 
MD11-24A008, Revision 02, March 27, 2000.

    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 chafing or damage is detected, prior to further 
flight, repair and install spiral wrap, in accordance with the 
service bulletin.
    (2) If no chafing or damage is detected, prior to further 
flight, install spiral wrap in accordance with the service bulletin.

    Note 3: Inspections, repairs, and installations accomplished 
prior the effective date of this AD in accordance with McDonnell 
Douglas Alert Service Bulletin MD11-24A008, Revision 01, dated 
December 2, 1999; are considered acceptable for compliance with the 
requirements of this AD.

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

[[Page 20329]]

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 4: 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 
Secs. 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 MD11-24A008, Revision 02, dated March 
27, 2000. 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.
    (e) This amendment becomes effective on May 19, 2000.

    Issued in Renton, Washington, on April 4, 2000.
Donald L. Riggin,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 00-8815 Filed 4-13-00; 8:45 am]
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