[Federal Register Volume 65, Number 73 (Friday, April 14, 2000)]
[Rules and Regulations]
[Pages 20322-20324]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 00-8812]


-----------------------------------------------------------------------

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 99-NM-265-AD; Amendment 39-11670; AD 2000-07-16]
RIN 2120-AA64


Airworthiness Directives; McDonnell Douglas Model MD-11 and MD-
11F Series Airplanes

AGENCY: Federal Aviation Administration, DOT.

ACTION: Final rule.

-----------------------------------------------------------------------

SUMMARY: This amendment supersedes an existing airworthiness directive 
(AD),

[[Page 20323]]

applicable to certain McDonnell Douglas Model MD-11 and MD-11F series 
airplanes, that currently requires modification of the external power 
feeder cable clamping installation. This amendment also requires a 
detailed visual inspection of the external power feeder cables to 
detect chafed or damaged wires; and repair, if necessary. This 
amendment is prompted by reports of damage to the external power feeder 
cables located under the forward cargo compartment floor, which was 
caused by excessive cable length and/or maintenance personnel stepping 
on the cables. The actions specified by this AD are intended to prevent 
arcing from occurring under the forward cargo compartment floor as a 
result of damaged external power feeder cables, a situation that could 
lead to a fire at this location.

DATES: Effective May 19, 2000.
    The incorporation by reference of McDonnell Douglas Alert Service 
Bulletin MD11-24A078, Revision 01, dated June 16, 1999, as listed in 
the regulations, is approved by the Director of the Federal Register as 
of May 19, 2000.
    The incorporation by reference of McDonnell Douglas Service 
Bulletin 24-78, dated May 10, 1994, as listed in the regulations, was 
approved previously by the Director of the Federal Register as of June 
15, 1994 (59 FR 27972, May 31, 1994).

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) by superseding AD 94-11-06, 
amendment 39-8922 (59 FR 27972, May 31, 1994), which is applicable to 
certain McDonnell Douglas Model MD-11 and MD-11F series airplanes, was 
published in the Federal Register on February 1, 2000 (65 FR 4784). The 
action proposed to continue to require modification of the external 
power feeder cable clamping installation. The action also proposed to 
require a detailed visual inspection of the external power feeder 
cables to detect chafed or damaged wires; and repair, 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 single comment received.
    The commenter supports the proposed rule.

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 as proposed.

Cost Impact

    There are approximately 110 airplanes of the affected design in the 
worldwide fleet. The FAA estimates that 46 airplanes of U.S. registry 
will be affected by this AD.
    The modification of the external power feeder cable clamping 
installation that is currently required by AD 94-11-06, and retained in 
this AD, takes approximately 3 work hours per airplane to accomplish, 
at an average labor rate of $60 per work hour. Required parts cost 
approximately $395 per airplane. Based on these figures, the cost 
impact of the currently required actions on U.S. operators is estimated 
to be $26,450, or $575 per airplane.
    The new actions that are required in this AD action will take 
approximately 1 work hour per airplane to accomplish, at an average 
labor rate of $60 per work hour. Based on these figures, the cost 
impact of the new requirements of this AD on U.S. operators is 
estimated to be $2,760, or $60 per airplane.
    The cost impact figures discussed above are based on assumptions 
that no operator has yet accomplished any of the current or new 
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 removing amendment 39-8922 (59 FR 
27972, May 31, 1994), and by adding a new airworthiness directive (AD), 
amendment 39-11670, to read as follows:

2000-07-16  McDonnell Douglas: Amendment 39-11670. Docket 99-NM-265-
AD. Supersedes AD 94-11-06, Amendment 39-8922.

    Applicability: Model MD-11 and MD-11F series airplanes, as 
listed in McDonnell Douglas Service Bulletin 24-78, dated May 10, 
1994; 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

[[Page 20324]]

accordance with paragraph (c) 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 arcing from occurring under the forward cargo 
compartment floor as a result of damaged external power feeder 
cables, a situation that could lead to a fire at this location, 
accomplish the following:

Restatement of Requirements of AD 94-11-06, Amendment 39-8922 
Modification

    (a) Within 90 days after June 15, 1994 (the effective date of AD 
94-11-06, amendment 39-8922), modify the external power feeder cable 
clamping installation in accordance with McDonnell Douglas Service 
Bulletin 24-78, dated May 10, 1994, or McDonnell Douglas Alert 
Service Bulletin MD11-24A078, Revision 01, dated June 16, 1999.

New Requirements of this AD

Inspection

    (b) Within 1 year after the effective date of this AD, perform a 
detailed visual inspection of the external power cables between 
stations Y=635.000 and Y=655.000 to detect chafed or damaged wires, 
in accordance with McDonnell Douglas Alert Service Bulletin MD11-
24A078, Revision 01, dated June 16, 1999. If any chafed or damaged 
wire is found, prior to further flight, repair in accordance with 
the service bulletin.

    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.''

Alternative Methods of Compliance

    (c) 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

    (d) 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

    (e) The actions shall be done in accordance with McDonnell 
Douglas Service Bulletin 24-78, dated May 10, 1994, and McDonnell 
Douglas Alert Service Bulletin MD11-24A078, Revision 01, dated June 
16, 1999.
    (1) The incorporation by reference of McDonnell Douglas Alert 
Service Bulletin MD11-24A078, Revision 01, dated June 16, 1999 is 
approved by the Director of the Federal Register in accordance with 
5 U.S.C. 552(a) and 1 CFR part 51.
    (2) The incorporation by reference of McDonnell Douglas Service 
Bulletin 24-78, dated May 10, 1994 was approved previously by the 
Director of the Federal Register as of June 15, 1994 (59 FR 27972, 
May 31, 1994).
    (3) 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.
    (f) 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. 00-8812 Filed 4-13-00; 8:45 am]
BILLING CODE 4910-13-P