AD 2003-04-17

[Federal Register Volume 68, Number 76 (Monday, April 21, 2003)]
[Rules and Regulations]
[Pages 19337-19339]
From the Federal Register Online via the Government Publishing Office [<a href="http://www.gpo.gov">www.gpo.gov</a>]
[FR Doc No: 03-9427]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2001-NM-166-AD; Amendment 39-13066; AD 2003-04-17]
RIN 2120-AA64


Airworthiness Directives; McDonnell Douglas Model MD-11 and MD-
11F 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 and MD-11F 
airplanes, that requires an inspection to detect damage of the wiring/
bundles routed to the wire support bar of the circuit breaker panel and 
to the circuit breakers, and an inspection of the wiring/bundles for 
correct routing. This amendment also requires installation of 
protective sleeving, spacers, and sta-straps; and corrective/follow-on 
actions, if necessary. The actions specified by this AD are necessary 
to prevent chafing and consequent arcing or loss of electrical power to 
associated avionics buses in the upper avionics circuit breaker panel 
of the main observer's station, which could result in smoke and/or fire 
in the cockpit. This action is intended to address the identified 
unsafe condition.

DATES: Effective May 27, 2003.
    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of May 27, 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; or 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: Technical Information: Brett Portwood, 
Aerospace Engineer, Systems and Equipment Branch, ANM-130L, FAA, Los 
Angeles Aircraft Certification Office, 3960 Paramount Boulevard, 
Lakewood, California 90712-4137; telephone (562) 627-5350; fax (562) 
627-5210.
    Other Information: Sandi Carli, Airworthiness Directive Technical 
Writer/Editor; telephone (425) 687-4243, fax (425) 227-1232. Questions 
or comments may also be sent via the Internet using the following 
address:

[[Page 19338]]

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attached electronic files must be formatted in Microsoft Word 97 for 
Windows or ASCII text.

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 and MD-11F airplanes was published in the Federal Register on 
August 29, 2002 (67 FR 55372). That action proposed to require an 
inspection to detect damage of the wiring/bundles routed to the wire 
support bar of the circuit breaker panel and to the circuit breakers, 
and an inspection of the wiring/bundles for correct routing. That 
action also proposed to require installation of protective sleeving, 
spacers, and sta-straps; and corrective/follow-on actions, if 
necessary.

Explanation of Editorial Change

    We have changed the service bulletin citation throughout this final 
rule to exclude the Evaluation Form. (The form is intended to be 
completed by operators and submitted to the manufacturer to provide 
input on the quality of the service bulletin; however, this AD does not 
include such a requirement.)

Opportunity To Comment

    Interested persons have been afforded an opportunity to participate 
in the making of this amendment. No comments were submitted in response 
to the proposal or the FAA's determination of the cost to the public.

Conclusion

    The FAA has determined that air safety and the public interest 
require the adoption of the rule as proposed.

Cost Impact

    There are approximately 195 Model MD-11 and MD-11F airplanes of the 
affected design in the worldwide fleet. The FAA estimates that 72 
airplanes of U.S. registry will be affected by this AD, that it will 
take approximately 3 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 $12,960, or $180 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. 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

0
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:

2003-04-17 McDonnell Douglas: Amendment 39-13066. Docket 2001-NM-
166-AD.

    Applicability: Model MD-11 and MD-11F airplanes, as listed in 
Boeing Alert Service Bulletin MD11-24A179, Revision 02, dated 
December 19, 2001; 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 (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 chafing and consequent arcing or loss of electrical 
power to associated avionics buses in the upper avionics circuit 
breaker panel, which could result in smoke and/or fire in the 
cockpit, accomplish the following:

Inspection, Corrective Actions, Modification, and Installation

    (a) Within 6 months after the effective date of this AD, do the 
actions specified in paragraphs (a)(1) through (a)(3) of this AD, 
per Boeing Alert Service Bulletin MD11-24A179, Revision 02, dated 
December 19, 2001, excluding Evaluation Form.
    (1) Do a detailed inspection to detect damage of the wiring/
bundles routed to the wire support bar of the circuit breaker panel 
and to the circuit breakers.

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

    (2) Do a general visual inspection of the wiring/bundles for 
correct routing. Make sure ABS9108 (16-gauge power feeders) routing 
provides adequate stress relief from the support bar to bus 
termination points.

    Note 3: 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.''

    (3) Install protective sleeving, spacers, and sta-straps.

[[Page 19339]]

Corrective/Follow-On Actions, If Necessary

    (b) Before further flight after doing the inspections required 
by paragraphs (a)(1) and (a)(2) of this AD, do the applicable 
corrective/follow-on action(s) specified in ``Table-Corrective/
Follow-On Actions'' of this AD per Boeing Alert Service Bulletin 
MD11-24A179, Revision 02, dated December 19, 2001, excluding 
Evaluation Form. Table--Corrective/Follow-On Actions is as follows:

                  Table.--Corrective/Follow-On Actions
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             If--                                Then--
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(1) Any damaged wiring/bundle  Repair or replace any damaged wiring/
 is detected.                   bundle with new wiring.
(2) Correct routing is         Replace the wire clamp located on the
 detected.                      support bar of the circuit breaker panel
                                with a new clamp.
(3) Incorrect routing is       Modify wire routing, and replace the wire
 detected.                      clamp located on the support bar of the
                                circuit breaker panel with a new clamp.
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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. 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 Permit

    (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 Boeing Alert 
Service Bulletin MD11-24A179, Revision 02, dated December 19, 2001, 
excluding Evaluation Form. 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; or 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

    (f) This amendment becomes effective on May 27, 2003.

    Issued in Renton, Washington, on April 10, 2003.
Ali Bahrami,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 03-9427 Filed 4-18-03; 8:45 am]
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