AD 2001-17-10

[Federal Register Volume 66, Number 163 (Wednesday, August 22, 2001)]
[Rules and Regulations]
[Pages 44039-44041]
From the Federal Register Online via the Government Publishing Office [<a href="http://www.gpo.gov">www.gpo.gov</a>]
[FR Doc No: 01-20937]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2000-NM-190-AD; Amendment 39-12401; AD 2001-17-10]
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 supersedes an existing airworthiness directive 
(AD), applicable to certain McDonnell Douglas Model MD-11 series 
airplanes, that currently requires a one-time inspection to detect 
riding, chafing, or damage of the wire bundles adjacent to the 
disconnect panel bracket of the observer's station. That AD also 
requires repair or replacement of damaged wires with new or serviceable 
wires; installation of anti-chafing sleeving on the wire bundles, if 
necessary; and installation of a grommet along the entire upper aft 
edge of the disconnect panel bracket. This amendment requires an 
identical one-time inspection, follow-on actions, and similar 
corrective actions, if necessary; but the installation of anti-chafing 
sleeving will be required for all airplanes. The actions specified by 
this AD are intended to detect riding or chafing of the wire bundles 
adjacent to the disconnect panel bracket assembly, which could result 
in a fire in the wire bundles and smoke in the cockpit. This action is 
intended to address the identified unsafe condition.

DATES: Effective September 26, 2001.
    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of September 26, 2001.

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: Brett Portwood, Aerospace Engineer, 
Systems and Equipment Branch, ANM-130L, FAA, Los Angeles Aircraft 
Certification Office, 3960 Paramount Boulevard, Lakewood, California 
90712; 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 97-10-12, 
amendment 39-10024 (62 FR 25839, May 12, 1997), which is applicable to 
certain McDonnell Douglas Model MD-11 series airplanes, was published 
in the Federal Register on February 20, 2001 (66 FR 10849). The action 
proposed to require a one-time inspection to detect riding, chafing, or 
damage of the wire bundles adjacent to the disconnect panel bracket of 
the observer's station; follow-on actions; corrective actions, if 
necessary; and installation of anti-chafing sleeving for all airplanes.

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.

Address Change for Obtaining Service Information

    The airplane manufacturer states that the referenced department 
name, number, and mail code of the address for obtaining service 
information are incorrect in the proposed AD. The correct address is 
Boeing Commercial Aircraft Group, Long Beach Division, 3855 Lakewood 
Boulevard, Long Beach, California 90846, Attention: Data and Service 
Management, Dept. C1-L5A (D800-0024). The airplane manufacturer 
requests that the proposed AD be revised accordingly. The FAA agrees 
and has revised this address in the final rule.

Clarify Referenced Paragraphs

    One commenter notes that the proposed AD refers to paragraph 3.B.2. 
of the Accomplishment Instructions of the referenced service bulletin 
for accomplishing the proposed actions. The commenter points out that 
the referenced service bulletin has two paragraphs 3.B.2 in the 
Accomplishment Instructions--one for Group 1 and another for Group 2. 
The commenter requests that the FAA clarify these references.
    The FAA agrees. Since additional work is NOT required for Group 2 
airplanes, our intent was that the required actions be done per Figures 
1, 2, and 3 of the referenced service bulletin, as applicable, which 
are the appropriate figures indicated in paragraph 3.B.2 of the 
Accomplishment Instruction for Group 1 airplanes. Therefore, the FAA 
has revised the final rule to reference Figures 1, 2, and 3, as 
applicable, rather than paragraph 3.B.2.

Explanation of Change to Applicability Statement

    As discussed under the heading ``Differences Between the Proposed 
AD and Service Bulletin'' in the preamble of the proposed AD, the FAA 
has consulted with the airplane manufacturer and determined that 
additional work is NOT required for Group 2 airplanes. As a result of 
this determination, we excluded Group 2 airplanes in the applicability 
statement of the proposed AD (i.e., airplanes on which anti-chafing 
sleeving was installed on the wire bundles per paragraph (a)(1) or 
(a)(2) of AD 97-10-12). Our intention was to give credit to operators 
of those airplanes on which the requirements of this AD had been 
accomplished previously, and that those airplanes continue to be 
operated per those requirements. However, since issuance of the 
proposed AD, we recognize that excluding those airplanes in the 
applicability statement is incorrect, because they would no longer be 
required to operate per the requirements of this AD. Therefore, we have 
removed that exclusion from the applicability statement and clarified 
this

[[Page 44040]]

point in a note that states, ``As allowed by the phrase, `Required as 
indicated, unless accomplished previously,' if the requirements of AD 
97-10-12 have already been accomplished, this AD does not require that 
those actions be repeated.''

Credit for Previously Installed Grommet

    One commenter requests that the FAA revise the proposed rule to 
specify that operators will be given ``credit'' for having previously 
accomplished the installation of a protective grommet per AD 97-10-12. 
The commenter suggests ways of revising the proposed AD to accommodate 
its request. As discussed above, the FAA has revised the final rule to 
address this commenter's request.

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 195 Model MD-11 series airplanes of the 
affected design in the worldwide fleet. The FAA estimates that 60 
airplanes of U.S. registry will be affected by this AD.
    The inspection and installation that are required by this AD action 
will take approximately 2 work hours per airplane to accomplish, at an 
average labor rate of $60 per work hour. The cost of required parts 
will be nominal. Based on these figures, the cost impact of the 
inspection and installation required by this AD on U.S. operators is 
estimated to $7,200, 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. 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 removing amendment 39-10024 (62 FR 
25839, May 12, 1997), and by adding a new airworthiness directive (AD), 
amendment 39-12401, to read as follows:

2001-17-10  McDonnell Douglas: Amendment 39-12401. Docket 2000-NM-
190-AD. Supersedes AD 97-10-12, Amendment 39-10024.

    Applicability: Model MD-11 series airplanes, as listed in 
McDonnell Douglas Alert Service Bulletin MD11-24A111, Revision 01, 
dated July 27, 2000; certificated in any category.

    Note 1: As allowed by the phrase, ``Required as indicated, 
unless accomplished previously,'' if the requirements of AD 97-10-12 
have already been accomplished, this AD does not require that those 
actions be repeated.


    Note 2: 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.

    Note 3: Where there are differences between the referenced 
service bulletin and the AD, the AD prevails.

    To detect riding or chafing of the wire bundles adjacent to the 
disconnect panel bracket assembly, which could result in a fire in 
the wire bundles and smoke in the cockpit, accomplish the following:

General Visual Inspection and Corrective Actions, If Necessary

    (a) Within 6 months after the effective date of this AD, perform 
a general visual inspection to detect riding, chafing, or damage of 
the wire bundles adjacent to the disconnect panel bracket, per 
Figure 1 of McDonnell Douglas Alert Service Bulletin MD11-24A111, 
Revision 01, dated July 27, 2000.

    Note 4: 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.''

    (1) If any riding or chafing is found, and if any damage is 
found: Before further flight, repair damaged wires; install anti-
chafing sleeving on the wire bundles; and install a protective 
grommet along the entire upper aft edge of the disconnect panel 
bracket; per Figures 2 and 3 of the service bulletin, respectively.
    (2) If any riding or chafing is found, but no damage is found: 
Before further flight, install anti-chafing sleeving on the wire 
bundles, and install a protective grommet along the entire upper aft 
edge of the disconnect panel bracket, per Figures 2 and 3 of the 
service bulletin, respectively.
    (3) If no riding, chafing, or damage is found: Before further 
flight, install anti-chafing sleeving on the wire bundles, and 
install a protective grommet along the entire upper aft edge of the 
disconnect panel bracket, per Figures 2 and 3 of the service 
bulletin, respectively.

[[Page 44041]]

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. 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 5: 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 MD11-24A111, Revision 01, dated July 
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: 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

    (e) This amendment becomes effective on September 26, 2001.

    Issued in Renton, Washington, on August 14, 2001.
Vi L. Lipski,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 01-20937 Filed 8-21-01; 8:45 am]
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