AD 2002-14-12

[Federal Register Volume 67, Number 139 (Friday, July 19, 2002)]
[Rules and Regulations]
[Pages 47653-47654]
From the Federal Register Online via the Government Publishing Office [<a href="http://www.gpo.gov">www.gpo.gov</a>]
[FR Doc No: 02-17531]


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

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2001-NM-157-AD; Amendment 39-12812; AD 2002-14-12]
RIN 2120-AA64


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

AGENCY: Federal Aviation Administration, DOT.

ACTION: Final rule.

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

SUMMARY: This amendment adopts a new airworthiness directive (AD), 
applicable to certain McDonnell Douglas Model MD-11 and -11F airplanes, 
that requires an inspection of the wiring in the fuel control panel of 
the wings for chafing damage and for proper routing of the wiring; and 
corrective action(s), if necessary. This action is necessary to prevent 
chafing of the wiring in a cutout area in the wing fuel control panel 
due to improperly routed wiring, which could result in electrical 
arcing in an abnormal fuel vapor zone and consequent possible ignition 
of the fuel vapor. This action is intended to address the identified 
unsafe condition.

DATES: Effective August 23, 2002.
    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of August 23, 2002.

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: <a href="/cdn-cgi/l/email-protection#47342629232e692426352b2e0721262669202831"><span class="__cf_email__" data-cfemail="8ffceee1ebe6a1eceefde3e6cfe9eeeea1e8e0f9">[email&#160;protected]</span></a>. Questions or comments sent via the 
Internet as 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 -11F airplanes was published in the Federal Register on 
October 5, 2001 (66 FR 50875). That action proposed to require an 
inspection of the wiring in the fuel control panel of the wings for 
chafing damage and for proper routing of the wiring; and corrective 
action(s), if necessary.

Comments

    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.

Explanation of Change to Applicability

    The FAA finds that Model MD-11F airplanes were not specifically 
identified by model name in the applicability of the proposed AD. 
However, those airplanes were identified by manufacturer's fuselage 
numbers in the effectivity listing of Boeing Alert Service Bulletin 
MD11-28A058, Revision 01, dated March 29, 2001, which was referenced in 
the applicability of the proposed AD. Therefore, we have revised this 
AD to specifically reference Model MD-11 and -11F airplanes where 
appropriate. In addition, we have revised the applicability of the 
existing AD to identify model designations as published in the most 
recent type certificate data sheet for the affected models.

Explanation of Change to Inspection Definition

    For clarification purposes, the FAA has revised the definition of a 
``general visual inspection'' in Note 2 of this final rule.

Conclusion

    After careful review of the available data, 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 78 Model MD-11 and -11F airplanes of the 
affected design in the worldwide fleet. The FAA estimates that 30 
airplanes of U.S. registry will be affected by this AD, that it will 
take approximately 1 work hour per airplane to accomplish the required 
inspection, 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 $1,800, or $60 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

[[Page 47654]]

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:

2002-14-12  McDonnell Douglas: Amendment 39-12812. Docket 2001-NM-
157-AD.

    Applicability: Model MD-11 and -11F airplanes, as listed in 
Boeing Alert Service Bulletin MD11-28A058, Revision 01, dated March 
29, 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 (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 of the wiring in a cutout area in the wing 
fuel control panel due to improperly routed wiring, which could 
result in electrical arcing in an abnormal fuel vapor zone and 
consequent possible ignition of the fuel vapor, accomplish the 
following:

Inspection and Corrective Action, If Necessary

    (a) Within 6 months after the effective date of this AD, do a 
general visual inspection of the wiring in the fuel control panel of 
the wings for chafing damage and for proper routing of the wiring, 
per Boeing Alert Service Bulletin MD11-28A058, Revision 01, dated 
March 29, 2001.

    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 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.''

    (1) Condition 1. If no chafing damage is found and if the wiring 
is NOT routed into the cutout area of the fuel control panel, no 
further work is required by this AD.
    (2) Condition 2. If no chafing damage is found and if the wiring 
is routed into the cutout area of the fuel control panel, before 
further flight, revise the wire routing out of the cutout area in 
the fuel control panel, per the service bulletin.
    (3) Condition 3. If any chafing damage is found and if the 
wiring is routed into the cutout area of the fuel control panel, 
before further flight, replace any damaged wire with a new wire, and 
revise the wire routing out of the cutout area in the fuel control 
panel, per the service bulletin.

    Note 3: Accomplishment of the actions specified in McDonnell 
Douglas service Bulletin MD11-28-058, dated January 3, 1995, before 
the effective date of this AD, is 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 
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 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 Boeing Alert 
Service Bulletin MD11-28A058, Revision 01, dated March 29, 2001. 
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 August 23, 2002.

    Issued in Renton, Washington, on July 2, 2002.
Jeffrey E. Duven,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 02-17531 Filed 7-18-02; 8:45 am]
BILLING CODE 4910-13-P