[Federal Register Volume 66, Number 141 (Monday, July 23, 2001)]
[Rules and Regulations]
[Pages 38139-38141]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 01-17591]


=======================================================================
-----------------------------------------------------------------------

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2000-NM-148-AD; Amendment 39-12308; AD 2001-13-26]
RIN 2120-AA64


Airworthiness Directives; McDonnell Douglas Model DC-10-10, -15, 
-30, and -40 Series Airplanes, and Model MD-10-10F and -30F Series 
Airplanes

AGENCY: Federal Aviation Administration, DOT.

ACTION: Final rule.

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

SUMMARY: This amendment adopts a new airworthiness directive (AD), 
applicable to certain McDonnell Douglas Model DC-10-10, -15, -30, and -
40 series airplanes, and Model MD-10-10F and -30F series airplanes, 
that requires a general visual inspection to detect chafing or damage 
of the feeder cables of the external ground power in the forward cargo 
compartment between certain fuselage stations; and repair, if 
necessary. This amendment also requires installation of spiral wrap on 
the feeder cables of the external ground power. This action is 
necessary to prevent chafing of the feeder cables during removal of the 
sump panels of the cargo floor, which could result in electrical arcing 
and damage to adjacent structure, and consequent smoke and/or fire in 
the forward cargo compartment. This action is intended to address the 
identified unsafe condition.

DATES: Effective August 27, 2001.
    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of August 27, 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: Natalie Phan-Tran, Aerospace Engineer, 
Systems and Equipment Branch, ANM-130L, FAA, Los Angeles Aircraft 
Certification Office, 3960 Paramount Boulevard, Lakewood, California 
90712-4137; telephone (562) 627-5343; 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 
DC-10 series airplanes, was published in the Federal Register on 
November 29, 2000 (65 FR 71076). That action proposed to require a 
general visual inspection to detect chafing or damage of the feeder 
cables of the external ground power in the forward cargo compartment 
between certain fuselage stations; and repair, if necessary. The action 
also proposed to require installation of spiral wrap on the feeder 
cables of the external ground power.

Change to the Applicability of Notice of Proposed Rulemaking (NPRM)

    On May 9, 2000, the FAA issued a Type Certificate (TC) for 
McDonnell Douglas Model MD-10-10F and MD-10-30F series airplanes. Model 
MD-10 series airplanes are Model DC-10 series airplanes that have been 
modified with an Advanced cockpit. The feeder cables of the external 
ground power in the forward cargo compartment installed on Model MD-10-
10F and MD-10-30F series airplanes (before or after the modifications 
necessary to meet the type design of a Model MD-10 series airplane) are 
identical to those on the affected Model DC-10 series airplanes. 
Therefore, all of these airplanes may be subject to the same unsafe 
condition. In addition, the manufacturer's fuselage number and factory 
serial number are not changed during the conversion from a Model DC-10 
to Model MD-10. We find that Model MD-10-10F and MD-10-30F series 
airplanes were not specifically identified by model in the 
applicability of the NPRM; however, they were identified by 
manufacturer's fuselage numbers in McDonnell Douglas Alert Service 
Bulletin DC10-24A147, Revision 02, dated March 6, 2000 (which was 
referenced in the applicability statement of the NPRM for determining 
the specific affected airplanes). Therefore, we have revised

[[Page 38140]]

the applicability throughout the final rule to include Model MD-10-10F 
and MD-10-30F series airplanes. We have also designated the specific 
affected Model DC-10 series airplanes.

Comments

    Interested persons have been afforded an opportunity to participate 
in the making of this amendment. Due consideration has been given to 
the comment received.

Request To Delete A Certain Access Requirement

    One commenter requests that the FAA not require removal of the 
cargo sump panels, which is done as part of accessing the inspection 
area per McDonnell Douglas Alert Service Bulletin DC10-24A147, Revision 
02, dated March 6, 2000 (which was referenced in the NPRM as the 
appropriate source of service information). The commenter states that 
it has received confirmation from Boeing that removal of the cargo sump 
panels is not required to accomplish the intent of the service 
bulletin. The commenter also states that this task adds substantial 
unnecessary work hours and cost.
    The FAA agrees. Since issuance of the NPRM, the FAA has reviewed 
and approved McDonnell Douglas Alert Service Bulletin DC10-24A147, 
Revision 03, dated April 30, 2001. This revision deletes the reference 
to the sump panels as a requirement to gain access and revises the 
effectivity heading to reflect Model MD-10 series airplanes. No 
additional work is required by this revision for airplanes previously 
modified by Revision 02 of the service bulletin. Therefore, we have 
revised the final rule to reference Revision 03 of the subject service 
bulletin as the appropriate source of service information for 
accomplishing the required actions and for determining the specific 
affected airplanes. In addition, we have included a new note to give 
operators credit for previously accomplishing the requirements of this 
AD per Revision 02 of the subject service bulletin.

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 260 Model DC-10 and MD-10-10F and -30F 
series airplanes of the affected design in the worldwide fleet. The FAA 
estimates that 171 airplanes of U.S. registry will be affected by this 
AD.
    For Groups 1, 2, and 3 airplanes, it will take approximately 5 work 
hours per airplane (including gaining and closing access) to accomplish 
the required inspection, at an average labor rate of $60 per work hour. 
Based on these figures, the cost impact of the inspection required by 
this AD on U.S. operators is estimated to be $300 per airplane.
    For Group 1 airplanes, it will take approximately 2 work hours per 
airplane (including gaining and closing access) to accomplish the 
required installation, at an average labor rate of $60 per work hour. 
Required parts will cost approximately $140 per airplane. Based on 
these figures, the cost impact of the installation required by this AD 
on U.S. operators of Group 1 airplanes is estimated to be $260 per 
airplane.
    For Group 2 airplanes, it will take approximately 3 work hours per 
airplane (including gaining and closing access) to accomplish the 
required installation, at an average labor rate of $60 per work hour. 
Required parts will cost approximately $140 per airplane. Based on 
these figures, the cost impact of the installation required by this AD 
on U.S. operators of Group 2 airplanes is estimated to be $320 per 
airplane.
    For Group 3 airplanes, it will take approximately 4 work hours per 
airplane (including gaining and closing access) to accomplish the 
required installation, at an average labor rate of $60 per work hour. 
Required parts will cost approximately $140 per airplane. Based on 
these figures, the cost impact of the installation required by this AD 
on U.S. operators of Group 3 airplanes is estimated to be $380 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. 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 adding the following new 
airworthiness directive:

2001-13-26  McDonnell Douglas: Amendment 39-12308. Docket 2000-NM-
148-AD.

    Applicability: Model DC-10-10, -15, -30, and -40 series 
airplanes, and Model MD-10-10F and -30F series airplanes; as listed 
in McDonnell Douglas Alert Service Bulletin DC10-24A147, Revision 
03, dated April 30, 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

[[Page 38141]]

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 feeder cables during removal of the 
sump panels of the cargo floor, which could result in electrical 
arcing and damage to adjacent structure, and consequent smoke and/or 
fire in the forward cargo compartment, accomplish the following:

Inspection, Installation of Spiral Wrap, and Repair, if Necessary

    (a) Within 1 year after the effective date of this AD, do the 
actions specified in paragraphs (a)(1) and (a)(2) of this AD per 
McDonnell Douglas Alert Service Bulletin DC10-24A147, Revision 03, 
dated April 30, 2001.
    (1) Do a general visual inspection to detect chafing or damage 
of the feeder cables of the external ground power in the forward 
cargo compartment between fuselage stations Y=879.000 and Y=1019.000 
left of centerline. If any chafing or damage is detected, before 
further flight, repair the feeder cables of the external ground 
power and adjacent structure.

    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 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.''

    (2) Install spiral wrap on the feeder cables of the external 
ground power.

    Note 3: Accomplishment of the inspection, repair, and 
installation per McDonnell Douglas Alert Service Bulletin DC10-
24A147, Revision 02, dated March 6, 2000, 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 McDonnell 
Douglas Alert Service Bulletin DC10-24A147, Revision 03, dated April 
30, 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 27, 2001.

    Issued in Renton, Washington, on July 9, 2001.
Vi L. Lipski,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 01-17591 Filed 7-20-01; 8:45 am]
BILLING CODE 4910-13-U