[Federal Register Volume 68, Number 2 (Friday, January 3, 2003)]
[Proposed Rules]
[Pages 320-322]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 03-47]



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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2002-NM-134-AD]
RIN 2120-AA64


Airworthiness Directives; McDonnell Douglas DC-10-30 Airplane

AGENCY: Federal Aviation Administration, DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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SUMMARY: This document proposes the adoption of a new airworthiness 
directive (AD) that is applicable to a single McDonnell Douglas Model 
DC-10-30 airplane. This proposal would require repetitive tests for 
electrical continuity and resistance and repetitive inspections to 
detect discrepancies of the fuel boost/transfer pump connectors; and 
corrective actions, if necessary. This action is necessary to prevent 
arcing of connectors in the fuel boost/transfer pump circuit, which 
could result in a fire or explosion of the fuel tank. This action is 
intended to address the identified unsafe condition.

DATES: Comments must be received by February 18, 2003.

ADDRESSES: Submit comments in triplicate to the Federal Aviation 
Administration (FAA), Transport Airplane Directorate, ANM-114, 
Attention: Rules Docket No. 2002-NM-134-AD, 1601 Lind Avenue, SW., 
Renton, Washington 98055-4056. Comments may be inspected at this 
location between 9 a.m. and 3 p.m., Monday through Friday, except 
Federal holidays. Comments may be submitted via fax to (425) 227-1232. 
Comments may also be sent via the Internet using the following address: 
[email protected]. Comments sent via fax or the Internet must 
contain ``Docket No. 2002-NM-134-AD'' in the subject line and need not 
be submitted in triplicate. Comments sent via the Internet as attached 
electronic files must be formatted in Microsoft Word 97 for Windows or 
ASCII text.
    The service information referenced in the proposed rule 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 FAA, Transport Airplane Directorate, 1601 Lind 
Avenue, SW., Renton, Washington; or at the FAA, Los Angeles Aircraft 
Certification Office, 3960 Paramount Boulevard, Lakewood, California.

FOR FURTHER INFORMATION CONTACT: Philip C. Kush, Aerospace Engineer, 
Propulsion Branch, ANM-140L, FAA, Los Angeles Aircraft Certification 
Office, 3960 Paramount Boulevard, Lakewood, California 90712; telephone 
(562) 627-5263; fax (562) 627-5210.

SUPPLEMENTARY INFORMATION:

Comments Invited

    Interested persons are invited to participate in the making of the 
proposed rule by submitting such written data, views, or arguments as 
they may desire. Communications shall identify the Rules Docket number 
and be submitted in triplicate to the address specified above. All 
communications received on or before the closing date for comments, 
specified above, will be considered before taking action on the 
proposed rule. The proposals contained in this action may be changed in 
light of the comments received.
    Submit comments using the following format:
    [sbull] Organize comments issue-by-issue. For example, discuss a 
request to change the compliance time and a request to change the 
service bulletin reference as two separate issues.
    [sbull] For each issue, state what specific change to the proposed 
AD is being requested.
    [sbull] Include justification (e.g., reasons or data) for each 
request.
    Comments are specifically invited on the overall regulatory, 
economic, environmental, and energy aspects of the proposed rule. All 
comments submitted will be available, both before and after the closing 
date for comments, in the Rules Docket for examination by interested 
persons. A report summarizing each FAA-public contact concerned with 
the substance of this proposal will be filed in the Rules Docket.
    Commenters wishing the FAA to acknowledge receipt of their comments 
submitted in response to this action must submit a self-addressed, 
stamped postcard on which the following statement is made: ``Comments 
to Docket Number 2002-NM-134-AD.'' The postcard will be date stamped 
and returned to the commenter.

Availability of NPRMs

    Any person may obtain a copy of this NPRM by submitting a request 
to the FAA, Transport Airplane Directorate, ANM-114, Attention: Rules 
Docket No. 2002-NM-134-AD, 1601 Lind Avenue, SW., Renton, Washington 
98055-4056.

Discussion

    The FAA has previously received reports of five instances of failed 
connectors in the fuel boost/transfer pump circuit on certain McDonnell 
Douglas Model DC-10 and MD-11 series airplanes. The connectors returned 
for evaluation exhibited arcing of the contacts to the shell in the 
back side of the connector and between the glass insert and potting 
material. Arcing also caused the potting material to be displaced from 
the glass seal in the connector backshell, which separated the contacts 
and wiring. Typically, the circuit breaker was not actuated, as the 
arcing event was faster than the time required for the circuit breaker 
to detect the event. The only indication has been that failed 
connectors cause loss of the fuel boost/transfer pump circuit. The 
cause of the connector failures is under investigation. Arcing of 
connectors of the fuel boost/transfer pump, if not corrected, could 
result in a fire or explosion of the fuel tank.

Other Relevant Rulemaking

    We previously issued AD 2002-13-10, amendment 39-12798 (67 FR 
45053, July 8, 2002), to require repetitive tests for electrical 
continuity and resistance and repetitive inspections to detect 
discrepancies of the fuel boost/transfer pump connectors; and 
corrective actions, if necessary. That AD applies to certain McDonnell 
Douglas Model DC-10-10, -10F, -15, -30, -30F, -30F (KC10A and KDC-10), 
-40, and -40F airplanes; Model MD-10-10F and -30F airplanes; and Model 
MD-11 and -11F airplanes.
    In the final rule for AD 2002-13-10, we note that, subsequent to 
the issuance of the notice of proposed rulemaking (NPRM) for that AD, 
the manufacturer issued Boeing Alert Service Bulletin DC10-28A228, 
including Appendix, Revision 02, dated December 7, 2001. Revision 02 of 
the service bulletin contains no new procedures beyond those in 
previous revisions of the service bulletin, but adds a single airplane, 
fuselage number 0106, to the effectivity listing. That airplane had 
been inadvertently omitted from the previous issue of the service 
bulletin.
    We state in AD 2002-13-10 that we may consider additional 
rulemaking to require accomplishment of the actions in that AD on the 
airplane added to Revision 02 of the referenced service bulletin. We 
have determined that such rulemaking is indeed necessary, and this 
proposed AD follows from that determination. We have included Note 1 in 
this proposed AD to clarify that this

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proposed AD is related to AD 2002-13-10.

Explanation of Relevant Service Information

    As specified previously in AD 2002-13-10, we previously reviewed 
and approved Boeing Alert Service Bulletin DC10-28A228, including 
Appendix, Revision 02, which describe procedures for repetitive tests 
(using a digital multi-meter and Quadtech 1864 megohm meter) for 
electrical continuity and resistance and repetitive general visual 
inspections to detect discrepancies (e.g, damage, arcing, loose parts, 
wear) of the fuel boost/transfer pump connectors (alternating current 
pumping unit); and corrective actions, if necessary. The corrective 
actions include replacement of the connector/wire assembly with a 
serviceable connector/wire assembly, and replacement of the pump with a 
serviceable fuel boost/transfer pump, as applicable. Accomplishment of 
the actions specified in the service bulletin is intended to adequately 
address the identified unsafe condition.

Explanation of Requirements of Proposed Rule

    Since an unsafe condition has been identified that is likely to 
exist or develop on other products of this same type design, the 
proposed AD would require accomplishment of the actions specified in 
the service bulletin described previously, except as discussed below.

Difference Between Proposed AD and Service Information

    Although the Accomplishment Instructions of Boeing Alert Service 
Bulletin DC10-28A228, including Appendix, Revision 02, refer to a 
reporting requirement using the form in the Appendix of the service 
bulletin, this proposed AD would not require such reporting. We do not 
need the information described in the Appendix to the service bulletin.

Interim Action

    This is considered to be interim action. The manufacturer has 
advised that it currently is developing a modification that will 
address the unsafe condition addressed by this AD. Once this 
modification is developed, approved, and available, we may consider 
additional rulemaking.

Cost Impact

    This proposed AD applies to one airplane and that airplane is of 
U.S. registry. It would take approximately 65 work hours to accomplish 
the proposed tests and inspections on that airplane, at an average 
labor rate of $60 per work hour. Based on these figures, the cost 
impact of the proposed AD on the single U.S. operator is estimated to 
be $3,900, per test or inspection cycle.
    The cost impact figure discussed above is based on assumptions that 
the operator has not yet accomplished any of the proposed requirements 
of this AD action, and that the operator would not accomplish those 
actions in the future if this proposed 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 proposed herein would 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 proposal would not have federalism implications 
under Executive Order 13132.
    For the reasons discussed above, I certify that this proposed 
regulation (1) is not a ``significant regulatory action'' under 
Executive Order 12866; (2) is not a ``significant rule'' under the DOT 
Regulatory Policies and Procedures (44 FR 11034, February 26, 1979); 
and (3) if promulgated, 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 copy of the draft 
regulatory evaluation prepared for this action is contained in the 
Rules Docket. A copy of it may be obtained by contacting the Rules 
Docket at the location provided under the caption ADDRESSES.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Safety.

The Proposed Amendment

    Accordingly, pursuant to the authority delegated to me by the 
Administrator, the Federal Aviation Administration proposes to amend 
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:

McDonnell Douglas: Docket 2002-NM-134-AD.

    Applicability: Model DC-10-30 airplane, fuselage number 0106, 
certificated in any category.

    Note 1: The requirements of this AD are identical to those in AD 
2002-13-10, amendment 39-12798, which applies to Model DC-10-10, -
10F, -15, -30, -30F, -30F (KC10A and KDC-10), -40, and -40F 
airplanes, and Model MD-10-10F and -30F airplanes; as listed in 
Boeing Alert Service Bulletin DC10-28A228, including Appendix, 
Revision 01, dated July 16, 2001; and Model MD-11 and -11F 
airplanes, as listed in Boeing Alert Service Bulletin MD11-28A112, 
including Appendix, dated December 11, 2000.


    Note 2: Airplane fuel tanks on which the fuel/boost pump and 
wiring connector have been physically removed and the fuel tank made 
inoperable are not subject to the requirements of this AD.


    Note 3: This AD applies to the airplane identified in the 
preceding applicability provision, regardless of whether it has been 
otherwise modified, altered, or repaired in the area subject to the 
requirements of this AD. If the airplane has 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 arcing of connectors of the fuel boost/transfer pump, 
which could result in a fire or explosion of the fuel tank, 
accomplish the following:

Repetitive Tests and Inspections

    (a) Within 6 months after the effective date of this AD, do 
tests (using a digital multi-meter and Quadtech 1864 megohm meter or 
an equivalent megohm meter that meets current and voltage 
requirements, as specified in the service bulletin) for electrical 
continuity and resistance and a general visual inspection to detect 
discrepancies (e.g., damage, arcing, loose parts, wear) of the fuel 
boost/transfer pump (alternating current pumping unit) by 
accomplishing all the actions specified in the Accomplishment 
Instructions of Boeing Alert Service Bulletin DC10-28A228, including 
Appendix, Revision 02, dated December 7, 2001. Repeat the tests and 
inspection thereafter every 18 months. Although the service bulletin 
refers to a reporting requirement using the Appendix of the service 
bulletin, such reporting is not required.


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    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 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.''

Corrective Actions, If Necessary

    (b) If the result of any test required by paragraph (a) of this 
AD is outside the limits specified in the service bulletin 
identified in that paragraph, or if any discrepancy is detected 
during any inspection required by paragraph (a) of this AD, before 
further flight, accomplish corrective actions (e.g., replacement of 
connector/wire assembly with serviceable connector/wire assembly, 
and replacement of the pump with a serviceable fuel boost/transfer 
pump), as applicable, in accordance with the Accomplishment 
Instructions of Boeing Alert Service Bulletin DC10-28A228, including 
Appendix, Revision 02, dated December 7, 2001. Although the service 
bulletin refers to a reporting requirement using the Appendix of the 
service bulletin, such reporting is not 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. 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

    (d) Special flight permits may be issued in accordance with 
Sec. Sec.  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.

    Issued in Renton, Washington, on December 27, 2002.
Ali Bahrami,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 03-47 Filed 1-2-03; 8:45 am]
BILLING CODE 4910-13-P