[Federal Register Volume 68, Number 80 (Friday, April 25, 2003)]
[Rules and Regulations]
[Pages 20336-20339]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 03-9981]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2003-NM-42-AD; Amendment 39-13127; AD 2003-08-14]
RIN 2120-AA64


Airworthiness Directives; McDonnell Douglas Model DC-10-10, DC-
10-10F, DC-10-15, DC-10-30, DC-10-30F, DC-10-30F (KC10A and KDC-10), 
DC-10-40, DC-10-40F, MD-10-10F, MD-10-30F, MD-11, and MD-11F Airplanes

AGENCY: Federal Aviation Administration, DOT.

ACTION: Final rule; request for comments.

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SUMMARY: This amendment adopts a new airworthiness directive (AD) that 
is applicable to certain McDonnell Douglas airplane models. This action 
requires revising the airplane flight manual (AFM) to include new 
operating limitations, installing placards to advise the flightcrew of 
certain minimum fuel levels to be maintained in the fuel tanks, and 
deactivating certain auxiliary fuel tanks. For fuel tanks that are not 
deactivated, this AD also requires replacement of certain existing fuel 
boost/transfer pumps with pumps inspected--and modified, if necessary--
per certain procedures. Accomplishment of this replacement will allow 
operators to remove the operating limitations from the AFM, remove the 
placards, and reactivate the auxiliary fuel tanks (if deactivated). 
This action is necessary to prevent electrical arcing in the connector 
for a fuel boost/transfer pump, which could result in a fire or 
explosion of a fuel tank. This action is intended to address the 
identified unsafe condition.

DATES: Effective May 12, 2003.
    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of May 12, 2003.
    Comments for inclusion in the Rules Docket must be received on or 
before June 24, 2003.

ADDRESSES: Submit comments in triplicate to the Federal Aviation 
Administration (FAA), Transport Airplane Directorate, ANM-114, 
Attention: Rules Docket No. 2003-NM-42-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. 2003-NM-42-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 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-

[[Page 20337]]

0024). This information may be examined at the FAA, Transport Airplane 
Directorate, 1601 Lind Avenue, SW., Renton, Washington; 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: Philip Kush, Aerospace Engineer, 
Propulsion Branch, ANM-140L, FAA, Los Angeles Aircraft Certification 
Office, 3960 Paramount Boulevard, Lakewood, California 90712-4137; 
telephone (562) 627-5263; fax (562) 627-5210.

SUPPLEMENTARY INFORMATION: The FAA has received reports indicating that 
chafed stator lead wires have been found on certain fuel boost/transfer 
pumps installed on all McDonnell Douglas Model DC-10-10, DC-10-10F, DC-
10-15, DC-10-30, DC-10-30F, DC-10-30F (KC10A and KDC-10), DC-10-40, DC-
10-40F, MD-10-10F, MD-10-30F, MD-11, and MD-11F airplanes. 
Investigation has revealed that this chafing is due to improper routing 
of the lead wires connecting the pumping unit stator to the pump 
connector during assembly of the pump. This improper routing could 
cause chafing of the lead wires, which could lead to a short circuit 
and electrical arcing, and result in a fire or explosion of the fuel 
tank.

Other Relevant Rulemaking

    The FAA previously issued AD 2000-22-21, amendment 39-11969 (65 FR 
69658, November 20, 2000). That AD applies to the same airplanes as 
this AD and requires revising the airplane flight manual (AFM) to 
ensure that the flightcrew is advised of appropriate procedures for 
disabling certain fuel pump electrical circuits following failure of a 
fuel pump electrical connector. For certain airplanes, that AD also 
requires revising the AFM to prohibit resetting of tripped fuel pump 
circuit breakers. Those actions are intended to prevent continued 
arcing following a short circuit of a fuel pump electrical connector, 
which could damage the conduit that protects the power lead wire inside 
the fuel tank and result in the creation of a potential ignition source 
in the fuel tank.
    We have also previously issued AD 2002-13-10, amendment 39-12798 
(67 FR 45053, July 8, 2002), which applies to certain McDonnell Douglas 
Model DC-10-10, DC-10-10F, DC-10-15, DC-10-30, DC-10-30F, DC-10-30F 
(KC10A and KDC-10), DC-10-40, DC-10-40F, MD-10-10F, MD-10-30F, MD-11, 
and MD-11F airplanes. That AD requires repetitive tests for electrical 
continuity and resistance; repetitive inspections to detect 
discrepancies of the fuel boost/transfer pump connectors; and 
corrective actions, if necessary. (Accomplishment of these actions 
necessitates removal of the fuel boost/transfer pumps from the 
airplane.) Those actions are intended to prevent arcing of connectors 
in the fuel boost/transfer pump circuit, which could result in a fire 
or explosion of the fuel tank. (We have also issued a separate notice 
of proposed rulemaking, Rules Docket No. 2002-NM-134-AD, that would 
require these same actions on one additional McDonnell Douglas Model 
DC-10-30 airplane that was omitted from the service information 
referred to in AD 2002-13-10.)

Explanation of Relevant Service Information

    The FAA has reviewed and approved Boeing Alert Service Bulletins 
DC10-28A240 and MD11-28A121, both dated January 6, 2003. These service 
bulletins describe operating limitations relating to maintaining 
minimum fuel levels in the airplane's fuel tanks. These service 
bulletins also describe procedures for performing maintenance actions 
on the fuel boost/transfer pumps, installing placards to ensure that 
the flightcrew is informed of minimum fuel levels that must be 
maintained in the fuel tanks, and deactivating certain auxiliary fuel 
tanks.
    These service bulletins also refer to a ``terminating action'' to 
be accomplished per Boeing Alert Service Bulletins DC10-28A239 or MD11-
28A120, both dated December 3, 2002; as applicable. The terminating 
action described in these service bulletins involves removing the 
installed fuel boost/transfer pumps; performing a detailed inspection 
of the pumps to determine whether certain lead wires are routed 
improperly; modifying the fuel boost/transfer pumps if the wires are 
routed improperly; and installing inspected and, if necessary, modified 
pumps on the airplane. Accomplishing these actions eliminates the need 
for the operating limitations, placards, and deactivation of the fuel 
tanks described previously. Boeing Alert Service Bulletins DC10-28A239 
and MD11-28A120 refer to Crane Hydro-Aire Service Bulletin 60-847-28-2, 
dated December 2, 2002, as the appropriate source of service 
information for accomplishing the inspection--and modification, if 
necessary--of the fuel boost/transfer pumps.

Explanation of the Requirements of the Rule

    Since an unsafe condition has been identified that is likely to 
exist or develop on other airplanes of the same type design, this AD is 
being issued to prevent electrical arcing in the connector for the fuel 
boost/transfer pump, which could result in a fire or explosion of the 
fuel tank. This AD requires accomplishment of the actions specified in 
the applicable service bulletins described previously, except as 
discussed below.

Differences Between Service Bulletins and This AD

    While Boeing Alert Service Bulletins DC10-28A240 and MD11-28A121 
contain procedures (under the heading ``Fuel Tank Maintenance'') for 
defueling the airplane prior to deactivating the fuel boost/transfer 
pumps, this AD does not require these procedures to be followed. We 
have determined that operators' standard procedures for such defueling 
will provide an acceptable level of safety.

Determination of Rule's Effective Date

    Since a situation exists that requires the immediate adoption of 
this regulation, it is found that notice and opportunity for prior 
public comment hereon are impracticable, and that good cause exists for 
making this amendment effective in less than 30 days.

Comments Invited

    Although this action is in the form of a final rule that involves 
requirements affecting flight safety and, thus, was not preceded by 
notice and an opportunity for public comment, comments are invited on 
this rule. Interested persons are invited to comment on this 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 under the caption ADDRESSES. All 
communications received on or before the closing date for comments will 
be considered, and this rule may be amended in light of the comments 
received. Factual information that supports the commenter's ideas and 
suggestions is extremely helpful in evaluating the effectiveness of the 
AD action and determining whether additional rulemaking action would be 
needed.
    Submit comments using the following format:
    [sbull] Organize comments issue-by-issue. For example, discuss a 
request to change the compliance time and a

[[Page 20338]]

request to change the service bulletin reference as two separate 
issues.
    [sbull] For each issue, state what specific change to the 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 rule that might 
suggest a need to modify the 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 that 
summarizes each FAA-public contact concerned with the substance of this 
AD will be filed in the Rules Docket.
    Commenters wishing the FAA to acknowledge receipt of their comments 
submitted in response to this rule must submit a self-addressed, 
stamped postcard on which the following statement is made: ``Comments 
to Docket Number 2003-NM-42-AD.'' The postcard will be date stamped and 
returned to the commenter.

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.
    The FAA has determined that this regulation is an emergency 
regulation that must be issued immediately to correct an unsafe 
condition in aircraft, and that it is not a ``significant regulatory 
action'' under Executive Order 12866. It has been determined further 
that this action involves an emergency regulation under DOT Regulatory 
Policies and Procedures (44 FR 11034, February 26, 1979). If it is 
determined that this emergency regulation otherwise would be 
significant under DOT Regulatory Policies and Procedures, a final 
regulatory evaluation will be prepared and placed in the Rules Docket. 
A copy of it, if filed, 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:

2003-08-14 McDonnell Douglas: Amendment 39-13127. Docket 2003-NM-42-
AD.

    Applicability: All Model DC-10-10, DC-10-10F, DC-10-15, DC-10-
30, DC-10-30F, DC-10-30F (KC10A and KDC-10), DC-10-40, DC-10-40F, 
MD-10-10F, and MD-10-30F, MD-11 and MD-11F airplanes; 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 (e) 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 electrical arcing in the connector for a fuel boost/
transfer pump, which could result in a fire or explosion of a fuel 
tank, accomplish the following:

Compliance Time for Initial Action

    (a) Do the actions specified in paragraph (a)(1) or (a)(2) of 
this AD.

Alternative 1: Airplane Flight Manual Revision, Placard 
Installation, and Fuel Tank Deactivation.

    (1) Within 45 days after the effective date of this AD, do the 
actions specified in paragraphs (a)(1)(i), (a)(1)(ii), and 
(a)(1)(iii) of this AD, per the Accomplishment Instructions of 
Boeing Alert Service Bulletin DC10-28A240, dated January 6, 2003 
(for Model DC-10-10, DC-10-10F, DC-10-15, DC-10-30, DC-10-30F, DC-
10-30F (KC10A and KDC-10), DC-10-40, DC-10-40F, MD-10-10F, and MD-
10-30F airplanes); or Boeing Alert Service Bulletin MD11-28A121, 
dated January 6, 2003 (for Model MD-11 and MD-11F airplanes); as 
applicable.
    (i) Revise the Operating Limitations section of the airplane 
flight manual (AFM) to include the applicable recommended operating 
limitations specified in section 3.B.1.a., 3.B.1.b., 3.B.1.c., 
3.B.1.d. or 3.B.1.e. of Boeing Alert Service Bulletin DC10-28A240; 
or section 3.B.1.a. of Boeing Alert Service Bulletin MD11-28A121; as 
applicable.
    (ii) Install placards to advise the flightcrew of certain 
minimum fuel levels that must be maintained in certain fuel tanks, 
as specified in section 3.B.1.f. of Boeing Alert Service Bulletin 
DC10-28A240 or section 3.B.1.b. of Boeing Alert Service Bulletin 
MD11-28A121, as applicable.
    (iii) Deactivate the upper auxiliary fuel tank, lower auxiliary 
fuel tank, aft auxiliary fuel tank, tail (horizontal stabilizer) 
fuel tank, and ER forward auxiliary tank, as applicable, as 
specified in section 3.B.2. of Boeing Alert Service Bulletin DC10-
28A240 or MD11-28A121, as applicable.

Alternative 2: Replacement of Pumps.

    (2) Within 45 days after the effective date of this AD, do 
paragraph (c) of this AD.
    Fuel Tank Deactivation: Resetting Circuit Breakers.
    (b) Circuit breakers that are opened to deactivate a fuel tank 
per this AD may be reset without accomplishing the continuity and 
resistance test of the fuel pump connector required by AD 2002-13-
10, amendment 39-12798, provided that there has been no reported 
problem with the fuel boost/transfer pump associated with the fuel 
tank.

Replacement of Pumps

    (c) For any fuel tank that is not deactivated per section 3.B.2. 
of Boeing Alert Service Bulletin DC10-28A240 or Boeing Alert Service 
Bulletin MD11-28A121, both dated January 6, 2003, as applicable, as 
specified in paragraph (a)(1)(iii) of this AD: Within 90 days after 
the effective date of this AD, except as provided by paragraph 
(a)(2) of this AD, replace any fuel boost/transfer pump having 
Hydro-Aire part number 60-847-1A, 60-847-2, or 60-847-3, with a 
serviceable fuel boost/transfer pump that has been inspected and 
modified per Crane Hydro-Aire Service Bulletin 60-847-28-2, dated 
December 2, 2002. Do this replacement per Boeing Alert Service 
Bulletins DC10-28A239, dated December 3, 2002 (for Model DC-10-10, 
DC-10-10F, DC-10-15, DC-10-30, DC-10-30F, DC-10-30F (KC10A and KDC-
10), DC-10-40, DC-10-40F, MD-10-10F, and MD-10-30F airplanes); or 
MD11-28A120, dated December 3, 2002 (for Model MD-11 and MD-11F 
airplanes); as applicable. Once the replacement has been 
accomplished, or once it has been determined that the fuel boost/
transfer pump does not have an affected Hydro-Aire part number, as 
identified above, the AFM revisions and placards specified in 
paragraph (a)(1)(i) and (a)(1)(ii) of this AD may be removed, and 
the fuel tanks that were deactivated as specified in paragraph 
(a)(1)(iii) of this AD may be reactivated.

Parts Installation and Fuel Tank Reactivation

    (d)(1) As of the effective date of this AD, no person may 
install a fuel boost/transfer pump having Hydro-Aire part number 60-
847-1A, 60-847-2, or 60-847-3, unless it has been inspected and 
modified, as applicable, per Crane Hydro-Aire Service Bulletin 60-
847-28-2, dated December 2, 2002.

[[Page 20339]]

    (2) As of the effective date of this AD, no person may 
reactivate a fuel tank deactivated per section 3.B.2. of Boeing 
Alert Service Bulletin DC10-28A240 or Boeing Alert Service Bulletin 
MD11-28A121, both dated January 6, 2003, as applicable, as specified 
in paragraph (a)(1)(iii) of this AD, unless paragraph (c) of this AD 
has been accomplished on the fuel boost/transfer pump for that tank.

    Note 2: AD 2002-13-10, amendment 39-12798, requires repetitive 
tests for electrical continuity and resistance, and repetitive 
inspections to detect discrepancies of the fuel boost/transfer pump 
connectors, and any applicable corrective actions. Accomplishment of 
these actions necessitates removal of the fuel boost/transfer pumps 
from the airplane. After the effective date of this AD, whenever the 
fuel boost/transfer pumps are removed from the airplane for 
accomplishment of the tests and inspections required by AD 2002-23-
10, they must be inspected and found to have properly routed lead 
wires before reinstallation, as specified in paragraph (c) of this 
AD.

Alternative Methods of Compliance

    (e) 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 or Operations Inspector, as 
applicable, who may add comments and then send it to the Manager, 
Los Angeles ACO.

    Note 3: 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

    (f) 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

    (g) The actions shall be done in accordance with Boeing Alert 
Service Bulletin DC10-28A239, dated December 3, 2002, and Boeing 
Alert Service Bulletin DC10-28A240, dated January 6, 2003; or Boeing 
Alert Service Bulletin MD11-28A120, dated December 3, 2002, and 
Boeing Alert Service Bulletin MD11-28A121, dated January 6, 2003; as 
applicable. 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; 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

    (h) This amendment becomes effective on May 12, 2003.

    Issued in Renton, Washington, on April 17, 2003.
Ali Bahrami,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 03-9981 Filed 4-24-03; 8:45 am]
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