[Federal Register: April 25, 2003 (Volume 68, Number 80)]
[Rules and Regulations]
[Page 20336-20339]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr25ap03-3]
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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:
9-anm-iarcomment@faa.gov. 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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