[Federal Register: April 10, 2003 (Volume 68, Number 69)]
[Rules and Regulations]
[Page 17544-17545]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr10ap03-2]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 2002-NM-134-AD; Amendment 39-13110; AD 2003-07-14]
RIN 2120-AA64
Airworthiness Directives; McDonnell Douglas DC-10-30 Airplane
AGENCY: Federal Aviation Administration, DOT.
ACTION: Final rule.
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SUMMARY: This amendment adopts a new airworthiness directive (AD),
applicable to a single McDonnell Douglas Model DC-10-30 airplane, that
requires 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: Effective May 15, 2003.
The incorporation by reference of Boeing Alert Service Bulletin
DC10-28A228, including Appendix, Revision 02, dated December 7, 2001,
as listed in the regulations, was approved previously by the Director
of the Federal Register as of August 12, 2002 (67 FR 45053, July 8,
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; 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 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: 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 a single McDonnell Douglas Model
DC-10-30 airplane was published in the Federal Register on January 3,
2003 (68 FR 320). That action proposed 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.
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.
Conclusion
The FAA has determined that air safety and the public interest
require the adoption of the rule as proposed.
Changes to 14 CFR Part 39/Effect on the Proposed AD
On July 10, 2002, the FAA issued a new version of 14 CFR part 39
(67 FR 47997, July 22, 2002), which governs the FAA's airworthiness
directives system. The regulation now includes material that relates to
altered products, special flight permits, and alternative methods of
compliance. However, for clarity and consistency in this final rule, we
have retained the language of the NPRM regarding that material.
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 AD applies to one McDonnell Douglas Model DC-10-30 airplane
and that airplane is of U.S. registry. It will take approximately 65
work hours to accomplish the required 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 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 the requirements of this AD
action, and that the operator would not 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
[[Page 17545]]
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
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:
2003-07-14 McDonnell Douglas: Amendment 39-13110. 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.
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.
Incorporation by Reference
(e) The actions shall be done in accordance with Boeing Alert
Service Bulletin DC10-28A228, including Appendix, Revision 02, dated
December 7, 2001. The incorporation by reference of that document
was approved previously by the Director of the Federal Register as
of August 12, 2002 (67 FR 45053, July 8, 2002). 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
(f) This amendment becomes effective on May 15, 2003.
Issued in Renton, Washington, on April 4, 2003.
Ali Bahrami,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 03-8740 Filed 4-9-03; 8:45 am]
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