Airworthiness Directives; McDonnell Douglas Model MD-11, MD-11F, DC-10-30 and DC-10-30F (KC-10A and KDC-10), DC-10-40, DC-10-40F, and MD-10-30F Airplanes, 31003-31005 [E7-10756]
Download as PDF
Federal Register / Vol. 72, No. 107 / Tuesday, June 5, 2007 / Proposed Rules
it has been modified in accordance with the
requirements of paragraph (g) of this AD.
Alternative Methods of Compliance
(AMOCs)
(i)(1) The Manager, Seattle Aircraft
Certification Office (ACO), FAA, has the
authority to approve AMOCs for this AD, if
requested in accordance with the procedures
found in 14 CFR 39.19.
(2) To request a different method of
compliance or a different compliance time
for this AD, follow the procedures in 14 CFR
39.19. Before using any approved AMOC on
any airplane to which the AMOC applies,
notify your appropriate principal inspector
(PI) in the FAA Flight Standards District
Office (FSDO), or lacking a PI, your local
FSDO.
Issued in Renton, Washington, on May 25,
2007.
Ali Bahrami,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. E7–10757 Filed 6–4–07; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2007–28351; Directorate
Identifier 2007–NM–074–AD]
RIN 2120–AA64
Airworthiness Directives; McDonnell
Douglas Model MD–11, MD–11F, DC–
10–30 and DC–10–30F (KC–10A and
KDC–10), DC–10–40, DC–10–40F, and
MD–10–30F Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
The FAA proposes to adopt a
new airworthiness directive (AD) for
certain McDonnell Douglas Model MD–
11, MD–11F, DC–10–30 and DC–10–30F
(KC–10A and KDC–10), DC–10–40, DC–
10–40F, and MD–10–30F airplanes. This
proposed AD would require measuring
the electrical resistance of the bond
between the No. 2 fuel transfer pump
adapter surface of the fuel tank and the
fuel transfer pump housing flange, and
performing corrective and other
specified actions as applicable. This
proposed AD results from a design
review of the fuel tank systems. We are
proposing this AD to prevent inadequate
bonding between the No. 2 fuel transfer
pump adapter surface of the fuel tank
and the fuel transfer pump housing
flange. Inadequate bonding could result
in a potential ignition source inside the
cprice-sewell on PROD1PC71 with PROPOSALS
SUMMARY:
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16:34 Jun 04, 2007
Jkt 211001
fuel tank if the fuel transfer pump and
structure interface are not submerged in
fuel, which, in combination with
flammable fuel vapors, could result in a
fuel tank explosion and consequent loss
of the airplane.
DATES: We must receive comments on
this proposed AD by July 20, 2007.
ADDRESSES: Use one of the following
addresses to submit comments on this
proposed AD.
• DOT Docket Web site: Go to https://
dms.dot.gov and follow the instructions
for sending your comments
electronically.
• Government-wide rulemaking Web
site: Go to https://www.regulations.gov
and follow the instructions for sending
your comments electronically.
• Mail: Docket Management Facility,
U.S. Department of Transportation, 400
Seventh Street, SW., Nassif Building,
room PL–401, Washington, DC 20590.
• Fax: (202) 493–2251.
• Hand Delivery: Room PL–401 on
the plaza level of the Nassif Building,
400 Seventh Street, SW., Washington,
DC, between 9 a.m. and 5 p.m., Monday
through Friday, except Federal holidays.
Contact Boeing Commercial
Airplanes, Long Beach Division, 3855
Lakewood Boulevard, Long Beach,
California 90846, Attention: Data and
Service Management, Dept. C1–L5A
(D800–0024), for the service information
identified in this proposed AD.
FOR FURTHER INFORMATION CONTACT: Serj
Harutunian, Aerospace Engineer,
Propulsion Branch, ANM–140L, FAA,
Los Angeles Aircraft Certification
Office, 3960 Paramount Boulevard,
Lakewood, California 90712–4137;
telephone (562) 627–5254; fax (562)
627–5210.
SUPPLEMENTARY INFORMATION:
Comments Invited
We invite you to submit any relevant
written data, views, or arguments
regarding this proposed AD. Send your
comments to an address listed in the
ADDRESSES section. Include the docket
number ‘‘FAA–2007–28351; Directorate
Identifier 2007–NM–074–AD’’ at the
beginning of your comments. We
specifically invite comments on the
overall regulatory, economic,
environmental, and energy aspects of
the proposed AD. We will consider all
comments received by the closing date
and may amend the proposed AD in
light of those comments.
We will post all comments we
receive, without change, to https://
dms.dot.gov, including any personal
information you provide. We will also
post a report summarizing each
substantive verbal contact with FAA
PO 00000
Frm 00025
Fmt 4702
Sfmt 4702
31003
personnel concerning this proposed AD.
Using the search function of that Web
site, anyone can find and read the
comments in any of our dockets,
including the name of the individual
who sent the comment (or signed the
comment on behalf of an association,
business, labor union, etc.). You may
review DOT’s complete Privacy Act
Statement in the Federal Register
published on April 11, 2000 (65 FR
19477–78), or you may visit https://
dms.dot.gov.
Examining the Docket
You may examine the AD docket on
the Internet at https://dms.dot.gov, or in
person at the Docket Management
Facility office between 9 a.m. and 5
p.m., Monday through Friday, except
Federal holidays. The Docket
Management Facility office (telephone
(800) 647–5227) is located on the plaza
level of the Nassif Building at the DOT
street address stated in the ADDRESSES
section. Comments will be available in
the AD docket shortly after the Docket
Management System receives them.
Discussion
The FAA has examined the
underlying safety issues involved in fuel
tank explosions on several large
transport airplanes, including the
adequacy of existing regulations, the
service history of airplanes subject to
those regulations, and existing
maintenance practices for fuel tank
systems. As a result of those findings,
we issued a regulation titled ‘‘Transport
Airplane Fuel Tank System Design
Review, Flammability Reduction and
Maintenance and Inspection
Requirements’’ (66 FR 23086, May 7,
2001). In addition to new airworthiness
standards for transport airplanes and
new maintenance requirements, this
rule included Special Federal Aviation
Regulation No. 88 (‘‘SFAR 88,’’
Amendment 21–78, and subsequent
Amendments 21–82 and 21–83).
Among other actions, SFAR 88
requires certain type design (i.e., type
certificate (TC) and supplemental type
certificate (STC)) holders to substantiate
that their fuel tank systems can prevent
ignition sources in the fuel tanks. This
requirement applies to type design
holders for large turbine-powered
transport airplanes and for subsequent
modifications to those airplanes. It
requires them to perform design reviews
and to develop design changes and
maintenance procedures if their designs
do not meet the new fuel tank safety
standards. As explained in the preamble
to the rule, we intended to adopt
airworthiness directives to mandate any
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Federal Register / Vol. 72, No. 107 / Tuesday, June 5, 2007 / Proposed Rules
cprice-sewell on PROD1PC71 with PROPOSALS
changes found necessary to address
unsafe conditions identified as a result
of these reviews.
In evaluating these design reviews, we
have established four criteria intended
to define the unsafe conditions
associated with fuel tank systems that
require corrective actions. The
percentage of operating time during
which fuel tanks are exposed to
flammable conditions is one of these
criteria. The other three criteria address
the failure types under evaluation:
Single failures, single failures in
combination with a latent condition(s),
and in-service failure experience. For all
four criteria, the evaluations included
consideration of previous actions taken
that may mitigate the need for further
action.
We have determined that the actions
identified in this AD are necessary to
reduce the potential of ignition sources
inside fuel tanks, which, in combination
with flammable fuel vapors, could result
in fuel tank explosions and consequent
loss of the airplane.
Model DC–10 airplanes have a fuel
boost pump and a fuel transfer pump
mounted to the fuel tank No. 2 lower
skin. The instructions for early DC–10s
called out electrical bonding to structure
on both fuel transfer pump housings;
however, a later drawing change did not
call out bonding for the fuel transfer
pump housing. The same condition
exists on Model MD–11 airplanes. It is
unknown whether there is an adequate
bond on these airplanes, and operators
need to make that determination.
Inadequate bonding could result in a
potential ignition source inside the fuel
tank if the fuel transfer pump and
structure interface are not submerged in
fuel, which, in combination with
flammable fuel vapors, could result in a
fuel tank explosion and consequent loss
of the airplane.
Relevant Service Information
We have reviewed Boeing Service
Bulletins DC10–28–250 and MD11–28–
129, both dated July 26, 2006. The
service bulletins describe procedures for
measuring the electrical resistance
between the No. 2 fuel transfer pump
adapter surface of the fuel tank and the
fuel transfer pump housing flange, and
performing corrective and other
specified actions as applicable. The
corrective actions include electrically
bonding the fuel tank No. 2 fuel transfer
pump access door surfaces and fuel
pump housing if the resistance
measurement is more than 2.5
milliohms. The other specified actions
include an electrical resistance bonding
test to verify the electrical resistance
between the fuel transfer pump housing
VerDate Aug<31>2005
15:43 Jun 04, 2007
Jkt 211001
and the structure is 2.5 milliohms
maximum. For airplanes on which the
electrical resistance is not achieved, the
procedures include reworking the
electrical bond until that electrical
resistance is achieved. Accomplishing
the actions specified in the service
information is intended to adequately
address the unsafe condition.
FAA’s Determination and Requirements
of the Proposed AD
We have evaluated all pertinent
information and identified an unsafe
condition that is likely to exist or
develop on other airplanes of this same
type design. For this reason, we are
proposing this AD, which would require
accomplishing the actions specified in
the service information described
previously.
Costs of Compliance
There are about 573 airplanes of the
affected design in the worldwide fleet.
This proposed AD would affect about
399 airplanes of U.S. registry. The
proposed measurement would take
about 1 work hour per airplane, at an
average labor rate of $80 per work hour.
Based on these figures, the estimated
cost of the proposed AD for U.S.
operators is $31,920, or $80 per
airplane.
Authority for This Rulemaking
Title 49 of the United States Code
specifies the FAA’s authority to issue
rules on aviation safety. Subtitle I,
Section 106, describes the authority of
the FAA Administrator. Subtitle VII,
Aviation Programs, describes in more
detail the scope of the Agency’s
authority.
We are issuing this rulemaking under
the authority described in Subtitle VII,
Part A, Subpart III, Section 44701,
‘‘General requirements.’’ Under that
section, Congress charges the FAA with
promoting safe flight of civil aircraft in
air commerce by prescribing regulations
for practices, methods, and procedures
the Administrator finds necessary for
safety in air commerce. This regulation
is within the scope of that authority
because it addresses an unsafe condition
that is likely to exist or develop on
products identified in this rulemaking
action.
Regulatory Findings
We have determined that this
proposed AD would not have federalism
implications under Executive Order
13132. This proposed AD 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
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Frm 00026
Fmt 4702
Sfmt 4702
responsibilities among the various
levels of government.
For the reasons discussed above, I
certify that the 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. 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.
We prepared a regulatory evaluation
of the estimated costs to comply with
this proposed AD and placed it in the
AD docket. See the ADDRESSES section
for a location to examine the regulatory
evaluation.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation
safety, Safety.
The Proposed Amendment
Accordingly, under the authority
delegated to me by the Administrator,
the FAA proposes to amend 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.
§ 39.13
[Amended]
2. The Federal Aviation
Administration (FAA) amends § 39.13
by adding the following new
airworthiness directive (AD):
McDonnell Douglas: Docket No. FAA–2007–
28351; Directorate Identifier 2007–NM–
074–AD.
Comments Due Date
(a) The FAA must receive comments on
this AD action by July 20, 2007.
Affected ADs
(b) None.
Applicability
(c) This AD applies to McDonnell Douglas
Model MD–11, MD–11F, DC–10–30 and DC–
10–30F (KC–10A and KDC–10), DC–10–40,
DC–10–40F, and MD–10–30F airplanes,
certificated in any category; as identified in
Boeing Service Bulletins DC10–28–250 and
MD11–28–129, both dated July 26, 2006.
Unsafe Condition
(d) This AD results from a design review
of the fuel tank systems. We are issuing this
AD to prevent inadequate bonding between
the No. 2 fuel transfer pump adapter surface
of the fuel tank and the fuel transfer pump
housing flange. Inadequate bonding could
result in a potential ignition source inside the
fuel tank if the fuel transfer pump and
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05JNP1
Federal Register / Vol. 72, No. 107 / Tuesday, June 5, 2007 / Proposed Rules
structure interface are not submerged in fuel,
which, in combination with flammable fuel
vapors, could result in a fuel tank explosion
and consequent loss of the airplane.
DEPARTMENT OF COMMERCE
Compliance
15 CFR Parts 744 and 772
(e) You are responsible for having the
actions required by this AD performed within
the compliance times specified, unless the
actions have already been done.
Measure Electrical Resistance/Corrective &
Other Specified Actions
(f) Within 60 months after the effective
date of this AD: Measure the electrical
resistance of the bond between the No. 2 fuel
transfer pump adapter surface of the fuel tank
and the fuel transfer pump housing flange in
accordance with the Accomplishment
Instructions of Boeing Service Bulletin
DC10–28–250 or MD11–28–129, both dated
July 26, 2006, as applicable.
(1) If the resistance measurement is 2.5
milliohms or less: No further action is
required by this paragraph.
(2) If the resistance measurement is more
than 2.5 milliohms: Before further flight,
electrically bond the fuel tank No. 2 fuel
transfer pump housing surfaces in
accordance with the service bulletin.
(3) Before further flight thereafter, do an
electrical resistance bonding test to verify the
electrical resistance between the fuel transfer
pump housing and the structure is 2.5
milliohms maximum. If that electrical
resistance is not achieved, rework the
electrical bond until the electrical resistance
is achieved. Do the actions in accordance
with the service bulletin.
Alternative Methods of Compliance
(AMOCs)
cprice-sewell on PROD1PC71 with PROPOSALS
(g)(1) The Manager, Los Angeles Aircraft
Certification Office (LAACO), FAA, has the
authority to approve AMOCs for this AD, if
requested in accordance with the procedures
found in 14 CFR 39.19.
(2) To request a different method of
compliance or a different compliance time
for this AD, follow the procedures in 14 CFR
39.19. Before using any approved AMOC on
any airplane to which the AMOC applies,
notify your appropriate principal inspector
(PI) in the FAA Flight Standards District
Office (FSDO), or lacking a PI, your local
FSDO.
Issued in Renton, Washington, on May 25,
2007.
Ali Bahrami,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. E7–10756 Filed 6–4–07; 8:45 am]
BILLING CODE 4910–13–P
Bureau of Industry and Security
[Docket No. 0612243150–63150–01]
RIN 0694–AD82
Authorization To Impose License
Requirements for Exports or
Reexports to Entities Acting Contrary
to the National Security or Foreign
Policy Interests of the United States
Bureau of Industry and
Security, Commerce.
ACTION: Proposed rule.
AGENCY:
SUMMARY: The Entity List (Supplement
No. 4 to part 744 of the Export
Administration Regulations) provides
notice to the public that certain exports
and reexports to parties identified on
the Entity List require a license from the
Bureau of Industry and Security (BIS)
and that availability of License
Exceptions in such transactions is
limited. This proposed rule would
expand the scope of reasons for which
BIS may add parties to the Entity List.
This proposed rule would also amend
the Export Administration Regulations
(EAR) to state explicitly that a party
listed on the Entity List has a right to
request that its listing be removed or
modified and would set procedures for
addressing such requests.
DATES: Comments concerning this rule
must be received by BIS no later than
August 6, 2007.
ADDRESSES: Comments on this rule may
be submitted to the Federal
eRulemaking Portal at https://
www.regulations.gov (follow the
instructions for submitting comments)
by e-mail directly to BIS at
publiccomments@bis.doc.gov (refer to
regulatory identification number 0694–
AD82 in the subject line), by fax at (202)
482–3355, or on paper to Regulatory
Policy Division, Office of Exporter
Services, Bureau of Industry and
Security, Room H2705, U.S. Department
of Commerce, 14th Street and
Pennsylvania Avenue, NW.,
Washington, DC 20230. Refer to
Regulatory Identification Number (RIN)
0694–AD82 in all comments.
FOR FURTHER INFORMATION CONTACT:
Mike Rithmire, Office of the Assistant
Secretary for Export Administration,
Bureau of Industry and Security, e-mail
mrithmir@bis.doc.gov, tel. ( 202) 482–
6105.
SUPPLEMENTARY INFORMATION:
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15:43 Jun 04, 2007
Jkt 211001
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Fmt 4702
Sfmt 4702
31005
Background
The Entity List (Supplement No. 4 to
part 744 of the EAR) provides notice to
the public of the identity of certain
parties whose presence as a recipient of
items subject to the Export
Administration Regulations (EAR) can
impose a license requirement in an
export or reexport transaction. The
reasons for which BIS may place an
entity on the Entity List are stated in
§§ 744.2, 744.3, 744.4, 744.6, 744.10 and
744.20 of the EAR.
In addition to those reasons, this
proposed rule would create a new
§ 744.11 to authorize BIS to add to the
Entity List entities that BIS has
reasonable cause to believe, based on
specific and articulable facts, have been,
are or pose a risk of being involved in
activities that are contrary to the
national security or foreign policy
interests of the United States or those
acting on behalf of such entities. This
new section would not be used to add
to the Entity List entities that are U.S.
persons (as defined in § 772.1 of the
EAR). This new section also would not
be used to add to the Entity List entities
for which the EAR already impose a
license requirement because those
entities are already listed on the List of
Specially Designated Nationals and
Blocked Persons published by the
Treasury Department, Office of Foreign
Assets Control.
Reason for the Changes Proposed by
This Rule
BIS is proposing to take this action to
focus its export control efforts more
closely on problematic potential
recipients of items that are subject to the
EAR, but who do not meet the criteria
currently set forth in §§ 744.2, 744.3,
744.4, 744.6, 744.10 or 744.20. With this
rule, the United States government
would be able to conduct prior review
and make appropriate licensing
decisions regarding proposed exports
and reexports to such recipients to the
degree necessary to protect its interests.
BIS would be able to tailor license
requirements and availability of license
exceptions for exports and reexports to
parties who have taken, are taking, or
will take actions that are contrary to
United States national security or
foreign policy interests without
imposing additional license
requirements that apply broadly to
entire destinations or items. BIS
believes that such targeted application
of license requirements would provide
the flexibility to deter use of items that
are subject to the EAR in ways that are
inimical to the interests of the United
States with minimal costs to and
E:\FR\FM\05JNP1.SGM
05JNP1
Agencies
[Federal Register Volume 72, Number 107 (Tuesday, June 5, 2007)]
[Proposed Rules]
[Pages 31003-31005]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E7-10756]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2007-28351; Directorate Identifier 2007-NM-074-AD]
RIN 2120-AA64
Airworthiness Directives; McDonnell Douglas Model MD-11, MD-11F,
DC-10-30 and DC-10-30F (KC-10A and KDC-10), DC-10-40, DC-10-40F, and
MD-10-30F Airplanes
AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).
ACTION: Notice of proposed rulemaking (NPRM).
-----------------------------------------------------------------------
SUMMARY: The FAA proposes to adopt a new airworthiness directive (AD)
for certain McDonnell Douglas Model MD-11, MD-11F, DC-10-30 and DC-10-
30F (KC-10A and KDC-10), DC-10-40, DC-10-40F, and MD-10-30F airplanes.
This proposed AD would require measuring the electrical resistance of
the bond between the No. 2 fuel transfer pump adapter surface of the
fuel tank and the fuel transfer pump housing flange, and performing
corrective and other specified actions as applicable. This proposed AD
results from a design review of the fuel tank systems. We are proposing
this AD to prevent inadequate bonding between the No. 2 fuel transfer
pump adapter surface of the fuel tank and the fuel transfer pump
housing flange. Inadequate bonding could result in a potential ignition
source inside the fuel tank if the fuel transfer pump and structure
interface are not submerged in fuel, which, in combination with
flammable fuel vapors, could result in a fuel tank explosion and
consequent loss of the airplane.
DATES: We must receive comments on this proposed AD by July 20, 2007.
ADDRESSES: Use one of the following addresses to submit comments on
this proposed AD.
DOT Docket Web site: Go to https://dms.dot.gov and follow
the instructions for sending your comments electronically.
Government-wide rulemaking Web site: Go to https://
www.regulations.gov and follow the instructions for sending your
comments electronically.
Mail: Docket Management Facility, U.S. Department of
Transportation, 400 Seventh Street, SW., Nassif Building, room PL-401,
Washington, DC 20590.
Fax: (202) 493-2251.
Hand Delivery: Room PL-401 on the plaza level of the
Nassif Building, 400 Seventh Street, SW., Washington, DC, between 9
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
Contact Boeing Commercial Airplanes, Long Beach Division, 3855
Lakewood Boulevard, Long Beach, California 90846, Attention: Data and
Service Management, Dept. C1-L5A (D800-0024), for the service
information identified in this proposed AD.
FOR FURTHER INFORMATION CONTACT: Serj Harutunian, Aerospace Engineer,
Propulsion Branch, ANM-140L, FAA, Los Angeles Aircraft Certification
Office, 3960 Paramount Boulevard, Lakewood, California 90712-4137;
telephone (562) 627-5254; fax (562) 627-5210.
SUPPLEMENTARY INFORMATION:
Comments Invited
We invite you to submit any relevant written data, views, or
arguments regarding this proposed AD. Send your comments to an address
listed in the ADDRESSES section. Include the docket number ``FAA-2007-
28351; Directorate Identifier 2007-NM-074-AD'' at the beginning of your
comments. We specifically invite comments on the overall regulatory,
economic, environmental, and energy aspects of the proposed AD. We will
consider all comments received by the closing date and may amend the
proposed AD in light of those comments.
We will post all comments we receive, without change, to https://
dms.dot.gov, including any personal information you provide. We will
also post a report summarizing each substantive verbal contact with FAA
personnel concerning this proposed AD. Using the search function of
that Web site, anyone can find and read the comments in any of our
dockets, including the name of the individual who sent the comment (or
signed the comment on behalf of an association, business, labor union,
etc.). You may review DOT's complete Privacy Act Statement in the
Federal Register published on April 11, 2000 (65 FR 19477-78), or you
may visit https://dms.dot.gov.
Examining the Docket
You may examine the AD docket on the Internet at https://
dms.dot.gov, or in person at the Docket Management Facility office
between 9 a.m. and 5 p.m., Monday through Friday, except Federal
holidays. The Docket Management Facility office (telephone (800) 647-
5227) is located on the plaza level of the Nassif Building at the DOT
street address stated in the ADDRESSES section. Comments will be
available in the AD docket shortly after the Docket Management System
receives them.
Discussion
The FAA has examined the underlying safety issues involved in fuel
tank explosions on several large transport airplanes, including the
adequacy of existing regulations, the service history of airplanes
subject to those regulations, and existing maintenance practices for
fuel tank systems. As a result of those findings, we issued a
regulation titled ``Transport Airplane Fuel Tank System Design Review,
Flammability Reduction and Maintenance and Inspection Requirements''
(66 FR 23086, May 7, 2001). In addition to new airworthiness standards
for transport airplanes and new maintenance requirements, this rule
included Special Federal Aviation Regulation No. 88 (``SFAR 88,''
Amendment 21-78, and subsequent Amendments 21-82 and 21-83).
Among other actions, SFAR 88 requires certain type design (i.e.,
type certificate (TC) and supplemental type certificate (STC)) holders
to substantiate that their fuel tank systems can prevent ignition
sources in the fuel tanks. This requirement applies to type design
holders for large turbine-powered transport airplanes and for
subsequent modifications to those airplanes. It requires them to
perform design reviews and to develop design changes and maintenance
procedures if their designs do not meet the new fuel tank safety
standards. As explained in the preamble to the rule, we intended to
adopt airworthiness directives to mandate any
[[Page 31004]]
changes found necessary to address unsafe conditions identified as a
result of these reviews.
In evaluating these design reviews, we have established four
criteria intended to define the unsafe conditions associated with fuel
tank systems that require corrective actions. The percentage of
operating time during which fuel tanks are exposed to flammable
conditions is one of these criteria. The other three criteria address
the failure types under evaluation: Single failures, single failures in
combination with a latent condition(s), and in-service failure
experience. For all four criteria, the evaluations included
consideration of previous actions taken that may mitigate the need for
further action.
We have determined that the actions identified in this AD are
necessary to reduce the potential of ignition sources inside fuel
tanks, which, in combination with flammable fuel vapors, could result
in fuel tank explosions and consequent loss of the airplane.
Model DC-10 airplanes have a fuel boost pump and a fuel transfer
pump mounted to the fuel tank No. 2 lower skin. The instructions for
early DC-10s called out electrical bonding to structure on both fuel
transfer pump housings; however, a later drawing change did not call
out bonding for the fuel transfer pump housing. The same condition
exists on Model MD-11 airplanes. It is unknown whether there is an
adequate bond on these airplanes, and operators need to make that
determination. Inadequate bonding could result in a potential ignition
source inside the fuel tank if the fuel transfer pump and structure
interface are not submerged in fuel, which, in combination with
flammable fuel vapors, could result in a fuel tank explosion and
consequent loss of the airplane.
Relevant Service Information
We have reviewed Boeing Service Bulletins DC10-28-250 and MD11-28-
129, both dated July 26, 2006. The service bulletins describe
procedures for measuring the electrical resistance between the No. 2
fuel transfer pump adapter surface of the fuel tank and the fuel
transfer pump housing flange, and performing corrective and other
specified actions as applicable. The corrective actions include
electrically bonding the fuel tank No. 2 fuel transfer pump access door
surfaces and fuel pump housing if the resistance measurement is more
than 2.5 milliohms. The other specified actions include an electrical
resistance bonding test to verify the electrical resistance between the
fuel transfer pump housing and the structure is 2.5 milliohms maximum.
For airplanes on which the electrical resistance is not achieved, the
procedures include reworking the electrical bond until that electrical
resistance is achieved. Accomplishing the actions specified in the
service information is intended to adequately address the unsafe
condition.
FAA's Determination and Requirements of the Proposed AD
We have evaluated all pertinent information and identified an
unsafe condition that is likely to exist or develop on other airplanes
of this same type design. For this reason, we are proposing this AD,
which would require accomplishing the actions specified in the service
information described previously.
Costs of Compliance
There are about 573 airplanes of the affected design in the
worldwide fleet. This proposed AD would affect about 399 airplanes of
U.S. registry. The proposed measurement would take about 1 work hour
per airplane, at an average labor rate of $80 per work hour. Based on
these figures, the estimated cost of the proposed AD for U.S. operators
is $31,920, or $80 per airplane.
Authority for This Rulemaking
Title 49 of the United States Code specifies the FAA's authority to
issue rules on aviation safety. Subtitle I, Section 106, describes the
authority of the FAA Administrator. Subtitle VII, Aviation Programs,
describes in more detail the scope of the Agency's authority.
We are issuing this rulemaking under the authority described in
Subtitle VII, Part A, Subpart III, Section 44701, ``General
requirements.'' Under that section, Congress charges the FAA with
promoting safe flight of civil aircraft in air commerce by prescribing
regulations for practices, methods, and procedures the Administrator
finds necessary for safety in air commerce. This regulation is within
the scope of that authority because it addresses an unsafe condition
that is likely to exist or develop on products identified in this
rulemaking action.
Regulatory Findings
We have determined that this proposed AD would not have federalism
implications under Executive Order 13132. This proposed AD 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.
For the reasons discussed above, I certify that the 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. 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.
We prepared a regulatory evaluation of the estimated costs to
comply with this proposed AD and placed it in the AD docket. See the
ADDRESSES section for a location to examine the regulatory evaluation.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Safety.
The Proposed Amendment
Accordingly, under the authority delegated to me by the
Administrator, the FAA proposes to amend 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. The Federal Aviation Administration (FAA) amends Sec. 39.13 by
adding the following new airworthiness directive (AD):
McDonnell Douglas: Docket No. FAA-2007-28351; Directorate Identifier
2007-NM-074-AD.
Comments Due Date
(a) The FAA must receive comments on this AD action by July 20,
2007.
Affected ADs
(b) None.
Applicability
(c) This AD applies to McDonnell Douglas Model MD-11, MD-11F,
DC-10-30 and DC-10-30F (KC-10A and KDC-10), DC-10-40, DC-10-40F, and
MD-10-30F airplanes, certificated in any category; as identified in
Boeing Service Bulletins DC10-28-250 and MD11-28-129, both dated
July 26, 2006.
Unsafe Condition
(d) This AD results from a design review of the fuel tank
systems. We are issuing this AD to prevent inadequate bonding
between the No. 2 fuel transfer pump adapter surface of the fuel
tank and the fuel transfer pump housing flange. Inadequate bonding
could result in a potential ignition source inside the fuel tank if
the fuel transfer pump and
[[Page 31005]]
structure interface are not submerged in fuel, which, in combination
with flammable fuel vapors, could result in a fuel tank explosion
and consequent loss of the airplane.
Compliance
(e) You are responsible for having the actions required by this
AD performed within the compliance times specified, unless the
actions have already been done.
Measure Electrical Resistance/Corrective & Other Specified Actions
(f) Within 60 months after the effective date of this AD:
Measure the electrical resistance of the bond between the No. 2 fuel
transfer pump adapter surface of the fuel tank and the fuel transfer
pump housing flange in accordance with the Accomplishment
Instructions of Boeing Service Bulletin DC10-28-250 or MD11-28-129,
both dated July 26, 2006, as applicable.
(1) If the resistance measurement is 2.5 milliohms or less: No
further action is required by this paragraph.
(2) If the resistance measurement is more than 2.5 milliohms:
Before further flight, electrically bond the fuel tank No. 2 fuel
transfer pump housing surfaces in accordance with the service
bulletin.
(3) Before further flight thereafter, do an electrical
resistance bonding test to verify the electrical resistance between
the fuel transfer pump housing and the structure is 2.5 milliohms
maximum. If that electrical resistance is not achieved, rework the
electrical bond until the electrical resistance is achieved. Do the
actions in accordance with the service bulletin.
Alternative Methods of Compliance (AMOCs)
(g)(1) The Manager, Los Angeles Aircraft Certification Office
(LAACO), FAA, has the authority to approve AMOCs for this AD, if
requested in accordance with the procedures found in 14 CFR 39.19.
(2) To request a different method of compliance or a different
compliance time for this AD, follow the procedures in 14 CFR 39.19.
Before using any approved AMOC on any airplane to which the AMOC
applies, notify your appropriate principal inspector (PI) in the FAA
Flight Standards District Office (FSDO), or lacking a PI, your local
FSDO.
Issued in Renton, Washington, on May 25, 2007.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. E7-10756 Filed 6-4-07; 8:45 am]
BILLING CODE 4910-13-P