Airworthiness Directives; Airbus Model A319-100 and A320-200 Series Airplanes; and A320-111 Airplanes, 9046-9048 [E6-2453]
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9046
Federal Register / Vol. 71, No. 35 / Wednesday, February 22, 2006 / Proposed Rules
(4) Milk received at pool plants in
excess of these limits shall be classified
pursuant to § 1000.44(a)(3)(v) and
§ 1000.44(b). Milk diverted to nonpool
plants reported in excess of this limit
shall not be producer milk. The handler
must designate, by producer pick-up,
which milk shall not be producer milk.
If the handler fails to provide this
information the provisions of
§ 1033.13(d)(6) shall apply.
(5) The market administrator may
waive these limitations:
(i) For a new handler on the order,
subject to the provisions of
§ 1033.13(e)(6), or
(ii) For an existing handler with
significantly changed milk supply
conditions due to unusual
circumstances;
(6) Milk may not be considered
producer milk if the market
administrator determines that handlers
altered the reporting of such milk for the
purpose of evading the provisions of
this paragraph.
Dated: February 15, 2006.
Lloyd C. Day,
Administrator, Agricultural Marketing
Service.
[FR Doc. 06–1586 Filed 2–21–06; 8:45 am]
BILLING CODE 3410–02–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
Comments Invited
[Docket No. FAA–2006–23948; Directorate
Identifier 2005–NM–246–AD]
RIN 2120–AA64
Airworthiness Directives; Airbus Model
A319–100 and A320–200 Series
Airplanes; and A320–111 Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Notice of proposed rulemaking
(NPRM).
cprice-sewell on PROD1PC66 with PROPOSALS
AGENCY:
SUMMARY: The FAA proposes to adopt a
new airworthiness directive (AD) for
certain Airbus Model A319–100 and
A320–200 series airplanes; and A320–
111 airplanes. This proposed AD would
require modifying the wiring to the fuel
pump control of the center fuel tank.
This proposed AD results from reports
that the low-pressure warning for the
fuel pumps of the center fuel tank has
come on in flight. We are proposing this
AD to ensure that the fuel pumps do not
run while dry, which could result in a
potential ignition source inside the
center fuel tank which, in combination
VerDate Aug<31>2005
14:42 Feb 21, 2006
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 March 24, 2006.
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 Airbus, 1 Rond Point Maurice
Bellonte, 31707 Blagnac Cedex, France,
for service information identified in this
proposed AD.
FOR FURTHER INFORMATION CONTACT: Tim
Dulin, Aerospace Engineer,
International Branch, ANM–116, FAA,
Transport Airplane Directorate, 1601
Lind Avenue, SW., Renton, Washington
98055–4056; telephone (425) 227–2141;
fax (425) 227–1149.
SUPPLEMENTARY INFORMATION:
Jkt 208001
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–2006–23948; Directorate
Identifier 2005–NM–246–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,
PO 00000
Frm 00053
Fmt 4702
Sfmt 4702
business, labor union, etc.). You may
review the 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’’ (67 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
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
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Federal Register / Vol. 71, No. 35 / Wednesday, February 22, 2006 / Proposed Rules
‘‘latch’’ when the refuel door is opened
or when switching from ‘‘Auto’’ to
‘‘Manual’’ mode for center pump
operation. Accomplishing the actions
specified in the service information is
intended to adequately address the
unsafe condition. The DGAC mandated
the service information and issued
French airworthiness directive F–2005–
173, dated October 26, 2005, to ensure
the continued airworthiness of these
airplanes in France.
cprice-sewell on PROD1PC66 with PROPOSALS
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 another 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.
The Joint Aviation Authorities (JAA)
has issued a regulation that is similar to
SFAR 88. (The JAA is an associated
body of the European Civil Aviation
Conference (ECAC) representing the
civil aviation regulatory authorities of a
number of European States who have
agreed to co-operate in developing and
implementing common safety regulatory
standards and procedures.) Under this
regulation, the JAA stated that all
members of the ECAC that hold type
certificates for transport category
airplanes are required to conduct a
design review against explosion risks.
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.
´ ´
The Direction Generale de l’Aviation
Civile (DGAC), which is the
airworthiness authority for France,
notified us that an unsafe condition may
exist on certain Airbus Model A319–100
and A320–200 series airplanes; and
A320–111 airplanes. The DGAC advises
that operators have reported that the
low-pressure warning for the fuel
pumps of the center fuel tank has come
on in flight. The probable cause is rewetting of the low-level sensors for the
center tank pumps when the airplane is
maneuvered, and when the altitude
changes. The warning also may come on
when the airplane experiences
turbulence. This condition, if not
corrected, could cause the fuel pumps to
run while dry, which could result in a
potential ignition source inside the
center fuel tank which, in combination
with flammable fuel vapors, could result
in a fuel tank explosion and consequent
loss of the airplane.
Difference Between French
Airworthiness Directive and This
Proposed AD
The applicability of French
airworthiness directive F–2005–173
excludes airplanes on which Airbus
Service Bulletin A320–28–1059 was
accomplished in service. However, we
have not excluded those airplanes from
the applicability of this proposed AD;
rather, this proposed AD includes a
requirement to accomplish the actions
specified in that service bulletin. This
requirement would ensure that the
actions specified in the service bulletin
and required by this proposed AD are
accomplished on all affected airplanes.
Operators must continue to operate the
airplane in the configuration required
by this proposed AD unless an
alternative method of compliance is
approved.
Relevant Service Information
Airbus has issued Service Bulletin
A320–28–1059, Revision 06, dated June
29, 2000. The service bulletin describes
procedures for modifying the wiring to
the fuel pump control of the center fuel
tank to ‘‘latch’’ the pumps off when the
low-level sensor has been dry for 5
minutes. The modification also includes
installing two-pole relays to release the
Costs of Compliance
This proposed AD would affect about
119 airplanes of U.S. registry. The
proposed actions would take about 17
work hours per airplane, at an average
labor rate of $65 per work hour. There
is no cost for parts. Based on these
figures, the estimated cost of the
proposed AD for U.S. operators is
$131,495, or $1,105 per airplane.
VerDate Aug<31>2005
14:42 Feb 21, 2006
Jkt 208001
FAA’s Determination and Requirements
of the Proposed AD
These airplane models are
manufactured in France and are type
certificated for operation in the United
States under the provisions of section
21.29 of the Federal Aviation
Regulations (14 CFR 21.29) and the
applicable bilateral airworthiness
agreement. Pursuant to this bilateral
airworthiness agreement, the DGAC has
kept the FAA informed of the situation
described above. We have examined the
DGAC’s findings, evaluated all pertinent
information, and determined that we
need to issue an AD for products of this
type design that are certificated for
operation in the United States.
Therefore, we are proposing this AD,
which would require accomplishing the
actions specified in the service
information described previously.
PO 00000
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9047
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:
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9048
Federal Register / Vol. 71, No. 35 / Wednesday, February 22, 2006 / Proposed Rules
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):
Airbus: Docket No. FAA–2006–23948;
Directorate Identifier 2005–NM–246–AD.
Comments Due Date
(a) The FAA must receive comments on
this AD action by March 24, 2006.
Related Information
(i) French airworthiness directive F–2005–
173, dated October 26, 2005, also addresses
the subject of this AD.
Affected ADs
(b) None.
Applicability
(c) This AD applies to Airbus Model A319–
111, –112, –113, –114, –115, –131, –132, and
–133 airplanes; and Model A320–111, –211,
–212, –214, –231, –232, and –233 airplanes;
certificated in any category; that have
received Airbus Modification 20024 in
production (installation of a center tank),
except airplanes on which Airbus
Modification 24373 has been accomplished.
Unsafe Condition
(d) This AD results from reports that the
low-pressure warning for the fuel pumps of
the center fuel tank has come on in flight. We
are issuing this AD to ensure that the fuel
pumps do not run while dry, which could
result in a potential ignition source inside the
center fuel tank 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.
Modification
(f) Within 20 months after the effective
date of this AD, modify the wiring to the fuel
pump control of the center fuel tank by doing
all actions specified in the Accomplishment
Instructions of Airbus Service Bulletin A320–
28–1059, Revision 06, dated June 29, 2000.
Credit for Previous Revisions of Service
Bulletin
(g) Modifications done before the effective
date of this AD in accordance with the
service bulletins identified in Table 1 of this
AD are acceptable for compliance with the
requirements of paragraph (f) of this AD.
cprice-sewell on PROD1PC66 with PROPOSALS
TABLE 1.—PREVIOUS REVISIONS OF
SERVICE BULLETIN
Airbus service
bulletin
Revision
level
A320–28–1059
04
A320–28–1059
05
VerDate Aug<31>2005
14:42 Feb 21, 2006
Date
February 4,
1999.
March 12,
1999.
Jkt 208001
Alternative Methods of Compliance
(AMOCs)
(h)(1) The Manager, International Branch,
ANM–116, Transport Airplane Directorate,
FAA, has the authority to approve AMOCs
for this AD, if requested in accordance with
the procedures found in 14 CFR 39.19.
(2) Before using any AMOC approved in
accordance with § 39.19 on any airplane to
which the AMOC applies, notify the
appropriate principal inspector in the FAA
Flight Standards Certificate Holding District
Office.
Issued in Renton, Washington, on February
10, 2006.
Kalene C. Yanamura,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. E6–2453 Filed 2–21–06; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 2001–NE–01–AD]
RIN 2120–AA64
Airworthiness Directives; Rolls-Royce
Corporation (Formerly Allison Engine
Company) 501–D Series Turboprop
Engines
Federal Aviation
Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
SUMMARY: The FAA proposes to
supersede an existing airworthiness
directive (AD) for Rolls-Royce
Corporation (formerly Allison Engine
Company) (RRC) 501–D series turboprop
engines. That AD currently requires
removal from service of certain turbine
rotor components at reduced life limits.
This proposed AD would require the
same actions but adds two new life
limits. This proposed AD results from
RRC reevaluating and revising
component life limits for 501–D22 series
turboprop engines. We are proposing
this AD to prevent uncontained turbine
rotor failure resulting in an in-flight
engine shutdown and possible damage
to the airplane.
DATES: We must receive any comments
on this proposed AD by April 24, 2006.
ADDRESSES: Use one of the following
addresses to submit comments on this
proposed AD:
• By mail: Federal Aviation
Administration (FAA), New England
PO 00000
Frm 00055
Fmt 4702
Sfmt 4702
Region, Office of the Regional Counsel,
Attention: Rules Docket No. 2001–NE–
01–AD, 12 New England Executive Park,
Burlington, MA 01803–5299.
• By fax: (781) 238–7055.
• By e-mail: 9–ane–
adcomment@faa.gov.
You can get the service information
identified in this proposed AD from
Rolls-Royce Corporation, P.O. Box 420,
Indianapolis, IN 46206–0420; telephone
(317) 230–6400; fax (317) 230–4243.
You may examine the AD docket at
the FAA, New England Region, Office of
the Regional Counsel, 12 New England
Executive Park, Burlington, MA.
FOR FURTHER INFORMATION CONTACT:
Michael Downs, Aerospace Engineer,
Chicago Aircraft Certification Office,
FAA, 2300 East Devon Avenue, Des
Plaines, IL 60018; telephone (847) 294–
7870; fax (847) 294–7834.
SUPPLEMENTARY INFORMATION:
Comments Invited
We invite you to submit any written
relevant data, views, or arguments
regarding this proposal. Send your
comments to an address listed under
ADDRESSES. Include ‘‘AD Docket No.
2001–NE–01–AD’’ in the subject line of
your comments. If you want us to
acknowledge receipt of your mailed
comments, send us a self-addressed,
stamped postcard with the docket
number written on it; we will datestamp your postcard and mail it back to
you. We specifically invite comments
on the overall regulatory, economic,
environmental, and energy aspects of
the proposed AD. If a person contacts us
verbally, and that contact relates to a
substantive part of this proposed AD,
we will summarize the contact and
place the summary in the docket. We
will consider all comments received by
the closing date and may amend the
proposed AD in light of those
comments.
Examining the AD Docket
You may examine the AD Docket
(including any comments and service
information), by appointment, between
8 a.m. and 4:30 p.m., Monday through
Friday, except Federal holidays. See
ADDRESSES for the location.
Discussion
On March 25, 2003, we issued AD
2003–07–02, Amendment 39–13098 (68
FR 15937, April 2, 2003). That AD
requires removing from service certain
turbine rotor components at reduced life
limits. That AD resulted from RRC
updating material properties and
recalculating component life limits.
That condition, if not corrected, could
result in uncontained turbine rotor
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]]>Agencies
[Federal Register Volume 71, Number 35 (Wednesday, February 22, 2006)]
[Proposed Rules]
[Pages 9046-9048]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E6-2453]
=======================================================================
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2006-23948; Directorate Identifier 2005-NM-246-AD]
RIN 2120-AA64
Airworthiness Directives; Airbus Model A319-100 and A320-200
Series Airplanes; and A320-111 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 Airbus Model A319-100 and A320-200 series airplanes; and
A320-111 airplanes. This proposed AD would require modifying the wiring
to the fuel pump control of the center fuel tank. This proposed AD
results from reports that the low-pressure warning for the fuel pumps
of the center fuel tank has come on in flight. We are proposing this AD
to ensure that the fuel pumps do not run while dry, which could result
in a potential ignition source inside the center fuel tank 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 March 24, 2006.
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 Airbus, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex,
France, for service information identified in this proposed AD.
FOR FURTHER INFORMATION CONTACT: Tim Dulin, Aerospace Engineer,
International Branch, ANM-116, FAA, Transport Airplane Directorate,
1601 Lind Avenue, SW., Renton, Washington 98055-4056; telephone (425)
227-2141; fax (425) 227-1149.
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-2006-
23948; Directorate Identifier 2005-NM-246-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 the 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''
(67 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 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
[[Page 9047]]
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 another 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.
The Joint Aviation Authorities (JAA) has issued a regulation that
is similar to SFAR 88. (The JAA is an associated body of the European
Civil Aviation Conference (ECAC) representing the civil aviation
regulatory authorities of a number of European States who have agreed
to co-operate in developing and implementing common safety regulatory
standards and procedures.) Under this regulation, the JAA stated that
all members of the ECAC that hold type certificates for transport
category airplanes are required to conduct a design review against
explosion risks.
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.
The Direction Generale de l'Aviation Civile (DGAC), which is the
airworthiness authority for France, notified us that an unsafe
condition may exist on certain Airbus Model A319-100 and A320-200
series airplanes; and A320-111 airplanes. The DGAC advises that
operators have reported that the low-pressure warning for the fuel
pumps of the center fuel tank has come on in flight. The probable cause
is re-wetting of the low-level sensors for the center tank pumps when
the airplane is maneuvered, and when the altitude changes. The warning
also may come on when the airplane experiences turbulence. This
condition, if not corrected, could cause the fuel pumps to run while
dry, which could result in a potential ignition source inside the
center fuel tank which, in combination with flammable fuel vapors,
could result in a fuel tank explosion and consequent loss of the
airplane.
Relevant Service Information
Airbus has issued Service Bulletin A320-28-1059, Revision 06, dated
June 29, 2000. The service bulletin describes procedures for modifying
the wiring to the fuel pump control of the center fuel tank to
``latch'' the pumps off when the low-level sensor has been dry for 5
minutes. The modification also includes installing two-pole relays to
release the ``latch'' when the refuel door is opened or when switching
from ``Auto'' to ``Manual'' mode for center pump operation.
Accomplishing the actions specified in the service information is
intended to adequately address the unsafe condition. The DGAC mandated
the service information and issued French airworthiness directive F-
2005-173, dated October 26, 2005, to ensure the continued airworthiness
of these airplanes in France.
FAA's Determination and Requirements of the Proposed AD
These airplane models are manufactured in France and are type
certificated for operation in the United States under the provisions of
section 21.29 of the Federal Aviation Regulations (14 CFR 21.29) and
the applicable bilateral airworthiness agreement. Pursuant to this
bilateral airworthiness agreement, the DGAC has kept the FAA informed
of the situation described above. We have examined the DGAC's findings,
evaluated all pertinent information, and determined that we need to
issue an AD for products of this type design that are certificated for
operation in the United States.
Therefore, we are proposing this AD, which would require
accomplishing the actions specified in the service information
described previously.
Difference Between French Airworthiness Directive and This Proposed AD
The applicability of French airworthiness directive F-2005-173
excludes airplanes on which Airbus Service Bulletin A320-28-1059 was
accomplished in service. However, we have not excluded those airplanes
from the applicability of this proposed AD; rather, this proposed AD
includes a requirement to accomplish the actions specified in that
service bulletin. This requirement would ensure that the actions
specified in the service bulletin and required by this proposed AD are
accomplished on all affected airplanes. Operators must continue to
operate the airplane in the configuration required by this proposed AD
unless an alternative method of compliance is approved.
Costs of Compliance
This proposed AD would affect about 119 airplanes of U.S. registry.
The proposed actions would take about 17 work hours per airplane, at an
average labor rate of $65 per work hour. There is no cost for parts.
Based on these figures, the estimated cost of the proposed AD for U.S.
operators is $131,495, or $1,105 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:
[[Page 9048]]
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):
Airbus: Docket No. FAA-2006-23948; Directorate Identifier 2005-NM-
246-AD.
Comments Due Date
(a) The FAA must receive comments on this AD action by March 24,
2006.
Affected ADs
(b) None.
Applicability
(c) This AD applies to Airbus Model A319-111, -112, -113, -114,
-115, -131, -132, and -133 airplanes; and Model A320-111, -211, -
212, -214, -231, -232, and -233 airplanes; certificated in any
category; that have received Airbus Modification 20024 in production
(installation of a center tank), except airplanes on which Airbus
Modification 24373 has been accomplished.
Unsafe Condition
(d) This AD results from reports that the low-pressure warning
for the fuel pumps of the center fuel tank has come on in flight. We
are issuing this AD to ensure that the fuel pumps do not run while
dry, which could result in a potential ignition source inside the
center fuel tank 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.
Modification
(f) Within 20 months after the effective date of this AD, modify
the wiring to the fuel pump control of the center fuel tank by doing
all actions specified in the Accomplishment Instructions of Airbus
Service Bulletin A320-28-1059, Revision 06, dated June 29, 2000.
Credit for Previous Revisions of Service Bulletin
(g) Modifications done before the effective date of this AD in
accordance with the service bulletins identified in Table 1 of this
AD are acceptable for compliance with the requirements of paragraph
(f) of this AD.
Table 1.--Previous Revisions of Service Bulletin
------------------------------------------------------------------------
Revision
Airbus service bulletin level Date
------------------------------------------------------------------------
A320-28-1059.................... 04 February 4, 1999.
A320-28-1059.................... 05 March 12, 1999.
------------------------------------------------------------------------
Alternative Methods of Compliance (AMOCs)
(h)(1) The Manager, International Branch, ANM-116, Transport
Airplane Directorate, FAA, has the authority to approve AMOCs for
this AD, if requested in accordance with the procedures found in 14
CFR 39.19.
(2) Before using any AMOC approved in accordance with Sec.
39.19 on any airplane to which the AMOC applies, notify the
appropriate principal inspector in the FAA Flight Standards
Certificate Holding District Office.
Related Information
(i) French airworthiness directive F-2005-173, dated October 26,
2005, also addresses the subject of this AD.
Issued in Renton, Washington, on February 10, 2006.
Kalene C. Yanamura,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. E6-2453 Filed 2-21-06; 8:45 am]
BILLING CODE 4910-13-P
