Airworthiness Directives; Airbus Model A319-100 and A320-200 Series Airplanes, 68379-68381 [05-22444]
Download as PDF
<![CDATA[
Federal Register / Vol. 70, No. 217 / Thursday, November 10, 2005 / Proposed Rules
Unsafe Condition
(d) This AD results from production
inspections that showed that the spring
assembly that controls rudder balance may
not have the correct pre-load on some
airplanes. We are issuing this AD to prevent
uncommanded yaw movements and
consequent reduced controllability 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.
68379
Service Bulletin Reference
(f) The term ‘‘service bulletin,’’ as used in
this AD, means the Accomplishment
Instructions of the applicable service bulletin
in Table 2 of this AD.
TABLE 2.—SERVICE BULLETINS
Bombardier airplane model
Bombardier service bulletin
CL–600–1A11 (CL–600) ...........................................................................
600–0714, including Appendix 1 and excluding Appendix 2, dated April
4, 2003.
601–0549, including Appendix 1 and excluding Appendix 2, dated April
4, 2003.
604–27–013, including Appendix 1 and excluding Appendix 2, dated
April 4, 2003.
CL–600–2A12 (CL–601), and CL–600–2B16 (CL–601–3A and CL–
601–3R).
CL–600–2B16 (CL–604) ...........................................................................
Modification and Rigging
DEPARTMENT OF TRANSPORTATION
(g) Within 12 months after the effective
date of this AD: Modify and rig the adjustable
rudder balance spring assembly for the
rudder control surface, in accordance with
the Accomplishment Instructions of the
applicable service bulletin in Table 2 of this
AD. Where the service bulletin specifies
contacting Bombardier for instructions on
making certain adjustments: Before further
flight, adjust according to a method approved
by the Manager, New York Aircraft
Certification Office (ACO), FAA; or Transport
Canada Civil Aviation (TCCA) (or its
delegated agent).
No Reporting Required
(h) Although the service bulletins
referenced in this AD specify to submit
certain information to the manufacturer, this
AD does not include that requirement.
Parts Installation
(i) After the effective date of this AD, no
person may install on any airplane a rudder
balance spring assembly unless it has been
modified and rigged in accordance with
paragraph (g) of this AD.
Alternative Methods of Compliance
(AMOCs)
(j)(1) The Manager, New York ACO, 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.
Related Information
(k) Canadian airworthiness directive CF–
2005–21, dated June 23, 2005, also addresses
the subject of this AD.
Issued in Renton, Washington, on October
31, 2005.
Ali Bahrami,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. 05–22445 Filed 11–9–05; 8:45 am]
BILLING CODE 4910–13–P
VerDate Aug<31>2005
15:31 Nov 09, 2005
Jkt 208001
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2005–22918; Directorate
Identifier 2005–NM–172–AD]
RIN 2120–AA64
Airworthiness Directives; Airbus Model
A319–100 and A320–200 Series
Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
SUMMARY: The FAA proposes to adopt a
new airworthiness directive (AD) for
certain Airbus Model A319–100 and
A320–200 series airplanes. This
proposed AD would require repetitive
inspections of the wing-tank fuel
pumps, canisters, and wing fuel tanks
for detached identification labels, and
corrective action if necessary. This
proposed AD results from several
incidents of detached plastic
identification labels found floating in
the wing fuel tanks. We are proposing
this AD to prevent plastic identification
labels being ingested into the fuel
pumps and consequently entering the
engine fuel feed system, which could
result in an engine shutdown.
DATES: We must receive comments on
this proposed AD by December 12,
2005.
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
PO 00000
Frm 00030
Fmt 4702
Sfmt 4702
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–2005–22918; Directorate
Identifier 2005–NM–172–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
E:\FR\FM\10NOP1.SGM
10NOP1
68380
Federal Register / Vol. 70, No. 217 / Thursday, November 10, 2005 / Proposed Rules
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 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. The
DGAC advises that, in several incidents,
plastic identification labels have been
found floating in the fuel tanks. There
are two types of labels and the
information on the labels identifies each
rib number in the vent box and the
manhole door fasteners in the wing fuel
tank, for inspection purposes.
Inspection of the airplanes revealed that
the varnish coating and adhesive on the
labels had deteriorated and the labels
detached from the wing structure.
Detached labels floating in the fuel tank
could be ingested into the fuel pumps
and consequently enter into the engine
fuel feed system. These conditions, if
not corrected, could result in an engine
shutdown.
Relevant Service Information
Airbus has issued Service Bulletin
A320–28–1102, Revision 01, dated
February 11, 2005. The service bulletin
describes procedures for repetitive
detailed visual inspections of the four
wing-tank fuel pumps and canisters for
detached identification labels, and
corrective action if necessary. The
corrective action involves removing any
label debris that is found, performing a
detailed visual inspection for debris of
the fuel filters and replacing the filters
if necessary, and replacing the fuel
pump if the inlet and outlet ports are
blocked. The service bulletin also
VerDate Aug<31>2005
15:31 Nov 09, 2005
Jkt 208001
recommends sending an inspection
report to Airbus.
Airbus has also issued Service
Bulletin A320–57–1117, dated July 16,
2002. The service bulletin describes
procedures for repetitive detailed visual
inspections for detached identification
labels in the collector cells between ribs
1 and 2, the surge tank between ribs 22
and 26, and the wing fuel tank and vent
box, and corrective action if necessary.
The corrective action involves removing
any label debris that is found, removing
any partially detached labels, and reidentifying certain fasteners and ribs.
The DGAC mandated the service
information and issued French
airworthiness directive F–2005–121,
dated July 20, 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 airplanes 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. For
any wing-tank fuel pump failure that
occurs, this proposed AD would also
require performing a detailed inspection
of the failed pump, the pump located in
the same half wing, and the associated
canister, and accomplishing any
applicable corrective action, including
replacing the pump.
Difference Between the Proposed AD
and French Airworthiness Directive
The French airworthiness directive
mandates changes to the master
minimum equipment list (MMEL). This
proposed AD will not mandate those
MMEL changes because the limits
imposed by the FAA-approved MMEL
meet or exceed those mandated by the
French airworthiness directive. We have
coordinated this issue with the DGAC.
Clarification of Inspection Terminology
In this proposed AD, the ‘‘detailed
visual inspections’’ specified in the
service bulletins are referred to as
PO 00000
Frm 00031
Fmt 4702
Sfmt 4702
‘‘detailed inspections.’’ We have
included the definition for a detailed
inspection in a note in the proposed AD.
Costs of Compliance
This proposed AD would affect about
74 airplanes of U.S. registry.
The inspection specified in Service
Bulletin A320–28–1102 would take
about 3 work hours (including an
operational test) per airplane, at an
average labor rate of $65 per work hour.
Based on these figures, the estimated
cost of this proposed inspection for U.S.
operators is $14,430, or $195 per
airplane, per inspection cycle.
The inspection specified in Service
Bulletin A320–57–1117 would take
about 6 work hours (including an
operational test) per airplane, at an
average labor rate of $65 per work hour.
Based on these figures, the estimated
cost of this proposed inspection for U.S.
operators is $28,860, or $390 per
airplane, per inspection cycle.
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
E:\FR\FM\10NOP1.SGM
10NOP1
Federal Register / Vol. 70, No. 217 / Thursday, November 10, 2005 / Proposed Rules
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):
Airbus: Docket No. FAA–2005–22918;
Directorate Identifier 2005–NM–172–AD.
Comments Due Date
(a) The FAA must receive comments on
this AD action by December 12, 2005.
Affected ADs
(b) None.
Applicability
(c) This AD applies to Airbus Model A319–
111, –112, –113, –114, –115, –131, –132, and
–133, and Model A320–211, –212, –214,
–231, –232, and –233 airplanes; certificated
in any category; as identified in Airbus
Service Bulletins A320–57–1117, dated July
16, 2002, and A320–28–1102, Revision 01,
dated February 11, 2005.
Unsafe Condition
(d) This AD results from several incidents
of detached plastic identification labels
found floating in the wing fuel tanks. We are
issuing this AD to prevent plastic
identification labels being ingested into the
fuel pumps and consequently entering the
engine fuel feed system, which could result
in an engine shutdown.
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.
Repetitive Inspections/Corrective Actions of
Four Wing-Tank Fuel Pumps and Canisters
(f) Within 600 flight hours after the
effective date of this AD: Perform a detailed
VerDate Aug<31>2005
15:31 Nov 09, 2005
Jkt 208001
inspection for detached identification labels
in the four wing-tank fuel pumps and
canisters, and do any applicable corrective
actions, by doing all the actions in
accordance with the Accomplishment
Instructions of Airbus Service Bulletin A320–
28–1102, Revision 01, dated February 11,
2005; except as provided by paragraph (j) of
this AD. Do any applicable corrective action
before further flight. Repeat the inspection
thereafter at intervals not to exceed 600 flight
hours.
(g) For any wing-tank fuel pump failure
that occurs after the effective date of this AD:
Before further flight, perform a detailed
inspection of the failed pump, the pump
located in the same half wing, and the
associated canister, in accordance with the
Accomplishment Instructions of Airbus
Service Bulletin A320–28–1102, Revision 01,
dated February 11, 2005. Do any applicable
corrective action, including replacing the
failed pump, before further flight.
Note 1: For the purposes of this AD, a
detailed inspection is: ‘‘An intensive
examination of a specific item, installation,
or assembly to detect damage, failure, or
irregularity. Available lighting is normally
supplemented with a direct source of good
lighting at an intensity deemed appropriate.
Inspection aids such as mirror, magnifying
lenses, etc., may be necessary. Surface
cleaning and elaborate procedures may be
required.’’
Inspections and Corrective Actions
Accomplished According to Previous Issue
of Service Bulletin
(h) Inspections and corrective actions
accomplished before the effective date of this
AD according to Airbus Service Bulletin
A320–28–1102, dated August 20, 2002; are
considered acceptable for compliance with
the corresponding actions specified in
paragraph (f) of this AD.
Repetitive Inspections/Corrective Actions of
the Collector Cells, Wing Fuel Tank and
Vent Box
(i) Within 72 months after the effective
date of this AD: Perform a detailed inspection
for detached identification labels in the
collector cells between ribs 1 and 2, the surge
tank between ribs 22 and 26, and the wing
fuel tank and vent box, and do any applicable
corrective actions, by doing all the applicable
actions in accordance with the
Accomplishment Instructions of Airbus
Service Bulletin A320–57–1117, dated July
16, 2002. Do any applicable corrective action
before further flight. Repeat the inspection
thereafter at intervals not to exceed 72
months.
No Reporting Required
(j) Although Airbus Service Bulletin A320–
28–1102, Revision 01, dated February 11,
2005, specifies submitting an inspection
report to the manufacturer, this AD does not
include that requirement.
Alternative Methods of Compliance
(AMOCs)
(k)(1) The Manager, International Branch,
ANM–116, Transport Airplane Directorate,
FAA, has the authority to approve AMOCs
PO 00000
Frm 00032
Fmt 4702
Sfmt 4702
68381
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.
Related Information
(l) French airworthiness directive F–2005–
121, dated July 20, 2005, also addresses the
subject of this AD.
Issued in Renton, Washington, on October
31, 2005.
Ali Bahrami,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. 05–22444 Filed 11–9–05; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2005–22594; Directorate
Identifier 2005–NE–28–AD]
RIN 2120–AA64
Airworthiness Directives; Rolls-Royce
Corporation (formerly Allison Engine
Company, Allison Gas Turbine
Division, and Detroit Diesel Allison)
250–B and 250–C Series Turboprop
and Turboshaft Engines
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
SUMMARY: The FAA proposes to adopt a
new airworthiness directive (AD) for
Rolls-Royce Corporation 250–B and
250–C series turboprop and turboshaft
engines with certain part numbers
(P/Ns) of gas producer rotor assembly tie
bolts manufactured by EXTEX Ltd.,
Pacific Sky Supply Inc., Rolls-Royce
Corporation (RRC), and Superior Air
Parts Inc. This proposed AD would
require operators to remove from service
affected gas producer rotor assembly tie
bolts. This proposed AD results from
eleven reports of RRC tie bolt failure
due to high cycle fatigue. We are
proposing this AD to prevent tie bolt
failure that could cause loss of engine
power, resulting in a first stage turbine
wheel overspeed and an uncontained
engine failure.
DATES: We must receive any comments
on this proposed AD by January 9, 2006.
ADDRESSES: Use one of the following
addresses to comment on this proposed
AD.
E:\FR\FM\10NOP1.SGM
10NOP1
]]>Agencies
[Federal Register Volume 70, Number 217 (Thursday, November 10, 2005)]
[Proposed Rules]
[Pages 68379-68381]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 05-22444]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2005-22918; Directorate Identifier 2005-NM-172-AD]
RIN 2120-AA64
Airworthiness Directives; Airbus Model A319-100 and A320-200
Series 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. This
proposed AD would require repetitive inspections of the wing-tank fuel
pumps, canisters, and wing fuel tanks for detached identification
labels, and corrective action if necessary. This proposed AD results
from several incidents of detached plastic identification labels found
floating in the wing fuel tanks. We are proposing this AD to prevent
plastic identification labels being ingested into the fuel pumps and
consequently entering the engine fuel feed system, which could result
in an engine shutdown.
DATES: We must receive comments on this proposed AD by December 12,
2005.
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-2005-
22918; Directorate Identifier 2005-NM-172-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
[[Page 68380]]
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 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. The DGAC advises that, in several incidents, plastic
identification labels have been found floating in the fuel tanks. There
are two types of labels and the information on the labels identifies
each rib number in the vent box and the manhole door fasteners in the
wing fuel tank, for inspection purposes. Inspection of the airplanes
revealed that the varnish coating and adhesive on the labels had
deteriorated and the labels detached from the wing structure. Detached
labels floating in the fuel tank could be ingested into the fuel pumps
and consequently enter into the engine fuel feed system. These
conditions, if not corrected, could result in an engine shutdown.
Relevant Service Information
Airbus has issued Service Bulletin A320-28-1102, Revision 01, dated
February 11, 2005. The service bulletin describes procedures for
repetitive detailed visual inspections of the four wing-tank fuel pumps
and canisters for detached identification labels, and corrective action
if necessary. The corrective action involves removing any label debris
that is found, performing a detailed visual inspection for debris of
the fuel filters and replacing the filters if necessary, and replacing
the fuel pump if the inlet and outlet ports are blocked. The service
bulletin also recommends sending an inspection report to Airbus.
Airbus has also issued Service Bulletin A320-57-1117, dated July
16, 2002. The service bulletin describes procedures for repetitive
detailed visual inspections for detached identification labels in the
collector cells between ribs 1 and 2, the surge tank between ribs 22
and 26, and the wing fuel tank and vent box, and corrective action if
necessary. The corrective action involves removing any label debris
that is found, removing any partially detached labels, and re-
identifying certain fasteners and ribs.
The DGAC mandated the service information and issued French
airworthiness directive F-2005-121, dated July 20, 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 airplanes 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. For any wing-tank fuel pump failure that occurs,
this proposed AD would also require performing a detailed inspection of
the failed pump, the pump located in the same half wing, and the
associated canister, and accomplishing any applicable corrective
action, including replacing the pump.
Difference Between the Proposed AD and French Airworthiness Directive
The French airworthiness directive mandates changes to the master
minimum equipment list (MMEL). This proposed AD will not mandate those
MMEL changes because the limits imposed by the FAA-approved MMEL meet
or exceed those mandated by the French airworthiness directive. We have
coordinated this issue with the DGAC.
Clarification of Inspection Terminology
In this proposed AD, the ``detailed visual inspections'' specified
in the service bulletins are referred to as ``detailed inspections.''
We have included the definition for a detailed inspection in a note in
the proposed AD.
Costs of Compliance
This proposed AD would affect about 74 airplanes of U.S. registry.
The inspection specified in Service Bulletin A320-28-1102 would
take about 3 work hours (including an operational test) per airplane,
at an average labor rate of $65 per work hour. Based on these figures,
the estimated cost of this proposed inspection for U.S. operators is
$14,430, or $195 per airplane, per inspection cycle.
The inspection specified in Service Bulletin A320-57-1117 would
take about 6 work hours (including an operational test) per airplane,
at an average labor rate of $65 per work hour. Based on these figures,
the estimated cost of this proposed inspection for U.S. operators is
$28,860, or $390 per airplane, per inspection cycle.
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
[[Page 68381]]
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):
Airbus: Docket No. FAA-2005-22918; Directorate Identifier 2005-NM-
172-AD.
Comments Due Date
(a) The FAA must receive comments on this AD action by December
12, 2005.
Affected ADs
(b) None.
Applicability
(c) This AD applies to Airbus Model A319-111, -112, -113, -114,
-115, -131, -132, and -133, and Model A320-211, -212, -214, -231, -
232, and -233 airplanes; certificated in any category; as identified
in Airbus Service Bulletins A320-57-1117, dated July 16, 2002, and
A320-28-1102, Revision 01, dated February 11, 2005.
Unsafe Condition
(d) This AD results from several incidents of detached plastic
identification labels found floating in the wing fuel tanks. We are
issuing this AD to prevent plastic identification labels being
ingested into the fuel pumps and consequently entering the engine
fuel feed system, which could result in an engine shutdown.
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.
Repetitive Inspections/Corrective Actions of Four Wing-Tank Fuel Pumps
and Canisters
(f) Within 600 flight hours after the effective date of this AD:
Perform a detailed inspection for detached identification labels in
the four wing-tank fuel pumps and canisters, and do any applicable
corrective actions, by doing all the actions in accordance with the
Accomplishment Instructions of Airbus Service Bulletin A320-28-1102,
Revision 01, dated February 11, 2005; except as provided by
paragraph (j) of this AD. Do any applicable corrective action before
further flight. Repeat the inspection thereafter at intervals not to
exceed 600 flight hours.
(g) For any wing-tank fuel pump failure that occurs after the
effective date of this AD: Before further flight, perform a detailed
inspection of the failed pump, the pump located in the same half
wing, and the associated canister, in accordance with the
Accomplishment Instructions of Airbus Service Bulletin A320-28-1102,
Revision 01, dated February 11, 2005. Do any applicable corrective
action, including replacing the failed pump, before further flight.
Note 1: For the purposes of this AD, a detailed inspection is:
``An intensive examination of a specific item, installation, or
assembly to detect damage, failure, or irregularity. Available
lighting is normally supplemented with a direct source of good
lighting at an intensity deemed appropriate. Inspection aids such as
mirror, magnifying lenses, etc., may be necessary. Surface cleaning
and elaborate procedures may be required.''
Inspections and Corrective Actions Accomplished According to Previous
Issue of Service Bulletin
(h) Inspections and corrective actions accomplished before the
effective date of this AD according to Airbus Service Bulletin A320-
28-1102, dated August 20, 2002; are considered acceptable for
compliance with the corresponding actions specified in paragraph (f)
of this AD.
Repetitive Inspections/Corrective Actions of the Collector Cells, Wing
Fuel Tank and Vent Box
(i) Within 72 months after the effective date of this AD:
Perform a detailed inspection for detached identification labels in
the collector cells between ribs 1 and 2, the surge tank between
ribs 22 and 26, and the wing fuel tank and vent box, and do any
applicable corrective actions, by doing all the applicable actions
in accordance with the Accomplishment Instructions of Airbus Service
Bulletin A320-57-1117, dated July 16, 2002. Do any applicable
corrective action before further flight. Repeat the inspection
thereafter at intervals not to exceed 72 months.
No Reporting Required
(j) Although Airbus Service Bulletin A320-28-1102, Revision 01,
dated February 11, 2005, specifies submitting an inspection report
to the manufacturer, this AD does not include that requirement.
Alternative Methods of Compliance (AMOCs)
(k)(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
(l) French airworthiness directive F-2005-121, dated July 20,
2005, also addresses the subject of this AD.
Issued in Renton, Washington, on October 31, 2005.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 05-22444 Filed 11-9-05; 8:45 am]
BILLING CODE 4910-13-P
