Airworthiness Directives; Airbus Model A321 Series Airplanes, 32542-32544 [05-11061]
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32542
Federal Register / Vol. 70, No. 106 / Friday, June 3, 2005 / Proposed Rules
Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13
[Amended]
2. The FAA amends § 39.13 by adding
the following new airworthiness
directive (AD):
Saab Aircraft AB: Docket No. FAA–2005–
21341; Directorate Identifier 2003–NM–
026–AD.
Comments Due Date
(a) The Federal Aviation Administration
must receive comments on this AD action by
July 5, 2005.
Affected ADs
(b) None.
Applicability
(c) This AD applies to certain Saab Model
SAAB 2000 series airplanes having Serial
Numbers 004 through 063 inclusive;
certificated in any category.
Unsafe Condition
(d) This AD was prompted by a report of
cracking of certain fastener holes in the lower
spar cap of the rear spar and in the lower
skin at the front spar. We are issuing this AD
to prevent cracking of the front and rear spar,
which could result in fuel leakage and
consequent reduced structural integrity of the
wing structure.
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.
Inspection
(f) Prior to the accumulation of 20,000 total
flight cycles, perform non-destructive tests
for cracking of the fastener holes in the lower
spar cap of the rear spar and in the lower
skin at the left-hand and right-hand sides of
the front spar, between WS20 and WS83
inclusive; by accomplishing all the actions
specified in Parts A, B, and C of the
Accomplishment Instructions of Saab Service
Bulletin 2000–57–038, dated December 18,
2002. If any cracking is detected, before
further flight, repair the cracking according to
a method approved by the Manager,
International Branch, ANM–116, FAA,
Transport Airplane Directorate, or the
Luftfartsverket (LFV) (or its delegated agent).
Modification
(g) Prior to the accumulation of 20,000 total
flight cycles, modify the fastener holes of the
front and rear spars and the rear spar web,
including related investigative actions, by
accomplishing all the actions specified in
Part D of the Accomplishment Instructions of
Saab Service Bulletin 2000–57–38, dated
December 18, 2002. If 1⁄4-inch fasteners are
needed for holes No. 7 and No. 8, before
further flight, contact the Manager,
International Branch, ANM116, FAA,
Transport Airplane Directorate for further
actions, or the LFV (or its delegated agent).
If any scratches or other damage is detected
on the skin surface or the surface of the front
spar, before further flight, repair in
accordance with a method approved by the
VerDate jul<14>2003
17:25 Jun 02, 2005
Jkt 205001
Manager, International Branch, ANM–116,
FAA, Transport Airplane Directorate, or the
Luftfartsverket (LFV) (or its delegated agent.)
Alternative Methods of Compliance
(AMOCs)
(h) 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.
Related Information
(i) Swedish airworthiness directive 1–182,
dated December 20, 2002, also addresses the
subject of this AD.
Issued in Renton, Washington, on May 26,
2005.
Ali Bahrami,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. 05–11060 Filed 6–2–05; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2005–21342; Directorate
Identifier 2004–NM–15–AD]
RIN 2120–AA64
Airworthiness Directives; Airbus Model
A321 Series 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 Airbus Model A321 series
airplanes. This proposed AD would
require repetitive measurements for
correct control rod gap of the hold-open
mechanism of all emergency doors, and
corrective actions if necessary. This
proposed AD would also require
replacing the control rods with new,
improved control rods, which would
terminate the repetitive measurements.
This proposed AD is prompted by a
report that an operator found it
impossible to lock emergency doors 2
and 3 in the open position. We are
proposing this AD to prevent failure of
the emergency doors to lock in the open
position, which could interfere with
passenger evacuation during an
emergency.
SUMMARY:
We must receive comments on
this proposed AD by July 5, 2005.
ADDRESSES: Use one of the following
addresses to submit comments on this
proposed AD.
DATES:
PO 00000
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Fmt 4702
Sfmt 4702
• 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.
• By 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.
For service information identified in
this proposed AD, contact Airbus, 1
Rond Point Maurice Bellonte, 31707
Blagnac Cedex, France.
You can examine the contents of this
AD docket on the Internet at https://
dms.dot.gov, or in person at the Docket
Management Facility, U.S. Department
of Transportation, 400 Seventh Street
SW., room PL–401, on the plaza level of
the Nassif Building, Washington, DC.
This docket number is FAA–2005–
21342; the directorate identifier for this
docket is 2004–NM–15–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 under
ADDRESSES. Include ‘‘Docket No. FAA–
2005–21342; Directorate Identifier
2004–NM–15–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 submitted 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 our docket
Web site, anyone can find and read the
comments in any of our dockets,
including the name of the individual
E:\FR\FM\03JNP1.SGM
03JNP1
Federal Register / Vol. 70, No. 106 / Friday, June 3, 2005 / Proposed Rules
who sent the comment (or signed the
comment on behalf of an association,
business, labor union, etc.). You can
review the DOT’s complete Privacy Act
Statement in the Federal Register
published on April 11, 2000 (65 FR
19477–78), or you can visit https://
dms.dot.gov.
Examining the Docket
You can 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 DMS
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 A321
series airplanes. The DGAC advises that
an operator found it impossible to lock
emergency doors 2 and 3 in the open
position due to an incorrect gap of the
polyamide control rods of the hold-open
release mechanisms. Investigation
revealed that the polyamide control rod
had lengthened due to water absorption
and kept the hold-open mechanism
constantly activated in the release
position. This condition, if not
corrected, could lead to failure of the
emergency doors to lock in the open
position, which could interfere with
passenger evacuation during an
emergency.
Relevant Service Information
Airbus has issued All Operators Telex
(AOT) A320–52A1120, Revision 2,
dated July 10, 2003. The AOT describes
procedures for repetitive measurements
to determine correct control rod gap of
the hold-open mechanism of the
emergency doors, and corrective actions
if necessary. Corrective actions include
shortening the polyamide control rod if
it is too long or, if it is too short,
replacing the rod with a new polyamide
control rod or an aluminum control rod.
Airbus has issued Service Bulletin
A320–52–1121, dated December 12,
2003. The service bulletin describes
procedures for replacing the polyamide
or interim aluminum control rods with
new, improved, water-resistant control
rods. Interim or final replacement of the
polyamide control rod eliminates the
need for the repetitive measurements
VerDate jul<14>2003
17:25 Jun 02, 2005
Jkt 205001
described by the AOT for that control
rod.
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–2004–040,
dated March 31, 2004, to ensure the
continued airworthiness of these
airplanes in France.
FAA’s Determination and Requirements
of the Proposed AD
This airplane model is manufactured
in France and is type certificated for
operation in the United States under the
provisions of § 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,
except as discussed under ‘‘Differences
Between French Airworthiness
Directive and This Proposed AD.’’
Differences Between French
Airworthiness Directive and This
Proposed AD
The applicability of French
airworthiness directive F–2004–040
excludes airplanes on which Airbus
Service Bulletin A320–52–1121 was
done in service. However, we have not
excluded those airplanes in 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. This difference has been
coordinated with the DGAC.
French airworthiness directive F–
2004–040 specifies to ‘‘inspect’’ the
hold-open mechanism. To prevent any
confusion, rather than an ‘‘inspection’’
of the hold-open mechanism, this
proposed AD would require a
‘‘measurement’’ to determine the control
PO 00000
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32543
rod gap of the hold-open mechanism, as
specified in the AOT.
Clarification of Service Information
The service information specifies
procedures for reporting measurement
results and accomplishment of the
control rod replacement to the
manufacturer; however, this proposed
AD would not make this requirement.
The FAA does not need this information
from operators.
Costs of Compliance
This proposed AD would affect about
28 airplanes of U.S. registry.
The measurement to determine
control rod gap would take about 2 work
hours per airplane, at an average labor
rate of $65 per work hour. Based on
these figures, the estimated cost of the
proposed measurement for U.S.
operators is $3,640, or $130 per
airplane, per measurement cycle.
The replacement of the control rods
with new, improved, water-resistant
control rods would take about 9 work
hours per airplane, at an average labor
rate of $65 per work hour. Required
parts would cost about $400 per
airplane. Based on these figures, the
estimated cost of the proposed
replacement for U.S. operators is
$27,580, or $985 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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32544
Federal Register / Vol. 70, No. 106 / Friday, June 3, 2005 / Proposed Rules
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. 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 FAA amends § 39.13 by adding
the following new airworthiness
directive (AD):
Airbus: Docket No. FAA–2005–21342;
Directorate Identifier 2004–NM–15–AD.
Comments Due Date
(a) The Federal Aviation Administration
must receive comments on this AD action by
July 5, 2005.
Affected ADs
(b) None.
Applicability
(c) This AD applies to Airbus Model A321
series airplanes, certificated in any category;
except for those airplanes that have received
Airbus Modification 33426 in production.
Unsafe Condition
(d) This AD was prompted by a report that
an operator found it impossible to lock
emergency doors 2 and 3 in the open
position. We are issuing this AD to prevent
failure of the emergency doors to lock in the
open position, which could interfere with
passenger evacuation during an emergency.
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.
VerDate jul<14>2003
17:25 Jun 02, 2005
Jkt 205001
Inspection of Emergency Exit Doors
(f) Within 600 flight hours after the
effective date of this AD and thereafter at
intervals not to exceed 600 flight hours,
perform a measurement for correct gap of the
control rod of the hold-open mechanism of
all emergency doors, in accordance with
Airbus All Operators Telex (AOT) A320–
52A1120, Revision 2, dated July 10, 2003. If
the gap of any control rod is not correct, prior
to further flight, apply all necessary
corrective actions in accordance with the
AOT.
Optional Interim Terminating Action
(g) Replacing the polyamide control rod of
any mechanism with an aluminum control
rod prior to accomplishing paragraph (h) of
this AD, as specified in AOT A320–52A1120,
Revision 2, dated July 10, 2003, terminates
the repetitive measurement required by
paragraph (f) of this AD for that mechanism.
Final Terminating Action
(h) Within 18 months after the effective
date of this AD, replace the polyamide or
interim aluminum control rods of the release
mechanisms with new, improved, waterresistant control rods according to the
Accomplishment Instructions of Airbus
Service Bulletin A320–52–1121, dated
December 12, 2003. This replacement
terminates the repetitive measurement
required by paragraph (f) of this AD.
Actions Accomplished Per Previous Issue of
Service Bulletin
(i) Actions accomplished before the
effective date of this AD according to Airbus
AOT A320–52A1120, dated June 5, 2003, or
Revision 1, dated June 19, 2003, are
considered acceptable for compliance with
the corresponding actions specified in this
AD.
No Reporting Requirement
(j) Although the service information
specifies procedures for reporting
measurement results and control rod
replacement to the manufacturer, this AD
does not require these reports.
Alternative Methods of Compliance
(AMOCs)
(k) 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.
Related Information
(l) French airworthiness directive F–2004–
040, dated March 31, 2004, also addresses the
subject of this AD.
Issued in Renton, Washington, on May 26,
2005.
Ali Bahrami,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. 05–11061 Filed 6–2–05; 8:45 am]
BILLING CODE 4910–13–P
PO 00000
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Fmt 4702
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2005–21345; Directorate
Identifier 2005–NM–005–AD]
RIN 2120–AA64
Airworthiness Directives; Empresa
Brasileira de Aeronautica S.A.
(EMBRAER) Model ERJ 170 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 all
EMBRAER Model ERJ 170 series
airplanes. This proposed AD would
require inspecting the hydraulic
pressure tubes at the outlet of the
engine-driven hydraulic pumps to
determine the part and serial numbers;
and replacing hydraulic pressure tubes
having certain serial numbers with new
hydraulic pressure tubes. This proposed
AD is prompted by failure of a hydraulic
system due to leakage of hydraulic fluid
from a crack in the pipe coming from
the pressure side of the engine driven
pump. We are proposing this AD to
prevent cracking of the hydraulic
pressure pipes, which could result in
failure of hydraulic system 1 or 2 or
both, and consequent reduced
controllability of the airplane.
DATES: We must receive comments on
this proposed AD by July 5, 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.
• By 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.
For service information identified in
this proposed AD, contact Empresa
Brasileira de Aeronautica S.A.
(EMBRAER), P.O. Box 343—CEP 12.225,
Sao Jose dos Campos—SP, Brazil.
E:\FR\FM\03JNP1.SGM
03JNP1
]]>Agencies
[Federal Register Volume 70, Number 106 (Friday, June 3, 2005)]
[Proposed Rules]
[Pages 32542-32544]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 05-11061]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2005-21342; Directorate Identifier 2004-NM-15-AD]
RIN 2120-AA64
Airworthiness Directives; Airbus Model A321 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 A321 series airplanes. This proposed AD would
require repetitive measurements for correct control rod gap of the
hold-open mechanism of all emergency doors, and corrective actions if
necessary. This proposed AD would also require replacing the control
rods with new, improved control rods, which would terminate the
repetitive measurements. This proposed AD is prompted by a report that
an operator found it impossible to lock emergency doors 2 and 3 in the
open position. We are proposing this AD to prevent failure of the
emergency doors to lock in the open position, which could interfere
with passenger evacuation during an emergency.
DATES: We must receive comments on this proposed AD by July 5, 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.
By 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.
For service information identified in this proposed AD, contact
Airbus, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France.
You can examine the contents of this AD docket on the Internet at
https://dms.dot.gov, or in person at the Docket Management Facility,
U.S. Department of Transportation, 400 Seventh Street SW., room PL-401,
on the plaza level of the Nassif Building, Washington, DC. This docket
number is FAA-2005-21342; the directorate identifier for this docket is
2004-NM-15-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 under ADDRESSES. Include ``Docket No. FAA-2005-21342;
Directorate Identifier 2004-NM-15-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 submitted 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 our
docket Web site, anyone can find and read the comments in any of our
dockets, including the name of the individual
[[Page 32543]]
who sent the comment (or signed the comment on behalf of an
association, business, labor union, etc.). You can review the DOT's
complete Privacy Act Statement in the Federal Register published on
April 11, 2000 (65 FR 19477-78), or you can visit https://dms.dot.gov.
Examining the Docket
You can 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 DMS receives them.
Discussion
The Direction G[eacute]n[eacute]rale de l'Aviation Civile (DGAC),
which is the airworthiness authority for France, notified us that an
unsafe condition may exist on certain Airbus Model A321 series
airplanes. The DGAC advises that an operator found it impossible to
lock emergency doors 2 and 3 in the open position due to an incorrect
gap of the polyamide control rods of the hold-open release mechanisms.
Investigation revealed that the polyamide control rod had lengthened
due to water absorption and kept the hold-open mechanism constantly
activated in the release position. This condition, if not corrected,
could lead to failure of the emergency doors to lock in the open
position, which could interfere with passenger evacuation during an
emergency.
Relevant Service Information
Airbus has issued All Operators Telex (AOT) A320-52A1120, Revision
2, dated July 10, 2003. The AOT describes procedures for repetitive
measurements to determine correct control rod gap of the hold-open
mechanism of the emergency doors, and corrective actions if necessary.
Corrective actions include shortening the polyamide control rod if it
is too long or, if it is too short, replacing the rod with a new
polyamide control rod or an aluminum control rod.
Airbus has issued Service Bulletin A320-52-1121, dated December 12,
2003. The service bulletin describes procedures for replacing the
polyamide or interim aluminum control rods with new, improved, water-
resistant control rods. Interim or final replacement of the polyamide
control rod eliminates the need for the repetitive measurements
described by the AOT for that control rod.
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-
2004-040, dated March 31, 2004, to ensure the continued airworthiness
of these airplanes in France.
FAA's Determination and Requirements of the Proposed AD
This airplane model is manufactured in France and is type
certificated for operation in the United States under the provisions of
Sec. 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, except as discussed under ``Differences Between
French Airworthiness Directive and This Proposed AD.''
Differences Between French Airworthiness Directive and This Proposed AD
The applicability of French airworthiness directive F-2004-040
excludes airplanes on which Airbus Service Bulletin A320-52-1121 was
done in service. However, we have not excluded those airplanes in 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. This difference has been
coordinated with the DGAC.
French airworthiness directive F-2004-040 specifies to ``inspect''
the hold-open mechanism. To prevent any confusion, rather than an
``inspection'' of the hold-open mechanism, this proposed AD would
require a ``measurement'' to determine the control rod gap of the hold-
open mechanism, as specified in the AOT.
Clarification of Service Information
The service information specifies procedures for reporting
measurement results and accomplishment of the control rod replacement
to the manufacturer; however, this proposed AD would not make this
requirement. The FAA does not need this information from operators.
Costs of Compliance
This proposed AD would affect about 28 airplanes of U.S. registry.
The measurement to determine control rod gap would take about 2
work hours per airplane, at an average labor rate of $65 per work hour.
Based on these figures, the estimated cost of the proposed measurement
for U.S. operators is $3,640, or $130 per airplane, per measurement
cycle.
The replacement of the control rods with new, improved, water-
resistant control rods would take about 9 work hours per airplane, at
an average labor rate of $65 per work hour. Required parts would cost
about $400 per airplane. Based on these figures, the estimated cost of
the proposed replacement for U.S. operators is $27,580, or $985 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
[[Page 32544]]
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. 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 FAA amends Sec. 39.13 by adding the following new
airworthiness directive (AD):
Airbus: Docket No. FAA-2005-21342; Directorate Identifier 2004-NM-
15-AD.
Comments Due Date
(a) The Federal Aviation Administration must receive comments on
this AD action by July 5, 2005.
Affected ADs
(b) None.
Applicability
(c) This AD applies to Airbus Model A321 series airplanes,
certificated in any category; except for those airplanes that have
received Airbus Modification 33426 in production.
Unsafe Condition
(d) This AD was prompted by a report that an operator found it
impossible to lock emergency doors 2 and 3 in the open position. We
are issuing this AD to prevent failure of the emergency doors to
lock in the open position, which could interfere with passenger
evacuation during an emergency.
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.
Inspection of Emergency Exit Doors
(f) Within 600 flight hours after the effective date of this AD
and thereafter at intervals not to exceed 600 flight hours, perform
a measurement for correct gap of the control rod of the hold-open
mechanism of all emergency doors, in accordance with Airbus All
Operators Telex (AOT) A320-52A1120, Revision 2, dated July 10, 2003.
If the gap of any control rod is not correct, prior to further
flight, apply all necessary corrective actions in accordance with
the AOT.
Optional Interim Terminating Action
(g) Replacing the polyamide control rod of any mechanism with an
aluminum control rod prior to accomplishing paragraph (h) of this
AD, as specified in AOT A320-52A1120, Revision 2, dated July 10,
2003, terminates the repetitive measurement required by paragraph
(f) of this AD for that mechanism.
Final Terminating Action
(h) Within 18 months after the effective date of this AD,
replace the polyamide or interim aluminum control rods of the
release mechanisms with new, improved, water-resistant control rods
according to the Accomplishment Instructions of Airbus Service
Bulletin A320-52-1121, dated December 12, 2003. This replacement
terminates the repetitive measurement required by paragraph (f) of
this AD.
Actions Accomplished Per Previous Issue of Service Bulletin
(i) Actions accomplished before the effective date of this AD
according to Airbus AOT A320-52A1120, dated June 5, 2003, or
Revision 1, dated June 19, 2003, are considered acceptable for
compliance with the corresponding actions specified in this AD.
No Reporting Requirement
(j) Although the service information specifies procedures for
reporting measurement results and control rod replacement to the
manufacturer, this AD does not require these reports.
Alternative Methods of Compliance (AMOCs)
(k) 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.
Related Information
(l) French airworthiness directive F-2004-040, dated March 31,
2004, also addresses the subject of this AD.
Issued in Renton, Washington, on May 26, 2005.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 05-11061 Filed 6-2-05; 8:45 am]
BILLING CODE 4910-13-P
