Airworthiness Directives; Airbus Model A300 B2 and B4 Series Airplanes, 45592-45595 [05-15593]
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45592
Federal Register / Vol. 70, No. 151 / Monday, August 8, 2005 / Proposed Rules
electromechanical gust lock system to
become unscrewed. We are proposing this
AD to prevent unscrewing of the spring
cartridge clevis from jamming the elevator,
which could lead to 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.
Restatement of Requirements of AD 2003–
09–03
Inspection
(f) For Model EMB–135BJ airplanes:
Within 30 days after May 14, 2003 (the
effective date of AD 2003–09–03), perform a
general visual inspection of each spring
cartridge of the elevator gust lock system to
determine if the lock washer projection
correctly fits the slots in the cartridge flange,
in accordance with EMBRAER Service
Bulletin 145LEG–27–0006, dated December
9, 2002. Before further flight, replace any
discrepant spring cartridge with a new part
having the same part number, in accordance
with the service bulletin; or replace the
spring cartridge, part number (P/N) KDP2611,
with a new, improved spring cartridge, P/N
KDP4235, as specified in paragraph (h) of
this AD. After the effective date of this AD,
only the replacement specified in paragraph
(h) may be accomplished. Repeat the
inspection at intervals not to exceed 800
flight hours until the replacement of the
spring cartridge is accomplished as required
by paragraph (h). Although the service
bulletin recommends that operators report
inspection results to EMBRAER, this AD does
not require such a report.
Note 1: For the purposes of this AD, a
general visual inspection is: ‘‘A visual
examination of an interior or exterior area,
installation, or assembly to detect obvious
damage, failure, or irregularity. This level of
inspection is made from within touching
distance unless otherwise specified. A mirror
may be necessary to ensure visual access to
all surfaces in the inspection area. This level
of inspection is made under normally
available lighting conditions such as
daylight, hangar lighting, flashlight, or
droplight and may require removal or
opening of access panels or doors. Stands,
ladders, or platforms may be required to gain
proximity to the area being checked.’’
(g) For airplanes not identified in
paragraph (f) of this AD: At the applicable
time specified in paragraph (g)(1) or (g)(2) of
this AD, perform a general visual inspection
of each spring cartridge of the elevator gust
lock system to determine if the lock washer
projection correctly fits the slots in the
cartridge flange, in accordance with
EMBRAER Service Bulletin 145–27–0098,
dated December 9, 2002. Repeat the
inspection at intervals not to exceed 800
flight hours after the initial inspection until
the replacement of the spring cartridge, P/N
KDP2611, with a new, improved spring
cartridge, P/N KDP4235, is done as specified
in paragraph (h) of this AD. Although the
service bulletin recommends that operators
report inspection results to EMBRAER, this
AD does not require such a report.
VerDate jul<14>2003
20:26 Aug 05, 2005
Jkt 205001
(1) For airplanes equipped with an
operational electromechanical gust lock
system on the elevator: Inspect within 30
days after May 14, 2003, in accordance with
PART I of the service bulletin. Before further
flight, replace any discrepant spring cartridge
with a new part having the same part
number, in accordance with PART I of the
service bulletin; or do the replacement
specified in paragraph (h) of this AD. After
the effective date of this AD, only the
replacement specified in paragraph (h) may
be accomplished.
(2) For airplanes that are not equipped
with an operational electromechanical gust
lock system on the elevator, but that are
equipped with provisions for the system:
Inspect within 60 days after May 14, 2003,
in accordance with PART II of the service
bulletin. Before further flight, replace any
discrepant spring cartridge with a new part
having the same part number, in accordance
with PART II of the service bulletin; or do
the replacement specified in paragraph (h) of
this AD. After the effective date of this AD,
only the replacement specified in paragraph
(h) may be accomplished. Alternatively,
removal of the spring cartridges terminates
the repetitive inspection requirement of this
AD during the time the cartridges are
removed.
New Requirements of This AD
Replacement of Spring Cartridge
(h) Within 5,500 flight hours or 36 months
after the effective date of this AD, whichever
comes first, replace the spring cartridge, P/N
KPD2611, with a new, improved spring
cartridge, P/N KDP4235, in accordance with
the Accomplishment Instructions of
EMBRAER Service Bulletin 145LEG–27–
0012, Revision 01, dated April 12, 2004 (for
Model EMB–135BJ airplanes); or Service
Bulletin 145–27–0102, Revision 02, dated
January 20, 2005 (for Model EMB–135ER,
–135KE, –135KL, –135LR, –145, –145ER,
–145MR, –145LR, –145XR, –145MP, and
–145EP airplanes); as applicable.
Accomplishing this replacement terminates
the repetitive inspections required by
paragraphs (f) and (g) of this AD.
Parts Installation
(i) As of the effective date of this AD, no
person may install a spring cartridge, P/N
KPD2611, on any airplane.
Cartridge Replacement According to
Previous Issue of Service Bulletin
(j) Spring cartridge replacements
accomplished before the effective date of this
AD in accordance with EMBRAER Service
Bulletin 145LEG–27–0012, dated March 2,
2004; or Service Bulletin 145–27–0102, dated
December 23, 2003, or Revision 01, dated
April 12, 2004; are considered acceptable for
compliance with the corresponding action
required by this AD.
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.
PO 00000
Frm 00022
Fmt 4702
Sfmt 4702
(2) AMOCs approved previously according
to AD 2003–09–03, amendment 39–13132,
are approved as AMOCs for the
corresponding provisions of this AD.
Related Information
(l) Brazilian airworthiness directive 2003–
01–03R1, dated July 26, 2004, also addresses
the subject of this AD.
Issued in Renton, Washington, on August
2, 2005.
Kevin Mullin,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. 05–15592 Filed 8–5–05; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2005–22035; Directorate
Identifier 2005–NM–016–AD]
RIN 2120–AA64
Airworthiness Directives; Airbus Model
A300 B2 and B4 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
Airbus Model A300 B2 and B4 series
airplanes. This proposed AD would
require an inspection to determine the
part number of all angle of attack (AOA)
sensors, and repetitive replacement of
the AOA sensors with new or
overhauled AOA sensors if necessary.
This proposed AD would also provide
an optional terminating action for the
repetitive replacements. This proposed
AD is prompted by reports of several
false stall warnings associated with
stick-shaker activation, occurring during
take-off. We are proposing this AD to
prevent false stall warnings associated
with stick-shaker activation, which
could result in increased pilot workload
as the pilot tries to determine the cause
of the stall warning and possible
reduction in the pilot’s ability to control
the airplane.
DATES: We must receive comments on
this proposed AD by September 7, 2005.
ADDRESSES: Use one of the following
addresses to submit comments on this
proposed AD.
• DOT Docket Web site: Go to http:/
/dms.dot.gov and follow the instructions
for sending your comments
electronically.
E:\FR\FM\08AUP1.SGM
08AUP1
45593
Federal Register / Vol. 70, No. 151 / Monday, August 8, 2005 / Proposed Rules
• 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
Backman, Aerospace Engineer,
International Branch, ANM–116, FAA,
Transport Airplane Directorate, 1601
Lind Avenue, SW., Renton, Washington
98055–4056; telephone (425) 227–2797;
fax (425) 227–1149.
SUPPLEMENTARY INFORMATION:
Comments Invited
We invite you to submit any relevant
written data, views, or arguments
regarding this proposed AD. Include the
docket number ‘‘FAA–2005–22035;
Directorate Identifier 2005-NM–016AD’’ 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.
dated November 2, 2004. Service
Bulletin A300–34–0092 describes the
following procedures:
• Replacing Honeywell ‘‘pencil’’
AOA sensors having P/N 965–4020–007
with ‘‘vane’’ AOA sensors between
frame (FR)18 and FR19.
• Replacing the current detectors in
relay boxes 252VU and 107VU with new
current detectors.
Airbus Service Bulletin A300–34–
0092 also specifies that accomplishing
the modification in that service bulletin
cancels the actions specified in Airbus
Service Bulletin A300–34–0176.
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.
FAA’s Determination and Requirements
of the Proposed AD
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 A300 B2
and B4 series airplanes. The DGAC
advises that it has received reports of
several false stall warnings associated
with stick-shaker activation, occurring
during take-off. Investigation revealed
that defective angle of attack (AOA)
sensors caused the false stall warnings.
This condition, if not corrected, could
result in increased pilot workload as the
pilot tries to determine the cause of the
stall warning and possible reduction in
the pilot’s ability to control the airplane.
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,
except as discussed under ‘‘Difference
Between the Proposed AD and Service
Bulletin.’’
Relevant Service Information
Airbus has issued Service Bulletin
A300–34–0176, Revision 01, dated
February 3, 2004, which describes the
following procedures:
• Inspecting zone 120 to determine
the part number (P/N) of all three AOA
sensors.
• Repetitively replacing any
Honeywell AOA sensor having P/N
965–4020–007 with a new or
overhauled AOA sensor.
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–2003–457 R1,
dated December 22, 2004, to ensure the
continued airworthiness of these
airplanes in France.
Airbus has also issued Service
Bulletin A300–34–0092, Revision 03,
Difference Between the Proposed AD
and Service Bulletin
Operators should note that, although
the Accomplishment Instructions of the
Airbus Service Bulletin A300–34–0176,
Revision 01, dated February 3,2004,
describe procedures for reporting
inspection findings, this proposed AD
would not require that action. We do
not need this information from
operators.
Costs of Compliance
The following table provides the
estimated costs for U.S. operators to
comply with this proposed AD.
ESTIMATED COSTS
Action
Inspection ............................
VerDate jul<14>2003
20:26 Aug 05, 2005
Average
labor rate
per hour
Work
hours
1
Jkt 205001
$65
PO 00000
Cost per
airplane
Parts
None ..................................
Frm 00023
Fmt 4702
Sfmt 4702
Number of
U.S.registered
airplanes
$65
E:\FR\FM\08AUP1.SGM
20
08AUP1
Fleet cost
$1,300.
45594
Federal Register / Vol. 70, No. 151 / Monday, August 8, 2005 / Proposed Rules
ESTIMATED COSTS—Continued
Action
Average
labor rate
per hour
Work
hours
Replacement if necessary,
per replacement cycle.
Optional terminating action
2
65
$3,300 ($1,100 per sensor)
3,430
20
7
65
$8,780 ................................
9,235
20
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. 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.
VerDate jul<14>2003
20:26 Aug 05, 2005
Number of
U.S.registered
airplanes
Cost per
airplane
Parts
Jkt 205001
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–2005–22035;
Directorate Identifier 2005–NM–016–AD.
Comments Due Date
(a) The Federal Aviation Administration
must receive comments on this AD action by
September 7, 2005.
Fleet cost
$68,600 per replacement
cycle.
$184,700.
required by this paragraph. If any Honeywell
AOA sensor having P/N 965–4020–007 is
found, before further flight, replace the AOA
sensor with a new or overhauled AOA sensor
having P/N 965–4020–007, in accordance
with the service bulletin. Repeat the
replacement thereafter at intervals not to
exceed 8,000 flight hours or 96 months,
whichever is first. Accomplishing the actions
specified in paragraph (g) of this AD
terminates the repetitive replacements.
Optional Terminating Action
(g) Replacement of all Honeywell AOA
sensors having P/N 965–4020–007 between
frame (FR)18 and FR19 with ‘‘vane type’’
AOA sensors; and replacement of the current
detectors in relay boxes 252VU and 107VU
with new current detectors; in accordance
with the Accomplishment Instructions of
Airbus Service Bulletin A300–34–0092,
Revision 03, dated November 2, 2004;
terminate the repetitive replacements
required by paragraph (f) of this AD.
No Reporting Requirement
Affected ADs
(b) None.
Applicability: (c) This AD applies to all
Airbus Model A300 B2–1A, B2–1C, B2K–3C,
and B2–203 airplanes; and Model A300 B4–
2C, B4–103, and B4–203 airplanes;
certificated in any category.
(h) Although Airbus Service Bulletin
A300–34–0176, Revision 01, dated February
3, 2004, specifies to submit certain
information to the manufacturer, this AD
does not include that requirement.
Unsafe Condition
(d) This AD was prompted by reports of
several false stall warnings associated with
stick-shaker activation, occurring during
take-off. We are issuing this AD to prevent
false stall warnings associated with stickshaker activation, which could result in
increased pilot workload as the pilot tries to
determine the cause of the stall warning and
possible reduction in the pilot’s ability to
control 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.
(i) As of the effective date of this AD, no
person may install an AOA sensor having
P/N 965–4020–007 on any airplane, unless it
is new or overhauled and is repetitively
inspected as required by paragraph (f) of this
AD.
Inspection and Repetitive Replacement, if
Necessary
(f) Within 4,500 flight hours or 36 months
after the effective date of this AD, whichever
is first: Inspect zone 120 to determine the
part number of all three angle of attack
(AOA) sensors, in accordance with the
Accomplishment Instructions of Airbus
Service Bulletin A300–34–0176, Revision 01,
dated February 3, 2004. If no Honeywell
AOA sensor having part number (P/N) 965–
4020–007 is found, then no further action is
PO 00000
Frm 00024
Fmt 4702
Sfmt 4702
Parts Installation
Credit for Previously Accomplished Actions
(j) Actions done before the effective date of
this AD in accordance with Airbus Service
Bulletin A300–34–0176, dated July 9, 2003,
are acceptable for compliance with the
corresponding requirements of paragraph (f)
of this AD.
Credit for Optional Terminating Action
(k) Actions done before the effective date
of this AD in accordance with Airbus Service
Bulletin A300–34–092, Revision 2, dated July
18, 1985, are acceptable for compliance with
the requirements of paragraph (g) of this AD.
Alternative Methods of Compliance
(AMOCs)
(l) 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.
E:\FR\FM\08AUP1.SGM
08AUP1
Federal Register / Vol. 70, No. 151 / Monday, August 8, 2005 / Proposed Rules
Related Information
(m) French airworthiness directive F–
2003–457 R1, dated December 22, 2004, also
addresses the subject of this AD.
Issued in Renton, Washington, on August
2, 2005.
Kevin Mullin,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. 05–15593 Filed 8–5–05; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2005–22036; Directorate
Identifier 2005–NM–009–AD]
RIN 2120–AA64
Airworthiness Directives; Airbus Model
A300 B2 and B4 Series Airplanes;
Model A300 B4–600, B4–600R, and F4–
600R Series Airplanes, and Model C4–
605R Variant F Airplanes (Collectively
Called A300–600 Series Airplanes);
and Model A310 Series Airplanes;
Equipped With General Electric CF6–
80A3 or CF6–80C2 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
certain Airbus airplane models, as
specified above. This proposed AD
would require installing electropneumatic locking bar devices (TRAS
lock systems) in the engine nacelles,
installing a dedicated and shielded
electrical circuit that is segregated from
the existing thrust reverser control
system, and performing related
investigative/corrective actions if
necessary. This proposed AD is
prompted by the manufacturer’s
reassessment of the thrust reverser
systems in the Airbus airplane models
specified above, which showed that the
thrust reverser could inadvertently
deploy in flight under certain
conditions. We are proposing this AD to
prevent inadvertent deployment of
thrust reversers in flight, which could
result in reduced controllability of the
airplane.
We must receive comments on
this proposed AD by September 7, 2005.
ADDRESSES: Use one of the following
addresses to submit comments on this
proposed AD.
DATES:
VerDate jul<14>2003
20:26 Aug 05, 2005
Jkt 205001
• DOT Docket Web Site: Go to http:/
/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–
22036; the directorate identifier for this
docket is 2005–NM–009–AD.
FOR FURTHER INFORMATION CONTACT: Tim
Backman, Aerospace Engineer,
International Branch, ANM–116, FAA,
Transport Airplane Directorate, 1601
Lind Avenue, SW., Renton, Washington
98055–4056; telephone (425) 227–2797;
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–
2005–22036; Directorate Identifier
2005–NM–009–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
PO 00000
Frm 00025
Fmt 4702
Sfmt 4702
45595
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 A300 B2
and B4 series airplanes; Model A300
B4–600, B4–600R, and F4–600R series
airplanes, and Model C4–605R Variant F
airplanes (collectively called A300–600
series airplanes); and Model A310 series
airplanes; equipped with General
Electric CF6–80A3 or CF6–80C2
engines. The DGAC advises that the
manufacturer has reassessed the thrust
reverser systems of those airplanes and
has determined that the thrust reverser
could inadvertently deploy in flight.
The manufacturer has developed a new,
improved design of the thrust reversers,
which provides an independent system
to prevent deployment of the thrust
reversers in flight. Inadvertent
deployment of the thrust reversers in
flight could result in reduced
controllability of the airplane.
Relevant Service Information
Airbus has issued the following
service bulletins (SBs), which describe
procedures for installing electropneumatic locking bar devices (TRAS
lock system) and a dedicated and
shielded electrical circuit that is
segregated from the existing thrust
reverser control system. The new
electrical circuit commands the locking
bar devices (TRAS locks), which would
be installed in the engine nacelles.
Implementation of the following SBs is
intended to provide an independent
system to prevent inadvertent
deployment of thrust reversers during
flight.
E:\FR\FM\08AUP1.SGM
08AUP1
Agencies
[Federal Register Volume 70, Number 151 (Monday, August 8, 2005)]
[Proposed Rules]
[Pages 45592-45595]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 05-15593]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2005-22035; Directorate Identifier 2005-NM-016-AD]
RIN 2120-AA64
Airworthiness Directives; Airbus Model A300 B2 and B4 Series
Airplanes
AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).
ACTION: Notice of proposed rulemaking (NPRM).
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SUMMARY: The FAA proposes to adopt a new airworthiness directive (AD)
for all Airbus Model A300 B2 and B4 series airplanes. This proposed AD
would require an inspection to determine the part number of all angle
of attack (AOA) sensors, and repetitive replacement of the AOA sensors
with new or overhauled AOA sensors if necessary. This proposed AD would
also provide an optional terminating action for the repetitive
replacements. This proposed AD is prompted by reports of several false
stall warnings associated with stick-shaker activation, occurring
during take-off. We are proposing this AD to prevent false stall
warnings associated with stick-shaker activation, which could result in
increased pilot workload as the pilot tries to determine the cause of
the stall warning and possible reduction in the pilot's ability to
control the airplane.
DATES: We must receive comments on this proposed AD by September 7,
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.
[[Page 45593]]
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 Backman, Aerospace Engineer,
International Branch, ANM-116, FAA, Transport Airplane Directorate,
1601 Lind Avenue, SW., Renton, Washington 98055-4056; telephone (425)
227-2797; fax (425) 227-1149.
SUPPLEMENTARY INFORMATION:
Comments Invited
We invite you to submit any relevant written data, views, or
arguments regarding this proposed AD. Include the docket number ``FAA-
2005-22035; Directorate Identifier 2005-NM-016-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 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 A300 B2 and B4
series airplanes. The DGAC advises that it has received reports of
several false stall warnings associated with stick-shaker activation,
occurring during take-off. Investigation revealed that defective angle
of attack (AOA) sensors caused the false stall warnings. This
condition, if not corrected, could result in increased pilot workload
as the pilot tries to determine the cause of the stall warning and
possible reduction in the pilot's ability to control the airplane.
Relevant Service Information
Airbus has issued Service Bulletin A300-34-0176, Revision 01, dated
February 3, 2004, which describes the following procedures:
Inspecting zone 120 to determine the part number (P/N) of
all three AOA sensors.
Repetitively replacing any Honeywell AOA sensor having P/N
965-4020-007 with a new or overhauled AOA sensor.
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-
2003-457 R1, dated December 22, 2004, to ensure the continued
airworthiness of these airplanes in France.
Airbus has also issued Service Bulletin A300-34-0092, Revision 03,
dated November 2, 2004. Service Bulletin A300-34-0092 describes the
following procedures:
Replacing Honeywell ``pencil'' AOA sensors having P/N 965-
4020-007 with ``vane'' AOA sensors between frame (FR)18 and FR19.
Replacing the current detectors in relay boxes 252VU and
107VU with new current detectors.
Airbus Service Bulletin A300-34-0092 also specifies that
accomplishing the modification in that service bulletin cancels the
actions specified in Airbus Service Bulletin A300-34-0176.
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, except as discussed under ``Difference Between
the Proposed AD and Service Bulletin.''
Difference Between the Proposed AD and Service Bulletin
Operators should note that, although the Accomplishment
Instructions of the Airbus Service Bulletin A300-34-0176, Revision 01,
dated February 3,2004, describe procedures for reporting inspection
findings, this proposed AD would not require that action. We do not
need this information from operators.
Costs of Compliance
The following table provides the estimated costs for U.S. operators
to comply with this proposed AD.
Estimated Costs
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Number of
Work Average Cost per U.S.-
Action hours labor rate Parts airplane registered Fleet cost
per hour airplanes
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Inspection.................. 1 $65 None........... $65 20 $1,300.
[[Page 45594]]
Replacement if necessary, 2 65 $3,300 ($1,100 3,430 20 $68,600 per
per replacement cycle. per sensor). replacement
cycle.
Optional terminating action. 7 65 $8,780......... 9,235 20 $184,700.
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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. 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-2005-22035; Directorate Identifier 2005-NM-
016-AD.
Comments Due Date
(a) The Federal Aviation Administration must receive comments on
this AD action by September 7, 2005.
Affected ADs
(b) None.
Applicability: (c) This AD applies to all Airbus Model A300 B2-
1A, B2-1C, B2K-3C, and B2-203 airplanes; and Model A300 B4-2C, B4-
103, and B4-203 airplanes; certificated in any category.
Unsafe Condition
(d) This AD was prompted by reports of several false stall
warnings associated with stick-shaker activation, occurring during
take-off. We are issuing this AD to prevent false stall warnings
associated with stick-shaker activation, which could result in
increased pilot workload as the pilot tries to determine the cause
of the stall warning and possible reduction in the pilot's ability
to control 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.
Inspection and Repetitive Replacement, if Necessary
(f) Within 4,500 flight hours or 36 months after the effective
date of this AD, whichever is first: Inspect zone 120 to determine
the part number of all three angle of attack (AOA) sensors, in
accordance with the Accomplishment Instructions of Airbus Service
Bulletin A300-34-0176, Revision 01, dated February 3, 2004. If no
Honeywell AOA sensor having part number (P/N) 965-4020-007 is found,
then no further action is required by this paragraph. If any
Honeywell AOA sensor having P/N 965-4020-007 is found, before
further flight, replace the AOA sensor with a new or overhauled AOA
sensor having P/N 965-4020-007, in accordance with the service
bulletin. Repeat the replacement thereafter at intervals not to
exceed 8,000 flight hours or 96 months, whichever is first.
Accomplishing the actions specified in paragraph (g) of this AD
terminates the repetitive replacements.
Optional Terminating Action
(g) Replacement of all Honeywell AOA sensors having P/N 965-
4020-007 between frame (FR)18 and FR19 with ``vane type'' AOA
sensors; and replacement of the current detectors in relay boxes
252VU and 107VU with new current detectors; in accordance with the
Accomplishment Instructions of Airbus Service Bulletin A300-34-0092,
Revision 03, dated November 2, 2004; terminate the repetitive
replacements required by paragraph (f) of this AD.
No Reporting Requirement
(h) Although Airbus Service Bulletin A300-34-0176, Revision 01,
dated February 3, 2004, specifies to submit certain information to
the manufacturer, this AD does not include that requirement.
Parts Installation
(i) As of the effective date of this AD, no person may install
an AOA sensor having P/N 965-4020-007 on any airplane, unless it is
new or overhauled and is repetitively inspected as required by
paragraph (f) of this AD.
Credit for Previously Accomplished Actions
(j) Actions done before the effective date of this AD in
accordance with Airbus Service Bulletin A300-34-0176, dated July 9,
2003, are acceptable for compliance with the corresponding
requirements of paragraph (f) of this AD.
Credit for Optional Terminating Action
(k) Actions done before the effective date of this AD in
accordance with Airbus Service Bulletin A300-34-092, Revision 2,
dated July 18, 1985, are acceptable for compliance with the
requirements of paragraph (g) of this AD.
Alternative Methods of Compliance (AMOCs)
(l) 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.
[[Page 45595]]
Related Information
(m) French airworthiness directive F-2003-457 R1, dated December
22, 2004, also addresses the subject of this AD.
Issued in Renton, Washington, on August 2, 2005.
Kevin Mullin,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 05-15593 Filed 8-5-05; 8:45 am]
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