Airworthiness Directives; ATR Model ATR42-200, ATR42-300, ATR42-320, ATR42-500, ATR72-101, ATR72-201, ATR72-102, ATR72-202, ATR72-211, ATR72-212, and ATR72-212A Airplanes, 71961-71963 [E8-28163]
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<![CDATA[
Federal Register / Vol. 73, No. 229 / Wednesday, November 26, 2008 / Proposed Rules
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation
safety, Incorporation by reference,
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 AD:
Arkansas Modification Center, Inc.: Docket
No. FAA–2008–1240; Directorate
Identifier 2008–NM–098–AD.
Comments Due Date
(a) We must receive comments by January
12, 2009.
Affected ADs
(b) None.
Applicability
(c) This AD applies to Hawker Beechcraft
Corporation Model BH.125 series 600A
airplanes and Model HS.125 series 700A
airplanes, certificated in any category; as
identified in Hawker Beechcraft Mandatory
Service Bulletin 24–3850, dated January
2008, which have been modified in
accordance with Supplemental Type
Certificate SA2271SW.
Unsafe Condition
(d) This AD results from a report indicating
that a blower motor of the cockpit ventilation
and avionics cooling system seized up and
gave off smoke. We are issuing this AD to
prevent smoke and fumes in the cockpit in
the event that a blower motor seizes and
overheats due to excessive current draw.
jlentini on PROD1PC65 with PROPOSALS
Compliance
(e) Comply with this AD within the
compliance times specified, unless already
done.
17:02 Nov 25, 2008
Jkt 217001
No Submission of Certain Information
(g) Although Hawker Beechcraft Mandatory
Service Bulletin 24–3850, dated January
2008, specifies to submit certain information
to the manufacturer, this AD does not
include that requirement.
Alternative Methods of Compliance
(AMOCs)
(h)(1) The Manager, Special Certification
Office, ASW–190, Rotorcraft Directorate,
FAA, ATTN: Andy Shaw, Aerospace
Engineer, Special Certification Office, ASW–
190, FAA, Southwest Regional Office, 2601
Meacham Boulevard, Fort Worth, Texas
76137; telephone (817) 222–5188; fax (817)
222–5785; has the authority to approve
AMOCs for this AD, if requested using the
procedures found in 14 CFR 39.19.
(2) To request a different method of
compliance or a different compliance time
for this AD, follow the procedures in 14 CFR
39.19. Before using any approved AMOC on
any airplane to which the AMOC applies,
notify your appropriate principal inspector
(PI) in the FAA Flight Standards District
Office (FSDO), or lacking a PI, your local
FSDO.
Issued in Renton, Washington, on
November 16, 2008.
Stephen P. Boyd,
Assistant Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. E8–28168 Filed 11–25–08; 8:45 am]
BILLING CODE 4910–13–P
products listed above. This proposed
AD results from mandatory continuing
airworthiness information (MCAI)
originated by an aviation authority of
another country to identify and correct
an unsafe condition on an aviation
product. The MCAI describes the unsafe
condition as:
[C]hafed wirings were found in the rear
baggage zone, closed [close] to the forward
side of the aft pressure bulkhead, due to
contact with an understructure securing
screw. The concerned wiring harness
includes rudder trim, pitch trim and stick
pusher control wires. Damages on those
wires might lead to the loss of fail safe
criteria for those critical functions.
The unsafe condition is reduced
controllability of the airplane. The
proposed AD would require actions that
are intended to address the unsafe
condition described in the MCAI.
DATES: We must receive comments on
this proposed AD by December 26,
2008.
You may send comments by
any of the following methods:
• Federal eRulemaking Portal: Go to
https://www.regulations.gov. Follow the
instructions for submitting comments.
• Fax: (202) 493–2251.
• Mail: U.S. Department of
Transportation, Docket Operations, M–
30, West Building Ground Floor, Room
W12–140, 1200 New Jersey Avenue, SE.,
Washington, DC 20590.
• Hand Delivery: U.S. Department of
Transportation, Docket Operations, M–
30, West Building Ground Floor, Room
W12–40, 1200 New Jersey Avenue, SE.,
Washington, DC, between 9 a.m. and 5
p.m., Monday through Friday, except
Federal holidays.
ADDRESSES:
Examining the AD Docket
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2008–1237; Directorate
Identifier 2008–NM–125–AD]
Inspection and Rework
(f) Within 600 flight hours or 6 months
after the effective date of this AD, whichever
occurs first, inspect the wiring diagrams
containing the cockpit blowers and compare
with the current airplane configuration, in
accordance with the Accomplishment
Instructions of Hawker Beechcraft Mandatory
Service Bulletin 24–3850, dated January
2008; except as provided by paragraph (g) of
this AD.
(1) If the current airplane configuration
does not match the applicable cockpit blower
wiring diagrams, before further flight, rework
the wiring using a method approved by the
Manager, Special Certification Office, ASW–
190, Rotorcraft Directorate, FAA. For the
VerDate Aug<31>2005
determination to be approved by the
Manager, Special Certification Office, as
required by this paragraph, the Manager’s
approval letter must specifically refer to this
AD.
(2) If the current airplane configuration
matches the applicable cockpit blower wiring
diagrams, before further flight, rework the
wiring in accordance with the
Accomplishment Instructions of Hawker
Beechcraft Mandatory Service Bulletin 24–
3850, dated January 2008.
71961
RIN 2120–AA64
Airworthiness Directives; ATR Model
ATR42–200, ATR42–300, ATR42–320,
ATR42–500, ATR72–101, ATR72–201,
ATR72–102, ATR72–202, ATR72–211,
ATR72–212, and ATR72–212A
Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
SUMMARY: We propose to adopt a new
airworthiness directive (AD) for the
PO 00000
Frm 00014
Fmt 4702
Sfmt 4702
You may examine the AD docket on
the Internet at https://
www.regulations.gov; or in person at the
Docket Operations office between 9 a.m.
and 5 p.m., Monday through Friday,
except Federal holidays. The AD docket
contains this proposed AD, the
regulatory evaluation, any comments
received, and other information. The
street address for the Docket Operations
office (telephone (800) 647–5527) is in
the ADDRESSES section. Comments will
be available in the AD docket shortly
after receipt.
FOR FURTHER INFORMATION CONTACT: Tom
Rodriguez, Aerospace Engineer,
International Branch, ANM–116,
Transport Airplane Directorate, FAA,
1601 Lind Avenue, SW., Renton,
Washington 98057–3356; telephone
(425) 227–1137; fax (425) 227–1149.
SUPPLEMENTARY INFORMATION:
E:\FR\FM\26NOP1.SGM
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71962
Federal Register / Vol. 73, No. 229 / Wednesday, November 26, 2008 / Proposed Rules
Comments Invited
We invite you to send any written
relevant data, views, or arguments about
this proposed AD. Send your comments
to an address listed under the
ADDRESSES section. Include ‘‘Docket No.
FAA–2008–1237; Directorate Identifier
2008–NM–125–AD’’ at the beginning of
your comments. We specifically invite
comments on the overall regulatory,
economic, environmental, and energy
aspects of this proposed AD. We will
consider all comments received by the
closing date and may amend this
proposed AD based on those comments.
We will post all comments we
receive, without change, to https://
www.regulations.gov, including any
personal information you provide. We
will also post a report summarizing each
substantive verbal contact we receive
about this proposed AD.
Discussion
The European Aviation Safety Agency
(EASA), which is the Technical Agent
for the Member States of the European
Community, has issued EASA
Airworthiness Directive 2008–0062,
dated April 1, 2008 (referred to after this
as ‘‘the MCAI’’), to correct an unsafe
condition for the specified products.
The MCAI states:
One ATR operator reported some spurious
‘‘Pitch disconnect’’ warning and ‘‘AIL and R
ELEV’’ Anti-Ice Horn Fault caution
annunciations which precluded the use of
the autopilot.
During the investigation, chafed wirings
were found in the rear baggage zone, closed
[close] to the forward side of the aft pressure
bulkhead, due to contact with an
understructure securing screw. The
concerned wiring harness includes rudder
trim, pitch trim and stick pusher control
wires. Damages on those wires might lead to
the loss of fail safe criteria for those critical
functions.
To address the identified unsafe condition,
this AD mandates a one-time inspection and
a routing modification of the electrical wires
in the bulkhead area.
jlentini on PROD1PC65 with PROPOSALS
The unsafe condition is reduced
controllability of the airplane. The
corrective action also includes
contacting ATR for repair instructions
and doing the repair if any damage
(chafing or contact between bundles of
cables and the airframe structure) is
found during the one-time inspection.
You may obtain further information by
examining the MCAI in the AD docket.
Relevant Service Information
ATR has issued Service Bulletins
ATR42–92–0015, ATR42–92–0018,
ATR72–92–1016, and ATR72–92–1018,
all dated February 11, 2008. The actions
described in this service information are
VerDate Aug<31>2005
17:02 Nov 25, 2008
Jkt 217001
intended to correct the unsafe condition
identified in the MCAI.
FAA’s Determination and Requirements
of This Proposed AD
This product has been approved by
the aviation authority of another
country, and is approved for operation
in the United States. Pursuant to our
bilateral agreement with the State of
Design Authority, we have been notified
of the unsafe condition described in the
MCAI and service information
referenced above. We are proposing this
AD because we evaluated all pertinent
information and determined an unsafe
condition exists and is likely to exist or
develop on other products of the same
type design.
Differences Between This AD and the
MCAI or Service Information
We have reviewed the MCAI and
related service information and, in
general, agree with their substance. But
we might have found it necessary to use
different words from those in the MCAI
to ensure the AD is clear for U.S.
operators and is enforceable. In making
these changes, we do not intend to differ
substantively from the information
provided in the MCAI and related
service information.
We might also have proposed
different actions in this AD from those
in the MCAI in order to follow FAA
policies. Any such differences are
highlighted in a Note within the
proposed AD.
Costs of Compliance
Based on the service information, we
estimate that this proposed AD would
affect about 48 products of U.S. registry.
We also estimate that it would take
about 5 work-hours per product to
comply with the basic requirements of
this proposed AD. The average labor
rate is $80 per work-hour. Required
parts would cost about $131 per
product. Where the service information
lists required parts costs that are
covered under warranty, we have
assumed that there will be no charge for
these costs. As we do not control
warranty coverage for affected parties,
some parties may incur costs higher
than estimated here. Based on these
figures, we estimate the cost of the
proposed AD on U.S. operators to be
$25,488, or $531 per product.
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
PO 00000
Frm 00015
Fmt 4702
Sfmt 4702
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 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 this proposed regulation:
1. Is not a ‘‘significant regulatory
action’’ under Executive Order 12866;
2. Is not a ‘‘significant rule’’ under the
DOT Regulatory Policies and Procedures
(44 FR 11034, February 26, 1979); and
3. Will not have a significant
economic impact, positive or negative,
on a substantial number of small entities
under the criteria of the Regulatory
Flexibility Act.
We prepared a regulatory evaluation
of the estimated costs to comply with
this proposed AD and placed it in the
AD docket.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation
safety, Incorporation by reference,
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 AD:
´
ATR–GIE Avions de Transport Regional
(Formerly Aerospatiale): Docket No.
E:\FR\FM\26NOP1.SGM
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Federal Register / Vol. 73, No. 229 / Wednesday, November 26, 2008 / Proposed Rules
FAA–2008–1237; Directorate Identifier
2008–NM–125–AD.
Comments Due Date
(a) We must receive comments by
December 26, 2008.
Affected ADs
(b) None.
Applicability
(c) This AD applies to the airplanes
identified in paragraphs (c)(1), (c)(2), and
(c)(3) of this AD, certificated in any category.
(1) ATR Model ATR42–200, ATR42–300,
and ATR42–320 airplanes, all serial numbers,
except serial numbers 1 through 107
inclusive, 110 through 112 inclusive, 114,
and 115, and except airplanes on which ATR
Service Bulletin ATR42–92–0018, dated
February 11, 2008, has been incorporated.
(2) ATR Model ATR42–500 airplanes, all
serial numbers, except serial numbers 667
and subsequent, and except airplanes on
which ATR Service Bulletin ATR42–92–
0018, dated February 11, 2008, has been
incorporated.
(3) ATR Model ATR72–101, ATR72–201,
ATR72–102, ATR72–202, ATR72–211,
ATR72–212, and ATR72–212A airplanes, all
serial numbers except serial numbers 756
and subsequent, and except airplanes on
which ATR Service bulletin ATR72–92–
1018, dated February 11, 2008, has been
incorporated.
Subject
(d) Air Transport Association (ATA) of
America Code 24: Electrical Power.
electrical routing in the rear baggage zone in
accordance with the Accomplishment
Instructions of ATR Service Bulletin ATR42–
92–0015 or ATR72–92–1016, both dated
February 11, 2008, as applicable.
(2) If any damage is found during the
inspection required by paragraph (f)(1) of this
AD, do the actions in paragraphs (f)(2)(i) and
(f)(2)(ii) of this AD.
(i) Before further flight contact ATR for
repair instructions, and do the repair.
(ii) Before further flight, modify the
electrical routing and protective sleeve in the
rear cargo compartment at frame 44 in
accordance with the Accomplishment
Instructions of ATR Service Bulletin ATR42–
92–0018 or ATR72–92–1018, both dated
February 11, 2008, as applicable.
(3) If no damage is found during the
inspection required by paragraph (f)(1) of this
AD: Within 5,000 flight hours after the
effective date of this AD, modify the
electrical routing and replace the protective
sleeve in the rear cargo compartment at frame
44 in accordance with the Accomplishment
Instructions of ATR Service Bulletin ATR42–
92–0018 or ATR72–92–1018, both dated
February 11, 2008, as applicable.
FAA AD Differences
Note 1: This AD differs from the MCAI
and/or service information as follows:
(1) Although the MCAI or service
information tells you to submit information
to the manufacturer, such submittal is not
required by this AD.
jlentini on PROD1PC65 with PROPOSALS
Reason
(e) The mandatory continuing
airworthiness information (MCAI) states:
One ATR operator reported some spurious
‘‘Pitch disconnect’’ warning and ‘‘AIL and R
ELEV’’ Anti-Ice Horn Fault caution
annunciations which precluded the use of
the autopilot.
During the investigation, chafed wirings
were found in the rear baggage zone, closed
[close] to the forward side of the aft pressure
bulkhead, due to contact with an
understructure securing screw. The
concerned wiring harness includes rudder
trim, pitch trim and stick pusher control
wires. Damages on those wires might lead to
the loss of fail safe criteria for those critical
functions.
To address the identified unsafe condition,
this AD mandates a one-time inspection and
a routing modification of the electrical wires
in the bulkhead area.
The unsafe condition is reduced
controllability of the airplane. The corrective
action also includes contacting ATR for
repair instructions and doing the repair if any
damage (chafing or contact between bundles
of cables and the airframe structure) is found
during the one-time inspection.
Other FAA AD Provisions
Actions and Compliance
(f) Unless already done, do the following
actions.
(1) Within 550 flight hours after the
effective date of this AD, perform a one-time
detailed inspection for damage of the
(h) Refer to MCAI EASA Airworthiness
Directive 2008–0062, dated April 1, 2008,
and ATR Service Bulletins ATR42–92–0015,
ATR42–92–0018, ATR72–92–1016, and
ATR72–92–1018, all dated February 11,
2008, for related information.
VerDate Aug<31>2005
17:02 Nov 25, 2008
Jkt 217001
(g) The following provisions also apply to
this AD:
(1) Alternative Methods of Compliance
(AMOCs): The Manager, International
Branch, ANM–116, Transport Airplane
Directorate, FAA, has the authority to
approve AMOCs for this AD, if requested
using the procedures found in 14 CFR 39.19.
Send information to ATTN: Tom Rodriguez,
Aerospace Engineer, 1601 Lind Avenue, SW.,
Renton, Washington 98057–3356; telephone
(425) 227–1137; fax (425) 227–1149. Before
using any approved AMOC on any airplane
to which the AMOC applies, notify your
appropriate principal inspector (PI) in the
FAA Flight Standards District Office (FSDO),
or lacking a PI, your local FSDO.
(2) Airworthy Product: For any
requirement in this AD to obtain corrective
actions from a manufacturer or other source,
use these actions if they are FAA-approved.
Corrective actions are considered FAAapproved if they are approved by the State
of Design Authority (or their delegated
agent). You are required to assure the product
is airworthy before it is returned to service.
Related Information
PO 00000
Frm 00016
Fmt 4702
Sfmt 4702
71963
Issued in Renton, Washington, on
November 16, 2008.
Stephen P. Boyd,
Assistant Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. E8–28163 Filed 11–25–08; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2008–1239; Directorate
Identifier 2008–NM–131–AD]
RIN 2120–AA64
Airworthiness Directives; Boeing
Model 747 Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
SUMMARY: We propose to adopt a new
airworthiness directive (AD) for certain
Boeing Model 747 airplanes. This
proposed AD would require repetitive
external surface high frequency eddy
current inspections to detect cracks in
the radius detail of the upper lobe
doubler on both sides of the airplane,
and applicable corrective action. This
proposed AD results from reports of
cracks in the radius detail of the upper
lobe doublers. We are proposing this AD
to detect and correct cracks in the upper
lobe doublers. Such cracks could result
in significant degradation of the fuselage
structure and reduce its ability to carry
flight loads from the vertical stabilizer,
which could adversely affect the
controllability of the airplane.
DATES: We must receive comments on
this proposed AD by January 12, 2009.
ADDRESSES: You may send comments by
any of the following methods:
• Federal eRulemaking Portal: Go to
https://www.regulations.gov. Follow the
instructions for submitting comments.
• Fax: 202–493–2251.
• Mail: U.S. Department of
Transportation, Docket Operations, M–
30, West Building Ground Floor, Room
W12–140, 1200 New Jersey Avenue, SE.,
Washington, DC 20590.
• Hand Delivery: U.S. Department of
Transportation, Docket Operations, M–
30, West Building Ground Floor, Room
W12–140, 1200 New Jersey Avenue, SE.,
Washington, DC 20590, between 9 a.m.
and 5 p.m., Monday through Friday,
except Federal holidays.
For service information identified in
this AD, contact Boeing Commercial
Airplanes, P.O. Box 3707, Seattle,
Washington 98124–2207.
E:\FR\FM\26NOP1.SGM
26NOP1
]]>Agencies
[Federal Register Volume 73, Number 229 (Wednesday, November 26, 2008)]
[Proposed Rules]
[Pages 71961-71963]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E8-28163]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2008-1237; Directorate Identifier 2008-NM-125-AD]
RIN 2120-AA64
Airworthiness Directives; ATR Model ATR42-200, ATR42-300, ATR42-
320, ATR42-500, ATR72-101, ATR72-201, ATR72-102, ATR72-202, ATR72-211,
ATR72-212, and ATR72-212A Airplanes
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking (NPRM).
-----------------------------------------------------------------------
SUMMARY: We propose to adopt a new airworthiness directive (AD) for the
products listed above. This proposed AD results from mandatory
continuing airworthiness information (MCAI) originated by an aviation
authority of another country to identify and correct an unsafe
condition on an aviation product. The MCAI describes the unsafe
condition as:
[C]hafed wirings were found in the rear baggage zone, closed [close]
to the forward side of the aft pressure bulkhead, due to contact
with an understructure securing screw. The concerned wiring harness
includes rudder trim, pitch trim and stick pusher control wires.
Damages on those wires might lead to the loss of fail safe criteria
for those critical functions.
The unsafe condition is reduced controllability of the airplane.
The proposed AD would require actions that are intended to address the
unsafe condition described in the MCAI.
DATES: We must receive comments on this proposed AD by December 26,
2008.
ADDRESSES: You may send comments by any of the following methods:
Federal eRulemaking Portal: Go to https://
www.regulations.gov. Follow the instructions for submitting comments.
Fax: (202) 493-2251.
Mail: U.S. Department of Transportation, Docket
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New
Jersey Avenue, SE., Washington, DC 20590.
Hand Delivery: U.S. Department of Transportation, Docket
Operations, M-30, West Building Ground Floor, Room W12-40, 1200 New
Jersey Avenue, SE., Washington, DC, between 9 a.m. and 5 p.m., Monday
through Friday, except Federal holidays.
Examining the AD Docket
You may examine the AD docket on the Internet at https://
www.regulations.gov; or in person at the Docket Operations office
between 9 a.m. and 5 p.m., Monday through Friday, except Federal
holidays. The AD docket contains this proposed AD, the regulatory
evaluation, any comments received, and other information. The street
address for the Docket Operations office (telephone (800) 647-5527) is
in the ADDRESSES section. Comments will be available in the AD docket
shortly after receipt.
FOR FURTHER INFORMATION CONTACT: Tom Rodriguez, Aerospace Engineer,
International Branch, ANM-116, Transport Airplane Directorate, FAA,
1601 Lind Avenue, SW., Renton, Washington 98057-3356; telephone (425)
227-1137; fax (425) 227-1149.
SUPPLEMENTARY INFORMATION:
[[Page 71962]]
Comments Invited
We invite you to send any written relevant data, views, or
arguments about this proposed AD. Send your comments to an address
listed under the ADDRESSES section. Include ``Docket No. FAA-2008-1237;
Directorate Identifier 2008-NM-125-AD'' at the beginning of your
comments. We specifically invite comments on the overall regulatory,
economic, environmental, and energy aspects of this proposed AD. We
will consider all comments received by the closing date and may amend
this proposed AD based on those comments.
We will post all comments we receive, without change, to https://
www.regulations.gov, including any personal information you provide. We
will also post a report summarizing each substantive verbal contact we
receive about this proposed AD.
Discussion
The European Aviation Safety Agency (EASA), which is the Technical
Agent for the Member States of the European Community, has issued EASA
Airworthiness Directive 2008-0062, dated April 1, 2008 (referred to
after this as ``the MCAI''), to correct an unsafe condition for the
specified products. The MCAI states:
One ATR operator reported some spurious ``Pitch disconnect''
warning and ``AIL and R ELEV'' Anti-Ice Horn Fault caution
annunciations which precluded the use of the autopilot.
During the investigation, chafed wirings were found in the rear
baggage zone, closed [close] to the forward side of the aft pressure
bulkhead, due to contact with an understructure securing screw. The
concerned wiring harness includes rudder trim, pitch trim and stick
pusher control wires. Damages on those wires might lead to the loss
of fail safe criteria for those critical functions.
To address the identified unsafe condition, this AD mandates a
one-time inspection and a routing modification of the electrical
wires in the bulkhead area.
The unsafe condition is reduced controllability of the airplane.
The corrective action also includes contacting ATR for repair
instructions and doing the repair if any damage (chafing or contact
between bundles of cables and the airframe structure) is found during
the one-time inspection. You may obtain further information by
examining the MCAI in the AD docket.
Relevant Service Information
ATR has issued Service Bulletins ATR42-92-0015, ATR42-92-0018,
ATR72-92-1016, and ATR72-92-1018, all dated February 11, 2008. The
actions described in this service information are intended to correct
the unsafe condition identified in the MCAI.
FAA's Determination and Requirements of This Proposed AD
This product has been approved by the aviation authority of another
country, and is approved for operation in the United States. Pursuant
to our bilateral agreement with the State of Design Authority, we have
been notified of the unsafe condition described in the MCAI and service
information referenced above. We are proposing this AD because we
evaluated all pertinent information and determined an unsafe condition
exists and is likely to exist or develop on other products of the same
type design.
Differences Between This AD and the MCAI or Service Information
We have reviewed the MCAI and related service information and, in
general, agree with their substance. But we might have found it
necessary to use different words from those in the MCAI to ensure the
AD is clear for U.S. operators and is enforceable. In making these
changes, we do not intend to differ substantively from the information
provided in the MCAI and related service information.
We might also have proposed different actions in this AD from those
in the MCAI in order to follow FAA policies. Any such differences are
highlighted in a Note within the proposed AD.
Costs of Compliance
Based on the service information, we estimate that this proposed AD
would affect about 48 products of U.S. registry. We also estimate that
it would take about 5 work-hours per product to comply with the basic
requirements of this proposed AD. The average labor rate is $80 per
work-hour. Required parts would cost about $131 per product. Where the
service information lists required parts costs that are covered under
warranty, we have assumed that there will be no charge for these costs.
As we do not control warranty coverage for affected parties, some
parties may incur costs higher than estimated here. Based on these
figures, we estimate the cost of the proposed AD on U.S. operators to
be $25,488, or $531 per product.
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 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 this proposed
regulation:
1. Is not a ``significant regulatory action'' under Executive Order
12866;
2. Is not a ``significant rule'' under the DOT Regulatory Policies
and Procedures (44 FR 11034, February 26, 1979); and
3. Will not have a significant economic impact, positive or
negative, on a substantial number of small entities under the criteria
of the Regulatory Flexibility Act.
We prepared a regulatory evaluation of the estimated costs to
comply with this proposed AD and placed it in the AD docket.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by
reference, 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 AD:
ATR-GIE Avions de Transport R[eacute]gional (Formerly Aerospatiale):
Docket No.
[[Page 71963]]
FAA-2008-1237; Directorate Identifier 2008-NM-125-AD.
Comments Due Date
(a) We must receive comments by December 26, 2008.
Affected ADs
(b) None.
Applicability
(c) This AD applies to the airplanes identified in paragraphs
(c)(1), (c)(2), and (c)(3) of this AD, certificated in any category.
(1) ATR Model ATR42-200, ATR42-300, and ATR42-320 airplanes, all
serial numbers, except serial numbers 1 through 107 inclusive, 110
through 112 inclusive, 114, and 115, and except airplanes on which
ATR Service Bulletin ATR42-92-0018, dated February 11, 2008, has
been incorporated.
(2) ATR Model ATR42-500 airplanes, all serial numbers, except
serial numbers 667 and subsequent, and except airplanes on which ATR
Service Bulletin ATR42-92-0018, dated February 11, 2008, has been
incorporated.
(3) ATR Model ATR72-101, ATR72-201, ATR72-102, ATR72-202, ATR72-
211, ATR72-212, and ATR72-212A airplanes, all serial numbers except
serial numbers 756 and subsequent, and except airplanes on which ATR
Service bulletin ATR72-92-1018, dated February 11, 2008, has been
incorporated.
Subject
(d) Air Transport Association (ATA) of America Code 24:
Electrical Power.
Reason
(e) The mandatory continuing airworthiness information (MCAI)
states:
One ATR operator reported some spurious ``Pitch disconnect''
warning and ``AIL and R ELEV'' Anti-Ice Horn Fault caution
annunciations which precluded the use of the autopilot.
During the investigation, chafed wirings were found in the rear
baggage zone, closed [close] to the forward side of the aft pressure
bulkhead, due to contact with an understructure securing screw. The
concerned wiring harness includes rudder trim, pitch trim and stick
pusher control wires. Damages on those wires might lead to the loss
of fail safe criteria for those critical functions.
To address the identified unsafe condition, this AD mandates a
one-time inspection and a routing modification of the electrical
wires in the bulkhead area.
The unsafe condition is reduced controllability of the airplane.
The corrective action also includes contacting ATR for repair
instructions and doing the repair if any damage (chafing or contact
between bundles of cables and the airframe structure) is found
during the one-time inspection.
Actions and Compliance
(f) Unless already done, do the following actions.
(1) Within 550 flight hours after the effective date of this AD,
perform a one-time detailed inspection for damage of the electrical
routing in the rear baggage zone in accordance with the
Accomplishment Instructions of ATR Service Bulletin ATR42-92-0015 or
ATR72-92-1016, both dated February 11, 2008, as applicable.
(2) If any damage is found during the inspection required by
paragraph (f)(1) of this AD, do the actions in paragraphs (f)(2)(i)
and (f)(2)(ii) of this AD.
(i) Before further flight contact ATR for repair instructions,
and do the repair.
(ii) Before further flight, modify the electrical routing and
protective sleeve in the rear cargo compartment at frame 44 in
accordance with the Accomplishment Instructions of ATR Service
Bulletin ATR42-92-0018 or ATR72-92-1018, both dated February 11,
2008, as applicable.
(3) If no damage is found during the inspection required by
paragraph (f)(1) of this AD: Within 5,000 flight hours after the
effective date of this AD, modify the electrical routing and replace
the protective sleeve in the rear cargo compartment at frame 44 in
accordance with the Accomplishment Instructions of ATR Service
Bulletin ATR42-92-0018 or ATR72-92-1018, both dated February 11,
2008, as applicable.
FAA AD Differences
Note 1: This AD differs from the MCAI and/or service information
as follows:
(1) Although the MCAI or service information tells you to submit
information to the manufacturer, such submittal is not required by
this AD.
Other FAA AD Provisions
(g) The following provisions also apply to this AD:
(1) Alternative Methods of Compliance (AMOCs): The Manager,
International Branch, ANM-116, Transport Airplane Directorate, FAA,
has the authority to approve AMOCs for this AD, if requested using
the procedures found in 14 CFR 39.19. Send information to ATTN: Tom
Rodriguez, Aerospace Engineer, 1601 Lind Avenue, SW., Renton,
Washington 98057-3356; telephone (425) 227-1137; fax (425) 227-1149.
Before using any approved AMOC on any airplane to which the AMOC
applies, notify your appropriate principal inspector (PI) in the FAA
Flight Standards District Office (FSDO), or lacking a PI, your local
FSDO.
(2) Airworthy Product: For any requirement in this AD to obtain
corrective actions from a manufacturer or other source, use these
actions if they are FAA-approved. Corrective actions are considered
FAA-approved if they are approved by the State of Design Authority
(or their delegated agent). You are required to assure the product
is airworthy before it is returned to service.
Related Information
(h) Refer to MCAI EASA Airworthiness Directive 2008-0062, dated
April 1, 2008, and ATR Service Bulletins ATR42-92-0015, ATR42-92-
0018, ATR72-92-1016, and ATR72-92-1018, all dated February 11, 2008,
for related information.
Issued in Renton, Washington, on November 16, 2008.
Stephen P. Boyd,
Assistant Manager, Transport Airplane Directorate, Aircraft
Certification Service.
[FR Doc. E8-28163 Filed 11-25-08; 8:45 am]
BILLING CODE 4910-13-P
