Airworthiness Directives; AEROTECHNIC Vertriebs-u. Service GmbH Honeywell CAS67A ACAS II Systems Appliances, 20780-20782 [E7-7993]
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20780
Federal Register / Vol. 72, No. 80 / Thursday April 26, 2007 / Proposed Rules
Issued in Renton, Washington, on April 19,
2007.
Ali Bahrami,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. E7–7979 Filed 4–25–07; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2007–27680; Directorate
Identifier 2007–CE–026–AD]
RIN 2120–AA64
Airworthiness Directives;
AEROTECHNIC Vertriebs-u. Service
GmbH Honeywell CAS67A ACAS II
Systems Appliances
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
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:
jlentini on PROD1PC65 with PROPOSALS
It was detected by the STC holder that in
earlier installations of the ACASII system
there were no isolation diodes installed in
the Heading and Attitude Valid lines. The
absence of an isolation diode in the valid
lines can prevent the valid flag to come up
even if a gyro fault exists. The problem has
only been detected for Heading Valid lines
but could equally affect the Altitude Valid
lines.
With installation of the ACASII, the
heading and attitude valid lines have to be
connected to the TPU67A. On valid state, the
signals are +28VDC. On invalid, the signals
are open. This condition of direct connection
(without an isolation diode installed) of the
valid lines to the TPU67A, if not corrected,
could cause the TPU67A to feed current into
the open stated valid lines. This prevents the
flag to appear even if the gyro is invalid,
providing the flight crew with erroneous
navigation information.
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 May 29, 2007.
ADDRESSES: You may send comments by
any of the following methods:
• DOT Docket Web Site: Go to https://
dms.dot.gov and follow the instructions
VerDate Aug<31>2005
21:14 Apr 25, 2007
Jkt 211001
for sending your comments
electronically.
• Fax: (202) 493–2251.
• Mail: Docket Management Facility,
U.S. Department of Transportation, 400
Seventh Street, SW., Nassif Building,
Room PL–401, Washington, DC 20590–
0001.
• 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.
• Federal eRulemaking Portal: Go to
https://www.regulations.gov. Follow the
instructions for submitting comments.
Examining the AD Docket
You may examine the AD docket on
the Internet at https://dms.dot.gov; or in
person at the Docket Management
Facility 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 Office (telephone (800) 647–
5227) is in the ADDRESSES section.
Comments will be available in the AD
docket shortly after receipt.
FOR FURTHER INFORMATION CONTACT: Karl
Schletzbaum, Aerospace Engineer, FAA,
Small Airplane Directorate, 901 Locust,
Room 301, Kansas City, Missouri 64106;
telephone: (816) 329–4146; fax: (816)
329–4090.
SUPPLEMENTARY INFORMATION:
Streamlined Issuance of AD
The FAA is implementing a new
process for streamlining the issuance of
ADs related to MCAI. This streamlined
process will allow us to adopt MCAI
safety requirements in a more efficient
manner and will reduce safety risks to
the public. This process continues to
follow all FAA AD issuance processes to
meet legal, economic, Administrative
Procedure Act, and Federal Register
requirements. We also continue to meet
our technical decision-making
responsibilities to identify and correct
unsafe conditions on U.S.-certificated
products.
This proposed AD references the
MCAI and related service information
that we considered in forming the
engineering basis to correct the unsafe
condition. The proposed AD contains
text copied from the MCAI and for this
reason might not follow our plain
language principles.
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
PO 00000
Frm 00007
Fmt 4702
Sfmt 4702
section. Include ‘‘Docket No.
FAA–2007–27680; Directorate Identifier
2007–CE–026–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 because 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 we receive
about this proposed AD.
ADDRESSES
Discussion
The European Aviation Safety Agency
(EASA), which is the Technical Agent
for the Member States of the European
Community, has issued EASA AD No.
2007–0059 dated March 5, 2007
(referred to after this as ‘‘the MCAI’’), to
correct an unsafe condition for the
specified products.
The MCAI states:
It was detected by the STC holder that in
earlier installations of the ACASII system
there were no isolation diodes installed in
the Heading and Attitude Valid lines. The
absence of an isolation diode in the valid
lines can prevent the valid flag to come up
even if a gyro fault exists. The problem has
only been detected for Heading Valid lines
but could equally affect the Attitude Valid
lines.
With installation of the ACASII, the
heading and attitude valid lines have to be
connected to the TPU67A. On valid state, the
signals are +28VDC. On invalid, the signals
are open. This condition of direct connection
(without an isolation diode installed) of the
valid lines to the TPU67A, if not corrected,
could cause the TPU67A to feed current into
the open stated valid lines. This prevents the
flag to appear even if the gyro is invalid,
providing the flight crew with erroneous
navigation information.
For the reasons stated above, this
Airworthiness Directive (AD) requires the
installation of isolation diodes into the signal
lines to the TPU67A to prevent reverse feed
of the valid lines.
You may obtain further information
by examining the MCAI in the AD
docket.
Relevant Service Information
Aerotechnic Vertiebs -u. Service
GmbH has issued Service Bulletin No.
DO228–119780–0104, Revision 2, dated
December 21, 2006. The actions
described in this service information are
intended to correct the unsafe condition
identified in the MCAI.
E:\FR\FM\26APP1.SGM
26APP1
Federal Register / Vol. 72, No. 80 / Thursday April 26, 2007 / Proposed Rules
FAA’s Determination and Requirements
of the 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 this State of
Design Authority, they have notified us
of the unsafe condition described in the
MCAI and service information
referenced above. We are proposing this
AD because we evaluated all
information and determined the unsafe
condition exists and is likely to exist or
develop on other products of the same
type design.
Differences Between This Proposed 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.
jlentini on PROD1PC65 with PROPOSALS
Costs of Compliance
The FAA is not aware of any airplanes
on the U.S. Registry that have the
affected equipment installed. All
airplanes with this equipment included
in the applicability of this rule currently
are operated by non-U.S. operators
under foreign registry; therefore, they
are not directly affected by this AD
action at this time. However, the FAA
considers this rule necessary to ensure
that the unsafe condition is addressed in
the event that any of these subject
airplanes are imported and placed on
the U.S. Registry.
Should an affected airplane be
imported and placed on the U.S.
Registry, accomplishment of the
required action would take
approximately 8 work-hours at an
average labor rate of $80 per work-hour.
Required parts would cost about $50 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.
VerDate Aug<31>2005
21:14 Apr 25, 2007
Jkt 211001
Based on these figures, the total cost
impact of this AD would be $690 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 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, 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:
PO 00000
Frm 00008
Fmt 4702
Sfmt 4702
20781
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:
AEROTECHNIC Vertriebs-u. Service GmbH:
Docket No. FAA–2007–27680;
Directorate Identifier 2007–CE–026–AD.
Comments Due Date
(a) We must receive comments by May 29,
2007.
Affected ADs
(b) None.
Applicability
(c) This AD applies to Honeywell CAS67A
ACAS II systems that are installed on, but not
limited to, DORNIER LUFTFAHRT GmbH
Models Dornier 228–100, Dornier 228–101,
Dornier 228–200, Dornier 228–201, and
Dornier 228–212 airplanes that:
(1) Had Supplemental Type Certificate No.
SA1310 installed prior to January 31, 2005;
and
(2) Are certificated in any category.
Subject
(d) Air Transport Association of America
(ATA) Code 34: Navigation.
Reason
(e) The mandatory continuing
airworthiness information (MCAI) states:
It was detected by the STC holder that in
earlier installations of the ACAS II system
there were no isolation diodes installed in
the Heading and Attitude Valid lines. The
absence of an isolation diode in the valid
lines can prevent the valid flag to come up
even if a gyro fault exists. The problem has
only been detected for Heading Valid lines
but could equally affect the Attitude Valid
lines.
With installation of the ACAS II, the
heading and attitude valid lines have to be
connected to the TPU67A. On valid state, the
signals are +28VDC. On invalid, the signals
are open. This condition of direct connection
(without an isolation diode installed) of the
valid lines to the TPU67A, if not corrected,
could cause the TPU67A to feed current into
the open stated valid lines. This prevents the
flag to appear even if the gyro is invalid,
providing the flight crew with erroneous
navigation information.
For the reasons stated above, this
Airworthiness Directive (AD) requires the
installation of isolation diodes into the signal
lines to the TPU67A to prevent reverse feed
of the valid lines.
Actions and Compliance
(f) Unless already done, within 100 flight
hours time-in-service (TIS) after the effective
date of this AD, modify the Honeywell
CAS67A ACAS II System Installation
following Aerotechnic Service Bulletin No.
DO228–119780–0104, Revision 2, dated
December 21, 2006.
E:\FR\FM\26APP1.SGM
26APP1
20782
Federal Register / Vol. 72, No. 80 / Thursday April 26, 2007 / Proposed Rules
FAA AD Differences
Other FAA AD Provisions
(g) The following provisions also apply to
this AD:
(1) Alternative Methods of Compliance
(AMOCs): The Manager, Standards Staff,
FAA, ATTN: Karl Schletzbaum, Aerospace
Engineer, FAA, Small Airplane Directorate,
901 Locust, Room 301, Kansas City, Missouri
64106; telephone: (816) 329–4146; fax: (816)
329–4090, has the authority to approve
AMOCs for this AD, if requested using the
procedures found 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.
(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.
(3) Reporting Requirements: For any
reporting requirement in this AD, under the
provisions of the Paperwork Reduction Act
(44 U.S.C. 3501 et seq.), the Office of
Management and Budget (OMB) has
approved the information collection
requirements and has assigned OMB Control
Number 2120–0056.
Related Information
(h) Refer to MCAI European Aviation
Safety Agency (EASA) AD No. 2007–0059,
dated March 5, 2007; and Service Bulletin
No. DO228–119780–0104 Revision 2, dated
December 21, 2006, for related information.
Issued in Kansas City, Missouri, on April
20, 2007.
Charles L. Smalley,
Acting Manager, Small Airplane Directorate,
Aircraft Certification Service.
[FR Doc. E7–7993 Filed 4–25–07; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2007–28015; Directorate
Identifier 2006–NM–210–AD]
jlentini on PROD1PC65 with PROPOSALS
RIN 2120–AA64
Airworthiness Directives; Boeing
Model 747–100, 747–100B, 747–100B
SUD, 747–200B, 747–200C, 747–300,
747–400, 747–400D, and 747SR Series
Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
AGENCY:
VerDate Aug<31>2005
21:14 Apr 25, 2007
Notice of proposed rulemaking
(NPRM).
ACTION:
Note: This AD differs from the MCAI and/
or service information as follows: No
differences.
Jkt 211001
SUMMARY: The FAA proposes to
supersede an existing airworthiness
directive (AD) that applies to all Boeing
Model 747–100, 747–100B, 747–100B
SUD, 747–200B, 747–200C, 747–300,
747–400, 747–400D, and 747SR series
airplanes. The existing AD currently
requires repetitive inspections for
cracking of the station 800 frame
assembly, and repair if necessary. This
proposed AD would revise certain
applicabilities and compliance times in
the existing AD. This proposed AD
results from several reports of cracks of
the station 800 frame assembly on
airplanes that had accumulated fewer
total flight cycles than the initial
inspection threshold in the original AD.
We are proposing this AD to detect and
correct fatigue cracks that could extend
and fully sever the frame, which could
result in development of skin cracks
that could lead to rapid
depressurization of the airplane.
DATES: We must receive comments on
this proposed AD by June 11, 2007.
ADDRESSES: Use one of the following
addresses to submit comments on this
proposed AD.
• DOT Docket Web site: Go to
https://dms.dot.gov and follow the
instructions for sending your comments
electronically.
• Government-wide rulemaking Web
site: Go to https://www.regulations.gov
and follow the instructions for sending
your comments electronically.
• Mail: Docket Management Facility;
U.S. Department of Transportation, 400
Seventh Street, SW., Nassif Building,
Room PL–401, Washington, DC 20590.
• Fax: (202) 493–2251.
• Hand Delivery: Room PL–401 on
the plaza level of the Nassif Building,
400 Seventh Street, SW., Washington,
DC, between 9 a.m. and 5 p.m., Monday
through Friday, except Federal holidays.
Contact Boeing Commercial
Airplanes, P.O. Box 3707, Seattle,
Washington 98124–2207, for service
information identified in this proposed
AD.
FOR FURTHER INFORMATION CONTACT: Ivan
Li, Aerospace Engineer, Airframe
Branch, ANM–120S, FAA, Seattle
Aircraft Certification Office, 1601 Lind
Avenue, SW., Renton, Washington
98057–3356; telephone (425) 917–6437;
fax (425) 917–6590.
SUPPLEMENTARY INFORMATION:
Comments Invited
We invite you to submit any relevant
written data, views, or arguments
regarding this proposed AD. Send your
PO 00000
Frm 00009
Fmt 4702
Sfmt 4702
comments to an address listed in the
section. Include the docket
number ‘‘Docket No. FAA–2007–28015;
Directorate Identifier 2006–NM–210–
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 may can visit https://
dms.dot.gov.
ADDRESSES
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
On May 31, 2006, we issued AD
2006–12–12, amendment 39–14638 (71
FR 33595, June 12, 2006), for all Boeing
Model 747–100, 747–100B, 747–100B
SUD, 747–200B, 747–200C, 747–300,
747–400, 747–400D, and 747SR series
airplanes. That AD requires repetitive
inspections for cracking of the station
800 frame assembly, and repair if
necessary. That AD resulted from
several reports of cracks of the station
800 frame assembly on airplanes that
had accumulated fewer total flight
cycles than the initial inspection
threshold in an existing AD that AD
2006–12–12 superseded. We issued AD
2006–12–12 to detect and correct fatigue
cracks that could extend and fully sever
the frame, which could result in
development of skin cracks that could
E:\FR\FM\26APP1.SGM
26APP1
]]>Agencies
[Federal Register Volume 72, Number 80 (Thursday, April 26, 2007)]
[Proposed Rules]
[Pages 20780-20782]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E7-7993]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2007-27680; Directorate Identifier 2007-CE-026-AD]
RIN 2120-AA64
Airworthiness Directives; AEROTECHNIC Vertriebs-u. Service GmbH
Honeywell CAS67A ACAS II Systems Appliances
AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (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:
It was detected by the STC holder that in earlier installations
of the ACASII system there were no isolation diodes installed in the
Heading and Attitude Valid lines. The absence of an isolation diode
in the valid lines can prevent the valid flag to come up even if a
gyro fault exists. The problem has only been detected for Heading
Valid lines but could equally affect the Altitude Valid lines.
With installation of the ACASII, the heading and attitude valid
lines have to be connected to the TPU67A. On valid state, the
signals are +28VDC. On invalid, the signals are open. This condition
of direct connection (without an isolation diode installed) of the
valid lines to the TPU67A, if not corrected, could cause the TPU67A
to feed current into the open stated valid lines. This prevents the
flag to appear even if the gyro is invalid, providing the flight
crew with erroneous navigation information.
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 May 29, 2007.
ADDRESSES: You may send comments by any of the following methods:
DOT Docket Web Site: Go to https://dms.dot.gov and follow
the instructions for sending your comments electronically.
Fax: (202) 493-2251.
Mail: Docket Management Facility, U.S. Department of
Transportation, 400 Seventh Street, SW., Nassif Building, Room PL-401,
Washington, DC 20590-0001.
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.
Federal eRulemaking Portal: Go to https://
www.regulations.gov. Follow the instructions for submitting comments.
Examining the AD Docket
You may examine the AD docket on the Internet at https://
dms.dot.gov; or in person at the Docket Management Facility 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 Office (telephone (800) 647-5227) is in the ADDRESSES section.
Comments will be available in the AD docket shortly after receipt.
FOR FURTHER INFORMATION CONTACT: Karl Schletzbaum, Aerospace Engineer,
FAA, Small Airplane Directorate, 901 Locust, Room 301, Kansas City,
Missouri 64106; telephone: (816) 329-4146; fax: (816) 329-4090.
SUPPLEMENTARY INFORMATION:
Streamlined Issuance of AD
The FAA is implementing a new process for streamlining the issuance
of ADs related to MCAI. This streamlined process will allow us to adopt
MCAI safety requirements in a more efficient manner and will reduce
safety risks to the public. This process continues to follow all FAA AD
issuance processes to meet legal, economic, Administrative Procedure
Act, and Federal Register requirements. We also continue to meet our
technical decision-making responsibilities to identify and correct
unsafe conditions on U.S.-certificated products.
This proposed AD references the MCAI and related service
information that we considered in forming the engineering basis to
correct the unsafe condition. The proposed AD contains text copied from
the MCAI and for this reason might not follow our plain language
principles.
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-2007-
27680; Directorate Identifier 2007-CE-026-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 because 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 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
AD No. 2007-0059 dated March 5, 2007 (referred to after this as ``the
MCAI''), to correct an unsafe condition for the specified products.
The MCAI states:
It was detected by the STC holder that in earlier installations
of the ACASII system there were no isolation diodes installed in the
Heading and Attitude Valid lines. The absence of an isolation diode
in the valid lines can prevent the valid flag to come up even if a
gyro fault exists. The problem has only been detected for Heading
Valid lines but could equally affect the Attitude Valid lines.
With installation of the ACASII, the heading and attitude valid
lines have to be connected to the TPU67A. On valid state, the
signals are +28VDC. On invalid, the signals are open. This condition
of direct connection (without an isolation diode installed) of the
valid lines to the TPU67A, if not corrected, could cause the TPU67A
to feed current into the open stated valid lines. This prevents the
flag to appear even if the gyro is invalid, providing the flight
crew with erroneous navigation information.
For the reasons stated above, this Airworthiness Directive (AD)
requires the installation of isolation diodes into the signal lines
to the TPU67A to prevent reverse feed of the valid lines.
You may obtain further information by examining the MCAI in the AD
docket.
Relevant Service Information
Aerotechnic Vertiebs -u. Service GmbH has issued Service Bulletin
No. DO228-119780-0104, Revision 2, dated December 21, 2006. The actions
described in this service information are intended to correct the
unsafe condition identified in the MCAI.
[[Page 20781]]
FAA's Determination and Requirements of the 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 this State of Design Authority, they
have notified us of the unsafe condition described in the MCAI and
service information referenced above. We are proposing this AD because
we evaluated all information and determined the unsafe condition exists
and is likely to exist or develop on other products of the same type
design.
Differences Between This Proposed 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
The FAA is not aware of any airplanes on the U.S. Registry that
have the affected equipment installed. All airplanes with this
equipment included in the applicability of this rule currently are
operated by non-U.S. operators under foreign registry; therefore, they
are not directly affected by this AD action at this time. However, the
FAA considers this rule necessary to ensure that the unsafe condition
is addressed in the event that any of these subject airplanes are
imported and placed on the U.S. Registry.
Should an affected airplane be imported and placed on the U.S.
Registry, accomplishment of the required action would take
approximately 8 work-hours at an average labor rate of $80 per work-
hour. Required parts would cost about $50 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, the total cost impact of this AD would be
$690 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 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, 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:
AEROTECHNIC Vertriebs-u. Service GmbH: Docket No. FAA-2007-27680;
Directorate Identifier 2007-CE-026-AD.
Comments Due Date
(a) We must receive comments by May 29, 2007.
Affected ADs
(b) None.
Applicability
(c) This AD applies to Honeywell CAS67A ACAS II systems that are
installed on, but not limited to, DORNIER LUFTFAHRT GmbH Models
Dornier 228-100, Dornier 228-101, Dornier 228-200, Dornier 228-201,
and Dornier 228-212 airplanes that:
(1) Had Supplemental Type Certificate No. SA1310 installed prior
to January 31, 2005; and
(2) Are certificated in any category.
Subject
(d) Air Transport Association of America (ATA) Code 34:
Navigation.
Reason
(e) The mandatory continuing airworthiness information (MCAI)
states:
It was detected by the STC holder that in earlier installations
of the ACAS II system there were no isolation diodes installed in
the Heading and Attitude Valid lines. The absence of an isolation
diode in the valid lines can prevent the valid flag to come up even
if a gyro fault exists. The problem has only been detected for
Heading Valid lines but could equally affect the Attitude Valid
lines.
With installation of the ACAS II, the heading and attitude valid
lines have to be connected to the TPU67A. On valid state, the
signals are +28VDC. On invalid, the signals are open. This condition
of direct connection (without an isolation diode installed) of the
valid lines to the TPU67A, if not corrected, could cause the TPU67A
to feed current into the open stated valid lines. This prevents the
flag to appear even if the gyro is invalid, providing the flight
crew with erroneous navigation information.
For the reasons stated above, this Airworthiness Directive (AD)
requires the installation of isolation diodes into the signal lines
to the TPU67A to prevent reverse feed of the valid lines.
Actions and Compliance
(f) Unless already done, within 100 flight hours time-in-service
(TIS) after the effective date of this AD, modify the Honeywell
CAS67A ACAS II System Installation following Aerotechnic Service
Bulletin No. DO228-119780-0104, Revision 2, dated December 21, 2006.
[[Page 20782]]
FAA AD Differences
Note: This AD differs from the MCAI and/or service information
as follows: No differences.
Other FAA AD Provisions
(g) The following provisions also apply to this AD:
(1) Alternative Methods of Compliance (AMOCs): The Manager,
Standards Staff, FAA, ATTN: Karl Schletzbaum, Aerospace Engineer,
FAA, Small Airplane Directorate, 901 Locust, Room 301, Kansas City,
Missouri 64106; telephone: (816) 329-4146; fax: (816) 329-4090, has
the authority to approve AMOCs for this AD, if requested using the
procedures found 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.
(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.
(3) Reporting Requirements: For any reporting requirement in
this AD, under the provisions of the Paperwork Reduction Act (44
U.S.C. 3501 et seq.), the Office of Management and Budget (OMB) has
approved the information collection requirements and has assigned
OMB Control Number 2120-0056.
Related Information
(h) Refer to MCAI European Aviation Safety Agency (EASA) AD No.
2007-0059, dated March 5, 2007; and Service Bulletin No. DO228-
119780-0104 Revision 2, dated December 21, 2006, for related
information.
Issued in Kansas City, Missouri, on April 20, 2007.
Charles L. Smalley,
Acting Manager, Small Airplane Directorate, Aircraft Certification
Service.
[FR Doc. E7-7993 Filed 4-25-07; 8:45 am]
BILLING CODE 4910-13-P
