[Federal Register: June 30, 2003 (Volume 68, Number 125)]
[Rules and Regulations]
[Page 38586-38588]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr30jn03-2]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 2003-CE-25-AD; Amendment 39-13208; AD 2003-13-08]
RIN 2120-AA64
Airworthiness Directives; Goodrich Avionics Systems, Inc.
TAWS8000 Terrain Awareness Warning System
AGENCY: Federal Aviation Administration, DOT.
ACTION: Final rule; request for comments.
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SUMMARY: This amendment adopts a new airworthiness directive (AD) that
applies to all Goodrich Avionics Systems, Inc. (Goodrich) TAWS8000
terrain awareness warning systems (TAWS) that are installed on
airplanes. This AD requires you to inspect the TAWS installation and
remove any TAWS where both the TAWS and any other device are connected
to the same baro set potentiometer. This AD also prohibits future
installation of any TAWS8000 TAWS that incorporates hardware ``Mod
None'', ``Mod A'', or ``Mod B''. This AD is the result of a test that
showed that TAWS8000 TAWS cause altitude errors in other instruments.
The actions specified by this AD are intended to prevent the loading of
the baro set potentiometer, which could result in an unacceptable
attitude error. Such a condition could cause the pilot to make flight
decisions that put the airplane in unsafe flight conditions.
DATES: This AD becomes effective on July 21, 2003.
The Director of the Federal Register approved the incorporation by
reference of certain publications listed in the regulation as of July
21, 2003.
The Federal Aviation Administration (FAA) must receive any comments
on this rule on or before August 29, 2003.
ADDRESSES: Submit comments to FAA, Central Region, Office of the
Regional Counsel, Attention: Rules Docket No. 2003-CE-25-AD, 901
Locust, Room 506, Kansas City, Missouri 64106. You may view any
comments at this location between 8 a.m. and 4 p.m., Monday through
Friday, except Federal holidays. You may also send comments
electronically to the following address: 9-ACE-7-Docket@faa.gov.
Comments sent electronically must contain ``Docket No. 2003-CE-25-AD''
in the subject line. If you send comments electronically as attached
electronic files, the files must be formatted in Microsoft Word 97 for
Windows or ASCII text.
You may get the service information referenced in this AD from
Goodrich Avionics Systems, Inc., 5353 52nd Street, SE., Grand Rapids,
Michigan 49512-9704; telephone: (616) 949-6600; facsimile: (616) 977-
6898. You may view this information at FAA, Central Region, Office of
the Regional Counsel, Attention: Rules Docket No. 2003-CE-25-AD, 901
Locust, Room 506, Kansas City, Missouri 64106; or at the Office of the
Federal Register, 800 North Capitol Street, NW., suite 700, Washington,
DC.
FOR FURTHER INFORMATION CONTACT: Brenda S. Ocker, Aerospace Engineer,
FAA, Chicago Aircraft Certification Office, 2300 East Devon Avenue, Des
Plaines, Illinois 60018; telephone: (847) 294-7126; facsimile: (847)
294-7834.
SUPPLEMENTARY INFORMATION:
Discussion
What events have caused this AD? The manufacturer has reported that
the TAWS8000 TAWS causes altitude errors in other instruments when both
the TAWS and any other device are connected to the same baro set
potentiometer. The unsafe condition was discovered during the
installation of a TAWS8000 TAWS in a Cessna 500 series airplane. The
TAWS8000 TAWS was connected to the baro set potentiometer output of a
Honeywell (Sperry) BA-141 altimeter that was also connected to a
Honeywell AZ-241 Air Data Computer. The altimeter showed that the
aircraft was 60 feet higher than the actual altitude. This unsafe
condition was confirmed with the laboratory test of a TAWS8000 TAWS
installation.
What are the consequences if the condition is not corrected? This
condition, if not corrected, could cause the pilot to make flight
decisions that put the airplane in unsafe flight conditions.
Is there service information that applies to this subject? Goodrich
has issued Service Memo SM 134, dated May 2, 2003.
What are the provisions of this service information? The service
memo specifies the following information:
[sbull] The TAWS8000 should not be connected to a baro set
potentiometer if that potentiometer is also connected to any other
device; and
[sbull] In existing installations where both the TAWS and any other
device are connected to the same baro set potentiometer, the TAWS8000
should be removed from the aircraft.
The FAA's Determination and an Explanation of the Provisions of This AD
What has FAA decided? The FAA has reviewed all available
information, including the service information referenced above; and
determined that:
[sbull] The unsafe condition referenced in this document exists or
could develop on type design airplanes equipped with a Goodrich
TAWS8000 TAWS that incorporates hardware ``Mod None'', ``Mod A'', or
``Mod B'';
[sbull] Any airplane with one of these TAWS8000 TAWS units should
have the actions specified in the above service memo incorporated; and
[sbull] AD action should be taken in order to correct this unsafe
condition.
What does this AD require? This AD:
[sbull] Requires inspection of the TAWS8000 TAWS to determine if
both the TAWS8000 TAWS and any other device are connected to the same
baro set potentiometer;
[sbull] Requires removal of any TAWS8000 TAWS with such an
installation configuration, which includes capping and stowing the
connecting wires; and
[sbull] Prohibits the future installation of any TAWS8000 TAWS that
incorporates hardware ``Mod None'', ``Mod A'', or ``Mod B'.
In preparation of this rule, we contacted type clubs and aircraft
operators to obtain technical information and information on
operational and economic impacts. We did not receive any information
through these contacts. If received, we would have included, in the
rulemaking docket, a discussion of any information that may have
influenced this action.
How does the revision to 14 CFR part 39 affect this AD? On July 10,
2002, FAA published a new version of 14 CFR part 39 (67 FR 47997, July
22, 2002), which governs FAA's AD system. This regulation now includes
material that relates to special flight permits, alternative methods of
compliance, and altered products. This material previously was included
in each individual AD. Since this material is included in 14 CFR part
39, we will not include it in future AD actions.
Will I have the opportunity to comment prior to the issuance of the
rule? Because the unsafe condition
[[Page 38587]]
described in this document could result in the pilot making flight
decisions that put the airplane in unsafe flight conditions, we find
that notice and opportunity for public prior comment are impracticable.
Therefore, good cause exists for making this amendment effective in
less than 30 days.
Comments Invited
How do I comment on this AD? Although this action is in the form of
a final rule and was not preceded by notice and opportunity for public
comment, FAA invites your comments on the rule. You may submit whatever
written data, views, or arguments you choose. You need to include the
rule's docket number and submit your comments to the address specified
under the caption ADDRESSES. We will consider all comments received on
or before the closing date specified above. We may amend this rule in
light of comments received. Factual information that supports your
ideas and suggestions is extremely helpful in evaluating the
effectiveness of the AD action and determining whether we need to take
additional rulemaking action.
Are there any specific portions of the AD I should pay attention
to? We specifically invite comments on the overall regulatory,
economic, environmental, and energy aspects of the rule that might
suggest a need to modify the rule. You may view all comments we receive
before and after the closing date of the rule in the Rules Docket. We
will file a report in the Rules Docket that summarizes each FAA contact
with the public that concerns the substantive parts of this AD.
How can I be sure FAA receives my comment? If you want us to
acknowledge the receipt of your comments, you must include a self-
addressed, stamped postcard. On the postcard, write ``Comments to
Docket No. 2003-CE-25-AD.'' We will date stamp and mail the postcard
back to you.
Regulatory Impact
Does this AD impact various entities? These regulations will 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.
Therefore, FAA has determined that this final rule does not have
federalism implications under Executive Order 13132.
Does this AD involve a significant rule or regulatory action? We
have determined that this regulation is an emergency regulation that
must be issued immediately to correct an unsafe condition in aircraft,
and is not a significant regulatory action under Executive Order 12866.
It has been determined further that this action involves an emergency
regulation under DOT Regulatory Policies and Procedures (44 FR 11034,
February 26, 1979). If it is determined that this emergency regulation
otherwise would be significant under DOT Regulatory Policies and
Procedures, a final regulatory evaluation will be prepared and placed
in the Rules Docket (otherwise, an evaluation is not required). A copy
of it, if filed, may be obtained from the Rules Docket.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by
Reference, Safety.
Adoption of the Amendment
0
Accordingly, under the authority delegated to me by the Administrator,
the Federal Aviation Administration amends part 39 of the Federal
Aviation Regulations (14 CFR part 39) as follows:
PART 39--AIRWORTHINESS DIRECTIVES
0
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]
0
2. FAA amends Sec. 39.13 by adding a new airworthiness directive (AD)
to read as follows:
2003-13-08 Goodrich Avionics Systems, Inc.: Amendment 39-13208;
Docket No. 2003-CE-25-AD.
(a) What airplanes are affected by this AD? Any Goodrich
TAWS8000 terrain awareness warning system (TAWS), part number (P/N)
805-18000-001, that incorporates hardware ``Mod None'', ``Mod A'',
or ``Mod B'', that is installed in, but not limited to, the
following airplanes that are certificated in any category. Airplanes
that are not in this list and have the TAWS installed through field
approval or other methods are still affected by this AD:
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Company Models
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Cessna Aircraft Company...... 421, 500, 501, 525, 525A, 550, 551, 650,
and S550.
DASSAULT AVIATION............ Mystere-Falcon 20 series.
Gulfstream Aerospace LP...... 1125 Westwind Astra.
Raytheon Aircraft Company.... 100, 200, 300, 400A, and F90.
Sabreliner Corporation....... NA-265.
The New Piper Aircraft Inc... PA-42-1000.
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(b) Who must comply with this AD? Anyone who wishes to operate
any airplane with one of the above referenced Goodrich TAWS
installed must comply with this AD.
(c) What problem does this AD address? The actions specified by
this AD are intended to prevent the loading of the baro set
potentiometer, which could result in an unacceptable attitude error.
Such a condition could cause the pilot to make flight decisions that
put the airplane in unsafe flight conditions.
(d) What must I do to address this problem? To address this
problem, you must accomplish the following actions:
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Actions Compliance Procedures
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(1) Inspect the TAWS8000 Within the next 5 In accordance with
TAWS (part number 805-18000- hours time-in- Goodrich Avionics
001 that incorporates service (TIS) after Systems, Inc.
hardware ``Mod None'', July 21, 2003 (the Service Memo SM
``Mod A'', or ``Mod B'') effective date of 134, dated
installation to determine this AD), unless May 2, 2003, and
if both the TAWS8000 TAWS already the applicable
and any other device are accomplished. installation
connected to the same baro manual.
set potentiometer.
[[Page 38588]]
(2) If both the TAWS8000 Before further In accordance with
TAWS and any other device flight after the Goodrich Avionics
are connected to the same inspection required Systems, Inc.
baro set potentiometer, in paragraph (d)(1) Service Memo SM
then remove the TAWS8000 of this AD. 134, dated
TAWS and cap and stow the May 2, 2003, and
connecting wires. the applicable
installation
manual.
(3) Do not install any As of July 21, 2003 Not Applicable.
TAWS8000 TAWS (part number (the effective date
805-18000-001 that of this AD).
incorporates hardware ``Mod
None'', ``Mod A'', or ``Mod
B'').
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(e) Can I comply with this AD in any other way? To use an
alternative method of compliance or adjust the compliance time,
follow the procedures in 14 CFR 39.19. Send these requests to the
Manager, Chicago Aircraft Certification Office (ACO). For
information on any already approved alternative methods of
compliance, contact Brenda S. Ocker, Aerospace Engineer, FAA,
Chicago ACO, 2300 East Devon Avenue, Des Plaines, Illinois 60018;
telephone: (847) 294-7126; facsimile: (847) 294-7834.
(f) Are any service bulletins incorporated into this AD by
reference? Actions required by this AD must be done in accordance
with Goodrich Avionics Systems, Inc. Service Memo SM 134,
dated May 2, 2003. The Director of the Federal Register approved
this incorporation by reference under 5 U.S.C. 552(a) and 1 CFR part
51. You can get copies from Goodrich Avionics Systems, Inc., 5353
52nd Street, SE, Grand Rapids, Michigan 49512-9704; telephone: (616)
949-6600; facsimile: (616) 977-6898. You may view this information
at FAA, Central Region, Office of the Regional Counsel, 901 Locust,
Room 506, Kansas City, Missouri, or at the Office of the Federal
Register, 800 North Capitol Street, NW., suite 700, Washington, DC.
(g) When does this amendment become effective? This amendment
becomes effective on July 21, 2003.
Issued in Kansas City, Missouri, on June 18, 2003.
Michael K. Dahl,
Acting Manager, Small Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 03-15854 Filed 6-27-03; 8:45 am]
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