[Federal Register: April 21, 2004 (Volume 69, Number 77)]
[Rules and Regulations]
[Page 21393-21395]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr21ap04-1]
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Rules and Regulations
Federal Register
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[[Page 21393]]
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 2003-CE-47-AD; Amendment 39-13584; AD 2004-08-15]
RIN 2120-AA64
Airworthiness Directives; Goodrich Avionics Systems, Inc.
TAWS8000 Terrain Awareness Warning System
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Final rule.
-----------------------------------------------------------------------
SUMMARY: The FAA supersedes Airworthiness Directive (AD) 2003-13-08,
which currently applies to all Goodrich Avionics Systems, Inc.
(Goodrich) TAWS8000 terrain awareness warning systems (TAWS) that are
installed on airplanes. AD 2003-13-08 currently 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. AD 2003-
13-08 also prohibits future installation of any TAWS8000 TAWS that
incorporates hardware ``Mod None'', ``Mod A'', or ``Mod B''. This AD is
the result of omitting from AD 2003-13-08 a provision that prohibits
reconfiguring an installed TAWS8000 TAWS after it passes the inspection
unless it incorporates hardware ``Mod C''. This AD retains the actions
of AD 2003-13-08 and prohibits future installation or reconfiguration
of any TAWS8000 TAWS that does not incorporate hardware ``Mod C''. We
are issuing this AD to prevent the loading of the baro set
potentiometer, which could result in an unacceptable altitude error.
That condition could cause the pilot to make flight decisions that put
the airplane in unsafe flight conditions.
DATES: This AD becomes effective on June 7, 2004.
On July 21, 2003 (68 FR 38586, June 30, 2003), the Director of the
Federal Register approved the incorporation by reference of Goodrich
Avionics Systems, Inc. Service Memo SM 134, dated May 2, 2003.
As of June 7, 2004, the Director of the Federal Register approved
the incorporation by reference of Goodrich Avionics Systems, Inc.
Service Memo SM 134, revised July 9, 2003; and Goodrich
Avionics Systems, Inc. Alert Service Bulletin SB A117, dated
July 9, 2003.
ADDRESSES: You may get the service information identified 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 the AD docket at FAA, Central Region, Office of the
Regional Counsel, Attention: Rules Docket No. 2003-CE-47-AD, 901
Locust, Room 506, Kansas City, Missouri 64106. Office hours are 8 a.m.
to 4 p.m., Monday through Friday, except Federal holidays.
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? Reports that the Goodrich TAWS8000
TAWS causes altitude errors in other instruments when both the TAWS and
any other device are connected to the same baro set potentiometer
caused us to issue AD 2003-13-08, Amendment 39-13208.
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 has happened since AD 2003-13-08 to initiate this action? We
omitted from AD 2003-13-08 a provision that prohibits reconfiguring an
installed TAWS8000 TAWS after it passes the inspection unless it
incorporates hardware ``Mod C''.
Since we issued AD 2003-13-08, Goodrich Avionics System, Inc. has
also developed a production improvement (Mod C) to eliminate the effect
of loading on the baro set potentiometer. Goodrich has issued an alert
service bulletin to implement this modification.
We received comments about the language in AD 2003-13-08. Owners/
operators are restricted from installing any TAWS8000 TAWS (part number
805-18000-001 that incorporates hardware ``Mod None'', ``Mod A'', or
``Mod B''). When the unit is modified to incorporate hardware ``Mod
C'', the unit will still have ``Mod None'', ``Mod A'', or ``Mod B''
marked on it. The intent of the AD was to allow for hardware
modifications other than ``Mod None'', ``Mod A'', or ``Mod B'' to be
installed.
What is the potential impact if FAA took no action? AD 2003-13-08,
as currently written, could cause confusion as to how to incorporate
the actions necessary in correcting the unsafe condition.
Has FAA taken any action to this point? We issued a proposal to
amend part 39 of the Federal Aviation Regulations (14 CFR part 39) to
include an AD that would apply to all Goodrich Avionics Systems, Inc.
(Goodrich) TAWS8000 terrain awareness warning systems (TAWS) that are
installed on airplanes. This proposal was published in the Federal
Register as a notice of proposed rulemaking (NPRM) on December 3, 2003
(68 FR 67611). The NPRM proposed to supersede AD 2003-13-08 with a new
AD that proposes to require you to inspect the TAWS installation and
modify any TAWS where both the TAWS and any other device are connected
to the same baro set potentiometer. This NPRM also proposed to prohibit
future installation or reconfiguration of any TAWS8000 TAWS that does
not incorporate hardware ``Mod C''.
Comments
Was the public invited to comment? We provided the public the
opportunity to participate in developing this AD. We received no
comments on the proposal or on the determination of the cost to the
public.
[[Page 21394]]
Conclusion
What is FAA's final determination on this issue? We have carefully
reviewed the available data and determined that air safety and the
public interest require adopting the AD as proposed except for the
changes discussed above and minor editorial corrections. We have
determined that these changes and minor corrections:
--Are consistent with the intent that was proposed in the NPRM for
correcting the unsafe condition; and
--Do not add any additional burden upon the public than was already
proposed in the NPRM.
Changes to 14 CFR Part 39--Effect on the AD
How does the revision to 14 CFR part 39 affect this AD? On July 10,
2002, the FAA published a new version of 14 CFR part 39 (67 FR 47997,
July 22, 2002), which governs the FAA's AD system. This regulation now
includes material that relates to altered products, special flight
permits, and alternative methods of compliance. 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.
Costs of Compliance
How many airplanes does this AD impact? We estimate that this AD
affects 80 airplanes in the U.S. registry.
What is the cost impact of this AD on owners/operators of the
affected airplanes? We estimate the following costs to accomplish the
inspection:
----------------------------------------------------------------------------------------------------------------
Total cost on U.S.
Labor cost Parts cost Total cost per airplane operators
----------------------------------------------------------------------------------------------------------------
1 workhour x $65 = $65........... Not applicable........... $65 $65 x 80 = $5,200
----------------------------------------------------------------------------------------------------------------
We estimate the following costs to accomplish any necessary
modifications that will be required based on the results of this
inspection. We have no way of determining the number of airplanes that
may need the modification:
----------------------------------------------------------------------------------------------------------------
Labor cost Parts cost Total cost per airplane
----------------------------------------------------------------------------------------------------------------
2 workhours x $65 = $130 (1 workhour to remove All units will be modified at the $130
and 1 workhour to replace). Goodrich Avionics Systems facility
under warranty.
----------------------------------------------------------------------------------------------------------------
Regulatory Findings
Will this AD impact various entities? We have determined that this
AD will not have federalism implications under Executive Order 13132.
This AD 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.
Will this AD involve a significant rule or regulatory action? For
the reasons discussed above, I certify that this AD:
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 summary of the costs to comply with this AD and
placed it in the AD Docket. You may get a copy of this summary by
sending a request to us at the address listed under ADDRESSES. Include
``AD Docket No. 2003-CE-47-AD'' in your request.
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. The FAA amends Sec. 39.13 by removing Airworthiness Directive (AD)
2003-13-08, Amendment 39-13208 (68 FR 38586, June 30, 2003), and by
adding a new AD to read as follows:
2004-08-15 Goodrich Avionics Systems, Inc.: Amendment 39-13584;
Docket No. 2003-CE-47-AD; Supersedes AD 2003-13-08, Amendment 39-
13208.
When Does This AD Become Effective?
(a) This AD becomes effective on June 7, 2004.
What Other ADs Are Affected By This Action?
(b) This AD supersedes AD 2003-13-08.
What Airplanes Are Affected by This AD?
(c) This AD affects all airplane models and serial numbers,
certificated in any category, that incorporate a Goodrich TAWS8000
terrain awareness warning system (TAWS), part number (P/N) 805-
18000-001, with ``Mod None'', ``Mod A'', or ``Mod B'' hardware
installed. This list of airplanes that have the TAWS8000 TWAS
installed includes, but is not limited to, the following airplanes.
Airplanes that are not in this list and have the TAWS installed
through field approval or other methods are still affected by this
AD:
------------------------------------------------------------------------
Company Models
------------------------------------------------------------------------
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
------------------------------------------------------------------------
[[Page 21395]]
What Is the Unsafe Condition Presented in This AD?
(d) The actions specified by this AD are intended to prevent the
loading of the baro set potentiometer, which could result in an
unacceptable altitude error. This condition could cause the pilot to
make flight decisions that put the airplane in unsafe flight
conditions.
What Must I Do To Address This Problem?
(e) To address this problem, you must do the following:
------------------------------------------------------------------------
Actions Compliance Procedures
------------------------------------------------------------------------
(1) Inspect the TAWS8000 Within the next 5 Follow Goodrich
TAWS (part number 805-18000- hours time-in- Avionics Systems,
001 that incorporates service (TIS) after Inc. Service Memo
hardware ``Mod None'', July 21, 2003 (the SM 134,
``Mod A'', or ``Mod B'') effective date of dated May 2, 2003,
installation to determine AD 2003-13-08), or Goodrich
if both the TAWS8000 TAWS unless already done. Avionics Systems,
and any other device are Inc. Service Memo
connected to the same baro SM 134,
set potentiometer. revised July 9,
2003, and the
applicable
installation
manual.
(2) If both the TAWS8000 Before further For removing the
TAWS and any other device flight after the TAWS8000 TAWS,
are connected to the same inspection required follow Goodrich
baro set potentiometer, in paragraph (d)(1) Avionics Systems,
remove the TAWS8000 TAWS of this AD. Inc. Service Memo
and cap and stow the SM 134,
connecting wires or replace dated May 2, 2003,
the TAWS8000 TAWS unit with or Goodrich
a unit that incorporates Avionics Systems,
hardware ``Mod C''. Inc. Service Memo
SM 134,
revised July 9,
2003, and the
applicable
installation
manual. For
replacing the
TAWS8000 TAWS,
follow Goodrich
Avionics Systems,
Inc. Alert Service
Bulletin SB A117, dated July
9, 2003.
(3) Do not install or As of June 7, 2004 Not Applicable.
reconfigure any TAWS8000 (the effective date
TAWS (part number 805-18000- of this AD).
001) that does not
incorporate hardware ``Mod
C''.
------------------------------------------------------------------------
May I Request an Alternative Method of Compliance?
(f) You may request a different method of compliance or a
different compliance time for this AD by following the procedures in
14 CFR 39.19.
(1) Unless FAA authorizes otherwise, send your request to your
principal inspector. The principal inspector may add comments and
will send your request to the Manager, Chicago Aircraft
Certification Office (ACO), FAA. For information on any already
approved alternative methods of compliance, 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.
(2) Alternative methods of compliance approved under AD 2003-13-
08, which is superseded by this AD, are approved as alternative
methods of compliance with this AD.
Does This AD Incorporate Any Material by Reference?
(g) You must do the actions required by this AD following the
instructions in Goodrich Avionics Systems, Inc. Service Memo SM
134, dated May 2, 2003; Goodrich Avionics Systems, Inc.
Service Memo SM 134, revised July 9, 2003; and Goodrich
Avionics Systems, Inc. Alert Service Bulletin SB A117,
dated July 9, 2003.
(1) On July 21, 2003 (68 FR 38586, June 30, 2003), and in
accordance with 5 U.S.C. 552(a) and 1 CFR part 51, the Director of
the Federal Register approved the incorporation by reference of
Goodrich Avionics Systems, Inc. Service Memo SM 134, dated
May 2, 2003.
(2) As of June 7, 2004, and in accordance with 5 U.S.C. 552(a)
and 1 CFR part 51, the Director of the Federal Register approved the
incorporation by reference of Goodrich Avionics Systems, Inc.
Service Memo SM 134, revised July 9, 2003; and Goodrich
Avionics Systems, Inc. Alert Service Bulletin SB A117,
dated July 9, 2003.
(3) You may get a copy from Goodrich Avionics Systems, Inc.,
5353 52nd Street, SE., Grand Rapids, Michigan 49512-9704; telephone:
(616) 949-6600; facsimile: (616) 977-6898. You may review copies at
FAA, Central Region, Office of the Regional Counsel, 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.
Issued in Kansas City, Missouri, on April 13, 2004.
James E. Jackson,
Acting Manager, Small Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 04-8792 Filed 4-20-04; 8:45 am]
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