[Federal Register Volume 68, Number 125 (Monday, June 30, 2003)]
[Rules and Regulations]
[Pages 38586-38588]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 03-15854]


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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: [email protected]. 
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:

------------------------------------------------------------------------
           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:

------------------------------------------------------------------------
           Actions                 Compliance            Procedures
------------------------------------------------------------------------
(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'').
------------------------------------------------------------------------

    (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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