[Federal Register Volume 68, Number 232 (Wednesday, December 3, 2003)]
[Proposed Rules]
[Pages 67611-67613]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 03-30074]


 ========================================================================
 Proposed Rules
                                                 Federal Register
 ________________________________________________________________________
 
 This section of the FEDERAL REGISTER contains notices to the public of 
 the proposed issuance of rules and regulations. The purpose of these 
 notices is to give interested persons an opportunity to participate in 
 the rule making prior to the adoption of the final rules.
 
 ========================================================================
 

  Federal Register / Vol. 68, No. 232 / Wednesday, December 3, 2003 / 
Proposed Rules  

[[Page 67611]]



DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2003-CE-47-AD]
RIN 2120-AA64


Airworthiness Directives; Goodrich Avionics Systems, Inc. 
TAWS8000 Terrain Awareness Warning System

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

-----------------------------------------------------------------------

SUMMARY: The FAA proposes to supersede 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 
proposed 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 proposed 
AD would retain the actions of AD 2003-13-08 and would also prohibit 
future installation or reconfiguration of any TAWS8000 TAWS that does 
not incorporate hardware ``Mod C''. We are issuing this proposed 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: We must receive any comments on this proposed AD by February 2, 
2004.

ADDRESSES: Use one of the following to submit comments on this proposed 
AD:
    [sbull] By mail: FAA, Central Region, Office of the Regional 
Counsel, Attention: Rules Docket No. 2003-CE-47AD, 901 Locust, Room 
506, Kansas City, Missouri 64106.
    [sbull] By fax: (816) 329-3771.
    [sbull] By e-mail: [email protected]. Comments sent 
electronically must contain ``Docket No. 2003-CE-47-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.
    You may get the service information identified in this proposed 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:

Comments Invited

    How do I comment on this proposed AD? We invite you to submit any 
written relevant data, views, or arguments regarding this proposal. 
Send your comments to an address listed under ADDRESSES. Include ``AD 
Docket No. 2003-CE-47-AD'' in the subject line of your comments. If you 
want us to acknowledge receipt of your mailed comments, send us a self-
addressed, stamped postcard with the docket number written on it. We 
will date-stamp your postcard and mail it back to you.
    Are there any specific portions of this proposed AD I should pay 
attention to? We specifically invite comments on the overall 
regulatory, economic, environmental, and energy aspects of this 
proposed AD. If you contact us through a nonwritten communication and 
that contact relates to a substantive part of this proposed AD, we will 
summarize the contact and place the summary in the docket. We will 
consider all comments received by the closing date and may amend this 
proposed AD in light of those comments and contacts.

Discussion

    Has FAA taken any action to this point? 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 proposed 
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 are the consequences if the condition is not corrected? AD 
2003-13-08, as currently written, could cause confusion as to how to 
incorporate the actions necessary in correcting the unsafe condition.
    Is there service information that applies to this subject? Goodrich

[[Page 67612]]

Avionics Systems, Inc. has issued Service Memo SM 134, Revised 
July 9, 2003, and Alert Service Bulletin SB A117, dated July 
9, 2003.
    What are the provisions of this service information? Goodrich 
Avionics Systems, Inc. Service Memo SM 134, Revised July 9, 
2003, introduces the release of product improvement hardware ``Mod C'' 
and restates the following information from the original issue of 
Service Memo SM 134:
    --The TAWS8000 should not be connected to a baro set potentiometer 
if that potentiometer is also connected to any other device; and
    --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.
    Goodrich Avionics Systems, Inc. Alert Service Bulletin SB 
A117, dated July 9, 2003, specifies upgrading all TAWS8000 
units to include hardware ``Mod C''.

FAA's Determination and Requirements of This Proposed AD

    What has FAA decided? The FAA has reviewed all available 
information, including the service information referenced above; and 
determined that:

    --The unsafe condition referenced in this document exists or could 
develop on type design airplanes equipped with a Goodrich TAWS8000 
TAWS, P/N 805-18000-001 that does not incorporate hardware ``Mod C'';
    --Any airplane with one of these TAWS8000 TAWS units, P/N 805-
18000-001 should have the actions specified in the above service 
information incorporated; and
    --AD action should be taken in order to correct this unsafe 
condition.
    What would this proposed AD require? This proposed AD would 
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 proposed AD would also prohibit future installation or 
reconfiguration of any TAWS8000 TAWS that does not incorporate hardware 
``Mod C''.
    How does the revision to 14 CFR part 39 affect this proposed AD? On 
July 10, 2002, we 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 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 would this proposed AD impact? We estimate that 
this proposed AD affects 80 airplanes in the U.S. registry.
    What would be the cost impact of this proposed AD on owners/
operators of the affected airplanes? We estimate the following costs to 
accomplish this proposed inspection:

----------------------------------------------------------------------------------------------------------------
                                                                  Total cost per
              Labor cost                      Parts cost             airplane      Total cost on U.S.  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 would be required based on the results of this 
proposed inspection. We have no way of determining the number of 
airplanes that may need the modification:

------------------------------------------------------------------------
                                                         Total cost  per
           Labor cost                  Parts cost            airplane
------------------------------------------------------------------------
2 workhours x $65 = $130 (1      All units will be                 $130
 workhour to remove and 1         modified at the
 workhour to replace).            Goodrich Avionics
                                  Systems facility
                                  under warranty.
------------------------------------------------------------------------

Regulatory Findings

    Would this proposed AD impact various entities? We have 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.
    Would this proposed AD involve a significant rule or regulatory 
action? For the reasons discussed above, I certify that this proposed 
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 proposed 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, Safety.

The Proposed Amendment

    Accordingly, under the authority delegated to me by the 
Administrator, the Federal Aviation Administration 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 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:

Goodrich Avionics Systems, Inc.: Docket No. 2003-CE-47-AD; 
Supersedes AD 2003-13-08, Amendment 39-13208.

[[Page 67613]]

When Is the Last Date I Can Submit Comments on This Proposed AD?

    (a) We must receive comments on this proposed airworthiness 
directive (AD) by February 2, 2004.

What Other ADs Are Affected by This Action?

    (b) This AD supersedes AD 2003-13-08, Amendment 39-13208.

What Airplanes Are Affected by This AD?

    (c) This AD affects the following airplane models and serial 
numbers that:
    (1) Are certificated in any category; and
    (2) Incorporate 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'', and is installed in, 
but 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 LPN............  1125 Westwind Astra.
Raytheon Aircraft Company...........  100, 200, 300, 400A, and F90.
Sabreliner Corporaiton..............  NA-265.
The New Piper Aircraft Inc..........  PA-42-1000.
----------------------------------------------------------------------------------------------------------------

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),       and the applicable
 if both the TAWS8000 TAWS     unless already        installation
 and any other device are      accomplished.         manual.
 connected to the same baro
 set potentiometer.
(2) If both the TAWS8000      Before further        Follow Goodrich
 TAWS and any other device     flight after the      Avionics Systems,
 are connected to the same     inspection required   Inc. Service Memo
 baro set potentiometer,       in paragraph (d)(1)   SM 134,
 remove the TAWS8000 TAWS      of this AD.           dated May 2, 2003,
 and cap and stow the                                and the applicable
 connecting wires or replace                         installation
 the TAWS8000 TAWS unit with                         manual.
 a unit that incorporates
 hardware ``Mod C''.
(3) Do not install or         As of the effective   Not Applicable.
 reconfigure any TAWS8000      date of this AD.
 TAWS (part number 805-18000-
 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 39.13.
    (1) 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 in accordance 
with AD 2003-13-08, which is superseded by this AD, are approved as 
alternative methods of compliance with this AD.

May I Get Copies of the Documents Referenced in This AD?

    (g) You may get copies of the documents 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 these documents at FAA, Central Region, 
Office of the Regional Counsel, 901 Locust, Room 506, Kansas City, 
Missouri 64106.

    Issued in Kansas City, Missouri, on November 25, 2003.
Michael Gallagher,
Manager, Small Airplane Directorate, Aircraft Certification Service.
[FR Doc. 03-30074 Filed 12-2-03; 8:45 am]
BILLING CODE 4910-13-P