[Federal Register Volume 69, Number 77 (Wednesday, April 21, 2004)]
[Rules and Regulations]
[Pages 21393-21395]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 04-8792]



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  Federal Register / Vol. 69, No. 77 / Wednesday, April 21, 2004 / 
Rules and Regulations  

[[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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