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

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Information about this document as published in the Federal Register.

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AGENCY:

Federal Aviation Administration, DOT.

ACTION:

Final rule; request for comments.

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.

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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.

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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:

  • 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.

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:

  • 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”;
  • Any airplane with one of these TAWS8000 TAWS units should have the actions specified in the above service memo incorporated; and
  • AD action should be taken in order to correct this unsafe condition.

What does this AD require? This AD:

  • 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;
  • Requires removal of any TAWS8000 TAWS with such an installation configuration, which includes capping and stowing the connecting wires; and
  • 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 Start Printed Page 38587described 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.

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List of Subjects in 14 CFR Part 39

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Adoption of the Amendment

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Accordingly, under the authority delegated to me by the Administrator, the Federal Aviation Administration amends part 39 of the Federal Aviation Regulations (

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PART 39—AIRWORTHINESS DIRECTIVES

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1. The authority citation for part 39 continues to read as follows:

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Authority: 49 U.S.C. 106(g), 40113, 44701.

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[Amended]
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2. FAA amends § 39.13 by adding a new airworthiness directive (AD) to read as follows:

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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:

CompanyModels
Cessna Aircraft Company421, 500, 501, 525, 525A, 550, 551, 650, and S550.
DASSAULT AVIATIONMystere-Falcon 20 series.
Gulfstream Aerospace LP1125 Westwind Astra.
Raytheon Aircraft Company100, 200, 300, 400A, and F90.
Sabreliner CorporationNA-265.
The New Piper Aircraft IncPA-42-1000.

(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:

ActionsComplianceProcedures
(1) Inspect the TAWS8000 TAWS (part number 805-18000-001 that incorporates hardware “Mod None”, “Mod A”, or “Mod B”) installation to determine if both the TAWS8000 TAWS and any other device are connected to the same baro set potentiometerWithin the next 5 hours time-in-service (TIS) after July 21, 2003 (the effective date of this AD), unless already accomplishedIn accordance with Goodrich Avionics Systems, Inc. Service Memo SM #134, dated May 2, 2003, and the applicable installation manual.
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(2) If both the TAWS8000 TAWS and any other device are connected to the same baro set potentiometer, then remove the TAWS8000 TAWS and cap and stow the connecting wiresBefore further flight after the inspection required in paragraph (d)(1) of this ADIn accordance with Goodrich Avionics Systems, Inc. Service Memo SM #134, dated May 2, 2003, and the applicable installation manual.
(3) Do not install any TAWS8000 TAWS (part number 805-18000-001 that incorporates hardware “Mod None”, “Mod A”, or “Mod B”)As of July 21, 2003 (the effective date of this AD)Not Applicable.

(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.

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Issued in Kansas City, Missouri, on June 18, 2003.

Michael K. Dahl,

Acting Manager, Small Airplane Directorate, Aircraft Certification Service.

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[FR Doc. 03-15854 Filed 6-27-03; 8:45 am]

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