[Federal Register Volume 66, Number 151 (Monday, August 6, 2001)]
[Proposed Rules]
[Pages 40926-40929]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 01-19094]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 99-CE-87-AD]
RIN 2120-AA64


Airworthiness Directives; GARMIN International GNS 430 Units

AGENCY: Federal Aviation Administration, DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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SUMMARY: This document proposes to adopt a new airworthiness directive 
(AD) that would apply to certain GARMIN International (GARMIN) GNS 430 
units that are installed on aircraft. The proposed AD would require you 
to modify the unit to incorporate circuitry changes to the GNS 430 
unit's deviation and flag outputs. The proposed AD is the result of 
reports of inaccurate course deviations caused by external electrical 
noise to the GNS 430 unit's course deviation indicator (CDI). The 
actions specified by the proposed AD are intended to prevent such 
external noise from causing inaccurate course deviation displays in the 
GNS 430 unit's CDI or horizontal situation indicator (HSI). Such 
displays could result in the pilot making flight decisions that put the 
aircraft in unsafe flight conditions.

ADDRESSES: The Federal Aviation Administration (FAA) must receive any 
comments on this rule on or before September 21,2001. Submit comments 
in triplicate to FAA, Central Region, Office of the Regional Counsel, 
Attention: Rules Docket No. 99-CE-87-AD, 901 Locust, Room 506, Kansas 
City, Missouri 64106. Comments may be inspected at this location 
between 8 a.m. and 4 p.m., Monday through Friday, holidays excepted.
    You may obtain service information that applies to the proposed AD 
from GARMIN International, 1200 East 151st Street, Olathe, Kansas 
66062. You may also examine this information at the Rules Docket at the 
address above.

FOR FURTHER INFORMATION CONTACT: Roger A. Souter, FAA,Wichita Aircraft 
Certification Office (ACO), 1801 Airport Road, Room 100, Wichita, 
Kansas 67209; telephone: (316) 946-4134; facsimile: (316) 946-4407; e-
mail: [email protected].

SUPPLEMENTARY INFORMATION:

Comments Invited

    How do I comment on the proposed AD? The FAA invites comments on 
this proposed 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 in triplicate to the address specified under the 
caption ADDRESSES. The FAA will consider all comments received on or 
before the closing date. We may amend the proposed rule in light of 
comments received. Factual information that supports your ideas and 
suggestions is extremely helpful in evaluating the effectiveness of the 
proposed AD action and determining whether we need to take additional 
rulemaking action.
    Are there any specific portions of the proposed AD I should pay 
attention to? The FAA specifically invites comments on the overall 
regulatory, economic, environmental, and energy aspects of the proposed 
rule that might suggest a need to modify the rule. You may examine all 
comments we receive before and after the closing date of the rule in 
the RulesDocket. We will file a report in the Rules Docket that 
summarizes each FAA contact with the public that

[[Page 40927]]

concerns the substantive parts of the proposed AD.
    We are re-examining the writing style we currently use in 
regulatory documents, in response to the Presidential memorandum of 
June 1, 1998. That memorandum requires federal agencies to communicate 
more clearly with the public. We are interested in your comments on 
whether the style of this document is clear, and any other suggestions 
you might have to improve the clarity of FAA communications that affect 
you. You can get more information about the Presidential memorandum and 
the plain language initiative at http://www.plainlanguage.gov.
    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. 99-CE-87-AD.'' We will date stamp and mail the postcard back 
to you.

Discussion

    What events have caused this proposed AD? The FAA has received 
information that external electrical noise to the course deviation 
indicator (CDI) of GARMIN GNS 430 units could result in the CDI or 
horizontal situation indicator (HSI) displaying inaccurate course 
deviations. This could prompt the pilot to make flight decisions that 
put the aircraft in unsafe flight conditions.
    Certain GNS 430 installations have received electrical noise 
between 1 and 3 volts alternating current (AC) peak-peak (induced into 
the GNS 430 CDI input) from other items installed on the aircraft. This 
high level of noise causes an undesirable oscillation of the CDI 
outputs, which results in inaccurate course deviation displays in the 
GNS 430 unit's CDI/HSI.
    The condition is installation dependent. The GNS 430 units continue 
to meet all requirements in the technical standard order (TSO). The 
condition occurs in aircraft with installations that impose large noise 
spikes upon the CDI D-bar control wiring. Such installations are 
autopilots, fan motors, or similar accessories.
    What are the consequences if the condition is not corrected?As 
described above, such external noise could cause inaccurate course 
deviation displays in the GNS 430 unit'sCDI/HSI. This could result in 
the pilot making flight decisions that put the aircraft in unsafe 
flight conditions.

Relevant Service Information

    Is there service information that applies to this subject?GARMIN 
has issued Service Bulletin No.: 9905, Revision A, dated September 17, 
1999.
    What are the provisions of this service bulletin? The service 
bulletin includes information on how to modify the GNS 430 unit to 
incorporate circuitry changes to the deviation and flag outputs. This 
includes:

--Main Board: removing and replacing six capacitors, removing two 
diodes, removing and replacing two resistors, and adding two resistors 
and two jumpers; and
--Nav Board: removing and replacing seven capacitors and adding four 
capacitors.

    This service bulletin also specifies the part number GNS 430 units 
that could exhibit the above condition.

The FAA's Determination and an Explanation of the Provisions of the 
Proposed AD

    What has FAA decided? After examining the circumstances and 
reviewing all available information related to the incidents described 
above, we have determined that:

--The unsafe condition referenced in this document exists or could 
develop on type design aircraft that incorporate the GARMIN GNS 430 
units;
--The actions specified in the previously-referenced service 
information should be accomplished on these aircraft; and
--AD action should be taken in order to correct this unsafe condition.

    What would the proposed AD require? This proposed AD would require 
you to modify the unit to incorporate circuitry changes to the GNS 430 
unit's deviation and flag outputs. The proposed actions would be 
accomplished in accordance with GARMIN Service Bulletin No.: 9905, 
Revision A, datedSeptember 17, 1999.

Cost Impact

    How many aircraft would the proposed AD impact? We estimate that 
2,010 affected GARMIN GNS 430 units could be installed on aircraft in 
the U.S. registry.
    What would be the cost impact of the proposed AD on owners/
operators of the affected aircraft? GARMIN will cover all workhours and 
parts costs associated with this modification under warranty. The 
proposed AD would not impose any cost impact upon the owners/operators 
of any aircraft incorporating one of the affected GNS 430 units.

Compliance Time of the Proposed AD

    What is the compliance time of the proposed AD? The compliance time 
of this proposed AD is within the next 6 months after the effective 
date of the proposed AD.
    Why is the proposed compliance time presented in calendar time 
instead of hours time-in-service (TIS)? The compliance time for this AD 
is presented in calendar time instead of hours TIS because the 
condition exists regardless of aircraft operation. The external noise 
outputs could occur and cause the inaccurate CDI/HSI displays 
regardless of the number of times and hours the aircraft was operated 
or the age of the GNS 430 unit. For these reasons, FAA has determined 
that a compliance based on calendar time should be utilized in the 
proposed AD in order to ensure that the unsafe condition is addressed 
within a reasonable time period on all aircraft with an affected GNS 
430 unit installed.

Regulatory Impact

    Would this proposed AD impact various entities? The regulations 
proposed herein 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. Therefore, it is determined that this 
proposed rule would not have federalism implications under 
ExecutiveOrder 13132.
    Would this proposed AD involve a significant rule or regulatory 
action? For the reasons discussed above, I certify that this action (1) 
is not a ``significant regulatory action'' under Executive Order 12866; 
(2) is not a ``significant rule'' under DOT Regulatory Policies and 
Procedures (44 FR 11034, February 26, 1979); and (3) if promulgated, 
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. A copy of the draft regulatory evaluation 
prepared for this action has been placed in the Rules Docket. A copy of 
it may be obtained by contacting the Rules Docket at the location 
provided under the caption ADDRESSES.

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 of the Federal Aviation Regulations as follows:

[[Page 40928]]

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. FAA amends Sec. 39.13 by adding a new airworthiness directive 
(AD) to read as follows:

Garmin International: Docket No. 99-CE-87-AD

    (a) What products are affected by this AD? This AD applies to 
the GNS 430 units that are specified in paragraph (a)(1) of this AD 
and are installed on aircraft. These GNS 430 units are installed in, 
but not limited to, aircraft that are certificated in any category 
and presented in paragraph (a)(2) of this AD:
    (1) GNS 430 Units, part number 011-00280-00: serial numbers 
96300001, 96300002, 96300017, 96300028, 96300034, 96300040, 
96300068, 96300104, 96300108, 96300122, 96300125, 96300130, 
96300142, 96300149, 96300161, 96300165, 96300218, 96300222, 
96300232, 96300269, 96300272, 96300308, 96300333, 96300340, 
96300348, 96300354, 96300369, 96300372, 96300382, 96300394, 
96300411, 96300413, 96300429, 96300437, 96300451, 96300484, 
96300485, 96300489, 96300504, 96300506, 96300513, 96300522, 
96300549, 96300563, 96300585, 96300587, 96300618, 96300621, 
96300624, 96300628, 96300641, 96300653, 96300664, 96300713, 
96300734, 96300756, 96300766, 96300781, 96300785, 96300786, 
96300808, 96300831, 96300837, 96300842, 96300846, 96300866, 
96300870, 96300872, 96300899, 96300916, 96300923, 96300925, 
96300929, 96300941, 96300961, 96300984, 96300987, 96301021, 
96301108, 96301130, 96301280, and 96301296 through 96303200.
    (2) Aircraft with the GNS 430 Unit Installation (other aircraft 
could have field approval installations):

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              TC holder                                             Airplane models
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Cessna Aircraft Company..............  172, 182, 206, 208, 210, 401, 402, 404, 406, 411, 414, 414A, 421A, 421B,
                                        421C, 425, 441, 500, 550, S550, 552, 560, 560XL, 501,525, and 551.
Mooney Aircraft Corporation..........  M20, M20A, M20B, M20C, M20D, M20E, M20F, M20G, M20J, M20K, M20L, M20M,
                                        M20R, M20S, and M22.
Raytheon Aircraft Company............  Beech Models E33, F33, G33, E33A, F33A, E33C, F33C, 35, 35R, A35, B35,
                                        B35TC, C35, D35, E35, F35, G35, H35, J35, K35, M35, N35, P35, S35, V35,
                                        V35TC, V35A, V35A-TC, V35B, V35B-TC, 36, A36, A36TC, 50, B50, C50, D50,
                                        D50A, D50B, D50C, D50E, E50, F50, G50, H50, J50, 60, A60, B60, 65-90, 65-
                                        A90, B90, C90, C90A, C90B, E90, F90, 100, A100, B100, 95-55, 95-A55, 95-
                                        B55, 95-C55, D-55, E55, 58, 58P, and 58TC.
Socata...............................  TBM 700.
The New Piper Aircaft, Inc...........  J3C-40, J3C-50, J3C-50S(Army L-4, L-4B, L-4H, and L-4J),J3C-65 (Navy NE-1
                                        and NE-2), J3C-65S, J3F-50, J3F-50S, J3F-60, J3F-60S, J3F-65 (Army L-
                                        4D), J3F-65S, J3L, J3L-S, J3L-65 (Army L-4C), J3L-65S, J4, J4A, J4A-S,
                                        J4E (Army L-4E), J5A (Army L-4F), J5A-80, J5B(Army L-4G), J5C, AE-1, HE-
                                        1, PA-11, PA-11S, PA-12, PA-12S, PA-14,PA-15, PA-16, PA-16S, PA-17, PA-
                                        18,PA-18A, PA-18A (Restricted), PA-18S, PA-18-``105'' (Special), PA-18S-
                                        ``105'' (Special), PA-18-``125'' (ArmyL-21A), PA-18AS-``125'', PA-18S-
                                        ``125'', PA-18-``135'' (Army L-21B), PA-18A-``135'', PA-18A-``135''
                                        (Restricted), PA-18AS-``135'', PA-18S-``135'', PA-18-``150'', PA-18A-
                                        ``150'', PA-18A-``150'' (Restricted), PA-18AS-``150'', PA-18S-``150'',
                                        PA-19 (Army L-18C), PA-19S, PA-20, P-20S, PA-20-``115'', PA-20S-``115'',
                                        PA-20-``135'',PA-20S-``135'', PA-22, PA-22-108, PA-22-135, PA-22S-135,
                                        PA-22-150, PA-22S-150, PA-22-160, PA-22S-160, PA-24, PA-24-250, PA-24-
                                        260, PA-24-400, PA-25, PA-25-235, PA-25-260,PA-28-140, PA-28-150, PA-28-
                                        151, PA-28-160, PA-28-161, PA-28-180, PA-28-235, PA-28S-160, PA-28R-180,
                                        PA-28S-180, PA-28-181, PA-28R-200, PA-28R-201, PA-28R-201T, PA-28RT-201,
                                        PA-28RT-201T, PA-28-201T, PA28-236, PA-32R-301 (SP), PA-32R-301 (HP), PA-
                                        32R-301T, PA-32-301, PA-32-301T, PA-36-285, PA-36-300, PA-36-375, PA-38-
                                        112, PA-46-310P, and PA-46-350P.
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    (b) Who must comply with this AD? Anyone who wishes to operate 
any aircraft with one of the affected GNS 430 units installed must 
comply with this AD.
    (c) What problem does this AD address? The actions specified by 
this AD are intended to prevent external noise from causing 
inaccurate course deviation displays in the GNS 430 unit's course 
deviation indicator (CDI) or horizontal situation indicator (HSI). 
Such displays could result in the pilot making flight decisions that 
put the aircraft in unsafe flight conditions.
    (d) What actions must I accomplish to address this problem? To 
address this problem, you must accomplish the following:

------------------------------------------------------------------------
           Action                Compliance time         Procedures
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(1) Modify the affected GNS   Within the next 6     In accordance with
 430 unit modified to          months after the      the MODIFICATION
 incorporate circuitry         effective date of     INSTRUCTIONS
 changes to the deviation      this AD.              section of GARMIN
 and flag outputs.                                   Service Bulletin
                                                     No.: 9905, Revision
                                                     A, dated September
                                                     17, 1999.
(2) Do not install an         As of the effective   In accordance with
 affected GNS 430 unit         date of this AD.      the MODIFICATION
 unless it has been modified                         INSTRUCTIONS
 as required by paragraph                            section of GARMIN
 (d)(1) of this AD.                                  Service Bulletin
                                                     No.: 9905, Revision
                                                     A, dated September
                                                     17, 1999.
------------------------------------------------------------------------

    (e) Can I comply with this AD in any other way? You may use an 
alternative method of compliance or adjust the compliance time if:
    (1) Your alternative method of compliance provides an equivalent 
level of safety; and
    (2) The Manager, Wichita Aircraft Certification Office, approves 
your alternative. Send your request through an

[[Page 40929]]

FAA Principal Maintenance Inspector, who may add comments and then 
send it to the Manager, Wichita Aircraft Certification Office.

    Note: This AD applies to any aircraft with the equipment 
installed as identified in paragraph (a) of this AD, regardless of 
whether the aircraft has been modified, altered, or repaired in the 
area subject to the requirements of this AD. For aircraft that have 
been modified, altered, or repaired so that the performance of the 
requirements of this AD is affected, the owner/operator must request 
approval for an alternative method of compliance in accordance with 
paragraph (e) of this AD. The request should include an assessment 
of the effect of the modification, alteration, or repair on the 
unsafe condition addressed by this AD; and, if you have not 
eliminated the unsafe condition, specific actions you propose to 
address it.

    (f) Where can I get information about any already-approved 
alternative methods of compliance? You can contact Roger A. Souter, 
FAA, Wichita Aircraft Certification Office (ACO), 1801 Airport Road, 
Room 100, Wichita, Kansas 67209; telephone: (316) 946-4134; 
facsimile: (316) 946-4407, e-mail: [email protected].
    (g) What if I need to fly the aircraft to another location to 
comply with this AD? The FAA can issue a special flight permit under 
sections 21.197 and 21.199 of the Federal Aviation Regulations (14 
CFR 21.197 and 21.199) to operate your aircraft to a location where 
you can accomplish the requirements of this AD.
    (h) How do I get copies of the documents referenced in this AD? 
You may obtain copies of the documents referenced in this AD from 
GARMIN International, 1200 East 151st Street, Olathe, Kansas 66062. 
You may examine 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 July 23, 2001.
Michael Gallagher,
Manager, Small Airplane Directorate, Aircraft Certification Service.
[FR Doc. 01-19094 Filed 8-3-01; 8:45 am]
BILLING CODE 4910-13-P