[Federal Register Volume 66, Number 232 (Monday, December 3, 2001)]
[Rules and Regulations]
[Pages 60140-60142]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 01-29325]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 99-CE-87-AD; Amendment 39-12516; AD 2001-23-17]
RIN 2120-AA64


Airworthiness Directives; GARMIN International GNS 430 Units

AGENCY: Federal Aviation Administration, DOT.

ACTION: Final rule.

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SUMMARY: This amendment adopts a new airworthiness directive (AD) that 
applies to certain GARMIN International (GARMIN) GNS 430 units that are 
installed on aircraft. This AD requires you to modify the unit to 
incorporate circuitry changes to the GNS 430 unit's deviation and flag 
outputs. This 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 this 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.

DATES: This AD becomes effective on December 28, 2001.
    The Director of the Federal Register approved the incorporation by 
reference of certain publications listed in the regulations as of 
December 28, 2001.

ADDRESSES: You may obtain the service information referenced in this AD 
from GARMIN International, 1200 East 151st Street, Olathe, Kansas 
66062. You may view this information at the Federal Aviation 
Administration (FAA), Central Region, Office of the Regional Counsel, 
Attention: Rules Docket No. 99-CE-87-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: 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:

Discussion

    What events have caused this 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 is the potential impact if FAA took no action? As described 
above, such external noise could cause inaccurate course deviation 
displays in the GNS 430 unit's CDI/HSI. This could result in the pilot 
making flight decisions that put the aircraft in unsafe flight 
conditions.
    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

[[Page 60141]]

an AD that would apply to certain GARMIN GNS 430 units that are 
installed on aircraft. This proposal was published in the Federal 
Register as a notice of proposed rulemaking (NPRM) on August 6, 2001 
(66 FR 40926). The NPRM proposed to 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, dated September 17, 
1999.
    Was the public invited to comment? The FAA encouraged interested 
persons to participate in the making of this amendment. The paragraphs 
that follow present the comment received on the proposal and FAA's 
response to this comment.

Comment Disposition

    What is the commenter's concern? The commenter states that the 
majority of, if not all, the owners/operators of aircraft with the 
GARMIN GNS 430 units installed have already complied with the proposed 
AD through the manufacturer's warranty program. The commenter 
recommends that FAA withdraw the NPRM.
    What is FAA's response to the concern? We do not concur with 
withdrawing the NPRM. Many of the airplanes equipped with the GARMIN 
GNS 430 units may actually incorporate the modification. However, AD 
action is the only way we can mandate that all units currently 
installed either have the modification incorporated or keep the 
modification incorporated and that all units installed in the future 
incorporate this modification.
    We are not changing the final rule as a result of this comment.

FAA's Determination

    What is FAA's final determination on this issue? After careful 
review of all available information related to the subject presented 
above, we have determined that air safety and the public interest 
require the adoption of the rule as proposed except for minor editorial 
corrections. We have determined that these minor corrections:

--Provide 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.

Cost Impact

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

Compliance Time of This AD

    What is the compliance time of this AD? The compliance time of this 
AD is within the next 6 months after the effective date of this AD.
    Why is the 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, we have determined that a compliance 
based on calendar time should be utilized in this 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

    Does this AD impact various entities? The regulations adopted 
herein 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, it is determined that this final rule does not 
have federalism implications under Executive Order 13132.
    Does this 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) 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 final evaluation prepared for this action is contained 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, Incorporation by 
reference, Safety.

Adoption of the Amendment

    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

    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 AD to read as follows:

2001-23-17  GARMIN International: Amendment 39-12516; Docket No. 99-
CE-87-AD.

    (a) What airplanes 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 
9630001, 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):

[[Page 60142]]



------------------------------------------------------------------------
          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..............  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.
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Socata.......................  TBM 700.
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The New Piper Aircraft, 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'' (Army L-
                                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:

------------------------------------------------------------------------
           Actions                 Compliance            Procedures
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(1) Modify the affected GNS   Within the next 6     In accordance with
 430 unit to incorporate       months after          the MODIFICATION
 circuitry changes to the      December 28, 2001     INSTRUCTIONS
 deviation and flag outputs.   (the effective date   section of GARMIN
                               of this AD).          Service Bulletin
                                                     No.: 9905, Revision
                                                     A, dated September
                                                     17, 1999.
------------------------------------------------------------------------
(2) Do not install an         As of December 28,    In accordance with
 affected GNS 430 unit         2001 (the effective   the MODIFICATION
 unless it has been modified   date of this AD).     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 (ACO), 
approves your alternative. Submit your request through an FAA 
Principal Maintenance Inspector, who may add comments and then send 
it to the Manager, Wichita ACO.

    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? 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 airplane 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 airplane to a location where 
you can accomplish the requirements of this AD.
    (h) Are any service bulletins incorporated into this AD by 
reference? Actions required by this AD must be done in accordance 
with GARMIN Service Bulletin No.: 9905, Revision A, dated September 
17, 1999. The Director of the Federal Register approved this 
incorporation by reference under 5 U.S.C. 552(a) and 1 CFR part 51. 
You may obtain copies from GARMIN International, 1200 East 151st 
Street, Olathe, Kansas 66062. 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.
    (i) When does this amendment become effective? This amendment 
becomes effective on December 28, 2001.


    Issued in Kansas City, Missouri, on November 14, 2001.
Michael K. Dahl,
Acting Manager, Small Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 01-29325 Filed 11-30-01; 8:45 am]
BILLING CODE 4910-13-U