Airworthiness Directives; GARMIN International Inc. GTX 33, GTX 33D, GTX 330, and GTX 330D Mode S Transponders, 2937-2941 [05-832]
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Federal Register / Vol. 70, No. 12 / Wednesday, January 19, 2005 / Rules and Regulations
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2004–18743; Directorate
Identifier 2004–CE–23–AD; Amendment 39–
13944; AD 2005–01–19]
RIN 2120–AA64
Airworthiness Directives; GARMIN
International Inc. GTX 33, GTX 33D,
GTX 330, and GTX 330D Mode S
Transponders
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule.
AGENCY:
SUMMARY: The FAA is adopting a new
airworthiness directive (AD) to
supersede Airworthiness Directive
2004–10–15, which applies to certain
GTX 330 and GTX 330D Mode S
transponders that are installed on
airplanes. AD 2004–10–15 currently
requires you to install GTX 330/330D
Software Upgrade Version 3.03, 3.04, or
3.05. This AD applies to certain GTX 33,
GTX 33D, GTX 330, and GTX 330D
Mode S transponders that are installed
on airplanes and is the result of
observations that the GTX 33/33D/330/
330D may detect, from other airplanes,
the S1 (suppression) interrogating pulse
below the minimum trigger level (MTL)
and, in some circumstances, not reply.
The GTX 33/33D/330/330D should still
reply even if it detects S1 interrogating
pulses below the MTL. Consequently,
this AD would require you to install a
GTX 33/33D/330/330D Software
Upgrade to at least Version 3.06. No
additional action is necessary for those
airplanes that have transponders
Software Upgrade 3.03 installed.
Software Upgrade Versions 3.03 and
3.06 correct a TAS, TCAD, and TCAS I
system ‘‘whisper-shout’’ problem that
could potentially lead to the aircraft not
being visible at certain ranges. TCAS II
systems are not affected. We are issuing
this AD to prevent interrogating aircraft
from possibly receiving inaccurate
replies due to suppression from aircraft
equipped with the GTX 33/33D/330/
330D Mode S transponders when the
pulses are below the MTL. The
inaccurate replies could result in
reduced vertical separation.
DATES: This AD becomes effective on
February 23, 2005.
As of February 23, 2005, the Director
of the Federal Register approved the
incorporation by reference of certain
publications listed in the regulation.
ADDRESSES: To get the service
information identified in this AD,
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contact GARMIN International Inc.,
1200 East 151st Street, Olathe, KS
66062; telephone: 913–397–8200. To
review this service information, go to
the National Archives and Records
Administration (NARA). For
information on the availability of this
material at NARA, go to: https://
www.archives.gov/federal_register/
code_of_federal_regulations/
ibr_locations.html or call (202) 741–
6030.
To view the AD docket, go to the
Docket Management Facility; U.S.
Department of Transportation, 400
Seventh Street, SW., Nassif Building,
Room PL–401, Washington, DC 20590–
001 or on the Internet at https://
dms.dot.gov. The docket number is
FAA–2004–18743.
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: 316–946–4107; e-mail
address: roger.souter@faa.gov.
SUPPLEMENTARY INFORMATION:
Discussion
What events have caused this AD?
The GTX 330/GTX 330D may detect
from other aircraft the S1 (suppression)
interrogating pulse below the MTL and,
in some circumstances, does not reply.
The GTX 330/330D should still reply
even if it detects S1 interrogating pulses
below the MTL, and this caused FAA to
issue AD 2004–10–15, Amendment 39–
13645 (69 FR 29212, dated May 21,
2004). AD 2004–10–15 currently
requires the incorporation of GTX 330/
330D Software Upgrade to at least
Version, 3.03, 3.04, or 3.05 on certain
GTX 330 and GTX 330D Mode S
transponders that are installed on
airplanes.
What has happened since AD 2004–
10–15 to initiate this action? After the
issuance of AD 2004–10–15, GARMIN
International Inc. discovered that minor
changes made to GTX 330/330D
Software Upgrades 3.04 and 3.05
inadvertently removed the correction to
not suppress the S1 pulse below MTL.
Garmin also discovered the Software
Upgrade must be installed on GTX 33
and GTX 33D Mode S transponders as
well as the GTX 330 and GTX 330D
Mode S transponders.
What is the potential impact if FAA
took no action? If these changes are not
incorporated, then interrogating aircraft
could possibly receive inaccurate
replies due to suppression from aircraft
equipped with the GTX 33/33D/330/
330D Mode S transponders when the
pulses are below the MTL. Software
PO 00000
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2937
Upgrade Version 3.03 and 3.06 correct
a TAS, TCAD, and TCAS I system
‘‘whisper-shout’’ problem that could
potentially lead to the aircraft not being
visible at certain ranges. TCAS II
systems are not affected. The inaccurate
replies could result in reduced vertical
separation.
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 certain GTX
330 and GTX 330D Mode S
transponders that are installed on
airplanes. This proposal was published
in the Federal Register as a notice of
proposed rulemaking (NPRM) on
October 7, 2004 (69 FR 60100). The
NPRM proposed to require you to install
GTX 33/33D/330/330D Software
Upgrade Version 3.03 or 3.06.
Comments
Was the public invited to comment?
We provided the public the opportunity
to participate in developing this AD.
The following presents the comments
received on the proposal and FAA’s
response to each comment:
Comment Issue: Direct the AD Only to
Those Products That Have the Old SW
Versions 3.00, 3.01, 3.02, 3.04, and 3.05
What is the commenter’s concern?
The NPRM currently requires
installation of GTX 330/330D Software
Upgrade Version 3.03 or 3.06 to comply
with the proposed AD, or later Software
Versions by way of an AMOC. The
commenter would like to direct the AD
only to those products that have the old
software versions 3.00, 3.01, 3.02, 3.04,
and 3.05 installed; so that if the new
software version 3.06 or later is installed
the AD does not affect that product. The
AD should not apply to future software
versions.
What is FAA’s response to the
concern? We concur. This was the
intent of the NPRM, and we have
reworded the AD to reflect this
comment.
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
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—Do not add any additional burden
upon the public than was already
proposed in the NPRM.
Docket Information
Where can I go to view the docket
information? You may view the AD
docket that contains information
relating to this subject in person at the
DMS Docket Offices between 9 a.m. and
5 p.m. (eastern standard time), Monday
through Friday, except Federal holidays.
The Docket Office (telephone 1–800–
647–5227) is located on the plaza level
of the Department of Transportation
NASSIF Building at the street address
stated in ADDRESSES. You may also view
the AD docket on the Internet at
https://dms.dot.gov.
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
5,400 airplanes in the U.S. registry.
What is the cost impact of this AD on
owners/operators of the affected
airplanes? Garmin International Inc.
will provide warranty only for Service
Bulletin No. 0409, dated July 19, 2004
(which incorporates Software Upgrade
3.06) installation as specified in the
service information. Although Software
Upgrade 3.03 is still in compliance with
this proposed AD, if previously
installed, Software Upgrade 3.03 is no
longer available through Garmin.
Authority for This Rulemaking
What authority does FAA have for
issuing this rulemaking action? Title 49
of the United States Code specifies the
FAA’s authority to issue rules on
aviation safety. Subtitle I, Section 106
describes the authority of the FAA
Administrator. Subtitle VII, Aviation
Programs, describes in more detail the
scope of the agency’s authority.
We are issuing this rulemaking under
the authority described in Subtitle VII,
Part A, Subpart III, Section 44701,
‘‘General requirements.’’ Under that
section, Congress charges the FAA with
promoting safe flight of civil aircraft in
air commerce by prescribing regulations
for practices, methods, and procedures
the Administrator finds necessary for
safety in air commerce. This regulation
is within the scope of that authority
because it addresses an unsafe condition
that is likely to exist or develop on
products identified in this AD.
the AD Docket. You may get a copy of
this summary by sending a request to us
at the address listed under ADDRESSES.
Include ‘‘Docket No. FAA–2004–18743;
Directorate Identifier 2004–CE–23–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
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:
I
PART 39—AIRWORTHINESS
DIRECTIVES
1. The authority citation for part 39
continues to read as follows:
I
Authority: 49 U.S.C. 106(g), 40113, 44701.
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
§ 39.13
[Amended]
I 2. FAA amends § 39.13 by removing
AD 2004–10–15, Amendment 39–13645
and adding a new AD to read as follows:
2005–01–19 GARMIN International Inc.:
Amendment 39–13944; Docket No.
FAA–2004–18743; Directorate Identifier
2004–CE–23–AD.
When Does This AD Become Effective?
(a) This AD becomes effective on February
23, 2005.
What Other ADs Are Affected by This
Action?
(b) This AD supersedes AD 2004–10–15,
Amendment 39–13645.
What Airplanes Are Affected by This AD?
(c) This AD affects GARMIN International
Inc. GTX 33, GTX 33D, GTX 330, and GTX
330D Mode S transponders that include
software versions 3.00, 3.01, 3.02, 3.04, or
3.05 that are installed on, but not limited to,
the following airplanes, certificated in any
category:
Manufacturer
Model
(1) Aermacchi S.p.A ...........................................
S.205–18/F, S.205–18/R, S.205–20/R, S.205–22/R, S208, S.208A, F.260, F.260B, F.260C,
F.260D, F.260E, F.260F, S.211A.
AL 60, AL 60–B, AL 60–F5, AL 60–C5, AM–3.
PA–60–600 (Aerostar 600), PA–60–601 (Aerostar 601), PA–60–601P (Aerostar 601P), PA–
60–602P (Aerostar 602P), PA–60–700P (Aerostar 700P), 360, 400.
14–19, 14–19–2, 14–19–3, 14–19–3A, 17–30, 17–31, 17–31TC, 17–30A, 17–31A, 17–31ATC
15A, 20, H–250, H–295 (USAFU–10D), HT–295, H391 (USAFYL–24), H391B, H–395
(USAFL–28A or U–10B), H–395A, H–700, H–800, HST–550, HST–550A (USAF AU–24A),
500.
402, 7GCA, 7GCB, 7KC, 7GCBA, 7GCAA, 7GCBC, 7KCAB, 8KCAB, 8GCBC.
A–1, A–1A, A–1B, S–1S, S–1T, S–2, S–2A, S–2S, S–2C.
BN–2, BN–2A, BN–2A–2, BN–2A–3, BN–2A–6, BN–2A–8, BN–2A–8, BN–2A–20, BN–2A–21,
BN–2A–26, BN–2A–27, BN–2B–20, BN–2B–21, BN–2A–26, BN–2A–27, BN–2B–20, BN–
2B–21, BN–2B–26, BN–2B–27, BN–2T, BN–2T–4R, BN–2A MK.III, BN2A MK. III–2, BN2A
MK. 111–3.
14–13, 14–13–2, 14–13–3, 14–13–3W.
(2) Aeronautica Macchi S.p.A .............................
(3) Aerostar Aircraft Corporation ........................
(4) Alexandria Aircraft, LLC ................................
(5) Alliance Aircraft Group LLC ..........................
(6) American Champion Aircraft Corp ................
(7) Sky International Inc .....................................
(8) B–N Group Ltd ..............................................
(9) Bellanca .........................................................
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2939
Manufacturer
Model
(10) Bombardier Inc ............................................
(11) Cessna Aircraft Company ...........................
(Otter) DHC–3, DHC–6–1, DHC–6–100, DHC–6–200, DHC–6–300.
170, 170A, 170B, 172, 172A, 172B, 172C, 172D, 172E, 172F (USAF T–41A), 172G, 172H
(USAF T041A), 172I, 172K, 172L, 172M, 172N, 172P, 172Q, 172R, 172S, 172RG, P172D,
R172E (USAF T–41 B) (USAF T–41 C AND D), R172F (USAF T–41 D), R175G, R172H
(USAF T–41 D), R172J, R172K, 175, 175A, 175B, 175C, 177, 177A, 177B, 177RG, 180,
180A, 180B, 180C, 180D, 180E, 180F, 180G, 180H, 180J, 180K, 182, 182A, 182B, 182C,
182D, 182E, 182F, 182G, 182H, 182J, 182K, 182L, 182M, 182N, 182P, 182Q, 182R, 182S,
182T, R182, T182, TR182, T182T, 185, 185A, 185B, 185C, 185D, 185E, A185E, A185F,
190, (LC–126A, B, C) 195, 195A, 195B, 210, 210A, 210B, 210C, 210D, 210E, 210F, T210F,
210G, T210G, 210H, T210H, 210J, T210J, 210K, T210K, 210L, T210L, 210M, T210M,
210N, P210N, T210N, 210R, P210R, T210R, 210–5 (205), 210–5A (205A), 206, P206,
P206A, P206B, P206C, P206D, P206E, TP206A, TP206B, TP206C, TU206D, TU206E,
TU206F, TU206G, 206H, T206H, 207, 207A, T207, T207A, 208, 208A, 208B, 310, 310A
(USAF U–3A), 310B, 310C, 310D, 310E (USAF U–3B), 310F, 310G, 310H, E310H, 310I,
310J, 310J–1, E310J, 310K, 310L, 310N, 310P, T310P, 310Q, T310Q, 310R, T310R, 320,
320A, 320B, 320C, 320D, 320E, 320F, 320–1, 335, 340, 340A, 336, 337, 337A (USAF 02B),
337B, T337B, 337C, 337E, T337E, T337C, 337D, T337D, M337B (USAF 02A), 337F,
T337F, T337G, 337G, 337H, P337H, T337H, T337H–SP, 401, 401A, 401B, 402, 402A,
402B, 402C, 411, 411A, 414, 414A, 421, 421A, 421B, 421C, 425, 404, 406, 441.
SR20, SR22.
112, 112TC, 112B, 112TCA, 114, 114A, 114B, 114TC.
DHC–2 Mk. I, DHC–2 Mk. II, DHC–2 Mk. III.
(Volaire) 10, (Volaire) 10A, (Aero Commander) 100, (Aero Commander) 100A, (Aero Commander) 100–180.
DA 20–A1, DA20–C1, DA 40.
EMB–110P1, EMB–110P2.
(12)
(13)
(14)
(15)
Cirrus Design Corporation ..........................
Commander Aircraft Company ...................
de Havilland Inc ..........................................
Dynac Aerospace Corporation ....................
(16) Diamond Aircraft Industries .........................
(17) Empressa Brasileira de Aeronautica S.A.
EMBRAER.
(18) Extra Flugzeugbau Gmbh ...........................
(19) Fairchild Aircraft Corporation ......................
(20) Global Amphibians, LLC .............................
(21)
(22)
(23)
(24)
(25)
(26)
(27)
Grob-Werke .................................................
Lancair Company ........................................
LanShe Aerospace, LLC .............................
Learjet Inc. ..................................................
Lockheed Aircraft Corporation ....................
Luscombe Aircraft Corporation ...................
Maule Aerospace Technology, Inc .............
(28) Mitsubishi Heavy Industries, Ltd .................
(29) Mooney Airplane Company, Inc ..................
(30) Moravan a.s ................................................
(31) Navion Aircraft Company, Ltd .....................
(32) New Piper Aircraft, Inc ................................
(33) Ostmecklenburgische Flugzeugbau GmgH
(34) Piaggio Aero Industries S.p.A .....................
(35) Pilatus Aircraft Ltd .......................................
(36) Prop-Jets, Inc ..............................................
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EA300, EA300L, EA300S, EA300/200, EA–400.
SA26–T, SA26–AT, SA226–T, SA226–AT, SA226–T(B), SA227–AT, SA227–TT, SA226–TC,
SA227–AC (C–26A), SA227–CC, SA227–DC (C–26B).
Colonial C–1, Colonial C–2, Lake LA–4, Lake LA–4A, Lake LA–4P, Lake LA–4–200, Lake
Model 250.
G115, G115A, G115B, G115C, G115C2, G115D, G115D2, G115EG, G120A.
LC40–550FG.
MAC–125C, MAC–145, MAC–145A, MAC–145B.
23.
18.
11A, 11E.
Bee Dee M–4, M–4, M–4C, M–4S, M–4T, M–4180C, M–4–180S, M–4–180T, M–4–210, M–4–
210C, M–4–210S, M–4–210T, M–4–220, M–4–220S, M–4–220T, M–5–180C, M–5–200, M–
5–210C, M–5–210TC, M–5–220C, M–5–235C, M–6–180, M–6–235, M–7–235, MX–7–235,
MX–7–180, MX–7–420, MXT–7–180, MT–7–235, M–8–235, MX–7–160, MXT–7–160, MX–
7–180A, MXT–7–180A, MX–7–180B, M–7–235B, M–7–235A, M–7–235C, MX–7–180C, M–
7–260, MT–7–260, M–7–260C, M–7–420AC, MX–7–160C, MX–7–180AC, M–7–420A, MT–
7–420.
MU–2B–25, MU–2B–35, MU–2B–26, MU–2B–36, MU–2B–26A, MU–2B–36A, MU–2B–40,
MU–2B–60, MU–2B, MU–2B–20, MU–2B–15.
M20, M20A, M20B, M20C, M20D, M20E, M20F, M20G, M20J, M20K, M20L, M20M, M20R,
M20S, M22.
Z–242L, Z–143L.
NAVION, Navion (L–17A), Navion (L17B), Navion (L–17C), Navion B, Navion D, Navion E,
Navion F, Navion G, Navion H.
PA–12, PA–12S, PA–18, PA–18S, PA–18 ‘‘105’’ (Special), PA–18S ‘‘105’’ (Special), PA–18A,
PA–18 ‘‘125’’ (Army L–21A), PA–18S ‘‘125,’’ PA–18AS ‘‘125,’’ PA–18 ‘‘135’’ (Army L–21B),
PA–18A ‘‘135,’’ PA–18S ‘‘135,’’ PA–18 ‘‘150,’’ PA–18A ‘‘150,’’ PA–18S ‘‘150,’’ PA–18AS
‘‘150,’’ PA–19 (Army L–18B), PA–19S, PA–20, PA–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–23, PA–23–160, PA–23–235, PA–23–250, PA–
E23–250, PA–24, PA–24–250, PA–24–260, PA–24–400, 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, PA–28–236, PA–30, PA–39, PA–40, PA–31P, PA–31T, PA–
31T1, PA–31T2, PA–31T3, PA–31P–350, PA–32–260, PA–32–300, PA–32S–300, PA–32R–
300, PA–32RT–300, PA–32RT–300T, PA–32R–301 (SP), PA–32R–301 (HP), PA–32R–
301T, PA–32–301, PA–32–301T, PA–34–200, PA–34–200T, PA–34–220T, PA–42, PA–42–
720, PA–42–1000, PA–42–720R, PA–44–180, PA–44–180T, PA–46–310P, PA–46–350P,
PA–46–500TP.
OMF–100–160.
P–180.
PILATUS PC–12, PILATUS PC–12/45, PC–6, PC–6–H1, PC–6–H2, PC–6/350, PC–6/350–H1,
PC–6/350–H2, PC–6/A, PC–6/A–H1, PA–6/A–H2, PC–6/B–H2, PC–6/B1–H2, PC–6/B2–H2,
PC–6/B2–H4, PC–6/C–H2, PC–6/C1–H2, PC–7.
200, 200A, 200B, 200C, 200D, 400.
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Manufacturer
Model
(37) Panstwowe Zakladv Lotnicze (PZL) ...........
PZL–104 WILGA 80, PZL–104M WILGA 2000, PZL–WARSZAWA, PZL–KOLIBER 150A, PZL–
KOLIBER 160A.
PZL M20 03, PZL M26 01.
35–33, 35–A33, 35–B33, 35–C33, 35–C33A, E33, E33A, E33C, F33, F33A, F33C, G33, H35,
J35, K35, M35, N35, P35, S35, V35, V35A, V35B, 36, A36, A36TC, B36TC, 35, A35, B35,
C35, D35, E35, F35, G35, 35R, F90, 76, 200, 200C, 200CT, 200T, A200, B200, B200C,
B200CT, B200T, 300, 300LW, B300, B300C, 1900, 1900C, 1900D, A100–1 (U–21J), A200
(C–12A), A200 (C–12C), A200C (UC–12B), A200CT (C–12D), A200CT (FWC–12D),
A200CT (RC–12D), A200CT (C–12F), A200CT (RC–12G), A200CT (RC–12H), A200CT
(RC–12K), A200CT (RC–12P), A200CT (RC–12Q), B200C (C–12F), B200C (UC–12F),
B200C (UC–12M), B200C (C–12R), 1900C (C–12J), 65, A65, A65–8200, 65–80, 65–A80,
65–A80–8800, 65–B80, 65–88, 65–A90, 70, B90, C90, C90A, E90, H90, 65–A90–1, 65–
A90–2, 65–A90–3, 65–A90–4, 95, B95, B95A, D95A, E95, 95–55, 95–A55, 95–B55, 95–
B55A, 95–B55B (T–42A), 95–C55, 95–C55A, D55, D55A, E55, E55A, 56TC, A56TC, 58,
58A, 58P, 58PA, 58TC, 58TCA, 99, 99A, 99A (FACH), A99, A99A, B99, C99, 100, A100
(U–21F), A100A, A100C, B100, 2000, 3000, 390, 19A, B19, M19A, 23, A23, A23A, A23–19,
A23–24, B23, C23, A24, A24R, B24R, C24R, 60, A60, B60, 18D, A18A, A18D, S18D,
SA18A, SA18D, 3N, 3NM, 3TM, JRB–6, D18C, D18S, E18S, RC–45J (SNB–5P), E18S–
9700, G18S, H18, C–45G, TC–45G, C–45H, TC–45H, TC–45J, UC–45J (SNB–5), 50 (L–
23A), B50 (L–23B), C50, D50 (L–23E), D50A, D50B, D50C, D50E–5990, E50 (L–23D, RL–
23D), F50, G50, H50, J50, 45 (YT–34), A45 (T–34A or B–45), D45 (T–34B).
BC–1A, AT–6 (SNJ–2), AT–6A (SNJ–3), AT–6B, AT–6C (SNJ–4), AT–6D (SNJ–5), AT–6F
(SNF–6), SNJ–7, T–6G, NOMAD NA–260.
SC–7 Series 2, SC–7 Series 3.
T67M260, T67M260–T3A.
TB9, TB10, TB20, TB21, TB200, TBM 700, M.S. 760, M.S. 760 A, M.S. 760 B, Rallye 100S,
Rallye 150ST, Rallye 150T, Rallye 235E, Rallye 235C, MS 880B, MS 885, MS 894A, MS
893A, MS 892A–150, MS 892E–150, MS 893E, MS 894E, GA–7.
AA–1, AA–1A, AA–1B, AA–1C, AA–5, AA–5A, AA–5B, AG–5B.
500, 500–A, 500–B, 500–U, 500–S, 520, 560, 560–A, 560–E, 560F, 680, 680E, 680F, 680FL,
680FL(P), 680T, 680V, 680W, 681, 685, 690, 690A, 690B, 690C, 690D, 695, 695A, 695B,
720, 700.
108, 108–1, 108–2, 108–3, 108–5.
P68, P68B, P68C, P68C–TC, P68 ‘‘Observer,’’ P68 ‘‘Observer 2,’’ P68TC ‘‘Observer,’’
AP68TP300 ‘‘Spartacus,’’ AP68TP 600 ‘‘Viator’’.
CH2000.
(38) PZL WSK/Mielec Obrsk ..............................
(39) Raytheon .....................................................
(40) Rockwell International Corporation .............
(41) Short Brothers & Harland Ltd .....................
(42) Slingsby Aviation Ltd ...................................
(43) SOCATA—Group Aerospatiale ...................
(44) Tiger Aircraft LLC ........................................
(45) Twin Commander Aircraft Corporation .......
(46) Univair Aircraft Corporation .........................
(47) Vulcanair S.p.A ...........................................
(48) Zenair Ltd. ...................................................
S1 interrogating pulses below the MTL. The
actions specified in this AD are intended to
prevent interrogating aircraft from possibly
receiving inaccurate replies, due to
suppression, from aircraft equipped with the
GTX 33/33D/330/330D Mode S transponders
when the pulses are below the minimum
trigger level (MTL). Software Upgrade
Versions 3.03 and 3.06 correct a TAS, TCAD,
and TCAS I system ‘‘whisper-shout’’ problem
that could potentially lead to the aircraft not
being visible at certain ranges. TCAS II
systems are not affected. The inaccurate
replies could result in reduced vertical
separation.
Actions
Compliance
Procedures
Install GTX 33/33D/330/330D Software Upgrade for transponders with software version
3.00, 3.01, 3.02, 3.04, 3.05 to at least
version 3.06. If version 3.03 is already installed, no further action is required. This
version is no longer available from Garmin.
This AD does not apply to software versions
past 3.05.
Install the software upgrade within 180 days
after February 23, 2005 (the effective date
of this AD), unless already accomplished.
Follow GARMIN Mandatory Software Service
Bulletin No.: 0304, Rev B, dated June 12,
2003 accomplished. (Software Upgrade
3.03) or GARMIN Mandatory Software Service Bulletin No.: 0409, dated July 19, 2004
(Software Upgrade 3.06).
May I Request an Alternative Method of
Compliance?
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:
316–946–4107; email address:
roger.souter@faa.gov.
Does This AD Incorporate Any Material by
Reference?
What Is the Unsafe Condition Presented in
This AD?
(d) This AD is the result of observations
that the GTX 33/33D/330/330D may detect,
from other airplanes, the S1 (suppression)
interrogating pulse below the minimum
trigger level (MTL) and, in some
circumstances, not reply. The GTX 33/33D/
330/330D should still reply even if it detects
(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. 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, Wichita Aircraft Certification Office
(ACO), FAA. For information on any already
VerDate jul<14>2003
15:11 Jan 18, 2005
Jkt 205001
PO 00000
Frm 00014
Fmt 4700
Sfmt 4700
What Must I Do To Address This Problem?
(e) To address this problem, you must do
the following:
(g) You must do the actions required by
this AD following the instructions in
GARMIN Mandatory Software Service
Bulletin No.: 0304, Rev B, dated June 12,
2003 (Software Upgrade 3.03) or GARMIN
Mandatory Software Service Bulletin No.:
0409, dated July 19, 2004 (Software Upgrade
3.06). The Director of the Federal Register
approved the incorporation by reference of
E:\FR\FM\19JAR1.SGM
19JAR1
Federal Register / Vol. 70, No. 12 / Wednesday, January 19, 2005 / Rules and Regulations
this service bulletin in accordance with 5
U.S.C. 552(a) and 1 CFR part 51. To get a
copy of this service information, contact
GARMIN International Inc. 1200 East 151st
Street, Olathe, KS 66062; telephone: 913–
397–8200. To review copies of this service
information, go to the National Archives and
Records Administration (NARA). For
information on the availability of this
material at NARA, go to: https://
www.archives.gov/federal_register/
code_of_federal_regulations/
ibr_locations.html or call (202) 741–6030. To
view the AD docket, go to the Docket
Management Facility; U.S. Department of
Transportation, 400 Seventh Street, SW.,
Nassif Building, Room PL–401, Washington,
DC 20590–001 or on the Internet at https://
dms.dot.gov. The docket number is FAA–
2004–18743.
Issued in Kansas City, Missouri, on January
7, 2005.
James E. Jackson,
Acting Manager, Small Airplane Directorate,
Aircraft Certification Service.
[FR Doc. 05–832 Filed 1–18–05; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 2004–CE–01–AD; Amendment
39–13943; AD 2005–01–18]
RIN 2120–AA64
Airworthiness Directives; Raytheon
Aircraft Company Beech 100, 200, and
300 Series Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule.
AGENCY:
SUMMARY: The FAA adopts a new
airworthiness directive (AD) to
supersede AD 93–25–07, which applies
to Raytheon Aircraft Company
(Raytheon) Beech 100, 200, and 300
series airplanes. AD 93–25–07 currently
requires you to repetitively inspect the
fuselage stringers for cracks and modify
at certain times depending on the
number of cracked stringers. This AD is
the result of FAA’s policy (since 1996)
to not allow airplane operation when
known cracks exist in primary structure.
The fuselage structure is considered
primary structure and operation is
currently allowed for a certain period of
time if less than five fuselage stringers
are cracked. Consequently, this AD
retains the inspection and modification
requirements of AD 93–25–07, but
requires you to repair any cracked
fuselage stringers. We are issuing this
AD to detect and correct any cracked
fuselage stringers in the rear pressure
VerDate jul<14>2003
15:11 Jan 18, 2005
Jkt 205001
bulkhead area, which could result in
structural damage to the fuselage. This
damage could lead to failure of the
fuselage with potential loss of control of
the airplane.
DATES: This AD becomes effective on
March 1, 2005.
As of March 1, 2005, the Director of
the Federal Register approved the
incorporation by reference of certain
publications listed in the regulation.
ADDRESSES: You may get the service
information identified in this AD from
Raytheon Aircraft Company, 9709 E.
Central, Wichita, Kansas 67201–0085;
telephone: (800) 429–5372 or (316) 676–
3140.
You may view the AD docket at FAA,
Central Region, Office of the Regional
Counsel, Attention: Rules Docket No.
2004–CE–01–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:
Steven E. Potter, Aerospace Engineer,
Wichita Aircraft Certification Office
(ACO), FAA, 1801 Airport Road,
Wichita, Kansas 67209; telephone: (316)
946–4124; facsimile: (316) 946–4107.
SUPPLEMENTARY INFORMATION:
Discussion
What events have caused this AD?
Reports of cracks on the fuselage
stringers in the rear pressure bulkhead
area on Raytheon Beech 100, 200, and
300 series airplanes caused us to issue
AD 93–25–07, Amendment 39–8773.
AD 93–25–07 currently requires the
following on Raytheon Beech Models
200, A200, B200, A100–1, 200C, A200C,
B200C, 200CT, A200CT, B200CT, 200T,
B200T, 300, B300, and B300C airplanes:
—Repetitive inspections of the fuselage
stringers for cracks; and
—Modification at certain times
depending on the number of cracked
stringers.
What has happened since AD 93–25–
07 to initiate this action? As currently
written, AD 93–25–07 allows continued
flight if cracks are found in less than
five fuselage stringers in the area of the
rear pressure bulkhead. In 1996, FAA
developed policy to not allow airplane
operation when known cracks exist in
primary structure, unless the ability to
sustain limit and ultimate load with
these cracks is proven. The fuselage
stringers in the area of the rear pressure
bulkhead are considered primary
structure.
This AD brings the actions of AD 93–
25–07 in compliance with FAA policy.
Therefore, FAA has determined:
—That airplane operation on the
affected airplanes should not be
PO 00000
Frm 00015
Fmt 4700
Sfmt 4700
2941
allowed for more than 25 hours timein-service (TIS) if less than five
fuselage stringers (Stringer Nos. 5
through 11) in the rear pressure
bulkhead are cracked; and
—That no operation should be allowed
until modification for any airplane
with five or more cracked fuselage
stringers (Stringer Nos. 5 through 11)
in the rear pressure bulkhead.
The FAA has also identified other
airplanes that should be affected by this
action.
What is the potential impact if FAA
took no action? Cracked fuselage
stringers in the rear pressure bulkhead
area, if not detected and corrected,
could result in structural damage to the
fuselage. This damage could lead to
failure of the fuselage with potential
loss of control of the airplane.
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 certain
Raytheon Beech 100, 200, and 300 series
airplanes. This proposal was published
in the Federal Register as a notice of
proposed rulemaking (NPRM) on
September 14, 2004 (69 FR 55369). The
NPRM proposed to supersede AD 93–
25–07 with a new AD that would retain
the requirement of repetitively
inspecting the fuselage stringers for
cracks, but would require the repair of
any cracked fuselage stringers. We also
proposed a grace period of 25 cycles for
all airplanes with less than five cracked
fuselage stringers. The repetitive
inspections would no longer be required
when all fuselage stringers (Nos. 5
though 11) in the rear pressure bulkhead
are modified.
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.
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
minor editorial corrections. We have
determined that these 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.
E:\FR\FM\19JAR1.SGM
19JAR1
]]>Agencies
[Federal Register Volume 70, Number 12 (Wednesday, January 19, 2005)]
[Rules and Regulations]
[Pages 2937-2941]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 05-832]
[[Page 2937]]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2004-18743; Directorate Identifier 2004-CE-23-AD;
Amendment 39-13944; AD 2005-01-19]
RIN 2120-AA64
Airworthiness Directives; GARMIN International Inc. GTX 33, GTX
33D, GTX 330, and GTX 330D Mode S Transponders
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Final rule.
-----------------------------------------------------------------------
SUMMARY: The FAA is adopting a new airworthiness directive (AD) to
supersede Airworthiness Directive 2004-10-15, which applies to certain
GTX 330 and GTX 330D Mode S transponders that are installed on
airplanes. AD 2004-10-15 currently requires you to install GTX 330/330D
Software Upgrade Version 3.03, 3.04, or 3.05. This AD applies to
certain GTX 33, GTX 33D, GTX 330, and GTX 330D Mode S transponders that
are installed on airplanes and is the result of observations that the
GTX 33/33D/330/330D may detect, from other airplanes, the S1
(suppression) interrogating pulse below the minimum trigger level (MTL)
and, in some circumstances, not reply. The GTX 33/33D/330/330D should
still reply even if it detects S1 interrogating pulses below the MTL.
Consequently, this AD would require you to install a GTX 33/33D/330/
330D Software Upgrade to at least Version 3.06. No additional action is
necessary for those airplanes that have transponders Software Upgrade
3.03 installed. Software Upgrade Versions 3.03 and 3.06 correct a TAS,
TCAD, and TCAS I system ``whisper-shout'' problem that could
potentially lead to the aircraft not being visible at certain ranges.
TCAS II systems are not affected. We are issuing this AD to prevent
interrogating aircraft from possibly receiving inaccurate replies due
to suppression from aircraft equipped with the GTX 33/33D/330/330D Mode
S transponders when the pulses are below the MTL. The inaccurate
replies could result in reduced vertical separation.
DATES: This AD becomes effective on February 23, 2005.
As of February 23, 2005, the Director of the Federal Register
approved the incorporation by reference of certain publications listed
in the regulation.
ADDRESSES: To get the service information identified in this AD,
contact GARMIN International Inc., 1200 East 151st Street, Olathe, KS
66062; telephone: 913-397-8200. To review this service information, go
to the National Archives and Records Administration (NARA). For
information on the availability of this material at NARA, go to: http:/
/www.archives.gov/federal_register/code_of_federal_regulations/
ibr_locations.html or call (202) 741-6030.
To view the AD docket, go to the Docket Management Facility; U.S.
Department of Transportation, 400 Seventh Street, SW., Nassif Building,
Room PL-401, Washington, DC 20590-001 or on the Internet at https://
dms.dot.gov. The docket number is FAA-2004-18743.
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: 316-946-4107; e-mail
address: roger.souter@faa.gov.
SUPPLEMENTARY INFORMATION:
Discussion
What events have caused this AD? The GTX 330/GTX 330D may detect
from other aircraft the S1 (suppression) interrogating pulse below the
MTL and, in some circumstances, does not reply. The GTX 330/330D should
still reply even if it detects S1 interrogating pulses below the MTL,
and this caused FAA to issue AD 2004-10-15, Amendment 39-13645 (69 FR
29212, dated May 21, 2004). AD 2004-10-15 currently requires the
incorporation of GTX 330/330D Software Upgrade to at least Version,
3.03, 3.04, or 3.05 on certain GTX 330 and GTX 330D Mode S transponders
that are installed on airplanes.
What has happened since AD 2004-10-15 to initiate this action?
After the issuance of AD 2004-10-15, GARMIN International Inc.
discovered that minor changes made to GTX 330/330D Software Upgrades
3.04 and 3.05 inadvertently removed the correction to not suppress the
S1 pulse below MTL. Garmin also discovered the Software Upgrade must be
installed on GTX 33 and GTX 33D Mode S transponders as well as the GTX
330 and GTX 330D Mode S transponders.
What is the potential impact if FAA took no action? If these
changes are not incorporated, then interrogating aircraft could
possibly receive inaccurate replies due to suppression from aircraft
equipped with the GTX 33/33D/330/330D Mode S transponders when the
pulses are below the MTL. Software Upgrade Version 3.03 and 3.06
correct a TAS, TCAD, and TCAS I system ``whisper-shout'' problem that
could potentially lead to the aircraft not being visible at certain
ranges. TCAS II systems are not affected. The inaccurate replies could
result in reduced vertical separation.
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 certain GTX 330 and GTX 330D Mode S
transponders that are installed on airplanes. This proposal was
published in the Federal Register as a notice of proposed rulemaking
(NPRM) on October 7, 2004 (69 FR 60100). The NPRM proposed to require
you to install GTX 33/33D/330/330D Software Upgrade Version 3.03 or
3.06.
Comments
Was the public invited to comment? We provided the public the
opportunity to participate in developing this AD. The following
presents the comments received on the proposal and FAA's response to
each comment:
Comment Issue: Direct the AD Only to Those Products That Have the Old
SW Versions 3.00, 3.01, 3.02, 3.04, and 3.05
What is the commenter's concern? The NPRM currently requires
installation of GTX 330/330D Software Upgrade Version 3.03 or 3.06 to
comply with the proposed AD, or later Software Versions by way of an
AMOC. The commenter would like to direct the AD only to those products
that have the old software versions 3.00, 3.01, 3.02, 3.04, and 3.05
installed; so that if the new software version 3.06 or later is
installed the AD does not affect that product. The AD should not apply
to future software versions.
What is FAA's response to the concern? We concur. This was the
intent of the NPRM, and we have reworded the AD to reflect this
comment.
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
[[Page 2938]]
--Do not add any additional burden upon the public than was already
proposed in the NPRM.
Docket Information
Where can I go to view the docket information? You may view the AD
docket that contains information relating to this subject in person at
the DMS Docket Offices between 9 a.m. and 5 p.m. (eastern standard
time), Monday through Friday, except Federal holidays. The Docket
Office (telephone 1-800-647-5227) is located on the plaza level of the
Department of Transportation NASSIF Building at the street address
stated in ADDRESSES. You may also view the AD docket on the Internet at
https://dms.dot.gov.
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 5,400 airplanes in the U.S. registry.
What is the cost impact of this AD on owners/operators of the
affected airplanes? Garmin International Inc. will provide warranty
only for Service Bulletin No. 0409, dated July 19, 2004 (which
incorporates Software Upgrade 3.06) installation as specified in the
service information. Although Software Upgrade 3.03 is still in
compliance with this proposed AD, if previously installed, Software
Upgrade 3.03 is no longer available through Garmin.
Authority for This Rulemaking
What authority does FAA have for issuing this rulemaking action?
Title 49 of the United States Code specifies the FAA's authority to
issue rules on aviation safety. Subtitle I, Section 106 describes the
authority of the FAA Administrator. Subtitle VII, Aviation Programs,
describes in more detail the scope of the agency's authority.
We are issuing this rulemaking under the authority described in
Subtitle VII, Part A, Subpart III, Section 44701, ``General
requirements.'' Under that section, Congress charges the FAA with
promoting safe flight of civil aircraft in air commerce by prescribing
regulations for practices, methods, and procedures the Administrator
finds necessary for safety in air commerce. This regulation is within
the scope of that authority because it addresses an unsafe condition
that is likely to exist or develop on products identified in this AD.
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
``Docket No. FAA-2004-18743; Directorate Identifier 2004-CE-23-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. FAA amends Sec. 39.13 by removing AD 2004-10-15, Amendment 39-13645
and adding a new AD to read as follows:
2005-01-19 GARMIN International Inc.: Amendment 39-13944; Docket No.
FAA-2004-18743; Directorate Identifier 2004-CE-23-AD.
When Does This AD Become Effective?
(a) This AD becomes effective on February 23, 2005.
What Other ADs Are Affected by This Action?
(b) This AD supersedes AD 2004-10-15, Amendment 39-13645.
What Airplanes Are Affected by This AD?
(c) This AD affects GARMIN International Inc. GTX 33, GTX 33D,
GTX 330, and GTX 330D Mode S transponders that include software
versions 3.00, 3.01, 3.02, 3.04, or 3.05 that are installed on, but
not limited to, the following airplanes, certificated in any
category:
------------------------------------------------------------------------
Manufacturer Model
------------------------------------------------------------------------
(1) Aermacchi S.p.A.......... S.205-18/F, S.205-18/R, S.205-20/R, S.205-
22/R, S208, S.208A, F.260, F.260B,
F.260C, F.260D, F.260E, F.260F, S.211A.
(2) Aeronautica Macchi S.p.A. AL 60, AL 60-B, AL 60-F5, AL 60-C5, AM-3.
(3) Aerostar Aircraft PA-60-600 (Aerostar 600), PA-60-601
Corporation. (Aerostar 601), PA-60-601P (Aerostar
601P), PA-60-602P (Aerostar 602P), PA-60-
700P (Aerostar 700P), 360, 400.
(4) Alexandria Aircraft, LLC. 14-19, 14-19-2, 14-19-3, 14-19-3A, 17-30,
17-31, 17-31TC, 17-30A, 17-31A, 17-31ATC
(5) Alliance Aircraft Group 15A, 20, H-250, H-295 (USAFU-10D), HT-
LLC. 295, H391 (USAFYL-24), H391B, H-395
(USAFL-28A or U-10B), H-395A, H-700, H-
800, HST-550, HST-550A (USAF AU-24A),
500.
(6) American Champion 402, 7GCA, 7GCB, 7KC, 7GCBA, 7GCAA,
Aircraft Corp. 7GCBC, 7KCAB, 8KCAB, 8GCBC.
(7) Sky International Inc.... A-1, A-1A, A-1B, S-1S, S-1T, S-2, S-2A, S-
2S, S-2C.
(8) B-N Group Ltd............ BN-2, BN-2A, BN-2A-2, BN-2A-3, BN-2A-6,
BN-2A-8, BN-2A-8, BN-2A-20, BN-2A-21, BN-
2A-26, BN-2A-27, BN-2B-20, BN-2B-21, BN-
2A-26, BN-2A-27, BN-2B-20, BN-2B-21, BN-
2B-26, BN-2B-27, BN-2T, BN-2T-4R, BN-2A
MK.III, BN2A MK. III-2, BN2A MK. 111-3.
(9) Bellanca................. 14-13, 14-13-2, 14-13-3, 14-13-3W.
[[Page 2939]]
(10) Bombardier Inc.......... (Otter) DHC-3, DHC-6-1, DHC-6-100, DHC-6-
200, DHC-6-300.
(11) Cessna Aircraft Company. 170, 170A, 170B, 172, 172A, 172B, 172C,
172D, 172E, 172F (USAF T-41A), 172G,
172H (USAF T041A), 172I, 172K, 172L,
172M, 172N, 172P, 172Q, 172R, 172S,
172RG, P172D, R172E (USAF T-41 B) (USAF
T-41 C AND D), R172F (USAF T-41 D),
R175G, R172H (USAF T-41 D), R172J,
R172K, 175, 175A, 175B, 175C, 177, 177A,
177B, 177RG, 180, 180A, 180B, 180C,
180D, 180E, 180F, 180G, 180H, 180J,
180K, 182, 182A, 182B, 182C, 182D, 182E,
182F, 182G, 182H, 182J, 182K, 182L,
182M, 182N, 182P, 182Q, 182R, 182S,
182T, R182, T182, TR182, T182T, 185,
185A, 185B, 185C, 185D, 185E, A185E,
A185F, 190, (LC-126A, B, C) 195, 195A,
195B, 210, 210A, 210B, 210C, 210D, 210E,
210F, T210F, 210G, T210G, 210H, T210H,
210J, T210J, 210K, T210K, 210L, T210L,
210M, T210M, 210N, P210N, T210N, 210R,
P210R, T210R, 210-5 (205), 210-5A
(205A), 206, P206, P206A, P206B, P206C,
P206D, P206E, TP206A, TP206B, TP206C,
TU206D, TU206E, TU206F, TU206G, 206H,
T206H, 207, 207A, T207, T207A, 208,
208A, 208B, 310, 310A (USAF U-3A), 310B,
310C, 310D, 310E (USAF U-3B), 310F,
310G, 310H, E310H, 310I, 310J, 310J-1,
E310J, 310K, 310L, 310N, 310P, T310P,
310Q, T310Q, 310R, T310R, 320, 320A,
320B, 320C, 320D, 320E, 320F, 320-1,
335, 340, 340A, 336, 337, 337A (USAF
02B), 337B, T337B, 337C, 337E, T337E,
T337C, 337D, T337D, M337B (USAF 02A),
337F, T337F, T337G, 337G, 337H, P337H,
T337H, T337H-SP, 401, 401A, 401B, 402,
402A, 402B, 402C, 411, 411A, 414, 414A,
421, 421A, 421B, 421C, 425, 404, 406,
441.
(12) Cirrus Design SR20, SR22.
Corporation.
(13) Commander Aircraft 112, 112TC, 112B, 112TCA, 114, 114A,
Company. 114B, 114TC.
(14) de Havilland Inc........ DHC-2 Mk. I, DHC-2 Mk. II, DHC-2 Mk. III.
(15) Dynac Aerospace (Volaire) 10, (Volaire) 10A, (Aero
Corporation. Commander) 100, (Aero Commander) 100A,
(Aero Commander) 100-180.
(16) Diamond Aircraft DA 20-A1, DA20-C1, DA 40.
Industries.
(17) Empressa Brasileira de EMB-110P1, EMB-110P2.
Aeronautica S.A. EMBRAER.
(18) Extra Flugzeugbau Gmbh.. EA300, EA300L, EA300S, EA300/200, EA-400.
(19) Fairchild Aircraft SA26-T, SA26-AT, SA226-T, SA226-AT, SA226-
Corporation. T(B), SA227-AT, SA227-TT, SA226-TC,
SA227-AC (C-26A), SA227-CC, SA227-DC (C-
26B).
(20) Global Amphibians, LLC.. Colonial C-1, Colonial C-2, Lake LA-4,
Lake LA-4A, Lake LA-4P, Lake LA-4-200,
Lake Model 250.
(21) Grob-Werke.............. G115, G115A, G115B, G115C, G115C2, G115D,
G115D2, G115EG, G120A.
(22) Lancair Company......... LC40-550FG.
(23) LanShe Aerospace, LLC... MAC-125C, MAC-145, MAC-145A, MAC-145B.
(24) Learjet Inc............. 23.
(25) Lockheed Aircraft 18.
Corporation.
(26) Luscombe Aircraft 11A, 11E.
Corporation.
(27) Maule Aerospace Bee Dee M-4, M-4, M-4C, M-4S, M-4T, M-
Technology, Inc. 4180C, M-4-180S, M-4-180T, M-4-210, M-4-
210C, M-4-210S, M-4-210T, M-4-220, M-4-
220S, M-4-220T, M-5-180C, M-5-200, M-5-
210C, M-5-210TC, M-5-220C, M-5-235C, M-6-
180, M-6-235, M-7-235, MX-7-235, MX-7-
180, MX-7-420, MXT-7-180, MT-7-235, M-8-
235, MX-7-160, MXT-7-160, MX-7-180A, MXT-
7-180A, MX-7-180B, M-7-235B, M-7-235A, M-
7-235C, MX-7-180C, M-7-260, MT-7-260, M-
7-260C, M-7-420AC, MX-7-160C, MX-7-
180AC, M-7-420A, MT-7-420.
(28) Mitsubishi Heavy MU-2B-25, MU-2B-35, MU-2B-26, MU-2B-36,
Industries, Ltd. MU-2B-26A, MU-2B-36A, MU-2B-40, MU-2B-
60, MU-2B, MU-2B-20, MU-2B-15.
(29) Mooney Airplane Company, M20, M20A, M20B, M20C, M20D, M20E, M20F,
Inc. M20G, M20J, M20K, M20L, M20M, M20R,
M20S, M22.
(30) Moravan a.s............. Z-242L, Z-143L.
(31) Navion Aircraft Company, NAVION, Navion (L-17A), Navion (L17B),
Ltd. Navion (L-17C), Navion B, Navion D,
Navion E, Navion F, Navion G, Navion H.
(32) New Piper Aircraft, Inc. PA-12, PA-12S, PA-18, PA-18S, PA-18
``105'' (Special), PA-18S ``105''
(Special), PA-18A, PA-18 ``125'' (Army L-
21A), PA-18S ``125,'' PA-18AS ``125,''
PA-18 ``135'' (Army L-21B), PA-18A
``135,'' PA-18S ``135,'' PA-18 ``150,''
PA-18A ``150,'' PA-18S ``150,'' PA-18AS
``150,'' PA-19 (Army L-18B), PA-19S, PA-
20, PA-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-23, PA-23-160, PA-23-235, PA-23-
250, PA-E23-250, PA-24, PA-24-250, PA-24-
260, PA-24-400, 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, PA-28-236, PA-30, PA-
39, PA-40, PA-31P, PA-31T, PA-31T1, PA-
31T2, PA-31T3, PA-31P-350, PA-32-260, PA-
32-300, PA-32S-300, PA-32R-300, PA-32RT-
300, PA-32RT-300T, PA-32R-301 (SP), PA-
32R-301 (HP), PA-32R-301T, PA-32-301, PA-
32-301T, PA-34-200, PA-34-200T, PA-34-
220T, PA-42, PA-42-720, PA-42-1000, PA-
42-720R, PA-44-180, PA-44-180T, PA-46-
310P, PA-46-350P, PA-46-500TP.
(33) Ostmecklenburgische OMF-100-160.
Flugzeugbau GmgH.
(34) Piaggio Aero Industries P-180.
S.p.A.
(35) Pilatus Aircraft Ltd.... PILATUS PC-12, PILATUS PC-12/45, PC-6, PC-
6-H1, PC-6-H2, PC-6/350, PC-6/350-H1, PC-
6/350-H2, PC-6/A, PC-6/A-H1, PA-6/A-H2,
PC-6/B-H2, PC-6/B1-H2, PC-6/B2-H2, PC-6/
B2-H4, PC-6/C-H2, PC-6/C1-H2, PC-7.
(36) Prop-Jets, Inc.......... 200, 200A, 200B, 200C, 200D, 400.
[[Page 2940]]
(37) Panstwowe Zakladv PZL-104 WILGA 80, PZL-104M WILGA 2000,
Lotnicze (PZL). PZL-WARSZAWA, PZL-KOLIBER 150A, PZL-
KOLIBER 160A.
(38) PZL WSK/Mielec Obrsk.... PZL M20 03, PZL M26 01.
(39) Raytheon................ 35-33, 35-A33, 35-B33, 35-C33, 35-C33A,
E33, E33A, E33C, F33, F33A, F33C, G33,
H35, J35, K35, M35, N35, P35, S35, V35,
V35A, V35B, 36, A36, A36TC, B36TC, 35,
A35, B35, C35, D35, E35, F35, G35, 35R,
F90, 76, 200, 200C, 200CT, 200T, A200,
B200, B200C, B200CT, B200T, 300, 300LW,
B300, B300C, 1900, 1900C, 1900D, A100-1
(U-21J), A200 (C-12A), A200 (C-12C),
A200C (UC-12B), A200CT (C-12D), A200CT
(FWC-12D), A200CT (RC-12D), A200CT (C-
12F), A200CT (RC-12G), A200CT (RC-12H),
A200CT (RC-12K), A200CT (RC-12P), A200CT
(RC-12Q), B200C (C-12F), B200C (UC-12F),
B200C (UC-12M), B200C (C-12R), 1900C (C-
12J), 65, A65, A65-8200, 65-80, 65-A80,
65-A80-8800, 65-B80, 65-88, 65-A90, 70,
B90, C90, C90A, E90, H90, 65-A90-1, 65-
A90-2, 65-A90-3, 65-A90-4, 95, B95,
B95A, D95A, E95, 95-55, 95-A55, 95-B55,
95-B55A, 95-B55B (T-42A), 95-C55, 95-
C55A, D55, D55A, E55, E55A, 56TC, A56TC,
58, 58A, 58P, 58PA, 58TC, 58TCA, 99,
99A, 99A (FACH), A99, A99A, B99, C99,
100, A100 (U-21F), A100A, A100C, B100,
2000, 3000, 390, 19A, B19, M19A, 23,
A23, A23A, A23-19, A23-24, B23, C23,
A24, A24R, B24R, C24R, 60, A60, B60,
18D, A18A, A18D, S18D, SA18A, SA18D, 3N,
3NM, 3TM, JRB-6, D18C, D18S, E18S, RC-
45J (SNB-5P), E18S-9700, G18S, H18, C-
45G, TC-45G, C-45H, TC-45H, TC-45J, UC-
45J (SNB-5), 50 (L-23A), B50 (L-23B),
C50, D50 (L-23E), D50A, D50B, D50C, D50E-
5990, E50 (L-23D, RL-23D), F50, G50,
H50, J50, 45 (YT-34), A45 (T-34A or B-
45), D45 (T-34B).
(40) Rockwell International BC-1A, AT-6 (SNJ-2), AT-6A (SNJ-3), AT-
Corporation. 6B, AT-6C (SNJ-4), AT-6D (SNJ-5), AT-6F
(SNF-6), SNJ-7, T-6G, NOMAD NA-260.
(41) Short Brothers & Harland SC-7 Series 2, SC-7 Series 3.
Ltd.
(42) Slingsby Aviation Ltd... T67M260, T67M260-T3A.
(43) SOCATA--Group TB9, TB10, TB20, TB21, TB200, TBM 700,
Aerospatiale. M.S. 760, M.S. 760 A, M.S. 760 B, Rallye
100S, Rallye 150ST, Rallye 150T, Rallye
235E, Rallye 235C, MS 880B, MS 885, MS
894A, MS 893A, MS 892A-150, MS 892E-150,
MS 893E, MS 894E, GA-7.
(44) Tiger Aircraft LLC...... AA-1, AA-1A, AA-1B, AA-1C, AA-5, AA-5A,
AA-5B, AG-5B.
(45) Twin Commander Aircraft 500, 500-A, 500-B, 500-U, 500-S, 520,
Corporation. 560, 560-A, 560-E, 560F, 680, 680E,
680F, 680FL, 680FL(P), 680T, 680V, 680W,
681, 685, 690, 690A, 690B, 690C, 690D,
695, 695A, 695B, 720, 700.
(46) Univair Aircraft 108, 108-1, 108-2, 108-3, 108-5.
Corporation.
(47) Vulcanair S.p.A......... P68, P68B, P68C, P68C-TC, P68
``Observer,'' P68 ``Observer 2,'' P68TC
``Observer,'' AP68TP300 ``Spartacus,''
AP68TP 600 ``Viator''.
(48) Zenair Ltd.............. CH2000.
------------------------------------------------------------------------
What Is the Unsafe Condition Presented in This AD?
(d) This AD is the result of observations that the GTX 33/33D/
330/330D may detect, from other airplanes, the S1 (suppression)
interrogating pulse below the minimum trigger level (MTL) and, in
some circumstances, not reply. The GTX 33/33D/330/330D should still
reply even if it detects S1 interrogating pulses below the MTL. The
actions specified in this AD are intended to prevent interrogating
aircraft from possibly receiving inaccurate replies, due to
suppression, from aircraft equipped with the GTX 33/33D/330/330D
Mode S transponders when the pulses are below the minimum trigger
level (MTL). Software Upgrade Versions 3.03 and 3.06 correct a TAS,
TCAD, and TCAS I system ``whisper-shout'' problem that could
potentially lead to the aircraft not being visible at certain
ranges. TCAS II systems are not affected. The inaccurate replies
could result in reduced vertical separation.
What Must I Do To Address This Problem?
(e) To address this problem, you must do the following:
------------------------------------------------------------------------
Actions Compliance Procedures
------------------------------------------------------------------------
Install GTX 33/33D/330/330D Install the Follow GARMIN
Software Upgrade for software upgrade Mandatory
transponders with software within 180 days Software Service
version 3.00, 3.01, 3.02, 3.04, after February Bulletin No.:
3.05 to at least version 3.06. 23, 2005 (the 0304, Rev B,
If version 3.03 is already effective date of dated June 12,
installed, no further action is this AD), unless 2003
required. This version is no already accomplished.
longer available from Garmin. accomplished. (Software Upgrade
This AD does not apply to 3.03) or GARMIN
software versions past 3.05. Mandatory
Software Service
Bulletin No.:
0409, dated July
19, 2004
(Software Upgrade
3.06).
------------------------------------------------------------------------
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. 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, Wichita Aircraft
Certification Office (ACO), FAA. For information on 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:
316-946-4107; email address: roger.souter@faa.gov.
Does This AD Incorporate Any Material by Reference?
(g) You must do the actions required by this AD following the
instructions in GARMIN Mandatory Software Service Bulletin No.:
0304, Rev B, dated June 12, 2003 (Software Upgrade 3.03) or GARMIN
Mandatory Software Service Bulletin No.: 0409, dated July 19, 2004
(Software Upgrade 3.06). The Director of the Federal Register
approved the incorporation by reference of
[[Page 2941]]
this service bulletin in accordance with 5 U.S.C. 552(a) and 1 CFR
part 51. To get a copy of this service information, contact GARMIN
International Inc. 1200 East 151st Street, Olathe, KS 66062;
telephone: 913-397-8200. To review copies of this service
information, go to the National Archives and Records Administration
(NARA). For information on the availability of this material at
NARA, go to: https://www.archives.gov/federal_register/code_of_
federal_regulations/ibr_locations.html or call (202) 741-6030. To
view the AD docket, go to the Docket Management Facility; U.S.
Department of Transportation, 400 Seventh Street, SW., Nassif
Building, Room PL-401, Washington, DC 20590-001 or on the Internet
at https://dms.dot.gov. The docket number is FAA-2004-18743.
Issued in Kansas City, Missouri, on January 7, 2005.
James E. Jackson,
Acting Manager, Small Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 05-832 Filed 1-18-05; 8:45 am]
BILLING CODE 4910-13-P
