60100 Federal Register / Vol. 69, No. 194 / Thursday, October 7, 2004 / Proposed Rules 

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.

§ 39.13 [Amended] 

2. The FAA amends § 39.13 by adding 

the following new airworthiness 

directive (AD):

Airbus: Docket No. FAA–2004–19264; 

Directorate Identifier 2004–NM–90–AD. 

Comments Due Date 

(a) The Federal Aviation Administration 

(FAA) must receive comments on this AD 

action by November 22, 2004. 

Affected ADs 

(b) None. 

Applicability: (c) This AD applies to Airbus 

Model A319, A320, and A321 series 

airplanes; certificated in any category; 

equipped with any Hamilton Sundstrand 

Auxiliary Power Unit (APU) alternating 

current (AC) generator having part number 

5906732, 5909006, or 5910047; with up to 

amendment 17 included; on which Airbus 

Modification 32614 has not been done. 

Unsafe Condition 

(d) This AD was prompted by a report of 

an explosion in the APU compartment which 

blew open the compartment doors. We are 

issuing this AD to prevent oil vapor leakage 

from the APU AC generator, which, when 

combined with an electric arc at the electrical 

receptacle, could result in a fire or explosion 

in the APU compartment during flight. 

Compliance: (e) You are responsible for 

having the actions required by this AD 

performed within the compliance times 

specified, unless the actions have already 

been done. 

Modification 

(f) For all airplanes: Within 20 months after 

the effective date of this AD, modify the APU 

AC generator by doing all the actions 

specified in the Accomplishment 

Instructions of Airbus Service Bulletin A320–

24–1106, dated May 26, 2003. Do the actions 

in accordance with the service bulletin. 

Concurrent Actions 

(g) For Model A320 and A321 series 

airplanes: Prior to or concurrently with 

accomplishing the modification required by 

paragraph (f) of this AD, do the modification 

of the APU AC generator specified in Airbus 

Service Bulletin A320–24–1082, Revision 01, 

dated March 15, 1996; by doing all the 

actions specified in the Accomplishment 

Instructions in accordance with the service 

bulletin. Prior accomplishment of the 

modification in accordance with Airbus 

Service Bulletin A320–24–1082, dated 

September 30, 1994, meets the requirements 

of this paragraph. 

Additional Source of Service Information

Note 1: Airbus Service Bulletin A320–24–

1106 refers to Hamilton Sundstrand Service 

Bulletin 90EGS01AG–24–18, dated February 

13, 2003, as an additional source of service 

information for accomplishment of the 

modification required by paragraph (f) of this 

AD.

Part Installation 

(h) As of the effective date of this AD, no 

person may install an APU AC generator 

having a part number listed in the old part 

number column specified in Paragraph 1.L. 

of Airbus Service Bulletin A320–24–1106, 

dated May 26, 2003; on any airplane, unless 

that generator has been modified in 

accordance with paragraphs (f) and (g) of this 

AD, as applicable. 

Alternative Methods of Compliance 

(AMOCs) 

(i) The Manager, International Branch, 

Transport Airplane Directorate, FAA, has the 

authority to approve AMOCs for this AD, if 

requested in accordance with the procedures 

found in 14 CFR 39.19. 

Related Information 

(j) French airworthiness directive F–2004–

019, dated February 4, 2004, also addresses 

the subject of this AD.

Issued in Renton, Washington, on 

September 30, 2004. 

Kevin M. Mullin, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service.

[FR Doc. 04–22565 Filed 10–6–04; 8:45 am] 

BILLING CODE 4910–13–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA 2004–18743; Directorate 

Identifier 2004–CE–23–AD] 

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: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: The FAA proposes to 

supersede Airworthiness Directive (AD) 

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 proposed 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 proposed 

AD would require you to install GTX 

33/33D/330/330D Software Upgrade 

Version 3.03 or 3.06. Software Upgrade 

Versions 3.03 and 3.06 correct a TAS, 

TCAD, and TCAS I system ‘‘whispershout’’ problem that could potentially 

lead to the aircraft not being visible at 

certain ranges. TCAS II systems are not 

affected. We are issuing this proposed 

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: We must receive any comments 

on this proposed AD by November 15, 

2004.

ADDRESSES: Use one of the following to 

submit comments on this proposed AD: 

• DOT Docket Web site: Go to

http://dms.dot.gov and follow the 

instructions for sending your comments 

electronically. 

• Government-wide rulemaking Web 

site: Go to http://www.regulations.gov

and follow the instructions for sending 

your comments electronically. 

• Mail: Docket Management Facility; 

U.S. Department of Transportation, 400 

Seventh Street, SW., Nassif Building, 

Room PL–401, Washington, DC 20590–

001. 

• Fax: 1–202–493–2251. 

• Hand Delivery: Room PL–401 on 

the plaza level of the Nassif Building, 

400 Seventh Street, SW., Washington, 

DC, between 9 a.m. and 5 p.m., Monday 

through Friday, except Federal holidays. 

To get the service information 

identified in this proposed AD, contact 

GARMIN International Inc. 1200 East 

151st Street, Olathe, KS 66062; 

telephone: 913–397–8200. 

To view the comments to this 

proposed AD, go to http://dms.dot.gov.

This is docket number 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; email address: 

roger.souter@faa.gov.

SUPPLEMENTARY INFORMATION: 

Comments Invited 

How do I comment on this proposed 

AD? We invite you to submit any 

Federal Register / Vol. 69, No. 194 / Thursday, October 7, 2004 / Proposed Rules 60101

written relevant data, views, or 

arguments regarding this proposal. Send 

your comments to an address listed 

under ADDRESSES. Include the docket 

number, ‘‘FAA 2004–18743; Directorate 

Identifier 2004–CE–23–AD’’ at the 

beginning of your comments. We will 

post all comments we receive, without 

change, to http://dms.dot.gov, including 

any personal information you provide. 

We will also post a report summarizing 

each substantive verbal contact with 

FAA personnel concerning this 

proposed rulemaking. Using the search 

function of our docket Web site, anyone 

can find and read the comments 

received into any of our dockets, 

including the name of the individual 

who sent the comment (or signed the 

comment on behalf of an association, 

business, labor union, etc.). This is 

docket number FAA 2004–18743. You 

may review the DOT’s complete Privacy 

Act Statement in the Federal Register

published on April 11, 2000 (65 FR 

19477–78) or you may visit

http://dms.dot.gov.

Are there any specific portions of this 

proposed AD I should pay attention to?

We specifically invite comments on the 

overall regulatory, economic, 

environmental, and energy aspects of 

this proposed AD. If you contact us 

through a nonwritten communication 

and that contact relates to a substantive 

part of this proposed AD, we will 

summarize the contact and place the 

summary in the docket. We will 

consider all comments received by the 

closing date and may amend this 

proposed AD in light of those comments 

and contacts. 

Docket Information 

Where can I go to view the docket 

information? You may view the AD 

docket that contains the proposal, any 

comments received, and any final 

disposition 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

http://dms.dot.gov. The comments will 

be available in the AD docket shortly 

after the DMS receives them. 

Discussion 

Has FAA taken any action to this 

point? 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 proposed 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? We are issuing this 

proposed AD to incorporate these 

changes and 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. 

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.

Is there service information that 

applies to this subject? GARMIN 

International Inc. has issued the Service 

Bulletin No. 0304, Revision B, dated 

June 12, 2003 (which incorporates 

Software Upgrade 3.03), and Service 

Bulletin No. 0409, dated July 19, 2004 

(which incorporates Software Upgrade 

3.06). 

What are the provisions of this service 

information? The service bulletins 

include:

—modification instructions for 

upgrading to software version 3.03 or 

3.06 and 

—a listing of parts required to perform 

the modification. 

FAA’s Determination and Requirements 

of This Proposed AD 

What has FAA decided? We have 

evaluated all pertinent information and 

identified an unsafe condition that is 

likely to exist or develop on other 

products of this same type design. For 

this reason, we are proposing AD action. 

What would this proposed AD 

require? This proposed AD would 

supersede AD 2004–10–15 with a new 

AD that would require you to install 

Garmin GTX 33/33D/330/330D Software 

Upgrade Version 3.03 or 3.06. 

How does the revision to 14 CFR part 

39 affect this proposed AD? On July 10, 

2002, we published a new version of 14 

CFR part 39 (67 FR 47997, July 22, 

2002), which governs FAA’s AD system. 

This regulation now includes material 

that relates to 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 would this 

proposed AD impact? We estimate that 

this proposed AD affects 5400 airplanes 

in the U.S. registry. 

What would be the cost impact of this 

proposed 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. 

What is the difference between the 

cost impact of this proposed AD and the 

cost impact of AD 2004–10–15? Garmin 

provided warranty credit for AD 2004–

10–15 and will provide warranty credit 

only for installation of Service Bulletin 

No. 0409, dated July 19, 2004 (which 

incorporates Software Upgrade 3.06) in 

the proposed AD. 

Regulatory Findings 

Would this proposed AD impact 

various entities? We have determined 

that this proposed AD would not have 

federalism implications under Executive 

Order 13132. This proposed AD 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. 

Would this proposed AD involve a 

significant rule or regulatory action? For 

the reasons discussed above, I certify 

that this proposed 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, 

60102 Federal Register / Vol. 69, No. 194 / Thursday, October 7, 2004 / Proposed Rules 

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 proposed AD and 

placed it in the AD Docket. You may get 

a copy of this summary by sending a 

request to us at the address listed under 

ADDRESSES. Include ‘‘AD Docket No. 

FAA 2004–18743; Directorate Identifier 

2003-CE–39–AD’’ in your request.

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 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.

§ 39.13 [Amended] 

2. The FAA amends § 39.13 by 

removing Airworthiness Directive (AD) 

2004–10–15, Amendment 39–13645 (69 

FR 29212–15, dated May 21, 2004), and 

by adding a new AD to read as follows:

GARMIN International Inc.: Docket No. FAA 

2004–18743; Directorate Identifier 2004–

CE–23–AD 

When Is the Last Date I Can Submit 

Comments on This Proposed AD? 

(a) We must receive comments on this 

proposed airworthiness directive (AD) by 

November 15, 2004. 

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 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 Corporation ................................. 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. 

(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 LLC ................................... 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. 

(6) American Champion Aircraft Corp ......................... 402, 7GCA, 7GCB, 7KC, 7GCBA, 7GCAA, 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. 

(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 Corporation ................................... SR20, SR22. 

(13) Commander Aircraft Company ............................ 112, 112TC, 112B, 112TCA, 114, 114A, 114B, 114TC. 

(14) de Havilland Inc ................................................... DHC–2 Mk. I, DHC–2 Mk.II, DHC–2 Mk. III. 

(15) Dynac Aerospace Corporation ............................. (Volaire) 10, (Volaire) 10A, (Aero Commander) 100, (Aero Commander) 100A, (Aero 

Commander) 100–180. 

(16) Diamond Aircraft Industries .................................. DA 20–A1, DA20–C1, DA 40. 

(17) Empressa Brasileira de Aeronautica S.A. 

EMBRAER.

EMB–110P1, EMB–110P2. 

(18) Extra Flugzeugbau Gmbh .................................... EA300, EA300L, EA300S, EA300/200, EA–400. 

(19) Fairchild Aircraft Corporation ............................... 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). 

(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. 

Federal Register / Vol. 69, No. 194 / Thursday, October 7, 2004 / Proposed Rules 60103

Manufacturer Model 

(23) LanShe Aerospace, LLC ...................................... MAC–125C, MAC–145, MAC–145A, MAC–145B. 

(24) Learjet Inc ............................................................ 23. 

(25) Lockheed Aircraft Corporation ............................. 18. 

(26) Luscombe Aircraft Corporation ............................ 11A, 11E. 

(27) Maule Aerospace Technology Inc ....................... 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. 

(28) Mitsubishi Heavy Industries, Ltd .......................... 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–20, MU–2B–15. 

(29) Mooney Airplane Company, Inc ........................... M20, M20A, M20B, M20C, M20D, M20E, M20F, M20G, M20J, M20K, M20L, M20M, 

M20R, M20S, M22. 

(30) Moravan a.s ......................................................... Z–242L, Z–143L. 

(31) Navion Aircraft Company, Ltd .............................. NAVION, Navion (L–17A), Navion (L17B), 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 Flugzeugbau GmgH ........ OMF–100–160. 

(34) Piaggio Aero Industries S.p.A .............................. P–180. 

(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. 

(37) Panstwowe Zakladv Lotnicze (PZL) .................... PZL–104 WILGA 80, PZL–104M WILGA 2000, 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 Corporation ...................... 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. 

(41) Short Brothers & Harland Ltd .............................. SC–7 Series 2, SC–7 Series 3. 

(42) Slingsby Aviation Ltd ............................................ T67M260, T67M260–T3A. 

(43) SOCATA—Group Aerospatiale ............................ 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. 

(44) Tiger AircraftLLC .................................................. AA–1, AA–1A, AA–1B, AA–1C, AA–5, AA–5A, AA–5B, AG–5B. 

(45) Twin Commander Aircraft Corporation ................ 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. 

(46) Univair Aircraft Corporation .................................. 108, 108–1, 108–2, 108–3, 108–5. 

60104 Federal Register / Vol. 69, No. 194 / Thursday, October 7, 2004 / Proposed Rules 

Manufacturer Model 

(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 Software Upgrade to at least Version 3.03 or 3.06.Install the software upgrade within 180 days 

after the effective date of this AD, unless already accomplished.

Follow 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, 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; e-mail address: 

roger.souter@faa.gov.

May I Get Copies of the Documents 

Referenced in This AD? 

(g) To get copies of the documents 

referenced in this AD, contact GARMIN 

International Inc. 1200 East 151st Street, 

Olathe, KS 66062; telephone: 913–397–8200. 

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, or on the Internet at http://dms.dot.gov.

The docket number is FAA 2004–18743.

Issued in Kansas City, Missouri, on 

September 29, 2004. 

Dorenda D. Baker, 

Manager, Small Airplane Directorate, Aircraft 

Certification Service.

[FR Doc. 04–22586 Filed 10–6–04; 8:45 am] 

BILLING CODE 4910–13–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA 2004–19119; Directorate 

Identifier 2004–CE–26–AD] 

RIN 2120–AA64 

Airworthiness Directives; Raytheon 

Aircraft Company, Model 390, Premier 

1 Airplanes

AGENCY: Federal Aviation 

Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: The FAA proposes to adopt a 

new airworthiness directive (AD) for 

certain Raytheon Aircraft Company, 

Model 390, Premier 1 airplanes. This 

proposed AD would require you to 

inspect the routing and security of the 

left and right main landing gear (MLG) 

squat switch wire harness installations 

for damage, repair any damage or 

replace components, and reinstall the 

squat switch wire harness. This 

proposed AD results from reports of 

damage to the left and/or right MLG 

wire harness assemblies, which resulted 

in various system failures/anomalies 

due to erroneous air/ground status 

signals. We are issuing this proposed 

AD to prevent damage to the wire 

harnesses, which could result in loss of 

lift dump, loss of pressurization, loss of 

transponder responses to interrogations, 

and failure of other systems utilizing 

air/ground status signals. This failure 

could lead to loss of control of the 

airplane.

DATES: We must receive any comments 

on this proposed AD by November 16, 

2004.

ADDRESSES: Use one of the following to 

submit comments on this proposed AD: 

• DOT Docket Web site: Go to 

http://dms.dot.gov and follow the 

instructions for sending your comments 

electronically. 

• Government-wide rulemaking Web 

site: Go to http://www.regulations.gov

and follow the instructions for sending 

your comments electronically. 

• Mail: Docket Management Facility; 

U.S. Department of Transportation, 400 

Seventh Street, SW., Nassif Building, 

Room PL–401, Washington, DC 20590–

001. 

• Fax: 1–202–493–2251. 

• Hand Delivery: Room PL–401 on 

the plaza level of the Nassif Building, 

400 Seventh Street, SW., Washington, 

DC, between 9 a.m. and 5 p.m., Monday 

through Friday, except Federal holidays. 

To get the service information 

identified in this proposed AD, contact 

Raytheon Aircraft Company, PO Box 85, 

Wichita, Kansas 67201–0085; telephone: 

(800) 625–7043. 

To view the comments to this 

proposed AD, go to http://dms.dot.gov. 

The docket number is FAA 2004–19119.

FOR FURTHER INFORMATION CONTACT:

Philip Petty, Aerospace Engineer, ACE–

119W, Wichita Aircraft Certification 

Office, 1801 Airport Road, Room 100, 

Wichita, Kansas 67209; telephone: (316) 

946–4139; facsimile: (316) 946–4107.

SUPPLEMENTARY INFORMATION: