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:

Federal Register / Vol. 69, No. 194 / Thursday, October 7, 2004 / Proposed Rules 60105

Comments Invited 

How do I comment on this proposed 

AD? We invite you to submit any 

written relevant data, views, or 

arguments regarding this proposal. Send 

your comments to an address listed 

under ADDRESSES. Include the docket 

number, ‘‘FAA 2004–19119; Directorate 

Identifier 2004–CE–26–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 2004–19119. 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 

What events have caused this 

proposed AD? FAA received reports of 

damage to the left and/or right MLG 

wire harness assemblies on Raytheon 

Model 390 airplanes. This resulted in 

various system failures/anomalies due 

to erroneous air/ground status signals. 

Improper installation of Kit 390–8103–

0001 may have resulted in the damage 

to the squat switch wire harness 

assemblies during normal extension and 

retraction operations. A damaged wire 

harness and/or squat switch installation 

may affect multiple systems on the 

airplane.

What is the potential impact if FAA 

took no action? Damage to the wire 

harnesses 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. 

Is there service information that 

applies to this subject? Raytheon 

Aircraft Company has issued Service 

Bulletin SB 32–3678, dated June 2004. 

What are the provisions of this service 

information? The service bulletin 

includes procedures for: 

—Inspecting the squat switch bracket 

for corrosion or cracking; 

—replacing the squat switch bracket, if 

damaged; 

—inspecting the MLG wiring harness; 

and 

—relocating the MLG wire harness tie 

straps and the M85052/1–8 mounting 

clamp. 

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 

require you to incorporate the actions in 

the previously-referenced service 

bulletin. 

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 98 airplanes in 

the U.S. registry. 

What would be the cost impact of this 

proposed AD on owners/operators of the 

affected airplanes? Raytheon Aircraft 

Company will provide warranty credit 

as specified in the service information. 

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, 

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 FAA 

2004–19119; Directorate Identifier 

2004–CE–26–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 adding 

the following new airworthiness 

directive (AD):

Raytheon Aircraft Company: Docket No. 

FAA 2004–19119, Directorate Identifier 

2004–CE–26–AD. 

60106 Federal Register / Vol. 69, No. 194 / Thursday, October 7, 2004 / Proposed Rules 

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 16, 2004. 

What Other ADs Are Affected by This 

Action? 

(b) None. 

What Airplanes Are Affected by This AD? 

(c) This AD affects the following airplane 

model and serial numbers that are 

certificated in any category: Model 390 

Premier I, Serials RB–1, RB–4 through RB–

84, RB–87 through RB–90, RB–92 through 

RB–96, RB–99 through RB–101, and RB–103 

through RB–106. 

What is the Unsafe Condition Presented in 

This AD? 

(d) This AD is the result of reports of 

damage to the left and/or right main landing 

gear (MLG) wire harness assemblies, which 

resulted in various system failures/anomalies 

due to erroneous air/ground status signals. 

The actions specified in this AD are intended 

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. 

What Must I Do To Address This Problem? 

(e) To address this problem, you must do 

the following:

Actions Compliance Procedures 

(1) For airplanes prior to serial number RB–100 

with Kit 390–8103–0001 installed, and for airplanes with production installation of the 

plunger-style squat switch, serial numbers 

RB–100, RB–101, and RB–103 through RB–

106, perform the following actions:.

Inspect within 30 days after the effective date 

of this AD. If damage is found, replace the 

switch bracket prior to further flight after the 

inspection.

Follow Raytheon Aircraft Company Service 

Bulletin SB 32–3678, dated June 2004. 

(i) Visually inspect the squat switch bracket for 

corrosion or cracking (damage).

(ii) If damage is found, replace the switch 

bracket with part number 390–810008–0003/

–0004.

(2) All airplanes affected by this AD perform the 

following actions:.

(i) Inspect MLG wiring harness service loop for 

excessive length in air mode (strut extended). 

The radius of the wire harness service loop 

should not exceed that of the brake hose 

service loop. The radius of the brake hose 

loop should not exceed the radius of the tire. 

If the length is excessive in air mode, correct 

in accordance with Raytheon Aircraft Company Service Bulletin SB 32–3678, dated 

June 2004. 

Within 30 days after the effective date of this 

AD.

Follow Raytheon arcart Company Service Bulletin SB 32–3678, dated June 2004. 

(ii) Remove and relocate tie straps and 

M85052/1–8 mounting clamp. 

(iii) Perform the landing gear operational test. 

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 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. 

May I Get Copies of the Documents 

Referenced in this AD? 

(g) To get copies of the documents 

referenced in this AD, contact Raytheon 

Aircraft Company, PO Box 85, Wichita, 

Kansas 67201–0085; telephone: (800) 625–

7043. 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 

2004–19119.

Issued in Kansas City, Missouri, on 

September 29, 2004. 

Dorenda D. Baker, 

Manager, Small Airplane Directorate, Aircraft 

Certification Service.

[FR Doc. 04–22585 Filed 10–6–04; 8:45 am] 

BILLING CODE 4910–13–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. 2003–CE–57–AD] 

RIN 2120–AA64 

Airworthiness Directives; LET a.s. 

Model Blanik L–13 AC Sailplanes

AGENCY: Federal Aviation 

Administration, DOT.

ACTION: Supplemental notice of 

proposed rulemaking (NPRM); 

Reopening of the comment period. 

SUMMARY: This document proposes to 

revise an earlier proposed airworthiness 

directive (AD) that would apply to all 

LET a.s. (formerly LET n.p.) (LET) 

Model Blanik L–13 AC sailplanes. The 

earlier NPRM would have required you 

to repetitively inspect the bedding of the 

front and rear control levers for cracks, 

and, if any cracks are found, replace 

with parts found free of cracks. The 

earlier NPRM resulted from mandatory 

continuing airworthiness information 

(MCAI) issued by the airworthiness 

authority for the Czech Republic. The 

MCAI is a report of one occurrence of 

cracks in the attachment of control 

levers on the control bridge. Since FAA 

issued the NPRM, FAA has received and 

evaluated new service information that 

eliminates the repetitive inspection, 

requires replacement of parts, and 

changes the serial number effectivity. 

Since these actions impose an 

additional burden over that proposed in 

the NPRM, we are reopening the 

comment period to allow the public the 

chance to comment on these additional 

actions.

DATES: The Federal Aviation 

Administration (FAA) must receive any