This section of the FEDERAL REGISTER

contains regulatory documents having general

applicability and legal effect, most of which

are keyed to and codified in the Code of

Federal Regulations, which is published under

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Rules and Regulations Federal Register

75223

Vol. 69, No. 241

Thursday, December 16, 2004

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39

[Docket No. FAA 2004–19119; Directorate 

Identifier 2004–CE–26–AD; Amendment 39–

13903; AD 2004–25–15] 

RIN 2120–AA64

Airworthiness Directives; Raytheon 

Aircraft Company, Model 390, Premier 

1 Airplanes

AGENCY: Federal Aviation 

Administration (FAA), DOT.

ACTION: Final rule.

SUMMARY: The FAA adopts a new 

airworthiness directive (AD) for certain 

Raytheon Aircraft Company, Model 390, 

Premier 1 airplanes. This AD requires 

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. 

We are issuing this AD to prevent 

damage to the wire harnesses, which 

could result in 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: This AD becomes effective on 

January 18, 2005. 

As of January 18, 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 Raytheon Aircraft Company, 

P.O. Box 85, Wichita, Kansas 67201–

0085; telephone: (800) 625–7043.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–

0001 or on the Internet at 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: 

Discussion 

What events have caused this 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 

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. 

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 Aircraft Company, Model 390, 

Premier 1 airplanes. This proposal was 

published in the Federal Register as a 

notice of proposed rulemaking (NPRM) 

on October 7, 2004 (69 FR 60104). The 

NPRM proposed to 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. 

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. 

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 

98 airplanes in the U.S. registry.

What is the cost impact of this AD on 

owners/operators of the affected 

airplanes? Raytheon Aircraft Company 

will provide warranty credit as specified 

in the service information. 

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 

75224 Federal Register / Vol. 69, No. 241 / Thursday, December 16, 2004 / Rules and Regulations 

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–2004–19119; 

Directorate Identifier 2004–CE–26–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:

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. FAA amends § 39.13 by adding a 

new AD to read as follows:

2004–25–15 Raytheon Aircraft Company:

Amendment 39–13903; Docket No. FAA–

2004–19119; Directorate Identifier 2004–E–

26–AD. 

When Does This AD Become Effective? 

(a) This AD becomes effective on January 

18, 2005. 

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 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, January 18, 2005. 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. 

(ii) Remove and relocate tie straps and 

M85052/1–8 mounting clamp. 

(iii) Perform the landing gear operational 

test. 

Within 30 days after the effective date of this 

AD, January 18, 2005.

Follow Raytheon Aircraft Company Service 

Bulletin SB 32–3678, dated June 2004. 

Federal Register / Vol. 69, No. 241 / Thursday, December 16, 2004 / Rules and Regulations 75225

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. 

Does This AD Incorporate Any Material by 

Reference? 

(g) You must do the actions required by 

this AD following the instructions in 

Raytheon Aircraft Company Mandatory 

Service Bulletin SB 32–3678, dated June 

2004. The Director of the Federal Register 

approved the incorporation by reference of 

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 

Raytheon Aircraft Company, P.O. Box 85, 

Wichita, Kansas 67201–0085; telephone: 

(800) 625–7043. 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: 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 http://

dms.dot.gov. The docket number is FAA–

2004–19119.

Issued in Kansas City, Missouri, on 

December 6, 2004. 

David R. Showers, 

Acting Manager, Small Airplane Directorate, 

Aircraft Certification Service.

[FR Doc. 04–27195 Filed 12–15–04; 8:45 am] 

BILLING CODE 4910–13–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration 

14 CFR Part 39

[Docket No. FAA–2004–18034; Directorate 

Identifier 2004–CE–18–AD; Amendment 39–

13905; AD 2004–25–17] 

RIN 2120–AA64

Airworthiness Directives; LETECKE ́

ZA ́ VODY Model L 23 SUPER—BLANIK 

Sailplanes

AGENCY: Federal Aviation 

Administration (FAA), DOT.

ACTION: Final rule.

SUMMARY: The FAA adopts a new 

airworthiness directive (AD) for certain 

LETECKE ́ ZA ́ VODY Model L 23 

SUPER—BLANIK sailplanes. This AD 

requires you to do a repetitive, nondestructive magnetic test (NDMT) 

inspection on the elevator rocker lever 

(part number A 730 201 N) for cracks. 

If cracks are found, this AD also requires 

you to return the part to the 

manufacturer. The manufacturer will 

send you a replacement part for 

installation. Installing the improved 

replacement part terminates the need for 

the repetitive inspections. This AD is 

the result of mandatory continuing 

airworthiness information (MCAI) 

issued by the airworthiness authority for 

the Czech Republic. We are issuing this 

AD to prevent failure of the elevator 

rocker lever caused by cracks that 

resulted from a defect in prior 

manufacturing procedures. Such failure 

could lead to loss of control of the 

sailplane.

DATES: This AD becomes effective on 

January 28, 2005. 

As of January 28, 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 LETECKE ́ ZA ́ VODY a.s., 686 04 

Kunovice 1177, Czech Republic. 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–

0001 or on the Internet at http://

dms.dot.gov. The docket number is 

FAA–2004–18034.

FOR FURTHER INFORMATION CONTACT:

Gregory A. Davison, Aerospace 

Engineer, FAA, Small Airplane 

Directorate, 901 Locust, Room 301, 

Kansas City, Missouri 64106; telephone: 

(816) 329–4130; facsimile: (816) 329–

4090.

SUPPLEMENTARY INFORMATION: 

Discussion 

What events have caused this AD?

The Civil Aviation Authority (CAA), 

which is the airworthiness authority for 

the Czech Republic, recently notified 

FAA that an unsafe condition may exist 

on certain LETECKE ́ ZA ́ VODY Model L 

23 SUPER—BLANIK sailplanes. The 

CAA reports that, during an accident 

investigation, cracks were found on the 

elevator rocker lever. 

The manufacturer has identified a 

problem with its quality control 

inspection procedures during the 

production of the original elevator 

rocker lever part prior to January 2004. 

Micro-cracks or voids were not detected 

when the parts left production and were 

installed on the affected sailplanes. 

These discrepancies may cause fatigue 

failure of the elevator rocker lever.

In January 2004, the manufacturer 

changed its manufacturing process and 

is currently replacing any existing 

defective elevator rocker levers within 

the specified affected sailplanes. 

What is the potential impact if FAA 

took no action? If not detected and 

corrected, cracks in the elevator rocker 

lever could cause the lever to fail. Such 

failure could result in loss of control of 

the sailplane. 

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 

LETECKE ́ ZA ́ VODY Model L 23 

SUPER—BLANIK sailplanes. This 

proposal was published in the Federal 

Register as a notice of proposed 

rulemaking (NPRM) on September 2, 

2004 (69 FR 53655). The NPRM 

proposed to require you to do a 

repetitive, non-destructive magnetic test 

(NDMT) inspection on the elevator 

rocker lever (part number A 730 201 N) 

for cracks. If cracks are found, the 

NPRM also proposed to require you to 

return the part to the manufacturer. The 

manufacturer will send you a 

replacement part for installation. 

Installing the improved replacement 

part would terminate the need for the 

repetitive inspections. 

What is the difference between this 

AD and the CAA AD? The CAA AD 

requires doing the initial inspection 

prior to further flight after the effective 

date of this AD. We are requiring that 

you do the initial inspection within the 

next 25 hours time-in-service (TIS) after 

the effective date of this AD. 

We do not have justification to require 

this action prior to further flight. We use 

compliance times such as this when we 

have identified an urgent safety of flight 

situation. We believe that 25 hours TIS 

will give the owners or operators of the 

affected sailplanes enough time to have 

the actions required by this AD done 

without compromising the safety of the 

sailplanes.