59788 Federal Register / Vol. 69, No. 193 / Wednesday, October 6, 2004 / Rules and Regulations 

bottom of each report page (e.g., 1 of 3, 

2 of 3, 3 of 3).

(c) If one or more exhibits are 

included on the form, provide a 

reference to such exhibit(s) under 

Explanation of Responses. If the exhibit 

is being filed in paper form pursuant to 

a hardship exemption under applicable 

FDIC rules, place the designation ‘‘P’’

(paper) next to the name of the exhibit 

in the exhibit reference. 

(d) If additional information is not 

reported in this manner, it will be 

assumed that no additional information 

was provided.

* * * * *

9. Amendments 

(a) If this form is filed as an 

amendment in order to add one or more 

lines of ownership information to Table 

I or Table II of the form being amended, 

provide each line being added, together 

with one or more footnotes under 

Explanation of Responses, as necessary, 

to explain the addition of the line or 

lines. Do not repeat lines of ownership 

information that were disclosed in the 

original form and are not being 

amended. 

(b) If this form is filed as an 

amendment in order to amend one or 

more lines of ownership information 

that already were disclosed in Table I or 

Table II of the form being amended, 

provide the complete line or lines being 

amended, as amended, together with 

notes under Explanation of Responses 

as necessary to explain the amendment 

of the line or lines. Do not repeat lines 

of ownership information that were 

disclosed in the original form and are 

not being amended. 

(c) If this form is filed as an 

amendment for any other purpose other 

than or in addition to the purpose 

described in items (a) or (b) of this 

General Instruction 9, provide one or 

more notes under Explanation of 

Responses, as necessary, to explain the 

amendment.

* * * * *

Form 5 Annual Statement of Changes 

in Beneficial Ownership of Securities

* * * * *

3. Statement for Issuer’s Fiscal Year 

Ended 

(Month/Day/Year) 

4. If Amendment, Date Original Filed 

(Month/Day/Year)

* * * * *

Table II—Derivative Securities 

Acquired, Disposed of, or Beneficially 

Owned (e.g., Puts, Calls, Warrants, 

Options, Convertible Securities)

* * * * *

9. Number of Derivative Securities 

Beneficially Owned at End of Issuer’s 

Fiscal Year (Instr. 4) 

10. Ownership Form of Derivative 

Securities: Direct (D) or Indirect (I) 

(Instr. 4)

* * * * *

Dated at Washington, DC, this 29th day of 

September, 2004.

By Order of the Board of Directors.

Federal Deposit Insurance Corporation. 

Robert E. Feldman, 

Executive Secretary.

[FR Doc. 04–22384 Filed 10–5–04; 8:45 am] 

BILLING CODE 6714–01–U

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration 

14 CFR Part 39

[Docket No. FAA–2004–19223; Directorate 

Identifier 2004–SW–20–AD; Amendment 39–

13813; AD 2004–20–08] 

RIN 2120–AA64 

Airworthiness Directives; MD 

Helicopters, Inc. (MDHI) Model 500N 

and 600N Helicopters

AGENCY: Federal Aviation 

Administration, DOT.

ACTION: Final rule; request for 

comments. 

SUMMARY: This amendment adopts a 

new airworthiness directive (AD) for 

MD Helicopters, Inc. (MDHI) Model 

500N and 600N helicopters. This action 

requires using a bright light and a 10×

or higher magnifying glass to inspect 

each forward and center thruster control 

cable assembly connector (connector) 

for corrosion pitting or cracking. If you 

find corrosion pitting or cracking, this 

AD also requires replacing the cable 

assembly with an airworthy cable 

assembly before further flight. This 

amendment is prompted by a report of 

a failure of the forward thruster cable 

assembly due to stress corrosion. The 

actions specified in this AD are 

intended to detect a corrosion-pitted or 

cracked connector and prevent failure of 

the cable assembly and subsequent loss 

of control of the helicopter.

DATES: Effective October 21, 2004. 

The incorporation by reference of 

certain publications listed in the 

regulations is approved by the Director 

of the Federal Register as of October 21, 

2004. 

Comments for inclusion in the Rules 

Docket must be received on or before 

December 6, 2004.

ADDRESSES: Use one of the following 

addresses to submit comments on this 

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; 

• Fax: (202) 493–2251; or 

• 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. 

You may get the service information 

identified in this AD from MD 

Helicopters, Inc., Attn: Customer 

Support Division, 4555 E. McDowell 

Rd., Mail Stop M615–GO48, Mesa, 

Arizona 85215–9734, telephone 1–800–

388–3378, fax 480–891–6782, or on the 

Web at http://www.mdhelicopters.com.

Examining the Dockets 

You may examine the docket that 

contains the AD, any comments, and 

any other information on the Internet at 

http://dms.dot.gov, or in person at the 

Docket Management System (DMS) 

Docket Offices between 9 a.m. and 5 

p.m., Monday through Friday, except 

Federal holidays. The Docket Office 

(telephone (800) 647–5227) is located on 

the plaza level of the Department of 

Transportation Nassif Building at the 

street address stated in the ADDRESSES

section. Comments will be available in 

the AD docket shortly after the DMS 

receives them.

FOR FURTHER INFORMATION CONTACT: John 

Cecil, Aviation Safety Engineer, FAA, 

Los Angeles Aircraft Certification 

Office, Airframe Branch, 3960 

Paramount Blvd., Lakewood, California 

90712–4137, telephone (562) 627–5228, 

fax (562) 627–5210.

SUPPLEMENTARY INFORMATION: This 

amendment adopts a new AD for the 

MDHI Model 500N and 600N 

helicopters. This action requires using a 

bright light and a 10× or higher 

magnifying glass to inspect each 

connector for corrosion pitting or 

cracking. If corrosion pitting or cracking 

is found, this AD also requires replacing 

the cable assembly with an airworthy

Federal Register / Vol. 69, No. 193 / Wednesday, October 6, 2004 / Rules and Regulations 59789

cable assembly before further flight. 

This amendment is prompted by a 

report of a failure of a cable assembly 

due to a stress corrosion crack. The 

actions specified in this AD are 

intended to detect a corrosion-pitted or 

cracked connector and to prevent failure 

of a cable assembly and subsequent loss 

of control of the helicopter.

We have reviewed MDHI Service 

Bulletin SB500N–027, SB600N–042, 

dated May 3, 2004 (SB). The SB 

describes procedures for inspecting the 

connectors on the forward and center 

cable assemblies for corrosion pitting or 

cracking. Also, the SB specifies 

replacing the cable assembly if 

corrosion pitting or cracking is found on 

the connectors. 

This unsafe condition is likely to exist 

or develop on other helicopters of the 

same type design. Therefore, this AD is 

being issued to detect a corrosion-pitted 

or cracked connector on a cable 

assembly and to prevent failure of the 

cable assembly, and subsequent loss of 

control of the helicopter. This AD 

requires a one-time inspection of the 

connectors on the cable assemblies for 

corrosion pitting or cracking. If 

corrosion pitting or cracking is found, 

this AD also requires replacing the cable 

assembly with an airworthy cable 

assembly before further flight. 

Accomplish the actions by following the 

SB described previously. 

The short compliance time involved 

is required because the previously 

described critical unsafe condition can 

adversely affect the controllability or 

structural integrity of the helicopter. 

Therefore, within the next 10 hours 

time-in-service or 30 days, whichever 

comes first, using a bright light and a 

10X or higher magnifying glass, inspect 

each connector for corrosion pitting or 

cracking. If corrosion pitting or cracking 

is found, replacing the cable assembly 

with an airworthy cable assembly is 

required before further flight and this 

AD must be issued immediately. 

Inspecting each connector and replacing 

the cable assembly if corrosion pitting 

or cracking is found is terminating 

action for the requirements of this AD. 

Since a situation exists that requires 

the immediate adoption of this 

regulation, it is found that notice and 

opportunity for prior public comment 

hereon are impracticable, and that good 

cause exists for making this amendment 

effective in less than 30 days. 

We estimate that this AD will affect 

66 helicopters. The inspections will take 

about 1 work hour at an average labor 

rate of $65 per work hour. Required 

parts will cost about $4520 per 

helicopter. Based on these figures, we 

estimate the total cost impact of the AD 

on U.S. operators to be $4,290 assuming 

no parts will need to be replaced. 

Comments Invited 

This AD is a final rule that involves 

requirements that affect flight safety and 

was not preceded by notice and an 

opportunity for public comment; 

however, we invite you to submit any 

written data, views, or arguments 

regarding this AD. Send your comments 

to an address listed under ADDRESSES.

Include ‘‘Docket No. FAA–2004–19223; 

Directorate Identifier 2004–SW–20–AD’’

at the beginning of your comments. We 

specifically invite comments on the 

overall regulatory, economic, 

environmental, and energy aspects of 

the AD. We will consider all comments 

received by the closing date and may 

amend the AD in light of those 

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 AD. Using the 

search function of our docket web site, 

you can find and read the comments to 

any of our dockets, including the name 

of the individual who sent the 

comment. 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.

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. 

For the reasons discussed above, I 

certify that the regulation: 

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 an economic evaluation 

of the estimated costs to comply with 

this AD. See the DMS to examine the 

economic evaluation.

List of Subjects in 14 CFR Part 39 

Air transportation, Aircraft, Aviation 

safety, Incorporation by reference, 

Safety.

Adoption of the Amendment

■ Accordingly, pursuant to 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. Section 39.13 is amended by adding 

a new airworthiness directive to read as 

follows:

2004–20–08 MD Helicopters, Inc.:

Amendment 39–13813. Docket No. 

FAA–2004–19223; Directorate Identifier 

2004–SW–20–AD. 

Applicability: The following model and 

serial number (S/N) helicopters, with forward 

thruster cable (cable) assembly and center 

cable assembly part number (P/N), installed, 

certificated in any category:

Model S/N Forward cable

assembly P/N 

Center cable

assembly P/N 

500N .... With a prefix of ‘‘LN’’ and 001 through 099 .............................................................................. 500N7201–55 500N7201–57 

600N .... With a prefix of ‘‘RN’’ and 003 through 068 ............................................................................. 500N7201–55 500N7201–59 

Compliance: Required as indicated, unless 

accomplished previously. 

To detect a corrosion-pitted or cracked 

forward or center cable assembly connector 

(connector) and to prevent failure of the cable 

assembly and subsequent loss of control of 

the helicopter, accomplish the following: 

(a) Within the next 10 hours time-inservice or 30 days, whichever comes first, 

using a bright light and a 10X or higher 

magnifying glass, inspect each connector for 

corrosion pitting or cracking by following the 

Accomplishment Instructions, paragraph 2., 

of MD Helicopter, Inc. Service Bulletin 

SB500N–027, SB600N–042, dated May 3, 

2004. If you find

59790 Federal Register / Vol. 69, No. 193 / Wednesday, October 6, 2004 / Rules and Regulations 

corrosion pitting or cracking, replace the 

cable assembly with an airworthy cable 

assembly before further flight. Replacing the 

cable assembly with an airworthy cable 

assembly is terminating action for the 

requirements of this AD. 

(b) To request a different method of 

compliance or a different compliance time 

for this AD, follow the procedures in 14 CFR 

39.19. Contact the Los Angeles Aircraft 

Certification Office, FAA, for information 

about previously approved alternative 

methods of compliance. 

(c) Do the inspection by following MD 

Helicopters, Inc. Service Bulletin SB500N–

027, SB600N–042, dated May 3, 2004. The 

Director of the Federal Register approved this 

incorporation by reference in accordance 

with 5 U.S.C. 552(a) and 1 CFR part 51. 

Copies may be obtained from MD Helicopters 

Inc., Attn: Customer Support Division, 4555 

E. McDowell Rd., Mail Stop M615–GO48, 

Mesa, Arizona 85215–9734, telephone 1–

800–388–3378, fax 480–891–6782, or on the 

Web at http://www.mdhelicopters.com.

Copies may be inspected at the National 

Archives and Records Administration 

(NARA). For information on the availability 

of this material at NARA, call 202–741–6030, 

or go to: http://www.archives.gov/

federal_register/code_of_federal_regulations/

ibr_locations.html.

(d) This amendment becomes effective on 

October 21, 2004.

Issued in Fort Worth, Texas, on September 

22, 2004. 

David A. Downey, 

Manager, Rotorcraft Directorate, Aircraft 

Certification Service.

[FR Doc. 04–22264 Filed 10–5–04; 8:45 am] 

BILLING CODE 4910–13–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2004–19229; Directorate 

Identifier 2004–NM–195–AD; Amendment 

39–13814; AD 2004–20–09] 

RIN 2120–AA64 

Airworthiness Directives; Bombardier 

Model CL–600–2B19 (Regional Jet 

Series 100 & 440) Airplanes

AGENCY: Federal Aviation 

Administration (FAA), DOT.

ACTION: Final rule; request for 

comments. 

SUMMARY: The FAA is adopting a new 

airworthiness directive (AD) for certain 

Bombardier Model CL–600–2B19 

(Regional Jet Series 100 & 440) 

airplanes. This AD requires repetitive 

inspections for cracks, sealant damage, 

and corrosion of the main fittings of the 

main landing gear (MLG), and corrective 

actions if necessary. This AD is 

prompted by a report of a cracked main 

fitting of the MLG. We are issuing this 

AD to detect and correct fatigue 

cracking of the main fitting of the MLG 

and consequent failure of the main 

fitting, which could result in the 

collapse of the MLG.

DATES: Effective October 21, 2004. 

The incorporation by reference of 

certain publications listed in the AD is 

approved by the Director of the Federal 

Register as of October 21, 2004. 

We must receive comments on this 

AD by December 6, 2004.

ADDRESSES: Use one of the following 

addresses to submit comments on this 

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. 

• Fax: (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. 

For service information identified in 

this AD, contact Bombardier, Inc., 

Canadair, Aerospace Group, P.O. Box 

6087, Station Centre-ville, Montreal, 

Quebec H3C 3G9, Canada. You can 

examine this information at the National 

Archives and Records Administration 

(NARA). For information on the 

availability of this material at NARA, 

call (202) 741–6030, or go to: http://

www.archives.gov/federal_register/

code_of_federal_regulations/

ibr_locations.html.

You can examine the contents of this 

AD docket on the Internet at http://

dms.dot.gov, or in person at the Docket 

Management Facility, U.S. Department 

of Transportation, 400 Seventh Street, 

SW., room PL–401, on the plaza level of 

the Nassif Building, Washington, DC. 

Docket Management System (DMS) 

The FAA has implemented new 

procedures for maintaining AD dockets 

electronically. As of May 17, 2004, new 

AD actions are posted on DMS and 

assigned a docket number. We track 

each action and assign a corresponding 

directorate identifier. The DMS AD 

docket number is in the form ‘‘Docket 

No. FAA–2004–99999.’’ The Transport 

Airplane Directorate identifier is in the 

form ‘‘Directorate Identifier 2004–NM–

999–AD.’’ Each DMS AD docket also 

lists the directorate identifier (‘‘Old 

Docket Number’’) as a cross-reference 

for searching purposes. 

Examining the Docket 

You can examine the AD docket on 

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

person at the Docket Management 

Facility office between 9 a.m. and 5 

p.m., Monday through Friday, except 

Federal holidays. The Docket 

Management Facility office (telephone 

(800) 647–5227) is located on the plaza 

level of the Nassif Building at the DOT 

street address stated in the ADDRESSES

section. Comments will be available in 

the AD docket shortly after the DMS 

receives them.

FOR FURTHER INFORMATION CONTACT: 

Technical information: Serge 

Napoleon, Aerospace Engineer, 

Airframe and Propulsion Branch, ANE–

171, FAA, New York Aircraft 

Certification Office, 1600 Stewart 

Avenue, suite 410, Westbury, New York 

11590; telephone (516) 228–7312; fax 

(516) 794–5531. 

Plain language information: Marcia 

Walters, marcia.walters@faa.gov.

SUPPLEMENTARY INFORMATION: Transport 

Canada Civil Aviation (TCCA), which is 

the airworthiness authority for Canada, 

notified the FAA that an unsafe 

condition may exist on certain 

Bombardier Model CL–600–2B19 

(Regional Jet Series 100 & 440) 

airplanes. TCCA advises that it has 

received a report of a cracked main 

fitting of the main landing gear (MLG) 

at the section between the forward face 

of the main fitting on the trunnion side 

and the area just above the upper attach 

lug radius of the shock strut. Laboratory 

examination has found that the fatigue 

crack was initiated from a corrosion pit 

located on the chamfer of the inner bore 

of the pintle pin socket of the main 

fitting of the MLG. This condition, if not 

detected and corrected in a timely 

manner, could cause failure of the main 

fitting of the MLG, which could result 

in the collapse of the MLG.

Relevant Service Information 

Bombardier has issued Alert Service 

Bulletin A601R–32–099, including 

Appendices A through D, dated 

September 15, 2004. The service 

bulletin describes the following 

procedures: 

• Repetitive detailed inspections for 

cracks of the inboard and outboard sides