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

50 titles pursuant to 44 U.S.C. 1510.

The Code of Federal Regulations is sold by

the Superintendent of Documents. Prices of

new books are listed in the first FEDERAL

REGISTER issue of each week.

Rules and Regulations Federal Register

67805

Vol. 69, No. 224

Monday, November 22, 2004

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2004–19613; Directorate 

Identifier 2004–SW–38–AD; Amendment 39–

13870; AD 2004–23–15] 

RIN 2120–AA64 

Airworthiness Directives; MD 

Helicopters, Inc. Model MD900 

Helicopters

AGENCY: Federal Aviation 

Administration, DOT.

ACTION: Final rule; request for 

comments. 

SUMMARY: This amendment adopts a 

new airworthiness directive (AD) for the 

MD Helicopters, Inc. (MDHI) Model 

MD900 helicopters. This action requires 

reducing the life limit of certain Notar 

fan system tension-torsion (TT) straps. 

This action also requires, at a specified 

time interval, removing each affected TT 

strap from the helicopter, doing a visual 

and x-ray inspection, and replacing any 

unairworthy part before further flight. 

Reporting the discovery of any 

unairworthy TT strap is also required. 

This amendment is prompted by two 

recent in-flight TT strap failures. The 

actions specified in this AD are 

intended to prevent failure of a TT strap 

resulting in loss of directional control 

and subsequent loss of control of the 

helicopter.

DATES: Effective December 7, 2004. 

The incorporation by reference of 

certain publications listed in the 

regulations is approved by the Director 

of the Federal Register as of December 

7, 2004. 

Comments for inclusion in the Rules 

Docket must be received on or before 

January 21, 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.

You may 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.

Examining the Docket 

You may examine the docket that 

contains the AD, any comments, and 

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:

Roger Durbin, Aviation Safety Engineer, 

FAA, Los Angeles Aircraft Certification 

Office, Airframe Branch, 3960 

Paramount Blvd., Lakewood, California 

90712, telephone (562) 627–5233, fax 

(562) 627–5210.

SUPPLEMENTARY INFORMATION: This 

amendment adopts a new AD applicable 

to MDHI Model MD900 helicopters with 

a TT strap, part number (P/N) 

900R3442009–103, 900R6442009–103, 

900R3442009–101, or 500N5311–5, 

installed. This action requires: 

• Before further flight, for TT strap, P/

N 900R3442009–103 and 900R6442009–

103, reducing the life limit from 3034 to 

2500 hours time-in-service (TIS);

• Within 10 hours TIS, for any TT 

strap that has accumulated 1190 or more 

hours TIS, doing a visual and x-ray 

inspection of each TT strap and 

replacing any unairworthy part before 

further flight; 

• Before the TT strap accumulates 

1200 hours TIS, for any TT strap with 

less than 1190 hours TIS, doing a visual 

and x-ray inspection of each strap and 

replacing any unairworthy part before 

further flight; and 

• Within 7 days, reporting 

information about any unairworthy TT 

strap to Roger Durbin, Aviation Safety 

Engineer, FAA, Los Angeles Aircraft 

Certification Office, Airframe Branch, 

3960 Paramount Blvd., Lakewood, 

California 90712, telephone (562) 627–

5233, fax (562) 627–5210.

This amendment is prompted by two 

recent in-flight TT strap failures. The 

cause of the failures is not known at this 

time, and this AD is interim action. We 

will consider further rulemaking once 

our investigation is complete. The 

actions specified in this AD are 

intended to prevent failure of a TT strap 

resulting in loss of directional control 

and subsequent loss of control of the 

helicopter. 

We have reviewed MD Helicopters 

Service Bulletin SB–900–095, dated 

November 3, 2004. The service bulletin 

advises of the reduction of the TT strap 

life limit and describes procedures for 

performing an inspection of each TT 

strap for nicks, cuts, cracks, or wear. 

Procedures for a Level II or higher X-Ray 

Technician to do and interpret an x-ray 

inspection of each TT strap for 

progressive fiber fractures are also 

included in the service bulletin. 

This unsafe condition is likely to exist 

or develop on other helicopters of the 

same type design. Therefore, this AD is 

being issued to prevent failure of a TT 

strap resulting in loss of directional 

control and subsequent loss of control of 

the helicopter. This AD requires, before 

further flight, reducing the life limit of 

67806 Federal Register / Vol. 69, No. 224 / Monday, November 22, 2004 / Rules and Regulations 

certain part-numbered TT straps. This 

AD also requires, depending on the 

hours accumulated on the TT strap, 

doing a visual and x-ray inspection 

within 10 hours TIS or before the 

accumulation of 1200 hours TIS and 

replacing any unairworthy part before 

further flight. Reporting the discovery of 

any unairworthy TT strap is also 

required. Accomplishing the 

inspections in accordance with the 

previously described service bulletin is 

required. The short compliance time 

involved is required because the 

previously described critical unsafe 

condition can adversely affect the 

controllability of the helicopter. 

Therefore, reducing the TT strap life 

limit before further flight, inspecting 

each TT strap at the specified time 

interval, and reporting information 

about any unairworthy TT strap is 

required within 7 days, and this AD 

must be issued immediately. 

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 

31 helicopters. It will take 

approximately 7 work hours for each 

inspection and replacement at an 

average labor rate of $65 per work hour. 

It will also cost $100 for each x-ray 

inspection. Required parts will cost 

approximately $757 per TT strap 

replacement. Based on these figures, we 

estimate the total cost impact of the AD 

on U.S. operators to be $40,672 

(assuming a visual and x-ray inspection 

on each helicopter and a TT strap 

replacement on 8% of the fleet). 

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–2004–19613; 

Directorate Identifier 2004–SW–38–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:

2004–23–15 MD Helicopters, Inc.:

Amendment 39–13870. Docket No. 

FAA–2004–19613; Directorate Identifier 

2004–SW–38–AD.

Applicability: Model MD900 helicopters, 

with a Notar fan system that has a tensiontorsion (TT) strap, part number (P/N) 

900R3442009–103, 900R6442009–103, 

900R3442009–101, or 500N5311–5, installed, 

certificated in any category. 

Compliance: Required as indicated, unless 

accomplished previously. 

To prevent failure of a TT strap in the 

Notar fan system, which could result in loss 

of directional control and subsequent loss of 

control of the helicopter, accomplish the 

following:

(a) Before further flight, for TT straps,

P/N 900R3442009–103 and 900R6442009–

103, reduce the life limit from 3034 to 2500 

hours time-in-service (TIS). 

(b) Within 10 hours TIS, for any TT strap 

that has accumulated 1190 or more hours 

TIS, remove the TT strap from the helicopter 

and do a visual and x-ray inspection in 

accordance with the Inspection Instructions, 

paragraph 2.B.(1). through (5). and Figures 1 

and 2 of MD Helicopters Service Bulletin 

SB900–095, dated November 3, 2004 (SB). 

Replace any unairworthy part before further 

flight. 

(c) Before the TT strap accumulates 1200 

hours TIS, for any TT strap with less than 

1190 hours TIS, remove the TT strap from the 

helicopter and do a visual and x-ray 

inspection in accordance with the Inspection 

Instructions, paragraph 2.B.(1). through (5). 

and Figures 1 and 2 of the SB. Replace any 

unairworthy part before further flight. 

(d) The x-ray inspection of the TT strap 

must be performed by a Level II or higher xray technician who is qualified under the 

guidelines established by MIL–STD–410E, 

ATA Specification 105, AIA–NAS–410, or an 

FAA-accepted equivalent for qualification 

standards. 

(e) Within 7 days, for any TT strap that you 

find unairworthy, report the helicopter serial 

number (S/N), the TT strap P/N and S/N, the 

total hours TIS on the TT strap, and a 

description of the part condition rendering it 

unairworthy. Report the information to Roger 

Durbin, Aviation Safety Engineer, FAA, Los 

Angeles Aircraft Certification Office, 

Airframe Branch, 3960 Paramount Blvd., 

Lakewood, California 90712, telephone (562) 

627–5233, fax (562) 627–5210. 

(f) Information collection requirements 

contained in this AD have been approved by 

the Office of Management and Budget (OMB) 

under the provisions of the Paperwork 

Reduction Act of 1980 (44 U.S.C. 3501 et 

seq.) and have been assigned OMB Control 

Number 2120–0056. 

(g) This AD revises the Airworthiness 

Limitations section of the maintenance 

manual by reducing the life limit of the TT 

strap, P/N 900R3442009–103 and 

900R6442009–103, from 3034 hours TIS to 

2500 hours TIS. 

(h) 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, Transport Airplane Directorate, 

FAA, for information about previously 

approved alternative methods of compliance. 

(i) The inspections shall be done in 

accordance with MD Helicopters Service 

Bulletin SB900–095, dated November 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 

Federal Register / Vol. 69, No. 224 / Monday, November 22, 2004 / Rules and Regulations 67807

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 

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.

(j) This amendment becomes effective on 

December 7, 2004.

Issued in Fort Worth, Texas, on November 

10, 2004. 

Kim Smith, 

Acting Manager, Rotorcraft Directorate, 

Aircraft Certification Service.

[FR Doc. 04–25542 Filed 11–19–04; 8:45 am] 

BILLING CODE 4910–13–U

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2004–19242; Directorate 

Identifier 2004–NE–21–AD; Amendment 39–

13871; AD 2004–23–16] 

RIN 2120–AA64 

Airworthiness Directives; McCauley 

Propeller Systems Five-Blade Propeller 

Assemblies

AGENCY: Federal Aviation 

Administration (FAA), DOT.

ACTION: Final rule; request for 

comments. 

SUMMARY: The FAA is adopting a new 

airworthiness directive (AD) for 

McCauley Propeller Systems propeller 

assemblies, part numbers (P/Ns) 

B5JFR36C1101/114GCA–0, 

C5JFR36C1102/L114GCA–0, 

B5JFR36C1103/114HCA–0, and 

C5JFR36C1104/L114HCA–0, installed 

on BAE Systems (Operations) Limited 

Jetstream Model 4100 series airplanes. 

This AD requires a one-time eddycurrent inspection of the propeller hub 

for cracks, and if necessary, replacing 

the propeller assembly. This AD results 

from three reports of cracked hubs. We 

are issuing this AD to detect cracked 

hubs, which could cause failure of the 

propeller hub and loss of control of the 

airplane.

DATES: This AD becomes effective 

December 7, 2004. The Director of the 

Federal Register approved the 

incorporation by reference of certain 

publications listed in the regulation as 

of December 7, 2004. 

We must receive any comments on 

this AD by January 21, 2005.

ADDRESSES: Use one of the following 

addresses to comment 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–

0001. 

• 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. 

Contact McCauley Propeller Systems, 

P.O. Box 7704, Wichita, KS 67277–7704, 

U.S.A.; telephone (800) 621–7767, for 

the service information identified in this 

AD.

FOR FURTHER INFORMATION CONTACT:

Timothy Smyth, Aerospace Engineer, 

Chicago Aircraft Certification Office, 

FAA, Small Airplane Directorate, 2300 

East Devon Avenue, Des Plaines, IL 

60018; telephone: (847) 294–7132; fax: 

(847) 294–7834.

SUPPLEMENTARY INFORMATION: We have 

received three reports of cracks in the 

hubs of certain McCauley Propeller 

Systems propeller assemblies. An 

operator reported an oil leak at the end 

of a flight. Investigation revealed a 

significant crack in the propeller hub. In 

addition, the same operator reported 

cracks in two other hubs that might be 

related to the first report. In both of 

those reports, the operator inspected the 

hub because of reported oil leaks. The 

operator performed a voluntary 

inspection program, and did not find 

any more cracks. About 30 percent of 

the remaining fleet has complied with 

the voluntary inspection over the past 

several months. No operator has 

reported any more cracked hubs. 

Although we believe the cracks are 

caused by fatigue, we don’t know the 

exact cause. One possibility is that 

operating the propeller in the restricted 

RPM range during ground operation is 

contributing to premature failure of the 

propeller hub. This condition, if not 

corrected, could result in failure of the 

propeller hub and loss of control of the 

airplane. 

Relevant Service Information 

We have reviewed and approved the 

technical contents of McCauley Alert 

Service Bulletin (ASB) No. ASB247A, 

Revision A, dated August 18, 2004. That 

ASB describes procedures for removing 

the propeller from the airplane, 

performing an eddy-current inspection, 

and installing the propeller after the 

inspection. 

FAA’s Determination and Requirements 

of This AD 

The unsafe condition described 

previously is likely to exist or develop 

on other McCauley Propeller Systems 

propeller assemblies, P/Ns 

B5JFR36C1101/114GCA–0, 

C5JFR36C1102/L114GCA–0, 

B5JFR36C1103/114HCA–0, and 

C5JFR36C1104/L114HCA–0, of the same 

type design. We are issuing this AD to 

detect cracked hubs, which could cause 

failure of the propeller hub and loss of 

control of the airplane. This AD requires 

performing a one-time eddy-current 

inspection of the propeller hub for 

cracks within:

• 200 hours time-since-last inspection 

(TSLI), but not later than 30 days after 

the effective date of this AD, on 

propeller assemblies with more than 

8,000 hours time-in-service (TIS) and, if 

necessary, replacing the propeller 

assembly. 

• 400 hours TSLI, but not later than 

60 days after the effective date of this 

AD, on propeller assemblies with 8,000 

or fewer hours TIS and, if necessary, 

replacing the propeller assembly. 

You must use the service information 

described previously to perform the 

actions required by this AD. 

FAA’s Determination of the Effective 

Date 

Since an unsafe condition exists that 

requires the immediate adoption of this 

AD, we have found that notice and 

opportunity for public comment before 

issuing this AD are impracticable, and 

that good cause exists for making this 

amendment effective in fewer than 30 

days. 

Interim Action 

These actions are interim actions and 

we might take further rulemaking 

actions in the future. 

Comments Invited 

This AD is a final rule that involves 

requirements affecting flight safety and 

was not preceded by notice and an 

opportunity for public comment; 

however, we invite you to send any 

written relevant data, views, or 

arguments on this AD. Send your 

comments to an address listed under 

ADDRESSES. Include ‘‘AD Docket No. 

FAA–2004–19242; Directorate Identifier 

2004–NE–21–AD’’ in the subject line of