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 

67808 Federal Register / Vol. 69, No. 224 / Monday, November 22, 2004 / Rules and Regulations 

your comments. We specifically invite 

comments on the overall regulatory, 

economic, environmental, and energy 

aspects of the rule that might suggest a 

need to adjust it. 

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 about this AD. Using the 

search function of the Docket 

Management System (DMS) web site, 

anyone can find and read the comments 

in any of our dockets, including the 

name of the individual who sent the 

comment (or signed the comment for an 

association, business, labor union, etc.). 

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 are reviewing the writing style we 

currently use in regulatory documents. 

We are interested in your comments on 

whether the style of this document is 

clear, and your suggestions to improve 

the clarity of our communications with 

you. You can get more information 

about plain language at http://

www.faa.gov/language and http://

www.plainlanguage.gov.

Examining the AD Docket 

You may examine the docket that 

contains the AD, any comments 

received, and any final disposition in 

person at the 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 

ADDRESSES. Comments will be available 

in the AD docket shortly after the DMS 

receives them.

Regulatory Findings 

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 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 at the address listed 

under ADDRESSES.

List of Subjects in 14 CFR Part 39 

Air transportation, Aircraft, Aviation 

safety, Incorporation by reference, 

Safety.

Adoption of the Amendment

■ 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. The FAA amends § 39.13 by adding 

the following new airworthiness 

directive:

2004–23–16 McCauley Propeller Systems:

Amendment 39–13871. Docket No. 

FAA–2004–19242; Directorate Identifier 

2004–NE–21–AD. 

Effective Date 

(a) This airworthiness directive (AD) 

becomes effective December 7, 2004. 

Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to 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. 

Unsafe Condition 

(d) 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. 

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.

Onetime Eddy-Current Inspection 

(f) Perform a onetime eddy-current 

inspection using the compliance times 

specified in Table 1 of this AD. Use 1.A. 

through 2.D.(7)(c) of the Accomplishment 

Instructions of McCauley Alert Service 

Bulletin (ASB) No. ASB247A, Revision A, 

dated August 18, 2004.

TABLE 1.—COMPLIANCE TIMES

If the propeller assembly has . . . Then inspect . . . 

(1) More than 8,000 hours time-in-service (TIS) on 

the effective date of this AD.

Within 200 hours time-since-last inspection (TSLI) or within 30 days after the effective 

date of this AD, whichever is earlier. 

(2) 8,000 or fewer hours TIS on the effective date of 

this AD.

Within 400 hours TSLI or within 60 days after the effective date of this AD, whichever is 

earlier. 

Credit for Previous Compliance 

(g) Performing the eddy-current inspection 

using McCauley ASB No. A247, dated April 

30, 2004, is acceptable for compliance with 

this AD. 

Reporting Requirements 

(h) The reporting requirement specified in 

2.D.(5) of the Accomplishment Instructions 

of Alert Service Bulletin No. ASB247A, 

Revision A, dated August 18, 2004, are 

approved by the Office of Management and 

Budget and assigned OMB control number 

2120–0056. 

Alternative Methods of Compliance 

(i) The Manager, Chicago Aircraft 

Certification Office, has the authority to 

approve alternative methods of compliance 

for this AD if requested using the procedures 

found in 14 CFR 39.19. 

Material Incorporated by Reference 

(j) You must use McCauley Propeller 

Systems Alert Service Bulletin No. ASB247A, 

Revision A, dated August 18, 2004, to 

perform the actions required by this AD. 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. You can get a copy from 

McCauley Propeller Systems, P.O. Box 7704, 

Wichita, KS 67277–7704, U.S.A.; telephone 

(800) 621–7767. You may review copies on 

the internet at http://dms.dot.gov, or at the 

National Archives and Records 

Administration (NARA). For information on 

Federal Register / Vol. 69, No. 224 / Monday, November 22, 2004 / Rules and Regulations 67809

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.

Related Information 

(k) None.

Issued in Burlington, Massachusetts, on 

November 10, 2004. 

Peter A. White, 

Acting Manager, Engine and Propeller 

Directorate, Aircraft Certification Service.

[FR Doc. 04–25543 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–2004–19618; Directorate 

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

13872; AD 2004–23–17] 

RIN 2120–AA64 

Airworthiness Directives; Mooney 

Airplane Company, Inc., Model M20M 

Airplanes

AGENCY: Federal Aviation 

Administration (FAA), DOT.

ACTION: Final rule; request for 

comments. 

SUMMARY: The FAA is adopting a new 

airworthiness directive (AD) to 

supersede Airworthiness Directive 91–

03–15, which applies to certain Mooney 

Airplane Company, Inc., (Mooney) 

Model M20M airplanes. AD 91–03–15 

currently requires you to replace the 

tailpipe coupling with improved 

tailpipe coupling. Since we issued AD 

91–03–15, a fire erupted in the lower 

left cockpit area on one of the airplanes 

affected by AD 91–03–15. The V-clamp 

that attaches the exhaust tailpipe to the 

turbocharger fell off, which allowed the 

exhaust tailpipe to detach from the 

turbocharger. Hot exhaust gases from 

the turbocharger outlet blasted the lower 

left firewall. This AD requires you to 

replace the existing radiant heat shield 

with the new improved design heat 

shield, deflector kit; replace the existing 

exhaust tailpipe-to-turbocharger V-band 

clamp with the new design V-band 

clamp; and modify the hydraulic brake 

fluid poly line. We are issuing this AD 

to prevent the V-clamp from detaching 

from the turbocharger and to prevent 

exposure of the firewall to hot exhaust 

gases, which could result in an in-flight 

fire. An in-flight fire could lead to loss 

of control of the airplane and passenger 

injury.

DATES: This AD becomes effective on 

December 1, 2004. 

As of December 1, 2004, the Director 

of the Federal Register approved the 

incorporation by reference of certain 

publications listed in the regulation. 

We must receive any comments on 

this AD by January 12, 2005.

ADDRESSES: Use one of the following 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–

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 

Mooney Airplane Company, Inc., Louis 

Schreiner Field, Kerrville, Texas 78028; 

telephone: (830) 896–6000. 

To view the comments to this AD, go 

to http://dms.dot.gov. The docket 

number is FAA–2004–19618.

FOR FURTHER INFORMATION CONTACT:

Garry D. Sills, Aerospace Engineer, 

Rotorcraft Directorate, ASW–150, 2601 

Meacham Blvd, Fort Worth, Texas 

76193; telephone: (817) 222–5154; 

facsimile: (817) 222–5960.

SUPPLEMENTARY INFORMATION: 

Has FAA taken any action to this 

point? The FAA issued AD 91–03–15, 

Amendment 39–6870 to prevent the 

discharge of high temperature exhaust 

gases inside the engine compartment 

that could result in the airplane cabin 

catching fire for certain Mooney Model 

M20M airplanes. AD 91–03–15 

currently requires replacing the tailpipe 

coupling.

What has happened since AD 91–03–

15 to initiate this AD action? The FAA 

received a report that a fire erupted 

below the pilot’s rudder pedals shortly 

after takeoff on one of the airplanes 

affected by AD 91–03–15, which caused 

smoke to fill the cabin. Investigation 

revealed that the V-clamp attaching the 

exhaust tailpipe to the turbocharger had 

fallen off. This allowed the exhaust 

tailpipe to drop away form the 

turbocharger. Hot exhaust gases from 

the turbocharger outlet were blasted 

onto the lower left firewall. The fire 

ignited in the left lower cockpit area 

below the rudder/brake pedals and 

behind the firewall. Hydraulic fluid 

ignited when a plastic hydraulic supply 

line behind the firewall melted. 

What is the potential impact if FAA 

took no action? The V-clamp could 

detach from the turbocharger and 

expose the firewall to hot exhaust gases, 

which could result in an in-flight fire. 

An in-flight fire could lead to loss of 

control of the airplane and passenger 

injury. 

Is there service information that 

applies to this subject? Mooney has 

issued Service Bulletin M20–283A, 

dated March 30, 2004. 

What are the provisions of this service 

information? The service bulletin 

includes procedures for:

—Replacing the existing radiant heat 

shield with the new heat shield, 

deflector kit; 

—Replacing the existing exhaust 

tailpipe-to-turbocharger V-band 

clamp; and 

—Modifying the hydraulic brake fluid 

poly line. 

FAA’s Determination and Requirements 

of the 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. 

Since the unsafe condition described 

previously is likely to exist or develop 

on other Mooney Model M20M 

airplanes of the same type design, we 

are issuing this AD to prevent the Vclamp from detaching from the 

turbocharger and to prevent exposure of 

the firewall to hot exhaust gases, which 

could result in an in-flight fire. An inflight fire could lead to loss of control 

of the airplane and passenger injury. 

What does this AD require? This AD 

supersedes AD 91–03–15 and requires 

you to incorporate the actions in the 

previously-referenced service bulletin. 

In preparing this rule, we contacted 

type clubs and aircraft operators to get 

technical information and information 

on operational and economic impacts. 

We did not receive any information 

through these contacts. If received, we 

would have included a discussion of 

any information that may have 

influenced this action in the rulemaking 

docket. 

How does the revision to 14 CFR part 

39 affect this 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