7934 Federal Register / Vol. 75, No. 35 / Tuesday, February 23, 2010 / Rules and Regulations 

Directorate, 1601 Lind Avenue, SW., Renton, 

Washington. For information on the 

availability of this material at the FAA, call 

425–227–1221 or 425–227–1152. 

(5) You may also review copies of the 

service information that is incorporated by 

reference 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. 

Issued in Renton, Washington, on February 

5, 2010. 

Stephen P. Boyd, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2010–3121 Filed 2–22–10; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2010–0093; Directorate 

Identifier 97–ANE–06–AD; Amendment 39– 

16198; AD 2010–04–05] 

RIN 2120–AA64 

Airworthiness Directives; McCauley 

Propeller Systems 1A103/TCM Series 

Propellers 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule; request for 

comments. 

SUMMARY: The FAA is superseding an 

existing airworthiness directive (AD) for 

McCauley Propeller Systems 1A103/ 

TCM series propellers. That AD 

requires, for certain serial numbers 

(S/Ns) of McCauley Propeller Systems 

1A103/TCM series propellers, initial 

and repetitive visual and dye penetrant 

inspections for cracks in the propeller 

hub, replacement of propellers with 

cracks that do not meet acceptable 

limits, and rework of propellers with 

cracks that meet acceptable limits. This 

AD requires, for all McCauley Propeller 

Systems 1A103/TCM series propellers, 

the same actions but at reduced 

compliance times. This AD also requires 

inspections of the bolt holes, reaming 

holes if necessary, and inspections of 

steel reinforcement plates and gaskets. 

This AD results from 16 reports received 

of propeller hubs found cracked since 

AD 2003–12–05 was issued. We are 

issuing this AD to prevent propeller 

separation due to hub fatigue cracking, 

which can result in loss of control of the 

airplane. 

DATES: Effective March 10, 2010. The 

Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in the 

regulations as of March 10, 2010. 

We must receive any comments on 

this AD by April 26, 2010. 

ADDRESSES: Use one of the following 

addresses to comment on this AD. 

• Federal eRulemaking Portal: Go to 

http://www.regulations.gov and follow 

the instructions for sending your 

comments electronically. 

• Mail: Docket Management Facility, 

U.S. Department of Transportation, 1200 

New Jersey Avenue, SE., West Building 

Ground Floor, Room W12–140, 

Washington, DC 20590–0001. 

• Hand Delivery: Deliver to Mail 

address above between 9 a.m. and 5 

p.m., Monday through Friday, except 

Federal holidays. 

• Fax: (202) 493–2251. 

FOR FURTHER INFORMATION CONTACT: 

Thomas Teplik, Aerospace Engineer, 

Wichita Aircraft Certification Office, 

FAA, Small Airplane Directorate, 1801 

Airport Road, Room 100, Wichita, KS 

67209; e-mail: thomas.teplik@faa.gov; 

telephone: (316) 946–4196; fax: (316) 

946–4107. 

SUPPLEMENTARY INFORMATION: The FAA 

amends 14 CFR part 39 by superseding 

AD 2003–12–05, Amendment 39–13190 

(68 FR 35155, June 12, 2003). That AD 

requires, for certain S/Ns of McCauley 

Propeller Systems 1A103/TCM series 

propellers, initial and repetitive visual 

and dye penetrant inspections for cracks 

in the propeller hub, replacement of 

propellers with cracks that do not meet 

acceptable limits, and rework of 

propellers with cracks that meet 

acceptable limits. That AD was the 

result of reports of hub cracking on the 

camber (forward) side of the propeller 

hub near the attachment bolt holes on 

certain propellers. That condition, if not 

corrected, could result in propeller 

separation due to hub fatigue cracking, 

which can result in loss of control of the 

airplane. 

Actions Since AD 2003–12–05 Was 

Issued 

Since AD 2003–12–05 was issued, we 

received 16 reports of propeller hubs 

found cracked. Two of the cracks were 

on propellers outside the propeller 

range of serial numbers affected by AD 

2003–12–05. These cracks began at a 

bolt hole and extended through to the 

hub outer surface. These propellers had 

fewer than 3,000 operating hours timein-service (TIS). AD 2003–12–05 

required inspections starting at 3,000 

operating hours TIS. We have not yet 

been able to determine the cause of the 

propeller hub cracking. 

Relevant Service Information 

We have reviewed and approved the 

technical contents of McCauley 

Propeller Systems Alert Service Bulletin 

(ASB) No. ASB221E, dated January 28, 

2010. That ASB describes, for all 

McCauley Propeller Systems 1A103/ 

TCM series propellers, procedures for 

initial and repetitive visual and dye 

penetrant inspections for cracks in the 

propeller hub, removal from service of 

propellers with cracks that do not meet 

acceptable limits, and rework of 

propellers with cracks that meet 

acceptable limits. 

FAA’s Determination and Requirements 

of This AD 

The unsafe condition described 

previously is likely to exist or develop 

on other McCauley Propeller Systems 

1A103/TCM series propellers of the 

same type design. We are issuing this 

AD to prevent propeller separation due 

to hub fatigue cracking, which can 

result in loss of control of the airplane. 

This AD requires, for all McCauley 

Propeller Systems 1A103/TCM series 

propellers, initial and repetitive visual 

and dye penetrant inspections for cracks 

in the propeller hub, including bolt 

holes, reaming holes if necessary, 

inspections of steel reinforcement plates 

and gaskets, removal from service of 

propellers with cracks that do not meet 

acceptable limits, and rework of 

propellers with cracks that meet 

acceptable limits. 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 less than 30 

days. 

Interim Action 

These actions are interim actions and 

we may 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 us any 

written relevant data, views, or 

arguments regarding this AD. Send your 

comments to an address listed under 

ADDRESSES. Include ‘‘Docket No. FAA– 

2010–0093; Directorate Identifier 97– 

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Federal Register / Vol. 75, No. 35 / Tuesday, February 23, 2010 / Rules and Regulations 7935 

ANE–06–AD’’ in the subject line of your 

comments. We specifically invite 

comments on the overall regulatory, 

economic, environmental, and energy 

aspects of the rule that might suggest a 

need to modify it. 

We will post all comments we 

receive, without change, to http:// 

www.regulations.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 the Web site, anyone 

can find and read the comments in any 

of our dockets, including, if provided, 

the name of the individual who sent the 

comment (or signed the comment on 

behalf of 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). 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http:// 

www.regulations.gov; or in person at the 

Docket Operations office between 9 a.m. 

and 5 p.m., Monday through Friday, 

except Federal holidays. The AD docket 

contains this AD, the regulatory 

evaluation, any comments received, and 

other information. The street address for 

the Docket Operations office (telephone 

(800) 647–5527) is the same as the Mail 

address provided in the ADDRESSES

section. Comments will be available in 

the AD docket shortly after receipt. 

Authority for This Rulemaking 

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 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 rulemaking 

action. 

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 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 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 

removing Amendment 39–13190 (68 FR 

35155, June 12, 2003), and by adding a 

new airworthiness directive, 

Amendment 39–16198, to read as 

follows: 

2010–04–05 McCauley Propeller Systems: 

Amendment 39–16198. Docket No. 

FAA–2010–0093; Directorate Identifier 

97–ANE–06–AD. 

Effective Date 

(a) This airworthiness directive (AD) 

becomes effective March 10, 2010. 

Affected ADs 

(b) This AD supersedes AD 2003–12–05, 

Amendment 39–13190. 

Applicability 

(c) This AD applies to McCauley Propeller 

Systems 1A103/TCM series propellers, all 

serial numbers. These propellers are installed 

on, but not limited to Cessna 152, Cessna 

A152, Reims F152, and Reims FA152 series 

airplanes, and on airplanes with Lycoming 

0–235–L2C reciprocating engines modified 

by Supplemental Type Certificates 

SA1763SO, SA5695NM, SA1000NW, and 

SA432NE. 

Unsafe Condition 

(d) This AD results from 16 reports 

received of propeller hubs found cracked 

since AD 2003–12–05 was issued. We are 

issuing this AD to prevent propeller 

separation due to hub fatigue cracking, which 

can result in 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. 

Initial Inspection of Propellers Not 

Previously Inspected 

(f) For propellers not previously inspected 

using McCauley Service Bulletin (Alert) No. 

221C, dated September 7, 1999, or McCauley 

Alert Service Bulletin (ASB) No. ASB221D, 

dated January 28, 2008, do the following: 

(1) For propellers with more than 1,500 

operating hours time-since-new (TSN) or 

unknown operating hours TSN on the 

effective date of this AD, within the next 50 

operating hours time-in-service (TIS), do the 

actions specified in paragraphs (h) through 

(m) of this AD. 

(2) For propellers with 1,500 or fewer 

operating hours TSN on the effective date of 

this AD, upon reaching 1,500 operating hours 

TSN or within the next 50 operating hours 

TIS, whichever is later, do the actions 

specified in paragraphs (h) through (m) of 

this AD. 

Initial Inspection of Propellers Previously 

Inspected 

(g) For propellers previously inspected 

using McCauley Service Bulletin (Alert) No. 

221C, dated September 7, 1999, or McCauley 

ASB No. ASB221D, dated January 28, 2008, 

do the following: 

(1) For propellers with more than 1,500 

operating hours TSN on the effective date of 

this AD, and with 750 or more operating 

hours time-since-last-inspection (TSLI), 

within the next 50 operating hours TIS, do 

the actions specified in paragraphs (h) 

through (m) of this AD. 

(2) For propellers with more than 1,500 

operating hours TSN on the effective date of 

this AD, and with fewer than 750 operating 

hours TSLI, before reaching 750 operating 

hours TSLI or within the next 50 operating 

hours TIS, whichever occurs later, do the 

actions specified in paragraphs (h) through 

(m) of this AD. 

(h) Visual- and dye-penetrant-inspect for 

cracks in the propeller hub. 

(i) Inspect the bolt holes and ream the 

holes if necessary. 

(j) Inspect the steel reinforcement plates 

and gaskets. 

(k) Remove propellers that are not within 

the bolt hole inspection limits or have cracks 

that are not within the rework limits. 

(l) Rework propellers that have cracks that 

meet acceptable rework limits. 

(m) Use the Accomplishment Instructions 

of McCauley ASB No. ASB221E, dated 

January 28, 2010, to do the inspections, 

rework, and removals from service. 

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7936 Federal Register / Vol. 75, No. 35 / Tuesday, February 23, 2010 / Rules and Regulations 

Repetitive Propeller Inspections 

(n) Thereafter, for all propellers, within 

every additional 750 operating hours TIS, 

perform the actions in paragraphs (h) through 

(m) of this AD. 

Alternative Methods of Compliance 

(o) The Manager, Wichita 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. 

Special Flight Permits 

(p) Under 39.23, we are limiting the 

availability of special flight permits for this 

AD. Special flight permits are available only 

if: 

(1) The operator has not observed abnormal 

propeller vibration or abnormal engine 

vibration. 

(2) The operator has not made earlier 

reports of abnormal propeller vibration, 

abnormal engine vibration, or other abnormal 

propeller operations that have not been 

addressed. 

Related Information 

(q) Contact Thomas Teplik, Aerospace 

Engineer, Wichita Aircraft Certification 

Office, FAA, Small Airplane Directorate, 

1801 Airport Road, Room 100, Wichita, KS 

67209; e-mail: thomas.teplik@faa.gov; 

telephone: (316) 946–4196; fax: (316) 946– 

4107, for more information about this AD. 

Material Incorporated by Reference 

(r) You must use McCauley Propeller 

Systems Alert Service Bulletin No. ASB221E, 

dated January 28, 2010, to perform the 

inspections, rework, and removals from 

service 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. Contact McCauley 

Propeller Systems, 5800 E. Pawnee, Wichita, 

KS 67218, telephone: (800) 621–7767; e-mail: 

productsupport@mccauley.textron.com; Web: 

http://www.mccauley.textron.com, for a copy 

of this service information. You may review 

copies at the FAA, New England Region, 12 

New England Executive Park, Burlington, 

MA; or 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/cfr/ibrlocations.html. 

Issued in Burlington, Massachusetts, on 

February 8, 2010. 

Peter A. White, 

Assistant Manager, Engine and Propeller 

Directorate, Aircraft Certification Service. 

[FR Doc. 2010–3113 Filed 2–22–10; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2010–0125; Directorate 

Identifier 2010–CE–005–AD; Amendment 

39–16208; AD 2010–04–15] 

RIN 2120–AA64 

Airworthiness Directives; SCHEIBEFlugzeugbau GmbH Model SF 25C 

Gliders 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule; request for 

comments. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for the 

products listed above. This AD results 

from mandatory continuing 

airworthiness information (MCAI) 

issued by the aviation authority of 

another country to identify and correct 

an unsafe condition on an aviation 

product. The MCAI describes the unsafe 

condition as: 

The aileron hinges and the stabilizer are 

fastened with steel tube rivets and brass tube 

rivets. 

During a complete overhaul, broken brass 

tube rivets have been detected. It has been 

determined that, due to production quality 

issue, the upset heads of the brass tube rivets 

could break under normal load conditions. 

This condition, if not corrected, could 

possibly lead to loss of control of the 

powered sailplane. 

This AD requires actions that are 

intended to address the unsafe 

condition described in the MCAI. 

DATES: This AD becomes effective 

March 15, 2010. 

On March 15, 2010, the Director of the 

Federal Register approved the 

incorporation by reference of certain 

publications listed in this AD. 

We must receive comments on this 

AD by April 9, 2010. 

ADDRESSES: You may send comments by 

any of the following methods: 

• Federal eRulemaking Portal: Go to 

http://www.regulations.gov. Follow the 

instructions for submitting comments. 

• Fax: (202) 493–2251. 

• Mail: U.S. Department of 

Transportation, Docket Operations, M– 

30, West Building Ground Floor, Room 

W12–140, 1200 New Jersey Avenue, SE., 

Washington, DC 20590. 

• Hand Delivery: U.S. Department of 

Transportation, Docket Operations, M– 

30, West Building Ground Floor, Room 

W12–140, 1200 New Jersey Avenue, SE., 

Washington, DC 20590, between 9 a.m. 

and 5 p.m., Monday through Friday, 

except Federal holidays. 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http:// 

www.regulations.gov; or in person at the 

Docket Management Facility between 9 

a.m. and 5 p.m., Monday through 

Friday, except Federal holidays. The AD 

docket contains this AD, the regulatory 

evaluation, any comments received, and 

other information. The street address for 

the Docket Office (telephone (800) 647– 

5527) is in the ADDRESSES section. 

Comments will be available in the AD 

docket shortly after receipt. 

FOR FURTHER INFORMATION CONTACT: Greg 

Davison, Aerospace Engineer, FAA, 

Small Airplane Directorate, 901 Locust, 

Room 301, Kansas City, Missouri 64106; 

telephone: (816) 329–4130; fax: (816) 

329–4090; e-mail: 

gregory.davison@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Discussion 

The European Aviation Safety Agency 

(EASA), which is the Technical Agent 

for the Member States of the European 

Community, has issued Emergency AD 

No. 2010–0011–E, dated January 25, 

2010 (referred to after this as ‘‘the 

MCAI’’), to correct an unsafe condition 

for the specified products. The MCAI 

states: 

The aileron hinges and the stabilizer are 

fastened with steel tube rivets and brass tube 

rivets. 

During a complete overhaul, broken brass 

tube rivets have been detected. It has been 

determined that, due to production quality 

issue, the upset heads of the brass tube rivets 

could break under normal load conditions. 

This condition, if not corrected, could 

possibly lead to loss of control of the 

powered sailplane. 

For the reason described above, this AD 

requires an inspection of the affected tube 

rivets and, if necessary, their replacement. 

You may obtain further information by 

examining the MCAI in the AD docket. 

Relevant Service Information 

SCHEIBE-Flugzeugbau GmbH has 

issued SCHEIBE AIRCRAFT GMBH 

Service Bulletin 653–64, dated 

November 10, 2009. The actions 

described in this service information are 

intended to correct the unsafe condition 

identified in the MCAI. 

FAA’s Determination and Requirements 

of the AD 

This product has been approved by 

the aviation authority of another 

country, and is approved for operation 

in the United States. Pursuant to our 

bilateral agreement with this State of 

Design Authority, they have notified us 

of the unsafe condition described in the 

MCAI and service information 

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