### 39801 Federal Register / Vol. 75, No. 133 / Tuesday, July 13, 2010 / Rules and Regulations

(1) The Director of the Federal Register approved the incorporation by reference of Bombardier Service Bulletin 84–29–22, Revision A, dated February 24, 2009, under 5 U.S.C. 552(a) and 1 CFR part 51.

(2) The Director of the Federal Register previously approved the incorporation by reference of the service information contained in Table 4 of this AD on September 2, 2008 (73 FR 47818, August 15, 2008).



### TABLE 

### 4—M ATERIAL 

### P REVIOUSLY 

### I NCORPORATED BY 

### R EFERENCE IN 

### AD 2008–17–06

Bombardier temporary amendment— Issue— Dated— To Bombardier Dash 8 Q400 Airplane Flight Manual—

13 ............................................................... 3 June 9, 2008 ............. Model 400 PSM 1–84–1A. 13 ............................................................... 3 June 9, 2008 ............. Model 401 PSM 1–84–1A. 13 ............................................................... 3 June 9, 2008 ............. Model 402 PSM 1–84–1A.

(3) On July 10, 2007 (72 FR 30968, June 5, 2007), the Director of the Federal Register approved the incorporation by reference of the temporary amendments identified in Table 5 of this AD.



### TABLE 

### 5—M ATERIAL 

### P REVIOUSLY 

### I NCORPORATED BY 

### R EFERENCE IN 

### AD 2007–12–03

Bombardier temporary amendment— Issue— Dated— To Bombardier Dash 8 Q400 Airplane Flight Manual—

13 ............................................................... 1 July 14, 2005 ............. Model 400 PSM 1–84–1A. 13 ............................................................... 1 July 14, 2005 ............. Model 401 PSM 1–84–1A. 13 ............................................................... 1 July 14, 2005 ............. Model 402 PSM 1–84–1A.

(4) For service information identified in this AD, contact Bombardier, Inc., 400 Co ˆ teVertu Road West, Dorval, Que  ́ bec H4S 1Y9, Canada; telephone 514–855–5000; fax 514– 855–7401; e-mail thd.qseries@aero.bombardier.com; Internet http://www.bombardier.com.

(5) You may review copies of the service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington. For information on the availability of this material at the FAA, call

425–227–1221.

(6) 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 June 25,

2010. Ali Bahrami, Manager, Transport Airplane Directorate, Aircraft Certification Service.
[FR Doc. 2010–16434 Filed 7–12–10; 8:45 am]

**BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION** 

**Federal Aviation Administration**

**14 CFR Part 39**

**[Docket No. FAA–2007–29176; Directorate Identifier 2007–NE–38–AD; Amendment 39–**  **16365; AD 2010–14–20]**

**RIN 2120–AA64**

**Airworthiness Directives; McCauley Propeller Systems Model 4HFR34C653/**  **L106FA Propellers**

**AGENCY :**  Federal Aviation Administration (FAA), DOT.

**ACTION :**  Final rule.

**SUMMARY :**  The FAA is adopting a new airworthiness directive (AD) for McCauley Propeller Systems model 4HFR34C653/L106FA propellers. This AD requires a onetime fluorescent penetrant inspection (FPI) and eddy current inspection (ECI) of the propeller hub for cracks. This AD results from reports of 10 hubs found cracked during propeller overhaul. We are issuing this AD to prevent failure of the propeller hub, which could cause blade separation, damage to the airplane, and loss of control of the airplane.

**DATES :**  This AD becomes effective August 17, 2010. The Director of the Federal Register approved the incorporation by reference of certain publications listed in the regulations as of August 17, 2010.

**ADDRESSES :**  You can get the service information identified in this AD from McCauley Propeller Systems, P.O. Box 7704, Wichita, KS 67277–7704; telephone (800) 621–7767.

The Docket Operations office is located at Docket Management Facility, U.S. Department of Transportation, 1200 New Jersey Avenue, SE., West Building Ground Floor, Room W12–140, Washington, DC 20590–0001.

**FOR FURTHER INFORMATION CONTACT :**  Jeff Janusz, Aerospace Engineer, Wichita Aircraft Certification Office, FAA, Small Airplane Directorate, 1801 Airport Road, Wichita, KS 67209; e-mail: jeff.janusz@faa.gov; telephone (316) 946–4148; fax (316) 946–4107.

**SUPPLEMENTARY INFORMATION :**  The FAA proposed to amend 14 CFR part 39 with a proposed AD. The proposed AD applies to McCauley Propeller Systems model 4HFR34C653/L106FA propellers. We published the proposed AD in the Federal Register on September 28, 2007 (72 FR 55120). We also published a supplemental proposed AD in the Federal Register on April 13, 2010 (75 FR 18774). Those actions proposed to require a onetime FPI and ECI of the propeller hub for cracks. 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 provided in the


### 39802 Federal Register / Vol. 75, No. 133 / Tuesday, July 13, 2010 / Rules and Regulations

**ADDRESSES** section. Comments will be available in the AD docket shortly after receipt.

Comments

We provided the public the opportunity to participate in the development of this AD. We received one comment on the original proposed AD, which we responded to in the supplemental proposed AD. We received no comments on the supplemental proposed AD, or on the determination of the cost to the public.

Conclusion

We have carefully reviewed the available data and determined that air safety and the public interest require adopting the AD as proposed. Costs of Compliance

We estimate that this AD will affect 128 propellers installed on airplanes of U.S. registry. We also estimate that it will take about 41.5 work-hours per propeller to perform the actions, and that the average labor rate is $85 per work-hour. Based on these figures, we estimate the total cost of the AD to U.S. operators to be $451,520. 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 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

■ Accordingly, under the authority delegated to me by the Administrator, the Federal Aviation Administration amends 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: 2010–14–20 McCauley Propeller Systems: Amendment 39–16365. Docket No. FAA–2007–29176; Directorate Identifier 2007–NE–38–AD.

Effective Date

(a) This airworthiness directive (AD) becomes effective August 17, 2010.

Affected ADs

(b) None.
Applicability

(c) This AD applies to McCauley Propeller Systems model 4HFR34C653/L106FA propellers.

Unsafe Condition

(d) This AD results from reports of 10 hubs found cracked during propeller overhaul. We are issuing this AD to prevent failure of the propeller hub, which could cause blade separation, damage to the airplane, 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.

(f) For propeller hubs with 6,000 or more operating hours time-since-new (TSN) on the effective date of this AD, perform the procedures in paragraphs (h) through (k) of this AD within 100 operating hours time-inservice after the effective date of this AD.

(g) For propeller hubs with fewer than 6,000 operating hours TSN on the effective date of this AD, perform the procedures in paragraphs (h) through (k) of this AD before the propeller hub reaches 6,100 operating hours TSN.
Onetime Propeller Hub Inspection

(h) Remove and disassemble the propeller, and etch the propeller hub, using paragraphs 1.A. through 2.D. of the Accomplishment Instructions of McCauley Propeller Systems Alert Service Bulletin No. ASB254, dated August 20, 2007.

(i) Perform a onetime fluorescent penetrant inspection (FPI) of the propeller hub, using paragraphs 3.A through 3.G. of the Accomplishment Instructions of McCauley Propeller Systems Alert Service Bulletin No. ASB254, dated August 20, 2007.

(j) For hubs that pass the FPI, perform a onetime eddy current inspection of the propeller hub, using paragraphs 4.A. through 4.F. of the Accomplishment Instructions of McCauley Propeller Systems Alert Service Bulletin No. ASB254, dated August 20, 2007.

(k) Remove cracked hubs from service and any other propeller parts found cracked.

Previous Credit

(l) If you performed the onetime inspection of the propeller hub using McCauley Propeller Systems Service Bulletin No. SB238A, or Alert Service Bulletin ASB254, both dated August 20, 2007, before the effective date of this AD, you have satisfied the inspection requirements of this AD.

Interim Action

(m) These actions are interim actions and we may take further rulemaking actions in the future.
Alternative Methods of Compliance

(n) 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

(o) Under 14 CFR part 39.23, we are limiting the special flight permits for this AD as follows:

(1) The propeller must have no signs of external oil leakage from the hub; and

(2) The propeller has no current reports of abnormal operation or vibration.

Related Information

(p) Contact Jeff Janusz, Aerospace Engineer, Wichita Aircraft Certification Office, FAA, Small Airplane Directorate,1801 Airport Road, Wichita, KS 67209; email: jeff.janusz@faa.gov; telephone (316) 946–4148; fax: (316) 946–4107, for more information about this AD.
Material Incorporated by Reference

(q) You must use McCauley Propeller Systems, Service Bulletin No. ASB254, dated August 20, 2007, to perform the inspections required by this AD. The Director of the Federal Register approved the incorporation by reference of this service bulletin in


### 39803 Federal Register / Vol. 75, No. 133 / Tuesday, July 13, 2010 / Rules and Regulations

accordance with 5 U.S.C. 552(a) and 1 CFR part 51. Contact McCauley Propeller Systems, P.O. Box 7704, Wichita, KS 67277–7704; telephone (800) 621–7767, 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 July 1, 2010. Francis A. Favara, Manager, Engine and Propeller Directorate, Aircraft Certification Service.
[FR Doc. 2010–16615 Filed 7–12–10; 8:45 am]

**BILLING CODE 4910–13–P**

**DEPARTMENT OF TRANSPORTATION**

**Federal Aviation Administration**

**14 CFR Part 39**

**[Docket No. FAA–2010–0308; Directorate Identifier 2010–NE–17–AD; Amendment 39–**  **16366; AD 2010–14–21]**

**RIN 2120–AA64**

**Airworthiness Directives; Thielert Aircraft Engines GmbH Model TAE**  **125–01 Reciprocating Engines**

**AGENCY :**  Federal Aviation Administration (FAA), DOT.

**ACTION :**  Final rule.

**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 an aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as:

Service has shown that the small outlet of the blow-by oil separators, part number 02– 7250–18100R1; 02–7250–18100R2; 02–7250– 18100R3; 02–7250–18100R4; 02–7250– 18300R1; 02–7250–18300R2; 02–7250– 18300R3; 02–7250–18300R4; or 02–7250– 18300R5, may cause a blow-by gas pressure increase inside the crankcase of the engine in excess of the oil seal design pressure limits. Leaking engine oil may adversely affect the gearbox clutch or the engine lubrication system. This condition, if not corrected, could lead to in-flight cases of engine power loss or ultimately, shutdown. We are issuing this AD to prevent loss of engine power or uncommanded engine shutdown during flight due to excessive crankcase blow-by gas
pressure. **DATES :**  This AD becomes effective August 17, 2010. The Director of the Federal Register approved the incorporation by reference of certain publications listed in this AD as of August 17, 2010.

**ADDRESSES :**  The Docket Operations office is located at Docket Management Facility, U.S. Department of Transportation, 1200 New Jersey Avenue SE., West Building Ground Floor, Room W12–140, Washington, DC
20590–0001.

**FOR FURTHER INFORMATION CONTACT :**  Tara Chaidez, Aerospace Engineer, Engine Certification Office, FAA, Engine and Propeller Directorate, 12 New England Executive Park, Burlington, MA 01803; e-mail: tara.chaidez@faa.gov; telephone (781) 238–7773; fax (781) 238–7199.

**SUPPLEMENTARY INFORMATION :** 

Discussion

We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 to include an AD that would apply to the specified products. That NPRM was published in the Federal Register on April 5, 2010 (75 FR 17084). That NPRM proposed to correct an unsafe condition for the specified products. The MCAI states that:

Service has shown that the small outlet of the blow-by separators, part number 02– 7250–18100R1; 02–7250–18100R2; 02–7250– 18100R3; 02–7250–18100R4; 02–7250– 18300R1; 02–7250–18300R2; 02–7250– 18300R3; 02–7250–18300R4; or 02–7250– 18300R5, may cause a blow-by gas pressure increase inside the crankcase of the engine in excess of the oil seal design pressure limits. Leaking engine oil may adversely affect the gearbox clutch or the engine lubrication system. This condition, if not corrected, could lead to in-flight cases of engine power loss or ultimately, shutdown.

Comments

We gave the public the opportunity to participate in developing this AD. We received no comments on the NPRM or on the determination of the cost to the public.

Conclusion

We reviewed the available data and determined that air safety and the public interest require adopting the AD as proposed. Costs of Compliance

Based on the service information, we estimate that this AD will affect about 250 Thielert Aircraft Engines GmbH model TAE 125–01 engines installed on airplanes of U.S. registry. We alsoestimate that it will take about 1.5 workhours per engine to comply with this AD. The average labor rate is $85 per work-hour. Required parts will cost about $1,500 per engine. Based on these figures, we estimate the cost of the AD on U.S. operators to be $406,875. 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 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 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 regulatory evaluation of the estimated costs to comply with this AD and placed it in the AD docket. 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 (phone (800) 647–5527) is provided in the

**ADDRESSES** section. Comments will be