## 16968 Federal Register / Vol. 77, No. 57 / Friday, March 23, 2012 / Proposed Rules

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 proposed AD would not have federalism implications under Executive Order 13132. This proposed AD would 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 proposed 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),

(3) Will not affect intrastate aviation in Alaska, and

(4) 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. List of Subjects in 14 CFR Part 39

Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. The Proposed Amendment

Accordingly, under the authority delegated to me by the Administrator, the FAA proposes to amend 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 (AD):
Pratt & Whitney Division: Docket No. FAA– 2012–0079; Directorate Identifier 2012– NE–06–AD.
(a) Comments Due Date

We must receive comments by May 22,
2012.
(b) Affected ADs

None. (c) Applicability

This AD applies to the following Pratt & Whitney Division turbofan engines:

(1) PW4052, PW4152, and PW4056 turbofan engines, including models with anydash number suffix, with the following highpressure turbine (HPT) stage 1 front hub part numbers (P/Ns) installed:

(i) P/N 51L201, or P/N 51L201–001, or P/N 51L601, or P/N 52L401; or

(ii) P/N 51L901 with a serial number (S/N) not listed in Table 9 of the Accomplishment Instructions of Pratt & Whitney Service Bulletin (SB) No. PW4ENG 72–795, Revision 2, dated April 5, 2011.

(2) PW4156A, PW4060, PW4060A, PW4060C, PW4062, PW4062A, PW4158, PW4460, and PW4462 turbofan engines, including models with any dash number suffix, with the following HPT stage 1 front hub P/Ns installed:

(i) P/N 51L201, or P/N 51L201–001, or P/N 52L401; or

(ii) P/N 51L901 with an S/N not listed in Table 9 of the Accomplishment Instructions of Pratt & Whitney SB No. PW4ENG 72–795, Revision 2, dated April 5, 2011.

(3) PW4164, PW4164C, PW4164C/B, PW4168, and PW4168A turbofan engines with an HPT stage 1 front hub P/N 51L901 installed with a S/N not listed in Table 27A of the Accomplishment Instructions of Pratt & Whitney SB No. PW4G–100–72–220, Revision 4, dated September 30, 2011.
(d) Unsafe Condition

This AD was prompted by Pratt & Whitney’s updated low-cycle-fatigue analysis that indicated certain HPT stage 1 front hubs could initiate a crack prior to the published life limit. This AD requires removing the affected HPT stage 1 front hubs from service using a drawdown plan. We are issuing this AD to prevent failure of the HPT stage 1 front hub, which could lead to an uncontained engine failure and damage to the airplane.
(e) Compliance

Comply with this AD within the compliance times specified, unless already done.
(f) Removal of HPT Stage 1 Front Hubs From Service

(1) For HPT stage 1 front hubs listed in paragraph (c)(1)(i) and (c)(1)(ii) of this AD, do the following:

(i) If the HPT stage 1 front hub has accumulated 17,000 or fewer cycles-since new (CSN) on the effective date of this AD, remove the HPT stage 1 front hub from service before accumulating 18,000 CSN.

(ii) If the HPT stage 1 front hub has accumulated more than 17,000 CSN on the effective date of this AD, remove the HPT stage 1 front hub from service beforeaccumulating an additional 1,000 cycles-inservice (CIS), or at the next piece-part exposure after the effective date of this AD, whichever occurs first.

(2) For HPT stage 1 front hubs listed in paragraphs (c)(2)(i), (c)(2)(ii), and (c)(3) of this AD, do the following:

(i) If the HPT stage 1 front hub has accumulated 12,700 or fewer CSN on the effective date of this AD, remove the HPT stage 1 front hub from service before accumulating 13,700 CSN.

(ii) If the HPT stage 1 front hub has accumulated more than 12,700 CSN on the effective date of this AD, remove the HPT stage 1 front hub from service before accumulating an additional 1,000 CIS, or at the next piece-part exposure after the effective date of this AD, whichever occurs first.
(g) Installation Prohibition

After the effective date of this AD, do not install or reinstall into any engine any HPT stage 1 front hubs listed in paragraph (c)(1)(i) and (c)(1)(ii) of this AD that are at piece-part exposure and exceed 18,000 CSN, or any HPT stage 1 front hubs listed in (c)(2)(i), (c)(2)(ii), and (c)(3) of this AD that are at piece-part exposure and exceed 13,700 CSN.
(h) Definition

For the purpose of this AD, piece-part exposure means that the part is completely disassembled and removed from the engine.
(i) Alternative Methods of Compliance (AMOCs)

The Manager, Engine Certification Office, may approve AMOCs for this AD. Use the procedures found in 14 CFR 39.19 to make your request. (j) Related Information

(1) For more information about this AD, contact James Gray, Aerospace Engineer, Engine Certification Office, FAA, 12 New England Executive Park, Burlington, MA; phone: 781–238–7742; fax: 781–238–7199; email: james.e.gray@faa.gov.

(2) For service information identified in this AD, contact Pratt & Whitney, 400 Main St., East Hartford, CT 06108; phone: 860– 565–7700; fax: 860–565–1605.

(3) You may review copies of the referenced service information at the FAA, Engine & Propeller Directorate, 12 New England Executive Park, Burlington, MA. For information on the availability of this material at the FAA, call 781–238–7125.

Issued in Burlington, Massachusetts, on March 14, 2012. Peter A. White, Manager, Engine & Propeller Directorate, Aircraft Certification Service.

[FR Doc. 2012–6965 Filed 3–22–12; 8:45 am]

**BILLING CODE 4910–13–P**



### DEPARTMENT OF TRANSPORTATION

**Federal Aviation Administration**

**14 CFR Part 39**

**[Docket No. FAA–2012–0324; Directorate Identifier 2012–CE–008–AD]** 

**RIN 2120–AA64**



### Airworthiness Directives; Burkhart **GROB Luft- und Raumfahrt GmbH Powered Sailplanes** 

**AGENCY**

### : Federal Aviation Administration (FAA), Department of Transportation (DOT).

**ACTION** 

### : Notice of proposed rulemaking (NPRM).

**SUMMARY**

### : We propose to adopt a new airworthiness directive (AD) for


## 16969 Federal Register / Vol. 77, No. 57 / Friday, March 23, 2012 / Proposed Rules

Burkhart GROB Luft- und Raumfahrt GmbH Models GROB G 109 and GROB G 109B powered sailplanes. This proposed AD results from mandatory continuing airworthiness information (MCAI) originated 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 excessive corrosion on the nose plate in the vertical stabilizer, which could cause the vertical stabilizer nose plate to fail. We are issuing this proposed AD to require actions to address the unsafe condition on these products.

**DATES** 

### : We must receive comments on this proposed AD by May 7, 2012.

**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.

For service information identified in this proposed AD, contact Grob Aircraft AG, Lettenbachstrasse 9, D–86874 Tussenhausen-Mattsies, Germany; telephone: +49 (0) 8268 998139; fax: +49 (0) 8268 998200; email: productsupport@grob-aircraft.com; Internet: http://www.grobaircraft.de.61.html. You may review copies of the referenced service information at the FAA, Small Airplane Directorate, 901 Locust, Kansas City, Missouri 64106. For information on the availability of this material at the FAA, call (816) 329–4148. 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 proposed 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**

### : Jim Rutherford, Aerospace Engineer, FAA, Small Airplane Directorate, 901 Locust, Room 301, Kansas City, Missouri 64106; telephone: (816) 329–4165; fax: (816) 329–4090; email: jim.rutherford@faa.gov.

**SUPPLEMENTARY INFORMATION** 

### :
Comments Invited

We invite you to send any written relevant data, views, or arguments about this proposed AD. Send your comments to an address listed under the

**ADDRESSES** 

### section. Include ‘‘Docket No. FAA–2012–0324; Directorate Identifier 2012–CE–008–AD’’ at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of this proposed AD. We will consider all comments received by the closing date and may amend this proposed AD because of those comments. We will post all comments we receive, without change, to http:// regulations.gov, including any personal information you provide. We will also post a report summarizing each substantive verbal contact we receive about this proposed AD.

Discussion

The European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Community, has issued AD No. 2012– 0027, dated February 14, 2012 (referred to after this as ‘‘the MCAI’’), to correct an unsafe condition for the specified products. The MCAI states:

Occurrences have been reported of finding heavily corroded nose plates, part number (P/ N) 109–2160.01, in the vertical stabiliser of some Grob G 109 powered sailplanes.

The investigation results concluded that the affected aeroplanes were based and operated near the seaside and therefore exposed to a salty environment, causing the excessive corrosion.

This condition, if not detected and corrected, could lead to failure of the vertical stabilizer nose plate, which functions as a horizontal stabiliser fitting, to support limit loads and consequent loss of control of the aeroplane.

For the reasons described above, this AD requires repetitive inspections and, depending on findings, replacement of the nose plate. 

### You may obtain further information by examining the MCAI in the AD docket.

Relevant Service Information

Grob Aircraft has issued Service Bulletin No. MSB817–58 and Service Bulletin No. MSB 817–060, both dated November 24, 2011, Repair Instruction Doc. No. RI 817–009, issue date November 17, 2011, and Repair Instruction Doc. No. RI 817–010/1, issue date December 20, 2011. 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 Proposed 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 referenced above. We are proposing this AD because we evaluated all information and determined the unsafe condition exists and is likely to exist or develop on other products of the same type design. Costs of Compliance

We estimate that this proposed AD will affect 59 products of U.S. registry. We also estimate that it would take about 6 work-hours per product to comply with the basic requirements of this proposed AD. The average labor rate is $85 per work-hour. Required parts would cost about $424 per product.

Based on these figures, we estimate the cost of the proposed AD on U.S. operators to be $55,106, or $934 per product.

In addition, we estimate that any necessary follow-on actions would take about 12 work-hours and require parts costing $243, for a cost of $1,263 per product. We have no way of determining the number of products that may need these actions. 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.


## 16970 Federal Register / Vol. 77, No. 57 / Friday, March 23, 2012 / Proposed Rules

Regulatory Findings

We determined that this proposed AD would not have federalism implications under Executive Order 13132. This proposed AD would 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 proposed 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),

(3) Will not affect intrastate aviation in Alaska, and

(4) 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. List of Subjects in 14 CFR Part 39

Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. The Proposed Amendment

Accordingly, under the authority delegated to me by the Administrator, the FAA proposes to amend 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 AD:

Burkhart GROB Luft- und Raumfahrt GmbH: Docket No. FAA–2012–0324; Directorate Identifier 2012–CE–008–AD.
(a) Comments Due Date

We must receive comments by May 7,
2012.
(b) Affected ADs

None. (c) Applicability

This AD applies to Burkhart GROB Luftund Raumfahrt GmbH Models GROB G 109 and GROB G 109B powered sailplanes, all serial numbers, certificated in any category.
(d) Subject

Air Transport Association of America (ATA) Code 55: Stabilizer.

(e) Reason

This AD results from mandatory continuing airworthiness information (MCAI) originated 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 excessive corrosion on the nose plate in the vertical stabilizer. We are issuing this AD to detect and correct corrosion and flaking on the nose plate, which could cause the vertical stabilizer nose plate to fail and result in loss of control of the sailplane.
(f) Actions and Compliance

Unless already done, do the following actions:

(1) Within 3 months after the effective date of this AD:

(i) Inspect, from the top, the front and rear side of the nose plate, part number (P/N) 109–2160.01, in the vertical stabilizer for corrosion and flaking following Part A of the Accomplishment Instructions in Grob Aircraft Service Bulletin No. MSB817–58, dated November 24, 2011. Repetitively thereafter inspect at intervals not to exceed 12 months.

(ii) Install an access panel on the left side of the vertical stabilizer following Grob Aircraft Repair Instruction Doc. No. RI 817– 010/1, issue date December 20, 2011, as specified in Grob Aircraft Service Bulletin No. MSB 817–060, dated November 24, 2011.

(iii) Through the access panel installed as required in paragraph (f)(1)(ii) of this AD, inspect, from below, the nose plate, P/N 109– 2160.01, for corrosion and flaking following Part B of the Accomplishment Instructions in Grob Aircraft Service Bulletin No. MSB817– 58, dated November 24, 2011. Repetitively thereafter inspect at intervals not to exceed 12 months.

(2) If any corrosion or flaking is found on the nose plate, P/N 109–2160.01, during any inspection required in paragraphs (f)(1)(i) or (f)(1)(iii) of this AD, replace P/N 109–2160.01 with a serviceable part. Do the replacement following Grob Aircraft Repair Instruction Doc. No. RI 817–009, issue date November 17, 2011, as specified in Grob Aircraft Service Bulletin No. MSB817–58, dated November 24, 2011. After replacement, continue with the repetitive inspections required in paragraphs (f)(1)(i) and (f)(1)(iii) of this AD.
(g) Other FAA AD Provisions

The following provisions also apply to this AD:

(1) Alternative Methods of Compliance (AMOCs): The Manager, Standards Office, FAA, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. Send information to ATTN: Jim Rutherford, Aerospace Engineer, FAA, Small Airplane Directorate, 901 Locust, Room 301, Kansas City, Missouri 64106; telephone: (816) 329–4165; fax: (816) 329– 4090; email: jim.rutherford@faa.gov. Before using any approved AMOC on any sailplane to which the AMOC applies, notify your appropriate principal inspector (PI) in the FAA Flight Standards District Office (FSDO), or lacking a PI, your local FSDO.

(2) Airworthy Product: For any requirement in this AD to obtain corrective actions from a manufacturer or other source, use these actions if they are FAA-approved. Corrective actions are considered FAA-approved if they are approved by the State of Design Authority (or their delegated agent). You are required to assure the product is airworthy before it is returned to service.

(3) Reporting Requirements: For any reporting requirement in this AD, a federal agency may not conduct or sponsor, and a person is not required to respond to, nor shall a person be subject to a penalty for failure to comply with a collection of information subject to the requirements of the Paperwork Reduction Act unless that collection of information displays a current valid OMB Control Number. The OMB Control Number for this information collection is 2120–0056. Public reporting for this collection of information is estimated to be approximately 5 minutes per response, including the time for reviewing instructions, completing and reviewing the collection of information. All responses to this collection of information are mandatory. Comments concerning the accuracy of this burden and suggestions for reducing the burden should be directed to the FAA at: 800 Independence Ave. SW., Washington, DC 20591, Attn: Information Collection Clearance Officer,
AES–200.

(h) Related Information

Refer to MCAI European Aviation Safety Agency (EAS) AD No. 2012–0027, dated February 14, 2012; Grob Aircraft Service Bulletin No. MSB817–58 and Grob Aircraft Service Bulletin No. MSB 817–060, both dated November 24, 2011; Grob Aircraft Repair Instruction Doc. No. RI 817–009, issue date November 17, 2011; and Grob Aircraft Repair Instruction Doc. No. RI 817–010/1, issue date December 20, 2011 for related information. For service information related to this AD, contact Grob Aircraft AG,Lettenbachstrasse 9, D–86874 TussenhausenMattsies, Germany; telephone: +49 (0) 8268 998139; fax: +49 (0) 8268 998200; email: productsupport@grob-aircraft.com; Internet: http://www.grob-aircraft.de.61.html. You may review copies of the referenced service information at the FAA, Small Airplane Directorate, 901 Locust, Kansas City, Missouri 64106. For information on the availability of this material at the FAA, call (816) 329–4148.

Issued in Kansas City, Missouri, on March
19, 2012. Earl Lawrence, Manager, Small Airplane Directorate, Aircraft Certification Service.
[FR Doc. 2012–7012 Filed 3–22–12; 8:45 am]

**BILLING CODE 4910–13–P**