### 9003 Federal Register / Vol. 78, No. 26 / Thursday, February 7, 2013 / Proposed Rules

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): Hamilton Sundstrand Corporation: Docket No. FAA–2013–0056; Directorate Identifier 2012–NE–48–AD.
(a) Comments Due Date

We must receive comments by March 25,
2013.
(b) Affected ADs

None. (c) Applicability

This AD applies to Hamilton Sundstrand Corporation 14SF–7, 14SF–15, and 14SF–23 series propellers, using Hamilton Sundstrand Corporation auxiliary pumps and motors (auxiliary feathering pumps), part number (P/N) 782655–3 (Aerocontrolex P/N 4122– 006009), with the following serial numbers (S/Ns):

(1) S/Ns 1 through 365, excluding 95, 108, 122, 177, 193, 278, 285, 293, 297, 310, and
362.

(2) S/Ns 366 through 710, excluding 387, 405, 423, 481, 506, 574, 584, 596, 632, and
669.

(3) S/Ns 711 through 1035, excluding 733, 824, 852, and 994.

(4) S/Ns 1036 through 1475, excluding 1038, 1054, 1081, 1086, 1098, and 1177.

(5) S/Ns 1476 through 1615, excluding
1523.

(6) S/Ns 4516 through 4521.
(d) Unsafe Condition

This AD was prompted by a report of a propeller not moving into the feathering position after an engine in-flight shutdown. We are issuing this AD to prevent propellers from failing to move into the feathering position after an engine in-flight shutdown. Propellers failing to feather can cause high drag on the propeller, asymmetric thrust, and difficulty of or impossibility in controlling the airplane. (e) Compliance

Comply with this AD within the compliance times specified, unless already done. (f) Auxiliary Feathering Pump Removal

Remove the affected auxiliary feathering pumps from service at the following:

(1) Not later than April 30, 2013, for the affected S/Ns listed in paragraph (c)(1) of this AD. (2) Not later than October 31, 2013, for the affected S/Ns listed in paragraph (c)(2) of this
AD.

(3) Not later than April 30, 2014, for the affected S/Ns listed in paragraph (c)(3) of this
AD.

(4) Not later than October 31, 2014, for the affected S/Ns listed in paragraph (c)(4) of this
AD.

(5) Not later than April 30, 2015, for the affected S/Ns listed in paragraph (c)(5) of this
AD.

(6) Not later than April 30, 2014, for the affected S/Ns listed in paragraph (c)(6) of this
AD.
(g) Installation Prohibition

After the effective date of this AD, do not install any auxiliary feathering pump listed as affected in paragraph (c) this AD, unless the auxiliary feathering pump has been properly modified. Properly modified auxiliary feathering pumps will have the letter ‘‘M’’ following the pump S/N, as described in Hamilton Sundstrand Corporation Alert Service Bulletin No. 14SF– 61–A165, dated September 25, 2012.
(h) Alternative Methods of Compliance (AMOCs)

The Manager, Boston Aircraft Certification Office, FAA, may approve AMOCs for this AD. Use the procedures found in 14 CFR 39.19 to make your request.

(i) Related Information

(1) For more information about this AD, contact Michael Schwetz, Aerospace Engineer, Boston Aircraft Certification Office, FAA, Engine and Propeller Directorate, 12 New England Executive Park, Burlington, MA 01803; phone: 781–238–7761; fax: 781– 238–7170; email: michael.schwetz@faa.gov.

(2) For service information identified in this AD, contact Hamilton Sundstrand Propeller Technical Team, One Hamilton Road, Mail Stop 1–3–AB43, Windsor Locks, CT 06096–1010; fax: 860–654–5107. You may view this 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 January 29, 2013. Colleen M. D’Alessandro, Assistant Manager, Engine & Propeller Directorate, Aircraft Certification Service.
[FR Doc. 2013–02719 Filed 2–6–13; 8:45 am]

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

**Federal Aviation Administration**

**14 CFR Part 39**

**[Docket No. FAA–2012–1329; Directorate Identifier 2012–NE–46–AD]** 

**RIN 2120–AA64**

**Airworthiness Directives; Engine Alliance Turbofan Engines** 

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

**ACTION :**  Notice of proposed rulemaking (NPRM).

**SUMMARY :**  We propose to adopt a new airworthiness directive (AD) for certain Engine Alliance GP7270 and GP7277 turbofan engines. This proposed AD wasprompted by damage to the highpressure compressor (HPC) stage 7–9 spool caused by failure of the baffle plate feature on affected HPC stage 6 disks. This proposed AD would require initial and repetitive borescope inspections of the baffle plate feature and removal from service of the HPC stage 6 disk before further flight, if the plate is missing material. This proposed AD would also require mandatory removal from service of these HPC stage 6 disks at the next HPC module exposure. We are proposing this AD to prevent uncontained failure of the HPC stage 7–9 spool, uncontained engine failure, and damage to the airplane.

**DATES :**  We must receive comments on this proposed AD by April 8, 2013.

**ADDRESSES :**  You may send comments, using the procedures found in 14 CFR 11.43 and 11.45, 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: Deliver to Mail address above between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays.

For service information identified in this proposed AD, contact Engine Alliance, 411 Silver Lane, East Hartford, CT 06118, phone: 800–565–0140; Web site: https://www.engine allianceportal.com. You may view this 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.


### 9004 Federal Register / Vol. 78, No. 26 / Thursday, February 7, 2013 / Proposed Rules

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 (phone: 800–647–5527) is in the
**ADDRESSES** section. Comments will be available in the AD docket shortly after receipt.

**FOR FURTHER INFORMATION CONTACT :**  Martin Adler, Aerospace Engineer, Engine & Propeller Directorate, FAA, 12 New England Executive Park, Burlington, MA 01803; phone: 781– 238–7157; fax: 781–238–7199; email: martin.adler@faa.gov.

**SUPPLEMENTARY INFORMATION :** 
Comments Invited

We invite you to send any written relevant data, views, or arguments about this proposal. Send your comments to an address listed under the **ADDRESSES** section. Include ‘‘Docket No. FAA– 2012–1329; Directorate Identifier 2012– NE–46–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:// www.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

We received reports of the baffle plate feature failing on HPC stage 6 disks, part number (P/N) 382–100–505–0 from high cycle fatigue. The failures resulted in material from the baffle plate feature causing damage to the HPC stage 7–9 spool, causing the spool to crack. Engine Alliance has introduced a redesigned HPC stage 6 disk with a different P/N, to eliminate the failures. This condition, if not corrected, could result in uncontained failure of the HPC stage 7–9 spool, uncontained engine failure, and damage to the airplane.

FAA’s Determination

We are proposing this AD because we evaluated all the relevant information and determined the unsafe condition described previously is likely to exist or develop in other products of the same type design. Proposed AD Requirements

This proposed AD would require initial and repetitive borescope inspections of the HPC stage 6 disk baffle plate feature and removal from service of any HPC stage 6 disk, P/N 382–100–505–0, before further flight if the feature is missing any material. This proposed AD would also require mandatory removal from service of these HPC stage 6 disks at the next HPC module exposure, but no later than accumulating 6,800 cycles-since-new on the disk. Costs of Compliance

We estimate that this proposed AD would affect no engines installed on airplanes of U.S. registry, and the cost to U.S. operators to be $0. 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 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 to the extent that it justifies making a regulatory distinction, 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): Engine Alliance: Docket No. FAA–2012– 1329; Directorate Identifier 2012–NE– 46–AD.
(a) Comments Due Date

We must receive comments by April 8,
2013.
(b) Affected ADs

None. (c) Applicability

This AD applies to Engine Alliance GP7270 and GP7277 turbofan engines with a high-pressure compressor (HPC) stage 6 disk, part number (P/N) 382–100–505–0, installed.
(d) Unsafe Condition

This AD was prompted by damage to the HPC stage 7–9 spool caused by failure of the baffle plate feature on affected HPC stage 6 disks. We are issuing this AD to prevent uncontained failure of the HPC stage 7–9 spool, uncontained engine failure, and damage to the airplane. (e) Compliance

Comply with this AD within the compliance times specified, unless already done. (f) Borescope Inspections

(1) For HPC stage 6 disks with fewer than 1,000 cycles-since-new (CSN) on the effective date of this AD, initially borescope inspect the baffle plate feature on the disk (360 degrees) before accumulating 1,500 CSN.

(2) For HPC stage 6 disks with 1,000 CSN or more on the effective date of this AD, initially borescope inspect the baffle plate feature on the disk (360 degrees) within the next 500 cycles-in-service (CIS).


### 9005 Federal Register / Vol. 78, No. 26 / Thursday, February 7, 2013 / Proposed Rules

(3) Thereafter, repetitively borescope inspect the baffle plate feature on the disk (360 degrees) within every 500 CIS.

(4) Remove the HPC stage 6 disk before further flight if found cracked or with missing material.
(g) Mandatory Removal From Service of Affected HPC Stage 6 Disks

At next HPC module exposure, but not to exceed 6,800 CSN on the HPC stage 6 disk, remove the HPC stage 6 disk, P/N 382–100– 505–0, from service.

(h) Installation Prohibition

After the effective date of this AD, do not install any HPC stage 6 disk, P/N 382–100– 505–0, into any HPC module.

(i) Definition

For the purpose of this AD, HPC module exposure is defined as separation of the flanges between the compressor case and the combustion diffuser case.
(j) 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.
(k) Related Information

(1) For more information about this AD, contact Martin Adler, Aerospace Engineer, Engine & Propeller Directorate, FAA, 12 New England Executive Park, Burlington, MA 01803; phone: 781–238–7157; fax: 781–238– 7199; email: martin.adler@faa.gov.

(2) Engine Alliance Service Bulletin No. EAGP7–72–236, pertains to the subject of this
AD.

(3) For service information identified in this AD, contact Engine Alliance, 411 Silver Lane, East Hartford, CT 06118, phone: 800– 565–0140; Web site: https:// www.engineallianceportal.com. You may view this 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 January 28, 2013. Robert J. Ganley, Acting Manager, Engine & Propeller Directorate, Aircraft Certification Service.
[FR Doc. 2013–02721 Filed 2–6–13; 8:45 am]

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

**Federal Aviation Administration**

**14 CFR Part 39**

**[Docket No. FAA–2009–0776; Directorate Identifier 2009–NE–32–AD]** 

**RIN 2120–AA64**

**Airworthiness Directives; Dowty Propellers Propellers** 

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

**ACTION :**  Notice of proposed rulemaking (NPRM).

**SUMMARY :**  We propose to revise an existing airworthiness directive (AD) that applies to all Dowty Propellers R408/6–123–F/17 model propellers. The existing AD currently requires initial applications of sealant between the bus bar assembly and the backplate assembly of certain line-replaceable units (LRUs), and repetitive applications of sealant on all R408/6–123–F/17 model propellers. Since we issued that AD, Dowty Propellers has introduced an optional terminating action to the applications of sealant. This proposed AD would add the optional terminating action. We are proposing this AD to prevent an in-flight double generator failure, which could result in reduced controllability of the airplane.

**DATES :**  We must receive comments on this proposed AD by April 8, 2013.

**ADDRESSES :**  You may send comments, using the procedures found in 14 CFR 11.43 and 11.45, 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: Deliver to Mail address above between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays.

For service information identified in this AD, contact Dowty Propellers, Anson Business Park, Cheltenham Road East, Gloucester GL 29QN, UK; phone: 44 (0) 1452 716000; fax: 44 (0) 1452 716001. You may view this 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. 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 (phone: 800–647–5527) is in the
**ADDRESSES** section. Comments will be available in the AD docket shortly after receipt.

**FOR FURTHER INFORMATION CONTACT :**  Michael Schwetz, Aerospace Engineer, Boston Aircraft Certification Office, FAA, Engine and Propeller Directorate, 12 New England Executive Park, Burlington, MA 01803; phone: 781– 238–7761; fax 781–238–7170; e- mail: michael.schwetz@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–2009–0776; Directorate Identifier 2009–NE–32–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:// www.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

On August 5, 2010, we issued AD 2010–17–11, Amendment 39–16403 (75 FR 51656, August 23, 2010), for all Dowty Propellers R408/6–123–F/17 model propellers. That AD requires initial applications of sealant between the bus bar assembly and the backplate assembly of LRUs serial numbers below DAP0347, and repetitive applications of sealant on all R408/6–123–F/17 model propellers. That AD resulted from mandatory continuing airworthiness information issued by an aviation authority of another country to identify and correct an unsafe condition on an aviation product. We issued that AD to prevent an in-flight double generator