### 9869 Federal Register / Vol. 77, No. 34 / Tuesday, February 21, 2012 / Proposed Rules

‘‘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, 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): Honeywell International Inc. (formerly AlliedSignal Inc., formerly Garret Turbine Engine Company): Docket No. FAA–2011–1045; Directorate Identifier 2011–NE–32–AD.
(a) Comments Due Date

We must receive comments by April 23,
2012. (b) Affected ADs

None.
(c) Applicability

(1) This AD applies to Honeywell International Inc. model TFE731–5 series engines, with a first stage low-pressure turbine (LPT1) rotor assembly, part number (P/N) 3075184–2, 3075184–3, or 3075184–4, installed.

(2) This AD also applies to Honeywell International Inc. models TFE731–5AR and –5BR series engines, with a first stage LPT1 rotor assembly, P/N 3075447–1, 3075447–2, 3075447–4, 3075713–1, 3075713–2, 3075713–3, or 3074748–5, installed.

(3) This AD also applies to Honeywell International Inc. models TFE731–4, –4R, –5AR, –5BR, and –5R series turbofan engines, with an LPT1 rotor assembly, P/N 3074748– 4, 3074748–5, 3075447–1, 3075447–2, 3075447–4, 3075713–1, 3075713–2, or 3075713–3, installed.

(d) Unsafe Condition

This AD was prompted by a report of a rim/web separation of an LPT1 rotor assembly. We are issuing this AD to prevent uncontained disk separation, leading to fuel tank penetration, fire, personal injury, and damage to the airplane.
(e) Compliance

Comply with this AD within the compliance times specified, unless already done.
(f) Engines Installed in Dassault-Aviation Falcon 20 and Construcciones Aeronauticas, S.A. (CASA) 101 Airplanes

(1) Remove the LPT1 rotor assembly at the next access to the LPT1 rotor assembly or at the next major periodic inspection, not to exceed 2,600 hours-in-service since last major periodic inspection, or 8 years after the effective date of this AD, whichever occurs first.

(2) Install an LPT1 rotor assembly that is eligible for installation.
(g) Engines Not Installed in DassaultAviation Falcon 20 or CASA 101 Airplanes

(1) Remove the LPT1 rotor assembly at the next core zone inspection, not to exceed 5,100 hours-in-service since last core zone inspection, or at the next time the LPT1 rotor disc is removed for cause, or 8 years after the effective date of this AD, whichever occurs first.

(2) Install an LPT1 rotor assembly that is eligible for installation.

(h) Definitions

(1) For the purpose of this AD, ‘‘next access’’ is when the low-pressure tie rod is unstretched.

(2) For the purpose of this AD, an LPT1 rotor assembly ‘‘eligible for installation’’ is an LPT1 rotor assembly not having a P/N listed in this AD.

(i) Installation Prohibition

After the effective date of this AD, if the rotor assembly must be replaced as specified in paragraph (f)(1) or (g)(1) of this AD, do not install any LPT1 rotor assembly listed by P/ N in paragraphs (c)(1), (c)(2), and (c)(3) of this AD, into any engine.
(j) Alternative Methods of Compliance (AMOCs)

The Manager, Los Angeles Aircraft Certification Office, FAA, may approve AMOCs for this AD. Use the procedures in 14 CFR 39.19 to request an AMOC.
(k) Related Information

(1) For more information about this AD, contact Joseph Costa, Aerospace Engineer, Los Angeles Aircraft Certification Office, FAA, Transport Airplane Directorate, 3960 Paramount Blvd., Lakewood, CA 90712– 4137; phone: 562–627–5246; fax: 562–627– 5210: email: joseph.costa@faa.gov.

(2) Honeywell International Inc. Service Bulletin (SB) No. TFE731–72–3768, SB No. TFE731–72–3769, and SB No. TFE731–72– 3770, pertain to the subject of this AD. Contact Honeywell Engines and Systems Technical Publications and Distribution, M/S 2101–201, P.O. Box 52170, Phoenix, AZ 85072–2170, phone: 602–365–2493 (General Aviation), 602–365–5535 (Commercial Aviation), fax: 602–365–5577 (General Aviation and Commercial Aviation), for a copy of this service information.

(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 February 3, 2012. Peter A. White, Manager, Engine & Propeller Directorate, Aircraft Certification Service.
[FR Doc. 2012–3861 Filed 2–17–12; 8:45 am]

**BILLING CODE 4910–13–P**

**DEPARTMENT OF TRANSPORTATION**

**Federal Aviation Administration**

**14 CFR Part 39**

**[Docket No. FAA–2008–0224; Directorate Identifier 2007–NE–44–AD]** 

**RIN 2120–AA64**

**Airworthiness Directives; Rolls-Royce Deutschland Ltd & Co KG (RRD)**  **Turbofan Engines**

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

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

**SUMMARY :**  We propose to rescind an airworthiness directive (AD) for RRD BR700–715A1–30, BR700–715B1–30, and BR700–715C1–30 turbofan engines. The existing AD resulted from the need to reduce the published life limits of high-pressure (HP) turbine stage 1 discs, part numbers (P/Ns) BRH20130 and BRH20131, and HP turbine stage 2 discs, P/Ns BRH19423 and BRH19427.


### 9870 Federal Register / Vol. 77, No. 34 / Tuesday, February 21, 2012 / Proposed Rules

Since we issued the existing AD, RRD has revised the approved published life limits of these parts to the same or higher limits as originally certified.

**DATES :**  We must receive comments on this proposed AD by April 23, 2012.

**ADDRESSES :**  You may send comments by any of the following methods:

• 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. 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 proposed AD, the regulatory evaluation, any comments received, and other information. The street address for the Docket Operations office (phone: 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.

**FOR FURTHER INFORMATION CONTACT :**  Mark Riley, Aerospace Engineer, Engine Certification Office, FAA, Engine & Propeller Directorate, 12 New England Executive Park, Burlington, MA 01803; phone: 781–238–7758; fax: 781–238– 7199; email: mark.riley@faa.gov.

**SUPPLEMENTARY INFORMATION :** 
Comments Invited

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

**ADDRESSES** section. Include ‘‘Docket No. FAA–2008–0224; Directorate Identifier 2007–NE–44–AD’’ at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of this proposed AD rescission. We will consider all comments received by the closing date and may amend this proposed AD rescission based on 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 with FAA personnel concerning this proposed AD rescission. 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).

Discussion

On March 17, 2009, we issued AD 2009–07–01 (74 FR 12086, March 23, 2009). That AD requires reducing the published life limits of BR700–715 turbofan engine HP turbine stage 1 discs, P/Ns BRH20130 and BRH20131, and HP turbine stage 2 discs, P/Ns BRH19423 and BRH19427.

Since we issued AD 2009–07–01 (74 FR 12086, March 23, 2009), RRD has revised the approved published life limits of these HP turbine stage 1 discs to the same or higher limits as originally certified. The European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Community, has issued EASA Airworthiness Directive Cancellation Notice 2007–0152–CN, dated December 22, 2011. EASA stated in that Cancellation Notice that they have approved published life limits for the affected parts that are increased to the same or higher value as originally certified. We have evaluated the information provided by RRD and EASA and have determined that an unsafe condition no longer exists in these HP turbine stage 1 and stage 2 discs. FAA’s Determination and Requirements of This Proposed AD Rescission

We are proposing this AD rescission of AD 2009–07–01 (74 FR 12086, March 23, 2009) because we evaluated all information and determined that allowing the increase in the published part life limits is acceptable. This proposed AD would rescind AD 2009–
07–01. 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 a practice, method, or procedure necessary for safety in air

commerce. Regulatory Findings

We determined that this proposed AD rescission would not have federalism implications under Executive Order 13132. This proposed AD rescission 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 rescission of a 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 regulatory evaluation of the estimated costs to comply with this proposed AD rescission and placed it in the AD docket. List of Subjects in 14 CFR Part 39

Air transportation, Aircraft, Aviation safety, 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 rescinding airworthiness directive (AD) 2009–07–01, Amendment 39–15860 (74 FR 12086, March 23, 2009):
Rolls-Royce Deutschland Ltd & Co KG (formerly BMW Rolls-Royce GmbH, formerly BMW Rolls-Royce Aero Engines): Docket No. FAA–2008–0224; Directorate Identifier 2007–NE–44–AD.


### 9871 Federal Register / Vol. 77, No. 34 / Tuesday, February 21, 2012 / Proposed Rules

(a) Comments Due Date

We must receive comments by April 23,
2012.
(b) Affected ADs

This AD rescinds AD 2009–07–01 (74 FR 12086, March 23, 2009).
(c) Applicability

This AD applies to Rolls-Royce Deutschland Ltd & Co KG BR700–715A1–30, BR700–715B1–30, and BR700–715C1–30 turbofan engines.

Issued in Burlington, Massachusetts, on February 10, 2012. Peter A. White, Manager, Engine & Propeller Directorate, Aircraft Certification Service.
[FR Doc. 2012–3864 Filed 2–17–12; 8:45 am]

**BILLING CODE 4910–13–P**

**DEPARTMENT OF TRANSPORTATION**

**Federal Aviation Administration**

**14 CFR Part 39**

**[Docket No. FAA–2012–0143; Directorate Identifier 2011–NM–077–AD]** 

**RIN 2120–AA64**

**Airworthiness Directives; Fokker Services B.V. Airplanes** 

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

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

**SUMMARY :**  We propose to supersede an existing airworthiness directive (AD) that applies to all Fokker Services B.V. Model F.28 Mark 0070 and 0100 airplanes. The existing AD currently requires revising the airworthiness limitations section (ALS) of the instructions for continued airworthinessfor certain airplanes, and the FAAapproved maintenance program for certain other airplanes, to incorporate new limitations for fuel tank systems. Since we issued that AD, Fokker Services B.V. has revised a Fokker 70/ 100 maintenance review board (MRB) document with revised limitations, tasks, thresholds, and intervals. This proposed AD would revise the maintenance program to incorporate the limitations, tasks, thresholds, and intervals specified in that Fokker MRB document. We are proposing this AD to reduce the potential of ignition sources inside fuel tanks, which, in combination with flammable fuel vapors, could result in fuel tank explosions and consequent loss of the airplane.

**DATES :**  We must receive comments on this proposed AD by April 6, 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, between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays.

For service information identified in this proposed AD, contact Fokker Services B.V., Technical Services Dept., P.O. Box 231, 2150 AE Nieuw-Vennep, the Netherlands; telephone +31 (0)252– 627–350; fax +31 (0)252–627–211; email technicalservices.fokkerservices@ stork.com; Internet http://www.my fokkerfleet.com. You may review copies of the referenced 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. 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 proposed AD, the regulatory evaluation, any comments received, and other information. The street address for the Docket Operations 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 :**  Tom Rodriguez, Aerospace Engineer, International Branch, ANM–116, Transport Airplane Directorate, FAA 1601 Lind Avenue SW., Renton, Washington 98057–3356; telephone (425) 227–1137; fax (425) 227–1149.

**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–2012–0143; Directorate Identifier 2011–NM–077–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 based on 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 July 9, 2004, we issued AD 2004– 15–08, Amendment 39–13742 (69 FR 44586, July 27, 2004). This AD required actions intended to address an unsafe condition on the products listed above.

Since we issued AD 2004–15–08, Amendment 39–13742 (69 FR 44586, July 27, 2004): The European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Community, has issued EASA Airworthiness Directive 2011– 0157, dated August 25, 2011 (referred to after this as ‘‘the MCAI’’), to correct an unsafe condition for the specified products. The MCAI states:

Fokker Services have published issue 8 of report SE–623 dated 17 March 2011, which is part of the Airworthiness Limitations Section of the Instructions for Continued Airworthiness, referred to in Section 06, Appendix 1, of the Fokker 70/100 Maintenance Review Board (MRB) document. The complete Airworthiness Limitations Section currently consists of: —Certification Maintenance Requirements

(CMRs)—report SE–473, issue 8, —Airworthiness Limitation Items (ALIs) and

Safe Life Items (SLIs)—report SE–623, issue 8, —Fuel ALIs and Critical Design

Configuration Control Limitations (CDCCLs)—report SE–672, issue 2. The instructions contained in those reports have been identified as mandatory actions for continued airworthiness.

For the reasons described above, this [EASA] AD retains the requirements of EASA AD 2011–0046, which is superseded, and requires the implementation of the inspections and limitations as specified in the Airworthiness Limitation Section of the Instructions for Continued Airworthiness, referred to in Section 06, Appendix 1 of the Fokker 70/100 MRB document, reports SE–473, SE–623 and SE–672 at the abovementioned issues. You may obtain further information by examining the MCAI in the AD docket.

The FAA has examined the underlying safety issues involved in fuel tank explosions on several large transport airplanes, including the adequacy of existing regulations, the service history of airplanes subject to those regulations, and existing maintenance practices for fuel tank