### 16917 Federal Register / Vol. 77, No. 57 / Friday, March 23, 2012 / Rules and Regulations

Required parts will cost about $37,200 per engine. Based on these figures, we estimate the total cost of the AD to U.S. operators to be $1,110,144.
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

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),

(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.
Adoption of the Amendment

Accordingly, under the authority delegated to me by the Administrator, the FAA 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 (AD):
2012–06–14 Pratt & Whitney: Amendment 39–16995; Docket No. FAA–2011–1176; Directorate Identifier 2011–NE–35–AD.
(a) Effective Date

This AD is effective April 27, 2012.
(b) Affected ADs

None. (c) Applicability

This AD applies to Pratt & Whitney JT9D– 7R4G2 and –7R4H1 turbofan engines.
(d) Unsafe Condition

This AD was prompted by the determination that a new lower life limit of9,000 cycles-since-new (CSN) for highpressure turbine (HPT) 1st stage air seals, part number (P/N) 735907, is necessary. Weare issuing this AD to prevent critical lifelimited rotating engine part failure, and damage to the airplane.
(e) Compliance

Comply with this AD within the compliance times specified, unless already done.
(f) Removal of HPT 1st Stage Air Seals, P/N 735907

Remove HPT 1st stage air seals, P/N 735907, from service as follows:

(1) For air seals that have fewer than 6,500 CSN on the effective date of this AD, remove the air seals from service before exceeding 9,000 CSN.

(2) For air seals that have 6,500 CSN or more on the effective date of this AD, do the following:

(i) If the engine has a shop visit before the air seal exceeds 9,000 CSN, remove the air seal from service before exceeding 9,000 CSN.

(ii) If the engine does not have a shop visit before the air seal exceeds 9,000 CSN, remove the air seal from service at the next shop visit, not to exceed 2,500 cycles from the effective date of this AD or 15,000 CSN, whichever occurs first.
(g) Installation Prohibition

(1) After the effective date of this AD, do not install or reinstall into any engine any HPT 1st stage air seal, P/N 735907, removed from service in accordance with paragraph (f) of this AD.

(2) After the effective date of this AD, do not install or reinstall into any JT9D–7R4G2 or JT9D–7R4H1 engine any HPT 1st stage air seal, P/N 735907, that exceeds the new life limit of 9,000 CSN. (h) Engine Shop Visit Definition For the purposes of this AD, an engine shop visit is the induction of an engine into the shop after the effective date of this AD, where the separation of a major engine flange occurs, except that the following maintenance actions, or any combination thereof, are not considered engine shop visits:

(1) Introduction of an engine into a shop solely for removal of the compressor top or bottom case for airfoil maintenance or variable stator vane bushing replacement.

(2) Introduction of an engine into a shop solely for removal or replacement of the stage 1 fan disk.

(3) Introduction of an engine into a shop solely for replacement of the turbine rear frame.

(4) Introduction of an engine into a shop solely for replacement of the accessory gearbox or transfer gearbox, or both.

(5) Introduction of an engine into a shop solely for replacement of the fan containment

case. (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

For more information about this AD, contact Ian Dargin, Aerospace Engineer, Engine & Propeller Directorate, FAA, 12 New England Executive Park, Burlington, MA 01803; phone: 781–238–7178; fax: 781–238– 7199; email: ian.dargin@faa.gov.
(k) Material Incorporated by Reference

None.

Issued in Burlington, Massachusetts, on March 16, 2012. Peter A. White, Manager, Engine & Propeller Directorate, Aircraft Certification Service.
[FR Doc. 2012–6952 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–2012–0288; Directorate Identifier 2012–NE–10–AD; Amendment 39–**  **16998; AD 2012–06–17]**

**RIN 2120–AA64**

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

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

**ACTION :**  Final rule; request for
comments.

**SUMMARY :**  We are adopting a new airworthiness directive (AD) for certain


### 16918 Federal Register / Vol. 77, No. 57 / Friday, March 23, 2012 / Rules and Regulations

Rolls-Royce Deutschland (RRD) Models Tay 611–8 and Tay 611–8C turbofan engines. This AD requires replacement of the high-pressure (HP) turbine spanner retaining nut. This AD was prompted by the discovery that certain HP turbine spanner retaining nuts were improperly heat treated after application of silver plating. We are issuing this AD to prevent failure of the HP turbine stage 2 disc, uncontained engine failure, and damage to the airplane.

**DATES :**  This AD becomes effective March 23, 2012.

We must receive comments on this 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 and follow the instructions for sending your comments electronically.

• Mail: 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 service information identified in this AD, contact Rolls-Royce Deutschland Ltd & Co KG, Eschenweg11, Dahlewitz, 15827 BlankenfeldeMahlow, Germany; phone: 49 0 33– 7086–1883; fax: 49 0 33–7086–3276. You may review copies of the referenced service information at the FAA, Engine & Propeller Directorate, 12 New England Executive Park, Burlington, MA 01803. 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 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 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; email: mark.riley@faa.gov; phone: 781– 238–7758; fax: 781–238–7199. **SUPPLEMENTARY INFORMATION :** 

Discussion

The European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Community, has issued EASA Emergency Airworthiness Directive 2012–0039–E, dated March 9, 2012, and EASA AD 2012–0039R1, dated March 14, 2012 (referred to after this as ‘‘the MCAI’’), to correct an unsafe condition for the specified products. The MCAI
states:

A recent quality investigation by RollsRoyce Deutschland has identified that certain stage 2 high-pressure turbine (HPT) disc spanner retaining nuts did not receive the proper heat treatment after application of silver plating. This condition, if not corrected, could result in a stage 2 HPT disc failure, possibly leading to release of high energy debris, resulting in damage to the aeroplane and/or injury to occupants. We are issuing this AD to prevent failure of the HP turbine stage 2 disc, uncontained engine failure, and damage to the airplane.

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

Relevant Service Information

RRD has issued Alert Service Bulletin No. TAY–72–A1769, dated March 9, 2012. The actions described in this service information are intended to correct the unsafe condition identified in the MCAI. FAA’s Determination and Requirements of This AD

This product has been approved by EASA and is approved for operation in the United States. Pursuant to our bilateral agreement with EASA, they have notified us of the unsafe condition described in the MCAI and service information referenced above. We are issuing this AD because we evaluated all information provided by EASA and determined the unsafe condition exists and is likely to exist or develop on other products of the same type design. This AD requires replacement of the HP turbine spanner retaining nut on certain serial number engines, within 20 flight cycles after the effective date of the AD or within 200 flight cycles since the last engine shop visit, whichever occurs first.

FAA’s Determination of the Effective Date

An unsafe condition exists that requires the immediate adoption of this AD. The FAA has found that the risk to the flying public justifies waiving notice and comment prior to adoption of this rule because of the short compliance time required to remove the unsafe condition. Therefore, we determined that notice and opportunity for public comment before issuing this AD are impracticable and that good cause exists for making this amendment effective in fewer than 30 days.

Comments Invited

This AD is a final rule that involves requirements affecting flight safety, and we did not precede it by notice and opportunity for public comment. We invite you to send any written relevant data, views, or arguments about this AD. Send your comments to an address listed under the **ADDRESSES** section. Include ‘‘Docket No. FAA–2012–0288; Directorate Identifier 2012–NE–10–AD’’ at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of this AD. We will consider all comments received by the closing date and may amend this 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 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). 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


### 16919 Federal Register / Vol. 77, No. 57 / Friday, March 23, 2012 / Rules and Regulations

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. 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 FAA 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 (AD): 2012–06–17 Rolls-Royce Deutschland Ltd & Co KG (Formerly Rolls-Royce plc, Derby, England): Amendment 39–16998; Docket No. FAA–2012–0288; Directorate Identifier 2012–NE–10–AD.
(a) Effective Date

This AD becomes effective March 23, 2012.
(b) Affected ADs

None. (c) Applicability

This AD applies to the following RollsRoyce Deutschland Ltd & Co KG (RRD) turbofan engines:

(1) TAY 611–8 engines, serial numbers (S/Ns) 16870, 16879, 16880, 16897, 18046, 18051, 18052, 18053, 18058, 18065, 18066, 18169, and 18194. (2) TAY 611–8C engine S/N 85313.

(d) Reason

This AD was prompted by the discovery that certain high-pressure (HP) turbine spanner retaining nuts were improperly heat treated after application of silver plating. We are issuing this AD to prevent failure of the HP turbine stage 2 disc, uncontained engine failure, and damage to the airplane.
(e) Actions and Compliance

Unless already done, do the following
actions.

(1) Within 20 flight cycles after the effective date of the AD or within 200 flight cycles since the last engine shop visit, whichever occurs first, remove the HP turbine spanner retaining nut from the combustion and HP turbine module, and install a new HP turbine spanner retaining

nut.

(2) Do not reinstall HP turbine spanner retaining nuts removed as specified in paragraph (e)(1) of this AD, into any engine.
(f) 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.
(g) Related Information

(1) For more information about this AD, contact Mark Riley, Aerospace Engineer, Engine Certification Office, FAA, Engine & Propeller Directorate, 12 New England Executive Park, Burlington, MA 01803; email: mark.riley@faa.gov; phone: 781–238– 7758; fax: 781–238–7199.

(2) Refer to MCAI European Aviation Safety Agency Emergency AD 2012–0039–E, dated March 9, 2012; AD 2012–0039R1, dated March 14, 2012; and RRD Alert Service Bulletin No. TAY–72–A1769, dated March 9, 2012, for related information.

(3) For service information identified in this AD, contact Rolls-Royce Deutschland Ltd & Co KG, Eschenweg 11, Dahlewitz, 15827 Blankenfelde-Mahlow, Germany; phone: 49 0 33–7086–1883; fax: 49 0 33–7086–3276. 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 19, 2012. Peter A. White, Manager, Engine & Propeller Directorate, Aircraft Certification Service.
[FR Doc. 2012–6995 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–2011–1090; Directorate Identifier 2011–NM–138–AD; Amendment**  **39–16986; AD 2012–06–05]**

**RIN 2120–AA64**

**Airworthiness Directives; Bombardier, Inc. Airplanes** 

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

**ACTION :**  Final rule.

**SUMMARY :**  We are adopting a new airworthiness directive (AD) for certain Bombardier, Inc. Model DHC–8–400 series airplanes. This AD was prompted by a report of the inability to open the airstair door while on the ground, because the airstair door seal did not deflate, which prevented the airstair door from opening. This AD requires changing the wiring that controls the pneumatic shut-off valve. We are issuing this AD to prevent the airstair door seal from not deflating, which could result in the airstair door not opening and could impede evacuation in the event of an emergency.

**DATES :**  This AD becomes effective April 27, 2012.

The Director of the Federal Register approved the incorporation by reference of a certain publication listed in this AD as of April 27, 2012.

**ADDRESSES :**  You may examine the AD docket on the Internet at http:// www.regulations.gov or in person at the U.S. Department of Transportation, Docket Operations, M–30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE., Washington, DC.

**FOR FURTHER INFORMATION CONTACT :**  Cesar Gomez, Aerospace Engineer, Airframe and Mechanical Systems Branch, ANE–171, FAA, New York Aircraft Certification Office, 1600 Stewart Avenue, Suite 410, Westbury, New York 11590; telephone (516) 228– 7318; fax (516) 794–5531.

**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 October 19, 2011 (76 FR 64847). That NPRM proposed to correct an unsafe condition for the specified products. The MCAI states: