Airworthiness Directives; Rolls-Royce Deutschland Ltd & Co KG Turbofan Engines, 2195-2197 [2012-31588]

Download as PDF 2195 Rules and Regulations Federal Register Vol. 78, No. 7 Thursday, January 10, 2013 This section of the FEDERAL REGISTER contains regulatory documents having general applicability and legal effect, most of which are keyed to and codified in the Code of Federal Regulations, which is published under 50 titles pursuant to 44 U.S.C. 1510. The Code of Federal Regulations is sold by the Superintendent of Documents. Prices of new books are listed in the first FEDERAL REGISTER issue of each week. DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2012–1202; Directorate Identifier 2012–NE–38–AD; Amendment 39– 17309; AD 2012–26–14] RIN 2120–AA64 Airworthiness Directives; Rolls-Royce Deutschland Ltd & Co KG Turbofan Engines Federal Aviation Administration (FAA), DOT. ACTION: Final rule; request for comments. AGENCY: We are adopting a new airworthiness directive (AD) for all Rolls-Royce Deutschland Ltd & Co KG BR700–715A1–30, BR700–715B1–30, and BR700–715C1–30 turbofan engines. This AD requires a one-time removal from service of the high-pressure (HP) compressor stages 1 to 6 rotor disc assembly before exceeding certain thresholds. This AD was prompted by a report of silver chloride-induced stress corrosion cracking of the HP compressor stages 1 to 6 rotor disc assembly, identified during overhaul. We are issuing this AD to prevent failure of the HP compressor stages 1 to 6 rotor disc assembly, which could result in uncontained failure of the engine and damage to the airplane. DATES: This AD becomes effective January 10, 2013. We must receive comments on this AD by February 25, 2013. 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 wreier-aviles on DSK5TPTVN1PROD with SUMMARY: VerDate Mar<15>2010 12:02 Jan 09, 2013 Jkt 229001 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, Eschenweg 11, Dahlewitz, 15827 BlankenfeldeMahlow, Germany; telephone: 49 0 33– 7086–1883; fax: 49 0 33–7086–3276. You may view 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: Frederick Zink, Aerospace Engineer, Engine Certification Office, FAA, Engine & Propeller Directorate, 12 New England Executive Park, Burlington, MA 01803; phone: 781–238–7779; fax: 781–238– 7199; email: frederick.zink@faa.gov. 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 Airworthiness Directive 2012–0230, dated October 30, 2012 (referred to hereinafter as ‘‘the MCAI’’), to correct an unsafe condition for the specified products. The MCAI states: Silver chloride-induced stress corrosion cracking was identified during overhaul of a BR700–715 engine, on the High Pressure Compressor (HPC) stages 1 to 6 rotor disc assembly. Subsequent evaluation concluded that the affected part life limitation values PO 00000 Frm 00001 Fmt 4700 Sfmt 4700 declared in the engine Time Limits Manual cannot be supported for high cyclic life HPC discs. This condition, if not corrected, could lead to uncontained HPC disc failure, possibly resulting in damage to, and/or reduced control of the aeroplane. You may obtain further information by examining the MCAI in the AD docket. FAA’s Determination and Requirements of This AD This product has been approved by the aviation authority of Germany, and is approved for operation in the United States. Pursuant to our bilateral agreement with Germany, they have notified us of the unsafe condition described in the MCAI 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 a onetime removal from service of the HP compressor stages 1 to 6 rotor disc assembly before exceeding certain thresholds. 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 times for HP compressor stages 1 to 6 rotor disc assemblies that are at or over the removal thresholds. 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–2012–1202; Directorate Identifier 2012–NE–38–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 E:\FR\FM\10JAR1.SGM 10JAR1 2196 Federal Register / Vol. 78, No. 7 / Thursday, January 10, 2013 / Rules and Regulations 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 wreier-aviles on DSK5TPTVN1PROD with 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. 12:02 Jan 09, 2013 Jkt 229001 15,700 flight CSN on the effective date of this AD, remove the rotor disc assembly from service within 300 flight cycles. List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. (2) BR700–715A1–30, BR700–715B1–30, and BR700–715C1–30 Turbofan Engines (All Flight Missions Except the Hawaiian Flight Mission) 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 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. VerDate Mar<15>2010 We prepared a regulatory evaluation of the estimated costs to comply with this AD and placed it in the AD docket. [Amended] 2. The FAA amends § 39.13 by adding the following new AD: ■ 2012–26–14 Rolls-Royce Deutschland Ltd & Co KG (Formerly Rolls-Royce Deutschland GmbH, formerly BMW Rolls-Royce GmbH): Amendment 39– 17309; Docket No. FAA–2012–1202; Directorate Identifier 2012–NE–38–AD. (a) Effective Date This airworthiness directive (AD) becomes effective January 10, 2013. (b) Affected ADs None. (c) Applicability This AD applies to all Rolls-Royce Deutschland Ltd & Co KG BR700–715A1–30, BR700–715B1–30, and BR700–715C1–30 turbofan engines. (d) Reason This AD was prompted by a report of silver chloride-induced stress corrosion cracking of the high-pressure (HP) compressor stages 1 to 6 rotor disc assembly, identified during overhaul. We are issuing this AD to prevent failure of the HP compressor stages 1 to 6 rotor disc assembly, which could result in uncontained failure of the engine and damage to the airplane. (e) Actions and Compliance Unless already done, do the following actions. (1) BR700–715A1–30 Turbofan Engines Operated Under the Hawaiian Flight Mission Only For BR700–715A1–30 turbofan engines operated under the Hawaiian Flight Mission only, do the following: (1) If the HP compressor stages 1 to 6 rotor disc assembly has accumulated 15,700 flight cycles since new or fewer on the effective date of this AD, remove the rotor disc assembly from service before exceeding 16,000 flight cycles since new (CSN). (2) If the HP compressor stages 1 to 6 rotor disc assembly has accumulated more than PO 00000 Frm 00002 Fmt 4700 Sfmt 4700 For BR700–715A1–30, BR700–715B1–30, and BR700–715C1–30 turbofan engines (all flight missions except the Hawaiian Flight Mission), do the following: (1) If the HP compressor stages 1 to 6 rotor disc assembly has accumulated 13,700 flight CSN or fewer on the effective date of this AD, remove the rotor disc assembly from service before exceeding 14,000 flight CSN. (2) If the HP compressor stages 1 to 6 rotor disc assembly has accumulated more than 13,700 flight cycles since new on the effective date of this AD, remove the rotor disc assembly from service within 300 flight cycles. (f) Terminating Action Performing the one-time removal from service of the stages 1 to 6 rotor disc assembly, as specified in this AD, is terminating action to this AD. (g) Definition For the purpose of this AD, flight cycles is the total flight CSN on the HP compressor stages 1 to 6 rotor disc assembly, without any pro-rated calculations applied for different flight missions. Guidance on calculating total flight cycles can be found in Rolls-Royce Deutschland Ltd & Co KG Notice to Operators BR715 engines NTO: No. 184, dated October 25, 2012. (h) 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. (i) Related Information (1) For more information about this AD, contact Frederick Zink, Aerospace Engineer, Engine Certification Office, FAA, Engine & Propeller Directorate, 12 New England Executive Park, Burlington, MA 01803; phone: 781–238–7779; fax: 781–238–7199; email: frederick.zink@faa.gov. (2) Refer to European Aviation Safety Agency AD 2012–0230, dated October 30, 2012, and Rolls-Royce Deutschland Ltd & Co KG Alert Service Bulletin No. SB–BR700–72– A900401, dated October 25, 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; telephone: 49 0 33–7086–1883; fax: 49 0 33–7086–3276. You may view 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. E:\FR\FM\10JAR1.SGM 10JAR1 Federal Register / Vol. 78, No. 7 / Thursday, January 10, 2013 / Rules and Regulations Issued in Burlington, Massachusetts, on December 27, 2012. Colleen M. D’Alessandro, Assistant Manager, Engine & Propeller Directorate, Aircraft Certification Service. Mahlow, Germany; phone: 49 0 33– 7086–1883; fax: 49 0 33–7086–3276. You may view this 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. [FR Doc. 2012–31588 Filed 1–9–13; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2012–1350; Directorate Identifier 2012–NE–40–AD; Amendment 39– 17313; AD 2012–27–01] RIN 2120–AA64 Airworthiness Directives; Rolls-Royce Deutschland Ltd & Co KG Turbofan Engines Federal Aviation Administration (FAA), DOT. ACTION: Final rule; request for comments. AGENCY: We are adopting a new airworthiness directive (AD) for certain Rolls-Royce Deutschland Ltd & Co KG (RRD) Model Tay 620–15 turbofan engines. This AD requires a one-time inspection of the low-pressure compressor (LPC) fan blades and if erosion is found their replacement before further flight. This AD was prompted by evidence of excessive leading edge erosion of the LPC fan blades on certain Tay 620–15 engines. We are issuing this AD to prevent failure of the LPC fan blade, which could result in uncontained engine failure and damage to the airplane. DATES: This AD becomes effective January 25, 2013. We must receive comments on this AD by February 25, 2013. 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, Eschenweg 11, Dahlewitz, 15827 Blankenfelde- wreier-aviles on DSK5TPTVN1PROD with SUMMARY: VerDate Mar<15>2010 12:02 Jan 09, 2013 Jkt 229001 2197 A1777, dated October 26, 2012. The actions described in this service information are intended to correct the unsafe condition identified in the MCAI. 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: Frederick Zink, Aerospace Engineer, Engine Certification Office, FAA, Engine & Propeller Directorate, 12 New England Executive Park, Burlington, MA 01803; phone: 781–238–7779; fax: 781–238– 7199; email: frederick.zink@faa.gov. SUPPLEMENTARY INFORMATION: This product has been approved by Germany and is approved for operation in the United States. Pursuant to our bilateral agreement with the European Community, EASA has 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 a one-time inspection of the LPC fan blades and if erosion is found their replacement before further flight. 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 2012–0234, dated November 6, 2012 (referred to after this as ‘‘the MCAI’’), to correct an unsafe condition for the specified products. The MCAI states: The Low Pressure Compressor (LPC) (fan) blades of certain Tay 620/15/20 and Tay 620– 15 engines show evidence of excessive leading edge erosion. Excessive material removal during the maintenance reduces the LPC (fan) blade chordal width and potentially changes the balance of the fan blade. Reduced chordal width can affect LPC (fan) blade performance and in combination with other circumstances could lead to a fan blade root failure and fan blade separation. This condition, if not detected and corrected, could lead to the LPC (fan) blade failure, potentially causing release of high-energy debris, possibly resulting in damage to the aeroplane and/or injury to the occupants. We are issuing this AD to prevent failure of the LPC fan blade, which could result in 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 NonModification Service Bulletin TAY–72– PO 00000 Frm 00003 Fmt 4700 Sfmt 4700 FAA’s Determination and Requirements of This AD FAA’s Determination of the Effective Date No domestic operators use this product. Therefore, we find that notice and opportunity for prior public comment are unnecessary and that good cause exists for making this amendment effective in less 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–2012–1350; Directorate Identifier 2012–NE–40–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 E:\FR\FM\10JAR1.SGM 10JAR1

Agencies

[Federal Register Volume 78, Number 7 (Thursday, January 10, 2013)]
[Rules and Regulations]
[Pages 2195-2197]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2012-31588]



========================================================================
Rules and Regulations
                                                Federal Register
________________________________________________________________________

This section of the FEDERAL REGISTER contains regulatory documents 
having general applicability and legal effect, most of which are keyed 
to and codified in the Code of Federal Regulations, which is published 
under 50 titles pursuant to 44 U.S.C. 1510.

The Code of Federal Regulations is sold by the Superintendent of Documents. 
Prices of new books are listed in the first FEDERAL REGISTER issue of each 
week.

========================================================================


Federal Register / Vol. 78, No. 7 / Thursday, January 10, 2013 / 
Rules and Regulations

[[Page 2195]]



DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2012-1202; Directorate Identifier 2012-NE-38-AD; 
Amendment 39-17309; AD 2012-26-14]
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 all 
Rolls-Royce Deutschland Ltd & Co KG BR700-715A1-30, BR700-715B1-30, and 
BR700-715C1-30 turbofan engines. This AD requires a one-time removal 
from service of the high-pressure (HP) compressor stages 1 to 6 rotor 
disc assembly before exceeding certain thresholds. This AD was prompted 
by a report of silver chloride-induced stress corrosion cracking of the 
HP compressor stages 1 to 6 rotor disc assembly, identified during 
overhaul. We are issuing this AD to prevent failure of the HP 
compressor stages 1 to 6 rotor disc assembly, which could result in 
uncontained failure of the engine and damage to the airplane.

DATES: This AD becomes effective January 10, 2013.
    We must receive comments on this AD by February 25, 2013.

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, Eschenweg 11, Dahlewitz, 15827 Blankenfelde-
Mahlow, Germany; telephone: 49 0 33-7086-1883; fax: 49 0 33-7086-3276. 
You may view 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: Frederick Zink, Aerospace Engineer, 
Engine Certification Office, FAA, Engine & Propeller Directorate, 12 
New England Executive Park, Burlington, MA 01803; phone: 781-238-7779; 
fax: 781-238-7199; email: frederick.zink@faa.gov.

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 
Airworthiness Directive 2012-0230, dated October 30, 2012 (referred to 
hereinafter as ``the MCAI''), to correct an unsafe condition for the 
specified products. The MCAI states:

Silver chloride-induced stress corrosion cracking was identified 
during overhaul of a BR700-715 engine, on the High Pressure 
Compressor (HPC) stages 1 to 6 rotor disc assembly. Subsequent 
evaluation concluded that the affected part life limitation values 
declared in the engine Time Limits Manual cannot be supported for 
high cyclic life HPC discs.

This condition, if not corrected, could lead to uncontained HPC disc 
failure, possibly resulting in damage to, and/or reduced control of 
the aeroplane.

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

FAA's Determination and Requirements of This AD

    This product has been approved by the aviation authority of 
Germany, and is approved for operation in the United States. Pursuant 
to our bilateral agreement with Germany, they have notified us of the 
unsafe condition described in the MCAI 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 a 
one-time removal from service of the HP compressor stages 1 to 6 rotor 
disc assembly before exceeding certain thresholds.

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 times for HP compressor stages 1 to 6 rotor disc 
assemblies that are at or over the removal thresholds. 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-2012-1202; Directorate 
Identifier 2012-NE-38-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

[[Page 2196]]

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 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

0
1. The authority citation for part 39 continues to read as follows:

    Authority: 49 U.S.C. 106(g), 40113, 44701.


Sec.  39.13  [Amended]

0
2. The FAA amends Sec.  39.13 by adding the following new AD:

2012-26-14 Rolls-Royce Deutschland Ltd & Co KG (Formerly Rolls-Royce 
Deutschland GmbH, formerly BMW Rolls-Royce GmbH): Amendment 39-
17309; Docket No. FAA-2012-1202; Directorate Identifier 2012-NE-38-
AD.

(a) Effective Date

    This airworthiness directive (AD) becomes effective January 10, 
2013.

(b) Affected ADs

    None.

(c) Applicability

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

(d) Reason

    This AD was prompted by a report of silver chloride-induced 
stress corrosion cracking of the high-pressure (HP) compressor 
stages 1 to 6 rotor disc assembly, identified during overhaul. We 
are issuing this AD to prevent failure of the HP compressor stages 1 
to 6 rotor disc assembly, which could result in uncontained failure 
of the engine and damage to the airplane.

(e) Actions and Compliance

    Unless already done, do the following actions.

(1) BR700-715A1-30 Turbofan Engines Operated Under the Hawaiian Flight 
Mission Only

    For BR700-715A1-30 turbofan engines operated under the Hawaiian 
Flight Mission only, do the following:
    (1) If the HP compressor stages 1 to 6 rotor disc assembly has 
accumulated 15,700 flight cycles since new or fewer on the effective 
date of this AD, remove the rotor disc assembly from service before 
exceeding 16,000 flight cycles since new (CSN).
    (2) If the HP compressor stages 1 to 6 rotor disc assembly has 
accumulated more than 15,700 flight CSN on the effective date of 
this AD, remove the rotor disc assembly from service within 300 
flight cycles.

(2) BR700-715A1-30, BR700-715B1-30, and BR700-715C1-30 Turbofan Engines 
(All Flight Missions Except the Hawaiian Flight Mission)

    For BR700-715A1-30, BR700-715B1-30, and BR700-715C1-30 turbofan 
engines (all flight missions except the Hawaiian Flight Mission), do 
the following:
    (1) If the HP compressor stages 1 to 6 rotor disc assembly has 
accumulated 13,700 flight CSN or fewer on the effective date of this 
AD, remove the rotor disc assembly from service before exceeding 
14,000 flight CSN.
    (2) If the HP compressor stages 1 to 6 rotor disc assembly has 
accumulated more than 13,700 flight cycles since new on the 
effective date of this AD, remove the rotor disc assembly from 
service within 300 flight cycles.

(f) Terminating Action

    Performing the one-time removal from service of the stages 1 to 
6 rotor disc assembly, as specified in this AD, is terminating 
action to this AD.

(g) Definition

    For the purpose of this AD, flight cycles is the total flight 
CSN on the HP compressor stages 1 to 6 rotor disc assembly, without 
any pro-rated calculations applied for different flight missions. 
Guidance on calculating total flight cycles can be found in Rolls-
Royce Deutschland Ltd & Co KG Notice to Operators BR715 engines NTO: 
No. 184, dated October 25, 2012.

(h) 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.

(i) Related Information

    (1) For more information about this AD, contact Frederick Zink, 
Aerospace Engineer, Engine Certification Office, FAA, Engine & 
Propeller Directorate, 12 New England Executive Park, Burlington, MA 
01803; phone: 781-238-7779; fax: 781-238-7199; email: 
frederick.zink@faa.gov.
    (2) Refer to European Aviation Safety Agency AD 2012-0230, dated 
October 30, 2012, and Rolls-Royce Deutschland Ltd & Co KG Alert 
Service Bulletin No. SB-BR700-72-A900401, dated October 25, 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; telephone: 49 0 33-7086-1883; fax: 49 
0 33-7086-3276. You may view 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.


[[Page 2197]]


    Issued in Burlington, Massachusetts, on December 27, 2012.
Colleen M. D'Alessandro,
Assistant Manager, Engine & Propeller Directorate, Aircraft 
Certification Service.
[FR Doc. 2012-31588 Filed 1-9-13; 8:45 am]
BILLING CODE 4910-13-P