Airworthiness Directives; Rolls-Royce Deutschland Ltd & Co KG Turbofan Engines, 68714-68716 [2012-27824]

Download as PDF 68714 Federal Register / Vol. 77, No. 222 / Friday, November 16, 2012 / Proposed Rules time specified in paragraph (l)(1) or (1)(2) of this AD. (1) If the inspection is done on or after the effective date of this AD: Submit the report within 30 days after doing the inspection. (2) If the inspection was done prior to the effective date of this AD: Submit the report within 30 days after the effective date of this AD. emcdonald on DSK7TPTVN1PROD with PROPOSALS (m) Other FAA AD Provisions The following provisions also apply to this AD: (1) Alternative Methods of Compliance (AMOCs): The Manager, International Branch, ANM–116, Transport Airplane Directorate, FAA, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. In accordance with 14 CFR 39.19, send your request to your principal inspector or local Flight Standards District Office, as appropriate. If sending information directly to the International Branch, send it to ATTN: Vladimir Ulyanov, Aerospace Engineer, International Branch, ANM–116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, Washington 98057– 3356; telephone (425) 227–1138; fax (425) 227–1149. Information may be emailed to: 9-ANM-116-AMOC-REQUESTS@faa.gov. Before using any approved AMOC, notify your appropriate principal inspector, or lacking a principal inspector, the manager of the local flight standards district office/ certificate holding district office. The AMOC approval letter must specifically reference this AD. AMOCs approved previously in accordance with AD 2010–02–10, Amendment 39–16181 (75 FR 4477, January 28, 2010), are approved as AMOCs for the corresponding provisions of this AD. (2) Airworthy Product: For any requirement in this AD to obtain corrective actions from a manufacturer or other source, use these actions if they are FAA-approved. Corrective actions are considered FAA-approved if they are approved by the State of Design Authority (or their delegated agent). You are required to assure the product is airworthy before it is returned to service. (3) Reporting Requirements: A federal agency may not conduct or sponsor, and a person is not required to respond to, nor shall a person be subject to a penalty for failure to comply with a collection of information subject to the requirements of the Paperwork Reduction Act unless that collection of information displays a current valid OMB Control Number. The OMB Control Number for this information collection is 2120–0056. Public reporting for this collection of information is estimated to be approximately 5 minutes per response, including the time for reviewing instructions, completing, and reviewing the collection of information. All responses to this collection of information are mandatory. Comments concerning the accuracy of this burden and suggestions for reducing the burden should be directed to the FAA at: 800 Independence Ave. SW., Washington, DC 20591, Attn: Information Collection Clearance Officer, AES–200. VerDate Mar<15>2010 15:42 Nov 15, 2012 Jkt 229001 (n) Special Flight Permits Special flight permits, as described in Section 21.197 and Section 21.199 of the Federal Aviation Regulations (14 CFR 21.197 and 21.199), are not allowed if any crack is found during any inspection required by this AD. (o) Related Information (1) Refer to MCAI EASA Airworthiness Directive 2011–0211, dated October 1, 2011, and the service information specified in paragraphs (o)(1)(i) through (o)(1)(vi) of this AD, for related information. (i) Airbus Mandatory Service Bulletin A330–32–3220, dated October 10, 2008. (ii) Airbus Mandatory Service Bulletin A330–32–3220, Revision 01, dated October 5, 2011. (iii) Airbus Mandatory Service Bulletin A330–32–3248, dated October 5, 2011. (iv) Airbus Mandatory Service Bulletin A340–32–4264, dated October 10, 2008. (v) Airbus Mandatory Service Bulletin A340–32–4286, dated October 5, 2011. (vi) Airbus Mandatory Service Bulletin A340–32–5087, dated October 10, 2008. (2) For service information identified in this AD, contact Airbus SAS—Airworthiness Office—EAL, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61 93 45 80; email airworthiness.A330-A340@airbus.com; Internet http://www.airbus.com. You may review copies of the referenced service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For information on the availability of this material at the FAA, call 425–227–1221. Issued in Renton, Washington, on November 8, 2012. Ali Bahrami, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2012–27847 Filed 11–15–12; 8:45 am] BILLING CODE 4910–13–P proposed AD was prompted by RRD performing an evaluation that determined that certain high-pressure turbine (HPT) stage 1 and stage 2 discs from a specific supplier may contain steel inclusions that may cause the discs to fail before they reach their current life limits. This proposed AD would require reducing the life limits for certain HPT stage 1 and stage 2 discs. We are proposing this AD to prevent failure of the HPT stage 1 and stage 2 discs, which could result in uncontained failure of the engine and damage to the airplane. DATES: We must receive comments on this proposed AD by January 15, 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: 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. For service information identified in this proposed AD, contact Rolls-Royce Deutschland Ltd & Co KG, Eschenweg 11, Dahlewitz, 15827 BlankenfeldeMahlow, 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. For information on the availability of this material at the FAA, call 781–238–7125. DEPARTMENT OF TRANSPORTATION Examining the AD Docket Federal Aviation Administration 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: Robert Morlath, Aerospace Engineer, Engine Certification Office, FAA, Engine & Propeller Directorate, 12 New England Executive Park, Burlington, MA 01803; phone: 781–238–7154; fax: 781–238– 7199; email: robert.c.morlath@faa.gov. 14 CFR Part 39 [Docket No. FAA–2012–1055; Directorate Identifier 2012–NE–33–AD] RIN 2120–AA64 Airworthiness Directives; Rolls-Royce Deutschland Ltd & Co KG Turbofan Engines Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). AGENCY: We propose to adopt a new airworthiness directive (AD) for all Rolls-Royce Deutschland Ltd & Co KG (RRD) BR700–710A1–10 and BR700– 710A2–20 turbofan engines, and certain BR700–710C4–11 model engines. This SUMMARY: PO 00000 Frm 00010 Fmt 4702 Sfmt 4702 E:\FR\FM\16NOP1.SGM 16NOP1 Federal Register / Vol. 77, No. 222 / Friday, November 16, 2012 / Proposed Rules 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–2012–1055; Directorate Identifier 2012–NE–33–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 with FAA personnel concerning this proposed 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). Discussion The European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Community, has issued EASA AD 2012– 0166, dated August 30, 2012 (referred to hereinafter as ‘‘the MCAI’’), to correct an unsafe condition for the specified products. The MCAI states: emcdonald on DSK7TPTVN1PROD with PROPOSALS The results of a recent quality review of high pressure turbine (HPT) stage 1 and stage 2 discs identified potential for steel inclusions in some production scale parts. Further investigation concluded that all affected parts were manufactured by Udimet 720I and melted by a certain supplier. Subsequent evaluation concluded that the affected parts life limitation values declared in the engine Time Limits Manual cannot be supported for discs with potential steel inclusion. This condition, if not corrected, could lead to an uncontained HPT disc failure, potentially resulting in damage to, and/or reduced control of the aeroplane. The FAA has further determined that the risk to the engine is increased by installing an HPT stage 1 disc and an HPT stage 2 disc from the affected population, on the same engine. Therefore the FAA is prohibiting the installation of an HPT stage 1 and HPT stage 2 disc from the affected population in the same engine. You may obtain VerDate Mar<15>2010 15:42 Nov 15, 2012 Jkt 229001 further information by examining the MCAI in the AD docket. FAA’s Determination and Requirements of This Proposed 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 and service information referenced above. We are proposing 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 proposed AD would require reducing the life limits for certain HPT stage 1 and HPT stage 2 discs that have a serial number listed in this proposed AD. Costs of Compliance We estimate that this proposed AD would affect about 10 engines installed on airplanes of U.S. registry. Prorated parts life will cost about $210,000. Based on these figures, we estimate the cost of the proposed AD on U.S. operators to be $2,100,000. Our cost estimate is exclusive of possible warranty coverage. 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 PO 00000 Frm 00011 Fmt 4702 Sfmt 4702 68715 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); 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 and placed it in the AD docket. List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. The Proposed Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA proposes to amend 14 CFR part 39 as follows: PART 39—AIRWORTHINESS DIRECTIVES 1. The authority citation for part 39 continues to read as follows: Authority: 49 U.S.C. 106(g), 40113, 44701. § 39.13 [Amended] 2. The FAA amends § 39.13 by adding the following new AD: Rolls-Royce Deutschland Ltd & Co KG (Formerly Rolls-Royce Deutschland GmbH, formerly BMW Rolls-Royce GmbH): Docket No. FAA–2012–1055; Directorate Identifier 2012–NE–33–AD. (a) Comments Due Date We must receive comments by January 15, 2013. (b) Affected Airworthiness Directives (ADs) None. (c) Applicability This AD applies to the following RollsRoyce Deutschland Ltd & Co KG (RRD) turbofan engines that have any of the highpressure turbine (HPT) stage 1 or stage 2 discs with a serial number (S/N) listed in Table 1 to paragraph (c) of this AD, installed: (1) RRD BR700–710A1–10 and BR700– 710A2–20 turbofan engines; and (2) BR700–710C4–11 model engines that have hardware configuration standard 710C4–11 or 710C4–11/10 engraved on the engine data plate. E:\FR\FM\16NOP1.SGM 16NOP1 68716 Federal Register / Vol. 77, No. 222 / Friday, November 16, 2012 / Proposed Rules S/Ns of HPT Stage 1 discs, Part No. (P/N) BRR23952 S/Ns of HPT Stage 2 discs, P/N BRR22008 LDRQA05719 LDRQA05720 LDRQA05721 LDRQA05722 LDRQA05723 LDRQA05724 LDRQA05726 LDRQA05727 LDRQA05841 LDRQA05842 LDRQA05791 LDRQA05944 LDRQA05945 Blankenfelde-Mahlow, Germany; phone: 49 0 33–7086–1883; fax: 49 0 33–7086–3276, for a copy of this service information. (3) 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. FOR FURTHER INFORMATION CONTACT: Issued in Burlington, Massachusetts, on November 5, 2012. Colleen M. D’Alessandro, Assistant Manager, Engine & Propeller Directorate, Aircraft Certification Service. TABLE 1 TO PARAGRAPH (C)—AFFECTED HPT STAGE 1 AND STAGE 2 DISCS SUPPLEMENTARY INFORMATION: [FR Doc. 2012–27824 Filed 11–15–12; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION (d) Reason This AD was prompted by RRD performing an evaluation that determined that certain HPT stage 1 and stage 2 discs from a specific supplier may contain steel inclusions that may cause the discs to fail before they reach their current life limits. We are issuing this AD to prevent failure of the HPT stage 1 and stage 2 discs, which could result in uncontained failure of the engine and damage to the airplane. (e) Actions and Compliance Unless already done, remove from service the HPT stage 1 and stage 2 discs listed by S/N in Table 1 to paragraph (c) of this AD, at the following: (1) For BR700–710A1–10, BR700–710A2– 20, and BR700–710C4–11 engine models (without RRD Mod 72–101466), remove the HPT stage 1 and stage 2 discs from service before accumulating 3,000 cycles-since-new (CSN). (2) For the BR700–710C4–11 engine model (with RRD Mod 72–101466), remove the HPT stage 1 and stage 2 discs from service before accumulating 2,300 CSN. (f) Installation Prohibition After the effective date of this AD, do not install an HPT stage 1 and an HPT stage 2 disc, identified by S/N in Table 1 to paragraph (c) of this AD, in the same engine. emcdonald on DSK7TPTVN1PROD with PROPOSALS (g) 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. (h) Related Information (1) For more information about this AD, contact Robert Morlath, Aerospace Engineer, Engine Certification Office, FAA, Engine & Propeller Directorate, 12 New England Executive Park, Burlington, MA 01803; phone: 781–238–7154; fax: 781–238–7199; email: robert.c.morlath@faa.gov. (2) Refer to European Aviation Safety Agency Airworthiness Directive 2012–0166, dated August 30, 2012, and Rolls-Royce Deutschland Ltd & Co KG Alert Service Bulletin SB–BR700–72–A900508, dated July 26, 2012, for related information. Contact Rolls-Royce Deutschland Ltd & Co KG, Eschenweg 11, Dahlewitz, 15827 VerDate Mar<15>2010 15:42 Nov 15, 2012 Jkt 229001 Federal Aviation Administration 14 CFR Part 71 [Docket No. FAA–2012–0655; Airspace Docket No. 12–AGL–6] Proposed Amendment of Class E Airspace; Hot Springs, SD Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). AGENCY: This action proposes to amend Class E airspace at Hot Springs, SD. Additional controlled airspace is necessary to accommodate new Standard Instrument Approach Procedures (SIAPs) at Hot Springs Municipal Airport. The FAA is taking this action to enhance the safety and management of Instrument Flight Rules (IFR) operations for SIAPs at the airport. Geographic coordinates of the airport would also be updated. DATES: 0901 UTC. Comments must be received on or before December 31, 2012. SUMMARY: Send comments on this proposal to the U.S. Department of Transportation, Docket Operations, 1200 New Jersey Avenue SE., West Building Ground Floor, Room W12–140, Washington, DC 20590–0001. You must identify the docket number FAA–2012– 0655/Airspace Docket No. 12–AGL–6, at the beginning of your comments. You may also submit comments through the Internet at http://www.regulations.gov. You may review the public docket containing the proposal, any comments received, and any final disposition in person in the Dockets Office between 9:00 a.m. and 5:00 p.m., Monday through Friday, except Federal holidays. The Docket Office (telephone 1–800– 647–5527), is on the ground floor of the building at the above address. ADDRESSES: PO 00000 Frm 00012 Fmt 4702 Sfmt 4702 Scott Enander, Central Service Center, Operations Support Group, Federal Aviation Administration, Southwest Region, 2601 Meacham Blvd., Fort Worth, TX 76137; telephone: (817) 321– 7716. Comments Invited Interested parties are invited to participate in this proposed rulemaking by submitting such written data, views, or arguments, as they may desire. Comments that provide the factual basis supporting the views and suggestions presented are particularly helpful in developing reasoned regulatory decisions on the proposal. Comments are specifically invited on the overall regulatory, aeronautical, economic, environmental, and energy-related aspects of the proposal. Communications should identify both docket numbers and be submitted in triplicate to the address listed above. Commenters wishing the FAA to acknowledge receipt of their comments on this notice must submit with those comments a self-addressed, stamped postcard on which the following statement is made: ‘‘Comments to Docket No. FAA–2012–0655/Airspace Docket No. 12–AGL–6.’’ The postcard will be date/time stamped and returned to the commenter. Availability of NPRMs An electronic copy of this document may be downloaded through the Internet at http://www.regulations.gov. Recently published rulemaking documents can also be accessed through the FAA’s Web page at http:// www.faa.gov/airports_airtraffic/ air_traffic/publications/ airspace_amendments/. You may review the public docket containing the proposal, any comments received and any final disposition in person in the Dockets Office (see ADDRESSES section for address and phone number) between 9:00 a.m. and 5:00 p.m., Monday through Friday, except Federal holidays. An informal docket may also be examined during normal business hours at the office of the Central Service Center, 2601 Meacham Blvd., Fort Worth, TX 76137. Persons interested in being placed on a mailing list for future NPRMs should contact the FAA’s Office of Rulemaking (202) 267–9677, to request a copy of Advisory Circular No. 11–2A, Notice of Proposed Rulemaking Distribution System, which describes the application procedure. E:\FR\FM\16NOP1.SGM 16NOP1

Agencies

[Federal Register Volume 77, Number 222 (Friday, November 16, 2012)]
[Proposed Rules]
[Pages 68714-68716]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2012-27824]


-----------------------------------------------------------------------

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2012-1055; Directorate Identifier 2012-NE-33-AD]
RIN 2120-AA64


Airworthiness Directives; Rolls-Royce Deutschland Ltd & Co KG 
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 all 
Rolls-Royce Deutschland Ltd & Co KG (RRD) BR700-710A1-10 and BR700-
710A2-20 turbofan engines, and certain BR700-710C4-11 model engines. 
This proposed AD was prompted by RRD performing an evaluation that 
determined that certain high-pressure turbine (HPT) stage 1 and stage 2 
discs from a specific supplier may contain steel inclusions that may 
cause the discs to fail before they reach their current life limits. 
This proposed AD would require reducing the life limits for certain HPT 
stage 1 and stage 2 discs. We are proposing this AD to prevent failure 
of the HPT stage 1 and stage 2 discs, which could result in uncontained 
failure of the engine and damage to the airplane.

DATES: We must receive comments on this proposed AD by January 15, 
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: 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.
    For service information identified in this proposed 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 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 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: Robert Morlath, Aerospace Engineer, 
Engine Certification Office, FAA, Engine & Propeller Directorate, 12 
New England Executive Park, Burlington, MA 01803; phone: 781-238-7154; 
fax: 781-238-7199; email: robert.c.morlath@faa.gov.

[[Page 68715]]


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-2012-1055; 
Directorate Identifier 2012-NE-33-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 
with FAA personnel concerning this proposed 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).

Discussion

    The European Aviation Safety Agency (EASA), which is the Technical 
Agent for the Member States of the European Community, has issued EASA 
AD 2012-0166, dated August 30, 2012 (referred to hereinafter as ``the 
MCAI''), to correct an unsafe condition for the specified products. The 
MCAI states:

    The results of a recent quality review of high pressure turbine 
(HPT) stage 1 and stage 2 discs identified potential for steel 
inclusions in some production scale parts. Further investigation 
concluded that all affected parts were manufactured by Udimet 720I 
and melted by a certain supplier. Subsequent evaluation concluded 
that the affected parts life limitation values declared in the 
engine Time Limits Manual cannot be supported for discs with 
potential steel inclusion.
    This condition, if not corrected, could lead to an uncontained 
HPT disc failure, potentially resulting in damage to, and/or reduced 
control of the aeroplane.

The FAA has further determined that the risk to the engine is increased 
by installing an HPT stage 1 disc and an HPT stage 2 disc from the 
affected population, on the same engine. Therefore the FAA is 
prohibiting the installation of an HPT stage 1 and HPT stage 2 disc 
from the affected population in the same engine. You may obtain further 
information by examining the MCAI in the AD docket.

FAA's Determination and Requirements of This Proposed 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 and service information 
referenced above. We are proposing 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 proposed AD would require reducing the life limits for 
certain HPT stage 1 and HPT stage 2 discs that have a serial number 
listed in this proposed AD.

Costs of Compliance

    We estimate that this proposed AD would affect about 10 engines 
installed on airplanes of U.S. registry. Prorated parts life will cost 
about $210,000. Based on these figures, we estimate the cost of the 
proposed AD on U.S. operators to be $2,100,000. Our cost estimate is 
exclusive of possible warranty coverage.

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); 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 and placed it in the AD docket.

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.


Sec.  39.13  [Amended]

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


Rolls-Royce Deutschland Ltd & Co KG (Formerly Rolls-Royce 
Deutschland GmbH, formerly BMW Rolls-Royce GmbH): Docket No. FAA-
2012-1055; Directorate Identifier 2012-NE-33-AD.

(a) Comments Due Date

    We must receive comments by January 15, 2013.

(b) Affected Airworthiness Directives (ADs)

    None.

(c) Applicability

    This AD applies to the following Rolls-Royce Deutschland Ltd & 
Co KG (RRD) turbofan engines that have any of the high-pressure 
turbine (HPT) stage 1 or stage 2 discs with a serial number (S/N) 
listed in Table 1 to paragraph (c) of this AD, installed:
    (1) RRD BR700-710A1-10 and BR700-710A2-20 turbofan engines; and
    (2) BR700-710C4-11 model engines that have hardware 
configuration standard 710C4-11 or 710C4-11/10 engraved on the 
engine data plate.

[[Page 68716]]



    Table 1 to Paragraph (c)--Affected HPT Stage 1 and Stage 2 Discs
------------------------------------------------------------------------
S/Ns of HPT Stage 1 discs, Part No.     S/Ns of HPT Stage 2 discs, P/N
           (P/N) BRR23952                          BRR22008
------------------------------------------------------------------------
             LDRQA05719                           LDRQA05791
             LDRQA05720                           LDRQA05944
             LDRQA05721                           LDRQA05945
             LDRQA05722
             LDRQA05723
             LDRQA05724
             LDRQA05726
             LDRQA05727
             LDRQA05841
             LDRQA05842
------------------------------------------------------------------------

(d) Reason

    This AD was prompted by RRD performing an evaluation that 
determined that certain HPT stage 1 and stage 2 discs from a 
specific supplier may contain steel inclusions that may cause the 
discs to fail before they reach their current life limits. We are 
issuing this AD to prevent failure of the HPT stage 1 and stage 2 
discs, which could result in uncontained failure of the engine and 
damage to the airplane.

(e) Actions and Compliance

    Unless already done, remove from service the HPT stage 1 and 
stage 2 discs listed by S/N in Table 1 to paragraph (c) of this AD, 
at the following:
    (1) For BR700-710A1-10, BR700-710A2-20, and BR700-710C4-11 
engine models (without RRD Mod 72-101466), remove the HPT stage 1 
and stage 2 discs from service before accumulating 3,000 cycles-
since-new (CSN).
    (2) For the BR700-710C4-11 engine model (with RRD Mod 72-
101466), remove the HPT stage 1 and stage 2 discs from service 
before accumulating 2,300 CSN.

(f) Installation Prohibition

    After the effective date of this AD, do not install an HPT stage 
1 and an HPT stage 2 disc, identified by S/N in Table 1 to paragraph 
(c) of this AD, in the same engine.

(g) 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.

(h) Related Information

    (1) For more information about this AD, contact Robert Morlath, 
Aerospace Engineer, Engine Certification Office, FAA, Engine & 
Propeller Directorate, 12 New England Executive Park, Burlington, MA 
01803; phone: 781-238-7154; fax: 781-238-7199; email: 
robert.c.morlath@faa.gov.
    (2) Refer to European Aviation Safety Agency Airworthiness 
Directive 2012-0166, dated August 30, 2012, and Rolls-Royce 
Deutschland Ltd & Co KG Alert Service Bulletin SB-BR700-72-A900508, 
dated July 26, 2012, for related information. 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, for a copy of this service information.
    (3) 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 November 5, 2012.
Colleen M. D'Alessandro,
Assistant Manager, Engine & Propeller Directorate, Aircraft 
Certification Service.
[FR Doc. 2012-27824 Filed 11-15-12; 8:45 am]
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