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Federal Register / Vol. 86, No. 128 / Thursday, July 8, 2021 / Rules and Regulations
2 For PW1919G, PW1921G, PW1922G, PW1923G, and PW1923GA model turbofan engines, the installation of EEC FADEC
software required by paragraph g5 of this AD terminates the repetitive BSI
requirements of paragraphs g1 and 2 of this AD.
i Installation Prohibition After the effective date of this AD, do not install EEC FADEC software earlier than version V2.11.10.4 or version V9.5.6.7 onto any engine identified in paragraph c of this AD.
j Definitions 1 For the purpose of this AD, a zero time spare is an engine that had zero flight hours time-in-service when it was installed on an airplane after the airplane had entered service.
2 For the purpose of this AD, EEC
FADEC software that is eligible for installation is EEC FADEC software version V2.11.10.4 or later for PW1519G, PW1521G, PW1521G3, PW1521GA, PW1524G, PW1524G3, PW1525G, PW1525G3 model turbofan engines and EEC FADEC software version V9.5.6.7 or later for PW1919G, PW1921G, PW1922G, PW1923G, and PW1923GA model turbofan engines.
k Alternative Methods of Compliance AMOCs 1 The Manager, ECO Branch, 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 manager of the certification office, send it to the attention of the person identified in Related Information. You may email your request to ANE-AD-AMOC@
faa.gov.
2 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.
3 AMOCs approved for AD 20192111
84 FR 57813, October 29, 2019 are approved as AMOCs for the corresponding provisions of this AD except for paragraphs g1i through iv and g3i and ii of this AD.
l Related Information For more information about this AD, contact Nicholas Paine, Aviation Safety Engineer, ECO Branch, FAA, 1200 District Avenue, Burlington, MA 01803; phone: 781
2387116; fax: 781 2387199; email:
nicholas.j.paine@faa.gov.
m Material Incorporated by Reference lotter on DSK11XQN23PROD with RULES1

None.

Federal Aviation Administration 14 CFR Part 39
Docket No. FAA20201174; Project Identifier MCAI201900135E; Amendment 3921594; AD 20211207
RIN 2120AA64

Airworthiness Directives; Rolls-Royce Deutschland Ltd & Co KG Type Certificate Previously Held by RollsRoyce Deutschland GmbH, Formerly BMW Rolls-Royce GmbH Turbofan Engines Federal Aviation Administration FAA, DOT.
ACTION: Final rule.
AGENCY:

The FAA is adopting a new airworthiness directive AD for certain Rolls-Royce Deutschland Ltd & Co KG
RRD BR700710A110, BR700
710A220 and BR700710C411 model turbofan engines. This AD was prompted by an investigation by RRD, which revealed a quality escape during the high-pressure turbine HPT stage 1
disk rim cooling air hole manufacturing process. This AD requires removing affected HPT disks from service prior to reaching specified compliance times or at the next engine shop visit, whichever occurs first. The FAA is issuing this AD
to address the unsafe condition on these products.
DATES: This AD is effective August 12, 2021.
The Director of the Federal Register approved the incorporation by reference of a certain publication listed in this AD
as of August 12, 2021.
ADDRESSES: For service information identified in this AD, contact RollsRoyce Deutschland Ltd & Co KG, Eschenweg 11, Dahlewitz 15827, Germany; phone: +49 33 7086 4040;
email: rrd.techhelp@rolls-royce.com.
You may view this service information at the FAA, Airworthiness Products Section, Operational Safety Branch, 1200 District Avenue, Burlington, MA
01803. For information on the availability of this material at the FAA, call 781 2387759. It is also available at https www.regulations.gov by searching for and locating Docket No.
FAA20201174.
SUMMARY:

Examining the AD Docket
Issued on June 23, 2021.
Lance T. Gant, Director, Compliance & Airworthiness Division, Aircraft Certification Service.
FR Doc. 202113873 Filed 7721; 8:45 am BILLING CODE 491013P

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DEPARTMENT OF TRANSPORTATION

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You may examine the AD docket at https www.regulations.gov by searching for and locating Docket No.
FAA20201174; or in person at Docket Operations between 9 a.m. and 5 p.m., Monday through Friday, except Federal
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holidays. The AD docket contains this final rule, the mandatory continuing airworthiness information MCAI, any comments received, and other information. The address for Docket Operations is U.S. Department of Transportation, Docket Operations, M30, West Building Ground Floor, Room W12140, 1200 New Jersey Avenue SE, Washington, DC 20590.
FOR FURTHER INFORMATION CONTACT:
Wego Wang, Aviation Safety Engineer, ECO Branch, FAA, 1200 District Avenue, Burlington, MA 01803; phone:
781 2387134; fax: 781 2387199;
email: wego.wang@faa.gov.
SUPPLEMENTARY INFORMATION:
Background The FAA issued a notice of proposed rulemaking NPRM to amend 14 CFR
part 39 by adding an AD that would apply to certain RRD BR700710A110, BR700710A220 and BR700710C411
model turbofan engines. The NPRM
published in the Federal Register on January 21, 2021 86 FR 6271. The NPRM was prompted by an investigation by RRD, which revealed a quality escape during the HPT stage 1
disk rim cooling air hole manufacturing process. In the NPRM, the FAA
proposed to require removing affected HPT disks from service prior to reaching specified compliance times or at the next engine shop visit, whichever occurs first. The FAA is issuing this AD
to address the unsafe condition on these products.
The European Union Aviation Safety Agency EASA, which is the Technical Agent for the Member States of the European Community, has issued EASA
AD 20190299, dated December 10, 2019 referred to after this as the MCAI, to address the unsafe condition on these products. The MCAI states:
An occurrence was reported of an HPT
stage 1 disc burst on an industrial gas turbine engine. Subsequent investigation revealed a quality escape during HPT stage 1 disc rim cooling air hole manufacturing process. A
review revealed that 28 HPT stage 1 discs were subject to a similar quality escape, two of which have been recovered and removed from service. The consequence of this manufacturing error is that the affected parts can no longer safely reach their Declared Safe Cyclic Life DSCL.
This condition, if not corrected, may lead to failure of an affected part, possibly resulting in release of high-energy debris, with consequent damage to, and/or reduced control of, the aeroplane. To address this potentially unsafe condition, RRD issued the NMSB, providing instructions to remove the engine from service for in-shop replacement of the affected part.
For the reasons described above, this EASA AD reduces the DSCL for the affected
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