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Federal Register / Vol. 86, No. 213 / Monday, November 8, 2021 / Rules and Regulations
c Applicability This AD applies to all Airbus SAS Model A319171N airplanes; Model A320271N, 272N, and 273N airplanes; and Model A321271N, 272N, 271NX, and 272NX
airplanes, certificated in any category.
d Subject Air Transport Association ATA of America Code 29, Hydraulic power.

j Additional AD Provisions
e Unsafe Condition This AD was prompted by a report of damage found at the rod-eye ends of two original rods installed to maintain an interface plate between the pylon and nacelle, and the need to clarify certain existing requirements from AD 20211808.
The FAA is issuing this AD to address damage that could lead to rupture of the rodeye ends, which could result in fuel and hydraulic pipe chafing, consequent fuel or hydraulic leakage, and possible fire.
f Compliance Comply with this AD within the compliance times specified, unless already done.
g Requirements Except as specified in paragraph h of this AD: Comply with all required actions and compliance times specified in, and in accordance with, European Union Aviation Safety Agency EASA AD 20210177R1, dated September 21, 2021 EASA AD 2021
0177R1.

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h Exceptions to EASA AD 20210177R1
1 Where EASA AD 20210177R1 refers to 06 August 2021 the effective date of the original issue of this AD, this AD requires using September 14, 2021 the effective date of AD 20211808.
2 Where EASA AD 20210177R1 refers to its effective date, this AD requires using the effective date of this AD.
3 Paragraph 4 of EASA AD 2021
0177R1 specifies to contact Airbus for approved instructions and, within the compliance times specified in those instructions, accomplish those instructions accordingly as an alternative corrective action if a defect is detected during inspection of an updated rod. As of the effective date of this AD, however, for that alternative, this AD requires repair of the defect before further flight using a method approved by the Manager, Large Aircraft Section, International Validation Branch, FAA; or EASA; or Airbus SASs EASA
Design Organization Approval DOA. If approved by the DOA, the approval must include the DOA-authorized signature.
4 The Remarks section of EASA AD
20210177R1 does not apply to this AD.
i Clarification of EASA AD 20210177R1
Paragraph 8 of EASA AD 20210177R1
allows installation of an affected part if it is serviceable and inspected within 750 flight hours after installation. The Definitions section of EASA AD 20210177R1 requires that a serviceable affected part pass an inspection before the next flight after installation. Therefore, this AD allows installation of an affected serviceable part
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after the effective date of this AD if it is inspected before further flight after installation and 750 flight hours thereafter.
All other provisions of paragraph 8 and Note 2 of EASA AD 20210177R1 apply to this AD, including the repetitive inspection of that part as required by paragraph 1 or 2 of EASA AD 20210177R1.
The following provisions also apply to this AD:
1 Alternative Methods of Compliance AMOCs: The Manager, Large Aircraft Section, International Validation 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 responsible Flight Standards Office, as appropriate. If sending information directly to the Large Aircraft Section, International Validation Branch, send it to the attention of the person identified in paragraph k of this AD.
Information may be emailed to: 9-AVS-AIR730-AMOC@faa.gov. Before using any approved AMOC, notify your appropriate principal inspector, or lacking a principal inspector, the manager of the responsible Flight Standards Office.
2 Contacting the Manufacturer: For any requirement in this AD to obtain instructions from a manufacturer, the instructions must be accomplished using a method approved by the Manager, Large Aircraft Section, International Validation Branch, FAA; or EASA; or Airbus SASs EASA Design Organization Approval DOA. If approved by the DOA, the approval must include the DOA-authorized signature.
3 Required for Compliance RC: Except as required by paragraph j2 of this AD, if any service information contains procedures or tests that are identified as RC, those procedures and tests must be done to comply with this AD; any procedures or tests that are not identified as RC are recommended. Those procedures and tests that are not identified as RC may be deviated from using accepted methods in accordance with the operators maintenance or inspection program without obtaining approval of an AMOC, provided the procedures and tests identified as RC can be done and the airplane can be put back in an airworthy condition. Any substitutions or changes to procedures or tests identified as RC require approval of an AMOC.
k Related Information For more information about this AD, contact Sanjay Ralhan, Aerospace Engineer, Large Aircraft Section, FAA, International Validation Branch, 2200 South 216th St., Des Moines, WA 98198; telephone and fax 206
2313223; email Sanjay.Ralhan@faa.gov.
l Material Incorporated by Reference 1 The Director of the Federal Register approved the incorporation by reference IBR of the service information listed in this paragraph under 5 U.S.C. 552a and 1 CFR
part 51.
2 You must use this service information as applicable to do the actions required by this AD, unless this AD specifies otherwise.

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i European Union Aviation Safety Agency EASA AD 20210177R1, dated September 21, 2021.
ii Reserved 3 For EASA AD 20210177R1, contact EASA, Konrad-Adenauer-Ufer 3, 50668
Cologne, Germany; telephone +49 221 8999
000; email ADs@easa.europa.eu; internet www.easa.europa.eu. You may find this EASA AD on the EASA website at https
ad.easa.europa.eu.
4 You may view this material at the FAA, Airworthiness Products Section, Operational Safety Branch, 2200 South 216th St., Des Moines, WA. For information on the availability of this material at the FAA, call 2062313195. This material may be found in the AD docket at https
www.regulations.gov by searching for and locating Docket No. FAA20210950.
5 You may view this material that is incorporated by reference at the National Archives and Records Administration NARA. For information on the availability of this material at NARA, email fr.inspection@nara.gov, or go to: https
www.archives.gov/federal-register/cfr/ibrlocations.html.
Issued on October 27, 2021.
Lance T. Gant, Director, Compliance & Airworthiness Division, Aircraft Certification Service.
FR Doc. 202124447 Filed 11421; 11:15 am BILLING CODE 491013P

DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration 14 CFR Part 39
Docket No. FAA20210257; Project Identifier MCAI202000712E; Amendment 3921772; AD 20212112
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 BR700710A220 model turbofan engines. This AD was prompted by flight data obtained from airplanes equipped with certain Rockwell Collins avionics and auto-throttle systems that demonstrated significant oscillation of the engine rotor revolution speed during flight. This AD requires initial and repetitive recalculation of the consumed and remaining service life of certain lifelimited parts LLPs. This AD also
SUMMARY:

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08NOR1