Airworthiness Directives; Rolls-Royce Deutschland Ltd & Co KG (Type Certificate Previously Held by Rolls-Royce plc) Turbofan Engines, 78215-78219 [2020-26730]

Download as PDF Federal Register / Vol. 85, No. 234 / Friday, December 4, 2020 / Rules and Regulations servicing of an SBA Supervised Lender’s 7(a) loan portfolio in accordance with § 120.535(d) upon the voluntary surrender of its SBA lending authority. § 120.470 8. Amend § 120.470 by removing paragraph (g) and redesignating paragraph (h) as paragraph (g). 9. Amend § 120.471 by: ■ a. Revising paragraph (a); ■ b. Redesignating paragraphs (b)(3) through (5) as paragraphs (b)(4) through (6) respectively; and ■ c. Adding new paragraph (b)(3). The revision and addition to read as follows: § 120.471 What are the minimum capital requirements for SBLCs? (a) Minimum capital requirements. (1) Beginning on January 4, 2024, each SBLC that makes or acquires a 7(a) loan must maintain, at a minimum, unencumbered paid-in capital and paidin surplus of at least $5,000,000, or 10 percent of the aggregate of its share of all outstanding loans, whichever is greater. (2) Any SBLC approved on or after January 4, 2021, including in the event of a change of ownership or control, must maintain the minimum capital requirement set forth in paragraph (a)(1) of this section. (3) Unless subject to paragraph (a)(1) or (2) of this section, an SBLC must comply with the minimum capital requirements that were in effect on January 3, 2021. (b) * * * (3) Unrestricted net assets (for nonprofit corporations); * * * * * ■ 10. Remove and reserve § 120.475. Jovita Carranza, Administrator. [FR Doc. 2020–26307 Filed 12–3–20; 8:45 am] BILLING CODE P VerDate Sep<11>2014 16:15 Dec 03, 2020 Jkt 253001 14 CFR Part 39 RIN 2120–AA64 ■ [Removed and Reserved] Federal Aviation Administration [Docket No. FAA–2019–0425; Project Identifier 2016–NE–13–AD; Amendment 39– 21346; AD 2020–25–04] [Amended] ■ § 120.475 DEPARTMENT OF TRANSPORTATION Airworthiness Directives; Rolls-Royce Deutschland Ltd & Co KG (Type Certificate Previously Held by RollsRoyce plc) Turbofan Engines Federal Aviation Administration (FAA), DOT. ACTION: Final rule. AGENCY: The FAA is superseding Airworthiness Directive (AD) 2016–24– 08 for all Rolls-Royce Deutschland Ltd. & Co KG (RRD) RB211–Trent 875–17, RB211–Trent 877–17, RB211–Trent 884–17, RB211–Trent 884B–17, RB211– Trent 892–17, RB211–Trent 892B–17, and RB211–Trent 895–17 model turbofan engines. AD 2016–24–08 required repetitive inspections of the engine upper bifurcation nose fairing assembly and repair or replacement of any fairing assembly that fails inspection. This AD retains the requirements to perform repetitive inspections of the engine upper bifurcation nose fairing assembly and repair or replacement of any fairing assembly that fails inspection. As a terminating action to these inspections, this AD also requires the modification of the engine upper bifurcation nose fairing assembly. The FAA is issuing this AD to address the unsafe condition on these products. DATES: This AD is effective January 8, 2021. The Director of the Federal Register approved the incorporation by reference of certain publications listed in this AD as of January 8, 2021. ADDRESSES: For service information identified in this final rule, contact Rolls-Royce plc, Corporate Communications, P.O. Box 31, Derby, England, DE24 8BJ; phone: (+44) 1332 242424; fax: (+44) 1332 249936; email: https://www.rolls-royce.com/contact/ civil_team.jsp; internet: https:// customers.rolls-royce.com/public/ rollsroycecare. 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) 238– 7759. It is also available at https:// www.regulations.gov by searching for SUMMARY: PO 00000 Frm 00019 Fmt 4700 Sfmt 4700 78215 and locating Docket No. FAA–2019– 0425. Examining the AD Docket You may examine the AD docket at https://www.regulations.gov by searching for and locating Docket No. FAA–2019–0425; or in person at Docket Operations between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this AD, 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, M– 30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE, Washington, DC 20590. FOR FURTHER INFORMATION CONTACT: Scott Stevenson, Aviation Safety Engineer, ECO Branch, FAA, 1200 District Avenue, Burlington, MA 01803; phone: (781) 238–7132; fax: (781) 238– 7199; email: Scott.M.Stevenson@faa.gov. SUPPLEMENTARY INFORMATION: Background The FAA issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 to supersede AD 2016–24–08, Amendment 39–18725 (81 FR 86567, December 1, 2016) (AD 2016–24–08). AD 2016–24–08 applied to all RR RB211–Trent 875–17, RB211–Trent 877–17, RB211–Trent 884–17, RB211– Trent 884B–17, RB211–Trent 892–17, RB211–Trent 892B–17, and RB211– Trent 895–17 model turbofan engines. The NPRM published in the Federal Register on June 24, 2019 (84 FR 29423). The NPRM was prompted by RRD developing a modification of the engine upper bifurcation nose fairing assembly that terminates the need for repetitive inspections of this part. In the NPRM, the FAA proposed to retain the requirements to perform repetitive inspections of the engine upper bifurcation nose fairing assembly and repair or replacement of any fairing assembly that fails inspection. As a terminating action, in the NPRM the FAA also proposed to require modification of the engine upper bifurcation nose fairing assembly. The FAA is issuing this AD to address the unsafe condition of these products. The European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Community, has issued EASA AD 2018– 0088, dated April 18, 2018 (referred to after this as ‘‘the MCAI’’), to address the unsafe condition on these products. The MCAI states: E:\FR\FM\04DER1.SGM 04DER1 78216 Federal Register / Vol. 85, No. 234 / Friday, December 4, 2020 / Rules and Regulations Inspection of in-service Trent 800 engines identified cracking and/or material release from the upper bifurcation fairing, which mates to the aeroplane thrust reverser upper bifurcation forward fire seal. Both sets of hardware create the engine firewall to isolate the engine compartment fire zone, which is a firewall feature of the aeroplane type design. Damage (missing materials and holes/ openings) to the upper bifurcation fairing creates a breach of the engine fire wall, which may decrease the effectiveness of the engine fire detection and suppression systems due to excess fan air entering the engine compartment fire zone. This could delay or prevent the fire detection and suppression system from functioning properly, and can result in an increased risk of prolonged burning, potentially allowing a fire to reach unprotected areas of the engine, strut and wing. This condition, if not detected and corrected, could lead to an uncontrolled fire, possibly resulting in damage to, or loss of, the aeroplane. To address this potential unsafe condition, RR published the NMSB to provide inspection instructions. Consequently, EASA issued AD 2016–0084 to require repetitive inspections of the upper bifurcation fairing and, depending on findings, accomplishment of applicable corrective action(s). Since that [EASA] AD was issued, RR developed modification (mod) 72–J803, which introduces a revised upper bifurcation nose fairing assembly, featuring an additional support bracket assembly at the right hand seal land. RR also published the modification SB to provide instructions for in-service engines. This modification removes the need for repetitive inspections. For the reasons described above, this [EASA] AD retains the requirements of EASA AD 2016–0084, which is superseded, and requires a modification, which constitutes terminating action for the repetitive inspections required by this [EASA] AD. You may obtain further information by examining the MCAI in the AD docket at https://www.regulations.gov by searching for and locating Docket No. FAA–2019–0425. Discussion of Final Airworthiness Directive Comments The FAA received comments from six commenters. The commenters were Rolls-Royce plc (RR); American Airlines (AAL); The Boeing Company (Boeing); Delta Air Lines, Inc. (DAL); and two individual commenters. Five commenters requested changes to this AD, which included adding or updating the unsafe condition, terminating action, installation prohibition, and credit for previous actions. One commenter requested clarification regarding on-wing rework. One commenter expressed support for the AD. The following presents the comments received on the NPRM and the FAA’s response to each comment. VerDate Sep<11>2014 16:15 Dec 03, 2020 Jkt 253001 Request To Remove Statement Indicating the Unsafe Condition Could Cause a Fire Boeing requested that paragraph (e), Unsafe Condition, of this AD be revised to replace ‘‘. . . could result in engine fire and damage to the airplane’’ with ‘‘. . . could result in reduced ability to detect and/or control an engine fire which could lead to damage to the airplane.’’ Boeing reasoned that unsafe condition is not expected to cause an engine fire. Instead, when material is liberated from the engine upper bifurcation nose fairing assembly, the core zone fire detection and extinguishing may be less effective in the event of a fire. This is due to airflow that may be allowed to pass into the fire zone through an alternate path and at an unknown rate compared to the intended design. The FAA partially agrees. The FAA agrees that a cracked engine upper bifurcation nose fairing assembly and material release would not lead to an engine fire. The unsafe condition of this AD, however, is not the cracking of the engine upper bifurcation nose fairing assembly and material release, but the resulting failure of the engine fire control system. Since the engine fire control system would be inadequate to detect and control an engine fire, regardless of cause, the resulting hazard is the engine fire and consequent damage to the airplane. The FAA did not change this AD. Request To Clarify Engine Upper Bifurcation Nose Fairing Assembly With FRSJ739 Repair DAL requested that Note 1 to paragraph (g)(3) of this AD be updated to clarify inspection if on-wing repair FRSJ739 was applied. DAL reasoned that RRD added a second sheet to Figure 1 when it published Revision 2 of RR Alert Non-Modification Service Bulletin (NMSB) RB.211–72–AJ165, on August 21, 2018. This second sheet includes the entire length of the bracket in Zone A if on-wing repair FRSJ739 was applied. The proposed AD did not provide any distinctions for on-wing repair FRSJ739. The FAA disagrees. As stated in Note 1 to paragraph (g)(3) of this AD, Figure 1 of RR Alert NMSB RB.211–72–AJ165, Revision 2, dated August 21, 2018, provides guidance on the engine upper bifurcation nose fairing assembly inspection locations. Operators are not required to use Figure 1 to comply with this AD. Therefore, this AD is not required to reference on-wing repair FRSJ739. PO 00000 Frm 00020 Fmt 4700 Sfmt 4700 Request To Add Credit for Previous Actions Paragraph DAL requested that the FAA add a Credit for Previous Actions paragraph to this AD for previous initial and repetitive inspections completed using RR Alert NMSB RB.211–72–AJ165, Initial Issue, dated March 31, 2016, required by AD 2016–24–08. The FAA disagrees. AD 2016–24–08 and this AD do not require use of RR Alert NMSB RB.211–72–AJ165 to perform the initial and repetitive inspections. RR Alert NMSB RB.211– 72–AJ165 is provided as guidance on engine upper bifurcation nose fairing assembly inspection locations. Therefore, this AD does not need to provide credit for inspections performed using RR Alert NMSB RB.211–72– AJ165. The FAA did not change this AD. Request To Update Terminating Action With the Latest Service Information AAL, Boeing, DAL, and an individual commenter requested that paragraph (h), Mandatory Terminating Action, of this AD be updated to include RR Service Bulletin (SB) RB.211–72–J803, Revision 2, dated April 1, 2019. The commenters reasoned that RR SB RB.211–72–J803, Revision 1, dated July 13, 2018, has been superseded by Revision 2, dated April 1, 2019. Boeing also suggested adding language that allows any later revisions of the service information to be equivalent action as RRD may publish further revisions. The FAA agrees to revise the reference to RR SB RB.211–72–J803 in paragraph (h) of this AD from Revision 1, dated July 13, 2018, to Revision 2, dated April 1, 2019. The FAA disagrees with adding language that allows any later revisions of the service information. Since later revisions of the service information have not been published or reviewed by the agency, the FAA will not require their use. With the update to RR SB RB.211–72– J803 in this AD from Revision 1, dated July 13, 2018, to Revision 2, dated April 1, 2019, the FAA determined the need to update the estimated costs to reflect the increase in labor hours from 2 workhours to 8 work-hours for both on-wing and in-shop visits. Request To Add On-Wing Mandatory Terminating Action DAL requested that the on-wing rework instructions introduced in the Accomplishment Instructions, paragraph 3.D., of RR SB RB.211–72– J803, Revision 2, dated April 1, 2019, be included as an option for the mandatory terminating action to the AD. DAL E:\FR\FM\04DER1.SGM 04DER1 Federal Register / Vol. 85, No. 234 / Friday, December 4, 2020 / Rules and Regulations added that paragraph (i), Installation Prohibition, will ensure that demodification of the engine upper bifurcation nose fairing assembly will not be possible once the reworked engine upper bifurcation nose fairing assembly is installed. The FAA agrees that the on-wing rework instructions should be added as an option to the mandatory terminating action in addition to the in-shop rework procedure. RR SB RB.211–72–J803, Revision 2, dated April 1, 2019, provides an option to perform the onwing rework instructions. As a result, operators can perform the rework inshop or on-wing. The FAA added the on-wing rework instructions to the mandatory terminating action section of this AD. The FAA also agrees that demodification of the engine upper bifurcation nose fairing assembly will not be possible once the reworked engine upper bifurcation nose fairing assembly is installed. As noted in the following comment response, the FAA removed the installation prohibition proposed in the NPRM as the mandatory terminating actions requiring the modification of the engine upper bifurcation nose fairing assembly makes this installation prohibition unnecessary. serviceable engine upper bifurcation nose fairing assembly that needs to be repaired or replaced per AD 2016–24– 08, but has not been, may be removed during non-related maintenance. The FAA infers that RR’s concern aligns with AAL reasoning that removal of a panel for on-wing activity, such as maintenance or repair unrelated to the rework, will make the part ineligible for installation. Therefore, AAL proposed that paragraph (i) of the proposed AD be revised to ‘‘After the effective date of this AD, do not install an engine upper bifurcation nose fairing assembly, P/N FK25470, onto any engine that has or had an engine upper bifurcation nose fairing assembly, P/N KH75280, installed.’’ The FAA agrees that the installation prohibition would prevent the installation of the engine upper bifurcation nose fairing assembly, P/N FK25470, onto any engine after the effective date of this AD, even for work unrelated to this AD. The mandatory terminating action requires the modification of engine upper bifurcation nose fairing assembly, P/N FK25470 and, as such, the installation prohibition is not necessary. The FAA removed the installation prohibition from this AD. Request To Revise Installation Prohibition Support for the AD An individual commenter expressed support for the AD as written. RR and AAL requested that paragraph (i), Installation Prohibition, of the proposed AD be revised. Rolls-Royce was concerned if an upper bifurcation panel (upper bifurcation nose fairing assembly) is required to complete an onwing repair, it will prevent the installation of the original panel without the part being modified to the later standard. AAL reasoned that a Conclusion The FAA reviewed the relevant data, considered the comments received, and determined that air safety requires adopting the AD as proposed. Accordingly, the FAA is issuing this AD to address the unsafe condition on these products. Except for minor editorial changes, and any other changes described previously, this AD is 78217 adopted as proposed in the NPRM. None of the changes will increase the economic burden on any operator. Related Service Information Under 1 CFR Part 51 The FAA reviewed RR SB RB.211–72– J803, Revision 2, dated April 1, 2019; Revision 1, dated July 13, 2018; and Initial Issue, dated December 7, 2017. The service information describes procedures for modification of the engine upper bifurcation nose fairing assembly. This service information is reasonably available because the interested parties have access to it through their normal course of business or by the means identified in ADDRESSES. Other Related Service Information The FAA reviewed RR Alert NMSB RB.211–72–AJ165, Revision 2, dated August 21, 2018. The NMSB provides guidance on engine upper bifurcation nose fairing assembly inspection locations. The FAA also reviewed AMM TASK 70–20–02, Water Washable Fluorescent Penetrant Inspection (Maintenance Process 213), and OMat 632, high sensitivity fluorescent penetrant inspection. This service information provides guidance on performing a fluorescent penetrant inspection. Costs of Compliance The FAA estimates that this AD affects 70 engines installed on airplanes of U.S. registry. Based on updated information since publication of the NPRM, the FAA revised the estimated number of engines installed on airplanes of U.S. registry from 125 in the NPRM to 70 in this final rule. The FAA estimates the following costs to comply with this AD: ESTIMATED COSTS Cost per product Labor cost Inspect engine upper bifurcation nose fairing assembly. Modify engine upper bifurcation nose fairing assembly. 3.25 work-hours × $85 per hour = $276.25 ... $0 $276.25 $19,337.50 8 work-hours × $85 per hour = $680 ............. 50 730 51,100 The FAA estimates the following costs to do any necessary repairs or replacements that would be required Parts cost Cost on U.S. operators Action based on the results of the mandated inspections. The agency has no way of determining the number of engines that might need these repairs or replacements: ON-CONDITION COSTS Action Labor cost Repair engine upper bifurcation nose fairing assembly 8 work-hours × $85 per hour = $680 ........................... VerDate Sep<11>2014 16:15 Dec 03, 2020 Jkt 253001 PO 00000 Frm 00021 Fmt 4700 Sfmt 4700 E:\FR\FM\04DER1.SGM Parts cost 04DER1 $500 Cost per product $1,180 78218 Federal Register / Vol. 85, No. 234 / Friday, December 4, 2020 / Rules and Regulations ON-CONDITION COSTS—Continued Action Labor cost Replace engine upper bifurcation nose fairing assembly. 30 work hours × $85 per hour = $2,550 ...................... 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. The FAA is 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 The FAA has 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 that this AD: (1) Is not a ‘‘significant regulatory action’’ under Executive Order 12866, (2) Will not affect intrastate aviation in Alaska, 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. List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. The Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA amends 14 CFR part 39 as follows: VerDate Sep<11>2014 16:15 Dec 03, 2020 Jkt 253001 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: a. Removing airworthiness directive AD 2016–24–08, Amendment 39–18725 (81 FR 86567, December 1, 2016); and ■ b. Adding the following new airworthiness directive: ■ ■ 2020–25–04 Rolls-Royce Deutschland Ltd & Co KG (Type Certificate previously held by Rolls-Royce plc): Amendment 39–21346; Docket No. FAA–2019–0425; Project Identifier 2016–NE–13–AD. (a) Effective Date This airworthiness directive (AD) is effective January 8, 2021. (b) Affected ADs This AD replaces AD 2016–24–08, Amendment 39–18725 (81 FR 86567, December 1, 2016). (c) Applicability This AD applies to all Rolls-Royce Deutschland Ltd. & Co KG (RRD) (Type Certificate previously held by Rolls-Royce plc) RB211–Trent 875–17, RB211–Trent 877– 17, RB211–Trent 884–17, RB211–Trent 884B–17, RB211–Trent 892–17, RB211–Trent 892B–17, and RB211–Trent 895–17 model turbofan engines. (d) Subject Joint Aircraft System Component (JASC) Code 7130, Engine Fireseals. (e) Unsafe Condition This AD was prompted by RRD developing a modification of the engine upper bifurcation nose fairing assembly as a result of reports of cracking and material release from an engine upper bifurcation fairing. The FAA is issuing this AD to prevent failure of the engine fire control system. The unsafe condition, if not addressed could result in engine fire and damage to the airplane. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Required Actions (1) Within 7,500 engine flight hours (FHs) since new or since the last inspection or within 150 flight cycles (FCs) after January 5, 2017 (the effective date of AD 2016–24–08), whichever occurs later, inspect the engine upper bifurcation nose fairing assembly for PO 00000 Frm 00022 Fmt 4700 Sfmt 4700 Parts cost 500 Cost per product 3,050 cracks or missing material. Use paragraph (g)(3) of this AD to perform the inspection. (2) Repeat the inspection required by paragraph (g)(1) of this AD within every 7,500 engine FHs since the last inspection. (3) Inspect the engine upper bifurcation nose fairing assembly as follows. Note 1 to Paragraph (g)(3): Figure 1 of Rolls-Royce plc (RR) Alert Non-Modification Service Bulletin (NMSB) RB.211–72–AJ165, Revision 2, dated August 21, 2018, provides guidance on the engine upper bifurcation nose fairing assembly inspection locations. (i) Visually inspect upper bifurcation fairing seal face 22, seal support 23, and Zone A for any cracks or material loss on the right side. (A) If fairing seal face 22 is found to have released material, repair or replace the fairing before further flight. (B) If there is a single crack found on fairing seal face 22, shorter than 6 mm, repair or replace the fairing within 100 engine FCs, or at the next engine shop visit, whichever occurs first. (C) If there is a single crack, longer than 6 mm, found on fairing seal face 22, repair or replace the fairing within 15 engine FCs or at the next engine shop visit, whichever occurs first. (D) If there are two or more cracks found on fairing seal face 22, replace the fairing within 15 engine FCs or at the next engine shop visit, whichever occurs first. (E) If there is any cracking or material loss found on seal support 23, replace the fairing within 15 engine FCs or at the next engine shop visit, whichever occurs first. (ii) If the visual inspection required by paragraph (g)(3)(i) of this AD does not detect any cracks, fluorescent penetrant inspect Zone A. (A) If a crack shorter than 6 mm is detected, repair or replace the fairing within 100 engine FCs, or at the next engine shop visit, whichever occurs first. (B) If a crack longer than 6 mm is detected, repair or replace the fairing within 15 engine FCs or at the next engine shop visit, whichever occurs first. Note 2 to Paragraph (g)(3)(ii): AMM TASK 70–20–02, Water Washable Fluorescent Penetrant Inspection (Maintenance Process 213), and OMat 632, high sensitivity fluorescent penetrant inspection, provides guidance on performing a fluorescent penetrant inspection. (h) Mandatory Terminating Action As a mandatory terminating action to the inspections of the engine upper bifurcation nose fairing assembly required by paragraph (g) of this AD, perform one of the following: (1) At the next engine shop visit after the effective date of this AD, modify the engine upper bifurcation nose fairing assembly in E:\FR\FM\04DER1.SGM 04DER1 Federal Register / Vol. 85, No. 234 / Friday, December 4, 2020 / Rules and Regulations accordance with the Accomplishment Instructions, paragraph 3.C., of RR Service Bulletin (SB) RB.211–72–J803, Revision 2, dated April 1, 2019; paragraph 3.B., Revision 1, dated July 13, 2018; or paragraph 3.B., Original Issue, dated December 7, 2017; or (2) Before the next engine shop visit after the effective date of this AD, modify the engine upper bifurcation nose fairing assembly in accordance with the Accomplishment Instructions, paragraph 3.D., of RR SB RB.211–72–J803, Revision 2, dated April 1, 2019. (i) Definition For the purpose of this AD, an ‘‘engine shop visit’’ is defined as the induction of an engine into the shop for maintenance involving the separation of pairs of major mating engine flanges, except that the separation of engine flanges solely for the purposes of transportation without subsequent engine maintenance does not constitute an engine shop visit. (j) 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. (k) Related Information (1) For more information about this AD, contact Scott Stevenson, Aviation Safety Engineer, ECO Branch, FAA, 1200 District Avenue, Burlington, MA 01803; phone: (781) 238–7132; fax: (781) 238–7199; email: Scott.M.Stevenson@faa.gov. (2) Refer to European Aviation Safety Agency (EASA) AD 2018–0088, dated April 18, 2018, for more information. You may examine the EASA AD in the AD docket at https://www.regulations.gov by searching for and locating Docket No. FAA–2019–0425. (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. 552(a) and 1 CFR part 51. (2) You must use this service information as applicable to do the actions required by this AD, unless the AD specifies otherwise. (i) Rolls-Royce plc (RR) Service Bulletin (SB) RB.211–72–J803, Revision 2, dated April 1, 2019. (ii) RR SB RB.211–72–J803, Revision 1, dated July 13, 2018. (iii) RR SB RB.211–72–J803, Initial Issue, dated December 7, 2017. (3) For RR service information identified in this AD, contact Rolls-Royce plc, Corporate VerDate Sep<11>2014 16:15 Dec 03, 2020 Jkt 253001 Communications, P.O. Box 31, Derby, England, DE24 8BJ; phone: (+44) 1332 242424; fax: (+44) 1332 249936; email: https:// www.rolls-royce.com/contact/civil_team.jsp; internet: https://customers.rolls-royce.com/ public/rollsroycecare. (4) You may view this service information at 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) 238–7759. (5) You may view this service information that is incorporated by reference at the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, email: fedreg.legal@nara.gov, or go to: https://www.archives.gov/federal-register/cfr/ ibr-locations.html. Issued on November 30, 2020. Lance T. Gant, Director, Compliance & Airworthiness Division, Aircraft Certification Service. [FR Doc. 2020–26730 Filed 12–3–20; 8:45 am] BILLING CODE 4910–13–P 78219 regulations is approved by the Director of the Federal Register as of December 4, 2020. ADDRESSES: Availability of matters incorporated by reference in the amendment is as follows: For Examination 1. U.S. Department of Transportation, Docket Ops–M30. 1200 New Jersey Avenue SE, West Bldg., Ground Floor, Washington, DC 20590–0001. 2. The FAA Air Traffic Organization Service Area in which the affected airport is located; 3. The office of Aeronautical Navigation Products, 6500 South MacArthur Blvd., Oklahoma City, OK 73169 or, 4. The National Archives and Records Administration (NARA). For information on the availability of this material at NARA, email fedreg.legal@ nara.gov or go to: https:// www.archives.gov/federal-register/cfr/ ibr-locations.html. DEPARTMENT OF TRANSPORTATION Availability Federal Aviation Administration All SIAPs and Takeoff Minimums and ODPs are available online free of charge. Visit the National Flight Data Center at nfdc.faa.gov to register. Additionally, individual SIAP and Takeoff Minimums and ODP copies may be obtained from the FAA Air Traffic Organization Service Area in which the affected airport is located. FOR FURTHER INFORMATION CONTACT: Thomas J. Nichols, Flight Procedures and Airspace Group, Flight Technologies and Procedures Division, Flight Standards Service, Federal Aviation Administration. Mailing Address: FAA Mike Monroney Aeronautical Center, Flight Procedures and Airspace Group, 6500 South MacArthur Blvd., Registry Bldg. 29, Room 104, Oklahoma City, OK 73169. Telephone (405) 954–4164. SUPPLEMENTARY INFORMATION: This rule amends 14 CFR part 97 by establishing, amending, suspending, or removes SIAPS, Takeoff Minimums and/or ODPS. The complete regulatory description of each SIAP and its associated Takeoff Minimums or ODP for an identified airport is listed on FAA form documents which are incorporated by reference in this amendment under 5 U.S.C. 552(a), 1 CFR part 51, and 14 CFR part 97.20. The applicable FAA Forms 8260–3, 8260–4, 8260–5, 8260– 15A, 8260–15B, when required by an entry on 8260–15A, and 8260–15C. The large number of SIAPs, Takeoff Minimums and ODPs, their complex nature, and the need for a special format make publication in the Federal 14 CFR Part 97 [Docket No. 31343 Amdt. No. 3933] Standard Instrument Approach Procedures, and Takeoff Minimums and Obstacle Departure Procedures; Miscellaneous Amendments Federal Aviation Administration (FAA), DOT. ACTION: Final rule. AGENCY: This rule establishes, amends, suspends, or removes Standard Instrument Approach Procedures (SIAPS) and associated Takeoff Minimums and Obstacle Departure procedures (ODPs) for operations at certain airports. These regulatory actions are needed because of the adoption of new or revised criteria, or because of changes occurring in the National Airspace System, such as the commissioning of new navigational facilities, adding new obstacles, or changing air traffic requirements. These changes are designed to provide safe and efficient use of the navigable airspace and to promote safe flight operations under instrument flight rules at the affected airports. DATES: This rule is effective December 4, 2020. The compliance date for each SIAP, associated Takeoff Minimums, and ODP is specified in the amendatory provisions. The incorporation by reference of certain publications listed in the SUMMARY: PO 00000 Frm 00023 Fmt 4700 Sfmt 4700 E:\FR\FM\04DER1.SGM 04DER1

Agencies

[Federal Register Volume 85, Number 234 (Friday, December 4, 2020)]
[Rules and Regulations]
[Pages 78215-78219]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2020-26730]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2019-0425; Project Identifier 2016-NE-13-AD; Amendment 
39-21346; AD 2020-25-04]
RIN 2120-AA64


Airworthiness Directives; Rolls-Royce Deutschland Ltd & Co KG 
(Type Certificate Previously Held by Rolls-Royce plc) Turbofan Engines

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule.

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

SUMMARY: The FAA is superseding Airworthiness Directive (AD) 2016-24-08 
for all Rolls-Royce Deutschland Ltd. & Co KG (RRD) RB211-Trent 875-17, 
RB211-Trent 877-17, RB211-Trent 884-17, RB211-Trent 884B-17, RB211-
Trent 892-17, RB211-Trent 892B-17, and RB211-Trent 895-17 model 
turbofan engines. AD 2016-24-08 required repetitive inspections of the 
engine upper bifurcation nose fairing assembly and repair or 
replacement of any fairing assembly that fails inspection. This AD 
retains the requirements to perform repetitive inspections of the 
engine upper bifurcation nose fairing assembly and repair or 
replacement of any fairing assembly that fails inspection. As a 
terminating action to these inspections, this AD also requires the 
modification of the engine upper bifurcation nose fairing assembly. The 
FAA is issuing this AD to address the unsafe condition on these 
products.

DATES: This AD is effective January 8, 2021.
    The Director of the Federal Register approved the incorporation by 
reference of certain publications listed in this AD as of January 8, 
2021.

ADDRESSES: For service information identified in this final rule, 
contact Rolls-Royce plc, Corporate Communications, P.O. Box 31, Derby, 
England, DE24 8BJ; phone: (+44) 1332 242424; fax: (+44) 1332 249936; 
email: https://www.rolls-royce.com/contact/civil_team.jsp; internet: 
https://customers.rolls-royce.com/public/rollsroycecare. 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) 238-7759. It is also available at https://www.regulations.gov by 
searching for and locating Docket No. FAA-2019-0425.

Examining the AD Docket

    You may examine the AD docket at https://www.regulations.gov by 
searching for and locating Docket No. FAA-2019-0425; or in person at 
Docket Operations between 9 a.m. and 5 p.m., Monday through Friday, 
except Federal holidays. The AD docket contains this AD, 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, M-30, West Building Ground Floor, 
Room W12-140, 1200 New Jersey Avenue SE, Washington, DC 20590.

FOR FURTHER INFORMATION CONTACT: Scott Stevenson, Aviation Safety 
Engineer, ECO Branch, FAA, 1200 District Avenue, Burlington, MA 01803; 
phone: (781) 238-7132; fax: (781) 238-7199; email: 
[email protected].

SUPPLEMENTARY INFORMATION:

Background

    The FAA issued a notice of proposed rulemaking (NPRM) to amend 14 
CFR part 39 to supersede AD 2016-24-08, Amendment 39-18725 (81 FR 
86567, December 1, 2016) (AD 2016-24-08). AD 2016-24-08 applied to all 
RR RB211-Trent 875-17, RB211-Trent 877-17, RB211-Trent 884-17, RB211-
Trent 884B-17, RB211-Trent 892-17, RB211-Trent 892B-17, and RB211-Trent 
895-17 model turbofan engines. The NPRM published in the Federal 
Register on June 24, 2019 (84 FR 29423). The NPRM was prompted by RRD 
developing a modification of the engine upper bifurcation nose fairing 
assembly that terminates the need for repetitive inspections of this 
part. In the NPRM, the FAA proposed to retain the requirements to 
perform repetitive inspections of the engine upper bifurcation nose 
fairing assembly and repair or replacement of any fairing assembly that 
fails inspection. As a terminating action, in the NPRM the FAA also 
proposed to require modification of the engine upper bifurcation nose 
fairing assembly. The FAA is issuing this AD to address the unsafe 
condition of these products.
    The European Aviation Safety Agency (EASA), which is the Technical 
Agent for the Member States of the European Community, has issued EASA 
AD 2018-0088, dated April 18, 2018 (referred to after this as ``the 
MCAI''), to address the unsafe condition on these products. The MCAI 
states:


[[Page 78216]]


    Inspection of in-service Trent 800 engines identified cracking 
and/or material release from the upper bifurcation fairing, which 
mates to the aeroplane thrust reverser upper bifurcation forward 
fire seal. Both sets of hardware create the engine firewall to 
isolate the engine compartment fire zone, which is a firewall 
feature of the aeroplane type design. Damage (missing materials and 
holes/openings) to the upper bifurcation fairing creates a breach of 
the engine fire wall, which may decrease the effectiveness of the 
engine fire detection and suppression systems due to excess fan air 
entering the engine compartment fire zone. This could delay or 
prevent the fire detection and suppression system from functioning 
properly, and can result in an increased risk of prolonged burning, 
potentially allowing a fire to reach unprotected areas of the 
engine, strut and wing.
    This condition, if not detected and corrected, could lead to an 
uncontrolled fire, possibly resulting in damage to, or loss of, the 
aeroplane.
    To address this potential unsafe condition, RR published the 
NMSB to provide inspection instructions. Consequently, EASA issued 
AD 2016-0084 to require repetitive inspections of the upper 
bifurcation fairing and, depending on findings, accomplishment of 
applicable corrective action(s).
    Since that [EASA] AD was issued, RR developed modification (mod) 
72-J803, which introduces a revised upper bifurcation nose fairing 
assembly, featuring an additional support bracket assembly at the 
right hand seal land. RR also published the modification SB to 
provide instructions for in-service engines. This modification 
removes the need for repetitive inspections.
    For the reasons described above, this [EASA] AD retains the 
requirements of EASA AD 2016-0084, which is superseded, and requires 
a modification, which constitutes terminating action for the 
repetitive inspections required by this [EASA] AD.

    You may obtain further information by examining the MCAI in the AD 
docket at https://www.regulations.gov by searching for and locating 
Docket No. FAA-2019-0425.

Discussion of Final Airworthiness Directive

Comments

    The FAA received comments from six commenters. The commenters were 
Rolls-Royce plc (RR); American Airlines (AAL); The Boeing Company 
(Boeing); Delta Air Lines, Inc. (DAL); and two individual commenters. 
Five commenters requested changes to this AD, which included adding or 
updating the unsafe condition, terminating action, installation 
prohibition, and credit for previous actions. One commenter requested 
clarification regarding on-wing rework. One commenter expressed support 
for the AD. The following presents the comments received on the NPRM 
and the FAA's response to each comment.

Request To Remove Statement Indicating the Unsafe Condition Could Cause 
a Fire

    Boeing requested that paragraph (e), Unsafe Condition, of this AD 
be revised to replace ``. . . could result in engine fire and damage to 
the airplane'' with ``. . . could result in reduced ability to detect 
and/or control an engine fire which could lead to damage to the 
airplane.'' Boeing reasoned that unsafe condition is not expected to 
cause an engine fire. Instead, when material is liberated from the 
engine upper bifurcation nose fairing assembly, the core zone fire 
detection and extinguishing may be less effective in the event of a 
fire. This is due to airflow that may be allowed to pass into the fire 
zone through an alternate path and at an unknown rate compared to the 
intended design.
    The FAA partially agrees. The FAA agrees that a cracked engine 
upper bifurcation nose fairing assembly and material release would not 
lead to an engine fire. The unsafe condition of this AD, however, is 
not the cracking of the engine upper bifurcation nose fairing assembly 
and material release, but the resulting failure of the engine fire 
control system. Since the engine fire control system would be 
inadequate to detect and control an engine fire, regardless of cause, 
the resulting hazard is the engine fire and consequent damage to the 
airplane. The FAA did not change this AD.

Request To Clarify Engine Upper Bifurcation Nose Fairing Assembly With 
FRSJ739 Repair

    DAL requested that Note 1 to paragraph (g)(3) of this AD be updated 
to clarify inspection if on-wing repair FRSJ739 was applied. DAL 
reasoned that RRD added a second sheet to Figure 1 when it published 
Revision 2 of RR Alert Non-Modification Service Bulletin (NMSB) RB.211-
72-AJ165, on August 21, 2018. This second sheet includes the entire 
length of the bracket in Zone A if on-wing repair FRSJ739 was applied. 
The proposed AD did not provide any distinctions for on-wing repair 
FRSJ739.
    The FAA disagrees. As stated in Note 1 to paragraph (g)(3) of this 
AD, Figure 1 of RR Alert NMSB RB.211-72-AJ165, Revision 2, dated August 
21, 2018, provides guidance on the engine upper bifurcation nose 
fairing assembly inspection locations. Operators are not required to 
use Figure 1 to comply with this AD. Therefore, this AD is not required 
to reference on-wing repair FRSJ739.

Request To Add Credit for Previous Actions Paragraph

    DAL requested that the FAA add a Credit for Previous Actions 
paragraph to this AD for previous initial and repetitive inspections 
completed using RR Alert NMSB RB.211-72-AJ165, Initial Issue, dated 
March 31, 2016, required by AD 2016-24-08.
    The FAA disagrees. AD 2016-24-08 and this AD do not require use of 
RR Alert NMSB RB.211-72-AJ165 to perform the initial and repetitive 
inspections. RR Alert NMSB RB.211-72-AJ165 is provided as guidance on 
engine upper bifurcation nose fairing assembly inspection locations. 
Therefore, this AD does not need to provide credit for inspections 
performed using RR Alert NMSB RB.211-72-AJ165. The FAA did not change 
this AD.

Request To Update Terminating Action With the Latest Service 
Information

    AAL, Boeing, DAL, and an individual commenter requested that 
paragraph (h), Mandatory Terminating Action, of this AD be updated to 
include RR Service Bulletin (SB) RB.211-72-J803, Revision 2, dated 
April 1, 2019. The commenters reasoned that RR SB RB.211-72-J803, 
Revision 1, dated July 13, 2018, has been superseded by Revision 2, 
dated April 1, 2019. Boeing also suggested adding language that allows 
any later revisions of the service information to be equivalent action 
as RRD may publish further revisions.
    The FAA agrees to revise the reference to RR SB RB.211-72-J803 in 
paragraph (h) of this AD from Revision 1, dated July 13, 2018, to 
Revision 2, dated April 1, 2019. The FAA disagrees with adding language 
that allows any later revisions of the service information. Since later 
revisions of the service information have not been published or 
reviewed by the agency, the FAA will not require their use.
    With the update to RR SB RB.211-72-J803 in this AD from Revision 1, 
dated July 13, 2018, to Revision 2, dated April 1, 2019, the FAA 
determined the need to update the estimated costs to reflect the 
increase in labor hours from 2 work-hours to 8 work-hours for both on-
wing and in-shop visits.

Request To Add On-Wing Mandatory Terminating Action

    DAL requested that the on-wing rework instructions introduced in 
the Accomplishment Instructions, paragraph 3.D., of RR SB RB.211-72-
J803, Revision 2, dated April 1, 2019, be included as an option for the 
mandatory terminating action to the AD. DAL

[[Page 78217]]

added that paragraph (i), Installation Prohibition, will ensure that 
de-modification of the engine upper bifurcation nose fairing assembly 
will not be possible once the reworked engine upper bifurcation nose 
fairing assembly is installed.
    The FAA agrees that the on-wing rework instructions should be added 
as an option to the mandatory terminating action in addition to the in-
shop rework procedure. RR SB RB.211-72-J803, Revision 2, dated April 1, 
2019, provides an option to perform the on-wing rework instructions. As 
a result, operators can perform the rework in-shop or on-wing. The FAA 
added the on-wing rework instructions to the mandatory terminating 
action section of this AD.
    The FAA also agrees that de-modification of the engine upper 
bifurcation nose fairing assembly will not be possible once the 
reworked engine upper bifurcation nose fairing assembly is installed. 
As noted in the following comment response, the FAA removed the 
installation prohibition proposed in the NPRM as the mandatory 
terminating actions requiring the modification of the engine upper 
bifurcation nose fairing assembly makes this installation prohibition 
unnecessary.

Request To Revise Installation Prohibition

    RR and AAL requested that paragraph (i), Installation Prohibition, 
of the proposed AD be revised. Rolls-Royce was concerned if an upper 
bifurcation panel (upper bifurcation nose fairing assembly) is required 
to complete an on-wing repair, it will prevent the installation of the 
original panel without the part being modified to the later standard. 
AAL reasoned that a serviceable engine upper bifurcation nose fairing 
assembly that needs to be repaired or replaced per AD 2016-24-08, but 
has not been, may be removed during non-related maintenance. The FAA 
infers that RR's concern aligns with AAL reasoning that removal of a 
panel for on-wing activity, such as maintenance or repair unrelated to 
the rework, will make the part ineligible for installation. Therefore, 
AAL proposed that paragraph (i) of the proposed AD be revised to 
``After the effective date of this AD, do not install an engine upper 
bifurcation nose fairing assembly, P/N FK25470, onto any engine that 
has or had an engine upper bifurcation nose fairing assembly, P/N 
KH75280, installed.''
    The FAA agrees that the installation prohibition would prevent the 
installation of the engine upper bifurcation nose fairing assembly, P/N 
FK25470, onto any engine after the effective date of this AD, even for 
work unrelated to this AD. The mandatory terminating action requires 
the modification of engine upper bifurcation nose fairing assembly, P/N 
FK25470 and, as such, the installation prohibition is not necessary. 
The FAA removed the installation prohibition from this AD.

Support for the AD

    An individual commenter expressed support for the AD as written.

Conclusion

    The FAA reviewed the relevant data, considered the comments 
received, and determined that air safety requires adopting the AD as 
proposed. Accordingly, the FAA is issuing this AD to address the unsafe 
condition on these products. Except for minor editorial changes, and 
any other changes described previously, this AD is adopted as proposed 
in the NPRM. None of the changes will increase the economic burden on 
any operator.

Related Service Information Under 1 CFR Part 51

    The FAA reviewed RR SB RB.211-72-J803, Revision 2, dated April 1, 
2019; Revision 1, dated July 13, 2018; and Initial Issue, dated 
December 7, 2017. The service information describes procedures for 
modification of the engine upper bifurcation nose fairing assembly. 
This service information is reasonably available because the interested 
parties have access to it through their normal course of business or by 
the means identified in ADDRESSES.

Other Related Service Information

    The FAA reviewed RR Alert NMSB RB.211-72-AJ165, Revision 2, dated 
August 21, 2018. The NMSB provides guidance on engine upper bifurcation 
nose fairing assembly inspection locations. The FAA also reviewed AMM 
TASK 70-20-02, Water Washable Fluorescent Penetrant Inspection 
(Maintenance Process 213), and OMat 632, high sensitivity fluorescent 
penetrant inspection. This service information provides guidance on 
performing a fluorescent penetrant inspection.

Costs of Compliance

    The FAA estimates that this AD affects 70 engines installed on 
airplanes of U.S. registry. Based on updated information since 
publication of the NPRM, the FAA revised the estimated number of 
engines installed on airplanes of U.S. registry from 125 in the NPRM to 
70 in this final rule.
    The FAA estimates the following costs to comply with this AD:

                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
                                                                                     Cost per      Cost on U.S.
                Action                         Labor cost           Parts cost        product        operators
----------------------------------------------------------------------------------------------------------------
Inspect engine upper bifurcation nose   3.25 work-hours x $85                 $0         $276.25      $19,337.50
 fairing assembly.                       per hour = $276.25.
Modify engine upper bifurcation nose    8 work-hours x $85 per                50             730          51,100
 fairing assembly.                       hour = $680.
----------------------------------------------------------------------------------------------------------------

    The FAA estimates the following costs to do any necessary repairs 
or replacements that would be required based on the results of the 
mandated inspections. The agency has no way of determining the number 
of engines that might need these repairs or replacements:

                                               On-Condition Costs
----------------------------------------------------------------------------------------------------------------
                                                                                                     Cost per
                    Action                                 Labor cost               Parts cost        product
----------------------------------------------------------------------------------------------------------------
Repair engine upper bifurcation nose fairing    8 work-hours x $85 per hour =               $500          $1,180
 assembly.                                       $680.

[[Page 78218]]

 
Replace engine upper bifurcation nose fairing   30 work hours x $85 per hour =               500           3,050
 assembly.                                       $2,550.
----------------------------------------------------------------------------------------------------------------

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.
    The FAA is 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

    The FAA has 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 that this AD:
    (1) Is not a ``significant regulatory action'' under Executive 
Order 12866,
    (2) Will not affect intrastate aviation in Alaska, 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.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Incorporation by 
reference, Safety.

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:
0
a. Removing airworthiness directive AD 2016-24-08, Amendment 39-18725 
(81 FR 86567, December 1, 2016); and
0
b. Adding the following new airworthiness directive:
    2020-25-04 Rolls-Royce Deutschland Ltd & Co KG (Type Certificate 
previously held by Rolls-Royce plc): Amendment 39-21346; Docket No. 
FAA-2019-0425; Project Identifier 2016-NE-13-AD.

(a) Effective Date

    This airworthiness directive (AD) is effective January 8, 2021.

(b) Affected ADs

    This AD replaces AD 2016-24-08, Amendment 39-18725 (81 FR 86567, 
December 1, 2016).

(c) Applicability

    This AD applies to all Rolls-Royce Deutschland Ltd. & Co KG 
(RRD) (Type Certificate previously held by Rolls-Royce plc) RB211-
Trent 875-17, RB211-Trent 877-17, RB211-Trent 884-17, RB211-Trent 
884B-17, RB211-Trent 892-17, RB211-Trent 892B-17, and RB211-Trent 
895-17 model turbofan engines.

(d) Subject

    Joint Aircraft System Component (JASC) Code 7130, Engine 
Fireseals.

(e) Unsafe Condition

    This AD was prompted by RRD developing a modification of the 
engine upper bifurcation nose fairing assembly as a result of 
reports of cracking and material release from an engine upper 
bifurcation fairing. The FAA is issuing this AD to prevent failure 
of the engine fire control system. The unsafe condition, if not 
addressed could result in engine fire and damage to the airplane.

(f) Compliance

    Comply with this AD within the compliance times specified, 
unless already done.

(g) Required Actions

    (1) Within 7,500 engine flight hours (FHs) since new or since 
the last inspection or within 150 flight cycles (FCs) after January 
5, 2017 (the effective date of AD 2016-24-08), whichever occurs 
later, inspect the engine upper bifurcation nose fairing assembly 
for cracks or missing material. Use paragraph (g)(3) of this AD to 
perform the inspection.
    (2) Repeat the inspection required by paragraph (g)(1) of this 
AD within every 7,500 engine FHs since the last inspection.
    (3) Inspect the engine upper bifurcation nose fairing assembly 
as follows.

    Note 1 to Paragraph (g)(3):  Figure 1 of Rolls-Royce plc (RR) 
Alert Non-Modification Service Bulletin (NMSB) RB.211-72-AJ165, 
Revision 2, dated August 21, 2018, provides guidance on the engine 
upper bifurcation nose fairing assembly inspection locations.

    (i) Visually inspect upper bifurcation fairing seal face 22, 
seal support 23, and Zone A for any cracks or material loss on the 
right side.
    (A) If fairing seal face 22 is found to have released material, 
repair or replace the fairing before further flight.
    (B) If there is a single crack found on fairing seal face 22, 
shorter than 6 mm, repair or replace the fairing within 100 engine 
FCs, or at the next engine shop visit, whichever occurs first.
    (C) If there is a single crack, longer than 6 mm, found on 
fairing seal face 22, repair or replace the fairing within 15 engine 
FCs or at the next engine shop visit, whichever occurs first.
    (D) If there are two or more cracks found on fairing seal face 
22, replace the fairing within 15 engine FCs or at the next engine 
shop visit, whichever occurs first.
    (E) If there is any cracking or material loss found on seal 
support 23, replace the fairing within 15 engine FCs or at the next 
engine shop visit, whichever occurs first.
    (ii) If the visual inspection required by paragraph (g)(3)(i) of 
this AD does not detect any cracks, fluorescent penetrant inspect 
Zone A.
    (A) If a crack shorter than 6 mm is detected, repair or replace 
the fairing within 100 engine FCs, or at the next engine shop visit, 
whichever occurs first.
    (B) If a crack longer than 6 mm is detected, repair or replace 
the fairing within 15 engine FCs or at the next engine shop visit, 
whichever occurs first.

    Note 2 to Paragraph (g)(3)(ii):  AMM TASK 70-20-02, Water 
Washable Fluorescent Penetrant Inspection (Maintenance Process 213), 
and OMat 632, high sensitivity fluorescent penetrant inspection, 
provides guidance on performing a fluorescent penetrant inspection.

(h) Mandatory Terminating Action

    As a mandatory terminating action to the inspections of the 
engine upper bifurcation nose fairing assembly required by paragraph 
(g) of this AD, perform one of the following:
    (1) At the next engine shop visit after the effective date of 
this AD, modify the engine upper bifurcation nose fairing assembly 
in

[[Page 78219]]

accordance with the Accomplishment Instructions, paragraph 3.C., of 
RR Service Bulletin (SB) RB.211-72-J803, Revision 2, dated April 1, 
2019; paragraph 3.B., Revision 1, dated July 13, 2018; or paragraph 
3.B., Original Issue, dated December 7, 2017; or
    (2) Before the next engine shop visit after the effective date 
of this AD, modify the engine upper bifurcation nose fairing 
assembly in accordance with the Accomplishment Instructions, 
paragraph 3.D., of RR SB RB.211-72-J803, Revision 2, dated April 1, 
2019.

(i) Definition

    For the purpose of this AD, an ``engine shop visit'' is defined 
as the induction of an engine into the shop for maintenance 
involving the separation of pairs of major mating engine flanges, 
except that the separation of engine flanges solely for the purposes 
of transportation without subsequent engine maintenance does not 
constitute an engine shop visit.

(j) 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: 
[email protected].
    (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.

(k) Related Information

    (1) For more information about this AD, contact Scott Stevenson, 
Aviation Safety Engineer, ECO Branch, FAA, 1200 District Avenue, 
Burlington, MA 01803; phone: (781) 238-7132; fax: (781) 238-7199; 
email: [email protected].
    (2) Refer to European Aviation Safety Agency (EASA) AD 2018-
0088, dated April 18, 2018, for more information. You may examine 
the EASA AD in the AD docket at https://www.regulations.gov by 
searching for and locating Docket No. FAA-2019-0425.

(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. 552(a) and 1 CFR part 51.
    (2) You must use this service information as applicable to do 
the actions required by this AD, unless the AD specifies otherwise.
    (i) Rolls-Royce plc (RR) Service Bulletin (SB) RB.211-72-J803, 
Revision 2, dated April 1, 2019.
    (ii) RR SB RB.211-72-J803, Revision 1, dated July 13, 2018.
    (iii) RR SB RB.211-72-J803, Initial Issue, dated December 7, 
2017.
    (3) For RR service information identified in this AD, contact 
Rolls-Royce plc, Corporate Communications, P.O. Box 31, Derby, 
England, DE24 8BJ; phone: (+44) 1332 242424; fax: (+44) 1332 249936; 
email: https://www.rolls-royce.com/contact/civil_team.jsp; internet: 
https://customers.rolls-royce.com/public/rollsroycecare.
    (4) You may view this service information at 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) 238-7759.
    (5) You may view this service information that is incorporated 
by reference at the National Archives and Records Administration 
(NARA). For information on the availability of this material at 
NARA, email: [email protected], or go to: https://www.archives.gov/federal-register/cfr/ibr-locations.html.

    Issued on November 30, 2020.
Lance T. Gant,
Director, Compliance & Airworthiness Division, Aircraft Certification 
Service.
[FR Doc. 2020-26730 Filed 12-3-20; 8:45 am]
BILLING CODE 4910-13-P
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