Federal Register / Vol. 85, No. 234 / Friday, December 4, 2020 / Rules and Regulations 78215 

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 [Amended] 

■ 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); 

* * * * * 

§ 120.475 [Removed and Reserved] 

■ 10. Remove and reserve § 120.475. 

Jovita Carranza, 

Administrator. 

[FR Doc. 2020–26307 Filed 12–3–20; 8:45 am] 

BILLING CODE P 

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 RollsRoyce 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: 

http://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: 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: 

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. 

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 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 

Federal Register / Vol. 85, No. 234 / Friday, December 4, 2020 / Rules and Regulations 78217 

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. 

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 onwing 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

Action Labor cost Parts cost Cost per 

product 

Cost on U.S. 

operators 

Inspect engine upper bifurcation nose fairing 

assembly.

3.25 work-hours × $85 per hour = $276.25 ... $0 $276.25 $19,337.50 

Modify engine upper bifurcation nose fairing 

assembly.

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 

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 Parts cost Cost per 

product 

Repair engine upper bifurcation nose fairing assembly 8 work-hours × $85 per hour = $680 ........................... $500 $1,180 

78218 Federal Register / Vol. 85, No. 234 / Friday, December 4, 2020 / Rules and Regulations 

ON-CONDITION COSTS—Continued 

Action Labor cost Parts cost Cost per 

product 

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

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 

■ 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 

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 

Federal Register / Vol. 85, No. 234 / Friday, December 4, 2020 / Rules and Regulations 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: 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 

Communications, P.O. Box 31, Derby, 

England, DE24 8BJ; phone: (+44) 1332 

242424; fax: (+44) 1332 249936; email: http:// 

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 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 97 

[Docket No. 31343 Amdt. No. 3933] 

Standard Instrument Approach 

Procedures, and Takeoff Minimums 

and Obstacle Departure Procedures; 

Miscellaneous Amendments 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: 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 

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. 

Availability 

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