81378 Federal Register / Vol. 85, No. 242 / Wednesday, December 16, 2020 / Rules and Regulations 

(i) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Strategic Policy 

Rotorcraft Section, FAA, may approve 

AMOCs for this AD. Send your proposal to: 

Manager, Strategic Policy Rotorcraft Section, 

FAA, 10101 Hillwood Pkwy, Fort Worth, TX 

76177; telephone 817–222–5110; email 9/ 

ASW/FTW/AMOC-Requests@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. 

(j) Related Information 

For more information about this AD, 

contact Kathleen Arrigotti, Aerospace 

Engineer, Large Aircraft Section, 

International Validation Branch, FAA, 2200 

South 216th St., Des Moines, WA; telephone 

206–231–3218; email kathleen.arrigotti@

faa.gov. 

(k) 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 this AD specifies otherwise. 

(i) European Union Aviation Safety Agency 

(EASA) AD 2020–0095, dated April 29, 2020. 

(ii) [Reserved] 

(3) For EASA AD 2020–0095, contact the 

EASA, Konrad-Adenauer-Ufer 3, 50668 

Cologne, Germany; telephone +49 221 8999 

000; email ADs@easa.europa.eu; internet 

www.easa.europa.eu. You may find this 

EASA AD on the EASA website at https://

ad.easa.europa.eu. 

(4) You may view this service information 

at the FAA, Office of the Regional Counsel, 

Southwest Region, 10101 Hillwood Pkwy, 

Room 6N–321, Fort Worth, TX 76177. For 

information on the availability of this 

material at the FAA, call 817–222–5110. This 

material may be found in the AD docket on 

the internet at https://www.regulations.gov 

by searching for and locating Docket No. 

FAA–2016–3343. 

(5) You may view this material that is 

incorporated by reference at the National 

Archives and Records Administration 

(NARA). For information on the availability 

of this material at NARA, email fedreg.legal@

nara.gov, or go to https://www.archives.gov/ 

federal-register/cfr/ibr-locations.html. 

Issued on December 3, 2020. 

Gaetano A. Sciortino, 

Deputy Director for Strategic Initiatives, 

Compliance & Airworthiness Division, 

Aircraft Certification Service. 

[FR Doc. 2020–27659 Filed 12–15–20; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2020–0592; Project 

Identifier AD–2020–00251–E; Amendment 

39–21352; AD 2020–25–10] 

RIN 2120–AA64 

Airworthiness Directives; General 

Electric Company Turbofan Engines 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: The FAA is adopting a new 

airworthiness directive (AD) for all 

General Electric Company (GE) GEnx1B64/P2, GEnx-1B67/P2, GEnx-1B70/ 

75/P2, GEnx-1B70/P2, GEnx-1B70C/P2, 

GEnx-1B74/75/P2, GEnx-1B76/P2, 

GEnx-1B76A/P2, and GEnx-2B67/P 

model turbofan engines with a certain 

high-pressure turbine (HPT) rotor stage 

2 disk installed. This AD was prompted 

by a report of the potential for 

undetected subsurface anomalies 

formed during the manufacturing 

process that could result in uncontained 

failure of the HPT rotor stage 2 disk. 

This AD requires an immersion 

ultrasonic inspection (USI) of the HPT 

rotor stage 2 disk and, depending on the 

results of the inspection, replacement of 

the HPT rotor stage 2 disk with a part 

eligible for installation. The FAA is 

issuing this AD to address the unsafe 

condition on these products. 

DATES: This AD is effective January 21, 

2021. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in this AD 

as of January 21, 2021. 

ADDRESSES: For service information 

identified in this final rule, contact 

General Electric Company, GE Aviation, 

Room 285, 1 Neumann Way, Cincinnati, 

OH 45215; phone: (513) 552–3272; 

email: aviation.fleetsupport@ge.com. 

You may view this service information 

at the FAA, Airworthiness Products 

Section, Operational Safety Branch, 

1200 District Avenue, Burlington, MA 

01803. For information on the 

availability of this material at the FAA, 

call (781) 238–7759. It is also available 

at https://www.regulations.gov by 

searching for and locating Docket No. 

FAA–2020–0592. 

Examining the AD Docket 

You may examine the AD docket at 

https://www.regulations.gov by 

searching for and locating Docket No. 

FAA–2020–0592; 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 

final rule, 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: 

Mehdi Lamnyi, Aviation Safety 

Engineer, ECO Branch, FAA, 1200 

District Avenue, Burlington, MA 01803; 

phone: (781) 238–7743; fax: (781) 238– 

7199; email: Mehdi.Lamnyi@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Background 

The FAA issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 by adding an AD that would 

apply to all GE GEnx-1B64/P2, GEnx1B67/P2, GEnx-1B70/75/P2, GEnx1B70/P2, GEnx-1B70C/P2, GEnx-1B74/ 

75/P2, GEnx-1B76/P2, GEnx-1B76A/P2, 

and GEnx-2B67/P model turbofan 

engines with a certain HPT rotor stage 

2 disk installed. The NPRM published 

in the Federal Register on June 12, 2020 

(85 FR 35816). The NPRM was 

prompted by a report of the potential for 

undetected subsurface anomalies 

formed during the manufacturing 

process that could result in uncontained 

failure of the HPT rotor stage 2 disk. In 

the NPRM, the FAA proposed to require 

an immersion USI of the HPT rotor stage 

2 disk and, depending on the results of 

the inspection, replacement of the HPT 

rotor stage 2 disk with a part eligible for 

installation. The FAA is issuing this AD 

to address the unsafe condition on these 

products. 

Discussion of Final Airworthiness 

Directive 

Comments 

The FAA received comments from six 

commenters. The commenters were Air 

Line Pilots Association, International 

(ALPA); The Boeing Company (Boeing); 

Cargolux Airlines International S.A. 

(Cargolux); GE Aviation; United Airlines 

(UAL) Engineering; and Qantas Airways 

Limited (Qantas). One commenter 

requested that the FAA update the 

Affected ADs paragraph of this AD. One 

commenter requested that the HPT rotor 

stage 2 disks be replaced instead of 

inspected. One commenter requested 

that the FAA update the Definitions 

paragraph of this AD. Two commenters 

requested adding credit for previous 

action. Three commenters supported the 

AD. The following presents the 

comments received on the NPRM and 

the FAA’s response to each comment. 


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Federal Register / Vol. 85, No. 242 / Wednesday, December 16, 2020 / Rules and Regulations 81379 

Request To Update Affected ADs 

UAL Engineering requested that the 

FAA update paragraph (b), Affected 

ADs, of this AD to note the impact of the 

reduced life limits imposed by AD 

2020–20–11 (85 FR 60898, September 

29, 2020) (AD 2020–20–11) when 

complying with this AD. UAL 

Engineering reasoned that multiple HPT 

rotor stage 2 disks are affected by both 

rules, and leaving paragraph (b) blank 

creates ambiguity for operators 

generating compliance documentation 

for the dual-affected disks and engines. 

The FAA disagrees. Paragraph (b) of 

this AD identifies superseded or revised 

ADs, or other ADs if the requirements of 

those ADs are affected (i.e., terminating 

actions). This AD does not meet any of 

those conditions. Although this AD 

affects certain HPT rotor stage 2 disks 

that also affected AD 2020–20–11, the 

ADs address separate root causes and 

have different compliance actions and 

times. To comply with this AD, the 

affected HPT rotor stage 2 disks must be 

inspected and replaced if a rejectable 

indication is found. If, in accordance 

with AD 2020–20–11, an affected HPT 

rotor stage 2 disk has already been 

removed from service, then no further 

action is necessary to comply with the 

requirements of this AD. 

Request To Replace Certain HPT Rotor 

Stage 2 Disks 

GE Aviation requested that HPT rotor 

stage 2 disks with serial numbers 

TMT3UA34, TMT3UA55, TMT4CT46, 

or TMT4CT47, be replaced instead of 

inspected. GE reasoned that AD 2020– 

20–11 supersedes this AD, and the disks 

should be replaced in accordance with 

AD 2020–20–11. 

The FAA disagrees. AD 2020–20–11 

does not supersede this AD. Both ADs 

address separate root causes and have 

different compliance actions and times. 

AD 2020–20–11 requires replacement of 

certain HPT rotor stage 2 disks before 

accumulating a specified number of 

cycles since new. This AD requires a 

USI of certain HPT rotor stage 2 disks 

and, depending on the results of the 

inspection, replacement of the HPT 

rotor stage 2 disk. This AD may require 

replacement of an HPT rotor stage 2 disk 

prior to the required compliance time 

specified in AD 2020–20–11. If, 

however, an HPT rotor stage 2 disk is 

removed from service per AD 2020–20– 

11, then the affected turbofan engine 

would no longer have an affected HPT 

rotor stage 2 disk installed and would 

fall outside of the applicability of this 

AD. 

Request To Update Definition of Engine 

Shop Visit 

Qantas requested that the FAA update 

the definition of an ‘‘engine shop visit’’ 

to exclude engines with 2,000 or fewer 

cycles since new (CSN) that install the 

new retaining clips for the HPT stage 2 

nozzle assembly (retaining clips) 

introduced in GEnx-1B Service Bulletin 

(SB) 72–0398 during a ‘‘Quick Turn’’ 

shop visit. Qantas reasoned that the 

definition of an ‘‘engine shop visit’’ in 

the NPRM would require the removal 

and inspection of an affected HPT rotor 

stage 2 disk during their planned lowtime engine elective ‘‘Quick Turn’’ shop 

visit for installation of the new retaining 

clips. Qantas concluded that additional 

disassembly, cost, and engine shop turn 

time will significantly affect the 

viability of the GE retaining clip ‘‘Quick 

Turn’’ program. 

The FAA disagrees with excluding 

low-time engines that install the new 

retaining clips for the HPT Stage 2 

Nozzle Assembly during a ‘‘Quick 

Turn’’ shop visit. Changing the 

definition to exclude the ‘‘Quick Turn’’ 

shop visit would possibly postpone the 

immersion USI of the HPT rotor stage 2 

disk required by this AD until a 

subsequent shop visit. As a result, the 

risk of failure of the HPT rotor stage 2 

disk would increase. Qantas did not 

provide documentation to show that 

excluding the ‘‘Quick Turn’’ shop visit 

from the definition of an engine shop 

visit offers an acceptable level of safety. 

The FAA, however, will consider 

requests for alternative methods of 

compliance if submitted documentation 

supports an acceptable level of safety. 

Request To Add Credit for Previous 

Action 

Cargolux and GE Aviation requested 

credit for previous performance of the 

immersion USI of the HPT rotor stage 2 

disk using GE GEnx-1B Cleaning, 

Inspection and Repair Manual (CIR) 72– 

53–41, Special Procedure 001, or GE 

GEnx-2B CIR 72–53–41, Special 

Procedure 001. Cargolux reasoned that 

GE GEnx-2B SB 72–0402 R00, dated 

November 20, 2019, refers to GEnx-2B 

CIR 72–53–41, Special Procedure 001. 

The FAA disagrees. This AD does not 

require the use of GE GEnx-1B CIR 

GEK112862, CIR 72–53–41, Special 

Procedure 001, Rev 31, dated January 

31, 2020, or GE GEnx-2B CIR 

GEK114120, CIR 72–53–41, Special 

Procedure 001, Rev 24, dated January 

31, 2020, to perform the immersion USI 

of the HPT rotor stage 2 disk. The CIR 

are referred to in the service information 

referenced in paragraph (i), Credit for 

Previous Action. Therefore, if an 

operator performs the actions using the 

CIR, the operator is performing the 

action using the service information and 

has complied with this AD. The FAA 

did not change this AD. 

Support for the AD 

ALPA, Boeing, and UAL Engineering 

expressed support for the AD as written. 

Conclusion 

The FAA reviewed the relevant data, 

considered any comments received, and 

determined that air safety requires 

adopting this AD as proposed. 

Accordingly, the FAA is issuing this AD 

to address the unsafe condition on these 

products. 

Related Service Information Under 1 

CFR Part 51 

The FAA reviewed GE GEnx-1B SB 

72–0463 R01, dated January 6, 2020, 

and GE GEnx-2B SB 72–0402 R01, dated 

January 8, 2020. This service 

information describes procedures for 

performing an immersion USI of the 

affected HPT rotor stage 2 disks on 

GEnx-1B and GEnx-2B model turbofan 

engines, respectively. 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. 

Costs of Compliance 

The FAA estimates that this AD 

affects 276 engines installed on 

airplanes of U.S. registry. 

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 

USI of HPT rotor stage 2 disk ........................ 8 work-hours × $85 per hour = $680 ............. $0 $680 $187,680 


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81380 Federal Register / Vol. 85, No. 242 / Wednesday, December 16, 2020 / Rules and Regulations 

The FAA estimates the following 

costs to do any necessary replacements 

that would be required based on the 

results of the required inspection. The 

agency has no way of determining the 

number of aircraft that might need this 

replacement: 

ON-CONDITION COSTS

Action Labor cost Parts cost Cost per 

product 

Remove and replace the HPT rotor stage 2 disk ........ 2 work-hours x $85 per hour = $170 ........................... $458,900 $459,070 

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 

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 adding 

the following new airworthiness 

directive: 

2020–25–10 General Electric Company: 

Amendment 39–21352; Docket No. 

FAA–2020–0592; Project Identifier AD– 

2020–00251–E. 

(a) Effective Date 

This airworthiness directive (AD) is 

effective January 21, 2021. 

(b) Affected ADs 

None. 

(c) Applicability 

(1) This AD applies to all General Electric 

Company (GE) GEnx-1B64/P2, GEnx-1B67/ 

P2, GEnx-1B70/75/P2, GEnx-1B70/P2, GEnx1B70C/P2, GEnx-1B74/75/P2, GEnx-1B76/P2, 

and GEnx-1B76A/P2 model turbofan engines 

that have a high-pressure turbine (HPT) rotor 

stage 2 disk, part number (P/N) 2383M86P02, 

and a serial number (S/N) listed in paragraph 

4, Appendix—A, Table 1, Table 2, or Table 

3, of GE GEnx-1B Service Bulletin (SB) 72– 

0463 R01, dated January 6, 2020, installed. 

(2) This AD applies to all GE GEnx-2B67/ 

P model turbofan engines that have a HPT 

rotor stage 2 disk, P/N 2383M86P02, and a 

S/N listed in paragraph 4, Appendix—A, 

Table 1, Table 2, or Table 3, of GE GEnx-2B 

SB 72–0402 R01, dated January 8, 2020, 

installed. 

(d) Subject 

Joint Aircraft System Component (JASC) 

Code 7250, Turbine Section. 

(e) Unsafe Condition 

This AD was prompted by a report of the 

potential for undetected subsurface 

anomalies formed during the manufacturing 

process that could result in uncontained 

failure of the HPT rotor stage 2 disk. The 

FAA is issuing this AD to prevent failure of 

the HPT rotor stage 2 disk. The unsafe 

condition, if not addressed, could result in 

uncontained HPT rotor stage 2 disk release, 

damage to the engine, and damage to the 

airplane. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Required Actions 

(1) For affected GE GEnx-1B engines, at the 

next engine shop visit after the effective date 

of this AD, or before the HPT rotor stage 2 

disk has accumulated 6,500 cycles since new 

(CSN), whichever occurs first, perform an 

immersion ultrasonic inspection (USI) of the 

HPT rotor stage 2 disk using paragraph 

3.B.(1) of GE GEnx–1B SB 72–0463 R01, 

dated January 6, 2020. 

(2) If, during the USI required by paragraph 

(g)(1) of this AD, a rejectable indication is 

found, before further flight, remove the HPT 

rotor stage 2 disk from service and replace it 

with a part eligible for installation. 

(3) For affected GE GEnx-2B engines, at the 

next engine shop visit after the effective date 

of this AD, or before the HPT rotor stage 2 

disk has accumulated 6,500 CSN, whichever 

occurs first, perform an immersion USI of the 

HPT rotor stage 2 disk using paragraph 

3.B.(1) of GE GEnx-2B SB 72–0402 R01, dated 

January 8, 2020. 

(4) If, during the USI required by paragraph 

(g)(3) of this AD, a rejectable indication is 

found, before further flight, remove the HPT 

rotor stage 2 disk from service and replace it 

with a part eligible for installation. 

(h) Definitions 

(1) For the purpose of this AD, an ‘‘engine 

shop visit’’ is when a major engine flange is 

separated for purposes other than the 

removal of the fan for transportation. 

(2) For the purposes of this AD, a ‘‘part 

eligible for installation’’ is: 

(i) An HPT rotor stage 2 disk that does not 

have an S/N listed in paragraph 4, 

Appendix—A, Table 1, Table 2, or Table 3, 

of GE GEnx-1B SB 72–0463 R01, dated 

January 6, 2020, or GE GEnx-2B SB 72–0402 

R01, dated January 8, 2020; or, 

(ii) An HPT rotor stage 2 disk that has 

successfully passed the immersion USI 

required by paragraph (g)(1) or (3) of this AD, 

or passed the immersion USI using GE GEnx1B SB 72–0463 R00, dated November 20, 

2019, or GE GEnx-2B SB 72–0402 R00, dated 

November 20, 2019, before the effective date 

of this AD. 

(i) Credit for Previous Action 

You may take credit for the immersion USI 

of the HPT rotor stage 2 disk required by 

paragraph (g)(1) or (3) of this AD if you 

performed this inspection before the effective 

date of this AD using GE GEnx-1B SB 72– 

0463 R00, dated November 20, 2019, or GE 


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Federal Register / Vol. 85, No. 242 / Wednesday, December 16, 2020 / Rules and Regulations 81381 

GEnx-2B SB 72–0402 R00, dated November 

20, 2019. 

(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 

For more information about this AD, 

contact Mehdi Lamnyi, Aviation Safety 

Engineer, ECO Branch, FAA, 1200 District 

Avenue, Burlington, MA 01803; phone: (781) 

238–7743; fax: (781) 238–7199; email: 

Mehdi.Lamnyi@faa.gov. 

(l) Material Incorporated by Reference 

(1) The Director of the Federal Register 

approved the incorporation by reference 

(IBR) of the service information listed in this 

paragraph under 5 U.S.C. 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) General Electric Company (GE) GEnx-1B 

Service Bulletin (SB) 72–0463 R01, dated 

January 6, 2020, and 

(ii) GE GEnx-2B SB 72–0402 R01, dated 

January 8, 2020. 

(3) For GE service information identified in 

this AD, contact General Electric Company, 

GE Aviation, Room 285, 1 Neumann Way, 

Cincinnati, OH 45215; phone: (513) 552– 

3272; email: aviation.fleetsupport@ge.com. 

(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/ibrlocations.html. 

Issued on December 3, 2020. 

Gaetano A. Sciortino, 

Deputy Director for Strategic Initiatives, 

Compliance & Airworthiness Division, 

Aircraft Certification Service. 

[FR Doc. 2020–27628 Filed 12–15–20; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2020–0842; Product 

Identifier 2020–NM–101–AD; Amendment 

39–21350; AD 2020–25–08] 

RIN 2120–AA64 

Airworthiness Directives; Yabora ̃

Indu ́ stria Aerona ́utica S.A. (Type 

Certificate Previously Held by Embraer 

S.A.) Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: The FAA is adopting a new 

airworthiness directive (AD) for certain 

Yabora ̃ Indu ́ stria Aerona ́utica S.A. 

Model ERJ 170 airplanes and Model ERJ 

190–100 STD, –100 LR, –100 ECJ, –100 

IGW, –200 STD, –200 LR, and –200 IGW 

airplanes. This AD was prompted by 

reports of installation of inverted poles 

of the horizontal stabilizer pitch trim 

switches on the control yokes, which 

causes opposite commands for the 

horizontal stabilizer. This AD requires 

installing supports for the horizontal 

stabilizer control yoke pitch trim 

switches and re-identifying the control 

yokes, as specified in two Ageˆncia 

Nacional de Aviac ̧a ̃o Civil (ANAC) ADs, 

which are incorporated by reference. 

The FAA is issuing this AD to address 

the unsafe condition on these products. 

DATES: This AD is effective January 21, 

2021. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in this AD 

as of January 21, 2021. 

ADDRESSES: For material incorporated 

by reference (IBR) in this AD, contact 

National Civil Aviation Agency (ANAC), 

Aeronautical Products Certification 

Branch (GGCP), Rua Dr. Orlando 

Feirabend Filho, 230—Centro 

Empresarial Aquarius—Torre B— 

Andares 14 a 18, Parque Residencial 

Aquarius, CEP 12.246–190—Sa ̃o Jose ́

dos Campos—SP, BRAZIL, Tel: 55 (12) 

3203–6600; Email: pac@anac.gov.br; 

internet www.anac.gov.br/en/. You may 

find this IBR material on the ANAC 

website at https://sistemas.anac.gov.br/ 

certificacao/DA/DAE.asp. You may 

view this IBR material at the FAA, 

Airworthiness Products Section, 

Operational Safety Branch, 2200 South 

216th St., Des Moines, WA. For 

information on the availability of this 

material at the FAA, call 206–231–3195. 

It is also available in the AD docket on 

the internet at https://

www.regulations.gov by searching for 

and locating Docket No. FAA–2020– 

0842. 

Examining the AD Docket 

You may examine the AD docket on 

the internet at https://

www.regulations.gov by searching for 

and locating Docket No. FAA–2020– 

0842; 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 final rule, 

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: 

Krista Greer, Aerospace Engineer, Large 

Aircraft Section, International 

Validation Branch, FAA, 2200 South 

216th St., Des Moines, WA 98198; 

telephone and fax 206–231–3221; 

Krista.Greer@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Discussion 

The ANAC, which is the aviation 

authority for Brazil, has issued ANAC 

AD 2020–05–01, effective May 26, 2020; 

and ANAC AD 2020–05–02, effective 

May 26, 2020 (ANAC AD 2020–05–01 

and ANAC AD 2020–05–02) (also 

referred to as the Mandatory Continuing 

Airworthiness Information, or the 

MCAI); to correct an unsafe condition 

for certain Yabora ̃ Indu ́ stria Aerona ́utica 

S.A. Model ERJ 170 airplanes and 

Model ERJ 190–100 STD, –100 LR, –100 

ECJ, –100 IGW, –100 SR, –200 STD, 

–200 LR, and –200 IGW airplanes. 

Model ERJ 190–100 SR airplanes are not 

certificated by the FAA and are not 

included on the U.S. type certificate 

data sheet; this AD therefore does not 

include those airplanes in the 

applicability. 

The FAA issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 by adding an AD that would 

apply to certain Yabora ̃ Indu ́ stria 

Aerona ́utica S.A. Model ERJ 170 

airplanes and Model ERJ 190–100 STD, 

–100 LR, –100 ECJ, –100 IGW, –200 

STD, –200 LR, and –200 IGW airplanes. 

The NPRM published in the Federal 

Register on September 17, 2020 (85 FR 

58004). The NPRM was prompted by 

reports of installation of inverted poles 

of the horizontal stabilizer pitch trim 

switches on the control yokes, which 

causes opposite commands for the 

horizontal stabilizer. The NPRM 

proposed to require installing supports 


khammond on DSKJM1Z7X2PROD with RULES